#### SBIR 98-1![](media/image1.emf){width="1.1006944444444444in" height="0.8263888888888888in"}

**NASA**

**Small Business Innovation Research**

**1998 Program Solicitation**

***A searchable copy of this***

***Solicitation can be found through***

***the NASA SBIR homepage at***

***http://sbir.nasa.gov***

**April 24, 1998 - July 7, 1998**

**Contents of NASA SBIR 98-1 Program Solicitation**

**1.0 Program Description [1](#program-description)**

1.1 Summary [1](#summary)

1.2 Program Features [1](#program-features)

1.3 Three-Phase SBIR Program [2](#three-phase-sbir-program)

1.4 Eligibility To Participate in SBIR
[2](#eligibility-to-participate-in-sbir)

1.5 General Information [3](#general-information)

2.0 Definitions:.
[4](#definitions-the-following-definitions-apply-for-purposes-of-this-solicitation.)

2.1 Research or Research and Development (R/R&D)
[4](#research-or-research-and-development-rrd)

2.2 Subcontract [4](#subcontract)

2.3 Socially and Economically Disadvantaged Small Business Concern
[4](#socially-and-economically-disadvantaged-small-business-concern)

2.4 Socially and Economically Disadvantaged Individual
[4](#socially-and-economically-disadvantaged-individual)

2.5 Small Business Concern (SBC) [4](#small-business-concern-sbc)

2.6 Women-Owned Small Business [5](#women-owned-small-business)

2.7 United States [5](#united-states)

2.8 Commercialization [5](#commercialization)

3.0 Proposal Preparation Instructions and Requirements
[5](#proposal-preparation-instructions-and-requirements)

3.1 Fundamental Considerations [5](#fundamental-considerations)

3.2 General Requirements [6](#general-requirements)

3.3 Required Format [6](#required-format)

3.4 Proposal Cover and Project Summary
[6](#proposal-cover-and-project-summary)

3.5 Technical Proposal [7](#technical-proposal)

3.6 Proposed Budget [9](#proposed-budget)

3.7 Addendum for Prior SBIR Phase II Awards
[9](#addendum-for-prior-sbir-phase-ii-awards)

3.8 Check List [9](#check-list)

4.0 Method of Selection and Evaluation Criteria
[9](#method-of-selection-and-evaluation-criteria)

4.1 Phase I [9](#phase-i)

4.2 Phase II [11](#phase-ii)

4.3 Debriefing of Unsuccessful Offerors
[13](#debriefing-of-unsuccessful-offerors)

5.0 Considerations [14](#considerations)

5.1 Awards [14](#awards)

5.2 Phase I Final Report [14](#phase-i-final-report)

5.3 Payment Schedule for Phase I [14](#payment-schedule-for-phase-i)

5.4 Treatment and Protection of Proposal Information
[14](#treatment-and-protection-of-proposal-information)

5.5 Rights in Data Developed Under SBIR Contracts
[15](#rights-in-data-developed-under-sbir-contracts)

5.6 Copyrights [16](#copyrights)

5.7 Patents [16](#patents)

5.8 Cost Sharing [16](#cost-sharing)

5.9 Profit or Fee [16](#profit-or-fee)

5.10 Joint Ventures and Limited Partnerships
[16](#joint-ventures-and-limited-partnerships)

5.11 Similar Proposals and Prior Work
[16](#similar-proposals-and-prior-work)

5.12 Contractor Commitments (Phase I)
[16](#contractor-commitments-phase-i)

5.13 Additional Information [17](#additional-information)

5.14 Property [18](#property)

6.0 Submission of Proposals [18](#submission-of-proposals)

6.1 The Submission Process [18](#the-submission-process)

6.2 Electronic Technical Proposal Preparation
[19](#electronic-technical-proposal-preparation)

6.3 Internet Submission [19](#internet-submission)

6.4 Postal Submission [19](#postal-submission)

6.5 Acknowledgment of Proposal Receipt
[20](#acknowledgment-of-proposal-receipt)

6.6 Withdrawal of Proposals [20](#withdrawal-of-proposals)

7.0 Scientific and Technical Information Sources
[21](#scientific-and-technical-information-sources)

7.1 Regional Technology Transfer Centers
[21](#regional-technology-transfer-centers)

7.2 National Technical Information Services [21](#section)

8.0 Research Topics [23](#research-topics)

8.1 AERONAUTICS AND SPACE TRANSPORTATION TECHNOLOGY
[24](#aeronautics-and-space-transportation-technology)

8.2 HUMAN EXPLORATION AND DEVELOPMENT OF SPACE
[48](#human-exploration-and-development-of-space)

8.3 EARTH SCIENCE [74](#earth-science)

8.4 SPACE SCIENCE [84](#space-science)

8.5 CROSSCUTTING TECHNOLOGIES [93](#crosscutting-technologies)

9.0 Submission Forms and Certifications
[131](#submission-forms-and-certifications)

**1998 NASA Small Business Innovation Research Program Solicitation**

# 1.0 Program Description

## 1.1 Summary

The National Aeronautics and Space Administration (NASA) invites
eligible small business concerns to submit Phase I proposals for its
1998 Small Business Innovation Research (SBIR) Program, which is
described in this NASA SBIR Program Solicitation. The 1998 solicitation
period for Phase I proposals begins April 24, 1998, and ends July 7,
1998. NASA seeks innovative concepts addressing the program needs
described in the SBIR Solicitation subtopics and offering commercial
application potential.

Subject to the availability of funds, NASA plans to select about 335
proposals no earlier than October 26, 1998 for negotiation of a Phase I
fixed-price contract. NASA anticipates that about 40 percent of these
Phase projects will be selected for Phase II development.

This Solicitation contains program background information, outlines
eligibility requirements for SBIR participants, describes the three SBIR
program phases, and provides the information needed for submitting
responsive proposals.

## 1.2 Program Features

**1.2.1 Legislative Basis.** This Solicitation is issued pursuant to the
authority contained in P.L. 97-219, as amended (Small Business
Innovation Development Act of 1982) (15 U.S.C. 638). SBIR policy is
provided by the Small Business Administration (SBA) through the SBA
Policy Directive, January 26, 1993.

**1.2.2 Program Purposes.** SBIR program purposes established by law
include stimulating technological innovation in the private sector,
strengthening the role of small business concerns in meeting Federal
research and development needs, increasing the commercial application of
federally supported research results, and fostering and encouraging
participation by socially and economically disadvantaged persons and
women-owned small businesses in technological innovation.

**1.2.3 Program Funding.** Participating agencies conduct SBIR programs
by reserving a small percent of their research and development budgets
for funding agreements with small business concerns for research or
research and development (R/R&D) during the first two phases of the
three-phase process described here. Each agency, at its sole discretion,
selects the technical topics and subtopics included in its Solicitation
and selects its SBIR awards. Follow-on Phase III activities are
capitalized by non-SBIR sources of funding for the pursuit of private
sector or government sales.

**1.2.4 Program Management.** The NASA SBIR program is an agency-wide
effort that contributes to NASA\'s mission in planning, directing, and
conducting research and development for civilian uses of space and
aeronautics. The program also encourages the commercialization of the
products of SBIR-sponsored R/R&D. All NASA Field Installations and
Headquarters Program Offices participate. The NASA Office of Aeronautics
and Space Transportation Technology provides overall policy direction
for the SBIR program, while the NASA Goddard Space Flight Center serves
as the Program Management Office. NASA Field Installations identify R&D
needs, evaluate proposals, make recommendations for selections, and
manage the individual projects. The NASA installations that implement
the program are the following:

> **ARC Ames Research Center**, Moffett Field, California
>
> **DFRC Dryden Flight Research Center**, Edwards, California
>
> **GSFC Goddard Space Flight Center**, Greenbelt, Maryland
>
> **HQ NASA Headquarters**, Washington, DC
>
> **JPL Jet Propulsion Laboratory**, Pasadena, California
>
> **JSC Lyndon B. Johnson Space Center**, Houston, Texas
>
> **KSC John F. Kennedy Space Center**, Kennedy Space Center, Florida
>
> **LaRC Langley Research Center**, Hampton, Virginia
>
> **LeRC Lewis Research Center**, Cleveland, Ohio
>
> **MSFC George C. Marshall Space Flight Center**, Marshall Space Flight
> Center, Alabama
>
> **SSC John C. Stennis Space Center**, Stennis Space Center,
> Mississippi

## 1.3 Three-Phase SBIR Program

**1.3.1 Phase I.** The purpose of Phase I is to determine the scientific
and technical merit and feasibility of the proposed innovation and the
quality of the performance of the small business concern with a
relatively small NASA investment before consideration of further Federal
support in Phase II. To be eligible for Phase I selection, a proposal
must be based on an innovation having high technical or scientific merit
that is responsive to a NASA need described by a subtopic in this
Solicitation. Proposals involving high risk are encouraged when the
anticipated payoff potential is great. Unsolicited proposals (those not
responsive to a subtopic) will be rejected.

Projects are expected to emphasize near-term applicability to NASA.
Selection preference will be given to eligible proposals where the
innovations are judged to have significant potential for commercial
application.

Phase I must concentrate on establishing, through analysis and/or
experiment, the scientific or technical merit and feasibility of the
proposed innovation and on providing a basis for continued development
in Phase II. Proposals must conform to the format described in Section 3
of this Solicitation. Evaluation and selection criteria are described in
Section 4.1. NASA is solely responsible for determining the relative
merit and value of proposed Phase I projects, selecting proposals for
award, and judging the value of Phase I results.

SBIR contractors must have the capability to independently conduct the
R/R&D they propose, and Phase I projects should not require the use of
NASA facilities or equipment (See Section 5.14). Phase I contractors
will have no more than six months in which to complete their Phase I
projects, and to submit their Phase I final reports and Phase II
proposals.

**1.3.2 Phase II.** The objective of Phase II is to continue development
of those innovations shown to be feasible in Phase I, and that have the
highest potential value to NASA and to the U.S. economy. The government
is not obligated to fund any specific SBIR Phase II proposal.
Participation in NASA SBIR Phase II is limited to those contractors
conducting NASA SBIR Phase I projects.

Phase II projects are chosen as a result of competitive evaluations of
Phase II proposals. Phase II proposals are more comprehensive than those
required for Phase I, and are to be prepared in accordance with
instructions provided in the Phase I contract. See Section 4.2.2 of this
Solicitation and the Phase I model contract for required contents of
Phase II proposals.

The Phase II proposal evaluation and selection criteria are provided in
Section 4.2. They include consideration of the results of Phase I, but
place greater emphasis non-SBIR funding commitments and evidence of
non-government commercial application potential than does Phase I.

Fixed-price contracts are employed in Phase II, with performance periods
up to two years.

**1.3.3 Phase III.** Phase III involves non-SBIR capital to develop
commercial applications of a project, either in the Federal government
or in the private sector. Phase I, II, and III awards are considered
competitive under the Competition in Contracting Act. NASA will give
special acquisition preference for Phase III contracts to firms having
valid business arrangements that pursue continued development of
technology, products, or services developed under NASA SBIR Phase I and
II.

## 1.4 Eligibility To Participate in SBIR

**1.4.1 Small Business Concern.** Only firms qualifying as small
business concerns as defined in Section 2.5 of this Solicitation are
eligible to participate in the SBIR program. Socially and economically
disadvantaged small business concerns and women-owned small business
concerns are particularly encouraged to propose.

**1.4.2 Place of Performance.** For both Phase I and II, the R/R&D must
be performed in the United States (see Section 2.7) .

**1.4.3 Principal Investigator.** The Principal Investigator is
considered key to the success of the effort; therefore a PI's
involvement with the project must be substantial. The following
requirements are mandatory:

**Functions.** The functions of the Principal Investigator (PI) are
planning and directing the SBIR project, leading it technically and
making substantial personal contributions during its implementation,
serving as the primary contact with NASA on the project, and ensuring
that the work proceeds according to contract agreements. Competent
management of PI functions is essential to project success. The Phase I
proposal shall describe the nature of the PI\'s activities and the
amount of time that the PI will apply personally on the project. The
amount of time the PI proposes to spend on the project must be
acceptable to the NASA contracting officer.

**Qualifications.** The qualifications and capabilities of the proposed
PI and the basis for PI selection are to be clearly presented in the
proposal. NASA has the sole right to accept or reject a substitute PI
based on factors such as education, experience, demonstrated ability and
competence, and any other evidence related to the specific assignment.

**Co-Principal Investigators.** Co-PI's are not acceptable.

**Misrepresentation or Substitution.** Misrepresentation of PI
qualifications and eligibility, or substitution of a PI by the offeror
at any time without NASA\'s advance written approval, will result in
rejection of the proposal or termination of the contract.

**Primary Employment.** The offeror must certify in the proposal that
the primary employment of the PI will be with the small business concern
at the time of award and during the conduct of the project. Primary
employment means the PI will average a minimum of 20 hours per week with
the small business concern, and that more than half of the PI's total
employed time (including all concurrent employers, consulting, and
self-employed time) is spent with the small business. If the PI does not
meet these primary employment requirements when the proposal is
submitted, the offeror must explain how these requirements will be met
if the proposal is selected for contract negotiations that may lead to
an award.

**Employees of Academic and Non-Profit Organizations.** An offeror
proposing a PI who is also to be employed concurrently in any capacity
by an academic or non-profit organization (The Organization) must
include, as part of the proposal, a written release statement by that
organization. The PI release statement shall approve concurrent primary
employment with the small business concern as defined above, and agree
to less than half-time employment by The Organization beginning no later
than the time of NASA SBIR contract award to the small business concern
and continuing thereafter during contract performance. It must
specifically release the employee from all duties, responsibilities, and
activities with The Organization required by or implied by employment in
that position as much as or more than half-time. Proposals that do not
include the required written release statement will be rejected.

## 1.5 General Information

**1.5.1 Electronic Distribution of Solicitation**. The 1998 SBIR Program
Solicitation is available only via electronic means through the NASA
SBIR/STTR home page **(http://sbir.nasa.gov)**, or by requesting an
electronic copy on Diskette. When requesting a diskette it is important
to specify the platform you are using (IBM or Mac), the word processing
application you use, and your complete address. Printed copies of the
Solicitation will not be distributed.

Offerors are encouraged to check the SBIR/STTR home page for updates on
the program. Any updates or corrections to the Solicitation will be
posted there.

**1.5.2 Other Means of Contacting NASA SBIR**

**SBIR Program Support Office**:

1)  [E-Mail]{.underline}. The e-mail address for contacting NASA to
    request a diskette containing the Solicitation or to request NASA
    SBIR information is sbirsupport@lan.alliedtech.com.

2)  [Facsimile Machine]{.underline}. Inquiries and requests may be made
    by facsimile to 301-918-8154 and must include the name, address, and
    telephone number of the person making the request and the specific
    questions or requests.

3)  [Telephone Information Inquiries]{.underline}. Information about the
    SBIR program is available by calling 301-918-1980. Office hours are
    8:30 a.m. to 5:00 p.m. Eastern Daylight Time (EDT), Monday through
    Friday.

**NASA SBIR Program Manager**:

Requests for general information about the NASA SBIR program should be
mailed to:

NASA Goddard Space Flight Center

SBIR Program Manager

Paul Mexcur, Code 710.3

Greenbelt, MD 20771-0001

**1.5.3 Questions About this Solicitation**. To ensure fairness,
questions relating to the intent and/or content of research topics in
this Solicitation cannot be answered during the Phase I Solicitation
period ending July 7, 1998. Only questions requesting clarification of
Solicitation instructions and administrative matters will be answered.

**1.5.4 Questions Regarding Proposal Status**. Except for an
acknowledgment of proposal receipt (to be e-mailed within 30 days of the
closing date), information about proposal status *will not be available*
until final selections are announced (See Section 6.5).

# 2.0 Definitions: The following definitions apply for purposes of this Solicitation.

## 2.1 Research or Research and Development (R/R&D)

Any activity that is (1) a systematic, intensive study directed toward
greater knowledge or understanding of the subject studied, (2) a
systematic study directed specifically toward applying new knowledge to
meet a recognized need, or (3) a systematic application of knowledge
toward the production of useful materials, devices, systems, or methods,
including the design, development, and improvement of prototypes and new
processes to meet specific requirements.

## 2.2 Subcontract

Any agreement, other than one involving an employer-employee
relationship, entered into by a Federal government funding agreement
awardee calling for supplies or services required solely for the
performance of the original funding agreement. See also Sections 3.5.1
Part 9 and 4.2.2 Part 9 of this Solicitation.

## 2.3 Socially and Economically Disadvantaged Small Business Concern

A socially and economically disadvantaged small business concern is one
that is: (1) at least 51% owned by (i) an Indian tribe or a native
Hawaiian organization or (ii) one or more socially and economically
disadvantaged individuals; and (2) whose management and daily business
operations are controlled by one or more socially and economically
disadvantaged individuals.

## 2.4 Socially and Economically Disadvantaged Individual

A member of any of the following groups: African Americans, Hispanic
Americans, Native Americans, Asian-Pacific Americans, Subcontinent Asian
Americans, other groups designated from time to time by SBA to be
socially disadvantaged, or any other individual found to be socially and
economically disadvantaged by SBA pursuant to Section 8(a) of the Small
Business Act, 15 U.S.C. 637(a).

## 2.5 Small Business Concern (SBC)

A small business concern is one that, at the time of award of Phase I
and Phase II funding agreements, meets the following criteria:

1.  Is independently owned and operated, is not dominant in the field of
    operation in which it is proposing, has its principal place of
    business located in the United States, and is organized for profit;

2.  Is at least 51% owned, or in the case of a publicly owned business,
    at least 51% of its voting stock is owned by United States citizens
    or lawfully admitted permanent resident aliens; and

3.  Has, including its affiliates, a number of employees not exceeding
    500 and meets the other regulatory requirements found in 13 CFR
    Part 121. Business concerns, other than investment companies
    licensed, or state development companies qualifying under the Small
    Business Investment Act of 1958, 15 U.S.C. 661, et seq., are
    affiliates of one another when, either directly or indirectly, (1)
    one concern controls or has the power to control the other or (2) a
    third party controls or has the power to control both. Control can
    be exercised through common ownership, common management, and
    contractual relationships. The term \"affiliates\" is defined in
    greater detail in 13 CFR 121. The term \"number of employees\" is
    also defined in 13 CFR 121.

Small business concerns include sole proprietorships, partnerships,
corporations, joint ventures, associations, or cooperatives. Eligible
joint ventures are limited to no more than 49% participation by foreign
business entities.

## 2.6 Women-Owned Small Business

A small business concern that is at least 51% owned by a woman or women
who also control and operate it. \"Control\" in this context means
exercising the power to make policy decisions. \"Operate\" in this
context means being actively involved in the day-to-day management.

## 2.7 United States 

Means the 50 states, the territories and possessions of the United
States, the Commonwealth of Puerto Rico, the Trust Territory of the
Pacific Islands, and the District of Columbia.

## 2.8 Commercialization

The process of developing markets and producing and delivering products
or services for sale (whether by the originating party or by others). As
used here, commercialization includes both government and non-government
markets.

# 3.0 Proposal Preparation Instructions and Requirements

## 3.1 Fundamental Considerations

**3.1.1 Responsiveness to NASA Need.** An SBIR Phase I proposal must
present a scientific or technical innovation that addresses a NASA
program need as described in a specific subtopic. If the proposed
innovation is judged to be not responsive to the subtopic selected by
the offeror, the proposal will be classed as non-responsive and rejected
without evaluation, in accordance with the SBA Policy Directive and the
terms of this Solicitation. SBIR projects should address R/R&D
activities requiring significant scientific or technical innovation,
either experimental or theoretical. They may or may not involve
construction and evaluation of a laboratory prototype and/or analyses.

**3.1.2 Phase I Proposal Objective.** A Phase I proposal must describe
the research effort needed to investigate the feasibility of the
proposed scientific or technical innovation . The objective of the Phase
I effort must be to determine whether the innovation has sufficient
technical merit for proceeding into Phase II R/R&D.

**3.1.3 SBIR Project Requirements.** The deliverable item at the end of
an SBIR Phase I contract shall be a professional-quality report that
justifies, validates, and defends the experimental and theoretical work
accomplished. Furthermore, this report must demonstrate the basis for
judgments about technical merit and feasibility of the innovation
presented in the Phase I proposal, and it should connect the Phase I
results to Phase II follow-on R/R&D and commercial applications.
Delivery of a product or service with the Phase I report may be
desirable, but it is not a requirement.

Deliverable items for Phase II contracts shall include products or
services in addition to professional-quality reports of further
developments or applications of the Phase I results. These deliverables
may include prototypes, models, software, or complete products or
services; however, the reported results of Phase II must address and
provide the basis for validating the innovation and the potential for
implementation of commercial applications.

**3.1.4 Unacceptable Objectives.** Proposed efforts directed toward
systems studies; market research; commercial development of existing
products or proven concepts; straightforward engineering design for
packaging or adaptation to specific applications; studies, laboratory
evaluations; and modifications of existing products without innovative
changes are examples of projects that are not acceptable for SBIR.

**3.1.5 Multiple Proposal Submissions.** An offeror may submit any
number of **different proposals** to any number of subtopics, but every
proposal must be based on a unique innovation, must be limited in scope
to just one subtopic, and may be submitted only under that subtopic.

**3.1.6 Identical Proposals. Identical proposals and substantially
similar proposals** based on the same innovation submitted by an offeror
to several subtopics are not permitted and will result in all such
proposals being rejected without evaluation.

## 3.2 General Requirements

**3.2.1 Page Limitation.** A Phase I SBIR proposal shall not exceed a
total of 25 standard 8 1/2 X 11 inch (21.6 x 27.9 cm) pages, including
cover page, budget, and all enclosures or attachments. Margins should be
1.0 inch (2.5 cm). All material submitted, except required listing of
Phase II awards (See Section 3.7), will be included in the page count.
Samples, videotapes, slides, or other ancillary items will not be
accepted. Offerors are requested not to use the entire 25-page allowance
unless necessary**. Proposals exceeding the 25 page limitation will be
rejected without consideration.** The program would prefer proposals
prepared on both sides of paper, if possible.

**3.2.2 Type Size.** No type size smaller than 10 point is to be used
for text or tables, except as legends on reduced drawings. Proposals
prepared with smaller font sizes will be rejected without consideration.

**3.2.3 Brevity and Organization.** The proposal should be logically
organized, direct, and concise.

## 3.3 Required Format

The required format for a Phase I NASA SBIR proposal is described in the
following paragraphs. All required items of information are to be
covered fully in the prescribed \"Part\" order, but the space allocated
to each will depend on the project chosen and the offeror\'s approach.
Promotional and non-project-related material should not be included.

Each proposal submitted to the SBIR program must contain the following
parts in the order presented:

1.  Proposal Cover Sheet (Form 9A), signed in ink, as page 1.

2.  Project Summary (Form 9B), as page 2.

3.  Technical Proposal (12 parts), including all graphics, and starting
    at page 3 with a table of contents.

4.  Summary Budget (Form 9C), signed in ink.

All of these parts must be presented within the 25-page limitation. **A
proposal not addressing all parts will be considered non-responsive to
this Solicitation and will be rejected without consideration.** Detailed
descriptions of all parts of the proposal follow.

## 3.4 Proposal Cover and Project Summary

**Note: The Proposal Cover Sheet and the Project Summary are public
information, and the Government may disclose them. Do not include
proprietary information on these forms.**

**3.4.1 Page 1: Proposal Cover Sheet (Form 9A).** A copy of the Proposal
Cover Sheet is provided in Section 9.0. Each offeror shall provide
complete information for each item and submit the form as required in
Section 6.0. The proposal title shall be concise and descriptive of the
proposed product. The title should not use acronyms or words like
\"Development of\" or \"Study of.\" The NASA research topic title must
not be used as the proposal title.

**3.4.2 Page 2: Project Summary (Form 9B).** A copy of the Project
Summary Sheet is provided in Section 9.0. Each offeror shall provide
complete information for each item and submit form 9B as required in
Section 6.0. **Without revealing proprietary information and limited to
200 words**, the technical abstract section shall summarize the
anticipated results and implications of the approach (both Phases I and
II). Potential commercial applications of the technology should also be
presented.

## 3.5 Technical Proposal

**3.5.1 The Technical Proposal** shall not contain any budget data and
**must consist of all twelve parts in the following order.** (Note:
Parts that are not applicable must be noted as "Not Applicable.")

**Part 1: Table of Contents.** Page 3 of the proposal shall begin with a
brief table of contents indicating the page numbers of each of the
sections of the proposal.

**Part 2: Identification and Significance of the Innovation.** **The
first paragraph of Part 2 shall contain (1)** **a clear and succinct
statement of the specific innovation proposed and why it is an
innovation**, and (2) a brief explanation of how the innovation is
relevant and important to meeting the need described in the subtopic.
The initial paragraph shall contain no more than 200 words. **NASA will
reject proposals that lack this introductory paragraph**. In subsequent
paragraphs, Part 2 may also include appropriate background and
elaboration to explain the proposed innovation.

**Part 3: Phase I Technical Objectives.** State the specific objectives
of the Phase I R/R&D effort including the technical questions to be
answered to determine the feasibility of the proposed innovation.

**Part 4: Phase I Work Plan.** A detailed description of the Phase I
R/R&D plan. The plan should indicate what will be done, where the work
will be done, and how the work will be carried out. Phase I R/R&D should
address the objectives and questions cited in Part 3, above. The methods
planned to achieve each objective or task should be discussed in detail.
Schedules, task descriptions and assignments, resource allocations,
estimated task hours for each key personnel, and planned accomplishments
including project milestones shall be included. Offerors are advised to
avoid including proprietary information if at all possible. See Section
5.4.1.

**Part 5: Related R/R&D.** Describe significant current and/or previous
R/R&D that is directly related to the proposal including any conducted
by the principal investigator or by the offeror. Describe how it relates
to the proposed effort and any planned coordination with outside
sources. The offeror must persuade reviewers of his or her awareness of
key recent R/R&D conducted by others in the specific subject area. At
the offeror\'s option, this section may include concise bibliographic
references in support of the proposal if they are confined to activities
directly related to the proposed work.

**Part 6: Key Personnel and Bibliography of Directly Related Work.**
Identify key personnel involved in Phase I activities including their
directly related education, experience, and bibliographic information.
Where vitae are extensive, summaries that focus on the most relevant
experience or publications are desired and may be necessary to meet
proposal page and font requirements. Key personnel are the principal
investigator and other individuals whose expertise and functions are
essential to the success of the project.

This part shall also establish and confirm the eligibility of the
principal investigator (see Section 1.4.3), and indicate the extent to
which other proposals recently submitted or planned for submission in
1998 and existing projects commit the time of PI concurrently with this
proposed activity. Any attempt to circumvent the restriction on PIs
working more than half-time for an academic or a non-profit organization
by substituting an ineligible PI will result in rejection of the
proposal.

**Part 7:** **Relationship with Phase II or other Future R/R&D.** State
the anticipated results of the proposed R/R&D effort if the project is
successful (through Phase I and Phase II). Discuss the significance of
the Phase I effort in providing a foundation for the Phase II R/R&D
continuation.

**Part 8: Company Information and Facilities**. This section shall
provide adequate information to allow the evaluators to assess the
ability of the SBC to carry out the proposed Phase I and projected Phase
II and Phase III activities. The offeror should describe the relevant
facilities and equipment currently available, and those to be purchased,
in order to adequately support the team\'s proposed activities. **NASA
will not fund the acquisition of equipment, instrumentation, or
facilities under SBIR Phase I contracts as a direct cost (Section
5.14).** The capability of the offeror to perform the proposed
activities and bring a resulting product or service to market must be
indicated. Qualifications of the offeror and its principals in marketing
related products or services or in raising capital should be presented.
If an offeror proposes the use of unique or one-of-a-kind Government
facilities, a statement, describing the uniqueness of the facility and
it\'s availability to the offeror at specified times, signed by the
appropriate Government Official must be included with the proposal.
**Proposals lacking this signed statement will be rejected without
evaluation.**

**Part 9: Subcontracts and Consultants.** Up to one-third of the
research and/or analytical work (contract cost less fee) in Phase I may
be conducted under subcontract or other business arrangements with
others. If the offeror intends such arrangements, they should be
described in detail including functions, services, number of hours and
labor rates, and extent of effort to be provided. The proposal must
include a signed statement by each participating organization or
individual that they will be available at the times required for the
purposes and extent of effort described in the proposal. For Phase I, a
minimum of two-thirds of the work (contract cost less profit) must be
performed by the proposing small business concern unless otherwise
approved in writing by the contracting officer.

**Part 10: Commercial Applications Potential.** The commercial potential
of the proposed SBIR project is a significant proposal evaluation factor
(see Section 4.1.2). Therefore, offerors will discuss in this section
the broad commercial applications they contemplate for their project
results and their plans to bring the technology to commercial
application. Offerors should discuss the following: (a) the specific
commercial products or services contemplated and the corresponding
target market niche; (b) expected unique competitive advantage of the
commercial products or services; (c) nature of the corresponding
contemplated commercial venture; (d) importance of the contemplated
commercial venture to the offeror\'s current competitive position and to
its strategic planning; and (e) the offeror's capability and plans to
bring the necessary physical, personnel, and financial resources to
bear, in a timely way, to result in a viable commercial venture in the
reasonable near term subsequent to Phase II (if awarded). Offerors
should also describe how they would seek non-SBIR funding needed for
Phase II and Phase III activities (see Section 4.2.2, Part 11).

**Part 11: Similar Proposals and Awards.** A firm may elect to submit
proposals for essentially equivalent work under other Federal program
solicitations or may have received or expect to receive other Federal
awards for essentially equivalent work. In these cases, the offeror will
inform NASA of related proposals and awards and must first certify on
the Proposal Cover whether the offeror (a) has received Federal
government awards for related work, or (b) has submitted currently
active proposals for similar work under other Federal government program
solicitations or intends to submit proposals for such work to other
agencies during 1998. For all such cases, the following information is
required:

1.  The name and address of the agencies to which proposals have been or
    will be submitted, or from which awards have been received;

2.  Dates of such proposal submissions or awards;

3.  Title, number, and date of solicitations under which proposals have
    been or will be submitted or awards received;

4.  The specific applicable research topic for each such proposal
    submitted or award received;

5.  Titles of research projects;

6.  Name and title of the principal investigator/project manager for
    each proposal that has been or will be submitted or award received.

**Note: Lack of the required certification on the cover page or failure
to declare the existence of related, similar or duplicate awards or
proposals will result in rejection of the offer or loss of an award. If
no such awards have been received or no such proposals have been
submitted or are intended, the offeror shall so state in this part of
the proposal.**

**Part 12: Previous NASA SBIR Awards.** Offerors must state the total
number of NASA SBIR Phase I and II awards received, and list those
received during the last five years, showing contract numbers, the year
of award, Phase I or II, the NASA Installations making the award, and
project titles. **If no NASA awards have been received, the offeror
shall so state.**

## 3.6 Proposed Budget

**3.6.1 Summary Budget.** Following the instructions provided with the
form, offerors shall complete Form 9C, SBIR Summary Budget, and include
it (and any explanation sheets, if needed) as the last page(s) of the
proposal. Enough information shall be submitted to explain the offeror's
plans for use of the requested funds to enable NASA to determine whether
the proposed budget is fair and reasonable.

**3.6.2 Property.** NASA will not fund facility acquisition under Phase
I (See Section 5.14). Proposed costs for materials may be included.
\"Materials\" means property that may be incorporated or attached to a
deliverable end item or that may be consumed or expended in performing
the contract. It includes assemblies, components, parts, raw materials,
and small tools that may be consumed in normal use. Any purchase of
equipment or products under an SBIR contract using NASA funds should be
American-made to the extent possible.

**3.6.3 Travel.** Travel during Phase I is not normally essential to
prove technical merit and feasibility of the proposed innovation.
However, where the offeror deems travel to be essential for these
purposes, it is necessary to limit it to one person, one trip to the
sponsoring NASA installation. Proposed travel must be described as to
purpose and benefits in proving feasibility, and is subject to
negotiation and approval by the contracting officer. Trips to
conferences are not allowed under the Phase I contract.

**3.6.4 Profit.** A profit or fee may be included in the proposed budget
as noted in Section 5.9.

**3.6.5 Cost Sharing.** See Section 5.8.

## 3.7 Addendum for Prior SBIR Phase II Awards

The Small Business Administration requires offerors who have received
more than 15 Phase II awards from all agencies since October 1, 1992, to
report those awards and their progress toward commercialization. The
listing of awards shall be included in a separate \"Addendum: Phase II
History\" that will not be counted against the Phase I 25-page proposal
limit. Information for each Phase II contract shall include:

\(1\) Name of awarding agency

\(2\) Date of award and date of completion

\(3\) Funding agreement number and amount

\(4\) Topic or subtopic name

\(5\) Project title

\(6\) Sources, dates and amounts of Federal and/or private sector Phase
III follow-on funding agreements

\(7\) Post-Phase II commercialization activities, including development,
marketing, sales, and projections

The Addendum should be concise.

## 3.8 Check List

The Check List included in this Solicitation is provided to assist the
offeror in completing a responsive proposal. It should not be submitted
with the proposal.

# 4.0 Method of Selection and Evaluation Criteria

All Phase I and II proposals will be evaluated and judged on a
competitive basis. NASA may elect to fund several or none of the offers
to the same subtopic.

## 4.1 Phase I

Proposals judged to be responsive to this Solicitation will be evaluated
on a competitive basis by peer review.

**4.1.1 Evaluation Process.** Proposals will be first screened for
compliance with administrative requirements of the Solicitation. Those
that pass are then reviewed to determine whether they respond to the
subtopic chosen by the offeror and have described a relevant, specific
innovation. Those found to be responsive are evaluated in greater depth
at the NASA Installation(s) responsible for the subtopic, using the
factors listed under Section 4.1.2. Other NASA Installations may also
evaluate and recommend for selection any proposals accepted for
evaluation.

Proposals are expected to provide all information needed for complete
evaluation, and evaluators are not required to seek additional
information. Evaluators are required to use judgment in assessing
proposal information, making use of their personal expertise, knowledge
and experience. Evaluations will be performed by NASA scientists and
engineers and by qualified experts outside of NASA (industry, academia,
and other government agencies) as required to determine or verify the
merit of every aspect of a proposal.

**4.1.2 Phase I Evaluation Criteria.** NASA will give primary
consideration to the scientific and technical merit and feasibility of
the Phase I proposal. The proposal's potential for commercial
application will also be a consideration. NASA will uniformly apply the
following evaluation factors and procedures to all proposals accepted
for review:

**Factor 1.** **Scientific and technical merit** and feasibility of the
proposed innovation; relevance to the subtopic; benefit to NASA; and the
specific objectives and approaches. Innovation and originality are
essential considerations.

**Factor 2. Experience and Qualifications of the offeror,** the
Principal Investigator and other key personnel, consultants, and
subcontractors, if any; and adequacy of instrumentation and facilities
to be available for the project.

**Factor 3. Soundness of the proposed work plan,** budget, and schedule
for meeting the Phase I objectives of determining the feasibility and
merit of the proposed innovation preparatory to proceeding to Phase II.

**Factor 4. Commercial potential** of the proposed innovation in terms
of future commercial products and services and the likelihood of the
offeror to bring successfully developed technology to commercial
application (see Section 2.8).

**Technical Merit and Feasibility.** The sum of the numerical scores for
factors 1, 2, and 3 constitutes the numerical value for the Technical
Merit and Feasibility of a proposal. Factor 1 has twice the weight of
both Factor 2 and Factor 3.

**Commercial Merit.** This evaluation will be distinct from the
evaluation of technical merit and feasibility and will apply an
adjectival rating to the proposals expressing one of the following
judgments of Commercial Merit: Excellent, Very Good, Average, Below
Average, Poor, or Insufficient Data Provided.

**Installation Selection Recommendations.** Each NASA Installation will
prioritize (rank) its recommendations for selection and submit them to
the SBIR Source Selection Official. Recommendations will note the
Technical Merit and Feasibility scores and the judgments of Commercial
Merit for each proposal and any special considerations. The number of
proposals recommended for selection by each Installation may exceed the
number finally selected.

**4.1.3 Selection.** The SBIR Source Selection Official has final
selection authority for choosing the specific proposals for contract
negotiation. Most selection decisions are aligned with priorities
recommended by each Installation. Other factors influencing selection
decisions include balance between NASA's strategic enterprises and
distribution between critical technology disciplines.

Firms selected for negotiations that may lead to contract awards will be
notified by mail. The list of selections will also be made available
electronically (see Section 1.5.2) and by NASA Press Release
announcement. Each notification letter will identify the Contracting
Officer at the NASA Installation responsible for negotiating the Phase I
contract.

**4.1.4 Contracting.** Fixed-price contracts for up to \$70,000 and
6-month duration will be issued. Simplified contract documentation is
employed. NASA will make the Phase I model contract and other documents
available to the public electronically through the Internet (see Section
1.5.2) at the time of selection announcement. Documents that will be
available include:

1.  The names and contract information for SBIR contracting officers at
    the NASA installations

2.  Certifications and Representations required to support negotiations

3.  The model SBIR contract

4.  The full text of contract clauses included in the contract by
    reference

## 4.2 Phase II

**4.2.1 Phase II Proposals.** The object of Phase II is to continue the
R/R&D effort from Phase I. Only NASA Phase I awardees may compete for
NASA Phase II projects. The SBIR Phase I contract will serve as a
request for proposal (RFP) for an SBIR Phase II follow-on contract.
Phase II proposals are more comprehensive than those required for Phase
I. Submission of a Phase II proposal is strictly voluntary and NASA
assumes no responsibility for any proposal preparation expenses.

**4.2.2 Phase II Proposal Contents**. Phase II proposals shall be
addressed in the following \"Part\" order listed. Failure to include any
requested information in the proposal may make it non-responsive to the
RFP.

**Part 1: Cover Page.** (Form provided by the NASA Field Center)

**Part 2: Project Summary.** (Form provided by the NASA Field Center)

**Part 3: Table of Contents.**

**Part 4: Results of the Phase I Project.** Briefly describe how Phase I
has proven the feasibility of the innovation, provided a rationale for
both NASA and commercial applications, and demonstrated the ability of
the offeror to conduct R/R&D.

**Part 5: Phase II Technical Objectives, Approach, and Work Plan.**
Define the specific technical objectives of the Phase II research and
technical approach to meet these objectives; and provide a work plan
defining specific tasks, performance schedules, milestones, and
deliverables.

**Part 6: Company Information.** Describe the capability of the firm to
carry out Phase II and Phase III activities including its organization,
operations, number of employees, R/R&D capabilities, and experience
relevant to the work proposed.

**Part 7: Facilities and Equipment.** Discuss requirements for and the
availability of equipment, instrumentation, and facilities required for
Phase II. If an offeror proposes the use of unique or one-of-a-kind
Government facilities, a statement, describing the uniqueness of the
facility and it\'s availability to the offeror at specified times,
signed by the appropriate Government Official must be included with the
proposal. **Proposals lacking this signed statement will be rejected
without evaluation.**

**Part 8: Key Personnel.** Identify the key personnel for the project,
confirm their specific availability for Phase II, and discuss their
qualifications in terms of education, work experience, and
accomplishments that are relevant to the project. For any PI who is an
employee of an academic or non-profit organization, provide a release
statement as described in Section 1.4.3 of this Solicitation. Proposals
that do not include the required written release statement will be
rejected.

**Part 9: Consultants and Subcontracts.** Describe in detail any
subcontracting, consultant, or other business arrangements and provide
written evidence of their availability for the project. For Phase II, a
minimum of one-half of the work (contract cost less profit) must be
performed by the proposing small business concern unless approved in
writing by the contracting officer.

**Part 10: Commercialization and Phase III Plans.** Describe: plans for
commercialization (Phase III) in terms of each of the following areas:

**(1) Product or Service Commercial Feasibility:** Provide a description
of the (a) contemplated commercial product and/or service, the
corresponding commercial venture, and the unique competitive advantage
of both; and (b) technical obstacles to commercial applications, as well
as plans to address these obstacles.

**(2) Market Feasibility and Competition:** Describe: (a) the target
market niche including the distinction between U.S. Government and other
markets; (b) the estimated potential market size in terms of revenues to
be realized by the offeror from U.S. Government markets and, separately,
from other markets; (c) the competitive environment in terms of present
and likely competing similar and alternative technologies, and
corresponding competing domestic and foreign entities; and (d)
significant developments within the targeted business sector; (e)
offeror's ability, if any, to protect relevant technology with patents
or rights to exclusive access.

**(3) Strategic Relevance to the Offeror:** Describe the relevance of
the targeted commercial venture to the offeror\'s: (a) current business
segments; (b) relative position with respect to its competitors; and (c)
strategic planning for the next 5 years.

**(4) Key Management and Technical Personnel and Organizational
Structure:** Describe: (a) the skills and experience of key management
and technical personnel relevant to bringing innovative technology to
commercial application, (b) current organizational structure, and (c)
plans and timeline for obtaining the balance of all necessary key
business development expertise and other staffing not currently
in-house.

**(5) Production and Operations:** Describe: (a) business development
progress to date regarding the contemplated commercial venture; (b)
obstacles, plans, and associated timetable of key milestones regarding
all key business development elements; and (c) sources and components of
private physical resources committed to date and plans for obtaining the
balance of the necessary physical resources.

**(6) Financial Planning:** Describe: (a) the amounts and sources of
private financial resources expended and committed to date with respect
to the technology development project, and separately, with respect to
business development of the targeted commercial venture; (b) significant
requirements of potential investors, creditors, and insurers of the
venture; (c) proforma statement of cash flow with respect to the
targeted commercial venture that includes best estimates of at least the
following major components and timing thereof: capital investment,
revenues, principal and interest payments, depreciation of relevant
assets, other operating expenses; and (d) evidence of the offeror's
current financial strength (audited or unaudited financial statements
may be appended to address this).

> **Part 11: Capital Commitments Supporting Phases II and III.**
> Describe and document capital commitments from non-SBIR sources or
> from internal funds for pursuit of Phase II and Phase III. Offerors
> for Phase II contracts are strongly urged to obtain valid non-SBIR
> funding support commitments for follow-on Phase III activities and
> additional support of Phase II from parties other than the proposing
> firm. Valid funding support commitments must provide that a specific,
> substantial amount will be made available to the firm to pursue the
> stated Phase II and/or III objectives. They must indicate the source,
> date, and conditions or contingencies under which the funds will be
> made available. Alternatively, self-commitments of the same type and
> magnitude that are required from outside sources can be considered. If
> Phase III will be funded internally, offerors should describe their
> financial position.
>
> Evidence of funding support commitments from outside parties must be
> provided in writing to the proposing entity and should accompany the
> Phase II proposal. Letters of commitment should specify available
> funding commitments, other resources to be provided, and any
> contingent conditions. Expressions of technical interest by such
> parties in the Phase II research or of potential future financial
> support are insufficient and will not be accepted as support
> commitments by NASA.

**Part 12: Related R/R&D.** Describe R/R&D related to the proposed work
and affirm that the proposed objectives have not already been achieved
and that the same development is not presently being pursued elsewhere
under contract to the government.

**Part 13: Proposal Pricing.** Special instructions for pricing the
Phase II proposal will be provided in the Phase I contract and may be
provided in writing from the contracting officer.

**4.2.3 Phase II Evaluation Factors.** The evaluation of Phase II
proposals that may result from Phase I contracts awarded under this
Solicitation will apply the following factors:

**Factor 1. Scientific/technical merit** and feasibility of the proposed
R/R&D, with special emphasis on its innovation, originality, and
technical payoff potential if successful, including the degree to which
Phase I objectives were met, the feasibility of the innovation, and
whether the Phase I results indicate a Phase II project is appropriate.

**Factor 2. Future importance and eventual value** of the product,
process, or technology results to the NASA mission.

**Factor 3. Capability of the Small Business Concern.** NASA will assess
the capability of the concern to conduct Phase II based on: (a) the
validity of the project plans for achieving the stated goals; (b) the
qualifications and ability of the project team (Principal Investigator,
company staff, consultants and subcontractors) relative to the proposed
research; and (c) the availability of any required equipment and
facilities.

**Factor 4. Commercial Potential.** Consideration will be given to the
following:

**(1) Commercial potential of the technology:** This includes an
assessment of the offeror's ability to demonstrate: (a) a specific,
well-defined commercial product or service based on the technology to be
developed; (b) a realistic target market niche of sufficient size; (c)
that the targeted commercial product or service has strong potential for
uniquely meeting a well-defined need within the target market niche; and
(d) a commitment of significant private financial, physical, and
technical personnel resources.

> **(2) Demonstrated commercial intent of the offeror:** This includes
> the assessment of the offeror\'s ability to demonstrate: (a) the
> importance of the targeted commercial venture to the offeror's current
> business and strategic planning; (b) a targeted commercial venture
> that does not rely on continued U.S. Government markets or on other
> U.S. Government support beyond Government need; and (c) the adequacy
> of all resource commitments for Phase III development of the
> technology to a state of readiness for commercial application.

**(3) Capability of the offeror to bring successfully developed
technology to commercial application:** This includes assessment of the
offeror\'s ability to demonstrate: (a) the offeror's past success in
bringing SBIR and other innovative technologies to commercial
application; (b) well-thought-out business planning; (c) strong
likelihood of the offeror's bringing the remaining necessary private
financial, physical, personnel and other resources to bear in a timely
way to achieve commercial application of the technology in the not too
distant term subsequent to Phase II; and (d) the strength of the current
and continued financial viability of the offeror.

In applying these commercial criteria, NASA will assess proposal
information in terms of credibility, objectivity, reasonableness of key
assumptions, independent corroborating evidence, internal consistency,
demonstrated awareness of key risk areas and critical business
vulnerabilities, and other indicators of sound business analysis and
judgment.

**4.2.4 Evaluation and Selection.** Factors 1, 2, and 3 will be scored
numerically. Factors 2 and 3 are of equal importance, while Factor 1 is
more important than either 2 or 3. The sum of the scores for Factors 1,
2, and 3 will comprise the Total Technical Merit score for a Phase II
proposal. Proposals receiving high numerical scores will be evaluated
and rated for their commercial potential using the criteria listed in
Factor 4 and by applying the same adjectival ratings as set forth for
Phase I proposals (see Section 4.1.2).

Each NASA Installation managing Phase I projects will use these factors
to evaluate the Phase II proposals it receives that are responsive to
the Phase II RFP. The Installation\'s SBIR Committee will then rank the
evaluated proposals on technical merit and commercial potential, noting
other considerations such as NASA priority. Their recommendations and
supporting information will then be submitted to the SBIR Source
Selection Official. Final selections by the SBIR Source Selection
Official will be based on recommendations from all Installations; NASA
Headquarters Program Offices assessments of project value to NASA
programs and plans; and any other evaluations or assessments
(particularly of commercial potential) that may become available to the
Source Selection Official.

## 4.3 Debriefing of Unsuccessful Offerors

After final Phase I and Phase II selection decisions have been
announced, an offeror may submit a written request for a debriefing
(proposal critique). Telephone requests for debriefings will not be
accepted. **Requests must be made within 60 days after notification has
been mailed to the offeror** that their proposal was not selected for
award. NASA is not obligated to accept late requests.

Debriefings are intended to acquaint the offeror with perceived
strengths and weaknesses of the proposal. NASA will provide comments by
the evaluators, but debriefings are not opportunities to reopen
selection decisions. Debriefings will not disclose the identity of the
proposal evaluators nor provide proposal scores, proposal rankings in
the competition, or the content of and comparisons with other proposals
with which they were in competition.

**4.3.1 Phase I.** For Phase I proposals, all requests for debriefing
must be directed in writing, either by mail or fax, to the SBIR Program
Manager (see Section 1.5.2). Written debriefings, which include the
comments of the evaluators, will be mailed only to the corporate
official designated in the proposal.

**4.3.2 Phase II.** To obtain debriefings on Phase II proposals,
offerors must mail written requests to the Contracting Officer at the
NASA Installation to which their Phase II proposal was submitted.
Debriefings may be made to either the corporate official or their
designee identified in writing to the contracting officer.

# 5.0 Considerations

## 5.1 Awards

Both Phase I and Phase II awards are subject to availability of funds.
NASA has no obligation to make any specific number of Phase I or Phase
II awards based on this Solicitation, and may elect to make several or
no awards in any specific technical topic or subtopic.

Resulting from this solicitation, NASA plans to announce the selection
of approximately 335 proposals for negotiation of fixed-price Phase I
contracts with values not exceeding \$70,000. Following contract
negotiations and awards, Phase I contractors will have up to six months
to carry out their proposed Phase I programs, prepare their final
reports, and submit Phase II proposals. NASA intends that all Phase I
projects resulting from this solicitation will be placed under contract
by early 1999.

NASA anticipates that approximately 40% of the successfully completed
Phase I projects resulting from this Solicitation will be selected for
Phase II continuations based on the results of Phase I activities and
competitive evaluations of Phase II proposals. Phase II funding
agreements are fixed-price contracts with performance periods not
exceeding 24 months and funding not exceeding \$600,000.

NASA is not responsible for any monies expended by the offeror before
award of any contract resulting from this Solicitation.

## 5.2 Phase I Final Report

A final report on the Phase I project must be submitted to NASA upon
completion of the Phase I research effort. The format, including hard
copy and electronic media, and number of copies shall be in accordance
with Phase I contract terms. The report shall elaborate the project
objectives, work carried out, results obtained, and assessments of
technical feasibility. Rights to these data are outlined in Section 5.5
of this Solicitation. Language used in the Phase I report may be used
verbatim in the Phase II proposal.

The Phase I final report shall include a single page project summary (on
a form provided by NASA for that purpose) identifying the purpose of the
research, a brief description of the research carried out, the research
findings or results including the degree to which the Phase I objectives
were achieved, and whether the results justify Phase II continuation.
The potential applications of the project results in Phase III,
separately addressing NASA and non-government commercial uses, will also
be included. The project summary is to be submitted without restriction
for NASA publication. Phase II reporting requirements are detailed in
the Phase I contract.

## 5.3 Payment Schedule for Phase I

Advance payments can be authorized as follows: one-third at the time of
award, one-third at project mid-point after award, and the remainder
upon acceptance of the final report by NASA. The first two payments will
be made 30 days after receipt of valid invoices. The final payment will
be made 30 days after acceptance of the final report and other
deliverables as required by the contract.

## 5.4 Treatment and Protection of Proposal Information

In the evaluation and handling of proposals, NASA will make every effort
to protect the confidentiality of the proposals and their evaluations.
All proposals will be converted into an electronic format (see Section
6.2), placed on a secure NASA only Internet server and access limited to
NASA evaluators only.

**5.4.1 Proprietary Information.** It is NASA policy to use information
(data) included in proposals for evaluation purposes only. Public
release of information in any proposal submitted will be subject to
existing statutory and regulatory requirements.

If proprietary information consisting of a trade secret, proprietary
commercial or financial information, or private personal information is
provided in an SBIR proposal, NASA will treat it in confidence to the
extent permitted by law, provided this information is clearly marked by
the offeror with the term \"confidential proprietary information\" and
provided the following legend appears on the title page of the proposal
as follows:

> \"For any purpose other than to evaluate the proposal, this data shall
> not be disclosed outside the government and shall not be duplicated,
> used, or disclosed in whole or in part, provided that if a funding
> agreement is awarded to the offeror as a result of or in connection
> with the submission of this data, the Government shall have the right
> to duplicate, use or disclose the data to the extent provided in the
> funding agreement. This restriction does not limit the Government\'s
> right to use information contained in the data if it is obtained from
> another source without restriction. The data subject to this
> restriction are contained in pages [\_\_\_\_\_\_]{.underline} of this
> proposal.\"

**5.4.2 Non-NASA Reviewers.** In addition to government personnel, NASA,
at its discretion and in accordance with 18-15.413-2 of the NASA FAR
Supplement, may utilize qualified individuals from outside the
government in the proposal review process. Any decision to obtain
outside evaluation shall take into consideration requirements for the
avoidance of organizational or personal conflicts of interest and the
competitive relationship, if any, between the prospective contractor or
subcontractor(s) and the prospective outside evaluator. Any such
evaluation will be under agreement with the evaluator that the
information (data) contained in the proposal will be used only for
evaluation purposes and will not be further disclosed.

**5.4.3 Release of Proposal Information.** By submission of a proposal,
the offeror agrees to permit the government to disclose publicly the
information contained on the Proposal Cover and the Project Summary.
Other proposal information (data) is considered to be the property of
the offeror, and NASA will protect it from public disclosure to the
extent permitted by law (see Section 5.5.3). Form B, Project Summary,
shall not contain proprietary information.

**5.4.4 Final Disposition of Proposals.** The government retains
ownership of the copies of proposals submitted for evaluation, and they
will not be returned to the offeror. Copies of all unsuccessful Phase I
proposals will be retained for one year after Phase I selections have
been made, after which time non-selected proposals will be destroyed.
Successful proposals will be retained in accordance with contract file
regulations, normally 6 years and 3 months from project completion.

## 5.5 Rights in Data Developed Under SBIR Contracts

Rights to data used in, or first produced under, any Phase I or Phase II
contract are specified in the clause at FAR 52.227-20, Rights in
Data\--SBIR Program. The clause provides for rights consistent with the
following:

**5.5.1. Non-Proprietary Data.** Some data of a general nature are to be
furnished to NASA without restriction (i.e., with unlimited rights) and
may be published by NASA. These data will normally be limited to the
project summaries accompanying any periodic progress reports and the
final reports required to be submitted (see Section 5.2). The
requirement for them will be specifically set forth in any contract
resulting from this Solicitation.

**5.5.2 Proprietary Data.** When data that is required to be delivered
under an SBIR contract qualifies as "proprietary," *i.e*., either data
developed at private expense that embody trade secrets or are commercial
or financial and confidential or privileged, or computer software
developed at private expense that is a trade secret, the Contractor, if
the contractor desires to continue protection of such proprietary data,
shall not deliver such data to the Government, but instead shall deliver
form, fit, and function data.

**5.5.3 Non-Disclosure Period.** The Government, for a period of 4 years
from acceptance of all items to be delivered under an SBIR contract,
shall use SBIR data, *i.e*., data first produced by the Contractor in
performance of the contract where such data are not generally known, and
which data without obligation as to its confidentiality have not been
made available to others by the Contractor or are not already available
to the Government, agrees to use these data for Government purposes, and
they shall not be disclosed outside the Government (including disclosure
for procurement purposes) during the 4 year period without permission of
the Contractor, except that such data may be disclosed for use by
support Contractors under an obligation of confidentiality. After the 4
year period the Government has a royalty-free license to use, and to
authorize others to use on its behalf, these data for Government
purposes, but the Government is relieved of all disclosure prohibitions
and assumes no liability for unauthorized use by third parties.

## 5.6 Copyrights

Subject to certain licenses granted by the Contractor to the Government,
the Contractor receives copyright to any data first produced by the
Contractor in the performance of an SBIR contract.

## 5.7 Patents

The Contractor may normally elect title to any inventions made in the
performance of an SBIR contract. The Government receives a nonexclusive
license to practice or have practiced for or on behalf of the Government
each such invention throughout the world. To the extent authorized by 35
U.S.C. 205, the Government will not make public any information
disclosing such inventions for a reasonable time to allow the Contractor
to file a patent application.

## 5.8 Cost Sharing

Cost sharing is permitted for proposals under this Program Solicitation.
However, cost sharing is not required, nor will it be a factor in
proposal evaluation except as a consideration for Phase II/III
commitments discussed in Section 4.2.2 Part 11. If included, cost
sharing should be shown in the summary budget but not included in items
labeled \"AMOUNT REQUESTED.\" No profit will be paid under cost-sharing
contracts.

## 5.9 Profit or Fee

Both Phase I and Phase II SBIR contracts should include a reasonable
profit except where cost-sharing is proposed. The reasonability of
proposed profit is determined by the Contracting Officer during contract
negotiations.

## 5.10 Joint Ventures and Limited Partnerships

Both joint ventures and limited partnerships are permitted, provided the
entity created qualifies as a small business concern in accordance with
the definition in Section 2.5. A statement of how the workload will be
distributed, managed, and charged should be included in the proposal. A
copy or comprehensive summary of the joint venture agreement or
partnership agreement should be appended to the proposal. This will not
count as part of the 25 page limit for the Phase I proposal.

## 5.11 Similar Proposals and Prior Work

If an award is made pursuant to a proposal submitted under this Program
Solicitation, the firm will be required to certify that it has not
previously been paid nor is currently being paid for essentially
equivalent work by any agency of the Federal government. Failure to
acknowledge or report similar or duplicate efforts can lead to the
termination of contracts or other actions.

## 5.12 Contractor Commitments (Phase I)

Upon award of a contract, the contractor will be required to make
certain legal commitments through acceptance of numerous clauses in the
Phase I contract. The outline that follows illustrates the types of
clauses that will be included in the Phase I contract. This is not a
complete list of clauses to be included in Phase I contracts, nor does
it contain specific wording of these clauses. Copies of complete
provisions will be made available prior to contract negotiations.

**5.12.1 Standards of Work.** Work performed under the contract must
conform to high professional standards. Analyses, equipment, and
components for use by NASA will require special consideration to satisfy
the stringent safety and reliability requirements imposed in aerospace
applications.

**5.12.2 Inspection.** Work performed under the contract is subject to
government inspection and evaluation at all reasonable times.

**5.12.3 Examination of Records.** The Comptroller General (or a duly
authorized representative) shall have the right to examine any directly
pertinent records of the contractor involving transactions related to
the contract.

**5.12.4 Default.** The government may terminate the contract if the
contractor fails to perform the contracted work.

**5.12.5 Termination for Convenience.** The contract may be terminated
by the government at any time if it deems termination to be in its best
interest, in which case the contractor will be compensated for work
performed and for reasonable termination costs.

**5.12.6 Disputes.** Any dispute concerning the contract that cannot be
resolved by mutual agreement shall be decided by the contracting officer
with right of appeal.

**5.12.7 Contract Work Hours.** The contractor may not require a
non-exempt employee to work more than 40 hours in a work week unless the
employee is paid for overtime.

**5.12.8 Equal Opportunity.** The contractor will not discriminate
against any employee or applicant for employment because of race, color,
religion, age, sex, or national origin.

**5.12.9 Affirmative Action for Veterans.** The contractor will not
discriminate against any employee or applicant for employment because he
or she is a disabled veteran or veteran of the Vietnam era.

**5.12.10 Affirmative Action for Handicapped.** The contractor will not
discriminate against any employee or applicant for employment because he
or she is physically or mentally handicapped.

**5.12.11 Officials Not to Benefit.** No member of or delegate to
Congress shall benefit from the SBIR contract.

**5.12.12 Covenant Against Contingent Fees.** No person or agency has
been employed to solicit or secure the contract upon an understanding
for compensation except bona fide employees or commercial agencies
maintained by the contractor for the purpose of securing business.

**5.12.13 Gratuities.** The contract may be terminated by the government
if any gratuities have been offered to any representative of the
government to secure the contract.

**5.12.14 Patent Infringement.** The contractor shall report to NASA
each notice or claim of patent infringement based on the performance of
the contract.

**5.12.15 American-Made Equipment and Products.** Equipment or products
purchased under an SBIR contract must be American-made whenever
possible.

## 5.13 Additional Information

**5.13.1 Precedence of Contract over Solicitation.** This Program
Solicitation reflects current planning. If there is any inconsistency
between the information contained herein and the terms of any resulting
SBIR contract, the terms of the contract are controlling.

**5.13.2 Evidence of Contractor Responsibility.** Before award of an
SBIR contract, the Government may request the offeror to submit certain
organizational, management, personnel, and financial information to
establish responsibility of the offeror. Contractor responsibility
includes all resources required for contractor performance, i.e.,
financial capability, work force, and facilities.

**5.13.3 Classified Proposals.** NASA will not accept classified
proposals.

**5.13.4 Unsolicited Proposals.** Unsolicited proposals will not be
accepted under the SBIR program. Unsolicited proposals include proposals
unrelated to a subtopic need.

## 5.14 Property

In accordance with the Federal Acquisition Regulations (FAR) Part 45, it
is NASA\'s policy not to provide facilities (capital equipment, tooling,
test and computer facilities, etc.) for the performance of work under
contract. An offeror will furnish their own facilities to perform the
proposed work as an indirect cost to the contract. Special tooling
required for a project may be allowed as a direct cost.

When an offeror cannot furnish their own facilities to perform required
tasks, an offeror may propose to acquire the use of commercially
available facilities. Rental or lease costs may be considered as direct
costs as part of the total funding for the project. If unique
requirements force an offeror to acquire facilities under a NASA
contract, they will be purchased as Government furnished equipment (GFE)
and titled to the Government.

An offeror may propose the use of unique or one-of-a-kind NASA
facilities if essential for the research. Offerors requiring a NASA
facility must clearly document and certify that there is no commercially
available facility to perform the R&D. It may be difficult, however, to
ensure availability, and non-availability may lead to non-selection.
Should an offeror propose the use of unique or one-of-a-kind NASA
facilities essential for the R/R&D, an agreement with the responsible
installation is required and costs for their use will be determined by
the installation. These costs may be chargeable in accordance with the
government property clause of the contract (See Section 4.1.4). Total
contract costs must not exceed the Phase I and Phase II funding limits
given in this Solicitation (See Section 5.1).

# 6.0 Submission of Proposals

## 6.1 The Submission Process

**6.1.1 Submission Requirements**

NASA is in the process of converting to a completely electronic process
for management of the SBIR and STTR programs. This management approach
requires that a proposing firm have Internet access via the World Wide
Web, and an E-mail address. The advantages to the firm are:

1.  Faster, cheaper, simpler submission of Phase I and Phase II
    proposals.

2.  Faster and better communication among awardee firms, contracting
    officers, and contracting officer's technical representatives
    (COTRs) will expedite Phase I and Phase II contract negotiation,
    administration and close-out.

3.  Faster and better communication between Phase I and Phase II awardee
    firms and NASA will facilitate success story collection, marketing
    surveys, intellectual property (i.e. patent) applications, and
    non-NASA marketing of resultant products.

**6.1.2 What Needs to Be Submitted**

A proposal submission is comprised of three parts:

1.  **Electronic Technical Proposal Submission.** (Section 6.2) The
    Electronic Technical Proposal must be submitted either with the
    Internet Submission (Section 6.3) or on electronic media with the
    Postal Submission (Section 6.4).

2.  **Internet Form Submission** of Proposal Cover Sheet (Form 9A),
    Project Summary Sheet (Form 9B), and Summary Budget Sheet (Form 9C)
    (Section 6.3) is required

3.  **Postal Submission** of the original signed proposal plus three
    copies. (Section 6.4)

  -----------------------------------------------------------------------
  Firms not able to obtain Internet access must request an exemption by
  calling (301) 286-5661 or (703) 281-1745 by Monday, June 22, 1998. For
  all other general SBIR inquiries call (301) 918-1980. 

  -----------------------------------------------------------------------

## 6.2 Electronic Technical Proposal Preparation

By **technical proposal**, we mean the **part of the submission as
described in Section 3.5.**

**Word Processor**. NASA converts all electronic technical proposal
files to PDF format for evaluation purposes. Therefore, NASA requests
that technical proposals be submitted in PDF format, and encourages
companies to do so. Other acceptable formats for PC are AmiPro,
ClarisWorks for Windows, MS Works, Text, MS Word, WordPerfect,
Postscript, and Adobe Acrobat. Other acceptable formats for Macintosh
are ClarisWorks, MS Works, MacWrite Pro, Text, MS Word, WordPerfect,
Postscript, and Adobe Acrobat**. If the file is self-extracting, then
the offeror is limited to MS Word or WordPerfect formats.** Unix and TeX
users please note, due to PDF difficulties with non-standard fonts,
please output technical proposal file to DVI format.

**Graphics**. The offeror is encouraged for reasons of space
conservation and simplicity, but not required, to embed graphics within
the word processed document. For graphics submitted as separate files,
the acceptable file formats (and their respective extensions) are:
Bit-Mapped (.bmp), Graphics Interchange Format (.gif), JPEG (.jpg), PC
Paintbrush (.pcx), WordPerfect Graphic (.wpg), and Tagged-Image Format
(.tif).  

**Data Compression.** Offerors are permitted to submit compressed data
files using the Internet or Postal Submission. For PC based submissions,
the Pkzip data compression application shall be used. For
Macintosh-based submissions, the Stuffit data compression application
shall be used.

**Limitations**. While only the paper copy will be screened for
administrative compliance, the various files comprising the electronic
version are required to exactly reflect the paper version.

**Virus Check**. The offeror is responsible for performing a virus check
on each submitted technical proposal. As a standard part of entering the
proposal into the processing system, NASA will scan each submitted
electronic technical proposal for viruses. **The detection, by NASA, of
a virus on any submitted electronic technical proposal, may cause
rejection of the proposal.**

## 6.3 Internet Submission 

An Electronic Handbook for submitting proposals via the World Wide Web
is available on the NASA SBIR/STTR Home Page (**http://sbir.nasa.gov**).
The handbook will electronically guide the submitting firm through the
various steps for submitting SBIR proposals, and issue secure user
identification and passwords for each submission. The electronic
handbook also includes: SBIR/STTR overview, schedules, previous awards
history, sample proposals, other Federal SBIR/STTR Internet sites, and
the 1998 SBIR Solicitation. In addition, the electronic handbook
supports secure electronic submission of Forms 9A, 9B and 9C, the
technical proposal, award announcements, and debriefings. Communication
between NASA and the firm will be via a combination of e-mail and
electronic handbooks.

**Important**: After you have submitted Forms 9A, 9B, and 9C via the
Internet, you may use the handbook for printing out the three forms on
your own printer. These forms should be used as part of your Postal
Submission.

## 6.4 Postal Submission 

Postal Submissions are comprised of:

1.  One original signed paper copy of the proposal, including paper
    copies of all original forms (printed from 6.3 above).

2.  Three additional signed paper copies of the entire proposal. Each
    proposal copy is to be stapled separately.

3.  The electronic technical proposal as defined in Section 6.2 (if
    Internet submission is not utilized). Do not submit Forms 9A, 9B,
    and 9C on electronic media. These must be submitted via the web
    site.

**6.4.1 Physical Packaging Requirements**

**Paper Copies of Proposal.** Do not use bindings or special covers.
Staple the pages of each copy of the proposal in the upper left-hand
corner only. Secure packaging is mandatory. NASA cannot process
proposals damaged in transit. All items for any proposal must be sent in
the same envelope. If more than one proposal is being submitted, each
proposal must be in its own envelope, but all proposals may be sent in
the same package. Do not send duplicate packages of any proposal as
\"insurance\" that at least one will be received.

**Electronic Media for Technical Proposal.** If electronic technical
proposals are submitted in the Postal Submission, they must be submitted
in duplicate (primary and backup) on acceptable electronic media.
Acceptable electronic media include 3.5-inch diskettes, Iomega ZIP
disks, or CD ROMs in either PC or Macintosh formats. Electronic media
can be used to submit multiple electronic technical proposals for
multiple submissions as long as: (1) each submission is placed in a
separate folder (or directory), and (2) the folder is named using the
Internet Submission provided Proposal Submission ID. Electronic media
shall be clearly labeled externally with the following information:
Primary or Backup, Proposal Title and Number, Offeror Name, Computer
Platform and Software used, Compression Program used (if any), and a
listing of all files on the media.

**6.4.2 Where to Send Proposals**

All proposals that are mailed through the U.S. Postal Service first
class, registered, or certified mail; proposals sent by express mail or
commercial delivery services; or hand-carried proposals **must be**
delivered to the following address between 8:30 a.m. and 5:00 p.m. EDT:

Allied Technology Group, Inc.

Mail Stop 120

4200 Forbes Blvd. Suite 106

Lanham, MD 20706-4342

The following telephone number may be used when required for reference
by delivery services: (301) 918-1980. **Proposals cannot be received on
Saturdays, Sundays, or Federal holidays.**

**6.4.3 Deadline for Proposal Receipt**

**Deadline for receipt of Phase I proposals is 5:00 p.m. EDT on Tuesday,
July 7, 1998. Any proposal received after that date and time will be
considered late.** Since the postmark (or other carrier's date mark)
will be the evidence on which the decision is made, offerors must assure
themselves that the postmark (or other carrier's date mark) is clear and
easily legible; hand cancellation is suggested. Postage meter date
stamps are not acceptable**. It is not sufficient for an electronically
submitted proposal to be on time, the signed original paper version must
be received at NASA by the date and time stated above.** Proposals may
not be submitted by facsimile. Late proposals will not be eligible for
award and will be rejected without review.

## 6.5 Acknowledgment of Proposal Receipt

NASA will acknowledge receipt of proposals by email to the address on
the proposal cover sheet. If a proposal acknowledgment is not received
within 30 days following the closing date of this Solicitation, the
offeror should call (301) 918-1980. NASA will not respond to such
inquiries made prior to August 7, 1998.

## 6.6 Withdrawal of Proposals

Proposals may be withdrawn by written notice, fax or telegram received
at any time before award. The proposal will remain the property of the
U.S. Government and will be destroyed.

# 7.0 Scientific and Technical Information Sources

## 7.1 Regional Technology Transfer Centers

NASA\'s network of Regional Technology Transfer Centers (RTTCs), listed
below, provides a variety of business planning and development services
to NASA SBIR offerors. However, NASA does not accept responsibility for
any services these centers may offer in the preparation of proposals.
RTTCs should be contacted directly to determine what services are
available and to discuss fees charged since these vary, depending upon
the organization and type of service requested. To contact any RTTC,
call or check web at http://nctn.hq.nasa.gov.

+----------------------------------+-----------------------------------+
| **Northeast:**                   | **Mid-Atlantic**                  |
|                                  |                                   |
| Center for Technology            | Mid-Atlantic Technology           |
| Commercialization                | Applications Center               |
|                                  |                                   |
| 1400 Computer Drive              | 3400 Forbes Avenue, 5^th^ Floor   |
|                                  |                                   |
| Westborough, MA 01581            | Pittsburgh, PA 15260              |
+----------------------------------+-----------------------------------+
|                                  |                                   |
+----------------------------------+-----------------------------------+
| **Southeast:**                   | **Mid-West:**                     |
|                                  |                                   |
| Southern Technology Applications | Great Lakes Industrial Technology |
| Center                           | Center                            |
|                                  |                                   |
| 13709 Progress Boulevard, Box 24 | 25000 Great Northern Corporate    |
|                                  | Center, Suite 260                 |
| Alachua, FL 32615                |                                   |
|                                  | Cleveland, OH 44070               |
+----------------------------------+-----------------------------------+
| **Mid-Continent:**               | **Far-West:**                     |
|                                  |                                   |
| Mid-Continent Technology         | Far-West Regional Technology      |
| Transfer Center                  | Transfer Center                   |
|                                  |                                   |
| 301 Tarrow, Suite 119            | University of Southern California |
|                                  |                                   |
| College Station, TX 77843-8000   | 3716 South Hope Street, Suite 200 |
|                                  |                                   |
|                                  | Los Angeles, CA 90007-4344        |
+----------------------------------+-----------------------------------+

## 

## 7.2 National Technical Information Services

The **National Technical Information Service**, an agency of the
Department of Commerce, is the Federal government\'s central
clearinghouse for publicly funded scientific and technical information.
For information about their various services and fees, call or write:

National Technical Information Service

US Department of Commerce

Springfield, VA 22161

Tel: 703-605-6000

Fax: 703-321-8547

On-line access to abstracts of research from all agencies is available
through the Federal Research in Progress (FEDRIP) databases accessible
through DIALOG, a private information service. For a free copy of the
FEDRIP Search Guide, call 703-487-4650 and ask for PR 847.

#   {#section-1 .unnumbered}

#   {#section-2 .unnumbered}

# 8.0 Research Topics

NASA has established a framework for making management decisions by
separating the Agency's program into externally focused Strategic
Enterprises through which we implement our mission and communicate with
our external customers (http://www.nasa.gov).

These Enterprises identify, at the most fundamental level, what we do
and for whom. They focus us on the ends, not the means, of our
endeavors. Each of our Strategic Enterprises is analogous to a strategic
business unit employed by private-sector companies to focus on and
respond to their customers\' needs. Each Strategic Enterprise has a
unique set of strategic goals, objectives, and strategies that addresses
the requirements of its primary external customers. Because each
Enterprise must align its programmatic thrusts with its own customers\'
needs, each requires its own individual strategy. Research topics and
subtopics in this Solicitation are organized by the four Enterprises:

***Aeronautics and Space Transportation Technology***

***Human Exploration and Development of Space***

***Earth Science***

***Space Science***

In addition, synergy among the Enterprises is captured in a separate
section in the Solicitation called ***Crosscutting Technologies***.

There is a total of 28 topics in this Solicitation, each with an
introduction followed by a list of subtopics. There is a total of 122
subtopics. These topics and subtopics are found in sections 8.1 through
8.5. Each section has a general introduction and its own table of
contents.

##   {#section-3 .unnumbered}

## 8.1 AERONAUTICS AND SPACE TRANSPORTATION TECHNOLOGY

NASA\'s Aeronautics and Space Transportation Technology Enterprise
pioneers the identification, development, verification, transfer,
application, and commercialization of high-payoff aeronautics
technologies. It seeks to promote economic growth and security and to
enhance U.S. competitiveness through safe, superior, and environmentally
compatible U.S. civil and military aircraft and through a safe,
efficient national aviation system. In addition, the Enterprise
recognizes that the space transportation industry can benefit
significantly from the transfer of aviation technologies and flight
operations to launch vehicles, the goal being reducing the cost of
access to space. The Enterprise will work closely with its aeronautics
customers, including U.S. industry, the Department of Defense, and the
Federal Aviation Administration, to ensure that its technology products
and services add value, are timely, and have been developed to the level
where the customer can confidently make decisions regarding the
application of those technologies.

> http://www.hq.nasa.gov/office/aero/

**01 Aviation Safety & Capacity [25](#aviation-safety-capacity)**

01.01 Human Factors in Aviation Operations
[25](#human-factors-in-aviation-operations)

01.02 Advanced Concepts in Air-Traffic Management
[26](#advanced-concepts-in-air-traffic-management)

01.03 Aircraft Ice Protection Systems
[26](#aircraft-ice-protection-systems)

01.04 High-Integrity Systems and Algorithms
[27](#high-integrity-systems-and-algorithms)

01.05 Automated On-Line Health Management and Data Analysis
[28](#automated-on-line-health-management-and-data-analysis)

01.06 Propulsion & Airframe Failure Data & Mitigation
[28](#propulsion-airframe-failure-data-mitigation)

02 High Speed Travel [29](#high-speed-travel)

02.01 Supersonic Transport Airframe Technologies
[29](#supersonic-transport-airframe-technologies)

02.02 Supersonic Transport Propulsion Technologies
[30](#supersonic-transport-propulsion-technologies)

03 Subsonic Transport Environmental Compatibility
[31](#subsonic-transport-environmental-compatibility)

03.01 Aircraft Noise Prediction and Reduction
[31](#aircraft-noise-prediction-and-reduction)

03.02 Propulsion System Noise Prediction and Reduction
[31](#propulsion-system-noise-prediction-and-reduction)

03.03 Subsonic Aircraft Systems Emissions Reduction
[32](#subsonic-aircraft-systems-emissions-reduction)

04 Space Transportation [33](#space-transportation)

04.01 Launch Vehicle Technologies [33](#launch-vehicle-technologies)

04.02 Advanced/Exotic Propulsion System Technologies
[34](#advancedexotic-propulsion-system-technologies)

04.03 Space Transfer Technologies [34](#space-transfer-technologies)

04.04 Lightweight Engine Components [35](#lightweight-engine-components)

04.05 Rocket Engine Test Operations [36](#rocket-engine-test-operations)

05 General Aviation Revitalization
[36](#general-aviation-revitalization)

05.01 General Aviation Transportation System Technologies
[37](#general-aviation-transportation-system-technologies)

05.02 Light Aircraft Engine Design, Systems, and Components
[37](#light-aircraft-engine-design-systems-and-components)

06 Next Generation Aircraft Systems Design & Analyses Tools
[38](#next-generation-aircraft-systems-design-analyses-tools)

06.01 Advanced Measurement Science and Ground Testing Technology
[38](#advanced-measurement-science-and-ground-testing-technology)

06.02 Unsteady Aerodynamics and Aeroelasticity
[39](#unsteady-aerodynamics-and-aeroelasticity)

06.03 Computation Advances for Aerospace Applications
[39](#computation-advances-for-aerospace-applications)

06.04 Rotorcraft/STOVL Aerodynamics and Dynamics
[40](#rotorcraftstovl-aerodynamics-and-dynamics)

06.05 Viscous Flow Computation, Modeling, and Control
[40](#viscous-flow-computation-modeling-and-control)

06.06 Internal Fluid Mechanics for Aeropropulsion Systems
[40](#internal-fluid-mechanics-for-aeropropulsion-systems)

06.07 Multi-Disciplinary Design Optimization and System Analysis of
Aerospace Vehicles
[41](#multi-disciplinary-design-optimization-and-system-analysis-of-aerospace-vehicles)

06.08 Modeling & Simulation of Aerospace Vehicles
[42](#modeling-simulation-of-aerospace-vehicles)

06.09 Hypersonic Airbreathing Propulsion & Vehicle Aerodynamics
[42](#hypersonic-airbreathing-propulsion-vehicle-aerodynamics)

06.10 Intelligent Design Methods for Aerospace Vehicles
[43](#intelligent-design-methods-for-aerospace-vehicles)

06.11 Instrumentation, Sensors, and Controls for Propulsion and Power
Systems
[43](#instrumentation-sensors-and-controls-for-propulsion-and-power-systems)

06.12 Revolutionary Propulsion, Propulsion Systems and Components
[44](#revolutionary-propulsion-propulsion-systems-and-components)

07 Experimental Flight Research [44](#experimental-flight-research)

07.01 Very High Altitude Aircraft Technology
[44](#very-high-altitude-aircraft-technology)

07.02 Flight Sensors, Sensor Arrays and Airborne Instrumentation
[45](#flight-sensors-sensor-arrays-and-airborne-instrumentation)

07.03 Hypersonic Vehicle Design and Systems Technology
[45](#hypersonic-vehicle-design-and-systems-technology)

07.04 Integrated Propulsion Systems for Airbreathing Hypersonic Flight
[46](#integrated-propulsion-systems-for-airbreathing-hypersonic-flight)

# 01 Aviation Safety & Capacity 

Aviation Safety represents the effective interaction and integration of
five component technologies: 1) zero-tolerance for error in safety
critical software and hardware, including software design and testing,
power and propulsion development, propulsion control and integration; 2)
design and implementation of an effective system to detect and restrict
propagation of error and failure in system heath monitoring and data
analysis; 3) environmental impact on system performance, including
effects of aging, stress, and icing and on information to human
monitors/operators; 4) effective and safe design for control of multiple
aircraft in the airspace system, through the integration of air and
ground based air traffic systems; and 5) integration of human factors in
all aspects of the aviation systems operation.

## 01.01 Human Factors in Aviation Operations 

Lead Center: ARC

An important objective in aviation human factors research is to address
the interaction of humans with engineered systems. As flight and Air
Traffic Control crew roles evolve from those of systems operators to
those of systems managers, innovative technologies (devices, techniques,
tools, models, and procedures) are needed that pertain to the
automation, environment, crew information processing, decision-making,
and associated cognitive factors. Innovative and economically attractive
approaches are sought to advance technologies supportive of both flight
safety and improved efficiency in the following areas:

**Reliable Operations**

-   Individual and crew performance factors.

-   Distributed decision-making involving operators, controllers and
    dispatchers.

-   Fatigue and circadian evaluation methods and countermeasures.

-   Error reduction in aircraft maintenance.

-   Methods of integrating air and ground roles and responsibilities
    under advanced Air Traffic Management (ATM) concepts.

-   Technologies for training on advanced systems and for evaluation of
    training effectiveness.

-   Human performance measurement technology suitable for use in and
    assessment of operational environments.

-   Simulation and modeling tools to assess benefits of new concepts.

    **Information Management and Display**

-   Advanced display technologies.

-   Integrated displays and procedures.

-   Operational concepts and crew system interfaces.

    **Human-Automation Interaction**

-   Design methods for human-centered automation.

-   Status monitoring systems that inform, advise, or aid the flight
    crew.

-   Flight path planning, re-planning, and communication aids.

## 01.02 Advanced Concepts in Air-Traffic Management  {#advanced-concepts-in-air-traffic-management .unnumbered}

Lead Center: ARC

Air-Traffic Management (ATM) combines the traditional separation
assurance performed by Air-Traffic Control (ATC) and the flight-path
management functions concerned with improving system capacity and
capability. The challenge for the next generation ATM system is to
accommodate growth in air traffic while reducing the aircraft accident
rate by a factor of five within 10 years, and by a factor of ten within
20 years. This can only be achieved by the introduction of technical
innovations in communication, navigation, and surveillance (CNS) and by
the development of decision support tools for controllers, pilots and
airline operations. It also requires a new look at the way airspace is
managed and automation of some crew functions, thereby intensifying the
need for a careful integration of machine and human performance.
Innovative and economically attractive approaches are sought to advance
technologies in the following areas:

-   Decision support tools (DST) to assist pilots, controllers and
    dispatchers in all parts of the airspace (en route, terminal and
    surface).

-   Integration of DST across different airspace.

-   Simulation and modeling tools to assess benefits of new concepts.

-   Integration of tools across different airspace.

-   Technologies and concepts leading to greater airborne operational
    independence.

-   Flight path planning, re-planning, and communication aids.

-   Distributed decision making involving operators and controllers.

-   Effect of communication, human performance, and other delays on the
    stability of the airspace.

-   System recovery and safety in the event of failure of sensors and
    decision support tools.

-   Weather modeling and improved trajectory estimation.

-   Advanced displays.

-   Methods of integrating air and ground roles and responsibilities.

-   Human factors and workload concepts relating to safe
    control/integration of aircraft and other ground vehicles systems.

    In addition, at airports the safe ground movement of aircraft,
    logistics and maintenance vehicles, and emergency vehicles is
    essential. Under adverse weather conditions (and particularly during
    emergency conditions) this safety is difficult to ensure and can be
    compromised. This subtopic solicits proposals for the development of
    novel concepts and innovative methods to integrate simultaneous
    movement of the ground vehicle service fleet and the aircraft fleet.
    The concept must address and provide for the needs of the ground
    vehicles, as well as aircraft. It must also address both normal and
    emergency operations. Concept development should include (but not be
    limited to) consideration of the technical areas listed above for
    Advanced Concepts in Air-Traffic Management and the following
    additional areas:

-   Implementation of Global Positioning System (GPS) navigation
    including assessment of system accuracy and environmental effects.

-   Data link - The concepts for implementing a compatible data link
    would be examined. Data transfer rates, error rates, link margins
    and a traffic analysis should be studied in the process of
    developing candidate data link hardware concepts.

-   System Integration - Development of a recommended system design that
    insures compatible simultaneous operation of aircraft and ground
    support vehicles during low visibility conditions.

## 01.03 Aircraft Ice Protection Systems  {#aircraft-ice-protection-systems .unnumbered}

Lead Center: LeRC

Improved protection against in flight aircraft icing remains an
important objective in aviation safety. NASA seeks proposals that
address ice protection, detection, and remote sensing technologies.
Proposals are invited that offer improvements through innovative design
concepts or integration of existing technologies. Of particular interest
are technologies that are compatible with emerging technologies being
utilized in new aircraft designs (i.e., sensitive electronic systems,
advanced wing design). Onboard systems must be aerodynamically
non-intrusive, practical, and must consider weight, power, and size for
integration into aircraft. This subtopic solicits innovative concepts
that will lead to highly effective and efficient ice protection systems
and techniques that are applicable to all classes of aircraft. To
receive consideration for funding, all proposals submitted under this
subtopic must demonstrate significant advancement over existing
technologies. The areas of greatest interest are:

-   Non-obtrusive and practical in-flight broad-area reactive ice
    detection that is sensitive to the full possible spectrum of
    temperatures, droplet sizes, and liquid water contents.

-   Practical, in-flight and/or ground-based, real-time, remote sensing
    of the super-cooled water droplet and temperature environment.
    Technology must be capable of quantifying the environment to allow
    for the prediction of the severity of airframe icing, and to
    identify potential avoidance and escape routes, and must have
    practical range and cloud penetration capability.

-   Lightweight, low power, and low-cost de-icing and anti-icing
    systems, including technologies that protect composite structures. A
    system must have minimal aerodynamic impact in both the normal and
    icing environments and should be capable of operating automatically
    or with minimal pilot interaction.

-   Onboard systems that can measure and assess changes in the
    aircraft\'s overall aerodynamic characteristics in real-time to
    provide the pilot advanced warning of hazardous performance effects
    caused by ice accretions.

-   Onboard ice management systems that operate, diagnose, and identify
    the status of the aircraft\'s ice protection systems. The diagnostic
    procedures must provide the pilot with a system operation status
    during flight and hardware maintenance updates as required. These
    systems should include the dual capacity to transmit meaningful ice
    sensing information to flight system displays and to ground-based
    weather service networks.

## 01.04 High-Integrity Systems and Algorithms  {#high-integrity-systems-and-algorithms .unnumbered}

Lead Center: LaRC

The simultaneously increasing complexity of flight systems, and demand
for their safe and reliable operation motivate development of techniques
for design of high-integrity avionics hardware and software. These
include formal, system-level methods for design of hardware and
software, providing verifiably safe and reliable execution of the
avionics functions. They also include guidance, navigation, and control
(GNC) and other vehicle management algorithms that contribute to flight
integrity by detecting and identifying adverse conditions such as
vehicle faults or erroneous controlled flight, then reconfiguring the
vehicle\'s GNC laws to ameliorate these conditions. In particular,
innovative approaches are sought in two main areas: (1) specification,
design, and analysis methods for high-integrity digital systems, and (2)
theory for synthesis and analysis of GNC algorithms and laws that
preserve performance or degrade gracefully as the vehicle experiences
breakdown of subsystems.

The system design methods of interest include the following:

-   Mathematics-based methods for specification, design, and analysis of
    digital systems.

-   Techniques and tools for integrating formal methods with existing
    methods, tools, languages, and development standards (such as,
    RTCA/DO-178B).

-   Metrics, measures, and experimental assessment of the effectiveness
    of particular software development techniques and processes.

-   Software safety and risk assessment methods.

-   Verified libraries for semi-automatic proof checkers.

-   Executable specification languages with complete formal semantics.

-   Formally defined specification and programming languages for
    developing time-critical applications and distributed and parallel
    software.

-   Automatic program generators.

-   Error detection and assessment methods, especially automated testing
    and verification techniques.

-   Automated tools and environments to support managing and developing
    safety-critical systems.

-   Innovative approaches to software and systems reuse.

    The GNC algorithms of interest include theory and synthesis
    techniques as follows:

-   Rapid reselection or recalculation of the vehicle\'s flight profile
    and/or GNC laws to accommodate sudden degradation of or change in
    its dynamics.

-   Efficient and reliable algorithms for fault detection and
    identification (FDI) with emphasis on FDI of system-level faults
    which adversely affect the vehicle\'s dynamics.

-   GNC laws that are robust or insensitive to system failures and/or
    FDI errors.

    Approaches that integrate elements from both areas are especially
    sought.

## 01.05 Automated On-Line Health Management and Data Analysis  {#automated-on-line-health-management-and-data-analysis .unnumbered}

Lead Center: DFRC

Online health monitoring is a critical technology for improving
transportation safety in the 21st century. Safe, affordable, and more
efficient operation of aerospace vehicles requires advances in online
health monitoring of vehicle subsystems and information monitoring from
many sources over local/wide area networks. On-line health monitoring is
a general concept involving signal processing algorithms designed to
support decisions related to safety, maintenance, or operating
procedures. The concept of on-line emphasizes algorithms that minimize
the time between data acquisition and decision-making. This subtopic
seeks solutions for on-line aircraft or spacecraft subsystem health
monitoring. Solutions should exploit multiple computers communicating
over standard networks where applicable. Solutions can be designed to
monitor a specific subsystem or a number of systems simultaneously.
Resulting commercial products might be implemented in a distributed
decision-making environment such as a virtual flight research center, a
disciplinary-specific collaborative laboratory, an on-board diagnostics
system, or a maintenance and inspection network of potentially global
proportion. Proposers should discuss who the users of resulting products
would be, e.g., research/test/development; manufacturing; maintenance
depots; flight crew; airports; flight operations or mission control; air
traffic management; or airlines. Proposers are encouraged to discuss
data acquisition, processing, and presentation components in their
proposal. Examples of desired solutions targeted by this subtopic
include:

-   Real-time autonomous sensor validity monitors.

-   Flight control system or flight path diagnostics for predicting loss
    of control.

-   Automated testing and diagnostics of mission-critical avionics.

-   Structural fatigue, life cycle, static, or dynamic load monitors.

-   Automated nondestructive evaluation for faulty structural
    components.

-   Electrical system monitoring and fire prevention.

-   Applications that exploit wireless communication technology to
    reduce costs.

-   Model-reference or model-updating schemes based on measured data
    that operate autonomously.

-   Proactive maintenance schedules for rocket or turbine engines,
    including engine life cycle monitors.

-   Predicting or detecting any equipment malfunction.

-   Middleware or software toolkits to lower the cost of developing
    online health monitoring applications.

-   Innovative solutions for harvesting, managing, archival, and
    retrieval of aerospace vehicle health data.

## 01.06 Propulsion & Airframe Failure Data & Mitigation  {#propulsion-airframe-failure-data-mitigation .unnumbered}

Lead Center: LeRC

NASA is concerned with data, analysis, concepts, and health monitoring
that apply to prevention of catastrophic engine and airframe failures,
and mitigation of hazardous or accident conditions. All classes and
types of aircraft are included. Research is desired which treats the
following issues: Aging aircraft (including airframe, engines, and
sub-systems) and the potential problems therein. Catastrophic engine
failure prevention and light-weight containment of fragments. Occupant
protection in a crash, including dynamic analysis, restraints, and
structural interaction. Prevention of in-flight and post-crash fires,
including detection & suppression concepts and fuel & fuel system
modifications to reduce flammability, provide inerting, and/or reduce
post-crash spills. Low-cost methods of obtaining related failure and
crash data and performing experimental testing. Integration of
technologies into existing or new aircraft for the above failure,
prevention, and mitigation issues.

# 02 High Speed Travel  {#high-speed-travel .unnumbered}

NASA\'s High Speed Research Program is investigating technology concepts
that support economic and environmental requirements of a successful
supersonic airliner, moving them out of the laboratory toward practical
application. NASA seeks innovations in aerodynamic performance
technologies encompassing high lift, transonic, and supersonic cruise
conditions, in airframe materials and structures that integrate minimum
weight with improved properties and durability and in flight deck
systems to improve pilot performance without forward windows. NASA also
seeks approaches to resolving environmental issues such as noise
reduction and atmospheric effects from engine emissions. Technologies
including innovative engine cycles, high temperature engine materials,
and propulsion systems that will meet low emissions and low noise
requirements also are requested.

## 02.01 Supersonic Transport Airframe Technologies  {#supersonic-transport-airframe-technologies .unnumbered}

Lead Center: LaRC

NASA seeks innovative technology advances that will support development
of long distance supersonic commercial transport aircraft. Innovations
should provide significant impact on performance, safety and cost, and
environmental effects of supersonic transport aircraft. These advances
should enable industry to render informed decisions regarding commitment
to supersonic transport (SST) production, provide technical solutions
for ensuring economic viability and environmental compatibility of
future supersonic transport aircraft, and be directed toward validated
designs and design methods for application by industry in supersonic
aircraft programs. Proposers should show affordable application of the
technologies and pathways to commercialization that includes FAA
certification if appropriate. Innovations in the following technical
areas are sought:

**Aerodynamic Performance:** Technology concepts that will provide large
improvements in aerodynamic performance (supersonic and transonic cruise
and low speed, high lift) and aerodynamic control of commercial
high-speed air transports. Improvements in supersonic cruise performance
are essential to ensure minimum weight supersonic transport designs.
Improvements at low speeds in takeoff and landing performance are
critical to reduce thrust required and engine takeoff noise. Effective
aerodynamic control concepts must provide proper vehicle trim, dynamic
response, and flight safety margins with minimum-weight penalty. A major
challenge in all of the speed regimes is to develop highly leveraged
technologies that integrate well with minimum weight, complexity, and
off-design penalties-.

**Environmental Issues:** Approaches to resolution of environmental
issues associated with the design and operation of a supersonic
transport are sought. NASA seeks definition of and technology
foundations for atmospheric effects from engine emissions, sonic boom,
and atmospheric radiation.

-   Innovative concepts for jet noise reduction associated with
    propulsion systems appropriate for the supersonic transport.

-   Enhanced understanding of the fundamentals of mixing noise and
    approaches for modeling and prediction.

-   Effects of sonic booms on marine wildlife.

    **Flight Deck:** Innovative and economically attractive technology
    concepts and systems that will provide significant improvements in
    the flight deck for commercial high speed air transports:

-   Advanced, high-resolution CCD sensors.

-   X-band and millimeter wave radar technology (including
    electronically scanned antennas/systems) for airborne traffic and
    ground object detection and ground imaging (integrated with existing
    weather/wind shear radar functions).

-   High-resolution, wide field-of-view display technology and concepts.

-   Ultra high bandwidth real time video image processing, sensor fusion
    and image-based object detection processing (especially in the area
    of machine algorithms for air-to-air collision and near-miss target
    detection from on-board video cameras).

-   Lightweight, high resolution, head-mounted displays.

    **Materials:** Innovative solutions are sought for the following:

-   Low-cost fabrication of PMC composite sandwich panels, including
    metallic surface preparations for bonding the PMC to titanium
    honeycomb.

-   Low-cost fabrication of PMC composite sandwich and skin-stringer
    panels, including advanced tow placement with *in situ*
    consolidation, resin transfer molding, and/or resin infusion.

-   Lightweight, multi-use insulation that provides thermal, acoustic,
    and radiation protection for the fuselage and/or thermal protection
    for the fuel in the wing.

-   High-temperature sealant material for the wing fuel tanks.

    **Structures:** Innovative solutions are sought for the following:

-   Analytical methods for composite structures to determine any of the
    following: compressive failure under combined loading, design of
    damage-tolerant sandwich panels including the effects of crack
    turning near tear straps, or dynamic fracture mechanics of composite
    fuselage shells subject to penetration.

-   Innovative, lightweight wing/fuselage structural design concepts
    that use low-cost manufacturing methods.

## 02.02 Supersonic Transport Propulsion Technologies  {#supersonic-transport-propulsion-technologies .unnumbered}

Lead Center: LeRC

NASA seeks innovative high-leverage propulsion technologies essential
for an economically viable supersonic transport (SST). In particular,
high-temperature engine materials are sought that will meet weight,
performance, and durability requirements. Also desired are
environmentally and economically compatible propulsion components that
produce low nitrogen oxide emissions, low noise, high performance, and
low specific fuel consumption. Innovative propulsion instrumentation and
controls concepts which are enabling for the critical propulsion
components or for improved performance and operability of the overall
SST propulsion system are also of interest. Specifically, proposals that
offer innovations or improvements in the following technical areas are
sought:

**Enabling Propulsion Materials**

-   Combustor lining materials with temperature capabilities up to 1200
    C with no film cooling.

-   Nozzle materials with temperature capabilities up to 1000 C.

-   Materials with durability of 18,000 hours.

-   Innovative manufacturing process modeling, and design methods for an
    economically viable SST.

    **Supersonic Transport Propulsion System Critical Components**

-   Low emissions (5 gram NOx/kg fuel), high temperature minimally
    cooled combustors incorporating, as appropriate, advanced materials
    for high temperature conditions and 18,000 hour durability.

-   Low-noise, lightweight, and highly efficient exhaust nozzles (noise
    below FAR Stage 36, Stage III and a cruise thrust coefficient of
    0.98).

-   Low-noise, high-flow per frontal area, efficient fan components.

-   Mixed compression inlet system for high-performance (cruise pressure
    recovery of 0.93), and low approach noise with stable operation.

    **Alternate Propulsion System Concepts**

-   Innovative engine cycles which would provide for both environmental
    compatibility and economic viability for SST\'s.

    **Propulsion Instrumentation and Controls**

-   Innovative instrumentation and sensors that provide information for
    diagnostics and control of the SST propulsion system and critical
    components. Optical, thin film and MEMS (Micro Electro-Mechanical
    Systems) sensors measuring temperature, pressure, density, velocity
    and emissions under harsh environments are of special interest.

-   Advanced concepts for active control of SST inlet system, robust
    control of overall propulsion system, integration of
    inlet/engine/flight control, and active control of low emission
    combustion system.

# 03 Subsonic Transport Environmental Compatibility  {#subsonic-transport-environmental-compatibility .unnumbered}

NASA has very aggressive goals for ensuring the noise and emission
environmental compatibility of future aircraft. They are to reduce the
perceived noise levels of future aircraft by a factor of two (10 EPNdB)
within ten years, and a factor of four (20 EPNdB) within 20 years and to
reduce emissions of future aircraft by a factor of three within 10 years
and a factor of five within 20 years. These goals are necessary to meet
increasingly stringent local, national, and international noise and
emission regulations while enhancing operating safety and productivity
and increasing aviation system throughput. Noise prediction and
reduction technologies are required in the areas of propulsion source
noise, nacelle aeroacoustics, airframe noise, and noise minimal flight
procedures for jet and propeller airplanes and rotorcraft. In addition,
aircraft interior noise reduction technologies are required to improve
passenger and crew comfort. Emissions reduction technologies are
required for a number of aerosols and particulates including nitrogen
oxides, sulfur oxides, carbon dioxide, and water vapor.

## 03.01 Aircraft Noise Prediction and Reduction  {#aircraft-noise-prediction-and-reduction .unnumbered}

Lead Center: LaRC

Innovative concepts, techniques, and methods are needed in a number of
areas of acoustics for developing more efficient and environmentally
acceptable airplanes and rotorcraft. Improvements in aircraft noise
prediction and control are needed for jet, propeller, rotor, fan,
turbomachinery, and airframe noise sources for community residents,
aircraft passengers and crew. Innovations in the following specific
areas are solicited:

-   Fundamental and applied computational fluid-dynamics techniques for
    aeroacoustic analysis.

-   Reduction concepts and prediction methods for jet noise of subsonic,
    supersonic, and hypersonic aircraft.

-   Concepts for active and passive control of fan, turbomachinery, and
    jet noise in engine nacelles.

-   Reduction concepts and prediction methods for rotorcraft and
    advanced propeller aerodynamic noise.

-   Simulation and prediction of aeroacoustic noise sources including
    airframe noise and propulsion-airframe integration.

-   Computational and analytical structural acoustics techniques for
    aircraft interior noise prediction.

-   Concepts for active and passive interior noise control for aircraft.

-   Prediction and control of high-frequency aeroacoustic loads on
    advanced aircraft structures and the resulting dynamic response.

## 03.02 Propulsion System Noise Prediction and Reduction  {#propulsion-system-noise-prediction-and-reduction .unnumbered}

Lead Center: LeRC

NASA's aggressive subsonic aircraft noise reduction goals will require
revolutionary advances in propulsion technologies. Some of the key
technologies needed to achieve these goals are fast, highly accurate
computational acoustic methods, advanced source identification
techniques, and revolutionary propulsion systems for reduced noise and
low cost. Advanced computational methods are needed that can both model
the relevant flow physics and be used in a design environment. Source
identification techniques are needed for both wind tunnel model scale
tests and full scale static engine tests to determine the locations of
the disturbances that contribute to the overall engine noise levels. It
is anticipated that revolutionary noise reduction concepts will be
needed to achieve future subsonic noise reduction goals. Therefore,
advanced noise reduction concepts need to be identified that provide
economical alternatives to conventional propulsion systems. NASA is
soliciting proposals in one or more of the following areas for
Propulsion System Noise Prediction and Reduction:

-   Highly accurate and efficient computational methods for the
    simulation of turbomachinery noise sources. Methods should have the
    potential of being 100 (or more) times faster than existing methods
    while accurately resolving acoustic disturbances.

-   Innovative source identification technique for turbomachinery noise.

-   The technique shall be described and demonstrated on a relevant
    source. A simple source may be used

-   where the solution is known to demonstrate the technique. A clear
    explanation on how the technique can be applied to turbofan engines
    should be included. The technique should be capable of identifying
    sources contributing to dominant engine components, such as fan and
    jet noise.

-   Fan Noise: The technique shall be capable of separating fan sources
    such as fan-alone versus fan/stator interaction for both tones and
    broadband noise. Sufficient resolution is needed to determine the
    location of the dominant sources on the aerodynamic surfaces.

-   Jet Noise: The technique shall be capable of locating both internal
    and external mixing noise for dual-flow nozzles found in modern
    turbofans.

-   Innovative turbofan source reduction techniques.

-   Methods shall emphasize noise reduction methods for fan, jet and
    core components without compromising performance for turbofan
    engines. A resulting engine system that incorporates one or more of
    the proposed methods should be capable of reducing perceived noise
    levels for subsonic engines anywhere from 10 to 20 EPNdB relative to
    FAR 36, Stage 3 certification levels.

## 03.03 Subsonic Aircraft Systems Emissions Reduction  {#subsonic-aircraft-systems-emissions-reduction .unnumbered}

Lead Center: LeRC

Current environmental concerns with subsonic aircraft center around
global warming an the impact on the earth\'s climate and, if not
addressed, may threaten future market growth. Carbon dioxide (CO2) and
oxides of nitrogen (NOx) are the major emittants of concern coming from
commercial aircraft engines. CO2 and NOx are both greenhouse gases which
impact the warming of the earth\'s climate. Also, NOx can destroy ozone
in the upper atmosphere which protects humans from harmful uv radiation
from the sun, and NOx can produce ozone in the lower atmosphere around
airports which appears as smog and causes breathing problems in humans.
Current state-of-the-art engines and combustors in most subsonic
aircraft are fuel efficient and meet the 1996 ICAO nitrogen oxide(NOx)
limits. The Kyoto Agreement is applying pressure for additional CO2
reductions, and Europe and the U.S. Environmental Protection Agency are
applying pressure for additional NOx reductions at takeoff and possibly
cruise conditions. Stringent CO2 and NOx limits could result in
emissions\' fees or limited access to some countries. Also, recent
observations of aircraft exhaust contrails (from both subsonic and
supersonic flights) have resulted in growing concern over aerosol,
particulate, and sulfur levels in the fuel. In particular, aerosols and
particulates from aircraft are suspected of producing high altitude
clouds which could adversely affect the earth's climatology.

NASA has set some very aggressive goals for reducing emissions of future
aircraft by a factor of three within ten years and by a factor of five
within twenty years. Advanced concepts research for reducing CO2 and
analytical and experimental research in characterization (intrusive and
non-intrusive) and control (through component design, controls, and/or
fuel additives) of gaseous, liquid and particulates of aircraft exhaust
emissions is sought. Specific subsonic aircraft operating conditions of
interest include the landing-takeoff cycle as well as the in-flight
portion of the mission. Areas of particular interest include the
following:

-   New concepts for reducing carbon dioxide, oxides of nitrogen (NO,
    NO2, NOy), unburned hydrocarbons; carbon monoxide, particulate, and
    aerosols emittants (novel propulsion concepts, injector designs to
    improve fuel mixing, catalysts, additives, etc.);

-   New fuels for commercial aircraft which minimize carbon dioxide
    emissions;

-   Innovative active control concepts for emission minimization with an
    integrated systems focus including emission modeling for control,
    sensing and actuation requirements, control logic development, and
    experimental validation are of interest; and

-   New instrumentation techniques are needed for the measurement of
    engine emissions such as NOy, SOx, HOx, atomic oxygen and
    hydrocarbons in combustion facilities and engines. Size, size
    distributions, reactivity, and constituents of aerosols and
    particulates are needed, as are temperature, pressure, density, and
    velocity measurements. Optical techniques that provide 2D and 3D
    data; time history measurements; and thin film, fiber optic, and
    MEMS-based sensors are of interest.

# 04 Space Transportation 

Affordable access to space must be the ultimate goal in order for
America to realize the potential for research and commerce in space.
NASA envisions the space frontier as a busy crossroads of U.S. led
international science, research, commerce, and exploration. Our
experience with this vast resource has already yielded new treasures of
scientific knowledge, life-enhancing applications for use on Earth and
fantastic celestial discoveries. The potential for the future seems
almost limitless. Goals include reducing the payload cost to Low Earth
Orbit by an order of magnitude, from \$10K to \$1K per pound, within 10
years and from \$1K to \$100\'s per pound by 2020.

## 04.01 Launch Vehicle Technologies 

Lead Center: MSFC

Advanced launch vehicle systems will require high mass fraction,
reliable system performance, and extended reusability in order to
achieve cost goals. This subtopic emphasizes innovative hardware
concepts, subsystems, and design and analysis tools to support
development of launch vehicles (not including propulsion systems) while
lowering operations cost. Methods, approaches, design and analysis
tools, and hardware developed under this subtopic should address
technical issues related to tanks, thermal protection systems,
structures, guidance, navigation and control (GN&C), supporting
discipline analysis, and system integration issues. Specific areas of
interest for advanced technologies and innovations include the
following:

-   Low-cost designs, concepts, and manufacturing processes for tanks
    and vehicle structures; and innovative approaches and techniques to
    reduce range costs of small launchers such as Bantam.

-   Control and health management of vehicle structural systems by using
    sensors and effectors that have little influence on the structural
    system parameters with the exception of the structural damping
    parameters. Continuous estimation of center of mass and inertial
    properties. Real-time retuning of control algorithms to reflect
    known changes in vehicle response or sensor performance, and
    accurate, continuous estimation of fuel remaining on-board.

-   Thermal-protection system concepts, instrumentation analysis tools,
    and testing techniques for reusable vehicles, cryo-tanks, and
    vehicle base regions.

-   Innovative system level models that support the design and analysis
    of integration of vehicle subsystems and propulsion systems into the
    vehicle (such as the ability to assess operability of the systems
    and to model the impacts of design changes on vehicle cost,
    operations, vehicle aerodynamics, and controllability).

-   Integrated CAD, solid-model, structural, dynamic, thermal, and
    fluid-flow analysis methods for multi-disciplinary analysis and
    optimization of launch vehicles, and vehicle subsystems; and
    improved vehicle analysis tools in the areas of stress, thermal,
    structural, and fluid dynamics.

-   Automated propellant management systems; and technologies and
    innovative engineering capabilities to produce propulsion storage,
    feed, pressurization, fill and drain, vent, and support/restraint
    systems that are robust, lighter, or require less volume.

-   Optimal fault detection and redundancy management strategies,
    on-board autonomous mission planning/abort mode determination,
    execution software and advanced navigation hardware/software
    architectures, and adaptive GN&C utilizing data from sensors such as
    the GPS.

-   Analysis and testing techniques for prediction and measurement of
    damage and stress including life prediction and dynamic response in
    structures containing ceramic-matrix, metal-matrix composites, or
    other composite materials; and nondestructive evaluation of
    structural integrity of vehicle materials and subsystems. Methods
    for efficient characterization of frequency response functions of
    large structures, and analysis and testing techniques for passive
    and active vibration isolation devices for launch vehicles and
    payloads.

##  {#section-4 .unnumbered}

## 04.02 Advanced/Exotic Propulsion System Technologies  {#advancedexotic-propulsion-system-technologies .unnumbered}

Lead Center: MSFC

Innovative, non-traditional propulsion technologies, devices and systems
that could contribute to dramatic reductions in launch costs and
in-space transportation time are solicited. Development of such
technologies are sought to enable ambitious commercial, robotic, and
human exploration missions in the future. Concepts that can be applied
to high-payoff commercial applications are of particular interest.
Important aspects that should be addressed in the proposal include
analyses addressing feasibility and mission suitability, and plans for
demonstrating concept feasibility via test/experiment. Areas of interest
include the following:

-   \"Breakthrough\" technologies and concepts based on the results of
    \"leading edge\" physics research. Of special interest are
    techniques for manipulation of relativistic phenomena, exploitation
    of vacuum zero-point fields and/or hyper-fast transportation

-   Technology developments in antimatter production, storage,
    transportation, and utilization for application as a propulsion
    energy source.

-   Propulsion applications of technology innovations in fission or
    fusion energy production.

-   Technology innovations for offboard, beamed power-driven propulsion.
    Of special interest is research leading to economical launch of
    small payloads.

-   Development of propulsion systems based on solar, laser or
    magnetically propelled sails or current loops. Of special interest
    are concepts that could be used for interstellar exploration.

-   Components and subsystems for advanced airbreathing/rocket combined
    cycle engines, deeply cooled turbojets and liquid air cycle engine
    concepts.

-   Advanced high-energy-density propellants and propellant
    storage/transfer techniques.

## 04.03 Space Transfer Technologies  {#space-transfer-technologies .unnumbered}

Lead Center: MSFC

Advanced, innovative, technologies and system concepts that will achieve
reductions in in-space transportation costs are sought. Technologies
which offer significant mass or specific impulse improvements over
current chemical systems are sought. Other technologies or system
concepts that offer improved durability, reduced cost, and reusability
over current systems are also of interest. Development of such systems
and related technologies are sought to enable ambitious commercial,
robotic, and human exploration missions in the future. Concepts that can
be applied to high-payoff commercial applications are of particular
interest. Proposals should emphasize the potential for reduction in
cost, and improvements in performance, reliability, operability or
maufacturability over existing systems. Areas of specific interest shall
include:

-   Chemical propulsion and fluid systems for engines that are used for
    orbit transfer, in-space transfer and ascent/descent missions are of
    interest. Other mission applications may include small chemical
    propulsion for reusable launch vehicles (in-space maneuvering and
    attitude control systems). Systems that use non-toxic (oxygen based)
    bipropelllants are of primary interest, but advances in conventional
    hypergolic propellants are also sought. One type of propellant
    combination of specific interest for missions to the Moon, Mars, or
    other planetary bodies include those that can be made from
    indigenous materials. Figures of merit include lower weight, reduced
    cost, longer life, improved maintainability, and higher reliability.
    System/component technologies include: materials compatible with
    high-temperature, oxidizing and reactive environments; components
    for fluid isolation, pressure/mass flow regulation, relief quick
    disconnect, and flow control; techniques for metering, injection,
    and ignition of fluids in combustion devices; gaseous storage and
    pressurization systems; non-intrusive component and system
    diagnostics; systems for liquid-free gas venting, gas free liquid
    propellant delivery, and mass quantity gauging in reduced gravity
    environments and systems/components for actuation of aero-surfaces
    and valves using hydraulic, electro-hydraulic or electromechanical
    power drives.

-   Enhancements to or development of new propulsion systems that use
    energy sources that do not have to be launched. These may be sources
    that are available in space such as solar interactions,
    electromagnetic fields, or atmospheres for capture. Or these sources
    may be the exchange of momentum between two bodies. Technologies may
    be in the following areas:

-   Components or system level technologies for solar thermal
    propulsion. These may include: solar collectors or concentrators,
    lightweight concentrator support structure, engine/thruster for
    solar energy conversion, controls and pointing technologies, and
    system level technologies.

-   Electrodynamic tether propulsion systems or component level
    technologies. These may include: tether materials or coatings for
    improved performance and lifetime, designs and analysis for tether
    behavior and dynamics, testing and characterization techniques for
    tethers, and system level technologies.

-   Momentum transfer tether propulsion systems or component level
    technologies. These may include: tether materials or coatings for
    improved performance and lifetime, designs and analysis for tether
    behavior and dynamics, testing and characterization techniques for
    tethers, and system level technologies.

-   Technologies for aerocapture or aeroassisted propulsion systems.
    These may include materials and thermal protection system
    technologies, modeling and analysis tools, and system integration
    issues.

## 04.04 Lightweight Engine Components  {#lightweight-engine-components .unnumbered}

Lead Center: MSFC

Next generation space propulsion systems must address the significant
challenge of achieving lower life-cycle cost, increased performance,
higher reliability and increased payload or vehicle mass fraction
relative to current propulsion systems. Recent emphasis in the
performance area has been placed on development of components having
increased operational temperature capability, reduced weight, and
reusability. Innovative designs and processing methodologies offer
potential for cost reduction. NASA, through this subtopic, is seeking
research proposals which emphasize justification for selection of
material constituents, (e.g. fibers, interface coatings, and fabric
architecture), control of processing parameters to ensure successful
scale-up and reproducibility, process verification with microscopic
analysis (e.g. SEM, XRD, BET, etc.) and macroscopic analysis (e.g.
tensile strength, interlaminar shear strength, thermal and physical
properties, etc.), application specific verification by testing for
permeability, thermal shock, etc., and nondestructive evaluation of
components and/or stock material. Phase I & II plans should include
delivery of components, test data, and analysis as appropriate. Specific
areas of interest include the following:

-   Development of lightweight turbomachinery components \[e.g.
    integrally bladed disks (blisks), rotors, stators, housings, seals,
    etc.\] having capability to operate in hot ( 1000°C) hydrogen rich
    steam and oxygen rich environments.

-   Development of fabrication techniques capable of producing uniform
    densities in CMC blisks for thicknesses ranging from one to three
    inches, and diameters up to eighteen inches.

-   Innovative technologies providing lower cost, lightweight combustion
    components (e.g. cooled and uncooled thrust chambers and nozzles,
    high load capacity nozzle structural components, injector
    faceplates, minimal erosion throats, etc.) for LOX/H2 and LOX/RP
    environments.

-   Attachment methodology development for joining polymer matrix
    composites (PMC), CMC and ceramic components to metallic and
    nonmetallic components (e.g. cooling channel manifolds to nozzles,
    transmission of high torque loads from metallic rotors to CMC
    blisks, flanging or connection of ducts to metallics, brazing,
    diffusion bonding, etc.)

-   Ultrahigh temperature (greater than 2000 degrees Celsius) propulsion
    and plasma confinement development for solar thermal absorbers and
    nuclear thermal applications.

-   Innovative, low cost (with metrics), fabrication methodology
    development for preceding lightweight component applications.

-   Development of functionally gradient materials for preceding
    applications.

-   Innovative, lightweight composite feedlines, ducts, and housings for
    applications ranging from cryogenic temperatures to 300°C.

-   Advancements in the non-destructive evaluation of light weight
    engine components, including the use of embedded or surface mount
    smart sensors for real time monitoring of engine components.

-   Design of inducers with a suction performance capability of over
    85,000 suction specific speed with a inducer tip flow coefficient of
    over .10.

## 04.05 Rocket Engine Test Operations  {#rocket-engine-test-operations .unnumbered}

Lead Center: SSC

Proposals are solicited for innovative concepts in the area of test
operations. Proposals should support the reduction of overall propulsion
test operations costs (recurring costs) and/or increase reliability and
performance of propulsion ground test facilities and operations
methodologies. Specific areas of interest in this subtopic include the
following:

**Facility and test article health monitoring technologies:**

-   Non-intrusive sensors for measuring flow rate, temperature,
    pressure, rocket engine plume constituents, effluent gas detection,
    hydrogen leak detection, and hydrogen fires.

-   Automated leak detection and/or visualization system for facility
    and test article propellant systems.

-   On-line particulate and quality sampling for facility propellant
    (liquid oxygen and hydrogen) and support gas systems (helium,
    hydrogen, oxygen, nitrogen, and missile-grade air).

    **Improvement in ground-test operation, safety, cost-effectiveness,
    and reliability:**

-   Smart system components (control valves, regulators, and relief
    valves) which provide real-time closed-loop, control, component
    configuration, automated operation, and component health.

-   Cryogenic propellant transfer system operation technologies which
    include automated propellant transfer, automated propellant-line
    (liquid hydrogen) purge systems, and automated and/or manual
    propellant-line quick-disconnect systems.

-   Liquid hydrogen boil-off recovery or utilization systems.

-   Innovative designs and/or operational techniques for self-pumping,
    supersonic diffusers for altitude testing of rocket motors.

-   Long-life, liquid-oxygen-compatible seal technology.

-   Cryogenic storage tank lifetime monitor systems for temperature
    cycles, stress, acoustics, pressure and shock.

    **Application of System Science to ground test operations in a
    resource constrained environment:**

-   Digital simulations techniques to support decision making processes
    to address reliability, availability, and return on investment and
    training of environment for test conductors.

-   Techniques to improve high speed data acquisition and high speed
    video systems for test area data and video transmissions.

-   Techniques to reduce required sample size to maintain acceptable
    levels of confidence in cost data.

-   Risk management techniques.

# 05 General Aviation Revitalization  {#general-aviation-revitalization .unnumbered}

Numerous factors combine to create opportunities for revitalization of
the U.S. general aviation industry and the role of a small aircraft
transportation system for business and personal travel in the 21st
century. These include rapid growth in air travel (increasing pressure
on National Airspace System (NAS) capacity and safety and for affordable
NAS operations for the government and users), declining numbers of
communities served by scheduled air carriers, increasingly stringent
international environmental standards, an aging fleet of small aircraft,
and aggressive foreign competition. NASA seeks innovative technologies
supporting advances in flight systems, airspace and ground systems
infrastructure, integrated design and manufacturing and aircraft
configuration design concepts as well as general aviation propulsion
technologies.

## 05.01 General Aviation Transportation System Technologies  {#general-aviation-transportation-system-technologies .unnumbered}

Lead Center: LaRC

NASA seeks innovative technologies to support advances for small
aircraft transportation systems that substantially increase the demand
for retrofit of existing aircraft, new aircraft and airport and airspace
utilization. Of specific interest are advanced, affordable, certifiable
technologies for human-factors engineered display of flight information
for total situational awareness, and simplified integration of flight
controls with displays, and propulsion systems. In addition,
improvements are desired in cost-effective, user-friendly improvements
in weather, traffic, and NAS facilities' information services. NASA also
seeks innovations in manufacturing methods and materials.

Specifically, proposals are sought for the following areas:

**Aircraft Configuration**

-   Advanced concepts for roadable aircraft are desired. This category
    must include a sound business plan for production with a technical
    plan providing for compatibility with the emerging National Airspace
    System architecture and a certification plan to meet at least one of
    the following applicable FARs: Part 103 (Ultra-lite vehicle), Part
    21.24 (Primary Category Aircraft), Part 23 (Certified Aircraft) or
    Part 27 (Rotorcraft), or Part 21.191 Advisory Circular AC No: 20-27
    series (Experimental Homebuilt Aircraft).

    **Flight System Technologies**

#### Information Systems and Pilot Vehicle Interface 

Cost-effective advances in emerging navigation displays, graphical
depiction methods, intuitive cockpit display systems, flight controls,
voice interface, communications and human factors engineering
technologies to aid pilot decision making and to reduce cockpit
workload.

#### Certifiable COTS for System Hardware and Software 

#### Affordable cockpit systems including sensors, attitude-heading reference systems, terrain and obstacle avoidance systems, and applications for standardized databus system architectures such as firmware, software, design and maintenance tools, and flight information and management products for airplane systems status and flight planning.  {#affordable-cockpit-systems-including-sensors-attitude-heading-reference-systems-terrain-and-obstacle-avoidance-systems-and-applications-for-standardized-databus-system-architectures-such-as-firmware-software-design-and-maintenance-tools-and-flight-information-and-management-products-for-airplane-systems-status-and-flight-planning. .unnumbered}

**Integrated Design and Manufacturing**

-   Innovative manufacturing methods and materials providing significant
    advances in the cost, safety, weight, and cabin comfort for general
    aviation aircraft through materials technology, structural designs
    and assembly, and crash-worthiness.

    All proposals should include supportability plans (support
    infrastructure, maintenance requirements, operations, and training),
    certification plans (cite Specific FAR's), compatibility with
    current and future airspace architecture, and a clear path to
    commercialization.

## 05.02 Light Aircraft Engine Design, Systems, and Components  {#light-aircraft-engine-design-systems-and-components .unnumbered}

Lead Center: LeRC

NASA seeks proposals that offer dramatic improvements in acquisition and
life cycle costs, performance, safety and reliability; environmental
compatibility (noise, emissions and fuel), ease of operation and
passenger comfort through innovative propulsion concepts and/or
integration of innovative propulsion technologies. Emphasis is placed on
cost reduction, ease of operation and comfort. Anticipated benefits must
be defined using appropriate theoretical and experimental data. Concepts
with a clear path to commercialization are highly preferred. Offerors
should address commercialization plans and FAA certification issues.
Proposals are sought in the following areas:

**Propulsion System and Component Technologies**

NASA seeks engine concepts (piston, turbine, unconventional) and engine
component technologies for light aircraft that will result in
substantial improvements over current piston engines. Any improvements
in areas such as performance, safety, and environmental compatibility
must be accomplished with affordability as a prime consideration. The
offeror must demonstrate acquisition and life cycle costs that are at
least comparable to current propulsion system costs. Substantially
reduced costs, at least 50% less than current systems, are highly
preferred.

**Engine Control and Health Monitoring Technology**

NASA seeks proposals for low-cost electronic engine control and health
monitoring systems which substantially reduce pilot workload, fuel
consumption, and engine emissions, and increase time between overhaul
(TBO) and safety. Engine diagnostics should focus on pilot notification
of engine status and operability, post-flight diagnostic methods, trend
analysis and maintenance aides. Much of this technology already exists,
but it is too costly and/or too costly to certify for light aircraft. In
some cases, cost reductions by orders of magnitude must be achieved.
Development of methods for using commercially available high volume
hardware and achieving low-cost software production and validation is
encouraged. Paths to FAA certification must be described.

# 06 Next Generation Aircraft Systems Design & Analyses Tools  {#next-generation-aircraft-systems-design-analyses-tools .unnumbered}

The Aeronautics Enterprise is engaged in developing the tools,
techniques, and technologies to revolutionize the design and development
processes of the aerospace industry with the goal to reduce the aircraft
development cycle time by one-half. The concept of design spans the
evaluation of requirements, consideration of manufacturing, operations
support, and other non-traditional domains, effective utilization of
ground and flight test results, up to the point of actual manufacture.
Information technology, advanced physics-based analytical tools, methods
to control the process of design, and innovative test instrumentation
are key areas in this effort.

## 06.01 Advanced Measurement Science and Ground Testing Technology  {#advanced-measurement-science-and-ground-testing-technology .unnumbered}

Lead Center: LaRC

The demand placed on ground and space test programs continually expands,
requiring increased global measurement capability, or higher bandwidth
and higher spatial resolution single-point measurements. These systems
will provide more information per test hour, whether the goal is better
CFD code validation for aerodynamics or new models for advanced
aerospace systems. Sensors must now be available for both cryogenic and
high temperature operation and be able to provide accurate information
in a relatively severe vibration environment. Proposed innovations must
emphasize near term practical applications, characterize the degree of
improvement over existing technologies, and identify commercial
applications as much as possible. Proposals for general or investigative
studies and systems analysis are not acceptable. Suggested areas of
interest and specific technologies for possible development include the
following:

-   Boundary layer characterization in both conventional and cryogenic
    wind tunnels.

-   Model attitude and deformation measurement system providing 0.005
    degree accuracies in a highly dynamic vibratory environment.

-   A model force measurement system having an accuracy of the order of
    0.01% FS and insensitivity to temperature gradients over a -240 F to
    +150 F temperature range.

-   Micro-Electro-Mechanical Systems (MEMS) for aerodynamic
    measurements\--including flow velocity, pressure, shear stress,
    and/or acceleration.

-   Sensors and systems for optical diagnostics such as global surface
    pressure measurement for subsonic through hypersonic wind tunnels.

-   Innovative molecular sensors for environmental and combustion
    measurements.

-   Onboard data systems and advanced data transmission technologies for
    wind tunnel model applications.

-   Systems for measuring combustion efficiency in SCRAM-jet pulse
    facilities.

    Also, propulsion research instrumentation is needed for fundamental
    studies of basic phenomena, design code validation, and engine
    systems tests in aeropropulsion facilities. Of special interest are
    optical techniques that quantify multiple parameters at multiple
    spatial points to provide 2D and 3D data in turbomachinery. Time
    history data is also important. Fluid parameters of interest include
    temperature, pressure, density, and velocity. Surface parameters of
    interest include temperature, pressure, stress, strain, deformation,
    and defect detection. Fiber optic, thin film, and micro
    electro-mechanical devices are also of interest.

## 06.02 Unsteady Aerodynamics and Aeroelasticity  {#unsteady-aerodynamics-and-aeroelasticity .unnumbered}

Lead Center: LaRC

The technical discipline of aeroelasticity is a critical ingredient
necessary in the design process of a flight vehicle for assuring freedom
from catastrophic aeroelastic and aeroservoelastic instabilities. This
discipline requires a thorough understanding of the complex interactions
between a flexible structure and the unsteady aerodynamic forces acting
on the structure, and at times, active systems controlling the flight
vehicle. Complex unsteady aerodynamic flow phenomena, particularly at
transonic mach numbers, are also very important because this is the
speed regime most critical to encountering aeroelastic instabilities. In
addition, aeroelasticity is presently being exploited as a means for
improving the capabilities of high performance aircraft through the use
of innovative active control systems using both aerodynamic and smart
material concepts. Studies to develop analytical and experimental
methodologies for reliably predicting the effects of aeroelasticity and
their impact on aircraft performance, flight dynamics, and safety of
flight are valuable. Areas of development to be considered include the
following:

-   Design methodologies that include CFD steady and unsteady
    aerodynamics, flexible structures, and active control systems.

-   Methods to predict aeroelastic phenomena and complex steady and
    unsteady aerodynamic flow phenomena, especially in the transonic
    speed range. Aeroelastic phenomena of interest include flutter,
    buffet, buzz, limit cycle oscillations, and gust response; flow
    phenomena of interest include viscous effects, vortex flows,
    separated flows, transonic nonlinearities, and unsteady shock
    motions.

-   Efficient methods to generate mathematical models of wind-tunnel
    models and flight vehicles for performing vibration, aeroelastic,
    and aeroservoelastic studies.

-   Unique control concepts that employ smart materials embedded in the
    structure and/or aerodynamic control surfaces for suppressing
    aeroelastic instabilities or for improving performance.

-   Techniques that support simulations, ground testing, wind-tunnel
    tests, and flight experiments of aeroelastic phenomena.

## 06.03 Computation Advances for Aerospace Applications {#computation-advances-for-aerospace-applications .unnumbered}

Lead Center: ARC

Improved and enhanced computational techniques are solicited for solving
large-scale scientific and engineering problems in many aerospace
disciplines. Improvements desired are increased computational speed,
graphics, and all aspects of data handling including storage, and
long-haul communications. Proposals may address any of the following
areas:

**Parallel processing:** Methods and software for exploiting parallel
processing and for easing the task of developing efficient FORTRAN-based
programs for parallel processing computers while retaining the
efficiency of programs transferred from one architectural design to
another; methods for predicting resulting system performance prior to
system construction. Architectures of interest include tightly coupled
multiple instruction-stream multiple data-stream (MIMD) and loosely
coupled MIMD including workstation clusters.

**Scientific data management:** Software tools and programming libraries
that support easy development of new applications that draw from
complex, multi-source, multi-disciplinary data, easy definition and
management of evolving schema and scientific and engineering data types,
data integration and exchange among scientific and engineering
disciplines, scientific data management at the \"data model\" level,
management and access of extremely large collections of extremely large
data sets.

**Graphics:** Computer graphics concepts capable of implementation in
software and hardware for visualizing complex computational results to
bring new understanding to the physical phenomena being modeled, with
emphasis on displaying and recording several physical quantities varying
over three dimensions and time.

## 06.04 Rotorcraft/STOVL Aerodynamics and Dynamics  {#rotorcraftstovl-aerodynamics-and-dynamics .unnumbered}

Lead Center: ARC

Many aspects of rotorcraft/STOVL (Short Take-Off and Vertical Landing)
aerodynamics and dynamics are not thoroughly understood or adequately
predicted to enable efficient and accurate design processes for
economically viable, civil aviation aircraft with vertical lift/STOVL
capability. NASA requires innovative methods, approaches, and
technologies that describe phenomena involved in rotorcraft/STOVL
aerodynamics, dynamics and acoustics, provide greater knowledge of the
detailed characteristics of these phenomena, and permit well-verified
designs. Innovative developments with applications to tilt rotors,
single main rotor and tandem helicopters, co-axial helicopters, and
rotors with circulation control are needed to refine next generation
rotorcraft and STOVL aircraft that will meet civilian global aviation
requirements for quieter, more efficient, lower DOC aircraft. These
requirements directly impact the enabling technology goals identified by
NASA to support the agency\'s mission in rotorcraft. Examples of
problems currently of importance include: efficient rotor design which
reduce design cycle time, improved vehicle performance with reduction in
ownership and operation costs, advanced active control
strategies/methodologies for aeromechanics control and enhanced vehicle
capability, innovative solutions to reducing airframe vibration, rotor
vibratory loads, and radiated noise. New analysis methodologies
addressing the unique aspects of civilian rotorcraft/STOVL aircraft
through CFD/CSM/CAA for individual and integrated vehicle systems are
also sought.

## 06.05 Viscous Flow Computation, Modeling, and Control  {#viscous-flow-computation-modeling-and-control .unnumbered}

Lead Center: LaRC

NASA interest in viscous flow computation, modeling and control
encompasses the entire spectrum of aerodynamic and aerothermodynamic
phenomena that may be encountered by subsonic-to-supersonic aircraft and
aerospace vehicles. The purpose of this subtopic is to advance the
understanding of static and dynamic behavior, transient phenomena,
maneuvering, stability and control, aerodynamic performance, heat
transfer, and combustion phenomena. Applications include both external
and internal flow fields and multiple body interactions; of interest are
innovative ideas, (i.e., plasma flow control and its potential impact on
vehicle performance). Areas of interest include the following:

-   Flow-physics modeling and control of transition and/or transitional
    flows, turbulence, and turbulence-related phenomena such as heat
    transfer, skin-friction, acoustics, mixing and combustion.

-   Control and/or mitigation of complex flow phenomena such as
    separation, vortical flows, including drag-due-to-lift, and shock
    wave drag.

-   Numerical methods for solving fluid-flow equations that increase
    computational efficiency, accuracy, speed, and utility, including
    construction of new algorithms, improved computer languages,
    improved boundary condition procedures, efficient grid-algorithm
    interfacing, and applications of automation techniques. Additional
    considerations are grid-generation procedures, unstructured grids,
    solution-adaptive procedures, and grid quality measures.

-   Analytical and numerical techniques that enhance the understanding
    of transition and turbulence phenomena and provide improved models
    to solve the Navier-Stokes equations.

-   Scientists\' workbenches with integrated, graphical tools for
    interactive geometry definition, grid-generation, flow
    visualization, and solution validation.

-   Innovative scientific visualization includes techniques to identify
    and visualize the details of complex flow fields around 3-D
    aircraft.

##  {#section-5 .unnumbered}

## 06.06 Internal Fluid Mechanics for Aeropropulsion Systems  {#internal-fluid-mechanics-for-aeropropulsion-systems .unnumbered}

Lead Center: LeRC

Innovative concepts are sought for analysis, design, test and
measurement technology which will allow significantly reduced design
cycle time with improved design quality in aeropropulsion systems for
low subsonic through hypersonic speeds. Areas of interest include the
following:

-   Inlets and nozzles: Advanced steady-state and time-dependent flow
    analyses as well as new instrumentation and visualization methods
    for flow fields including shocks, boundary layers, boundary-layer
    control, separation, heat transfer, surface cooling, jet mixing and
    noise prediction. Unsteady boundary condition models for the effects
    of upstream or downstream components.

-   Turbomachinery: Advanced flow codes and physical models for both
    steady and unsteady flows including shocks, viscous effects, heat
    transfer and tip-clearance effects in fans, compressors, turbines
    and wave rotors. Novel concepts for instrumentation and flow
    visualization.

-   Combustors: Highly efficient flow codes and novel measurement
    techniques for the flows and physical processes in a combustor or
    wave rotor passage including fuel injection, spray evaporation and
    mixing, reaction mechanisms and kinetic rates for hydrocarbon
    oxidation and soot formation, formation of solid and gaseous exhaust
    emissions and the effects of endothermic fuels in high speed
    systems.

-   Computational methods for internal flows: Innovative algorithms and
    techniques for solving internal flow problems. This includes
    multiblock, unstructured and solution-adaptive grid schemes. New
    methods for solid modeling and grid generation. Software strategies
    to simplify the parallel implementation of the above methodologies.
    Intelligent software for pre- and post-processing, as well as
    aerodynamic design system integration and automation. New techniques
    for optimization of the aerothermodynamic performance of propulsion
    systems and components.

-   Aeropropulsion systems simulation: New products for cost-effective
    computational simulation of both full systems and subsystems. Of
    particular interest are multi-level of fidelity analysis techniques
    that capture the appropriate physics at the appropriate fidelity for
    full system simulation and multidisciplinary techniques which
    facilitate multidisciplinary data exchange and integration with
    design systems, coupling of single discipline codes and multiphysics
    approaches.

## 06.07 Multi-Disciplinary Design Optimization and System Analysis of Aerospace Vehicles  {#multi-disciplinary-design-optimization-and-system-analysis-of-aerospace-vehicles .unnumbered}

Lead Center: LaRC

Multidisciplinary design optimization (MDO) is a collection of
design-oriented analysis and systems optimization methods for the design
of complex engineering systems and subsystems that exploits the
synergism of mutually interacting phenomena. Advanced vehicles which are
viable from both the performance and affordability standpoints often
require delicate trade-offs between not only the traditional performance
disciplines, such as structures, propulsion, aerodynamics, controls,
electromagnetics, materials and flight decks, but also between them and
such nontraditional disciplines as requirements, manufacturing, safety,
cost and operations. MDO requires design-oriented tools, i.e. tools
which augment the analysis result with sensitivity analyses
(derivatives), approximations and/or rapid reanalysis capability. MDO
also requires optimization methods and tools that can be used in
conjunction with multidisciplinary analyses to assist engineers in
developing improved designs. Systems analysis (SA) for aerospace
vehicles involves assessing the impact of changes in mission
requirements and/or technologies on systems design and operations of
interdependent subsystems. Effective SA performed early in the design
process can increase performance and reduce the potential for downstream
design changes, thus minimizing cost increases and schedule slips. This
subtopic seeks innovative proposals for application software embodying
the mathematical and algorithmic aspects of both MDO and SA methods for
aerospace vehicles, such as:

-   Efficient, design-oriented, multidisciplinary analysis of complex
    physical models.

-   Efficient, design-oriented multidisciplinary sensitivity analysis of
    complex physical models.

-   Efficient tools to approximate system disciplinary or
    multidisciplinary responses using zero-, first- and possibly
    higher-order system information.

-   Optimization methods for multidisciplinary systems with large
    numbers of design variables and constraints, and with both
    continuous and discrete design variables.

-   Optimization methods that account for uncertainties in problem
    parameters.

-   Incorporation of requirements definition, vehicle manufacturing,
    operations, safety and cost along with engineering design in MDO/SA.

-   Enhanced weight-based and process-based cost-modeling methods.

-   Vehicle sizing and scaling algorithms, with provisions for tracking
    the impact of technology improvements and the uncertainties
    associated with those improvements.

-   Low-cost robust MDO/SA software suitable for small business.

## 06.08 Modeling & Simulation of Aerospace Vehicles  {#modeling-simulation-of-aerospace-vehicles .unnumbered}

Lead Center: DFRC

Safer and more efficient design of advanced aerospace vehicles such as
the X-33 and the High Speed Civil Transport require advancement in
current predictive design tools. The goal of this subtopic is to develop
more efficient software tools for predicting and understanding the
response of an airframe under the simultaneous influence of aerodynamics
and the control system, in addition to pilot commands. The benefit of
this effort will ultimately be increased flight safety (particularly
during flight tests), more efficient aerospace vehicles, and an
increased understanding of the complex interactions between the vehicle
subsystems.

This subtopic solicits proposals for novel, multi-disciplinary, linear
or nonlinear, dynamic systems simulation techniques. Proposals should
address one or more of the objectives listed below:

-   Prediction of steady and unsteady pressure and thermal load
    distributions on the aerospace surfaces, or similar distributions
    due to propulsive forces, by employing accurate finite element CFD
    techniques.

-   Effective finite element numerical algorithms for multidisciplinary
    systems response analysis with adaptive three-dimensional grid/mesh
    generation at selected time steps.

-   Effective use of high-performance computing machines, including
    parallel processors, for integrated systems analysis or
    pilot-in-the-loop simulators.

-   Innovative applications of high-performance computer graphics or
    virtual reality systems for visualizing the computer model or
    results.

-   Correlation of predictive analyses with test data or model update
    schemes based on measured information.

## 06.09 Hypersonic Airbreathing Propulsion & Vehicle Aerodynamics  {#hypersonic-airbreathing-propulsion-vehicle-aerodynamics .unnumbered}

Lead Center: LaRC

Innovative ideas and application of computational and experimental
techniques are sought that will account for the complex
aerothermodynamic, mixing, and combustion phenomena impacting the design
and development of future space transportation vehicles, aero-assist
orbital transfer vehicles, planetary entry probes, and hypersonic
airbreathing propulsion systems. Applications include laminar,
transitional, and turbulent nonreacting and reacting viscous flows and
gas dynamics from continuum to free-molecule. Interest is in innovations
resulting in improved and more efficient methods to define the
aerodynamic performance, stability and control, heat transfer, and shear
and pressure loads on future space transportation vehicles as well as to
analyze engine flow path and to assess its performance. Phenomena of
interest include, but are not limited to, equilibrium and finite-rate
chemistry, thermodynamic and transport properties of multicomponent
mixtures, gaseous radiation, gas-surface interactions, mixing and
combustion, shock-wave/boundary-layer interactions, and laminar,
transitional, and turbulent reacting flow modeling. Some examples
include the following:

-   Innovative concepts for hypersonic vehicles and airbreathing
    propulsion systems with potential for improved performance and
    reduced structural weight fraction.

-   Numerical methods with enhanced accuracy and efficiency for solving
    fluid-flow equations for hypersonic vehicles and airbreathing
    propulsion systems.

-   Advanced test techniques and flow diagnostics (including
    nonintrusive flow diagnostics and surface diagnostics) for
    developing definitive databases in hypersonic facilities, including
    shock-expansion pulse facilities.

-   Global measurement techniques for pressure and heat transfer in high
    Mach number flows.

-   Model fabrication techniques with reduced cost and construction
    time.

-   Analysis, design, and optimization techniques and graphical user
    interfaces for hypersonic vehicles and airbreathing propulsion
    systems.

## 06.10 Intelligent Design Methods for Aerospace Vehicles  {#intelligent-design-methods-for-aerospace-vehicles .unnumbered}

Lead Center: ARC

America\'s aerospace community must have revolutionary new system design
tools to meet the demands of the 21st century. These include distributed
design teams, greater product complexity, adaptation to lack of detailed
knowledge early in the design process, and, most importantly, reduced
design cycle time and cost. Fortunately, emerging information technology
(such as soft computing, fuzzy logic, advanced algorithms, and
artificial intelligence), integrated with traditional aerospace vehicle
technologies, can enable the development of such revolutionary systems.
NASA intends to lead the charge to develop the next generation of design
tools, that will decrease current design cycle time and cost by 50%.
These tools will interconnect the design, operations, maintenance, and
training databases and will also lead to advances in teaming that change
the current integrated product teams into integrated, multidisciplinary,
geographically-distributed product teams. Specific technology areas
include the following:

-   Computational models using algorithmic and reasoning technologies as
    well as neural networks, fuzzy logic and genetic algorithms to allow
    improvements in the cost, speed, and robustness of high-fidelity
    physics-based analysis and design processes as well as intelligent
    agents to include cost discriminators from large amounts of
    parametric systems and mission data.

-   Interactive graphic-based tools, machine-independent human/machine
    interfaces, including web-based technologies, to facilitate
    integration of disciplinary software in analysis and design
    processes, and, to direct, redirect and monitor process execution.

-   Algorithmic and reasoning technologies to allow for collaborative
    environments including remote execution on geographically
    distributed and heterogeneous computer systems as well as frameworks
    to support establishment of collaborative and distributed design
    environments capable of optimally handling complex aerospace vehicle
    analysis and design processes.

-   Interface standards and data protocols, technologies and systems for
    storage and query of variable fidelity, multi-source,
    multi-discipline design data sets, and techniques to present static
    and dynamic -3D datasets to ultimately maximize the potential for
    human direction of aerospace design and analysis processes. This
    technology includes AI-based agents for feature detection, and
    fuzzy-reasoning data selection and presentation.

-   Instrumentation and test techniques that provide high fidelity
    global surface or global field design data, and knowledge-based
    processes/tools that result in reduced testing and flexible
    operations.

-   Common parameterized geometry and discretization tools (e.g.,
    computational grids) for all disciplines required in aerospace
    vehicle analysis and design.

## 06.11 Instrumentation, Sensors, and Controls for Propulsion and Power Systems 

Lead Center: LeRC

Advanced technology concepts in instrumentation, sensors, and controls
need to be developed to significantly improve overall aircraft safety,
environmental compatibility, performance, affordability, reliability and
durability.

-   Advanced thin film, optical, and MEMS (Micro Electro-Mechanical
    Systems) sensors for use in aeropropulsion systems are needed for
    ground and flight applications. Air temperature, pressure, density,
    chemical species, and velocity measurements, and engine component
    surface temperature, pressure, strain, and deformation measurements
    are of interest. Reliability at high temperatures and pressures is a
    requirement. Compatibility with advanced propulsion system materials
    such as ceramics and composites is desired.

-   High-temperature integrated electronics and sensors will be needed
    as advanced aircraft control systems move toward the use of
    electromagnetic actuators and distributed control architectures.
    Both signal-level and power-level electronics that can operate at
    high temperatures are needed. Silicon carbide is being developed as
    a semiconductor material for these applications. Innovations are
    sought in silicon carbide high purity crystal growth and doping,
    integrated device and sensor fabrication with special emphasis on
    metallization and device packaging for use in high temperature
    hostile environments.

-   Emerging MEMS technologies with application to novel
    multidisciplinary propulsion concepts and turbomachinery flow
    control problems are of considerable interest. Concepts which
    consider development and integration of MEMS based sensing and
    actuation devices and robust control logic into an overall
    integrated system with experimental validation of the integrated
    system will be emphasized.

-   Advanced active control technologies for control of propulsion
    system components such as fan, compressor, combustor etc. are of
    considerable interest. Concepts which focus on integrated system
    development including novel sensing and actuation schemes will be
    emphasized. Of particular interest are advanced concepts in active
    clearance control.

## 06.12 Revolutionary Propulsion, Propulsion Systems and Components  {#revolutionary-propulsion-propulsion-systems-and-components .unnumbered}

Lead Center: LeRC

NASA seeks highly innovative concepts for propulsion, propulsion
systems, and components for advanced aerospace vehicles including
subsonic, supersonic, and hypersonic flight. The emphasis in this
subtopic is high-risk technology areas that can revolutionize air travel
and create new markets for U.S. industry. Propulsion system components
include inlets, propellers, fans, compressors, combustors, turbines,
nozzles, fuels, and recuperators and/or regenerators. Specific technical
areas of interest include the following:

-   Advanced cooling concepts that provide reduced coolant penalties.
    This can include innovative cooling systems, materials concepts,
    fuel cooling of the combustor, and endothermic fuels and/or fuel
    additives to increase the heat-sink capacity or cooling capacity of
    the fuels.

-   Development of new fuels for air-breathing vehicles in the speed
    range of mach 0 (takeoff) to 25 that provide higher propellant
    density, net improvement in thrust efficiency, or thrust
    augmentation. Proposals should address analytic assessments of
    feasibility, practical demonstrations of fuel additive techniques
    using minimal/efficient/smart delivery systems, and/or
    demonstrations of thrust augmentation in nozzle test flows.

-   Innovative concepts relating to the combustion process, including
    techniques to identify the onset of combustion instability in
    lean-burn, low-NOX combustors, designs to avoid instabilities, and
    active and passive combustion controls.

-   Greater cycle efficiency with an emphasis on thermodynamic cycles
    including combined cycles. Specific examples include topping cycles,
    cycles which employ recuperators, and inlet flow conditioning which
    allows turbomachinery to operate at high speed flight conditions.

-   Micro air-breathing propulsion systems and their integration into
    airframes, such as propulsion system integration into the skin of
    the wing or totally within the wing.

-   Innovative concepts relating to injectors, mixing, and sprays for
    increased efficiency and performance, and reduced emissions. This
    also includes injection of gelled fuels into airbreathing engines.

# 07 Experimental Flight Research  {#experimental-flight-research .unnumbered}

Experimental flight research is an invaluable for exploring new concepts
and for complementing and strengthening laboratory research. The
subjects covered under this topic area are focused on (1) bringing
innovative technology into flight research to explore new aerodynamic
and airbreathing/rocket propulsion concepts and (2) radically improving
the overall effectiveness of the flight research process. Aerodynamic
areas of interest range from concepts applicable to hypersonic orbit
insertion to low Reynold's number high-altitude long duration
atmospheric sampling applications. Propulsion areas of interest include
entire system concepts which may incorporate combined propulsion cycles
as well as innovative technology addressing system elements such as high
density fuel, engine system components, or regenerative power systems.

## 07.01 Very High Altitude Aircraft Technology  {#very-high-altitude-aircraft-technology .unnumbered}

Lead Center: DFRC

NASA currently has no subsonic flight capability above 70,000 feet. The
physical properties of the atmosphere change quickly at altitudes above
80,000 feet, and atmospheric flight at such extreme altitudes poses
significant challenges in several aerospace technology areas. This
subtopic solicits innovative proposals that advance technologies toward
the development of subsonic aircraft for sustained flight above 100,000
feet altitude. NASA is interested in an atmospheric sampling aircraft,
manned or unmanned, with a high subsonic speed range, capable of at
least three hours endurance at the high altitude with a 1000-pound
payload. Specific areas of interest include:

-   Over the horizon command and control systems.

-   Collision avoidance systems for unpiloted or autonomous operations.

-   High power density, regenerative power sources.

-   High altitude subsonic aerodynamics, propulsion, structures and
    materials, aeroelastic and aeroservoelastic flight dynamics.
    Proposals for studies involving the development of specific design
    configurations are not of interest unless the contractor is
    proposing the feasibility of innovative concepts that have not been
    previously reported in the open literature.

## 07.02 Flight Sensors, Sensor Arrays and Airborne Instrumentation  {#flight-sensors-sensor-arrays-and-airborne-instrumentation .unnumbered}

Lead Center: DFRC

Real-time measurement techniques are needed to acquire aerodynamic,
structural and propulsion system performance characteristics in flight
and to safely expand the flight envelope of aerospace vehicles. The
scope of this topic is the development of sensors, sensor systems,
sensor arrays or instrumentation systems for improving the state-of-the
art in aircraft ground or flight testing. The goals are to improve the
effectiveness of flight testing by: simplifying and minimizing sensor
installation, measuring new parameters, improving the quality of
measurements, minimizing the disturbance to the measured parameter from
the sensor presence, deriving new information from conventional
techniques, or combining sensor suites with embedded processing to add
value to output information. This subtopic solicits proposals for
improving airborne sensors and sensor-instrumentation systems in
subsonic, supersonic and hypersonic flight regimes. These sensors and
systems are required to have fast response, low volume, minimal
intrusion and high accuracy and reliability, and include wireless
technology. Innovative concepts are solicited in the following areas:

**Vehicle Environmental Monitoring**

-   Nonintrusive air data parameters (airspeed, air temperature, ambient
    and stagnation pressures, Mach number, air density, flow angle).

-   Off-surface flow field measurement and/or visualization (laminar,
    vortical, and sepatated flow, turbulence) zero to 50 meters from the
    aircraft.

-   Boundary layer flow field, surface pressure distribution, acoustics
    or skin friction measurements or visualization.

-   Any of the above measurements in hypersonic flow.

    **Vehicle Condition Monitoring**

-   Optical arrays for robust flight control surface position and
    velocity measurement.

-   Sensor arrays for structural load monitoring.

-   Robust arrays for engine monitoring and control applications.
    Advanced instrumentation for aeropropulsion flight tests. Thin film
    and fiber optic sensors, especially those compatible with advanced
    propulsion system materials such as ceramics and composites, and
    capable of withstanding the high temperatures and pressures
    associated with turbomachinery.

-   Onboard Processing for data condensation, failed sensor
    identification or other valuable on-board processing capability.

## 07.03 Hypersonic Vehicle Design and Systems Technology  {#hypersonic-vehicle-design-and-systems-technology .unnumbered}

Lead Center: LaRC

Innovative system-oriented research is sought to support, develop,
and/or enable advanced hypersonic technologies that could impact the
design and optimization of future hypersonic vehicles. The focus is on
hypersonic airbreathing vehicles with emphasis on hypersonic cruise
airplanes and single- or two-stage-to-orbit vehicles.

Design/analysis software/algorithms and graphical user interfaces to the
software to address hypersonic vehicle design and performance prediction
needs can include the following:

-   Conceptual and preliminary design.

-   Total multi-disciplinary configuration design and optimization.

-   Three-dimensional methods for external and internal
    vehicle/propulsion flowpath analyses (includes CFD and closed form
    methods or a combination thereof).

-   Vehicle sizing and scaling.

-   Subsystems design/database including sizing, integration, and
    networking routines with or without power balance capabilities.

-   Methods for design/analysis of cooled leading edges including heat
    load predictions.

-   Inverse design methods.

-   Trajectory design, analysis, and optimization.

-   Aerodynamic performance prediction methods.

    Advanced hardware and systems with the potential to reduce
    structural weight fraction and/or increase vehicle performance are
    sought and can include:

-   Heat exchangers, reactors, and secondary coolant designs for
    endothermic fuel systems.

-   Propulsion cycles applicable from Mach 0 to 25 and accompanying
    design and integration techniques.

-   Heat-rejection radiators, compact, high-performance convective heat
    exchangers, and cooling panel design.

-   Lightweight, durable coating or insulation systems that can
    significantly reduce the aerothermal heat load to external/internal
    surfaces with those improvements.

-   MHD propulsion/flowpath.

-   Systems for reduction of drag at hypersonic speeds

-   Plasma augmented propulsion.

-   Systems for reduction of aeroheating at hypersonic speeds

-   Innovative flight controls.

-   Specialized hypersonic fuel systems.

## 07.04 Integrated Propulsion Systems for Airbreathing Hypersonic Flight  {#integrated-propulsion-systems-for-airbreathing-hypersonic-flight .unnumbered}

Lead Center: LeRC

Innovative ideas and applications of computational and experimental
techniques are sought that will facilitate the integration of elements
such as ejector-ramjets, ramjets, scramjets, and rockets into systems
such as an ejector-ramjet-based combined-cycle propulsion system. These
systems should be capable of accelerating a vehicle to low-earth orbit
or to a high mach number (such as M=8 to M=15) for cruise. Use of
advanced turbo-ramjets and dry turbojets in turbine-based combined-cycle
systems is also encouraged. System elements of interest include, but are
not limited to, inlets, combustors, cowls, moving surfaces to change
engine area ratios, seals, nozzles, instruments, sensors and controls.
Specific areas of interest include the following:

-   High thrust performance of ejector-ramjets or alternative elements
    at take-off of the hypersonic vehicle in either a vertical or
    horizontal orientation.

-   Optimization of the flowpaths and transitions in operation, for an
    ejector-ramjet-based space launch system. This might include
    transitions from initial ejector-ramjet to ramjet, from ramjet to
    scramjet, and from scramjet to rocket.

-   Use of internal fluid mechanics and computational fluid dynamics
    (CFD) techniques to accurately predict flows in all parts of the
    engine flow path from vehicle inlet surfaces to nozzle end-plane.
    Thermodynamic cycle optimizations for engine cooling by propellants
    and detailed modeling of thermodynamic cycles with engine cooling.

-   Optimization of the design and placement of propellant injectors and
    igniters throughout engine system; use of lightweight, durable
    techniques for flight-weight engine fabrication.

-   Innovative instrumentation, sensors, and controls/control
    methodologies that are unique to airbreathing hypersonic propulsion
    systems, including optical techniques and thin-film, fiber-optic,
    and micro electro-mechanical systems (MEMS) sensors. Advanced,
    robust, and multivariable control technologies that lead to enhanced
    performance and reliability.

-   Practical means of capturing air and separating the oxygen or
    enriching air during early phases of hypersonic air-breathing
    flight, for use during later stages, to improve overall flight
    performance and efficiency.

-   Advanced technologies for integrated propulsion systems and
    propulsion/airframe integration not already mentioned above, such as
    pulse detonation-techniques for the low speed portion of operation
    of integrated air-breathing propulsion systems for hypersonic
    vehicles, or laser-driven/laser-assisted hypersonic airbreathing
    propulsion cycles.

    New designs, design optimizations and manufacturing technologies
    that would advance the state of art in design, manufacture and the
    testing of minature propulsion systems for remotely controlled or
    autonomous micro-airplanes smaller than twelve inches wing span to
    be used for hypersonic research, remote sensing and/or observation.
    Some items of interest are turbines and turbine components such as
    combustors, fuel injectors and rotating components. Also of interest
    are miniature heat pumps, reciprocating engines and electric or
    solar powered motors. In addition, NASA is interested in the control
    systems that would allow efficient operation of minature engines.

-   Techniques / methodology for experimental assessment of scramjet
    engine air mass capture in flight tests with proof-of-concept in
    ground tests.

-   Techniques / methodology for experimental assessment of fuel-air
    mixing and reaction in scramjet flight tests with proof-of-concept
    in ground tests.

-   Methodology for achieving geometric variations of engine flowpath,
    including fuel injectors, consistent with sequential airbreathing
    modes over wide Mach range.

-   Flowpath improvements/optimizations to increase dual-mode scramjet
    performance for practical, integrated propulsion systems for
    hypersonic cruise or flight to orbit. Ideas to improve inlet
    efficiency/operability, fuel/air mixing and combustion efficiency,
    and nozzle flowpath energy recovery.

-   Ground test techniques that enhance facility operation and enable
    experimental assessment / optimization of scramjet flowpaths at Mach
    8 to 15.

##   {#section-6 .unnumbered}

## 8.2 HUMAN EXPLORATION AND DEVELOPMENT OF SPACE

The mission of the Human Exploration and Development of Space (HEDS)
Enterprise is to open the space frontier by exploring, using and
enabling the development of space and to expand the human experience
into the far reaches of space. In exploring space, HEDS brings people
and machines together to overcome the challenges of distance, time and
environment. Robotic science missions survey and characterize other
bodies as precursors to eventual human missions. In using space, HEDS
emphasizes learning how to live and work there and utilize the resources
and unique environment. In enabling the development of space, HEDS
serves as a catalyst for commercial space development. And throughout,
this Enterprise will employ breakthrough technologies and ingenious
designs to revolutionize human space flight.

http://www.osf.hq.nasa.gov/heds/

08 Increase Knowledge of Nature\'s Processes Using the Space Environment
[49](#increase-knowledge-of-natures-processes-using-the-space-environment)08.01
Understanding and Utilizing Gravitational Effects on Molecular Biology
and for Medical Applications
[49](#understanding-and-utilizing-gravitational-effects-on-molecular-biology-and-for-medical-applications)08.02
Understanding and Utilizing Gravitational Effects on Animals
[50](#understanding-and-utilizing-gravitational-effects-on-animals)08.03
Understanding and Utilizing Gravitational Effects on Biotechnology and
Materials Science
[50](#understanding-and-utilizing-gravitational-effects-on-biotechnology-and-materials-science)08.04
Exploiting Gravitational Effects for Combustion, Fluids, Synthesis, and
Vibration Technology
[51](#exploiting-gravitational-effects-for-combustion-fluids-synthesis-and-vibration-technology)08.05
Understanding and Utilizing Gravitational Effects on Plants
[52](#understanding-and-utilizing-gravitational-effects-on-plants)09
Explore and Settle the Solar System
[52](#explore-and-settle-the-solar-system)09.01 *In-Situ* Resources
Utilization (ISRU) of Planetary Materials
[52](#in-situ-resources-utilization-isru-of-planetary-materials)09.02
Spacecraft/Habitat Monitoring, Safety, and Radiation Protection
[54](#spacecrafthabitat-monitoring-safety-and-radiation-protection)09.03
On-Board Human Health Maintenance and Countermeasures
[55](#on-board-human-health-maintenance-and-countermeasures)09.04
Spacecraft Life Support Infrastructure
[56](#spacecraft-life-support-infrastructure)09.05 Space Crew
Performance Enhancements and Accommodations
[59](#space-crew-performance-enhancements-and-accommodations)09.06 Human
Space Mission Thermal Control
[60](#human-space-mission-thermal-control)09.07 Cryogenic Fluids,
Handling, and Storage [61](#cryogenic-fluids-handling-and-storage)09.08
Extravehicular Mobility/Activity
[61](#extravehicular-mobilityactivity)09.09 Robotics
[63](#robotics)09.10 Advanced Manufacturing and Nanotechnology
[65](#advanced-manufacturing-and-nanotechnology)10 Achieve Routine Space
Travel [65](#achieve-routine-space-travel)10.01 Advanced Corrosion
Technology [66](#advanced-corrosion-technology)10.02 Environmental and
Ecological Technologies
[66](#environmental-and-ecological-technologies)10.03 Launch and Landing
Site Instrumentation and Meterological Technologies
[67](#launch-and-landing-site-instrumentation-and-meterological-technologies)10.04
Operations Industrial Engineering
[68](#operations-industrial-engineering)11 Enrich Life On Earth Through
People Living and Working in Space
[69](#enrich-life-on-earth-through-people-living-and-working-in-space)11.01
Commercial Microgravity Research
[69](#commercial-microgravity-research)11.02 Telemedicine and Health
Diagnostic Services and Communications
[70](#telemedicine-and-health-diagnostic-services-and-communications)11.03
Technological Methods for Enhancing Public Understanding/Involvement of
Science/Technology Programs
[71](#technological-methods-for-enhancing-public-understandinginvolvement-of-sciencetechnology-programs)12
Advance Space Communications and Operations
[72](#advance-space-communications-and-operations)12.01 Flight/Ground
System Autonomous Operations
[72](#flightground-system-autonomous-operations)

# 08 Increase Knowledge of Nature\'s Processes Using the Space Environment  {#increase-knowledge-of-natures-processes-using-the-space-environment .unnumbered}

HEDS contributes to the creation of new scientific knowledge by
conducting scientific investigations in several related areas. One area
focuses on gravity-dependent phenomena using both Earth and space-based
facilities. HED\'s basic research programs study the fundamental and
direct relationship between gravity and certain biological, chemical and
physical processes. In these investigations, gravity is used as an
experimental variable much as temperature and pressure are in similar
studies. The objectives of this topic include understanding the
fundamental role of gravity and the space environment in biological,
chemical, and physical systems.

## 08.01 Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications  {#understanding-and-utilizing-gravitational-effects-on-molecular-biology-and-for-medical-applications .unnumbered}

Lead Center: JSC

Microgravity provides a unique environment for new methods of processing
biological materials that have medical applications or lead to spin-offs
in medicine and biotechnology. Current space research includes: new
methods for free-fluid, electric-field purification of living cells or
proteins, development of space bioreactors for culture of fragile cells
that have applications in biomedical and cancer research, tissue
engineering systems which take advantage of microgravity to grow 3-D
tissue constructs, testing the effectiveness of drugs and biomodulators
on growth and physiology of normal and transformed cells, methods of
growing large protein crystals and analysis of the three-dimensional
structure to aid drug designs to mimic or inhibit the biological
function of these proteins, and methods for measuring specific cellular
and systemic immune functions of persons under physiological stress.
Biotechnology research systems also are being developed for micro-g
research on the International Space Station. Specific areas of interest
are:

-   New methods for culturing mammalian cells in bioreactors, including
    advanced bioreactor designs and support systems, miniature sensors
    (for measurement of pH, oxygen, carbon-dioxide, glucose, and
    metabolites within the cell culture fluid medium), and
    microprocessor controllers.

-   Methods for separation and purification of living cells, proteins
    and biomaterials, especially those using electrokinetic or magnetic
    fields that obviate thermal convection and sedimentation, enhance
    phase partitioning, or use laser light and other force fields to
    manipulate target cells or biomaterials.

-   Techniques or apparatus for macro-molecular assembly of biological
    membranes, bio-polymers, and molecular bio-processing systems;
    bio-compatible materials, devices, and sensors for implantable
    medical applications including molecular diagnostics, in vivo
    physiological monitoring and microprocessor control of prosthetic
    devices.

-   Methods and apparatus which allow microscopic imaging and
    biophysical measurements of cell functions, effects of electric or
    magnetic fields, photoactivation, and testing of drugs or
    biocompatible polymers on live tissues.

-   Quantitative applications of molecular biology, fluorescence image
    and flow cytometry, and new methods for measurement of cell
    metabolism, cytogenetics, immune cell functions, DNA, RNA,
    oglionuceotides, intracellular proteins, secretory products, and
    cytokine or other cell surface receptors.

-   Micro-encapsulation of drugs, radiocontrast agents, crystals, and
    development of novel drug delivery systems wherein immiscible liquid
    interactions, electrostatic coating methods, and drug release
    kinetics from microcapsules or liposomes can be altered under
    microgravity to better understand and improve manufacturing
    processes on Earth. This includes methods for improving the
    controlled release from transdermal drug devices, ionaphoresis,
    controlled hyperthermia and new drug delivery systems for inhalation
    and intranasal administration.

-   Miniature bioprocessing systems which allow for precise control of
    multiple environmental parameters such as low level fluid shear,
    thermal parameters, pH, conductivity, external electromagnetic
    fields and narrow-band light for fluorescence or photoactivation of
    biological systems.

## 08.02 Understanding and Utilizing Gravitational Effects on Animals  {#understanding-and-utilizing-gravitational-effects-on-animals .unnumbered}

Lead Center: ARC

The interests of the Gravitational Biology and Ecology Program in this
subtopic area will focus on technologies that aid the investigation of
all phases of organism growth, development and their interactions with
other organisms in the space environment. Such studies will range from
organism development, including gametogenesis through fertilization,
embryonic development and maturation, through ecological system
stability. Studies may include a variety processes such as metabolism
and metabolic control, through genetic expression and the control of
development. Of particular interest are technologies that require
minimal power, and can non-invasively measure physical, chemical,
metabolic and development parameters. While such measurements will
ultimately be made in environments at one or more of several gravity
ranges: \"microgravity\" (10-2 to 10-6 x g), \"planetary\" gravity (1 x
g (Earth); 0.38 x g (Mars) or 0.12 x g (Moon)) or hypergravity (up to 2
x g), refined and stable measurements are as important as gravity
independence. Of interest are sustained instrument sensitivity, accuracy
and stability, and reductions in the need for frequent measurement
standardization. Parameters requiring measurement include: pH,
temperature, pressure, ionic strength, gas concentration (O2, CO2, CO,
NO2, etc.), and solute concentration (e.g., Na+, K+, Ca2+, Mg2+, SO4 2-,
Cl-, PO4 3-, etc.). In the case of new techniques and instruments, a
clear path toward miniaturization, reduction in power demands and
increased spaceworthiness should be identified.

## 08.03 Understanding and Utilizing Gravitational Effects on Biotechnology and Materials Science  {#understanding-and-utilizing-gravitational-effects-on-biotechnology-and-materials-science .unnumbered}

Lead Center: MSFC

NASA has interest in experiments that characterize and utilize the
influence of microgravity on biotechnology processes and materials
science. Areas of interest include protein crystal growth and structural
analysis techniques, separation science and technology, advanced
electronic and photonic materials research, metals and alloys
technology, glass and ceramic materials technology. Another area relates
to microgravity processing approaches such as containerless processing
and advanced thermal processing techniques. Innovations are sought in
the following:

-   Electronic and photonic materials leading to solid-state detectors
    with improved properties, and controlled crystal growth for
    scientific and commercial applications. Metallic alloys with
    improved grain structures by directional solidification and
    processing involving supercooling and undercooling states.

-   Polymers, composites, and other materials that incorporate sensory,
    effector, and self-repair technologies.

-   Simulation capabilities that will elucidate the interaction of
    transport properties during liquid state processing and can lead to
    desired microstructures and properties. Experimental design
    methodologies combining advanced process models, optimization
    techniques, and control.

-   Experiments and theoretical research in separation techniques and
    protein crystal growth for a greater understanding of such processes
    in the reduced-gravity environment of space.

-   Instrumentation to determine the influence of crystallization
    parameters on the size and quality as well as growth rates of
    protein crystals that lead to commercial and medical applications.

-   Mathematical modeling, new methods, materials, and techniques to
    exploit the potential of microgravity for the improvement and
    understanding of biochemical separation processes.

-   Development of technology in eucaryotic cell biology that takes
    advantage of the unique microgravity environment(or simulated
    environment) for innovative approaches to drug screening, biological
    product production, or organ/tissue remodeling.

-   Automatic drug separation and purification from plants and cell
    cultures grown under confined conditions anticipated for prolonged
    residence in microgravity or off-Earth habitats.

-   Advancement of high-yield protein or recombinant drug expression
    systems that function in cultures grown under simulated
    microgravity.

-   Experimental sample containment, instrumentation, or processing
    approaches that enhance scientific return or minimize impact to
    experiment samples. Two examples are (1) containerless processing to
    control impurities and nucleation sites or allow processing of
    reactive melts, and (2) provide rapid cooling of the sample to
    enhance microstructural analysis.

-   Thermal insulation or heating approaches that enhance safety and use
    resources more efficiently.

-   Microgravity furnace technology for minimizing power, enhancing
    thermal axial gradients, and improving quench performance, while
    maintaining flat solidification interfaces, and minimizing
    disturbances to the sample.

-   Microgravity furnace instrumentation technologies to better
    understand sample health and experiment status while minimizing the
    instrumentation\'s effect on the sample.

-   Methods for integrating the furnace with the sample containment
    system to allow fast, cheap microgravity experiments.

-   Advanced modeling techniques that can simulate the slow translation
    of a sample container relative to a host furnace for gradient
    processing, rapid translation for quench, and the quench. Methods
    for simplifying this type of modeling process.

-   Technology and instrumentation leading to the formation, interaction
    and synthesis of particulate materials on Earth and in planetary
    environments and their application to the establishment of
    extraterrestrial outposts.

-   Materials and studies leading to applications in radiation shielding
    during human extraterrestrial exploration of space.

## 08.04 Exploiting Gravitational Effects for Combustion, Fluids, Synthesis, and Vibration Technology  {#exploiting-gravitational-effects-for-combustion-fluids-synthesis-and-vibration-technology .unnumbered}

Lead Center: LeRC

NASA seeks innovative proposals for products to improve the operation
and safety of orbiting spacecraft based on chemical and physical
processes that exploit the microgravity and partial gravity environment.
Also sought are products for application to NASA missions involving Mars
and the Moon and for ground-based application and commercialization
based on principles, understandings, or testing in simplified,
non-convective microgravity and partial gravity fields.

For some demonstrations to support product development, the NASA Lewis
Research Center can provide access and assistance to outside
investigators in its unique facilities, including the Space Experiment
Laboratory, the 2.2-second and 5.2-second drop towers, and
parabolic-trajectory (20 seconds of low gravity) aircraft. (See Section
5.14) Specific areas of interest are:

-   Products based on combustion or related chemical reactions in
    gaseous, liquid, solid, or mixed phases for application to
    spacecraft operational needs or to derived ground systems, aided by
    principles, models, or demonstrations validated in the simplified
    environment of microgravity and partial gravity.

-   Products based on physical contact or transport in fluid, dispersed,
    or mixed phases for application to spacecraft operational needs or
    to derived ground systems, aided by principles, models, or
    demonstrations validated in the simplified environment of
    microgravity and partial gravity.

-   Small-scale intermetallic, ceramic, or similar products produced
    through combustion synthesis in solid, filter-flow, thermite, or
    other reactions, with product uniformity, composition, or yield
    controlled or improved by exposure to the non-convective
    microgravity and partial gravity environment.

-   Products to measure, isolate, or control acceleration, vibration, or
    jitter for application to spacecraft operational needs or to space
    experiment payloads or to derived ground systems.

-   Sensors, instrumentation, and diagnostics systems for application to
    non-disturbing measurement of chemical, thermal, or flow parameters
    in microgravity and partial gravity or to derived ground systems,
    based on principles, models, or demonstrations validated in
    microgravity or partial gravity.

-   Products to promote or improve fire safety through prevention,
    detection, suppression, or post-fire restoration for application to
    spacecraft or to derived ground systems, aided by principles,
    models, or demonstrations validated in microgravity or partial
    gravity.

-   Transport phenomena associated with chemical process technologies
    and chemical separation processes in microgravity and partial
    gravity as well as in the Earth-bound environment.

-   Technology that explains, enables or improves combustion and fluid
    processes in partial gravity environments to promote application of
    these processes to NASA\'s missions involving Mars and/or the Moon.

## 08.05 Understanding and Utilizing Gravitational Effects on Plants  {#understanding-and-utilizing-gravitational-effects-on-plants .unnumbered}

Lead Center: KSC

The focus of this subtopic for the Gravitational Biology and Ecology
program is improved understanding of the role of gravity on plants. This
requires innovative support equipment for observing, measuring, and
manipulating the responses of plants to environmental variables. Areas
of specific concern and emphasis include:

-   Measuring the atmospheric and radiation environment and optimizing
    the lighting and nutrient delivery systems for plants.

-   Innovative approaches to storage, transportation, maintenance, and
    *in situ* analyses of seeds and growing plants.

-   Sensors with low power requirements and low mass to monitor the
    atmosphere and water (nutrient) environment, as well as automated
    control and data logging systems for the experiment containers to
    measure performance indicators such as respiration (whole plant,
    shoot, root), evapotranspiration, photosynthesis, and other
    variables in plants.

-   Variable gravity centrifuge capabilities with monitoring and
    environmental controls identical to the stationary component.

-   Data analysis and control.

-   Expert data management systems.

-   Modular seeding and/or planting units to minimize labor.

-   Sensors for atmospheric, liquid and solid analyses, including
    atmospheric and liquid contaminants such as ethylene and other
    biogenic compounds as well as analyses of hydroponic and solid media
    for N, P, K, Cu, Mg and micronutrients.

-   Capabilities for specimen storage, manipulation and dissection.

-   Video-image analysis for plant health.

-   Sensors for primary environmental parameters and microbial
    organisms.

-   Remote sensors to identify biological stress.

-   Expert control systems for environmental chambers.

-   Biotelemetry monitors and biological monitors carried on remotely
    controlled spacecraft.

# 09 Explore and Settle the Solar System  {#explore-and-settle-the-solar-system .unnumbered}

The International Space Station Program and Mars Exploration studies
have defined technology and research needs that are critical to their
individual goals. These include: research on human adaptation to the
space environment; regenerative and bioregenerative life support;
telerobots and robot assistants; space and planet surface suits;
utilization of indigenous resources for propellants, life support
consumables, radiation protection, and construction materials; micro-
and nano technologies, manufacturing processes, and advanced materials.
All are sought to enable humans to live and work in space or on a
planet, to enhance performance, reduce cost, and maintain the health and
well being of the crew.

## 09.01 *In-Situ* Resources Utilization (ISRU) of Planetary Materials  {#in-situ-resources-utilization-isru-of-planetary-materials .unnumbered}

Lead Center: JSC

Significant benefits for future human missions to the Moon, Mars, and
other planetary bodies may be attained by making maximum use of local,
indigenous materials as a source for propellants, life support
consumables, radiation protection, and construction materials. By
pursuing the philosophy of \"Make what you need at the planet instead of
bringing it all the way from Earth\", *in situ* resource utilization
(ISRU) can result in reduction of mass requirements for the exploration
mission, reduction in risk, and reduction in cost of the mission. It can
also enable industrial and commercial participation in planetary
exploration and expand human presence on the planet surface. One example
of *in situ* propellant production employs the hydrogen reduction
process for extracting oxygen from lunar minerals and glass. In
addition, a number of techniques have been proposed for extracting and
storing oxygen from the carbon dioxide atmosphere of Mars. In general,
these processes require a number of subsystems, each of which could
benefit from innovative approaches and technology advances. It is also
possible that water could be extracted from permafrost deposits located
at shallow depths in some locations on Mars. Key goals are to minimize
the mass which must be brought from the Earth (including the equipment
required to move or process the material), minimize power consumption,
be truly innovative and not already in the literature. Areas for
investigation of specific methods and processes for *in situ* resource
utilization include the following:

**Surface Resources:**

-   Methods and systems for extracting, processing, and manufacturing
    in-situ materials that can be used for construction of habitable
    structures on the moon or Mars. New methods for constructing
    buildings, radiation shielding structures, and tunneling techniques
    are needed. Novel methods for underground development of habitable
    structures (perhaps using natural features such as caves or lava
    tubes) on the moon or Mars are also needed.

-   Methods for processing surface materials into useful equipment (e.g.
    solar panels, radio antennas, replacement parts etc.) which require
    no further manufacturing or assembly.

-   Methods and systems for digging, sorting, mineral separation, and
    transporting lunar regolith or other materials to a reactor. Such
    systems should be lightweight, efficient, and capable of operating
    with minimal human supervision.

-   Methods for extracting oxygen from lunar regolith that are power
    efficient and require a minimum of Earth-supplied reagents and
    consumables. Alternatives and improvements to previously-studied
    methods, such as reactors that expose lunar regolith to hydrogen gas
    at elevated temperature, are of interest. However, emphasis should
    be placed on innovative designs that minimize power requirements.

-   Microbial methods for extracting oxygen, decomposing water, and
    extracting solar wind hydrogen from soils (typically present on the
    moon at 50 parts per million levels) from the Moon or Mars as an
    attractive alternate approach to propellant and consumable
    production.

-   Methods for digging, extracting, and collecting water (including
    that which may be trapped in permafrost) that may be present on the
    surface or subsurface of Mars, which minimize power requirements and
    equipment mass which must be brought from Earth.

    **Atmospheric Resources:**

-   Methods to condense water vapor from the Mars atmosphere that are
    low mass or can be constructed from local materials with a minimum
    of equipment that must be brought from Earth.

-   Microbial methods for extracting oxygen from the Mars atmosphere, or
    for decomposing water.

-   Innovative processes and alternative approaches for extracting
    propellants and/or consumables including oxygen from the Mars
    atmosphere which have low power requirements and minimize the amount
    of equipment that must be brought from Earth. Processes currently
    being investigated include Sabatier/water-electrolysis reactor,
    reverse water gas shift reactor, and solid-oxide electrolysis
    (zirconia) cells. Oxygen extracted from the Mars atmosphere may be
    used for: production of propellant for transportation systems,
    production of oxygen for life support system gases, and production
    of cryogenics for extravehicular activity suits. Systems should be
    capable of operating autonomously, independent from continual
    earth-based control. Current scenarios for Mars exploration envision
    the following production needs for ascent oxygen propellant to
    support a single mission: 1 to 2 metric tonnes (for Mars robotic
    missions) and 30 to 40 metric tonnes (for Mars human missions).

## 09.02 Spacecraft/Habitat Monitoring, Safety, and Radiation Protection  {#spacecrafthabitat-monitoring-safety-and-radiation-protection .unnumbered}

Lead Center: JSC

Manned space missions require a variety of environmental monitoring and
biomedical activities to protect crew health and to counter the effects
of space on human physiology. Research disciplines include cell biology,
clinical chemistry, endocrinology, immunology, hematology, microbiology,
muscle physiology, pharmacology, nutrition, radiation biology,
toxicology, and air and water quality. Quantitative assessments require
innovative, space-flight compatible approaches in clinical laboratory
operations, environmental health monitoring and maintenance of crew
health. Special requirements for long-term operations of monitoring
systems and data management arise from manned operations in the
International Space Station. Areas in which innovations are solicited
include the following:

-   Assessment of the overall acceptability of the environment for human
    habitation and methods for assessing associated risks and thresholds
    for unacceptable contamination levels.

-   In-flight monitoring of the chemical, microbial, and physical
    quality of the spacecraft environment, including recycled water,
    atmosphere, food, and surfaces. Of particular interest are the
    detection, identification, quantitative measurement, and removal of
    organic contaminants and the assessments of potential health-effects
    for low level contamination in recycled water and air.

-   Real-time and quantitative broad spectrum or target
    compound-specific analyzers for trace contaminants in spacecraft
    atmospheres and/or recycled water. The instrument must be compact,
    feature low power consumption, low maintenance, highly automated
    (requiring minimal crew intervention) and must be functional for
    long periods of time.

-   Real-time and quantitative broad spectrum or target
    compound-specific analyzers for trace contaminants in spacecraft
    atmospheres and/or recycled water. The instrument must be compact,
    feature low power consumption, low maintenance, highly automated
    (requiring minimal crew intervention) and must be functional for
    long periods of time.

-   Maintenance of microbial quality of the atmosphere, water and
    surfaces during spaceflight and means of assessing their
    effectiveness, including new, clinical microbiology methods for
    rapid identification of pathogens, methods for measuring biofilms
    and novel systems for sterilization.

-   In-flight monitoring of non-ionizing, neutron and charged-particle
    radiation for determining interior and exterior environment of
    manned spacecraft, organ doses and the cytogenetic and
    carcinogenetic effects of protons and heavy ions, especially at low
    doses; measurement of effectiveness of radio-protectants and
    development of new biological and chemical radio-protectants against
    acute and late effects cellular effects of particulate and high
    energy cosmic radiation at cellular and organism level; development
    of biomarkers and amplified assays for measuring radiosensitivity
    and genetic damages by charged particles in human cells; development
    of computer biophysical models for organ dose calculation and for
    extrapolation of radiation data from cell to organism and from
    animal to human.

-   Miniaturized optical sensors (infrared, ultraviolet, or visible
    light), electrochemical sensors, and biological sensors for
    measuring chemical contaminants in the atmosphere or water systems.
    These sensors are used for providing outputs for caution and
    warning, support of control functions, or safety precautionary
    measures.

-   Microsensor devices capable of multifunctional monitoring of various
    chemical species or combined chemical/biological species in either
    air or aqueous medium. Of particular interest is the development of
    sensors that do not require calibration, are reversible with no or
    at least reproducible hysteresis, are sensitive over a two decade
    range of concentration (ppm), can operate in real-time fluid-flow
    conditions and for extended periods (months) of time. Chemical
    species of interest include formaldehyde, carbon monoxide,
    mercaptans, ethanol, acetaldehyde, and amines in air and organic
    species such as urea, acetic acid, amines and inorganic species such
    as nitrate, phosphate, magnesium, iron, zinc and potassium in water.

## 09.03 On-Board Human Health Maintenance and Countermeasures  {#on-board-human-health-maintenance-and-countermeasures .unnumbered}

Lead Center: JSC

Human presence in space requires an understanding of the effects of
microgravity and other components of the space environment of the
physiological systems of the body and on the psychology of the crew.
Countermeasures must be developed to oppose the deleterious changes that
occur in space or upon return to Earth. Health care and medical
intervention also must be provided over extended duration missions. As
launch costs are extremely sensitive to mass and volume, sensors and
instruments must be small and light with an emphasis on multi-functional
aspects. Low-power consumption is a major consideration, as are design
enhancements to improve the operation, design reliability, and
maintainability of these instruments in microgravity. As the efficient
utilization of time is extremely important, innovative instrumentation
setup, ease of usage, improved astronaut (patient) comfort, non-invasive
sensors, and easy-to-read information displays are all-important
considerations.

**Health Monitoring and Countermeasures:**

-   Methods and equipment to maintain and assess levels of aerobic and
    anaerobic physical capability.

-   Methods to monitor physical activity and loads placed on different
    segments of the human body.

-   Exercise equipment able to load the musculoskeletal and
    cardiovascular systems and monitor, record, and provide feedback
    about performance.

-   Approaches for sustaining, maximizing, assessing, and modeling
    individual as well as team performance.

-   Countermeasures against deleterious changes in body systems in
    flight or upon returning to the ground. Changes include space
    adaptation syndrome effects such as space motion sickness, in-flight
    loss of muscle and bone mass, post-flight orthostatic intolerance,
    and post-flight reduction in neuromuscular coordination.

-   Assessment of gas bubble formation or growth in the body after
    in-flight or ground-based decompression, and to prevent or minimize
    associated decompression sickness.

-   Means to apply artificial gravity and reduce deleterious effects
    associated with short-arm centrifuges.

-   Approaches to achieve health care and intervention within the
    operational constraints of space flight, including pharmaceuticals
    having extended shelf-life, diagnostic methods and procedures,
    medical monitoring, dental care and surgery, and blood replacement
    technology.

-   In-flight procedures and techniques for assessing the human
    metabolism of proteins, carbohydrates, lipids, vitamins, and
    minerals.

-   In-flight specimen collection and analysis to evaluate physiological
    and metabolic and pharmacological responses of astronauts.
    Non-invasive methods to measure crew performance and related
    factors.

-   Novel software methods for documentation, storage, retrieval,
    analysis, and diagnosis of crew health.

**Sensors and Instrumentation:**

-   Instrumentation to used for in-flight and ground-based studies for
    reliable and accurate non-invasive monitoring of human physiological
    functions such as the cardiovascular, musculoskeletal, neurological,
    gastrointestinal, pulmonary, immuno-hematological, and hematological
    systems

-   Improve non-invasive methods to evaluate the functioning of the
    cardiovascular, neurological, musculoskeletal, and pulmonary
    systems.

-   Non-invasive instruments to provide quantitative data to establish
    the effectiveness of an exercise regimen in ground-based research.

-   Smart sensors capable of sensor data processing and sensor
    reconfiguration.

-   Ultrasonic doppler systems for blood flow analysis.

-   Virtual medical instrumentation.

-   Automated biomedical analysis.

-   Microgravity blood, urine, and respiratory gas analyzers.

-   Microgravity refrigeration systems for the storage of biological
    samples and incorporating refrigerants acceptable for use in a
    spacecraft environment.

## 09.04 Spacecraft Life Support Infrastructure  {#spacecraft-life-support-infrastructure .unnumbered}

Lead Center: JSC

Advanced life support systems are essential for the success of future
human planetary exploration. Striving for self-sufficiency and
autonomous operation, future life support systems will integrate
physical and chemical processes with biological processes, resulting in
hybrid systems. These hybrid systems, which include plant growth systems
for the production of food and oxygen and utilization of recovered
wastes, represent an additional closure of regenerative life support
systems to further reduce mass and to promote self-sufficiency.
Requirements include operability in micro-and partial-gravity, high
reliability, minimal use of expendables, ease of maintenance, and low
system weight and power. Innovative, efficient, practical concepts are
desired in all areas of regenerative physicochemical and biological
processes for the basic life-support functions of air revitalization,
water reclamation, waste management, plant food production, and sensors
and controls. Also innovative, cost-effective concepts are desired to
assess, predict, control and enhance the effect of microgravity and
partial-gravity on the operation and performance of physicochemical and
biological life support technologies including approaches to safely
integrate flight experiments into the International Space Station. In
addition to these space exploration related applications, innovative
regenerative life support approaches which could have terrestrial
application are encouraged. Proposals should strive to conduct Phase II
experimental development that could be integrated into a functional life
support system. Areas in which innovations are solicited include the
following.

**Air revitalization:**

-   Oxygen, carbon dioxide, and water-vapor concentration, separation,
    and control techniques.

-   Separation of carbon dioxide from a mixture primarily of nitrogen,
    oxygen, and water vapor to maintain concentrations of carbon dioxide
    below 0.3 % by volume.

-   Separation of nitrogen and oxygen from carbon dioxide to reduce
    concentrations of nitrogen and oxygen to less than 0.2 % by volume.

-   Removal of trace gases with regenerable sorbent beds, improved
    oxidation techniques or other methods.

**Water Reclamation:**

-   Efficient, direct treatment of waste water (e.g., urine, wash water,
    and condensates) without requiring expendables to produce potable
    and hygiene water including stabilization of waste water and purge
    gases prior to storage, processing, or overboard-venting. In
    particular, processes are required that reduce impurities in
    composite waste streams from greater than 500 PPM total organic
    carbon (TOC) content to less than 0.25 PPM TOC and inorganic salts
    from greater than 1000 PPM dissolved solids to less than 50 PPM.

-   Removal of ammonium ion from bioreactor process effluent streams
    from 500 PPM to less than 0.25 PPM.

-   Potability maintenance techniques.

-   Post-treatment of processed water by *in situ* organic removal from
    100 PPM TOC to less than 0.25 PPM TOC and removal of microorganisms
    from ten million CFU per ml to one CFU per ml.

-   Recovery of water from wastewater concentrates (i.e., brine from
    reverse osmosis).

-   *In situ* cleaning and sterilization of potable water systems.

-   Removal of sodium chloride from waste water (i.e., bioreactor
    effluent, reverse osmosis brine, etc.) to less than 10 PPM to enable
    it's use in plant growth nutrient solutions.

    **Waste Management:**

-   Biological and physicochemical technologies for recovering resources
    (e.g., carbon dioxide, water, nitrogen, hydrogen, etc.) from wastes
    (trash, plant biomass, human solid wastes, etc.). Functions to be
    performed are: waste stabilization and pretreatment, processing of
    the wastes, and product and by-product post-treatment. Waste
    processing technologies include incineration, aerobic biodigestion,
    anaerobic biodigestion, wet oxidation, supercritical oxidation,
    steam reforming, electrochemical oxidation and catalytic oxidation.
    Product and by-product post-treatment technologies should eliminate
    undesirable by-products such as nitric oxide and sulfur dioxide.

-   Treatment of laboratory, metabolic, and other wastes for storage.

-   Microbial techniques for waste treatment in micro- or
    partial-gravity.

    **Plant Growth and Food Production:**

-   Crop/Plant production systems required for the growth of plants for
    food and/or contributing to the reclamation of water, purification
    of air, and recovery of resources. Examples of such systems
    include: 1) sources for plant lighting such as high-efficiency lamps
    or solar collectors; 2) transmission and distribution systems for
    plant lighting including luminaires, light pipes and fiber optics;
    and 3) nutrient delivery systems, including hydroponics, solid
    substrates and materials for germination and wicking.

-   Mechanization and automation of propagation, seeding, and plant
    biomass processing. Plant biomass processing includes harvesting,
    separation of inedibles from edibles, cleaning and storage of
    edibles (seed, vegetable, and tubers) and removal of inedibles for
    final resource recovery processing.

-   Heat removal techniques for the plant growth lighting.

-   Facility or system sanitation methods to prevent excessive build-up
    of microorganisms within nutrient delivery systems.

-   Food and surface disinfectant system (i.e. hydrogen peroxide
    generator)

-   Health measurement of plant growth systems from parameters such as
    rate of photosynthesis, transpiration, respiration, nutrient uptake.
    Data acquisition should be non-invasive or remotely sensed using
    spectral, spatial, and image analysis. System modeling and
    decision-making algorithms may be included.

    **Sensors:**

-   Sensors emphasizing accuracy, operational reliability, real-time
    multiple measurement functions, in-line operation, self-calibration,
    and low energy consumption for monitoring and control of the life
    support processes. Species of interest include nutrient composition
    of plant growth hydroponic delivery systems, dissolved gases and
    ions in water reclamation processes, and atmospheric gaseous
    constituents including trace gases in air revitalization processes.
    Both invasive and non-invasive techniques will be considered.

## 09.05 Space Crew Performance Enhancements and Accommodations  {#space-crew-performance-enhancements-and-accommodations .unnumbered}

Lead Center: JSC

The goal of this subtopic is improving crew and ground operations
performance and productivity in a system context; documenting the
cost-effectiveness of the improvements; and developing innovative
concepts in crew accommodations and equipment required to support
complex, future manned space missions including missions of 5 years
without resupply. Desired products include innovative hardware and
software to enhance ground support operations and training, and
in-flight operations and environment. Specific areas for innovations
include:

**Human Factors:**

-   Advanced methods for collection and analysis of human performance
    with minimal human operator involvement. For example, methods of
    tracking body motion in 6 DOF without elaborate markers, setup,
    calibration or environmental constraints; automatically identifying
    categories of performance from videotaped records, such as time
    spent at a given task, time spent in translation, time spent in
    interaction with other crew members.

-   Technologies or tools to evaluate, measure or enhance habitability,
    including spacecraft interior layout; illumination and material
    reflectivity; lightweight acoustic control methods. An area of
    special interest would be in techniques for reconfiguring spacecraft
    habitable areas, including stowage, galley, sleep compartments,
    waste management systems, etc., for optimal use in both micro-g
    during transit to a planetary surface, and in partial-g on the
    planetary surface.

-   Technology, development tools, and quantitative methods for
    designing, evaluating and/or enhancing human interfaces with
    computers and information systems (e.g., displays, access methods)
    or remotely controlled systems (e.g., tele-operations, augmented
    feedback).

    **On-board Crew Support Systems:**

-   Novel food and/or food systems for microgravity including food
    processing, engineering an a shelf life extension of at least 3
    year; packaging and preservation technologies which minimize waste;
    improvements in acceptability; ease of handling in microgravity;
    food safety.

-   Processing and preparation of chamber grown wheat, rice, soybeans,
    sweet potatoes and potatoes into foods. Conversion to ingredients
    such as sugar and oil, as well as final products, including meat and
    dairy analogs, with emphasis on automation and utilization of food
    waste.

-   Personal hygiene systems in a zero-gravity environment. Examples:
    total body cleaning, hair grooming, cleansing agents compatible with
    closed-loop life support systems. -Personal crew equipment: flame
    and soil resistant clothing, portable lighting, safety and emergency
    equipment, and body and equipment restraints.

-   Housekeeping for zero-gravity including: habitat cleaning, trash
    management, apparel cleaning, particulate reduction and control, and
    cleansing agents compatible with closed-loop life support systems.

-   Tools, techniques, software for an in-flight maintenance system to
    maintain complex systems. Includes: expert diagnostics, in-flight
    manufacturing tools/techniques.

-   development of a hand held digital Single Lens Reflex type camera
    system with 32 bit color, ISO sensitivity range from 100 - 3200,
    image resolution equal.

    **Crew Training and Ground Operations**

-   Training and tutoring systems for mission operations support,
    including distributed cooperative training, virtual reality
    training, intelligent computer-based training, and authoring tools.
    Procedures or technology for evaluating effectiveness of different
    training methods.

    In addition, NASA seeks innovative data analysis technologies to
    support human space missions. Among these will be long duration
    missions throughout the solar system and the continually operating
    International Space Station. A small number of crewmembers, aided by
    intelligent robots, will deal with large quantities of highly
    complex and critical information. Ground support will be limited by
    communications constraints and by budgetary constraints. Proposals
    are sought in the following areas:

-   Immersive environments: real-time environments to enhance a human
    operator\'s ability to interact with large quantities of complex
    data, especially at distant locations.

-   Intelligent data analysis techniques: capable of interpreting,
    explaining, exploring, and classifying large quantities of
    heterogeneous data.

-   Intelligent software agents: goal-driven data analysis systems
    capable of adaptation and learning, and of collaborating with other
    agents and people.

-   Simplified user interfaces, including natural language interfaces.

    **Systems Automation for Human Space Vehicles:**

    Long duration space missions, as the International Space Station and
    missions to the Moon and Mars, will require an unprecedented degree
    of systems automation and maintainability. A key element in human
    space flight is the effective utilization of the crew members time
    and decision making ability. Functions should be routinely delegated
    to autonomous systems except when crew analysis and decision making
    are required. Specific areas of interest include the following:

    **Planning, Scheduling, and Resource Management**

-   Management of the actions of subsystems within the larger context of
    system flight rules and constraints.

-   Onboard planning, sequencing, monitoring, and re-planning of
    activities, including systems and crew activities.

    **Onboard Data Management**

-   Methods for selecting and summarizing vehicle systems and payload
    data for crew and for ground consideration.

-   Autonomous calibration of sensors and instruments.

    **Fault Detection and Recovery**

-   Support for developing and operating autonomous fault protection
    systems, with provision for crew oversight.

    **Onboard Software Architectures and Operating Systems**

-   Onboard operating systems and architectures for hosting software for
    crew-supervised autonomy.

    **Design, Testing, and Validation Tools**

-   Languages, environments, simulation tools for use in designing and
    testing autonomous and crew supervised autonomy systems.

## 09.06 Human Space Mission Thermal Control  {#human-space-mission-thermal-control .unnumbered}

Lead Center: JSC

Future human space missions will operate in more severe environments
than in the past. There is a need for highly efficient, lightweight, low
power and reliable internal and external active thermal control systems
for piloted spacecraft, rovers and planetary bases. Areas in which
innovations are solicited include the following:

-   Fault tolerant fluid to fluid heat exchangers that cannot fail in a
    way which permits leakage between fluid loops

-   Heat pumps to acquire waste heat at near 0 degrees C and reject the
    heat via a radiator at approximately 50 degrees C

-   Internal heat pumps to provide cabin dehumidification with a fluid
    heat sink of 15 to 25 degrees C

-   Flexible radiators which can be stowed compactly for transport and
    deployed for use

-   Micro-meteoroid tolerant and freeze/thaw tolerant radiators

-   Environmentally friendly, non-toxic single and two-phase working
    fluids that either freeze below 75 degrees Kelvin or do not
    significantly change density upon freezing or thawing

-   Two-phase heat transport loops and associated controls

-   Interactive, user-friendly, graphical computation techniques
    utilizing state-of-the-art low-cost work stations for analysis and
    prediction of performance for thermal and fluid systems

-   Thermal energy storage systems · Controllable water evaporator heat
    rejection devices for use in vacuum environments

    \* Note: thermal control innovations are also sought under the Plant
    Growth and Food Production section of the Spacecraft Life Support
    Infrastructure subtopic and under the Thermal Control subtopic in
    the Power, Propulsion, and Thermal Technology topic.

## 09.07 Cryogenic Fluids, Handling, and Storage  {#cryogenic-fluids-handling-and-storage .unnumbered}

Lead Center: LeRC

Component or concept proposals are being solicited to improve the
performance, operating efficiency safety and reliability of cryogenic
fluid storage and handling in all gravity environments (10^-6^ g to 1 g)
and Martian surface environments (i.e., dust, CO2 atmosphere). Tanks of
high energy propellant fluids, stored in their most efficient state, as
low pressure subcritical cryogenic fluids are susceptible to fluid loss
through environmental heating. Novel concepts are being solicited to
significantly reduce the heat conduction through tank supports and
penetrations and reduce solar radiation losses with insulating materials
or by intercepting shields. The ability to transfer cryogenic liquids in
nominal, reduced and low gravity conditions from storage vessels or
production facilities to user tankage is also critical. Cryogenic fluids
are used for life support, propulsion, and power systems. Innovations in
the following areas are needed:

-   Lightweight, low thermal conductivity cryogenic tank strut and
    support concepts.

-   Low thermal conductivity cryogenic tank penetrations, i.e.,
    instrumentation feed-throughs, feedlines, vent lines.

-   Lightweight, insulating thermal protection schemes.

-   Robust insulation concepts for multiple launch/landing and
    ambient/vacuum pressure cycles.

-   Devices for vapor free acquisition of cryogenic liquids. · Small,
    low power, lightweight (2 liter/minute) liquid oxygen transfer
    pumps.

-   Tank pressure control (e.g., thermodynamic vent) and/or integrated
    tank boiloff control and product liquefaction technologies.

-   Lightweight mechanical fittings and flexhoses with low heat leak.

-   Autonomous cryogenic disconnects and couplings.

-   Flowmeters and densitometers for measurement of densified,
    multi-phase cryogens at flow rates of 1.4 to 5.6 liters per second.

-   Instrumentation for monitoring cryogens in low gravity including
    mass quantity gauging, liquid-vapor sensing and free surface
    imaging.

-   Cryogenic Pumping Systems without cryogenic seals. As an example,
    magnetically coupled pumps that can handle Liquefied Natural Gas
    (LNG), Liquid Oxygen (LO2) or Liquid Hydrogen (LH2). Magnetically
    coupled pumps eliminate one of the significant leak potentials in
    today\'s ground systems.

-   Cryogenic Quick Disconnects are particulate sensitive. Mating these
    disconnects remotely raises concern of seal damage and subsequent
    leaks at cryogenic temperatures. QDs in all sizes (0.25 to 10.0 inch
    diameter) are needed for future exploration missions and future
    launch vehicles.

-   Cryogenic Couplings are also particulate and scratch sensitive.
    Development of robust sealing couplings that are compatible with
    cryogenic temperatures and Liquid Oxygen compatible are also needed
    for future exploration missions and future launch vehicles.
    Diameters of 0.25 to 10.0 inches

## 09.08 Extravehicular Mobility/Activity  {#extravehicular-mobilityactivity .unnumbered}

Lead Center: JSC

Advanced extravehicular activity (EVA) systems are necessary for the
successful support of future human space missions. Complex missions
require innovative approaches for maximizing human productivity and for
providing the capability to perform useful work tasks. Requirements
include reduction of system hardware weight and volume; increased
hardware reliability, durability, and operating lifetime (before
resupply, recharge and maintenance, or replacement is necessary) reduced
hardware and software costs; increased human comfort; and
less-restrictive work performance capability in the space environment,
in hazardous ground-level contaminated atmospheres, or in extreme
ambient thermal environments. All proposals must lead to specific Phase
II experimental development that could be integrated into a functional
EVA system. Innovations sought include the following:

**Environmental Protection:**

-   Radiation protection technologies that protect the suited crewmember
    from radiation particles.

-   Puncture protection technologies that provide self-sealing
    capabilities when a puncture occurs and minimizes punctures and cuts
    from sharp objects.

-   Dust and abrasion protection materials to exclude dust and withstand
    abrasion.

-   Thermal insulation suitable for use in low ambient pressure, but not
    vacuum, environment.

    **EVA Mobility:**

-   Space suit gloves, produced with size-reproducible manufacturing
    processes, that provide highly dexterous hand, fingers, and thumb
    mobility and tactile sensitivity, and that incorporate active
    thermal control capability for removing and/or adding heat depending
    upon external ambient thermal conditions and hand-grasp surface
    temperature.

-   Space suit soft joints that provide dual-axis capability and low
    torque in rotational components and that also minimize stowage
    volume, and that are lightweight, low cost, and large range.

-   Space suit shoulder that can accommodate large range of suit
    pressures from 3.5 to 8.3 psi, is low torque, lightweight, and low
    cost.

-   Space suit low profile waist bearing that maximizes torso rotation
    that is necessary for partial gravity mobility requirements and is
    also lightweight and low cost.

    **Life Support System:**

-   Long-life and high-capacity chemical oxygen storage systems for an
    emergency supply of oxygen for breathing, such as:

-   Chlorate candles that provide reliable backup oxygen supply.

-   Potassium superoxide/fullerine stowage of oxygen to reduce volume.

-   Low-venting or non-venting regenerable individual life support
    subsystem(s) concepts for crewmember cooling, heat rejection, and
    removal of expired water vapor and carbon dioxide.

-   Fuel cell technology that can provide power to a space suit.

-   Convection and freezable radiators that will be low cost and weight
    for thermal control.

-   Water membrane evaporator that can provide reliable cooling at Mars
    pressure.

-   Microencapsulated wax and carbon brush garments that provide direct
    thermal control to crewmember.

-   High reliability pumps and fans.

-   CO2 and humidity control devices which, while minimizing
    expendables, function in a CO2 environment.

**Sensors/Communications/Cameras:**

-   Information displays and input and output interfaces for use by the
    EVA-suited individual, including displays for obtaining status
    information of and/or controlling systems performance or work-task
    related equipment.

-   CO2, bio-med, and core temperature sensors with reduced size,
    lightweight, increased reliability, and packaging flexibility.

-   IR camera that displays temperature of environment for safe handling
    of objects and are integratable into a spacesuit.

-   Visual camera that provides excellent environment awareness for
    crewmember and public and are integratable into a spacesuit.

-   Microphone on glove that detects flows and proper operation of
    equipment by glove sound sensors.

-   Mini-mass spectrometer that detects N2, CO2, NH4, O2, and hydrazine
    partial pressures.

-   Radio/laser communications that provides good communications among
    crew and base.

    **Integration:**

-   Robotics interfaces that permit autonomous robot control by voice
    control via EVA.

-   Minimum loss airlock providing quick exit and entry.

-   Recharge and checkout systems that lower EVA overhead time for crew.

-   Work tools that assist the EVA crewmember during movement in
    zero-gravity and at worksites. Specifically, devices that provide
    temporary attachments, that rigidly restrain equipment to other
    equipment and the EVA crewmember, and that contain provisions for
    tethering and storage of loose articles such as tool sockets and
    extensions.

-   Surface mobility devices for EVA crewmembers.

## 09.09 Robotics

Lead Center: JSC

Proposals are solicited for innovative concepts that will both increase
robotic dexterity manipulation capabilities, and reachability, and also
increase capabilities for humans to interact with and to control robotic
systems to perform on-orbit operations while minimizing the workload to
EVA and IVA astronauts, and ground operators:

**Robotic Manipulators, End Effectors, and Joints**

Proposals are sought which include improvements to robotic joints,
actuators, end-effectors, tools, and mechanisms. Proposals should
address issues associated with space compatibility. Specific areas of
interest include the following:

-   Increased power to weight ratio and reduced scale actuators
    including magnetostrictive motors and synthetic muscles.

-   Miniaturized actuator control and drive electronics.

-   Miniaturized sensing systems for manipulator position, rate,
    acceleration, force and torque.

-   Robotic grasping and handling systems that accommodate existing EVA
    tools including, human-sized multi-fingered dexterous end-effectors.

-   Anthropomorphic systems.

-   Tools, fastening systems, and fluid connectors that accommodate both
    EVA astronauts and robotic systems.

-   Sensor-guided tools providing higher precision or lower contact
    forces.

-   Miniature mechanisms for planetary robotics applications such as
    rovers and sub-surface explorers. Novel mechanisms are needed to
    enable exploration of planetary bodies by low-power, low-weight
    robotic systems. Examples include rock fracture devices, sample
    manipulation and caching devices, instrument placement devices,
    sub-surface sampling devices, and the actuation components for these
    devices.

-   Low-mass and low-power surface and sub-surface sampling devices
    (e.g., scraping, drilling, impact or vibratory surface penetration)
    for planetary surface exploration.

-   Miniature, low-power, low-weight mechanisms are needed to enable
    planetary exploration and science by rovers, sub-surface explorers,
    aerobots, and underwater robots.

    **Human/Robotic Interface**

    Proposals that improve operator efficiency via advanced displays,
    controls and telepresence interfaces, improve ground based robotic
    control technology, and improve the ability of humans and computers
    to seamlessly control robotic systems are sought. Specific
    technology requirements include the following:

-   Tactile feedback devices that provide operator awareness of contact
    between work space objects and the robot structure. Key aspects of
    this technology are ergonomics and safety.

-   Force feedback devices that provide operator awareness of
    manipulator and payload inertia, gripping force, and forces and
    moments due to contact with external objects. Key aspects of this
    technology are ergonomics and safety.

-   Stereo graphic display systems that provide high fidelity depth
    perception, field of view, and high resolution.

-   Ground-based control technology which is able to compensate for time
    delays of several seconds.

-   User interface that does not require the operator to wear
    exoskeletons to control the motions of the robot.

-   Tracking position and orientation of user appendages, (i.e., head,
    arms, fingers, eyes) for the purpose of providing motion commands to
    the robot. Key aspects of this technology are to free the operator
    of any exoskeletons or devices attached to the body that impede or
    restrict operator movements.

-   Adaptive fault tolerant software: Systems capable of dynamic
    reconfiguration and learning.

-   Intelligent autonomous systems: Artificial intelligence based
    systems and architectures, with provision for crew oversight.

##   {#section-7 .unnumbered}

## 09.10 Advanced Manufacturing and Nanotechnology  {#advanced-manufacturing-and-nanotechnology .unnumbered}

Lead Center: JSC

Proposals are sought to establish and maintain state-of-the-art
manufacturing, hardware production, manufacturing processes, and
application of nanotechnology as they relate to future spacecraft.
Proposals in the following areas should be focused on hardware or
software products.

**Manufacturing Technology:**

Improve rapid prototyping using the Stereolithography (SLA) and Fusion
Deposition Modeling (FDM) techniques to produce functional prototypes
and working models, including use of single wall nanotubes. Improve
composites manufacturing using fiber placement, filament winding,
laminations, pultrusion, and resin transfer molding (RTM) techniques.
Improve the manufacture and precision of miniature mechanical components
and electronic assemblies, and develop micro- and nanotechnologies to
manufacture components.

**Nanotechnology:**

Potential applications and manufacturing techniques of single walled
carbon nanotubes (SWNT), or \"Buckey tubes\". Applications include
structural reinforcement, electronic, magnetic, lubricating, and optical
devices.

**Non-Metallics Manufacturing:**

Improve non-metallic manufacturing and fabrication using a wide range of
materials. Complete electronic fabrication and assembly, and printed
circuit board fabrication. Improve metal finishing of aerospace
components on metallic and nonmetallic surfaces and on ferrous and
non-ferrous alloys.

**Machine Tool Programming:**

Lessen the time necessary to program computer numerical control (CNC)
machinery using computer-aided design/computer-aided manufacturing
(CAD/CAM) programs. Machine tool operations of interest include
multi-axis milling, turning, electrical discharge machining (EDM), wire
electrical discharge machining (WEDM), and surface and cylindrical
grinding.

**Sheet Metal and Welding:**

Improve the use of state-of-the-art equipment for programmable
equipment. Improve welding techniques using processes that involve
ferrous and nonferrous alloys, including shielded arc, gas metal arc,
oxy-fuel, gas tungsten arc, plasma, ultrasonic, friction-stir,
resistance spot and seam, laser and other emerging technologies.

**Manufacturing Process Development:**

Improve the efficiency of space flight hardware production through the
development of new processes, advanced technology, and concurrent
engineering. Of special interest are advanced flexible manufacturing
systems where each part can have more than one process plan and can be
performed on alternate machines or simultaneously deal with alternate
routing options, and virtual manufacturing systems that include the
development of qualitative and quantitative procedures.

# 10 Achieve Routine Space Travel  {#achieve-routine-space-travel .unnumbered}

NASA's Human Space Flight Program seeks to open the space frontier by
exploring, using and enabling its development, and to expand the human
experience into the far reaches of space through the attainment of safe,
reliable, low-cost transportation. NASA seeks technologies to support
the development of sensors and instrumentation systems, including
ecological, environmental, and weather measurement technologies, for use
in ground processing, launch, and landing of space vehicles and
payloads. NASA seeks innovative technologies to prevent, detect, and
retard corrosion of ground processing equipment and facilities. NASA
also seeks innovative industrial engineering concepts, methodologies,
and processes that will enable a more cost-effective and efficient
hardware processing schedule.

## 10.01 Advanced Corrosion Technology  {#advanced-corrosion-technology .unnumbered}

Lead Center: KSC

Advanced technologies are solicited to prevent, detect, retard, or
control corrosion on systems such as ground support equipment or
facility infrastructure to improve the safety, reliability, and reduce
maintenance costs associated with the exposure to the extremely
corrosive launch environment at the Kennedy Space Center. New and
innovative techniques derived from technologies such as
electrochemistry, protective coatings, cathodic protection, chemical
treatments, and inhibitors could be used to enhance the corrosion
control effort for all affected systems. The launch environment at KSC
significantly contributes to the degradation of hazardous fluid and high
pressure gas systems, potable water distribution piping, steel
reinforced concrete structures, steel and aluminum access structures,
and all types of ground support equipment. Technologies developed in
this area are easily transferred to the commercial community and are
considered excellent dual use candidates. Corrosion technology is an
area of great potential growth based on the magnitude of problems in the
transportation and infrastructure industry. Specific areas of interest
include:

-   Real time salt and rainwater pH sensors for seacoast environment
    monitoring

-   Techniques to arrest corrosion of embedded reinforcing steel in
    concrete

-   Production of seamless tubing from corrosion resistant alloys

## 10.02 Environmental and Ecological Technologies  {#environmental-and-ecological-technologies .unnumbered}

Lead Center: KSC

Proposals are solicited for innovative and commercially viable
technologies in environmental management, environmental and ecological
monitoring, life sciences flight payloads and laboratory functions.
Innovative technologies are needed that will improve the capability to
collect and analyze environmental and ecological data. Of particular
emphasis are the development of systems to monitor ecological
parameters, biological organisms and environmental conditions remotely
over long periods of time under field and controlled chamber conditions.
Improved sensors for surface and ground water, ambient air, plant growth
chambers, animal holding rooms, bioreactors, and incubators are needed.
For sensors, miniaturization and automation should be emphasized along
with reliability and minimal calibration requirements. Techniques to
significantly improve and automate data management capabilities are
required, especially those that incorporate geographical information
system technologies for environmental and ecological monitoring and
selected growth chamber data which lend themselves to spatial dependent
manipulations. Innovative remediation technologies are also important,
particularly methods that minimize the impact to surrounding lands and
facilities. Methodologies to minimize or prevent the generation of
pollution during operations are also emphasized. Specific areas of
emphasis are:

-   Expert data and information management systems for improving
    environmental management and control including those with GIS
    capabilities.

-   Laboratory and field measurement devices including miniaturization
    of devices used in environmental monitoring, control and
    remediation.

-   Sensors for environmental parameters and microbial organisms,
    including remote sensors.

-   Remediation of chemical and petroleum soil and ground water
    contamination including in-situ methods and portable systems.

-   Expert control systems for environmental chambers.

-   Tools to identify the soil characteristics of a contaminated site,
    e.g., conductivity, transmissivity, and electrical differential.

-   Pollution preventing refrigerants, coatings, and non-ozone depleting
    cleaning substitutes.

-   Control technologies for volatile organic compounds (including those
    generated during painting operations and operation of power
    generators) and toxic and hazardous air pollutants (including
    nitrogen tetroxide, hydrazine and monomethylhydrazine).

-   Control technologies for cost effective waste minimization and/or
    reuse of industrial wastewater and hypergol waste.

## 10.03 Launch and Landing Site Instrumentation and Meterological Technologies  {#launch-and-landing-site-instrumentation-and-meterological-technologies .unnumbered}

Lead Center: KSC

This subtopic focuses on the development of sensors, transducers,
instrumentation systems and meteorological technologies uniquely suited
to and used for ground processing, launch, and landing of space vehicles
and payloads. This includes detection of hazardous gases, hydrogen
leaks, fires, and toxic vapors; transducers for cryogenic and hypergolic
servicing systems, data acquisition, and controls; optical and acoustic
sensors and systems; field inspection and testing; contamination
monitoring for payload processing; landing aids; weather and
environmental sensors for ground processing, launch, and landing
operations; and advanced sensors for automated ground operations
including automated surface and structural inspection, remote sensing,
and real-time vision systems for automated control and monitoring of
ground processing. Areas in which innovations are sought include:

-   Advanced Hazardous Gas Detection Technology. Planned usage is
    realtime multigas detection around space vehicle propellant systems
    during propellant loading, ground test firings, prelaunch checkout,
    launch and ascent (up to approximately 18 g rms shock and
    vibration).

-   Small, inexpensive, lightweight, rugged mass spectrometer capable of
    reliably measuring at least from 1 ppm to 100,000 ppm hydrogen,
    helium, oxygen and argon in a nitrogen background, and from 1 ppm to
    100,000 ppm hydrogen, nitrogen, oxygen, and argon in a helium
    background, during test firings, prelaunch checkout, launch and
    ascent (up to approximately 18 g rms shock and vibration).

-   Small, lightweight, rugged high vacuum pump for mass spectrometer
    system, capable of 60 liter/second or greater throughput, requiring
    no cryogenic fluids or inputs other than electrical power, and
    capable of operation without external roughing or backing pumps,
    during test firings, prelaunch checkout, launch and ascent (up to
    approximately 18 g rms shock and vibration).

-   Small, lightweight, rugged sample delivery system capable of
    delivering samples at ambient pressures ranging from 1 atmosphere
    down to approximately 100 Torr from multiple points within a space
    vehicle through sample tubing to a mass spectrometer analyzer at
    regulated inlet pressure. Gases are as specified above. System
    attributes include rapid sample transport, low swept volume upstream
    of the analyzer inlet and sufficient health checks to verify proper
    operation, during test firings, prelaunch checkout, launch and
    ascent (up to approximately 18 g rms shock and vibration).

-   The threat of adverse weather is a major cause of delay to launch,
    landing and ground operations. Lightning triggered by launch
    vehicles as they ascend is of special concern because current
    technology is inadequate to observe the conditions conducive to
    triggered lightning. An operationally viable real-time method is
    required to measure the spatial distribution of the intensity of
    electric fields in and around clouds in the vicinity of the launch
    site near the time of launch. Techniques such as rocket probes or
    non-eyesafe LIDARs which pose potential risks to personnel or
    equipment are not operationally viable. Remote sensing techniques
    are strongly preferred. High reliability, high probability of
    detection and low false alarm rate are essential. Cost is a
    significant consideration. Techniques relying exclusively on surface
    field mill or conventional radar observations are known to be
    inadequate. Techniques such as dual-polarization radar which rely on
    the presence of ice in the clouds are of severely limited value
    since electric fields in warm clouds and in clear air near clouds
    are also sought, but a reliable method of assuring that a detached
    thunderstorm anvil is charge-free would be of significant benefit.

-   Portable, direct-reading sensors and area monitors for hydrazine and
    monomethyl hydrazine capable of measuring at least 1 to 1000 ppb in
    air with normal ambient humidity range, with 15-30 seconds to
    achieve 90% of final reading, 15 minute or less warmup, accurate to
    the greater error of +/- 2 ppb or 10% of reading, and operating 3-6
    months without calibration and maintenance.

-   Small rugged O2 sensor for leak detection on rocket engines. Range
    of at least 250 ppm to 250,000 ppm with accuracy equal or greater
    than plus or minus 5% of reading. The sensor must be capable of
    operation from approximately 32 to 130 degrees F and survive
    approximately -224 to +175 degrees F. Response time should be 10
    seconds or less to indicate 90% of a change in concentration. The
    sensor should not be capable of causing a hazard, contamination, or
    corrosion when used on or around rocket engines during ground or
    flight testing.

-   Benchtop size pressure transducer dynamic calibration system capable
    of exciting pressure transducers with either shock or sinusoidal
    pressure variations from at least 0.1 to 1.0 psi, selectable (170
    dB), and from at least 1 to 5000 Hz frequency range. Traceability to
    NIST primary standards is required via combination of reference
    transducers, basic physical measurements, and calculation with
    supporting engineering error analysis.

-   Small, inexpensive camera or sensor capable of imaging and uniquely
    identifying hydrogen and hydrazine fires. Resolution should be at
    least 160 x 120 pixels or equivalent, higher resolution is
    preferred. The camera or sensor should be capable of seeing a six
    inch or smaller hydrogen flame at least 50 feet against a blue sky
    background, and must be rugged to withstand shock and vibrations
    induced by nearby liftoff of Space Shuttle or similar launch
    vehicle.

-   Small, rugged hydrogen leak detection sensors capable of measuring
    at least 100-100,000 ppm in air, nitrogen, or helium backgrounds.
    The sensor must respond to 90% of a change in concentration in 15-30
    seconds. The sensor must also be impervious to changes in oxygen
    concentration, ambient temperature, humidity, and other
    environmental factors.

-   Portable, reliable, and easily operated innovative field inspection
    sensors or systems capable of detecting and measuring flaws on
    flight hardware including debonds of insulation, structural cracks,
    surface defects, and corrosion.

-   Portable, reliable, and easily operated innovative field instruments
    to test aerospace fastener functionality, such as bolt preload,
    cracks under rivet heads, and weld seam integrity, without requiring
    hazardous field operations.

-   Point sensors for hydrazine, monomethyl hydrazine, and nitrogen
    dioxide capable of measuring at least from 1 to 100 ppm in 15
    seconds or less with small size (0.007 cubic meters or less) at the
    leak or sample location and operating 3-6 months without calibration
    and maintenance, during test firings, prelaunch checkout, launch and
    ascent (up to approximately 18 g rms shock and vibration).

## 10.04 Operations Industrial Engineering  {#operations-industrial-engineering .unnumbered}

Lead Center: KSC

Kennedy Space Center (KSC) operations have many unique aspects which
require development of innovative industrial engineering (IE)
technologies in order to obtain the substantial benefits derived from
applying IE principles in other organizations. Operations IE is a
technical discipline devoted to the science of process improvement and
optimization of operational phases of complex systems. The Space Shuttle
is NASA's first major program with a long-term operational phase. All
major current and potential future human space flight programs (the
International Space Station, X-vehicles, and Mars missions) are also
projected to have lengthy operational phases. Payload processing
activities are also emphasizing repeatable processes and improved
customer satisfaction. Therefore, operations IE technologies are
becoming even more strategically important to NASA. Operations IE
proposals should address the generic challenges of "doing more with
less" and delivering safer, better, faster, and cheaper products.
Advanced tools for improving/managing processes and performance
measurement systems are needed for spacecraft processing at KSC.
Proposals should also identify potential applications for enhancing the
operational phases of new NASA programs. Proposals may address the
development of new concepts, methodologies, processes, and/or software
support systems which advance the state-of-the-art in one or any
combination of the following general areas of interest: operations
research, process simulation modeling, statistical process control,
experimental design, planning and scheduling systems, project management
risk analysis, cost-benefit analysis, methods analysis, work
measurement, human factors, ergonomics, facility layout/design, incident
analysis, performance metrics, management information systems, and
benchmarking. Specific interests for the 1998 solicitation include (but
are not limited to) those listed below:

-   Advanced decision analysis, human factors, and operations research
    tools for optimizing utilization of scarce resources and minimizing
    the potential for human error during human missions to Mars and
    aircraft/reusable spacecraft (Shuttle and X-33) maintenance
    activities.

-   Advanced statistical quality control techniques for ensuring high
    quality, affordable manufacturing and processing of unique space
    hardware supporting human exploration and development of space.

-   Tools to facilitate a project management approach to large-scale
    transition and change in technical organizations. The tools should
    incorporate a set of best practices for successfully designing,
    implementing, and managing desired changes. The tools should also
    support strategic planning efforts through development, deployment,
    and refinement of goals, objectives, and organizational alignment
    measures.

-   Structured approaches for relating process-level and
    organization-level metrics.

-   A system that assists organizations in assessing risks associated
    with different proposed organizational approaches as they organize
    to most effectively meet changing needs. The changes may include
    personnel levels, roles, responsibilities, relationships, products,
    and skills.

-   A tool for rapidly assessing cost, schedule, and technical risks of
    proposed Shuttle hardware and software upgrades.

-   A tool for optimizing facility layouts for flight hardware, ground
    support equipment, and support functions. The tool should include an
    expert system capability to assist in multi-flow assessment planning
    and account for random unplanned activities and varying
    requirements.

-   Advanced data analysis, mining, and warehousing tools to assist in
    the development and maintenance of metrics supporting
    performance-based contracting and process improvement activities.

-   Innovative methods for human factors training and evaluation of
    training effectiveness.

-   Advanced task/methods analysis and procedure design techniques to
    enable effective implementation of advanced software and hardware
    systems in spacecraft test and checkout operations. Techniques
    should maximize work place safety and minimize the potential for
    human errors.

-   Advanced tools to measure and improve human-computer interaction
    with consoles and portable data collection devices.

-   Advanced technology to facilitate group work and distributed
    decision-making.

#  {#section-8 .unnumbered}

# 11 Enrich Life On Earth Through People Living and Working in Space  {#enrich-life-on-earth-through-people-living-and-working-in-space .unnumbered}

By its nature, the exploration and development of Space expands our
knowledge and fosters technologies that have great potential benefit on
Earth. The HEDS enterprise will be alert to and communicate the early
medical, educational, economic, and social benefits from its programs.
The objectives of this topic include promoting knowledge and
technologies that promise to enhance our health and quality of life;
broadening and strengthen our nation\'s achievements in science, math,
and engineering; involve our nation\'s citizens in the adventure of
exploring space; and joining other nations in the international
exploration and settlement of space.

## 11.01 Commercial Microgravity Research  {#commercial-microgravity-research .unnumbered}

Lead Center: MSFC

In accordance with the Space Act, as amended, to \"Seek and encourage to
the maximum extent possible the fullest commercial use of space,\" NASA
facilitates the use of space for commercial products and services. The
products may utilize information from in-space activities to enhance an
Earth-based effort, or may require in-space manufacturing. This subtopic
has the goal of commercial demonstration of pivotal technologies or
processes and the transfer of these technologies to industry in space or
on earth. Automated processes and hardware that will reduce crew time
are a priority.

This subtopic, therefore, has two goals. First, the commercial
demonstration of pivotal technologies or processes, second, the
development of associated infrastructure equipment for commercial
experimentation and operations in space, or the transfer of these
technologies to industry in space or on Earth. Automated processes and
hardware (robotics) which will reduce crew time are a priority. All
agency activity in microgravity including those in life science and
microgravity sciences which lead to commercial products and services are
of interest. Some specific areas for which proposals are sought include:

**Cell System Biotechnology**

Instrumentation to analyze cell reactor systems and characterize cell
structure in micro-gravity in order to develop enhanced drug therapies
that can also be applied to pharmaceutical development and
commercialization.

**Biomedical and Agricultural**

Instrumentation or techniques that exploit space-derived capabilities or
data to support the commercial development of space by the agricultural,
medical or pharmaceutical industry. This includes, in particular:

-   Innovative techniques for dynamic control and cryogenic preservation
    of protein crystals.

-   Innovations in preparation of protein crystals for x-ray diffraction
    experiments without the use of frangible materials.

-   Physiological measurement in micro-g of bone growth and immune
    system in micro-g.

-   Agricultural research, i.e., genetic engineering of plants using
    micro-g.

-   Innovative research in plant derived pharmaceuticals using micro-g.

    **Materials Science**

-   Applications using space-grown semiconductor crystals including
    epitaxilly grown materials for commercial electronic devices. The
    applications will also attempt to use the knowledge of the space
    grown material behavior to enhance ground processing of the
    materials to achieve equivalent performance of space-grown materials
    in electronic circuitry.

-   Applications using space-grown optical electronic materials such as
    fluoride glasses and non-linear optical compounds for commercial
    optical electronic devices and to achieve equivalent performance of
    space grown materials in ground processing.

-   Innovations using non-linear optical material to be processed in
    space.

-   Innovations for new space-processed glasses for optical electronic
    applications.

    **Microgravity Payloads**

    Design/develop microgravity payloads for space station applications
    that lead to commercial products or services.

    Enabling commercial technologies that promote the human exploration
    and development of space.

    **Combustion Science**

    Innovative applications in combustion research that will lead to
    developing commercial products or improved processes through the
    unique properties of space or through enhanced or innovative
    techniques on the ground.

    **Food Technology**

    Innovative applications of space research in food technology that
    will lead to developing commercial food products or improved food
    processes through the unique properties of space or through enhanced
    or innovative techniques on the ground.

## 11.02 Telemedicine and Health Diagnostic Services and Communications  {#telemedicine-and-health-diagnostic-services-and-communications .unnumbered}

Lead Center: JSC

Telemedicine, the integration of telecommunications, computer, and
medical technologies, permits NASA to monitor the physiological and
medical impact of space flight on astronauts. Innovative technologies
are being sought to support the current flight programs, such as Space
Shuttle, International Space Station and possible tools for support of
Space exploration programs of the future. During the past four decades,
NASA telemedicine technologies have found many applications in the
delivery of health care on Earth. Innovations in the following
technologies and applications (including hardware and software) in
telemedicine are being sought:

-   Dynamic imaging - (Full-motion, high-resolution images incorporating
    audio.) Dynamic imaging may be divided into interactive televideo
    (IATV), with parties at both ends communicating in real time (e.g.,
    patient-physician consultations, interactive continuing education),
    and store-and-forward, with video and audio clips transmitted for
    review at a later time, in the equivalent of audio-video e-mail
    (e.g., physician-physician consultations that are not dependent of
    immediate review, audio-video clips retrieved for tele-education).

-   Static imaging-single-frame visual images, typically of much higher
    resolution than is required for IATV consultations (which are
    generally of a resolution similar to a commercial TV picture).
    Examples include teleradiology, telepathology, and teledermatology.
    Although configured as a store-and-forward technology, static
    imaging may also be done in real time.

-   Biomedical monitoring and sensing - involves the acquisition,
    processing, communication, and display of electrical, physical, or
    chemical aspects of a human\'s health or physiologic state. This
    mode of telemedicine may be used for real time monitoring or for
    store-and-forward applications.

    The resolution, motion-handling, and interactivity of the
    telemedicine modalities are quite different, the hardware, software,
    and transmission requirements for these modalities are likewise very
    different. Information indexing and retrieval and the management of
    large databases are essential components of telemedicine. The
    following hardware and software technologies are of particular
    interest.

    **Hardware:**

-   Integrated transportable computerized medical systems capable of
    medical data acquisition, storage, retrieval and communication for
    use in environments with little or no medical facilities and
    expertise.

-   Data compression systems.

-   Wireless communication systems.

-   Intelligent sensor communication and interpretation systems.

-   Advanced human/computer interface systems.

    **Software:**

-   Data mining technology.

-   Data compression technology.

-   Decision support technology.

-   Data security technology.

-   Wireless communication technology.

-   Intelligent sensor distributed data communication and Interpretation
    technology.

-   Advanced human/computer interface technology.

## 11.03 Technological Methods for Enhancing Public Understanding/Involvement of Science/Technology Programs  {#technological-methods-for-enhancing-public-understandinginvolvement-of-sciencetechnology-programs .unnumbered}

Lead Center: MSFC

The future of Human Exploration and Development of Space (HEDS) is
heavily reliant on NASA customer engagement. Public access to HEDS
programs and HEDS understanding of customer expectations must be
integrated into a seamless information exchange and information
processing and decision system allowing HEDS managers to respond
promptly to customer expectations through program modification and/or
new program development.

Educational Outreach\--Within the commercial research and development
program, there needs to be an educational outreach plan that links
commercial research centers, academia, and industry to bring the
achievements of commercial space development (new drugs, materials such
as special tooling, agricultural products, etc.) into the classroom. The
educational outreach will be \"tiered\" to target specific levels of
education: primary, secondary, and college students through
post-doctoral research.

Proposals may address the development of new concepts, methodologies,
technologies, processes, software support systems and/or training
systems which advance the state of the art in techniques to improve
distribution and feedback for information about NASA programs, strategic
planning and knowledge derived from space based activities. Included are
the following:

**Information Distribution and Exchange:**

-   Technologies to distribute NASA information and data in an
    entertaining, educational and user friendly manner.

-   Technologies to improve the accessibility of NASA and NASA program
    Internet homepages and tools to visually coordinate and
    systematically integrate related subpages and other information
    distribution systems.

-   Technologies to improve customer feedback and involvement in NASA
    planning activities and to encourage direct customer participation
    in NASA activities. · Virtual tour (reality) technology for
    educating the public about NASA programs. Customer Analysis and
    Modeling:

-   Technologies to improve decision making through modeling and
    analyzing complex and conflicting customer needs and desires.

-   Technologies to assist optimization modeling and statistical
    analysis for \"best outcome\" program structuring and restructuring.

-   Metrics technologies for continual program evaluation and real-time
    response of program impact to NASA customers. Training:

-   Innovative software support technologies enabling familiarization
    and awareness-level training of NASA programs for NASA employees and
    other outreach volunteers.

    Technologies to promote NASA in the K-12 schools that are portable
    and easy to use that do not rely on the schools for any assisting
    hardware (e.g., overhead projectors should not be needed as a
    separate piece of hardware). Innovative technologies that promote
    math and science that would appeal to all children (including girls
    and minorities) using space scenarios as the backdrop.

# 12 Advance Space Communications and Operations  {#advance-space-communications-and-operations .unnumbered}

For frequent, affordable, capable space missions in the 21st century,
key technologies that contribute to lowering life-cycle costs and
increasing scientific returns are required. This includes technologies,
concepts, and advanced techniques for reliable telecommunication
services, microelectronics, flight computing, autonomous spacecraft
guidance, navigation, tracking and control, \'intelligent\' and
automated ground and flight systems, data transfer, handling and
storage, high-speed data communications networks. For NASA's use of
commercial services, advanced techniques and products that support
commercial LEO/MEO/GEO satellite networks are needed.

## 12.01 Flight/Ground System Autonomous Operations  {#flightground-system-autonomous-operations .unnumbered}

Lead Center: JSC

Development of spacecraft with a high degree of on-board autonomy,
possessing autonomous navigation and control, self-monitoring, and smart
instruments will enhance the efficiency of upcoming NASA flights. The
challenges include selective migration of operations functions to the
spacecraft, new onboard software architecture and operating system
concepts to integrate these functions, and new software design. NASA
seeks innovations that demonstrate the following characteristics:
spacecraft and instruments appearing as nodes on a network; similar
ground and flight operating systems; spacecraft interfaces that appear
the same to ground support systems; system operations requiring minimal
hands-on effort; centralized anomaly resolution; and direct delivery of
science data to users. In the area of on-board autonomy, areas of
interest include:

-   Guidance, navigation, and control.

-   Planning, scheduling, and resource management.

-   Onboard data management.

-   Fault detection and recovery.

-   Onboard software architectures and operating systems.

-   Design, testing, and validation tools.

    Innovations should use commercial standards for development,
    off-the-shelf hardware and software when possible, and have a high
    degree of commercialization potential.

    Areas of interest include:

-   Multimedia for access and control of all mission-specific data and
    processes.

-   Direct access to and control of instruments and their returned data
    by the investigators.

-   Distributed intelligent agents for automation of spacecraft and
    ground operations functions.

-   Advanced applications of expert system, model-based, and agent-based
    technologies in mission-operations automation.

-   Internet-based and Java-based approaches to mission operations.

-   Advanced data and information visualization techniques for mission.

-   Reuse of mission operations software on NT platforms in addition to
    UNIX.

-   Flexible plug and play architecture and standards.

-   Plug and play commercial software components that execute operations
    functions.

-   Techniques and tools for incorporating legacy applications into plug
    and play architectures.

-   Techniques for electronic documentation, electronic process control,
    massive distributed databases, intelligent archiving and retrieval,
    data analysis and visualization and other advanced information
    technologies.

-   Innovations for greater capacity high-speed data communication
    networks that are the result of increased data transfer and storage
    requirements.

## 8.3 EARTH SCIENCE {#earth-science .unnumbered}

NASA\'s Earth Science Enterprise uses satellites and other tools to
intensively study the Earth in an effort to expand our understanding of
how natural processes affect us, and how we might be affecting them.
Such studies will yield improved weather forecasts, tools for managing
agriculture and forests, information for fishermen and local planners,
and, eventually, the ability to predict how the climate will change in
the future. Earth Science has three main components: a series of
Earth-observing satellites, an advanced data system, and teams of
scientists who will study the data. Key areas of study include clouds;
water and energy cycles; oceans; the chemistry of the atmosphere; land
surface; water and ecosystem processes; glaciers and polar ice sheets;
and the solid Earth. Working together with the nations of the world,
Earth Science seeks to improve our knowledge of the Earth and to use
that knowledge to the benefit of all humanity.

http://www.hq.nasa.gov/office/mtpe/

13 Earth Measurement Systems [74](#earth-measurement-systems)13.01 Lidar
Systems For Ranging and Altimetry
[74](#lidar-systems-for-ranging-and-altimetry)13.02 Remote Sensing
Technology for Coastal Research
[75](#remote-sensing-technology-for-coastal-research)13.03 Lidar Systems
for Atmospheric Measurements
[76](#lidar-systems-for-atmospheric-measurements)13.04 Airborne
Stratospheric and Ecosystem Science Instruments
[77](#airborne-stratospheric-and-ecosystem-science-instruments)13.05
Earth-Orbiting Flight Measurement Systems
[78](#earth-orbiting-flight-measurement-systems)13.06 Measurement and
Enhancement of Satellite Scientific Data Quality and Applicability
[79](#measurement-and-enhancement-of-satellite-scientific-data-quality-and-applicability)13.07
*In Situ* Measurement Systems for Earth Observing Satellites
[80](#section-10)13.08 Synthetic Aperture Radar for Spacecraft
Applications
[80](#synthetic-aperture-radar-for-spacecraft-applications)13.09
Microwave Radiometry Technology
[81](#microwave-radiometry-technology)13.10 Mechanical and
Electromechanical Systems for Spacecraft and Instruments
[82](#mechanical-and-electromechanical-systems-for-spacecraft-and-instruments)13.11
Spaceborne Payload Pointing, Platform Control & GPS Guidance
[82](#spaceborne-payload-pointing-platform-control-gps-guidance)

# 13 Earth Measurement Systems  {#earth-measurement-systems .unnumbered}

NASA is fostering innovations that support implementation of the Earth
Science (ES) program. ES is an integrated international enterprise to
study the Earth system. ES uses the unique perspective available from
orbit to study land cover and land use changes, short and long term
climate variability, natural hazards, and environmental changes.
Additionally, ES uses in-situ and airborne measurements to complement
those acquired from Earth orbit. The largest ground and data system ever
undertaken will provide the facility for command and control of flight
segments and for processing, distribution, storage, and archival of vast
amounts of data.

## 13.01 Lidar Systems for Ranging and Altimetry  {#lidar-systems-for-ranging-and-altimetry .unnumbered}

Lead Center: GSFC

Major subsystem improvements are needed for airborne and space-based
laser altimeter sensors of planetary surface topography, vegetation,
clouds, and aerosols; and also for low signal level, ground-based
satellite laser ranging systems that measure laser pulse time-of-flight
to either cooperative reflectors or laser transponders on satellites.
Innovations are required in laser sensor subsystems as well as in the
overall efficiency, compactness, and reliability of the sensor with the
goal of developing a new generation of instrumentation for low-cost,
flight missions and autonomous operation. Specific technology challenges
include the following:

-   Pulsed Nd:YAG laser oscillators based on aluminum-free diode-pumping
    with greater than or equal to 6% overall electrical-to-optical
    efficiency and greater than 10 mJoule pulse energy for space-based
    laser altimeter missions.

-   Compact, conductively-cooled near-infrared laser transmitters with
    \< 5 nsec pulses, single spatial mode, several mjoule performance at
    kHz pulse rates.

-   Diode-pumped, Q-switched neodymium-based microlaser/amplifier
    systems operating reliably at few kHz rates with frequency-doubled
    pulsewidth less than or equal to 150 psec & 200 mW power at 532 nm.

-   Quadrant Geiger-mode avalanche, photo diodes or comparable
    microchannel plate photomultipliers with a quantum efficiency
    approaching 40% @ 532 nm, less than or equal to 400 psec risetime,
    and submicrosecond gating at 2 kHz rates.

-   Large aperture, ultralight-weight, scanning lidar receivers with
    high efficiency, narrow field-of-view, & narrowband filtering.

-   Silicon avalanche photo diodes, photodiode arrays, and photon
    counting detectors with quantum efficiency greater than 35% at 1064
    nm wavelength; and high efficiency, high speed, & low noise
    detectors for the 1500 to 2200 nm wavelength region.

-   Adaptive photon-counting correlation range receivers capable of
    extracting satellite range data with high time resolution (\< 20
    psec) during daylight operations.

-   High detectivity, spectrally diverse receivers including narrowband
    notch filters, high transmission narrow bandpass optical filters, &
    multi-channel array detection.

-   Optical devices for high spectral resolution measurements of
    Fabry-Perot interferometer output, specifically diffractive optic
    technologies.

-   Broadly-tunable narrowband laser sources throughout the visible to
    mid-IR region for incorporation into compact, lightweight species
    measuring instrumentation.

## 13.02 Remote Sensing Technology for Coastal Research  {#remote-sensing-technology-for-coastal-research .unnumbered}

Lead Center: SSC

The coastal region is comprised of ecosystems marked by frequent change
and widely fluctuating transitional boundaries of land and water. Remote
sensing technology is needed to better identify and delineate important
coastal environmental phenomena and to characterize their temporal and
spatial dynamics. This includes imaging in the solar reflected spectral
region over a range of temporal and spatial scales. Emerging
applications will study the complexity and dynamics of the zone
extending several kilometers seaward or inland of the shoreline.
Significant remote sensing technologies exist currently that have the
ability to characterize:

-   Both surface and subsurface water variables (e.g., temperature,
    salinity, suspended materials) and their changes with depth.

-   Vegetation changes occurring on small spatial scales or for which
    the spectral response is influenced by changing water level.

-   Natural hazards (e.g., hurricanes, sea level rise) and man-induced
    pressures on land cover and land use change in near shore areas.

-   Subsurface soil and sediment properties and their changes with depth
    in environments covered by vegetation or water.

    Efforts to integrate multiple sensors and/or supporting
    instrumentation are needed. Specific technological areas of focus
    include the following:

    **High Spatial Resolution, Hyperspectral/Thermal Airborne and
    Ground-Based Sensor Technology:**

-   Broad emphasis on imagery of dry land and wetland vegetation, and
    water targets within the incident solar (ca. 400-2,500 nm) and
    emitted thermal (8-14 mm) spectra.

-   Ground pixel resolution of 1 square meter or better while
    maintaining a scan swath width of 0.5 km or more for airborne
    systems.

-   Image resolution of 640 by 512 pixels or better for ground-based
    instruments.

-   Hyperspectral bands of: 10 nm or better spectral resolution to span
    the 400 nm-NIR range; 20 nm or better resolution to span the
    NIR-2,500 nm range.

-   One or more bands in the 8-14 mm range.

-   Co-registration of all channels in a data cube that contains GPS
    coordinates for target location.

-   Channel selectivity based on application.

-   Radiometric calibration for each channel.

    **High Resolution, Low Frequency, Subsurface-Penetrating Sensor
    Technology:**

-   Emphasis on measurement for a stratified depth profile in soils,
    peatlands, wetlands, and shallow marine environments.

-   Examples of variables of interest for characterization:
    organic/mineral sediment type; inundation/wetness condition;
    presence of archeological and other anomalies (e.g., mineral
    deposits, pipelines); physicochemical water properties (e.g.,
    salinity, dissolved compounds/pollutants).

-   Low frequency range (100 Hz - 500 MHz).

-   Spatial resolution: vertical \<2m; lateral \<10m.

-   Depth penetration: desired range of 1m minimum - 30m maximum
    (including water depth).

-   Incorporate capability for good geopositioning.

-   Desirable to incorporate innovative, independent technologies to
    measure variables (e.g., temperature) for improved inversion data
    analyses.

    **Moderate Resolution Hyperspectral Sensor Technology from Earth
    Orbit:**

-   Spectral sampling at 10nm bandwidth over 0.4-2.5 mm with high signal
    to noise ratio over 5-80% albedo.

-   Spatial resolution and coverage of \~30km swath at 30m GSD from
    \~490km altitude.

-   Emphasis on spectral and radiometric calibration and
    spatial/spectral co-registration of the data cube to enable advanced
    surface retrievals and compensation of atmospheric/scattering
    effects.

-   Demonstrations of interest include: size/mass reductions in
    integrated camera/spectrometer systems utilizing modular
    architectures, high read rate VIS/NIR and SWIR focal planes with
    reduced power/cooling needs, integrated sensor system electronics,
    on-board processing and data reduction tailored to data type and
    application.

## 13.03 Lidar Systems for Atmospheric Measurements  {#lidar-systems-for-atmospheric-measurements .unnumbered}

Lead Center: LaRC

Innovative developments are needed in lidar technology for the remote
measurement of atmospheric aerosols, clouds, molecular species (ozone,
water vapor, carbon monoxide, methane, and nitrous oxide) and
meteorological parameters (density, pressure, temperature, and wind
profiles). Specifically, technologies for expanding the measurement
capabilities of current airborne lidar systems and for the next
generation of spaceborne and Unmanned Aeronautical Vehicle (UAV) lidar
systems are sought. Technology innovations may include lidar components,
subsystems, and complete systems and may address reduced weight or power
or increased energy efficiency, reliability, or autonomous operation.

**For atmospheric constituent measurements:**

-   Solid-state laser technology for tunable and/or fixed frequency,
    high-energy (\>500 mJ at more than 10 Hz) pulsed lasers for
    spaceborne applications. This includes solid-state laser materials
    compatible with diode pumping and high efficiency (\>2.5% wallplug)
    and new or improved optical materials for high efficiency frequency
    conversion. Of prime interest are long-lifetime, low weight and
    volume materials and technologies applicable to lasers operating in
    the 0.28-0.32, 0.47-0.54, 0.7-1.1, and 1.5-2.4 micron regions; also
    interested in the 3.2-4.7 micron region. Also needed are
    single-mode, line-narrowed, compact sources for injection seeding in
    the 0.7-1.1 and 0.28-0.32 micron regions and high reliability, high
    efficiency, conductively cooled diode arrays operating in wavelength
    regions for pumping solid-state lasers.

-   Lidar receiver technology for large (\> 3m2), lightweight collection
    apertures having multiple-wavelength operation from UV to near IR
    are needed. Inherent spectral selection/dispersion and high peak
    transmission (50-80 %), electromagnetically tuned, narrow bandwidth
    (10-100 picometers) filtering are desirable. Small- and large-angle
    scanning (up to 3 degrees and 30-60 degrees off nadir, respectively)
    of 0.5-meter and 1.0-meter lidar systems are needed for space. Low
    mass and few to no moving parts.

-   Signal detection and processing subsystems with quick recovery (less
    than 3 microseconds) from saturation and high-speed, high-quantum
    efficiency (30-80 %) detectors with low-noise and good linearity are
    needed for lidar operation over large dynamic ranges.

-   For UAV applications, compact, high repetition rate, narrow
    linewidth laser transmitter systems are needed that produce energies
    from micro- to milliJoules (30 to 50 mJ) per pulse. Laser energies
    of more than 100 mJ at 30-1000 Hz in the UV and more than 200 mJ at
    10-20 Hz in the 355, 940, and 1064 nm region are needed.

    **For coherent wind measurements:**

-   Low mass, compact optics for deflecting a circularly polarized laser
    beam for a conical scan. Diameters of 5 cm to 2 m with an immediate
    need of up to 50 cm. Preservation of laser beam quality is required.

-   Technology for autonomous operation and alignment maintenance of
    coherent lidar systems.

-   Fast (few tens of microseconds) lag-angle compensation optics
    technology for precise, reliable steering of the optical axis of a
    space-based Doppler lidar.

-   Single-element and array detectors having high bandwidth, high
    quantum efficiencies over the entire bandwidth, linearity, and
    minimum cooling requirements. Also, an optical detector combined
    with a preamplifier in a single integrated circuit, with combined
    bandwidth up to several GHz.

-   Diode-laser arrays operating near .79 micrometers having pulse
    lengths \>1.0 ms, energy densities \>1.3 J/cm2, duty cycle \> .02,
    and narrow beam divergence.

-   High efficiency methods for concentrating the emissions from nominal
    1.0 cm square arrays to 4.0 mm diameter spot sizes.

-   Tunable single-mode semiconductor lasers or other compact, single
    frequency sources for use as injection seeders and/or local
    oscillators, with linewidths 0.1-0.2 MHz operating in the 1.8-2.2
    micron and 3.0-3.5 micron regions.

-   780- or 850-nm external grating lasers coupled into PM fiber and
    capable of delivering 10mW into the fiber. These products should be
    fiber coupled (input and output) tapered amlifiers (MOPA) at 780- or
    850- nm. Should capable of \>200mW into PM fiber and should be
    compact/lightweight.

    **For direct detection wind measurements:**

-   Techniques, components, and systems for measurement of the wind
    field and wind shear in the lower atmosphere using direct-detection,
    with accuracy better than 1 meter/second and range resolution better
    than 50 meters. Eye safety is a consideration.

-   Technology for high quantum efficiency (\>10 %), low dark count
    (\<1000 counts/second) photon counting detectors at 1064 nanometers
    that should be compatible with long term operation in space
    environment.

-   Single mode, diode pumped, pulsed, solid state laser at 355, 946,
    and 1064 nanometers with a narrow spectral width \<30 MHz at 1064
    nanometers. High wall plug efficiency, passive cooling, compact,
    rugged design, and 10 watt average for multi-year satellite
    missions.

-   High spectral resolution filters for direct detection of winds at
    355 and 1064 nanometers. The filter to have a 100 MHz bandwidth
    (FWHM) at 1064 nanometers, and a 1 GHz bandwidth (FWHM) at 355
    nanometers. Also, high throughput, out of band spectral blocking,
    frequency tunable, and frequency stabilization that should be
    compatible with long term operation in space environment.

##  {#section-9 .unnumbered}

## 13.04 Airborne Stratospheric and Ecosystem Science Instruments  {#airborne-stratospheric-and-ecosystem-science-instruments .unnumbered}

Lead Center: ARC

NASA requires innovations in methods for making measurements from
stratospheric airborne platforms (both conventional and remotely
piloted), and new methods in data analyses and model development.
Measurements of interest include both remote and *in situ* measurements
of the stratosphere, as well as, the surface of the Earth from
stratospheric platform aircraft such as the NASA ER-2 and unmanned
aeronautical vehicles (UAVs). Stratospheric composition measurements
include the identity and concentration of gaseous species, the number,
size, shape and composition distributions of cloud and aerosol
particles, and radiative properties and fields. Remote measurements for
the biosphere include species, community and land use identities,
biophysical and biochemical characteristics, and biodiversity measures
of ecosystems on land and in water, and their relationship to
geophysical variables. Field instrumentation is needed to correlate the
airborne measurements with exchange of biogenic trace gases between the
biosphere and the atmosphere. These measurements are critical to NASA
and also have many commercial applications such as water and land usage
for city planning and agribusiness, resource management, disease
monitoring, ecosystem remediation and natural disaster (earthquake,
fires and floods) assessment. Innovations needed include:

-   Advanced platforms, instrumentation and technology with increased
    speed, sensitivity, accuracy, specificity, and space-time coverage
    for the investigation of both physical and chemical stratospheric
    phenomena.

-   Advanced detector, source, pointing/tracking and miniaturization
    technology as well as improved sensor survival for long periods in
    harsh environments.

-   Self-diagnosis techniques that provide a continuous measure of data
    quality and instrument health. Real-time adjustments in sensor
    operation to compensate for instrument degradation or changes in
    sensed properties.

-   Data processing techniques that increase the usefulness of raw data
    in answering specific questions of current concern.

-   Analysis and modeling of the chemistry and dynamics of species
    measured from the ER-2 and future very high altitude science
    platform aircraft.

-   Improvements and applications of Digital Array Scanned
    Interferometry and innovative miniaturized CCD cameras for
    ecosystem, aquatic, atmospheric and edaphic analyses from
    laboratory, to field, to airborne, then to space.

-   Innovative uses of laser and other high speed/repeat cycle
    instrumentation for measurement of architectural properties of plant
    canopies and field measurement of biogenic trace gas fluxes of a
    variety of gas species, including CO2, N2O, NO, etc.

-   Technology to improve the real time acquisition of data about
    disaster assessment problems, including thermal scanners that can
    quantitatively measure high wildfire temperatures, can downlink or
    uplink these data to communications systems. Also, image processing
    and rectification procedures for automating the overlay of these
    data onto base maps for decision making.

-   Miniaturized data acquisition and storage system for advanced
    platforms (UAVs).

-   Direct application for recording of transient electrical bursts,
    e.g. lightning.

-   High capacity, high speed system (Time resolution \<1ms; storage \>
    2 gigabytes).

-   Light weight, low volume (\<2 kg; \<75 cubic cm).

-   Advanced platforms (UAVs) having altitude capability between the
    Earth\'s surface and 23 kilometers with an endurance of not less
    than 3 hours, and slow speed (i.e., under 8 meters per second) to
    permit slow responding meteorological sensors to sample properly.

-   Advanced platforms (UAVs) having lift capable of supporting 3-10
    kilograms of payload mass and the appropriate volume.

-   Advanced platforms (UAVs) having flight altitude, speed, pattern
    orientation, etc., controllable from the ground using a combination
    of the GPS and small computer technology (i.e., a GPS/PC-based
    autopilot).

## 13.05 Earth-Orbiting Flight Measurement Systems  {#earth-orbiting-flight-measurement-systems .unnumbered}

Lead Center: GSFC

NASA seeks development of smaller, less resource intensive instruments
and spacecraft for obtaining measurements from Earth-orbit required by
the Earth Science Enterprise program. Proposals are sought for
technologies that support advanced capabilities in Earth system science
including the following:

-   New mechanical and electrical devices and innovative packaging that
    provide significant reductions in system volume, mass, and power for
    the whole spectrum of Earth observing instruments such as:

-   Acousto-optic spectrometers and/or digital auto-correlators for
    passive microwave radiometers.

-   Frequency-agile and variable bandpass optical filters to enable
    radiometer imaging in frame camera mode.

-   Well-calibrated radiometers for atmospheric correction of
    multi/hyper-spectral imaging spectrometers.

-   Solid-state, local oscillators and mixers for 1-5 THz heterodyne
    microwave radiometers.

-   Low disturbance, long-life micro mechanical coolers for 50-80 K
    focal planes.

-   High energy, solid-state lasers for wind measurements.

-   Techniques to improve and simplify ground, airborne, and in-orbit
    calibration and validation of spectrometers and radiometers as well
    as to facilitate the transfer of standards from one platform to
    another.

-   Detector systems that cover the wavelength bands of interest to
    Earth science that require minimal or no active cooling such as
    SWIR, MWIR, and TIR detector arrays that operate at elevated
    (non-cryogenic) temperatures to enable smaller, lighter, and lower
    power multispectral and hyperspectral solar reflected and thermal
    infrared imaging systems.

-   Miniature passive atmospheric remote sensing systems for
    tropospheric and stratospheric chemistry measurements, atmospheric
    dynamics, earth radiation, clouds, aerosols, and other measurements
    important to monitoring global change. Advanced sensor technologies
    include, but are not limited to, ultraviolet through far-infrared
    detectors, ground and flight calibration sources/techniques, and
    advanced signal processing.

-   Approaches that eliminate the need for scanning mechanisms and
    moving parts.

-   Methods to improve operational life of instruments and spacecraft.

-   Simplifications to traditional design, development, integration, and
    test programs for flight hardware.

-   Formation flying and management of constellations of Earth observing
    and remote sensing spacecraft.

-   Smart command and data handling systems and increased levels of
    autonomy for remote sensing spacecraft in low Earth and synchronous
    orbits.

-   Large format, high sensitivity active pixel arrays for smart sensor
    concepts in the UV thru thermal IR spectral region. High degree of
    on-focal-plane integration to incorporate signal processing
    functions and micro-optic beam conditioning. There is a particular
    desire for arrays which do not require active cooling in order to
    reduce power and size of future instrumentation.

-   Extension of this technology into the far-IR, a region of
    significant scientific interest not yet benefiting from the same
    level of sensor development, is of special interest.

## 13.06 Measurement and Enhancement of Satellite Scientific Data Quality and Applicability  {#measurement-and-enhancement-of-satellite-scientific-data-quality-and-applicability .unnumbered}

Lead Center: SSC

Proposals are sought for the development of advanced technologies to
enhance the commercial application of the commercial remote sensing
industry and enhance the commercial application of earth science data.
Focus areas are to provide tools for interpretation, visualization or
analysis of remotely sensed data; and to provide qualitative and
quantitative analysis tools and techniques for performance analysis of
remotely sensed data. Areas of specific interest include:

-   Visualization of multi-variate geospatial data including remotely
    sensed data from the following: 1) airborne and satellite platforms,
    vector data from public and private archives, 2) cartographic
    databases from public and private sources, 3) continuous surface
    data held as a raster data model, and 4) 3-D data held in a true 3-D
    raster model.

-   Innovative approaches that contribute to the understanding of data
    through the display and visualization of some or all of the above
    data types including providing the linkages and user interface
    between the cartographic model and attribute databases.

-   Innovative approaches for incorporation of GPS data into *in situ*
    data collection operations with dynamic links to spatial databases,
    including environmental models.

-   Data merge and fusion software for efficient production of
    commercial digital products.

-   Data mining systems to allow content-based searches of ES databases
    and reduction of bandwidth transmission to essential-only data.

-   Techniques to enhance performance of wide-area networks supporting
    highly distributed data production, archive, and access functions.

-   Autonomous classification systems of high-resolution digital data.

-   Fusion of science data sets to correlate similar data sets from
    diverse spacecraft and aerial vehicles and provide unique,
    commercially useful information products.

-   Innovative techniques for the validation of thermal and LIDAR
    imaging systems.

-   Software to commercialize the digital topography and vegetation
    canopy data products that are obtained by airborne and space-based
    active optical sensors.

-   Innovative techniques to automate quality assurance processes for
    science data products.

-   Unique, innovative data reduction and analysis methodologies and
    algorithms, particularly for hyperspectral data sets.

##  {#section-10 .unnumbered}

## 13.07 *In Situ* Measurement Systems for Earth Observing Satellites  {#in-situ-measurement-systems-for-earth-observing-satellites .unnumbered}

Lead Center: GSFC

Proposals are sought for the development of *in situ* measurement
systems that will enhance the scientific utility of the Earth Science
Enterprise program and that will broaden the uses of its systems to
include products of interest to commercial and governmental entities
around the world including: NOTE: we are not looking for Unpiloted
Aerial Vehicles (UAVs), but rather for sensors that could fly on these
and other suborbital platforms.

-   Autonomous GPS-located ocean platforms to measure and transmit to
    remote terminals upper ocean and lower atmosphere properties
    including temperature, salinity, momentum, light, humidity,
    precipitation, and biology. Similar sensor packages for use onboard
    ships while under way.

-   Autonomous low-cost systems to measure surface and lower atmospheric
    parameters including soil moisture, precipitation, temperature, wind
    speed and humidity.

-   Systems for *in situ* measurements of cloud radiative properties
    including extinction, absorption, scattering phase function and
    phase function asymmetry.

-   Small, lightweight instruments suitable for balloon, kite, or small
    remotely piloted aircraft for *in situ* measurement of cloud
    parameters and atmospheric trace gases.

-   High sensitivity measurement of atmospheric trace gas mixing ratios.
    Robust instrumentation for unattended operation in harsh
    environments.

-   Systems and devices for measurement of atmospheric aerosol chemical,
    microphysical, and radiative properties. Autonomy desired for
    ground-station network applications and deployment aboard aircraft.

-   Systems to measure line- and area-averaged rain rate at the surface
    over lines of at least 100 meters and areas of at least 100x100
    meters.

-   Lightweight, low-power systems that integrate the functions of
    inertial navigation systems and GPS receivers for characterizing the
    flight path of remotely piloted vehicles.

-   Low-cost, stable (\<1% over several months) portable radiometric
    sources for field characterization of spectral radiometers.

-   Innovative approaches for the gathering, storing, and forwarding of
    *in situ* measurements using common carrier infrastructures.

-   Lightning location techniques to locate VLF sferic sources (5 to 15
    kHz) within 100 km at ranges of 2000 km or more.

-   Low cost, lightweight, deployable sensors for *in situ* and aircraft
    measurements of liquid and ice hydrometers in cloud and
    precipitation systems.

-   Hardware and algorithm approaches for wind measurements using
    spaceborne precipitation and cloud lidars.

-   Systems for *in situ* measurements of atmospheric electrical
    parameters including electric and magnetic fields, conductivity, and
    optical emissions.

-   Wide-band microwave radiometer capable of high-speed
    characterization of cloud parameters, including liquid and ice phase
    precipitation, that can operate in harsh environmental conditions
    (e.g., on-board ships).

-   Autonomous GPS-located air borne sensors that remotely sense
    atmospheric wind profiles in the troposphere and lower stratosphere
    with high spatial resolution and accuracy.

## 13.08 Synthetic Aperture Radar for Spacecraft Applications  {#synthetic-aperture-radar-for-spacecraft-applications .unnumbered}

Lead Center: JPL

The two main problems to solve for spaceborne synthetic aperture radar
(SAR) programs are to reduce the radar instrument cost and to increase
the use of SAR data among the remote sensing community. Advances in
radar technology are sought to enable low cost spaceborne SAR.
Technologies which may lead to advances in radar architecture design,
hardware, and algorithms are the focus of this subtopic. In order to
increase the SAR user community, this subtopic will also consider SAR
data applications and post processing techniques. For SAR applications,
the frequencies of interest include L-band, C-band, and X-band. The
required bandwidth varies from 20 MHz to 300 MHz to achieve the desired
resolution. The synthetic aperture technique is also applied to a radar
ice sounder, which is a low frequency radar with very high percentage
bandwidth. Specific areas in which advances are needed include:

**Synthetic Aperture Radar:**

-   Electronically steerable phased-array antenna architectures.

-   Shared aperture, multi-frequency antennas.

-   Lightweight antenna structures and deployment mechanisms.

-   High-efficiency, low-cost transmit/receive modules.

-   Advanced radar system architectures including flexible, broadband
    signal generation and autonomous radar control concepts.

-   Advanced radar component technologies including low-loss RF switch;
    high-efficiency power converters; high-speed analog-to-digital
    converters; low-sidelobe chirp waveform generator.

-   Data acquisition, storage and on-board processing technology.

-   SAR data processing algorithms and data reduction techniques.

-   SAR data applications and post-processing techniques.

    **Radar Sounder:**

-   Synthetic aperture processing technique to increase resolution.

-   Broad-band (100 % or more) low frequency (\<100MHz) antenna.

-   Highly efficient, broadband, low frequency (\<100 MHz) transmitter.

-   Low-power, highly integrated radar components.

## 13.09 Microwave Radiometry Technology  {#microwave-radiometry-technology .unnumbered}

Lead Center: GSFC

Proposals are sought for the development of techniques and/or components
that enhance the calibration accuracy of microwave radiometers or save
cost and time of development. Both the spaceborne and airborne microwave
radiometer systems are included in this category. The airborne
radiometers are important scientific instruments in their own right, and
they are frequently used to calibrate space-borne instruments. A few
examples of well-known space-borne microwave radiometers include the
TRMM Microwave Imager (TMI), the Special Sensor Microwave Imager (SSMI),
and its next generation, SSMIS, the Advanced Microwave Sounding Unit
(AMSU-A, AMSU-B), Microwave Humidity Sounder (MHS) and its newer
version, HSB. New ideas of improving the calibration techniques are
sought for microwave radiometers such as the examples cited above, both
in their on-board calibration sub-systems, as well as pre-launch testing
methodology.

**On-board calibration systems:**

-   Improvements in Hot and Cold Reference Targets (also known as Hot
    load and Cold Load) designs.

-   New designs for on-board calibration systems with improved
    calibration accuracy and long-term stability are desired. Different
    target designs and/or new calibration sources, e.g., using stable
    noise generators, can be considered.

-   This item also includes improvements in linearity and stability of
    the instrument so that a stable calibration is maintained over time.

-   Optimization of pre-launch calibration methodology for on-board
    calibration systems. We seek new ideas to improve the pre-launch
    testing methodologies with an aim to increase the overall
    calibration accuracy and/or to save test time and cost.

**Post launch validation:**

-   Techniques are desired for validating the instrument\'s measurement
    after it is on-orbit, e.g., by comparing with ground truths, or with
    other similar space-borne instruments in space and time coincidence.
    The validation can also include techniques that can be used for
    post-launch geolocation.

    **Subsystems:**

-   MMIC receivers and low noise amplifiers for millimeter and microwave
    radiometers at 60 to 425 GHz. Specific frequencies of interest
    include 118, 183, 380, and 425 GHz.

-   Technologies for 2 to 6 meter deployable or inflatable antennas with
    a surface finish in the range of 12.5 to 50 micrometers rms that
    will enable missions with inherently large apertures.

-   Compact, low mass, high efficiency microwave sources suitable for
    radiometers.

##  {#section-11 .unnumbered}

## 13.10 Mechanical and Electromechanical Systems for Spacecraft and Instruments  {#mechanical-and-electromechanical-systems-for-spacecraft-and-instruments .unnumbered}

Lead Center: GSFC

Proposals are sought for new concepts in the areas of structures,
mechanisms, control systems, transducer technology, and electronics as
they apply to the development of advanced mechanical and
electromechanical components or systems for use in spacecraft or
precision space flight instruments. The scope of this subtopic includes
new materials and fabrication processes as well as new techniques and
tools for modeling, analysis, design, and test of mechanical and
electromechanical components and systems. The objective is to provide
concepts that will enable reliable operation in the space environment
with increased performance and efficiency while reducing design and
production costs. This topic spans applications that include:

-   Regulating and tracking mechanisms like precision mechanisms for
    scanning the mirror in a Michelson or Fabry-Perot interferometer.

-   Antenna pointing mechanisms and inertially stabilized platforms.

-   Low power and long life mechanisms that can be used in instruments
    operating in cryogenic environments of a few degrees Kelvin.

-   Magnetic bearings for mechanisms in space flight instruments or
    spacecraft subsystems such as long life optical beam chopping
    mechanisms.

-   Low vibration reaction and momentum wheels and high speed flywheels
    for the integration of the spacecraft attitude and power systems.

-   Micro-Electro-Mechanical Systems (MEMS) and
    Micro-Opto-Electro-Mechanical Systems (MOEMS) for instruments.

-   Active control of large lightweight structures.

-   Vibration isolation platforms that counter microphonic disturbances
    to delicate mechanisms or the detector assembly in a precision
    instrument.

-   Large spacecraft appendages like solar arrays and instrument booms.

-   Large aperture telescopes.

-   Electromechanical and opto-mechanical devices for adaptive optical
    systems such as fast beam steering mirrors.

-   Deformable mirrors and focus adjustment mechanisms.

-   Stored energy actuators (e.g. spring energy) or phase change alloy
    type actuators.

-   Lightweight precision deployable structures for large aperture
    telescopes. Structures must be extremely compact for launch and have
    a reliable and positionally repeatable deployment scheme. Structural
    stability over wide temperature ranges is emphasized.

-   Rapid prototyping methods for medium to large structures (meters3 as
    opposed to centimenters3). Structures need not be of flight
    materials.

-   Multifunctional structures (e.g. structures that combine electronics
    and/or thermal management).

-   Low cost manufacturing techniques for small and large flight
    structures which are not mass produced.

-   Structures with extremely high or extremely low thermal
    conductivity.

-   Novel deployment-to-orbit mechanisms for multiple (micro, nano, or
    pico) satellite systems.

## 13.11 Spaceborne Payload Pointing, Platform Control & GPS Guidance  {#spaceborne-payload-pointing-platform-control-gps-guidance .unnumbered}

Lead Center: GSFC

The development of spacecraft flight and ground system technologies for
the following items are essential to meet the Earth Science Guidance,
Navigation and Control (GN&C) needs of the future: 1) miniaturization of
GN&C systems and components, 2) enhanced functionality and autonomy of
GN&C systems/components, 3) advanced analytic processes, architectures,
and techniques, and 4) GN&C systems utilizing GPS. Specific areas
include:

-   Enhanced performance as well as reduced cost, mass, power, volume,
    and reduced complexity of all spacecraft GN&C system elements.

-   Components with new or enhanced sensing capabilities.

-   Concepts for autonomous guidance of space transportation systems
    during atmospheric flight phases.

-   New concepts for spacecraft control including but not limited to,
    formation flying techniques such as master/slave satellite
    strategies, coordinated viewing/pointing, and virtual platforms.

-   Control theory, filtering techniques, processing advances, software
    architectures, and advanced sensors. Improved environmental models
    for attitude and trajectory determination and prediction.

-   Concepts for monitoring spacecraft functions and environmental
    conditions.

-   Assessing health status and optimizing performance through in-flight
    identification, fault detection stabilization, and re-configurable
    control.

-   Rigid and flexible body control methods that are robust to
    parametric uncertainty and modeling error.

-   Computer aided engineering and design tools and parallel algorithms
    for analysis and development of GN&C systems. Innovative testbed
    development capabilities in the area of computer and dynamic
    simulation of multiple satellites using spacecraft processors to
    communicate and maintain the formation.

-   Methods for in-flight attitude sensor alignment and transfer
    function calibration.

-   Filtering techniques and expert systems applications for near
    real-time trajectory determination and control.

-   Autonomous performance of ground system functions including attitude
    and trajectory determination, monitoring of spacecraft functions and
    environmental conditions, assessing ground system and spacecraft
    health status, ground system fault detection, orbital event and
    attitude dependent prediction support utilizing advanced techniques
    such as fuzzy logic and neural networks.

-   Low power and mass propulsive attitude control actuators and related
    subsystem components for nanosatellites in constellation or
    formation flying missions. Actuators to consume less than one watt
    of power at three volts, providing impulse bits on the order of one
    micro-N-sec for 3-axis nanosats or 40 milli-N-sec for
    spin-stabilized nanosats.

-   Low cost momentum wheels that can both store momentum and provide
    electrical power when used in pairs.

    GPS receiver hardware and algorithms that use GPS code and carrier
    signals to provide spacecraft navigation, attitude, and time:

-   Combined navigation and attitude space receivers.

-   Advanced antenna designs.

-   Navigation techniques that may employ WAAS corrections.

-   Relative navigation via a cross-satellite communications link, and
    formation flight of satellite constellations.

-   Navigation, attitude, and control for spacecraft proximity
    operations.

## 8.4 SPACE SCIENCE {#space-science .unnumbered}

NASA\'s Space Science Enterprise seeks to discover the mysteries of the
universe, explore the solar system, find planets around other stars, and
search for life beyond Earth. From Origins to Destiny, the Enterprise
seeks to chart the evolution of the Universe, its galaxies, stars,
planets, and life. Its mission includes four science themes: Sun-Earth
Connection - SEC (Space Physics), Solar System Exploration - SSE
(Planetary Science), Structure & Evolution of the Universe -- SEU
(Astrophysics), and Astronomical Search for Origins and Planetary
Systems. Each of these themes has a committee made up of both NASA and
non-NASA scientists. Among their activities is the creation of a
scientific roadmap for the next twenty years \-- a plan for future space
missions that will probe the mysteries of the universe.

http://www.hq.nasa.gov/office/oss/osshome.htm

14 Space-Based Large Telescopes [84](#space-based-large-telescopes)14.01
Large Aperture Space Telescope Technologies
[84](#large-aperture-space-telescope-technologies)15 *In Situ*
Exploration And Sample Return
[85](#in-situ-exploration-and-sample-return)15.01 *In Situ* Science
Payload Systems [86](#in-situ-science-payload-systems)15.02 Instrument
Deployment, Sample Acquisition and Retrieval Systems
[86](#instrument-deployment-sample-acquisition-and-retrieval-systems)16
Astrophysical and Space Physics Observations
[87](#astrophysical-and-space-physics-observations)16.01 Technologies in
Support of Gamma Ray, Cosmic Ray, and X-Ray Observations
[87](#technologies-in-support-of-gamma-ray-cosmic-ray-and-x-ray-observations)16.02
Technologies in Support of Gravity Wave, Radio, Sub-millimeter, Far-IR,
and IR Observations
[88](#technologies-in-support-of-gravity-wave-radio-sub-millimeter-far-ir-and-ir-observations)16.03
Heliospheric Plasmas and Fields Sensors
[88](#heliospheric-plasmas-and-fields-sensors)17 Space-Based Optical
Interferometers [89](#space-based-optical-interferometers)17.01
Metrology and Starlight Detection Systems
[90](#metrology-and-starlight-detection-systems)17.02 Active Optics
[90](#active-optics)17.03 Ultra-quiet Precision Systems
[91](#ultra-quiet-precision-systems)

# 14 Space-Based Large Telescopes {#space-based-large-telescopes .unnumbered}

Innovative products are sought that enable or enhance technologies
critical to achievement of large-aperture, high-performance optical
space telescopes at greatly reduced cost, weight, and packaging volume.
This topic benefits the development of the Next Generation Space
Telescope (NGST), a key element of NASA\'s Origins Program. The NGST is
a six to eight-meter aperture telescope that is to be launched in 2006 -
2007. The telescope will be designed to have near-diffraction limited
performance in the range of wavelengths between 500 and 5000 nanometers
and to operate at 30 K. The mass of the optical system is expected to be
less than 1000 kilograms.

## 14.01 Large Aperture Space Telescope Technologies  {#large-aperture-space-telescope-technologies .unnumbered}

Lead Center: MSFC

The NGST, the Hubble Space Telescope Replacement, will be made much more
powerful in resolution and light-gathering ability by greatly increasing
the aperture size. It also will be necessary to operate the telescope at
cryogenic temperatures and at a substantial distance from the Earth.
Therefore, low mass of critical components such as the primary mirror
and support and/or deployment structure is extremely important. It is
also essential to develop actuators, deformable mirrors and other
components for operation in a cryogenic environment. In order to meet
the stringent optical alignment and tolerances necessary for a high
quality telescope and to provide a robust design, there are potential
significant benefits possible from employing systems that can adaptively
correct for image degrading sources from inside and outside the
spacecraft. This subtopic also includes correction systems for large
aperture space telescopes that require control across the entire
wavefront, typically at low bandwidth. The following technologies are
sought:

-   New lightweight mirror concepts development.

-   New materials that reduce mass and improve performance.

-   High precision fabrication methods and equipment to produce the
    highest quality optical surfaces.

-   Metrology during fabrication to monitor, control, and verify results
    of the process.

-   Technologies for testing new mirror materials and shapes in relevant
    environments.

-   Segmented and membrane mirrors technology development.

-   New coatings and methods for applying them.

-   Lightweight structural concepts that enable packaging the large
    aperture into the relatively small launch vehicle payload envelope.

-   Deployable optical benches to achieve reference baseline dimensions
    greater than those of the payload envelope.

-   Innovative, precision, lightweight deployable mechanisms for
    segmented and thin membrane primary mirrors operating in a cryogenic
    environment.

-   High resolution (2 nm) long stroke (6mm) cryogenic actuators.

-   Powerful new analytical models, simulations, and evaluation
    techniques and new integrations of suites of existing software tools
    allowing a broader and more in-depth evaluation of design
    alternatives and identification of optimum system parameters.

-   Active and adaptive mirror systems that compensate for sources of
    distortion (structural deformations arising from misalignments,
    thermally driven dimensional changes and dynamics from overall
    vehicle motions, and moving mechanical systems on-board the
    spacecraft) to the image produced in the telescope.

-   Innovative methods of detecting and characterizing errors.

-   New control algorithms and methodologies for turning error
    information into corrective commands.

-   Precision actuation to accomplish corrective measures.

-   Embedded microelectronics to reduce the size and mass of an adaptive
    control system.

-   Image stabilization technologies enhancements.

-   Measures that reduce the effects of the dynamics from internal
    mechanisms.

-   Innovative solutions for momentum exchange systems.

-   Momentum management systems that are not life-limited by
    consumables.

-   Momentum management, pointing and attitude control, and on-orbit
    metrology systems that are integral with the adaptive and active
    correction system to achieve high optical performance, robust
    adaptability, reliability, and long life.

-   Develop methods to conduct on-orbit system identification through
    the acquisition of experimental data for the purpose of correlating
    computer simulations and diagnosing possible structural dynamic
    problems. Structural excitation techniques that do not employ
    consumables should be developed as well.

# 15 *In Situ* Exploration and Sample Return 

Solar system exploration is now embarked on a new phase, one that uses
highly capable robotic space systems to explore the atmosphere, surface
and subsurface of planets, satellites, and small bodies by means of *in
situ* measurements and sample return. Understanding the nature and
history of our solar system, the similarities and differences between
Earth and other planets, how life may have originated and persisted
beyond Earth, and the potential for human habitation within the solar
system are specific space science goals for which *in situ* exploration
is particularly relevant, if not critical. To accomplish the goals of
future missions, innovative science payload technologies are needed for
in situ measurements of the atmosphere, surface, and subsurface. Novel
devices and approaches are needed for deployment of instrumentation,
sample acquisition, transfer to sample collection sites or sample return
vehicles, and for positioning of in situ instruments. Innovations are
also required to achieve the cleanliness requirements for planetary
protection and integrity of samples used for in situ analysis and sample
return.

## 15.01 *In Situ* Science Payload Systems 

Lead Center: JPL

NASA's space science missions will increasingly rely on *in situ*
characterization of the atmosphere, surface and subsurface regions of
planets, satellites, and small bodies. Achieving the solar system
exploration goals will require innovative components and miniaturized
instruments for *in situ* analysis that offer significant improvements
over the state-of-the-art in terms of size, mass, cost, power,
performance, and robustness. These instruments may be deployed on
surface landers and rovers, subsurface penetrators, hydrobots, and
cryobots, and atmopheric sondes and probes. These instruments must be
capable of withstanding extended operation in space and planetary
environmental extremes, which include temperature, pressure, radiation,
and impact stresses. A reasonable target for a science instrument
concept is 1 kilogram mass, 1 liter volume, and 1 watt-hour of energy,
although for mission critical capabilities, additional resources might
be available. Innovations in enabling instrument component and support
technologies are also solicited. Topics include new sensors with
improved performance relative to the state-of-the-art, as well as
miniaturized valves, pumps, injectors, micro fluidics, and integrated
sample handling methodologies. A wide range of *in situ* instruments are
of interest---geological, mineralogical, chemical, biological, physical,
and environmental---with a near-term focus on Mars and Europa. This does
not preclude the submission of proposals in areas of longer term
interest which include comets, asteroids, Venus, and the outer planets.
Examples of technology challenges include, but are not limited to the
list provided below.

-   Measurement of evolved gases and volatiles from soils, rock, and
    ices

-   Near and far-field compositional analysis of soils, rocks, and ices

-   Mineralogy of rocks and soils

-   Geological stratigraphy

-   Geochronology

-   Chemical reactivity of soils, rocks, and ices

-   Analysis of particle size distribution and morphology of surface
    soil and dust

-   Measurement of toxic potential of Martian soil and dust with respect
    to human habitability

-   Compositional profiling of planetary atmospheres

-   Measurement of dissolved gases, ions, organics, dissolved solids,
    etc. in liquid water

-   Detection & measurement of organic molecules, including chiral
    analysis

-   Measurement of total inorganic carbon and total organic carbon

-   Measurement of isotope ratios for carbon, nitrogen, and oxygen in
    organic compounds

-   Measurement of seismic, electromagnetic, and magnetic properties

-   Measurement of meteorological phenomenon

-   Characterization of the radiation environment (protons, neutrons,
    energetic cosmic)

-   Particles (electrons and protons) and fields measurements for space
    plasma and solar studies

## 15.02 Instrument Deployment, Sample Acquisition and Retrieval Systems  {#instrument-deployment-sample-acquisition-and-retrieval-systems .unnumbered}

Lead Center: JPL

Future scientific exploration of planets and small bodies will require
improvements in the tools for *in situ* sample selection, collection,
protection, and retrieval, and for placement of instruments on or below
the surface. These tools will be required to operate in extreme
environments including high temperature, high pressure environments as
well as low temperature, near vacuum environments. Novel devices and
approaches are needed in the areas of manipulation and positioning of
instruments, penetration of surface materials that have a wide range of
properties, acquisition and storage of pre-determined amounts of
material, protection of samples from handling and environmental damage,
placement of samples into analysis systems, and the transfer of samples
to collection sites or delivery systems. Example technology concepts
include, but are not limited to, the following:

**Surface Operations**:

-   Mini-sample acquisition mechanisms with integrated feedback sensing

-   Low-power miniature rock crushing and transport system

-   Impact technologies for rock fragmentation

-   Impulse cancellation/reduction techniques for sampling devices

-   Mini-extendable stinger/plunger end-effectors

-   Instrument placement techniques

    **Sub-Surface Operations:**

-   Low reaction force coring and drilling devices operating within
    planetary and small-body gravity environments

-   Low power rock ablation for spectrometry of subsurface materials

-   Anchoring techniques for microgravity bodies

**Atmospheric Operations:**

-   Instrument deployment mechanisms from balloons and aerobots

-   Balloon materials for extreme environments

-   Passive entrapment devices for atmosphere/particulate collection

    **Operations in Wet Environments**:

-   Sample acquisition in wet environments including mini-pump and
    transport systems

-   Sample acquisition within sub-surface ice environments

-   Passive entrapment devices for liquid collection

    **Innovations for Planetary Protection and Sample Return:**

-   Sample confinement techniques for sterile insertion and maintenance
    of uncontaminated samples within a cache container.

-   Sample containment techniques (biologic, thermal, and mechanical)
    for planetary sample return. Techniques should be robust to Mars,
    space, and Earth re-entry environments.

-   Techniques for biological monitoring of samples throughout the
    sample return mission (Mars, Mars-Earth transit, and Earth
    re-entry).

# 16 Astrophysical and Space Physics Observations  {#astrophysical-and-space-physics-observations .unnumbered}

The technical requirements to support the Structure and Evolution of the
Universe (SEU) and the Sun-Earth Connection (SEC) science themes
missions are extremely diverse, which is a consequence of the
wide-ranging nature of the investigations. Technology developments are
sought in the system context from energy detection through data
reduction and scientific visualization needed to implement SEU missions.
Technology developements are also needed in the areas of plasma,
particle, fields and imaging sensors needed to support SEC missions.

## 16.01 Technologies in Support of Gamma Ray, Cosmic Ray, and X-Ray Observations  {#technologies-in-support-of-gamma-ray-cosmic-ray-and-x-ray-observations .unnumbered}

Lead Center: GSFC

The SEU program seeks innovative technologies to enhance the scope,
resolution, and efficiency of high energy detection systems. Proposals
are solicited for innovations ranging from readout electronics to optics
systems that provide order-of-magnitude performance enhancements.
Achieving the increased measurement resolutions typical of future SEU
missions, requires instruments with substantially larger aperture sizes
and focal lengths. Example supporting technologies to enhance x-ray,
gamma-ray, and cosmic-ray detection systems are listed below.

-   Advances are sought in high-density interconnects for connecting
    detector arrays. Low power (\< 200 mW per linear chain) ASIC
    electronics for read-out of the strip and pixilated arrays. High
    density capacitor/resistor arrays on a single substrate to interface
    strip and pixilated detectors to readout electronics.

-   Advances are sought in cascade shower detectors to detect three
    dimensional development of the electromagnetic cascade shower
    induced by a high energy gamma ray (\>0.1 eV).

-   Advances are sought in large arrays (\~120x120) of superconducting
    TES (transition edge sensor) X-ray microcalorimeters (2 eV FWHM at
    count rates up to a KHz in the 0.3-12 keV band). SQUID based
    read-out electronics with switching and sampling rates from 1-10
    MHz. Robust x-ray filter substrates for cryogenic instruments in the
    range 50 eV to 12 keV to act as input filters for these arrays.
    Closely packed 2-dimensional calorimeter array structures employing
    unique methods of thermal isolation and batch processed fabrication
    techniques.

-   Advances are sought in cryogenic x-ray detection sub-systems
    technologies including microcalorimeter arrays and tunnel junction
    arrays integrated with cryocoolers and electronics.

-   Advances are sought in large, lightweight optics subsystems
    technologies including replicated thin shells, conical foil mirrors,
    spherical optics, and variable line density diffraction gratings,
    capillary optics, innovative imaging techniques, and multi-layer
    coatings.

-   Advances are sought in lightweight, extendible optical benches,
    particularly in precision deployment mechanism design, passive
    thermal control, and disturbance isolation.

-   For extendible reflectors, advances are sought in low-mass reflector
    panels, active alignment control, and nonlinear microdynamics
    modeling.

## 16.02 Technologies in Support of Gravity Wave, Radio, Sub-millimeter, Far-IR, and IR Observations  {#technologies-in-support-of-gravity-wave-radio-sub-millimeter-far-ir-and-ir-observations .unnumbered}

Lead Center: JPL

Technologies of interest in this subtopic tend to be specialized or
optimized to meet the specific needs of the SEU theme. Technologies for
gravity wave, radio, submillimeter, far-infrared, and infrared
wavelengths include the following:

-   Ultra-low-noise accelerometers used to enable the detection of fine
    distortions in space-time due to the arrival of a gravitational
    wave. These have a sensitivity requirement of \<1e-15 g/sqrt(Hz).

-   Micro-Newton thrusters required to cancel out the solar radiation
    force on the spacecraft, correct for fluctuations in that force, and
    control spacecraft attitude.

-   Separated spacecraft interferometers to determine changes in the
    distance between test masses in different spacecraft separated by \~
    107 km.

-   Active and passive cooling technology, for submillimeter emissions,
    to cool the reflector/antenna/detector areas to temperatures in the
    40K - 150K range. Development is needed in lightweight sunshades and
    advanced high efficiency radiators.

-   Cryogenic detectors and electronics, including HT superconducting
    detectors(bolometers,etc) low-noise amplifiers, digitizers,
    multi-plexers, low jitter and phase noise oscillators up to 5 THz,
    and LO amplifiers.

-   Phase-controlled, low absorption, reflective coatings for infrared
    cryogenic Fabry-Perot applications.

-   Tunable optical filters for use in cryogenic systems.

-   Low-mass, thermally stable precision reflectors and telescope
    technology(CFR and SiC materials).

-   Low-current, superconducting magnets for operation at and below 10
    degrees K, and associated flux pumps.

## 16.03 Heliospheric Plasmas and Fields Sensors  {#heliospheric-plasmas-and-fields-sensors .unnumbered}

Lead Center: GSFC

Over 99% of the matter in the universe is in the plasma state. The
extended corona of the sun, or solar wind, along with the ionospheres
and magnetospheres (where present) of the planets, are the most
immediate examples. Partial ionization is the rule and in general, fast
charged particles coexist with neutral gas exospheres of varying
relative density. Research designed to improve our knowledge and
understanding of \"space weather\" requires accurate measurements of the
composition, flow, and thermodynamic state of space plasmas. Low energy
charged particle analyzers and DC to RF electromagnetic field sensors
provide the foundation of this capability based on direct in situ
measurement. Complementing direct measurements, fast neutral atom
imagers, UV and X-ray photon imagers, and radar imaging all provide
wide-ranging remote sensing of energetic phenomena occurring within
space plasmas. Plasma and fields instrumentation is often severely
constrained by spacecraft resources. Therefore, miniaturization and
autonomy are common technological development themes across this entire
category of sensors. Specific technologies are sought in the following
categories:

**Particle Sensors and Imagers**

The Sun-Earth connection program seeks novel sensors that enhance the
scope, resolution, and resource-efficiency of plasma particle
measurements in the energy range from a fraction of an electron volt up
to a few hundred keV. Examples of the types of technical innovations
that would be of interest include:

-   Improved techniques for imaging of the charged particle velocity
    distribution such that a complete distribution can be measured in a
    time comparable to or shorter than the ion cyclotron period.

-   Direct charged particle velocity measurements using measurement of
    the particle time-of-flight.

-   Spectrographic (mass and energy or velocity) imaging of fast neutral
    atoms with improved sensitivity and angular resolution.

-   Techniques for the high-efficiency conversion of low energy neutral
    atoms (less than 1 keV) to ions.

-   Improved techniques for the regulation of spacecraft floating
    potential near the local plasma potential, at low local plasma
    density, or in the presence of very high temperature electron
    plasmas (keV and higher).

-   Miniaturized and autonomous systems for the above.

    **Field Sensors**

-   Improved techniques for measurement of the DC electric field (and by
    extension the plasma drift velocity), especially in the direction
    parallel to the spin axis of a spinning spacecraft.

-   Measurement of the floating potential (relative to local plasma
    potential) of a spacecraft over the range -50V\< Vs/c \< 50 V, in
    any conditions of sunlight or plasma.

-   Measurement of the gradient of the electric field in space around a
    single spacecraft or cluster of spacecraft.

-   Improved techniques (or recovery of old metalurgical techniques) for
    low noise, high resolution measurement of the DC magnetic field in
    interplanetary space.

-   Improved techniques for the measurement of the gradients (curl) of
    the magnetic field in space local to a single spacecraft or group of
    spacecraft.

-   Direct measurement of the local electrical current density at levels
    typical of space plasma structures such as shocks, magnetopauses,
    and auroral arcs.

-   Miniaturized and autonomous systems for the above.

    **Electromagnetic Imaging Systems**

-   Improved techniques for spectrometric imaging of UV emissions
    emanating from regions of energetic plasma phenomena interacting
    with atmospheric gases, such as the aurora and dayglow.

-   Adaptations of UV imaging to diverse spacecraft orbits and vantage
    points (field-of-view and resolution).

-   Adaptations of X-ray imaging to diverse spacecraft orbits and
    vantage points (field-of-view and resolution).

-   Spectrometric imaging of X-ray emissions from regions of energetic
    particle interactions with atmospheric gases.

-   Radar sounding and echo imaging of plasma structures from
    spacecraft.

-   Miniaturized and autonomous systems for the above.

    **Support Electronics**

    Miniaturized and autonomous plasma, fields, and photon imaging
    systems will require the development of novel, miniaturized, low
    power support electronics to process and analyze the detector
    signals for delivery to spacecraft systems. Generic functions will
    make development of custom chips cost-effective in some cases.
    Examples include:

-   Low power digital time-of-flight analyzer chips with sub-nanosecond
    resolution and multiple channels of parallel processing.

-   Low power radiation-tolerant microprocessors and associated
    autonomous operating systems.

# 17 Space-Based Optical Interferometers  {#space-based-optical-interferometers .unnumbered}

Optical interferometry figures prominently in NASA\'s plans for 21st
century space science. As part of the Origins Program three major
interferometry scientific missions are planned: the Space Interferometry
Mission (SIM), the Terrestrial Planet Finder (TPF), and the Keck
Interferometer (ground-based). This topic is looking for high-risk,
high-payoff, innovative concepts that will help to achieve the
interferometry goals, including reduction of cost and schedule. The
grand technical challenges of optical interferometry include: 200
picometer positional measurement over distances up to 100 meters;
mechanical stabilization to order of 1 nanometer; and system level
modeling, integration, and test of interferometer instruments. Relevant
technologies include: laser metrology, active optics, thermally stable
optics, precision deployable structures, vibration
isolation/suppression, realtime control algorithms and software, and
integrated modeling software.

## 17.01 Metrology and Starlight Detection Systems  {#metrology-and-starlight-detection-systems .unnumbered}

Lead Center: JPL

The next generation of astrophysics missions will require highly precise
control of active optics on flexible structures. Laser metrology gauges
provide the sensing for these control loops. These missions have needs
in metrology subsystems architectures, components and data processing.
Detection of stellar interferometric fringes in beam combiners is
critical to measurements of astrophysical objects. A nulling beam
combiner at low temperatures is needed for detecting and characterizing
extra-solar planets. Innovations are needed in instrument design and
fabrication, optical components, and detectors. Performance extension
into the 5 to 10 micron regime is desired. Proposals for concepts in the
following areas are solicited:

**Metrology**

-   Linear metrology gauges relative accuracy of less than 100
    picometers

-   Ultra-stable lasers for metrology gauges

-   Frequency shifters for metrology gauges.

-   Integrated lightweight beam launchers.

-   Full-aperture metrology gauges.

-   Embedded grating technology

-   Optical surface measurements at l/1000 to l/10000 wavelength
    accuracy.

-   Fiber-optic systems and components with low polarization cross-talk
    for routing metrology laser signals.

-   Star simulator for testing a variable (up to 10 meter) baseline
    interferometer

    **Interferometeric Detection**

-   Interferometeric beam combiners at visible and infrared wavelengths.

-   Low-background, low noise infrared detectors (5 to 10 micron
    regime).

-   High frame rate/ultra-low read noise CCD and infrared detector
    arrays.

-   Ultra-high contrast (109) beam combining techniques to suppress
    starlight and image extra-solar planets.

-   Low-temperature beam combiners and detectors.

-   Wide-band, low reflection coatings.

-   Single-mode, infrared fiber waveguides in the 2-10 micrometer
    regime.

-   Wavefront sensors, l/1000 wavelength accuracy.

## 17.02 Active Optics  {#active-optics .unnumbered}

Lead Center: JPL

Methodologies, hardware components, and systems to actively control
optics either on a spaceborne interferometer or a ground-based
interferometer will be required. These systems will concentrate on high
bandwidth pathlength control and tip/tilt control required by
interferometers. Wavefront control for large aperture interferometers
such as the Keck is also of interest. Proposals from the following areas
will be considered:

-   Multiprocessor computer systems for interferometers.

-   Control architecture, design and algorithms for interferometers.

-   Thermally stable large field of regard, high accuracy gimbals ( +,-
    7.5 o, 17 mas 1 s).

-   Thermally stable high-bandwidth, momentum-compensated steering
    mirrors.

-   Six DOF pointing and displacement mechanisms, with high pointing
    stability and low power

-   High-precision optical encoders.

-   Long-throw, high-precision optical delay lines.

-   Automated alignment sensors and systems.

-   Thermally stable articulating mirrors for automated optical
    alignments.

-   Thermally stable micromechanical actuators

-   Ultra-precise sensors such as nano-g accelerometers and fine
    guidance sensors

-   Infrared wavefront sensors (2 to 10 micron regime)

-   Actuators for controlling position and figure of segmented optics.

-   Adaptive optics systems and components.

-   Deformable mirrors for ground-based telescopes.

-   Deformable mirrors with extremely high actuator density.

-   Systems to control interferometer Spacecraft constellations,
    including formation flying acquisition/maintainance sensors,
    actuators and algorithms

-   Multifunctional approaches.

## 17.03 Ultra-quiet Precision Systems  {#ultra-quiet-precision-systems .unnumbered}

Lead Center: JPL

Concepts, components, subsystems, algorithms, and software necessary to
attenuate vibrational motions of the system and key components when
subjected to excitation over a broad frequency range, including low
frequencies that may be excited by thermal or other sources will be
required. Significant goals are reduction of cost, mass, volume, power,
and adverse side-effects such as heat generation; or an increase in
performance, robustness and redundancy. Novel methodologies including
non-deterministic approaches, algorithms, test data, software in support
of high-fidelity, and integrated modeling of complex opto-mechanical
systems will be required to meet these objectives. This covers the areas
of structural finite element models, acoustic models, thermal models,
modeling of vibration isolation and suppression sub-systems, modeling of
actively controlled optical systems, and any test data essential to
validating the models. The magnitude of the vibrational motions of
interest is in the 1-10 nanometer range. A new class of deployable
structural concepts and approaches capable of achieving precise
post-launch deployment; maintaining structural linearity and
repeatability in the deployed condition; and retaining the desired
features of reliability, reduced weight and stowed launch volume will be
required. The linear baseline of the deployed structures ranges from
10-100 meters. Novel concepts in a deployment system, materials,
coatings, actuators, sensors, controllers, power, mechanisms, and others
contributing to the final goals are solicited. Areas of interest
include:

**Vibration Attenuation**

-   Isolation of noisy subsystems from the structure.

-   Attenuating the motion of the structural vibration modes and
    traveling waves.

-   Isolation of the quiet subsystem from the structure.

-   Novel sensors and actuators to achieve the desired performance.

-   Multifunctional sensors, actuators, electronics, controllers, and
    power for actuators and other applicable components or subsystems.

-   Passive, semi-active or active approaches for vibration attenuation.

-   Use of smart materials and adaptive structures concepts.

-   Adaptive control-structure capabilities adjustable during the
    mission operation. Integrated Modeling

-   Innovative approach for structural modeling capable of
    characterizing broadband dynamic response.

-   New concepts to reconcile integrated structural models to measured
    data.

-   New techniques to accurately predict synthesized model response from
    component level tests..

-   Structural modeling techniques for thermally induced vibrations in
    joint-dominated structures.

-   Modeling of slosh phenomenon at cryogenic temperatures.

-   Integrated design optimization techniques and algorithms for
    precision optical systems.

-   Analytical characterization of nanometer-level static, thermal and
    dynamic induced structural distortions for optical elements,
    opto-mechanical components and precision deployment mechanisms.

-   Novel test concepts and approaches to verify accuracy of high
    fidelity integrated model predictions.

    **Precision Deployables**

-   Test approaches and concepts that can be validated by ground tests.

-   A deployed system that is linear and repeatable within 1 nanometer
    at structural motions of around 10 nanometers in the space
    environment including thermal, space effects, etc.

-   A deployment system capable of surviving the ground test and launch
    environments.

-   A thermally active or passive system to retain the structural
    dimensions to within 10 millimeters.

-   Precision 10-50 meter long metrology boom deployed to within less
    than 1 millimeter accuracy at the tip.

-   Semi-passive or active approaches to correct for quasi-static
    deformations to within 1 micrometer.

-   Novel use of smart materials and adaptive structures technologies.

##   {#section-12 .unnumbered}

## 8.5 CROSSCUTTING TECHNOLOGIES

In addition, underlying the activities of NASA programs are critical
crosscutting technologies that may support multiple Strategic
Enterprises. Within this Solicitation, this synergistic crosscutting
activity primarily supports the science-based Enterprises of Space
Science and Earth Science.

18 Power, Propulsion, and Thermal Technology
[94](#power-propulsion-and-thermal-technology)18.01 Thermal Control
[94](#thermal-control)18.02 Energy Conversion and Storage and Electric
Power [95](#energy-conversion-and-storage-and-electric-power)18.03 Power
Management and Distribution
[96](#power-management-and-distribution)18.04 In-Space Propulsion
[97](#in-space-propulsion)19 Materials, Structures, and Environmental
Effects [97](#materials-structures-and-environmental-effects)19.01
Materials, Material Processing, and Coatings for Launch Vehicle and
Spacecraft Components
[98](#materials-material-processing-and-coatings-for-launch-vehicle-and-spacecraft-components)19.02
Thermal Protection Materials and Systems for Hypersonic Vehicles and
Spacecraft
[99](#thermal-protection-materials-and-systems-for-hypersonic-vehicles-and-spacecraft)19.03
Materials for Propulsion and Power
[99](#materials-for-propulsion-and-power)19.04 Structures for Propulsion
and Power [100](#structures-for-propulsion-and-power)19.05 Space
Environmental Effects and Contamination
[101](#space-environmental-effects-and-contamination)19.06 Smart
Materials and Embedded Components for High Performance Aerospace Systems
[102](#smart-materials-and-embedded-components-for-high-performance-aerospace-systems)19.07
Low Density/Reduced Mass Materials for Aerospace Systems
[103](#low-densityreduced-mass-materials-for-aerospace-systems)19.08
Non-Destructive Evaluation of Materials and Structures
[103](#non-destructive-evaluation-of-materials-and-structures)19.09
Bonding and Joining Technologies
[104](#bonding-and-joining-technologies)19.10 Inflatable Structures and
Systems [104](#inflatable-structures-and-systems)19.11 Balloon Vehicles
& Aerobots [105](#balloon-vehicles-aerobots)20 Design Tools, Systems
Analysis, and Simulation
[105](#design-tools-systems-analysis-and-simulation)20.01 Advanced
Concepts of Virtual Spacecraft Design and Visualization
[106](#advanced-concepts-of-virtual-spacecraft-design-and-visualization)20.02
Advanced Design, Analysis and Simulation Tools
[106](#advanced-design-analysis-and-simulation-tools)21 Avionics, Data
Systems, and Data Storage
[107](#avionics-data-systems-and-data-storage)21.01 Microelectronics for
Space Systems [107](#microelectronics-for-space-systems)21.02
Highly-Integrated Multifunctional and Adaptive Structures for Aerospace
Systems
[108](#highly-integrated-multifunctional-and-adaptive-structures-for-aerospace-systems)21.03
Autonomous Guidance, Navigation, and Control for Aerospace Systems
[108](#autonomous-guidance-navigation-and-control-for-aerospace-systems)21.04
Data management and Electronics for Aerospace Subsystems
[109](#data-management-and-electronics-for-aerospace-subsystems)22
Instruments and Sensing [110](#instruments-and-sensing)22.01
Spectroscopic and Multi-spectral Imaging Sensors in the UV to Far IR
[110](#spectroscopic-and-multi-spectral-imaging-sensors-in-the-uv-to-far-ir)22.02
High Energy Sensing [111](#high-energy-sensing)22.03 Microwave,
Millimeter and Submillimeter Sensing Technology
[112](#microwave-millimeter-and-submillimeter-sensing-technology)22.04
Cryogenic Support Systems [113](#cryogenic-support-systems)22.05 MEMS
and Meso Scale Processes and Devices for Instrument Systems
[113](#mems-and-meso-scale-processes-and-devices-for-instrument-systems)22.06
Instruments for Exobiology [114](#instruments-for-exobiology)23
Spacecraft Miniaturization Technologies
[115](#spacecraft-miniaturization-technologies)23.01 Near Earth
Nano-Satellite Technology
[115](#near-earth-nano-satellite-technology)23.02 Deep Space
Microspacecraft Subsystems
[116](#deep-space-microspacecraft-subsystems)24 Intelligent Systems
[116](#intelligent-systems)24.01 Automated Reasoning for Autonomous
Systems [117](#automated-reasoning-for-autonomous-systems)24.02 Human
Centered Computing [118](#human-centered-computing)24.03 Data Analysis
and Visualization [119](#data-analysis-and-visualization)24.04 Data
Understanding and Adaptive Methods
[120](#data-understanding-and-adaptive-methods)25 Telerobotics
[121](#telerobotics)25.01 Robotic Systems Including Perception,
Planning, and Analysis
[121](#robotic-systems-including-perception-planning-and-analysis)25.02
Telerobotic Servicing [122](#telerobotic-servicing)25.03
Tele-Operations/Virtual Environment
[122](#tele-operationsvirtual-environment)26 Communications
[123](#communications)26.01 RF and Optical Communications for Deep Space
Missions
[123](#rf-and-optical-communications-for-deep-space-missions)26.02 RF
and Optical Communications for Earth Satellites
[124](#rf-and-optical-communications-for-earth-satellites)27 Instrument
Optics Technologies [125](#instrument-optics-technologies)27.01 Optical
Materials, Fabrication Techniques and Metrology
[125](#optical-materials-fabrication-techniques-and-metrology)27.02
Light Control, Lasers and, Other Precision Sources
[126](#light-control-lasers-and-other-precision-sources)27.03
Diffractive Optics: Design and Fabrication Techniques
[127](#diffractive-optics-design-and-fabrication-techniques)27.04 Optics
Technologies for Space and Earth Observing Systems
[127](#optics-technologies-for-space-and-earth-observing-systems)28
Interdisciplinary Technologies in Astrobiology
[128](#interdisciplinary-technologies-in-astrobiology)28.01 Technologies
for Understanding the Origin and Distribution of Life in the Universe
[128](#technologies-for-understanding-the-origin-evolution-and-distribution-of-life-in-the-universe)28.02
Technologies for Understanding the Evolution of Biological Systems in
Space
[128](#technologies-for-understanding-the-evolution-of-biological-systems-in-space)28.03
Technologies for Understanding the Evolution of the Earth\'s Atmosphere
and Ecosystem
[129](#technologies-for-understanding-the-evolution-of-the-earths-atmosphere-and-ecosystem)

# 18 Power, Propulsion, and Thermal Technology  {#power-propulsion-and-thermal-technology .unnumbered}

A large portion of the size and weight of a spacecraft is required to
deliver reliable electrical power, thermal control, and on-orbit
propulsion. Future NASA missions depend upon the continued advancement
of these critical technologies. NASA seeks innovative concepts and
advanced technologies needed for static and dynamic energy conversion,
storage, management, and distribution systems for high performance
spacecraft and for advanced transportation systems. Advanced thermal
control technologies and on-orbit propulsion and chemical propulsion
systems for future space missions are areas in which NASA also seeks
innovative proposals.

## 18.01 Thermal Control  {#thermal-control .unnumbered}

Lead Center: GSFC

Future spacecraft, space facilities (manned and unmanned) and
instruments will require increasingly sophisticated thermal control
technology and may operate in increasingly severe thermal environments.
Heat load centers will be more numerous and more widely dispersed, flux
levels will increase, and very tight temperature control will be
required. Some applications may require significantly increased power
levels. Others may require extremely low heat loss for extended periods.
Low cost, low weight, and high reliability are prime technology drivers.
Specific areas for which innovative proposals are sought include:

**Unmanned spacecraft:**

-   Advanced thermal control of chip level electronics.

-   Cryogenic heat pipes and CPLs (8 K to 60 K) with diode and flexible
    capabilities. Advanced wicks (2 micron or less) are also of
    interest.

-   Low mass, high performance modular heat pumps for both manned and
    unmanned (spacecraft and balloon) applications.

-   Advanced thermal control coatings such as variable absorptive and
    emissive property coatings/devices and white, sprayable, conductive
    thermal control coatings with low outgassing characteristics are of
    interest.

-   Methods for enhancing thermal control through electrohydrodynamics,
    advanced materials with high conductivity and low CTE, advanced
    radiators, improved contact conductance (predictable, repeatable,
    high thermal conductivity), and long-life high temperature
    insulation (above 2300 K).

-   Instrumentation and automated software that will enhance system
    thermal control and monitoring; for locating component failures and
    for performing isolation and recovery operations.

    **Life and biomedical space experiments:** These require
    refrigerator/freezer (R/F) equipment to provide storage for
    experiment supplies and specimens. Current storage systems operate
    at +4 C and -20 C. Their power consumption, mass, and crew
    maintenance time are areas needing improvement. Future missions will
    be longer duration (i.e., greater than 90 days compared to 14 days
    for Shuttle missions). They will require a wider range of storage
    temperatures and R/F equipment types. Areas in which innovations are
    solicited include the following:

-   Energy efficient, reliable, low-maintenance refrigeration and
    freezing system concepts for thermal storage at low-temperatures (+4
    C, -20 C, & -70 C) and cryogenic (-183 C) storage for laboratory
    supplies and specimens, -70 C freeze-drying, and -196 C quick-snap
    freezing.

-   Concepts for lightweight, low-heat leak, freezer storage cabinets
    that maximize the specimen storage capacity for the amount of rack
    space.

-   Concepts for logistically efficient transfer/transport of frozen
    specimens on and between spacecraft, and for processing on Earth
    while maintaining specimen storage temperatures.

    **Human space missions:** Future human space missions will operate
    at higher power levels and in more severe thermal environments than
    in the past. There is a need for advanced thermal hardware to
    provide highly efficient, lightweight, reliable internal and
    external active thermal control systems (ATCS) for piloted
    spacecraft and planetary bases. Areas in which innovations are
    solicited include the following:

-   Fault tolerant fluid to fluid heat exchangers; a non toxic, single
    and two phase working fluid that freezes below 75 K or does not
    change density upon freezing; room temperature phase change devices;
    and a controllable, reliable water evaporator for use in a vacuum.
    Lightweight, two-phase systems with self-diagnostic, repair and
    correction capability are also of interest.

-   Interactive computational techniques for analysis and control of
    thermal fluid systems. Spacecraft system design codes that integrate
    thermal, mechanical and power systems to minimize total mass.

-   Lightweight, high-efficiency heat pumps (275 to 370 K).

-   Flexible, lightweight, micrometeoroid tolerant, highly reliable
    radiators that can be stowed for transport and deployed for use on
    spacecraft or planetary surfaces.

## 18.02 Energy Conversion and Storage and Electric Power  {#energy-conversion-and-storage-and-electric-power .unnumbered}

Lead Center: LeRC

Innovative concepts for systems and components are solicited in the
areas of both static and dynamic energy conversion systems. Power levels
of interest range from tens of milliwatts to many kilowatts. This area
includes photovoltaics, AMTEC, thermophotovoltaics, thermoelectrics,
thermionics and thermodynamic conversion systems. Additionally, NASA
programs require energy storage systems having high energy-density and
cycle life. This includes rechargeable batteries, fuel cells and
competing alternatives with high-power-density such as lightweight
flywheels and ultra-capacitors. Specific areas of interest are:

-   Photovoltaic technology with targeted cell efficiencies over 30 %
    and array performance up to 1000 watts per kilogram and 400 watts
    per square meter. Potential concepts include rigid arrays, thin film
    arrays, and various concentrator configurations. High radiation
    resistance also is a requirement for some missions, as is operation
    in low temperature, low intensity or high temperature, high
    intensity conditions

-   Advanced solar thermal power conversion technologies for earth
    orbiting spacecraft and/or orbit transfer vehicles. Concentrators
    may be rigid or inflatable, primary or secondary and address issues
    such as manufacturing, coatings, efficiency, packaging/deployment,
    and pointing/tracking. Receivers may utilize heat pipe or direct
    absorption technologies intended to minimize mass and volume. Topics
    of interest in power conversion include the investigation of compact
    heat exchangers, advanced materials, and control methods, as they
    relate to life, reliability and manufacturability. Heat rejection
    areas of interest include composite materials, heat pipes, pumped
    loop systems, and packaging and deployment. Also of interest are
    highly integrated systems which combine elements of the above
    subsystems and show system level benefits.

-   Thermal-to-electric conversion concepts are sought that would
    utilize Radioisotope Heater Units (RHUs) or General Purpose Heat
    Source (GPHS)modules as heat sources and have electrical outputs
    from tens of milliwatts to 100\'s of watts and efficiencies greater
    than 20 %. Systems of interest include AMTEC, thermophotovoltaics,
    thermoelectrics and Stirling. Small light weight heat reaction
    systems are also needed. Concurrent with NASA\'s trend toward
    micro-satellites, NASA also has an interest in power systems based
    on micromachining fabrication techniques.

-   Nickel-hydrogen and nickel metal hydride battery technology with
    goals of at least 100 watt-hour per kilogram and 10-year life in LEO
    and GEO for spacecraft and space systems. Also, lithium and
    lithium-polymer batteries for planetary spacecraft and probes with
    goal of 200 watt-hour per kilogram for low and/or wide temperature
    operations.

-   Proton exchange membrane and solid oxide fuel cell and fuel
    cell-electrolyzer systems.

-   Portable, rechargeable energy storage concepts with increased energy
    density over Ni-Cd and Ni-H2, but which require only hundreds, not
    thousands of cycles. Proposed concepts for EVA and in-cabin energy
    storage can include a variety of approaches such as secondary
    batteries, fuel cells, ultra or super capacitors or flywheels;
    however, the primary criteria are high energy density (both weight
    and volume)portability, and safety.For unique applications requiring
    few \"cycles\" very high energy density primary battery systems are
    of interest where sufficient energy storage can trade against
    rechargeability.

-   Demonstration as a pilot project of a flywheel energy storage unit
    for use as an uninterruptable power source (UPS). The flywheel
    system will be run in parallel with an existing UPS for 60 Hz backup
    power.

-   Future planetary missions require high specific energy and high
    energy density primary and rechargeable batteries capable of
    operating at low temperatures. Planetary probes require primary
    batteries capable of providing 500 Wh/kg specific energy and 1000
    Wh/l at ambient temperature. Further, these batteries must be
    capable of delivering 30-50% of their ambient specific energy at
    temperatures as low as -100 C. Lithium primary with advanced cathode
    materials and electrolytes and other advanced electrochemical
    systems having these capabilities are of interest. In the
    rechargeable lithium battery area, the primary technology drivers
    are specific energy (150 Wh/kg), energy density (300 Wh/l), cycle
    life (1000 deep discharge cycles) and low temperature operating
    capability (-60 C to ambient). Rechargeable lithium ion batteries
    with advanced anode and cathode materials and liquid/polymer
    electrolytes and other advanced battery systems capable of meeting
    the above performance criteria are of interest.

## 18.03 Power Management and Distribution {#power-management-and-distribution .unnumbered}

Lead Center: LeRC

Innovative concepts utilizing advanced technology are needed to manage
and distribute power in lighter, smaller, cheaper, more durable, and
high performance spacecraft and to improve reliability and reduce
overall costs (including operations) for advanced transportation
systems. New concepts in power control and distribution, power
applications which greatly impact specific systems, and technological
advances that substantially improve a broad range of space power and
aircraft systems are of interest. Advances for power management and
distribution (PMAD) systems are sought in the following areas:

-   Materials, surfaces, and components that are durable for atomic
    oxygen, soft x-ray, electron, proton, and ultraviolet radiation and
    thermal cycling environments, lightweight electromagnetic
    interference shielding, and high-performance, environmentally
    durable radiators.

-   Low Earth orbital atomic oxygen simulation and protective coating
    technologies.

-   Advanced electronic materials, devices and circuits, including, but
    not limited to, transformers, transistors, integrated circuits,
    capacitors, electro-optical devices, micro electro-mechanical
    systems(MEMS), sensors, low-profile low loss magnetic cores, and
    packaging with improved characteristics capable of high-temperature,
    low-temperature (cryogenic), or wide-temperature operation or
    radiation resistance for use in PMAD systems, motor drives,
    electrical actuation, or electro-mechanical systems. Electronic
    devices and circuits to deliver high-efficiency power at less than 3
    volts (logic levels).

-   Management, control and monitoring of power systems, adjustable
    speed drives, or autonomous operation of space power systems.

-   Advanced packaging technologies which enable integral thermal
    control of space power electronics while reducing package volume and
    mass or which combine electromagnetic interference shielding and
    thermal control.

-   Fault detection, isolation, and system reconfiguration, including
    \"smart components\", built-in test, and vehicle health management
    concepts.

-   Advanced PMAD electronics for small low-cost spacecraft to simplify
    interfaces, streamline integration and testing, as well as to reduce
    size and mass through the use of new technologies and topologies.

-   Advanced power conditioning devices for space and Earth science
    payloads to reduce size and mass through the use of hybrid,
    multi-chip and other improvements in discrete electronics for
    housekeeping and control of a wide range of regulated voltages.

-   Modular, integrated spacecraft PMAD building blocks which
    drastically reduce system size, mass, and recurring cost through the
    use of the highest levels of integration based on monolithic,
    application-specific integrated circuits, mixed mode
    application-specific integrated circuits, field programmable gate
    arrays, advanced power packaging techniques, and flexible reusable
    architectures.

## 18.04 In-Space Propulsion  {#in-space-propulsion .unnumbered}

Lead Center: LeRC

Propulsion system mass is a major issue for a wide range of spacecraft
(e.g., communications and remote sensing satellites, reusable vehicles,
and interplanetary spacecraft). Innovations are sought to enhance
propulsion and fluid system capabilities for functions including orbit
insertion, orbit maintenance, precision positioning, de-orbit, reaction
control, and planetary primary propulsion. Both chemical and electrical
systems are of interest and technologies at the component, sub-system,
and system level will be considered. Key aims of this subtopic are
technology advancements which will lead to 1) significant
miniaturization, 2) reduced system, operations, and/or overall costs, 3)
prolonged mission or systems lifetimes, 4) improved reliability, and/or
5) enabling mission functions.

Areas of interest include:

-   Electric and chemical propulsion technologies for satellites and
    spacecraft less than 50 kilograms, including the micro
    electro-mechanical system (MEMS) class. These propulsion concepts
    should emphasize system simplicity, low power requirements, and
    minimal mass.

-   Propellant management components for miniature electric and chemical
    propulsion systems, including very low-leak rate valves, regulators,
    flow control devices, multifunctional components, and ignition
    sources.

-   Electric propulsion technologies for Earth-space and planetary
    transportation applications, including thrusters, advanced power
    processing, and propellant system technologies.

-   High performance monopropellants for small spacecraft applications.
    Included in this area are ignition techniques for these propellants
    that will meet the severe duty cycle requirements of on-orbit
    propulsion functions.

-   Radiation-cooled rocket chamber materials for long-life ( 6 hours)
    operation in high-temperature, aggressively oxidizing combustion
    environments. In particular, innovative fabrication technologies for
    ceramic matrix composites that will produce dense, lightweight
    structures.

-   Systems to provide high precision attitude control for small
    spacecraft. Components should reduce total propulsion system mass
    and volume by a factor of two or better, while maintaining or
    improving reliability and performance of existing chemical
    components and systems. Components include propellant storage and
    expulsion devices, propellant feed systems, valves, absolute
    isolation devices, flow management and regulation devices, and
    thermal control hardware for chemical systems. For electric systems,
    technologies of interest include energy storage and delivery,
    propellants and feed, initiation and long life, and control.

# 19 Materials, Structures, and Environmental Effects  {#materials-structures-and-environmental-effects .unnumbered}

NASA seeks innovative materials and structures technologies for
improving performance and affordability of future aerospace systems.
Advancements are sought that reduce mass, volume, processing/fabrication
cost, and design analysis cost and inaccuracies for a broad range of end
applications to spacecraft, launch and space transfer vehicles,
aircraft, and their power and/or propulsion systems. Improvements which
increase component functional utility, enable in-situ non-destructive
monitoring and test, and provide active adjustment and adaptation are
also sought . Technologies are needed which extend the reliability and
life of systems operating in environments which may include combinations
of extreme and cycling temperatures, extreme mechanical stresses,
chemical interactions, and space environments including vacuum and
ultra-violet, electromagnetic fields, solar particles and galactic
radiation, atomic oxygen, micrometeoroids, and planetary surface
atmospheres and dust.

## 19.01 Materials, Material Processing, and Coatings for Launch Vehicle and Spacecraft Components  {#materials-material-processing-and-coatings-for-launch-vehicle-and-spacecraft-components .unnumbered}

Lead Center: MSFC

NASA seeks innovative materials and structures technologies for
improving performance and affordability of future aerospace systems.
Advancements are sought that reduce mass, volume, processing/fabrication
cost, and design analysis cost and inaccuracies for a broad range of end
applications to spacecraft, launch and space transfer vehicles,
aircraft, and their power and/or propulsion systems. Improvements that
increase component functional utility, enable *in situ* non-destructive
monitoring and test, and provide active adjustment and adaptation are
also sought. Technologies are needed which extend the reliability and
life of systems operating in environments which may include combinations
of extreme and cycling temperatures, extreme mechanical stresses,
chemical interactions, and space environments including vacuum and
ultra-violet, electromagnetic fields, solar particles and galactic
radiation, atomic oxygen, micrometeoroids, and planetary surface
atmospheres and dust.

Enhancements in the following areas are of interest:

-   Innovative fabrication technology that combines advanced materials
    and processing techniques; non-autoclave curing and alternate curing
    techniques, e.g., x-ray or electron beam, UV.

-   Rapid, multidimensional preformed fabrication for continuous
    fiber-reinforced composites with simple or complex geometry and/or
    large dimensions.

-   Manufacturing processes for LOX-compatible and reusable composite
    lines, ducts, and cryotanks.

-   Production of lightweight tooling and mandrels for composite
    structures.

-   Processing techniques for non-uniform composite structures.

-   Damage-resistant composite structures (residual strength property
    measurement and prediction after impact).

-   Advanced materials and processes for both oxygen-rich and
    high-temperature applications.

-   Advanced ceramics/composites for propulsion system components
    including turbopump components, lines/ducts, cooled and uncooled
    nozzle applications, and valve components.

-   Improved structural integrity materials for use in end-item
    component processing with rapid-prototyping technologies.

-   Process control instrumentation for characterization and
    verification of material properties, including thermal, optical,
    electrical, mechanical and moisture absorption and composition
    utilizing new and innovative state-of-the-art technologies.

-   Coatings technologies vital in developing advanced high-temperature
    superalloy-, intermetallic-, and ceramic-matrix composites with
    enhanced structural, environmental, and use-temperature capability.

-   On-orbit repair for coating, bonding, seals, and structures.

-   Adhesive bonding materials with high-performance capabilities in
    extreme environments such as cryogenic temperatures and elevated
    temperatures above 520 K.

-   Surface preparation techniques for substrates such as aluminum,
    steels, titanium, epoxy and graphite composites, glasses, and
    ceramics.

-   Paints and other surface coatings for space flight applications that
    are adherent to standard substrates and are free of flaking, low
    outgassing, stable alpha and epsilon, stable electrical behavior,
    and resistant to ionizing radiation and atomic oxygen.

-   Thread locking compounds that have a range of predictable shear
    strengths and low outgassing.

-   Optical cements with a stable refractive index resistant to ionizing
    radiation and low outgassing.

-   Atomic oxygen resistant flexible coatings for materials such as
    thermal blankets and flexible composite structures. Proposals are
    also sought for innovative thermal spray or cold spray coating
    processes, and for novel uses of existing thermal spray processes
    that substantially improve material properties, combine dissimilar
    materials in new and useful ways, or drastically increase
    efficiency, equipment life, or allow new applications previously
    limited by the current state of the art. Applications of interest
    include but are not limited to:

-   Dense deposits of refractory metals, ceramics, and metal carbides.
    Thickness greater than 0.125 inch is of particular interest.

-   Application of thermally sprayed coatings to non-metallic and
    composite materials to enhance or extend utility or service
    limitations.

-   Coatings for protection of materials to be used in gaseous
    oxygen-rich environments.

-   Coating or spraying processes that allow forming of dense, high
    quality metallic or ceramic structural parts of complex geometry.

-   Improvements in thermal spray hardware that improve operational life
    of frequently replaced components, particularly for plasma spray
    hardware.

-   Thermal spray processes, hardware, or materials that allow
    application of high melting point materials to heat-sensitive
    substrate materials.

-   Thermal spray or liquid metal forming without the use of a vacuum
    chamber.

## 19.02 Thermal Protection Materials and Systems for Hypersonic Vehicles and Spacecraft  {#thermal-protection-materials-and-systems-for-hypersonic-vehicles-and-spacecraft .unnumbered}

Lead Center: ARC

Future hypersonic vehicles and spacecraft require new thermal
protections materials (both ablative and reusable) and novel thermal
protection systems that are lightweight and durable with lower
fabrication and operational costs than those currently available.
Design, analysis, and optimization of such materials systems requires
innovative applications of computational and experimental technology to
account for complex high-temperature multiphase phenomena that occur in
the external flow, on the heatshield surface, and inside the materials.
This subtopic solicits innovative concepts for novel lightweight and
durable, rigid or flexible, reusable or ablative materials and systems
having good thermal-shock resistance and temperature capabilities in the
range from 800 to 3100 K. Possible reusable materials include refractory
oxides, carbides, nitrides, borides and certain refractory metals. Mass
efficient ablative materials using novel technologies are also sought.
Possible material forms are fiber-fiber composites, fiber matrix
composites, foams and felts, and various woven systems, as well as thin
film, multilayer technologies. New minimum-weight, load-bearing or
non-structural thermal protection systems using new components and
processing methods are of interest, as are concepts for new and
innovative lightweight solutions to cryogenic tank insulation for
application to new reusable launch vehicles. Important proposal
considerations are reduced weight, reduced fabrication or operational
costs, improved performance, and improved robustness in adverse
environmental conditions.

This subtopic also solicits new computational and experimental
technologies for accurate measurement and modeling of mass and energy
transport through TPS materials with detailed treatment of conductive,
convective, and radiative heat transfer effects; for investigation of
gas/solid interaction phenomena in reacting flow environments; and for
rapid trajectory-based computational techniques. Technology applications
of interest include the extension of computational end experimental
methodologies to the phenomena listed above; diagnostics for high
enthalpy test facilities; and experiments to validate computational
methods and to measure relevant TPS material physical properties.

## 19.03 Materials for Propulsion and Power  {#materials-for-propulsion-and-power .unnumbered}

Lead Center: LeRC

Technologies to be addressed relate to advanced materials, their
development, and their application to primary propulsion systems
(aircraft gas turbines, rocket-based combined cycles, and rocket
engines) and auxiliary power sources in aircraft and space vehicles.
Proposals are sought to address the following areas:

**High temperature polymers and polymer matrix composites** for 18,000
hour life applications at temperatures from 280 to 320C:

-   Materials and related technologies (automated cure, resin transfer
    molding, weaving and braiding) to enable low-cost manufacturing of
    composite components.

-   Cost competitive non-mutagenic diamines for use in polyimides,
    especially low cost routes for synthesis of alpha-alpha
    prime-bis(4-aminophenyl)-p-xylene(BAX).

-   Electron beam curable polyimides for high temperature applications.

-   Processable adhesives of low void content.

-   Overlay coatings for oxidation protection.

    **Monolithic nickel-base superalloys and intermetallics, especially
    TiAl and NiAl:**

-   Low-cost processing and joining technology.

-   Alloying to improve toughness of NiAl.

-   Fiber coatings to improve compatibility with commercial oxide or
    carbide fibers.

-   High thermal conductivity copper alloys and composites.

**Ceramic matrix composites**:

-   Stronger, more creep-resistant high-temperature fibers.

-   Environmentally resistant and/or low-cost fiber coatings (SiC
    reinforced and oxide/oxide composites).

-   More affordable and stronger, tougher, and more
    environmentally-durable composites.

-   Low cost alternatives to fiber reinforcement.

    **Lubricants, Tribology:**

-   Liquid, vapor phase, and mist lubricant formulations for gas turbine
    engine applications to 400 C.

-   Wear resistant and fretting fatigue resistant coatings for titanium
    alloys.

    **Thermal Barrier Coatings(TBC) with emphasis on nondestructive
    evaluation techniques with the potential to provide:**

-   Quality control of plasma sprayed and physical vapor deposited TBCs.

-   Operational inspection of TBC coated parts enabling
    identification/overhaul/replacement prior to engine damage.

## 19.04 Structures for Propulsion and Power  {#structures-for-propulsion-and-power .unnumbered}

Lead Center: LeRC

Proposals are sought for innovative and commercially viable concepts for
propulsion and power structural and mechanical systems. Innovative
structural and mechanical concepts for advanced space propulsion systems
are also sought. The focus is on problems related to structures that
operate at extreme temperatures, in hostile aero-thermo-chemical
environments, and at high stresses. The objective is to provide
structural and mechanical concepts that enable reliable operation,
increased efficiencies, reduced design-to-production time, and reduced
life-cycle costs.

**Machinery Dynamics:** Innovative mechanical systems for controlling
destructive aeroelastic and rotordynamic instabilities and vibration in
turbomachinery. Specific items of interest are:

-   Blade vibration dampers

-   Blade Deflection and Tip Clearance Measurement Systems

-   High Temperature (e.g. 1000oF) Coils, Probes, and Touchdown Bearings
    for Magnetically Suspended Turbomachinery

-   High Speed (e.g. 50 to 100K rpm) Touchdown Bearings for Magnetically
    Suspended Flywheels

    **Structural Mechanics Computational Methods**: Analytical tools for
    simulating the performance of critical structural components and
    systems; optimizing and tailoring their capabilities; and modeling
    life-cycle performance from material selection to system
    requirements. Areas of interest are:

-   Life-Cycle Modeling

-   Composite structures

-   Multi-disciplinary design optimization and tailoring

-   Material processing modeling

    **Bearings**: Proposals are sought for innovative and commercially
    viable concepts for advanced analysis modeling of rolling element
    bearings and/or fluid film bearings for use in high-speed,
    high-load, high temperature, aircraft turbine engines or mechanical
    drive systems. The advanced concepts should provide next-generation
    design tools to increase design confidence, reduce design and
    analysis time for bearings, reduce development cost, and
    significantly reduce the development time for aircraft propulsion
    systems. The advanced codes should consider (but not be limited to)
    ball, cylindrical, tapered, and spherical rolling elements as well
    as fluid film journal and thrust bearings. The codes should also
    consider (but not be limited to) stress analysis, life analysis,
    lubrication effects, temperature effects, rotordynamics effects,
    misalignment, and distortion. State-of-the-art processing algorithms
    as well as effective graphical user interfaces should be considered.

    **Life-Prediction**: Life-prediction models and failure theories for
    assessing the durability and integrity of structural components
    manufactured from advanced high-temperature materials. These
    materials include: advanced metallics; intermetallic, polymeric,
    ceramics and ceramic matrix composites. Technical areas of interest
    include:

-   Damage mechanics and viscoplastic constitutive models

-   Fatigue crack initiation and growth models

-   Brittle structures modeling

-   Fracture mechanics/modeling

    **Experimental Mechanics:** Experimental research at the coupon
    level investigating the physical mechanisms of deformation and
    damage evaluation in advanced aeropropulsion materials. Experimental
    research at the subelement level aimed at the
    verification/validation of analytical models and analysis methods
    under prototypical leading conditions. Areas of interest are:

-   Non-destructive evaluation methods and standards

-   Mechanical test methods and standards

-   Benchmark structural testing

    **Probabalistic Durability, Reliability, & Risk Assessment:**
    Economically viable, safe, and environmentally-compatible new
    structural systems incorporating state-of-the-art materials must
    contend with a host of failure modes while operating under severe
    thermal-mechanical loading conditions. Assessing the risks of
    achieving adequate structural durability and reliability will rely
    heavily on our ability to probabilistically model deterministically
    observed material flow and failure behavior. Such behavior can be
    determined from both laboratory experiments on coupons and simulated
    or actual components where data exist or can be economically
    generated. Probabalistic analysis research is to concentrate on
    macroscopic crack initiation type failure mechanisms and
    specimen/component fracture modes. Fracture Mechanics or Damage
    Mechanics based approaches are not being sought under this element.
    Major failure mechanisms include: Fatigue, Excessive Inelastic
    Deformation, Creep-Rupture, Creep-Fatigue Interaction, Cyclic
    Relaxation, Creep-Fatigue-Environmental/Coatings Interactions,
    Thermal and Thermomechanical Fatigue, Cumulative Damage, Multiaxial
    Interactions, Brittle Fracture, Wear, Galling, Fretting, and
    Buckling.

## 19.05 Space Environmental Effects and Contamination  {#space-environmental-effects-and-contamination .unnumbered}

Lead Center: MSFC

Innovative concepts are sought for the development of materials,
processes, electronics and systems to mitigate, and/or survive the space
environment, and techniques that predict the environment experienced by
spacecraft in the near-Earth and deep space environments. This subtopic
is concerned with the electromagnetic fields, ionizing radiation,
meteoroid and orbital debris, contamination, plasma and thermosphere,
and thermal and solar components of the environment. Specific areas for
which proposals are sought include:

-   Miniature sensors to measure the vehicle environment and
    life-predicting tools based on previous flight-experiment data and
    models.

-   Elimination of contamination on spacecraft surfaces and/or
    mechanisms for in-flight cleaning.

-   Approaches for measuring, predicting, and verifying spacecraft
    molecular and particulate contamination, including reliable
    molecular monitoring systems, compact particulate-monitoring
    systems, and mass-transport models to predict molecular
    direct-transfer, backscattering, particle transport, and surface
    effects.

-   Low cost, lightweight materials and protective coatings that
    mitigate environmental effects.

-   New processing and application techniques that reduce the cost of
    current, space-qualified materials and coatings.

-   Cost-effective methods for ground-based simulation of the
    environment.

-   Techniques for electrically grounding spacecraft to mitigate
    spacecraft charging and mitigation design guidelines.

-   Preventing or mitigating the effects of space plasma electrical
    discharges on solar arrays and surfaces.

-   Instrumentation to determine absolute electrical potentials of
    interplanetary and planetary surface spacecraft.

-   Stable, electrically conductive but thermally advantageous coatings
    for spacecraft surfaces.

-   Electrically insulating materials with the capability of \"bleeding
    off\" buried charge.

-   Instrumentation to detect *in situ* buried charge in insulators.

-   Controlling spacecraft potentials actively or passively.

-   Other methods to mitigate harmful effects of space plasma and
    spacecraft charging.

-   Damage location and mitigation technologies for meteoroids /orbital
    debris.

-   Development of mitigation design guidelines for ionizing radiation.

-   Electromagnetic Interference (EMI) susceptibility characterization
    of new technology devices.

-   Developing innovative, low-cost electronic components or systems
    that show tolerance to the infrared (IR) environment.

-   New materials and coatings, including electrically conductive,
    thermal-control coatings that mitigate the environmental effects.

-   New techniques to reduce the cost of current, space-qualified
    materials and coatings.

-   Device for cleanrooms to measure particulate and/or molecular
    contamination of surfaces exposed to gaseous environment. Adaptation
    of quartz crystal microbalance technology, or other innovative
    technology, for use in monitoring cleanrooms and sample processing
    enclosures. Sensitivity of ng/cm2 deposition desired, and the device
    should be portable and designed to not add contamination to the
    cleanroom.

## 19.06 Smart Materials and Embedded Components for High Performance Aerospace Systems {#smart-materials-and-embedded-components-for-high-performance-aerospace-systems .unnumbered}

Lead Center: LaRC

Innovative concepts are being sought for the development of smart
materials and components for applications in high-performance aerospace
systems. Material systems of interest include piezoelectric and
electrostrictive materials, optical fibers, films, and coatings for
sensing external stimuli. Novel techniques are being sought for
embedding sensors, actuators, and electronics into composite systems for
active shape control and vibration stabilization. Novel approaches are
sought for actuation devices that have high displacement resolution at
cryogenic temperatures and hold position without power. Innovations in
microsensors and microactuators are also needed.

Innovations also are being sought in the use of actuators and sensors
for deployment and adjustment of structures for controllability, system
identification, vibration attenuation, shape control, static adjustment,
enhanced reliability, and reduced costs. Computer tools also are needed
for modeling and analyzing the dynamic performance of smart material
systems including piezoelectric coupling, dynamic response, and finite
element modeling approaches. Such tools should be able to be run on
desktop computers, account for test conditions, and have design and
analysis capability.

Passive damping, active damping, and low shock release devices also are
sought for single, on-orbit deployment (e.g., solar arrays and antennas)
where simultaneous deployment is critical. Damping devices must be
insensitive to a wide temperature range, operate continuously in either
direction, be adjustable and provide manual disengagement for quick
reset. Release devices, besides being low shock, must be low power and
mass, temperature insensitive and must be quick to replace/reset. In
addition, these damping and release devices should require a minimal
space to operate, and must withstand launch and landing loads.

Monolithic rheological fluid devices for holding mechanisms are
solicited. Conventional rheological fluid clamps and brakes offers
compact holding mechanisms with typically very modest requirements for
holding power. However, these devices frequently require substantial
capacitors for operation. Recent advanced in thin film supercapacitors
and ultracapacitors offer opportunities for integration of compact,
monolithic integration of electrical and mechanical function.

## 19.07 Low Density/Reduced Mass Materials for Aerospace Systems  {#low-densityreduced-mass-materials-for-aerospace-systems .unnumbered}

Lead Center: LaRC

Innovative approaches are being sought for the development of
low-density materials, processing and fabrication technology, forming
and joining technology, and process modeling to lower the weight,
improve structural efficiency, and reduce the acquisition costs of
airframe structures, launch vehicles, and spacecraft. Low-density
materials include polymers, polymer-matrix composites, light metallic
alloys, metal-matrix composites, metal laminates, inorganic glasses,
ceramics, ceramic-matrix composites, carbon-carbon composites,
refractory-matrix composites, material system blends, composite
reinforcement architectures, adhesives, films, sealants, coatings and
insulating systems. The anticipated airframe structural applications of
low-density materials include a variety of service environments and
temperatures ranging from cryogenic to elevated temperatures projected
for supersonic and hypersonic airframe structures. These low density
materials also may have applications on small satellites, manned
platforms and associated instrument subsystems in space environments
ranging from low Earth orbit to geosynchronous orbit.

Future spacecraft designs require substantial weight reduction in order
to reduce cost yet maintain equivalent or improved performance. New
materials technology that provide high thermal conductivity with reduced
mass is sought. In many applications, these materials must be capable of
carrying structural loads as well. Low coefficient of thermal expansion
(CTE) is also beneficial in many applications. Low cost manufacturing
methods of these materials are sought, as many current technology
materials are prohibitively expensive to produce. Applications in both
cryogenic and room temperature regimes are solicited. Specific areas for
which proposals are sought include the following:

-   Spacecraft structural material.

-   Aeroshells.

-   Low CTE optical benches and mirrors.

-   Instrument and electronics box enclosures.

-   Mechanical interface material between electronics boxes and
    spacecraft baseplates.

-   Cost reduction methods for producing candidate materials.

## 19.08 Non-Destructive Evaluation of Materials and Structures  {#non-destructive-evaluation-of-materials-and-structures .unnumbered}

Lead Center: LaRC

Innovative concepts are being solicited for the development of
non-destructive evaluation (NDE) sensors and instrumentation, and
computational modeling for signal processing and data interpretation.
Evaluation sciences include ultrasonics, laser ultrasonics, optics,
video optics/metrology, thermography, electromagnetics, acoustic
emission, and x-ray radiography, and related management of digital NDE
data. NDE technologies may be applied to characterizing material
properties, assessing effects of defects in materials; evaluating of
mass-loss in materials; *in situ* monitoring and control of materials
processing; detecting cracks, porosity, foreign material (inclusions),
corrosion, and dis-bonds in structures; detecting cracks under bolts;
and *in situ* monitoring of structural durability. NDE concepts would be
applied to low-density material systems of interest to NASA including
polymers, polymer-matrix composites, light metallic alloys, metal matrix
composites, metal laminates, inorganic glasses, ceramics, carbon-carbon
composites, refractory-matrix composites, material system blends,
aluminum-lithium weldments, composite reinforcement architectures,
adhesives, sealants, advanced bearings, and coatings. The anticipated
structural applications to be considered for NDE development include a
variety of service environments and temperatures projected for subsonic,
supersonic and hypersonic aircraft structures, and launch vehicles and
spacecraft. There is additional specific interest in noncontacting,
remote, rapid, and less geometry sensitive technologies that reduce
acquisition costs or improve system sensitivity, stability, and
operational costs.

Proposals for innovative and commercially viable concepts for NDE of
propulsion and power structural systems are sought. Focus is on
nondestructive materials characterization and life prediction of high
temperature engine materials and components operating at high stresses
and in hostile aero-thermo-chemical environments. Materials include
superalloys and monolithic ceramics, and polymeric, intermetallic, and
ceramic matrix composites.

## 19.09 Bonding and Joining Technologies  {#bonding-and-joining-technologies .unnumbered}

Lead Center: MSFC

NASA seeks innovative technologies for bonding and joining of materials
to improve the performance and affordability of future aerospace
systems. Advancements are sought that improve joint efficiency, allow
joining of a wider range of materials, improve the quality and
cost-effectiveness of the joint, and extend the understanding of factors
influencing these characteristics.

-   Technologies and processes are sought for joining of aluminum
    alloys, especially in the application of cryotankage and structures
    for future space vehicles. Of particular interest are those
    applicable to high-performance aluminum-lithium alloys and aluminum
    metal-matrix composites. Additionally, methods for low-cost
    fabrication in the more common aluminum alloys and other structural
    metallic alloys are of interest.

-   Technologies are needed to improve control of welding, brazing and
    other joining processes as they are applied to joints for aerospace
    vehicles. These technologies should be compatible with the quality
    requirements for aerospace vehicles, and should include process
    control technologies as well as non-destructive examination methods.

-   Techniques are needed for in-space welding and its associated
    operations, including welding, brazing, cutting, joint preparation,
    and non-destructive examination. These techniques would be applied
    to aluminum, stainless, and titanium alloys in plate and tube forms.

-   Techniques and processes are sought for the joining of dissimilar
    refractory metals and ceramics capable of withstanding repeated
    cycling to or long-term sustained operation at very high
    temperatures (approaching the melting points of the materials being
    joined). Materials of interest include, but are not limited to,
    refractory metals such as TZM and titanium, ceramics such as
    mullite, alumina or silicon nitride, various carbon-carbon
    composites, graphite and CVD diamond. The requirement for sustained
    operation at high temperature severely restricts the use of active
    metal braze techniques, while the requirement for repeated high
    temperature cycling makes it essential that detailed consideration
    be given in the proposal to problems of CTE mismatch. Material
    properties of particular interest in the bonded assemblages include
    the electrical conductivity of the joint and its stability in both
    oxidizing and reducing atmospheres at high temperature. Prospective
    uses for the techniques developed under this subtask include the
    construction of ultracompact, highly-efficient furnaces and
    evaporators to enable particle experiments on the Space Shuttle and
    Space Station, bonding leading-edge components in supersonic
    aircraft such as the National Aerospace Plane and fabrication of
    structural components for use on space missions close to the Sun
    such as Solar Probe. These techniques should have broad application
    in the commercial arena where the use of advanced ceramics and
    composites has been severely hindered by the inability to join such
    materials into components capable of withstanding the same harsh
    environments as the materials themselves.

## 19.10 Inflatable Structures and Systems  {#inflatable-structures-and-systems .unnumbered}

Lead Center: JPL

A new class of deployable space structures has emerged that has
tremendous potential for enabling missions based on using large, low
cost, light weight and mechanically reliable structures. The technology
has advanced to the point of accommodating the design and manufacture of
thin membrane structures with enough geometric precision to be
considered for a number of applications including booms, solar-array
support structures, sun shade support structures, planar array antennas,
solar concentrators, and reflector antennas. Proposals that take
advantage of the inherent capabilities of inflatables to provide low
package volume for transport while enabling large volume applications
will be considered. Elements of this technology include space
rigidizable and thin membrane film materials; manufacturing, handling,
processing and assembly techniques for flexible materials; concepts for
the control of deployment dynamics of inflatable structures; ground
based deployment approaches for large inflatable structures and
analytical performance simulation for these unique structures.
Requirements are for new techniques for the space based rigidization of
thin flexible materials that are long term dimensionally stable.

The availability of thin polymer films that have high radiation
resistance and lend themselves to handling, processing and fabrication
of high precision doubly curved surfaces are desirable. New and
innovative deployment control concepts that account for the effects of
residual air and the release of materials strain energy while
maintaining member expansion rates and prescribed dimensional changes
are needed. New ground based deployment test techniques for large
inflatable structures that utilize fixturing to offset the effects of
gravity loading, vacuum drop testing and 0-g aircraft tests or some
combination of them needs to be addressed. The value of this technology
for specific applications will be realized when analytical tools are
available for the prediction of structural, dynamic, thermal and long
term dimensional stability of these structures.

## 19.11 Balloon Vehicles & Aerobots  {#balloon-vehicles-aerobots .unnumbered}

Lead Center: GSFC

Innovations in materials structures and systems concepts have enabled
lighter than air vehicles to play an expanding role in NASA's space and
earth science programs. Smaller robotic balloons, known as Planetary
Aerobots will carry scientific payloads into the atmosphere of Mars,
Venus, Titan and the outer planets in order to investigate their
atmospheres *in situ* and their surfaces from close proximity. Their
envelopes will be subject to extreme environments and must support
missions with a range of durations. Miniature balloons capable of long
duration flight also are emerging as an important tool in terrestrial
climate investigations and weather prediction. Such balloons also have
potential commercial significance for communications. A new generation
of stratospheric balloons based on advanced balloon envelope
technologies will be able to deliver large balloon craft and payloads of
several 1000 Kg to above 99.9% of the Earth's absorbing atmosphere and
maintain them there for months of continuous observation. The Ultra Long
Duration Balloon (ULDB) with volumes up to 1 million cubic meters must
survive a demanding set of environmental conditions beginning with the
fabrication of the material and balloon through launch, ascent and
float. NASA is seeking innovative and cost effective solutions in
support of this development activity in the following areas (proposers
should specify the size range of vehicles to which their technologies
apply):

-   High strength to weight composite envelope materials suitable for
    fabrication into balloon vehicles.

-   Efficient and cost effective balloon envelope seaming fabrication
    and inspection techniques.

-   Buoyancy control methods involving no consumables to limit balloon
    diurnal altitude excursions or temperature/differential pressure
    fluctuations and/or enable altitude control needed for planetary
    missions.

-   Autonomous precision parafoil and parachute systems for recovery of
    terrestrial ballooncraft and targeting of planetary probes and
    sondes.

-   Deployment and inflation of balloon envelopes in planetary
    atmospheres.

-   Latitude trajectory control for altering balloon trajectories to
    avoid overflight of no-fly zones on earth and enable global
    reconnaissance of the planets.

-   Innovative balloon design concepts for including zero-pressure,
    superpressure, Montgolfere and reversible fluid balloons.

-   Techniques for contamination and sterilization of planetary balloon
    materials to meet planetary protection requirements.

# 20 Design Tools, Systems Analysis, and Simulation  {#design-tools-systems-analysis-and-simulation .unnumbered}

This topic provides advanced visualization and computational
capabilities to rapidly design and simulate aerospace products in a
collaborative environment linking science, technology, and engineering
teams. Tools and interfaces (computer-to-computer and human-to-computer)
are required at several levels of fidelity to provide the means to
\"virtually\" assemble, visualize and test vehicles and mission
scenarios. Traditional methods (based on physical principles) and
non-traditional methods (based on intelligent learning systems) will aim
at addressing uncertainties, risk, and cost. Methods for rapid
verification and validation of new design and simulation models are
included, and should address new areas such as microspacecraft
technology. Risk of including such emerging technology will be reduced
by integrating advanced process and product models with actual hardware
and software components.

## 20.01 Advanced Concepts of Virtual Spacecraft Design and Visualization  {#advanced-concepts-of-virtual-spacecraft-design-and-visualization .unnumbered}

Lead Center: JPL

There is a critical and growing need to achieve better mission designs
and hardware, with fewer resources, in less time. From a mission and
system perspective, enhanced performance and reduced cost requires:
uniform system information storage, seamless integration of tools and
applications, continuity of products through the mission life-cycle, and
efficient methods for optimization. Design environment innovations must
include collaborative development processes, and rigorous validation of
decisions and products, with scalable, open architectures. Other
required elements are: interface tools that allow efficient creation and
modification of mission scenarios with minimal support by software
engineers; and methods for collaborative scenario visualization,
including advanced displays, language, and adaptive interfaces.

-   Advanced human/computer interface: 2D and 3D displays; effectors
    (manipulation of virtual objects)

-   Interactive and collaborative agents: natural language interface;
    user guidance; connection to underlying agent-based infrastructure.
    Interfaces and tools for web-based collaborative computing and
    design.

-   Scenario specification and selection: graphical and linguistic
    programming.

-   Discipline tools: object-oriented design environment architectures,
    object reuse, and object instantiation for maximum flexibility;
    object request brokers; mega-programming and tools control
    languages.

-   Full life cycle: database containing documentation, hyperlinks, and
    standard product formats.

-   Validation: compliance matrices, peer review support, design
    walk-through support, comparison of results obtained by new methods
    with those from traditional methods.

-   Verification: tools for virtual system and hardware prototyping and
    performance verification.

-   Advanced product models: smart product models and object modeling
    languages, analytical, behavioral, simulation and CAD model
    integration with objects.

-   Non-deterministic tools: intelligent non-deterministic tools to
    provide uncertainty predictions for design and analysis assumptions.
    Application of uncertainty technologies, to establish an initial
    reliability based design, in order to remove conservatism in
    traditional margin-of-safety design approaches.

-   Automatic tool interoperability: publish and subscribe
    architectures.

-   In order to reduce design cycle time, innovative approaches to
    systems requirements capture are needed, perhaps using software
    models. The new approach should be based on some fundamentally new
    scheme for producing system requirements and flowing them down to
    subsystems; it should provide a capability to \"execute\"
    requirements against a (changing) mission scenario, testing whether
    the requirements can satisfy the scenario and if not, where the
    mismatches occur. It must also allow designs to be continuously
    tested against requirements for compliance as the designs evolve.

## 20.02 Advanced Design, Analysis and Simulation Tools  {#advanced-design-analysis-and-simulation-tools .unnumbered}

Lead Center: GSFC

**Instrument Modeling and Simulation**

The continued need to reduce cost of future microwave to x-ray
scientific instruments requires innovations in design, modeling,
analysis and verification. An integrated, reusable, multidisciplinary,
collaborative approach using modeling and simulation tools, and
multidisciplinary processes are essential. Areas of interest are:

-   Efficient, integrated end-to-end modeling and analysis tools for
    characterizing the performance, parametrically optimizing the
    design, verifying the design, and \"virtual testing and
    calibration.\" This is to include tools for active optical systems
    particularly for the diffraction-limited image retrieval, and the
    wavefront retrieval of segmented or deployed optical systems.

-   End-to-end instrument systems simulation tools that include the
    integration of the measurement phenomena, the environment and the
    instrument subsystems, especially the optics, electro-optics,
    opto-mechanics, sensors and signal processing.

-   Smart Product Models and Object Modeling Languages, analytical,
    behavioral physical properties integrate with design and modeling
    tools.

-   Non-deterministic tools to provide uncertainties and to use
    reliability rather than margin-of-safety for design validation.

    **Mission, Spacecraft, and Ground Segment Systems Design and
    Modeling**

    There is a growing need to achieve better mission designs, with
    fewer resources, in less time. From a mission and system
    perspective, there is need to have a single system data repository,
    seamless tool interoperability, continuity of products through the
    mission life-cycle, and efficient methods for mission optimization.
    These design environment innovations must include collaborative
    development processes, and rigorous validation of decisions and
    products. Areas of interest include:

-   Discipline Tools: object oriented architectures, object reuse, and
    object instantiation.

-   Advanced Product Models: Smart Product Models and Object Modeling
    Languages, analytical, behavioral, simulation and CAD model
    integration with objects.

-   Automatic Tool Interoperability: publish and subscribe
    architectures, Object Request Brokers, mega-programming and tools
    control languages.

-   Full Life-cycle: database contained documentation, hyperlinks,
    standard product formats.

-   Validation: model validation, compliance matrices, peer review
    support, design walk-through support.

-   Product Standards: STEP-ISO 10303, JAVA, DORBA, OML, etc.

# 21 Avionics, Data Systems, and Data Storage  {#avionics-data-systems-and-data-storage .unnumbered}

This topic seeks innovative technologies that significantly reduce the
mass, volume and cost of spacecraft and multispacecraft missions through
technical advances in microelectronics and advanced flight computing
technologies, guidance, navigation and control systems, and through
modular and multifunctional spacecraft architectures that integrate
spacecraft subsystems. These goals are to be achieved together with
increasing the functional capability of the systems, and improving their
system reliability. System on a chip solutions, advanced computing
technologies, component packaging, integrating spacecraft subsystems,
new methods for attitude sensing, three-dimensional-chip stacking and
multichip modules, and advanced design automation are among the many
concepts being considered in a revolutionary redesign of spacecraft.

## 21.01 Microelectronics for Space Systems  {#microelectronics-for-space-systems .unnumbered}

Lead Center: JPL

Innovations are sought that significantly reduce the power, mass, volume
and cost of spacecraft through advances in microelectronics, computing
technologies, and avionics architectures. These goals are to be achieved
together with increased functional capabilities and improvement of
system reliability. The technologies being sought include:

-   Systems on a chip technologies that integrate telecommunications,
    power management, data processing and storage, or data sensors
    technologies into a common microsystem.

-   Three-dimensional VLSI, chip stacking, multi-chip-module stacking
    and other advanced packaging techniques.

-   Low power components and advanced power management techniques.

-   High performance, low power and low cost subsystem interface.

-   Low temperature microelectronics components.

-   Low power, COTS-based radiation tolerant (including SEU) components.

-   Space qualifiable, high-density, non-volatile mass memory.

-   Fault tolerance design techniques for severely power and mass
    constrained environments and extreme long life missions.

-   On-board maintenance design and analysis.

-   Advanced design automation.

-   Low power, high bandwidth integrated fiber optic transceivers with
    spacecraft network interfaces.

-   Design automation, emulation tools, and environments for end to end
    hardware, mission application software, and operating system
    developments appropriate for space and high use of COTS derived
    hardware and software components.

-   Concepts and designs for real time *in situ* test and validation of
    design integrity and performance for spacecraft systems.

-   High resolution, high sampling rate analog-digital converters, and
    digital signal processing hardware components with algorithm design
    environments for rapid design and prototyping.

##  {#section-13 .unnumbered}

## 21.02 Highly-Integrated Multifunctional and Adaptive Structures for Aerospace Systems  {#highly-integrated-multifunctional-and-adaptive-structures-for-aerospace-systems .unnumbered}

Lead Center: LaRC

NASA seeks concepts for reducing spacecraft size and mass, and for
improving the performance of aerospace vehicles through the use of
highly-integrated multifunctional and adaptive structures.
Multifunctional structures combine two or more functions in load-bearing
structural elements. For example, a multifunctional structure may
incorporate imbedded electronics, thermal management, and radiation
shielding in a lightweight composite panel. An adaptive or smart
structure may incorporate sensing, processing, and actuation so that it
can respond to changes in its environment, reconfigure its geometry,
control its dynamics, or repair itself when damaged.

Innovative technologies are sought in the following areas:

-   Techniques for the structural integration of low-volume electronics
    packaging such as chip-on-structure, chip-on-flex (flexible
    circuitry), and imbedded electronics.

-   Concepts for integrating electronics, thermal management, radiation
    shielding with lightweight composite structures.

-   Concepts for integrating lightweight composite optics and support
    structures for compact instruments.

-   Methods to rapidly assemble and disassemble or repair
    highly-integrated multifunctional structures or imbedded
    electronics.

-   Reconfigurable structures that incorporate imbedded actuators or
    smart materials to enable changes in geometry

-   Adaptive structures that are capable of reactive responses to
    environmental stimuli.

-   Self-healing materials.

-   Electrochromic materials for active control of surface thermal and
    optical properties.

-   Multifunctional structural elements that incorporate lightweight
    radiation shielding materials to protect astronauts from the harmful
    effects of galactic cosmic rays and solar particle events.

-   Lightweight radiation shielding materials that enable the use of
    lower-cost commercial off-the-self microelectronic parts in high
    radiation environments.

-   Multifunctional structures that incorporate both power generation
    and telecommunications functions.

-   Lightweight, load-bearing polymer and plastic batteries.

-   Interchangeable structural components that can be used for more than
    one function.

-   Integration of two or more spacecraft systems functions in miniature
    components for micro-spacecraft and sensorcraft.

## 21.03 Autonomous Guidance, Navigation, and Control for Aerospace Systems  {#autonomous-guidance-navigation-and-control-for-aerospace-systems .unnumbered}

Lead Center: JPL

Innovative concepts for autonomous guidance, navigation, and control for
aeronautic and for space systems including new methods and
high-precision low-power, and low-mass sensors and actuators are
solicited for future NASA missions. Specific areas for which proposals
are sought include:

-   Micro-star and -feature trackers, micro-inertial measurement units
    and micro-reaction wheels with masses on the order of hundreds of
    grams.

-   Environmental models to enhance attitude sensor measurements and
    spacecraft dynamics simulations.

-   Advanced architectures, algorithms and software for high precision
    autonomous control of formation flying spacecraft. High precision
    G&C constellation sensors including optical, celestial, and RF.

-   Miniature spacecraft control capable of autonomously monitoring
    spacecraft functions and environmental conditions; assessing health
    status and optimizing performance through in-flight identification,
    fault detection, stabilization, and re-configurable control;
    utilizing fuzzy logic, neural networks, and control techniques.

-   Advanced techniques for control of both rigid and flexible body
    control, that are robust parametric uncertainty and modeling error,
    to improve system reliability, operational capability, and to reduce
    life cycle cost. Digital filter algorithms to achieve precision
    pointing and tracking performance with micro-measurement and
    actuation systems.

-   Advanced architectures, algorithms, and software for high precision
    autonomous controlled landing and sample return on small planetary
    bodies. This includes sensor system, algorithms hazard avoidance and
    rendezvous and docking.

-   Computer-aided engineering and design tools as well as parallel
    algorithms to better manage complex tasks required for guidance and
    control. Advances in these tools should allow faster trade studies,
    cut analysis costs, allow quick prototyping of flight software, and
    provide reliable interpretation of real-time simulations.

-   Concepts, architectures, and algorithms for guidance of space
    transportation systems during atmospheric flight phases. Emphasis is
    on technology that enhances system availability under various
    atmospheric conditions and maximizes vehicle autonomy.

-   Guidance and navigation methods for proximity operations in Earth
    orbit based on use of the Global Positioning System (GPS).

-   Autonomous onboard guidance and relative navigation techniques
    (hardware, software, sensors) for the formation flying of
    satellites. Position accuracy on the order of a few centimeters is a
    goal. Navigation techniques can utilize, but are not limited to the
    GPS/WAAS.

-   GPS receiver hardware and algorithms that use GPS code and carrier
    signals in innovative ways to provide spacecraft navigation,
    attitude, and timing information.

-   Techniques for the optimization of control functions to enhance the
    performance of aeronautical vehicles in the face of real parameter
    uncertainties.

-   High resolution optical or other nonintrusive techniques to measure
    position, and rates of a magnetically levitated body (e.g.,
    bearings). This would be at moderately high sampling rates, (i.e.,
    more than 100 samples /sec).

## 21.04 Data Management and Electronics for Aerospace Subsystems  {#data-management-and-electronics-for-aerospace-subsystems .unnumbered}

Lead Center: GSFC

Proposals in data systems technologies are sought that will allow
enhanced science requirements, reduced levels of mission funding,
shorter schedules and reduced availability of flight electronic
components. The following technology innovations are sought:

-   Subsystem data transfer - communications between various spacecraft
    subsystems and instruments. Development of technologies and
    architectures that increase the rate of data transfer above 20
    Mbits/s are necessary to achieve the autonomous control and science
    data requirements.

-   Intra-system data transfer - communications within the spacecraft
    subsystem (between cards within a box). Technologies for
    communications within a box that would replace the conventional
    passive backplanes to achieve data throughput.

-   Volatile data storage - large capacity Solid State Recorders (SSRs)
    are required to store data until the next ground. Components and
    packaging techniques that would allow greater density and lower cost
    SSRs for higher science data rates and smaller spacecraft.

-   Non-volatile data storage - components and systems to record data
    and retain it without power. Removed from the flight configuration
    and played back on the ground.

-   Ruggedized recorders - components to support recording requirements
    0of balloon projects.. Technologies that allow 1 Terabit
    non-volatile recorders to be dropped from balloons (up to 130,00
    feet altitude) to the earth (10-g shocks).

-   General purpose data processing - higher levels (spacecraft
    computers that match or exceed the commercially available desktop
    computers) of general purpose CISC and RISC processing.

-   Special purpose data processing - higher levels of onboard science
    data processing such as histogramming, feature recognition and image
    registration are necessary to match the data gathering capabilities
    of future instruments with the limits of spacecraft to earth
    communications. Development of technologies such as Digital Signal
    Processors (DSP) and related hardware is necessary to address this
    future need.

-   Configurable hardware - pure hardware solutions with on orbit design
    flexibility. Technologies such as radiation hardened Field
    Programmable Gate Arrays (FPGAs) and reprogrammable architectures.

-   Low-power electronics - low voltage (\<5 V) technologies. Low
    voltage, such as 3.3 V or 2.5 V or lower technologies to achieve the
    power constraints of smaller spacecraft.

-   Multiprocessing architectures - components, architectures and
    protocols to achieve parallel scalar computers on board spacecraft.

    NASA projects continue to face the goals of decreased payload weight
    and volume and increased functionality. This effort is to develop
    miniaturized microelectronic systems utilizing advanced substrate
    technologies and high-density component packaging techniques, such
    as chip-on-board and stacked configurations. NASA is soliciting the
    following technologies needs to incorporate into miniaturized
    instrument and spacecraft subsystem electronics modules for
    next-generation spacecraft:

-   Higher density and greater functionality in a miniaturized scheme.

-   \"Order of magnitude improvement\" (weight and volume) over
    traditional packaged parts with printed wiring board configurations.

-   Non-traditional substrate materials (silicon, diamond-like
    materials, etc.) to address challenges in thermal and interconnect.

-   State-of-the-art miniaturized contacts as interconnect between
    layers in stacked packaging.

-   Capability for technology insertion as instrument and spacecraft
    electronics subsystem modules.

# 22 Instruments and Sensing  {#instruments-and-sensing .unnumbered}

NASA has a strong and ongoing interest in advanced instrument and
sensing technologies to enable new and improved measurement capabilities
across discipline and Enterprise lines. NASA is seeking innovative
technologies for remote and in-situ instruments that provide improved
sensitivity, spatial resolution or imaging performance; better frequency
or energy coverage, better overall efficiency and robustness; and lower
cost. Of primary interest are technologies that have the effect of
reducing instrument demands on mission resources (such as mass, volume,
power, cooling requirements, or cost).

## 22.01 Spectroscopic and Multi-spectral Imaging Sensors in the UV to Far IR  {#spectroscopic-and-multi-spectral-imaging-sensors-in-the-uv-to-far-ir .unnumbered}

Lead Center: JPL

Advances in state-of-the art imaging, multispectral imaging systems, and
spectroscopic systems in the wavelength region from 10 nm to 1 mm are
sought. This includes detectors, readout electronics, and technology for
the conversion of electromagnetic radiation to an electrical signal, and
the conditioning and transmission of the signal from the focal plane
array. Innovations that result in significant reduction of instrument
mass, volume, power or data rate with simultaneously improved scientific
return, are of particular interest. Of special interest are technologies
that benefit NASA\'s emerging Origins thrust, including large format,
high sensitivity arrays with stable performance and radiation tolerance
covering the 0.5-20 micrometer range; hybrid IR arrays (including novel
intrinsic, extrinsic, and bandgap-engineered materials; InGaAs
detectors; quantum well infrared photodetectors, and higher-temperature
or uncooled infrared focal-plane arrays); and long wavelength IR
detection systems with ultra-low noise, with the goal of single photon
counting. The following technology innovations are sought:

-   Readouts for deep-cryogenic detectors with low noise, low leakage
    and reduced focal plane power dissipation. Cryogenic technologies of
    interest include cryo-CMOS, GaAs, germanium, and superconductors.

-   Sensor readout electronics with emphasis on low-power, single-chip
    imaging systems, optical readouts and couplers, readouts for high
    background, long wavelength detectors, high-speed, large format
    arrays for optical communication in visible and IR. Advanced readout
    systems with on-chip signal processing such as on-focal-plane
    digitization with high resolution (14 bits dynamic range), dynamic
    range management, and specialty imagers such as star trackers,
    fringe counters, and sensors for wave-front correction.

-   Robust and highly sensitive UV detectors in large format arrays.
    Single photon counting is a goal, and solar blindness is a
    significant advantage.

-   Detector/array calibration and characterization techniques,
    particularly for challenging applications in extremely low
    signal/background environments.

-   Solid state polarimeter detectors including both linear and full
    stokes vector devices.

-   Linear photon counting arrays emphasizing wavelengths at 355, 532,
    and 1064 nanometers (e.g., Geiger Mode APD).

## 22.02 High Energy Sensing {#high-energy-sensing .unnumbered}

Lead Center: GSFC

Advanced detectors, detector arrays, readout electronics and other
supporting and enabling technologies are needed to support
next-generation Earth, space, planetary, and life science missions.
Proposals are solicited for innovations ranging from new detector
concepts to improvements to existing detectors that provide
order-of-magnitude performance enhancements. The following capabilities
in x-ray, gamma-ray, and cosmic-ray detectors and supporting
technologies are desired:

-   Double sided fine pitch (100 micron to 0.5 mm) silicon strip x-ray
    and gamma-ray detectors. Must be capable of being arrayed to
    increase area.

-   High energy resolution Ge strip and pixel detectors. The spatial
    resolution of the pixels or strips should be as small as 0.5
    millimeters.

-   Technologies for increasing the collecting area to telescope mass
    ratio in x-ray region of 500 eV to 30 keV (e.g. inflatable and
    deployable structures).

-   Low power (\< 200 mW per linear chain) ASIC electronics for charged
    particle, x-ray, and gamma-ray detectors.

-   Flight-qualified, high-density interconnects for connecting arrays
    of segmented semiconductor detectors.

-   Development of improved growth and characterization techniques for
    Cadmium Zinc Telluride (CdZnTe) material for use in gamma-ray
    detectors.

-   Large arrays (\~120x120) of superconducting TES (transition edge
    sensor) x-ray microcalorimeters (2 eV FWHM at count rates up to a
    KHz in the 0.3-12 keV band).

-   SQUID based read-out electronics for large arrays of TES
    microcalorimeters. Switching and sampling rates from 1-10 MHz.

-   Closely packed 2-dimensional calorimeter arrays employing unique
    methods of thermal isolation and batch processed fabrication
    techniques.

-   Robust x-ray filter substrates for cryogenic instruments in the
    range 50 eV to 12 keV.

-   Small (\<2 mm x 2 mm) low noise wire bondable resistors (100-200
    Mohm) with less than 4% resistance changes from room temperature to
    1 K.

-   High-sensitivity, high-energy-resolution, solid-state scintillation
    detectors.

-   Silicon detector arrays (e.g., CCDs or active pixel sensors) with
    x-ray response in the 1 keV to 50 keV range for spectrometer
    applications.

-   GAS micro-strip detectors or micro-gap detectors, optimized for low
    energy x-ray operation in relatively low-rate environments.

-   High density capacitor/resistor arrays on a single substrate, to
    interface strip detectors to analog ASICs.

-   Pixelated Cadmium Zinc Telluride (CdZnTe) arrays with pixel sizes in
    the range of 3 mm as well as 500 microns.

-   Pixel arrays of high-resolution germanium detectors with sizes near
    1 mm.

-   High-performance analog VLSI electronics for readout and processing
    of signals from both CdZnTe and Ge arrays.

-   Focusing optics for hard x-rays (grazing incidence mirrors) for
    energies to at least 100 keV.

## 22.03 Microwave, Millimeter and Submillimeter Sensing Technology  {#microwave-millimeter-and-submillimeter-sensing-technology .unnumbered}

Lead Center: JPL

Many NASA future astrophysics, space science, planetary and atmospheric
remote sensing programs and missions require microwave-to submillimeter
wavelength capability. There are current needs for spectrally pure
radiation sources for heterodyne applications through 10 THz, novel
light weight diffraction limited antenna systems, low loss THz optics,
large bandwidth transmitters and receivers in the 3 cm to 30 micron
wavelength range. Pressing requirements are for 1) heterodyne sources in
the 1.2 to 3 THz region, 2) very low power backend spectrometers and 3)
broad banded sources with 50+mW output in the 60-120 GHz range. More
long term requirements are for radiometer system components which can be
integrated into very small, low cost, low power receiver systems and
millimeter wave very large bandwidth/data rate transmitter and receiver
systems. There is also beginning to be some interest in high resolution
submillimeter wavelength imaging technology. The focus is on low cost
durable technology for application on rocket, balloon and aircraft
platforms and at remote/autonomous observatory sites. The technology
should also have the potential for adaptation to space applications with
lifetimes of 5 years or more. The possibility of cooled operation should
be evaluated since many Earth remote sensing receivers typically operate
near LN2 temperatures and astrophysics receivers are
cryogenically-cooled to liquid Helium or lower temperatures to achieve
near quantum-noise-limited performance.

For the heterodyne remote sensing systems, there is an emphasis on 1)
broad band (10%) tunable sources with at least a few micro watts output
in the 1.2 THz to 10 THz frequency range and 2) 120-1200 GHz sources
capable of delivering 20% bandwidth and 100+ micro watts of power with
less than 6 watts DC input. Additional source needs include 1) broad
band (20%) high power 20+mW active multipliers (x2 and x3) above 60 GHz
and 2) broad banded (20%) solid state sources capable of generating
50+mW in the 40-300 GHz frequency range. Preference will be given to
fundamental oscillator sources. All of the sources should be phase
lockable and should be able to achieve less than 25 kHz line width below
1200 GHz and less than 100 kHz line width above 1.2 THz. In addition to
the source needs, the long term goal of this effort is to be able to
build complete MMIC heterodyne receivers so special attention will be
paid to higher-frequency and higher-output power MIC and MMIC
technology.

The specific needs are as follows:

-   Broad band (10-20+%) low power solid state local oscillator sources
    capable of delivering 100+ micro Watts CW in the 120-1200 GHz region
    and 1+ micro Watt CW in the 1.2-10 THz region. Broad band mixers
    suitable for use in very sensitive heterodyne receivers have been
    developed in this frequency range and are currently limited to by
    the availability and performance of the local oscillators. A single
    local oscillator source that could tune over any significant portion
    of the 1.2-3 THz band with a few micro watts of power would find
    immediate use in several different programs. Preference will be
    given to fundamental frequency sources that require less than 30 W
    of power and could be used in long lifetime applications.

-   Robust, compact, solid-state, phase-lockable oscillator or active
    multiplier sources with 50+ mW and 20+% band width in the 60-120 GHz
    Range.

-   Very compact low power high efficiency sources that could be
    integrated into MMIC receiver systems in the 120-300 GHz frequency
    range.

-   Heterodyne receiver integration at the circuit and/or chip level is
    needed to extend monolithic microwave integrated circuit (MMIC)
    capability into the submillimeter regime. Integration of all or part
    of the local oscillator, multiplier chain, mixer, and intermediate
    frequency amplifier is one example. There is also a specific need to
    demonstrate radiometer systems using phased-arrays and MMIC LNA(Low
    Noise Amplifier) radiometers from 60 GHz to 300GHz or higher. There
    is also a need to demonstrate arrays of high performance radiometers
    for imaging through 1.2 THz.

-   Low power multi-channel spectrometers that analyze intermediate
    frequency signal bandwidths as large as 20 GHz with a frequency
    resolution of \<1 MHz, that are small and lightweight, and that use
    low power (\<5 mW per channel) with high stability and lifetimes
    greater than five years.

-   Compact and reliable millimeter and submillimeter instrumentation
    that produces low noise images simultaneously in multiple spectral
    bands.

-   Lightweight and compact radiometer calibration references covering
    100-1000 GHz frequency range.

-   Lightweight, field portable, and compact radiometer calibration
    target references covering frequencies up to 1000 GHz. The reference
    must be temperature stable to within 1 Kelvin with a minimum of 3
    temperature settings between 250 and 350 Kelvin.

-   Low cost special purpose ground based receivers to detect signals
    radiated from satellites that are already in space for estimating
    rain rate, water vapor, and cloud liquid water.

-   Very large bandwidth/data rate millimeter wave transmitters and
    receives for the next generation of earth to space based
    communications.

## 22.04 Cryogenic Support Systems  {#cryogenic-support-systems .unnumbered}

Lead Center: GSFC

Future space missions will have operational lifetimes of 5 to 15 years
and will require similar lifetimes for cryogenic cooling systems. Both
the lifetime and the reliability of the cryogenic systems are critical
performance concerns. Mechanical coolers, radiative coolers, stored
cryogenic fluids and combinations of these will be considered. Of
interest are long life, low vibration, low mass, low cost, high
efficiency cryogenic coolers for cooling detectors, telescopes and
instruments; for the storage and liquefaction of cryogenic propellants;
and for hybrid systems in the 0.05 to 150 K temperature range. The
following are of particular interest:

-   Highly reliable, efficient, low cost Stirling, pulse tube, reverse
    Brayton, magnetic, solid-state cooler technology and hybrid systems,
    including hybrids with radiative coolers. Emphasis will be placed on
    technologies leading to small, low mass, low cost cooling systems.

-   Low cost compressors and pulse tube cooler efficiency improvements
    for 0.1 - 10 W cooling in the 7 - 120 K range for space missions;
    coolers for robotic and manned missions to the Moon and Mars
    (requirements from 100 W @ 20 K with 1 year life to 10 W @ 90 K with
    7 year life and oxygen liquefiers for use on Mars over the 3 W to
    400 W range); a 0.5 W @ 100 K cooler that can start after 4 years of
    storage at temperatures down to 100 K; phase change thermal
    reservoirs or passive storage technology in the 100 - 250 K range
    for returning samples from planets, asteroids, and comets; and novel
    micro-scale coolers for integrated focal plane packages.

-   Innovative technologies for: hybrid coolers using sorption
    refrigeration lower stage integrated with a radiative upper stage to
    provide 100 mW at 10 to 40 K; temperature stability enhancement for
    solid hydrogen sublimation stages in continuous 10-K sorption
    cryocoolers: low cost, light weight cryogenic (60 K to 120 K)
    radiators: active and passive vibration cancellation of mechanical
    cooler generated vibration, both at cryogenic and ambient
    temperatures. Other areas of interest include: stable, high
    conductivity interface materials, high conductivity, low coefficient
    of thermal expansion (CTE) materials; and high conductivity,
    flexible thermal links.

-   Future missions to the Martian or Lunar surface will take advantage
    of indigenous resources for producing propellants. Liquid oxygen,
    and potentially other cryogens, will be produced and stored on the
    planet surface. Innovative technologies are needed for the cryogenic
    support systems for these propellant production and storage units.
    Specific technology areas include high capacity liquefaction systems
    for oxygen, cryocooler systems with high cooling capacity (25
    watts), and very low heat leak oxygen dewars.

## 22.05 MEMS and Meso Scale Processes and Devices for Instrument Systems  {#mems-and-meso-scale-processes-and-devices-for-instrument-systems .unnumbered}

Lead Center: JPL

NASA urgently requires miniature instrument systems and their components
which will significantly impact the overall size, mass and power
requirements of both robotic and human missions. This subtopic
specifically solicits proposals for devices and instruments that utilize
micro electro-mechanical systems (MEMS) or meso scale fabrication
techniques or process developments which have specific application to
the fabrication of such devices (e.g. three dimensional high aspect
ratio fabrication, self assembly, large area replication, etc.). This
subtopic addresses the application of MEMS or meso scale fabrication
technologies for *in situ* micro-instruments which are capable of
operating in space and planetary environments under stresses that might
include severe heat, cold, vacuum, high impact, and radiation.
Innovations in miniaturization are desired not only in sensors (motion,
chemical, biological, geological, environmental, electromagnetic,
spectral, spatial, etc.), but also in enabling technology such as:
vacuum pumps; micro power systems, thermal and power management;
packaging; sample collection and processing; and mechanisms for
deployment and mobility of sensors and antennae. The recent increase in
emphasis on biological and chemical *in situ* analysis and the
requirement for drastic reductions in size, weight and power consumption
of spacecraft and instruments, creates an opportunity to propose
ultra-miniaturized instruments which might utilize combinatorial methods
(arrays of thin film sensors) spectroscopic tools (Raman spectroscopy,
gas chromatography, capillary electrophoresis, mass spectroscopy) or
miniature suboptical microscopy (scanning electron or atomic force
microscopes).

Preparation for the human exploration of Mars has been established as a
NASA priority. Accordingly, we also solicit MEMS or meso scale
micro-instruments designed to measure and monitor habitability, to
control *in situ* resource utilization facilities, or to facilitate
communication and mobility on the Martian surface. The next generation
of spacecraft will use deployable structures for many purposes such as
antennas, solar sails, and telescopes. Micro-instrument concepts will be
entertained for sensing structure motion and for structure control.
Research instrumentation is needed for fundamental studies of basic
phenomena, design code validation, and experimental tests in aerospace
facilities such as combustion labs and drop towers. Of special interest
are techniques that quantify multiple parameters at multiple spatial
points to provide 2D and 3D data in turbo-machinery, around airframes,
and in microgravity fluids. Time history data is also important. Fluid
parameters of interest include temperature, pressure, density, and
velocity, chemical composition. Surface parameters of interest include
temperature, pressure, strain, deformation, and defect detection.
Proposals are also solicited for educational products that bring
inexpensive micro instruments to the classroom, either at the K-12 or at
the university level. Proposals should be comprehensive, addressing
instructional materials, in-service training, and distribution
mechanisms in addition to hardware. Of particular value are products
that simulate actual or proposed *in situ* instrument payloads. The
latter might be distributed with corresponding simulants of planetary
material, and could be coordinated with mission activities.

## 22.06 Instruments for Exobiology  {#instruments-for-exobiology .unnumbered}

Lead Center: ARC

Exobiology seeks to understand the origin and evolution of life and
life-related processes and materials throughout the universe. This
requires a specialized cadre of advanced analytical instruments and
systems for future solar system exploration missions. In light of a
pending sample return, Mars is of special interest for both Earth-based
laboratory applications as well as flight experiments. New analytical
devices must be highly accurate and precise while performing meaningful
analyses on very small samples containing exobiologically-important
elements (C,H,N,O,P, and S) and their compounds, e.g., H2O, NOx, CH4.
Typically, advanced instruments would identify and measure
biogenically-important chemical and elemental components of
extraterrestrial atmospheres, soils, ices, sedimentary rocks, and
minerals, e.g.,evaporites, clays, and silica, cometary materials.
Miniaturization and other techniques to decrease hardware complexity and
increase flight capability of the devices or systems for efficient use
of spacecraft resources is paramount. Examples include, but are not
limited to, the following:

-   Gas chromatographs, including innovative detectors, columns, and
    samplers, for identification and detection of gases and organic
    compounds at parts-per-billion levels.

-   Infrared reflectance and transmittance spectrometers and subsystems
    to conduct molecular spectrometry of extraterrestrial surface
    samples and to identify and measure the C, O, and N isotopes
    contained in CO2 and NOx with precision of 0.1 % or better.

-   Electrochemical or other elemental and geochemical devices or
    sensors to sensitively measure composition of single or multiple
    extraterrestrial surface and atmospheric components, e.g., H2O, CO3.

-   Novel or advanced chemical analyzers, e.g., ion mobility
    spectrometers, Raman spectrometers, for molecular analysis of
    nanogram or smaller quantities of exobiologically-important
    molecules.

-   Remotely-operated device which illuminates and provides full color
    images of rocks and soils with magnification range of 2-100x.

-   System for obtaining and delivering representative extraterrestrial
    materials e.g., Mars soils, from a minimum depth 1 meter for return
    to Earth.

    Containment systems for returning the extraterrestrial materials
    samples (atmosphere, evolved gases, rocks, particulates or dust, and
    core sections are all desired) to Earth after collection. Such
    systems must isolate and maintain pristine (uncontaminated) samples
    with retained volatile during handling and transit to Earth. Forward
    and backward biological isolation of the sample is critical.

# 23 Spacecraft Miniaturization Technologies  {#spacecraft-miniaturization-technologies .unnumbered}

A renewed thrust to reduce cost and enhance science missions can be
achieved with revolutionary advances in miniaturization over traditional
spacecraft systems. Micro (10 Kg) and nano-satellites (\<10 Kg) of all
varities will enable new missions that are currently impractical.

## 23.01 Near Earth Nano-Satellite Technology  {#near-earth-nano-satellite-technology .unnumbered}

Lead Center: GSFC

It is scientifically desirable to fly one hundred nano-satellites in a
constellation to make multi-point measurements of key physical processes
between the Sun and Earth. The successful development of these
nano-satellites will enable a class of lightweight, low power, low cost,
high technology science missions, capable of making both in-situ and
remote onboard measurements. Each nano-satellite will be fully
functional and weigh a maximum of 10 kg, which includes all onboard
propellant mass. As a reference, the nano-satellite should be considered
a cylindrical spacecraft with dimensions on the order of 30 cm diameter
by 10 cm high. The recurring cost goal for manufacturing and testing
these nano-satellites is less than \$500K each, such that one hundred
nano-satellites can be produced within a cost cap of \$50M. It is
expected that all onboard electronics survive a radiation total dose
rate of 100K rads over a 2 year mission lifetime. Proposed concepts in
the following technology areas will be considered:

-   Advanced, miniaturized propulsion thrusters and/or feed system
    components for both orbital maneuvers and attitude control, with
    associated control electronics operating at 3.3 V and power
    consumption \~ 1 W.

-   Solutions for high levels of electronics integration, in order to
    effectively combine spacecraft subsystem electronics and instrument
    electronics into the smallest possible mass, power, and volume.

-   Onboard RF communications electronics capable of transmitting data
    to the ground and receiving ground commands from a distance of 3-5
    Earth radii. A reasonable target total mass is 0.5 kg and power
    consumption is 500 mW, with a data transmission rate of 10 Kbps and
    a command rate of 1 Kbps. It is expected that the tracking system be
    coupled with this communications subsystem, so to maximize
    efficiency in mass and power.

-   Methods for providing complete autonomous operation - deployment,
    operational state configuration, position determination, downlink
    transmission, and reconfiguration to accommodate changes in
    performance.

-   Inter-satellite communications techniques for a constellation of
    satellites.  The communications protocol must handle unique
    challenges of multiple path artifacts, such as duplicate messages
    and stale messages. Inter-constellation communications will be used
    to alert other elements of the constellation of significant events,
    to coordinate the operations of the constellation (e.g., station
    keeping) and to relay data from elements of the constellation to the
    ground.

-   Innovative data management and visualization techniques to handle
    data from dozens or hundreds of identical spacecraft.  The data
    includes the downlink data, and also other data associated with the
    operation - data bases of command and telemetry parameters, tracking
    data, flight software loads, command loads, and acquisition data.
    This data must be managed and presented to operators in a manner
    that prevents confusion.

-   Lightweight, efficient solar array panels that minimize the
    effective array mounting area required.

-   Lightweight, high output battery cells which can be space qualified.

-   Lightweight yet strong composite structural materials that may also:
    provide thermal control, serve as an effective electronics ground
    plane, and provide some radiation shielding for electronics.

-   Low cost manufacturing techniques that satisfy the cost goal stated
    above.

## 23.02 Deep Space Microspacecraft Subsystems 

Lead Center: JPL

The strategic plan within the Office of Space Science at NASA calls
forintense exploration of a wide variety of bodies in the Solar System
within a modest budget. To achieve this will require revolutionary
advances over the capabilities of traditional spacecraft systems and a
broadening of the toolset through the introduction of new kinds of space
exploration systems. Microspacecraft systems (as small as \~10kg, \~10W,
or less) of all varieties will enable new missions that are currently
impractical. These systems will include, but are not limited to,
orbiters, landers, atmospheric probes, rovers, penetrators, aerobots
(balloons), planetary aircraft, subsurface vehicles (ice/soil), and
submarines. Also of interest are delivery of distributed sensor systems
consisting of networks of tiny (\<\<1 kg) individual elements which
combine sensors, control, and communications in highly integrated
packages, and which are scattered over planetary surfaces, atmospheres,
oceans, or subsurfaces. New technology is needed in all spacecraft
subsystem areas, as well as new areas to address this diverse set of
needs.

Applicable technology areas include, but are not limited to:

-   Miniaturization and/or power reduction in all spacecraft subsystem
    areas with application in a variety of harsh environments
    (temperature, radiation, mechanical shock, etc.).

-   Avionics, including highly integrated \"systems on a chip\".

-   Propulsion, including chemical and other techniques, also including
    techniques for machining / manufacturing ultra small parts, and
    materials joining technologies for microtubes and mini/micro
    components.

-   Power Generation and Management, including isotope power, and solar
    power, and miniature power electronics.

-   Energy Storage, including primary and secondary batteries, fuel
    cells, and other approaches.

-   Thermal Management, including active and passive techniques.

-   Integration of functions such as engineering sensors and science
    instruments, structure, thermal, cabling, propulsion, etc.

-   Advances in atmospheric entry systems including ultra-lightweight (a
    few percent of entry mass) aeroshell technologies, and lightweight
    pressure vessels which support external pressures of 100+ bars in
    harsh environments (chemical, radiation, temperature, etc.).

-   Advances in techniques and devices for relay communications through
    atmospheres, ice layers, soil, and oceans.

-   Methods and devices for orientation knowledge, navigation,
    locomotion, autonomy, and control of microspacecraft systems in/on
    planetary atmospheres, surfaces, subsurface, and submarine
    environments.

# 24 Intelligent Systems  {#intelligent-systems .unnumbered}

The development of Intelligent Systems technologies addresses key
strategic technical challenges facing NASA, including the reduction of
mission costs, the continuing return of high quality science data
through constrained communications bandwidths, and the launching of a
new era of exploration, characterized by a sustained presence and
in-depth scientific studies. Automated reasoning for autonomous systems
will be applied to both the engineering and science elements of
exploration missions to provide a more robust closed-loop spacecraft
capability. Human-centered computing concepts will be used to optimize
the performance of human-machine systems during all aspects of the
design, development, and operational phases of these missions. Data
management techniques will be applied across the spectrum, from
understanding and mining NASA's huge data sets to directing data
acquisition intelligently at the remote platforms and instruments.

## 24.01 Automated Reasoning for Autonomous Systems  {#automated-reasoning-for-autonomous-systems .unnumbered}

Lead Center: ARC

NASA is planning to fill space with robotic explorers, carrying our
intelligence and our curiosity, to explore the universe beyond in ways
never before possible. To survive decades of operation, these remote
agents need to be smart, adaptable, curious, wary, and self-reliant in
harsh and unpredictable environments. NASA is soliciting research in
automated reasoning for autonomous systems that will enable the design,
construction and operation of a new generation of remote agents that
perform progressively more exploration at much lower cost than
traditional approaches. To achieve ambitious exploration goals,
researchers must develop autonomous control kernels that can be
commanded by simple, high-level, goal-directed behaviors, such as \"make
an attitude determination followed by a course correction\". These
mechanical explorers will be programmable through compositional,
commonsense models of hardware and operations behavior. This model-based
programming paradigm will allow control systems of spacecraft to be
plugged together like lego blocks from libraries of existing models, and
will permit novel behaviors to be programmed in a simple intuitive
manner. Using these models onboard, the automaton will close the loop on
sensor information at the goal level, using advanced deductive planning
and execution, scheduling, diagnosis and recovery capabilities to ensure
that goals are being met. This goal-directed, model-based programming
paradigm is already beginning to emerge through systems like the Deep
Space One Remote Agent Architecture.

Achieving capable intelligent robotic explorers will also require
systems that learn from their interactions with their environment and
adapt in real-time, by using model-based deductive methods to help
coordinate and direct collections of biologically-inspired adaptive
methods. Remote agents will need to be curious and wary, requiring
capabilities for taking action to gain information, assessing risk,
planning contingencies and preparing backup resources, or redirecting
plans to reduce risk. Finally, these automaton will often act as teams,
requiring significant distributed coordination and collaboration
capabilities. Specific areas of interest for automated reasoning include
the following:

**Remote Agent Architectures**

-   Architectures for onboard operation that support goal-directed
    commanding, model-based programming, and the plug and play of
    automated reasoning components.

-   End to end architectures that provide a seamless coupling of
    automated reasoning capabilities for flight and ground operations,
    and that support easy migration from ground to flight.

-   Single and multi-agent architectures that allow the level of
    autonomy to be easily, precisely and dynamically adjusted.

-   Architectures that use automated reasoning to coordinate intelligent
    design synthesis and science opportunity analysis.

    **Planning, Scheduling, and Resource Management**

-   Planning and scheduling systems that use component-based models to
    support plan generation and dynamic replanning concurrent with
    execution.

-   Advanced planning and scheduling systems that support any-time
    generation of flexible plans, goal-prioritization, resource
    optimization, contingency, and sensor-based, iterative and adaptive
    planning.

-   Centralized and decentralized methods for generating plans by
    coordinating a heterogenous set of special purpose planners.

    **Executives**

-   Goal-directed systems for plan and command sequence execution.

-   Procedural executives with services for configuration management,
    resource management and plan running.

-   Model-based executives that perform significant deduction within the
    reactive control loop, and hybrid procedural/deductive executives.

-   Distributed, multi-agent execution capabilities.

    **Fault Protection and Model-based Reasoning Systems**

-   Model-based and statistical methods for monitoring, command
    confirmation, fault isolation, and diagnosis from sensor
    information.

-   Model-based reasoning and planning methods for robust recovery &
    repair, including establishment of a safe operating state as a
    minimal goal, and preservation procedures from models.

**Reasoning Kernels**

-   Algorithms for high performance deduction and search in real-time,
    including any-time, systematic and stochastic search algorithms and
    incremental truth maintenance systems.

-   Methods for efficiently abstracting, approximating and compiling
    models.

-   Decision theoretic and adaptive reasoning kernels.

**Large-scale, Declarative Modeling and Software Engineering
Environments**

-   Unified languages for model-based programming and declarative
    specification of software and hardware behaviors.

-   Collaborative environments for large scale model building,
    specification and reuse. Methods that operate on these declarative
    models/specifications include document generators, visual debugging
    environments and automated modeling algorithms.

-   Advanced techniques for process support, requirements engineering
    and reverse engineering.

-   Methods for code synthesis and controller generation from
    declarative specifications and models.

-   Tools for automatically generating high fidelity, fault injection
    from component-based models.

-   Automated generation of test sequences from component models, and
    analytic verification methods, including model checking and theorem
    proving.

-   Methods for modeling, code synthesis, simulation, testing and
    validation, as above, that operate from hybrid discrete/continuous
    models.

##  {#section-14 .unnumbered}

## 24.02 Human Centered Computing  {#human-centered-computing .unnumbered}

Lead Center: ARC

Human-centered computing, an approach to the design and implementation
of computer systems, seeks to integrate computational systems with human
performance and capabilities, such that the total system amplifies,
corrects, and leverages the capabilities of both people and machines.
Aerospace missions, including the human exploration of space, combine a
high degree of automation with often unique system complexity and
substantial risk to human lives. The design of computer systems
necessarily must take into account not only how people will
\"interface\" with the systems, but fundamental aspects of human
perceptual-motor coordination, cognitive operations, and group dynamics.
Human-centered computing focuses on the \"delta\" that respects the
particular contributions of humans and machines, designs machines and
operational procedures to complement each other, and exploits the
understanding of the differences between people and machines to build
more capable computer systems. To advance along these lines, proposals
are sought in the following areas:

-   Advanced AI systems/architectures for mixed-initiative system
    planning, monitoring, and control, with provision for crew
    oversight. Architectures that have predictable behaviors, leave
    people in control, and expose their workings in ways comprehensible
    to people with different skills.

-   \"Cognitive prostheses\" that qualitatively change the capabilities
    of human perception, pattern analysis, scientific domain modeling,
    reasoning, and collaborative activity. Such tools could incorporate
    any of a variety of modeling techniques such as knowledge-based
    systems and neural networks, and fit tool operations to ongoing
    human physical interaction, judgment, and collaborative activity.

-   Information technology enabling comprehensive sharing of
    project-related information and data, which supports intelligent
    organization, access, and presentation of the information.
    Particularly, tools that fit the human activities of scientific
    inquiry and engineering design, and relate the contributions of
    individuals to the developing plans and products of teams.

-   \"Knowledge management\" tools that relate technical models of human
    knowledge to: a) nonverbal concepts and perceptual skills, b) the
    daily activities of workers, including especially how databases are
    actually used in practice, c) informal on-the-job learning, and d)
    the career trajectories of novices, experts, and retiring employees.

-   Agent-based tools for information gathering, reminding, and
    alerting; job performance aids that provide cognitive assistance in
    the context of the daily activities and interests of operations
    personnel and crew.

-   Communication technologies and software tools that enable mission
    control teams to work together when they are located at different
    sites and working on several projects.

-   Tools for software requirements analysis that incorporate and relate
    models of databases, legacy systems, and work practices.

-   Workflow systems that allow teams of users to formalize and
    routinely reconfigure their own document templates, processing
    categories, operating procedures, and archival records.

-   Software systems that provide specialized support for collaborative
    science and engineering tasks, including design, data collection,
    experimentation, analysis, and model construction to enable
    scientists and engineers to collaborate as part of distributed
    project teams at physically separate sites.

-   Computing architectures that address the limitations of
    knowledge-based systems and neural networks, relative to human
    capabilities, advancing the state-of-the-art in automated perceptual
    categorization, non-verbal conceptualization, and coordination
    across multiple sensory modalities. Applications might include
    planetary probes and rovers with new kinds of instrumentation,
    signal processing, and sensing-through-movement.

-   Visualization tools combining \"virtual reality\" projection with
    actual objects in the environment, conveying information about
    object identity, part relationships, and assembly or operational
    procedures.

## 24.03 Data Analysis and Visualization  {#data-analysis-and-visualization .unnumbered}

Lead Center: GSFC

All NASA projects will face the daunting prospect of having to deal with
databases of unprecedented size and complexity. We must develop
techniques for electronic documentation, electronic process control,
massive distributed databases, intelligent archiving and retrieval, and
data analysis and visualization. NASA is soliciting technologies to
perform a wide range of functions including:

-   Automatic data calibration and validation.

-   Data viewing and real-time data browse.

-   Automated planning of image product generation.

-   Natural language interfaces for user to develop high-level queries.

-   Analyze historical and/or online ESE sensor data to detect
    anomalies, identify unexpected values or trends, and detect and
    classify events automatically.

-   Integrate several types of modeling algorithms and directly
    interface with both UNIX and Windows NT relational database
    management systems.

-   Rapidly implement the resulting modeling in an online application
    from within the data modeling environment.

-   Automated, computationally efficient procedures for rendering from
    CAD/CAM files.

-   Representation and manipulation of multidimensional and
    hyperspectral data.

-   Automatic image data retrieval based on content.

-   Softbots and agent-based problem solvers to provide answers to high
    level inquiries.

-   Use of sonification in scientific data analysis.

-   Automation of project process information storage and retrieval.

-   Image data mining \-- tools to provide rapid access to objects of
    interest within image databases, query by content, example, or
    sketch, user interfaces to support query specification and
    refinement, database strategies.

-   Trainable object recognition.

-   \"Intelligent\" (goal-directed) data acquisition and/or compression.

-   Active vision.

-   Parallel processing and real-time vision/recognition.

-   Integration of information from multiple sources such as independent
    databases and real-time sensors.

-   Content-based queries of large, geographically distributed
    collections of images (e.g., as found on the Internet).

-   Automatic image registration and change detection.

-   Automatically analyze historical and/or online ESE sensor data to
    detect anomalies, identify unexpected values or trends, and detect
    and classify events.

-   The environment must integrate several types of modeling algorithms
    and directly interface with both UNIX and Window NT relational
    database management systems.

-   An additional key requirement is to be able to rapidly implement the
    resulting modeling in an online application from within the data
    modeling environment.

## 24.04 Data Understanding and Adaptive Methods  {#data-understanding-and-adaptive-methods .unnumbered}

Lead Center: JPL

NASA now collects terabyte-scale datasets routinely from its missions,
and charges the scientific community with extracting usable and
scientifically relevant information from them.  These datasets may be
planetary or stellar images, multispectral images, or field and particle
event-lists.  They may also be engineering time series about spacecraft
health collected from on-board sensors. In addition to the ongoing
challenges entailed by handling, analyzing and mining very large data
sets in archives, NASA now also needs a new framework for performing
science data evaluation onboard spacecraft. The future NASA mission set
will feature smaller and more numerous spacecraft in an environment of
highly constrained uplink and downlink communications, requiring
substantial onboard intelligent computation to achieve its goals. New
onboard science capabilities will enable mission activities to be
directed by scientists without the assistance of a ground sequencing
team, robust capture and redirection in making discoveries at the target
body, accommodation of the realities of constrained communication links,
and the continued return of quality science products from missions.

Through onboard decision-making, scientist-trained recognizers, and
judicious use of knowledge discovery methods, a portion of the
scientist\'s awareness can be projected to the space platform, providing
the basis for scientist-directed downlink prioritization and the
processing of raw instrument data into science information products.
This software-based partnership between scientist and space platform can
evolve during the mission as the scientist becomes increasingly
comfortable with the direct relationship with the space platform,
intermediate scientific results emerge, and scientist-directed software
updates are uploaded. This subtopic enlists help in developing a new
generation of tools and algorithms for effective acquisition and
analysis of data and image sets, appropriate for ground or onboard use.
Of special interest are: (1) the ability to deal quantitatively with
uncertainty present in data, perhaps in a statistical framework; (2)
development of flexible models through which observables are linked to
quantities of scientific or engineering interest; (3) harnessing
database technology for organizing the observed data, models, and
inferred knowledge, perhaps in onboard archives, and (4) system concepts
for handling interactions between onboard science analysis and event
detection capabilities and other functions of an autonomous spacecraft.
One or more of these areas should be addressed by every proposal.
Specific technical topics of interest include:

-   Automated classification of data.

-   Supervised and unsupervised learning methods.

-   Knowledge discovery techniques.

-   Image analysis and segmentation.

-   Statistical pattern recognition.

-   Time-series feature extraction and analysis.

-   Trainable object recognition.

-   Automatic image registration and change detection.

-   Spatiotemporal data mining.

-   Automated planning of image and data product generation.

-   \"Intelligent\" (goal-directed) data acquisition and/or compression.

-   Science data analysis algorithms designed for scalable computing.

-   System concepts for onboard science.

# 25 Telerobotics  {#telerobotics .unnumbered}

NASA seeks innovations in the field of telerobotics that will improve
remotely controlled robotic operations capabilities for future planetary
exploration and Space Station missions. Space telerobotics technology
requirements include teleoperated and automated control of
non-repetitive tasks, sometimes with significant time delay between
operator control and manipulator action. Flexible manipulators will
perform complex tasks in a dynamic space environment using novel
locomotion, and having the ability to recover from unplanned events.One
goal is that by the year 2004, 50 percent of the EVA-required operations
on orbit may be conducted telerobotically. Specific areas where
innovation is sought include long term survivability of robotic systems,
machine intelligence (sensing, perception, planning, and reasoning),
sub-surface exploration, robotic dexterity, and navigation capabilities
of on-orbit and planetary systems.

## 25.01 Robotic Systems Including Perception, Planning, and Analysis  {#robotic-systems-including-perception-planning-and-analysis .unnumbered}

Lead Center: JPL

Innovative technologies are sought to support robotic exploration of
solar system bodies by intelligent, low power, and low weight robotic
systems. Advanced mobility and manipulation systems are needed as well
as their on-board and ground-based sensing, perception, planning and
reasoning systems.

-   Microrover (less than 30kg) and nanorover (less than 1kg) related
    technologies are needed to support planetary surface exploration
    over rugged terrain. Surface mobility concepts under consideration
    include walking machines, wheeled rovers, unique suspension systems,
    hybrid locomotion, and hopping/jumping machines.

-   Technologies are needed to support exploration in shallow and deep
    locations below the surface and underwater.

-   Aerobot technologies will support exploration in the atmospheres of
    Venus, Mars, Titan and the outer planets including high (740 K)
    and/or low (75 to 200 K) temperatures and extreme pressures (100
    bars). Technologies include: gondola instrument pointing and
    attitude control to optimize stereo imaging for 3D surface
    reconstruction and analysis; on-board perception for relative and
    absolute position determination; and altitude control, lateral
    mobility, and path planning techniques and systems.

-   Technologies for manipulation from rovers, landers and underwater
    vehicles are needed.

-   Component mechanism technologies to support planetary robots are
    needed, such as low-mass high-torque actuators, collapsible wheels
    and structures, legs, and lightweight manipulators and masts.

-   Miniature sensors are needed such as stereo cameras, Sun-based
    location sensors, and integrated multi-functional sampling
    mechanisms.

-   Earth-based perception, planning, and analysis technologies are
    needed to enable distributed planning of resource constrained
    missions. Scene analysis will assist in localization, task
    selection, and path planning. Internet-based stereo visualization
    will enhance scientific understanding of the scene.

-   On-board perception and planning technologies are needed including
    science data analysis, target selection, near and distance feature
    identification, visual servoing of instruments to targets, path
    planning, autonomous navigation, multi-sensor fusion, and fault
    detection and recovery.

    Sensing and perception and planning to provide both the capability
    to function under a variety of conditions without human intervention
    and provide a means for efficient interaction with the human when
    needed. These approaches may include capabilities for:

-   Situation assessment, response planning and associated sensing and
    environmental modeling;

-   Natural language understanding and language planning as a modality
    for efficient interaction;

-   Plan representation which integrates functionally with language
    understanding and planning to support instrutability;

-   Improved safety and reliability of plans and plan execution based on
    innovative architectures, sensing methods, plan representation
    techniques, etc.;

-   Support of simultaneous deliberative planning and safe real time
    action, including reaction to insure safety.

    Operation of the ISS will require the ability to view the outside of
    the station from user selected viewpoints as required by a variety
    of external maintenance jobs. Since locations at which cameras can
    be mounted on station are limited, a flying camera controlled by the
    crew is of particular interest. One of the enabling technologies for
    such a camera is a light weight, low power sensor/system that
    provides relative navigation with respect to the station without
    requiring the addition of external markers, antennas or other
    extensive exterior modifications.

-   Optical Correlation pattern recognition, particularly in hardware
    implementation and algorithm development.

## 25.02 Telerobotic Servicing  {#telerobotic-servicing .unnumbered}

Lead Center: JSC

Proposals are solicited for innovative concepts which will increase the
capabilities for robotic systems to perform servicing of space systems
while minimizing the workload to EVA and IVA astronauts, and ground
operators. Technologies that will improve worksite efficiency with tools
and fastening systems, expand the range of servicing tasks beyond box
ORU replacement, improve operator efficiency with advanced displays and
control systems, and offload on-orbit servicing to ground based
operators are sought. Specific technology requirements include the
following:

-   Ground-based control technology for space-based robots which is able
    to compensate for time delays of several seconds without move and
    wait strategies.

-   Ground-based real-time simulations that contain methods for
    calibrating and synchronizing with space-based robotic worksites
    through video or other sensor information.

-   Supervised and traded control systems which allow for seamless human
    interaction. The ability to accommodate both planned and unplanned
    human and autonomous operations within a task are essential.

-   Space system maintenance planning tools, and individual ORU
    maintenance task planning and execution tools.

-   Target and non-target based identification and acquisition of ORUs.
    Ability to operate robustly in the adverse lighting conditions of
    space is essential.

-   Tools and fastening systems that accommodate both EVA astronauts and
    servicing robots well and improve the time to remove and replace
    ORUs. Smart sensor-guided tools that provide higher precision or
    lower contact forces are one potential approach toward this
    objective.

-   An electrically operated robotic arm suitable for handling
    moderately heavy payloads from a mobile vehicle in a hazardous
    environment. Unit should be suitable for use in a Class One,
    Division One, Group A environment.

## 25.03 Tele-Operations/Virtual Environment {#tele-operationsvirtual-environment .unnumbered}

Lead Center: ARC

Innovative hardware and software are needed for using virtual
environments techniques and technologies to enhance teleoperations
applications. Teleoperations, in this context, includes telerobotics,
telescience, telepresence, and distributed, collaborative virtual
environments. Application areas include flight and ground operations
development, analyses, training, and support. Areas in which innovation
are solicited include the following:

-   Internet-based interactive command generation and display
    technologies for distributed collaborative on-orbit and planetary
    robotics applications. Examples include integrated voice,
    videoconferencing, planning tools and visualization, stereo
    visualization, and mission simulation and Internet securuty.

-   Immersive multi user and collaborative virtual environments that
    include high fidelity visual image generation and haptic feedback.
    Haptic feedback includes physics based systems capable of simulating
    dynamic six degree of freedom force and motion interactions based on
    inertial properties.

-   Body ported telescience operational support systems for stand-alone
    and collaborative in situ activities.

-   Functionality would include multimedia procedural and reference
    support; two way data, video, and audio communications; and
    efficient user interfaces that facilitate intensive manual
    activities.

-   Cost effective payload training systems in standalone and
    distributed, collaborative virtual environments for both individual
    payloads and multiple payloads integrated into a space station
    environment. These systems would include remote interaction with
    high fidelity hardware/software simulators. Focus areas include
    cognitive operational and science discipline training as well as
    gross and fine motor manipulative skills training

# 26 Communications  {#communications .unnumbered}

All NASA missions rely on telecommunications for their successful
completion. NASA develops innovative communications technologies for its
own use and collaborates with US industry in the development of
commercial technologies that have the potential to satisfy NASA system
needs. To fulfill these goals, NASA conducts a program of research and
technology at the device, subsystem and system level in such areas as
microwave, millimeter wave, and optical communications; digital
processing, modulation, and coding; communications architectures,
networks, and system protocols.

## 26.01 RF and Optical Communications for Deep Space Missions  {#rf-and-optical-communications-for-deep-space-missions .unnumbered}

Lead Center: JPL

NASA\'s goals for future interplanetary missions require advances in
higher-capability, smaller, and more power-efficient spaceborne
telecommunications. Due to the enormous distances from Earth, design of
these systems imposes unique challenges for transmitter sources with
higher effective isotropic radiated power (EIRP) and higher receiver
sensitivities, while maintaining low power consumption and low system
mass. Technology options being considered include improved radio
frequency and optical communication systems. Additionally, sensors being
planned for future Earth-orbital missions will produce significantly
higher data rates as well. For these missions, the limitations on
communications come not from physics, but from limits on RF spectrum
allocation. To circumvent this limitation, NASA is developing
high-data-rate laser communication systems. Data rates up to several
Gbps can be transmitted from Earth-orbit-to-ground, or via space-space
relay.

Areas in RF communications where innovations are sought include:

-   Modulation and coding techniques and network designs for deep-space
    communications that reduce cost, spacecraft power and mass,
    bandwidth and operations requirements.

-   Ultra-small, low-cost, low-power, deep-space transponders and
    components. Including low-voltage and high-efficiency integrated
    circuits such as microwave monolithic integrated circuits (MMICs)
    and MMIC filters. Signal-processing circuits for receivers that
    provide carrier tracking, command and ranging capabilities.
    Low-voltage, multi-function MMIC designs with integrated filters to
    provide low-noise down-conversion, automatic gain-control,
    up-conversion, and transceiver functions at Ka-band (32 GHz). MMIC
    modulators to provide large linear phase modulation (above 2.5
    radians), high-data rate BPSK/QPSK modulation at Ka-band. Miniature,
    ultra-stable oscillators for deep space communications and GPS
    applications. Miniature, low-loss X-band (8.4 GHz) and Ka-band
    switches and diplexers.

-   Low-mass, high-gain, high-efficiency antennas typically with
    diameters less that 2 meters, integral with spacecraft surfaces, or
    that can be reliably stowed in low volumes.

-   Photonic technologies that permit new and more efficient ways to
    implement RF communications and phased-array systems including
    components and techniques applicable to i) optical-RF signal
    distribution systems, ii) optically controlled transmit-receive
    modules, iii) optical beam-forming networks, iv) optical samplers,
    modulators, detectors, mixers and RF-locked semiconductor lasers.

    Also of interest to the RF communications system development is:

-   Miniature, high-efficiency power amplifiers and RF power devices
    operating in the X- or Ka-band, transmitters with output power
    levels ranging from 3 watts to 20 watts, and both innovative
    solid-state as well as thermionic devices that can survive the space
    environment with mean-time-to-failure of ten years or more. MMICs
    supporting miniature, high-efficiency power amplifiers at Ka-band
    (primary focus) and X-band (secondary focus) such as gain blocks,
    multi-bit digital phase shifters and power cells. Support elements
    like low-loss, miniaturized isolators, high-efficiency integrated
    DC-DC power converters, and miniaturized power dividers and
    combiners. Advanced packaging concepts and techniques for the
    packaging and miniaturization of high-efficiency power amplifiers at
    X- and Ka-band.

    For optical communication systems, innovative concepts are solicited
    for space-based applications in the following areas:

-   Ultra-lightweight, baffled, thermally stable diffraction-limited
    telescopes.

-   Efficient, space-qualifiable, lightweight diode and diode-pumped
    lasers and/or laser driver-modulators.

-   High-speed (equal to or greater than 1.0 GHz) modulators for
    diode-lasers with more than 200 milliwatts of output power.

-   Acquisition, tracking, and pointing techniques that reduce mass,
    power and complexity.

-   Focal-plane-array detectors with built-in (on-chip) processing
    and/or focal plane arrays combining redundant CCD and QAPD sensors.

-   High-speed, high quantum-efficiency, very low noise FPA\'s (eg. CCD,
    APS, CID) with large field of view ( 5 mrad) and small pixel sizes
    (eg. CCD, APS, CID) with large field of view (\> 5 mrad) and small
    pixel sizes (\< 20 micron).

    Also interested in infra-red (1 - 2 micron) FPAs:

-   Lightweight, low-power, two-axis, mechanical and non-mechanical beam
    steering devices with steering ranges greater than 1 degree.

-   Optical phase-control devices.

-   Narrow-band (0.1 Angstrom), high-throughput (more than 0.60) optical
    filters.

-   Lightweight stray-light control concepts.

-   Power-efficient modulation and coding systems.

    Also of interest for optical free-space communication are
    technologies to enable low-cost ground reception systems including:

-   Low-cost optical telescopes (photon-buckets) from 3 to 10 meters in
    diameter.

-   Low-cost 1-m diameter optical telescopes that can accurately track
    Earth-orbiting satellites.

-   Ultra-narrow-band (0.01 to 0.5 Angstrom) optical filters.

-   Adaptive-optics systems to mitigate the effects of atmospheric
    turbulence.

-   Innovative concepts for low-cost telescope mounts and enclosures.

-   High-efficiency, high-speed, optical detectors and detector
    amplifiers. Also highly efficient, integrated detector amplifiers
    with bandwidths greater than 1 GHz and large optical signal
    collection diameters.

-   Clock and data signal recovery assemblies with 20 dB input signal
    dynamic range and update dates of 1 kHz.

## 26.02 RF and Optical Communications for Earth Satellites  {#rf-and-optical-communications-for-earth-satellites .unnumbered}

Lead Center: LeRC

Innovations are sought for application to commercial satellite
communications and NASA missions. Advanced techniques and products
(radio frequency and optical) are invited that support commercial low,
medium, and geostationary Earth orbiting (LEO, MEO, GEO) satellite
networks for integrated, fixed, transportable, and mobile broadcast
and/or wireless communications and information services. Innovations are
expected to offer significant improvements in performance, weight, power
efficiency, reliability and/or cost. Products are sought in the
following areas:

-   Software/hardware technologies to enhance Internet applications,
    videoconference, multimedia and video distribution techniques and
    applications over satellite networks. Innovative approaches to
    software simulation tools for rain fade compensation and for
    evaluating the effects of mutual interference between space and
    terrestrial wireless systems.

-   Wide scan angle (+/- 60 deg), low profile, transmit/receive Ka-band
    antennas, Ku/Ka band transceivers and closed-loop
    acquisition/tracking algorithms for aeronautical communication
    satellites.

-   Vacuum and solid-state electronics amplifiers with improved
    performance at frequencies up to 100 GHz including ancillary
    technologies such as electron emission, computer-aided design and
    electronic materials and device characterization that are required
    in the development of microwave power modules, vacuum
    microelectronic devices, traveling wave tubes and MMICs

-   RF components and sub-systems based on Si and SiGe or novel
    materials such as ferroelectrics, diamond films and high-temperature
    superconducting films or utilizing microfabrication techniques

-   Bandwidth and power efficient single or multi-channel digital
    modems; aggregate rates from 100 Mbps to 1.2 Gbps; single chip or
    chip set integration; and novel robust coding schemes for high
    performance data links and next generation data on demand systems.

-   Innovative application of critical on-board satellite signal
    processing, switching and routing functions for 100 fold increase in
    capacity with no increase in mass and power.

-   Latency-tolerant data communication protocols and enhanced
    Asynchronous Transfer Mode (ATM) and related network technologies
    for interoperable space-terrestrial networks. Data protocols for
    LEO/MEO networks.

-   Low cost, Ka-band flat plate array antennas, 2 watt Ka-band, MMIC
    power amplifiers and low noise block down-converters for USAT
    applications. Low cost, precision tracking Ka-band earth terminals
    for high data rate (OC-3 to OC-12) direct to-Earth downlinks from
    LEO/MEO spacecraft.

-   Novel system designs and advanced optical technologies are needed to
    enable efficient ultra high data rate communications on
    space-to-space, space-to-ground, and/or ground-to-space links for
    GEO or non-GEO satellite networks. Areas of interest include
    lightweight, low cost and thermally stable telescopes; efficient,
    high power (1 W) semiconductor diode lasers and arrays; high
    bandwidth modulators and detectors; techniques to mitigate the
    effects of atmospheric attenuation/turbulence and methods to reduce
    mass, power and complexity of the acquisition/tracking/pointing
    process.

-   Software/hardware technologies to enhance configuration management,
    performance monitoring, fault isolation, and security of data
    communications networks involving satellite links integrated with
    terrestrial networks.

-   Low cost, hand-held transceivers/display units capable of receiving
    only, transmitting only, and both receiving and transmitting
    satellite-relayed disaster-related warning or mitigation information
    broadcast over special frequencies allocated for emergency and
    weather use.

-   Very low weight, high data rate, mobile communications and data
    compression technologies suitable for use in conjunction with remote
    sensing instruments placed in Unmanned Aerial Vehicles (UAVs) and
    supporting real-time transmission of video and multi-spectral images
    back to science investigators.

# 27 Instrument Optics Technologies  {#instrument-optics-technologies .unnumbered}

The continued need to reduce cost and improve performance of future
scientific payloads involving optical instrumentation requires
innovations in optical component design, materials, fabrication
techniques, metrology and control technologies encompassing the
electromagnetic spectrum from the gamma-ray region through the infrared.
These innovations are needed in support of future astronomy,
astrophysics, planetary and earth-observing missions which must be
downsized in mass, volume and cost while achieving significant
improvement in performance.

##  {#section-15 .unnumbered}

## 27.01 Optical Materials, Fabrication Techniques and Metrology  {#optical-materials-fabrication-techniques-and-metrology .unnumbered}

Lead Center: MSFC

Novel optical materials, specialized optical fabrication techniques, and
new optical metrology instruments and components for earth and space
based applications are needed, as follows:

-   Develop novel materials and fabrication techniques for producing
    ultra-lightweight mirrors, high-performance diamond turned optics,
    and ultra-smooth (2-3 angstrom rms) replicated optics that are both
    rigid and lightweight. Lightweight silicon carbide optics and
    structures are also desired.

-   Develop optics for focusing EUV and x-ray radiation, where
    reductions in fabrication time and cost are sought. Developments are
    also needed in the areas of surface roughness and figure
    characterization of EUV and curved x-ray optics, especially Wolter
    systems.

-   Develop novel materials and fabrication techniques for producing
    cryogenic optics. Testing techniques, including both full- and sub-
    aperture testing, for cryogenic optics are needed. Also desired are
    techniques for testing the durability of and stress in coatings used
    in harsh environments, particularly cryogenic optics.

-   Develop novel techniques for producing and measuring coatings and
    polarization control elements. Optical coatings for use in the EUV,
    UV, visible, IR and far IR for filters, beamsplitters, polarizers,
    and reflectors will be considered. Broadband polarizing- and
    non-polarizing cube-type beamsplitters are also needed.

-   Perform development related to fabrication of x-ray, gamma-ray, and
    neutron collimators that have the precision necessary to achieve
    arcsecond or sub-arcsecond imaging in solar physics and astrophysics
    when used in stationary multi-grid arrays or as rotating modulation.

-   Develop portable and miniaturized state-of-the-art optical
    characterization instrumentation and rapid, large-area
    surface-roughness characterization techniques are needed. Also,
    develop calibrated processes for determination of surface roughness
    using replicas made from the actual surface. Traceable surface
    roughness standards suitable for calibrating profilometers over
    sub-micron to millimeter wavelength ranges are needed.

-   Develop instruments capable of rapidly determining the approximate
    surface roughness of an optical surface, allowing modification of
    process parameters to improve finish, without the need to remove the
    optic from the polishing machine. Techniques for testing the figure
    of large, convex aspheric surfaces to fractional wave tolerances in
    the visible are needed.

-   Develop efficient, analytical, optical modeling and analysis
    programs capable of determining the ground-based and space-based
    performance of complex aberrated optical telescopes and instrument
    systems will be considered. Also, simple, well documented, flexible
    programs which generate commands to operate a numerically controlled
    polishing machine, given the tool wear profile and surface error map
    are desired.

-   Develop very low scattered light optical material thin film mirror
    coatings or mirrors for broad-band white light applications to
    planet detection space telescopes.

## 27.02 Light Control, Lasers and, Other Precision Sources  {#light-control-lasers-and-other-precision-sources .unnumbered}

Lead Center: GSFC

Lasers and electro-optic devices are required for Earth and Space
Science instruments. We are seeking for the following devices:

-   High power (\> 5W) fiber optic amplifers for use with single
    frequency or very narrow band spectroscopic sources in the 800-860
    nm and 930 - 950 nm wavelength ranges.

-   High power (\> 5W) semiconductor optical amplifers for use with
    single frequency or very narrow band spectroscopic sources in the
    800-860 nm and 930-950 nm wavelength ranges.

-   Tunable narrow band optical filters compatible with semiconductor
    and Nd host based lasers.

-   Tunable atomic vapor absoprtion filters compatible with
    semiconductor and Nd host based lasers.

-   Electrically efficient (\> 5%) ultraviolet lasers in the 300-350 nm
    wavelength range.

-   Efficient (\> 5%) tunable single frequency high power (\> 100 mW)
    fiber optic lasers.

-   Efficient (\> 30%) frequency doubling devices for low power (diode)
    lasers.

-   Techniques for producing smooth diamond mirrors and membranes for
    x-ray and IR beamsplitters and windows. For UV/IR systems:

-   desire a free-standing diameter of 2 inches or greater.

-   desire 1/2 to 1/4 fringe at HeNe (0.63 um) for operation longward of
    absorption (\> 6 microns wavelength).

-   desire 1/40 fringe at HeNe for operation from UV to mm.

-   Narrow-bandwidth acousto-optic tunable filters that can be tuned
    across large wavelength regions (\> 2 octaves) from the visible
    through the infrared (0.4 to 5.0 microns).

-   Continuous-wave high-resolution (narrow-line) infrared solid-state
    lasers that are tunable from 1.0 to 5.0 microns.

## 27.03 Diffractive Optics: Design and Fabrication Techniques  {#diffractive-optics-design-and-fabrication-techniques .unnumbered}

Lead Center: MSFC

New and innovative design tools, techniques and fabrication methods are
needed to fully exploit the inherent possibilities of diffractive optics
to reduce size weight and costs in optical systems and components. Areas
of interest include:

-   Generalized design software for kinoform diffractive optical
    elements with applications toward direct write electron
    beam-lithography, or photo-lithography fabrication techniques.

-   Design and modeling methodologies software for multilevel
    sub-wavelength structures.

-   New low-cost fabrication methods for producing diffractive optic
    elements.

-   High aspect ratio structures electron beam lithography fabrication
    techniques.

-   Metrology techniques for high aspect ratio (3:1) sub-micron
    structures.

-   Large aperture, with sub-micron feature size, diffractive optic
    fabrication techniques.

-   Innovations are sought in using analog spatial light modulators
    (SLMs) as diffractive optical elements for the control of light.
    Application areas in which analog devices and methods might be
    applied include spot generation for directing light waves to
    disparate destinations, active optics for dynamic correction of
    environmentally induced aberrations, spatial (rather than angular)
    addressing of optical memory, and compact and simple display of
    dynamic image information.

-   Large area (2cm squared) blazed diffractive optical element
    deposited on a curved surface with optical power for remote sensing
    computed-tomography imaging spectrometers in the visible and
    infrared.

-   Design and fabrication of diffractive optics for multi-wavelength
    operation. These could be elements that are useful for wavelength
    demultiplexing of white light passively illuminated scenes and/or
    for specialized spectrometry applications.

-   Diffractive optics for use in compact, lightweight instrumentation.

## 27.04 Optics Technologies for Space and Earth Observing Systems  {#optics-technologies-for-space-and-earth-observing-systems .unnumbered}

Lead Center: GSFC

The continued need to reduce cost and improve performance of future
scientific payloads involving optics requires innovations in optical
component technologies encompassing the electromagnetic spectrum from
the gamma-ray through the infrared. These innovations are to support new
astronomy, astrophysics, planetary- and Earth-observing experiments,
which must be miniaturized while compensating improvements in
capabilities. Aspects of instrument development that can benefit from
new technology cover the spectrum from optical system design and
modeling, through optical materials and thin-film coatings and their
characterization, to wavefront sensing and component and subsystem
testing. These need to be applied to integrated optical system
components such as spectrometers, hyperspectral systems, and diffractive
elements.

-   Improved optical techniques for image-motion compensation and image
    quality.

-   Fiber-optic routing of signals for communications, control, and
    metrology of optical instruments.

-   Use of small fiber bundles for sampling small fields of view and
    integral-field spectroscopy.

-   Novel techniques for producing high-performance, low-scatter,
    optical materials and coatings for use from soft X-ray through far
    IR in reflector, filter, polarizer, and beamsplitter applications.

-   Techniques for producing and mapping low-scatter, defect-free
    coatings for the EUV and soft x-ray regions.

-   High-accuracy measurements of refractive index at cryogenic
    temperatures.

-   Thin foil filters and proportional counter windows and
    high-throughput, rugged support meshes for the x-ray and EUV
    regions.

-   High-performance, diamond-turned optics and lightweight silicon
    carbide optics and structures are desired.

-   Techniques for producing smooth diamond membranes for X-ray and IR
    window applications.

-   Thin film technology for the soft X-ray through EUV spectral
    regions, including advances in high-throughput, low-scatter,
    defect-free coatings, and defect-mapping methodology, particularly
    for mirrors in the 13-nm region.

-   State-of-the-art optical characterization instrumentation for
    miniaturized components.

-   Novel optical system design and analysis software, particularly with
    regard to factoring in as-manufactured performance and programmatic
    parameters.

# 28 Interdisciplinary Technologies in Astrobiology  {#interdisciplinary-technologies-in-astrobiology .unnumbered}

Astrobiology is the study of the living universe. It provides a
scientific foundation for multidisciplinary studies of (1) the orgin and
distribution of life in the universe, (2) an understanding of the role
of gravity in living systems and (3) the study of the Earth\'s
atmospheres and ecosystems.

## 28.01 Technologies for Understanding the Origin, Evolution and Distribution of Life in the Universe  {#technologies-for-understanding-the-origin-evolution-and-distribution-of-life-in-the-universe .unnumbered}

Lead Center: ARC

Astrobiology studies on the emergence of living systems from molecular
chaos require technologies to search for extant or extinct life, to
obtain an organic history of planetaries bodies, to explore water
sources, and to distinguish microorganisms and biologically important
molecular structures within complex chemical mixtures. The search for
life on other planetary bodies will also require systems capable of
moving and deploying instruments across and through varied terrain to
access biologically important environments.

NASA seeks innovations in the following technology areas:

**Mobility Systems:**

-   Innovative techniques that meet these needs are required, e.g., for
    Mars, technologies that would enable or enhance the performance of
    long distance ground roving, tunneling, or flight vehicles and for
    Europa, technologies to enable the penetration of ice. Desirable
    features include the ability to carry an array of instruments and
    imaging systems, to provide an aseptic operation mode, and to
    maintain a pristine research environment.

-   Low cost light weight systems to assist in the selection and
    acquistion of the most scientifically interesting samples are also
    of significant interest.

**Analytical Tools:**

-   High sensitivity (femtomole or better), high resolution methods
    applicable to all biologically relevant classes of compounds for
    separation of complex mixtures into individual components.

-   High sensitivity (femtomole or better) characterization of molecular
    structure, chirality, and isotopic composition of biogenic elements
    (H, C, N, O, S) embodied within individual compounds and structures.

-   High spatial resolution (5 angstrom level) electron microscopy
    techniques to establish details of external morphology, internal
    structure, elemental composition and mineralogical composition of
    potential biogenic structures.

-   Development of modern, innovative computer software to support
    astrobiological studies of the origin and evolution of life. The
    areas of special interest are (1) biomolecular and cellular
    simulations, (2) evolutionary and phylogenetic algorithms and
    interfaces, (3) DNA computation, and (4) image reconstruction and
    enhancement for remote sensing.

-   Nondestructive structural characterization of micro-areas or
    microsamples of rocks and minerals by diffraction (1-100 micron
    scale of observation).

## 28.02 Technologies for Understanding the Evolution of Biological Systems in Space  {#technologies-for-understanding-the-evolution-of-biological-systems-in-space .unnumbered}

Lead Center: ARC

An essential element of Astrobiology is understanding the evolutionary
development of biological processes leading from single cell organisms
to multicellular specimens and to complex ecological systems over
multiple generations. Throughout its evolution, life on Earth has been
exposed to the constant force of gravity. Therefore, it is axiomatic
that gravity helped shape and continues to influence the structure,
function, and ongoing evolution of all living organisms. Because of its
pervasive influence, understanding the effects of gravity on the
evolution of living systems is a fundamental question of substantial,
inherent scientific value in our quest to understand life. In addition,
radiation of varying levels is assumed to have varying effects on the
development and evolution of life. Currently, man-tended microgravity
flights, e.g., Shuttle, Mir, International Space Station, provide
excellent opportunities to study the effects of both varying gravity
levels and radiation on life, and numerous Space Life Science facilities
have been developed to utilize these platforms. With the omnipresent
nonpathogenic organisms currently found on board spacecraft, the effects
of varying radiation exposure on biofilms and general microbial mutation
in spacecraft and habitat interiors may provide an example for study
opportunities aboard current Shuttle launches. Knowledge of the effects
of radiation and gravity on lower organisms, plants, humans, and other
animals, as well as elucidation of the basic mechanisms by which these
effects occur, will be of direct benefit to the quality of life on Earth
through applications in medicine, agriculture, industrial biotechnology,
environmental management, and other activities dependent on
understanding biological processes over multiple generations.

In support of the above areas of investigation, technologies must be
developed in the following categories:

-   Biotechnology: determining mutation rates and genetic stability in a
    variety of organisms as well as accurately determining protein
    regulation changes in microgravity and radiation environments.

-   Automated chemical analytical instrumentation for determining gross
    metabolic characteristics of individual organisms and ecologies, as
    well as chemical composition of environments.

-   Imaging technology with high resolution and low power requirements.

-   Habitat support: technologies for supporting miniature ecosystems,
    isolated from their support environments, and transmitting data
    collected with the automated chemical analytical instrumentation
    described above. Candidate technologies include sensor and telemetry
    systems as well as variable-spectrum, low power light sources for
    simulating conditions on the early earth.

-   Algorithms for processing and analyzing recovered data.

    These technologies must be miniaturized to minimize weight, volume
    and power requirements and must operate autonomously for extended
    periods of time to accommodate monitoring multiple generations of
    organisms. Thus, instrumentation must be self-calibrating, require
    no or minimal consumables and be remotely commanded.

## 28.03 Technologies for Understanding the Evolution of the Earth\'s Atmosphere and Ecosystem  {#technologies-for-understanding-the-evolution-of-the-earths-atmosphere-and-ecosystem .unnumbered}

Lead Center: ARC

Astrobiology includes the study of evolution, which is essentially the
study of ecological processes through time. Astrobiology intersects with
NASA\'s Earth Science (ES) through the highly accelerated rate of change
in Earth\'s biosphere being brought about by human actions. One
particular area of study applicable to astrobiology with direct links to
ES is microbe-environment interactions. These interactions can be seen
in carbon cycles and nitrogen cycles. Some examples of rapid changes
that affect these microbial processes are increases in UV, increases in
average and seasonal temperatures, and changes in the length of the
growing season-all of which are key issues in both ES and astrobiology.
This research requires unique instrumentation and information science
technologies that are not covered in the ES program, including:

-   Miniature to microscopic, high resolution, field worthy, smart
    sensors or instrumentation for the accurate and unattended
    monitoring of environmental parameters that include but are not
    limited to, solar radiation (190-800 nm at \< 1nm resolution), ions
    and gases of the various oxidation states of carbon and nitrogen (at
    the nanomolar level for ions in solution and at the femtomolar or
    better level for gases), in a variety of habitats (e.g., marine,
    freshwater, acid/alkaline hot springs, Antarctic climates or
    boreholes into the Earth).

-   High resolution, high sensitivity (femtomolar or better) methods for
    the isolation and characterization of nucleic acids (DNA/RNA) from a
    variety of organic and inorganic matrices.

-   Mathematical models capable of predicting the combined effects of
    elevated pCO2 (change in Co2 over the eons) and solar UV radiation
    on carbon sequestration and N2O emissions from experimental data
    obtained from field and laboratory studies of C-cycling rates,
    N-cycling rates, as well as diurnal and seasonal changes in solar
    UV.

-   Microscope DASI (Digital Array Scanning Interferometer) or its
    equivalent to study soil cores, microbial communities, pollen
    samples, etc., in a laboratory environment for the detailed
    spectrscopic analysis relevent to evolution as a function of climate
    changes.

# 9.0 Submission Forms and Certifications

**NASA SBIR 98-1 SOLICITATION**

**FORM 9A - PROPOSAL COVER**

Subtopic Last 4 digits Change

Number of Firm\'s Phone \# Letter

PROPOSAL NUMBER **98-1** **.** **(Instructions on Reverse Side)**

SUBTOPIC TITLE

PROJECT TITLE

FIRM NAME

MAIL ADDRESS

CITY/STATE/ZIP

PHONE FAX

CEO E-MAIL PI E-MAIL

PHASE I AMOUNT REQUESTED: \$ DURATION: MONTHS

**ENDORSEMENTS:** Principal Investigator: Corporate/Business Official:

Typed Name

Title

Signature

Date

**PROPRIETARY NOTICE (If Applicable, See Sections 5.4.1 & 5.5)**

*NOTICE:* For any purpose other than to evaluate the proposal, this data
shall not be disclosed outside the government and shall not be
duplicated, used, or disclosed in whole or in part, provided that if a
funding agreement is awarded to this proposer as a result of or in
connection with the submission of these data, the Government shall have
the right to duplicate, use, or disclose the data to the extent provided
in the funding agreement. This restriction does not limit the
Government\'s right to use Information contained in the data if it is
obtained from another source without restriction. The data subject to
this restriction are contained in pages \_\_\_\_\_\_\_\_\_\_ of this
proposal.

####### PROPOSAL COVER INSTRUCTIONS

General\--Complete Form 9A and sign it in ink. This original cover sheet
shall be submitted with the original paper copy of the proposal. Make
photocopies to use as the cover sheet for other copies of your proposal
and submit an extra copy separately. (See Sections 3.2, 3.3, 3.4 and 6.1
for further instructions)

1\. Proposal Number\--This number does not change even if the firm gets
a new phone number. Complete the proposal number as follows:

a.  Enter the four-digit subtopic number.

b.  Enter the last four digits of your firm\'s telephone number.

c.  If you are submitting different proposals under the same subtopic,
    enter a change letter as appropriate to differentiate proposal
    numbers.

Example I: A company with telephone number 273-8126 submits one proposal
to subtopic 06.03. The proposal number is 06.03-8126.

Example II: A company with telephone number 392-4826 submits three
different proposals to subtopic 11.03. The proposal numbers are:
11.03-4826, 11.03-4826A, and 11.03-4826B

2\. Subtopic Title: Enter the title of the subtopic that this proposal
will address. Use abbreviations as needed.

3\. Project Title: Enter a brief, descriptive title using no more than
80 keystrokes (characters and spaces). Do not use the subtopic title.
Avoid words like \"development\" and \"study\".

4\. Firm Name: Enter the full name of the company submitting the
proposal. If a joint venture, list the company chosen to negotiate and
receive contracts. If the name exceeds 40 keystrokes, please abbreviate.

5\. Address: Enter address where mail is received.

State: Enter 2-letter designation (example Maine: ME)

Zip Code: Enter 5- or 9-digit code

Phone: Enter general phone and Fax number of the firm.

CEO E-Mail: Enter e-mail address for Business Official

PI E-MAIL: Enter e-mail address for Principal Investigator

6\. Phase I: Amount Requested: Enter proposal amount from Budget
Summary. The amount requested should not exceed \$70,000. Round to
nearest dollar. Do not enter cents. Duration: Enter the proposed
duration in months. If the proposed duration is other than 6 months, be
sure to discuss the reason in the text of the proposal.

7\. Certifications: The offeror must respond to the follow­ing
certifications cited briefly on the proposal cover. Put a check in the
appropriate boxes.

7(a), (b), (c). See definitions in Section 2 of this solicitation

7(d). Limits on subcontracting and consultants. By answering yes, the
offeror certifies that a minimum of two-thirds of the research and/or
analytical effort for the proposed project will be performed by the
small business concern, as described in Section 3.5.1, Part 9.

7(e). Eligibility of the Principal Investigator. By answering yes, the
offeror certifies that the proposed principal investigator meets all the
require­ments described in Section 1.4.3 and, if the PI is currently the
employee of an academic or a non-profit research organization, a copy of
the release letter from that organization is also included.

###### CONTINUED

7(f). Prior federal funding. By answering yes, the offeror certifies
that they have received federal funds for substantially similar work and
these projects are described in Part 11 of the proposal. By answering
no, the offeror certifies that no such funds have been received.

7(g). Proposals to other agencies. By answering yes, the offeror
certifies that they have submitted or plan to submit proposals of
similar content to another federal agency and that these proposals are
described in Part 11 of the proposal. By answering no, the offeror
certifies that no such proposals are presently under consideration or
will be submitted this year.

7(h). Subcontracts and agreements. By answering yes, the offeror
indicates that a copy of any subcontracting or consulting agreements
described in Part 9 of the proposal is included as required in Section
3.5. If such agreements are lengthy, the signature page should be
included. These copies may be submitted in a reduced size.

7(i). Government Furnished Equipment. By answering yes, the offeror
certifies that unique, one-of-a-kind Government Furnished Facilities or
Government Furnished Equipment are required to perform the proposed
activities and that appropriate authorizations have been obtained (see
Section 3.5.1 Part 8, Section 4.2.2 Part 7, and Section 5.1.4). By
answering no, the offeror certifies that no Government Furnished
Facilities or Government Furnished Equipment are required to perform the
proposed activities.

8 No substantially duplicative proposal is submitted to more than one
subtopic. By answering yes, the offeror certifies that only one proposal
for substantially the same activity has been submitted within this
Solicitation.

9\. Endorsements: The proposal should be signed by the proposed
Principal Investigator and an official of the firm qualified to make a
contractual commitment on behalf of the firm. The PI and the Corporate
Official may be the same person. The copy of the cover sheet submitted
as the single original should have original signatures.

**SBIR 98-1 SOLICITATION**

**FORM 9B - PROJECT SUMMARY**

Subtopic Last 4 digits Change

Number of Firm\'s Phone \# Letter

PROPOSAL NUMBER **98-1** **.** **(Instructions on Reverse Side)**

PROJECT TITLE

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

POTENTIAL COMMERCIAL APPLICATIONS

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name,
Mail Address, City/State/Zip)

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)

PROPOSAL PAGE 2

**INSTRUCTIONS FOR PROJECT SUMMARY**

1\. **Proposal Number**: (See instruction for Form 9A, Cover Sheet).

2\. **Project Title**: Enter the same title as shown on your Proposal
Cover.

3\. **Technical Abstract**: Provide a summary of 200 words or less of
your proposed project. The abstract must not contain proprietary
information and must describe the proposed innovation. (See Section
3.4.2. for how it addresses the stated subtopic requirement, the project
objectives, the effort proposed, the results anticipated, and the
expected NASA ap­plica­tions and benefits)

4.  **Potential Commercial Applications**: Summarize the direct or
    indirect commercial potential of the project, assuming the goals of
    the proposed research or R&D are achieved.

5\. **Name and Address of Principal Investigator**: Enter name,
organization name and mailing address as shown in the Proposal Cover
sheet.

6\. **Name and Address of Offeror**: Enter firm name and mailing address
as shown on the Proposal Cover sheet.

**SBIR 98-1 SOLICITATION**

**FORM 9C - SBIR PROPOSAL SUMMARY BUDGET**

FIRM: PROPOSAL NUMBER:

DIRECT LABOR:

Category Hours Rate Cost

\$

TOTAL DIRECT LABOR:

1.  \$

OVERHEAD RATE % of Total Direct Labor

OVERHEAD COST:

2.  \$

OTHER DIRECT COSTS:

Category Cost

\$

TOTAL OTHER DIRECT COSTS:

\(3\) \$

(1)+(2)+(3)=(4) SUBTOTAL: (4) \$

G&A RATE % of Subtotal G&A COSTS:

\(5\) \$

(4)+(5)=(6) TOTAL COSTS (6) \$

ADD PROFIT or SUBTRACT COST SHARING PROFIT/COST SHARING:

\(7\) \$

(6)+(7)=(8) AMOUNT REQUESTED:

\(8\) \$

**This proposal is submitted in response to NASA SBIR Program
Solicitation 98-1 and reflects our best estimates as of this date:**

NAME AND TITLE (Typed): SIGNATURE:

DATE:

**INSTRUCTIONS FOR SBIR SUMMARY BUDGET**

By using this form, the offeror submits to the Government a pricing
proposal of estimated costs with detailed information for each cost
element, consistent with the offeror\'s cost accounting system (See
Section 3.6 for further information). This summary does not eliminate
the need to fully document and justify the amounts requested in each
category. Such documentation should be contained, as appropriate, on a
budget explanation page immediately following the budget in the
proposal. (See below for discussion on various categories)

\(1\) **Direct Labor**\--Enter labor categories (e.g., principal
investigator, laboratory assistant, administrative staff), hourly rates
of pay and the hours for each labor category.

\(2\) **Overhead**\--Specify current rate(s) and base(s). The offeror
may use whatever number and types of overhead rates that are in
accordance with the firm\'s accounting system and approved by the
cognizant federal negotiating agency, if available. If no rate(s) has
(have) been negotiated, a reasonable indirect cost (overhead) rate(s)
may be requested for Phase I that will be subject to approval by NASA.
Multiply Direct Labor by the Overhead Rate to determine the Overhead
Cost.

\(3\) **Other Direct Costs**

a\. Materials and Supplies: Indicate types required and estimate costs.

b\. Documentation Costs or Page Charges: Estimate cost of preparing and
publishing project results.

c\. Subcontracts: Include a completed budget\--including hours and
rates\--and justify details. (See Sections 3.5, Part 9 and 5.12 for
further information)

d\. Consultant Services: Indicate name, daily compensation, and
estimated days of service. (See Section 3.5, Part 9 for further
information.)

e\. Computer Services: Computer equipment leasing is included here.

List all other direct costs that are not otherwise included in the
categories described above.

\(4\) **General and Administrative (G&A)**\--Specify current rate and
base. Use current rate negotiated with the cognizant federal negotiating
agency, if available. If no rate has been negotiated, a reasonable
indirect cost (G&A) rate may be requested for Phase I, subject to
approval by NASA. Multiply (4) Total Direct Cost by the G&A Rate to
determine G&A Cost.

\(5\) **Profit or Cost Sharing**\--See Sections 3.6.4, 5.8, and 5.9.

\(6\) **Amount Requested**\--This should exclude any cost-sharing and
not exceed \$70,000.

**For assistance in completing your proposal, use this checklist to
ensure your submission is complete.**

**CHECK LIST**

**1. General**

> 1.1 The offeror has read all instructions in this Solicitation and
> understands that proposals not meeting all requirements may be
> non-responsive and may not be evaluated.

1.2 The offeror understands that proposals must be received by NASA no
later than by 5:00 p.m. EDT on July 7, 1998. (Section 6.4.3).

> 1.3 Postal Submission includes the original signed proposal plus three
> copies. (Section 6.4).
>
> 1.4 The entire proposal (including any supplemental material) shall
> not exceed a total of 25 8.5 x 11 inch pages (Section 6.4).
>
> 1.5 The entire proposal must be submitted in the order outlined below.
> (Section 3.1).

**2. Cover Form 9A**

2.1 The proposal and innovation is submitted for one topic only.
(Section 3.4).

2.2 Certifications in Form 9A are completed. (Section 3.4.1, 3.6.1)

2.3 The period of technical performance does not exceed six months and
the funding request does not exceed \$70,000. (Section 5.1).

2.4 Form 9A submitted via Internet (Section 6.3).

2.5 Printed Version of Form 9A is signed (Section 6.4) and included in
Postal Submission.

**3. Summary Form 9B**

3.1 Form 9B submitted via Internet (Section 6.3).

3.2 Printed Version of Form 9B (Section 6.4) is included in Postal
Submission.

**4. Technical Proposal**

4.1 The proposed innovation is described in the first paragraph of the
Technical Proposal (Section 3.5).

4.2 The technical proposal contains all twelve parts in order. (Section
3.5).

4.3 Phase-II objectives are discussed (Section 3.5).

4.4 Commercial applications potential is discussed. (Section 3.5).

4.5 Any pages containing proprietary information are labeled
\"Confidential Proprietary Material\" and kept to the minimum essential
for the proposal. (Section 3.5).

4.6 The Electronic Technical Proposal was:

> 4.6.1 submitted over the Internet, (Section 6.3) OR
>
> 4.6.2 placed on an electronic media and included with the Postal
> Submission Package. (Section 6.4).

**5. Budget Form 9C**

5.1 Form 9C submitted via Internet (Section 6.3).

5.2 Printed Version of Form 9C is signed (Section 6.4) and included in
Postal Submission.