/ 

NASA Technical Memorandum 58277 

* 

1 Research and Technology 

Annual Report 1986 
- ~~ ~ ~~~ ~ ~~~~ ~ 

NASA Technical Memorandum 58277 

Research and Technology 

Annual Report 1986 

December 1986 

* 

Prepared by 

Office of the Director of Engineering 

Lyndon €3. Johnson Space Center 

Houston, Texas 
Preface 

This report is prepared on an annual basis for the purposes of highlighting 

the fiscal year research and technology (R&T) activities. Its intent is to better 

inform the R&T Program Managers of significant accomplishments that 

promise practical and beneficial program application. The report is not 

inclusive of all R&Tactivities. Thisdocument will be updated in November of 

each year. 

The JSC Annual R&T Report is compiled by the Office of the Director of 

Engineering. The personnel listed below have coordinated the technical 

inputs IUI LII~II I~x~~~LIvG~~~~~~,~~ 

directed to them or to the technical monitors listed in the Significant Task 

indices. 

' .- *--AI--:- ------*:*a- -e-+;rrne nf thn rnnnrt nyv.'Y... nptailpd - nllnqtinns may be -.-..__ ~ 

M. E. GoodhartKode EA3 Overall Coordination 

71 3-483-2703 

A. M. WhitnahKode ED 

71 3-483-6607 Technology 

Aeronautics and Space 

P. C. JohnsonKode SD Life Sciences 

713-483-71 11 

I. D. Browne/Code SN 

71 3-483-51 32 

Solar System Exploration 

A. M. WhitnahKode ED Space Flight Advanced Programs 

71 3-483-6607 

For information or additional copies, contact M. E. GoodhartKode EA3 

71 3-483-2703 

iii 
Contents 

I 

1 Office of Space Sciences and Applications 

1 Life Sciences Summary 

5 Life Sciences Significant Tasks 

17 Solar System Exploration Summary 

23 

35 Office of Aeronautics and Space Technology 

35 Summary 

41 Significant Tasks 

53 Office of Space Flight 

53 Advanced Programs Summary 

59 Advanced Programs Significant Tasks 

71 Index 

Solar Syster, Exploratioii Sigi;ifizant Tasks 
Space Sciences and 

Applications 

Life Sciences 

Summary 

i p 
Office of Space 

Sciences and 

Applications 

Life Sciences 

In preparation for man’s permanent 

presence in space, researchers at the 

Johnson Space Center (JSC) are developing guidelines for a high-quality, 

permanent health care delivery system 

for the Space Station. The Medical 

Operations Branch of the Medical 

Sciences Division is actively pursuing 

the goai oi ensuring the neaiih ana 

safety of the Space Station crews. An 

active preventive medicine program 

that includes safety education, emergency medical treatment and contingency procedures, frequent medical 

checkups before and during flight, inflight exercise and countermeasures, 

and a well-designed health maintenance 

facility (HMF) should help to prepare 

the crew to cope with environmental 

hazards. 

The design of the Space Station 

HMF presents a special challenge. 

Intended to provide preventive, diagnostic, and therapeutic medical care 

forthecrew, theHMF must bedesigned 

to meet the unique circumstances and 

needs of the Space Station in its micro-g 

environment. Space and weight limitations are primary design drivers. Quick 

accessto medical equipment isanother 

important requirement. A functional 

analysis currently being conducted will 

identify high-use and critical-use items 

so that these may be positioned conveniently for the user. Avoiding obsolescence and continuous resupply are 

complex problems being addressed to 

guarantee nearly 100°/~ reliability. 

To help differentiate life-threatening 

problems from self-limiting minor illnesses, the HMF must provide the 

capability to monitor certain physiological parameters: cardiographic, including arrhythmia detection; blood 

pressure; respiration; body temperature; 

and transcutaneous blood gases. Noninvasive cardiac output monitoring is 

considered desirable. Toward this end, 

a technique has been developed to 

permit the estimation of central venous 

Summary 

The parallel swing used to collect preflight and postflight data for DSO’s 433 and 439. 

pressure without the discomfort and 

inconvenienceof venipuncture. Also, a 

complete “crash cart” capability is 

planned and will include a defibrillator 

with adhesive electrode and external 

pacer, a bag-valve-mask, and a set of 

cardiadtrauma drugs and accessories. 

All treatment and patient monitoring 

equipment will feed data back to the 

HMF medical computer. A medical decision support system (MDSS) is being 

developed to provide computer assistance. The MDSS will provide an integrated medical information management system for the HMF. The system 

will have preventive, diagnostic, and 

therapeutic computer-assisted medical 

management, algorithms, checklists, 

procedures, and indexed medical reference materials as well as computerassisted inventory management of 

medical supplies and pharmaceuticals. 

All the information collected by the 

MDSS will be downlinked regularly to 

the NASAflight surgeon and to groundbased medical consultants. 

In addition to the treatment and 

monitoring equipment, a medical analytical laboratory will be onboard the 

Space Station as a subsystem of the 

HMF. The constraints imposed by the 

unique Space Station environment 

necessitate that instrumentation be evaluated for clinical performance, fluid 

handling, sample requirements, reagent 

stability, and other factors which could 

be influenced by micro-g. To meet these 

requirements, a comprehensive instrument evaluation program addressing 

these factors was undertaken. 

Along with the HMF work, groundbased and flight research programs are 

being continued. To help in understanding space adaptation syndrome (SAS), a 

lightweight helmet with electronic sensors and stimulators has been constructed 

for use in micro-g vestibular investigations. 

To aid the researchers in obtaining 

microvolume blood samples, a kit containing tools that permit rapid and precise 

aliquoting and distribution of small-animal 

blood samples has been fabricated. 

OSSA 3 
Ground-based studies simulating 

space flight are being conducted to 

investigate the extent and rate of trabecular and cortical bone loss as well 

as the rate and degree of recovery. A 

new piece of equipment, the OsteoAnalyzer, a prototype of which was 

used on Skylab missions, is being used 

to investigate bone demineralization. 

The problem of decompression sickness (“bends”) has been of concern to 

NASA. Past experiments at JSC have 

shown that increased duration of 100% 

O2 prebreathing decreases the incidence of decompression sickness 

symptoms and venous gas emboli 

(bubbles in the pulmonary artery). 

Experiments to elucidate the dynamics 

of this washout process have been 

conducted on 19 individuals of both 

genders for 51 runs. 

Many of the ground-based and flight 

research programs have been supplemented by in-flight medical research 

performed under the Detailed Supplementary Objective (DSO) Program of 

JSC. The DSO is a mechanism for the 

study of operational problems, including medical problems, the solutions of 

which are of vital importance to Space 

Shuttle operations. Candidate investigations are extensively reviewed by the 

Life Sciences Directorate and Space 

Transportation System (STS) boards 

and committees before they are finally 

manifested on a particular mission. 

Medical DSO’s have been a part of 

many Space Shuttle flights to date; 

more than 50 DSO’s have been flown 

on the Space Shuttle. A large number 

of these investigations occurred on 

SpaceShuttleflightsSTS-8, STS51-D, 

and STS 61-C. 

Some investigations (such as 403 

and 404) revealed no abnormalities in 

neurophysiological function even 

though abnormalities had been predicted. Others have demonstrated interesting and somewhat unexpected findings. For example, DSO 433 revealed 

that, during the early postflight period, 

passive tilting of the crewmember’s 

head produces a perception of linear 

translation. Surprisingly, DSO 459 

showed that ocular counterrolling could 

be produced in flight but to a lesser 

degree than on the ground. 

OF POQR QUALITY 

e 

. 

In-flight data collection with the ocular counterolling goggles 

(DSO 459). 

Health maintenance facility display panel. 

4 OSSA 
Space Sciences and 

Applications 

Life Sciences 

Significant Tasks 
Considerations in the Design of a 

Health Maintenance Facility for 

the Space Station 

TM: James S. Logan/SDZ 

PI: Mary M. Jurmain/SDZ 

Reference OSSA 1 

The NASA Space Station Program 

differs from previous manned space 

programs in that it represents the 

beginning of man's permanent presence 

in space. Crews will live and work in the 

Space Station for monthsat a time, and 

considerable research and activity is 

being devoted to making the facility as 

habitable and as comfortable as possible. 

Thedesign of thespacestation health 

maintenance facility (HMF) presents a 

special challenge. Intended to provide 

preventive, diagnostic, and therapeutic 

medical care for crewmembers during 

missions, the HMF must bedesigned to 

meet the unique circumstances and 

needsof the Space Station and itszerog environment. 

Space limitation is a primary design 

driver. The HMF equipment (excluding 

exercise devices) is expected to occupy 

two 42-in. equipment racks. This space 

limitation will require miniaturization 

and repackaging of equipment and 

subsequent detailed safety, reliability, 

and quality assurance analyses to 

ensure that the repackaged equipment 

will meet all requirements. 

Current plans are to place the HMF in 

the habitation module, where the crew 

will live and perform basic Space Station 

operations. With the recent decision to 

eliminate two modules from the Space 

Station design, spaceavailability iseven 

more critical. The team designing the 

HMF is currently considering a configuration that would permit the HMF to 

share space with the exercise equipment 

area and that would remove the patient 

restraint device from a high-trafficarea. 

(The patient restraint device combines 

the functions of stretcher, hospital bed, 

and treatment table.) 

Quick access to medical equipment 

is another important requirement. A 

functional analysis being conducted 

will identify high-use and critical-use 

items so that these may be positioned 

conveniently for the user. It should be 

noted, however, that access to items in 

zero g may differ from that on Earth, 

since translating in zero g may permit 

easier access to highly placed items. 

I 

- 

Exercise will be particularly important 

for preventive health care onboard the 

Space Station. The zero-g environment 

causes a decrease in cardiovascular 

fitness, muscularstrength, and immune 

response. Regular exercise can mitigate 

this deterioration. 

Since preparation for and cleanup 

afterexercisecan take30 min or longer, 

and crewmembers will have many other 

activities to perform, adhering to a 

regular exercise schedule presents a 

challenge. Thus, crewmembers must 

be motivated to use the exercise equipment. Members of the HMF design 

team are designing computer software 

that will help exercising crewmembers 

monitortheir own progressand compete 

with other crewmembers if they wish. 

Although thespacestation isexpected 

to have some physicians as crewmembers, a physician may not be aboard at 

all times. The availability of a quick 

rescuevehicle hasnot been determined. 

Performing medical procedures in 

zero g will require new techniques and 

skills. Therefore, crewmembers must 

be trained carefully, and the HMF must 

be designed such that nonphysicians 

can operate it. Central computer access 

will simplify some procedures, but 

equipment also must retain the capability of independent operation and, in 

some cases, be transportable to other 

areas of the Space Station or to a 

rescue vehicle. 

Design of the Space Station HMF 

presents an enormous challenge but 

also promises thesatisfaction of setting 

precedents in space medical care that 

will endure for many years. 

PRECEDING PAGE BLANK, NOT FILMm 

Inside view of habitability module. 

I/ 

e/' 

, 4 
ORlGZNAL PAGE IS 

OF POOR QUALITY 

Treatment Capabilities for Space 

Station Health Maintenance 

Facility 

TM: James S. LoganlSDP 

PI: Michael F. Stolle/SD2 

Reference OSSA 2 

The existence of a permanently manned 

Space Station, extended periods of 

living in space, reduced criteria for 

personnel selection, and limited rescue 

capability present unique medical problems. A dedicated neaitn maintenance 

facility (HMF) is therefore an essential 

medical capability. 

A set of premises was established to 

determine treatment capabilities to be 

included in the HMF. First, planned 

rescue capability is for a maximum 

response time requirement of 45 days. 

Second, only one critically ill crewmemberwill betreatedatanyonetime. 

Third, off-the-shelf medical equipment 

will be used as much as possible. Fourth, 

the most likely illnessesexpected to be 

encountered onboard Space Station, 

and the needed treatment capability, 

must be considered. Fifth, some illnesses are expected to have low probabilities of occurrence, but treatment 

capability for them must exist. Sixth, 

current program guidelines do not 

assurethata physician isalwayspresent. 

Based on these premises, it was determined that certain physiologic parameters must be monitored: cardiographic, 

including arrhythmia detection; blood 

pressure; respiration; temperature; and 

transcutaneous blood gases. Noninvasive cardiac output monitoring is considered desirable. A complete “crash 

cart” capability is planned and will 

include a defibrillator with adhesive 

electrodes and external pacer, a bagvalve-mask, and a set of cardiadtrauma 

drugs and accessories. 

In addition, a complete pharmacy 

and central supply facility is planned. 

The pharmacy will contain nonprescription and prescription drugs and will 

provide adequate drug control and 

patient record update through communication with the HMF medical 

computer. All treatment equipment and 

patient monitors will feed data to the 

HMF medical computer. 

Infusion of drugs and fluids will be 

provided with pumps to infusesolutions 

made from rehydrated packages of 

saline, lactated Ringer’s, etc. Pulmonary 

and oxygen therapy will be delivered 

by means of a fully controllable ventilator. Medical antishock trousers 

(MAST’s) will be included as part of the 

trauma treatment section. Control of 

body fluids and secretions in a weightless environment will require use of an 

aspirator, sponges, and collection bags. 

In addition to medical equipment, a 

system is provided to restrain the patient 

during procedures and to provide stability to the medical officer so that no 

conscious effort to maintain position is 

sickness is a possibility for humans 

living and working in a vacuum, a 

hyperbaric treatment facility is planned. 

required. ks!!y, since decnmpreccion 

Transportation of the patient and of 

necessary medical life support equipment has been a major consideration. 

A complete transport pack for a Space 

Shuttle rescue mission is planned. This 

transport pack will consist of a patient 

monitor, a defibrillator and cardiac/ 

trauma pack, MAST’s, an aspirator, a 

transport computer (with patient record 

input), a ventilator, an intravenous (IV) 

system, and the patient restraint system. 

Many vendors of commercial equipA set of decision criteria was selected 

to determine, using tradeoff studies, 

equipment that best meets the requirements. Based on these criteria, the 

most appropriate hardware to provide 

the quality of care necessary aboard 

the Space Station will be selected. 

* 

~ 

men! prcvide?hese medica! c+aSi!i?ies. 

Conceptual on-orbit HMF module. 

i &.% 

HMF FRONT FACE 

1. PATIENT MONITOR 17. HEMATOLOGY 

2. HYPERBARIC &TRANSPORT PACK 18. INVENTORY CONTROL 

3. VENTILATOR/PULMONARY 19. DIGITAL MICROSCOPE 

4. IVPUMPS 21. MICROBIOLOGY 

5. SUCTION 22. INCUBATOR 

6. CENTRAL SUPPLY 23. AIRWAY SUPPLIES 

7. CARDIAC OUTPUT MONITOR 24. LIFE SUPPORT, CRITICAL CARE, 8. 

8. FLUID THERAPY MONITORING INSTRUMENTATION 

9. AIR/FLUID SEPARATION 25. PHARMACY 

FUNCTION ASSESSMENT 20. BLOOD GASES 

10. CRASH CART DEFIBRILLATOR 26. DENTAL INSTRUMENTS 

11. COMPUTER 27. IV FLUID PRODUCTION 

12. MEDICAL COMPUTING/ 28. IV FLUID RECONSTITUTION 

13. COMPUTER 30. XRAY IMAGE RECEPTOR 

14. PHYSICIAN’S INSTRUMENTS 31. SUPPLIES 8. EQUIPMENT 

15. PHYSICIAN’S INSTRUMENTS 32. BIOLOGICAL WASTE DISPOSAL 

16. CHEMISTRY 33. GLOVEBOX 

COMMUNICATION 29. XRAY SOURCE 

8 OSSA 
Computerized Medical Decision 

Support for the Space Station 

Health Maintenance Facility 

TM: James S. Logan/SD2 

PI: David V. OstledSD2 

Reference OSSA 3 

A medical decision support system 

(MDSS) is being developed to provide 

computer assistance to medical officers 

on NASA’s Spacestation in conjunction 

with the health maintenance facility 

(HMF). The Space Station will have 

medical care requirements beyond 

those of previous space systems. The 

Space Station will have90-day missions 

with resupply by the Space Shuttle at 

30- or 60-day intervals. Space Station 

medical officers may not always be 

physicians. As a minimum, two 

primedic-trained astronauts will be 

designated as Space Station medical 

officers. 

The MDSS will provide an integrated 

medical information management system for the HMF. The system will have 

preventive, diagnostic, and therapeutic 

computer-assisted medical management algorithms; computer-assisted 

medical checklists, procedures, and 

indexed medical reference materials; 

and computer-assisted inventory management of medical supplies and pharmaceuticals. Through Space Station 

services, the MDSS also will support 

theexchange of electronic mail between 

any crewmemberand the ground-based 

crew surgeon and will support secure 

two-way voice communications among 

crew medical officers, NASA flight 

surgeons, and ground-based medical 

consultants. Additionally, all information collected by the MDSS will be 

downlinked regularlyto the NASAflight 

surgeonsand toground-based medicai 

consultants. Each HMF subsystem will 

provide peripheral processing of realtime data measurements. Thus, each 

subsystem will transmit processed and 

verified measurements and information 

to the MDSS. 

Functional block diagram of the HMF medical decision support system. 

Report/ 

Edit/Entry Display/ 

Graphics 

Knowledge 

Base Textbook 

Medical 

Records MIB Support 

Image Processing 

Ulaueform display 

Sampled waveform data will not be 

stored in theMDSSonboard thespace 

Station but will be transmitted to the 

ground for research purposes. The 

medical information bus (MIB), under 

development by an MIB working group, 

is specified as the communication 

medium between the MDSS and HMF 

subsystems. Data from the subsystems 

will be recorded automatically in medical records maintained by the MDSS. 

Design around a standardized MIB will 

enable substitution of new clinically 

validated instruments for the instruments initially provided in the HMF. 

The MDSS will have an integrated 

kernel of system services. A medical 

records system will provide a complete 

record of each crewmember’s medical 

history, a record of all physiological 

measuremenis, arid a iecoid O: medi~~! 

notations made by the medical officer 

while on the Space Station. A medical 

knowledge base will be created to 

provide medical protocols fordiagnosis, 

treatment, and medical record processing support. An electronic medical 

textbook will be created by selecting 

and extensively indexing medical texts 

for reference material on the Space 

Station. The MDSS will use the hardware 

elements developed for the Space 

Station data management system, a 

distributed network of redundant processors and mass storage devices that 

will provide common data base management support and ground communications support for the Space Station. 

MDSS applications will use the kernel 

services to allow entry of information 

into the medical record, text and graphic 

display of information from the medical 

record, radiological image display, and 

specific medical protocol implementation. In addition to the medical protocol 

support, the MDSS will provide communications to a ground network of 

medical specialists in theevent of major 

medical contingencies. Protocols, algorithms, and systems used in the MDSS 

will be the predecessors of those needed 

to provide medical care for future longduration space flight. 

OSSA 9 
Mechanical Ventilation for 

Medical Patients Aboard the 

Space Station 

TM: James S. Logan/SDS 

PI: Bruce A. McKinley/SDS 

Dwayne R. Westenskow 

Reference OSSA 4 

Assistance in breathing is commonly 

required by medical patients with severe 

cardiorespiratory disease. Breathing 

can beassisted by meansof aventilator, 

an electromechanical instrument, to 

supply oxygen and to remove carbon 

dioxide through a breathing tube and 

circuit connected to the patient’s trachea. Disease states that may require 

mechanical breathing assistance aboard 

Space Station could include several 

categories of injury and illness. 

Whereas proper and timely use of 

mechanical ventilatory support could 

save a patient’s life, the appropriate 

instrumentation and apparatus must 

beavailable to permit mechanical ventilation in the Space Station setting and, 

if needed, during transport from the 

Space Station to Earth. This equipment 

is being selected, tested, and developed 

as a component of the Space Station 

health maintenance facility (HMF). 

Several mechanical ventilators are 

available for use in hospitals. Some of 

these instruments are sufficiently compact and lightweight to be used during 

patient transport. Accurate monitoring 

and control of the patient and the 

instrument also are required during 

mechanical ventilation. For Space Station, medical monitoring is intended to 

be supplied at the instrument, at an 

onboard medical computer, and at 

ground-based medical consultant terminals. The Siemens model 9OOC ventilator was selected for initial design 

efforts because of its compact pneumatics system, its low electrical power 

requirements, its modularity, and other 

advantages. 

A system to provide complete mechanical ventilatory support and monitoring 

(on site and at consultant remote 

terminals) is being designed by bioengineers at the University of Utah. 

Information from theventilator is monitored constantly to provide a continuous 

record of ventilatory status and of lung 

function parameters that indicate 

changes in ventilatory support effected 

manually by the onsite medical attend10 OSSA 

ant. A second major function of the 

system underdevelopment is to indicate 

changes in patient ventilatorystatus, to 

provide warnings indicating parameters 

of concern, and to provide integrated 

analysis and backup of instrument 

alarms to assist the remote consultants 

in advising and the onsite medical 

attendants in adjusting appropriate 

ventilator controls. The pneumatics unit 

of the Siemens 9OOC ventilator and 

dataflow from theventilator electronics 

module to various monitoring sites are 

illustrated. 

Hardware related to mechanical ventilation of a patient includes breathing 

circuits, endotracheal tubes, and instruments to permit correct positioning of 

an endotracheal tube in the patient’s 

airway. Supply of oxygen and air (or 

nitrogen) to theventilator instrument at 

appropriate pressures is also required 

and is planned to be from Space Station 

respirable atmosphere supplies. Capability for manual ventilation when using 

a bag-valve-mask assembly also is being 

planned. 

(TO ROOM AIR) C 

(FROM PATIENT) 

ELECTRONIC ! CONTROL 

Space Station HMF mechanical ventilator system data flow. 

Siemens 9OOC pneumatics unit. 
Dynamics of Whole-Body 

Nitrogen Washout While 

Breathing 100% Oxygen 

TM: David J. Horrigan, Jr./SDS 

James M. Waligora/SD5 

PI: John H. Gilbert WSD5 

Benjamin F. Edwards, Jr./SDS 

Reference OSSA 5 

Past experiments at the Johnson Space 

Center (JSC) haveshown that increased 

duration of 100% oxygen (0,) prebreathing decreases the incidence of 

decompression sickness symptoms 

("bends") and venous gas emboli (bubbles in the pulmonary artery). Experiments to elucidate the dynamics of this 

washout process have been conducted 

at JSC over the past 2 yr. 

The recent experiments involved the 

use of 1 1 male and 8female test subjects, 

who breathed 100°/~ O2 from a sealed 

mask for 210 rnin in each of three body 

positions: (1) sitting, (2) supine, and (3) 

supine with a 6O head-down wholebody tilt. Measurements of incremental 

breath volume and corresponding 

instantaneous nitrogen (N,), O,, and 

carbon dioxide (CO,) breath fractions 

during the entire respiratory cycle were 

made using a computer-controlled mass 

spectrometer. Respiratory tidal volume 

and average breath N2, 02, and C02 

percentage measurements were recorded at the end of each breath. 

Analysis of these data gave the total 

volume of N,expired during each breath 

and the total N2 volume eliminated 

during the procedure. This information 

was combined with previously measured 

and/or calculated physical parameters. 

Statistical analyses on 51 runs of the 19 

individuals in the various body positions 

suggest gender- and position-related differences in N2 washout rates (mVrnin) 

and/or fraction of the expired gas (N,). 

With a 3-by-2 analysis of variance 

(ANOVA) (three positions, two genders), 

N2 washout rates were not affected by 

position but were significantly different 

throughout the experiment between males 

and females, with females having lower 

rates. Significant differences in N2 expired 

gas fraction were seen, however, throughout the 90-min interval between both 

gender and position levels. Gender/ 

position interaction was significant only 

at the 15-min interval. Total N2 volume 

washed out during the run is also significantly lower in females than in males. 

When a contrast analysis of the 

position data is performed on the N2 

expired gas fractions, significant differences are seen between the sitting 

and supine positions through 90 min, 

but no differences are noted in comparisons of sitting and head-down positions 

or of supine and head-down positions. 

(See figure.) A significant difference 

also seen at 15 min between supine and 

head-down positions suggests that 

cephalad movement of the viscera may 

be affecting respiratory efficiency leading to altered tidal volumes. 

When the N, expired gas fraction or 

the N2 washout rates were graphed 

over time, a three-phase exponential 

curve was seen. The slopes of each 

phase were compared by means of the 

3-by-2 ANOVA. The first phase generally 

ended at about20 rnin into the washout, 

and the second phase ended ai abuiii 

80 to 90 min. The third washout phase 

asymptotically approached a constant 

washout rateor fraction, and no rigorous 

equation could be derived to describe 

it. The slopes of these phases were not 

significantly different when gender or 

body position were compared. 

~~ 

Regression computed using N2 washout rates compared to total body water, 

average tidal volume, vital capacity, 

and total body fat mass revealed the 

closest correlation with total body water 

(r = 0.85). When graphed, these data 

points showed gender-oriented washout 

rates as falling upon a continuous line 

with data from female subjects around 

the lower end of the spectrum and data 

from males at the upper end. This 

observation would explain the consistent and significant differences between 

male and female washout rates and 

expired volumes described previously 

and also explains the lack of differences 

between the slopes of the exponential 

washout curves when they were graphed 

as natural logarithms. This finding 

implies that the physiological processes 

involved in the washout process are not ---A-- A--.--Arrn+ Tha Aiffornnpec cppn ycllucl UGpGlt"~~8,. I II~YIIIYIY.I" -I--.. 

in washout rates are most likely dependent only on body-size-related parameters. 

Position-related expired N, fraction (combined data from male and female subjects). 

-3 

-4 

z 

0 

to -5 4 

U a 

cu 

Z 

-6 

E 

n 

X 

0 

% -7 

I! 

-8 

-9 

0 20 40 60 80 100 120 140 160 180 

TIME, MIN 

0 HEAD DOWN 0 SUPINE A SITTING 

OSSA 11 
Clinical Laboratory Capability for 

the Health Maintenance Facility 

TM: Bernard J. Mieszkuc/SD4 

PI: Karen Gaiser/SD4 

Reference OSSA 6 

The Space Station represents the beginning of man's permanent presence 

in space. A system for in-flight health 

care and maintenance is essential for 

the success of the program. The health 

maintenance facility (HMF) will provide 

therapeutic capabilities within the Space 

Station. One of the major subsystems 

of the HMF is the medical analytical 

laboratory, which will provide in-flight 

analytical capability to facilitate medical 

diagnosis and to guide appropriate 

therapy. Some of the components of 

this subsystem include bloodhrine 

chemistry, hematology, and microbi- 

:.. st:-C.. ....^..^-..:.*^ -1:^^-^^.:^ --A 11 1-1 llyl I1 PI PVPI IlIVP, Ulclyl IUDLIC., QI IU 

ology. 

One of the guidelines for the development of the HMF is that off-the-shelf 

instrumentation be used where applicable because of proven analytical 

performance and reduced developmental costs. The constraints imposed 

by the unique Space Station environment necessitate that instrumentation 

be evaluated for clinical performance, 

fluid handling, sample requirements, 

reagent stability, and other factors which 

could be influenced by micro-g. Addimicro-g, such assize, weight, and power 

specifications, must be considered. 

?icnz!!\/ ,, fartnrc .--.-.- nnt ..". inf1iinnec.A .I..."".,".." h\r "J 

ORtGlNAL PAGE 

OF POOR QUALKY 

A comprehensive instrument evaluation 

program addressing clinical performance, human factors, reagent requirements, and micro-g compatibility was 

undertaken. Specifically, clinical performance evaluation includes instrument precision, linearity, accuracy, 

calibration requirements, and correlation with standard methods. Human 

factors include maintenance, ease of 

operation, technician prompts, and 

troubleshooting and repair. Reagent 

preparation, liquid handling, and shelf 

I ife. M icro-g corn pati bi I ity considers 

the mechanical and analytical operation 

of the instrument in micro-g. 

rmn, ,irnrn'3ntr +-LA ;..+e ..,.,-.AI on+ r+nrr.-rr I vv UI I UI I 0-8 I w CUR= I I I ~u abbuu I I I atui ayc, 

Technician evaluating a clinical chemistry analyzer. 

12 OSSA 
Processing Kit for Microvolume 

Blood Samples 

TM: Philip C. Johnson/SD 

PI: Theda DriscoWSD4 

Ron NachtmanlSD4 

. Reference OSSA 7 

Researchers working with small animals 

are restricted to microvolumetric sequential blood samples to prevent 

affecting the animal’s hematology and 

chemistry values. These small blood 

samples must be processed immediately 

after they are obtained because of their 

rapid loss of moisture. Manipulation of 

the glass micropipettes used in obtaining volumetric samples is difficult because they are small and fragile. As a 

solution to these problems, a kit containing tools that permit rapid and 

precise aiiquoting ana aisiribuiion of 

small-animal blood samples has been 

developed. Small boxes, originally 

designed for cosmetics, were modified 

for hematology work, resulting in kits 

for processing one or two microvolumetric blood specimens. These 117- by 

90- by 10.5-mm kits are prepackaged, 

color coded for easy animal subject 

identification, and labeled with the date 

of the experiment. The transparent 

boxes show the number and type of 

hematology and chemistry samples 

collected and aliquoted after a single 

blood draw. 

Inside the kits, 10-pl micropipettes are 

sandwiched between Velcro strips 

attached to elevated platforms. This 

arrangement allows each blood specimen to be aliquoted efficiently into 

micropipettes, which are later removed 

for processing. In addition to micropipettes, the kits contain a micropipette 

holder, for safe handling and manipulating of the pipette; a blowout bulb, 

for transferring blood samples into 

diluting and staining fluids; and prelabeled, color-coded miniature test 

tubes, to ensure proper sample identification in preparation for various analyses. The kit is large enough to accommodate additional micropipettes, miniature test tubes, capsules with reticulocyte stains, etc., depending on the 

requirementsof a particular experiment. 

Beesuse zf ?he ease \Si?!! which pmcessed samples and disposables can be 

replaced, use of the kits is highly 

practical in space-flight animal experiments. 

The kits, as configured in the photograph, were used recently to collect 

samples for two consecutively timed 

phlebotomies of 50 and 30 pI, which 

yielded eight 10-pl blood samples from 

asingle laboratoryanimal. These types 

of kits presently are used in the ground 

research of life sciences experiments 

012 and 141, which are to be flown on 

the first Space Life Sciences Space 

Shuttle mission. 

Processing kit for microvolume blood samples. Dimensions of the closed kit are 117 by 90 by 

10.5 mm. This compact box contains items for aliquoting, transferring, and storing multiple 

blood samples obtained from small laboratory animals. 

OS6A 13 
OsteoAnalyzer 

TM: Philip C. Johnson/SD 

PI: Adrian D. LeBlanc/SDS 

Reference OSSA 8 

w 

A number of physiological changes 

occur in humanssubjected tothespace 

environment. Among these changes is 

bone mineral loss. Bone demineralization is of concern because reduced 

bone mass is recognized as the most 

important factor in the etiology of 

osteoporosis. Bene mineral loss xis 

not considered clinically important in 

U.S. space flights of 3-month duration; 

however, it is of concern in more 

extended or repeated space flights. 

The body contains two basic types of 

bone, cortical and trabecular. Cortical 

bone is compact, found largely in the 

long bones of the body, and requires 

about 15 yr for complete turnover. 

Trabecular bone, however, istheforcebearing structural support typeof bone 

found typically in the spine, the heel, 

and the forearm. This second type of 

bone requires about 5 yr for complete 

turnover. Bone loss associated with 

aging osteoporosis appears to affect 

trabecular bone before it affects cortical 

bone. Therefore, it seems more advantageous to screen for early bone loss 

by measuring trabecular bone changes. 

However, since some therapies result 

in building trabecular bone at the 

expense of cortical bone, measuring 

cortical bone is necessary also. 

OR~G~JAL PAGE 63 

The new OsteoAnalyzer, a prototype of 

which was used on Skylab missions, is 

being used to investigate bone demineralization. A self-contained mechanical 

scanner, equipped with power supply 

and specially configured microcomputer, helps researchers determine bone 

mineral content noninvasively, in vivo, 

with a radiation exposure less than that 

of a single chest X-ray. The versatility 

of the OsteoAnalyzer allows a wide 

range of measurements of bothcortical 

and trabecular bones. It is expected 

that with this information, a better 

understanding of the processesleading 

to osteoporosis can be achieved. 

110 

z 

dl00 

v) 

Q 

m 

LL 

0 

s 90 

JQ 

CC 

w 

z 

5 80 

5 

-I 

z 

Q 70 

a 

0 

60 

Ground-based studies simulating space 

flight are being conducted to investigate 

the extent and rate of trabecular and 

cortical bone loss as well as the rate 

and degree of recovery. A large normative data base has been developed in 

collaboration with investigators at the 

- 

- OF POOR QUALlTl X f SEM 

- 

- 

- 

I I I I I I I 

University of Texas Medical School, at 

Baylor College of Medicine, and at 

Texas Woman's University for use in 

NASA's longitudinal studies. Histomorphometric studies are being conducted along with bone mineral measurements to develop an understanding 

of the mechanisms involved in spaceflight-induced bone loss. Although the 

fundamental process underlying 

changes in bone during space flight is 

poorly understood, investigations of 

uvul lLb.l IIIGu=.ut~~ LU p~eve~ ILUI LU ieauce 

bone mineral lossareongoing, including 

those using low-dose fluoride ingestion 

and exercise. 

fi~,,"+o,-r..l",,"-,.+,. -..-..--A -.-I1-4 

BASELINE, 

WEEKS 

n = 16 

The graph shows the decrease in 

mineral content of the heel boneduring 

28 wk of bed rest. Bed rest is used in 

bone research studies because the 

decrease in skeletal mineral over time 

may be similar to the losses of bone 

mineral observed during prolonged 

spaceflight. After 6 months of inactivity 

in bed rest, the subjects lost 30% of the 

bone mineral in the heel bone. Bone 

mineral relates to the density of a bone, 

and loss in bone mineral can be equated 

io ioss of bone. Clinically significant 

osteoporosisoccurs when an individual 

loses 20% to 30% of the bone mineral. 

. 

1-4 5-8 9-12 13-16 17-20 21-24 25-28 

BED REST, 

WEEKS 

7 7 9 13 12 0 6 

The OsteoAnalyzer being employed to assess bone mineral content of a subject's foot. Bone 

mineral measurements help in understanding the mechanisms involved in space-flightinduced bone loss. 

14 OSSA 
ORIGINAL F9.GE !,5 

OF POOR QUAL!fY 

Helmet for Vestibular 

Investigations Aboard Spacelab 

TM: Millard F. Reschke/SB5 

PI: Mary Catherine McStravikKB5 

Reference OSSA 9 

A lightweight helmet with an array of 

electronic sensors and stimulators has 

been constructed for use in micro-g 

vestibular investigations to study space 

adaptation syndrome aboard Spacelab. 

The subject wearing this helmet sits in 

a rotating chair, which provides the 

vestibular stimuli. A restraint device 

attached to the chair confines the head 

motion to X-, Y-, or Z-axis. A light-tight 

dual independent visor system permits 

either or both eyes to be visually 

stimulated or recorded. Stimulation or 

monitoring of the eyes is accomplished 

by modular attachment sto these visors. 

A camera locked into place on the 

helmet visor records torsional eye 

movements. One of the subject’s eyes 

is covered with an opaque contact 

lens marked with a line. This lineallows 

the investigatortocompute thesubject’s 

eye movement since the contact lens 

moves congruently with the eye. The 

lens also blocks out visible light and 

fixation points. The movements of the 

video-recorded eye are synchronized 

with theoppositeeye, which isexposed 

to various visual stimuli. In addition to 

the camera, optokinetic and lightemitting-diode modules are also attached to the visors. Instrumentation in 

these modules is used to measure the 

subject’s horizontal and vertical eye 

movements (right to left and up and 

down). The linear orthogonal accelerometers on the helmet indicate translational rotation of the head about the 

orthogonal axes (pitch, roll, and yaw). 

The helmet isstabilized on thesubject’s 

head with inflatable liners and a biteboard assembly. The biteboard assembly consists of the mouthpiece, the 

mouthpiece connector, and the assembly’s quick-disconnect fitting. This 

assembly isdesigned for rapid removal 

in case of space motion sickness. 

Mounted on the back of the rotating 

chair is the helmet interface box that 

supplies power to all of the electronic 

modules. Thisunit also includescables 

and connectors that transmit output 

analog signals. The signals from the 

sensors areamplified, conditioned, and 

sent to the computer for formatting. 

This helmet is scheduled for flight on 

the first In-Flight Medical Laboratory 

Space Shuttle mission. 

--u --- D 

1 - 5==: --- r 

The helmet being tested on a subject flying in the KC-135 aircraft equipped to fly reducedgravity parabolas. 

Drawing of the helmet with its array of electronic sensors and connectors. 

VISOR 

CELEROMETER 

CAMERA 

CCELEROME 

PAIRS CHI NIBITE-BAR 

ASSEMBLY 

.TER 

OSSA 15 
Validation of Noninvasive Means 

of Measuring Central Venous 

Pressure in Humans 

PI: J. B. CharledSDS 

Reference OSSA 10 

Exposure to micro-g is associated with 

cardiovascular changes in space-flight 

crewmembers. Such changes as headward shift of the body fluids and 

elimination of the intravascular hydrostatic pressure gradient act to reduce 

an individual’s orthostatic tolerance. 

These changes are referred to as 

cardiovascular deconditioning. On 

return to Earth’s gravity, an upright 

individual is less able to counter the 

increased hydrostatic pressure. The 

reduced plasma volume, diminished 

smooth muscle tone, and impaired reflex 

responses limit the development of 

adequate blood pressure for cerebral 

perfusion with a possible result of 

orthostatic intolerance. 

Because a large part of cardiovascular 

adaptation to micro-g results from the 

fluid shifts, an understanding of the 

cardiovascular and neurohumoral effects of micro-g must begin with a 

knowledge of the provocative stimuli 

for these changes. A clinically useful 

indicator of cardiopulmonary blood 

volume is central venous pressure 

(CVP), which reflects the functional 

state of the heart. This parameter is 

usually determined from direct measurementsof blood pressure in thevena 

cava at the level of the right atrium, 

using a long catheter which has been 

threaded through a vein in the arm or 

neck. However, to be widely applied in 

studies on Earth and during space 

flight, a technique with less operational 

impact than that of venous catheterization is required. 

Recently, a technique has been developed to permit the estimation of CVP 

without the discomfort and inconvenience of venipuncture. This method 

involves monitoring the venous blood 

flow in a jugular or antecubital vein 

while the subject’s intrathoracic pressure is varied until the venous flow is 

transiently interrupted. Intrathoracic 

pressure is increased by imposing a 

slight, variable, end-expiratory airway 

resistance via a mouthpiece. The 

pressure generated within the mouthpiece can be related to intrathoracic 

pressure; the pressure that transiently 

stops venous blood flow equals CVP. 

The noninvasive technique for estimating CVP requires the subject to determine the 

intrathoracic pressure (measured at the mouth) which transiently stops jugular blood flow 

(measured by Doppler flowmeter). Congressman Bill Nelson demonstrated the feasibility of 

repeated CVP determinations daily throughout the STS 61-C flight. 

Changes in CVP estimated noninvasively in one subject on STS 61-C are compared with those 

measured invasively in four subjects on Spacelab 1. The noninvasiveestimate isalso within the 

95% confidence interval of the direct measurements. 

11 I I I I I I I I 

0 1 2 3 4 5 6 7 a 

TIME IN FLIGHT, DAYS 

$ SL-1 (n = 4): KIRSCH 

o STS 61-C (n = 1): CHARLES 

16 OSSA 
Space Sciences and 

Applications 

Solar System Exploration 

Summary 
Office of Space 

Sciences and 

Applications 

Solar System 

Exploration 

Introduction 

The exploration of the solar system as it 

is conducted at the Johnson Space 

Center (JSC) is primarily pursued 

through programs of planetary science 

research and space science research. 

Planetary science research is broadly 

aimed at understanding the processes 

that are significant contributors to the 

present and past stages of planetary 

history, principally to the terrestrial 

planets. These studies are performed by 

analysis of planetary materials, experimental simulation of planetary conditions 

and processes, remote-sensing observations, and theoretical modeling to interpret observational data. The research 

is basic to understanding requirements 

for future space missions, including 

science rationale and experiment 

design. 

Space science research at JSC is 

broadly aimed at understanding the 

processes operating in the space environment and at applying that understanding to science and space flight 

operations in that environment. The 

research is most often basic research 

on the natural phenomena, either 

through direct study and measurement 

of the phenomenaorthrough laboratory 

simulations. The research is basic to 

understanding requirements of current 

and future missions and to the design 

of scientific experiments. 

Highlights of recent planetary science 

and space science research at JSC are 

described in the following summary. 

Extraterrestrial Materials Studies 

A fundamental part of JSC's solar 

system exploration effort is the study 

of extraterrestrial materials: lunar samples, meteorites, and cosmic dust. As 

scientists have found from insights 

made possible by the returned lunar 

samples, there is no substitute for the 

detailed study of actual samples of 

other worlds. 

Summary 

ORIGINAL PAGE FS 

OF POOR QUALITY 

Lunar sample processing laboratory. Nitrogen-filled cabinets protect lunar samples from 

terrestrial contamination while research analysts study and prepare the samples for shipment 

to research laboratories. Lunar samples are stored in the vault that can be seen through the 

window at the end of the laboratory. 

The Moon is the cornerstone of 

planetary science. Lunar sample studies 

have been fundamental in developing 

our understanding of theearly evolution 

and continued development of planetary 

bodies and have led to major revisions 

in our understanding of processes for 

the accumulation of planetesimals and 

the formation of planets. Studies of 

lunar samples have increased our 

understanding of impact cratering, 

meteoroid and micrometeoroid fluxes, 

the interaction of planetary surfaces 

with radiations and particles, and even 

the historyoftheSun. Furthermore, the 

treasures returned through the Apollo 

Program provide information that is 

required for a return to the Moon, 

beginning with new exploration (Lunar 

Geoscience Observer), followed by 

intensive study (new sample return 

missions), and eventually culminating 

in a lunar base and in lunar resource 

utilization. 

Much of the information gained from 

meteorites cannot be obtained from 

any other source currently available. 

The records preserved in these migratory chun ks of matter that have come to 

Earth are difficult to read, but recent 

studiesof them have revolutionized our, 

understanding of the origin and early 

evolution of the solar system. Meteoritics, the study of meteorites, is an 

attempt toanswer major questions about 

the age and origin of the solar system, 

the composition and evolution of the 

Sun and the planets, the presence of 

ancient magnetic fields and heating 

events, and the internal and surface 

processes on planets and asteroids. 

The scientific value of meteorites is 

vast in relation to their limited quantity, 

and the secrets contained in these 

OSSA 19 
extraterrestrial gifts have only begun to 

be unraveled. 

Cosmic dust, thought to be primitive 

solar system material, is another extraterrestrial material of intensive scientific 

study. The most common sources of 

cosmic dust are believed to be the small 

bodies of the solar system, asteroids 

and comets, although some of the dust 

may come from interstellar space. Both 

comets and asteroids are thought to be 

relatively unchanged objects left over 

when the larger planets formed, and 

preserved clues about the origin of the 

solar system. Cometary dust is of 

particular interest and is the subject of 

studies by JSC scientists because 

comets must have formed in the outermost fringes of the original solar nebula 

where temperatures were low enough 

for ices to form and survive. In these 

distant regions, it is even possible that 

some of the interstellar dust particles 

that helped form the solar system were 

trapped and preserved in the icy comets. 

dust !rem these objects shcn!(! cnnt2in 

Planetary Crustal Studies 

The formation of planetary crusts 

through primordial differentiation is a 

fundamental topic of Earth and planetarysciences. If meaningful modelsare 

to be developed fortheevolution of the 

solar system, physical and chemical 

constraints must be developed for the 

processes involved in the evolution of 

the solid objects in the solar system. 

Crust-forming rocks, which represent 

material that was segregated from the 

mantles of the planets, can provide 

information about both crustal and 

mantle evolution. 

Although the mantle of a planet can 

be expected to have evolved with time, 

present-day mantle compositions provide evidence about only the present 

result of that evolution. Many different 

evolutionary paths, however, may have 

been followed to the present point in 

time. Crustal rocks, which were formed 

at many different times during theevolution of a planet and which are essentially 

the only materials available for study, 

providean excellent opportunity to trace 

the evolutionary path or paths. 

In contrast to the Moon, where the 

predominant volume of the crust was 

formed in thefirst 10%of its history, the 

crustal rocks of the Earth represent 

85% of the planet’s history. This extensive crustal history of the Earth presents 

many complications in deciphering 

evolutionary 

Observation port of lunar sample processing cabinet. The horizontal window of the observation 

port permits detailed examination, microscopic study, and photography while the lunar 

samples remain in the protective nitrogen atmosphere of the processing cabinet. 

20 OSSA ORlGtNAL PAGE IS 

OF POOR QUALITY 

mechanisms that are not a problem on 

a planetary body such as the Moon, 

which has had little activity in the last 3 

Gyr, but may also be viewed as an asset 

in identifying and elucidating the major 

mechanisms in the evolution of Earth’s 

crust and mantle. 

The isotopic signatures of source 

regionsfrom which crust-forming rocks 

are derived are keys to understanding 

the evolution of the mantles and crusts 

of planetary bodies. At JSC, these 

signatures are the subject of research 

that will assist in developing hypotheses 

of terrestrial mantle-crust evolution and 

that will serve as a basis for interplanetary comparative studies. 

Mars Processes Studies 

Even though the surface of Mars has 

been thoroughly mapped by Mariner 

and Viking orbiters, and rough chemical 

data from two sites have been obtained 

by the Vi king landers, major unanswered 

questions about the planet still exist. 

The rocks look like volcanic lavas, but 

little is known about their chemistry 

and nothing at all about their mineral 

composition, ages, origin, and how 

they fit into the evolution of the planet. 

The reactions between the atmosphere 

and the rocks, and the chemistry of 

martian weathering, are also unknown. 

Until such time as returned martian 

samples are available for study, scientists at JSC are attempting to understand better the chemical, physical, 

and mineralogical state of the martian 

surface and the weathering processes 

that modify it. Their research includes 

experimental and theoretical studies of 

the spectral and other physicochemical 

properties of pure and substituted ironbearing compounds, theoretical and 

experimental studies of the effects of 

optical scattering on reflectance spectra, 

laboratory studies of materials weathered in terrestrial environments considered to be analogous to those on 

Mars, and studies of selected materials 

weathered in the laboratory under 

simulated martian conditions. This 

approach permits extensive feedback 

and scaling of processes observed under 

terrestrial conditions to martian conditions and permits study of processes 

not expected to be significant under 

terrestrial conditions. 

Another JSC study of Mars processes 

has assessed the mineralogical factors 

associated with martian dust particles 
08!G12VAL PAGE IS 

OF POOR QUALITY 

as condensation nuclei and has linked 

those factors of significance to the formation of frosts on Mars. The experimental results not only confirm previous 

observations by atmospheric physicists 

that heterogeneous nucleation of ice 

depends significantly on the chemical 

and physical properties of the substrate 

but also indicate that, in general, crystalline minerals are expected to be better 

nucleators of condensates than are 

cryptocrystalline mineraloids. The significanceof volatile materials on presentday Mars is of majorscientific importance 

and has practical implications for planning future missions to Mars. 

’ 

Earth Remote-Sensing Studies 

The exploration of the solar system has 

a common denominator: fitting planet 

Earth into the ever-expanding informational mosaic of how the universe began, 

how it evolved, and how it isstructured. 

A quarter century of Earth study from 

space has produced an immense volume 

of information, but it hasalso underlined 

the fact that a great deal is still to be 

learned about the near-Earth environment. 

In 1965 and 1966, 2 of 17 scientific, 

engineering, and medical investigations 

conducted by astronauts during Gemini 

maiiy gsals, biii they ~ii be ieu”dCed :O 

missions involved synoptic terrain and 

weather photography experiments. The 

results of that and subsequent handheld photography by flightcrews clearly 

established the value of Earth photography for a multitude of scientific 

disciplines. 

These investigations continue as JSC 

scientists provide support to Space 

Transportation System (STS) astronauts 

for the acquisition of Earth-looking 

photography. In consultation with 

scientific investigators, sites for photography are selected, researched, and 

documented in training manuals for 

each STS mission. Flightcrews are 

briefed on photographic techniques 

and on specific sites of geological, 

meteorological, and oceanographic 

interest. Support continues during 

ongoing environmental processes, and 

postmission activity includes debriefing 

flightcrews, cataloging and indexing 

mission photographs, and updating a 

computerized data base. 

Because direct ground measurements 

of biomass and production for large 

areas of the Earth’s surface are not 

feasible, JSC scientists also are attempting to demonstrate the validity of 

using remote-sensing techniques to 

monitor vegetation characteristics by 

measuring biomass, productivity, and 

missiGns i:: !hc f=:m sf uplinking 

leaf area for specific regions of boreal 

forest. The overall goal of this research 

is to contribute to the measurement of 

the global biomass and net primary 

productivity. An understanding of 

physical relationships and appropriate 

statistical procedures are used to 

develop models relating biomass and 

productivity to leaf area indices, and 

relating leaf area indices to remotely 

sensed spectral images. 

Still other Earth studies being conducted at JSC and employing remotesensing techniques seek to determine 

whether there is unique information in 

the polarization of solar visible and 

near-infrared radiation reflected from 

the Earth’s surface and atmosphere to 

support development of operational 

and/or advanced research sensors that 

inc!u& &serl:l!i()fi ()f !hl! lylrjgh!P, 

In astudysponsored by the Director’s 

Discretionary Fund, some interesting 

results are being obtained. The following 

definitive statements can be made 

relative to the process. 

1. The degree of polarization of 

terrestrial scenes as viewed from orbital 

altitude, normally between 0 and 0.2, 

can be 0.5 or more. 

2. Degree of polarization appears to 

besuitableas an additional variable for 

classification of some scene components. 

Polarization pair of imagesof the Red Sea and the Gulf of Aden takenduring STS mission 51-A. (Image reversed for analysis purposes.) Maximum 

image to the left includes polarized reflected light plus one-half of the unpolarized light. The image to the right contains the other one-half of the 

unpolarized light. 

OSSA 21 
Contours in degree of polarization. Tight gradients in the water along 

the Red Sea indicate turbidity or bottom contours. Note fine detail in 

land patterns. 

3. Systematic changes in degree of 

polarization can occur across a scene 

because of geometric effects. Reversal 

in phase of polarization occurswithin a 

scene at times. 

4. There is a distinct improvement in 

signal-to-noise ratio when the polarized 

component isdiscarded in manyscenes 

as theatmosphericscattering contribution to path radiance is diminished. A 

similar effect is indicated for water 

penetration. 

5. Some patterns not discernible in 

intensity are apparent in degree of 

polarization images. 

6. Significant variation in degree of 

polarization occurs between colors in 

some scene components. 

Radiation Environment Studies 

The work of JSC scientists also involves 

directly supporting operational radiation dosimetry requirements forall STS 

missions, providing the conceptual 

design and development of advanced 

radiation dosimetry systems for the 

Space Station, serving as co-investigators of complex radiation experiments 

both on the STS and on the Space 

Station, and conducting radiation environment studies. 

A recent special meeting held under 

the auspices of the Space Station 

Radiation Committee at NASA Headquarters resulted in reviewing the use 

of radiation belt models to predict 

radiation doses expected in the Space 

22 OSSA 

Impact pit in thermal protection system tile of Space Shuttle Atlantis 

after maiden voyage. This impact was made by orbital debris. 

Station. Among other findings, it was 

determined that the modelsdate back to 

1964 and 1970 and, in order to update 

the models, new dataare required. Such 

an update is very important in view of 

the significant temporal decrease in the 

strength of the Earth’s magnetic dipole 

moment and the associated adiabatic 

effects on the spatial distribution of the 

trapped radiation. Experimental and 

analytical investigations in this area are 

being pursued by JSC scientists, who 

also are using dosimetry data obtained 

on projects ranging from Project Mercury 

to the Space Shuttle Program to draw 

conclusions about the stability of the 

Earth’s inner Van Allen belt radiation 

environment. 

Auniquetechniquetoextract trappedradiation belt spectra using passive 

dosimeters carried aboard STS vehicles 

is another recent accomplishment of 

JSC scientists. Data from Space Shuttle 

missionsSTS51-D, STS51-G, STS51- 

F, and STS 51-8 have been analyzed to 

show that the measured spectra are 

harder than the predicted spectra from 

the “best” trapped environment model, 

the modified Sawyer-Vette AP-8 model. 

This result is important because it 

provides hard evidence that the SawyerVette AP-8 model is incorrect at Space 

Shuttle orbital altitudes. 

Impact Studies 

problem for future space activities. In 

this area, the primary objective of 

experimentation now being performed 

at JSC is to understand better the 

impact processes and the collisional 

hazards posed by meteoroids and 

orbital debrisfor spacecraft and materials used for space applications. Impact 

features in spacecraft and exposed 

surfaces of satellitesare being analyzed 

to determine the relative proportions of 

micrometeorites and orbital debris 

particles and to determine the particle 

types and compositions for each major 

particle class based on impact residue 

and impact morphology. Mathematical 

models for predicting hypervelocity 

impact crater growth in composite 

materials also are being developed 

through experimental laboratory 

studies. 

Inaddition,the NASAKC-135aircraft 

equipped to f 1 y red uced-g ravity parabolas is being employed to provide the 

low-gravity conditions necessary for 

conducting experiments to measure 

ejection velocities from craters formed 

by relatively low-velocity impacts and 

to provide the capability of impacting 

free-floating targets. The velocities of 

crater ejecta are important in planetary 

cratering studies, and the free-floating 

operations will be useful in investigations of accretional dynamics and the 

evolution of asteroid populations. 

Previous studies have indicated that 

orbital debris may be a significant 

ORlGlNAL PAGE SS 

OF POOR QUALITY 
Space Sciences and 

Applications 

Solar System Exploration 

Significant Tasks 
Lunar Zircons 

PI: Charles Meyer, Jr./SN2 

Reference OSSA 11 

One of the outstanding problems of 

lunar science is to determine how and 

when the lunar crust formed. One 

model is that a global magma ocean 

slowly crystallized to form the wide 

diversityof rocksthat werefound in the 

lunar highlands. Lunar granite would 

be the last rock to form in thissequence 

of differentiation. According to this 

model, the date when the initially molten 

lunar crust finished crystallizing can be 

determined from dating the granite. 

Zircons are i mportant in the geoch ronological study of lunar samples. Although 

zircons are rare and difficult to find in 

lunar samples, there are a few in the 

lunar highlands. Usually, they are found 

as individual crystals unattached to 

other minerals. A few have been found 

included in small rock clasts in the 

matrices of the breccias. 

The uranium (U) content of lunar 

zirconsrangesfrom 10to500p/m.The 

radioactive decay of uranium to two 

isotopes of lead (Pb) provides a way to 

measure the age of the zircons and of 

the rock fragments in which they are 

found. The uranium and lead isotope 

ratios in small zircons found in thin 

sections of lunarsamples are measured 

in situ using a sensitive high-massresolution ion microprobe at the 

Australian National University. The 

illustration summarizes the ages obtained in this investigation. These results 

show that zircon-containing lunar rocks 

are older than the majority of lunar 

rocks. 

+---A -I----+-A-h hrn-rinr brrm +hn LI~~G-GBGI##G#I~ 1mb11 UIT-*.IL~O iiviii .,IC. 

Tiny euhedral zircons located in small 

fragments of lunar granite are found to 

have the highest uranium content and 

can easily be dated by the ion microprobe technique. The ages of several 

granites are determined to be greater 

than 4300 Myr, which would mean that 

the original lunar magma ocean finished 

crystallizing within 200 Myr of the initial 

formation of the Moon. 

In general, lunar zircons are relatively 

homogeneous in both chemical and 

isotopic composition. However, the 

zircon in a unique clast found in a thin 

section of lunar breccia 73235 has been 

found to be unusually variable in composition. Thisclast consists of numerous 

fragments of broken zircon included in 

a calcium-rich plagioclase assemblage 

with a polygonal metamorphic texture. 

Variations in backscatter-electron intensity of the zircon clearly define 

chemically distinct regions within the 

interior as well as a unique overgrowth. 

(See figure.) These regions are found 

to be chemically distinct in trace 

amounts of uranium, yttrium (Y), and 

ytterbium (Yb). The overgrowth has 

distinctly different Th/U and YNb ratios. 

Isotopic analysis of the interior and of 

the overgrowth allow us to piece 

together the following story. Approximately 431 0 Myr ago, a relatively large 

within a plagioclase-rich rock. Sometime afterward, this zircon-plagioclase 

assemblage was fractured and recrystallized. An overgrowth of new zircon 

occurred 4180 Myr ago. Based on the 

polygonal texture of the plagioclase, 

this was a metamorphic event. Finally, 

this clast was incorporated in a melt 

sheetderived from a large impact about 

400 Myr ago. 

Until recently, it has not been possible 

to study the early history of the Moon 

because large unbrecciated samples 

were required for geochronological 

studies. The lunar soil samples, core 

tubes, and breccias contain many small 

rock fragments that can now be studied 

(XOO pm), zoned zircon crystallized by this new microscopic technique. 

I ORIGINAL PAGE IS + -mrY - 

OF POOR QUALITY I 

X - Granlte 

- Overgrowth 

Summary of ion microprobe ages (207PbPMPb ages) of lunar zircons. 

Backscatter-electron image of zircons in lunar sample 73235 showing variations in chemical 

composition and overgrowth. 

OSSA 25 
Composition of Comet Halley 

Dust Particles 

PI: Herbert A. ZooWSN3 

Reference OSSA 12 

Comets are remarkable objects. It is 

commonly believed that all of the 

several hundred comets observed to 

date originated with the formation of 

our solar system about 4.6 Gyrago and 

have been in orbit around our Sun ever 

since. No comet has ever been observed 

to arrive directly from interstellar space. 

The comets that we actually observe, 

however, are all rather recent visitors to 

the inner solar system. The dramatic 

tail or halo that alerts us to the presence 

of a comet also is evidence that the 

comet is rather rapidly disintegrating 

with time. Comets probably do not 

remain active for more than a few 

thousand years in the terrestrial region 

of the solar system. Comets, therefore, 

appear to have been stored in the cool 

outer reaches of our solar system for all 

but the last tiny fraction of their lives. 

They may have retained, in unaltered 

form, the original gas and dust grains 

from which they originally accreted. 

These grains may, additionally, be 

primordial grainsfrom the nebularcloud 

which collapsed to form our solar 

system. Comets are the most promising 

storage place for such grains, if they 

exist in our solar system. 

Until the Giotto spacecraft flyby of 

Comet Halley on March 14, 1986, and 

the flyby of the two U.S.S.R. Vega 

spacecraft the previous week, however, 

almost nothing was known about the 

chemical composition of cometary 

grains. All three spacecraft had nearly 

identical experiments onboard to 

measure the chemistries of individual 

cometary dust grains, and all three 

experiments gave excellent results. 

In the figure are shown three examples 

of mass spectra obtained on Halley 

dust particles. The peaks labeled 12 

and 16 are due to singly ionized carbon 

and oxygen ions, respectively. One 

clearly sees, in spectrum a, the three 

isotopes of magnesium - 24.25, and 

26 (the last two are not labeled) and the 

two isotopes of silver - 107 and 109. 

The latter ions are derived from the 

10%-silver-doped platinum target. One 

also sees sodium, silicon, sulfur, and 

iron in this spectrum. In spectrum b. 

only low-Z elements are seen, a not 

uncommon occurrence. Spectrum c 

depicts an impact by a pure silicate 

grain, apparently a magnesium-rich 

olivine or pyroxene. Other nearly pure 

mineral grains, such as sodium chloride 

and iron sulfide, were also observed. 

Although analysis of the Comet Halley 

dust grains and gas in the coma is only 

in the preliminary stage, much has 

already been learned. The gas-to-dust 

ratio appears to lie somewhere between 

4 and 10, the gas is mostly water (80% 

to 95% H20) with lesser amounts of 

carbon dioxide and other gases, and 

the dust grains are highly variable in 

composition. This last observation is 

very interesting as it was not known 

before flight whether the dust grains 

would vary in composition from grain 

to grain. Enigmas remain. Are the dust 

grains in their primordial state - which 

would indicate a variety of source 

regions - or have they been chemically 

processed in the comet to give the 

variety of chemistries that we observed? 

How is the gas stored? Is it as crystals 

of ice between the dust grains or does it 

reside in the pore space of fragile, 

porous dust grains? More work lies 

ahead to resolve these and other 

questions. 

Three separate mass spectra obtained with the PIA time-of-flight mass spectrometer during the 

Comet Halley flyby on March 14, 1986. The vertical scale is logarithmic, and time increases 

from right to left. Most peaks are labeled with the associated mass numbers. The figure is taken 

from Kissel et al., Nature, vol. 321, 1986, pp. 336-337. 

24 

1u 

I 

1 I 1 1 I I 1 I 1 I I I 

12 h 

1 I 1 I I I 1 I I I I I I 

28 24 

1 I I I 1 I I I 1 1 I I I 

26 OSSA 
Evolution of the Archean Mantle 

PI: Donald A. Morrison/SN4 

Reference OSSA 13 

The terrestrial planets are separated 

into core, mantle, and crustal domains. 

The compositions of these domains 

and the chronologies of their development are crucial elements in planetary 

evolution. The mantle of a planet evolves 

with time, and many different evolutionary pathsare possible. Crustal rocks 

formed by partial melting events in the 

mantle at different times provide some 

indication of the evolutionary path 

followed. 

Significant understanding of the basic 

processes involved in the generation of 

the Earth and Moon crust and mantle 

has been achieved through considera- 

?inn n!?he urznium-leprf (IJ-Ph) system 

The Pb isotopic system is very sensitive 

to differences in U/Pb ratios established 

early in Earth mantle evolution because 

of the relatively short half life of 235U 

and the consequent early and rapid 

production of 207Pb. Existing data, 

although far from complete, suggest 

that major continental blocks of the 

Earth were derived from mantle sources 

which followed different evolutionary 

paths. The Superior Province of Canada, 

for example, appears to have been 

derived from a mantle source with a 

lower U/Pb ratio than those of other 

regions. 

To test this hypothesis, scientists have 

completed Pb isotopic analyses for two 

2.7-Gyr intrusives in the Wabigoon 

subprovince of the Superior Province. 

The initial lead isotopic compositions 

are among the lowest measured fOr2.7- 

Gyr rocks of the Superior Province. 

The ratios imply a single-stage U/Pb 

ratio of 7.5, significantly less radiogenic 

than the mantle value predicted by the 

classic plumbotectonic model. The low 

U/Pb value indicated is in agreement 

with the low values for radiogenic 

strontium (Sr) and neodymium (Nd) 

obtained forthesame units. Collectively, 

thedatasuggest that the mantlesource, 

or sources, of the western Superior 

Province crustal rocks has a unique 

signature and that it is more depleted in 

radiogenic parent isotopes than is the 

mantle underlying most other continental terrains. 

A comparison between major continental blocks is shown in the figure. The 

squares represent new Superior Province data. The lead data show that the 

source region of the Superior Province 

had been depleted at least several 

hundred millionyearspriorto theonset 

of the pervasive 2.7-Gyr magmatism. 

The depletion may be primary or the 

result of earlier melting events. 

The lead data also show that preexisting crust (more than 50 Myr older 

approximately) was not involved in the 

generation of the rocks analyzed. Older 

crust (>3.0 Gyr) does occur in the 

western Superior Province, and its lack 

of involvement in later crust formation, 

either through recycling or partial 

melting, has important implications for 

the mechanism of crust-mantle interaction during the Earth's Archean period. 

Averaged initial lead ratios for South Africa, Superior Province, and Australia. 

10 

16 

14 

12 

10 

207 PUP04 Pb 

4 b.y. 

AVERAGED INITIAL LEAD RATIOS FOR: 

A SOUTH AFRICA 

SUPERIOR PROVINCE 

0 AUSTRALIA 

4.57 b.y. 206 Pb/204 Pb 

10 12 14 16 16 

OSSA 27 
Spectral Evidence for Hematite on 

Mars 

PI: Richard V. MorridSN4 

Reference OSSA 14 

0.4- 

z 0.3- H 

Y 

> 

c 

U y 0.2- 

LL W a 

The inverse problem in the interpretation 

of laboratory reflectance spectra of 

well-characterized materials is to use 

the data to infer the physicochemical 

state of remotely sensed planetary 

surfaces. It is difficult to establish 

uniqueness in such inversions because 

planetary surfaces are complex assemblages of phases and because the 

factors that influence reflectance spectra are not well enough understood. 

The reflectance spectra of Mars, obtained mainly by Earth-based telescopic 

observations, are specific examples of 

the inverse problem. 

*&-+- -pmm 

9- *. f 

I 

As shown in the first figure, the composite bright region spectrum of Mars 

is characterized by features that include 

an absorption edge (400 to 750 nm) 

through the visible wavelength region 

that is responsible for the characteristic 

reddish color of Mars and a shallow 

absorption band centered near870 nm. 

Both of these spectral features are 

generally attributed to ferric iron. In 

addition, the relatively featureless nature 

of the absorption edge and the shallow 

nature of the band have suggested to 

some investigators that the ferriccontaining phases are poorlycrystalline, 

implying that specific mineralogical 

identifications are not possible. The 

870-nm band minimum does imply that 

the ferric oxide is hematite (FeZO3). 

However, the absorption edge for hematite, as represented by crystalline 

powders having mean particlediameters 

larger than approximately 100 nm, is 

excessively steep (560 to 750 nm) to be 

consistent with the martian data. The 

problem with this line of reasoning is 

that it presumes that theaforementioned 

hematitespectra are in fact representative for hematite over all particle 

diameters. 

0.41 

During the past year, scientists at the 

Johnson Space Center have studied 

the spectral properties of extremely 

fine-grained (less than approximately 

50 nm) hematite particles and found 

that their spectral properties differ 

markedly from those of their coarsegrained equivalents. The hematite particles were produced by impregnating 

silica gel that has 6-nm-diameter pores 

28 OSSA 

1 

with a ferric nitrate solution and then 

heating the impregnated gel at 550' C. 

Representative spectra for s mples 

containing 0 to 24 wt% Fez>, are 

illustrated. Except for the absorptions 

near1400and 1900nmthatareinherent 

to the silica gel and not due to ferric 

iron, the trend is for the absorption 

edge to move into the visible region 

and for the absorption at 870 nm to 

deepen and change in shape from 

inflection, to plateau, to minimum. The 

spectrum of the most iron-rich sample 

is essentially the same as that typically 

found for pure and relatively coarse 

hematite powders. Presumably, the 

inflection and plateau result because 

the hematite particles in those samples 

aresosmall thattheydonot haveafully 

z 0.3- H 

Y 

> 

c U 

LL W

y 0.2- 

a 

Mars bright region 

spectrum. 

0.1- 

- 

developed and ordered hematite structure over most of their volumes. 

The martian spectral featurescaused 

by ferric iron can now be accounted for 

solely, but perhaps not uniquely, by 

hematite present in a range of particle 

diameters. This conclusion can beseen 

in the third figure, which is the spectrum 

of a mechanical mixture containing 5% 

of the silica gel with 24 wt% Fez03 and 

the balance containing the gel with 0.5 

wt% FeZO3. Like the martian spectra, 

this spectrum has a shallow band 

minimum at 870 nm together with an 

absorption edge extending from 400 to 

750 nm. Thus, the identification of the 

phase hematite as a mineral on the 

martian surface is entirely consistent 

with the spectral data. 

d 

Representative spectra for various hematite concentrations. 

0.6 

0.2 

0.2 0.6 1.0 1.4 1.8 

WAVELENGTH (MICRONS) 

Spectrum of mechanical mixture of silica 

gel with hematite. 

y 0.4 

LL W a 

0.2 

0.2 0.6 1.0 1.4 1.8 

WAVELENGTH (MICRONS) 

0.6 1.0 1.4 1.8 

WAVELENGTH (MICRONS) 
ORIGINAL PAGE IS 

OF POOR QUALITY 

Monitoring the Earth With Space 

Shuttle Photographs 

PI: Charles A. WoodfSN4 

Reference OSSA 15 

From space, the Earth is seen to be an 

integrated body, a continuous mosaic 

of land, water, and clouds that blend 

without the artificial boundaries that 

appear on most maps. To understand 

and to utilize the Earth wisely, we must 

consider it as an entity. Volcanic eruptions anywhere on theglobe need to be 

monitored to assess the climatic and 

geodynamic potential on a continental 

scale. Deforestation in the Amazon River 

basin or along the Congo River affects 

chemical inputs into the atmosphere 

and the biological diversity of the largest 

remaining natural component ot the 

biosphere on Earth. Likewise, geologic 

structures that control earthquakes or 

mineral distribution do not stop at 

national boundaries. Global monitoring 

of the Earth is at hand. 

Fortunately, a remarkable photographic 

documentation of thestateof the Earth 

has been accumulating during the last 

25 yr. This long record has accrued 

through astronaut photography of the 

Earth. These photographs differ from 

satellite images in that each of the 

nearly 70 000 pictures was taken 

because a scientifically trained astronaut recognized a feature of interest on 

land, in theoceans, or in theatmosphere. 

The pictures taken during the first 24 

Space Shuttle missions are especially 

valuable for studying the global systems 

of the Earth because they are now 

completely cataloged and thus can be 

more easily acquired and used than 

could previous Earth photography. The 

cataloging of the 37 000 Space Shuttle 

photographs, as well as geoscientific 

training of theSpaceShuttleastronauts, 

was coordinated by the Johnson Space 

Center (JSC). Currently, JSC scientists 

are developing automated techniques 

to improveefficiency in selecting targets 

for future photography by Space Shuttle 

astronauts. Additionally, information on 

Earth photographs takin by Gemini, 

Apollo, and Skylab astronauts is being 

entered into the computerized data 

base to allow these early pictures to be 

retrieved easily for crew-traihing ‘and 

scientific analysis. 

. 

Photographs of the Earth from space 

provide scientists with broad synoptic 

views that encourage the investigation 

of interrelationships rather than of 

details. A single Space Shuttle photograph can depict the geology of a 

mountain range or a fault belt in its 

entirety, rather than in the piecemeal 

fashion required for aerial photographs. 

Photographs taken by astronautsalso 

document new discoveries of features 

that the human observer realizes are 

important. Thus, photographs by Gemini astronauts demonstrated the existence of large-scale circulatory eddies 

in the oceansthat were hard to recognize 

from the limited perspective of shipboard data. Additionally, astronaut 

photographs reveal details of hurricanes 

and other weather phenomena that are 

invisible to weather satellites, but 

excessively large or inaccessible for 

study from the ground or from airplanes. 

JSC is working with other government 

organizations to make this national 

legacy of space photographs more 

easily available to researchers. The 

Earth Resources Observation Systems 

Data Center in Sioux Falls, South 

Dakota, uses a computerized version of 

catalogs of Space Shuttle pictures to 

inform customers of the Earth regions 

that have been photographed. The Air 

and Space Museum of the Smithsonian 

Institution is currently completing a 

single videodisk of all 37 000 Space 

Shuttle photographs to be sold to the 

public at a nominal price. 

Space Shuttle astronauts take advantage of an orbital vantage point to detect and document 

unexpected events such as this volcanic eruption in Indonesia. Crewmembers of the STS-8 

Space Shuttle mission photographed an eruption plume from Ili Boleng volcano on the island 

of Adonara (40 km long by 20 km wide), but the eruption was not otherwise recorded. 

OSSA 29 
Satellite-Derived Leaf Area Index 

and Vegetation Maps as Input to 

Global Carbon Cycle Models 

PI: Gautam Badhwar/SN3 

Reference OSSA 16 

The role of natural and anthropogenically altered land surface features in 

physical, chemical, and biological processes on a global scale is of concern to 

an expanding world population and is 

exempiiiiea by ine carbon dioxide 

climate controversy. The reason for 

this concern lies in the very complex 

feedback processesat work in the Earth 

land/atmosphere/ocean system. This 

controversy has underscored the need 

for improved understanding of the 

atmosphere, of oceans, of biota, and of 

their interactions. The critical function 

of terrestrial vegetation as a transport 

medium for the flux of important constituents, such as carbon, has been 

well recognized and can be seen in the 

annual cycles of theatmosphericcarbon 

dioxide measurements. These observations clearly indicate that vegetation 

actively participates in the storage and 

cycling of carbon and interactsdirectly 

with the atmosphere. The current estimatesof the total land area, the biomass, 

and the productivity of vegetation are 

known to only a factor of 2 at continental 

scale, and to a factor of as much as 10 

at plot level. Satellite-carried sensors 

provide an objective and practical 

method of vegetation mapping. 

In 1983and 1984, acombined helicopter/ 

ai rcrafthatell ite-based experi ment was 

performed in the Superior National 

Forest to map types of vegetation and 

to determine the leaf area index of 

forest canopies. This hierarchical 

approach is unique in that it provided, 

for the first time, a calibrated means of 

going from plot level to a continental 

scale and knowing the.information loss 

that occurs on the way. 

Analyses of both the helicopter and the 

aircraft data have shown that the spectral data can allow a determination of 

the leaf area index tof20Y0at plot level. 

With this calibration, the leaf area index 

maps over the region from Landsat 

multispectral scanner data in 1979 and 

1982 show definite changes in vegetation and the leaf area of various canopies. (See.figure.) These results suggest that satellites can provide key 

These studies are critical if capabilities 

to monitor the vegetative resources of 

the Eaflh and to understand the lifesustaining processes of the Earth are to 

be developed. 

inpLI! !e g!eba! carbm cyclg mGde!s. 

ORIGINAL PAGE 13 

OF POOR QUAhsrr 

Percentage change in the leaf area index from 1979 to 1982 for aspen canopies near Ely, 

Minnesota. 

I 30 OSSA 
Radiation Environment Models 

and the Atmospheric Cutoff 

PI: Andre1 KonradVSN3 

Reference OSSA 17 

Alva C. Hardy/SNB 

To predict the Space Station radiation 

environment expected after the turn of 

the century, scientists at the Johnson 

Space Center (JSC) used the radiation 

environment models AP-8 MIN and AP8 MAX for protons with energies above 

30 MeV and used the magnetic field 

model IGRF 1975. In the process, 

scientists encountered an almost exponential increaseof the radiation intensity 

with time in the South Atlantic Anomaly 

(SAA) region. Such an unexpected and 

rather unrealistic result forced a review 

of the calculation methodology and the 

structuring of the models. 

. 

The figure shows flux-altitude profiles 

for the years 1965, 1995, and 2025. 

These profiles were calculated at an 

altitude of 500 km at the center of the 

trapped-radiation SAA. Not only does 

the flux apparently increase with time, 

it also increases disproportionately at 

low altitudesand even below the surface 

of the Earth. If real, such an increase 

would have significant implications. 

Interpretation of this phenomenon 

rests simply on the fact that the particle 

fluxcontained in the model asafunction 

of magnetic field intensity B and beam 

path length L has built into it, also as a 

function of 8 and L, the atmospheric 

cutoff of 1964 for solar minimum and 

1970forsolar maximum. In otherwords, 

within experimental uncertainties, AP8 MIN and AP-8 MAX represent for 

those two epochs the average particle 

distribution as it existed deep within 

the magnetosphere and within the 

atmospheric cutoff region. 

As a result of the well-documented 

temporal decrease in the magnitude of 

the geomagnetic dipole moment, locations of a fixed magnetic field intensity 

are found at progressively closer distances to the Earth. Consequently, flux 

values associated with fixed B values 

move to lower altitudes, and the models 

artificially move the atmospheric cutoff 

to loweraltitudes. Since the flux gradient 

within the geomagnetic cutoff is very 

steep, the order of magnitude of the flux 

increases within a short time period, and 

even subterranean fluxes are predicted. 

Obviously, this flux is an artifact of the 

model and has no physical significance. 

Pending the development of more 

sophisticated models that take into 

account the independence of the 

atmospheric cutoff from the magnetic 

field, the scientists at JSC recommend 

two approaches that will produce 

reasonable results. 

1. AP-8 and AP-8 MIN and MAX 

models should be used in conjunction 

with appropriate magnetic field models 

forepochs 1964and 1970, respectively, 

and no attempt should be made to 

project the radiation environment into 

the future. Although this approach will 

produce reasonable predictions of 

exposure doses when averaged over all 

longitudes, it may give poor results for 

individual orbits because the westward 

drift of the magnetic field is not 

accounted for. 

2. An alternate and operationally more 

accurate approach was suggested by 

Vette and Sawyer. This approach 

involves expressing the particle flux 

not as a function of B and L but rather 

as a function of BIB, and L, where Bo is 

the minimum value of the magnetic 

field on an L shell. Both L and BIB are 

nearly independent of the value o? the 

magnetic dipole; thus, a particle distribution tied to these parameters will 

show little change with time. The 

trapped-radiation environment models 

currently available from the National 

Space Science Data Center incorporate 

these changes. 

Projections of South Atlantic Anomaly flux as a function of altitude as determined using 

magnetic field model IGRF 1975. 

1000 

900 

800 

700 

5 600 

500 

3 

t 400 

4: 300 

200 

100 

0 

-100 

- 

3 

1 10 100 1000 10000 

FLUX (cm* seer1 

OSSA 31 
Solar Maximum Mission Satellite 

and Space Shuttle Orbiter Impact 

Craters 

PI: David S. McKay/SN4 

Reference OSSA 18 

The size distribution, flux, composition, 

and source of orbital debris in the size 

range of about 1 mm and smaller is not 

well understood, although preliminary 

data indicate that such material may be 

an important component of the entire 

c:bi!a! debris ccmplex. Submillimztz: 

debris may have significant effect on 

critical spacecraft components including lenses, windows, mirrors, sensors, 

critical electronics, and other hardware 

which must be directly exposed to the 

space environment. To identify material 

in this size range using optical and 

radar detection is difficult. However, a 

significant amount of this material is 

known to have impacted spacecraft 

surfaces, and some of these surfaces 

have been analyzed. Essentially, all 

returned spacecraft hardware which 

has had any significant exposure to 

space contains small impacts from 

orbital debris as well as from tiny 

micrometeorites. 

In most cases, the shape and morphology of the impact feature provides 

some information on the velocity of the 

projectile. Significantly, most impact 

features contain some residue from the 

impacting projectile, and it can be 

analyzed using sophisticated electron 

microscope techniques. 

Detailed analyses of impactson these 

returned surfaces should provide hard 

data on the composition, the flux, the 

velocity distribution, and, ultimately, 

the source of submillimeter orbital 

debris.An additional important implication of analyzing the submillimeter 

debris population is that this population 

will provide a flux curve that can be 

extrapolated to larger sizes and compared to optical and radar data. This 

comparison will provide independent 

information on the entire orbital debris 

corn plex. 

Scientists at the Johnson Space Center 

(JSC) have analyzed more than 1 m2 of 

returned thermal blanket from thesolar 

Maximum Mission (Solax Max) satellite, 

which had spent more than 4 yr in 

space before retrieval. Returned thermal 

insulation blanket material (Kapton and 

Mylar) and louvers (aluminum) contain 

morethan 1000 impact holesand craters 

larger than 40pm in an area of approximately 1 m2. The largest hole is about 1 

mm. The JSC scientists have cataloged 

these featuresand made them available 

to interested investigators throughout 

the country for scientific study. Approximately one-third of these impacts were 

made by micrometeorites, but at least 

one-third and possibly two-thirds were 

made by orbital debris in the submillimeter size range. A significant component of the impacting projectiles 

appears to be composed of paint 

pigments, apparently released into orbit 

from degraded spacecraft paints. Other 

materials include aluminum-rich residues derived from solid-propellant 

rocket exhausts, from spacecraft fragmentation, or from both sources and a 

variety of materials including substances 

of low atomic number (possibly plastics) 

which have not yet been associated 

with specific spacecraft components. 

In a related study of Space Shuttle tiles 

from the 0 r b i t er A tlantis i m med i atel y 

after her maiden voyage, researchers 

found one high-velocity impact crater 

likely formed by orbital debris. This 

crater, which was clearly caused by a 

hypervelocity impact, created a melted 

pit and formed a surrounding spall 

zone. Analysis of residue in the pit area 

revealed traces of aluminum, iron, and 

chromium. Because aluminum and 

chromium are not abundant elements 

in most micrometeorites, the researchers believe that the projectile was most 

likely an orbital particle. This impact 

did not do any significant damage 

because the crater (spall) diameterwas 

less than 1 mm, but it does suggest the 

possibility of damage to future Orbiter 

flights and to the Space Station from 

larger objects or from the growing 

orbital debris complex. 

Spray pattern on an aluminum panel immediately beneath the Solar 

Max satellite impact hole shown in previous photograph. This spray 

pattern contains melted and splashed aluminum from the outer 

aluminum layer as well as residue from the projectile. Note the change 

in scale of the photograph. This spray pattern is about 4 times larger 

than the overlying hole (SEM photograph). 

Impact hole in a Solar Max satellite aluminum louver returned from 

space (scanning electron microscope (SEM) photograph). 

1 32 OSSA 
Impact Experiments in ReducedGravity Environments 

PI: Mark J. Cintala/SN12 

Reference OSSA 19 

Impact cratering occurs on every solid 

object in the solar system; no other 

geologic process has operated as continuously or as inexorably. In efforts to 

unravel the physics behind the process, 

planetary scientists have determined 

that the gravitational acceleration is a 

principal factor in determining the sizes 

and possibly the shapes of craters. 

Theoretical investigations predict that, 

under otherwise constant impact conditions, a crater would be larger if the 

strength of the gravity field in which it 

formed were decreased. At the same 

time, the duration of crater growth 

would increase. It is important to 

understand the relationship between 

crater dimensions and the g-level, for 

example, if one were to compare impact 

craters on different planets. Another 

important factor influenced by gravity 

is the time required for agiven crater to 

grow; this time is directly related to 

ejection velocities. The removal of 

potential meteorites from their parent 

bodies is intimately tied to this gravityscaling effect. 

Friedrich HordSN4 

Most solid objects in the solar system 

have gravitational accelerations substantially lowerthan that of Earth. Thus, 

determining the effects of gravity on 

various aspects of the cratering process 

would require experimentation in different gravity fields. Some aspects can 

be and have been examined at high glevels through the use of centrifuges; 

study of other phenomena, however, 

require low g-levels. TheSpaceShuttle 

Orbiters and the Space Station could, 

in principle, serveas platformson which 

low-gravity experimentation could be 

conducted. With the potential use of 

these vehicles in mind, researchers are 

conducting a series of investigations to 

provide engineering and scientific data 

for use in designing the facilities to be 

flown and the experimental program 

that might be pursued. 

The NASA KC-135 aircraft equipped 

to fly reduced-gravity parabolas can 

support low-g accelerations for more 

than 45 sec at a time, depending on the 

desired g-level. It also can support 

instruments sufficiently large that useful 

impact experiments can be performed 

during flight. An impact facility for 

flight on the KC-135 has been constructed. It consists of an impact chamber, cameras, lighting, a modified airdriven pellet gun, and a microcomputer 

for sequencing and collecting acceleration and cabin pressure data. Some 

preliminary experimentation has been 

conducted during parabolic flight, 

resulting in 27 shots to date at g-levels 

ranging from 0.089 to 0.539. 

These experiments were only of a 

precursor nature and were intended to 

test procedures, diagnostic equipment, 

and theexperimental apparatus. Impact 

velocities were limited to 0.1 km/sec on 

the KC-135, ascompared to the typical 

lunar impact velocity of 15 km/sec; 

these low velocities were dictated by 

experiments, not by technological limitations. Nevertheless, some important 

conclusions can already be made on 

safety i;unsi&iaiions in these 

the basis of these early results: (1) 

Impact cratering experimentation in lowgravity environments is not only possible 

but practical. In no case were insurmountable difficulties encountered, and 

the data quality is high. (2) When all 

other conditions were kept as constant 

as possible, crater sizes did indeed 

increase as the g-level dropped. The 

resultsagree well with theoretical predictions. (3) The time taken for craters to 

growasafunctionof theg-level had the 

correct qualitative trend - i.e., it takes 

craters longer to form in weaker gravity 

fields - but displayed a considerable 

quantitative divergence from the predicted relationship. This disparity could 

be caused by poor statistics from the 

small number of reduced-gravity experiments currently available, or it could 

theory and reality. More experiments 

are being planned to evaluate the two 

possibilities. 

ispiesen: real diff~~~~ce be!~/een 

ORIGINAL PAGE IS 

OF POOR QUALITY 

A crater being formed in a sand target during an experiment at 0.4g. Sequencing and digital data 

recording are performed with the computer. 

I 

4 

"a 

~~ 

OSSA 33 
Photographic and Television 

Enhancement in Support of the 

STS 51-L Investigation 

PI: David E. PittdSN3 

Reference OSSA 20 

Photographic and television (TV) data 

formed a primary source of information 

on the cause and related sequence of 

events of the Space Transportation 

System (STS) 51-Laccident. The visual 

analysis subteam was formed as an ad 

hcc c:ganiza:ion to pe:fo:m :he photographic and TV data analysis at the 

Johnson Space Center (JSC).Accurate 

image interpretation required a knowledge of the objects and of phenomena 

contained in the images, as well as 

knowledge about image formation, 

processing techniques, and enhancing 

techniques. 

To optimize the image information 

extraction process, teams of image 

interpreters and engineers were formed 

to analyze all the available data. Analysis 

and photoenhancement activities were 

performed at JSC and assigned to 

nationally recognized government and 

industrial laboratories to increase 

thoroughness and objectivity.The mission timeline was broken into eight 

parts to ensure thoroughness and to 

describe the significant events: (1) 

characterizesmoke at launch, (2) search 

for continued smoke, (3) determine 

time and location of initial flare, (4) 

identify first evidence of hydrogen leak, 

(5) characterize right solid rocket 

booster (SRB) motion relative to stack, 

(6) characterize vehicle breakup dynamics, (7) characterize postexplosion 

condition of SRB's, and (8) examine 

underwater and salvage photography 

for critical evidence. 

Much of the engineering hypothesis 

testing required a determination of the 

timeand the location of anevent.Timing 

was determined by using an lnterrange 

Instrumentation Group (I R I G)-B code 

placed on the film products during 

exposure. An exact location was determined by superimposing hidden-line 

and wire-frame computer-aided drawing/camera (CAD/CAM) drawings upon 

enhanced digitized images. The CAD/ 

CAM systems incorporated the location 

of the camera and the best estimated 

trajectory from STS 51-L in order to 

produce a vector image of the STS 51-L 

stack that represented the view from 

that camera position. This vector image 

was read into the JSC image processing 

system from digital tape and was 

mathematically registered to the digitized and enhanced three-color photograph by using a tiepoint registration 

routine that preserved axis isotropy by 

allowing changes only to scale, translation, and rotation. Using this approach 

with several camera positions (viewing 

angles), researchers determined the 

location of the burnthrough in the right 

SRB to be near the aft attachment ring 

atanangleof315" f10";therecovered 

debris showed that the burnthrough 

extended from 296" to 318". 

Numerous other studies involved the 

manipulation of CAD/CAM drawings 

with the image analysis system. Among 

these were the mnlje~en? nf ?he right 

SRB relative to the stack just before the 

explosion, the dynamics of the SRB's 

after the explosion, and the location of 

the smoke puff at launch. Conclusions 

reached in all of these studies at JSC 

were corroborated by other national 

laboratories. Additional information can 

be obtained from STS 51-L JSC Visual 

Data Analysis Sub-Team Report, 

JSC-22175. volumes I and II. 

Digitized photograph from camera E207, frame 42, on which a computer-aided hidden-line 

drawing is superimposed, showing the location of the flame between the right SRB and the 

external tank, near the aft attachment ring. 

34 OSSA 
Aeronautics and 

Space Technology 

Summary 

. 
Office of 

Aeronautics and 

Space Technology 

Introduction 

The Lyndon B. Johnson Space Center 

(JSC), through the research and technology (R&T) programs funded by the 

Office of Aeronautics and SpaceTechnology (OAST), has continued to provide sound analytical evaluations for a 

varieiy of iechnoiogicai issues. During 

fiscal year (FY) 1986, JSC provided 

support fora number of activities, which 

were primarilysponsored by the Space 

R&T Base Program (UPN 506) and the 

Systems Technology Program (UPN 

549). In addition, the Aeronautics R&T 

Base Program (UPN 505) provided 

complementary funding to the Space 

R&T Base Program for continued support in advanced information systems 

technologies. 

Generally, the R&T activities are 

centered around projects developing 

technological readiness in areas of 

advanced life support systems (namely, 

thermal management), composite 

materials, communication systems/ 

telemetry data, human factors technology (as it relates to man/machine systems 

interface), space flight vehicle control 

systems, systems analysis (regarding 

proposed lunar/Mars manned missions), 

and the development of a closed-loop 

life support system. Likewise, JSC continues to provide the overall integration 

management and program planning in 

support of the National Space Transportation System (NSTS) Orbiter Experiments (OEX) Program. 

Space and Energy Conversion 

The JSC participated in two projects 

under thesponsorship of the Spaceand 

Energy Conversion R&T Program (formerly Thermal and Power). These programs provide the thermal management 

of large spacecraft systems and of crew 

support and air revitalization processes. 

The objective of the thermal management 

activity is to develop the technology 

First integrated two-phase thermal management system thermal vacuum test in JSC chamber A. 

for a system with multihundred-kilowatt 

capacity that can operate much like a 

public utility and thus can easily be 

expanded and adapted to accommodate 

increasing needs. Key technologiesare 

the development of a two-phase, 

constant-temperature heat transport 

bus with contact heat exchangers and 

modular space-constructible heat pipe 

radiators. A prototype that has undergone extensive testing at the JSC 

vacuum chamber demonstrated succesfully the viability of the two-phase 

system management concept. 

Likewise, efforts have been expended 

in air revitalization techniques to 

PRl!!ZFIT,WG PAGE BLANK, NOT FILMED 

accomplish oxygen reclamation by 

employing electrochemical carbon 

dioxide removal technology. Electrolysis of carbon dioxide is a desired goal 

to recover the metabolic oxygen in 

future long-duration space missions. 

Research activities have centered 

around the various elements of an 

electrochemical depolarized carbon 

dioxide cell technology to increase 

process efficiency and flexibility. Currently, three different cell types are 

being fabricated and will subsequently 

be parametrically and life tested. The 

JSC is developing the thermal management and the air revitalization process 

OAST 37 
technologiesas part of thespacestation 

Program. 

Materials and Structure 

Composite materials are being used for 

space applications on an increasing 

scale. In orbit, these materials are 

exposed to potentially damaging hypervelocity impacts from meteoroids and 

orbital debris. To evaluate the various 

composite materials, researchers used 

experimental data from the light-gas 

gun at the JSC Orbital Debris Impact 

Laboratory to develop math models 

capable of predicting the hypervelocity 

impact crater growth. Verification and 

refinement of the model predictions 

have been accomplished incorporating 

a new custom-designed, ultra-highspeed, rotating mirror framing camera. 

Further evaluations will be accomplished using more massive, spherical 

projectiles and incorporating the camera 

diagnostic capability. 

Space Data and Communication 

In 1983, JSC established a Beta Test 

Program forthe Adacomputer language. 

The communication and tracking systems technologies have been closely 

coordinated with the BetaTest Program 

to ensure their readiness for the upcoming SpaceStation Program. Efforts 

have been expended in analyzing Adarelated issues such as the capability of 

mixing Ada with other languages, the 

use of Ada in real-time applications, 

the Ada run-time environment, and the 

software tool set required for effective 

Ada software development and maintenance. As a result of these efforts, 

Ada has been selected for the Space 

Station Program. 

Information Science 

The primary language used with the 

Space Shuttle onboard systems is 

HALE. The HAL6 Language Control 

Board objective is to provide language 

support for the standard HALE compiler, tools, and documentation. A 

number of objectives are currently in 

progress and include developing an 

interactive debugger capability, developing an interactive interface between 

maintainers and complier, archiving 

historical files and documentation, and 

evaluating the possibility of converting 

the BYRON language to Ada. 

ORIGINAL PAGE IS 

OF POOR QUALITY 

Human Factors 

Human factors research is focused on 

the development of technologies that 

will lead to increased efficiency of 

rnanlrnachine interaction and thus 

increase man's effectiveness in space. 

A major part of this effort is in developing methods and techniques to ensure 

proper design integration of humans 

with various machine systems. Techniques for modeling human movement 

and strength capability are being developed for use in Space Station design. 

A second area of research is the 

concern with multiple aspects of communication through crew station display 

and control consoles using various 

factors such as graphic formats, color 

coding, interactive display techniques, 

etc. The objective is to develop the use 

of graphic illustrations and diagrams in 

manhachine interfaces that will aid 

the controller in managing space subsystem elements. 

Space Flight 

The OEX Program is JSC's major 

activity in the STS R&T. The program 

was initiated in order to use the Space 

Shuttle as a flight research vehicle for 

acquiring data in thevarious technology 

disciplines that augment the space 

vehicle design R&T base. The JSC 

principal functions are to provide overall 

management and planning support to 

OAST, to accompl ish experi mentl 

Orbiter compatibility assessments, and 

to manage the physical integration of 

theexperiments into thevehicle. Several 

OEX experiments have been flown 

aboard thespaceshuttle. In 1986,four 

major experiments were flown: the 

Shuttle Infrared Leeside Temperature 

Sensing (SILTS) Experiment, theshuttle 

Entry Air DataSystem (SEADS) Experiment, the Shuttle Upper Atmosphere 

Mass Spectrometer (SUMS) Experiment, and the Advanced Autopilot 

Experiment (AAPE). 

Space Shuttle Columbla in preparation for flight STS 614. 
The SILTS experiment, sponsored 

by the Langley Research Center (LaRC), 

is installed on top of a vertical stabilizer 

in a pod capped at the leading edge by 

a hemispherical dome. Within thisdome 

is an infrared scanner that views the 

upperfuselageand the leftwing through 

two silicon windows. High-resolution 

infrared imagery is obtained during 

entry and is the first data obtained for 

an entry vehicle under flight conditions. 

The information will be used to increase 

understanding of leeside aeroheating 

phenomena with applications in enabling less conservative thermal protection 

system design. The SILTS experiment 

was flown on STS mission 61-C on 

January 12 through 18, 1986, aboard 

the Space Shuttle Orbiter Columbia. 

Despite several problems on the first 6ii-m nnn rr6 ... inn Qn lllylll, dW" 0s- "I ..ally ,#,,uyul, Ull" "V 

sec of fuselage imagery were obtained, 

and the data will be forthcoming in a 

report to be produced by LaRC. Suitable 

corrections of anomalies are underway 

and will be reported in appropriate 

forums. 

The SUMS experiment obtains measurements of freestream atmospheric 

density during entry in the hypersonic, 

rarefied-flow regime. These measurements, combined with acceleration 

measurements from the companion 

experiment High-Resolution Accelerometer Package (HiRAP), allow the 

calculation of Orbiter aerodynamic 

coefficients in a flow regime previously 

inaccessible to experimental techniques. The SUMS also measures equilibrium gas composition at the inlet 

port and makes the experiment a pathfinder for future mass spectrometer 

applications in studying aerothermodynamic properties of the transition 

flowfield. With successive flights, the 

resultant data base will aid in development of analysis techniques and laboratory facilities for prediction of winged 

entry vehicle performance in hypersonic, rarefied flow. Also sponsored by 

LaRC, the major portion of the SUMS 

hardware was derived from a flight 

spareunitfrom theViking Project upper 

atmosphere massspectrometer (UAMS) 

system. It measures gases with mass 

numbers ranging from 1 through 50 

(including hydrogen at the low end and 

carbon dioxide at the high end). 

In ordertoaccomplish accurate flight 

aerodynamic research, precise knowledge of vehicle attitude and state is 

. 

. 

required. These data, commonly referred to as air data, include vehicle angle 

of attack, angle of sideslip, free stream 

dynamic pressure, Mach number, total 

pressure, etc. An evaluation of the 

Orbiter baseline air data system indicated that flight air data would not be 

available for speeds greater than approximately Mach 3.5 and that the accuracy 

of theavailableairdata from that system 

would not satisfy aerodynamic research 

requirements. The SEADS was therefore 

developed under the OEX Program to 

make the measurements required for 

precisely determining the air data across 

the Orbiter's atmospheric flight speed 

range (i.e., hypersonic, supersonic, transonic, and subsonic Mach numbers) or 

from lift-off to 280 000 ft during ascent 

andfrom280000ft to touchdown during 

e!??ry. 

The key to incorporation of the SEADS 

into the Space Shuttle Orbiter was the 

development of a technique for penetrating the Orbiter's reinforced carboncarbon (RCC) nose cap to obtain the 

required pressure measurements. The 

SEADS nose cap penetration assembly 

evolved as a result of extensive design, 

fabrication, and test programs that 

evaluated h igh-temperatu re (greater 

than 2600" F) materials and configuration concepts. The coated columbium 

penetration assembly selected was then 

fabricated for installation in a specially 

modified baseline geometry nose cap. 

The SEADS nose cap contains an array 

Configuration of SEADS in the Orbiter Columbia. 

of 14 penetration assemblies, associated 

coated columbium pressure tubing, 

support structure, dual pressure transducers, and system monitoring instrumentation. Data from the SEADS pressure transducers are transmitted to the 

support system for OEX (SSO) and 

stored on the OEX recorderfor postflight 

data analysis. 

The SEADS was flown for the first 

time on Columbia, during STS 61-C on 

January 12 to 18, 1986. The SEADS 

data were recorded on the OEX recorder 

as designed. Data review indicates that 

all transducers remained operational 

and provided viable data. Postlanding 

inspection of the SEADS RCC nosecap 

and columbium ports revealed them to 

be in excellent condition. Visual inspection of the nose cone showed interesting 

f!nw pa??erns armnd ?he SE.A.!X ports. 

Pressure testing of theSEADS pressure 

ports and tubes to verify structural 

integrity of the system proved that the 

system was tighter than it was before 

flight, as was expected. An estimated 

temperature of 2400' F was sustained 

with no evidence of port catalytic overtemperature. SEADS is ready for its 

second flight. 

System Analysis 

The JSC was invited to participate in 

the System Analysis R&T Program for 

involving activities that are beyond the 

current Space Station level of activities. 

OAST 39 
Initial efforts resulted in a review of the 

technologies that will requireenhancement to support advanced programs. 

The following four topics were then 

selected for additional development: 

1. In-flight training for a manned 

2. The use of lunar materials for 

3. Food production on lunar and 

4. In situ resources utilization 

Mars mission 

construction on the Lunar surface 

martian surfaces 

Activities have already begun in these 

areas; however, results from these 

efforts are not expected to be documented until FY 1987. 

Systems Technology 

The current approach for the control of 

subsystems in manned spacecraft is 

highly labor intensive for the flight 

crew and for ground support personnel. 

A permanently manned Space Station 

will requirea highdegreeofautomation 

for the control of its systems and 

subsystems to reduce significantly the 

demand for monitoring the control. 

Efficiently organized local and archival 

data storage and the rapid retrieval and 

display of subsystem status will be 

required to maintain operations across 

thevarious subsystems. A program has 

been completed that demonstrates the 

technology now available to allow 

generic automation techniques to be 

applied in controlling spacecraft subsystems. 

Conceptual lunar base operations. 
Aeronautics and 

Space Technology 

Significant Tasks 
Two-Phase Thermal Management 

System Component Development 

TM: Richard C. Parish/EC2 

Reference OAST 1 

The use of liquid and vapor phases of a 

thermal control working fluid forspacecraft thermal management has been 

studied by various NASA centers for 

several years. Recently, Space Station 

designers have baselined two-phase 

systems for heat acquisition and transport aboard the Space Station vehicle 

and associated free-flying platforms 

because of the obvious benefits these 

systems exhibit in reduced pumping 

power, system isothermality, and heat 

load flexibility. There are, however, 

uncertainties in the design process 

because of the limited amount of 

in!orma?inn available on liauid/vapor 

flow and heat transfer characteristics 

in a reduced-gravity environment. 

To enhance the understanding of 

fluid behavior in a two-phase thermal 

management system (TPTMS) in a 

micro-g environment, the Johnson 

Space Center (JSC) initiated an effort 

to create a test stand that is capable of 

being flown aboard the JSC KC-135 

aircraft equipped to fly reduced-gravity 

parabolas and that is also suitable for 

Two-phase thermal management test stand. 

ground testing in JSC laboratory facilities. This test stand, depicted in the 

figure, will include components of a 

candidateTPTMS and will enable measurement of pressure drop, measurement of component thermal characteristics, and visualization (Le., high-speed 

filming) and measurement of liquid/ 

vapor flow phenomena. The test stand 

will include the basic components 

required of a two-phase transport loop 

such as evaporator, condenser, pump, 

accumulator, and pressure control valve. 

The pump being used isadevelopmental 

pitot, phase-separation pump known 

as a rotary fluid management device. 

This type of pump handles varying 

ratios of liquidhapor mixtures, separating the liquid from the vapor, returning 

liquid to the evaporator for heat load 

acquisition, and delivering vaporto the 

condenser for heat load rejection. Such 

a pump will allow the use of flowthrough evaporators and will eliminate 

the need foractive control of the liquid 

supply. The liquid/vapor mixture that 

exits the evaporator in the wet vapor 

return line will be the focus of attention 

during ground and reduced-gravity 

testing to assess various two-phase 

fluid flow phenomena. 

11 ROTARY FLUID 11 

High-speed filming and highresolution pressure drop measurements 

will be accomplished in a 17-ft-long 

transparent line section to evaluate 

normal versus reduced-gravity flow 

characteristics in the transport lines. 

Condensation of the thermal working 

fluid (Refrigerant-114) will also be 

observed, filmed, and measured in an 

acrylic-covered condenser section. The 

initial flight of the TPTMS test stand 

wasscheduledfor December 1986.The 

test stand is intended to be available 

for subsequent flights aboard the KC135 to allow testing of alternate component designs and to enable further 

data generation and evaluation. 

As a result of the comparative testing 

between the laboratory and reducedgravity aircraft environments, significant 

intormation shouia be extracted concerning the operation of the TPTMS in 

an Earth-orbit environment. Because 

only limited data exist regarding the 

effects of reduced gravity on liquid/ 

vapor flow regimes, this experiment 

will improve the data base significantly 

and will provide confidence to the 

aerospace community on the utility of 

TPTMS's for future spacecraft. 

Rotary Fluid Management 

Device (RFMD) - 

THFRMAL 

OEMISTER BARRIER 

STATIONARY / HERMFT CALLVSFALtD 

PITOT / SIIPPORTHOUSlNG \ 5TATIOVAUI 

PUMP 

NO 2 

LxMr STATiOlyrRv PITOT PiTor PUMP 

NO 3 

PRECEDING PAGE BLANK, NOT FWE13 

OAST 43 
Thermal Management for OnOrbit Energy Systems 

TM: J. Gary Rankin/EC2 

Reference OAST 2 

Manned and unmanned space platforms 

projected for the 1990's and later will 

produce electrical power levels of 

several hundred kilowatts. Efficient 

thermal management is mandatory 

because generation, transfer, and storage of the electrical energy needed for 

these appiications wiii require the 

dissipation of huge quantities of waste 

heat. No low-cost, reliable orbital 

thermal management system capable 

of providing this level of heat rejection 

exists. Such a system would need to 

overcome limitations inherent in current 

system designs. Ways to increaseenergy 

capacity, reject waste heat, and provide 

power for a broad range of space 

applications necessitate an entirely new 

technical concept in thermal management. 

The key to the thermal management 

concept lies in the creation of a thermal 

utility system, analogous to municipal 

public utilities, in which basic trunk 

lines are provided for individual customer integration. The system must be 

designed such that changes in location 

or usage load of individual customers 

have minimal effect on the utility's 

capability to serve the loads of the 

remaining customers. Such a centralized 

system would allow reduced operational 

and payloads integration costs, as well 

as reduced cost for all payload users, 

by having common instrument thermal 

designs. Keys to reduction in thermal 

management system costs include 

system modularity; subsystem integration; growth capability to very large 

satellites; volume and weight reduction; 

extended life by maintenance and 

replacement; and expansion of the 

thermal management technology base 

to provide simpler, more reliable 

systems. 

ORIGINAL PAGE IS 

Of POOR QUALlW 

To meet these requirements, concepts 

involving two-phase (gadliquid) heat 

transport devices are being developed. 

A centralized, pump-assisted, two-phase 

heat transport loop (or thermal bus) 

transfers heat by evaporation and condensation of the working fluid rather 

than by sensible heat changes of a 

single-phase cooling fluid. This loop 

operates at an almost constant temperature over its entire length, making 

users unaffected by their order of 

p!acement arGund ?he !mp. Such 8 

thermal bus is capable of transporting 

large thermal loads over long distances 

with pumping requirements that are 

minimal compared to single-phase 

system requirements. 

A complete 25-kW, pumped, two-phase, 

thermal bus system has been designed. 

This system contains five separate 

evaporators of different types. Four 

separate but identical condensers provide the heat sink by allowing acontact 

interface with eithersimulated oractual 

high-capacity heat pipe radiator elements. Fifty meters of both vapor and 

liquid transport lines are included to be 

representative of Space Station dimensions. The system (minus one of the 

evaporators) has undergone extensive 

testing at the NASA Johnson Space 

Center (JSC) in ambient and thermal 

vacuum environments using Freon-1 1 

as the working fluid. Integrated twophase system thermal vacuum testing 

also included an instrument pallet 

Space Flight Center for delivering heat 

to the central bus and included fullsize, high-capacity heat pipe radiators 

for providing the heat sink to the bus. 

This system-level testing has successfully demonstrated the viability of 

the two-phase system thermal management concept for future space missions. 

Additional testing will be conducted at 

JSC with the fifth evaporator installed 

and with ammonia as the two-phase 

working fluid for even higher thermal 

performance. 

+hr\rm-l Cl~an A-sz-l--~A L..aL- P--1-1---1 LI 1-8 na*at vu~u~v~~v~cu uy iiic uuuuaiu 

Layout of integrated two-phase system thermal vacuum test. 

I 44 OAST 
Direct Electrolysis of Carbon 

Dioxide for Oxygen Reclamation 

TM: Robert J. Cusick/EC3 

Reference OAST 3 

Breathing oxygen (0,) must be recovered from metaboliccarbon dioxide 

(CO,) to reduce thespacecraft logistics 

penalty for long-duration manned missions. An air revitalization process to 

accomplish 0, reclamation removes 

the COP from the cabin atmosphere by 

any one of several methods and breaks 

the CO, molecule into solid waste 

carbon and metabolic breathing 0,. 

Advanced techniques, well-developed 

to date, involve a two-phase liquid/gas 

process of reclaiming the 0, in the 

form of water (H,O) followed by electrolysis to 0, and hydrogen (H,) at a 

Another technique to reclaim 0, is a 

single-phase, fluidic gas process for 

directly electrolyzing the collected COP 

to 0, and carbon monoxide (CO) at a 

voltage approaching 1 .OV using a solid 

oxide zirconia (ZrO,) electrolyte. Operation at 1000° C virtually eliminates the 

high overvoltage inherent with lowtemperature electrolysis cells and 

thereby offers a potential powersavings. 

The single-fluid-phase nature also offers 

an advantage of simpler mechanical 

hardware with fewer moving parts for 

application in micro-g operations. 

vG!!Ggc sf 1.5 !s ! .6 v. 

Typical electrolysis cells consist of, as 

a minimum, three discrete functional 

parts: the anode, the electrolyte, and 

the cathode. These parts require some 

method of bonding or joining and 

thereby incur additional contact resistance and resultant higher operating 

cell voltage. At the high operating 

temperature of a solid oxide CO, 

electrolysis cell, the typical design is 

further corn plicated by the requirement 

for several high-temperature seals. This 

fuel cell technology transfer which 

originally began with the Department 

of Energy offers a single unitized cell of 

which the three functional parts, 

deposited on a porous ceramic tubular 

support, jointlyform the sealing function 

in addition to their primary functionsof 

carrying current and permitting conduction of O2 as an oxide ion. 

The unique property of stabilized 

ZrO, to conduct electricity at elevated 

temperatures, exclusively through the 

migration of oxygen ions, is the basis of 

the solid oxide COS electrolysis cell. 

Thin electrodeand electrolyte layers, 4 

mils or less, are formed in the novel cell 

fabrication process of electrochemical 

vapor deposition. A typical cell tube 

and exploded view are illustrated. The 

COP is electrolyzed to 0, and CO. The 

CO is reduced to solid carbon (C) and 

CO, by another air revitalization and 

COP reduction process. Another key 

feature offered by the COP electrolysis 

cell is the direct electrolysis of metabolically produced water vapor to 0, 

and H,, thereby yielding complete 0, 

reclamation from the crew’s metabolized 

CO, and H20 byproducts. 

Solid oxide electrolyte cell structure. 

Three different cell types are currently 

being fabricated and will subsequently 

be parametrically and life tested, with 

destructive micrographic analysis following the test. All three cell types are 

fabricated on a tubular porous ceramic 

support tube. The first type consists of 

many banded cells of 0.5- to 2-cm 

active width, electrically connected in 

series. Oxygen is generated, evolves 

from the anodic inside of the tube, and 

is maniout to the cabin atmosphere 

from a cell tube bundle. 

The second cell type is a tubular 

single cell along the entire active tube 

length of 30 cm. A compact, cubicclose-packed arrangement can be 

achieved in a cell bundle buildup that 

can accommodate series as well as 

series/parallel connections, thus increasing the associated reliability of 

this cell geometry. The third cell type is 

also a tubular single cell, but the cell 

interconnection path is not a single 

longitudinal one of the second cell type 

but rather is made of several bands 

around the cell tube. 

I 

- 02 

FIRST CELL TYPE 

0.9 

0.8 THEORETICAL 

0.7 

3 100% co 

fGAS OUTLET 

100% cog 

+ 

GAS INLET 

OAST 45 
Hypervelocity Impact Studies of 

Composite Materials 

PI: Jeanne Lee Crews/SN12 

Reference OAST 4 

Composite materials are being used for 

space applications on an increasing 

scale. In orbit, these materials are 

exposed to potentially damaging hypervelocity impacts from meteoroids and 

orbital debris. The relative impact velocities can range from 1 to 16 km/sec for 

orbital debris and from 11 to 72 km/sec 

for meteoroids. 

Extensive research into the hypervelocity impact resistance of metals and metal 

alloys has been conducted in the past. 

Mathematical models relating the extent 

of damage to impact velocity, projectile/ 

target geometry, and material properties 

of projectile and target have been developed for these metallic materials based 

on extensive experimental data. Similar 

research on composite materials has 

been lacking. Such a study of graphite 

fiber composites is being conducted at 

the Johnson Space Center using the 

small light-gasgun in the Orbital Debris 

Impact Laboratory to obtain experimental 

hypervelocity impact data. 

The Universityof Texas is performing 

the data analysis on the test samples by 

using an ultrasonic C-scannertodetermine the extent of the internal damage 

and by visuallyexamining thesectioned 

specimens to observe the crater, spallation, and delamination damage. The 

test samples to date consist of 16-, 32-, 

48-, and 96-lamina plates (6 by 6 in.) of 

a quasi-isotropic graphite-epoxy layup 

(a quasi-isotropic layup was chosen to 

simplify thedamageanalysis). The test 

matrix consisied ui vai-yiiig the iai-iiiiia 

count and the projectile density for 

impact velocities ranging from 4 to 7.5 

km/sec. 

A mathematical model for predicting 

the hypervelocity impact crater growth 

in a graphite-epoxy plate was developed 

and relates the time history of crater 

growth to the resistive pressure of the 

target material and to the resistive 

pressure of the radial expansion of the 

projectile during the penetration process. The model predicts crater growth 

reasonably well for the existing test 

conditions; however, the test matrix to 

date has been restricted to cylindrical 

projectiles of 5 mg mass. Further 

verification and refinement of the model 

ORIGINAL PAGE IS 

OF POOR QUALITY 

will be accomplished using more massive, spherical projectiles (mass of 70 

mg) and incorporating a high-speed 

camera diagnostic capability. 

A larger bore launch (4.3 mm) capability is currently being developed, and 

a new high-speed camera has recently 

been incorporated into the Orbital 

Debris Impact Laboratory diagnostic 

capabilities. The new camera system is 

a custom-designed, state-of-the-art, 

rotating mirrorframing camera, using a 

camera is capable of exposing 80 frames 

of 35-mm infrared film at 2 X 106 

frames/sec. Even at that framing rate, 

conventional illuminating systems were 

not fast enough to “freeze” a 300-pm 

particle traveling at speeds in excess of 

7 km/sec. The 860-mm, 100-W laser 

diode used for this system has a pulse 

duration on the order of 5 nsec. 

The larger bore launch capability will 

allow the launching of aluminum 

spheres as large as %-in., and the highspeed camera will provide the exact 

state of the impacting projectile, the 

exact velocity of the projectileat impact, 

the velocity and shape of the ejecta 

(front), and the projectile/shield plume 

growth (rear). 

’ 

I^^^_ 

I~D~I diode foi iiiiiige illiimifi~ti~~. The 

Examples of high-speed framing camera capabilities. Top: A 0.057-in. graphite-epoxy panel being impacted by a 5-mg nylon slug (0.07 by 0.07 in.) 

traveling at avelocity of 5.99 km/sec. (Exposure time 5 nsec.) Bottom: A 0.04-in. 6061 aluminum panel being impacted bya4.99-mg slug (0.07 by 

0.07 in.) traveling at a velocity of 5.8 km/sec. (Exposure time = 5 nsec.) 

t = -2 psec t = -1 psec t=o t = +1 psec t = +2 psec t = +3 psec t = +4 psec 

t = -2 psec t = -1 psec t=O t = +l psec t = +2 psec t = +3 psec t = +4psec 

46 GAS? 
Testing and Analysis of the 

Department of Defense Ada 

Language 

TM: Stephen GormanlFR12 

Reference OAST 5 

At the beginning of fiscal year (FY) 

1983, the Johnson Space Center (JSC) 

established the Ada Beta Test Program 

with the University of Houston at Clear 

Lake (UH-CL). The period of performance was through June 31, 1986, and 

was completed this year. The purpose 

was to analyze the efforts of the Department of Defense (DOD) to manage the 

ever-increasing costs of software development and maintenance, with special 

emphasis on their high-order computer 

language, Ada. The UH-CL was joined 

on a voluntary basis by more than 30 

different contractors studying various 

aspects of the Ada technology. NASA 

and UH-CL also employed contractors 

such as Softech and lntermetrics to 

study specific subjects of interest more 

closely. 

This activity has had extraordinary 

success in transferring technology to 

mainstream NASA activity. The Space 

Station Program has recently specified 

that all operational Space Station software will be developed in Ada. The JSC 

and UH-CL have jointly sponsored two 

minisymposiums on current Ada research and one full-scale symposium 

entitled, “The First National Conference 

on Ada Programming Language Applications for the NASA Space Station,” 

which drew more than 400 participants. 

The results presented in these symposiums as well as the continuing 

consultationsand presentations by task 

personnel have helped to provide the 

confidence required for the Space 

Station Program Office to move ahead 

as it has. 

Examples of Ada research at JSC for 

FY 1986 are the development of a 

benchmarking capability for assessing 

compiler implementations; evaluation 

of existing Adarun-time environments; 

development of extended run-time 

environment requirements for the anticipated Space Station distributed 

computer configuration; study of the 

common APSE interface set (CAIS) 

issues; analysisof Ada tools developed 

for DOD and available in the DOD 

SIMTEL library; and definition of training issues specific to learning modern 

software engineering methodologies 

and to using Ada. Additional task 

personnel have assisted NASA in presenting concerns and issues at Ada 

boards and committees such as the 

Ada Run-Time Working Group, Ada 

Board, Kernel Interface Team, CAIS 

Working Group, and others. 

Software engineering research interfaces. 

The Request for Proposal (RFP) forthe 

Space Station Software Support Environment states, “The Space Station 

Program has adopted Ada as its primary 

software language. The full intent of 

Ada and its associated software engineering principles shall be required.” 

This statement establishes Ada firmly 

as an important element of the Space 

Station Program. It also points out the 

logical area of concern for further 

NASA software-related research, which 

is in the area of new methods of software 

engineering and the establishment of 

state-of-the-art software development 

and maintenance environments. The 

focus of research must be expanded to 

encompass theentire software lifecycle 

from conceptual design through sustaining engineering and eventual retirement of the software. To pursue this 

end, UH-GL isestablishing thesottware 

Engineering Research Center with anticipated joint participation from NASA. 

SPACE STATION SOFTWARE 

SUPPORT ENVIRONMENT 

DOD CONCEPTS TO 

CONTROL SPIRALING 

SORWARE COSTS 

a Ada SPECIFICATIONS 

0 - 181M 

3a 

NASA ASSUMES A 

POSmON OF LEADERSHIP IN 

I SPACE STATION 

PROGRAM CHOOSES Ado AS THE COMPUTER 

LANGUAGE 

. -. . . - DOD COMPILER IMPLEMENTATIONS SYMPOSIUMS 

PRESENTATIONS 

OAST 47 
HAL/S lntercenter Board 

TM: Dave SykeslFR24 

Reference OAST 6 

The High-Order Assembly Language 

for Shuttle (HAL/S) Language Definition 

and User Group, also referred to as the 

NASA HALE Board, was established 

in 1977 to provide language support for 

the standard HAL/S compiler, tools, 

and documentation. Its objectives are 

to maintain the standard compiler and 

documentation, to control change 

requests and discrepancy reports, and 

to improve user tools and interfaces in 

order to maintain compiler viability in 

evolving environments. 

The technical objectives and the status 

of each for fiscal year (FY) 1986 are as 

follows: 

1. An interactive debugger is being 

developed to improve debugging HALE 

programs on the IBM 360 system. 

Coding was completed on the required 

commands; testing, however, was not 

completed. This program will be completed and delivered in FY 1987. 

2. Development began on an interactive interface between the HAL compiler maintainers and the compiler. 

Requirements, design and program 

descriptions, and user guide documents 

will be produced. Interactive software 

will be coded and tested to allow 

automation of thecompiler maintenance 

task. Coding and testing were completed 

on CLISTS and will allow much greater 

automation. This activity will continue 

in FY 1987 because automation will be 

completed in sequential steps, the first 

of which is not complete. 

Primary functions of the HAL/S Language Control Board. 

I I INTERACTIVE 1 I IMAINTENANCE~ I ARCHIVE I I BYRON I 

DEBUGGER INTERFACE CLEANUP SOFTWARE 

48 OAST 

3. Organization of the HALE archives 

material to provide future maintainers a 

more reliable mechanism for accessing 

historical files and documents was 

performed. Documentation and tapes 

from several different locations were 

collected at a central library. The new 

collection was catalogued using an 

automated data base system. The library 

is now complete, and maintenance only 

will continue through FY 1987. 

4. A program design language 

(BYRON) was applied to existing HAL/S 

code to analyze possible conversion to 

Ada. The HAL/S statements were integrated into BYRON code to test Ada 

development methodology with HAL/S. 

All coding and testing of the conversion 

of a HALE module to Ada using BYRON 

has been completed. The report of the 

findings of this task will be completed 

in early FY 1987. 
Human Strength and Motion 

Modeling 

TM: Barbara J. Woolford/SP34 

Reference OAST 7 

The Johnson Space Center is building 

a computerized model of human capabilities for use in spacecraft design and 

mission planning. This software will 

model human physical features such 

as size, strength, and motion. Current 

capabilities include specifying anthropometric percentiles and automatically 

constructing a properly sized human 

body. The motion modeling capabilities 

includeautomatic positioning of a body 

in a configuration to reach a specified 

object, given some restraint condition. 

The most difficult parameter to 

account for is that of strength in zero g. 

Quantitative data are not available. It is 

known that the strength that can be 

applied in zero-g is partially a function 

of restraint type and also is greatly 

affected by whether the astronaut is 

working in shirtsleeves or in a pressurized space suit. 

The instrument for measuring strength 

is the Cybex dynamometer, which 

recordstorqueexerted while it controls 

the velocity at which the participant 

can rotate the tool. A constant velocity 

is required, because strength is also a 

function of the speed at which the 

motion is performed. The Cybex has 

been packaged in a waterproof containerfor use in the Weightless Environment Test Facility (WETF), and a stand 

has been designed to permit mounting 

the Cybex in the KC-135 aircraft for 

testing during parabolic flight with 30- 

sec periods of weightlessness. 

The purpose of the experiment is to 

collect strength data on suited and 

shirtsleeved astronauts in three environments: the laboratory setting in lg, 

the WETF in neutral buoyancy, and the 

KC-135 aircraft in true (but brief) zero 

g. This data will be of two types: singlejoint rotation, such as elbow flexion or 

shoulder abduction, to provide data to 

the computer model; and complex 

motion, such as rotating an extravehicular activity (EVA) wrench, to provide 

operations data. The packaged Cybex 

has been flown on the KC-135 three 

times. Data from similar tests in the 

WETF will be collected for comparison 

and validation of WETF simulations. 

The plans for fiscal year 1987 are to 

completethetest matrixand to incorporate the force capability data into the 

computer model. 

ORlGlMAh PAGE 1s 

LW POOR QUALITY 

Astronaut Pierre Thuot exercises his right elbow joint in the KC-135 aircraft equipped to fly 

gravity-reduced parabolas. He is held in place by EVA foot restraints and does not have a 

handhold available. 

OAST 49 
Crew Station Human Factors 

TM: J.T. Malin/EF 

Reference OAST 8 

The purpose of the Johnson Space 

Center (JSC) Human Factors Laboratory 

(HFL) is to examine user interaction 

with advanced display, control, and 

computer technologies. This project 

involves performing several research 

studies, collecting human performance 

data from users interacting with these 

technologies, and providing recommendations detailing how these technologies may be incorporated into 

spacecraft work stations to optimize 

the man/ machine interface. 

Theapproach taken was todevelop a 

user needdadvanced technologies 

matrix from which 12 general research 

issues were derived. An issue was 

chosen (e.g., programmability/multifunctionality or voice recognition1 

production), and a literature search 

was performed. Specific experimental 

topics were chosen; experiments were 

designed; human performance data 

were collected and analyzed; and technical reports were prepared. 

Six technical reports have been published, with topics ranging from user 

interaction with programmable display 

and control devices to the human factors 

of expert systems. The most recent 

area of investigation involves the electronic display of procedural information. 

A crew operations research work station, 

incorporating several types of display 

and control devices, and a user interface 

management system for the rapid prototyping and evaluation of human/ 

computer interface efforts have been 

developed. The HFL is responsible for 

developing the human/computer interfacedesign guidefortheSpaceStation 

Program. Contacts have also been 

established with industry, the Department of Defense, and other NASA 

centers. 

As a result of this program, human 

performance data have been input into 

the Space Station design. A facility 

with personnel devoted to spacecraft 

human factors has been established at 

JSC. Additionally, contacts through the 

HFL bring new technologies and information to JSC and to the manned 

space program. 

In the future, researchers at the HFL 

plan to continue the research program 

through the examination of user interaction with multifunctional displays and 

controls and through the electronic 

display of procedural information. 

Additionally, researchers will begin to 

examine user interaction with intelligent 

computer systems. The user/computer 

interface rapid prototyping capability 

will be expanded. 

HFL crew research operations work station (foam-core mockup). 

\ 

ORIGINAL PAGE IS 

QF POOR QUALITV 
ORIGINAL PAGE IS 

OF 20GR QiiiiiiTr' 

Advanced Autopilot Experiment 

TM: Jerry Woodfill/EXS 

Reference OAST 9 

The Advanced Autopilot Experiment 

(AAPE) demonstrated a new class of 

autopilot incorporating a unique control 

approach that features real-time failure 

configuration and optimization. This 

approach employsan optimizing linear 

select algorithm and a multidimensional 

phase-space rotational and translational 

control law (an improvement over 

autopilots employing one or more twodimensional phase planecontrol laws). 

Control systems based on this phasespace philosophy have potential applications in several vehicles for which 

fuel economy and rapid failure recovery 

are requirements. Autopilots in this 

ciass are adapatabie to most spacecraft 

in which reaction control system (RCS) 

and/or control moment gyro effectors 

are used. Effectors do not need to be 

placed orthogonally and may be 

blended. The AAPE software was incorporated into the Space Shuttlesoftware and resided in the Space Shuttle 

computer memory. 

The experiment operated during the 

orbital flight phase of Space Transportation System (STS) missions STS 

51-G and STS 61-B and resulted in 

fewer jet firings, reduced computer 

burden, improved vehicle response, less 

propellant consumption, and more 

flexibility. 

On STS 61-B. a radar corner reflector 

(target) was deployed during an extravehicular activity by astronaut Woody 

Spring for use during stationkeeping 

exercises. By sighting an Orbiter television (TV) camera on the deployed 

target, astronauts could make a comparison of AAPE and primary flight 

system (PFS) control for a prescribed 

maneuver. 

The target was constructed of flat 

aluminum plates which werestored in a 

crew cabin locker and erected into a 

sphere by a crewmember before deployment. Target deployment occurred 

during a loss-of-signal communication 

period but was recorded on Orbiter 

video so that quantitative assessments 

of maintaining position could be made 

after flight. In general, the ground 

observers noted a steadier position of 

the target on the TV monitor during 

AAPE control than during periods of 

PFS control. 

When the target was deployed, the 

remote manipulator system camera was 

10 ft from it. Cargo bay lights provided 

adequate illumination of the target 

during nightside passes. The crew 

reported that the reflective tape on the 

target enhanced visibilityasthe Orbiter 

separated from the target. The entire 

process of assembling, tethering, and 

deploying the target went smoothly 

and established a concept which may 

prove useful on future missions. 

Initial testingof the AAPE (before target 

deployment) demonstrated such reliable 

operation that the planned 15 min of 

AAPE control were extended to 1 hr in 

orderto observevehicle handling qualities during maneuvers at the 35-ft 

stationkeeping distance. The switchover 

after target deployment was very 

smooth. 

The AAPE controlled the vehicle for 

more than 30 hrduring the mission and 

provided much greater confidence in 

arA- ~)CP 4- AA~C -- a4...--- 4c -:- IIWIII I I cl tu nnrL awitwaic IJ IIIIII 

its use as an operational system. The 

crew reported that the AAPE performed 

one of the cleanest velocity-vector 

maneuvers ever run, that it held attitude 

tighterthan the primarydigital autopilot 

(DAP), and that with the AAPE, the 

problem of cross coupling between 

translation and rotation encountered 

with the primary DAP was lessened. 

The low-Z mode worked correctly. 

Because of the AAPE's optimized 

use of a combination of vernier and 

primary thrusters for attitude hold 

(rather than selecting one or the other 

as the PFS does), the RCS fuel consumption was reduced between 10% 

and 20% for extended periods. 

On STS 61-B, the Orbiter vernier 

thrusters were inhibited to provide a 

comparison with a 0.1 " deadband test 

maintained attitude to 0.07"/body axis, 

using approximately one-fifth the RCS 

propellant required by the PFS for 

control to only O.S"/axis. 

---a ---- A -- CTC tz4 n TL- ~~n

~CIIWIIIICU WII QIQ JI-u. IIIG nnrri 

Radar corner reflector deployed as AAPE target during STS 614 mission. 

OAST 51 
Automated Subsystem Control for 

Life Support Systems 

TM: Frank H. Samonski/EC3 

Reference OAST 10 

The current approach for the control of 

subsystems in manned spacecraft is 

labor intensive both for the flight crew 

and for ground support personnel. A 

permanently manned Space Station will 

require highly automated control of its 

systems and subsystems to reduce 

significantly thedemand for monitoring 

the control. Efficiently organized local 

and archival data storage and the rapid 

retrieval and display of subsystem status 

will be required to maintain operations 

across the various subsystems. A program has been completed that demonstrates the technology now available to 

allow generic automation techniques 

to beapplied in thecontrol of spacecraft 

su bsystems. 

To ensure the generic nature of the 

automated subsystem control techniques developed, an applications study 

was conducted to determine the controlling and monitoring requirements 

of three representative Space Station 

systems: the environmental control and 

life support system; the electrical power 

system; and the guidance, navigation, 

and control system. Based on the results 

of this study, a family of generic 

automation controllers was designed, 

and a specific configuration was selected for application to the air revitalization group of subsystems within the 

environmental control and life support 

system. 

Four identical controllers were then 

fabricated: three to control and monitor 

the three subsystems within the air 

revitalization group - electrochemical 

carbon dioxide (CO,) concentration, 

Sabatier C02 reduction, and acid electrolyte oxygen generation - and the 

Space Station Technology Program automated subsystem control for life support system 

(ASCLSS). 

OBJECTIVE GENERIC AUTOMATION AND 

CONTROL FOR SPACE STATION 

SUBSYSTEMS 

DEVELOPMENT/DEMONSTRATlON 

NASA JSC ASCLSS PROGRAM + 

GENERIC CONTROLLER 

0 COMMON, CARPLEVEL HARDWARE ELEMENTS 

COMMON, LAYERED OPERATIONAL SOFTWARE 

0 PROCEDURES/GUIDELINES FOR SUBSYSTEM 

APPLICATION SOFTWARE DEVELOPMENT + + 

CONTINUING DEVELOPMENTS APPLICATIONS 

0 GENERIC 110 DESIGN/ 

0 INTEGRATION TO PROCESS 

SOFTWARE TOOLS FOR ADA 

DEVELOPMENT 

HARDWARE 

ARE IN DEVELOPMENT 

NASA SPACE STATION 

TEST BEDS AND TECHNOLOGY 

DEMONSTRATIONS 

I 

BENEFITS 

GENERIC AUTOMATION AND 

CONTROL OF SPACE STATION 

SUBSYSTEMS 

CONTROLS RESPONSlBlLlN 

REMAINS WITH THE 

SUBSYSTEM DEVELOPER 

APPROACH FULFILLS NEED FOR 

COMMONALITY. ON-ORBIT 

MAINTENANCE, AND LOWER 

DEVELOPMENT AND LIFE 

CYCLE COSTS 

fourth to perform the supervisory and 

sequencing functions necessary for the 

three subsystems to work in an integrated manner to accomplish the atmosphere revitalization function. Stateof-the-art electronics technology was 

employed in the generic controller and 

included the Military Standard 1750A 

16-bit microprocessor, which uses a 

standard instruction set for software 

programming and adual-redundant data 

bus for high-speed communications 

between the four controllers. 

In parallel with the design and fabrication of the four controllers, process 

simulators were developed using three 

personal computers to emulate the 

chemical and electrochemical processes 

of the three subsystems. A fourth and 

more powerful personal computer was 

adapted to perform the manhachine 

interface functions, including the retrieval display of data and the command 

link for selecting various operating 

modes. 

A unique approach was developed 

for the design and coding, in higher 

order language, of the software required. 

Referred to as a layered software 

stucture, identical code was used in 

each of the four controllers to accomplish common functions such as data 

base management and systems control. 

The process control software, which is 

unique to each of the subsystems, 

interfaces with only the common systems control software and not directly 

with the subsystem simulators. Assembly language code was selected for 

the small fraction of software referred 

to as the operating system to maximize 

the speed of data acquisition, of data 

transmission, and of data base updating. 

The fabrication of the controllers and 

the preparation of the software has been 

completed. A comprehensive acceptance 

test was conducted successfully, and 

the complete system was delivered to 

the Johnson Space Center in July 1986. 

Various system evaluation tests are being 

conducted to verify performance and to 

evaluate the dynamics in the transitions 

between the operating modes. Recommendations are being prepared to 

enhance the display of information to 

the operator and to examine the fidelity 

of the processsirnulators. A continuation 

effort is being planned and would replace 

one of the subsystem simulators with 

actual process hardware. 

52 OAST 
Space Flight 

Advanced Programs 

Summary 
Office of Summary 

Space Flight 

ORBGRNAL PAGE IS 

OF POOR QUALIN 

introduction 

The Office of Space Flight (OSF) 

Advanced Programs activity is directed 

toward enhancing and expanding the 

National Space Transportation System 

(NSTS). 

Early in fiscal year (FY) 1986, the 

maiden flightofthefourth SpaceShuttle 

Orbiter, Atlantis, marked the completion 

of the initial STS fleet. The following 

mission, which was dedicated to the 

German Spacelab, highlighted international cooperation in the Space 

Shuttle Program. It was the first Space 

Shuttle flight to be chartered completely 

by another country, and it carried a 

record-breaking eight-member crew, 

two of whom were West German payload 

specialists. The Spacelab’s experimental 

facilities were arranged according to 

scientific disciplines into “payload elements” which included melting furnaces, facilities for the observation of 

fluid physics phenomena, chambers to 

provide specific environmental conditions for living test objects, and the 

vestibular sled, which exposed the in the Spacelabmodule. 

astronauts to defined accelerations in I --- .I, - 

order to study the function of the inner 

Space Shuttle Orbiter Atlantis landing after her maiden flight. 

Guy Bluford, Ernst Messerschmid, Reinhard Furrer,and James Buchli performing experiments 

ear. During the 7-day mission, 70 . experiments in micro-g materials processing, life sciences, communications, 

and navigation were conducted with 

the scientific operations being controlled from the German Space Operations Center near Munich. 

During FY 1986, the first construction 

of large structures in space was also 

demonstrated with two flight experiments. The Experimental Assembly of 

Structures in Extravehicular Activity , 

(EASE) project consisted of six aluminum beams,each 12ft long, and demon- I > 

strated assembly techniques in which 

the crewmembers moved about the 

structure as required. The Assembly 

Concept for Construction of Erectable 

Space Structures (ACCESS) project 

consisted of 93 tubularaluminum struts, 

* 
On-orbit assembly of the Assembly Concept for Construction of Erectable Space Structures 

(ACCESS) during mission STS 61-B. 

with 1 in. diameter. The crewmembers, 

working from a fixed platform, assembled thestruts intoa45-ft-long truss. In 

addition to the assembly task, the 

maintenance, and the repair, procedures 

were investigated by stringing flexible 

cable along the ACCESS truss to 

simulate the installation of electrical 

cables. The crewmembers also removed 

and replaced individual struts to demonstrate repair capability. 

Four communications satellites were 

deployed, including two for foreign 

governments. Telephone, television, and 

wire services are being provided for 

Mexico by the Morelos-B satellite; a 

similar satellite, AUSSAT-2, was deployed for the Australian National 

Satellite System. 

Advanced Space Flight Technology 

Future space transportation missions, 

which will orbit planets with atmospheres, can obtain significant performance improvements (when compared 

to all propulsive concepts) byaerobraking within the atmosphere. In order to 

stimulateadvancesin thedisciplinesof 

aerothermodynamics, aerodynamics, 

and guidance, navigation, and control 

(GNBC). the aeroassisted flight experiment (AFE) has been proposed to fly 

onboard the Space Shuttle in 1992. The 

AFE isa NASA intercenter project which 

will provide the technology for an 

aeroassisted orbital transfer vehicle 

(AOTV). During the year, the elliptical, 

raked-off cone concept developed at 

the Johnson Space Center (JSC) was 

chosen as the AFE baseline configuration. The heatshield structure is planned 

to be conventional aluminum skin and 

stringer covered with thermal protection 

system tiles similar to those used on 

the Space Shuttle. Eleven scientific 

experiments are being integrated into 

the heatshield and carrier vehicle structure. Also under study are several atmospheric guidance algorithms which 

are being considered for use on the 

AFE. All concepts employ banking 

about the velocity vector to control 

motion in the vertical plane. 

With the new flight vehicles, new 

techniques in GN&C are being developed to facilitate multiple-vehicle mission planning and operations. The newly 

developed automated rendezvous and 

proximity operations simulation software was developed as a tool for 

performing parametric analysis of rendezvous ana proximiiy operations for a 

reference nonmaneuvering vehicle 

(Space Station or Orbiter) and as many 

as five maneuvering free-flyers. The 

six-degree-of-freedom (DOF) proximity mode offers a variety of attitude 

control regimes, a model of a relative 

position/attitude determination sensor, 

and the capability tocorrelate propellant 

expenditure by axis and function. 

The simulation will model first-order 

error sources and environmental effects 

to the level necessary for making 

credible judgments about operational 

feasibilityand for assessing subsystem 

performance requirements. An analysis 

of the global positioning system (GPS) 

has shown it to be capable of highly 

accurate spacecraft navigation, and it 

has been baselined in this role for 

future spacecraft designs. It can also 

be applied to nonclassical navigation 

functions. A series of studies hasshown 

. 

. 

The GPS will be able to supplement traditional spacecraft navigation systems. 

/ 

KOMMUNICATI 

56 OSF 

ORIGINAL PAGE IS 

OF. POOR QUALITY 
OF POOR QUALITY 

that structural deformations can be 

measured directly with GPS, and, by 

using a data link to relay state vector 

information between two vehicles, GPS 

can serve as a very accurate tracking 

aid. The GPS clock can be used as a 

timebase with an accuracy of 25 nsec. 

Finally, the system can be used to 

measure coarse vehicle attitude. 

Enhanced Manned Systems 

Future manned missions, with larger 

crew sizesand longerduration activities, 

will require more efficient manned 

systems in order to minimize or to 

eliminate resupply requirements and to 

improve man’s effectiveness. 

A comprehensive survey of existing 

all” p”4CllLlal Icycllclclllva ellvilullmental control and life support system 

(ECLSS) technology was conducted 

during the year. The study included 

both physicochemical and biological 

concepts and considered the potential 

commonality between the ECLSS of 

the Space Station and of future advanced missions such as the manned 

lunar base. Definition of advanced space 

missions, identification of unique mission drivers, and development of a 

tradeoff methodology were also 

performed. 

Increased extravehicular activity 

(EVA) requirements of Space Shuttle 

missions and the developing Space 

Station Program have emphasized the 

need for improved glove design and 

performance. These requirements include capability for hand mobility and 

dexterity functions at suit pressure 

levels ranging from 4.0 to 8.0 psia, 

capability to maintain load-bearing 

capacity (man loads and pressure 

loads), thermal protection, and abrasion 

and puncture protection. The key glove 

performance issue becomes one of 

finding the right balance between the 

protection capability and the performance capability of the functional glove. 

Productivity requires mobility, comfort, 

ease of donning and doffing, tactility, 

and safety assurance. Glove design 

complexity increases with the differential pressure between the glove and the 

vacuum of space and with EVA task 

requirements. In order to maintain and 

improve EVA glove mobility features 

for high-operating-pressure (8.0 psia) 

glove assemblies, a series of mobility 

joint elements is currently under 

-.,A ..-*--a:- --.------A:..- ^- 

Internal detail of the 8.0-psi glove. 

development. During theyear, prototype 

8.0-psi glove assemblies have been 

delivered to JSC for preliminary test 

and evaluation activities. Follow-on 

design and development activities for 

enhancing the various glove mobility 

featureswill be planned based on results 

of the testing activities. 

Work continues this year on a variety 

of standard fixtures for aid in servicing 

satellites from the Space Shuttle and 

the manned Space Station. In addition 

to a joint NASA/Department of Defense 

(DOD) study effort entitled “Satellite 

Assembly, Maintenance, and Repair” 

(SAMS), conceptual designs of several 

fixtures were initiated. These include a 

satellite holding device, a force/torque 

sensing system for the Space Shuttle 

remote manipulator arm, and a telerobotic work system (TWS), which 

consists of a pair of manipulators 

controlled from theSpaceShuttlecabin. 

The TWS also shows promise as a 

“smart”first stage forthe orbital maneuvering system being developed as an 

adjunct to the STS. 

Another area of concentrated research has been the generation of 

communication equipment required for 

the increased operations when the 

NASA manned Spacestation becomes 

operational. Infrared crew communications systems have been studied both 

for crew voice communication and for 

data transmission, with a special 

emphasis on providing wireless physiological data from astronauts in the 

Space Station. Free-space laser transmission has been studied, and emphasis 

is being placed on improving its applicability for space operations. Another 

area of great potential is the communication of data optically through the 

Space Shuttle windows without the 

need for data cable penetrations. 

OSF 57 
Manned Presence Above Low Earth 

Orbit 

Lunar base concept studies have 

pointed out the advantages of using 

lunar resources for the construction 

and operation of a lunar facility. Students and faculty from Clemson University, working at JSC, constructed 

equipment for an experiment todemonstrate the production of glass fibers. 

The experiment successfully produced 

a larger quantityof glassfibersfrom an 

Apollo 16 simulated soil sample (terrestrial soil with the correct mineral 

composition) without any preprocessing.Thefibersare being testedfortheir 

material properties and appear suitable 

for making fiberglass. 

Another study has concentrated on 

appropriate propellants for supporting 

a lunar base, including propellants 

which could be manufactured from 

lunar resources. The propellants 

recommended for initial analysis and 

vehicle performance tradeott Studies 

Conceptual lunar base. 

include liquid oxygen, liquid hydrogen, 

aluminum magnesium, silane, and 

monomethy hydrazine. A tradeoff study 

based on the NASA/JSC-supplied lunar 

mission transportation model has 

focused attention on several liquid 

oxygen/h yd rogen and alum i nu m/oxygen propulsion system concepts. Lunar 

propellant processing techniques that 

are applicable to these propulsion 

systems include hydrogen reduction 

for oxygen production and acid leaching 

tor aiuminum production. 

' 

ORIGINAL PAGE 1s 

OF POOR QUALITY 

1 58 OSF 
Space Flight 

Advanced Programs 

Significant Tasks 
Satellite Services System 

TM: Gordon RysavylEX2 

Reference OSF 1 

The fully operational Space Transportation System must meet requirements 

for a wide range of satellite servicing 

functions, including capability for payload deployment and retrieval, payload 

support on sortie missions, and satellite 

support servicing within, or adjacent 

to, the Space Shuttle cargo bay. Potential satellite support requirements include: (1) resupply of expendable items 

such as propellants or raw materialsfor 

processing; (2) checkout, maintenance, 

and repair; (3) reconfiguration of 

sensors; and (4) component exchange. 

Previous studies defined the requirements and provided conceptual designs 

equipment. Some of this equipment is 

now available or under development, 

and the remainder consists of newly 

identified items for future development 

consideration. 

ui various items of saiSllite S~~L.;C~S 

FTS system enhancing RMS capabilities. 

ORIGINAL PAGE IS 

OF POOR QUALIN 

The envisioned servicing equipment 

will be capable of multiple uses on the 

Space Shuttle, the Space Station, and 

orbital maneuvering vehicles and will 

provide services for satellites of wideranging varieties and orbital locations. 

This commonality will be achieved by 

maintaining standard interfaces, which 

are being developed in conjunction 

with the definition and development of 

the servicing equipment. Based on 

customer inputs through study contracts and workshops, concepts are 

defined and given testbed evaluations 

leading to flight hardware specifications. 

The NASA goals are to baseline 

standardize the servicing interfaces, 

thus allowing satellite developers to 

consider servicing in their original 

design phase. 

----vi- rnnrirrinn aniiinmfint yr?,Ir,,b ~bI”I”IIly b\1Y‘p“‘I”I1. YII” 

:‘RECEDLNG PAGE BLANK, NOT 

Major activities initiated and conducted 

in 1986 include the conceptual design 

of aversatile, lightweight satel!ite holding device, development of a force/ 

torque sensing (FTS) system for the 

remote manipulator system (RMS), 

telerobotic work system concept development (see OSF 2 for details), and a 

joint NASA/Department of Defense 

(DOD) study program called Satellite 

Assembly, Maintenance, and Servicing 

(SAMs). 

The satellite holding device will be 

used for the maintenance, repair, 

checkout, and temporary berthing of 

satellites during on-orbit operations. It 

and avionics interfaces. The satellite 

holding device is stowed within the 

Orbiter cargo bay and is deployed over 

the longeron for use. Its berthing interface with the satellite is compatible 

with the previous serviceable satellites 

developed by the Goddard Space Flight 

Center, to maintain commonality. 

The FTS system is currently being 

developed for the Orbiter RMS. This 

system will consist of a forcehorque 

sensor on the RMS, a computer and 

video graphics generator on the Orbiter 

aft flight deck, an interconnection with 

the closed circuit television monitors 

and recorders, and a graphics retrieval 

and information display (GRID) compass computer keyboard interface. The 

hardware is presently being manufactured to class D payload guidelines and 

will be used asan operational prototype 

in helping to manipulate noncritical 

payloads and in assisting in the performance of other RMS tasks. 

The SAMs study effort will consider 

DOD, NASA, and commercial spacecraft 

and will cover all aspects of on-orbit 

servicing, including requirements, 

spacecraft design, hardware/tools, mission scenarios, and system analysis. 

Theculmination of this first-phase study 

will lead to the identification of selected 

hardware and procedural proof-ofconcept evaluations to be conducted in 

thesecond phaseoftheSAMS program. 

t:;i!! inc!u& prcljisicns fcr f!giA, ps*ler, 

OSF 61 
Telerobotic Work System 

Definition Study 

TM: Lyle M. JenkindEX2 

Reference OSF 2 

The requirements for servicing, assembling, and maintaining space systems have created the need to provide 

supplements and alternatives to extravehicular activity (EVA) by crews of the 

Space Shuttle and the Space Station. 

Remote operating systems that increase 

the capability. and productivity of the 

space crew can effectively meet the 

need. Systems using automation and 

robotics technology to perform tasks in 

timercritical and hazardous situations 

are new tools to be developed for the 

SpaceTransportation System capability. 

Work station equipment. 

An EVA by the astronauts has been 

demonstrated as an effective and versatile means of working on satellites and 

of building structures in space. Remote 

operating systems with a capability 

equivalent to the astronaut in an extravehicular mobility unit (EMU) offer an 

increase in productivity and retain 

operational redundancy by keeping 

tasks compatible with backup by the 

EMU-equipped astronaut. The increase 

in crew productivityfora remote operating system can be augmented by 

technology evolution from teleoperation 

to telepresence to supervisory control 

of a monitored robotic mode. Sensors 

feed data on conditions at the work site 

to the operator’s displays as well as to 

the computer. The operator and the 

computer work together in controlling 

dexterous manipulators to accomplish 

intricate tasks that presently can be 

done only by an EVA astronaut. The 

implementation of this approach is being 

studied in the concept of a telerobotic 

work system (TWS). 

The TWS is a concept that applies 

teleoperations, telepresence, and robotic technology to space operations. 

The TWS concept is being developed 

in system definition studies by Grumman 

Aerospace Corporation and Martin 

Marietta Aerospace. The concepts defined are anthropomorphic in configuration with two dexterous arms approximately the length of human arms. 

Television cameras transmit views of 

the work site to the operator located in 

the Space Shuttle Orbiter cabin or in a 

Space Station module. Initial results of 

the studies have formed the basis for 

consideration of a similar system for 

thespacestation. Grumman performed 

laboratory simulations of Space Station 

structure assembly using dual manipulators in master-slaveand six-degreeof-freedom rate control modes. Martin 

Marietta is developing control station 

concepts compatible with the Orbiter 

cabin constraints. Early flight experiments will be needed to resolve the 

effect of zero g on the system, control, 

and tasks. 

LIGHTS AND 

WRIST CAMERAS 

AND LIGHTS 

MANIPULATO 

62 OSF 
Rendezvous/Proximity Operations 

Guidance, Navigation, and 

Control System Study 

TM: William L. Jackson/EHW 

Reference OSF 3 

The requirements for interactive space 

traffic control will be increasing as new 

vehicles (manned and unmanned) and 

capabilities are developed for the space 

fleet. Automated systems to support 

these requirements must be developed 

and used to maximize fleet productivity. 

The design of automated systems is 

greatly enhanced by developing tools 

and local work stations that the design 

engineer can use for performing parametric analyses on an evolving design. 

The automated rendezvous and proximity operations simulation has been 

.tP?e!npPd i” rPcpcrnce ?c! ?hl? need. 

A reference nonmaneuvering particle 

(Space Station or Orbiter) and as many 

as five maneuvering free-flyers can be 

defined. An important design featureof 

the simulation is an asynchronous task 

executive, which propagates all platforms to the time of the next scheduled 

event and allows the user to define and 

execute new applications or subsystem 

algorithms without modifying the program structure. 

Thesimulation provides genericsubsystem models for rendezvous navigation sensors, the inertial subsystem, 

and the global positioning system. A 

maneuver command file executive, 

together with a newly developed algorithm for maneuver computations, 

allows arbitrary sequences of maneuvers 

to be specified and executed. Maneuver 

computations account for theeffectsof 

finite thrust and all modelled disturbing 

accelerations. 

In the proximity operations mode, the 

si m u lation switches to six-deg ree-offreedom (DOF) equations of state for 

each free-flyer and activates the proximity operations applications executive. 

This task interfaces with the command 

file executive to implement a userspecified suite of proximity operations 

activities including position hold, soft 

dock approach, transfer, etc. The proximity operations applications task 

provides subroutine templates for 

implementing new types of commands 

and activities, and it standardizes the 

interface with the six-DOF autopilot, 

which controls attitude and translation. 

A feature of the command file executive 

permits halt points to be defined by the 

user, so that new commands may be 

entered during the course of the run. 

The proximity mode offers a variety of 

attitude control regimes, a model of a 

relative position/attitude determination 

sensor, and the capability to account 

propellant expenditure by axis and 

function (attitude or translation). 

In general, the simulation models 

first-order error sources and environmental effects to the level necessary to 

make credible judgments about operational feasibility, subsystem performance requirements, and consumable 

stores. The simulation is coded in ANSI 

Fortran 77, and can execute on any 

compatible machine, including IBM 

PC’s, VAX, and CYBER. 

Automated rendezvous and proximity operations simulator program elements and architecture. 

PROGRAM MAINE 

CONSTANTS AND 

INlT PHYSICAL TAPE ORBNAV 

ARRAYS 

SUB INPUT 

READ STATE VECTS TAPE TAPEW 

RDVZ FILTER AND AND RDVZ SENSOR DATA 

SENSOR DATA 

I 

SUB EXEC 

PROPAGATE STATE 

VECTOR TO NEXT EVENT 

I L 

05 10 I 

SUB DELTAV 

CALL TASKS 

SCHEDULED AT 

EVENT TIME: EXECUTE RDVZ 8-DOF POSITION/ATT 

< RETURN > MANEUVER I I DIGITALAUTOPILOT I I 

TURN ON RDVZ RADAR EXECUTE PLATFORM LASER PROX-OPS 

AND STAR TRACKER ALIGNMENT REL POSIATT SANSOR 

02 07 12 

PAOX-OPS ATTITUDE 

PROCESSOR 

HARDCOPY OUTPUT 

FOR REF AND FREE- EXECUTE RENDEZVOUS 

FILTER MEASUREMENTS 

13 

I 

SUB RDVZEXEC SUB CMDEXEC 

EXECUTE RDVZ MNVR OUTPUT RELATIVE RDVZfPROX COMMAND 

SEQUENCE COMMANDS TRAJECTORY PLOT FILE FILE PROCESSOR 

TAPE NEWDAT 

INITIALIZE AND RESET PROXIMITY OPERATIONS RDVZfPROXRENDEZVOUS FILTER APPLICATIONS EXEC OPS CMD FILE 

OSF 63 
Interactive Graphics Control 

System Design 

TM: E. 1. KubiaWEH2 

Reference OSF 4 

Recent advances in the technologies of 

microcomputers and high-speed 

graphics allow a truly interactive 

approach to the solution of complex 

guidance, navigation, and control 

(GN&C) analysis problems. As a computationally intensive program is being 

executed on a host microcomputer, ine 

analyst can be simultaneously viewing 

the output data in a variety of formats 

(e.g., two-dimensional (2-D), 3-D, etc.) 

and can make appropriate midrun 

changes. This solution approach is a 

boon to complex analysis problems in 

that it benefits both analysis efficiency 

and, because it typically improves 

insight, analysis quality. 

In fiscal year (FY) 1986, the promise 

of this interactive technology was illustrated by several significant analysis 

applications. These applications involved tethered satellite dynamics, control moment gyro (CMG) momentum 

management, and optimal jet selection 

theory. 

To support studies of tether dynamics, 

high-speed graphicswere used to depict 

the relative motion of multiple tethered 

objects connected by either massless 

or “bead” element tethers. The motion 

could be observed in any plane or 

choice of planes, as shown in the 

accompanying figure, oreven in 3-D by 

isometric viewing. Using this capability, 

theanalyst could readily (1) differentiate 

between tumbling and normal tether 

librations, (2) identify subtle errors in 

run construction (initial conditions), 

(3) visualize instabilities in release/ 

reel-in dynamics, and (4) characterize 

the potential for recontact in various 

failure scenarios. 

Comprehension of CMG steering and 

of momentum management control laws 

was promoted by the design of a 3-D 

representation which showed the time 

varying the relative motion of momentum vectors of the individual CMG’s. 

During data playback, the analyst could 

manually adjust the viewing eyepoint 

to obtain the best perspective of the 

rotating vectors. Therefore, for various 

spacecraft maneuvers, the analyst could 

quickly grasp how well individual control 

law objectives were met and how close 

the CMG’s were to saturation (coalignment). 

64 OSF 

Finally, an application was made of 

optimal jet logic theory which provides 

substantial heuristic insight into an 

otherwise mathematically complex 

problem. The basic problem statement 

is as follows: Given a desired rate 

change in a state vector, determine the 

selection of thrusters and corresponding 

thruster on-times which produce the 

desired rate change with a minimum 

net on-time. A two-part mathematical 

derivation had been made. First, for 

any given ratechange, it defined which 

thruster combinations could be optimal 

(correspondingly, some combinations 

are never optimal). Second, given a 

specific rate change request, it showed 

how to choose the particular combination which is optimum. Although this 

mathematical concept applies to general 

n-degree-of-freedom (DOF) formulations, a typical application would be to 

three-DOF spacecraft rotational control, 

and for this case graphical visualization 

was of immense benefit. It can be 

shown for the sets of optimal thrusters 

that the end points of the thruster 

acceleration vectors define planar surfaces with faces (triangular surfaces) 

corresponding to the optimality boundaries. If a surface is penetrated by the 

desired rate changevector (or its extenTether control dynamics. 

sion), then the set of thrusters which 

define the surface vertices are the 

optimal set of thrusters. Since the planar 

surfaces define an overall “closed” 

surface (convex polytope), there will in 

general be only one intersection or one 

set of optimal thrusters. This application 

hasspawned insights into controllability 

criteria which are currently being 

developed. 

Although past accomplishments more 

than justify the concept of interactive 

control system design, a key iask 

objectivestill remains. Thisobjective is 

to perform midrun interactive control 

system design for a problem involving 

complex dynamics. The availability of 

the high-speed microcomputer will 

complete the required environment to 

meet this most demanding objective. 

Simulation and analysis programs are 

currently being hosted that will provide 

design capability for the complex onorbit problems of optimal control in 

rendezvous and proximity operations. 

A key goal for FY 1987 is to converge on 

the remaining objective by using these 

analysis tools in the interactive environment to perform fundamental control 

system synthesis. 

3de 

Front 1 
Data and Software Systems 

Commonality 

TM: Robert G. Musgrove/EHG 

Reference OSF 5 

The advent of long-duration, manned 

spaceflight programs, literally spanning 

generations, requires that considerable 

attention be paid to designing systems 

that can be replaced, maintained, shared 

(or reused), and upgraded with minimum impact to the mission. Nowhere is 

it more important to carry forward this 

philosophy than in the development of 

the spaceborne computing systems. 

Reuse and maintainability of software 

and hardware systems for long-lifecycle systems have resulted in the 

emergence of the term “commonality,” 

which, for large-scale, evolving flight 

systems. can be reduced tn a simp!o 

definition of the attribute of planned 

sharing of system resources where the 

resources are defined as hardware, 

software, faci I ities, tools, etc. 

The Data and Software Systems 

Commonality Research and Technology 

Objective and Plan (RTOP) has as its 

ultimategoal the development of guidelines and groundrules which could be 

implemented as agency policy with the 

objective of promoting commonality 

across flight programs. For some time, 

commonality initiatives had been 

under way on a local basis within each 

of the NASA Programs or Centers, but 

it had not yet drawn an agency focus. 

As a means of providing this focus, 

activity for the fiscal reporting year 

1986 was divided into two major components. First, a comprehensive survey 

was conducted by Center and by 

Program to determine commonality 

initiatives and to identify who was 

performing the work. In June, this work 

culminated in a two-day roundtable 

session held at the Johnson Space 

Center (JSC) with representativesfrom 

NASA Headquarters, NASA field centers, the Department of Defense, industry, and academia to report briefly 

the status of commonality initiatives 

and to determine ways of directing 

attention to commonality on a NASAwide basis. The consensus of the 

roundtable session was that commonality should definitely become a major 

agency concern and that conducting a 

workshop would be a good means of 

providing the proper focus. The participants then assisted in defining the 

initial strategies fortopical content and 

key workshop participants. 

+ 

. 

From June to October, activity concentrated on defining detailed thematic 

content, on structuring the agenda to 

provide an adequate balance of views, 

on securing presenters and panelists, 

and on finalizing the considerable 

logisticsof publicizing, organizing, and 

staging the 3-day conference entitled 

“Workshop on Commonality in Computing for NASA Flight Systems.” 

Because commonality is still perceived 

by many as an abstraction, its interpretation can have many facets, and it is 

difficult to quantify accurately the 

benefits in terms of a well-understood 

econometric model. The problem is 

further compounded because most 

major flight projects have figured separately the costs to implement and the 

costs to maintain. Therefore, a key goal 

make the first step toward translating 

commonality from an abstract concept 

into candidate implementations or 

policy scenarios. 

Nearly400 people attended the workshop on commonality, which brought 

together representatives from government, industry, and academia to share 

views and experiences regarding commonality. The workshop was structured 

toaddress why commonality is needed, 

how standards might apply to commonality, what management issues are 

associated with commonality, and what 

lessons have been learned by those 

of !he ~~rksh~p WGS the atieiiipi iv 

with experience. As would be expected 

of this kind of forum, especially the first 

one that NASA has dedicated to address 

commonality specifically, more issues 

than recommendations surfaced. However, along with the issues came some 

good advice from those who have 

experienced the time when commonality was not a consideration and from 

those who are concerned about the 

future if it does not become one. 

The individual papers and a summary 

of the panel discussions will be compiled for publication to be released in 

early calendar year 1987. Beyond these 

proceedings, however, JSC intends to 

synthesize the issues, to develop and to 

prioritize suggested scenarios for 

addressing those issues, and to brief 

iheseio NASA Headquarters as possible 

implementation approaches across 

programs. 

A key message of the commonality 

workshop was best expressed by a 

workshop panelist who defined commonality as a state of mind or being. It 

must be embraced as an objective, but 

rewards and incentives must be clear 

before it will gain acceptance. For a 

product to achieve commonality and 

widespread acceptance, it must have 

(1) the capability to fulfill a need, (2) 

transportability (commonality) as a 

stated goal, and (3) management committed to it. 

Data and software systems commonality relationships. 

DEVELOPMENT 

ENVIRONMENT 

COMMONALITY .$ 

SOFTWARE 

ENGINEERING 

COMMONALITY 

/, / ALGORITHM 

OSF 65 
Orbital Transfer Vehicle 

Guidance, Navigation, and 

Control System Technology 

TM: Gene McSwain/EHS 

Reference OSF 6 

The next generation of space vehicles 

will include space-based reusable orbital 

transfer vehicles (OTV’s) that employ 

aerobraking to return to low Earth orbit. 

Aerobraking reduces the operational 

costsof an OTV by reducing theamount 

of propellant that must be delivered by 

the Space Shuttle to low Earth orbit. 

The focus of this study, as outlined in 

the following description, is the development of the guidance, navigation, 

and control technology required to 

perform aerobraking returns to the 

Space Station routinely. 

The lift-to-drag ratio (LID) for an 

operational lifting-brake OTV will be a 

critical factor in the vehicle configuration and basic design. A high LID, on 

the order of 0.3, is preferable from a 

guidance standpoint since it provides 

more trajectory control authority during 

the critical phases of aeroassist. Unfortunately, a high LID presents problems 

in terms of vehicle packaging (center of 

gravity location, aerobrake shape) and 

thermal protection because of a high 

angle of attack. Protection of payloads 

from flowfield impingement isalso more 

difficult at large angles of attack. For 

these reasons, it is important that the 

guidance LID requirements be identified. A requirements budget that identifies the impact of error and dispersion 

sources on the required LID has been 

developed. These sources include 

atmospheric variations (density bias, 

shear, etc.), navigation errors, entry 

trajectory perturbations (primarily 

flightpath angle), roll reversal rates and 

accelerations, and uncertainties in 

vehicle aerodynamic properties. 

An operational global positioning system (GPS) will provide spacecraft such 

as OTV’s with the opportunity for very 

precise autonomous navigation. For differential velocity (Av) maneuvers (either 

thrusting or aerobraking), an inertial 

measurement unit (IMU) will continue 

to be required as an attitude reference 

and asa navigation support during translational maneuvers. Highly accurate 

inertial systems that are capable of 

operating for an extended period without 

an external update to support IMU atignment may not be required in the GPS 

era. This reduced requirement should 

lower costs and add to the list of 

potential IMU candidates. 

The primary objective of this study 

task is to determine whether the use of 

GPS and a tracking and data relay 

satellite (TDRS) will permit a relaxation 

of the performance requirements for 

other navigation aids. If GPS and/or 

TDRS can effectively update the IMU 

alignment error estimates, then less 

frequentstellarupdateswill berequired. 

If sufficient coverage is provided by 

GPS and/or TDRS during key mission 

phases, and if the measurement geometry is effective, then the accuracy 

requirementson the IMU may be relaxed 

and the cost may be reduced. 

As part of this study, a linear covariance simulation has been developed 

to study navigation system performance 

on typical OTV mission phases. The 

initial studies will use an inertial navigation system (INS) with performance 

characteristics comparable to those of 

the Honeywell linear INS. In subsequent 

studies, the IMU performance characteristics will be degraded and stellar 

update frequency will be reduced to 

determine the sensitivity of the navigation performance. 

Current spacecraft (particularly manned 

systems) require redundancy in the 

navigation system components. The 

Space Shuttle Orbiters with three gimballed IMU’s and the inertial upper 

stage which uses a five-gyro strapdown 

package are good examples of these 

spacecraft. Fault detection for soft 

failure conditions typically involves 

somesort of voting or midvalueselection 

logic to isolate a faulty component or 

system. This method often involves 

extra redundancy to break a tie between 

two measurements. Consideration has 

been given to using the GPS radio 

navigation to aid the fault detection 

and isolation process (and perhaps 

determine the best performing components in the overall system). Future 

studies will evaluate the use of two or 

three low-cost strapdown inertial systems as a means of providing reliable, 

fault-tolerant navigation. 

, 

* 

GPS-aided navigation for low Earth orbit (LEO) to geosynchronous Earth orbit (GEO) transfer. 

1c /--OTVATGE0 

.MAIN-BEAM DISTANCE 

LIMIT 6 36,000nmi 

\ AV - 7980fth 

H - 150mi 

66 OSF 
Advanced Space Flight 

Simulation Technology 

TM: Kathleen J. Healey/EF 

Reference OSF 7 

An analysis of advanced program 

requirements in the area of expert systems identified several high-potential 

areas for further investigations. These 

areas, in priority order, are (1) expert 

systems that operate in a real-time 

dynamic environment and interface with 

flightcrew and/or flight subsystems; 

(2) expert systems that facilitate the 

development, operation, and configuration management of real-time simulations supporting advanced programs; 

and (3) automated flight system design 

tools. 

Four prototype expert systems were 

developed. and one has been selected 

for furtherenhancement and integration 

in an appropriate environment. The 

prototypes developed were (1) a 

simulation-aided design tool for distributed control of large space structures, 

(2) a simulation configuration expert 

system, (3) an intelligent end effector 

expert system, and (4) a rendezvous 

expert system. 

The simulation-aided design tool for 

distributed control of large space structures allows for rapid prototyping of 

symbolic candidate designs of distributed controllers for attitude and translation of large-scale, flexible structures. 

It has proven to be a powerful and easyto-use tool. The second item, the 

simulation configuration expert system, 

determines optimum configurations for 

thesoftwareof a largesimulation facility. 

An optimum configuration is defined 

as an allocation of software routines to 

processors that satisfies routine frequency requirements and data dependencies and that minimizes the duty 

cycle of the implementation. The third 

item, the intelligent end effector expert 

system, is a collection of expert systems 

for scheduling and controlling a simulated dual arm end effector on line. The 

expert system includes an automatic 

task interpreter and a trajectory planner. 

The rendezvous expert system is a realtime rendezvous procedures generator 

designed to assist the Space Shuttle 

flightcrew during a rendezvous of the 

Space Shuttle with a target such as the 

Space Station. 

The rendezvous expert system has been 

selected for further development and 

integration because it addresses the 

area identified as having the highest 

potential for advanced programs and 

because it takes full advantage of a 

major real-time engineering simulation 

facility that is available to the 

researchers and that providesan excellent environment for integration. This 

facility is the Systems Engineering 

Simulation (SES) Laboratory, which is 

located at the Johnson Space Center 

and is used extensively for real-time 

engineering eval uat i on of advanced 

concepts and for on-orbit procedures 

development and flightcrew familiarization. 

Rendezvous between the Space 

Shuttle and a target is a highly demanding, crew intensive maneuver 

involving multiple Space Shuttle subsystems. When subsystem failures 

occur, a rendezvous maneuver in progress is often aborted. The rendezvous 

expert system is designed to assist the 

crew, to alleviate their workload under 

both nominal and off-nominal conditions, and, in many cases, to generate 

successful procedures for rendezvous 

completion under conditions which 

would currently result in a rendezvous 

abort. 

The prototype rendezvous expert system 

currently addresses selected portions 

of a rendezvous maneuver and is 

integrated with a custom-built simulation OftheSpaceShuttle, itssubsystems, 

and the Space Station. The expert 

system interfaces with the flightcrew 

via a display, which is illustrated in the 

figure. Information available to the crew 

includes advisories that certain subsystems are operating in suboptimal 

modes, descriptions of the current and 

possible next states of the subsystems, 

advice on the optimum next states for 

subsystems requiring state transitions, 

and explanations for the expert system's 

selection of the optimum next states. 

The rendezvous expert system will 

be enhanced and modified for integration with the SES and the SES's Space 

Shuttle aft cockpit. Completion of this 

project will enable engineering evaluations, procedures development, and 

crew familiarization with a real-time 

expert system integrated in an appropriate and realistic environment. 

Information as displayed by the rendezvous expert system. 

ORBITER SUBSYSTEMS STATUS 

DIGITAL AUTO PILOT 

MODE SUB-OPTIMAL 

FUEL LOW 

CONTROL MALFUNCTION 

COMMANDED 

ATTITUDE NO ERROR 

CURRENT-STATE 

SENSORS COAS-SUBOPTIMAL 

LWJ I DAP CONFIG SETTINGS 

GAIN LOW 

RATE-LIMIT LOW 

DEADBAND LOW 

MODE NORMAL 

A SUBOPTIMAL STATE 

(HIGH PRECISION) 

(HIGHER-POWERED JETS) 

CURRENT STATE 

EXPLANATION 

CHANGE DAP CONFIG SETTINGS 

GAIN FROM LOW TO HIGH 

RATE-LIMIT FROM LOW TO HIGH 

DEADBAND FROM LOW TO HIGH 

WILL GAIN 

FUEL-EFFICIENCY 

WHILE SACRIFICING 

PRECISION 

POSSIBLE NON-TIMEOUT TRANSITION 

DAP CONFIG SETTINGS: 

(LOW PRECISION) 

GAIN niGn 

RATE-LIMIT HIGH 

DEADBAND HIGH 

MODE (HIGHER-POWERED NORMAL JETS) 

THE OPTIMAL STATE: 

POSSIBLE NEXT STATE 

OSF 67 
Space-Shuttle-Derived HighAltitude Atmospheric Density 

Model 

TM: Joe D. Gamble/ED3 

Reference OSF 8 

Flight data from theearly SpaceShuttl 

entries indicated significant gradients 

in the atmospheric density profiles in 

the mesosphere region (approximately 

50 to 90 km). Changes in densityof 15% 

to 20% occurring over altitude increments of less than 1 km were observed 

on SpaceTransportation System (STS) 

mission STS-4. Since advanced entry 

vehiclessuch as theaeroassisted orbital 

transfer vehicle (AOTV) will be using 

this altitude region for much of their 

maneuvering, accurate models of the 

atmospheric densityare required. Early 

design studies of the AOTV haveshown 

a particular sensitivity of the guidance 

performance to large density gradients 

occurring overa small altitudevariation. 

It has been difficult in the past toobtain 

accurate measurements of density 

changes over small altitude increments 

near the upper bounds of the mesosphere. Since the Space Shuttle provides 

continuous accelerometer measurements during its descent, it represents 

an ideal test vehicle for obtaining highresolution density measurements. 

68 OSF 

An activity has been established for 

obtaining sufficient high-altitude density 

measurements from the Space Shuttle 

entries to build a statistical data base 

that can be used to improve atmosphere 

models in the mesosphere region. 

Accelerometer measurements from the 

Orbiter inertial measurement unit and 

aerodynamic coefficient identification 

package are used to derive the atmospheric densityalong theentry trajectory. 

Thesedataare compared and correlated 

to density models of various existing 

atmosphere models and to the model 

derived from a best estimated trajectory 

reconstruction of the entry trajectory. 

These analyses are being used to help 

define density dispersions for application in the preliminary design of 

advanced vehicles such as the AOTV. 

A data base has been compiled from 

the first 22 Space Shuttle entry flights 

and will be available for use on IBMcompatible personal computers. Comparison of these data to existing atmosphere models indicates that the Marshall 

Space Flight Center’s global reference 

atmosphere model produces density 

perturbations similar to those observed 

on the Space Shuttle entries when the 

random perturbation option is used. As 

additional Space Shuttle data are 

acquired, a statistical model including 

seasonal and limited latitudinal effects 

will beconstructed and used to evaluate 

existing atmosphere models further. 

Ratio of Space-Shuttle-derived density profiles to U.S. 1976 standard atmosphere for 22 Space 

Shuttle flights. 

M 

E 

S 

0 

S 

P 

ti 

E 

R 

E 

.5 .6 .7 .8 .9 1.0 1.1 1.2 1.3 1.4 1.5 

PIP76 
Lunar Base Missions and 

Opportunities 

TM: Barney B. RobertsfED13 

Reference OSF 9 

The Johnson Space Center (JSC) is 

responsible for the definition of future 

lunar bases. This definition includes 

the missions (i.e., those surface elements or activities that producevaluable 

products, including scientific knowledge), thesurfacesystems that support 

and enable the missions, and the 

required supporting transportation systems. Thus, to be able to define effectively a lunar base and its associated 

surface and space support infrastructure, it is necessary first to generate a 

data base of all conceivable missions. 

In this context, a mission is a single or 

multipurpose objective that has some 

definite end product and that can be 

segregated in some way, usually by a 

piece of hardware that is unique to the 

objective or required for support of the 

objective. Recent studies sponsored by 

JSC have begun to assemble such a 

data base. These studies have resulted 

in the systematic definition, appraisal, 

and documentation of future civilian 

space missions. In particular, efforts 

have focused on defining a complex 

data base of specific missions in terms 

of objectives, infrastructure demands, 

. 

set, it is possible (1) to develop a broad 

range of scenariosforthe future civilian 

space programs that emphasize a singular or multifaceted set of goals and 

(2) to determine infrastructure requirements and associated impacts. 

The lunar base mission data base 

permits record of and access to data 

regarding currently planned missions 

and future opportunities at the Moon. 

At the present time, 72 missions are in 

the mission data base. These missions 

are not acomplete listing of all possible 

advanced spaceactivities; however, they 

are representative of currently planned 

activities and the view of what the 

future might bring, based on inquiries 

with interested membersof thescientific 

cmmuni!y. Each missie!? i!?c!udes!he 

following qualitative and quantitative 

information: (1) brief description of the 

mission; (2) mission objective and 

rationale; (3) benefits and goals; (4) 

specific mission data, including mass 

and volume of equipment, desired orbit 

or location, and estimated start date 

and duration; (5) data and communication requirements; (6) operational and 

servicing requirements; (7) technology 

development status; and (8) cost (mission costs currently are not available). 

A possible martian exploration effort with base elements such as greenhouses, habitat and 

laboratory modules, and transverse vehicles. 

The missions in the data base can be 

divided into five basic types of missions: 

those that (1) utilize lunar resources, 

(2) advance the scientific knowledge 

base, (3) benefit man on Earth, (4) 

develop and demonstrate technologies 

to support the space infrastructure, 

and (5) extend man’s presence in space. 

Future activities will be to develop 

these mission elements and to assemble 

them into ordered sets that reflect a 

particular advocacy or collection of 

advocacies. 

Lunar base mission resource allocation. 

ASTROPHYSICS (15 MISSIONS) 

LIFE SCIENCES (10 MISSIONS) 

MATERIALS AND MANUFACTURING 

PROCESS (21 MISSIONS) 

PHYSICAL SCIENCES (10 MISSIONS) 

POWER AND THERMAL SYSTEMS 

(6 MISSIONS) 

(2 MISSIONS) 

0 PLANETARY EXPLORATION 

COMMUNICATIONS (1 MISSION) 

EARTH OBSERVATIONS (1 MISSION) 

OTHER (6 MISSIONS) 

RESOURCE USE (31%) 

MANNED PRESENCE (3%) 

LUNAR TECHNOLOGIES (15%) 

EARTH APPLICATIONS (1%) 

0 ADVANCED SCIENCE (50%) 

OSF 69 
Laser/Optical/lnf rared 

Communication System 

TM: James C. Lamoreux/EEG 

Reference OSF 10 

Several communications requirements 

forthe Spaceshuttleand Spacestation 

programs can best be satisfied with 

optical techniques. The data transfer 

requirements between the crew cabin 

and the payload bay change as the 

missions and payloads change. Some 

payloads need special accommodations 

requiring additional cable penetration 

through the cabin/payload bay interface. Quantitative physiologicdata from 

crewmembers is required during specified activities. The implementation of 

the collection and communication of 

thesedata toacomputerand/or recorder 

should not interfere with the activities 

of the crewmember. Furthermore, 

secure, reliable, short-rangecommunication links with a high data rate are 

required for proximity operations and 

for robotic applications in both the 

Space Station and the Space Shuttle 

Programs. The objective of this task is 

to develop systems based on laser and 

electro-optic technology that will satisfy 

the unique communication requirements and will enhance NASA missions 

and capabilities planned for the next 

decade. 

The efforts in this project are concent rated on developing configurations, 

techniques, hardware, and flight experiments to provide such capabilities as 

wireless infrared (IR) physiological data 

links; multichannel, wireless IR crew 

communications; free-space laser communication linksfor transmitting voice, 

commands, and data for manned and 

robotic proximity operations and for 

attached or detached payload operations; microwave and/or high-data-rate 

transmission over fiber optics; and 

optical communication through spacecraft windows or across rotating interfaces. 

Substantial progress has been made in 

several of these areas. A two-channel 

simplex IR physiological data link 

system has been completed and demonstrated, and multichannel systems 

for simplex physiological data and 

duplexvoice transmission are now being 

designed and developed. These advanced designs may use fiberopticsas 

passive transmitters and receivers and 

will allow crewmembers to move from 

module to module without losing communications or having to reconfigure 

the communication link. 

A free-space duplex laser communications link has been established and is 

being tested and evaluated. Future 

efforts will concentrate on improving 

performance and adaptability to space 

applications. 

Techniquesfor transmitting high-rate 

data through an aft Space Shuttle 

window have been breadboarded, using 

fiber optics and self-focusing lenses, 

and candidate fiber optic cables and 

connectors are being tested in a 

thermal-vacuum space environment. 

Infrared communications using a multichannel system. 

70 OSF 

I 
Index 
Index 

Reference 

Number 

OSSA 1 

OSSA 2 

OSSA 3 

OSSA 4 

OSSA 5 

OSSA 6 

OSSA 7 

Significant Task 

Office of Space Sciences and Applications 

Life Sciences 

Considerations in the Design of a Health Maintenance Facility for the Space Station 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: James S. Logan/SD2 

Task Performed by: Technology Incorporated Contract NAS 9-1 7200 

Treatment Capabilities for Space Station Health Maintenance Facility 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: James S. Logan/SD2 

Principal Investigator: Michael F. Stolle/SD2 

Task Performed by: Technology Incorporated Contract NAS 9-1 7200 

Computerized Medical Decision Support for the Space Station Health Maintenance Facility 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: James S. Logan/SD2 

Principal Investigator: David V. Ostler/SD2 

Task Performed by: Technology Incorporated Contract NAS 9-17200 

Mechanical Ventilation for Medical Patients Aboard the Space Station 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: James S. Logan/SD2 

Principal Investigators: Bruce A. McKinleyKD2 and Dwayne R. Westenskow 

Task Performed by: Technology Incorporated Contract NAS9-17200 

Princlpa! !nver!iga!r?r: ?!ary h!. Jur!-!?ai!?!SE2 

Lyndon B. Johnson Space Center 

Lyndon B. Johnson Space Center 

Lyndon B. Johnson Space Center 

University of Utah Contract NAS 9-17345 

Lyndon B. Johnson Space Center 

Dynamics of Whole-Body Nitrogen Washout While Breathing 100% Oxygen 

Funded by: Life Sciences (UPN-199) 

Technical Monitors: David H. Horrigan, Jr./SD5 and James M. Waligora/SD5 

Principal Investigators: John H. Gilbert III/SD5 and Benjamin F. Edwards, Jr./SD5 

Task Performed by: Technology Incorporated Contract NAS 9-17200 

Lyndon B. Johnson Space Center 

Clinical Laboratory Capability for the Health Maintenance Facility 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: Bernard J. MieszkudSD4 

Principal Investigator: Karen Gaiser/SD4 

Task Performed by: Northrop Services, Inc. Contract NAS 9-15425 

Lyndon B. Johnson Space Center 

Processing Kit for Microvolume Blood Samples 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: Philip C. Johnson/SD 

Principal Investigators: Theda Driscoll/SD4 and Ron NachtmanISD4 

Task Performed by: Northrop Services, Inc. Contract NAS 9-1 5425 

PR3XXOING PAGE BLANK NOT FILMED 
Reference 

Number 

OSSA 8 

Significant Task 

OSSA 9 

OSSA 10 

OSSA 11 

OSSA 12 

OSSA 13 

OSSA 14 

OSSA 15 

OSSA 16 

OSSA 17 

OSSA 18 

OSSA 19 

Osteo Anal yzer 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: Philip C. JohnsonISD 

Principal Investigator. Adrian D. LeBlanc/SD5 

Task Performed by: Technology Incorporated Contract NAS 9-1 7200 

Helmet for Vestibular Investigations Aboard Spacelab 

Funded by: Life Sciences (UPN-199) 

Technical Monitor: Millard F. Reschke/SB5 

Principal Investigator: Mary Catherine McStravick/SB5 

Task Performed by: Technology Incorporated Contract NAS 9-17200 

Validation of Noninvasive Means of Measuring Central Venous Pressure in Humans 

Funded by: Life Sciences (UPN-199) 

Principal Investigator: John B. Charles/SD5 

Task Performed by: Lyndon 6. Johnson Space Center 

Solar System Exploration 

Lunar Zircons 

Funded by: Planetary Materials (UPN-152) 

Principal Investigator: Charles Meyer, Jr./SN2 

Task Performed by: Lyndon 6. Johnson Space Center 

Composition of Comet Halley Dust Particles 

Funded by: N/A 

Principal Investigator: Herbert A. Zook/SN3 

Task Performed by: Lyndon B. Johnson Space Center 

Evolution of the Archean Mantle 

Funded by: Planetary Materials (UPN-152) 

Principal Investigator: Donald A. Morrison/SN4 

Task Performed by: Lyndon €3. Johnson Space Center 

Spectral Evidence for Hematite on Mars 

Funded by: Planetary Materials (UPN-152) 

Principal Investigator: Richard V. Morris/SN4 

Task Performed by: Lyndon 6. Johnson Space Center 

Monitoring the Earth With Space Shuttle Photographs 

Funded by: N/A 

Principal Investigator: Charles A. Wood/SN4 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Satellite-Derived Leaf Area Index and Vegetation Maps as Input to Global Carbon Cycle Models 

Funded by: Resource Observation (UPN-677) 

Principal Investigator: Gautam BadhwarBN3 

Task Performed by: Lyndon B. Johnson Space Center 

Radiation Environment Models and the Atmospheric Cutoff 

Funded by: N/A 

Principal Investigators: Andrei Konradi/SN3 and Alva C. Hardy/SNB 

Task Performed by: Lyndon 6. Johnson Space Center 

Solar Maximum Mission Satellite and Space Shuttle Orbiter Impact Craters 

Funded by: Planetary Materials (UPN-152) 

Principal Investigator: David S. McKay/SN4 

Task Performed by: Lyndon 6. Johnson Space Center 

Impact Experiments in Reduced-Gravity Environments 

Funded by: Microgravitgy (UPN-674) 

Principal Investigators: Mark J. Cintala/SN12 and Friedrich Horz/SN4 

Task Performed by: Lyndon 6. Johnson Space Center 

Lyndon 6. Johnson Space Center 

74 INDEX 
Reference 

Number 

OSSA 20 

OAST 1 

OAST 2 

OAST 3 

OAST 4 

OAST 5 

OAST 6 

OAST 7 

OAST 8 

OAST 9 

OAST 10 

Significant Task 

Photographic and Television Enhancement ..I Support of the STS 51-L Investigation 

Funded by: N/A 

Principal Investigator: David E. Pitts/SN3 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Lyndon 6. Johnson Space Center 

Office of Aeronautics and Space Technology 

Two-Phase Thermal Management System Component Development 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: R. C. Parish/EC2 

Task Performed by: Sunstrand Energy Systems Contract NAS 9-17195 

Thermal Management for On-Orbit Energy Systems 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: J. G. Rankin/ECP 

Task Performed by: Grumman Aerospace Corporation Contract NAS 9-16781 

Direct Electrolysis of Carbon Dioxide for Oxygen Reclamation 

Funded by: Spa~e iieseaich iiiid Techiiii~gy Base ;UF::-%X; 

Technical Monitor: R. J. Cusick/ECB 

Task Performed by: Westinghouse Electric Corp. Contract NAS 9-17590 

Hypervelocity Impact Studies of Composite Materials 

Funded by: Sapce Research and Technology Base (UPN-506) 

Principal Investigator: J. L. Crews/SNlP 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Testing and Analysis of the Department of Defense Ada Language 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: S. A. Gorman/FR12 

Task Performed by: University of Houston Contract NAS 9-17010 

HAL& lntercenter Board 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: C. D. Sykes/FR24 

Task Performed by: lntermetrics Contract NAS 9-17355 

Human Strength and Motion Modeling 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: B. J. Woolford/SP34 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Crew Station Human Factors 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: J. T. Malin/EF 

Task Performed by: lntellicorp Contract TBD 

Advanced Autopilot Experiment 

Funded by: Space Research and Technology Base (UPN-506) 

Technical Monitor: J. R. WoodfWEX3 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Automated Subsystem Control for Life Support Systems 

Funded by: System Technology (UPN-549) 

Technical Monitor: F. H. Samonski/EC3 

Task Performed by: Honeywell, Inc., Space and Strategic Avionics Division Contract NAS 9-16895 

INDEX 75 
OSF 1 

OSF 2 

OSF 3 

OSF 4 

OSF 5 

OSF 6 

OSF 7 

OSF 8 

OSF 9 

OSF 10 

Reference 

Number 

Sign if ican t Task 

Office of Space Flight 

Satellite Services System 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Gordon Rysavy/EX2 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Telerobotic Work System Definition Study 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Lyle M. Jenkins/EX2 

Task Performed by: Grumman Aerospace Corporation Contract NAS 9-17229 

Rendezvous/Proximity Operations Guidance, Navigation, and Control System Study 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: William L. Jackson/EH24 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Interactive Graphics Control System Design 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Edward T. Kubiak/EH2 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Data and Software Systems Commonality 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Robert G. Musgrove/EH6 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Orbital Transfer Vehicle Guidance, Navigation, and Control System Technology 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Gene McSwain/EH2 

Task Performed by: Charles Stark Draper Laboratory Contract NAS 9-16023 

Advanced Space Flight Simulation Technology 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Kathleen J. Healey/EF 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Space-Shuttle-Derived High-Altitude Atmospheric Density Model 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Joe 0. Gamble/ED3 

Task Performed by: Flight Mechanics and Control, Inc. Contract NAS 9-17394 

Lunar Base Missions and Opportunities 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: Barney B. Roberts/EDl3 

Task Performed by: Battelle Columbus Labs Contract NAS 9-17356 

Laser/Optical/lnlrared Communications System 

Funded by: Advanced Development (UPN-906) 

Technical Monitor: James C. Lamoreux/EE6 

Task Performed by: Lockheed Engineering and Management Services Co., Inc. Contract NAS 9-15800 

Martin Marietta Aerospace Contract NAS 9-17230 

Arthur D. Little, Inc. Contract NAS 9-17335 

McDonnell Douglas Technical Services Co. Contract NAS 9-16715 
1. Report No. 

NASA TM-58277 

12. Sponsoring Agency and Address 

National Aeronautics and Space Administration 

Washington, D.C. 20546 

2. Government Accession No. 3. Recipient's Catalog No. 

1 Technical Memorandum 

4. Title and Subtitle 

Research and Technology 

1986 Annual Report of the Lyndon B. Johnson Space Center 

7. Author(s) 

9. Performing Organization Name and Address 

Lyndon B. Johnson Space Center 

Houston, Texas 77058 

14. Sponsoring Agency Code 

5. Report Date 

December 1986 

6. Performing Organization Code 

8. Performing Organization Report No. 

s-557 

10. Work Unit No. 

569-85-00-00-72 

11. Contract or Grant No. 

13. TvDe of ReDOrt and Period Covered 

15. Supplementary Notes 

19. Security Classif. (of this report) 

Unclassified 

16. Abstract 

Johnson Space Center accomplishments in new and advanced concepts during 1986 are highlighted. 

Included are research funded by the Office of Aeronautics and Space Technology; Solar System 

Exploration and Life Sciences research funded by the Office of Space Sciences and Applications; and 

Advanced Programs tasks funded by the Office of Space Flight. Summary sections describing the role of 

the Johnson Space Center in each program are followed by one-page descriptions of significant projects. 

Descriptions are suitable for external consumption, free of technical jargon, and illustrated to increase 

ease of comprehension. 

20. Security Classif. (of this page) 

Unclassified 

17. Key Words (Suggested by Author(s)) 

Research and Technology 

R &T 

RTOP 

Advanced Programs 

18. Distribution Statement 

Unclassified - Unlimited 

Subject Category 99 

I 21. No. of Pages 

72 I 

22. Price' 

I I I 

'For sale by the National Technical Information Service, Springfield, Virginia 22161 

U. S. GOVERNMENT PRINTING OFFICE 1987-761-013/40572 

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