Mark J. Hyatt

Glenn Research Center, Cleveland, Ohio

Sharon Straka

Goddard Space Flight Center, Greenbelt, Maryland

The Dust Management Project: Final Report

NASA/TM—2011-217037

December 2011
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Mark J. Hyatt

Glenn Research Center, Cleveland, Ohio

Sharon Straka

Goddard Space Flight Center, Greenbelt, Maryland

The Dust Management Project: Final Report

NASA/TM—2011-217037

December 2011

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135
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7115 Standard Drive

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The Dust Management Project: Final Report 

Mark J. Hyatt 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Sharon Straka 

National Aeronautics and Space Administration 

Goddard Space Flight Center 

Greenbelt, Maryland 20771 

Abstract 

A return to the Moon to extend human presence, pursue scientific activities, use the Moon to prepare 

for future human missions to Mars, and expand Earth’s economic sphere, will require investment in 

developing new technologies and capabilities to achieve affordable and sustainable human exploration. 

From the operational experience gained and lessons learned during the Apollo missions, conducting longterm operations in the lunar environment will be a particular challenge, given the difficulties presented by 

the unique physical properties and other characteristics of lunar regolith, including dust. The Apollo 

missions and other lunar explorations have identified significant lunar dust-related problems that will 

challenge future mission success. Comprised of regolith particles ranging in size from tens of nanometers 

to microns, lunar dust is a manifestation of the complex interaction of the lunar soil with multiple 

mechanical, electrical, and gravitational effects. The environmental and anthropogenic factors effecting 

the perturbation, transport, and deposition of lunar dust must be studied in order to mitigate it’s potentially 

harmful effects on exploration systems and human explorers. The Dust Management Project (DMP) was 

tasked with the evaluation of lunar dust effects, assessment of the resulting risks, and development of 

mitigation and management strategies and technologies related to Exploration Systems architectures. To 

this end, the DMP supported the overall goal of the Exploration Technology Development Program 

(ETDP) of addressing the relevant high priority technology needs of multiple elements within the 

Constellation Program (CxP) and sister ETDP projects. Project scope, approach, accomplishments, 

summary of deliverables, and lessons learned are presented. 

1

NASA/TM—2011-217037 1
NASA/TM—2011-217037 2
NASA/TM—2011-217037 3
The Dust Management Project (DMP) was structured to address cross-cutting agency 

needs, and to pursue multiple mitigation strategies in parallel and at different levels. The 

Work Breakdown Structure (WBS) of the project reflects this multiprong approach Work Breakdown Structure (WBS) of the project reflects this multiprong approach.

In this document following are descriptions of the various WBS elements, grouped by type in 

accord with the WBS structure. At the highest level, WBS element 1.2, the Systems 

Engineering & Integration activity was used to help manage the overall project portfolio. The 

technical approaches pursued within the DMP then were broadly grouped within the 

following three WBS elements. 

Basic technology assessment of feasibility activities, typically working at an earlier 

Technology Readiness Level (TRL), fall under the 1.5 WBS element ("Technology 

Development Areas"). These efforts range from surface modification to dirt removal 

techniques, and include generic mechanical component evaluation to understand how 

mechanisms are affected in the presence of particulates.

Technology integration into example systems, typically at a mid-TRL, was grouped under 

the 1 6 WBS element ( the 1.6 WBS element ( Technology "Technology Focus Areas Focus Areas )" With specific applications targeted both . With specific applications targeted, both

dust mitigation and dust tolerance technologies fall within this WBS element.

In order to assess technologies' tolerance for or effect upon dust and larger particulates, 

reasonable simulants of (lunar) regolith are needed. Under the 1.4 WBS element were 

grouped both the characterization of regolith and the study of simulants for comparison 

("Simulants"). Indeed, even the very basis for comparison of simulant to regolith had to be 

developed, dependent on the type of testing pursued.

This document then concludes with some words on lessons learned and project transition 

comments.

NASA/TM—2011-217037 4
Element Overview 

The Systems Engineering and Integration (SE&I) element of the DMP is responsible for performing 

portfolio assessments, developing and implementing processes to ensure the delivery and integration 

of DMP products that meet customer requirements and schedule. The development and application 

of this disciplined approach comprised of technical processes and supporting infrastructure, is 

implemented by multidisciplinary teams consisting of DMP developers, customers, and external 

subject matter experts. This overall approach to technology portfolio management includes the 

following primary objectives: 1) Baseline traceability mapping of the DMP portfolio to approved level 

1 & 2 req p uirements and capability ; needs 2)p g Ensure that specific DMP technology p development tasks 

and application areas map to relevant TPP needs; 3) Establish a mechanism to assess the 

performance of DMP technologies and mitigation strategies at certain stages in their development; 

4) Review the technology development efforts of other entities to identify synergies and to avoid 

duplication of effort; and 5) Prepare DMP technology developers and CxP customers for insertion of 

DMP technologies into customer programs / systems 6 months prior to the customer Preliminary 

Design Review (PDR). 

NASA/TM—2011-217037 5
Process Development and Implementation

The following processes were developed and/or implemented by the DMP SE&I to achieve 

the objectives of the project element as described above. 

Traceability Mapping

Level 1 & 2 Requirements/Needs - Demonstrates traceability of the DMP portfolio to the 

Exploration Architecture Requirements Document (EARD) and Constellation Architecture 

Requirements Document (CARD). 

Constellation Prog ( ) gy ram (CxP) Technology Prioritization Process - Rationale statements 

indicate the specific capability/product offered by the DMP task to support the requirement 

and to indicate DMP task alignment.

Assessments and Mechanisms

Technology Assessment /Gap Analysis - Assess related technology development activities 

in other NASA programs, other Government agencies, and the commercial sector to 

eliminate unnecessary duplication of effort.

Request for Information - Leverage the expertise of non-NASA sectors to complement 

and/or supplement the current Exploration Technology Development Program (ETDP) 

technology development portfolio to ensure the most optimal solutions are deployed for dust 

mitigation within available funding profile.

Technical Exchange Meeting Implementation - Bridge CxP projects working to develop their 

dust mitigation capability needs and requirements with DMP SE&I and investigators to 

promote direct customer promote direct customer-developer interaction. developer interaction.

NASA/TM—2011-217037 6
Decision Gate Process (DGP) – The DGP provides an objective mechanism for the 

evaluation of DMP Technology Development and Application Areas at Technology 

Readiness Levels (TRL) 3 through 6. The process offers frequent opportunities with multiple Readiness Levels (TRL) 3 through 6. The process offers frequent opportunities with multiple

decision gates to weed-out non-performing technologies before too much is invested in them 

and while there is time to identify an alternate technology or deviation from an earlier 

development plan. The DGP also provides an opportunity for DMP investments to 

demonstrate maturity at identified points and on schedule to instill customer confidence that 

each DMP deliverable has met qualifying metrics each step of the way. The process also 

affords a mechanism to identify the best performing, highest customer priority technologies, 

so that in times of budget reduction, investments may be allocated appropriately to ensure 

the most chance of success for those technologies the most chance of success for those technologies.

Technology Insertion / Infusion Process (TIP) – The TIP provides a step-wise process 

flow and accompanying documentation to support actual technology insertion of DMP 

technologies into customer systems. The process identifies insertion requirements from both 

developer and customer perspectives in preparation for insertion.

CxP Lunar Regolith Community of Practice (LunRCoP) – The LunRCoP promotes 

interaction of the CxP and DMP staff with other internal as well as external technology interaction of the CxP and DMP staff with other internal as well as external technology

developers and researchers to share issues, solutions, and best practices from the 

perspective of a multi-disciplinary community focused on particle management.

NASA/TM—2011-217037 7
Report complete, loaded to windchill at: 

htt //i l ti https://ice.exploration.nasa.gov/Wi d hill/ t k t /j /f ld / i j ? id f ld t f ld ndchill/netmarkets/jsp/folder/view.jsp?oid=folder~wt.folder

.SubFolder%3A2061516197&u8=1

NASA/TM—2011-217037 8
Summary of Major Deliverables

Th SE&I t ib t d l j d li bl t th DMP th f th j t The SE&I contributed several major deliverables to the DMP over the course of the project

in addition to the development and/or implementation of the processes described above. 

These contributions range in scope from internal reviews to surveys of both agency-wide 

dust efforts and similar activities being performed by those in related fields that may have 

applicability to NASA needs. A summary of major accomplishments is provided below.

Catalog of Agency Investments in Research and Technology Development for Dust 

Mitigation - This assessment reviewed internal Agency-wide dust-related activities. These 

agency efforts were captured under several categories to include: Programs, Working 

Groups, Workshops, and Studies; Research Projects; Technology Development Projects; 

and Facilities and Simulants. Past projects were captured in an Archive section. 

Assessment of Portfolio Alignment with Dust-Relevant Results of the Constellation 

Program Technology Prioritization Process (TPP) - Each task within the DMP portfolio 

maps to one or more CxP TPP capability need items in the 2008-2009 time period. The 

DMP focused on dust-related needs that were ranked highest and that represent those 

closest to the focus of the current DMP portfolio and intended project scope. Several DMP 

WBS elements map to more than one TPP. As with the higher-level requirements, rationale 

statements describing how each DMP task maps to a particular TPP were captured. 

Dust Management Project Task Traceability Map - The primary objectives of this effort 

were to (1) establish a baselined mapping of individual DMP tasks to requirements and 

capabilities as provided by the Exploration Systems Mission Directorate (ESMD) and the 

CxP, , as well as the TPP, and (2) g facilitate continuing cap p ture of refined customer capability

needs and requirements and maintain active mapping of DMP efforts. The following 

requirements document was released from this effort - DUST-REQ-0001. 

NASA/TM—2011-217037 9
Cradle Schema and Initial Project Data – Utilizing customer-defined CxP capability needs 

through review of the TPP results and CxP operational scenarios, developed CRADLE 

schema for the DMP to establish formal mapping of DMP research and technology portfolio 

to known CxP customer requirements. Schema for operational, interface, testing facility, and 

verification criteria were developed. DMP technology development portfolio data was 

entered to implement requirements traceability and tracking. 

Lunar Regolith Community of Practice Website http://tia.arc.nasa.gov/lunrcop The 

LunRCoP is a virtual forum managed by the CxP and implemented by the DMP that 

provides a facilitated infrastructure to the community of engineers, scientists, and project 

managers focused on different aspects of fugitive particle management with the purpose of 

mitigating hardware degradation created by exposure to lunar regolith. The LunRCoP melds 

the knowledge of the research and scientific inquiry focused community with the community 

designing systems that tolerate dust in an effort to leverage the collective know-how. 

The Lunar Dust Smart Buyer Clinic, June 26, 27, and 28, 2007. This workshop applied a 

hands-on approach to working through possible mitigation and cleaning options for affected 

components and systems to gain perspective on needs in terms of technology capability 

gaps, best practices, and design standards that will allow NASA to develop systems capable 

of continued op p eration in the lunar environment. A final report and supporting materials are 

available.

Lunar Regolith Industry Focus Group, August 13 and 14, 2007. In preparation for 

human exploration of the lunar surface, NASA is interested in obtaining information from 

industries that design equipment to operate in dusty environments. As successful surface 

exploration is dependent upon components and systems that reliably operate in the 

presence of lunar “soil,” NASA has particular interest in learning how other entities develop 

co po e ts a d syste s des g ed to o t a pa t c e mponents and systems designed to work within a particle-fou ed e o e t o t at a e led environment or that are

involved in the clean-up and maintenance of internal environments or components and 

systems. A final report and supporting materials are available.

Lunar Regolith Behavior Workshop, August 12-14, 2008. To better understand the lunar 

regolith as a system of multiple particle sizes, NASA needs to determine what operations 

may elicit transport, redistribution, and the nature of redistribution so that it may gain an 

advanced perspective on the technology capability gaps, operational approaches and design 

standards that will enable us to develop system standards that will enable us to develop systems that are capable of sustained operation in that are capable of sustained operation in

the lunar environment. The objective of the Lunar Regolith Behavior Workshop was to 

identify surface activities that will affect regolith transport and redistribution, identify current 

unknowns related to the behavioral characteristics of regolith, and to design possible 

investigations to understand regolith behavior. A final report and supporting materials are 

available.

Assessment of Testing Needs and Test Facilities for the Lunar Dust Management 

Project Part 1 Preliminary Needs and Facility Availability Project. Part 1. Preliminary Needs and Facility Availability Overview Overview. The primary The primary

objectives of this assessment were to: 1) Establish the preliminary testing needs and testing 

philosophy of the DMP, 2) Identify the current available NASA and non-NASA testing 

facilities that are applicable for dust testing, and 3) Identify gaps between testing needs and 

current testing capabilities. A final report and supporting materials are available.

Assessment of Testing Needs and Test Facilities for the Lunar Dust Management 

Project. Part 2. Operational Capabilities of Enclosed Vacuum Facilities. The primary 

objectives of the overall facility assessment we objectives of the overall facility assessment were to: 1) Identify the currently available NASA to: 1) Identify the currently available NASA

and non-NASA enclosed and analog testing facilities that are potentially applicable for 

testing with dust in the environment, 2) Determine the relevant current operational 

capabilities (“readiness”) of the facilities, and 3) Identify gaps between testing needs and 

current testing capabilities. A final report and supporting materials are available.

NASA/TM—2011-217037 10
Request for Information (RFI) - NASA Lunar Dust Management Project Commercial 

Technologies for Mitigation of Lunar Dust. An RFI was developed by the DMP to solicit 

technologies and systems from commercial and other non technologies and systems from commercial and other non-NASA organizations to address NASA organizations to address

key technology focus areas for lunar dust mitigation. The intend was to leverage the 

expertise of non-NASA sectors to complement and/or supplement NASA’s current 

technology development portfolio to ensure the most optimal solutions are deployed for dust 

mitigation within available funding profiles.

Decision Gate Process CO2 Shower TRL3 Review - This report serves as the record of 

the results of the DGP as applied to the DMP’s CO2 Shower task that was evaluated for TRL 

3 in December 2009 The task is lead by Nick Mardesich of the Jet Propulsion Laboratory 3 in December 2009. The task is lead by Nick Mardesich of the Jet Propulsion Laboratory. 

The CO2 Shower was assessed according to established technical and programmatic 

criteria that were scored and discussed by a Review Team comprised of DMP management, 

DMP SE&I, a subject matter expert (SME) in precision cleaning, and CxP customer 

representatives from the Lunar Surface Systems (LSS) Environmental Control and Life 

Support Systems (ECLSS) and ExtraVehicular Activity (EVA) projects. Specific criteria were 

developed for the CO2 Shower technology within the general definition of TRL 3 to provide 

reviewers with a refined meaning of the TRL to allow more objectivity in the assessment. 

Other criteria included availability of resou Other criteria included availability of resources technical hurdles to be overcome for , technical hurdles to be overcome for

successive TRLs, expertise of the task team, and the priority of the technology. A final report 

and supporting materials are available.

NASA/TM—2011-217037 11
Conference Proceedings

The SE&I released several reports over the course of the project to include a few that are 

listed as conference proceedings.

R. Kohli, J. Fishman, M.J. Hyatt, P. Abel, and P. Delaune, “Achieving a prioritized 

research & technology development portfolio for the Dust Management Project,” 

IEEE Aerospace Conference, Big Sky, Montana, March 7-14, 2009. Abstract—The NASA 

Lunar Dust Management Project (DMP) has been established to address relevant high 

priority needs for lunar dust mitigation technologies to be used during lunar surface 

operations. To this end, an important goal of the project is to ensure that DMP only invests in 

research and technologies (R&T) that have been assessed and prioritized to meet NASA 

needs for lunar exploration. To facilitate the process, comparison/decision criteria were 

developed to assess and prioritize internal and external technology solution alternatives. 

This paper describes the technologies and presents the assessment methodology. 

R. Kohli, M. Boulavsky , H. Yee, J. Fishman, P. Craven, R. Easter, and M. Hyatt, 

“Assessment of Testing g Needs and Facilities for the Lunar Dust Management 

Project,” IEEE Aerospace Conference, Big Sky, Montana, March 6-13, 2010. Abstract—

The NASA Dust Management Project has been established to address relevant high priority 

needs for lunar dust mitigation technologies to be used during lunar surface operations. A 

key task of the project is to support the assessment of test planning and test facility 

requirements for dust mitigation technology evaluation and demonstration. The overall 

objectives of the assessment include a) delineation of testing philosophy and needs and b) 

the identification and evaluation of the capabilities of available and suitable NASA and nonNASA test facilities to identify potential gaps NASA test facilities to identify potential gaps between between testing needs and current operational testing needs and current operational

testing capabilities. The approach, methodology and initial results of this ongoing 

assessment are described in this paper.

NASA/TM—2011-217037 12
A. Chait, “Charging Processes of Lunar Dust in Anisotropic Solar Wind Plasma 

Lunar Dust, Plasma & Atmosphere: The Next Steps”, presented at the Laboratory for 

Atmospheric and Space Physics, University of Colorado, Boulder, January 27 Atmospheric and Space Physics, University of Colorado, Boulder, January 27-29,

2010. Abstract—We analyze the fundamental mechanisms of charging of a dust particle in 

the moon environment by tenuous anisotropic solar wind plasma. The majority of work on 

dusty (complex) plasmas is largely concerns with laboratory plasmas, whose parameters 

are considerably different from those corresponding to the solar wind plasma at the moon 

orbit. We derive a charging equation for dust grain, and calculate basic properties such as 

characteristic charging time and floating potential as functions of grain size and plasma 

parameters, including the plasma streaming velocity. We show that charging of small grains 

is time is time-dependent and could last e g 3 dependent and could last, e.g., 30 min or longer for sub min or longer for sub-micron particles We then micron particles. We then

extend the applicability of these findings from two component (electron/proton) plasma to the 

general case of multi-component plasma, with properties specific to solar wind composition. 

The presence of helium and other heavy ions accelerates the charging process and slightly 

decreases the floating value of grain potential in comparison to two-component solar wind 

plasma Finally, we distinguish between the lunar surface dust distribution and that which is 

expected to be found and adhered to surfaces placed off the lunar soil.

V Pines M Zlatkowski, V. Pines, M. Zlatkowski and A Chait “Charging of Dust Grains by Anisotropic Solar , and A. Chait, Charging of Dust Grains by Anisotropic Solar

Wind Multi-Component Plasma” Advances in Space Research, Volume 45, Issue 6, 

March 15, 2010, pp. 812-822. Abstract— In this paper we study the charging process of 

small grain particles by anisotropic multicomponent solar wind plasmas (electrons, protons 

and heavy ions), versus two-component (electron/proton) plasmas. We are focusing 

attention on the important characteristics of the charging process, namely the charging time, 

floating potential and current content as functions of plasma parameters such as He++/H+ 

(α/p) number density and Tα/Tp temperature ratios of alpha particles to protons, as well as 

plasma streaming velocity plasma streaming velocity ν0 Measured statistical properties of solar wind plasma . Measured statistical properties of solar wind plasma

parameters at AU show considerable variations in α/p -temperature ratios from 1 to 10, in 

α/p-number density ratio from 0.01 to 0.35, as well as in values of streaming velocity ν0 from 

200 to 1000 km/s and more.

NASA/TM—2011-217037 13
The DMP has developed a comprehensive research, technology, and systems development 

approach t t th ifi d d i t id tifi d f E l ti S t f h to meet the specific needs and requirements identified for Exploration Systems for 

Lunar Surface Systems (LLS), Lunar Lander Project Office (LLPO), Orion Crew Vehicle, and 

Extravehicular Activity (EVA). It also includes required characterization of lunar regolith to 

inform the engineering design process for these systems, the definition of requirements and 

characterization of existing and future lunar regolith simulants, and the development and 

production of Highland and Mare simulant types. Each element has been selected for its 

potential benefits in lunar dust environment knowledge generation, dust management/

mitigation, or environmental testing. The DMP technology portfolio is organized with respect 

to multi-application technology development areas (Electrodynamic Dust Shield, Lotus 

Coating, SPARCLED, and CO2 Shower), specific technology focus areas (Mechanical 

Components, Thermal Control Surfaces, Connectors, and Surface Power), and Simulants. 

Detailed descriptions for each of the technology elements, technology application focus 

areas, and simulant development are summarized .

NASA/TM—2011-217037 14
NASA/TM—2011-217037 15
This task is focused on the development of EDS technology to minimize dust accumulation on 

surf d aces exposed t t ohtl e ex ernal l i t df unar environment and aff t ec ed bl f t y lunar surface operati T ons.he 

non-mechanical, electrodynamic cleaning method removes dust particles and prevents dust 

accumulation on surfaces by applying a multi-phase traveling electric field to electrodes that are 

embedded in the surface to lift and transport charged and uncharged particles off and away from the 

surface.1 The technology is currently at a TRL-3.

The EDS technology has applicability to surfaces exposed to the external lunar environment that 

need protection, including surface power systems (solar panels, energy storage battery modules, 

interface cold p ), p y ( , p , , p , g ), lates), optical systems (windows, view ports, cameras, spectrometers, light sources),

thermal radiators, connectors (quick disconnects and umbilical systems), ISRU sample recovery 

chambers and steel plates for ISRU production plant design, and sealing surfaces of the airlock hatch 

and suit port. 

NASA/TM—2011-217037 16
NASA/TM—2011-217037 17
NASA/TM—2011-217037 18
See summary included in Technology Insertion Process, referenced on chart 6 of this 

present ti a on.

NASA/TM—2011-217037 19
NASA/TM—2011-217037 20
NASA/TM—2011-217037 21
NASA/TM—2011-217037 22
NASA/TM—2011-217037 23
NASA/TM—2011-217037 24
See DMP Technology Insertion Process, referenced on chart 6

NASA/TM—2011-217037 25
NASA/TM—2011-217037 26
NASA/TM—2011-217037 27
NASA/TM—2011-217037 28
See DMP Technology Insertion Process, referenced on chart 6

NASA/TM—2011-217037 29
NASA/TM—2011-217037 30
This dust removal process is dependent on the astronauts EVA suits having EDS grids as part of the 

suit d i D t ill l t th it f th M ’ f Th ti ti f th EDS it design. Dust will accumulate on the suits from the Moon’s surface. The activation of the EDS

screen will remove most of the dust, approximately 10% dust loading of micron size particles will 

remain. VanderWaal adhesion force will keep these small particles adhere to the suits. The 

astronauts will then be sealed in the CO2 shower, located in the shadow of the vehicle to maintain 

temperature, and sprayed with CO2 to 0.1 to 0.2 atmospheres obtained from the habitat O2

scrubbers. The CO2 gas will crystallize on the dust particles reducing the VanderWaal force and 

allowing the micron size particles to be removed, and allowing the astronaut to enter the habitat. 

Initial test have shown that a dust loading of 8% can be reduced to 3.5%. 

NASA/TM—2011-217037 31
Figure 3 are the test samples prepared with EDS grids on glass slides mounted to solar cells 

on t f b b t t Li ht t i i th h th l lid b it d top of carbon substrates. Light transmission through the glass slide can be monitored

before and after dust application and EDS removal. Figure 4 is the test systems with gas 

and electrical ports with an inner CO2 pressure chamber, Figure 5. The pressure chamber 

has a plate that can be cooled to -160 C to crystallize CO2 gas Figure 6.

NASA/TM—2011-217037 32
See DMP Technology Insertion Process, referenced on chart 7

NASA/TM—2011-217037 33
Webex presentation from 2009 delta TCR package, resides on Windchill in Dust project 

cl t d t ti f ld loseout documentation folder.

NASA/TM—2011-217037 34
The DMP has developed a comprehensive research, technology, and systems development 

approach t t th ifi d d i t id tifi d f E l ti S t f h to meet the specific needs and requirements identified for Exploration Systems for 

Lunar Surface Systems (LLS), Lunar Lander Project Office (LLPO), Orion Crew Vehicle, and 

Extravehicular Activity (EVA). It also includes required characterization of lunar regolith to 

inform the engineering design process for these systems, the definition of requirements and 

characterization of existing and future lunar regolith simulants, and the development and 

production of Highland and Mare simulant types. Each element has been selected for its 

potential benefits in lunar dust environment knowledge generation, dust management/

mitigation, or environmental testing. The DMP technology portfolio is organized with respect 

to multi-application technology development areas (Electrodynamic Dust Shield, Lotus 

Coating, SPARCLED, and CO2 Shower), specific technology focus areas (Mechanical 

Components, Thermal Control Surfaces, Connectors, and Surface Power), and Simulants. 

Detailed descriptions for each of the technology elements, technology application focus 

areas, and simulant development are summarized.

NASA/TM—2011-217037 35
A general description is provided on the scope of the dust mitigation research in relation to the 

M h i l C t d M h i T h l i i ti t d i l d b i Mechanical Components and Mechanisms area. Technologies investigated include bearings, gears, 

and seals. Points-of-contact are listed as well as respective NASA Centers GRC, MSFC, and JPL. 

The primary thrust of the research effort is to identify contamination issues on various mechanical 

components through testing in a relevant environment including lunar simulant.

NASA/TM—2011-217037 36
A number of mechanical components were tested with lunar simulant. A baseline study of 

cont i t d t t f h d d Th B l taminated grease tests for gearheads was done. The Bal-S l t t d ith ith Seal was tested with either 

JSC-1A or LHT-2M and its performance was observed in keeping simulant out of the 

seal/shaft interface. A prototype low-temperature mechanism dust seal was also tested. 

Contaminated bearing tests were conducted at JPL and MSFC. Simple rotary and linear test 

mechanisms were fabricated to test Mars heritage bearings in vacuum. JPL used a Dust 

Tolerant Bearing Testbed as well as a bearing analysis tool to test bearings having different 

geometries and materials.

NASA/TM—2011-217037 37
Endurance testing continues for the low-temperature mechanism dust seal in vacuum and 

with NU LHT ith NU LHT-2M i l t O 200 000 l t 40 h b l t d th f 2M simulant. Over 200,000 cycles at ~40 rpm have been completed thus far 

with minimal drag torque and temperature rise on the shaft/seal interface. The goal is to 

reach 1,000,000 cycles. A final report was completed on the Barden Bearing linear and 

rotary seal tests. The report is being published through NASA channels. Finally work 

continues on identifying a bearing manufacturer for the ceramic roller race bearing design

at JPL.

NASA/TM—2011-217037 38
The rail-race bearing concept requires test evaluation to validate the current design. As 

such it TRL l l i t 2 Th B l h, its TRL level is at 2. The Bal-S l d B d b i t h l h M ti Seal and Barden bearing technology have some Martian 

design heritage. In addition testing has been completed for both in vacuum with lunar 

simulant (JSC-1a for the Barden Bearing and NU-LHT-2M for the Bal-Seal). As such their 

TRL levels are approximately 3-4. A more integrated test of the technology in a proposed 

system (i.e., wheel bearing housing) would be necessary to raise the current TRL level.

NASA/TM—2011-217037 39
A number of co-op, internship support was necessary for successful implementation of the 

t t/ l i h i l t test/analysis mechanical component program.

The reports and references for this task are available on Windchill, in the Dust Project 

Closeout Documentation folder.

NASA/TM—2011-217037 40
NASA/TM—2011-217037 41
NASA/TM—2011-217037 42
NASA/TM—2011-217037 43
NASA/TM—2011-217037 44
NASA/TM—2011-217037 45
This task showed that vehicles moving on the lunar surface will be subject to triboelectric 

ch i t l l i t l t i th t i d M B f th h d harging at levels approximately twice that experienced on Mars. Because of the hard

vacuum environment, mitigation techniques employed on Mars rovers will be ineffective.

Should this effort be resumed, possible mitigation techniques will be explored. The best 

approaches will involve preventing charging in the first place. We have proposed that 

matching the electron work function of surfaces in contact with regolith with the work 

function of regolith itself will, in principle, prevent charge transfer. Whether this principle can 

be translated into practical materials is unknown.

NASA/TM—2011-217037 46
Delivery of the cold wall for VF-21 is delayed until early October 2010. Once in-house, it will be 

i t ll d d t t d installed and tested as resources are mad il bl Thi ill id f ilit bl f t ti de available. This will provide a facility capable of testing 

component and subsystems in a dusty, high vacuum environment. With hard vacuum and cold wall, it 

will simulate lunar surface conditions. The addition of 7 torr of CO2 and a change of simulants will 

allow similar testing under Mars surface conditions.

Specific tests on solar arrays that were planned for next year are on hold pending guidance from CxP 

Lunar Surface Systems.

NASA/TM—2011-217037 47
VF-21 will be fully operational by the end of October. TRL for specific testing remains 

unch d ange .

NASA/TM—2011-217037 48
NASA/TM—2011-217037 49
A testing infrastructure and protocol was developed to evaluate the effect of dust on thermal control 

surf Thi i l d d th l ti f th L D t Adh i B ll j (LDAB) hi h fid lit faces. This included the completion of the Lunar Dust Adhesion Bell jar (LDAB), a high fidelity 

lunar simulation facility. Within the LDAB, lunar simulant is dried by heating to 200 C in vacuum for 

24 hr. It is also subjected to an air plasma for 60 min to oxidize organic contaminants from the 

surface, and a hydrogen/helium plasma for 60 min to simulate the effects of the solar wind. The 

plasmas also emit a large amount of energetic vacuum ultraviolet light which can generate free 

radicals on the particulate surface. The samples of the white thermal control paint AZ-93 and the 

second surface mirrors silver teflon (AgFEP) and aluminized teflon (AlFEP) can be heated using a

20 sun solar simulator and cooled in a 30 K cold box. The activated dust can be sifted onto the 

samples through an electron beam, which charges the particles. The emphasis was on determining 

the effects of sub-monolayers of dust, since the minimum effect was desired. It was also reasoned 

that thick layers of dust can probably be removed by conventional means, such as brushing, but that 

there is likely to by some residual layer of dust afterwards. Using the heating and cooling curves, a 

finite element thermal model of the samples within the LDAB was used to determine the solar 

absorptance () and the thermal emittance () of the samples, both pristine and dusted. The 

fractional dust coverage was determined by sampling 50 random, non-overlapping frames (of 604) 

under an optical microscope at 100. The effects of fractional dust coverage, substrate, solar angle 

of incidence, dust particle size, and dust type (color) were determined. The steady state temperature 

of the radiator was not appreciably affected by a sub-monolayer of dust.

NASA/TM—2011-217037 50
The  and  of dusted thermal control surfaces was calculated using the optical properties of 

th f d f th d t i i l l f i t d l Thi l i f d the surfaces and of the dust using a simple rule of mixtures model. This analysis was found

to overestimate the effect of dust coverage by about a factor of 2, probably due to the optical 

depth of the distributed dust grains being less than the individual grain size.

Although the electrodynamic dust shield technology appears promising to remove dust from 

thermal control surfaces, the initial tests were plagued by unforeseen materials issues. As of 

the end of FY10 those issues had not yet been resolved, though resolution appears near.

NASA/TM—2011-217037 51
NASA/TM—2011-217037 52
At the start of the project, the technology readiness level was described as TRL 1. The 

A ll d t t d th t l d t ld b diffi lt bl f th l t l Apollo program demonstrated that lunar dust would be a difficult problem for thermal control

surfaces. It was discovered that dust had a strong effect on the  of thermal control 

surfaces, and that it would not be removed by simple brushing with a nylon bristle brush. 

The relationship between the amount of dust on a thermal control surface and the effect on 

thermal performance was unknown. Neither were effects such as dust particle size, dust 

color, or angle of incidence. Further, there were no lunar environment simulation facilities 

where experiments on the effects of dust on thermal control surfaces could be studied.

After three y , ears of work, the broad outlines of the effects of dust on both AZ-93 white paint 

and AgFEP or AlFEP thermal control surfaces are understood. It is known that if the dust 

particles are smaller than 50 m, that their size distribution is not important. It is known that 

there is no solar incidence angle dependence on the  beyond simple geometry. It is known 

that the color of the particles is important with the lightest dust degrading the / of AZ-93 by 

a factor of 2.5 and the darkest by a factor of 5. The effect is even more striking with AgFEP 

with the lightest degrading / by a factor of about 1.5 and the darkest by a factor of about 

6.5. It is known that these thermal control surfaces on composite radiator substrates have 

higher / than those on aluminum substrates It is also known that a monolayer of dust than those on aluminum substrates. It is also known that a monolayer of dust

particles will not appreciably change the radiator operating temperature for a given heat 

load.

Cont’d next chart

NASA/TM—2011-217037 53
Progress has also been made in the area of dust mitigation, moving three technologies into 

TRL 4. It has been shown that texturing an AZ-93 thermal control paint does not affect the 

adhesion of dust particles to it in a simulated lunar environment but that texturing an FEP adhesion of dust particles to it in a simulated lunar environment, but that texturing an FEP

surface lowers the adhesion. Similarly, although work function matching coatings over an 

AZ-93 thermal control paint does not affect the adhesion of dust particles to it in a simulated 

lunar environment, the same coating on an FEP surface lowers the adhesion dramatically. 

And study of bristle brushes has yielded two configurations that show promise of being able 

to remove more than 90% of the dust from either an AZ-93 or an FEP surface. 

In addition, there are three more mitigation technologies that are at TRL 3 and if supported 

could be tested to push them to the TRL 4 within a year. These include the electrodynamic 

dust shield under development at NASA KSC, the lotus coating under development at NASA 

GSFC, and a coating developed under the LASER program by Ball Aerospace.

The goal of this technology development program was to raise the TRL to 6. All that is 

required to bring the dust effects on thermal control surfaces characterization efforts up to 

this level is the testing of lunar regolith samples to verify the simulant results. The largest 

obstacle to this is obtaining lunar regolith samples from the CAPTEM, which to date has 

been unwilling to release the 10 to 30 g of material it would require The resources for been unwilling to release the 10 to 30 g of material it would require. The resources for

verification would be modest, 1.0 FTE/WYE and $25K.

The requirements to raise the dust mitigation program to TRL 6 are less certain. Although 

there are promising mitigation strategies, none is considered to be without considerable 

technical risk. Fundamental work to better understand the physics of adhesion under lunar 

environment conditions is required to guide mitigation efforts. If at least one of the 

technologies under development proves to be e technologies under development proves to be effective ffective the resources to carry out the , the resources to carry out the

evaluation of the technology would require a three year effort funded at about 2.5 FTE/WYE 

plus $100K per year. This is in addition to resources to further develop the dust mitigation 

technology and provide samples for test, which varies with the technology.

NASA/TM—2011-217037 54
NASA/TM—2011-217037 55
NASA/TM—2011-217037 56
Technology Description: Self explanatory, all references to regolith infer lunar regolith

Future Application: Application of simulants is rather dubious since we were never 

granted any regolith to compare simulant properties to. Further, various physical properties 

are in different stages of development, due in part to budgetary constraints and current 

technology to assess those properties being undeveloped. See below for specific properties.

Particle Size distribution: Simulant and regolith in the >dust size range have been 

evaluated by Qem Scan (see Fig. 2 above) to TRL=6. However the dust size range is largely 

unmeasured to high TRL satisfaction. Some work done by JSC on Lunar Regolith has left 

simulants undone such that there is no adequate comparison and work done at GRC on 

simulants falters from lack of Lunar regolith samples to compare. Little if any substantive 

work has been done with Lunar Regolith because of the questionable integrity of regolith 

samples. The TRL for the Dust fraction is at approximately 2-3.

Sample composition: The elemental analysis we have for simulants and Lunar regolith 

are irrelevant as it is mineralogical composition that is required in order to successfully 

demonstrate comparability. Simulant and Lunar regolith in the >dust size range have been 

evaluated by Qem Scan (see Fig. 2) to TRL=6. However the dust size range is largely 

unmeasured to high TRL satisfaction. It was anticipated that the cyclone (see Fig. 1) would 

answer many questions in the dust size range; however, that technology is, at best, only at 

TRL 3 with respect to the challenging simulant samples. Little if any substantive work has 

been done with Lunar Regolith for several reasons, including but not limited to: no effort 

expended; questionable integrity of regolith samples; little automated equipment exists for 

characterization at this pg p g article size range. The TRL for composition in the dust range is 1.

NASA/TM—2011-217037 57
Particle Shape: The equipment required to get the appropriate information has just become 

available. Simulant data has been gathered and is under reduction. No Lunar regolith has 

been granted for comparison at this time Current TRL=2 been granted for comparison at this time. Current TRL=2-3.

Surface Energy: Surface energy has been determined for simulants to the TRL=6 level; 

however, no Lunar regolith was granted so the TRL=1 Lunar for regolith. Since there is no 

comparison between Lunar regolith and simulant, the overall TRL=2-3 for simulant until such 

comparison is made.

Magnetic Susceptibility: Magnetic susceptibility on a per particle basis has been 

determined for simulants to the TRL=6 level; however no regolith was granted so the determined for simulants to the TRL=6 level; however, no regolith was granted so the

TRL=1 for regolith. Since there is no comparison between regolith and simulant, the overall 

TRL=2-3 for simulant until such comparison is made.

Surface Activation: The equipment required to get the appropriate information has just 

become available. Attempts to adapt it to providing information for simulants has started.

No regolith has been granted for comparison at this time. Current TRL=1.

Adh i es on: Th i t i d t t th i t i f ti h j t b The equipment required to get the appropriate information has just become 

available. Attempts to adapt it to providing information for simulants has started. No regolith 

has been granted for comparison at this time. Current TRL=1.

Abrasion: It is difficult to assess this global topic since it covers the span of skin, fabric, 

metals, ceramics, plastics, etc. None-the-less, some progress has been made in certain 

areas. Fabric has been evaluated in simulant by two independent methods. For metals and 

plastics, technology has been developed (see Fig. 4) to a useful stage and quantitative data 

taken. These methods are not suitable for use with regolith due to the quantity of abrasive 

required. The current TRL for Fabrics is 2-3. 

Tribocharging: This topic has moved to elsewhere in the DMP and is no longer covered 

under this WBS.

Miscellaneous topics:

Spectral Properties – This topic is covered elsewhere but will also be touched upon here. 

Literature values appearing on integrated emissivity are questionable due to the fact that 

many were taken by telemetry which is inherently less accurate. Ground based 

measurements on simulants are well founded and equipment is available for such 

measurements. Unfortunately one of the two required instruments does not appear to be 

working properly. No Regolith has been obtained for comparison. The overall TRL for this 

effort is 2-3.

Thermal properties – There are two specific items wrapped up under this heading. Melting 

and phase transitions have been determined of several simulants and their major and some 

minor components (see Fig. 3). Water determination has been hampered by coevolution of 

carbon dioxide complicating stand-alone thermogravimetric assay and loss on ignition. No 

Regolith has been obtained to compare these results to (although none is necessary for the 

gravimetry since no water of carbon dioxide exists in non shadowed regolith). The TRL for 

this effort is in the 2-3 range.

NASA/TM—2011-217037 58
Summary of Accomplishments: Rolled up in slide 1 commentary

Remaining Content (not limited to FY10): Considerable work in characterization is required 

before any simulant will be suitable for TRL=6 testing of equipment. Literally no work has 

been done on regolith (especially the dust fraction). Simple mineral matching is no 

guarantee that the simulant will perform as regolith. Many studies have indicated that the 

agglutinate content of regolith completely changes its properties. Further, the water (and 

carbonate) content of simulants is an additional complicating issue.

NASA/TM—2011-217037 59
TRL at project Start: 1

Current TRL: 1-3 depending on property (as justified by dialog under frame

1) What is needed to get to TRL 6: Providing there are no other properties to be added as 

comparisons between simulant and regolith.

This estimate assumes that access to regolith will be granted when necessary. 

As such TRL 6 may never be achievable for some properties.

NASA/TM—2011-217037 60
Selected References, complete bibliography is on Windchill, in the Dust Project Closeout 

D t ti f ld Documentation folder.

NASA/TM—2011-217037 61
Technology Description and Future Applicability: 

The Simulant Task was assigned to Marshall Space Flight Center (MSFC) in 2003

(pre-ESAS/pre-ETDPO) with the following objectives: 1) reproduce the characteristics of 

lunar regolith (representing the multiple lunar regions such as mare, highlands, and polar) in 

simulants, 2) develop processes to controllably reproduce regolith characteristics,

3) produce simulants as inexpensive as practical, 4) produce simulants in the amount 

needed, and 5) produce simulants to meet users’ schedules. In order to successfully realize 

these goals/objectives, the following must be accomplished: 1) understand the 

characteristics of the lunar regolith and how it is produced (i.e., study lunar samples),

2) develop techniques/methodologies to reproduce the characteristics of lunar regolith,

3) understand which aspects of the lunar regolith, such as composition, particle size, particle 

shape, and density, are applicable to each individual technology being developed for use on 

the lunar surface, 4) advise simulant users on the most appropriate simulant to use for their 

individual project (i.e., notify users of the risks involved with simulant use and their 

limitations for accurately reproducing the lunar regolith and be knowledgeable of all available 

simulants), 5) collect users’ data to evaluate the effectiveness of the prescribed simulant and 

apply the results to the next generation of simulants, and 6) create a method to compare 

simulants to the lunar regolith and to other simulants quantitatively (hence the creation of the 

Figures of Merit software) for purposes of judging which simulant(s) has the best fit for the 

application.

NASA/TM—2011-217037 62
Before the lunar architecture was formulated, MSFC oversaw the SBIR Phase III contract 

with Orbitec in Madison, WI who was responsible for developing and delivering 16 tons of 

JSC-1A (a mare simulant) since the previously made JSC-1 which was made by JSC many 

years ago was all but exhausted. In order to meet the renewed interest and demand for 

lunar simulants, fourteen tons of the Medium grain size (JSC-1A); 1 ton of the Fines grain 

size (JSC-1AF); and 1 ton of the Coarse grain size (JSC-1AC) were made. Much of this 

simulant has been distributed to the user community. 

After the first lunar architecture was released in late 2005 with a proposed landing site near 

the lunar poles, a different type of simulant was required – one that represented the lunar 

polar region. Since no Apollo missions had visited the poles, there were no samples brought 

back to Earth from that locale. Thus, other means of predicting the moon’s polar regolith 

properties were required and, fortunately, some alternatives existed. Based upon lunar flybys and other “remote” research, lunar scientists were of the opinion that the polar regions 

were similar to the lunar highlands regions of the Moon. And, NASA was in possession of 

actual lunar samples from the highlands region which were brought back from the Apollo 16 

mission. 

In the mean-time, the Simulant Team at MSFC contracted with the US Geolog y ical Survey

(USGS) in Denver to assist in developing, characterizing, and producing simulants. Using 

this Apollo 16 lunar sample and research data, the first simulant created under the 

MSFC/USGS partnership was a highlands prototype simulant named “NU-LHT-1M” 

(NASA/USGS, Lunar Highlands Type, series 1, grain size Medium). Since its creation, a 

second generation (NU-LHT-2) has been produced reflecting multiple grain sizes, and a 

third is in development. Each new generation typically increases in fidelity as needed in 

order to meet the users’ test requirements. That is, each generation becomes more like the 

lunar regolith. However, it is important to note that no lunar lunar regolith. However, it is important to note that no lunar simulant simulant (however good) will (however good) will

ever replicate the actual lunar regolith 100%. Due to the differences in the weathering 

conditions due to Earth’s atmosphere as well as other factors, terrestrial Earth materials are 

more altered than the lunar regolith. 

In order to produce the NU-LHT simulant, Apollo 16 core samples were used to investigate 

and target mineralogy and composition were defined. Different feedstocks (mined terrestrial 

rocks) from around the world were investigated for suitability. Different methods of 

processing (crushing grinding milling blend processing (crushing, grinding, milling, blending and melting) were also investigated to , and melting) were also investigated to

assess how different process techniques could make the terrestrial rock “look and act” like 

lunar regolith. Once the appropriate feedstocks and processing techniques were defined, 

“recipes” were developed and production of the simulant(s) commenced. Research and 

development continues on the Simulant Task for new types of feedstock (both natural and 

synthetic) to make new types of simulants, including a high-titanium mare basalt.

The Simulant Team created an online Simulant Survey/Request Form to help identify the 

users’ needs more effectively The Team used that information to get a general idea of the needs more effectively. The Team used that information to get a general idea of the

user’s task and their objectives in using the simulant(s). The Team then contacted the user 

to establishment interfaces and clarify and verify the simulant application. In addition, this 

communication assisted the user in obtaining the best simulant for their task and to provide 

consultation and guidance in the proper use of the simulant including any downsides 

involved with the simulant selection. This method provides the most confidence that the risk 

associated with that lunar technology is reduced as much as possible, thereby, assuring 

greater mission success.

NASA/TM—2011-217037 63
Summary of Accomplishments (FY08 – FY10):

Programmatically, the last two years have been extremely productive. The Team supported 

the normal programmatic/project activities including the Technical Content Reviews, 

Integrated Baseline Reviews, PPBE exercises, and Project Plan updates. Additionally, the 

Team supported several TIMs and Workshops as requested by the customer and made 

presentations on the Simulant Task status. Other activities of the Simulant Team included 12 

conferences attended, 19 conference papers written, 13 media appearances or events 

(newspaper, Internet, and tradeshow booths), and numerous Education and Public Outreach 

events (e.g., talks to students, simulants used in educational settings, etc.). 

The Simulant Team also kept track of specific Small Business Innovative Research (SBIR) 

projects as Contracting Officer’s Technical Representatives. These SBIR projects involved 

creating lunar regolith simulant components (such as agglutinates or nanophase iron) or 

technologies for in situ resource utilization and the study of the lunar regolith. Aside from 

outreach and SBIR work, the Simulant Team focused on the simulant user’s needs. The 

Simulant Team initiated teleconferences with the simulant users to ascertain their needs and 

to provide guidance on the simulant selection(s). The Simulant Team notified the users of 

limitations of the simulant regarding how well it replicated the lunar regolith, as well as the 

safe and proper handling of simulants. Several of the documents related to simulants, 

simulant use, and other Simulant Team activities are posted on the In Situ Resource 

Utilization (ISRU) public website (http://isru.msfc.nasa.gov).

NASA/TM—2011-217037 64
The Simulant Team organized a 2009 Lunar Regolith/Simulant Users Workshop that was 

held in Huntsville, Alabama. This Workshop was attended by over 120 individuals 

representing various NASA centers including ETDPO and representing various NASA centers including ETDPO and CxP projects; industry; academia; projects; industry; academia;

and internationals. As a prelude to the Workshop, a Lunar Regolith/Simulant 101 “course” 

was conceived and held to educate users less familiar with regolith and simulants. A Survey 

was developed that is the tool for collecting regolith and simulant requirements based on 

users’ projections. Thirty-five (35) simulant requests/surveys were collected from ETDPO 

and CxP, and teleconferences/webexes were set up between the simulant user and the 

Simulant Team. This data was assimilated and analyzed to assist with forecasting simulant

types, fidelities, and quantity requirements in addition to budget requests. A Simulant Users’ 

Needs Document was written summarizing the results The Team also provided Needs Document was written summarizing the results. The Team also provided simulants simulants to

the users as supply and budgets allowed. Results from these simulant user tests have been 

collected, but others have yet to be received. 

A total of twenty-one (21) documents were written by the Simulant Team members (see 

reference list). A book is also being written, tentatively entitled “Lunar Regolith Simulant”, 

for publication by CRC Press. This book was borne out of the Simulant Project Lead’s idea 

to have a short course titled, Lunar Regolith/Simulant 101, offered as part of the 2009 Lunar 

Regolith/Simulant User s’ Workshop to assist the novice user in understanding lunar regolith Workshop to assist the novice user in understanding lunar regolith

and simulants.

NASA/TM—2011-217037 65
Summary of Accomplishments (FY08 – FY10) (Cont.):

Technologically, the Simulant Task has progressed very well. Literature searches with 

respect to lunar regolith samples were performed to define references for site-specific lunar 

regions that needed to be simulated. Once the best Apollo mission location(s) were 

identified to represent the simulant locale desired, various Apollo samples were requested 

from the CAPTEM Board for further examination if warranted. The Team was approved to 

receive Apollo 16 core samples 64001/64002 to study. Scanning electron microscopy (SEM) 

and energy dispersive spectroscopy (EDS) were employed to define the lunar highlands 

region composition (bulk chemistry and mineralogy). Particle size distributions were 

obtained from the literature as well as re-measured. Particle shape data is lacking for actual 

lunar regolith samples and is one of the properties that must still be measured using Apollo 

samples in order to produce higher fidelity simulants. Some shape data, however, using 

simulants has recently been measured and collected by KSC/Dr. Phil Metzger and is being 

incorporated into the FoM database. 

The Simulant Team developed the Figure of Merit (FoM) software from algorithms designed 

to quantitatively compare simulant properties to lunar regolith and to other simulants. The 

FoM software was updated as new data came in and comes in – from both Apollo samples 

and new simulant characterization data. The Simulant Team also designed and 

implemented efficient, effective, and economical simulant development processes for both 

the Simulant NU-LHT series prototypes and production (large scale) phases. While the team 

has made strides in these areas, more work is needed to bring the costs of high fidelity 

simulants down and to address the specific challenges such as the incorporation of nanop g hase iron in agg p lutinates. All of this progress has been described in the Simulant 

Development Recipes and Process Document. 

NASA/TM—2011-217037 66
Approximately 2000 kg of the NU-LHT series simulant was produced. In addition to

NU-LHT-2M, four other simulants (FJS-1, Chenobi, OB-1, and JSC-1A) have been 

characterized for composition, size, and shape – documentation has been developed and 

updated based on these results. Two low fidelity excavation grade simulants were recently 

produced from the NU-LHT series feedstock (one with glass and agglutinates and one 

without). Feedstock development continues, including agglutinate production (with 

nanophase iron), mineral separation techniques, and mineral synthesis to produce higher 

fidelity simulants. Work also continues on characterizing simulants not developed by the 

NASA/USGS partnership but by others for purposes of assessing their potential use for 

individual tasks (e.g., Black Point 1). In addition to simulants, material that could later be 

used to make simulants was developed for specific experiments. Case in point, a Dark Test 

Material (DTM-1) was developed by the team for GRC/J. Gaier to be used in “worst case 

scenario” thermal/spectral testing. 

NASA/TM—2011-217037 67
Remaining Tasks to be Performed:

There are still a few documents to be finalized by the Simulant Team for fiscal year 2010. 

The first is the Simulant Development Recipes and Process Document (SC-49-50). This 

document, which is being written by the USGS, will contain all the recipes and process 

controls developed and used to produce the NU-LHT series simulant prototypes. The 

second is an update to the Simulant User’s Guide, which includes the Fit-for-Purpose Matrix. 

Recent contributions of simulant user data will aid in the document update. The Fit-forPurpose Matrix advises simulant users on the simulant that will most likely meet their needs, 

and what specific limitations exist for the individual simulants with regard to specific tasks. 

However, a word of caution – the Simulant User’s Guide and “Fit-for-Purpose” Matrix are not 

meant to be used in place of conferring with simulant experts who can provide consultation 

and guidance as necessary. It is critical that engineers consult with simulant experts to 

ensure that appropriate simulants are being used properly. Finally, the Lunar Regolith 

Simulant Book will proceed towards publication. The publisher, CRC Press, continues to 

receive updates on the progress of the book. No definitive deadline has been set for its 

publication, but it is expected to be complete early spring of 2011. 

NASA/TM—2011-217037 68
TRL Status and Steps to TRL 6 Progression:

Since the Simulant Task does not involve developing flight hardware it is somewhat difficult Since the Simulant Task does not involve developing flight hardware, it is somewhat difficult

to label it in the traditional NASA-defined TRL levels. At the request of the program, though, 

the Simulant Task was estimated to be at a TRL 3 at the start of the effort. Advances in 

technologies and processes have occurred over the last few years during the making of the 

prototype simulants and, eventually, the simulants resulting in a TRL 5 rating. Examples of 

this include progress made in the separation of minerals, manufacture of synthetic minerals, 

and new milling techniques. 

I d t hi TRL 6 th In order to achieve TRL 6, there are several thi th t d t th t ill di tl d l things that need to occur that will directly and

indirectly influence the advancement of the technologies. First, the user requirements for 

simulants must be better defined which will drive simulant properties and fidelities. Next, 

more sources of different types of feedstocks (both terrestrial and synthetic) must be located 

and/or developed/manufactured. This will raise the simulant fidelity and mitigate risk to the 

hardware. One of the most important items for advancing the technology readiness is to 

develop new ways for processing/manufacturing the simulants whether it be making the 

process more efficient, less energy intensive, quicker, or more tight in quality control; any 

and all of these areas should be tackled to improve the simulant product. After the simulants 

are made (whether by NASA or others), more testing is required to verify their closeness to 

lunar regolith. In some cases as more technologies are advanced to improve measurements 

in accuracy or precision or to higher resolutions, even the Apollo lunar samples will probably 

need to be re-examined and re-studied. Proceeding from small-scale production quantities 

to large-scale quantities will require technologies that can assure quality control and product 

assurance between batches of simulants. As these areas are addressed and technologies 

matured, they should be documented in the appropriate files. It is expected that these 

advances could raise the Simulant Task from TRL from 5 to 6 in the next two to three years 

assuming the budget was provided. 

NASA/TM—2011-217037 69
Simulant Task Documentation:

Currently, a total of twenty one (21) documents have been written by the Simulant Team that 

specify any number of tasks undertaken over the last several years based on the 

achievements to date. These documents include: plans for acquiring lunar samples; user 

requirements reports; simulant applications and best uses; material safety data sheets; 

instructions for splitting samples and handling simulants; figure of merit user’s guide; and 

other publications, test reports, NASA Science and Technology Information reports, and 

deliverables. Some of these detail the plan of study for Apollo samples, the results of studies 

on the Apollo samples, and the recommendations for simulant development based on those 

samples. Other documents detail how simulants are compared to regolith via Figures of 

Merit, and the rationale behind the four properties chosen as Figures of Merit. Many 

publications document the work of the Simulant Team in defining the appropriate feedstocks, 

the process controls for simulants, and the evaluation techniques for those simulants. Of the 

twenty one publications listed here, nine are most pertinent to simulant users. These are 

specific to user’s needs, such as descriptions of simulant types, comparisons of simulants 

and regolith, recommendations for the appropriate simulants for given tasks, handling 

instructions, and material safety data sheets.

NASA/TM—2011-217037 70
Outreach and Status of Deliverables:

Numerous students and college faculty were sponsored, supported, or participated in work 

for the Simulant Task so education (STEM) and outreach endeavors were emphasized.

Kyle Chavez's first summer (2007) as a NASA intern was spent supporting several 

fabrication activities. Kyle returned for a second summer (2008) internship and set up an 

extensive Microsoft Excel (Microsoft Corporation) spreadsheet to gather and sort inputs from 

the simulant users survey questionnaire that was linked from the ISRU website. Ariel Baines 

spent one summer internship (2009) supporting the simulant activity by developing 

requirements and designing a simulant database. Rashidi Hunter (summer 2009), a 

mathematics and engineering intern from Morehouse College, worked on statistical models 

of >1 cm particles in the lunar regolith. Dr. William Cross, Department of Materials and 

Metallurgical Engineering from the South Dakota School of Mines and Technology, spent the 

summer of 2009 at MSFC and designed beneficiation techniques (specifically, mineral 

separation techniques) that can be used for simulant development or for lunar regolith 

examination. This topic continues to be researched by Dr. Cross’s senior students. Robert 

West and Alfredo Wetzel studied X-ray radiographs of Apollo 16 cores to estimate variation 

in porosity and density, as well as estimating larger particle size abundance. Intern William 

Betts (Fall 2009) worked on defining shape parameters, analyzing data for volatile loss in 

simulants, and compiling data on “extinct” simulants. Interns Emily Dixon and Matthew 

Pendleton (summer 2010) completed analysis of shape for five different simulants, although 

they were not funded specifically by the Simulant Task.

NASA/TM—2011-217037 71
The Simulant Task also produced five (5) different simulants with two levels of fidelity.

NU-LHT-1D was a first 1D was a first-generation dust generation, dust-sized simulant simulant with a target particle size of less with a target particle size of less

than 20 μm. None of the dust fraction remains available as it was all distributed to the users. 

NU-LHT-2M is a second-generation simulant with a target particle size of less than 1 mm. 

Approximately 200 kg of 2 M remains available for use. The coarsest simulant, NU-LHT-2C, 

has a particle size less than 10 cm. Just recently, two additional simulants, NU-LHT-2E 

(excavation grade with no glass or agglutinates) and NU-LHT2EG (excavation grade with 

glass and agglutinates) have been produced in amounts of 500 kg each. The excavation 

grade simulants have good physical properties but have low fidelity chemistry properties and 

are thus not appropriate for reactor processing such as are, thus, not appropriate for reactor processing such as carbothermal carbothermal methods The methods. The

NU-LHT-1D, -2M, and -2C series simulants are fairly high fidelity in both the physical and 

chemical (mineralogical) properties so are appropriate for reactor processing and 

mechanical type testing, for instance. The Simulant User’s Guide and “Fit-for-Purpose” 

Matrix are a good source of information for simulants; experts should also be consulted.

All of these simulants were completely designed, produced, and characterized by the 

Simulant Team.

NASA/TM—2011-217037 72
Lunar Regolith/Simulant Survey Results (Total Requests by Program/Project and Year):

There is a great need for simulant, as revealed by the Lunar Regolith Simulant Survey 

results. In fact, presently the quantity requested far exceeds the supply. Constellation and 

Lunar Surface Systems projects constitute the majority of the simulant requests (87%), 

primarily from the Human Robotic Systems. Exploration Technology Development 

constitutes approximately 13% of the demand. The task requiring the greatest amount of 

simulant is mobility (gears, seals, wheels, connectors), followed closely by oxygen 

extraction, excavation, and construction. Other uses that do not require much simulant are 

tasks such as dust mitigation, human health, heat transfer, fire protection, life support 

systems, and radiation shielding. Within six years, approximately 137,703 kg of simulants 

were estimated for use by all users that filled out the survey/request form. It is the great 

need for simulants by numerous tasks that makes the availability of high fidelity simulants 

and all types of simulants critical to planetary surface technology development and other 

areas.

While the Simulant Team focused on lunar simulants, they are also prepared to expand the 

suite of simulants to Mars, asteroids, and other bodies that robots, hardware, and/or humans 

will explore. The Survey is a living, breathing document that will evolve and change as 

users’ requirements change and will be updated annually as a minimum. 

NASA/TM—2011-217037 73
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NASA/TM—2011-217037 78
NASA/TM—2011-217037 79
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The Dust Management Project: Final Report 

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13. SUPPLEMENTARY NOTES

14. ABSTRACT

A return to the Moon to extend human presence, pursue scientific activities, use the Moon to prepare for future human missions to Mars, 

and expand Earth’s economic sphere, will require investment in developing new technologies and capabilities to achieve affordable and 

sustainable human exploration. From the operational experience gained and lessons learned during the Apollo missions, conducting longterm operations in the lunar environment will be a particular challenge, given the difficulties presented by the unique physical properties and 

other characteristics of lunar regolith, including dust. The Apollo missions and other lunar explorations have identified significant lunar 

dust-related problems that will challenge future mission success. Comprised of regolith particles ranging in size from tens of nanometers to 

microns, lunar dust is a manifestation of the complex interaction of the lunar soil with multiple mechanical, electrical, and gravitational 

effects. The environmental and anthropogenic factors effecting the perturbation, transport, and deposition of lunar dust must be studied in 

order to mitigate it’s potentially harmful effects on exploration systems and human explorers. The Dust Management Project (DMP) is 

tasked with the evaluation of lunar dust effects, assessment of the resulting risks, and development of mitigation and management strategies 

and technologies related to Exploration Systems architectures. To this end, the DMP supports the overall goal of the Exploration 

Technology Development Program (ETDP) of addressing the relevant high priority technology needs of multiple elements within the

Constellation Program (CxP) and sister ETDP projects. Project scope, approach, accomplishments, summary of deliverables, and lessons 

learned are presented. 

15. SUBJECT TERMS

Dust; Lunar 

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