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OCT 26 1998 13:01 FR PT DIVISION OFFICE 281 483 9988 TO 873016210162 P.01/01 

REPORT DOCUMENTATION PAGE Form Approved 

OMB No. 0704-0188 

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1. AGENCY US! ONLY (Leave Blank) I :z. REPORT DATE 

August 1998 

,3. ru;r-vrot 1 lYPE ANO TES COVERED 

TecblUtal~cClorandunt 

4. TITU! AND SUBTITLE 5. FUNDING NUMBERS 

Johnson Space Center Research & T~hnoloe)' 1997 Annual Report 

6. AUTHOR(S) 

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZAnON 

REPORT NUMBERS 

Lyndon B. Johnson Space Center 

Houston, S-830 Texas 770S8 

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORING 

AGENCY REPORT NUMBER 

National Aeronautics and Space Administration 

Washinston, D.C. 20546-0001 TM·l998-104827 

11. SUPPLEMENTARY NOTES 

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Unclassified/Unlimited 

Available from the NASA Center for AeroSpace Information (CASI) 

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(301) 621-0390 Subject Category: 99 

13. ABSTRACT (Maximum 200 words) 

This report highlights key projects and technologies at Johnson Space Center forl997. The report focuses on the ~mmerclal 

potential of the projects and technolosies and is arrinied by CorpTech Major Products Groups. Emerging technoloaies In these 

major disciplines are swnntari.zed: solar system sciences, life sciences, technolo;y transfer, ~mputer sciences, space 

tecbnolol)', and human support technoloi}'. These NASA advances have a range of potential commereial applications, from a 

school internet manager for netWorks to a. liquid metal mirror for optical measurements. 

For general commertial information or commercialization information about a specific tehcnolo,y, contact the NASA JSC 

Office of Technology Transfer and Commercialization at: NASA JSC, mail code HA, 2101 NASA Rd 1, Houston, TX., 

770SS·3696; Tel: (281) 483·3809; Fax: (281) 244·84S2; E-mail: commercialization@jsc.nasa.iov; Web page: 

http://tcchnoloi)'.jsc..nasa.aov 

14. SUBJECT TERMS 

Research Projects, Research and Development. NASA Programs, Technology Utilization, 

Space TechnoloJY Experiments 

11. ~'"r:.~'!I!!.~LASSII"ICATION 

OF REPORT 

18. ~~~RITY CLASSIFICATION 

OFTHISPAGE 

18. ~~C~F~ITY ~~SSlt·ICATION OF ABSTRACT 

Unclanified Unclassified Unclassified 

Standard P:orm 298 (Rev Feb 89) ( rm II s.o-o 5 

, 5. NUMBER OF PAGES 

93 

16. PRICE COOl! 

20. LIMITATION OF ABSTRACT 

Unlimited ·- __ .... {: 

Pr.oai'*l ~ANSI S1CI. 23&-18 

211-102 

---· 
-~I i 
Johnson Space Center 

NASA Technical Memorandum 104827 

Johnson Space Center 

Research and 

Technology 

Annual Report 1997 
Tl. 
Johnson Space Center 

Foreword 

The 1997 NASA Johnson Space Center Research and Technology report highlights key projects and technologies 

at Johnson Space Center throughout 1997. This year, special attention is given to the commercial potential of these 

projects and technologies. With that in mind, this report is arranged by CorpTech® Major Product Groups. 

For additional technical information on a particular project, contact the technical point of contact listed at the 

bottom of each page. For general commercialization information or commercialization information about a specific 

technology, contact the NASA-JSC Office of Technology Transfer and Commercialization at: NASA/JSC, Mail Code 

HA, 2101 NASA Rd L Houston, TX 77058-3696. Tel: (281) 483-3809, Fax: (281) 244-8452, E-mail: 

commercialization@jsc.nasa.gov, Web page: http://technology.jsc.nasa.gov. 

111 
II 
Johnson Space Center 

Contents 

Foreword ................................................................................................................................................................................................................................... iii 

Automation 

Automated Control Center Demonstration Project (ACCDP) .................................................................................................................................................... 3 

Improved Human Productivity in Advanced Life Support ......................................................................................................................................................... 5 

Robonaut ..................................................................................................................................................................................................................................... 7 

RMS Assistant Project ................................................................................................................................................................................................................. 9 

Chemicals 

Zeoponic Plant Growth Media Research and Development 

Computer Hardware 

11 

Field Deployable Trainer ............................................................................................................................................................................................................ 13 

Computer Software 

A Computational Fluid Dynamics/Direct Simulation Monte Carlo Analysis ........................................................................................................................... 15 

Advanced Training Technologies .............................................................................................................................................................................................. 17 

Cooperating Expert System (CoopES) ...................................................................................................................................................................................... 19 

Electronic Documentation Project (EDP) ................................................................................................................................................................................. 21 

Extravehicular Activity (EVA) Display Assembly .................................................................................................................................................................... 23 

Human Interaction Design for Cooperating Automation and Anomaly Response Systems ..................................................................................................... 25 

High Volume Data Management (HVDM) ............................................................................................................................................................................... 27 

Information-Sharing Protocol (ISP) Technology ...................................................................................................................................................................... 29 

Intelligent Computer-Aided Training Tool Development ......................................................................................................................................................... 31 

Intelligent Flight Activity Planner (IFAP) ................................................................................................................................................................................. 33 

Internet Library Information Access Device ............................................................................................................................................................................. 35 

School Internet Manager Over Networks .................................................................................................................................................................................. 37 

Effects of Lighting on Human Performance in Training ........................................................................................................................................................... 39 

SINDAIFLUINT Version 3.2 .................................................................................................................................................................................................... 41 

Space Operations Intelligent Computer Aided Training (ICAT) ............................................................................................................................................... 43 

Simulation Virtual Machine (SVM) .......................................................................................................................................................................................... 45 

Thermal Synthesizer System, Version 6.0 ................................................................................................................................................................................. 47 

Shared Virtual Environments for Team Training ...................................................................................................................................................................... 49 

Visual Proximity Operations Processor (VPOP) ....................................................................................................................................................................... 51 

v 
Energy 

Electtohydrodynamic Heat Pipe Loop Studies 

Electrolysis Performance Improvement Concept Study (EPICS) Flight Experiment 

New Lithium-BCX D Cell Development for Flight Applications 

Solar Heat Pump Development 

53 

55 

57 

59 

Environmental 

Advanced Technology Space Suit 61 

Lunar-Mars Life Support Test Project 63 

Medical 

Multi-Channel BioLog With FETRODES 65 

Telecommunications 

Autonomous Exttavehicular Robotic Camera (AERCam) Il Integrated Ground Demonstration 

Autonomous Extravehicular Robotic Camera (AERCam) Sprint 

Globally Interconnected Advanced Network Telepresence (GIANT) 

67 

69 

71 

Test and Measurement 

Flammability Testing of Composites Using Cone Calorimetry ................................................................................................................................................. 73 

Fluid Flow Measurements Using Series Probes ......................................................................................................................................................................... 75 

Fluid Flow Volume Measurements .............................................................................................................................................................................................. 77 

Insttumented Mechanical Impact Test (IMIT) Facility .............................................................................................................................................................. 79 

Liquid Metal Mirror for Optical Measurements of Orbital Debris ............................................................................................................................................ 81 

Regolith Evolved Gas Analyzer (REGA) ................................................................................................................................................................................... 83 

Camera Irnages From Luminance Maps .................................................................................................................................................................................... 85 

Transportation 

Variable Specific Impulse Magnetoplasma Propulsion 

X-38 Project 

VI 

87 

89 

~--· -

-

2 Automation 

ACCDP/GNC Operations Assistant 

System Architecture 

~-------------------t 1GNC Asce-nt 1: 

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1111: : i 

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11 Jl 

1111 

Automation of the GN&C Flight Control Task 

,__ 

~ 
Johnson Space Center 

Automated Control Center Demonstration Project (ACCDP) 

Benefit 

The ACCDP is demonstrating the feasibility of control center automation in support of human space flight. Automation of Mission 

Control Center (MCC) flight control tasks will result in decreased cost and improved employee utilization and will enable an office/home 

multipurpose support room (MPSR) allowing consolidation/reduction of flight control room (FCR) positions. It is anticipated that 

implementation of operations automation for International Space Station will result in even higher savings. The first task undertaken by the 

project is automation of the guidance, navigation and control (GNC) flight control task (GNC Operations Assistant). 

The GNC Operations Assistant will operate as an intelligent operations assistant for the GNC flight control position. The GNC 

Operations Assistant will interact as a flight control team member with the goal of automating GNC tasks to the highest degree that is 

reasonable. The GNC Operations Assistant will manage applications and data analysis, make recommendations to on-console flight 

controllers, and prepare and maintain required routine documentation. 

Accomplishment 

Completed task analysis of selected Shuttle flight control positions, GNC selected as first position to prototype since it provides a 

challenge and is typical of other FCR positions. The GNC Operations Assistant is being developed for release in early calendar year 1998. 

Identified key technologies critical for MCC automation development and have established interfaces with key research and development 

institutions technology infusion support. 

Background 

ACCDP is a new project started in fiscal year 1997 to test new and commercial technology for infusion into the MCC, to demonstrate 

new smart displays and intelligent system monitoring, to provide a baseline to build a life cycle cost and schedule assessment for full-scale 

deployment, and to prototype new operations concepts and flight control team organizational structures. Current focus is on a GNC 

Operations Assistant and Office/Home MPSR. 

For further technical information, contact Mitchell Macha at (281) 483-7059 or mitchell.g.macha I @jsc.nasa.gov 

Automation 3 
Crew Tasks 

Manual Labor 

Crew Knowledge 

Crew Cognitive/ 

Action Tasks 

Computer-Based Assistance 

Robotics 

Knowledge System 

(Advanced Life Support Syst,em 

Engineering Environment) 

Intelligent 

Monitoring and 

Control 

Improved Human Productivity in Advanced Life Support Systems Through Use of Sensors, 

Computers, and Actuators 

4 Automation 

~ 
Johnson Space Center 

Improved Human Productivity in Advanced Life Support 

Benefit 

By eliminating the need for crew and test engineer/ground personnel to monitor and control life support systems or perform manual labor 

during nominal operations, and by minimizing crew and test engineer/ground personnel interaction for off-nominal operations of selected 

subsystems/automation in response to anomalies, crew time is freed for science and engineering/technology objectives on human space 

exploration missions beyond Earth orbit, operations costs are greatly reduced, crew safety is improved, and human productivity is greatly 

increased. 

Accomplishment 

The Automation, Robotics, and Simulation Division performed a successful demonstration of reduction of crew time or test engineer/ 

operator time to near zero for operations oftwo regenerative life support systems through implementation and test during the Lunar-Mars Life 

Support Test Project of crew-adjustable autonomous intelligent monitoring and control for: 

o Product Gas Transfer-Transferring oxygen generated by crop growth in one test chamber to another where four human test subjects 

were using the oxygen in their activities and generating carbon dioxide for transfer to the crop growth chamber. 

o Variable Pressure Growth Chamber Monitoring Robot-Making measurements at multiple locations in the crop growth chamber of 

light for photosynthesis, air temperature, humidity, air speed, leaf temperature, in addition to recording video camera views of the 

nealth of the crop. 

The success of these regenerative life support systems applications of autonomous monitoring and control is a stepping stone to full-scale 

deployment of autonomous monitoring and control in the upcoming, high-fidelity NASA Bioregenerative Planetary Life Support Systems Test 

Complex (BIO-Plex), which involves human tests for periods up to 425 days. 

Background 

Long-duration human exploration space missions require regenerative life support systems that are nearly self-sustaining. The NASA 

Advanced Life Support Program addresses this need. Activities in this program include the Lunar-Mars Life Support Test Project and the 

BIO-Plex design and implementation. The Crew and Thermal Systems Division is the NASA Advanced Life Support Program Lead Center 

Program Office. JSC's three-tiered intelligent systems architecture provides a generic approach to achieving flexible autonomy of computercontrolled machines, giving humans supervision by exception through shared and traded control, supported by situation awareness information. 

For further technical information, contact Cliff Farmer at (281) 483-9529. 

Automation 5 
-

Robonautics 

For further technical information, contact Karl Zimmer at (281) 483-1718 or karl.j.zimmerl @jsc.nasa.gov 

6 Automation 
Johnson Space Center 

Robonaut 

Benefit 

The technology which can replicate the human's dexterity and perception capabilities is very immature at this time. The ""dexterous" robots 

which exist today on earth or are slated for on-orbit use in the near future (i.e., the International Space Station, or ISS) require a large amount of 

accommodation (special targets, special structural interfaces, etc.) from their host system and thus can only be used to replace the human at the 

worksite for a limited set of specially designed tasks. They are also too large to fit through tight extravehicular activity (EVA) access corridors and do 

not possess adequate speed and dexterity to handle small and complex items, or soft and flexible materials, or even common EVA interfaces. 

Furthermore, the teleoperator controls for these robots, which consist of flat panel displays and joystick-like hand controllers, are grossly inadequate 

for coordinating the high level of dexterity inherent in complex EVA tasks. 

The Robonaut project selected a dexterous robotic hand, as the sole interface tool, over multiple limited-use tools. Robotic hand advantages 

over multiple changeout tools include reduced weight, volume, and-since tool changeout is not needed-reduced task timelines. Additionally, the 

robotic hand concept can be adapted to new and unplanned interfaces without requiring development of a new tool. The robotic arms are sized to fit 

through tight EVA corridors and have the strength and dexterity of an EVA astronaut. The telepresence system provides an easily learned interface that 

allows intuitive control of all degrees of freedom. 

Accomplishment 

The Robonaut Project team has developed a design concept which calls for two 7-degrees-of-freedom (DOF) arms, two 12-DOF multifinger 

robotic hands, and a 3+ DOF stereo camera platform. The dexterous hand module has a 12-DOF dexterous hand and 2-DOF wrist. With four fingers 

and a thumb in a human hand-like arrangement, it will emulate. as a minimum, a suited crew member's reach and dexterity, as according to NASA 

STD-3000; JSC-26626, "EVA Hardware Generic Design Requirements Document"; and SSP-4162. "U.S. On-Orbit Segment Specification." The 

robotic hands are designed to handle common EVA tools, such as an ORU handling tool (a.k.a. "ice cream scoop"), to grasp irregularly shaped objects, 

and to handle a wide spectrum of tasks requiring human-like dexterity. The first prototype of this design is nearing completion and will be tested later 

this year. The design of the 7-DOF arms provides the size, strength, and range of motion of an EVA astronaut. The 7-DOF arm design, a 5-DOF 

segment+ a 2-DOF wrist, is undergoing detailed joint design, and bench testing will be completed this year. The complete arm fabrication, assembly, 

and testing is scheduled for next year. 

The Robonaut will be initially operated using telepresence equipment. such as a head-mounted display. body-mounted position sensors, positionsensing gloves, or force-reflective arm and hand masters. Future developments call for embedding subconscious or reflexive behaviors to free up 

operators from the lowest levels of control. Robonaut I (FY97 -98) is developing an integrated dexterous arm-hand module evaluated against a set of 

one-handed EVA tasks. Tasks performed will be beyond capabilities of current space-based dexterous robots and will not require the use of specialized 

robotic interfaces. The evaluation includes the following tasks: manipulate EVA tether hooks, install and remove portable foot restraints, pull Velcro 

tabs to remove multilayer insulation, mate and demate electrical connectors, and grasp and actuate ORU handling tools. The performance metric will 

be to complete these tasks in less than twice the time it would take an EVA-suited astronaut. 

Background 

ISS will rely significantly on robotics for external maintenance. The tasks have been specifically designed with interfaces compatible to 

existing robotic systems interface standards (RSIS Vol. II). However, there still exists a significant workload for EVA astronauts that is not compatible 

with the existing robotic systems on ISS. The Automation. Robotics, and Simulation Division at JSC has previously developed the laboratory-based 

dexterous anthropomorphic robotic test bed (DART) and the full immersion telepresence test bed (FITT). The DART/FITT system proved capable of 

performing operations with EVA hardware not designed for robotic interface. Further, two-handed operations with flexible materials, such as tying a 

knot in a rope, have been performed with increasing simplicity over time. By identifying the need for more capable robots and human interface, and 

combining it with previous experience with DART/FITT. the Robonaut concept has been developed. 

Automation 7 
00 

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3 

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II 
Johnson Space Center 

RMS Assistant Project 

Benefit 

The Remote Manipulator System (RMS) Assistant is a forerunner project to prove technical feasibility and cost-effectiveness of reducing 

the workload of the crew and flight controllers through automation. This project focused on the development of an intelligent software 

approach to monitor/advise real-time crew operations, to provide various levels of automation, and to provide automated tools for the flight 

controller to collect, retrieve, and analyze mission data. In addition, a reusable automation architecture was developed to support not only the 

RMS operations but also other Orbiter subsystems. 

Accomplishment 

The RMS Assistant project has successfully demonstrated three objectives: develop a reusable automation architecture, ease crew 

operation, and enhance flight controller tools. The system will not only improve situational awareness and assist the crew, but will also provide 

flight controllers with automated tools to improve flight operations efficiency. Examples of these enhanced capabilities for both the flight 

controllers and the crew include "smart" malfunctions, procedure tracking and verification, and automated situation assessment. 

The system was designed so that the above-mentioned functions are searnlessly integrated in a distributed processing architecture. The 

system health monitoring module automatically detects and recommends a malfunction procedure block based on the current procedure context 

and assigns a priority tag and sends it to the procedure tracking and verification (PTV) module. The PTV module switches from the current 

procedure, and starts to monitor and verify the highest priority malfunction. In parallel, there is an intelligent situation capture module that 

collects and stores information relevant to the ongoing activity. The situation objects not only capture and assemble the data in a chronological 

matter, but also organize the data into a hierarchical relational network such that the information can easily be accessed and retrieved for nearreal-time analysis. This architecture was also designed to support various degrees of automation: If computer command and control 

capabilities are accessible and permissible, the user will be able to select fully or partially autonomous modes of operations. Otherwise, the 

system operates in manual modes where the intelligent software assists (monitors/advises) the crew in performance of tasks. 

Background 

There is great emphasis on upgrading the Space Shuttle Orbiter to reduce costs and prolong its use beyond the year 2012. The RMS 

Assistant project was intended to provide a proof of concept of an automation approach not only for RMS operations but also for other Orbiter 

subsystem operations. This type of automated support capability would significantly improve safety by providing the crew with additional 

insight information and cut the costs of operating the Orbiter by reducing ground control operation involvement during routine operations. 

For further technical information, contact Lui Wang at (281) 483-8074 or lui.wangl @jsc.nasa.gov 

Automation 9 
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Johnson Space Center 

Zeoponic Plant Growth Media Research and Development 

Benefit 

Long-duration space missions will require life support systems that are capable of providing air, water, and food to human crews over 

long periods. A large component of such systems will be plants. Plants will not only be a source of food, but will also play a major role in air 

revitalization and water recovery. NASA scientists are developing substrates as a highly productive, simple plant growth medium capable of 

growing selected food crops for use in a regenerative life support system. These substrates, called zeoponics, have demonstrated excellent 

potential for growing plants in space-based life support systems. 

Accomplishment 

Zeoponic substrates are being developed to support plant growth for advanced life support systems in ground-based test beds and for 

flight experiments on both the Space Shuttle and the International Space Station. Zeoponics materials have been used to grow wheat with 

comparable production of wheat grown in an inert matrix with nutrient solution applications. The first Space Shuttle flight (STS-60) 

experiments with zeoponics verified its mechanical properties for air and water movement. In a second Space Shuttle (STS-63) flight 

experiment, wheat and bra~sica plants were grown in microgravity for eight days. During the flight the wheat grew about 12 em in height and 

the brassica plants, which were planted prior to launch, continued to develop flowers and set seeds. 

Zeoponics media are being developed and tested for use in the International Space Station Plant Research Unit. Two patents were 

granted, and NASA has negotiated with two companies for co-exclusive licensing rights. Additionally, researchers at Johnson Space Center 

worked with the Tennessee Valley Authority's Natural Fertilizer Development Center and the International Fertilizer Development Center to 

develop methods to pelletize and granularize the synthetic apatite to improve its dissolution characteristics. 

A laboratory-scale pilot plant was developed to increase Johnson Space Center's capability to produce zeoponics media for flight and 

ground-based testing and commercialization requirements. The rate of production of synthetic apatite was increased a hundredfold; the rate of 

production of saturated zeolite was increased tenfold. 

Experiments conducted on the zeoponic substrates included verification of nutrient loads on the matrix as well as plant growth 

experiments to evaluate performance. Experiments were completed that evaluated plant growth in second-generation (second major 

reformulation) and third-generation zeoponic media using agronutrient-substituted hydroxylapatites. Additional experiments have been 

initiated to examine the moisture status of zeoponics media in terms of supplying water and nutrients to plants. 

Background 

Zeoponic substrates are made up of a combination of zeolite minerals and a synthetic calcium phosphate mineral (synthetic apatite). 

Zeolites are crystalline, hydrated minerals that contain loosely bound ions within their crystal structures. Synthetic apatite has several essential 

plant growth nutrients incorporated into its structure. Zeoponics have been designed to slowly release these plant growth nutrients into "soil" 

solution where they become available for plant uptake. Ion composition and pH are thus passively controlled by the chemistry of the medium. 

The zeoponic substrate system requires only water, which can be applied by a static watering system that uses the natural matric suction of the 

medium as the driving force for water flow. 

For further technical information, contact Don Henninger at (281) 483-5034 or donald.l.henningerl @jsc.nasa.gov 

Chemicals 11 
-

N 

Tl 
Johnson Space Center 

Field Deployable Trainer 

Benefit 

Cost effective: In many instances, instructorless training can be cheaper than instructor-led exercises. 

Better: lnstructorless training can be much more effective. since it is self-paced and available 24 hours per day. Repeated return to the 

material for review has no additional cost. Instructorless training can ensure consistency in the presented material across the entire student 

population. 

Training material delivery: The costs for delivery of computer-based training lessons on CD-ROMs, when mass produced, are 

significantly less than even a black & white training manual, as little as $1 per article. 

Accomplishment 

To date, 3 customized deliveries of an integrated software package including CD-ROMs have been provided and flown on 3 separate 

NASNMir missions. In excess of 20 computer-based training lessons have been developed, and multiple custom software tools have been 

developed. Support for the remaining NASNMir missions has been initiated, and new areas of development are in work. 

Background 

The first prototype field deployable trainer, the Crew On-Orbit Support System (COSS). is an operational system currently in use on 

board the Russian Space Station Mir in support of the American astronaut. The COSS provides psychological support, real-time support tools, 

and on board refresher & proficiency maintenance training. All integration & development of the products are done at much lower cost than 

previous flight software and training products. By providing in situ instructorless training, mission success is enhanced. Cost-effectiveness is 

achieved by using commercial-off-the-shelf software and hardware products for product development. 

For further technical information, contact Sean Kelly at (281) 244-7484 or sean.m.kelly 1 @jsc.nasa.gov 

Computer Hardware 13 
CFD Predicted Number Density Contours 

Axisymmetric PRCS plume 

7 

oo 2 4 6 8 10 

Distance in meters 

DSCM prediction of Number Density - Inner Domain 

Breakdown 

Number Density 

3.21E19 

2.470E19 

1.580E19 

·--~ 9.6652E18 

6.231E18 

' 3.937E18 

2.487E18 

'' 1.571E18 

8.830E17 

6.274E17 

3.964E17 

2.504E17 

1.582E17 

1E17 

Number Density 

1.00E22 

7.94E21 

6.31E21 

5.01E21 

3.96E21 

3.16E21 

::1 ~~~~i 1.59E21 

1.26E21 

1.00E21 

7.94E2D 

6.31E20 

5.01E20 

3.98E20 

3.16E20 

2.51E20 

Iii 2.00E20 

1.58E20 

1.26E20 

1.00E20 

y 

l)._. 

Inner domain size: 16 by 6 by 6 meters 

14 Computer Software 

CFD-Predicted Number Density Contours for 

Axisymmetric PRCS Plume 

DSMC-Predicted Number Density Contours for 

Axisymmetric PRCS Plume 

~ 
Johnson Space Center 

A Computational Fluid Dynamics/Direct Simulation Monte Carlo Analysis 

Benefit 

An accurate understanding of plumes and plume impingement during Orbiter docking is critical to the success of the Shuttle/Mir 

missions and the International Space Station (ISS). The three-dimensional flow fields generated during these types of missions will be 

complex, spanning flow conditions from continuum to rarefied. The computational fluid dynamics/direct simulation Monte Carlo (CFD/ 

DSMC) capability represents an important tool for engineering analysis for these missions. Ambitious application of these techniques fostered 

the development of an enhanced capability as well as a base of extremely intensive computations. 

Accomplishment 

High-fidelity numerical analyses of plume and plume impingement flow fields are performed to support the design of Shuttle Orbiter 

docking approaches to the Mir and ISS. These analyses will help to avoid placing adversely high loads on fragile ISS components such as solar 

panels and radiators. Another advantage of these analyses is that their complexity pushes the limits of applicability of the employed 

methodologies and drives the development of enhancements such as implementation on massively parallel super computers. The development 

of a highly accurate tool for benchmarking the pressure and heating loads on solar panels and radiators produced from Orbiter primary reaction 

control system engine firings is complete, and efforts are under way to adapt the tool to other applications such as human missions to Mars. 

Background 

While plume impingement problems are certainly not new to spacecraft operations, the Shuttle/Mir missions represent extremely 

ambitious docking maneuvers. This results from the high thrust (870 lbs) of the engines, the large masses of both the Orbiter and the Mir, the 

large surface area of Mir's solar panels, the requirement for primary reaction control system firings when the two spacecraft are at close range, 

and the complex three-dimensional nature of the plume flow fields generated by nozzle scarfing and dual jet firings. Because these dockings 

are inherently complex, scientists need to understand on-orbit plumes and the resulting plume impingement forces and heat loads to a degree 

never before required. 

Because of the large changes in flow field densities, the basic physics of the problem changes from one area of the flow field to another. 

This fact greatly increases the difficulty of the analysis and must be accounted for in the analysis procedure. In addition. the procedure must 

account for the challenges presented by the complex geometries encountered as well as the inherent three-dimensional nature of the flow. 

High-fidelity analysis of gas flows is generally done by numerically solving a set of governing equations subject to boundary constraints. 

For most analyses, referred to as computational fluid dynamics, the Navier-Stokes equations are employed as the governing equation set. 

However, Navier-Stokes equations are valid for continuum flows but not for rarefied gas flows where the fundamental physics differs. For 

these, the Monte Carlo method has proven to be the most versatile, accurate, and efficient method for high-fidelity flow analysis. This method 

differs from computational fluid dynamics because it simulates the behavior of gas molecules, rather than solving a governing set of partial 

differential equations, by using simulated molecules which move and interact with solid surfaces in a way which can be predicted by each 

molecule's velocity vector. Collisions among molecules, however, are treated probabilistically through the use of a Monte Carlo technique 

conceived by Bird which is based on fundamental concepts of kinetic theory. The accuracy and efficiency of this approach have been 

demonstrated and are well understood. 

For further technical information, contact Forrest Lumpkin at (281) 483-2955 or forrest.e.lumpkin 1 @jsc.nasa.gov 

Computer Software 15 
Virtual ISS 

Lab Module 

Two Virtual Astronauts Participating in a Cooperative Task On Board the 

Human Research Facility Module 

16 Computer Software 

-
Johnson Space Center 

Advanced Training Technologies 

Benefit 

Virtual environments (also known as virtual reality) serve to enhance the effectiveness, broaden the availability, and reduce the cost of 

ground-based training. Further, these same technologies, delivered on-orbit, can be used to provide "just-in-time" training for both in-flight 

maintenance operations and the conducting of in-flight scientific experiments. The application of these technologies brings uniformity and 

verifiability to training, increasing safety and the probability of mission success. In addition to training, the potential of virtual environments to 

aid in the visualization of scientific and engineering data is tremendous. 

Accomplishment 

The Virtual Environment Technology Laboratory (VETL) has demonstrated success at sustaining and enhancing ongoing efforts to 

develop and deploy virtual environment technology for use by NASA in training and data visualization. For example, a prototype shared 

virtual environment for training International Space Station crews in the operation and maintenance of science experiments has been 

successfully demonstrated. Additionally, the Laboratory has already had extraordinary success in catalyzing the transfer of NASA-developed 

technology into the private sector in the areas of oil exploration, education, and medicine. 

Background 

In 1995, NASA and the University of Houston executed a Space Act Agreement to establish a joint VETL. The primary objectives of the 

VETL are to develop and deploy enabling technologies that support the building of training and data visualization applications that utilize 

virtual environments and intelligent computer-aided training technology. 

For further technical information, contact Susan Tomey at (281) 244-7486 or susan.e.tomeyl @jsc.nasa.gov 

Computer Software 17 
Antenna Management 

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18 Computer Software 

EECOMRCRS -

RMS Situational Awareness Display 

Examples of CoopES for Flight Control 

PCPOCC 
Johnson Space Center 

Cooperating Expert System (CoopES) 

Benefit 

The cost of ground support of human space operations can be significantly reduced by modernizing mission control facilities and 

introducing automated technologies. The CoopES project applies modem software technologies to mission support applications software. It 

exploits distributed computing infrastructures to (l) apply new and commercial technologies to mission operations, (2) design cooperating 

intelligent systems, and (3) implement certified software applications which solve specific flight support problems and reduce operational 

costs. 

Accomplishment 

Several new and enhanced capabilities were completed in fiscal year (FY) 1996 and integrated into the Johnson Space Center (JSC) 

Mission Control Center (MCC) for use by the flight control team during shuttle operations. The new software capabilities delivered for FY96 

included the Emergency, Environmental, and Consumables Manager (EECOM) Regenerative C02 Reduction System (RCRS), the Flight 

Dynamics Officer Auto Deorbit Landing Pad, and an extravehicular mobility unit PC-based telemetry logger. The new hardware/software 

capabilities delivered for FY96 were the PC Payload Operation Control Center (POCC) payload decommutation server. The enhanced 

software capabilities delivered for FY96 included the Instrumentation and Communications Officer (IN CO) Antenna Management and the 

INCO Operational Instrumentation Monitor which included the Data Signal Conditioner. Also, during FY96, CoopES commenced 

development of the Remote Manipulator Subsystem (RMS) Situational Awareness Display. The CoopES project is facilitating the 

consolidation of flight controller positions. 

Background 

The CoopES project was initiated to facilitate the infusion of technology into the MCC to enable JSC to carry out flight operations more 

effectively and efficiently. The project team works directly with the flight control team to identify specific flight support problems, identify 

technologies that most effectively provide the needed capabilities, and deliver certified software which solves the problem. 

For further technical information, contact Mitchell Macha at (281) 483-7059 or mitchell.g.machal @jsc.nasa.gov 

Computer Software 19 
20 Computer Software 

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Johnson Space Center 

Electronic Documentation Project (EDP) 

Benefit 

The complex nature of space flight systems and operations demand a robust capability for construction, organization, and control of very 

large amounts of information. This information is created in a variety of ways and on a number of platforms, but has a common need for 

organization, rapid access, non-linear traversal, and a high degree of configuration control. The EDP system is designed and implemented 

specifically with these requirements in mind. The look and operation of the document viewer is the same across platforms. This has eased the 

transition into the use of electronic books, as users must only learn one application for all of the different types of books in the library, and can 

take that same knowledge and experience with them across platforms and environments. The user of the EDP tools, whether in the office or on 

console, has access to the same document and annotation files. 

Accomplishment 

No spaceflight operation has been conducted out of the new Johnson Space Center Mission Control Center (MCC) without full library 

and real-time operations use and support by EDP. The library of supported books includes the Flight Data File, Flight Rules, Space Shuttle 

Systems Handbook drawings, MCC operations notes. and console handbooks. To date, the operational library contains over 750 books, not 

including those archived from past flights. Over 2500 book translation jobs have been executed in the MCC, and normal document turnaround 

in the library is less than one hour. replacing turnaround of several hours at a reproduction facility or several days at a print shop. 

Background 

The EDP concept was to develop an innovative approach to injecting electronic book technology into the operations environments of the 

Johnson Space Center. The system wa.<; to provide an electronic capability to display, distribute, and control crew/ground controller procedures 

and documentation. The system had to broadly accept document input from a variety of sources. It had to integrate cleanly into a pre-existing 

infrastructure both within the MCC and the Johnson Space Center office systems. The system had to be highly secure, with protection for not 

only its own data and systems, but also for those to which it was connected. Yet the security had to be implemented in a manner so as not to 

inhibit the system utility to users. The EDP system had to support users on a variety of hardware platforms and software operating systems, yet 

maintain the same functional "look and feel" across these platforms so as to minimize the training and transition impacts to each of these 

platforms. 

For further technical information, contact Tony Griffith at (281) 244-5813 or anthony.d.griffith 1 @jsc.nasa.gov 

Computer Software 21 
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Extravehicular Activity (EVA) Display Assembly 

Benefit 

Unlike the paper cuff checklist that is compiled months in advance of a Space Shuttle mission. the International Space Station (ISS) 

scenarios require the capability for real-time procedure modifications to address ongoing, changing tasks. The information stored electronically 

in the EVA display computer will provide the astronauts with updated procedures necessary to perform the required task during a spacewalk. 

In addition, the EVA display assembly will provide the astronauts with the flexibility of electronically receiving real-time procedure updates 

and/or video necessary to complete their tasks. 

Accomplishment 

The EVA display assembly is a redesign of the electronic cuff checklist, which failed to meet the requirements for future use on ISS. The 

EVA display assembly comprises two parts: the EVA display is a device designed to attach to the glove gauntlet of the U.S. extravehicular 

mobility unit (EMU), and the EVA display computer contains the processing and data storage hardware. The EVA display assembly will 

provide the EVA crew members with all of the text and graphical data necessary to complete their required tasks, with the additional capability 

of storing caution and warning data from the spacesuit or other future hardware. In addition, it is also capable of supporting video, either from 

video clips stored in memory or via composite video input. Updated procedures can be electronically transferred to the EVA display computer 

via a PCMCIA card, which is compatible with both Space Shuttle and ISS laptops. Likewise, it will also be compatible for both Shuttle and 

ISS locker stowage. The first fully integrated engineering unit will be completed by March 1998. 

Background 

EVA missions have been growing both in number and complexity. The two Hubble Space Telescope repair missions are good examples 

of this, both of which required five consecutive EVAs to complete all of the necessary repairs. All of these planned EVA missions required 

extensive training to ensure success; however, unlike Space Shuttle missions, Space Station missions will require real-time, day-to-day 

adjustments to procedures to achieve mission success. 

Presently, astronauts rely on a paper, cuff-mounted checklist to refer to the simple text and graphics information that aids them in 

performing complex EVA missions. The paper cuff checklist is limited to 25 note-card-size pages (double-sided), which are printed and 

assembled over several months before a scheduled EVA mission. Although this method has been successful for years on Space Shuttle flights, 

it will not meet the logistical constraints of ISS maintenance EVAs since the crew will only receive supplies every 90 days or more. 

For further technical information, contact Tony Wagner at (281) 483-3485 or anthony. wagner! @jsc.nasa.gov 

Computer Software 23 
Show Plots 

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--EUENT- --OBSERUED-- --EXPECTED--

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lease centerline latches 5 to 8 18 sec 20 sec 

lease centerline latches 9 to 12 17 sec 20 sec 

*release centerline latches 1 to 4 34 sec 20 sec 

release centerline latches 13 to 16 17 sec 20 sec 

release starboard forward bulkhead latches 25 sec 30 sec 

re I ease starboard aft bu I khead I atches 25 sec 30 sec 

* op,en starboard door 56 sec 63 sec 

reI ease port forward bu I khead I atches 25 sec 30 sec 

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Situation Event Review Window, With Details Selected for Aborted Operation 

24 Computer Software 

I IIIII 

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Johnson Space Center 

Human Interaction Design for Cooperating Automation and Anomaly 

Response Systems 

Benefit 

New methods and designs are being developed to improve human interaction designs for intelligent computer systems for control 

centers, to support and automate real-time monitoring, anomaly detection, and anomaly response. The objective is to develop low-cost usermaintainable cooperative automation software. One type of software will provide intelligent situation assessment, summarization, and 

presentation, to enable operators to interact with systems by exception, rather than in a mode of constant vigilance. Another type of software 

will support team decision-making about anomaly causes and courses of action, by providing early and rapid electronic access to developing 

information from multiple organizations involved in anomaly response, and searches of archived information for relevant analysis results from 

past anomaly cases. 

Accomplishment 

Human interaction designs, operational prototypes and system requirements were completed for two systems for aiding ground 

controllers in monitoring and reviewing events and situations. SPORT (situation playback Orbiter data reduction complex (ODRC) retrieval 

tool) provides real-time data playback and plots for situation review, and automates data retrieval requests. The situation data collection and 

review system selects data for organized logs and plots, for presentation and review. The situation review displays are designed to aid anomaly 

identification and comparison of expected with observed operations times and data during an event. These designs have been adapted and 

implemented in the Space Shuttle Remote Manipulator System Assistant Project. A related Ohio State University Technical Report has been 

completed, "Coordination Across Shift Boundaries in Space Shuttle Mission Control.'' 

Scenarios and storyboards have been developed for a specification tool for the situation data collection and review system, to 

incrementally develop specifications for capture and viewing of the situation data. 

Human interaction designs and a World Wide Web-based mockup were completed for an Internet-browser-based anomaly response 

tracking and integrated system. A related Ohio State University Technical Report has been completed, "A Cognitive Analysis of Functionally 

Distributed Anomaly Response in Space Shuttle Mission Control." 

A Human Interaction Design Field Guide documents methods of iterative design used and refined by the team during the project. A Website version of this Field Guide and a Guidelines and Lessons Learned document are also products of this project. 

Background 

This project is interdisciplinary, involving human factors, computer science, and engineering professionals with specialization in 

intelligent systems technology. The approach is to design the automation software as a team player that is so informative and cooperative that 

it provides on-the-job training as well as timely information briefings. The focus is on gaining an understanding of operator tasks and systems, 

expertise, and difficulties, leading to useful and usable software designs. Further information concerning the methods and goals of this type of 

project is available in the just-completed book chapter, "'Paradigms for Intelligent Interface Design," in the 1997 Second Edition of the 

Handbook of Human-Computer Interaction. 

For further technical information, contact Jane Malin at (281) 483-2046 or jane.t.malin 1 @jsc.nasa.gov 

Computer Software 25 
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Document Viewer Workflow Display 

26 Computer Software 
Johnson Space Center 

High Volume Data Management (HVDM) 

Benefit 

Significant efficiency and cost benefit is being implemented through a vast decrease in printed documents due to the Electronic 

Documentation Project (EDP), and shall be further enhanced in this task. Through use of electronic, vs. paper, change processing, an 

approximate 40% time savings is realized. By empowering process engineers to independently build their own system flows, an estimated 

.5EP per new process savings can be realized. Building on the Internet experience of EDP, HVDM will allow Internet access to the document 

libraries for remote users and Space Station international partners. Primary savings will come from additional Web-based utilization of the 

EDP libraries for remote NASA users, as well as elimination of the developer involvement in process definition of workflow tasks. Both of 

these items will serve to radically broaden the scope and user support of the systems originally built for EDP 

Accomplishment 

Currently completing the first year of the project, in cooperation with NASA's Jet Propulsion Laboratory, HVDM is finishing deployment 

for two workflow installations, as well as prototyping candidate solutions for the workflow auto-process engine and viewer client/server 

implementation. Possible future cooperative development with the Adobe Corporation is being investigated. 

Background 

As a follow-on to the EDP, the HVDM will develop a system to interface the EDP viewer as a client/server application (vs. an embedded 

database) to the Internet as a Web helper application. HVDM will also build an automated process definition engine for the EDP workflow 

system. This will allow process engineers to define or refine their process flows without a dependence on developer support to make these 

changes. A future cooperative development with the Adobe Corporation is being considered to more fully leverage from the NASA use of the 

PDF document format. 

For further technical information, contact Tony Griffith at (281) 244-5813 or anothony.d.griffithl @jsc.nasa.gov 

Computer Software 27 
PROP 

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28 Computer Software 

PROP 

Server 

ISP 

Center-wide 

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Application 

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Local Area Architectural Overview of 

Information -Sharing Protocol 

Wide Area Architectural View of InformationSharing Protocol 

-
Johnson Space Center 

Information-Sharing Protocol (ISP) Technology 

Benefit 

An ISP developed for use in the Johnson Space Center (JSC) Mission Control Center (MCC) provides the capability to distribute 

telemetry data to any location in the world. This project will help the flight support community migrate toward the use of standard off-the-shelf 

solutions to the challenging problems posed by manned spaceflight support. It will demonstrate this migration through concrete pilot projects. 

And it will explore the integration issues involved when off-the-shelf products need to be interfaced with highly specialized, custom software. 

Accomplishment 

During fiscal year 1996, ISP technology was applied to the MCC to distribute data between work groups and the capability was 

implemented to distribute information to the Shuttle Internet home page, which provides the information to the public. In addition to JSC, ISP 

technology has been provided to the Goddard Space Flight Center where it is used to distribute Hubble Telescope data and to Marshall Space 

Flight Center to receive mission and simulation data. 

Background 

The old mainframe-based MCC did not provide an adequate platform for the introduction of information-sharing capabilities. The 

upgrade of the JSC MCC to a workstation-based architecture provided the opportunity to introduce these technologies. This project integrates 

off-the-shelf software technologies into mission support software. Commercial and existing government software is integrated into the MCC 

distributed computing infrastructure to more effectively and efficiently support Shuttle and International Space Station (ISS) missions. There 

are three parts to our proposal: (1) integration of off-the-shelf (commercial and existing NASA-developed) software into the MCC infrastructure, (2) development of fault-tolerant systems, and (3) development of PC-based real-time data distribution and analysis capabilities for 

Shuttle and ISS telemetry. 

For further technical information, contact Mitchell Macha at (281) 483-7059 or mitchell.g.macha 1 @jsc.nasa.gov 

Computer Software 29 
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Workstation-Based Intelligent Computer-Aided Training System 

30 Computer Software 

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Johnson Space Center 

Intelligent Computer-Aided Training Tool Development 

Benefit 

Johnson Space Center has developed workstation-based, intelligent computer-aided training systems that can deliver intensive, 

comprehensive training at the rate and quality needed for the space program. These workstation systems can deliver intensive training to large 

numbers of trainees, independent of integrated simulations, and can significantly reduce the amount of on-the-job or simulator-based training 

necessary to achieve acceptable levels of performance. Intelligent computer-aided tools will greatly reduce the time, expense, and expertise 

required for automated development of intelligent computer-aided training systems. 

Accomplishment 

A suite of tools is being designed and developed in coordination with the International Space Station training office for the creation of 

intelligent computer-aided training systems. Objectives are to refine and evaluate current approaches toward evaluating actions, building 

remediation models, and building scenario generation models. The tool set will reduce the need for programming expertise and enable 

intelligent computer-aided training systems to be maintained more easily than is possible with existing software tools. Currently, intelligent 

computer-aided training developers code by hand the data files used by the general architecture. This is time-consuming, tedious, and errorprone. The tools will enable the data files to be built through a graphical user interface that can be used even by nonprograrnmers. 

Background 

Training NASA astronauts. flight controllers. and other ground-support personnel has historically required extensive on-the-job or 

simulator-based training for individuals to acquire the knowledge and skills necessary for acceptable performance or certification. Current 

flight rates and the loss of experienced personnel to retirement and transfer severely reduce the ability of traditional training approaches to 

produce an adequate number of trained personnel. Over the past 8 years, a general purpose intelligent computer-aided training architecture has 

been created which enables faster implementation of intelligent computer-aided training systems. The architecture is composed of seven 

modules and is designed to generate appropriate scenarios for each student. evaluate student actions, and provide remediation upon errors. 

Each module has a well-defined relationship with the other modules, allowing module algorithms to be upgraded without a ripple effect. In a 

typical intelligent computer-aided training system, the development of the simulated work environment often takes 50% or more of the total 

time required to build the intelligent computer-aided training system. In some cases, especially at NASA, simulations already exist which meet 

the requirements of the intelligent computer-aided training system. The general purpose intelligent computer-aided training architecture has 

already addressed the reuse of existing simulations by defining a protocol for the simulations to use. Any simulation that can be modified to 

address this protocol can be transformed into an intelligent computer-aided training system. To reduce duplication of existing simulations. the 

initial version of the intelligent computer-aided training tools will be designed specifically to work with the part task trainers currently being 

developed. 

For further technical information, contact Bob Savely at (281) 483-8105 or robert.t.savely 1@ jsc.nasa.gov 

Computer Software 31 
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32 Computer Software 

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Johnson Space Center 

Intelligent Flight Activity Planner (IFAP) 

Benefit 

Because of the great importance, diversity and complexity of the time lines developed by the flight planners, NASA could dramatically 

benefit from an automated approach to flight planning. However, no tool currently exists which is both comprehensive and flexible enough to 

accommodate the flight planners' needs. 

Accomplishment 

Phase I of the project, which has been completed, applied artificial intelligence (AI) problem solving expertise to the automation of the 

flight schedule development process. Phase I resulted in the design of a feasible, full-scale intelligent flight planner. One of the major 

objectives of Phase II will be the implementation of this tool. 

IFAP is designed to capture the expertise of experienced planners and provide comprehensive, interactive planning assistance. IFAP can 

automatically plan flights, taking into consideration resources, conditions, constraints and planner heuristics or rules of thumb to improve the 

scheduling. By making use of generic sequence and activity definitions and relevant constraints, IFAP will generate a time line from scratch or 

replan all or portions of an existing timeline. The result will have no resource conflicts, no broken constraints. By utilizing planner rules of 

thumb, IFAP can improve on this correct schedule. Because IFAP will incorporate planner expertise, even a novice planner could produce 

quality timelines. In addition to offering automatic planning and replanning capabilities, the human element is retained. The planner maintains 

control of the timeline and can interact with it, edit sequences or activities, and preserve these changes during the replanning process. 

Background 

IFAP was conceived to infuse artificial intelligence into the planning tools for Mission Operations, thereby improving the productivity of 

the planner, improving the quality of the timelines produced for the mission, and providing knowledge capture, allowing less experienced 

planners to produce quality timelines. The concept underlying the IFAP scheduling engine is the abstraction of scheduling ground rules from 

the actual time line planning data. IFAP provides intelligent entity hierarchies to organize the data. The planner defines a hierarchy of 

intelligent entities to control the scheduling engine. The IFAP hierarchies include Timeline Hierarchy, Sequence Hierarchy, Activity Hierarchy, 

Individual Resource Hierarchy, Pooled Resource Hierarchy, External Condition Hierarchy, and Activity Condition Hierarchy. 

For further technical information, contact Mark Jernigan at (281) 483-9528 or j.m.jemiganl @jsc.nasa.gov 

Computer Software 33 
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ILIAD-Internet Library Information Assembly Database 

34 Compllter Software 
Johnson Space Center 

Internet Library Information Access Device 

Benefit 

The Internet Library Information Access Device (ILIAD) searches the web and returns documents that best match your query to you by 

electronic mail. ILIAD is ideal for those with low band-width connections, the vision impaired. persons having email-only service. or users 

wanting a fast, cheap. text-only interface to the Web. Users query ILIAD by electronic mail or through a standard web interface. ILIAD 

exploits meta-search technology. using multiple Internet search engines, and returns a small number of information-rich text documents to the 

user by return email. This mode of interaction provides efficient web access while requiring minimal hardware, software and connectivity from 

the user. 

Accomplishment 

The ILIAD application was originally fielded in July '95 at the Johnson Space Center (JSC) and has been in essentially continuous 

service since that time. ILIAD has been used by thousands of people over the past three years and continues to be a popular service, receiving 

the "Bot Spot of the Week" award in December '97. The latest version (5.0) is now running at JSC and the Texas Education Network (TENET) 

and has been transferred to the Research, Rehabilitation and Training Center for Blindness and Low Vision at Mississippi State University. The 

source code has also been licensed by a commercial interest. 

Background 

ILIAD was originally conceived to act as an electronic information assistant for teachers. As the Internet grew in size and complexity, it 

became impractical and inefficient to maintain a database for the contents of the entire Web, thus ILIAD became one of the first so-called 

"meta-searchers"- agents that synthesize results from multiple Internet search engines. The ILIAD email interface was initially conceived to 

minimize user requirements for hardware. software, and connectivity. In practice, this agent-based approach resulted in a flexible, efficient, 

and popular Internet search and retrieval tool. 

For further technical information, contact Bob Shelton at (281) 483-5901 or robert.o.sheltonl @jsc.nasa.gov 

Computer Software 35 
Example of SIMON 

36 Computer Software 

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School Internet Manager Over Networks 

Benefit 

The School Internet Manager Over Networks (SIMON) is a data-miner and lesson-builder developed for K-12 teachers. SIMON 

maximizes NASA's investments in educational Web content by exploiting agent technology to do searches off-line, providing a simple, natural 

interface for automatic lesson generation, and giving teachers intellectual control over electronic information sources. 

Accomplishment 

SIMON is a suite of Macintosh applications designed and implemented in approximately 12 months with production release 9/30/97. To 

afford the widest possible dissemination, the executable applications are available free to educators at <http://www.jsc.nasa.gov/stb/ 

simon.html>. The source code has been licensed to two commercial interests for further development. Dissemination statistics collected 

following release of version l.O (10/97-2/98) show SIMON in use or evaluated in 146 schools by 255 teachers. 

The free version also includes a lesson library consisting of 22 curriculum units gleaned from NASA educational Web resources. The 

development team works in conjunction with the Texas Education Network (TENET), local school districts, and the Johnson Space Center 

Education and Information Services Branch to provide continuing evaluation and dissemination of the product. The latest release (1130/98) 

includes cross-platform viewing (the MACINTOSH-specific component is now limited to one server machine), enhanced retrieval options, and 

support for building lessons from interactive browsing a~ well as the original off-line search. 

Background 

As set forth in the charter establishing the space agency, NASA is committed to advance excellence in education by bringing new 

knowledge and technology into the classroom. To this end, the Agency supports the development of outstanding educational content which, to 

an increasing extent, has seen widespread dissemination over the Internet. Experience with teachers being trained to integrate these resources 

into classroom lessons and activities suggests the need for a technology solution to bridge the gap between Web pages and classroom-ready 

materials. SIMON is designed to address these needs by providing low-cost Internet connectivity, supporting time-effective off-line searches, 

facilitating creation of standard, reusable lessons aligned by teachers to their specific learning objectives, and providing intellectual control 

over electronic information used in the classroom. 

For further technical information. contact Bob Shelton at (281) 483-5901 or robert.o.sheltonl @jsc.nasa.gov 

Computer Software 37 
Fig l. Docking target model with no shadow or glare. 

Fig. 2. Docking target model with shadows and glare. 

Effects of Lighting on Human Performance in Training 

38 Computer Software 

8 I I I 

7 

6 

5 

4 

3 

2 

1 

0 

35 Tinflf (sl~ontl 5 

Fig. 3. A comparison of times to complete the 

actual task. Group A trained without lighting. 

Group B trained with lighting. 

-....--
Johnson Space Center 

Effects of Lighting on Human Peiformance in Training 

Benefit 

When time constraints are imposed on a task, training with lighting effects improves task performance without sacrificing accuracy. In 

addition, subjective evidence reveals that subject'> who trained with lighting effects had lower stress levels when executing the actual ta<>k. 

While computer technology is not yet able to generate "real-time" ray tracing images for training, lighting conditions can be modeled for 

specific cao;es using existing computer hardware lighting parameters and special case shadowing effects. The results also support the use of 

lighting and illumination techniques for non-computerized image creation using mockups and artificial lights. 

Accomplishment 

To compare task performance with respect to different types of training, a simple alignment task, similar to the alignment of the Orbiter 

with the Mir docking target, was used (figures I & 2). Two different experiments were conducted with two groups of subjects, those trained 

without lighting and those with lighting. The first experiment emphasized alignment accuracy only. Subjects were allowed any amount of time 

needed to obtain the required alignment. Objective results were not conclusive but subjects who trained with lighting images felt more 

confident 1) that their test results were accurate, 2) that their training would generalize to other tasks, and 3) that the training was reasonably 

realistic. The second experiment emphasized alignment accuracy and alignment response time. In thise case, subjects trained with lighting 

(Group B) as part of the scenario had a significant advantage (average execution time 34.9 seconds) over those who did not (Group A with 

average execution time of 40.7 seconds). See figure 3. 

Background 

Many of the tasks performed by astronauts while in orbit, such as the deployment of payloads, depend on obtaining visual cues, either 

from a camera image or direct viewing. Direct exposure to intense sunlight and to rapidly changing sunlight direction makes crew response to 

high-contrast shadows and variations of incident light angles an essential part of carrying out mission operations. Training with mockups and 

lighting hardware has received positive response from crews prior to missions involving docking. However, much of the crew training is done 

with computer simulators using conventional shaded geometric models. These models do not simulate actual lighting environments which 

include effects such as shadows and glare. The purpose of this project was to compare the effect of different types of training images on actual 

task performance. Specifically, the effect of computer task training with accurate lighting images, shadows and glare, were compared to 

computer task training with basic shaded models with no shadows and glare effects. 

For further technical information, contact James Maida at (281) 483-1113 or James.Maida@jsc.nasa.gov 

Computer Software 39 
Plen 2 

Accumulator 

June 

200 

Conn 6 

(MFRSET) 

Conn 5 

(STUB E) 

SINDA/FLUINT Version 3.2 

40 Computer Software 

Tube 1 

N\r-35W 

June 50 

• 

• 

Rad 50 

Tank 1 

Evaporator 

Tube 2 

Condenser model: Divide into 5 equal 

sections of 0.5 m each. June N contains 

the volume of Conn N, whose wall is 

modeled by Rad N. 

June 40 June 30 

• • 

June 20 

• 

Conn 10 

(STUB 

..,. 

• 

Rad 40 Rad 30 Rad 20 Rad 10 

-,_____ 
Johnson Space Center 

SINDAIFLUINT Version 3.2 

Benefit 

The Systems Improved Numerical Differencing Analyzer/Fluid Integrator (SINDAIFLUINT) is a thermaUfluid design and analysis 

software that frees analysts from the constraints of geometric analysis which bog down finite element solvers. As a general purpose thermaU 

fluid network solver, it can model system-level designs that are too large or ill-defined for other software. Since it is completely user 

extensible, the execution can be customized with user-supplied logic, producing a code designed specifically for individual user needs. 

Accomplishment 

This program provides the following capabilities and features: 20,000 nodes, 100,000 conductors, 100 thermal submodels, and 25 fluid 

submodels. SINDAIFLUINT can model two-phase flow, capillary devices, fluids defined by users, gravity and acceleration body forces on a 

fluid, and variable volumes. It enables simulation of nonuniform heating and facilitates modeling of thin-walled heat exchangers. It also has the 

ability to model nonequilibrium behavior within two-phase volumes. As a thermal analyzer, SIND A can handle such interrelated phenomena as 

sublimation, diffuse radiation within enclosures, transport delay effects, and sensitivity analysis. 

Improvements recently added to SIND A include calculator registers to achieve spreadsheet-like functionality in a manner integral to the 

program and the ability to model single- and two-phase mixtures of working fluids with one substance in the mixture being either a real gas 

(with arbitrary user-defined properties) or a condensable/volatile substance (e.g., liquid water and steam). 

A graphical user interface. training, user support, and other machine versions are commercially available. 

Background 

SIND A is a software system for solving lumped-parameter representations of physical problems governed by diffusion-type equations. 

Although originally designed for analyzing thermal systems represented in electrical-analog lumped-parameter form, it can be used on other 

classes of physical systems that can be modeled in this form. FLUINT is an advanced one-dimensional fluid analysis program that solves 

equations of arbitrary fluid-flow networks. The working fluids can be single-phase vapors, single-phase liquids, or two-phase. The SINON 

FLUINT system enables the analysis of the mutual influences of thermal and fluid problems. 

While the software package is often described as two packages, it is really two components of a whole and cannot be easily separated. 

The SIND A system, comprised of a programming language, preprocessor, and a subroutine library, has a language designed for working with 

lumped-parameter representations and finite-difference solution techniques. The preprocessor accepts programs written in the SINDAIFLUINT 

language and converts them into FORTRAN. The SINDAIFLUINT library consists of a large number of FORTRAN subroutines that perform a 

variety of commonly needed actions. Using these subroutines can greatly reduce the programming effort required to solve many problems. 

A complete run of a SINDAIFLUINT model is a four-step process. First, the user's desired model is run through the preprocessor which 

writes out data files for the processor to read and translates the user's program code. Second, the translated code is compiled. The third step 

requires linking the user's code with the processor library. Finally, the processor is executed. SINDA!FLUINT is therefore like an extension of 

FORTRAN, able to accommodate user instructions and customization. 

For further technical information, contact Eugene Ungar at (281) 483-9115 or eugene.k.ungar 1 @jsc.nasa.gov 

Computer Software 41 
Instructor Tools 

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Space Operations Intelligent Computer-Aided Training 

42 Computer Software 

-

-- --

Student 
Johnson Space Center 

Space Operations Intelligent Computer Aided Training (/CAT) 

Benefit 

The Johnson Space Center (JSC) has a vision to provide intelligent instructorless simulation-based training to space flight crew members 

and ground flight controllers. This will reduce the cost of future space flight training in the following ways. First. intelligent instructorless 

lessons will reduce the number of exercises requiring instructor support, thereby slowing the trend toward greater numbers of instructors as 

space missions grow longer and more complex. Secondly, facility costs will decrease in some cases because intelligent instructorless training 

will permit greater fidelity training on the smaller, less expensive training systems, thereby reducing the number of training sessions required 

on the large, expensive training simulators where instructors will still be needed. An additional benefit of intelligent instuctorless training is 

greater flexibility for scheduling training around a student's other appointments. On the other hand, intelligent instructorless systems are also 

more expensive to develop than today's conventional training systems. Research and development is needed to reduce the development costs of 

intelligent instructorless training systems and to improve the quality of correctional feedback given to the student. 

Accomplishment 

JSC is updating and enhancing the software that provides the basic foundation upon which ICAT systems are built. This basic foundation 

is called the core ICAT architecture (Fig. 1). Typically. for each new training application to be developed (e.g .. an ICAT for environmental 

control and life support systems training). an expert instructor and a computer programmer are both needed full-time to build the required 

application-specific lesson files, plus the programmer must integrate the ICAT core with the simulation environment used by the students 

during current instructor-led training sessions. This research and development project will improve and update the technology used within the 

instructor tools, which will be enhanced and upgraded so that much less of the programmer's time is needed and so the expert instructor's 

lesson-building tasks are facilitated. Although much progress was made in earlier projects toward this end, this research and development 

project will significantly improve the core ICAT architecture and the instructor tools. 

During fiscal year 1997. the Space Operations ICAT project redesigned the instructor tools and delivered the Beta 1 version of the new 

Instructor Tool Suite. A preliminary user's guide was also developed, and requirements for the appropriate test application were investigated. 

Introduction and Background 

During the Apollo and Space Shuttle eras, space flights have been monitored closely by large teams of flight controllers on the ground. 

However, space flight missions during the era of the Space Station and beyond will present significant challenges because of their length and 

complexity. For example. the scenario where large numbers of tlight controllers monitor complex space station functions (or advanced Mars or 

Lunar spacecraft functions) around the clock, for months and years, is clearly a very expensive scenario. Large teams of developers and 

operators also make training for space flights very expensive. Ways to reduce operations and training costs significantly must be found in order 

to make advanced space missions economically feasible. 

For further technical information, contact Susan Tomey at (281) 244-7486 or susan.e.tomey 1 @jsc.nasa.gov 

Computer Software 43 
Space Station Training Facility (SSTF) 

Simulation Host 

Models and 

interface agents 

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executive 

Simulation Virtual Machine 

44 Computer Software 

LAN FlemotePiatforms 

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SSIF Students 
Johnson Space Center 

Simulation Virtual Machine (SVM) 

Benefit 

The SVM is a software executive that provides distributed processing, message passing, and rate monotonic scheduling for simulation 

models for the Space Station Training Facility (SSTF) at Johnson Space Center. SVM provides an excellent basis for distributed processing 

both in real-time and transaction processing software applications. It provides the commercial and military industry with a foundation that 

enables software processing from old mainframe architectures to distributed architectures. SVM is currently being investigated as a real-time 

solution for commercial space network simulations and Department of Defense wargaming applications. 

Accomplishment 

SVM lowers development costs and enhances code reuse by influencing structural consistency throughout a project using a documented 

object-oriented software architecture. SVM's executive lowers integration costs by shielding the application from the computer hardware 

specifics and by providing a standard interface to applications. SVM's executive is designed to support a distributed hardware environment 

(multi-task, -CPU, -node. -platform) and provides parallel, rate-monotonically scheduled execution threads, thread-to-thread time-consistent 

data-homogeneous message communication, and other executive functionality such as moding, datastore, and data term visibility. SVM is also 

based on standards and therefore relatively easy to rehost to different computer platforms. SVM's structural consistency and executive's 

flexibility lowers maintenance/upgrade costs by reducing the amount of work required to understand the software, change the software, and add 

new capabilities. 

Background 

To successfully train the crew and distributed ground systems for Space Station assembly/operations, a "virtual simulation" must occur 

between geographically distributed students. By adopting a common set of standards and objective-oriented techniques, problems related to the 

distribution of the training participants can be minimized. When implemented effectively, a virtual simulator can reuse existing assets for 

greater fidelity and capability at a significant cost and time savings. SVM provides the infrastructure software for implementing the virtual 

simulation for the SSTF. 

For further technical information, contact Barbara Pearson at (281) 244-8295 or barbara. pearson I@ jsc.nasa.gov 

Computer Software 45 
TSS Thermal Radiation Analysis Results for the 

ACRV-X Spacecraft 

46 Computer Software 

• • 

• • 

• ~C'~ 

• 

• 0.5 

• 

• 0.37 

• 0.30 

TSS Geometrical Mathematical Model of the ACRV-X 

Spacecraft 

~ 

r-
Johnson Space Center 

Thermal Synthesizer System, Version 6.0 

Benefit 

The TSS is a comprehensive set of analysis tools that will enable engineers to focus on defining analysis problems rather than 

programming syntax. TSS differs from existing analysis tools because it provides a friendly and flexible user interface, an interactive modeling 

environment with three-dimensional color graphics, and state-of-the-art analysis algorithms which support distributed processing. It combines 

the functionality of SINDNFLUINT and radiation analysis with an easily understood user-interface environment. All this is coupled with 

powerful interactive color graphics and a geometric modeling capability. 

Accomplishment 

TSS is composed of many different applications: the geometry, radiation conductance, orbit, heatrate, heatsource, animation, 

conductance-capacitance, SINDA85. XU plot, and translator applications. Each application handles a different portion of the thermal analysis 

process. Since all of the modeling, analysis, and post-processing functions are integrated into a single system, users can now focus on thermal 

engineering instead of learning to interact with the computer system. A consistent, user-frinedly intervace which uses menus, incons, and 

command language replaces the nongraphical, batch-job-oriented, machine-specific interaction of earlier systems. Interactive visualization of 

models and results provides instant feedback, eliminating the need for large stacks of printouts. In this way, TSS has significantly improved 

engineering efficiency and allowed engineers to have greater confidence in their analysis results. An integrated method of visualizing the 

thermal radiation analysis results did not exist. The opposite graphic shows a TSS-produced, geometrical mathematical model of the assured 

crew return vehicle (ACRV)-X spacecraft and thermal radiation analysis results for the same spacecraft. 

Recently, new capabilities have been added to TSS (version 6.0). A NASTRAN translator has been added so that thermal analysts can 

work structural analyses more easily. New methods have made radiation calculations for varying geometries faster. This would help in 

analyzing articulating spacecraft such as satellites with solar arrays. Trajectories can now be analyzed as well as orbits. Heat sources can now 

vary with time or orbit position. 

Background 

Before TSS was developed, engineers had to laboriously construct models with hand calculations and card image input. Once completed, 

the input deck was submitted to a preprocessor that checked the model for typographical errors. This same process was used to generate and 

display spacecraft orbits. Since the input was complicated and the method of input made errors inevitable, even more time had to be spent 

verifying the geometry, the articulation transformations, and the orbit. The analysis results created voluminous stacks of computer printouts. 

TSS is available from COSMIC (V 4.0) by license for a period of 10 years to approved licensees. Version 6.0 is available directly from 

NASA for all government contractors. The licensed program product includes the executable code and one copy of the supporting 

documentation. 

For further technical information, contact Andy Hong at (281) 483-4423 or andrew.e.hongl @jsc.nasa.gov 

Computer Software 4 7 
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8 

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Johnson Space Center 

Shared Virtual Environments for Team Training 

Benefit 

Virtual environments have the potential to significantly enhance the training of NASA astronauts and ground-based personnel for a 

variety of activities. At the same time, this technology offers significant cost savings and increased training throughput. Following the 

successful use of virtual environments in preparing the flight team of the first Hubble Space Telescope (HST) repair and maintenance mission 

[STS-61; see R.B. Loftin and P.J. Kenney, 'Training the Hubble Space Telescope Flight Team," IEEE Computer Graphics & Applications, Vol. 

15, No.5, pp. 31-37 (September, 1995).], attention has been focused on the use of shared virtual environments to support the training ofteams 

of astronauts for the International Space Station. Such shared environments can be used for both mission planning and mission training, 

reducing the need for extensive travel. 

Accomplishment 

In 1995 the first shared virtual environment between the U.S. and Europe was demonstrated. Astronaut Bernard Harris (physically 

located in Building 12 at the Johnson Space Center) entered a virtual environment with Astronaut Ulf Merbold (physically located at the 

Fraunhofer Institute for Computer Graphics in Darmstadt, Germany). Their shared environment consisted of models of the Space Shuttle 

payload bay and the HST. The two astronauts spent over 30 minutes performing the major activities associated with the changeout of the 

HST's solar array drive electronics (SADE). Their work included the real-time hand-off of the replacement SADE in exchange for the original 

SADE. At the conclusion of the task the two astronauts shook hands and waved good-bye. This first experiment has been followed by 

investigations involving additional sites, more complex procedures, and alternative communication channels. Currently, a test bed between 

Houston and the NASNMarshall Space Flight Center in Huntsville, Alabama, is in routine use to develop and test training approaches for 

operation and maintenance ofthe Biotechnology Facility (now operating in the Mir Space Station) within the International Space Station. 

Background 

Historically NASA has trained teams of astronauts by bringing them to the Johnson Space Center to undergo generic training followed by 

mission-specific training. This latter training begins after a crew has been selected for a mission and often begins as much as two years before 

launch. While some Space Shuttle flights have included an astronaut from a foreign country, the International Space Station will be 

consistently crewed by teams comprised of astronauts from two or more of the partner nations. As the task of training crews for the Space 

Station comes closer to realization, the cost, in terms of both travel and physical "wear and tear," appears ever larger. The Information Systems 

Directorate and the University of Houston, in cooperation with the Mission Operations Directorate, have been exploring virtual environment 

technology as a partial answer to the problem of helping international crews prepare for their missions. These explorations have been 

accomplished by generating duplicate graphical environments at each site (using Silicon Graphics Onyx Infinite Reality Engine workstations) 

and exchanging state change data (for example, the movement of one astronaut's hand or the translation of a suited astronaut to a new site) via 

a variety of communication channels [from a commercial Integrated Services Digital Network (ISDN) to ATM-based OC-3 networks]. 

For further technical information, contact Bob Savely at (281) 483-8105 or robert.t.savelyl @jsc.nasa.gov 

Computer Software 49 
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Johnson Space Center 

Visual Proximity Operations Processor (VPOP) 

Benefit 

The VPOP provides enhanced situational awareness to the Shuttle flight control team by converting downlisted telemetry into a 3D 

animation of Shuttle rendezvous and proximity operations activities. Hundreds of digital parameters from various sensors and effectors are 

combined with a high-fidelity environment model to produce a 3D reconstruction of the Shuttle motion relative to a free-flying target vehicle. 

This "virtual" space can be viewed from many perspectives, including crew out-the-window views, views from the target vehicle, as well as 

God's eye views. Trajectories based on the various available sensors can be quickly reconstructed and displayed on the large screen in the 

Flight Control Room for the team to see. As an added benefit, these images can also be broadcast on NASA TV as a Public Affairs tool. 

Accomplishment 

By utilizing existing software packages for data acquisition, data distribution, telemetry computation, and 3D scene animation, the 

required capability was delivered in less than one year from project inception at a cost that was less than projected. Over the last year, the tool 

has continued to be improved based on feedback from flight control personnel. 

Background 

During Shuttle proximity operations activities, the flight control team has historically relied on digital information to provide situational 

awareness and relative motion information. Visual information is further limited by the absence of downlink video. VPOP will enhance 

situational awareness with the addition of new views, better filtering of raw sensor data, and detection of Orbiter jet plume impingement. The 

system also provides the ability to animate relative motion based on ground tracking states and downlinked Global Positioning Satellite 

information. 

For further technical information, contact Don Pearson at (281) 483-8052 or don.j.pearsonl @jsc.nasa.gov 

Computer Software 51 
Test Bed to Study 

Electrohydrodynamic 

Heat Pipe Concept 

Circumferential 

Wall Grooves 

Arterial Groove 

I N-OT TO SCALE I 

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Johnson Space Center 

Electrohydrodynamic Heat Pipe Loop Studies 

Benefit 

An electrohydrodynamic heat pipe concept for use in the design of more efficient, lightweight radiators has potential applications in both 

aerospace and commercial systems. For spacecraft, the design can reduce the mass and power requirements of associated thermal systems. 

Earth applications of electrohydrodynamic technology include nonmechanical pumping systems for industries and utilities, and improved 

condensers for commercial cooling systems. 

Accomplishment 

A heat pipe has been fabricated that has vapor and liquid channels separated by a single arterial groove along the full length, as shown in 

the cross section at left. At the evaporator end, liquid is wicked from the liquid channel by the arterial groove and wall grooves on the 

circumference of the vapor channel. A thin liquid film then covers the vapor channel at the evaporator end, and the liquid vaporizes to gas 

when heat is applied. The pressure gradient generated in the channel forces the vapor to the cooler condenser end, where condensation forms a 

liquid film. The wall grooves and arterial gap at the condenser end then return liquid to the liquid channel. The heat pipe typically relies on 

capillary forces to return the condensate to the evaporator along the liquid channel, and then the process repeats. The electrohydrodynamic 

augmentation to the heat pipe includes the addition of an electrohydrodynamic pumping section between the evaporator and condenser ends to 

assist the condensate return to the evaporator. 

A test bed was built for the heat pipe and its support equipment, which includes a power supply, instrumentation, fill system, and coolant 

loop for the condenser. The test bed was designed to allow the heat pipe to be tested at various inclination angles to assess the onset of dryout 

with increased flow resistance. Initial tests with electrohydrodynamic augmentation have produced an over 100% increase in the heat pipe 

transport capacity at various condenser environments. Instantaneous recovery of the heat pipe during dryout was demonstrated as well. 

Background 

The radiator subsystem, which rejects waste heat to space, usually makes up the largest mass of the thermal control system of human 

spacecraft. The Electrohydrodynarnic Heat Pipe Loop Studies Program was initiated by the Johnson Space Center Crew and Thermal Systems 

Division to develop an efficient heat pipe radiator for space applications such as orbiting platforms and interplanetary vehicles. Electrohydrodynarnic technology involves interactions of electric fields and free charges in a dielectric fluid medium to provide nonmechanical pumping. 

Program goals included applying electrohydrodynamic augmentation to increase the heat pipe transport capacity by at least 100%, to maintain 

peak performance during transients, and to reduce the overall heat pipe radiator weight by at least 30%. This radiator design also provides 

increased tolerance to micrometeoroids and orbital debris because heat is rejected individually by the surfaces of connected pipes, and the 

puncture of an individual pipe would not significantly diminish overall system performance. 

For further technical information, contact Katy Hurlbert at (281) 483-4546 or kathryn.hurlbertl @jsc.nasa.gov 

Energy 53 
54 Energy 

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• 

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CONCEPT STWY 

.(jfeSgstta.k Cl.f.'Wt!lMCI\CM(il The Mechanical/Electrochemical 

Assembly and Control/Monitor 

Instrumentation 

~ 

!--
Johnson Space Center 

Electrolysis Performance Improvement Concept Study (EPICS) Flight 

Experiment 

Benefit 

Onboard generation of oxygen is expected to reduce the annual resupply weight for the Space Station by approximately 5,455 kg 

(12,000 lbs) with an associated reduction in logistics costs. The objectives of the EPICS flight experiment are to demonstrate and validate the 

static feed electrolyzer operation in rnicrogravity, and to investigate performance improvements possible in rnicrogravity. If successful, the 

results of this Shuttle middeck experiment can be used to improve the static feed electrolyzer process efficiency for such activities as life 

support, propulsion, energy storage, and space manufacturing. 

Accomplishment 

Significant progress has been made on the development of the EPICS flight experiment. Developmental testing was conducted using an 

engineering model to verify key functional aspects of the EPICS design and provide engineering data to finalize the flight design. Based on the 

EPICS engineering model developmental testing, 21 changes were incorporated into the unit. The final design, fabrication, assembly, and 

ground testing were also completed. Then the experiment was certified for flight and flown on STS-69 in September 1995. Due to 

unanticipated shutdowns, however, only partial success was achieved. Changes were made before a reflight of the EPICS in 1997. Although 

not fully successful, the reflight did produce data for three full runs on one integrated electrolysis unit. 

Background 

A space environment is needed for this experiment because the static feed electrolyzer process has not been operated in rnicrogravity, 

data on gas and liquid transport in microgravity are very limited, and one-g test results are compromised by buoyancy and gravity-affected fluid 

configuration within the electrolysis cells. A lower-cell voltage operation may result from microgravity etTects on the distribution of liquid 

electrolyte, the gas/liquid interfaces with the cell, and the capillary forces on fluids within the pores of the electrodes and the electrolyte matrix. 

The EPICS experiment will examine the effects of rnicrogravity on electrolyte distribution in the static feed electrolyzer electrolyte 

retention matrix by determining performance characteristics of electrode/matrix assemblies that have different matrix thicknesses and electrode 

pore sizes and that operate at varying current densities. 

The experimental hardware consists of a mechanical/electrochemical assembly and control/monitor instrumentation. The mechanical/ 

electrochemical assembly is composed of three separate, self-contained, integrated electrolysis units, ancillary components, and the enclosure. 

Each integrated electrolysis unit is made up of an integrated electrolysis cell, a thermal control plate, and 0 2 and H2 accumulators. The 

integrated electrolysis cell consists of an electrolyzer cell core and a recombiner cell core (fuel cell concept) that enable the experiment to be 

self-contained. The control/monitor instrumentation controls the operation of the experiment via the mechanical/electrochemical assembly 

components and provides for monitoring and control of critical parameters and storage of experimental data. 

The experiment is designed for independent operation because it requires only electrical energy and cabin air for cooling. The water 

supply for electrolysis will be self-contained in the experiment. The experiment is designed to be compatible with the weight. power, and heatrejection capability of two standard middeck locker spaces. 

For further technical information, contact Sandra Brasseaux at (281) 483-9224 or sandra.brasseauxl @jsc.nasa.gov 

Energy 55 
SS 304 L Lid 

TGI Welded 

Ni 200 Current 

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Lithium Anode ---H 

Carbon Cathode 

Anode Screen 

56 Energy 

Terminal Cap 

Glass-to-Metal 

Hermetic Seal 

Separator 

304 L Stainless 

Steel Case 

Insulator 

Wound Construction 

from "Your Guide to Lithium Batteries," 

Electrochem Industries, New York 

-
Johnson Space Center 

New Lithium-BCX D Cell Development for Flight Applications 

Benefit 

A new version of the lithium-BCX D cell is being developed for Space Shuttle applications. This cell will be safer for use in confined 

space, but will still meet current flight requirements and make possible many more onboard applications than are now allowed. A similar 

design approach shall also be used in the current flight lithium C cell, and in the soon-to-be-certified lithium DD cell used in the extravehicular 

mobility unit/personal life support system battery application. 

Accomplishment 

An improved electrolyte (BCX II) that uses a gallium salt in lieu of aluminum salt has been applied to Orbiter D cell batteries. This new 

salt, which reduces voltage delay. has already been incorporated into a flight-qualified C cell version of the universal configuration. In 

addition, a modification to the electrolyte in the form of lowered molarity will reduce short circuit hazard potential because it will not produce 

sufficient current on short circuits to raise a cell to hazardous temperature levels. Tests by the cell vendor, Wilson Greatbatch Limited, as well 

as at NASA in-house facilities. showed that electrolyte levels with a value of 0.4 molarity (rather than the previous value of 1.0 molar) give the 

optimum combination of reduced short circuit hazard potential while meeting the minimum capacity requirements of the D cell's l-amp 

applications. On D cells ordered for NASA in-house tests, preliminary Wilson Greatbatch Limited tests revealed approximately 8 AH capacity 

(which is sufficient to meet all known applications), with the maximum temperature achieved on short circuits of~ 50 milliohms of less than 

90°C. The basic cell design is tolerant to close to 150°C, either fresh or discharged. All this contributes to a projected tolerance to an internal 

cell short as well. This cell design in the D size is now certified for flight use. 

Background 

The current Orbiter lithium-BCX flight D cell configuration, qualified in 1988, was a modified, high-temperature-tolerant version of a 

hand-wound cell with an electrode area of approximately 125 cm2 that was originally qualified in 1982. Since 1982, Wilson Greatbatch 

Limited has modified its product line to accommodate machine-wound cells of approximately twice the electrode area (thinner plates to 

facilitate machine winding). thus effecting a "universal" design approach for all cell sizes. The original philosophy in establishing the 

qualified configuration of the lithium-BCX D cell was to stay as close as possible to the vendor's commercial product in design, manufacturing 

processes, quality control. and use experience, thus increasing the availability of and confidence in the cell for flight use. But as the vendor's 

product line evolved, adhering to the original cell configuration became more difficult, and in fact confidence in and availability of the cells 

decreased. Thus it became necessary to requalify the cell configuration to realign the NASA flight configuration more closely with the Wilson 

Greatbatch Limited universal product. The problems of simply using the commercial version of the D cell are: 1) The BCX I electrolyte is 

more subject to passivation, or voltage delay. under conditions of long, open circuit voltage storage and at higher loads; and 2) The increased 

electrode plate area results in a cell with greater rate capability, which also increases inherent short circuit hazard potential. 

For further technical information, contact Bobby Bragg at (281) 483-9060 or bobby.j.braggl @jsc.nasa.gov 

Energy 57 
Ul 

00 
Johnson Space Center 

Solar Heat Pump Development 

Benefit 

Solar energy technology, long recognized as environmentally benign, has practical applications in both aerospace and earth-based energy 

systems. Solar heat pumps can significantly reduce the mass of thermal control systems on spacecraft for future human missions such as a 

lunar or Mars base habitat. On Earth, solar heat pumps are promising for a variety of cooling applications such as refrigeration in remote 

locations. 

Accomplishment 

A NASA site was one of five test sites in the United States chosen as part of the recently completed Electric Power Research Institute 

Solar Photovoltaic Heat Pump Project. A solar photovoltaic-powered vapor compression cycle heat pump was installed in the Johnson Space 

Center Advanced Life Support Laboratory to provide partial cooling. The equipment consisted of a 3 kW Solarex photovoltaic (PV) array, a 

5-ton-capacity Trane variable-speed heat pump, and power electronics which coupled the first two and controlled the system. The transition 

between PV and building-supplied backup power was smooth, even on partly cloudy days. One hundred percent solar operation of the heat 

pump compressor was successfully demonstrated. Of the five test sites, the NASA site had the best coincidence between the solar energy 

resource and the heat pump energy demand. A reduction in heat pump energy demand from Houston Lighting & Power Company during peak 

time periods was also demonstrated, especially when the PV heat pump was used in conjunction with a programmable set-back thermostat. 

The Crew and Thermal Systems Division has completed the conceptual design of a lunar base solar PV heat pump using a similar arrangement 

to reduce power system mass by 43% through direct coupling to the heat pump. 

Testing is under way on three smaller-scale solar heat pumps in a solar PV refrigerator application. Thermoelectric, Stirling, and vapor 

compression heat pumps are being tested (one at a time) in the same super-insulated refrigerator cabinet. The work is being done through a 

Space Act Agreement between Johnson Space Center and Oceaneering Space Systems. Besides the space application for the advanced 

refrigerators, there is a vast commercial potential for solar refrigeration in parts of the world which do not have electricity. Each of the three 

heat pumps will be run in a mode where they are directly connected to the solar PV panel without batteries. Instead, the refrigerators will rely 

on thermal energy storage to stay cold during the night and cloudy days. 

Background 

Thermal control systems require significant mass and volume resources. In most cases, thermal radiators, which dissipate waste heat to 

space, make up about half of the system's mass. In a lunar base located at a moderate latitude, radiators cannot dissipate the heat by direct 

radiation to space during the hottest part of the day because the lunar surface temperature is so high. On Earth, air conditioners are used to 

solve the same problem. On the moon, a heat pump can be used to raise the radiator temperature to a level that makes direct radiation possible. 

For both a lunar base and many Earth applications, solar energy is a good power source because it is most available at midday when the heat 

pump is required the most. Johnson Space Center and several industry partners are cooperating to develop highly efficient solar heat pumps 

that combine the thermal control and power control subsystems to solve various problems. 

For further technical information, contact Mike Ewert at (281) 483-9134 or mkhael.k.ewertl @jsc.nasa.gov 

Energy 59 
'I I 
Johnson Space Center 

Advanced Technology Space Suit 

Benefit 

As we prepare to embark upon plantetary exploration, the present shuttle/station space suit will be ineffective for the forecasted 

conditions of the Moon or Mars. The present suit is for zero-G and is not intended for walking on rough rocky surfaces. The outer thermal 

protection garment will work in the vacuum of the moon, but will not work in the low-pressure atmosphere of Mars. The high dust 

environments of the Moon and Mars will require new hardware. methods. and techniques to keep the dust out of the bearings and attachment 

mechanisms. For this reason. a new outer dust-resistant covering will need to be developed. 

The life support systems will also need to be changed. The sublimator cooling system will not work on Mars. For such long missions. 

system reliability and robustness must be increased. Also. astronaut maintenance capability must be incorporated and a modular portable life 

support system must be developed. 

New technologies in both the pressurized garment and life support must be incorporated to lower both the initial cost and the operating 

cost of extravehicular activity (EVA) systems. Additionally, a decrease in the overall system weight will enhance the increase in EVAs 

expected for exploration activities. 

Accomplishment 

The overall goal of this project is to perform a human test of a new bottoms-up space suit development in a thermal vacuum environment 

in the year 2000. The first step is to develop laboratory table top layouts of the various support loops. Once the details of component operation 

and technology have been verified. a major design effort will miniaturize and package these systems for maintenance. These subsystems will 

be tested, optimized, and mated with the other subsystems for an integrated test with a person. 

Background 

As exploration begins to shift from a zero-G operation to a planetary walking focus. it will shift from an activity where EVAs are done 

approximately twice a year to one where they are done every other day. Maintenance on EVA will shift from a highly trained technician and 

engineering team on the ground. to an astronaut caring for his own space suit prior to use. Instead of every EVA being choreographed prior to 

execution, a rich electronic sensing and learning environment must be available to the astronaut to help him deal with any situation real-time 

and without ground support. 

For further technical information, contact Mike Lawson at (281) 483-9124 or b.m.lawson1 @jsc.nasa.gov 

Environmental 61 
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62 Environmental 
Johnson Space Center 

Lunar-Mars Life Support Test Project 

Benefit 

In the process of developing life support self-sufficiency for human beings, researchers at Johnson Space Center (JSC) are discovering 

improved technologies for air revitalization, water recovery, and thermal control. Improved technologies in any of these areas of regenerative 

life support systems will have a wide range of applications for government and industry alike. 

Accomplishment 

Future long-duration crewed space missions will require life support systems which use integrated biological and physicochemical 

processes to provide an efficient, robust, and reliable life support capability with a minimal need for resupply. To help meet this need. JSC has 

implemented a coordinated plan that will perform the necessary research, technology development, integration, and verification of regenerative 

life support technologies to provide safe, reliable, and self-sufficient human life support systems. Researchers at JSC initiated the Early Human 

Testing Initiative project. renamed in 1997 the Lunar-Mars Life Support Test Project (LMLSTP), to investigate the performance characteristics 

of these integrated systems using human test subjects in a controlled environment ground test facility. 

Background 

The LMLSTP consists of a series of four advanced life support systems tests with human test subjects. Tests will be conducted using 

both physicochemical and biological systems and will involve crews of one to four test subjects for 15 to 90 days. These tests, scheduled 

through 1997, are: 

• A 15-day regenerative life support systems test in JSC's Variable Pressure Growth Chamber with one human test subject. This test began 

July 24, 1995, and was completed on August 8, 1995. The chamber was used principally to verify performance of biological air 

revitalization life support systems (using higher plants) with physicochemical subsystems as backups. 

• A 30-day regenerative life support systems test in JSC's Life Support Systems Integration Facility with four test subjects. The test began 

June 12, 1996, and was completed on July 12. 1996. This facility was used to verify performance of integrated physicochemical life 

support systems for air revitalization, water recovery, and thermal control. 

• A 60-day regenerative live support systems test in the Life Support Systems Integration Facility with four test subjects. This test began on 

January 13, 1997 and was completed on March 13, 1997. The existing physicochemical life support systems were augmented with 

selected representative Space Station life support components to provide baseline performance information. 

• A 90-day regenerative life support systems test in the Life Support Systems Integration Facility with four test subjects in combination with 

the Variable Pressure Growth Chamber. This test began September 19, 1997 and will be completed on December 19. The facilities will be 

integrated and used in tandem to verify performance of biological (i.e., higher plant) and physicochemical air revitalization functions. 

Incorporation of microbial bioreactor technology for water recovery and incineration technology for solid waste processing is aJso 

scheduled for this test. 

Over the next two fiscal years, continued efforts with the LMLSTP will increase the technical base needed for developing integrated life 

support systems and testing such systems with humans. 

For further technical information, contact Trish Petete at (281) 483-2834 or patricia.petete 1 @jsc.nasa.gov 

Environmental 63 
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For further technical information, contact Deborah Harm 

at (281) 483-7222 or deborah.l.harml @jsc.nasa.gov 

64 Medical 

~ 

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Johnson Space Center 

BioLog With FETRODES 

Benefit 

For space travelers and others whose work makes them susceptible to long periods of motion sickness, understanding the physiologic 

mechanisms underlying motion sickness symptoms is essential for the development of effective and timely countermeasures. Time spent in 

space is very valuable. Decreased productivity for astronauts is a costly consequence of motion sickness. Researchers at Johnson Space 

Center are using physiologic measures of motion sickness as objective indicators of symptom severity and occurrence, and as clues to 

understanding the physiological mechanisms involved in the development and resolution of symptoms. Electrogastrography and the frequency 

components of cardiac interbeat intervals are two noninvasive physiological variables which may be useful indicators of the development of 

motion sickness symptoms and changes in autonomic nervous system activity associated with motion sickness. Since absorption of oral drugs 

may be reduced under conditions of abnormal gastric activity, information on gastric activity on orbit is important to optimize the in-flight 

administration of oral medications. Understanding changes in nutrient absorption will be important for long-duration missions. 

Accomplishment 

Reduced gastric motility has long been recognized as a characteristic of acute motion sickness, and gastric stasis appears to accompany 

space motion sickness. In a spaceflight study, bowel sounds were found to be greatly decreased or absent in subjects experiencing motion 

sickness symptoms. One limitation of this study was the inability to time-lock events-such as eating, drinking, or motion sickness 

symptoms-to the data, so only general documentation of conditions was possible. Determining exactly where a symptom is reported in 

relation to the data is essential because changes in gastric frequency/amplitude have been noted prior to conscious awareness of symptoms. 

Researchers needed a system which could provide continuous, quality data recording in ambulatory subjects for the first several days of 

flight and time-locking of symptom reports and other events to the data. NASA contracted the developers of FETRODES, snap-on converter 

assemblies which consist of a temperature-compensated amplifier that has an extremely high input impedance and a very low output 

impedance, to develop a digital data logger incorporating this same technology. They developed BioLog with FETRODES, an ambulatory 

physiological data recorder for assessment of autonomic and gastric function. The FETRODES circuitry is built into a tiny enclosure which 

snaps onto any disposable electrode. Amplification of the electrogastrographic signal at the source greatly increases the signal-to-noise ratio, 

making ambulatory recording of the electrogastrogram possible. The developers, UFI, customized a system to supply both electrogastrographic and electrocardiographic data in a single channel. 

Background 

Electrogastrography is a noninvasive technique that uses surface electrodes to record myoelectric activity of the stomach. Both the 

frequency and amplitude of the electrogastrogram has been shown to be affected by motion sickness symptoms. Data are stored on a static 

random access memory card only slightly thicker than a standard credit card. The BioLog unit uses 1- or 2-megabyte cards interchangeably. 

A 2-megabyte card can store 48 hours of data. A 3-V lithium coin battery maintains data on the card for up to one year even when the 

equipment is powered off. Data are downloaded from the card to a personal computer via a card reader that is connected to the parallel port of 

the computer. The entire contents of a 2-megabyte random access memory card can be downloaded to a binary file in fewer than five minutes. 

The BioLog is small and lightweight and, using a custom-designed pocket, can be either belt-mounted or attached to a subject's clothing with 

Velcro. The unit is easily operated. It produced data of exceptional signal quality when flown aboard STS-60. 

Medical 65 

Johnson Space Center 

Autonomous Extravehicular Robotic Camera (AERCam) II Integrated 

Ground Demonstration 

Benefit 

External views of the Space Shuttle, International Space Station (ISS) and future Lunar-Mars transfer vehicles are needed to assist 

onboard crews and ground flight controllers in performing visual inspection associated with assembly, maintenance and servicing tasks. 

Related non-visual inspection requirements are expected to include hydrazine sensing, vibration measurement. and ammonia leak detection. To 

address these needs, the JSC Automation, Robotics and Simulation Division is developing a free-flying camera and sensor platform: The 

AERCam is a low-volume, low-mass free-flyer that is not subject to the limitations of fixed cameras, manipulator-based cameras, or 

extravehicular activity (EVA) crew accommodations. AERCam will exploit its high level of system intelligence to minimize crew workload 

associated with inspection tasks. It will have the capability to: 

• Provide EVA camera views unobtainable by any other means. 

• Fly autonomously to a commanded location (such as a desired viewing position for a point of interest). 

• Conduct autonomous search patterns for visual or non-visual inspections. 

• Intelligently screen inspection data to determine if further human analysis is required. 

• Stationkeep to an EVA astronaut to send camera views of EVA activities back to the intravehicular activity (IVA) crew and ground 

controllers. 

Accomplishment 

To achieve the final configuration. the AERCam project was divided into 3 development phases. The first two phases are ongoing: 

• AERCam I, called Sprint. is teleoperated with hand controllers by an IVA crew member. Video from cameras onboard the Sprint 

platform will be sent to the IVA crew and ground controllers. Sprint is manifested to fly in November 1997 on STS-87 as an ISS Risk 

Mitigation Experiment. 

• AERCam II automates the guidance, navigation. control, stationkeeping, and inspection functions, allowing the operator to issue task 

level commands. An Integrated Ground Demonstration (IGD) is planned for October 1997. The hardware ofthe IGD unit will then 

be redesigned and repackaged with an emphasis on miniaturization for a Shuttle flight experiment. 

Background 

The ISS Program has requested that the Sprint be flown as an ISS Risk Mitigation Experiment, and has developed an Experiment 

Integration Plan identifying the Human Exploration and Development of Space Program need for "generic functional support for enhanced 

viewing." AERCam IIIIII springboard from Sprint to meet longer-term ISS enhancement needs described in Space Station Program document 

SSP 50198, "Space Station Requirements for Advanced Engineering and Technology Development (AETD)." The AETD goals addressed by 

AERCam are: Reduce crew EVA time by 50% for maintenance tasks and visual inspection, develop and integrate autonomous inspection 

technologies and improve viewing capabilities, improve autonomous control algorithms to provide capability to handle planned tasks and 

flexibility to accomplish unplanned tasks, enhance interfaces to reduce routine task time and complexity, and develop technology that targets 

human involvement with the robot at a high level, with the long-term aim of developing a totally autonomous robotic system. 

For further technical information, contact Steve Fredrickson at (281) 483-1457 or steven.e.fredrickson 1 @jsc.nasa.gov 

Telecommunications 67 

..... 
II 
Johnson Space Center 

Autonomous Extravehicular Robotic Camera (AERCam) Sprint 

Benefit 

Adequate views that allow Orbiter intravehicular activity (IVA) crews to observe extravehicular activities (EVAs), inspect a location without an EVA, or 

view locations not visible by an EVA crew member or remote manipulator system camera from available cameras can be difficult if not impossible to obtain. 

The International Space Station (ISS) camera views are even more restricted due to the much larger structure that has to be viewed. In addition, the number of 

locations without camera coverage is greater. A camera that has the capability to be positioned without major impact to the actual design of the Orbiter or ISS 

would prove to be extremely useful to obtain these views. Such a camera has been constructed and is called Sprint. 

The Sprint is the first in a series of AERCams. Sprint is intended to be only a small teleoperated camera platform, where future AERCams will be 

developed with more capability, range. and lifetime. The purpose of Sprint is to demonstrate that a free-flying camera platform can be designed to augment 

on-orbit operations. The objectives are: 

• Provide the opportunity to examine the utility of a free-flying camera in close proximity to a spacecraft and EVA crew. 

• Provide a basic set of required capabilities for a free-flying camera as a development version of a future operational vehicle that would be used on 

orbit by either the Orbiter or ISS. 

This device can be used to directly support an EVA by giving IVA crew members the ability to freely move their eyepoint independent of cameras 

attached to the shuttle or the EVA crew. A production version of the Sprint could be used for inspection either as a precursor to an EVA, to provide support 

during an EVA, or in lieu of an EVA. 

Accomplishment 

The AERCam Sprint free-flyer: 

• Is a small, safe, unobtrusive, free-flying camera platform for use outside a spacecraft. 

• Has a self-contained propulsion system, giving it the capability to be propelled with six degrees of freedom. 

• Has an automatic attitude hold capability. 

• Is a slowly moving (-0.25 fps) spherical vehicle, covered in a soft, cushioned material to prevent damage in the event of an impact. 

• Is controlled from inside the cabin by an operator using a small control station. 

The operator will input motion commands from a hand controller. The commands will be sent from the control station to the free-flyer via an r.f. linlc 

Data from the free-flyer will be sent to the control station with information regarding the free-flyer's health, consumables, etc. The video will come from either 

of two cameras with different lenses transmitted by radio signal. The video signal will be received via the extravehicular mobility unit TV receiver and 

displayed on a laptop computer with video display capability. When operating, the video can be displayed on either the Sprint video monitor or on the standard 

Orbiter monitors. The data and video will be sent to the ground for viewing there. All video and data will be recorded on orbit as well a~ on the ground. 

Background 

The Sprint is the first in the AERCam series of robotic EVA tools designed to aid or enhance on-orbit EVA operations. Future robotic devices in the 

series will become more autonomous and intelligent, with much more capability. This will allow the robot to perform tasks without constant monitoring from a 

crew member. ISS will realize the greatest benefit from these tools in that they will decrease the amount of mundane EVA maintenance tasks that must be 

performed, and aid in those that are. The Sprint was proposed in the spring of 1995 and funded by NASA Headquarters Code X (now Code M) for FY96. 

Sprint is manifested on STS-87, scheduled to launch in November 1997. 

For further technical information. contact Cliff Hess at (281) 483-9142 or clifford. w.hess 1 @jsc.nasa.gov 

Telecommunications 69 
IPS 

Gateway 

Advanced Network 

Telepresence 

70 Telecommunications 

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Globally Interconnected Advanced Network Telepresence (GIANT) 

Benefit 

The GIANT implements enabling technology for Space Station distributed planning. It will prototype telepresence-videoconference, 

electronic whiteboard. data distribution, and application sharing-in support of the globally dispersed systems and payload planners for onorbit Space Station operations. Reduced manpower, continuous operations and extremely shortened process times for completing weekly plans 

demand the efficiency and productivity improvements offered by these emerging technologies. GIANT will deploy an Initial Operational 

Capability by the end of fiscal year 1998 both to support early Station operations and to verify concepts and hardware/software suites needed 

for a Full Operational Capability. 

Accomplishment 

A task agreement has been negotiated with Jet Propulsion Laboratory's Multimedia Lab for architecture consulting, and systems 

engineering/integration. Evaluation of 3 leading commercial off-the-shelf systems has been completed, and an initial buy of 4 systems will be 

submitted for approval by mid-August. GIANT is establishing the charter prototype capability for the newly formed Johnson Space Center 

Collaborative Environment User's Group. 

Background 

Manpower and travel cuts demand that new ways be found to accomplish the Station mission. Telepresence offers alternatives to 

physical meetings (too expensive) and audio-only (inadequate). Telepresence concepts are particularly cost-effective in terms of investment 

($5K for desktop tools vs. $50K for ViTS rooms) and operation ($120/hour vs. $1000/hour), as well as eliminating time lost while traveling. 

The GIANT project integrates emerging technologies to provide a mission capability. 

For further technical information, contact Bruce Hilty at (281) 483-1932 

Telecommunications 71 
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Flammability Testing of Composites Using Cone Calorimetry 

Benefit 

During combustion, oxygen depletion occurs in confined spaces such as building fires. The controlled-environment cone calorimeter 

provides a unique capability by allowing evaluation of fire parameters under oxygen-depleted conditions of ground fires and under oxygenenriched environments encountered in spacecraft environments. The comprehensive data acquired with this apparatus provides the majority of 

fire parameters used for modeling, allowing for future fire-safe designs. 

Accomplishment 

Fully developed fires were simulated for composites. The controlled-atmosphere cone calorimeter test showed that phenolic composites 

had the lowest ignitability. peak heat release rate, propensity to flashover, and smoke production rate among the composites evaluated (flameretarded epoxy composites and phenolic composites containing fiberglass, ararnid, and graphite fiber-reinforcements). Phenolic/graphite 

showed the highest flame resistance. 

Background 

A commercially available cone calorimeter was modified to allow testing in oxygen concentrations from 0% to 50%. The cone 

calorimeter test measures the ignitability, heat release rate, total heat released, effective heat of combustion, specific extinction area, soot yield, 

mass loss rate, and the evolution of CO, C02

, and other combustion products. In the controlled-atmosphere cone calorimeter, the sample is 

exposed to a specific incident heat flux in a horizontal or vertical orientation and bums in a controlled oxygen environment. The inflow 

combustion gas is provided by mixing oxygen and nitrogen at different ratios. The heat release rate during combustion, which is generally 

considered to be one of the most important fire properties of materials, is measured by using the oxygen-consumption principle. The principle 

depends on the fact that the heat of combustion of most organic materials per unit mass of oxygen consumed is essentially constant and has an 

average value of 13.1 MJ/kg. The mass loss rate is measured using a load cell, and the specific extinction area is measured using a heliumneon laser. The CO and C02 yield during combustion is determined by a CO/C02 analyzer. 

For further technical information, contact Harry Johnson at (505) 524-5722 or harry.p.johnsonl @wstf.nasa.gov 

Test & Measurement 73 
-

Closed-Loop Test Configuration to Measure Velocity Rates 

74 Test & Measurement 
Johnson Space Center 

Fluid Flow Measurements Using Series Probes 

Benefit 

These probes have demonstrated an ability to measure volume fractions, fluid velocities, slug passage, slug lengths, bubble passage, and 

bubble size. They show promise of working effectively on the expected flow regimes in an oil well line. Potentially, the probes could have 

many useful applications in industries ranging from aerospace to oil and gas. 

Accomplishment 

There are many potential applications for probes of this type in industry and government. Possible aerospace applications include 

measurements of heliurn!hydrazine flow during rocket tests at White Sands Test Facility, liquid/gas flow in hydrogen or oxygen lines in Orbiter 

engines, and liquid/gaseous Freon flow in zero-g tests with the KC-135 aircraft at the Johnson Space Center. Oil industry representatives have 

expressed interest in the probes as a potential method of measuring the fraction and velocity of oil, water, and natural gas flowing in a pipeline, 

and for monitoring the oil contamination (traces) in water for environmental compliance. 

This technique has other potential space applications in measuring the flow of liquid and gaseous oxygen or hydrogen under zero-g 

conditions within the Space Station. It also has ground-based applications in measuring gas-water-oil flow from undersea oil wells as well as 

other possible uses in measuring volume fractions and the velocity of multiple liquids having different dielectric constants. A patent (5675259) 

was issued on 10/7/97 

Background 

These probes were developed to help measure the volume fraction of two or more fluids flowing through a pipe or mixing in a reservoir. 

Each probe measures the instantaneous complex dielectric constant of the fluid in intermediate proximity. As long as separation of the 

complex dielectric constants of each fluid is possible, several or even many fluids can be identified and measured in the same flow stream or 

reservoir. By using multiple probes, the velocity of each fluid as well as the distribution of each constituent can generally be determined. 

Computations are made from data streams taken by each probe. The closed-loop test configuration used to measure the velocity rates of slug 

flow and homogeneous flow for mixtures of oil, water, and air (gas) is pictured opposite. 

The catalyst for the development of a radio frequency/microwave technique for measuring two-phase flow was a need to monitor the 

flow of monomethyl hydrazine and helium through an inlet pipe of a reaction control system at the White Sands Test Facility. The relative 

amounts of helium and hydrazine flowing into the thruster jet could not be instantaneously measured. Researchers realized that, since the 

relative dielectric constants of helium (approximately 1) and hydrazine (approximately 19.2) were sufficiently different, the fluids could easily 

be identified by the different impedance seen by a capacitance probe. 

Some potential applications of the AC fluid flow probe would require the use of multiple probes placed in the flow stream. For example, 

consider the problem of measuring the volume fraction of oil, water, natural gas, and oil/water emulsions flowing in a pipeline. The number of 

possible flow regimes influences where the probes are located in the flow stream. Placing probes at strategic locations within a cross-section 

of the pipe, the volume fractions of each constituent can be calculated statistically from the information obtained by each probe in the data 

stream. Also, by using at least two probes separated by a known distance, the velocity of each constituent can, in most cases, be measured. 

Probes must be designed to have minimum effect on the flow while having good strength and durability characteristics. Additionally, the 

probes should be as self-cleaning as possible and not interfere with each other either electrically or physically. The sampling rate can be high, i.e., 

thousands of samples per second. Tests have successfully shown the presence and identity of minute discontinuities within a continuous flow. 

For further technical information, contact Dickey Arndt at (281) 483-1438 or g.d.arndtl @jsc.nasa.gov 

Test & Measurement 75 
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76 Test & Measurement 
Johnson Space Center 

Fluid Flow Volume Measurements 

Benefit 

Researchers at Johnson Space Center (JSC) are interested in a flow meter that can accurately measure (to within ± 4%) the volume of 

urine voided by astronauts in a zero-g environment (approximately 200 to 900 milliliters). The current urine monitoring system does not meet 

the required tolerance at the low volume or high volume end. A capacitance probe has been developed to measure the flow volume of a single 

homogeneous fluid for slow flow rates. This probe design is a modification of another probe, also developed at JSC, to measure volume 

fractions, flow rates, and flow regimes of multiple fluids flowing through a pipe. The primary modification to the probe is that all flow is 

directed through the active region, or orifice. 

Accomplishment 

This capacitance probe has demonstrated the capability of measuring total fluid volume of a single fluid for slow to moderate flow rates. 

Some variations in flow rates can be accommodated with little impact on measurement accuracy, as long as some maximum flow rate is not 

exceeded for a given probe. If the flow rate profile is known and is the same for each trial run, volume measurements can be made with great 

accuracy. 

The probe may have application for the measurement of urine volume in a low-gravity environment. At the present stage of 

development, the probe can provide volume measurements to within ±4% using tap water. Variations in urine salt content are measured by a 

conductance probe and a correction factor is applied to the volume measurement to account for the differences in conductance. 

This technique is now being developed into a prototype system for a flight demonstration. A patent (#5,596,150) was issued on 1121197 

for this probe technique. 

Background 

Analysis reveals that a narrow orifice helps avoid the nonlinearity at differing flow rates. The geometry of the probe's deflector and the 

air flow control also influence linearity. The key to the probe's performance is an increasing flow rate which results in more of the orifice 

being filled with liquid, without completely blocking air flow. 

The active region of the capacitance probe is formed by the center conductor extension of a 1 /8-in. coaxial cable and the outer shield of 

two other segments of coaxial cable. The length of the active region is approximately 1 in. now, but can be increased to accommodate larger 

flow rates. 

The outer segment coaxial cables can also provide the necessary rigidity for most applications. The probe's active region is two-sided to 

double the flow volume. The coaxial cable can be made of any length desired and, provided that cable losses do not exceed 1 or 2 dB, has 

minimal effect on the performance. 

For the most accurate volume measurements, the probe was designed to exacting characteristics. The volumetric meter pictured opposite 

uses radio frequency electronics to provide quadrature phase detection for both a capacitance probe and a conductance probe for volume 

measurements. The conductance probe is used to derive a correction factor for salt content to obtain a true volume. 

For further technical information, contact Dickey Arndt at (281) 483-1438 or g.d.arndt1 @jsc.nasa.gov 

Test & Measurement 77 
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Johnson Space Center 

Instrumented Mechanical Impact Test (/MIT) Facility 

Benefit 

New state-of-the-art high-strength. lightweight, composite overwrapped pressure vessels (COPYs) are currently in use on spacecraft for 

the high-pressure containment of gases and/or propellants. COPYs are highly susceptible to impact damage during all stages of spacecraft 

buildup, installation, and operation. A COPY rupture-in-use due to impact damage is a highly catastrophic event. The IMIT can provide the 

delivery of an "intelligent" impact to a COPY in either the pressurized or unpressurized condition and develop an impact damage profile. This 

profile comprises both impact magnitude measurement (quantitative) and damage indicators (qualitative). This work will contribute to the 

writing of industry standards which will then control COPY safe use. 

Accomplishment 

The facility consists of a remotely operated personal computer-controlled !MIT located within a high-pressure test cell. The IMIT is 

installed with a specially designed COPY blast enclosure which can accommodate most mid-sized high-pressure COPVs currently being 

manufactured for spacecraft use. The White Sands Test Facility is currently using this test facility in support of a joint U.S. Air Force/NASA 

program aimed at the enhanced technology of composite overwrapped pressure vessels. One of the major achievements of this program, along 

with impact damage threshold definition and characterization, will be a comprehensive impact damage control plan designed for COPY safe 

use. 

Background 

The facility contains a remotely operated industry-standard drop-weight-type impact tester which is equipped with semiconductor strain 

gages to record high-speed, real-time responses from impactor TUP/COPY impact events. Impact data (such as force vs. time, impact energy, 

impact velocity, rebound energy and maximum impact deflection) can be recorded in a digital format for subsequent analysis. This facility is 

configured to allow COPY pressurization to the required test pressure with either gaseous nitrogen or deionized water. The IMIT is installed 

with an integral blast enclosure designed to contain and dissipate any burst-upon-impact event that might occur during test. The blast 

enclosure is equipped with Lexan® view port(s) permitting high-speed filming of the impact events. Inside the blast enclosure a rigid 

mounting arrangement is provided which permits presentation of almost any point on the COPY surface to the impactor. This facility is 

designed for flexibility in use and can be reconfigured to accommodate almost any required reactive impact event involving both reactive test 

article(s) and/or reactive media such as liquid oxygen. 

For further technical information, contact Harry Johnson at (505) 524-5722 or harry.t.johnsonl @wstf.nasa.gov 

Test & Measurement 79 
00 

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Johnson Space Center , 

Liquid Metal Mirror for Optical Measurements of Orbital Debris 

Benefit 

Scientists at the Johnson Space Center have developed and built a unique tool for observing and measuring orbital debris-a telescope 

that uses liquid mercury to form a thin, reflective surface. Currently, the most sensitive tool for monitoring orbital debris in low Earth orbit is 

the Haystack radar used by NASA. For an optical telescope to approach the sensitivity of this radar, its optical collecting aperture would need 

to be very large, at least 3 m in diameter. The cost of such a mirror, which would have to be fabricated from glass or quartz, is conservatively 

estimated at over $5 million. Taking advantage of recent advances in mirror technology that use a rotating pool of liquid mercury, scientists 

worked on a low-cost alternative to the large glass mirror. They spent several years and approximately $400,000 developing and building a 

telescope that employs a liquid metal mirror 3 m in diameter. With its excellent optical quality, the telescope is expected to detect debris as 

small as 1 to 2 em orbiting at an altitude of 500 km. The optical quality of the telescope very nearly matches that of the Haystack radar, 

providing a low-cost alternative for monitoring the orbital debris environment. 

Accomplishment 

Haystack radar measurements of the small orbital debris population, as small as 1 em orbiting at 500 km, have been under way for about 

7 years. These statistical measurements give information about debris flux at various altitudes but lack detailed orbit information for each 

detected object. It has been known for some time that radar and optical techniques do not see exactly the same debris population. Some 

objects have high optical reflectivity but low radar reflectivity, and vice versa. This instrument can develop a statistical profile of orbital debris 

in low and middle Earth orbits as well as in geosynchronous orbit. Consequently, its optical measurements could be used to supplement radar 

measurements to get a more complete picture of the debris environment. Studies with the telescope will complement those being conducted 

with the Haystack radar. Comparing these two sets of data will provide a better understanding of the orbital debris environment-knowledge 

that is important for all orbiting spacecraft, including the planned Space Station. The telescope, which requires extremely dark skies for 

optimal performance, has been moved from Houston, Texas, to a location high in the mountains near Cloudcroft, New Mexico. 

Background 

The liquid mercury telescope functions much like the Haystack radar. It "stares" at a particular slice of space, observing those objects 

which pass through the selected area. Although most orbital debris studies use radar rather than telescopes, telescopes offer some distinct 

advantages. They are less expensive to operate and can detect objects in high orbits, such as geosynchronous orbits, with smaller collecting 

apertures. 

The largest component of the telescope is a parabolic dish just over 3 yards in diameter. Several gallons of liquid mercury pool in the 

center of the dish. To use the telescope, the dish is spun up to a rate of 10 rpm. Centrifugal force and surface tension cause the liquid mercury 

to spread out in a thin layer over the dish, creating a reflective surface as good as any polished glass mirror's. Because the dish must be 

extremely stable to produce this reflective surface, it rests on a cushion of air. 

Researchers are aware of the inherent dangers of working with liquid mercury. They observe a number of safety precautions and have 

established procedures for spills and safety processes. Over the next year at Cloudcroft, the telescope will continue to gather data on the 

orbital debris environment under a contract with the National Science Foundation and the Associated Universities for Research in Astronomy. 

Long-range plans are to move the telescope to a location on the equator where debris in low inclinations can be observed. 

For further technical information, contact Glen Cress at (281) 483-0414 or glen.h.cressl @jsc.nasa.gov 

Test & Measurement 81 
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Atmosphere Monitor 

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Mass Spectrometer 

Hydrogen Supply 

82 Test & Measurement 

Regolith 

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Spacecraft Sampler 

Furnace 

Command, Control & 

Data Computer 

Power 

Thermocouple 

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Power Controller 

Spacecraft 

Communication 

Regolith Evolved Gas Analyzer 

Spacecraft 

Power 

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Johnson Space Center 

Regolith Evolved Gas Analyzer (REGA) 

Benefit 

The extraction of oxygen is a key example of in situ resource utilization (ISRU) which will directly support an early human presence on 

the Moon. This is because one of the largest elements in any rocket is the oxidizer required to bum the fuel. Nearly 85% of the propellant 

mass of a liquid hydrogen-liquid oxygen rocket is oxygen. Locally produced oxygen for rocket propulsion promises by far the greatest cost 

and mass saving of any in situ resource for lunar applications. Human missions which employ ISRU will certainly be preceded by robotic 

spacecraft. Scientists and engineers at Johnson Space Center are currently developing flight instruments which will demonstrate oxygen 

production on the Moon. Oxygen can be extracted from the lunar soil, or regolith, by a variety of methods. One of the simplest and best 

studied is reduction of FeO by hydrogen gas, to produce water vapor. REGA is designed to demonstrate this process, as well as to measure 

volatiles and their interactions with the regolith. 

Accomplishment 

REGA is currently in the final year of development. The project includes design and prototyping of the furnace unit, sample load/dump 

system, gas plumbing, mass spectrometer, and data system, followed by integration of the various subsystems into a single functional 

instrument. To date we have: 

• Fabricated four prototype furnaces and two heater models for full-scale testing 

• Fabricated a gas delivery system 

• Integrated the REGA furnace prototype with a mass spectrometer 

• Demonstrated that the prototype furnace can repeatedly heat 1 g of lunar soil simulant to 900°C in hydrogen to extract oxygen 

• Quantified the effects of composition, temperature, and hydrogen flow rate on oxygen yield from 19 lunar soil and glass samples 

Currently we are constructing a complete initial REGA prototype. We will optimize the design in a second instrument and fabricate and 

program the control system. A parallel effort will complete a small dedicated mass spectrometer for integration into the REGA instrument. 

The final product of our three-year effort will be a fully operational breadboard instrument. All REGA subsystems are designed such that they 

can be upgraded for space qualification. We are producing an instrument with sufficient maturity that it can be successfully proposed for a 

variety of lunar and planetary missions. 

Background 

REGA's Regolith Reactivity Analysis mode will provide quantitative data on the interactions of planetary surface materials with a variety 

of gases. In the lunar application, regolith samples can be heated and reacted with hydrogen to liberate oxygen. The Evolved Gas Analysis 

mode will provide identification and quantitative data on volatile species evolved from the sample at various programmed temperature steps. 

Priority lunar targets include samples from permanently shadowed craters and the regolith of volcanic terrain containing volatiles from 

outgassing. REGA's Atmospheric Composition Analysis mode employs a mass spectrometer run in a configuration open to the atmosphere. 

Assuming that the spacecraft outgassing background can be overcome, this analysis will provide quantitative compositional data, including 

isotopic abundances. The mass spectrometer will monitor the atmosphere over time and may detect transient gas events. 

For further technical information, contact Dave McKay at (281) 483-5048 or david.s.mckayl @jsc.nasa.gov 

Test & Measurement 83 
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STS-74 Downlinked Video: Predicted by Model 

84 Test & Measurement 
Johnson Space Center 

Camera Images From Luminance Maps 

Benefit 

An accurate computer-based camera model will allow preflight lighting analysis to predict the best times during an orbit for camera 

viewing of a specific activity. Such analysis is critical to mission success for operations that depend on camera viewing. Quick assessment of 

lighting impacts due to flight schedule changes can also be provided with this predictive camera model. For example. the performance of the 

camera-based Space Vision System (SVS) during Space Station assembly will depend on good camera images during the Shuttle berthing 

operations for Station assembly and pre-launch camera selection and location can be optimized for examination of critical components while on 

orbit. 

Accomplishment 

Post-processing techniques of luminance maps created by a physically based lighting program were able to model the camera parameters 

of automatic light control (ALC) and gamma control (image transfer function) for the CTVC (Shuttle color camera). To model ALC, the 

lumiance map is scanned for a specified region that does not vary in luminance more than a designated amount determined by the ALC settings 

of average (AVG), normal (NORM) or peak (PEAK). A scale factor is then calculated that will display the average luminance in this area as 

the average brightness in the image (128 on a color scale between 0 and 255). This scale factor is applied to the entire image (Figure 1). The 

light entering the camera is displayed by controlling the CTVC camera with two gamma mode settings. GAMMA BLACK STRETCH and 

GAMMA LINEAR. For gamma control. only the camera's influence on the transfer function was modeled. Influences on the display from 

monitors and printers were not considered in this project. To validate results. computer-generated images were compared to ground-based 

images created with CTVC and lights. Video images broadcast from the Shuttle were also used for comparison as well. 

Background 

The purpose of this project is to develop and validate computer models of the Shuttle TV cameras based on the scene illumination and the 

camera parameters such as noise, gamma. and gain. The input to the camera model is an accurate computer calculation of the scene luminance, 

i.e .. the amount oflight reflected from objects in the scene into the camera lens. Such calculations can be very accurate but are slow ( -20 

minutes) to generate. This computer model of a Shuttle TV camera will allow pre-flight prediction of lighting conditions for camera-based 

operations. 

For further technical information, contact Jim Maida at (281) 483-1113 or james.c.maida 1 @jsc.nasa.gov 

Test & Measurement 85 

Johnson Space Center 

Variable Specific Impulse Magnetoplasma Propulsion 

Benefit 

This work is strongly geared toward a new space propulsion technology, enabling very rapid human and robotic transit to Mars (3 months 

one way) and beyond. In addition to their application to interplanetary travel, variable specific impulse magnetoplasma rockets (VASIMRs) 

will also have a profound effect on the economics of the commercial satellite market by virtue of their greatly improved payload mass fraction 

over conventional chemical rockets. The improvements in propulsion efficiency will enable access to and from geostationary space by orbit 

transfer vehicles using this technology. It will also allow the periodic maintenance and repair of large communications stations in orbit. 

Other areas of technology transfer include high-voltage and solid-state power conditioning and conversion, cryogenic fluid dynamics, 

gauging and control, space applications of new high-temperature superconducting materials at high magnetic field (2 - 3 Tesla), and a wide 

array of new plasma diagnostics for rapid collection of science and system data. Magnetoplasma technology will drive important developments 

in solid-state power devices, materials, coatings and magnetic energy storage systems using state-of-the-art superconductors. 

Accomplishment 

Plasma is generated and confined in the central cell of an asymmetric magnetic mirror. The device consists of a multi-coil central 

solenoidal cell with two high-field end cells. Ions and/or electrons are electromagnetically plasma-heated through cyclotron resonance heating. 

While the present configuration is potentially capable of steady-state operation, it is unnecessary to do so at this time. The scope of this 

investigation centers on achieving stability at the much shorter characteristic times associated with rapid (microseconds) plasma disruptions. 

Typical stable discharges can last from 1 to 10 seconds, depending on magnet heating constraints. Pure steady-state operation could be 

achieved in a superconducting device. 

Routine low-power plasma operations in the lab were demonstrated in the summer of 1995. No plasma instabilities were encountered, 

thus paving the way for high-power plasma discharges. Main effort in 1997 has been to configure the lab for high-power plasma operations 

and system diagnostics. Low-power plasma characterization in the central cell has been accomplished with reciprocating Langmuir and Mach 

probes. A newly designed Lorentz Force Accelerator has been installed and successfully fired into the system as a high-density plasma injector. 

Other radio frequency-based plasma injection devices, such as Helicon plasma sources, have also been tested and are being considered for full 

implementation. A full, 2-D code, mapping the magnetic field throughout the entire machine. has been developed. A Monte Carlo simulation 

which follows the trajectories of plasma particles in the magnetic expansion nozzle has also been developed. 

Background 

Our research group is pursuing the experimental characterization of high-density magnetized plasma discharges in our high-field facility 

located at the Advanced Space Propulsion Laboratory (ASPL). These studies focus on identifying plasma stability criteria as functions of 

density, temperature, and magnetic field strength. Plasma heating is accomplished by electron cyclotron resonance at frequencies of 2.45 and 

14.7 GHz. and by ion cyclotron resonance at 1-10 MHz. Plasma discharges in argon and helium are now routinely generated. Electron density 

and temperature are measured by a movable double Langmuir probe, and by fast Langmuir and Mach reciprocating probes. Ion exhaust 

velocity is measured by a retarding potential energy analyzer. System enhancements will include direct heating of hydrogen ions by these 

techniques, and much higher plasma densities. 

For further technical information, contact Franklin Chang-Diaz at (281) 244-8923 or franklin.chang-diazl @jsc.nasa.gov 

Transportation 87 
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Johnson Space Center · 

X-38 Project 

Benefit 

The X-38 is a technology demonstration vehicle designed to meet the generic requirements for a crew return vehicle (CRY), and to be 

capable of evolutionary growth to satisfy requirements for other human spacecraft. The International Space Station requires a CRY to provide 

a means for returning Station crew members to Earth for several contingency cases: (I) an ill or injured crew member who cannot wait until 

the next scheduled Shuttle flight to return to Earth; (2) a Station contingency which renders it uninhabitable; (3) the inability to perform 

resupply for the Station. The CRY derived from the X-38 is expected to be significantly cheaper than other CRY options that have been 

evaluated. 

Accomplishments 

Vehicle configuration studies and system trade studies, and bench tests of components and subsystems, conducted during 1995 and 1996 

provided definition of the vehicle concepts and an overall plan for the X-38 project. Scaled Composites fabricated airframes for two 

atmospheric test vehicles in 1996 and delivered them to the Johnson Space Center (JSC) for structural verification and systems installation & 

checkout. Flight testing of the parafoil to be used for landing illustrated the need for improvements in the parafoil deployment and flight 

characteristics. These modifications have been successfully addressed with an intensive analytical and sub-scale/full-scale test effort 

continuing through 1997. Outfitting and checkout of the first atmospheric flight test vehicle, vehicle 131, was completed in June 1997, and the 

vehicle was shipped to Dryden Flight Research Center (DFRC) for flight testing. At DFRC, NASA's B-52 will be used to carry the vehicle to 

altitude before the vehicle is released for a short period of free flight, followed by parafoil deploy and inflation, flight to the ground, and 

landing on the lake bed. Four B-52 captive carry flights have been accomplished to date to check out systems in the flight environment, verify 

procedures, and prepare for the actual release flight scheduled for February 1998. Vehicle 132, similar to 131 except for an active flight control 

system, is approaching completion at JSC and is planned to be shipped to DFRC in March 1998. The active flight control system of 132 will 

allow longer free-flight times and more detailed verification of vehicle aerodynamic characteristics and flight control system behavior. 

Aerodynamic analyses and wind tunnel testing are being performed to verify the effectiveness of outer mold line changes made to the 

basic X-24A shape to optimize the vehicle for the CRV application. The spaceflight test vehicle for the X-38 program. vehicle 201, has 

tentatively been assigned a flight date of March 200 I. Design reviews of V20 1 systems have been performed in late 1997, and construction of 

this vehicle has begun in building 220. The top-level performance requirements for the CRY derived from the X-38 are being baselined with 

the Space Station program. 

Background 

The Soyuz capsule will provide interim CRY function for the early Station. The Soyuz does not represent a viable long-term solution for 

the following reasons: (1) The crew size limitations imposed by Soyuz eliminates about 40% of the U.S. astronaut corps; (2) the crew training 

requirements for Soyuz represent a major impact to U.S. crew members; (3) the characteristics of the Soyuz do not make it satisfactory for 

transport of ill or injured crew members. Previous cost estimates for a CRY to replace the Soyuz were beyond the capability of the Station 

budget. In addition to its use as a Station CRY, other potential growth applications for the X-38 include an earth-to-orbit crew transport vehicle 

and a vehicle for other orbit-to-orbit transportation. The concept selected for the X-38 vehicle is a lifting body shape based on the USAF/ 

Martin X-24A flown in the 1960s. 

For further technical information, contact John Hooper at (281) 483-4471 or john.c.hooperl @jsc.nasa.gov 

Transportation 89 
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