NASA Technical Memorandum 104760

JSC Director's Discretionary Fund

1992 Annual Report

Compiled by the New Initiatives Office

Lyndon B. Johnson Space Center

Houston, Texas

National Aeronautics and Space Administration

Lyndon B. Johnson Space Center

Houston, Texas

Janua_ 1993

Preface

Johnson Space Center's (JSC) capability to identify and initiate creative research supports an important aspect of the NASA's benefit to the nation. As an independent

research medium, the Center Director's Discretionary Fund (CDDF) often initiates

investigations of significant value to the agency, with eventual spinoff to commercial

uses. The project selection criteria assures overall aid to the NASA mission, as well as

providing development opportunities for JSC's science and engineering staff.

During FY92, the Office of the Inspector General conducted a routine audit of the

CDDF. The audit did not identify any serious deficiencies. Their findings substantiated

the belief that the CDDF is one of the most effective uses of resources in the NASA

budget. The $1,694,000 funding for FY92 was distributed among 27 projects with participation across the Center directorates.

The following is a brief status report on selected projects that made outstanding

progress and produced notable results.

Several space-based medical research investigations reflect direct potential for Earth

benefits. The use of stable isotopes of deuterium and oxygen to measure crew energy utilization was developed and demonstrated in bed-rest studies. Techniques

for noninvasive administration of motion sickness medication showed promise.

Partially hydrogenated, soybean oil microspheres assured bioavailability from the

intranasal dose of promethazine.

Research on the potential of recycling essentials for crew support on spaceflights

was continued. The Regenerative Life Support Systems test bed, an integrated

biological and physicochemical life support system, tested a unique, hydroponic,

nutrient-delivery system by growing lettuce and wheat. The Hybrid Regenerative

Water Recovery System demonstrated successful processing of waste water that was

collected from shower, hand wash, laundry, and urinal sources. An 85 percent yield

of potable water was achieved - demonstrating the efficiency and stability of the

process.

Investigation of two-phase fluid flow under simulated zero gravity and low-gravity

conditions in KC-135 aircraft was continued. Excellent test results were obtained

that will provide data and verified models to support design of two-phase systems.

Preliminary results indicate the existence of a new flow regime for low-g conditions,

presently named the stratified annular regime.

IU JSC CDDF 1992 Annual Report
Natural and man-made hypervelocity particles in low-Earth orbit constitute a substantial collision hazard to spacecraft. Hypervelocity particle tests on light-weight

collisional bumpers in an open mesh pattern demonstrate a potential performance

advantage over the conventional continuous-foil shields. A related investigation at

White Sands Test Facility is evaluating the effects of hypervelocity particles on

pressure vessels.

The use of microcalorimetry for measuring the long-term compatibility of hydrazine

with selected materials has shown a good correlation in the initial short-duration

tests. Testing techniques have resulted in a patent disclosure.

A patent application was also made on the design for a shape-memory-alloy release

nut. Further, a NASA Tech Brief award was received for the concept, which will be

less hazardous than conventional explosive-release devices.

The Habitation Development Tool was demonstrated and put into use by JSC to

provide realistic computer estimates of the requirements for crew accommodations

for advanced missions and concepts. Spacecraft and surface habitat needs can be

efficiently evaluated for different crew numbers and mission durations.

Training is a major cost element in present and future NASA operations. Multi

media, videography, music, image processing, artificial intelligence, computer

graphics, databases, and data communication are _eing evaluated as supplements

to current training techniques. Virtual environment technology may also provide

alternatives to physical simulators. Laboratory evaluations are making excellent

progress in this promising field.

The Electronic Still Camera provides high resolution digital images for transmission

to the ground. Through CDDF support, the time to record an image has been reduced to 3.7 seconds, with a goal of one second p_ r image achievable.

For additional information on the projects described in this report, contact the individual investigators, or call Lyle Jenkins at (713) 283-5405.

William J. Huffstetler

Manager, New Initiatives Office

JSC CDDF 1992 Annual Report iv
Contents

Project Page

Determination of Human Energy Utilization During Space Flight Using

Doubly Labeled Water

Helen W. Lane, Ph.D ..............................................................................................

Search Coil System to Record Eye Movements for Studies of Eye, Head,

and Hand Coordination

Jacob J. Bloomberg, Ph.D ........................................................................................

Impact Experiments into Multiple-Mesh Targets

Friedrich HSrz, Ph.D ..............................................................................................

B Cell Radiosensitivity and Protection by Cytokines

Peggy Whitson, Ph.D .............................................................................................

Loading, Electromyograph, and Motion During Exercise

Linda Taggart, M.D ...............................................................................................

Sustained Release Nasal Delivery System

Lakshmi Putcha, Ph.D ............................................................................................

Electronic Still Camera Upgrades

Phyllis Grounds ......................................................................................................

Two-Phase Flow Characterization for Fluid Components and Variable

Gravity Conditions

Katy Miller ..............................................................................................................

Hybrid Regenerative Water Recovery System

Eugene H. Winkler .................................................................................................

Pershing Precision Planetary Landing Studies

Timothy E. Fisher ...................................................................................................

Shape Memory Alloy Actuators and Release Techniques

Darin N. McKinnis ................................................................................................

4

7

11

14

17

19

21

25

28

3O

v JSC CDDF 1992 Annual Report
Project Page

Performance Analysis via Taguchi Methods

Ivan Johnson .......................................................................................................... 33

Artemis Strategic Defense Initiative Engine Feasibility Demonstration

Joe Riccio ................................................................................................................ 36

Common Lunar Lander (Artemis) Mockup

William Schnieder , Ph.D ....................................................................................... 38

Adaptive Neural Net Controller for a 7-Degree-of-Freedom Robot Arm

Timothy F. Cleghorn, Ph.D ................................................................................... 41

Multimedia Applications

Lui Wang ............................................................................................................... 43

Virtual Environments for Training

Robert T. Savely .................................................................................................... 46

Onboard Training Hardware Evaluation

Ven C. Feng ........................................................................................................... 49

Pressurized Vessels Subject to Hypervelocity Particle Impact

Michelle A. Rucker ................................................................................................ 51

Long-Term Material/Fuel Interactions Predicted by l_licrocalorimetry

Radel L. Bunker ..................................................................................................... 53

Real-Time Multipurpose Monitor for Assessing Confined Atmospheres

Harold D. Beeson ................................................................................................... 56

Monitoring to Determine the Health of the Orbital Maneuvering System

and Reaction Control System

Bob Kowalsh" ......................................................................................................... 59

Assured Vision for Space Operations

Kumar Krishen, Ph.D ............................................................................................ 62

Regenerative Life Support System Test Bed Project

Donald Henninger, Ph.D ................................................................................................ 66

JSC CDDF 1992 Annual Report vi
Project Page

Lunar Surface Systems

]eri W. Brown .........................................................................................................

In Situ Resource Utilization

David S. McKay, Ph.D ..........................................................................................

Threshold Low-Cost Intermediate Technology Experiment

Mass Measurement Device

Edgar Castro ..........................................................................................................

69

73

77

vii JSC CDDF 1992 Annual Report

Figures

Figure

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

Isotope elimination preflight - one subject (STS-45) .......................................

Isotope elimination inflight - one subject (STS-45) .........................................

Damage suffered by 10 successive meshes (1 through 10) impacted

by a 3.17 mm diameter glass projectile at 5.7 km/s .......................................

Witness plates monitoring the debris that exits targets composed

of N meshes and that possess a cumulative specific shield mass of

MS; v=5.9 km/s for all experiments; width of individual frames:

0 cn_. o.,...°o.°..°o.H.°.....,°.°°o,..°.,..,°......H.,...,,°o°o ,.,,°°°...°...,.,H, *°l,., .,,o,* HH°, HI°,,°°°.O°°,O.°°,,

Effect of low dose gamma irradiation on B cell activation ............................

Summary of the promethazine release profiles from microsphere

formulations .........................................................................................................

USAF Phillips Laboratory/Foster-Miller Test Package aboard the

KC-135 aircraft .....................................................................................................

Schematic of the HRWRS ...................................................................................

Isometric view of the Artemis Vehicle without payload ...............................

Overall view of the Artemis Mockup ...............................................................

Closeup view of construction details of the Artemis Mockup .....................

A multimedia computing environment ...........................................................

A conceptual drawing of the networked multimedia

scrapbook ..............................................................................................................

Space station cupola model ................................................................................

Space Shuttle and IntellSat .................................................................................

Master plot from HYKIN for molybdenum ....................................................

Page

2

3

9

10

13

18

23

26

39

40

40

44

44

48

48

54

JSC CDDF 1992 Annual Report viii
Figure

17

18

19

20

21

22

Flow diagram of front-end of AI interface ............................. . ........................

Perception system architecture ..........................................................................

Lettuce crop growing in the variable pressure growth chamber

(VPGC) ..................................................................................................................

Hyperbaric lunar airlock concept .....................................................................

Initial Mars habitat concept ...............................................................................

Composite photo of the prototype MMD in the compressed and

deployed positions ..............................................................................................

Page

58

64

67

71

72

79

ix JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: Determination of Human Energy Utilization

During Space Flight Using Doubly Labeled Water

PROJECT MANAGERS: Helen W. Lane, Ph. D./SD4/(713) 483-9147

Everett K. Gibson, Jr., Ph. D./SN/(713) 483-6224

Randall J. Gretebeck, Ph.D./SD4/(713) 483-9945

PURPOSE OF INVESTIGATION: Establish a self-supporting laboratory using water

labeled with the stable isotopes deuterium and oxygen-18 to measure energy utilization

in humans, and to develop this technology to measure the energy utilization of crew

members during space flight.

AUTHORIZED FUNDING FY92: $60k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FYg0 FYgt FY92 FY93 FY94

In-house: $20k $40k $0 $40k $40k

Contractor: 30k 10k 60k 10k 10k

Grants: 0 0 0 0 0

RTOP, Program

or other: 0 0 0 0 0

Total funds: $50k $50k $60k $50k $50k

OBJECTIVE AND APPROACH

Exposure to microgravity induces physiological and biochemical changes that

may interfere with the health and normal

functioning of humans in space. The

availability of nutrients and the energy

(caloric) requirements in microgravity

may also differ from those on the ground.

Traditional ground-based methods for

determination of crew energy (calories)

utilization have been difficult or impossible to perform in space. Therefore, the

objective of this project is to establish a

self-supporting laboratory using water

labeled with the stable isotopes deuterium and oxygen-18 to measure energy

utilization in humans, and to develop this

technology to measure the energy utilization of crew members during space flight.

The first objective was to build and test

the analytical systems for purification of

1 JSC CDDF 1992 Annual Report
hydrogen and oxygen from human physiological specimens. From this data,

models will be developed for using

doubly labeled water (DLW) in space.

ACCOMPLISHMENTS

The hardware required to build the

isotope purification system was obtained

in FY90, and the system for oxygen analysis was completed and tested in FY90/91.

Pilot studies were conducted to validate

the precision and accuracy of the oxygen

system by splitting samples and having

our results compared with those of a

weU-established independent laboratory.

Pilot studies to validate the precision and

accuracy of the hydrogen purification

system were completed in FY91 by using

international water standards. The methodology employed in the oxygen analysis

used a novel approach which is not well

known in some scientific areas, so a

preliminary methods study was reported

at the International Conference on Geochronology, Geochemistry, and Isotopic

Geochemistry in Canberra, Australia, in

1990. A manuscript based on this report

has been published (ref. 1). Preliminary

studies have also been conducted to measure the isotopic concentration of water

used in the Orbiter. This water is produced as a by-product of the fuel cells

and is used by the crew for drinking and

food preparation. These studies have

found that this water has a higher concentration of deuterium and oxygen-18

than the normal ground water used to fill

the Orbiter potable water tanks prior to

launch.

A ground-based, bed-rest study supported by the extended duration Orbiter

(EDO) to measure energy utilization in

adult men was completed in FY92 and

preliminary results have been published

in abstract form (ref. 2). A simulated

Orbiter water study supported by Research and Technology Objectives and

Plans Program funds to test the effects of

drinking water with isotopic enrichments

similar to those found on the Orbiter has

been completed, and portions of this

study have been presented at the 43rd

Congress of the International Astronautical Federation. Another study utilizing

the technology developed by this project

to determine total body water by deuterium dilution was submitted to the Aerospace Medical Association for presentation at the 1993 annual meeting. A flight

study supported by the EDO has been

conducted on STS-45 and STS-47, which

used DLW to measure energy utilization

in crew members during spaceflight.

Figure I shows the preflight, and

8.40

"3 8.28

Z_ 8.16

0

9

O

14

_ 7,92

780

NERGY INTAKE " 11,3111 Kj/dsy (2723 k_l/d4y)

DEUTERIUM

y " -0.0878x * 8.383

RVal 0.997

OXYGEN-I. _

y"-_108x- 8.401 _,,_

• i ivel " 0 GiE9

1 2 3 4 5

TIME (DAYS)

ENERGY EXPENOITDRE - 9,774 kj/day (2335 kcsl/day)

Figure 1.- Isotope elimination preflight - one

subject (5TS-45).

JSC CDDF 1992 Annual Report 2
Figure 2, the inflight isotope elimination

rates for one subject on STS-45.

In summary, we now have in place a

"state-of-the-art" laboratory for using

DLW to measure energy utilization. With

this laboratory in place we have been able

to obtain funding from EDO and RTOP to

conduct ground-based as well as flight

studies.

PLANNED FUTURE WORK

Future efforts include developing models

to determine optimum dosing, sample

collection, and data analysis protocols for

use during Shuttle flights, and determine

the effects of recycled water on the

accuracy of DLW for use on Space Station

Freedom. Studies are in progress comparing the use of saliva versus urine

samples on the accuracy of the DLW

method to ease sample collection in

space, and obtain data from female crew

members. Modifications of the oxygen

purification system are being planned to

accommodate microliter sample sizes,

which are necessary due to difficulties in

collecting large amounts of physiological

fluids during space flight. In addition, a

methodology study for deuterium analysis will be conducted. The flight study

which began with STS-45 and STS-47 has

been manifested on STS-58 and STS-60,

and will continue until 36 subjects have

been tested.

REFERENCE DOCUMENTS

8.40

w

N

_ 8.2g

Z_ 6.16

0

q

• 8.07

0

_< 7.96

a

7,85

0

Flight day F03

NERGY INTAKE " g,lS40 K_Oey (2303 k©lllldly)

_ DEUTERIUM

_._ Y " "O'OBr'x " 83966

y - -o.o_, .. 8.3,1999 __..._

04 2 3 4 5 6

F FO5 FD6 FO7 FOB FDg

TiME {DAYS)

ENERGY EXPENDITURE - 10,984 kj/day (2624 kcallday)

Figure 2.- Isotope elimination inflight - one

subject (STS-45).

,

.

Socki, R.A.; Karlsson, H.R.; and

Gibson, E.K. Jr.: Extraction technique for the determination of

oxygen-18 in water using

preevacuated glass vials. Analytical Chemistry, 64(7), 1992,

pp. 829-831.

Gretebeck, R.J.; Davis-Street J.;

Shoeller, D.; and Lane, H.W.:

Energy regulation during ten days

of simulated microgravity.

FASEB J., vol. 6,1992, Al117.

JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: Search Coil System to Record Eye Movements

For Studies of Eye, Head, and Hand

Coordination

PROJECT MANAGER: Jacob J. Bloomberg, Ph.D./SD5/(713) 483-0436

IN-HOUSE TEAM MEMBER: William P. Hueb.ner, Ph.D.

PURPOSE OF INVESTIGATION: Determine how adaptive modification of visualvestibular interaction affects eye, head, and hand coordination, enabling predictions to

be made concerning crew responses in the space environment.

AUTHORIZED FUNDING FY92: $30k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

EXtl FY92 FY93 FY94

In-house: $50k $30k $15k 0

Contractors: 50k 0 0 0

Grants: 0 0 0 0

RTOP, Program

or other: 0 75k 75k 75k

Total funds: $100k $105k $901,-. $75k

OBJECTIVES AND APPROACH

The central nervous system integrates

multisensory information to determine

body spatial orientation relative to the

environment. Exposure to microgravity

during space flight induces alteration in

this internal construct producing perceptual and sensory-motor disturbances

during adaptation to zero g and readaptation to a one-g environment. With

plans for extended duration missions

(specifically, involving development of

the proposed Space Station and future

missiov.s to Mars), these alterations in

perceptual and sensory-motor constructs

are of 1:articular importance.

The ability to accurately coordinate eye,

head, aad hand movements is essential

for safe Shuttle operation. Astronauts'

vestibular responses are known to change

both or achieving orbit and following

return to Earth. Little is known, however,

JSC CDDF 1992 Annual Report 4
about the role vestibular information

plays in the coordination of eye, head,

and hand movements. Therefore, the first

objective of this study is to investigate the

role vestibular information plays in the

formulation of goal-directed eye and

hand localization of targets.

The second objective of this study is to

determine if adaptive alterations in eyehead coordination produce commensurate alterations in the ability to manually

locate target positions; and conversely, if

adaptive modification in eye-hand coordination transfers to the eye-head system.

This investigation will help elucidate the

basic mechanisms underlying the spatial

programming of coordinated eye, head,

and hand movements along with their

adaptive properties.

Subjects are seated on a rotatable chair for

presentation of whole-body, passive

rotation. Following termination of a

transient rotational displacement, in

darkness, they are asked to point and

generate eye movements toward the

position of a previously seen, stationary,

Earth-fixed target; the errors between the

perceived and true target positions are

recorded. These tests are repeated following exposure to stimuli which cause

various combinations of visual, vestibular, and proprioceptive conflict. Postadaptation test results will help determine the adaptive transfer characteristics

between the eye-head and eye-hand

systems based on observed errors in

manual and ocular localization of the

stationary target.

Developing a basic scientific understanding of the underlying mechanisms involved in the adaptation process will aid

in the identification and testing of

countermeasures that will reduce or

eliminate the risk associated with these

neural adaptive changes. A countermeasure which can readapt one system may

actually help readapt all of these sensorymotor systems. Conversely, it may be that

each system needs its own readaptation

countermeasure.

Measurement of Gaze, Head, and Arm

Motion

The angle of gaze (angular eye position

with respect to space) and head rotation

is obtained directly using a magnetic

field/scleral search coil technique with a

6-ft 3 field coil system (CNC Engineering,

Seattle, WA). This system basically works

as follows. A rotating magnetic vector is

established about the subject using field

coils driven by an oscillator. The subject

wears a contact lens (sylastic annulus)

with a coil of very fine copper wire embedded in it. The alternating magnetic

field induces a minute current within this

search coil. The phase of the signal induced in the search coil is compared with

the phase of the signal induced in a

stationary reference coil using special

phase-detector amplifiers. The resulting

phase difference indicates the angle of the

coil (and thus, the angle of the eye) in

space. A similar coil may be attached to

the head to measure angular head position.

A commercially available, active matrix,

liquid-crystal-display computer projection system has been used to measure the

ability to point toward targets following

rotation. With this system real-time

measurement of hand-pointing trajectories can be obtained using a small, handheld laser.

5 JSC CDDF 1992 Annual Report
FY 92 ACCOMPLISHMENTS PLANNED FUTURE WORK

A unique, state-of-the-art, experimental setup designed to investigate eye,

head, and hand coordination following vestibular input was established.

A laser pointing system that derives

and measures hand-pointing accuracy

was developed and integrated into the

program.

The experimental program funded by

the Research and Technology Objecfives and Plans Program has been

implemented, work continues.

These experiments will provide the initial

ground-based data required for a basic

understanding of the possible interactions

between various sensory-motor systems

when one or more of these systems has

been altered. In the future, we hope to

perform similar experiments on upcoming Spacelab missions that will include

SLS-4 (Neurolab) and the Shuttle-Mir

Biomedical I Mission (SMB-1).

JSC CDDF 1992 Annual Report 6
TITLE OF INVESTIGATION: Impact Experiments into Multiple-Mesh

Targets: Concept Development of a LightWeight Collisional Shield

PROJECT MANAGER: Friedrich H6rz, Ph. D. / SN4 / (713) 483-5042

PURPOSE OF INVESTIGATION:

protection of spacecraft.

Develop light-weight coUisional shields for

AUTHORIZED FUNDING FY92: $45k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

In-house: $0 $0 $0

Contractor: 35k 45k 50k

Grants: 0 0 0

RTOP, Program

or other: 0 0 0

Total funds: $35k $45k $50k

OBJECTIVE AND APPROACH

Natural and man-made hypervelocity

particles in low-Earth orbit constitute a

substantial collision hazard to spacecraft.

Suitable protection can be provided by

passive shields, mounted at some standoff distance from the flight system, that

intercept the projectile and cause it to

fragment, melt and vaporize, decelerate,

and disperse. Acceptable shields must

decrease the specific energy particle (erg/

an 2) encountered by a flight system to

some threshold value which can be

tolerated by the system. Substantial

efforts are under way to develop acceptable shields of minimum specific shield

mass (g/cm 2) that will keep launch mass

and associated costs low ( ref. 1).

The current feasibility study argues that

shock physics does not demand a laterally contiguous shield, the traditional

approach. Relatively transparent meshes

should suffice, provided their meshopening (M) is smaller than the diameter

of a prospective projectile (Dp), and as

long as the mesh wires are tl_ck (T)

7 JSC CDDF 1992 Annual Report
enough to disrupt the impactor. It was

demonstrated via DDF funds in FY91 that

T of single meshes (ref. 2) is equivalent to

T of contiguous sheets (ref. 3) in controlling the degree of projectile fragmentation. The current effort explores the

effects of multiple meshes and repetitive

shock interactions as theorized in reference 4 and as experimentally demonstrated for contiguous shields by reference 5.

FY92 ACCOMPLISHMENTS

The project utilized soda-lime glass

projectiles of 3.175 mm diameter, at

1-6 km/s impact velocity, and target

meshes constructed from aluminum that

had wires 0.25-1.59 mm thick; meshopenings were 3.175 and 1.59 mm, i.e., 0.5

and 1.0 Dp. Typical experiments employed 5 6r 10 meshes and specific shield

masses ranged from 0.08 to 1.71 g/cm 2.

This compares to 0.467 g/cm 2 for the

projectile and to 3 g/cm 2 for a single

aluminum sheet at the ballistic limit

(T=11 mm) at projectile speeds of 6 km/s.

Thus, most tests employed light-weight

shields indeed. A witness plate was

placed behind each target to monitor the

ensuing debris cloud and assess the

damage suffered by a prospective flight

system. The following variables were

addressed: impact velocity(V); separation distance (S) of successive meshes;

total, specific shield mass (SM), and

mesh-size (M).

Figures 3 and 4 represent typical experimental products and results. Figure 3

shows the damage sustained by each of

10 suco_sive meshes. Note that mesh 9

and 10 were not damaged at all. Figure 4

portrays the damage suffered by the

witness plates as the number of meshes

increases from I to 10. It is obvious that

increasing numbers of meshes increasingly comminute the impactors to

generate progressively less damage on

the witness plate. Note that experiment

982 (fig. 3 ) uses meshes of M=0.5 Dp,

while all other experiments in Figure 4

employ meshes of M=I.0 Dp (at essentially constant shield mass; 5M). The

effects of mesh size (M) are thus to afford

more physical interactions and increased

comminution, coupled with increased

deceleration of the debris based on the

shallow nature of witness-plate craters.

The effects of separation distance (S) are

pronounced as well, because the incipient

debris cloud is permitted to increasingly

dispersewith increasingS. This resultsin

a significantlydifferentdepositionof

kineticenergy intosuccessivemeshes and

ina decTeasedspecificenergy (=ergs/

cm2) forthatdebriswhich reachesthe

witnessplate.The specificSM does

controlcomminution and decelerationof

the debrisdoud, yet massive mesh

shieldsareasundesirableas massive

contiguous platesbecause the mass

displao._dfrom theshielditselfwillfrequentlyexceed projectilemass, thus

adding tothe orbitaldebrisproblem. The

effectsofvelocity(V) aremodest. The

multiplemeshes resultin qualitatively

similarwitness-platedamage over the

entire,#elocityrange investigated,

I-6km,'s. This isa most desirableshield

properlybecause singlesheetpenetrationsare highlyvelocity-dependent.

JSC CDDF 1992 Annual Report 8
Figure 4.- Witness plates

monitoring the debris that exits

targets composed of N meshes

and that possessa cumulative

specific shield mass of MS;

V=5.9 km/s for all experiments;

width of individual frames:

30 crr_

 Spectfic

Mass (SM)

5

i/iiiiii_ _!_

!i iiiiiil iiiiii!iii

o

.

H6rz F. et al.: (1992b) Dimensionally

Scaled Penetration Experiments.

Article submitted to the International Journal of Impact Engineering.

HSrz, F.: Discontinuous Meteorite

Bumper; Patent Disclosure,

NASA JSC, May 1990.

. Cour-Palais, B.G. and Crews, J.J.: A

Multi-Shock Concept for Space

Craft Shielding, International

Journal of Impact Engineering.,

vol. 10, 1990, pp. 135-146.

JSC CDDF 1992 Annual Report 10
Figure3.- Damagesufferedby10

successive meshes (1 through 10)

impacted by a 3.17 nun diameter

glass projectile at 5.7 km/s. Note,

for internal scale, mesh opening M

is 1.59 mm or 0.5 D

p.

T _ O_2_lOmm

H m I0

S w 25_mm

i10

PLANNED FUTURE WORK REFERENCE DOCUMENTS

The present experimental conditions

were designed to permit direct comparison with single-sheet penetrations that

were sponsored from non-DDF sources

(ref. 3). This limits direct comparison

with other light-weight shield

developments (e.g., ref. 1, ref. 5). Mesh

experiments that constitute high-fidelity

analogs to the light-weight shields of

reference 5 are planned for FY93 to quantify such comparisons.

1

,

Christiansen, E.L.: Performance

Equations for Advanced Orbital

Debris Shields, AIAA 92-1462,

1992.

H6rz, F. et al.: (1992a) Comparisons

of Continuous and Discontinuous Shields, NASA TM 104749,

1992.

9 ]SC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: B Cell Radiosensitivity and Protection by

Cytokines

PROJECTMANAGER: Peggy Whitson, Ph.D./SD4/(713) 483-7046

IN-HOUSE TEAM MEMBER: Clarence F. Sams, Ph.D./SD4/(713) 483-7160

PURPOSE OF INVESTIGATION: Determine if naturally produced hormones,

termed cytokines, were capable of modifying the radiosensitivity of antibody-producing B cells.

AUTHORIZED FUNDING FY92: $25k

FUNDING EXPENDITURES AND PROJECTIONS:

FYg0 FY91 FY92

In-house: $0 $0k $0k

Contractors: 0 35k 25k

Grants: 0 0 0

RTOP, Program

or other: 0 0 0

Total funds: $0 $35k $25k

OBJECTIVE AND APPROACH

A number of naturally occurring hormones, termed cytokines, have been

shown to be capable of protecting lymphocytes from ionizing radiation under both

in vivo and in vitro conditions. This property is believed to be due to the ability of

these agents to reduce the transition time

from a radiosensitive quiescent (Go) state

to a less radiosensitive activated (G1)

state. Mature bone-marrow derived

lymphocytes, or B cells, circulate

throughout the vascular system in a

quiescent state exhibiting a relatively

high radiosensitivity to ionizing radiation. Because B ceils are solely responsible for the production of antibodies,

and, as such, are indispensable for human

survival, their radiosensitivity (particularly during long-duration space flights)

could lead to immune suppression which,

in turn, could severely limit the mission

goals or threaten crew members' lives. It

was hypothesized that the well-characterized inhibitory effects of sublethal (low

dose) radiation on B-cell activation by

antigenic or mitogenic stimuli damaged

11 JSC CDDF 1992 Annual Report
specific radiosensitive sitesin the lymphocyte activation cascade.This inherent

radiosensitivity of one or more activation

events would then be responsible for

precluding lymphocyte entry into the cell

cycle and subsequent differentiation into

antibody-producing cells. This project is

now in the process of identifying the

activation event(s) that are radiosensitive,

and thus, most likely to be involved in

the differential radiosensitivity between

quiescent and activated B lymphocytes.

It was further hypothesized that pretreatment of B lymphocytes with specific

permissive cytokines abrogates or significantly reduces B cell radiosensitivity. To

perform these studies, purified human

peripheral B cells are gamma-irradiated

at the University of Texas Medical Branch

(UTMB) and analyzed at the Johnson

Space Center using both tissue culture

and molecular biology techniques and

equipment.

FY92 ACCOMPLISHMENTS

B Lymphocyte Purification

Several B cell purification protocols were

investigated for their abilities to eliminate

T cells, monocytes, and NK cells from

peripheral blood "buffy coats." When

lymphocytes were eluted from a CD19-

bead column, >99 percent of the

unattached cells were CD 3 + (T cells).

However, the attached cells were only

45 percent CD 20 + (B cells). In a second

protocol, lymphocytes were incubated

with monoclonal antibodies directed

against T cells, monocytes, and NK cells.

Following incubation, the final cell pellet

contained no detectable monocytes,

10 percent T cells and 85 percent B cells.

Therefore, this procedure was adopted

for the studies described below.

B Cell Activation by $. aureus Cowans I

(SAC)

Formalin treated SAC can activate B cells

via both protein kinase C and protein

tyrosine kinase systems. Additionally,

SAC activated cells are capable of

proceeding through cell division and

ultimately differentiating into antibodyproducing cells. Prior to our radiosensitivity studies, we ran several experiments to determine the optimal concentration of SAC needed for B cell activation. The results of these studies

indicated that a 1:3000 dilution of SAC

stock solution resulted in a maximum

increase in B cell metabolism.

B Cell Radiosensitivity

Purified B ceils were rested overnight in

RPMI-1640 media containing 10 percent

fetal calf serum, then removed from the

incubator and subjected to either 0, 25 or

100 cGy of gamma irradiation (137Cs

source; 79.7 cGy/min) then returned to

the incJbator for 2 hours. At this time

approl_riate samples were activated with

SAC a1_d returned to the incubator for an

additional 70 hours. All samples were

pulsed with bromodeoxyuridine (BrdU;

10 ttM) for 2 hours and fixed in ice cold

70 percent ethanol. Following this procedure, the samples were permeabilized

with T _¢een 20 and incubated for 30

minutes with a fluorescent conjugated

antibody to BrdU, then washed and

resuspended in propidium iodide. Then

the saxnples were analyzed for fluorescence by flow cytometry using an EPICS

JSC CDDF 1992 Annual Report 12
(a)

i

<c) I

.j "-"

I --

(b)

'..- :

--. °

(d)

.:",__:. •

Log Red Fluorescence

Figure 5.- Effect of low dose gamma irradiation

on B cell activation.

V instrument. In figure 5, Go/G1 cells

are identified in quadrant 3 (lower left);

S phase cells are identified in quadrants

I and 2 (top); and G2/M phase cells are in

quadrant 4 (lower right).

Panel (a): Resting B cells were primarily

in Go/G1 phase (90.5 percent) with

few in S (1.2 percent) and G2/M (5.6

percen0 phases.

Panel (b): Cells activated, but not

irradiated, now show a significant

increase in S phase (11.6 percent),

similar G2/M (4.2 percent) and

reduced Go/G1 phase (84.1 percent).

Panel (c): Cells irradiated (25 cGy), then

activated, exhibit a small reduction in

activation; S phase is reduced to 9.8

percent, Go/G1 is 85.2 percent, and

G2/M is 5.0 percent.

Panel (d): Cells irradiated (100 cGy), then

activated, exhibit a significant

reduction in activation; S phase is

down to 4.0 percent and more of the

cells remain in Go/G1 (87.4 percent).

These results suggest that low-dose

gamma irradiation can significantly

interfere with B cell activation events.

PLANNED FUTURE WORK

A Research and Technology Objectives

and Plans (RTOP) proposal was submitted to the Radiation Health RTOP.

The proposal has not been reviewed due

to a lack of new funding for this RTOP.

13 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGER:

PURPOSE OF INVESTIGATION:

Loading, Electromyograph, and Motion During

Exercise

Linda Taggart M. D./SD2/(713) 483-3610

Describe muscle activation patterns, motion, and

loads in relation to biomechanical segments of the musculosketetal system using exercise equipment designed for shuttle use.

AUTHORIZED FUNDING FY92: $57k

FUNDING EXPENDITURES AND PROJECTIONS:

FY91

In-house: $0

Contractors: 0

Grants: 0

RTOP, Program

or other: 0

Total funds: $0

(Projected)

FY92 FY93

$8k $0 $0

49k 40k 0

0 0 0

11k 0 0

$68k $40k $0

OBJECTIVE AND APPROACH

Astronauts experience decreased loads

while living and working in space which

results in decreased bone strain. The

human skeleton responds to mechanical

strain, a function of bone-loading conditions and bone strength, by remodeling in

the lines of stress. Bone is deposited when

strain increases and is reabsorbed when

strain decreases. Bone strength is decreased exponentially when bone density

decreases, as bone strength is proportional to density squared for trabecuiar

bone. Remodeling may result in bone

mass altd architecture unsuited to a

return to gravitational loading and place

the astronaut at risk for stress fractures

and traumatic fractures. Significant calcium less from bone remodeling occurs in

long-duration flights, with Skylab astronauts losing 4.5 percent and 7.9 percent

from the Caicaneus during the 84-day

mission.

Exercise countermeasures should be

designed to simulate the loading pattern

to which the astronauts' skeletons are

modeled to decrease the resorption and

be effective for skeletal

JSC CDDF 1992 Annual Report 14
maintenance and calcium homeostasis.

Measurement of the factors involved in

mechanical loading of the skeleton can

give an idea of the accuracy of the simulation and allow adjustment of exercise

equipment and protocols prior to the

development of long-term changes. This

will speed the countermeasures development process, and decrease risk of acute

and cumulative musculoskeletal injury to

the astronauts. Muscle activity, body

segment motion, and externally applied

loads contribute to skeletal loading and

remodeling. Description of these factors

during exercise in one g creates a basis for

comparison of the accuracy of exercise in

reproducing these loading factors in

weightlessness.

Loading factors of muscle activity, externally applied loads, and motion of the

biomechanical segment can be measured

with skin-mounted electromyograph

(EMG) electrodes and accelerometers and

with load cells and tensiometers on

exercise equipment/body contact interface. Body kinematics can be determined

through accelerometers and a video

camera. Measurements can be made in

the lab while the subject is exercising on

the bicycle ergometer and on the treadmill.

The methodology to describe muscle

activation patterns, motion, and loads in

relation to biomechanical segments of the

musculoskeletal system of volunteers,

using exercise equipment designed for

shuttle use, will be developed and

proven. Descriptive analysis will be

performed for EMG and external loads

magnitudes, directions, and durations,

and for concomitant body segment

motion.

Anticipated results

The product will be an analysis of EMG

activity, body part accelerations, externally applied loads, and relative body

segment positions over time during

exercise on shuttle equipment used on the

ground. These same measurements can

be performed during exercise in space

using the developed methodology. The

accuracy of exercise countermeasures in

space in duplicating the musculoskeletal

loading conditions of exercise in gravity

can be determined and used to develop

countermeasures that are effective for the

maintenance of skeletal strength. In

addition, data collected to assist in countermeasure development can be utilized

for mathematical modeling of loads and

expected bone remodeling. [The mathematical model assumes a steady state,

requires the appropriate laboratory

development of transfer functions for the

EMG to load and for verification of methodology, and ignores time dependency

until further basic research defines time

function.

FY92 ACCOMPLISHMENTS

• October 1991 - July 1992: Acquired

hardware: Teac 28 channel

August 1992: Tested EMG preamplifiers and utilized them to support exercise study

September 1992: Received math

processing software; interface software; and cables or computer. Requested computer memory upgrade

and math coprocessor received tension

and compression load

15 JSC CDDF 1992 Annual Report
PLANNED FUTURE WORK

• November 1992: Testequipment and

software

• December 1992- February 1993: Data

acquisition

• December 1992 - May 1993: Data

analysis

June - August 1993: Write report and

proposal to apply techniques to measurement in space and to compare

them

JSC CDDF 1992 Annual Report 16
TITLE OF INVESTIGATION: Sustained Release Nasal Delivery System

PROJECT MANAGER: Lakshmi Putcha, Ph.D./SD4/(713) 483-7760

PURPOSE OF INVESTIGATION: Develop a sustained-release-dosage delivery

system for promethazine.

AUTHORIZED FUNDING FY92: $30k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FY92 FY93 FY94

In-house: $0 $15k $30k

Contractors: 30k 0 0

Grants: 0 30k 15k

RTOP, Program

or other: 0 0 5k

Total funds: $30k $45k $50k

OBJECTIVE AND APPROACH

The objective of the proposed project is to

identify and develop a sustained-releasedosage form of promethazine that can be

administered by a noninvasive route

(intranasal) to crew members during

spaceflight for the control of motion

sickness symptoms.

Several polymeric systems [polymethylmethacrylate (Eudragit RL) and cellulosic

based polymers] will be tested for their

ability to provide sustained release of

promethazine hydrochloride. Microspheres, 50-100um in size, will be prepared by a rotating disc method. The

micros-pheres contain 50 percent active

drug by weight.

Microencapsulation, coupled with controlled release technology, will be utilized

to produce novel delivery systems. In

vitro and in vivo experiments will be

conducted to characterize the delivery

kinetics and bioavailability, respectively.

ACCOMPLISHMENTS

Microsphere formulation of promethazine was successfully synthesized with

six different microsphere carrier systems.

17 JSC CDDF 1992 Annual Report
Releasekinetics of theseformulations

were tested by in vitro drug release techniques (rotating basket method, USP

XXII) and compared to neat drug dissolution in a pH 7.0 buffer at 37°C. The

release kinetics resulting from combining

neat drug with a potential carrier

(monoglyceride cubic phase gel, which

may be used to maintain the microspheres of the drug) was also tested.

Finally, the ethylcellulose microsphere

formulation was incorporated in a gel

carrier (monoglyceride cubic phase gel)

and tested for in vitro release characteristics. Results of these experiments are

presented in Figure 6. The KLX (partially

hydrogenated soybean oil) microspheres showed promising release characteristics at the 50 percent loading

(fig. 6). This formulation was later

modified to achieve complete release

i i 1 i I I i

6O

O

_ 40

2O

0 I I I I } I J

0 1 2 3 4 5 6 7 8

Time in Hours

Figure 6.- Summary of the promethazine release

profiles from microsphere formulations.

within 5 hours. This was required to

assure maximal bioavailability from the

intrana._al dose, which has a limitation of

short residence time.

PLANNED FUTURE WORK

Preliminary animal studies will be conducted in canines to determine the pharmacokinetics and bioavaflability of the

sustained-release formulation. Absolute

bioavailability will be determined by

comparing the intranasal dosage form to

intravenous injection of promethazine

hydroc_oride.

A Research and Technology Objectives

and Plans (RTOP) proposal will be prepared and submitted for funding to

conduct clinical evaluation of the new

formulation and for comparative efficacy

studies.

REFERENCE DOCUMENTS

Ii Geary, R.S. and Lew, C.W.: Formulation development of a novel

nasal delivery system for

promethazine. Grant proposal,

Southwest Research Institute,

San Antonio, Texas, 1992.

2, Ra}'2mev, N.: "Development of

tablets with prolonged action,

containing promethazine hydrochloride. W."Pharmacokinetic

investigation of promethazine

hydrochloride following oral

administration in rabbits," Probl.

Farmacol. Farm., 1, 1987,

pp. 18-26.

JSC CDDF 1992 Annual Report 18
TITLE OF INVESTIGATION: Electronic Still Camera Upgrades

PROJECT MANAGER: Phyllis Grounds/SP43/(713) 483-7479

IN-HOUSE TEAM MEMBER: S. Douglas Holland

PURPOSE OF INVESTIGATION: Provide for improvements to the Electronic Still

Camera (ESC) System, which will increase the camera's capabilities to record and transmit high resolution digital images to the ground from orbiting spacecraft.

AUTHORIZED FUNDING FY92: $60k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FY91 FY92 _ FY94

In-house: $0 $0 $60k $50k $0

Contractors: 0 0 0 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other: 0 0 0 0 0

Total funds: $0 $0 $60k $50k $0

OBJECTIVE AND APPROACH

The objective of this task is improving

JSC's ESC to provide NASA with a high

resolution digital camera system which

can be utilized in lieu of film cameras on

long-duration missions. The ESC has

flown on four Shuttle missions as a Detailed Test Objective with great success,

but has been limited to recording one

image every 15 seconds. Also, the camera

has only one fixed film speed (ASA or

ISO equivalent). This limits the selection

of exposures that can be used to photograph a given scene. The current task is

to decrease the time to take and record an

image to one second, and provide a

minimum of three selectable ASA equivalents. This will be accomplished by

incorporating an 80386SL microprocesser

chip set to replace the obsolete 8088

processer currently being used, which

will increase the system speed, incorporating a faster hard disk drive, reducing

19 JSC CDDF 1992 Annual Report
the electromagnetic noise in the analog

circuits, and boosting the gain on the

read-out amplifiers selectively.

FY92 ACCOMPLISHMENTS

The task got a late start in FY92, but much

has been accomplished. The circuitry for

the 80386SL has been designed and

breadboarded. Testing of the breadboard

with the camera is in progress. Testing of

several new hard disks is also in progress.

The record time has been reduced to 3.7

seconds per image without doing anything to optimize the system. A record

time of one second per image should be

easily achieved. Methods of reducing the

electromagnetic noise in the analog circuits are currently being investigated. A

good deal of work still remains to be

done in this area.

PLANNED FUTURE WORK

An effort to develop a laboratory prototype camera with a higher resolution

imaging sensor is planned to be completed in FY93. This upgrade will incorporate a 2048 x 2048 charge-coupled

device imaging sensor and the necessary

circuit changes, along with the current

upgrades, into a laboratory-prototype

camera.

JSC CDDF 1992 Annual Report 20
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBER:

PURPOSEOF INVESTIGATION:

Two-Phase Flow Characterization for Fluid

Components and Variable Gravity Conditions

Katy MiUer/EC2/(713) 483-4546

John Dzenitis - Co-Project Manager

Investigate gas-liquid flow regimes and pressure

drops in tubing and components, and two-phase flows for variable gravity conditions

applicable to the Space Station Freedom and Moon/Mars exploration.

AUTHORIZED FUNDING FY92: $55k

FUNDING EXPENDITURES AND PROJECTIONS:

FYg0 FY91

In-house: $0 $5k

Contractors: 0 0

Grants: 0 45k

RTOP, Program

or other: 0 120k

Total funds: $0 $170k

(Projected)

$50k $0 $0

0 0 0

5k 0 0

108k 0 0

$163k $0 $0

This program was planned as a 2-year effort. The program was terminated in FY92

when the test equipment was returned to the USAF Phillips Laboratory, at the

completion of the 2-year loan period.

OBJECTIVE AND APPROACH

This program was initiated in FY91 to

investigate gas-liquid flow regimes and

pressure drops in tubing and components

and two-phase flows for variable gravity

conditions.

The JSC Director's Discretionary Fund

Program provided for the variable

21 JSC CDDF 1992 Annual Report
gravity testing to support the development of thermal control systemsfor the

Moon and Mars missions. In addition,

both the Propulsion and Power Division

and the Crew and Thermal Systems

Division at (JSC) provided Space Station

funding to investigate flow regimes and

pressure drops expected in the Space

Station Active Thermal Control System

(ATCS) and Utility Distribution System.

The objectives of this program included

A study of the two-phase flow

phenomena in fluid components (e.g.

smoothpipes, bellow lines, quick

disconnect fittings) at zero-g

conditions

• An expansion of the data base for twophase flow for zero-g conditions

Development of a data base for twophase flow for low-g conditions (e.g.

Moon-g, Mars-g)

• Validation of models for two-phase

flow analysis

Providing data and models to support

the Space Station ATCS and future

two-phase systems design

Zero-g and low-g data were gathered

using the USAF Phillips Laboratory/

Foster-MiUer experiment package, which

was on loan to JSC for the duration of this

program. Initially, test flights were

conducted aboard the NASA KC-135

aircraft at Ellington Air Field to ensure

that all instrumentation for the

experiment package could operate

adequately in the KC-135 test environment. Five test flight series were conducted and dedi-cated to collecting the

two-phase flow data. Ground testing was

conducted at Texas A&M University in

conjunction with the flight series to

provide a one-g data base. Since the final

testing was completed in August 1992,

extensive data reduction and analyses

have been conducted.

FY92 ACCOMPLISHMENTS

Flight series were conducted aboard the

KC-135 aircraft in November and

December 1991 and in January and July

of 1992. Figure 7 shows the USAF

Phillips Laboratory/Foster-Miller

experiment package in its test configuration aboard the KC-135 aircraft.

Ground testing was also conducted at

Texas A&M University from March to

August of 1992. Extensive data reduction

and analysis have been ongoing

throughout FY92.

A large flow-regime data base has been

developed for smooth tubes in four

gravity levels (i.e. zero-g, Moon-g,

Mars-g, one-g). Preliminary results

indicate the existence of a new flow

regime for low-g conditions, presently

named the stratified annular regime.

This regime is similar to the annular

regime seen in zero-g with the exception

that the fluid film coating the tube is

much thicker on the bottom due to the

low-gravity effects.

JSC CDDF 1992 Annual Report 22
Figure7.-USAF

PhillipsLaboratory/Foster-Miller

Experiment

Package aboard

theKC-135

aircraft.

More limited pressure drop data was

also obtained from the testing for the

smooth tubes and component test

sections for zero-g and low-g conditions.

Analyses are continuing to finalize this

data for the report.

Program results and applications to the

Space Station and future programs will

be documented in an internal JSC report,

"JSC-32261 Two-Phase Flow Characterization for Fluid Components and Four

Gravity Levels" scheduled to be

published in early FY93.

PLANNED FUTURE WORK

The JSC Crew and Thermal Systems

Division plans to pursue a flight

experiment related to two-phase flow

research in support of future programs.

In addition, future Research and

Technology Objectives and Plans (RTOP)

proposals may be initiated to develop

two-phase thermal control systems for

the Moon and Mars missions.

REFERENCE DOCUMENTS

lo Best, Frederick, Miller, Kathryn M.

and Reinarts, Thomas: Refrigerant

12 Zero-Gravity Flow Regime Data

from KC-135 Flight Testing,

Proceedings of the Fifth

International Meeting on Nuclear

Reactor Thermal Hydraulics,

September 21-24, 1992.

23 JSC CDDF 1992 Annual Report
. Dzenitis, John M., and Miller,

Kathryn M.: Two-Phase Flow

Characterization for Fluid

Components and Variable Gravity

Conditions. Proceedings of the 9th

Symposium on Space Nuclear

Power Systems, January 12-16,

1992.

° Gecrgevich, Vladimir; and Best,

Frederick: Dynamic and

Kinematic Waves Analyzed for

Microgravity, Proceedings of the

Fifth International Meeting on

Nuclear Reactor Thermal

Hydraulics, September 21-24, 1992.

JSC CDDF 1992 Annual Report 24
TITLE OF INVESTIGATION:

PROJECT MANAGER:

Hybrid Regenerative Water Recovery System

Eugene H. Winkler, Branch Chief/EC3/(713)

483-9255

IN-HOUSE TEAM MEMBERS: Charles E. Verostko/EC3/(713) 483-9228

Marybeth Edeen/EC7/(713) 483-9122

PURPOSE OF INVESTIGATION: Demonstrate an integrated and regenerative

biological and physicochemical system for the treatment of waste water to produce

potable water for reuse.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FY90 FY91 FY92 FY93 FY94

In-house: $0 $0 $0 $75k $0

Contractors: 0 50k 50k 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other:

Total funds:

0 190k 358k

$0 $240k $408k

297k 0

$372k $0

OBJECTIVE AND APPROACH

The major objective of the Hybrid Regenerative Water Recovery System (HRWRS)

is to demonstrate that waste water can be

processed into potable quality water for

reuse. The unique nature of this system

resides in the integration of biological

and physicochemical subsystems. The

system collects and processes waste water

from a four-person crew (approximately

120 liters per day). The waste water

sources are the urinal, shower, hand

wash, dish wash, and shower. Automated

collection of the waste water and logging

of production amounts is followed by

transportation of the waste water to a

central tank. Cooling of the waste water

prohibits degradation of urea to ammonia

and hence an elevated pH (undesirable

25 JSC CDDF 1992 Annual Report
from the biological treatment viewpoint).

The water is then sent to the first treatment subsystem - a 2-stage, aerobic,

trickling-filter bioreactor. Here, total

organic carbon levels of 400-600 mg/1

(parts per million) are reduced by oxidation to less than 50 mg/l. Additionally,

the nitrogen content of the waste water is

converted from ammonia and organic

nitrogen to nitrate. The second subsystem

in the HRWRS is the reverse osmosis

unit. Inorganic contaminants in the

bioreactor effluent are reduced from

approximately 2,000 mg/1 to less than 50

mg/1. However, a concentrated brine (15

percent of the total influent volume) is

produced which is currently not recovered. The reverse osmosis permeate is

then treated by the third subsystem - a

photocatalytic oxidation unit. Trace

organic carbon is removed to less than

500 g/1 (NASA's requirement for

potable water use). Product water disinfection is also accomplished by this subsystem. Due to the batch nature of the

current unit, only a fraction of the reverse

osmosis permeate can be treated. A

schematic of the system is shown in

Figure 8.

FY92 ACCOMPLISHMENTS

The treatment of waste water by the

HRWRS was initiated in December 1991

with the inoculation of the bioreactors

with effluent from a local waste water

treatment plant. Since that time, over

56,000 t of waste water have been treated.

Bioreactor performance has been remarkable despite several off-nominal conditions. The reverse osmosis subsystem has

operated for 170 hours at 5.7 t/min

permeate production. Limited success has

I SHOWER _---

I URINE _._

ANO URINE

FLUSH

•r

HAND WASH AND TRICKLING "-_

TRANSPORT FILTER

SYSTEM IOREACTO

,. LAUNDRY 1

I DISH WASH

OSMOSIS I_1 CATALYTIC OXIDATION

rUNTREATED' 

| REVERSE /

/ omom /

L _R_ j

Figure 8.- Schematic of the HRWRS.

JSC CDDF 1992 Annual Report 26
been achieved with the photocatalytic

oxidation subsystem. However, water of

potable quality has been produced. The

automated waste water collection and

transport system has functioned without

fault for the entire duration of the test.

PLANNED FUTURE WORK

reverse osmosis permeate. Incorporation

of solid waste (predominantly inedible

plant biomass) treatment subsystems will

be initiated. Evaluation of two, advanced,

electrochemical-breadboard systems (a

total-water recovery system and a posttreatment system) developed under Small

Business Innovation Research (SBIR)

Phase II contracts will be performed.

Anticipated FY93 accomplishments will

include continued testing of the HRWRS

and parallel testing with an alternate

design bioreactor (procured with other

funding sources). Testing of several

pretreatment and posttreatment technologies will be performed, including techniques for the recovery of reverse osmosis

brine. Attempts will be made to initiate

closure of the gas loop from the

bioreactors. An immobilized enzyme

reactor will be designed and fabricated

in-house to be used for polishing of

REFERENCE DOCUMENTS

1. Verostko, C.E., Edeen, M.A. and

Packham, N.J.C.: A Hybrid Regenerative Water Recovery System for

Lunar/Mars Life Support Applications. Presented at the 22nd International Conference on Environmental Systems, Society of Automotive Engineers, Seattle,

Washington, July, 1992.

27 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBER:

PURPOSE OF INVESTIGATION:

Pershing Precision Planetary Landing Studies

Timothy E. Fisher/EE6/(713) 483-1456

Tracking Techniques Branch

EE6/BiU Culpepper

Capture existing Department of Defense hardware

and knowledge of precision terminal-guidance systems for application to precision

landing on the Moon and Mars. Use this knowledge to improve the advanced planning

of lunar and Mars programs.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FYg0 FY91 FY92 FY93 FY94

In-house: $0 $0 $0 $50k $50k

Contractors: 0 0 50k 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other:

Total funds:

0 10k 40k 40k 40k

$0 $10k $90k $90k $90k

OBJECTIVE AND APPROACH

The objective of the task is the evaluation

of Pershing missile terminal-guidance

hardware to lunar and planetary missions. Available Pershing II flight hardware will be acquired for JSC laboratories

through a contract with the original

hardware manufacturer for installation,

training, and technical support. In-house

studies using the flight hardware and

actual flight video recordings will

estimate performance on natural terrains.

This work will be extended to estimate

performance on lunar and martian terrains.

FY92 ACCOMPLISHMENTS

Loral l)efense Systems, Akron, Ohio,

maker of the Pershing II terminal-guidance system, was placed under contract.

This contract provided for the delivery

JSC CDDF 1992 Annual Report 28
and installation of the hardware in JSC

laboratories, training on its theory and

use as well as providing technical support to our evaluation at JSC. Due to

delays in getting a contract in place, not

all phases of the contract were completed

in FY92. The Pershing hardware was

delivered and installed in JSC's laboratories and training was given on how to run

simulated missions with the Integrated

Evaluation System. The Reference Scene

Generation Facility could not be installed

due to a missing critical component

which is being replaced. The remaining

tasks should be completed in early FY93

using the FY92 funding.

PLANNED FUTURE WORK

The activities initiated in FY92 will be

completed in FY93. At this point, NASA

will be able to estimate the performance

of the radar area guidance (RADAG)

system using actual radar data and correlator hardware. These estimates will be

based on the White Sands Missile Range,

the most lunar/martian-like terrain for

which we have actual data. These tests

will be conducted with in-house civil

service personnel.

Future work will entail an additional

contract with Loral Defense Systems to

take advantage of their unique expertise

in building radar return predictions from

various types of terrain data (optical,

Synthetic Aperture Radar (SAR), etc.) and

the ensuing RADAG correlator performance estimates. Loral will be provided

with the best knowledge available of the

lunar and martian surfaces and will

predict the radar returns from those

surfaces. From these predictions, actual

correlator performance, and hence total

guidance performance, can be predicted.

An additional task for Loral will be to

develop a software simulation capability

for this system. It will simulate the current state of the hardware (correlator and

reference scene generation algorithms) as

well as the enhanced work that Loral has

already undertaken under separate studies. This simulation capability would be

modular to allow different a) correlation

algorithms and parameters, b) surface

data inputs, and c) surface sensor models

(radar, SAR, ladar, etc.) This modular

construct will allow NASA to further

expand the system to study alternate

sensors and correlation techniques. The

result will be a simulation capability that

will allow NASA to design a terminalguidance sensor appropriate for our often

changing requirements.

The existing Pershing RADAG system

provides altitude and ground-relative

positions only. With the capabilities

developed on this program, NASA

should have enough in-house expertise

and tools to develop not only a terminalguidance navigation sensor, but also

include a ground-track velocity and a

hazard-avoidance sensor system all in a

single, efficient package with a single

sensor (e.g. without additional hardware). This work can be conducted inhouse until appropriate Research and

Technology Objectives and Plans funding

can be obtained.

29 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: ShapeMemory Alloy Actuatorsand Release

Techniques

PROJECT MANAGER:

PURPOSE OF INVESTIGATION:

vices based on Shape Memory Alloys.

AUTHORIZED FUNDING FY92: $36k

FUNDING EXPENDITURES AND PROJECTIONS:

Darin N. McKilmis/EP52/(713) 4&3-9052

In-house:

Contractors:

Evaluate and test promising actuators and de-

(Projected)

FY90 EX,91 FY92 FY93 FY94

$(3 $43 $36k $0 $43

0 0 0 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other: 0 0 0 0 0

Total funds: $0 $0 $36k $0 $0

OBJECTIVE AND APPROACH

Shape Memory Alloy (SMA) devices are

finding applications in the computer,

robotics, automotive, aerospace, construction, and medical industries replacing or

supporting mechanical, electromechanical, and pyrotechnic devices. SMAs are

not usually considered in subsystem

trade studies due to their cross-discipline

applications and recent growth in viable

devices. Efforts are being focused on

devices which can be most readily applied to current or near-term programs

and

vehicles. Promising actuators and release

mechanisms will be taken into environment testing of appropriate programs,

e.g. Sh_ttle/Inertial Upper Stage (IUS),

Assured Crew Return Vehicle, and Common L',mar Lander. Knowledge and data

gained will allow SMA actuators and

devices to be considered in future subsystem trade studies as a viable and

understood alternative. Recent aerospace

applic_tions of SMAs indicate that they

are a v.able alternative to other actuator

types.

JSC CDDF 1992 Annual Report 30
• The U.S.S.R. used SMA fasteners to

make an addition to Mir in 1991.

An SMA release device was baselined

by TRW for the Total Ozone Mapping

Spectrometer with qualification underway.

The Naval Research Laboratory is

funding development of several SMA

actuators for Navy satellites. Test

flights will start in 1993.

This investigation started with three SMA

actuators for evaluation and testing: a

release bolt, a rotary actuator, and a JSCdesigned release nut. Midway through

the year another device was added to the

study, a linear SMA release system, the

Nitinol Fuzing Element Separation System (NFESS). Under contract, Boeing

Defense and Space Group completed

fabrication and initial testing of the

NFESS. Larger potential cost benefits and

greater demonstrated maturity of the

NFESS indicated that it should receive

priority in evaluation and testing. Because

of its late entry into the study, existing

fabrication and testing capabilities of

Boeing were utilized to accelerate the

design and test schedule beyond in-house

capabilities. Requirements and

deliverables were determined to stay

within the study budget and

1-year schedule. A full description of the

NFESS design and testing can be found in

reference 1.

Nitinol Fuzing Element Separation System requirements were to

Design an SMA fuzing element that

could support a 5000 lb tensile load

and release on command at high

speed. This load was selected to scale

with requirements for the Shuttle/IUS

release system, Super*Zip.

Design a sequentially operated, electrical control circuit to fuze the SMA

element.

• Fabricate the SMA fuzing element, the

test fixture, and control circuit.

Install and perform tests of assembled

mechanism, recording maximum

loading, time to release, and power

required for release.

The results and conclusions of testing

Showed that 3200 lbs caused premature shearing of the mounting holes.

The decision was made to perform the

release test with the system loaded to

a maximum of 2000 lbs.

Showed that a successful release of a

2000 Ib load was recorded in a total

release time of 838 milliseconds. The

power required for release of each

subset of elements was 6 kW (6v at

1000 amps), supplied by a 12v marine

battery.

All objectives of the experiment were

achieved. Future work will achieve the

original requirement of a 5000 lb load

with better selection of SMA material and

greater provision for mounting-structure

stress. No additional power or release

time will be required by the change. The

research team feels that the experiment

verified the SMA fuzing element technology, and has potential in large-load

restraint and release applications.

31 JSC CDDF 1992 Annual Report
FY92 ACCOMPLISHMENTS

Completed design study and submitted patent application for SMA release

nut

• Procured materials for SMA release

nut

• Conducted initial testing of

Frangibolt, an SMA release bolt

Designed, fabricated, and tested the

Nitinol Fuzing Element Separation

System

• Initiated initial design concepts for

SMA Laser Firing Controller

• Received NASA Tech Briefs Award

for SMA release nut

PLANNED FUTURE WORK

No follow-on funding is requested

from the JSC Director's Discretionary

Fund

Extend initial testing of devices tested

to date: Frangibolt and the Nitinol

Fuzing Element Separation System

• Conduct initial testing of the SMA

rotary actuator

• Fabricate and test the JSC-designed

SMA Segmented Release Nut

• Support laser initiation of pyrotechnic

devices. Development and testing in

FY93 and FY94 of the Shape Memory

Metal Precision Actuator (SMMPA), a

laser pointing and aligning device

developed by Boeing. Designed for

accurately pointing or aligning telescopes and optical sensors, the

SMMPA would be used for firing

control of a laser-firing system for

pyrotechnic devices. Acting as a laser

distributor and Safe and Arm, the

device would permit use of a singlelaser firing unit to initiate all the

pyrotechnic functions on a spacecraft.

Evaluation and testing of SMA actuators and release techniques will continue to stay abreast of industry developments and defense research

activities, and to meet in-house actuator requirements. Lockheed, Boeing,

GE-Astro, Raychem, TiNi Alloy,

Swenson Technologies, Hi-shear,

Memry Metals, and others are developing SMA devices and techniques.

Co_aboration with the Naval Research Laboratory will prevent duplication of effort.

REFERENCE DOCUMENTS

° Julien, G.J.; Nitinol Fuzing Element

_Separation System (Research

Experiment Test Repot0 9-5541-

MR92-134 Reference: Purchase

Order T-4137S, Boeing Defense

and Space Group, Seattle, Wash

,ngtoD..

JSC CDDF 1992 Annual Report 32
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBERS:

PURPOSE OF INVESTIGATION:

vehicle design.

AUTHORIZED FUNDING FY92: $45k

FUNDING EXPENDITURES AND PROJECTIONS:

Performance Analysis via Taguchi Methods

Ivan Johnson, ETS/(713) 483-8097

Ivan Johnson and Mike Tigges

Reduce the number of simulations required in

FYg2 FY93

In-house: $0 $0

Contractors: 0 0

Grants: 45k 0

RTOP, Program

or other: 0 60k

Total funds: $45k $60k

(Projected)

$o

0

0

OBJECTIVE AND APPROACH

Using the NASA LifeSat vehicle design as

an example, the goals of this task were to

demonstrate that using the Robust Design

Technique (Taguchi's Method), the set of

design parameters could be found which

maximizes the quality of vehicle design,

uses fewer numbers of simulations, and

achieves a level of confidence rivaling

that obtained by using the Monte Carlo

Analysis Technique.

FY92 ACCOMPLISHMENTS

The University of Houston was issued a

University Research Grant to investigate

ways of achieving our task objectives

with a team A and team B approach.

Team A concentrated on experimental

design using Taguchi's Method orthogohal arrays (OAs) and other areas in Robust Design. Team B concentrated on

taking an analytical approach, approximating outliers for the target's footprint

33 JSC CDDF 1992 Annual Report
dispersions, and a method of efficiently

measuring reliability. The results of

team A showed that for OAs:

Condusions derived from the experiments were valid over the entire

experimental region spanned by the

control factors and their settings.

There is a large savings of experimental effort and therefore a reduction of computational time for simulations.

• Data analysis can be done easily.

Orthogonal arrays and their experiments are designed deterministically

and not randomly.

A Monte Carlo simulation with 1000

samples and a simulation based on OAs

with 27 samples were used to obtain two

footprints of the landing range.

Statistical parameters (mean and standard deviation) of the landing range

were compared for both methods, and

differences were found to be small.

The method of Analysis of Variance

(ANOVA) was applied to evaluate the

contribution of noise factors on the performance of the LifeSat vehicle, based on

the results of the simulation prescribed

by the OAs. The performance was determined by the landing position and the

performance parameters.

In conclusion, team A proved that the use

of OAs for simulation is a valuable and

time-saving method which provides

accurate results comparable to the Monte

Carlo simulation. The performance of a

design can be evaluated within a short

period of time and can be improved by

using design models. The analysis of

results can be done easily with ANOVA.

Further work, however, is recommended

to develop the proposed method into one

that can be routinely used by NASA with

confidence.

Based on a simplified LifeSat model, a

FORTRAN program was developed by

team B for the equations of motion in the

spherical coordinate system.

The dependence of the LifeSat footprint

on atmospheric density at sea level, on

vehicle drag coefficient, and on wind

speed was plotted and observed to be

nearly linear. It was calculated that in

the dispersion ranges of interest, the

errors caused by linear approximation

were less than 8 percent.

Using such a linear approximation, the

footprint function in terms of three parameters was determined by six simulations. The landing reliability was calculated for selected normal dispersions of

the parameters and various peak

G-loads.

It was aoted that for each G-load associated with a given set of nominal values of

the parameter, six simulations were

needed to determine the footprint function. However, no additional simulations

were required to compute the reliabilities

for different dispersions of the parameters under the given nominal values.

Both teams presented theirresultsin a

divisicn-wide presentation, delivered

prototypical software, and delivered final

reports.

JSC CDDF 1992 Annual Report 34
PLANNED FUTURE WORK REFERENCEDOCUMENTS

Apply to more highly nonlinear

systems.

Use higher level of OAs.

o Mistree, F.; Lautenschlager, O.; and

Erikstad, S.: "Simulation Reduction Using Taguchl Method."

DDF Final Report, 1992.

@

Implement several tools together for

a total design.

Study additional cases to validate

method.

o Rao, J. R. J.; and Chen, Y. C.: "An

Analytic Model for Footprint

Dispersions and its Application

to Mission Design." DDF Final

Report, 1992.

• Completion date would be September 30, 1993.

35 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBER:

PURPOSE OF INVESTIGATION:

Artemis Strategic Defense Initiative Engine FeasibUity Demonstration

Joe Riccio/EP4/(713) 483-0405

Landon Moore/EP4

Determine the feasibility of using high thrust-toweight ratio, advanced materials engines developed under Strategic Defense Initiative

(SDI) programs for applications such as the Artemis main propulsion system.

AUTHORIZED FUNDING FY92: $100k

FUNDING EXPENDITURES AND PROJECTIONS:

FYg0

In-house: $0 $0

Contractors: 0 0

Grants: 0 0

RTOP, Program

or other: 0 0

Total funds: $0 $0

(Projected)

FY92 FW3 FY94

$0 $0 $0

100k 0 0

0 0 0

120k 0 TBD

$220k $0 TBD

OBJECTIVE AND APPROACH

The Artemis project has defined weight

reduction of subsystems as a high-priority task. In recent years, high thrust-toweight ratio, advanced materials engines

have been developed and tested under

many SDI programs which can offer

significant weight savings and packaging

advantages to a program such as Artemis.

The life required of these engines in the

SDI missions is approximately 10 to 12

seconds, whereas for an Artemis-type

missio_ the life requirement is approximately 800 to 1000 seconds. Some of the

SDI engines have been tested to approximately 250 seconds with excellent results.

However, none of these engines have

been tested to durations approaching that

of the Artemis mission. The objective of

this eff_)rt is to assess the ultimate life

capability of these engines to determine

their a_,plicability to the Artemis mission.

The approach to meet this objective is to

first, purchase an SDI 100 lbf engine, and

second; test it at the JSC to determine its

JSC CDDF 1992Annual Report 36
ultimate life capability. Next, channel

this experience base and test data into an

Artemis Advanced Development Engine

which demonstrates all the capabilities

required for the Artemis mission. Finally,

move into the qualification and flight

engine program.

FY92 ACCOMPLISHMENTS

FY92 Center Director's Discretionary

Funds were received in May 1992. The

procurement cycle was then started to

purchase a 100 lbf SDI engine from

Rocketdyne on a sole-source basis. The

contract was negotiated and the authority

to proceed given in September. In

addition, preliminary planning for the

required test facility modifications and

upgrades occurred in FY92.

PLANNED FUTURE WORK

The Rocketdyne SDI engine is scheduled

to be delivered February 1, 1993. Life

testing should take place immediately

thereafter, concluding in February. The

test data and final report are planned to

be published in early April. Based on

knowledge gained through this test

program, the procurement cycle for the

Advanced Development Artemis Engine

could begin in late FY93.

37 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: Common Lunar Lander (Artemis)

Mockup

PROJECT MANAGER: William Schnieder, Ph.D./ES6, (713)483-8939.

IN-HOUSE TEAM MEMBERS: Jimmy D. Bradley/ES63 (713) 4&3-8812,

Ted W. Tsai/ES64 (713) 48,3-8953,

Timothy E. Pelischek/ES22 (713) 483-8843

PURPOSE OF INVESTIGATION: Fabrication of a full-scale mockup of the Common

Lunar Lander, including the installation and mounting of the representative subsystem

models. System development test for landing gear energy attenuation. Concept evaluation and development test for off-loading a lunar-rover-type vehicle to the lunar

surface.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

FY91 FY92

(Projected)

FY93 FY94

In-House: $0 $50k $0 $0

Contractors: 0 0 0 0

Grants: 0 0 0 0

RTOP, Program

or other:

Total funds:

0 0 0 0

$0 $50k $0 $0

OBJECTIVE AND APPROACH

Recognizing that a full-scale mockup was

valuable in supporting the phase A study

of the Artemis Common Lunar Lander

design, a decision was made to proceed

with the design and fabrication of a fullscale, high-fidelity mockup to use as an

enginoering tool for subsystem location

and installation, and structural concept

evaluation. The model's design would

resemt.le the intended flight vehicle

configm'ation, but would use available inhouse materials and manufacturing

techniques.

JSC CDDF 1992 Annual Report 38
ACCOMPLISHMENTS

Approximately 75drawings were produced and provided to the JSCTechnical

ServicesDivision for fabrication of parts

and final assembly. Figure 9 is aComputer-Assisted-Design isometric of the

mockup.

A list of components used to assemble the

completed structure include:

• Round, tubular struts (100 primary,

105 secondary - 205 total)

• I-beams (4 upper, 4 lower - 8 total)

• Node joints (33 primary, 72 secondary

- 105 total)

End fittings for struts (200 primary,

210 secondary - 410 total)

Avionics attach panels (2 outer,

2 inner - 4 total)

• Attach brackets for engines

(4 primary, 6 RCS - 10 total)

• Attach brackets for external avionics

(antennas, radar, etc)

• Adapter attach ring

The assembled mockup is pictured in

figures 10 and 11. In-house testing

Figure 9.- Isometric view of the Artemis Vehicle without payload.

39 JSC CDDF 1992 Annual Report
Figure 10.- Overall view of the

Artemis Mockup.

results will refine the engineering needed

to proceed with this landing leg design in

the next project phase.

Rover off-loading ramps have been investigated. One concept has been fabricated

for in-house testing. This will be used for

display with the mockup, as well as

technical evaluation of the concept of

inflatable ramps.

PLANNED FUTURE WORK

Figure 11.- Closeup view of construction details

of the Artemis Mockup.

characterizes the performance of the loadlimiting landing pad concept proposed

for the Common Lunar Lander. The

Future activity is dependent on decisions

for continuation of the Artemis Program.

The mockup will be a key element in

implementation of a vehicle for continuing exl: loration of the Moon.

JSC CDDF 1992 Annual Report 40
TITLE OF INVESTIGATION: Adaptive Neural Net Controller for a 7-Degreeof-Freedom Robot Arm.

PROJECT MANAGER:

PURPOSEOF INVESTIGATION:

7-Degree-of-Freedom (DOF) Robot Arm.

AUTHORIZED FUNDING FY92: $60k

FUNDING EXPENDITURES AND PROJECTIONS:

Timothy F. Cleghorn, Ph.D./PT41/(713) 483-8090

Develop an adaptive Neural Net Controller for a

FYg0 FY91

In-house: $0 $15k

Contractors: 50k 0

Grants: 0 45k

RTOP, Program

or other: 0 0

Total funds: $50k $60k

FY92

$0

0

60k

40k

$100k

OBJECTIVE AND APPROACH

The objective of this project is to develop

for NASA the technologies needed to

perform autonomous space robotics. The

approach was to develop a simulation of

an adaptive robot arm controller to run

on the Silicon Graphics computer. This

controller is a neural net, which uses

simulated stereo vision for input. The

initial task in FY90 developed the graphics model of the Robotics Research

Corporation's 7-DOF arm and the neural

net which allowed the end effector to

learn to capture a stationary sphere in the

robot's workspace. The FY91 task was to

expand this neural net to allow the robot

to grasp the center of a stationary cylinder as well as the sphere. The FY92 task

was to expand the network further to

allow the system to track and capture

moving targets, including the cylinder

and sphere. Additional plans called for

the inclusion of tactile, force and torque

sensing, which would permit obstacle

avoidance. In addition, it was planned to

port the entire software simulation to a

hardware robot arm.

FY92 ACCOMPLISHMENTS

Deliveries of all code, including source

code, together with a short video of the

41 JSC CDDF 1992 Annual Report
simulation, and the final report have been

received. Evaluation of the code will be

provided in the future.

PLANNED FUTURE WORK

No activity planned at this time.

, Kuperstein, M.; and Rubenstein, J.:

Implementation of an Adaptive

Neural Controller for SensoryMotor Coordination. IEEE

Control Systems Magazine, Volume 9: Number 3, April 1989,

pp. 25-30.

REFERENCES

° Michael Kuperstein, Ph.D., Developing an Adaptive Neural Net

Controller for a 7-DOF Robot

Arm: Final Task Report, FY90,

FY91, FY92.

JSC CDDF 1992 Annual Report 42
TITLE OF INVESTIGATION: Multimedia Applications

PROJECT MANAGER: Lui Wang

PT/Software Technology Branch

(713) 483-8080

PURPOSE OF INVESTIGATION: Explore the potential of multimedia and define

system configuration requirements for potential application to simulators and trainers.

AUTHORIZED FUNDING FY92: $66k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FYg0 ELgA FY92 FY93 FY94

In-house: $0 $0 $0 $50k $50k

Contractors: 0 0 66k 0 0

Grants: 0 0 0 0 0

RTOP, Program 0

or other:

0 0 0 0

Total funds: $0 $0 $66k $50k $50k

OBJECTIVE AND APPROACH

Multimedia embraces many technologies

and disciplines including videography,

music, signal, and image processing,

artificial intelligence, computer graphics,

data bases, and data communication. It is

the fastest growing segment in the computer industry today. With the incorporation of animation, audio, video, and

interactive navigational links, digital

multimedia technology is changing the

way computers are applied (figure 12).

For instance, computers are emerging as

successful supplements to formal

classroom instruction and as viable alternatives to expensive hands-on simulators

and trainers. In education and aerospace

training environments, it has also become

necessary to maximize resources.

Whether these resources are in the form

of instructors, materials, or time, all must

be prudently allocated in a cost-effective

manner. Computerized instruction utilizing existing tools and developing technologies is being substantiated with a

43 JSC CDDF 1992 Annual Report
Slides Mu_s_ [_

TVNideo

lll,i,,

(_ Z_ Scanner

Movie/Film

Audio

CD-ROM

D_

i

Figure 12.- A multimedia computing

environment.

growing list of applications and increasing return on investment. Such applications can better stimulate human senses

and help the transfer of information

better than traditional, computer-based

systems.

Using the knowledge gained from FY92

activities, multimedia technologies were

incorporated in the Software Technology

Branch's existing applications. They

included Hyperman, the intelligent,

electronic-documentation system, and

several Intelligent Computer-Aided

Training systems. The state-of-the-art,

commercially available, multimedia

components were evaluated for the PC,

UNIX, and MAC environments. The

FY93 activities will be focused in the area

of networked multimedia for information

retrieval and display. A networked

multimedia scrapbook (figure I3) with

audio and video indexing, annotation,

and remote display capabilities will be

developed on UNIX-based workstations.

Figure 13.- A conceptual drawing of the

networked multimedia scrapbook.

FY92 ACCOMPLISHMENTS

Center Director's Discretionary Funds

were used to procure the following

equipment

One Macintosh Quadra 900 with a

digital video compression board, a

color scanner, and CD-ROM

One UNIX-based Parallax digital

_ideo subsystem with compression

_nd decompression capabilities for

the SUN Sparc station

One PC-based Super Video Winflows digital video subsystem with

compression and decompression

capabilities for the PC

JSC CDDF 1992 Annual Report 44
Multimedia software development

tools, PC X-Window server, and

networking software

One SONY Laserdisk player and

an audio/video computer control

interface

Delivered the Automated Information

Center to the Information Systems

Directorate Product Center

Explored cross-platform animation

and digital video capabilities between

Macintosh, PC, and UNIX environments

Provided technical consultations to

NASA and other governmental organizations (e.g. JSC's Public Affairs

Office, Space Station Training, and

Safety Reliability and Quality Assurance)

• Developed interactive multimedia

presentations

PLANNED FUTURE WORK

• Procure SiLicon Graphics Indigo UNIX

Workstations

• Develop intelligent multimedia

retrieval software on a distributed

Transfer Communication Protocol/

Internet Protocol network as shown in

figure 13.

• Continue studies of cross-platform

development issues

• Develop a test bed to support the

evaluation of the procured hardware

• Conduct a comprehensive evaluation

and document the results

45 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGERS:

IN-HOUSE TEAM MEMBERS:

PURPOSE OF INVESTIGATION:

technology for use in NASA astronaut training tasks.

Virtual Environments for Training

Robert T. Savely/PA/(713) 483-8105

Frank E. Hughes/DT/(713) 283-5623

Beth Holewinski/DT/(713) 283-8131

Lui Wang / PT4 / (713) 483-8080

Explore the potential of virtual environment

AUTHORIZED FUNDING FY92: $61k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FYg0 FY91 FY92 FY93 FY94

In-house: $0 $74k $61k $50k $0

Contractors: 0 0 0 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other:

Total funds:

0 0 0 0 0

$0 $74k $61k $50k $0

OBJECTIVE AND APPROACH

Training is a major cost element for

existing and future NASA operations.

Virtual environment technology may

provide alternatives to physical simulators (especially for part-task training) and

avoid their high construction and

maintenance costs. The integration of

the JSC's Intelligent Computer-Aided

Training (ICAT) technology with virtual

environment technology will permit

ICAT systems to address a larger variety

of trair ing tasks with the potential for

unprecedented real-ism for the visual,

audito:'y, and tactile senses. In addition

to the integration of ICAT technology

with vi rtual environment technology, this

project will compare a virtual environment approach to Space Station cupola

training with projection dome and pancake window

JSC CDDF 1992 Annual Report 46
approaches. Ultimately, the project team

intends to produce an ICAT application

for asuitable SpaceShuttle or Space

Station training task. Finally, this project

will explore the long-distance networking

of virtual environment systems for data

visualization and engineering design

applications.

As an ancillary to the project, technology

requirements to drive virtual environment research and development will be

determined.

This investigation is a joint project between the Space Station Training Office

(DT) and the Software Technology

Branch (PT4).

FY92 ACCOMPLISHMENTS

JSC Director's Discretionary Funds

were used to procure a VPL Research,

Inc., High Resolution EyePhone System and a stand-alone DataGlove

System.

Hardware was delivered to the Software Technology Laboratory October

9, 1992.

Implementation of an enhanced Space

Station cupola environment (originally developed in FY91) is underway

(figure 14).

A graphical model of the Hubble

Space Telescope (HST) has been

integrated with a library of digitized

photographs of the HST to investigate

the use of virtual environments for

training in on-orbit maintenance and

repair missions.

A payload interaction environment

has been created to study the efficacy

of virtual environments for training in

support of missions similar to STS-49

(figure 15).

Design and assembly of a Virtual

Environment Development Suite has

been initiated. This suite of software

tools will provide for rapid development and low-cost maintenance of

virtual environments.

The Shared Virtual Environments

Project (with the Marshall Space

Flight Center and U.S. Army Human

Engineering Lab) continues to explore

the issues related to sharing, through

networks, virtual environments over

long distances.

An educational spinoff- a Virtual

Physics Laboratory - has been created

to demonstrate the potential of the

technology for educational applications.

PLANNED FUTURE WORK

Procure tactile and force feedback

systems for evaluation (11 / 1 / 92 -

2/1/93).

Develop a test bed to support the

evaluation of the procured hardware

(11 / 1/92 - 12/31/92).

Conduct a comprehensive evaluation

and prepare a report detailing the

results (1/1/93 - 6/1/93).

• Integrate selected systems with existing virtual environments (e.g.,

47 JSC CDDF 1992 Annual Report
Figure14.- Space

Station cupola model.

Figure 15.- Space

Shuttle and lntellSat.

Payload Interaction, Space Station

Freedom, and HST. This will serve to

demonstrate and test the effectiveness

of adding this additional dimension to

a virtual environment for training

(3/1/93 - 9/30/93).

Identify technology needs to enhance

the ability of virtual environment

technology to support future training

req_drements (ongoing).

JSC CDDF 1992 Annual Report 48
TITLE OF INVESTIGATION: Onboard Training Hardware Evaluation

PROJECT MANAGER: Ven C. Feng/DT22/(713) 283-5897

IN-HOUSE TEAM MEMBER: Sean M. Kelly / DT33 / (713) 283-5603

PURPOSE OF INVESTIGATION: Evaluate hardware and software for use as an

onboard training platform on extended-duration orbiter flights for Space Station

Freedom and future missions.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

In-house: $0 $0 $50k $0 $0

Contractor: 0 0 0 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other: 0 0 0 0 100k

Total funds: $0 $0 $50k $0 $100k

OBJECTIVE AND APPROACH

An onboard training platform could

provide crewmembers with on-orbit

proficiency training to ensure crew safety

and mission success. Specifically, an

onboard trainer should refresh crew

members in cognitive and psychomotor

skills and knowledge, allow instructors to

obtain and evaluate data to verify training effectiveness and improve future

training. Implementation of the project

has applications of lessons learned to

lunar/Mars missions.

Two factors which negatively influence

on-orbit task performance are the length

of time between training and execution of

tasks, and differences between one-g and

wg training. Reports on the magnitude

of performance decrement have thus far

been largely subjective. Since the Skylab

missions, the longest U.S. space mission

has been 16 days. Therefore, additional

empirical data is required to substantiate

the need for onboard training. Gathering

this information while utilizing existing

hardware and software allows a costeffective means to obtain that data.

49 JSC CDDF 1992 Annual Report
The Onboard Training Project has procured a Silicon Graphics Indigo workstation to host a near-real time, kinematic

simulation of Space Station Freedom

(SSF) robotics systems. The robotics

domain was chosen as the evaluation

domain, since it incorporates both psychomotor and cognitive skills. The SSF

robotics domain also has a direct analog

in the Shuttle Remote Manipulator System, therefore data obtained via SSF

robotics may be applied directly to

shuttle tasking. After integration of the

platform, volunteers will operate the

simulation while selected cognitive and

psychomotor parameters are collected.

After analysis of the preliminary findings,

the results and prototype trainer will be

submitted to the Astronaut Office and

Training Division for evaluation. With

approval, a flight unit will be constructed

and flown as a Detailed Test Objective

(DTO). Multiple flights of varying (long)

duration are required for the on-orbit task

efficiency data base to reach statistically

significant conclusions.

FY92 ACCOMPLISHMENTS

In FY92, the Onboard Training Project

• Obtained Silicon Graphics Personal

Iris workstation

• Received estimates for rotational and

translational hand controllers from

NASA Technical Services and the

Automation and Robotics Division

Procured Silicon Graphics Indigo

workstation (W-4D310VGX Graphics

Supercomputing Workstation): Appropriation 802/30105, PWC: 307-51-

07-6A, PWC: 569-226-DM-00-6F

Began related efforts to manifest a

Spacehab onboard training flight

experiment (DTO 1210) as part of the

Crew Personal Support Computer

project. This project will test the

efficiency of "just in time" onboard

training.

PLANNED FUTURE WORK

Continue coordination with Space

Station Training Division Robotics

Group for integration (and upgrades)

of Magik software on indigo workstation

• Procure rotational and translational

hand controllers (FY94)

• Submit platform for crew and instructor evaluation and validation

• Gather ground-based cognitive and

psychomotor data

• Build and manifest the flight experiment

JSC CDDF 1992Annual Report 50
TITLE OF INVESTIGATION: Pressurized Vessels Subject to Hypervelocity

Particle Impact

PROJECT MANAGER: Michelle A. Rucker/RF/(505) 524-5730

IN-HOUSE TEAM MEMBERS: Rob Poe, Arnold Zamora, LESC

PURPOSE OF INVESTIGATION: Study the failure modes of pressurized vessels

following hypervelocity particle impact.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

FYg0 FY91 FY92

(Projected)

FY93

In-house: $0 $0 $0 $0

Contractors: 0 15k 50k 60k

Grants: 0 0 0 0

RTOP, Program

or others: 0 0 15k 15k

Total funds: $0 $15k $65k $75k

OBJECTIVE AND APPROACH FY92 ACCOMPLISHMENTS

Testing is being performed with a 4.3 mm

(.17-caliber) two-stage light-gas gun.

Projectiles up to 3.1 mm (.12-inch diameter) are accelerated to 7 km/sec

(22,966 ft/sec) to impact selected test

vessels in simulation of orbital debris

and micrometeoroid impacts. Vessel

failure is monitored using an array of

instrumentation.

During FY92 we received a shipment of

1.31 (80 in 3) aluminum pressure vessels,

free of charge, from Structural Composites Industries (SCI). A series of tests was

conducted on these vessels. Variables

included vessel pressure, pressurized

media (nitrogen, water, and a combination of nitrogen and water), projectile

size, and vessel-mounting hardware.

51 JSC CDDF 1992 Annual Report
Preliminary results indicate that mounting technique may have an effect on the

severity of pressure-vessel failure following impact. These results are expected to

have far-reaching implications regarding

mounting techniques for pressure vessels

on spacecraft.

Additionally, there appear to be great

variations in vessel failure modes depending on whether a projectile impacts

into a liquid-filled or gas-filled vessel;

similar variations are seen in vessels that

are impacted either above or below the

liquid level when filled with liquid or gas

mixtures. Although additional work is

needed, these results are expected to

affect shielding requirements for spacebased pressure vessels. In particular,

results indicate that only portions of a

pressure vessel, rather than the entire

vessel, may need to be shielded from

orbital debris and micrometeoroids. This

will significantly change operational

requirements and may reduce shielding

costs.

A paper detailing these results will be

presented at the First European

Conference on Space Debris in April,

1993. Results will also be presented to the

JSC Meteoroid and Debris Protection

Working Group.

PLANNED FUTURE WORK

Additional testing on compositeoverwrapped pressure vessels, also

provided by SCI, is planned for FY93. A

Research and Technology Objectives and

Plans (RTOP) proposal to investigate the

implications of this work to space-based

pressure vessels will be submitted later

this year.

REFERENCE DOCUMENTS

. Rucl<er, M. A.; and Garcia, B.: Evalu

ation of Pressure Vessels Subject to

]-Iypervelocity Projectile Impact.

National Aeronautics and Space

Administration, White Sands Test

Facility, test plan no. TP-WSTF668.

JSC CDDF 1992 Annual Report 52
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBERS:

PURPOSE OF INVESTIGATION:

Long-Term Material/Fuel Interactions Predicted

by Microcalorimetry

Radel L. Bunker/RF/(505) 524-5733

Dennis D. Davis, Steve D. Hornung, LESC

Determine if microcalorimetry can be used to

predict the long-term effects of materials on hypergolic fuels such as hydrazine.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FYg0 FY91 FY92 FY93

In-house: $0 $0 $0 $0

Contractors: 0 30k 50k 50k

Grants: 0 0 0 0

RTOP, Program or other: 0 0 15k 10k

Total funds: $0 $30k $65k $60k

OBJECTIVE AND APPROACH

Many materials catalyze the decomposition of hydrazine to nitrogen and ammonia with the liberation of heat.

N2H 4 (1)--) 1/3 N 2 (g) + 4/3 NH 3 (g)

AH=-123 kl

The decomposition reaction of hydrazine

can be followed by several techniques

including measurement of pressure

generated by the product gases, quantification of products by chemical analysis,

or calorimetric measurements of the heat

generated.

The objective of this project is to determine if microcalorimetric data can be

used to make reliable long-term estimates

of hydrazine-material compatibility.

To meet this objective, the project was

divided into three phases: small-scale,

long-term exposure studies (approximately 2 years); microcalorimetric studies; and data correlation between the two

studies.

53 JSC CDDF 1992 Annual Report
FY92ACCOMPLISHMENTS

Progress on the long-term exposure

studies continues this fiscal year. These

studies are performed with three materials (Stainless Steel 304L, Inconel, and

Hastelloy C) of varying reactivity immersed in hydrazine. The hydrazine and the

metal were loaded into a 15 ml ampule,

which was then sealed and placed into a

temperature-controlled water bath. At

selected time intervals, ampules were

removed from the water bath and placed

into an opening fixture designed and

constructed at the White Sands Test

Facility for this project (a patent disclosure has been submitted). Four sets of

data have been collected over the last 250

days.

A Hart microcalorimeter was purchased

this fiscal year and is currently being

evaluated using various pure metals and

some alloys immersed in hydrazine at

temperatures ranging from 25 ° to 50 ° C.

Approximately 50 tests have been performed. Experimental, safety, data

collection, and computerized data collection procedures have been developed.

These procedures will be used during

Phase 2 of this project.

The data analysis program developed for

this project, called "HYKIN," is used to

study hydrazine decomposition kinetics.

The program is designed to correlate

microcalorimetric, Test 15, long-term

exposure, configurational, and ARC data

in terms of the common denominator of

chemical reactivity, mole/(sec m2), and

plot the data on a master plot. An example of a master plot is shown in

figure 16 for molybdenum. The ordinate

is the log of the rate of the molybdenum

catalyzed decomposition of hydrazine.

The abscissa is inverse absolute temperature in Kelvins. The dotted line is extrapolated ARC data. The solid lines

represent error limits for the ARC extrapolation. As shown in figure 16, the

Figure 16.- Master plot

from HYKIN for

molybdenum. _ Molybdenum

_c -15

-2 ARC

2_,, I [] Test 15

"3_- i I + i

37.0 30.0 10 000/T 23.0 16.0

Microcal

JSC CDDF 1992 Annual Report 54
microcalorimetry data is in excellent

agreement with the ARC extrapolated

data. Long-term data will be added

when it becomes available.

PLANNED FUTURE WORK

During FY93, the long-term exposure

studies and the microcalorimetry studies

will be completed and the data will be

correlated to determine if microcalorimetry can predict long-term exposure

effects. Particular attention will be paid

to incorporating surface passivation and

activation features (i.e., decreasing and

increasing reactivity) into the predictive

method for long-term material and fuel

interactions.

During FY93, the master plot concept will

be extended to include the long-term

exposure materials as well as a variety of

other materials for which ARC, Test 15,

and literature results are available.

At the end of FY93, a final report which

summarizes the findings of this project

will be prepared and published. Results

from these studies will also be presented

at the Joint Army-Navy-NASA-AirForce (JANNAF) Propellant Development

and Characterization Subcommittee

Meeting (ref. 1), and at the JANNAF

Safety and Environmental Subcommittee

Meeting (ref. 2).

REFERENCE DOCUMENTS

. Hornung, S. D.; Davis, D. D.; Bunker,

R. L.: "Evaluation of Microcalorim

etry for Determining Material

Reactivity with Hydrazine". Unpublished JANNAF paper,

Lawrence Livermore National

Laboratories, Livermore CA, April

1993.

. Davis, D. D.; Hornung, S. D.; Bunker,

R. L.: "Correlation of Long-term

and Microcalorimetric Results for

Hydrazine/Materials Interactions". Unpublished JANNAF

paper, NASA White Sands Test

Facility, Las Cruces, NM, August

1993.

55 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBERS:

PURPOSE OF INVESTIGATION:

Real-Time Multipurpose Monitor for Assessing

the Integrity of Confined Atmospheres

Harold D. Beeson/RF/(505) 524-5542

T. Roth, T. Shelley, D. Emery, LESC

Develop and demonstrate a prototype system

capable of real-time monitoring of confined atmospheres with artificial intelligence

feedback.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

EX92 FY93

In-house: $40k $0 $25k

Contractors: 0 50k 0

Grants: 0 0 0

RTOP, Program

or other:

Total funds:

0 0 0

$40k $50k $25k

OBJECTIVES AND APPROACH

The objective of this study is to develop

and demonstrate a prototype system

capable of real-time monitoring of confined atmospheres with artificial intelligence (AI)-generated feedback.

The project is divided into three phases

that correspond to the 3 years of requested funding. In Phase I (FY91),

existing detector technology was reviewed, and appropriate gas and vapor

data were identified and collected. The

fabrication of a bench-scale test and

monitoring system began using existing

hardware. The end result of Phase 1 was

a demonstration of the feasibility of

Phase 2.

In Phave 2 (FY92), the fabrication of a

bench-_cale test and monitoring system

was completed. The design of a configurational test system was completed and

software to enable file conversion and

transfer was written. Guidelines and

JSC CDDF 1992 Annual Report 56
methodologies were developed to aid in

the construction of an "event" data base

which forms the foundation of the AI

system. The AI interface was developed

and is currently undergoing verification.

In Phase 3 (FY93), the development of the

event data base will be completed along

with final verification of the AI interface.

The monitoring system (hardware and

software) will be evaluated using the configurational test system as a mockup

environment.

FY92 ACCOMPLISHMENTS

In FY92, a bench-scale test chamber (see

ref. 1) was fabricated. An atmospheric

interface for the mass spectrometer was

identified and tested using the benchscale test chamber, which aided in the

acquisition of spectral data pertaining to

overheated wires possessing Kaptonbased wire insulation. The procedures

required to construct the required event

data base from off-gas data present at the

White Sands Test Facility were established. The AI interface process was

begun and is progressing. A translation

software routine was written to convert

data gathered by the test instrumentation

and transfer this data to high-speed

processors for analysis. This data was

then read into a sophisticated software

package (PV-Wave) where auto and

cross-correlation processes are performed

(figure 17). This process forms the foundation of the AI interface. Therefore, the

conclusion was made that it would be

feasible to develop unsupervised pattern

recognition algorithms.

PLANNED FUTURE WORK

Phase 3 (FY93) is targeted for completion

of the event database and the refinement

of the AI interface with the establishment

of a supervised learning system for characterizing unknown classifications of

events. The configurational test system

will undergo checkout and the entire

monitoring system (hardware and software) will be evaluated in the mockup

environment. Based on accomplishments, additional Research and Technology Objectives and Plans funding will be

sought. We will coordinate this effect

with the Space and Life Sciences directorate.

REFERENCE DOCUMENTS

. Beeson, H. D.; "Real-Time Multi

purpose Monitor for Assessing

the Integrity of Confined At

mospheres," in JSC Director's

Discretionary Fund Program 1991

Annual Report, NASA TM 104

745, November 1991, p. 75.

57 JSC CDDF 1992 Annual Report
u_%DSti from Mmsl ,__ r U_C_

--,_d_ck_undJ L _m.t.ASC_

]R_dl_taInto _ ( matt NmNUeplots

FV.WAVE formm_ to

M_ _ec l_oel

I _f_Cakulll_ Dlm:rls_lul_ _Calcut_Cm "relattO__l.dl f- Fm'txXh calcuhl_:

F_ both _eetm _loJln_.'_

J_ L m'll_a_cF_ J _

Figure 17.- Flow diagram of front-end of AI interface.

JSC CDDF 1992 Annual Report 58
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN HOUSE TEAM MEMBERS:

Vehicle Monitoring Devices and Techniques to

Determine the Health of the Orbital Maneuvering System and Reaction Control System

Bob Kowalski/RD/(505) 524-5516

Ralph Tapphorn, Bill Smith, Randy Burton,

Joe Kurtz, Tim Roth, LESC.

PURPOSE OF INVESTIGATION: Develop and demonstrate vehicle monitoring

devices and techniques to determine the health of the shuttle Orbital Maneuvering

System (OMS) and Reaction Control System (RCS) systems.

AUTHORIZED FUNDING FY92: $50k

FUNDING EXPENDITURES AND PROJECTIONS:

FY91 FY92

In-house: $0 $0 $0

Contractors: 0 0 50k

Grants: 0 0 0

RTOP, Program

or other: 0 15k 125k

Total funds: $0 $15k $175k

(Projected)

FY93 FY94

$50k $50k

0 0

0 0

150k 150k

$200k $200k

OBJECTIVES AND APPROACH

Application of vehicle health monitoring

(VHM) techniques is expected to benefit

the shuttle program directly by providing

a means to reduce the cost of operations

during shuttle Orbiter checkouts at the

Kennedy Space Center (KSC). Long-term

benefits for the Space Station Freedom

and the Space Exploration Initiatives

programs are anticipated; in particular,

the flexibility of including VHM concepts

during initial design phases of these

programs will reduce their costs of implementation. Industrial spin-offs of many

of the VHM devices and techniques

should be enhanced by assisting the

National Laboratories with the technology transfer process.

59 JSC CDDF 1992 Annual Report
The main objective is to develop the technology to perform VHM on OMS and

RCSsystems. This will be accomplished

by investigating the application of sensors,microelectronics, and nondestructive evaluation (NDE) technology to the

shuttle OMS and RCS systems on a component level and by demonstrating proven techniques applicable to flight VHM

devices or ground support operation

using the White Sands Test Facility

(WSTF) propulsion test beds.

FY92 ACCOMPLISHMENTS

During FY92, all of the planned activities

for the year were accomplished.

A literature search and technology survey

was initiated and is still ongoing. Shuttle

OMS/RCS hardware failure modes

documented at KSC, WSTF and JSC were

evaluated. Results of this evaluation

allowed the program to focus on three

areas: 1) monitoring performance of

primary reaction control system thruster

valves, 2) monitoring internal and external propellant leaks and 3) uniquely

adapting existing sensors and procedures

for VHM.

Chemical sensor technology was evaluated for use in propellant leak detection,

both internal and external to the system.

Four state-of-the-art technologies were

identified: spectroscopic, polymer, Pd

diode, and ion mobility. Component test

fixtures were developed to allow bench

top evaluation of the sensors. The

near-infrared absorption spectrum for

mono-methyl hydrazine was measured

with a peak absorption at 15 micrometers. The concentration-pathlength

product was also determined. A test

chamber for point-chemical sensors was

fabricated for use in a wide range of

pressures.

Much attention was given to investigating technologies for valve-motion sensors. Tt'ree nonintrusive sensors were

procured to monitor primary RCS pilotoperated valve movement. The sensors

concepts that were chosen were magnetic

field perturbation (Hall) sensors, acoustic

emission sensors, and current sensors. A

bench top, gas-flow system was developed to test the technologies. These

sensors were able to detect the operation

of both the pilot and main stages of the

valve. Valve response as a function of

pressure was also determined.

Existing fleet leader instrumentation was

evaluated for VHM application with

respect to helium-regulator and checkvalve performance during an OMS fleet

lead firing. At the present time, data

analysis is continuing and no conclusions

can be drawn.

Two papers will be presented at the

Fourth .annual Space System Health

Management Technology Conference at

the UniJersity of Cincinnati in November. They are entitled: "Application of a

Hall Effect Sensor to Monitor Pilot-and

Main-Stage Movement in a Pilot-Operated Valve," to be presented by Tim

Roth, l.ockheed Engineering & Sciences

Company (LESC); and "Application of

Acoustic Emission to Vehicle Health

Monito_'ing," to be presented by Bill

Smith, LESC.

JSC CDDF 1992 Annual Report 60
PLANNED FUTURE WORK

Phase II work planned for FY93 includes

development of a VHM demonstration

for the primary thruster pilot-operated

valve located on the Fleet Lead test article, acquisition and fabrication of other

sensor devices and equipment, testing of

OMS/RCS components with known

failures, and establishing a trend data

base for measured signatures.

Phase HI work planned for FY94 calls for

the completion of demonstration testing

and the evaluation of concepts for automated checkouts and artificial intelligence as employed in the aircraft industries. Final results of proven VHM

techniques will be evaluated for applicability in the reduction of shuttle turnaround costs. A final report will be

completed and recommendations made

to the project office.

REFERENCE DOCUMENTS

° Sensor Technology Sourcebook:

Guide to Worldwide Research &

Development. Technical Insights,

Inc., Fort Lee, New Jersey, 1992.

61 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBER:

PURPOSE OF INVESTIGATION:

properties needed for robotic planetary operations.

AUTHORIZED FUNDING FY92: $19k

FUNDING EXPENDITURES AND PROJECTIONS:

Assured Vision for Space Operations

Kumar Krishen, Ph. D. / IA4 / (713) 283-5875

Marie Collin / IA4 / (713) 283-5752

Define a means to comprehend objects and surface

(Projected)

In-house: $0 $0 $0 $0 $0

Contractors: 0 0 19k 31k 0

Grants: 0 4k 8k 0 0

RTOP, Program

or other: 0 36k 100k 100k 0

Total funds: $0 $40k $127k $131k $0

The project funding has been shared by several organ.zations: NATO ($12k), ITMI:

Industry and Technology of Machine Intelligence, Grenoble, France ($236k), and

NASA/Johnson Space Center ($50k).

OBJECTIVE AND APPROACH

A vision system should be able to perceive a planetary environment for any

location and any time on the surface and

to describe the scene in terms of surface

roughness, material characteristics, and

surface orientation. To achieve this

autonomous scene analysis, multifrequency and multimode sensing devices

are used. The capabilities of sensors

ranging from visible to infrared, and

microwaves are exploited because of

complementary capabilities in different

environmental conditions (dust, specular

reflections, night, short range, long

range.. ) and different sensitivities to the

needed surface characteristics (roughness,

dielectric constant and orientation). The

assured vision system is based on the

JSC CDDF 1992 Annual Report 62
physical analysis of the mechanisms

underlying the sensor perception.

An adaptive, multisensing approach will

be developed according to the illumination conditions (figure 18). To this end, a

sensor selection module will automatically

select the best set of sensors and their

sensing modes, according to the mission

requirements and the environmental

conditions to assure the scene perception.

Then the perceived data will be processed

by a sensor fusion module that will interpret the perceived scene. The scene perception and interpretation capabilities

will be based on the physical models

underlying the reflection and emission

phenomena. These physical models take

into account the relation between the

environmental illumination (which can be

active in case of radar sensors, or passive

in case of thermal or visible sensors), the

surface characteristics, and the perceived

data. Then these physical models will be

used with fuzzy-logic techniques to

perform the fusion of the multisensor

data and to interpret the physical and

geometrical properties of the sensed

surfaces.

FY92 ACCOMPLISHMENTS

sensing strategies for the perception of

surface characteristics have been identified.

The results of this preliminary analysis

have been reported in three technical

reports (ref. 1, 2 and 3). These results as

well as the newly developed approach

have also been presented to a National

Conference (ref. 4) and three International

Symposiums (ref. 5, 6 and 7).

PLANNED FUTURE WORK

The next steps for the assured vision

system development include implementation and testing of the sensor selection

rules and implementation of the sensor

fusion method for recovering the surface

characteristics. This part represents the

application stage of the theoretical analysis conducted during FY92.

A simulated environment is being designed to develop and test the selection

and fusion modules of the vision system.

This simulated environment will be

realized using a graphical interface and

simulated sensor data. The development

steps of the simulation with their completion dates are:

During FY 1992, the perception problems

related to the space environmental conditions have been identified, the approach

for overcoming these problems has been

analyzed and selected, the theoretical

basis for the implementation of the approach has been settled, the surface

characteristics and their relative influence

on the sensor returns have been identified

and modeled for each sensor, and the

October 1992 - Simulation of the lunar

environment (lunar surface and man

made objects) and illumination conditions (over a lunar day and for any given

location on the surface).

November 1992 - Simulation of the sensor data for visible, infrared, and microwave data.

63 JSC CDDF 1992 Annual Report
Figure18.- Perception

system architecture.

!iiii. sensor1 [I

__ sensor2

|1 ........I

I I

_" _ 'E iIiiil',l

December 1992 - Simulation of the sensor

selection module: autonomous selection

of the sensors and sensing modes to

perceive the scene.

February 1993 - Simulation of the data

fusion module: recovering of the surface

properties (roughness, orientation, dielectric constant, temperature, emissivity,

reflectivity) to allow for further interpretation and operation control. Presentation of the results.

March-July 1993 - Demonstration of the

assured vision system (ref. 8).

Several teams are involved in this development: ITMI for the scientific support,

Robotic Applications Division (ER421/

IGOAL) for the graphical interface of the

simulation, and the Software Technology

Branch (PT4) for consulting on the data

fusion module.

REFERENCE DOCUMENTS

. CoUin, M. F.: Perception for Space

Robotics. Unpublished technical

report n° 3/18, NASA Johnson

Space Center, Houston, Texas,

October 1991.

, Collin, M. F.: Perception for Space

Robotics. Unpublished technical

report n g 6/18, NASA Johnson

Space Center, Houston, Texas,

January 1992.

° Coilin, M. F.: Perception for Space

Robotics. Unpublished technical

report n ° 9 and 12/18, NASA

Johnson Space Center, Houston,

Texas, July 1992.

JSC CDDF 1992 Annual Report 64
,

,

.

CoUin, M. F.; and Krishen,K.: Assured Vision for Assured Vision

in Space Applications, Space

Operations Application and

Research Workshop, Houston,

August 1992.

Krishen, K.; and CoUin, M. F.: Space

robotics vision techniques, International Union of Radio Science,

Houston, May 1992.

CoUin, M. F.; and Krishen, K.: Sensor

Fusion for Assured Vision in

Space Applications, International

Union of Radio Science, Houston,

May 1992.

, Collin, M. F.; Krishen, K.; and

Pampagnin, L. H.: Adaptive

multisensor fusion for planetary

exploration rovers, International

Symposium on Artificial Intelligence, Robotics and Automation

for Space Robotics, Toulouse,

France, September 1992.

. CoUin, M. F.; Krishen, K.; and Pesty,

R.: Multisensor data integration

for space operations, submitted to

International SPIE Symposium on

Sensor Fusion for Aerospace

Applications, Orlando, Florida,

April 1993.

65 JSC CDDF 1992 Annual Report
TITLE OF INVESTIGATION: Regenerative Life Support System

Test Bed Project

PROJECT MANAGER: Donald Henninger, Ph.D./EC3/(713) 483-5034

IN-HOUSE TEAM MEMBERS: Mike Hoy / EC3 / (713) 483-0268

Daniel Barta, Ph D./EC3/(713)483-0268

Marybeth Edeen/EC7/(713) 483-9122

PURPOSE OF INVESTIGATION: Evaluate Regenerative Life Support System

(RLSS) approaches in which plants are grown in a closed, controlled environment in

conjunction with physicochemical subsystems.

AUTHORIZED FUNDING FY92: $300k

FUNDING EXPENDITURE AND PROJECTIONS:

(Projected)

FYgO FY91 FY92 FY93

In-house: $0 $0 $0 $0

Contractors: 300k 300k 300k 185k

Grants: 0 0 0 0

RTOP, Program

or other: 0 0 0 0

Total funds: $300k $300k $300k $185k

OBJECTIVE AND APPROACH

The objective of the RLSS Test Bed Project

is to use higher plants grown in a closed,

controlled environment in conjunction

with physicochemical-based life support

systems to provide an integrated biological/physicochemical life support system

test bed for evaluation of various RLSS

approaches. The biological component of

the test bed will be fully automated to

grow c_ndidate crops from seed to harvest without the need for human intervention. Additionally, one of the test

bed's two growth chambers (figure 19)

will be )perable at both ambient and

reduced atmospheric pressures to more

closely :luplicate candidate lunar and

Mars habitat environments. The test bed

will be :omplemented by incorporation

of a human metabolic simulator which

will supply variable metabolic loads to

JSC CDDF 1992 Annual Report 66
Figure 19.- Lettuce crop growing in the variable pressure growth chamber (VPGC).

the system to simulate the presence of a

crew. Major objectives of the test bed

include quantification of life support

capabilities of higher plants (i.e. oxygen

production, carbon dioxide uptake, and

water conditioning via transpiration),

determination of interactions between the

biological and physicochemical life support system components, and investigation of integrated control system approaches for providing variable life

support capabilities on demand. Data

from the RLSS Test Bed Project will be

used to define requirements for the

planned Human-Rated Test Facility

(HRTF) being developed at JSC.

FY 92 ACCOMPLISHMENTS

The RLSS Test Bed Project achieved

several key accomplishments during

FY92, including completion of buildup of

the Ambient Pressure Growth Chamber

(APGC), and a successful 90-day dwarf

wheat crop growth test in the Variable

Pressure Growth Chamber (VPGC). The

wheat crop provided valuable insight on

systems interactions which is being

incorporated in the VPGC systems modeling activity. The build up of the APGC

included the implementation of numerous system upgrades which had been

identified as a result of the testing that

67 JSC CDDF 1992 Annual Report
was conducted in the VPGC, and the

design of a unique hydroponic nutrient

delivery system. Checkout of a physicochemical CO2 removal system (known as

SAWD II - Solid Amine Water Desorption) was initiated with the purpose of

integrating the system with the plant

growth chambers during FY93. Other

key activities performed in FY92 include

supporting off-line plant growth experiments, biomass production analyses, and

plant growth hardware (i.e. hydroponic

tray design and nutrient wicking material) evaluations in the RLSS Laboratory.

PLANNED FUTURE WORK

No additional effort is planned for this

JSC Director's Discretionary Fund (DDF)

project. A new DDF proposal has been

submitted and received preliminary

approval for modification of the VPGC to

perform detailed plant growth testing

and analysis at reduced pressures.

REFERENCE DOCUMENTS

. Henninger, D. L., et al.: "Johnson

Space Center's Regenerative Life

Support Systems Test Bed," International Conference on Life Support

and Biospherics, University of

Alabama in Huntsville, February,

1992.

. Barta, D.J.: "Troubleshooting Problems With Leafy Crops," 12th

Annual Conference on Hydroponics,

tIydroponic Society of America,

April, 1992.

o Barta, D. J., et al.: "Regenerative Life

Support Systems Test Bed Performance: Lettuce Crop Characterization," 22nd International Conference

on Environmental Systems, Society

of Automotive

Engineers, 1992.

JSC CDDF 1992 Annual Report 68
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBERS:

PURPOSEOF INVESTIGATION:

Lunar Surface Systems

Jeri W. Brown/SP/(713) 483-6036

Nathan Moore, Laurie Weaver, David Ray

Use computer simulations, mockups, and partial

gravity simulator to develop and evaluate requirements for crew operations on the

surface of the Moon and Mars.

AUTHORIZED FUNDING FY92: $75k

FUNDING EXPENDITURES AND PROJECTIONS:

FY90

In-house: $0

Contractors: 0

Grants: 0

RTOP, Program

or other: 0

Total funds: $0

OBJECTIVE AND APPROACH

(Projected)

FY91 FY92 FY93 FY94

$0 $0 $70k $0

0 75k 0 0

0 0 0 0

0 0 0 0

$0 $75k $0 $0

Develop mockups and computer simulations of the systems and facilities needed

for crew operations on the Moon and

Mars. These representations will convey

conceptual designs, aid in requirements

definition, and help evaluate alternative

approaches. Projections of technology

needs and integrated man-in-loop test

capabilities for surface systems will be

products of the activity. The FY92 activity is concentrated in four subtask areas:

• Hyperbaric Airlock- Identify toplevel and secondary guidelines and

rationale for a lunar airlock that can

accommodate hyperbaric treatment

for the crew; define a conceptual

design based on an "inside-out"

approach, and document design with

hypermedia 3-D computer models;

employ a multidisciplinary team.

Initial Mars Habitat - Explore requirements for a 6-person, 500-day

surface stay-time initial Mars habitat,

69 JSC CDDF 1992 Annual Report
focusing on habitation systems to

support routine human operations,

basic habitation needs, and surface

science and exploration.

• Habitation Development ToolDevelop a habitat parametric model

(i.e., computer-based tool) to facilitate

the definition of habitat concepts and

configurations, to facilitate estimation

of habitat mass and volume, and to

provide the user with a range of

options for crew size, mission length,

and system configuration.

• Partial Gravity Simulator- Salvage

and upgrade the Apollo partialgravity-simulator hardware to support research, technology, and evaluations for exploration missions. Test

the hardware and make changes to

increase the simulator's response and

performance. Construct a new support structure to allow increased

vertical and horizontal translation for

human subjects.

FY92 ACCOMPLISHMENTS

Hyperbaric Lunar Airlock - Top-level

functions as summarized from the

guidelines document (Lunar Airlock

Mission and Functional Guidelines,

JSC-25921, May 1992) were identified.

Using the functions as a checklist,

available airlock designs (e.g.,

Shuttle, Space Station) were assessed

for applicability. Unique

requirements for partial-g operations

(e.g, EMU and equipment logistics

transfer, hyperbaric treatment, dust

con_ol, airlock control, and conservation of consumables) were defined,

including dimensional and volumetric constraints. The two- and threeperson concepts are shown in

figure 20.

Initial Mars Habitat - A mission

profile was defined to identify crew

size, stay time, crew-tended capabilities, logistics issues, and assumed

transportation shroud constraint.

Mission objectives were synthesized

resulting in a two-level, verticalcylinder-configuration with required

living and working areas (figure 21).

The concept supports three basic

functions (crew sustenance; habitation systems operations; and science).

The concept was documented in a

stand-alone, interactive, hypermedia

computer program.

• Habitation Development Tool- User

changes were incorporated into the

Phase I tool. A radiation shield mass

estimation model based on existing

reference materials was developed.

Ap_llo and Skylab crew accommodatiox_s data bases were expanded. The

toot provided rapid estimates of

habitable mass and volume when

applied by a person knowledgeable

about human support requirements

and previous spaceflight programs.

The tool was also applied to

JSC CDDF 1992 Annual Report 70
Figure 20.- Hyperbaric lunar airlock

concept.

parametric study of the effects of

mission parameters on habitable

element sizing.

• Partial Gravity Simulator- Initial

simultaneous tests of vertical- and

horizontal-drive servosystems were

successfully completed. Safety features were added to the system.

Analyses and tests were conducted to

obtain appropriate pressure-vessel

rating. Proof load tests of gimbal and

vertical servo were completed. A

failure modes and effects analysis

was prepared and a Test Readiness

Review completed for approval to

conduct tests and evaluations with

human subjects.

PLANNED FUTURE WORK

Habitation Development Tool - Incorporate radiation shield model; further develop subsystem data base and expand

Apollo/Skylab data. Expand subsystem

selection options.

71 JSC CDDF 1992 Annual Report
Figure 21.- Initial

Mars habitat concept.

JSC CDDF 1992 Annual Report 72
TITLE OF INVESTIGATION:

PROJECT MANAGER:

IN-HOUSE TEAM MEMBERS:

In Situ Resource Utilization

David S. McKay, Ph.D./SN/(713) 483-5048

Thomas A. Sullivan, Ph.D./SN4/(713) 483-0681

Carlton C. Allen, Ph.D./LESC C-23/(713)

483-2630

PURPOSE OF INVESTIGATION: Develop the technology necessary for the utilization of In Situ Resources as part of the developing Space Exploration Initiative program. Establish laboratory projects, develop skills and experience, and acquire necessary equipment and instruments. Subcontract engineering design studies and work

on the procurement, testing, and storage of lunar simulant material.

AUTHORIZED FUNDING FY92: $150k

FUNDING EXPENDITURES AND PROJECTIONS:

rY91 FY92

In-house: $0 $0 $0

Contractors: 0 150k 150k

Grants: 0 0 0

RTOP, Program,

or other: 0 0 85k

Total funds: $0 $150k $235k

(Projected)

FY93 FY94

$0 $0

150k 0

0 0

0 0

$150k $0

OBJECTIVE AND APPROACH

Three separate studies have been conducted under this project. The production of oxygen from lunar regolith material is the goal of two different chemical

techniques, hydrogen reduction of basalt

and glass and the sulfate process. The

third project focuses on the production of

ceramics by sintering, the bonding of

solid material by melting at the edges.

"Bricks" formed from sintered regolith

could be used for construction material

and radiation shielding at a lunar

outpost.

73 JSC CDDF 1992 Annual Report
Hydrogen Reduction of Basalt and Glass

Direct reduction of the iron in lunar

basalt and glassby hydrogen is being

investigated as a method of liberating

oxygen. The objectives of this program

are to define the conditions under which

reduction occurs and use this information

to support the production of oxygen at a

lunar base.

Sulfate Process

This project explores modifications to a

terrestrial commercial process in order to

release oxygen from ilmenite. The reactions are carried out in solution. The

three major process steps have been

studied to explore their kinetics and

yields. Concept development based on

this and other data suggests that an

efficient process is likely and points the

way to future lab studies which will be

done in the coming year.

Ceramics

The purpose of this study is to investigate the sintering behavior of the lunar

regolith. Experiments are designed to

determine the range of conditions under

which sintering takes place and the best

methods for heating the material. The

project has also responded to the needs of

other investigators for large amounts of

lunar soil simulant.

FY92 ACCOMPLISHMENTS

Hydrogen Reduction of Basalt and Glass

Laboratory experiments and analysis

during FY92 led to determinations of the

mechanism, kinetics and yields of oxygen

from a range of lunar glass compositions

(ref. 1). Reduction experiments on basalt

and glass were carried out in both fixed

and fluidized beds to compare their

efficiencies. A method of improving

process speed and yield by preoxidizing

the feedstock was developed. Project

personr_el provided all analytical support

for the first set of oxygen production

experiments to utilize actual lunar

samples (ref. 2). This study led to the

development of a remote-sensing predictor for oxygen yield from lunar soil,

based on parameters which can be determined from lunar orbit. An extensive

survey was conducted to assess current

technologies for separating water from

hydrogen gas at high temperatures. The

project sponsored a design study by

Eagle Engineering for oxygen-producing

flight experiments on the Artemis lander

and at the First Lunar Outpost. This

work led to the concept design of a fullscale test bed which will be used in FY93

to study oxygen production, material

handlip, g, and instrument control.

Sulfate Process

Laboratory work in FY92 covered the

three rrajor process steps: acid digestion,

recover y of sulfur from the reactants, and

electrolysis of the acid solution to produce oxygen. Experiments determined

the parameters for digestion of lunar

simulant basalt and its constituent minerals (ref. 3). A series of tests in a furnace

equipp__d with a sensitive microbalance

established the kinetics of sulfur recovery by ;_yrolysis. Recovery was shown to

be significantly enhanced when pyrolysis

was cat"tied out in a flowing hydrogen

atmosphere. An electrolytic cell was

JSC CDDF 1992 Annual Report 74
constructed and experiments to determine oxygen yield were initiated. In

addition, a patent application covering

the entire process was updated and

resubmitted (ref. 4).

Ceramics

Full-scale "bricks" with the compressive

strength of concrete were produced by

sintering lunar simulant basalt (ref. 5). A

long series of tests determined the optimum heating, cooling, and insulation

parameters for brick production. Test

samples of basalt were sintered for the

first time by a combination of microwave

and radiant heating. An experimental

program determined the optimum conditions for vibratory compaction of lunar

soil simulants. This technique could be

used as an alternative to pressure compaction in preparing material for sintering. The project placed subcontracts to

the University of Texas at Dallas and

Texas A&M University to procure, characterize, store, and distribute 20 metric

tons of lunar soil simulant for spacesuit

testing and other large-volume uses.

PLANNED FUTURE WORK

Hydrogen Reduction of Basalt

and Glass

The major goal for FY93 is to fabricate

and use our test bed to scale up oxygen

output to that of a lunar pilot plant. In

the process, feedstock and product handling methods, as well as instrument

control procedures, will be developed. In

addition, we will pursue the promising

technique of preoxidation to increase

oxygen yield. Further analytical work

will be carried out on reduced lunar

basalt and tests will be conducted on

lunar pyroclastic glass.

Sulfate Process

A key FY93 goal is to optimize the electrolysis procedure, which produces

oxygen from lunar minerals digested in

sulfuric acid. Sulfur recovery by improved pyrolysis techniques will be

tested. The effects of varying acid concentrations of mineral digestion will be

demonstrated. Competing designs will

be evaluated, with the aim of maximizing

yield while simplifying the overall sulfate

process. A patent application for this

process has been filed and is in negotiation.

Ceramics

Innovative changes to the brick-making

process will be investigated, with the goal

of dramatically improving the products.

The radiation protection potential of

bricks will be compared to that of loose

regolith. Large quantities of lunar soil

simulant will be tested for engineering

properties and distributed to a variety of

investigators.

REFERENCE DOCUMENTS

, Allen, C.C.; McKay, D.S.; and Morris,

R.V.: "Lunar Oxygen - The Reduction of Glass by Hydrogen,"

Engineering, Construction, and

Operations in Space III, Am. Soc.

Civil Eng., 1992, pp. 629-640.

75 JSC CDDF 1992 Annual Report
.

.

o

Allen, C.C.; Gibson, M.A.; Morris,

R.V.; Keller, L.P.; and McKay,

D.S.: "Lunar Resources - Oxygen

from Rocks and Soil," Geology of

the Apollo 17 Landing Site, Lunar &

Planetary Inst., 1992.

Sullivan, T.A.: Method for Producing

Oxygen from Lunar Materials.

U.S. patent pending, 1992.

Sullivan, T.A.: "A Modified Sulfate

Process to Lunar Oxygen," Engineering, Construction, and Operations in Space IIl, Am. Soc. Civil

Eng., 1992, pp. 641-650.

So Allen, C.C.; Hines, J.A.; McKay, D.S.;

and Morris, tLV.: "Sintering of

Lunar Glass and Basalt," Engineering, Construction, and Operations in Space III, Am. Soc. Civil

Eng., 1992, pp. 1209-1218.

JSC CDDF 1992 Annual Report 76
TITLE OF INVESTIGATION: Threshold Low-Cost Intermediate Technology

Experiment (T-LITE) Mass Measurement Device

PROJECT MANAGERS: Edgar Castro/ES221/(713) 483-8841 and Kelley

Cyr/XP/(713) 283-5466

IN-HOUSE TEAM MEMBERS: Tony Dao, Kevin Hames, Leah Pate, Henry

Wyndon, Ed Strong, Keith Speckman, Jerry Valle,

Heath Hendrickson, Ann Arnett, Mike Jenson,

Scott Merkle.

PURPOSE OF INVESTIGATION: Design a mass measurement flight experiment.

AUTHORIZED FUNDING FY92: $20k

FUNDING EXPENDITURES AND PROJECTIONS:

(Projected)

FY90 FY91 FY92 FY93 FY94

In-House: $1k $10k $20k $39k $0

Contractors: 0 0 0 0 0

Grants: 0 0 0 0 0

RTOP, Program

or other: 0 0 0 0 0

Total funds: $1k $10k $20k $39k $0

OBJECTIVE AND APPROACH

The T-LITE is an activity sponsored by

the Threshold Group to provide NASA

employees with the opportunity to build

teamwork and leadership skills by working on a Shuttle flight experiment. The TL1TE concept calls for the extensive use of

in-house resources and off-the-shelf

components to keep the cost down. The

experiment selected for the initial T-LITE

project was the Mass Measurement Device (MMD) proposed by Tim Pelischek.

The MMD uses the principle of linear

acceleration to determine the mass of a

crew member in a microgravity environment.

The purpose of this device is to provide

the crew with a convenient method of

weighing themselves while in space on

long-duration missions. The target

77 JSC CDDF 1992 Annual Report
accuracy of the device is repeatability

within + 1 percent. Since the crew will

use the device primarily to monitor

weight trends, the absolute accuracy of

the device is not as critical as consistent

results. The team will design the device

to fit inside a standard Shuttle middeck

locker with a goal of fitting inside a halfsize locker. The MMD will fly as a development test objective or detailed supplementary objective and will meet the

design requirements associated with

those payloads.

The MMD uses Newton's second law of

motion: the acceleration of an object is

directly proportional to the force acting

on it and inversely proportional to the

mass of the object. The mass of an object

can be determined by applying a known

force to it and measuring the resulting

acceleration. In the MMD, an elastomer

tube applies a force to a three-sided

device resembling a scissor-jack. The

force transfers through a triangulation of

load cells to a plate on which the crew

member may stand or kneel.

FY92 ACCOMPLISHMENTS

The activity for FY92 focused on preparations for a zero-gravity test flight on the

KC-135. An engineering test bed was set

up on the air-bearing floor (ABF) facility

in Building 13. The prototype testing

aimed at refining the mechanical and

electronic systems and the data analysis

software. An electromagnetic release

system was added to the MMD design.

Extensive testing of both static and dynamic behaviors was conducted on the

ABF. A major goal of the testing was to

improve the absolute accuracy and consistenc_, of the device. The objective was

achieved in July when a series of 50 tests

was conducted using 5 different masses

ranging from 98 to 319 pounds. The

difference between the actual mass and

the mass estimated by the MMD was less

than 2 percent. Also, the mass estimates

for a given weight varied by about 2

percent.

In addition to developing the F=ma method, an alternative method, based on the

principle of harmonic motion of a springmass system, was developed. The displacement of the mass is a function of the

initial displacement and the cosine of the

elapsed time, multiplied by the square

root of the spring constant, divided by

the mass. For the MMD, the initial displacement and the spring constant are

fixed, therefore the mass can be estimated

if the displacement and time are known.

Two switches are positioned along the

deployment path of the MMD such that

one switch is opened when the device

begins to deploy and the second switch is

dosed when the device nears the end of

deployment. The switches are positioned

so that the displacement of the device

between the switches is constant. The

time interval between the two switches is

then a function of the mass. The timebased model offers some advantages over

the F=ma method since it does not require

sensiti,,e load cells and accelerometers,

and the computations are simpler. Preliminary testing indicates that the timebased model results are comparable to

the F=ma model, however, additional

testing is required to determine which

method will work best in actual practice.

JSC CDDF 1992 Annual Report 78
It was previously thought that, for testing

conducted on the KC-135 zero-g aircraft,

the MMD would have to be "free-flying"

to eliminate noise from the natural vibration of the aircraft. The free-flying mode

of testing posed great difficulties because

of the need to use a very heavy countermass. To determine the best test mode, a

system for monitoring the acceleration

environment on board the KC-135 was

developed. A system of three accelerometers, set up to measure acceleration in

the three linear motion axis', and a chart

recorder, was flown on the KC-135. The

results were used to determine that the

best method of testing was to attach the

device to the floor. A noise-canceling

accelerometer would also be added to the

base of the MMD.

PLANNED FUTURE WORK

Prototype testing will proceed with both

dead-weights and human subjects on the

precision AFB in Building 9. The prototype will be improved with a new hinge

system, improved switch attachment, and

a shock-absorbing mech-anism.

Once the objectives of the prototype test

phase are reached, the testing on the KC135 will begin. The KC-135 testing will

consist of two series of two flights each.

The first flight series is scheduled for the

first quarter of 1993. The follow-on flight

test is scheduled for the second quarter of

1993. If the KC-135 testing is successful,

then the plan is to conduct an Orbiter test

flight in late 1993.

Figure 22.- Composite photo of the

prototype MMD in

the compressed and

deployed positions.

"/9 JSC CDDF 1992 Annual Report


REPORT DOCUMENTATION PAGE For.,Approved

OMB No. 0704-0188

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1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED

January 1993 Technical Memorandum

4 TfTLE AND SUBTITLE 5 FUNDING NUMBERS

JSC Director's Discretionary Fund

1992 Annual Report

6. AUTHOR(S)

Compiled by Lyle Jenkins, New Initiatives Office

7. PERFORMINGORGANIZATIONNAME(S)ANDADDRESS(ES)

New Initiatives Office

National Aeronautics and Space Administration

Johnson Space Center

Houston, Texas 77058

9. SPONSORING/MONITORINGAGENCYNAME(S)ANDADDRESS(ES)

National Aeronautics and Space Administration

Washington, D.C. 20546-001

8. PERFORMING ORGANIZATION

REPORT NUMBER

S-70g

10. SPONSORING / MONITORING

AGENCY REPORT NUMBER

NASA-TM-104760

11. SUPPLEMENTARY NOTES

12a. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified/Unlimited

Subject Category 99

12b. DISTRIBUTION CODE

1 3. ABSTRACT (Maximum 200 words)

Annual report of the Johnson Space Center Director's Discretionary Fund documenting

effective use of resources. The $1,694,000 funding for FY92 was distributed among 27

projects. The projects are an overall aid to the NASA mission, as well as providing

development opportunities for the science and engineering staff with eventual spinoff to

commercial uses. Projects described include space-based medical research such as the

use of stable isotopes of deuterium and oxygen to measure crew energy use and techniques

for noninvasive motion sickness medication. Recycling essentials for space crew support

is conducted in the Regenerative Life Support and the Hfbrid Regenerative Water Recovery

test beds. Two-phase fluid flow simulated under low-grtvity conditions, hypervelocity

particle impact on open mesh bumpers, and microcalorimetry to measure the long-term

hydrazine/material compatibility were investigated. A oatent application was made on a

shape-memory-alloy release nut. Computer estimate of crew accommodations for advanced

concepts was demonstrated. Training techniques were evaluated using multimedia and

virtual environment. Upgrades of an electronic still camera provide high resolution

images from orbit. For additional information on the p_ojects, contact the individual

investigators or Lyle Jenkins at (713) 283-5405.

14. SUBJECTTERMS 15. NUMBEROFPAGES

Discretionary Fund, NASA mission

17 SECURITY CLASSIFICATION

OF REPORT

Unclassified

18. SECURITY CLASSIFICATION

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19. SECURITY CLASSIFICATION

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Uncl ass' fled

16. PRICE CODE

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