Edited by Richard W. Orloff, 01/2001/Page 1 

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-69 

PRESS KIT 

AUGUST 1995 

WAKE SHIELD FACILITY-2 

SPARTAN-201; CAPL-02/GBA; IEH 
Edited by Richard W. Orloff, 01/2001/Page 2 

STS-69 INSIGNIA 

STS069-S-001 -- Designed by the crewmembers, the STS-69 insignia symbolizes the multifaceted nature of 

the flight's mission. The primary payload, Wake Shield Facility (WSF), is represented in the center by the 

astronaut emblem against a flat disk. The insignia also signifies the importance of human beings in space 

exploration, reflected by the planned space walk supporting Space Station assembly. The two stylized 

space shuttles highlight the ascent and entry phases of the mission. Along with the two spiral plumes, the 

stylized space shuttles symbolize a NASA first - the deployment and recovery on the same mission of two 

spacecraft (both the Wake Shield Facility and the SPARTAN). The constellations Canis Major and Canis 

Minor represent the astronomy objectives of the SPARTAN and International Extreme Ultraviolet 

Hitchhiker (IEH) payload. The two constellations also symbolize the talents and dedication of the support 

personnel who make Space Shuttle missions possible. 

S82-35627 -- The five points of the star in the STS-5 insignia represent the fifth, and first operational 

shuttle flight following four successful test flights. 

The NASA insignia design for space shuttle flights is reserved for use by the astronauts and for other 

official use as the NASA Administrator may authorize. Public availability has been approved only in the 

form of illustrations by the various news media. When and if there is any change in this policy, which we 

do not anticipate, it will be publicly announced. 

PHOTO CREDIT: NASA or National Aeronautics and Space Administration. 
Edited by Richard W. Orloff, 01/2001/Page 3 

PUBLIC AFFAIRS CONTACTS 

Ed Campion Policy/Management 202/358-1778 

 NASA Headquarters 

 Washington, DC 

 

 

Rob Navias 

 Johnson Space Center 

 Houston, TX 

Mission Operations 

Astronauts 

713/483-5111 

 

Bruce Buckingham 

 Kennedy Space Center, FL 

Launch Processing 

KSC Landing Information 

407/867-2468 

 

June Malone 

 Marshall Space Flight Center 

 Huntsville, AL 

External Tank/SRBs/SSMEs 205/544-0034 

 

Cam Martin 

 Dryden Flight Research Center 

 Edwards, CA 

DFRC Landing Information 805/258-3448 

For Information on STS-69 Experiments & Activities 

Jim Cast 

 NASA Headquarters 

 Washington., DC 

WSF-2, CGBA, CMIX, EPICS 202/358-1779 

 

Don Savage 

 NASA Headquarters 

 Washington, DC 

SPARTAN-201 202/358-1547 

 

Doug Isbell 

 NASA Headquarters 

 Washington, DC 

IEH 202/358-1547 

 

Mike Braukus 

 NASA Headquarters 

 Washington, DC 

BRIC, NIH-C4 202/358-1979 

 

Tammy Jones CAPL/GBA, GAS 301/286-5566 

 Goddard Space Flight Center 

 Greenbelt, MD 
Edited by Richard W. Orloff, 01/2001/Page 4 

CONTENTS 

GENERAL BACKGROUND 

General Release 5 

Media Services Information 7 

Quick-Look Facts 8 

DTOs/DSOs 9 

Shuttle Abort Modes 10 

Summary Timeline 11 

Orbital Events Summary 12 

Payload and Vehicle Weights 13 

Crew Responsibilities 14 

 

CARGO BAY PAYLOADS & ACTIVITIES 

Wake Shield Facility-2 (WSF-2) 15 

SPARTAN-201-03 22 

Extreme Ultraviolet Hitchhiker (IEH) 27 

Capillary Pumped Loop-2/Gas Bridge Assembly (CAPL-2/GBA) 31 

Get Away Special (GAS) 22 

STS-69 Extravehicular Activities (EVA) 35 

 

IN-CABIN PAYLOADS 

Space Tissue Loss/National Institutes of Health-Cells (STL/NIH-C) 36 

Commercial Generic Bioprocessing Apparatus-7 (CGBA) 37 

Biological Research in Canister (BRIC) 39 

Electrolysis Performance Improvement Concept Study (EPICS) 40 

Commercial MDA ITA Experiments (CMIX) 41 

 

STS-69 CREW BIOGRAPHIES 43 
Edited by Richard W. Orloff, 01/2001/Page 5 

RELEASE: 95-121 

TWO DEPLOY/RETRIEVE PAYLOADS AND A SPACEWALK 

HIGHLIGHT FIFTH SHUTTLE MISSION OF 1995 

The fifth Space Shuttle flight of 1995 will be highlighted by the deployment and retrieval of two scientific 

spacecraft and a spacewalk to practice for Space Station activities and evaluate space suit design 

modifications. 

Leading the five-person STS-69 crew will be Mission Commander David M. Walker, making his fourth 

space flight. Pilot for the mission is Kenneth D. Cockrell, making his second flight. The three mission 

specialists are James S. Voss, serving as Payload Commander and Mission Specialist 1. Voss will be 

making his third flight. Jim Newman, Mission Specialist 2 is making his second flight and Michael L. 

Gernhardt, Mission Specialist 3 is making his first flight. 

Launch of Endeavour is currently scheduled for August 5, 1995, at 10:45 a.m. EDT. The planned mission 

duration is 10 days, 20 hours and 29 minutes. An on-time launch on August 5 would produce a landing at 

7:14 a.m. EDT on August 16 at the Kennedy Space Center’s Shuttle Landing Facility. 

The STS-69 mission will mark the second flight of the Wake Shield Facility-2 (WSF-2), a 12-foot 

diameter, stainless steel disk which will be deployed and retrieved using the Shuttle robot arm. While the 

WSF flies free of the Shuttle, it will generate an “ultra-vacuum” environment in space within which to 

grow thin semiconductor films for next-generation advanced electronics. The commercial applications for 

these new semiconductors include digital cellular telephones, high- speed transistors and processors, fiber 

optics, opto-electronics and high-definition television. 

The SPARTAN 201 free-flyer will be making its third flight aboard the Shuttle. The SPARTAN 201 

mission is a scientific research effort aimed at the investigation of the interaction between the Sun and its 

outflowing wind of charged particles. SPARTAN’s goal is to study the outer atmosphere of the Sun and its 

transition into the solar wind that constantly flows past the Earth. 

This flight of SPARTAN 201 is intended to coincide with the passage of the Ulysses spacecraft over the 

Sun’s north polar region. Ulysses, a cooperative deep space mission of the European Space Agency and 

NASA, was launched from the Space Shuttle in 1990 with the goal of studying the Sun at high 

heliographic latitudes. 

Last year, Ulysses flew over the south pole of the Sun, becoming the first spacecraft ever to do so. The 

spacecraft returned a wealth of scientific information about this previously unexplored region. Recently, 

Ulysses data observed, for the first time, periodic oscillations originating from deep within the Sun’s 

interior. 

STS-69 will see the first flight of the International Extreme Ultraviolet Hitchhiker (IEH-1), the first of five 

planned flights to measure and monitor long-term variations in the magnitude of absolute extreme 

ultraviolet (EUV) flux coming from the Sun, and to study EUV emissions from the plasma torus system 

around Jupiter originating from its moon Io. 

Also flying aboard Endeavour will be the combined Capillary Pumped Loop-2/Gas Bridge Assembly 

(CAPL-2/GBA) payload. This experiment consists of the CAPL-2 Hitchhiker payload designed as an inorbit microgravity demonstration of a cooling system planned for the Earth Observing System Program and 

the Thermal Energy Storage-2 payload, part of an effort to develop advanced energy generation 

techniques. Also a part of this payload are several Get Away Special (GAS) experiments which will 

investigate areas such as the interaction of spacecraft attitude and orbit control systems with spacecraft 

structures, fluid-filled beams as structural dampers in space and the effects of smoldering combustion in a 

long-term microgravity environment. 
Edited by Richard W. Orloff, 01/2001/Page 6 

On the tenth flight day, two astronauts will leave Endeavour’s crew cabin for about six hours to perform 

several tasks that will broaden NASA’s experience base for building and maintaining the Space Station and 

for other future spacewalks. The astronauts will perform a number of tasks designed to evaluate and verify 

specific assembly and maintenance tasks for the Space Station. The spacewalk also will evaluate spacesuit 

design modifications to protect spacewalkers from the extremely cold space environment. 

Another payload being flown with a connection to the development of the Space Station is the Electrolysis 

Performance Improvement Concept Study (EPICS). Supply of oxygen and hydrogen by electrolyzing 

water in space will play an important role in meeting NASA’s needs and goals for future space missions. 

On-board generation of oxygen is expected to reduce the annual resupply requirement for the Space Station 

by approximately 12,000 pounds. The oxygen generation assembly which was initially baselined for the 

Space Station Freedom Program is the Static Feed Electrolyzer (SFE). The EPICS hardware being flown 

on STS-69 will demonstrate and validate the SFE electrochemical process in microgravity, as well as 

investigate performance improvements thought possible in a microgravity environment. 

There are various payloads which have made several flights aboard the Space Shuttle which will be flying 

once again. The payloads are the National Institutes of Health- Cells-4 (NIH-C4) experiment that will 

continue examining bone loss during space flight; the Biological Research in Canister-6 (BRIC-6) that will 

continue the study of the processing of outside signals by mammalian cells and the gravity-sensing 

mechanism within mammalian cells, which scientists are still trying to identify. 

Two other frequent flyers on the Shuttle are the commercial experiments (CMIX-4) whose objectives will 

include analysis of cell change in microgravity along with studies of neuro-muscular development 

disorders. Also flying is the Commercial Generic Bioprocessing Apparatus-7 (CGBA-7). CGBA is a 

secondary payload that serves as an incubator and data collection point for experiments in pharmaceuticals 

testing and biomedicine, bioprocessing and biotechnology, agriculture and the environment. 

STS-69 will be the 9th flight of Space Shuttle Endeavour and the 71st flight of the Space Shuttle System. 

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS.) 
Edited by Richard W. Orloff, 01/2001/Page 7 

MEDIA SERVICES INFORMATION 

NASA Television Transmission 

NASA Television is available through Spacenet-2 satellite system, transponder 5, channel 9, at 69 degrees 

West longitude, frequency 3880.0 MHz, audio 6.8 Megahertz. 

The schedule for television transmissions from the Orbiter and for mission briefings will be available 

during the mission at Kennedy Space Center, FL; Marshall Space Flight Center, Huntsville, AL; Dryden 

Flight Research Center, Edwards, CA; Johnson Space Center, Houston; NASA Headquarters, Washington, 

DC. The schedule will be updated to reflect changes dictated by mission operations. 

Television schedules also may be obtained by calling COMSTOR 713/483-5817. COMSTOR is a 

computer data base service requiring the use of a telephone modem. A voice update of the television 

schedule is updated daily at noon Eastern time. 

Status Reports 

Status reports on countdown and mission progress, on-orbit activities and landing operations will be 

produced by the appropriate NASA newscenter. 

Briefings 

A mission press briefing schedule will be issued prior to launch. During the mission, status briefings by a 

Flight Director or Mission Operations representative and when appropriate, representatives from the 

payload team, will occur at least once per day. The updated NASA television schedule will indicate when 

mission briefings are planned. 

Access by Internet 

NASA press releases can be obtained automatically by sending an Internet electronic mail message to 

domo@hq.nasa.gov. In the body of the message (not the subject line) users should type the words 

“subscribe press- release” (no quotes). The system will reply with a confirmation via E-mail of each 

subscription. A second automatic message will include additional information on the service. 

Informational materials also will be available from a data repository known as an anonymous FTP (File 

Transfer Protocol) server at ftp.pao.hq.nasa.gov under the directory /pub/pao. Users should log on with the 

user name “anonymous” (no quotes), then enter their E-mail address as the password. Within the /pub/pao 

directory there will be a “readme.txt” file explaining the directory structure. 

The NASA public affairs homepage also is available via the Internet. The page contains images, sound and 

text (press releases, press kits, fact sheets) to explain NASA activities. It also has links to many other 

NASA pages. The URL is: http://www.nasa.gov/hqpao/hqpao_home.html

Pre-launch status reports from KSC are found under ftp.hq.nasa.gov/pub/pao/statrpt/ksc, and mission 

status reports can be found under ftp.hq.nasa.gov/pub/pao/statrpt/jsc. Daily TV schedules can be found 

under ftp.hq.nasa.gov/pub/pao/statrpt/jsc/tvsked. 

Access by fax 

An additional service known as fax-on-demand will enable users to access NASA informational materials 

from their fax machines. Users calling (202) 358-3976 may follow a series of prompts and will 

automatically be faxed the most recent Headquarters news releases they request. 

Access by Compuserve 

Users with Compuserve accounts can access NASA press releases by typing “GO NASA” (no quotes) and 

making a selection from the categories offered. 
Edited by Richard W. Orloff, 01/2001/Page 8 

STS-69 QUICK LOOK 

Launch Date/Site: August 5, 1995/KSC Launch Pad 39B 

Launch Time: 10:45 a.m. EDT 

Launch Window: 2 hours, 30 minutes 

Orbiter: Endeavour (OV-105) - 9th flight 

Orbit/Inclination: 200 nautical miles/28.45 degrees 

Mission Duration: 10 days, 20 hours, 29 minutes 

Landing Date: August 16, 1995 

Landing Time: 7:14 a.m. EDT 

Primary Landing Site: Kennedy Space Center, FL 

Abort Landing Sites: Return to Launch Site: - KSC 

 Transoceanic Abort Landing: - Banjul, The Gambia 

 Ben Guerir, Morocco 

 Moron, Spain 

 Abort Once Around - Edwards AFB, CA 

 

Crew: Dave Walker, Commander 

 Ken Cockrell, Pilot 

 Jim Voss, Payload Commander, Mission Specialist 1 

 Jim Newman, Mission Specialist 2 

 Mike Gernhardt, Mission Specialist 3 

 

EVA Crewmembers: Voss (EV 1), Gernhardt (EV 2) 

 

Cargo Bay Payloads: Wake Shield Facility 

 SPARTAN-201 

 IEH-01 

 CAPL/GBA 

 

Middeck Payloads: BRIC 

 CGBA 

 CMIX 

 EPICS 

 STL/NIH-C 
Edited by Richard W. Orloff, 01/2001/Page 9 

Developmental Test Objectives/Detailed Supplementary Objectives 

DTO 301D: Ascent Structural Capability Evaluation 

DTO 305D: Ascent Compartment Venting Evaluation 

DTO 306D: Descent Compartment Venting Evaluation 

DTO 307D: Entry Structural Capability 

DTO 312: ET TPS Performance 

DTO 414: APU Shutdown Test 

DTO 415: Water Spray Boiler Electrical Heater Capability 

DTO 653: Evaluation of the MK-1 Rowing Machine 

DTO 656: PGSC Single Event Upset Monitoring 

DTO 667: Portable In-Flight Landing Operations Trainer (PILOT) 

DTO 671: EVA Hardware for Future EVA Missions 

DTO 672: EMU Electronic Cuff Checklist 

DTO 679: KU-Band Communications Adapter Demonstration 

DTO 700-8: GPS Developmental Flight Test 

DTO 700-10: Orbiter Space Vision System Flight Video Taping 

DTO 805: Crosswind Landing Performance 

DTO 831: Manipulator Position Display as an Aid to RMS Operators 

DTO 833: EMU Thermal Comfort Evaluations 

DTO 914: Space Linear Acceleration Mass Measurement Device Evaluation 

DTO 1210: EVA Operations Procedure/Trainer 

DSO 482: Cardiac Rhythm Disturbances During EVA 

DSO 483: Back Pain Pattern in Microgravity 

DSO 485: Inter Mars TEPC 

DSO 489: EVA Dosimetry Evaluation 

DSO 491: Characterization of Microbial Transfer During Space Flight 

DSO 492B: In-Flight Evaluation of a Portable Clinical Blood Analyzer 

DSO 494: Influence of Microgravity and EVA on Pulmonary Oxygen Exchange 

DSO 604: Visual Vestibular Integration as a Function of Adaptation 

DSO 605: Postural Equilibrium Control During Landing/Egress 

DSO 608: Effects of Space Flight on Aerobic and Anaerobic Metabolism in Exercise 

DSO 610: In-Flight Assessment of Renal Stone Risk 

DSO 624: Pre and Postflight Measurement of Cardiorespiratory Responses to Submaximal Exercise 

DSO 901: Documentary Television 

DSO 902: Documentary Motion Picture Photography 

DSO 903: Documentary Still Photography 
Edited by Richard W. Orloff, 01/2001/Page 10 

SPACE SHUTTLE ABORT MODES 

Space Shuttle launch abort philosophy aims toward safe and intact recovery of the flight crew, Orbiter and 

its payload. Abort modes for STS-69 include: 

• Abort-To-Orbit (ATO) -- Partial loss of main engine thrust late enough to permit reaching a minimal 

105-nautical mile orbit with the orbital maneuvering system engines. 

• Abort-Once-Around (AOA) -- Earlier main engine shutdown with the capability to allow one orbit of 

the Earth before landing at the Edwards AFB, CA. 

• Transatlantic Abort Landing (TAL) -- Loss of one or more main engines midway through powered 

flight would force a landing at either Banjul, The Gambia; Ben Guerir, Morocco; or Moron, Spain. 

• Return-To-Launch-Site (RTLS) -- Early shutdown of one or more engines, and without enough energy 

to reach a TAL site, would result in a pitch around and thrust back toward the Kennedy Space Center 

until within gliding distance of the Shuttle Landing Facility. 
Edited by Richard W. Orloff, 01/2001/Page 11 

MISSION SUMMARY TIMELINE 

Flight Day 1 Flight Day 7 

Launch/Ascent WSF Plume Tests 

OMS-2 Burn WSF Retrieval 

IEH Activation 

WSF Activation Flight Day 8 

RMS Checkout WSF CHAWS Operations 

 WSF Berthing 

Flight Day 2 IEH Operations 

IEH Operations Cabin Depress 

CMIX Operations Electronic Cuff Checklist Checkout 

SPARTAN-201 Deploy 

Flight Day 9 

Flight Day 3 Off Duty Time 

Deorbit Burn GLO Operations 

IEH Operations EMU Checkout 

Rendezvous Burns Crew News Conference 

Exercise DTOs and DSOs 

Flight Day 10 

Flight Day 4 EVA Prep 

SPARTAN-201 Retrieval EVA (6 hours) 

WSF Communications Checkout 

Flight Day 11 

Flight Day 5 Flight Control System Checkout 

WSF Ram Cleaning and ADACS Checkout Reaction Control System Hot Fire 

WSF Deploy GLO Operations 

WSF Science Monitoring Cabin Stow 

 

Flight Day 6 Flight Day 12 

WSF Science Monitoring Deorbit Prep 

Secondary Experiment Operations Entry 

Rendezvous Burns KSC Landing 
Edited by Richard W. Orloff, 01/2001/Page 12 

STS-69 ORBITAL EVENTS SUMMARY 

Event Mission Elapsed Time Eastern Time/Date 

 

Launch 0/00:00 10:45 AM, August 5 

OMS-2 0/00:43 11:28 AM, August 5 

SPARTAN Release 1/00:33 11:18 AM, August 6 

SPARTAN Grapple 2/23:13 9:58 AM, August 8 

OMS-3 3/02:59 1:44 PM, August 8 

OMS-4 3/03:43 2:28 PM, August 8 

WSF Release 3/18:33 5:16 AM, August 9 

WSF Grapple 6/00:07 10:50 AM, August 11 

OMS-5 7/00:08 10:53 AM, August 12 

OMS-6 7/00:52 11:37 AM, August 12 

EVA Begins 8/17:03 3:48 AM, August 14 

EVA Ends 8/23:13 9:58 AM, August 14 

Deorbit Burn 10/19:29 6:14 AM, August 16 

Landing 10/20:29 7:14 AM, August 16 
Edited by Richard W. Orloff, 01/2001/Page 13 

PAYLOAD AND VEHICLE WEIGHTS 

 Pounds

 

Orbiter (Endeavour), empty and 3 SSMEs 174,249 

Wake Shield Facility (WSF) 4,364 

WSF Support Equipment 3,882 

SPARTAN-201 2,842 

SPARTAN-201 Support Equipment 2,405 

BRIC 54 

CGBA 121 

CMIX 70 

EPICS 102 

STL 69 

DTOs/DSOs 694 

Shuttle System at SRB Ignition 4,519,985 

Orbiter Weight at Landing 219,718 
Edited by Richard W. Orloff, 01/2001/Page 14 

STS-69 CREW RESPONSIBILITIES 

Task Prime Backup 

 

Wake Shield Systems Gernhardt Voss 

Wake Shield Science Newman Voss 

WSF Deploy and Retrieve Newman Voss 

SPARTAN Systems Gernhardt Voss 

SPARTAN Deploy/Retrieve Gernhardt Newman 

Rendezvous Walker Cockrell/Newman 

IEH Cockrell Voss/Walker 

BRIC Gernhardt Voss 

CAPL/GBA Newman Voss 

CGBA Voss Walker 

CMIX Gernhardt Voss 

EVA Voss Gernhardt 

EVA Coordinator Cockrell 

EVA RMS Newman 

EPICS Gernhardt Newman 

STL/NIH-C Cockrell Voss 

Earth Observations Cockrell Newman 
Edited by Richard W. Orloff, 01/2001/Page 15 

WAKE SHIELD FACILITY-2 (WSF-2) 

The Wake Shield Facility (WSF) is a 12-foot diameter, stainless steel disk designed to generate an “ultravacuum” environment in space within which to grow thin films for next generation advanced electronics. 

This mission -- the second in a planned series of four -- represents the utilization of a unique attribute of 

space, the “ultra-vacuum.” The STS-69 crew will deploy and retrieve WSF-2 during the mission. NASA’s 

Office of Space Access and Technology, Wash. DC, is the sponsor of the WSF-2. 

The principle objectives of the WSF-2 mission include: performance of WSF as a free-flyer far enough 

away from the Orbiter to achieve and characterize for the first time an uncontaminated “ultra-vacuum” in 

low-Earth orbit; and, demonstrate the feasibility of epitaxial growth of high quality compound 

semiconductor thin films and heterostructures required for future advanced electronic and optoelectronic 

devices as part of the four-flight WSF proof-of-concept program. 

The first flight of the WSF-1 occurred aboard Discovery on STS-60 in February of 1994. Because of 

difficulties in attitude control, experiments were performed only while WSF-1 was attached to the Shuttle’s 

robot arm. Although the results of WSF-1 did demonstrate wake formation and thin film growth, water 

vapor contamination from the Shuttle interfered with the achievement of “ultra vacuum” necessary for 

achieving the growth of semi-conductor materials superior to those that can be grown on Earth. Following 

this first flight, a WSF advisory committee reviewed flight anomalies and approved corrective actions. 

Subsequently, a NASA independent review board evaluated all systems and unanimously agreed that 

WSF-2 was ready for flight. 

Results from the four planned WSF flights may have a significant impact on the microelectronics industry 

because the use of advanced semiconducting thin film materials in electronic components holds a very 

promising economic advantage. The commercial applications for high quality semiconductor devices are 

most critical in the areas of cellular telephones, high-speed transistors and processors, high-definition 

television, fiber optic communications and opto-electronics. The majority of electronic components used 

today are made of the semiconductor silicon, but there are many other materials that could achieve higher 

predicted performance than silicon. Atomic quality, sample size, and sample processing all suffer for 

compound semiconductors, and improving these parameters would result in high quality semiconductor 

materials which could lead to a new generation of electronic components. 

Epitaxy, the growth of atomically ordered thin films in a vacuum environment, is one method of generating 

such advanced materials. A prime barrier to improving epitaxial films is the limit on the quality of the 

vacuum which can be generated in an industrial growth chamber. To improve the material, the vacuum in 

which it is grown must be improved. The vacuum of space can make this improvement possible. 

Low-Earth Orbit (LEO) space can be used to grow compound semiconductor materials such as gallium 

arsenide, by creating a vacuum “wake” behind an object moving in orbit. The moderate natural vacuum in 

LEO has enough atoms present to contaminate a growing film. A vehicle in orbit, such as the WSF, can 

push those atoms out of the way, leaving few, if any, behind in its wake, thus the name. The unique ultravacuum produced in space by the WSF will be 1,000 to 10,000 times better than the best laboratory 

vacuum chambers on Earth. Using this ultra-vacuum in space, the WSF holds the promise of producing the 

next generation of semiconductor materials and the devices they will make possible. 

The WSF was designed, built, and managed by the Space Vacuum Epitaxy Center (SVEC)--a NASA 

Center for the Commercial Development of Space based at the University of Houston, -- with its principle 

industry partner, Space Industries, Inc. (SII), League City. Twelve additional corporate partners support the 

WSF program, including: Advanced Modular Power Systems, Ann Arbor, MI; American Xtal Technology, 

Dublin, CA; AKZO Chemicals, Inc., Houston, TX; Honeywell Satellite Systems, Phoenix, AZ; Ionwerks, 

Houston, TX; International Stellar Technology, Inc., Houston, TX; Instruments, S.A., Inc., Edison, NJ; 

Lockheed Martin, Syracuse, NY; MKS Instruments, Andover, MA; and S. I. Diamond, Inc., Houston, TX. 

In addition, Baylor University, Case Western Reserve University, Lamar University, the University of 

Texas 
Edited by Richard W. Orloff, 01/2001/Page 16 

at Dallas, the University of Texas at Austin; the University of Toronto; NASA’s Johnson Space Center, 

NASA’s Marshall Space Flight Center, NASA’s Lewis Research Center, and the U.S. Air Force Phillips 

Laboratories are members of the SVEC consortium. 

Program Overview 

The space ultra-vacuum concept was first identified by NASA more than 20 years ago, but there was no 

need identified at that time for its use. The recent interest of scientists and corporate researchers in epitaxial 

thin film growth has motivated the use of space to create the ultra-vacuum in which to grow better thin 

films. 

Recognizing this scientific opportunity as a new economic opportunity in 1987, SVEC formed a 

consortium of interested industries, academic institutions and government laboratories to utilize LEO for 

thin film growth. In 1989, SVEC partnered with its industry members, led by SII, Inc., and with NASA’s 

Johnson Space Center to build the WSF using an innovative commercial approach. 

The SVEC commercial approach to space hardware development foregoes extensive paperwork, uses 

commercial off-the-shelf hardware where possible, and maintains design simplicity, while not 

compromising safety. It does, however, prudently accept some risk in mission success through not 

designing for the traditional 100% reliability goal of most aerospace programs. This unique approach has 

allowed the WSF to be produced at less than one sixth or $30 million -- the cost of a traditional aerospace 

hardware development program -- in a 10-year period. 

Hardware Description 

The WSF hardware consists of the Shuttle Cross Bay Carrier mounting equipment and the Free Flyer. The 

Carrier remains in the Shuttle and has a latch system which holds the Free Flyer to it. The Shuttle’s robot 

arm will be used to remove the Free Flyer from the Carrier and deploy it into space. The WSF will follow 

behind the Shuttle at a station- keeping distance of 30 nautical miles. 

The Free Flyer is a fully-equipped spacecraft on its own, with cold gas propulsion for separation from the 

Shuttle and a momentum bias attitude control system. Sixty kilowatt- hours of energy, stored in silver-zinc 

batteries, power the thin-film growth furnaces, substrate heaters, process controllers, and a sophisticated 

array of vacuum characterization devices, including mass spectrometers and total pressure gauges. 

Weighing approximately 8,100 pounds altogether, (the Free Flyer itself is 4,350 pounds), the WSF 

occupies one quarter of the Shuttle payload bay. Process control equipment and vacuum characterization 

equipment are located on the back (wake side) of the free flyer, while the controller electronics, attitude 

control system, batteries and support equipment are located on the front (ram side). The WSF radio 

frequency communications system routes telemetry and commands, including video, from the Cross Bay 

Carrier, through the Shuttle systems to both WSF ground personnel and the flight crew. 

The WSF as a Versatile Space Platform 

As a free-flying platform, the WSF’s wake side -- the “ultra-clean side” -- is used on this mission primarily 

for ultra-pure thin-film growth. The ram side --the “dirty side” -- houses the avionics platform and also is 

used to accommodate other experiments and space technology applications. The ram side has more than 65 

square feet of usable surface in the form of the outer shield, which will support other space payloads. 
Edited by Richard W. Orloff, 01/2001/Page 17 

Since the WSF is mounted horizontally in the Shuttle payload bay, the open volume below the WSF is 

effectively used by mounting additional payload canisters on the Cross Bay Carrier. The Carrier’s power 

and data capabilities are extended to the payload canisters, prompting the name “Smart Cans.” Based on 

NASA’s Goddard Space Flight Center’s Get Away Special Canisters (GAS Cans), the Smart Cans also 

provide the opportunity for other payloads to fly with the WSF (however, they stay inside the Orbiter 

payload bay during the entire mission.) Candidates for these supplemental payload opportunities have been 

actively pursued by SVEC, resulting in nine additional experiments being undertaken on WSF-2 in a 

cooperative manner. 

What is Epitaxial Thin Film Growth? 

Epitaxial thin film growth is an approach to generating atomically ordered thin films of semiconductor 

oxides and metals with a reduced number of defects through the growth of material on a crystalline 

substrate in a vacuum. In epitaxy, a prepared surface, or substrate, is exposed in a vacuum to atomic or 

molecular beams of elements such as aluminum (Al), arsenic (As), gallium (Ga), or indium (In). The 

substrate acts as an atomic pattern, or template, upon which the atoms form crystalline thin films. The 

atoms grow in layers which follow the atomic structure pattern of the substrate. A thin film of new 

materials then grows on top of the substrate in an atom-by-atom, atomic-layer-by-atomic-layer manner to 

form a “wafer” with an ultra-high purity. This growth technique is defined as Molecular Beam Epitaxy, 

and has been used as a laboratory technique for studies in new thin film electronic materials for the past 20 

years. It has been shown during this time that the vacuum environment within which the materials are 

grown is critical to the quality of the thin film. 

WSF-2 can grow epitaxial thin films on seven different substrate wafers with material from seven different 

source furnaces, or cells. The principle objectives of thin film experiments are the growth of high purity 

films and high electron mobility structure in aluminum, gallium, arsenide type systems. 
Edited by Richard W. Orloff, 01/2001/Page 18 

Cooperative Payloads: Free-Flyer Experiments 

The Global Positioning System (GPS) is a dual mode experiment from the University of Texas at Austin 

using a GPS receiver to determine precision position and velocity of the WSF and employing GPS signal 

strength attenuation to determine atmospheric temperature profiles. Partially funded by a NASA Johnson 

Space Center regional university grant, the GPS experiment will operate during the free flight portion of 

the WSF mission recording position, velocity, signal strength and diagnostic information. The system will 

be activated by ground command from the JSC Payload Operations Control Center (POCC). Data will be 

collected onboard, stored in an unique solid state recording device developed for this mission by JSC, and 

analyzed post flight. 

NASA engineers and scientists working jointly with SVEC will undertake the ambitious Shuttle Plume 

Impingement Experiment in support of Space Station development. The complex interaction between 

Shuttle jet firings and space structures is a critical concern to Space Station planners. The WSF Free Flyer, 

loaded with environmental diagnostic equipment, is the ideal target for this study -- a cost- effective means 

to multiply benefits to differing program goals. A complex and extensive series of Shuttle thruster firings at 

a variety of distances from the WSF have been developed to use the WSF’s response as measure of the 

characteristics of the Shuttle’s thruster plumes. 

The Neutral Mass Spectrometer (NMS) was developed in a team effort by the University of Texas at 

Dallas and Lamar University, Beaumont, TX. This experiment will test a magnetic-sector field mass 

spectrometer designed to measure the ultra-vacuum created in the wake of the WSF. Located on the WSF 

outer shield, the NMS will be ground commanded for operations during the free flight portion of the WSF 

mission. 

The Cosmic Dust and Orbital Debris Experiment Monitor (CoDEM) is an experiment from the Baylor 

University Space Science Laboratory. This experiment will collect and characterize the near WSF 

environment with in-situ measurements of dynamic and physical characteristics of particulate matter. The 

ensemble of detectors will measure particle time-of-flight, impact plate plasma, and particle impact 

momentum. This experiment incorporates high sensitivity, high reliability integrated detectors into a 

package capable of returning captured materials for laboratory examination. 

This state-of-the-art detector will employ thin-film plasma, impact plate plasma, and particle impact 

momentum devices to measure hypervelocity impacts of cosmic dust or orbital debris. These measurements 

will permit determination of mass, density, and velocity. The experiment will attempt to capture dust grains 

using micropore foams and a substance called aerogel. CoDEM is a self-contained experiment which 

requires no interaction from the ground during on-orbit operations. 

The Earth Reference Attitude Determination System (ERADS), from Honeywell Satellite Systems, uses 

a combination of Earth and Sun sensors in combination on the rim of the WSF. The sensor has an annular 

field of view which permits Earth limb and star field viewing. ERADS is activated and controlled from the 

ground, collecting data in an on-board data recorder. Data will be processed post flight. Real time 

interaction is limited to state of health and system activation/deactivation. 

The University of Toronto Institute for Aerospace Studies has developed a Materials Exposure 

Experiment for collecting data on atomic oxygen interaction with various materials. This is a passive 

exposure experiment mounted on top of the WSF batteries facing into the velocity vector (ram direction). 

The experiment will expose over 150 samples of 26 different materials to the space environment. The 

objective is to gather data on how this affects these materials. 

The Hyper Velocity Impact Capture Experiment, developed by NASA’s Jet Propulsion Laboratory, is a 

passive debris collection/exposure experiment which has flown on previous Shuttle missions. The 

experiment has three collectors -- two on the WSF free flyer, and one remaining on the Cross Bay Carrier 

in the Shuttle payload bay. The objective is to measure space debris around the WSF and compare it to data 

collected on 
Edited by Richard W. Orloff, 01/2001/Page 19 

previous space flights. The two exposure plates on the free flyer are mounted on the outer shield, the large 

collector facing into the velocity vector and the smaller facing the opposite direction. 

The Cross Bay Carrier collector is mounted on the port side of the carrier facing out of the Shuttle bay. The 

objective is to gather information about the flow of debris around the WSF. The capture medium will be 

aerogel. 

Charging Hazards and Wake Studies (CHAWS), an experiment from the Air Force Phillips Laboratory 

located at Hanscom AFB, MA, expands the understanding of the interactions of the space environment 

with space systems and the hazards these interactions create for satellite systems. Goals are to: measure the 

ambient low energy positively charged particles, and study the magnitude and directionality of the current 

collected by a negatively charged object in the plasma wake. The experiment consists of two sensors and 

control electronics. The Langmuir probe is located on the wake side of the WSF, and the other sensor is 

located on the ram side at the nadir position near the edge of the outer shield. 

The CHAWS experiment will collect its primary data while the WSF is attached to the Shuttle robot arm. 

Shuttle attitude and the robot arm position will be varied to expose the sensors and allow the “mapping” of 

plasma wake around the Shuttle. Real-time data and command is used to control the CHAWS during the 

operations. The payload will be controlled by Air Force personnel from the JSC POCC. CHAWS 

operations will be conducted during a six-hour period at the conclusion of the WSF free flight mission. 

This experiment is a re- flight of the experiment flown during WSF-1 on STS-60. 

Cooperative Payloads: Cross Bay Carrier Experiments 

The Iowa Joint Experiment on Microgravity Solidification, constructed by the Iowa Space Grant 

Consortium, is carried in a WSF SMART Can located on the Cross Bay Carrier. The overall objective of 

the experiment is to examine the effects of a microgravity environment on the solidification process of a 

tin-cadmium alloy imbedded with particulate matter. The experiment consists of six test cells, heaters and a 

control processor located in the “Can”. The on-board computer is a 486 processor with 3 megabytes of 

flash memory. The cells, 1 inch diameter by 4 inches long stainless steel tubes, will be heated to melt the 

samples, held at this temperature, and then passively cooled. The temperature of the cells will be monitored 

and recorded by the on-board computer processor. Samples will be analyzed post-flight. 

During the WSF-2 mission, the experiment will be activated by the crew using the Shuttle standard switch 

panel. All experiment events are pre-programmed and the experiment will be autonomous. 

The Advanced Process Controller (APC) is a joint Space Industries and Space Vacuum Epitaxy Center 

venture for development and space qualification of a PC type process controller. Future uses of the 

controller include the automated control of the commercial WSF. The process controller will be located in 

a “Can” and will be used to monitor temperatures, current and voltage as well as providing relay control 

functions. The APC will be activated by the flight crew using the standard switch panel. Ground 

commanding will originate from the POCC at JSC. 

An engineering team at JSC has developed Long Range AutoTRAC, a video system for testing lightenhanced photogrammetric ranging techniques on-orbit. The video camera/light emitting diode (LED) 

combination instrument is located on the Wake Shield Cross Bay Carrier. The LEDs will illuminate four 

retroreflectors located on the ram side of the WSF, and the camera will view the returned light. Video 

images will be stored for post-flight analysis to determine range, bearing and attitude of the WSF. 
Edited by Richard W. Orloff, 01/2001/Page 20 

Other Experiments Supported by WSF 

The MagField Experiment undertaken by tenth grade students at Gregory Jarvis High School in Mohawk, 

New York, will determine the variation of the Earth’s magnetic field from magnetometer and electron 

diffraction data obtained during the Wake Shield mission. An electron beam, used for in-situ diffraction 

measurement of the atomic structure of growing semiconductor thin films, is deflected by the Earth’s 

magnetic field. The amount and direction of the deflection can be used to determine the magnitude and 

direction of the Earth’s magnetic field as a function of the WSF’s orbital position. 

Data collected during the WSF mission will be given to the school for post-flight analysis. The high school 

students will work with Space Vacuum Epitaxy Center researchers in applying the WSF magnetic field 

data to the identification of variations of the Earth’s magnetic field from that of an ideal magnetic dipole 

field. 

Mission Scenario 

On Flight Day 4, the WSF will be grappled by the Shuttle arm and removed from the Cross-Bay Carrier. 

The WSF will be positioned by the arm to be scoured by the highly reactive atomic oxygen found in LEO, 

and by the Sun’s heat. The cleaning will last from one-and-a-half to three hours. Some systems tests will be 

run during this cleaning cycle, such as communications checks between the Carrier and the Free Flyer, 

checks of the Free Flyer batteries, and activation of the primary video camera on the wake side of the Free 

Flyer. 

After the cleaning is done, the arm will move the WSF to the release position near the center of the payload 

bay. The Free Flyer will separate from the arm and move under its own nitrogen gas thrusters to about 30 

nautical miles behind the Shuttle to isolate it from Shuttle contamination sources (such as water dumps, 

fuel cell purges and engine firings). 

The WSF will stay 30 nautical miles behind the Shuttle while growing the thin films. During this time, it 

will be operated from the POCC at JSC. The SVEC team will monitor and control all aspects of WSF 

operations in close cooperation with the astronaut crew. Cooperative payloads will be operated from the 

Commercial Payload Command Center located at Space Industries a few miles from JSC in League City, 

TX. On Flight Day 6, the Shuttle will rendezvous with the Free Flyer. Every member of the STS-69 crew 

has a vital role to play during the WSF rendezvous and capture, and the integral plume experiment. During 

approach, David Walker and Kenneth Cockrell will fly Endeavor in a complex series of maneuvers 

designed to expose the WSF to carefully controlled thruster exhaust plumes. James Newman and Michael 

Gernhardt will coordinate the plume experiment initiation and data acquisition, and James Voss will track 

the WSF position by video. After the astronauts recapture the WSF, it will stay on the Shuttle arm above 

the payload bay during the astronaut sleep period for extended WSF environmental measurements. 

On Flight Day 7, the CHAWS experiment will be performed. The astronauts will position the WSF to the 

point above the overhead windows and maneuver it to gather plasma flow data around the WSF. The 

Auroral Photography Experiment B camera will be used in support of the plasma flow studies to view the 

Shuttle glow phenomenon on the CHAWS plasma probe from the Shuttle’s aft flight deck windows. 

Plasma flow data will be acquired for two full orbits after which the WSF will be re-stowed for return to 

Earth. 

Future Plans for the WSF Program 

The WSF program consists of four flights at roughly one year intervals. During these four flights, the WSF 

program will characterize the uncharted neutral and plasma wake formed by a vehicle in LEO; grow thin 

films in the unique wake ultra-vacuum; and demonstrate the ability to grow commercial quantities of 

epitaxial thin films in space, establishing the “proof-of-concept” required for industry to fully embrace the 
Edited by Richard W. Orloff, 01/2001/Page 21 

space epitaxial growth technology. To accomplish these goals, the WSF program is designed to evolve, 

with the WSF-3 flight in 1996, increased capability in number and types of thin film grown, and in 

command and control of the growth process through ground operations from a commercial payload control 

center. WSF-3 also will see the addition of solar panels, additional on-board computing capabilities, and 

robotic substrate sample manipulation for extended orbital operations. WSF-4 in 1998 is expected to have 

the capability of processing up to 300 epitaxial thin film wafers. 

Beyond the first “proof-of-concept” flights, full commercial use of the WSF is projected. This “Mark II” 

phase envisions -- a WSF Free Flyer orbiting for a five-year manufacturing cycle. The 4,350-pound weight 

of the Free Flyer makes it economically unfeasible to launch and retrieve for every batch of wafers grown. 

Since each 300 wafer batch only weighs about ten pounds, it is clearly more suitable to launch only the raw 

materials and bring back only the finished wafers. Therefore, the WSF Mark II would be launched into 

orbit and then periodically serviced from the Space Station. 

Conclusion 

Accomplishing the objectives of the four flight test program is expected to prove the theory that electronic 

materials grown in space can be of higher quality than those grown on Earth, can be processed in space, 

and can be produced in large areas. The electronics industry’s need for high-speed optical and highfrequency electronic devices will continue to drive advanced materials development and improvement. The 

ever-increasing use of electronic materials worldwide and the ability to grow them in thin film form in 

space is expected to give commercial viability to the use of the space ultra-vacuum to produce advanced 

electronic materials. 
Edited by Richard W. Orloff, 01/2001/Page 22 

NASA SPECIAL PAYLOADS DIVISION ON STS-69 

STS-69 marks a major milestone for payloads from the Goddard Space Flight Center. All three of the 

payloads are part of NASA’s effort to produce faster, better, and cheaper access to space and all three of 

the payloads come from the Special Payloads Division (SPD) at Goddard. Not only are both of the Shuttle 

projects under SPD represented, but all of the Shuttle programs administrated by the SPD have at least one 

experiment flying on STS-69. 

The SPARTAN Project is flying the third SPARTAN 201 (SP201-03) mission in a series of four, which is 

a primary payload. The White Light Coronograph (WLC) instrument on SP201 is a Goddard Laboratory 

for Astronomy and Solar Physics Division instrument. The other two bridges, International Extreme 

Ultraviolet Hitchhiker (IEH-1) and Capillary Pumped Loop-2 (CAPL-2)/Get Away Special Bridge 

Assembly (GBA-6) are from the Shuttle Small Payloads Project (SSPP). IEH-1 has three Hitchhiker 

Program experiments and a Hitchhiker-Jr Program experiment. CAPL-2/GBA(6) has one Hitchhiker 

experiment, one Complex Autonomous Payload using the Get Away Special (GAS) carrier, and four GAS 

payloads. 

SPARTAN 201-03 

The SPARTAN 201-03 mission is a scientific research effort aimed at the investigation of the interaction 

between the Sun and its outflowing wind of charged particles. SPARTAN’s goal is to study the outer 

atmosphere of the Sun and its transition into the solar wind that constantly flows past the Earth. The 

mission involves the deployment and operation of the free-flying SPARTAN spacecraft from Space Shuttle 

Endeavour. 

This mission -- the third for SPARTAN -- is intended to coincide with the passage of the Ulysses 

spacecraft over the Sun’s north polar region. As the Ulysses spacecraft passes high over the north pole of 

the Sun, its instruments are sampling the physical properties of electrons, protons, and ions in the solar 

wind flowing past the spacecraft. These properties include variations of temperature, density, ionic 

composition, and magnetic and velocity fields. At the same time, intensive collaborative observations of 

the source of the solar wind at the Sun are planned, including SPARTAN 201-03 and a variety of other 

ground and space-based experiments. 

SPARTAN 201-03 Science and Instruments 

Science Objectives 

The primary objective of the SPARTAN 201-03 mission is to understand the physical circumstances of the 

corona at the Sun during the time of the Ulysses north polar passage. It had been suspected for about 20 

years that the polar regions of the Sun were sources for high speed solar wind streams. This hypothesis was 

finally confirmed by measurements made by the Ulysses spacecraft during the south polar passage in 

September 1994. 

The SPARTAN solar viewing instruments will be used to define conditions at the base of the heliosphere 

where the solar wind has its origins. The great mysteries yet to be solved are what process accelerates the 

solar wind and, still more basic, why the corona is so much hotter than the underlying layers of the Sun. 
Edited by Richard W. Orloff, 01/2001/Page 23 

Instruments 

The two scientific instruments on SPARTAN 201-03 are the Ultraviolet Coronal Spectrometer (UVCS) 

and the White Light Coronagraph (WLC). 

The UVCS is used to measure characteristics of the light emitted by neutral hydrogen atoms in the solar 

corona. It also measures the brightness of light emitted by hot, highly-charged atomic ions. These 

measurements are used to determine line-of-sight velocities, kinetic temperatures, densities, and bulk 

outflow velocities for some of the major constituents in the corona and solar wind. This device was 

developed by the Smithsonian Astrophysical Observatory, Cambridge, MA. 

The WLC is a specialized telescope which produces an artificial eclipse of the Sun so that the constantlychanging shape and form of the solar corona can be imaged. The experiment is operated by the Goddard 

Space Flight Center and was developed by the High Altitude Observatory, Boulder, CO. 

The UVCS will return spectroscopic data for ionized hydrogen and five-times ionized oxygen located in 

coronal regions from 1.35 to 4 solar radii. The light used by UVCS is in the extreme ultraviolet region of 

the spectrum. Radiation from these ions is unobservable from the surface of the Earth because of 

atmospheric absorption. 

The WLC instrument images the white light (electron- scattered) component of the corona to provide 

information on the detailed coronal structure. Space-borne instruments of this type are free from the glare 

caused by light-scattering within the Earth’s atmosphere. They allow the corona to be imaged at distances 

high above the Sun’s surface. Together, these two instruments will be used to investigate properties of the 

solar corona at the base of the solar wind. These include: 

• The distribution of temperature and density distributions for both electrons (WLC) and protons and 

heavy ions (UVCS). 

• Detection of bulk flows in the lower corona and inference of systematic velocity fields in the corona. 

• Detection of heating of the lower corona by the deposition of energy carried by hydromagnetic waves 

(WLC and UVCS). 
Edited by Richard W. Orloff, 01/2001/Page 24 

Science Background 

Why Investigate the Corona and Solar Wind? 

The modern world is becoming increasingly dependent upon advanced communication, navigation, and 

other technologies. These technologies have occasionally fallen victim to disruptions in operation caused 

by changes in “space weather” due to solar variations. Earlier this year NASA’s Wind spacecraft 

determined that space weather effects were the primary reason that two spacecraft -- Anik E-1 and GOES-8 

-- experienced equipment problems last year. Therefore, knowledge of the influences of the Sun upon the 

Earth is not only important, but ultimately required for optimal design and operation of some of these key 

systems. 

The Sun is a magnetic variable star whose energy -- including heat, light, X-rays, gamma-rays and the solar 

wind -- dominates and powers the solar system. The thin, hot upper atmosphere of the Sun, called the solar 

corona, achieves enormous temperatures -- about two million degrees -- and is the interface between the 

Sun and the solar wind. The solar wind is a continual torrent of electrically charges particles blown away 

from the Sun in all directions. 

Gusts in the solar wind flowing past the Earth’s magnetic field are responsible for disruptions felt on Earth 

associated with space weather. The interplay of forces is responsible for dramatic global effects. One 

spectacular example of the effects of this interplay in the Earth’s polar atmospheres are aurora, called the 

Northern and Southern lights. Other more indirect effects of the solar wind may be highly disruptive, such 

as electric power distribution system failures, radio communication disruptions, aerial magnetic 

prospecting or surveys, and diminished performance and reliability of spacecraft in Earth orbit. 

Additional background information and graphics on SPARTAN 201, Ulysses, and the Sun may be 

obtained from the World-Wide Web directly through the SPARTAN 201-03 Home Page at: 

http://umbra.gsfc.nasa.gov/spartan or via links through the STS-69 Mission Home Page at: 

http://shuttle.nasa.gov 
Edited by Richard W. Orloff, 01/2001/Page 25 

Key Spacecraft Characteristics 

Mass: 2,845 lbs. with instruments 

 

Power: 28 Volt DC batteries, 18 kwh capacity 

 

Command and Data System: Pulse Code Modulation (PCM) system with 10 gigabyte tape 

recorder for science and engineering data storage onboard 

 

Attitude Control System: Three axis stabilized cold gas (GN2) pointing system, +/- 30 arcsec accuracy using Sun sensors 

 

Construction: Reusable bolted aluminum service module and instrument carrier 

 

Communications: In-bay communication through Shuttle laptop computer also 

known as the Payload General Support Computer, used for final 

solar target input. No communication while in free-flight 

 

Science Mission Duration: 45 hours of free-flight 

 

Advanced Instrumentation Systems: (1) UVCS: first spectral diagnostics of coronal proton temperature, 

and coronal bulk flows; (2) WLC: first externally occulted orbital 

coronagraph with a two-dimensional solid-state detector for 

precision photometry. 

Mission Operations 

After the SPARTAN is deployed by the Shuttle, the spacecraft operates on its own for 43 hours, achieving 

a maximum distance of 70 to 100 nautical miles from the Shuttle at mid-mission. 

After its independent operation, SPARTAN is placed into a safe-hold condition, and is recovered and 

placed into the Shuttle cargo bay. The internal tape recorder is removed from the spacecraft after landing 

and data are recovered during tape playback. 

Background 

The SPARTAN program is designed to provide easy and relatively inexpensive access to Earth orbit via 

the Space Shuttle for science experiments. SPARTAN’s design consists of a basic carrier, which, with the 

addition of a science experiment, becomes a complete spacecraft designed to meet specific science 

objectives on each mission. SPARTAN missions include stellar, solar, Earth fine-pointing, and 

microgravity science and technology experiments requiring space exposure away from the Space Shuttle. 

The SPARTAN program was conceived in the mid-1970s and developed by the Special Payloads Division, 

Goddard Space Flight Center, and the U.S. Naval Research Laboratory, Washington, DC, to extend the 

capabilities of sounding rocket-class science experiments by making use of the Space Shuttle. 

In June 1985, a SPARTAN mission successfully carried an X-Ray telescope aboard STS-51G. Another 

carrier, SPARTAN Halley, was on board Shuttle Mission STS-51L. In April 1993 and September 1994, 

SPARTAN 201 was flown aboard the Space Shuttle Discovery on missions STS-56 and STS-64. The 

SPARTAN 204 carrier system was carried aboard STS-63 in February 1995. 

The SPARTAN project is managed by NASA’s Goddard Space Flight Center for the Office of Space 

Science, Washington, DC. Goddard provides the SPARTAN carrier and manages its integration with the 

Shuttle. 
Edited by Richard W. Orloff, 01/2001/Page 26 

SPARTAN Team 

SPARTAN 201-03 Project Manager: Craig Tooley, Goddard Space Flight Center Greenbelt, MD 

UVCS Principal Investigator: Dr. John Kohl, Smithsonian, Astrophysical Observatory, Cambridge, MA 

WLC Principal Investigator: Dr. Richard Fisher, GSFC 

Space Physics Division Director: Dr. George Withbroe, NASA Headquarters, Washington, DC 

SPARTAN Program Manager: Paul DeMinco, NASA Headquarters 

Special Payloads Division Director: Robert Weaver, GSFC 

Discipline Scientist for Solar Physics: Dr. William Wagner, NASA Headquarters 

STS-69 Mission Scientist: Dr. Richard Fisher, GSFC 
Edited by Richard W. Orloff, 01/2001/Page 27 

INTERNATIONAL EXTREME ULTRAVIOLET HITCHHIKER (IEH-1) 

IEH-1 is the first of five planned flights to measure and monitor long-term variations in the magnitude of 

absolute extreme ultraviolet (EUV) flux coming from the Sun, and to study EUV emissions from the 

plasma torus system around Jupiter originating from its moon Io. 

These observations are accomplished by the two complementary experiments that comprise IEH, the Solar 

Extreme Ultraviolet Hitchhiker (SEH) and the Ultraviolet Spectrograph Telescope for Astronomical 

Research (UVSTAR). 

SEH and UVSTAR are international cooperative investigations. International partners in IEH-1 from the 

Italian Space Agency will study the EUV emission of hot stellar objects. The NASA portion of the science 

is sponsored by the Solar System Exploration Division, NASA Headquarters. 

The EUV spectrum contains very short wavelength light that does not penetrate the Earth’s atmosphere. 

Because these wavelengths are blocked by the atmosphere, scientists must use instruments above the 

atmosphere to study this portion of the solar flux. Useful models of the Earth’s atmosphere (or any other 

planetary atmosphere) require accurate knowledge of the sun’s absolute EUV irradiance. It is widely 

recognized in the scientific community that more accurate long-term solar measurements of this type are 

urgently needed, given that the solar spectrum changes from day to day, from one solar rotation to the next, 

and it changes even more dramatically over the 11-year solar cycle. 

Solar Extreme Ultraviolet Hitchhiker (SEH) 

SEH is a set of instruments designed and built to provide research scientists with a tool to accurately 

measure solar flux (the amount of light passing through a given area in a given time) in the Extreme 

Ultraviolet (EUV) region of the solar spectrum. 

Using an EUV solar spectrometer, a device that measures the wavelengths of non-visible light, the SEH 

instrument will take a photograph of the EUV solar spectrum between 250 and 1700 angstroms. (The 

shortest wavelength of light which we can see with our eyes is deep blue and has a wavelength of 4,000 

angstroms. The longest is red with a wavelength of 7,000 angstroms. The light this instrument will view on 

STS- 69 is a very deep blue) SEH also takes measurements with gas cell experiments, using helium and 

neon gas. These gas cells provide extremely accurate brightness-type measurements of the solar EUV, 

much like a light meter on a camera. 

Relatively little is known about this important EUV energy source, even though there have been previous 

missions conducted to measure the solar EUV radiation. This is because absolute measurements in the 

EUV are difficult, and EUV- related technology is still maturing. 

This difficulty is well known, and most past missions have produced data with rather large uncertainties, 

due primarily to instrument calibration uncertainties and time- dependent instrument sensitivity changes 

which are difficult to separate clearly from the variability of solar EUV emissions. The stability of the SEH 

instrument removes these difficulties. 

The SEH set of instrumentation was most recently flown successfully on a sounding rocket mission on 

September 4, 1990. The combination of spectral and brightness data reveals not only what wavelengths are 

in the solar EUV spectrum, but also provides an exact measurement of the absolute flux in that region, 

providing the most reliable absolute solar EUV data available. 

The SEH experiment was developed and built at the University of Southern California, with Dr. Darrell 

Judge as the principal investigator and Don McMullin as the experiment manager. 
Edited by Richard W. Orloff, 01/2001/Page 28 

Consortium for Materials Development in Space Complex Autonomous Payload (CONCAP IV-03) 

CONCAP IV-03 is the third flight of an experiment that studies the growth of organic nonlinear optical 

(NLO) crystals and thin films. The materials being used are of great interest because they can be used in 

the photonics industry. Photonics is the use of laser light instead of electrons through wires to send bits of 

information. The advantage of photonics is the elimination of mechanical components, switches, and wear 

items, and the increased speed of information transferal that lasers offer. 

NLO materials are the key to many optical applications now and in the future, with optical computing 

being a prime example. Many studies have suggested that the photonics industry ultimately will grow to 

the scale of the current electronics industry. Just as material improvements in silicon were essential to 

electronics, so too are improved optical materials required for advances in photonics. NLO materials play 

the same role in photonics and optoelectronics that semiconductors do in the electronics industry. The issue 

in this project is whether crystals grown in microgravity can speed the evolution of photonics. 

A total of two crystals and 45 thin films will be grown. It is anticipated that the lack of gravity will achieve 

two goals: it will avoid convection, leading to crystals with more uniform composition; and it will avoid 

the deformation of the crystals under their own weight “sagging” at the relatively high growth temperatures 

where they are extremely soft. 

Nonlinear optical crystals have two important properties: frequency doubling and the pockets effect. When 

a laser beam passes through the crystal it comes out with twice the frequency of the original beam, a 

phenomenon known as “frequency doubling.” Frequency doubling is important because it doubles the 

range of frequencies available for laser applications. Currently, lasers only operate at a limited number of 

frequencies with some very important frequencies missing for scientific and commercial applications. 

When an electric field is applied to some NLO materials, the index of refraction of the material changes, a 

phenomenon known as the “pockets effect.” When the index of refraction changes, so does the path of 

light traveling through the crystal. The pockets effect allows a crystal to act as a high speed switch. 

CONCAP IV-03 is contained in a Hitchhiker canister and uses the Hitchhiker-Jr (HH-J) carrier avionics 

system. This experiment is the first to use HH-J which utilizes the Payload and General Support Computer 

located in the aft flight deck and operated by a crewmember. 

CONCAP IV-03 is managed by the Consortium for Materials Development in Space, at the University of 

Alabama at Huntsville. The experiment manager is Bill Carswell. 

Shuttle GLO Experiment (GLO-3) 

This experiment originated as the “Shuttle Glow” experiment sponsored by the USAF/Phillips Laboratory. 

It also is referred to as the Arizona Airglow Experiment. The nature of the instrument makes it ideal for 

studies of Earth’s thermosphere. Consequently, it has become a joint program with NASA’s Space Physics 

Division of the Office of Space Science. 

Scientists continue to investigate the mysterious shroud of luminosity, called the “glow phenomenon,” 

observed by astronauts on past Shuttle missions. Theory suggests that the glow may be due to atmospheric 

gasses on the windward or ram side surface of the Space Shuttle colliding and interacting with gaseous 

engine effluents and contaminate outgassing molecules. The glow intensity is weak, decreases with altitude 

and requires some special conditions for good detection -- both the Sun and Moon must be below the 

horizon, for example, so the spatial extent of the glow will be mapped precisely (0.1 degrees). The effects 

of ambient magnetic field, orbit altitude, mission elapsed time, Shuttle thruster firings, and surface 

composition on the intensity and spectrum of the glow also will be measured. An optical emission model 

will then be developed from the data. 
Edited by Richard W. Orloff, 01/2001/Page 29 

According to Dr. David J. Knecht, Phillips Laboratory program manager for GLO, the experiment consists 

of imagers and spectrographs, which are bore-sighted to the imagers, so that both sensors are focused onto 

the same area of observations, e.g. the Shuttle tail. Imagers serve to unambiguously identify the source 

region of the glow spectrum as well as to map the spatial extent of the luminosity. Unique features of the 

sensors are their high spectral and spatial resolution. Each spectrograph employs a concave holographic 

grating that focuses and disperses light within a small field of view (0.1 by 8.5 degrees) over the 

wavelength range of 115-1100 nanometers. The sensor comprises 9 separate channels, each of which 

operates simultaneously and independently, to cover individual segments of the spectrum. 

The Shuttle glow experiments are short compared to the total flight time of the mission; therefore, the 

remainder of the flight is dedicated to studies of Earth’s atmosphere. The scientific objectives are related to 

the Ionosphere, Thermosphere and Mesosphere section of the NASA Space Physics Division. Active 

participants who have ground-based instrumentation try to make observations throughout the campaign. 

The data is correlated and deposited in a data bank at the National Center for Atmospheric Research, 

Boulder, Colorado, for use by the community. The coordination of this data is important to relate local 

observation to the global picture provided by the GLO observations from the Shuttle. 

Dr. Edmond Murad from the Phillips Laboratory and Dr. A. Lyle Broadfoot from the University of 

Arizona are co- principal investigators on GLO. 

Ultraviolet Spectrograph Telescope for Astronomical Research (UVSTAR). 

Response in the solar system to the solar input measured by SEH will be observed by a complementary set 

of instruments called UVSTAR. On this Shuttle mission, the UVSTAR instrumentation will measure EUV 

and Far Ultraviolet (FUV) emissions in the Jovian system, and the SEH will provide the solar flux data 

needed for proper context. 

UVSTAR is a pair of telescopes with imaging spectrographs that are sensitive to EUV and FUV 

wavelengths, from 500-850 angstroms and 800-1250 angstroms respectively. From the Space Shuttle, 

UVSTAR will form spectrally resolved images of stars and extended emission regions such as the Io 

plasma torus. Observing time will be shared to achieve objectives in both planetary science and stellar 

astronomy. 

UVSTAR offers an important advantage for Io torus research in its capability to form simultaneous images 

of the torus in each of its brightest emission lines. The spectral dispersion is great enough to separate 

images of most of the important emissions. 

The EUV spectrum of the plasma torus is rich in information about the ion composition, density, and 

electron temperature of the plasma. Studies of the spectrum and shape of the torus will help answer 

fundamental scientific questions about the source of the energy and how material becomes a part of the 

torus. 

Although ground-based studies of torus emissions at visual wavelengths have added much to our 

knowledge of this plasma, measurements in the EUV offer a more direct means of studying certain 

processes in the torus. Recent EUV measurements by the Hopkins Ultraviolet Telescope on the Astro-2 

Shuttle mission and the Extreme Ultraviolet Explorer spacecraft have emphasized the importance of this 

wavelength range. 

UVSTAR also will complement and extend observations planned by the Galileo spacecraft, which arrives 

in orbit around Jupiter on December 7. Galileo’s orbital geometry limits its opportunities for viewing the 

plasma torus with its UV instruments, especially with the EUV spectrograph. 
Edited by Richard W. Orloff, 01/2001/Page 30 

UVSTAR will provide observations of the Jovian system at greatly improved spectral resolution. The 

imaging spectrographs will measure the intensity of several important emission lines of ionized sulfur and 

ionized oxygen as a function of position and time in the torus, measure molecular and atomic hydrogen 

from Jupiter’s dayglow and aurora, and possibly help to clarify the coupling between the torus and the 

aurora. 

UVSTAR includes capabilities for independent target acquisition and tracking. Rough pointing will be 

provided by orienting the Shuttle. The finder telescope will locate the target and move the optical axis to it. 

Pointing control will then be transferred to the tracker telescope. A computer- controlled digital feedback 

system will hold the UVSTAR on target by canceling the Shuttle’s attitude control motions. 

UVSTAR was prepared for flight jointly by principal investigators Dr. A. Lyle Broadfoot of the Lunar and 

Planetary Laboratory, University of Arizona and Dr. Roberto Stalio of the Center for Advanced Research 

in Space Optics, University of Trieste, Italy. Dr. Broadfoot is the lead principal investigator for the Io 

plasma torus observations. Dr. Stalio is the lead principal investigator for the astronomical observations. 
Edited by Richard W. Orloff, 01/2001/Page 31 

CAPILLARY PUMPED LOOP/ 

GET AWAY SPECIAL BRIDGE ASSEMBLY (CAPL-02/GBA) 

The combined CAPL-2/GBA (6) payload consists of the CAPL-2 Hitchhiker payload, the Thermal Energy 

Storage-2 (TES- 2) payload, and five GAS payloads on a single cross-bay structure called the GBA. 

The Shuttle Space Payloads Project (SSPP) Office has responsibility for the mission management, safety, 

payload integration, and mission operations of the payload. Chris Dunker, from SSPP, is the mission 

manager. 

Capillary Pumped Loop (CAPL-2) 

The CAPL-2 payload is an in-orbit microgravity demonstration of the full-scale capillary pumped loop 

system planned for the Earth Observing System (EOS) Program. The CAPL-2 payload is a reflight of the 

CAPL-1 Hitchhiker payload flown on STS-60 in February 1994, with modifications to enhance the startup 

of its capillary system. The CAPL-2 flight will verify the heat transport requirements of the thermal control 

system under design for the EOS. 

This experiment uses an evaporator plate with a capillary pump that vaporizes a liquid ammonia working 

fluid by the use of heaters. The vapor ammonia then travel through a three-meter-long line to heat 

exchangers, where the vapor is condensed to a liquid and returned to the evaporator plate via a three-meterlong liquid line. Heat rejection is accomplished via heat pipes that carry the heat from the exchangers to a 

radiator. A unique feature of the CAPL-2 is that all of the pumping is done by capillary forces, with no 

mechanical moving parts. The CAPL-2 utilizes separate electronics control modules for telemetry, 

command, and power. The CAPL-2 electronics are, in turn, connected to the Hitchhiker avionics as a 

standard, easy-to-use Shuttle carrier system. During the mission, a control center at Goddard will issue 

commands to the CAPL-2 experiment, monitor its performance and conduct real-time mission analysis on 

the CAPL-2 system. 

The Capillary Pumped Loop is sponsored by NASA’s Mission to Planet Earth and developed by the 

Goddard Space Flight Center Thermal Engineering Branch with Jentung Ku as the principal investigator. 

Dan Butler is the experiment manager. 

Thermal Energy Storage (TES) 

The Thermal Energy Storage (TES-2) experiment also is part of the CAPL-2/GBA-6. The TES-2 payload 

is designed to provide data for understanding the long-duration behavior of thermal energy storage fluoride 

salts that undergo repeated melting and freezing in microgravity. The TES-2 payload is designed to study 

the microgravity behavior of voids in Lithium Fluoride-Calcium Fluoride eutectic, a thermal energy storage 

salt. Data from this experiment will validate a computer code called TESSIM, useful for the analysis of 

heat receivers in advanced solar dynamic power system designs. 

Solar dynamic power systems provide power by converting solar energy to electrical power. During solar 

conditions some of the Sun’s energy is also used to melt a thermal energy storage salt which resides in a 

heat receiver. In shade, or eclipse conditions, the thermal energy salt freezes giving up its thermal energy 

such that electrical power may be continually provided. 

TES-2 occupies a standard five cubic-foot Get Away Special canister and is expected to develop internal 

temperatures in excess of 700 degrees Celsius in order to melt the fluoride salts. When the thermal energy 

salt is melted, it expands approximately 30 percent in volume. As the thermal salt cools, it solidifies and 

shrinks, thus causing voids or pockets to form in the salt. This void formation affects both the heat 

absorption rate of the salt, and the design of the heat receiver containers holding the salt. 
Edited by Richard W. Orloff, 01/2001/Page 32 

Repeated melt/freeze cycles will characterize the void formation and movement of the void in the salt. 

Understanding and predicting the melt/freeze behavior of contained thermal energy storage salt in the onorbit microgravity environment will lead to an improved design for solar dynamic system heat receivers. 

TES-2 is the second of four flight experiments. It is flying as a Complex Autonomous Payload (CAP) 

managed by the Shuttle Small Payloads Project at Goddard Space Flight Center, Greenbelt, MD. 

The TES experiment conception, design and fabrication took place at NASA’s Lewis Research Center, 

Cleveland, OH. Carol Tolbert is the TES-2 principal investigator and Frank Robinson Jr. is the TES-2 

project manager. 
Edited by Richard W. Orloff, 01/2001/Page 33 

GET AWAY SPECIAL (GAS) PAYLOADS 

Four Get Away Special (GAS) payloads are planned for STS-69. Each will be contained in a standard fivecubic-foot canister. The four payloads are as follows: 

G-515 

European Space Agency, Noordwijk, The Netherlands 

The Control Flexibility Interaction Experiment will study active damping control loops using a flexible 

plate and two piezo (pressure) actuators for better understanding of the interaction of spacecraft attitude 

and orbit control systems with spacecraft structures. 

This experiment will verify the feasibility of an active damping system, autonomous in operation, as part of 

an overall spacecraft control system. The experiment will show through a scaled simulation a cantilevered, 

flexible plate being perturbed and then having its motion detected and damped automatically. 

The experiment duration will be around two hours and will include several runs of the perturbation - 

control loop. Expected disturbances induced by Space Shuttle maneuvers are welcome to proof of the 

concept of active damping. 

Since 1990, the In-Orbit Technology Demonstration Program of the European Space Agency has flown 

four Get Away Special payloads and one Hitchhiker payload on board a U.S. Space Shuttle. 

G-645 

Millcreek Township School District, Erie, PA 

McDowell High School, LORD Corp. 

G-645 will investigate the performance of Electroheological (ER) fluid-filled beams as structural dampers 

in space. The experiment consists of two instrumented aluminum beams filled with ER fluid. The beams 

are moved from rest into a deflected position by an actuator; they are then held in this position by electromagnets. A 5000-volt current is applied to the beams, activating the ER fluid. On a command from the 

computer, the beams are released, and the frequency and decay rate are measured and recorded on a 

computer chip. The cycle is repeated without the 5000-volt application, and the full test is repeated six 

times each hour during the first three days of the flight. 

ER fluid is such that when it is subjected to an electric field, its flow characteristics are changed. The fluid 

becomes more viscous and exhibits more resistance to shear stress which increases the damping of the 

fluid. 

The objective of this payload is to conduct a structural damping evaluation of ER fluid-filled beams in a 

space environment. By subjecting the ER fluid-filled beams to launch, orbit, and re-entry conditions, the 

vibratory performance of these beams will be monitored and the effect of microgravity determined. 

G-702 

NASA Lewis Research Center, Cleveland, OH 

The Microgravity Smoldering Combustion (MSC) experiment, will study the effects of smoldering 

combustion in a long- term microgravity environment. This experiment will focus on one-dimensional 

smoldering of polyurethane foam. 
Edited by Richard W. Orloff, 01/2001/Page 34 

Smoldering is a non-flaming form of combustion that takes place in the interior of porous combustible 

materials. Common examples of smoldering are non-flaming embers, charcoal briquettes, and cigarettes. 

The objective of the study is to provide a better understanding of the controlling mechanisms of 

smoldering, both in microgravity and Earth gravity. As with other forms of combustion, gravity affects the 

availability of air and transport of heat, and therefore the rate of combustion. The results of the 

microgravity experiments will be compared with identical ones carried out in Earth’s gravity. They also 

will be used to verify present theories of smolder combustion. The results of the study will provide new 

insights into the process of smoldering combustion. 

Professor Carlos Fernandez-Pello of the University of California, Berkeley, is the principal investigator for 

the MSC experiment. Dr. David Urban of NASA’s Lewis Research Center is project scientist, and John M. 

Koudelka of Lewis is project manager. 

G-726 

NASA Langley Research Center, Hampton, VA 

The Joint Damping Experiment (JDX) is a structural dynamics experiment designed to study the nonlinear, gravity dependent behavior of a pin-jointed truss. A precise knowledge of the dynamics and 

damping of space structures is vital to the robust design of future NASA missions involving precision 

structures. Many proposed designs for large space structures use light-weight trusses composed of highstiffness members which exhibit very little damping. Deployable truss structures using pinned joints 

typically have significantly higher damping than erectable trusses using “tight” mechanical joints. 

However, joint damping is difficult to predict and highly dependent on preload across the joint interface. 

JDX will allow comparison of damping in microgravity and 1-G environments. Flight testing has 

previously been conducted on an aircraft which provides a short duration microgravity environment. 

The JDX test article consists of three cubic (8x8 inches) bays of a truss structure mounted within a GAS 

canister. One end of the structure is cantilevered to the bottom of the GAS canister. A mass is attached to 

the free end to lower the fundamental resonant frequencies of the structure. A controller/data acquisition 

system, an excitation assembly consisting of linear actuators, linkages, and electromagnets, plus a set of 

sealed batteries, also are housed. 

JDX is designed to be fully autonomous. On ascent, a baroswitch applies power to the controller. During 

the first astronaut sleep period (when vehicle accelerations are minimal), the controller conducts a series of 

tests. During each of the 30 planned tests, one of three vibration modes of the truss is excited and the 

resulting vibration decay is recorded. 

The JDX is conducted by the Department of Mechanical and Aerospace Engineering, Utah State 

University. JDX is funded by the NASA Office of Space Access and Technology through the In-Space 

Technology Experiments Program. Technical oversight and project administration is provided by NASA’s 

Langley Research Center. JDX is designed to be a relatively simple and inexpensive space flight 

experiment and was competitively selected by NASA for its innovative approach to the study of structural 

dynamics in space. JDX and similar projects provide the university community with a unique opportunity 

to perform basic engineering science experiments in the space environment and to contribute to the 

nation’s space expertise. 
Edited by Richard W. Orloff, 01/2001/Page 35 

EXTRAVEHICULAR ACTIVITY DEVELOPMENT FLIGHT TEST-2 

Two astronauts will leave Endeavour’s crew cabin for about six hours on the 10th day of the mission to 

perform several tasks that will broaden the capabilities and experience base for building and maintaining 

the International Space Station and for other future spacewalks. 

The extravehicular activity, conducted by Mission Specialists Jim Voss and Michael Gernhardt, supports 

four different Detailed Test Objectives (DTOs). 

DTO 833 is designed to evaluate spacesuit design modifications to protect spacewalkers from the 

extremely cold space environment and their ability to perform in such conditions. At the start of the EVA, 

one of the crewmembers will install two thermal cubes in the payload bay to collect temperature data on 

the space environment. One cube will be mounted on the end of the Shuttle’ s robot arm, and the other 

cube will be mounted at the task board worksite. 

As another part of the test, engineers will collect temperature data within the spacesuit throughout the 

entire spacewalk. Temperature data also will be collected on modified crew garments which are designed 

to bypass the present Liquid Cooling Ventilation Garment. 

DTO 671 consists of a number of tasks designed to evaluate and verify specific assembly and maintenance 

tasks for the Space Station. Each of the two EVA astronauts will spend about an hour performing a variety 

of tasks at a board mounted on the starboard side of the payload bay. The tasks include working with 

handrails, fasteners and connectors while the spacewalker is both free-floating and positioned in a fixed 

foot restraint. The amount of time and effort required for specific tasks also will be assessed during this 

time. 

Throughout the EVA, any specific instructions the crew member may need will be displayed on an 

Electronic Cuff Checklist, which represents DTO 672. The checklist, which has been tested on two 

previous missions, is being flown to demonstrate its on-orbit use and to gain the experience necessary to 

move toward operational use. 

Comments from the crewmembers on all of the tests will be evaluated as part of DTO 1210, which will 

help ground crews improve EVA operations. 

For the spacewalk, Voss will be designated as EV1 and will have red stripes around the legs of his 

spacesuit, while Gernhardt will be EV2. Pilot Ken Cockrell will assist the spacewalkers from inside the 

crew cabin. 

The spacewalk is the 30th EVA of the Shuttle program. 
Edited by Richard W. Orloff, 01/2001/Page 36 

NATIONAL INSTITUTES OF HEALTH-CELLS 4 

Effect Of Space Flight On Bone Cell Formation And Loss During Space Flight 

Principal Investigator: 

Dr. Russell T. Turner 

Mayo Clinic 

Rochester, MN 

Weightlessness results in bone loss. The bone loss is similar to that which occurs in people who undergo 

prolonged bed rest or, in some cases, lose the use of one of their limbs due to injury or disease. The exact 

cause of the bone loss is not yet clear but is at least partially due to decreased activity of osteoblasts, the 

cells which produce the matrix which mineralizes to become bone. Weightlessness results in decreased 

bone formation in rodents, as well as humans. Studies performed on rats implicate a protein which is 

produced by bone cells and is important in the communication between cells. The gene for that protein was 

found to be expressed in bone at reduced level immediately following space flight but that level was 

dramatically increased (within 24 hours) when normal activity was reestablished after landing. 

This experiment will determine if gene expression is reduced in cultured bone cells following space flight 

and how quickly the levels return to normal after flight. Results from this experiment will help determine 

the usefulness of cultured bone cells in understanding how gravity functions to maintain bone cell activity. 

Osteoblasts And Bone Formation In Microgravity 

Principal Investigator: 

Dr. Robert Majeska 

Mount Sinai School of Medicine 

New York, NY 

Bone loss during space flight is well documented, but remains not yet fully understood. Among the 

unanswered issues are the direct effects which microgravity exerts on bone cells, and the mechanisms by 

which these cells recognize changes in gravity. This study will focus on bone cells of the osteoblast family, 

which synthesize bone matrix and also may participate in its breakdown (resorption) by regulating the 

formation and activity of bone-resorbing cells. The experiment will test the hypothesis that microgravity 

can produce direct effects on osteoblastic cells similar to those of regulatory hormones. In addition, the 

study will examine whether microgravity alters the interaction of osteoblastic cells with their matrix, 

resulting in changes in shape or cellular organization known to affect cell function. 

In this study, cells will be cultured in the middeck compartment of the Shuttle in the Space Tissue Loss 

culture device. Parallel control cultures will be maintained on Earth under identical conditions. During the 

flight, batches of both control and experimental cells will be fixed for analysis and samples of culture 

medium will be collected for biochemical changes. Following the flight, the cells will be analyzed to 

identify changes in shape and function. Samples of medium culture will be analyzed to identify the 

presence of bone matrix proteins and matrix-degrading enzymes which may participate in early stages of 

bone change. 

The NIH-C4 payload is sponsored by NASA’s Office of Life and Microgravity Sciences and Applications 

and the National Institute of Arthritis and Musculoskeletal Diseases. 
Edited by Richard W. Orloff, 01/2001/Page 37 

COMMERCIAL GENERIC BIOPROCESSING APPARATUS (CGBA- 7) 

General 

STS-69 will mark the seventh flight of BioServe’s Commercial Generic Bioprocessing Apparatus (CGBA7). BioServe is a NASA Center for the Commercial Development of Space based at the University of 

Colorado in Boulder, CO, and at Kansas State University in Manhattan, KS. The CGBA is a middecklocker secondary payload that serves as a housing, incubator and data collection point for BioServe’s 

Fluids Processing Apparatuses (FPAs). FPAs are multi-purpose devices that are essentially multichambered syringes that, upon activation, permit fluids to be mixed. After a specified period of time, the 

FPAs can be activated again to “fix,” or stop, an experiment prior to return to Earth. CGBA-7 will support 

experiments in pharmaceuticals testing and biomedicine, bioprocessing and biotechnology, agriculture and 

the environment. 

One of the strengths of the CGBA/FPA payload is that it is capable of addressing a wide variety of 

experimenter needs. The CGBA/FPA also has proven to be an exceptionally reliable payload: quality 

sample/data return rates from previous flights have exceeded 99%. Highlights of the experiments to be 

flown in the CGBA during the STS-69 mission include: 

Bacteriorhodopsin Polymerization 

(Manufacture of Uniform Three-Dimensional Polymer Matrices Containing Bacteriorhodopsin for use in 

Memory Architectures) 

Principal Investigators: Dr. Robert Birge, Deshann Govender, Center for Molecular Electronics, 

University of Syracuse, NY 

Bacteriorhodopsin is a protein that has promise as a data storage medium. It is hoped that access to 

microgravity will permit the formation of more homogenous bacteriorhodopsin polymers. During the STS69 mission, BioServe will assist Dr. Birge of the Center for Molecular Electronics (a consortium of 

university and industry with interests in protein-based mass memories) in his efforts to optimize the 

formation of the bacteriorhodopsin matrix needed to develop the protein matrix materials needed for 

improved three-dimensional optical memory storage devices. Bacteriorhodopsin-based memories offer the 

promise of exceptionally high data storage densities for future computer applications. 

Water Purification 

(Disinfection of Pseudomons aeruginosa with Low Levels of Polyiodide, Silver, Copper, and Silver/Copper 

Resins) 

Principal Investigator: Dr. George Marchin, Kansas State University. 

Kansas State University’s Dr. George Marchin, working with BioServe Affiliate WTC-Ecomaster 

(Minnesota), will determine if a combination of silver and copper resin materials will be effective in 

disinfecting Pseudomons bacterial contamination with applications to the microbial check valve used on 

the Shuttle. In addition to water purification applications in space, products developed by Dr. Marchin 

have already found wide use in industry for a variety of water purification applications. 
Edited by Richard W. Orloff, 01/2001/Page 38 

Bone Cell Growth in Space 

(Development, Growth and Activation of Bone Marrow Macrophages, Phase II) 

Principal Investigators: Dr. Keith Chapes, Dr. A. Forsman, Dr. A. Beharka, Kansas State University 

This second flight of bone marrow macrophages supports BioServe-affiliate Chiron’s (Emeryville, CA) 

interests in two ways. First, Dr. Chapes and his colleagues seek to test whether the transcription of receptor 

proteins or cytokines are altered by space flight. A second goal is to determine if culturing the 

macrophages in an agar culture system alters cell behavior during space flight as compared to ground 

controls. The information gathered during this flight may contribute to Chiron’s growing understanding of 

immune suppression. This information has application to terrestrial efforts to understand and mitigate 

immune-related diseases and disorders. For space flight applications, this work may result in therapies or 

methods that could eventually be used to reduce the risk of infection by astronauts during exposure to 

space flight. This ability will become progressively more important as astronauts spend more time in space. 

Stabilization and Activation of Cells in Space 

(CeReS-Mediated Cell Stabilization and Reversal) 

Principal Investigators: Dr. Terry C. Johnson, Dr. H. Fattaey, Kansas State University 

Working in collaboration with Dr. Floyd Taub of Syncrocell (Silver Spring, MD), Drs. Johnson and 

Fattaey have been working with a unique sialoglycopeptide that has the property of stopping the activities 

of cells in such a way that they can subsequently be “re-activated.” The applications for space-based 

biological research are important: a colony of cells can be “stabilized” prior to launch, “activated” in orbit 

and, finally,” stabilized” again prior to their return to Earth. This both accommodates launch holds and 

permits the cells to conduct all of their desired activities in microgravity without the confounding effects of 

a gravity field. The terrestrial applications for biotechnology applications and a variety of unique disease 

treatments may be even more significant, however. For example, it may be that desired groups of diseased 

or cancerous cells can be “stabilized” and subsequently “re- activated” such that drugs can be delivered to 

the cells when they are most receptive to them. This has the promise of increasing the effectiveness of 

existing drugs and therapies considerably. 

Growth of Biological Crystals in Space 

(Crystallization of Oligonucleotides and Proteins in Space) 

Principal Investigators: Dr. Paul Todd, Dr. Michael Sportiello, University of Colorado 

Working with researchers from NeXstar (Boulder, CO), Drs. Todd and Sportiello will seek to accomplish 

two objectives. First, they will attempt to grow large, high- quality crystals of ribonucleic acid in order to 

determine the three-dimensional structure. Also during the flight of a new, proprietary crystallization 

methodologies will be investigated which hold the promise of permitting the formation of crystals of higher 

quality. After the crystals are returned to Earth, they will be subjected to a variety of analysis techniques. 

With an understanding of the structure of the crystals in hand, researchers will then possess invaluable 

information that can be used for the design of new drugs. 

Dr. George Morgenthaler is the Director of the BioServe CCDS. Dr. Louis Stodieck is responsible for 

mission management for CGBA-07. 
Edited by Richard W. Orloff, 01/2001/Page 39 

BIOLOGICAL RESEARCH IN CANISTER - 06 

Principal Investigator: 

Dr. Ingrid Block 

German Aerospace Research Establishment 

The processing of outside signals by mammalian cells is a complex pathway, and gravity is one signal 

which is received by these cells. The gravity-sensing mechanism within mammalian cells has not been 

identified. To study this intracellular signal transmission, the Biological Research in Canister-06 (BRIC06) payload will fly a unicellular eucaryote cell culture of slime mold (Physarum polycephalum) as a 

model system. The investigator will examine the cultures for specific chemical concentrations which are 

signs of the signal transduction process. Dr. Block has flown three previous space flight experiments and 

has answers to some pieces of the transduction pathway puzzle. The BRIC-06 flight will add another piece 

to the puzzle of how gravity is sensed within mammalian cells. 

The slime mold will be housed inside 36 petri dishes which are stacked inside three aluminum canisters in 

the Shuttle’s middeck area. On flight day-two, crew members will place one set of samples in the gaseous 

nitrogen freezer which will instantly fix the samples at their current state. This procedure will be repeated 

on flight day-three for a second set of samples. The third set of samples will remain at ambient temperature 

throughout the mission. Upon landing, all the samples will be removed from the Shuttle and returned to the 

landing site laboratory. Ambient samples then will be frozen and shipped, along with the inflight-frozen 

samples, to Dr. Block’s laboratory in Germany. 

The Biological Research in Canister payload is the sixth in a series of payloads which studies the effects of 

microgravity on plants, small animals, and cell cultures. The experiment is sponsored by NASA’s Office of 

Life and Microgravity Sciences and Applications, Wash, DC. 
Edited by Richard W. Orloff, 01/2001/Page 40 

ELECTROLYSIS PERFORMANCE IMPROVEMENT ONCEPT STUDY (EPICS) 

Background 

Supply of oxygen and hydrogen by electrolyzing water in space will play an important role in meeting 

NASA’s needs and goals for future space missions. 

On-board generation of oxygen is expected to reduce the annual resupply weight for the Space Station by 

approximately 12,000 pounds with an associated reduction in logistics costs. The oxygen generation 

assembly which was initially baselined for the Space Station Freedom program is the Static Feed 

Electrolyzer (SFE) manufactured by Life Systems, Inc. The EPICS flight experiment will demonstrate and 

validate the SFE electrochemical process in microgravity, as well as investigate performance improvements 

projected possible in a microgravity environment. 

The space environment is needed for this experiment because the SFE process has not been operated in 

microgravity, data on gas and liquid transport in microgravity is very limited, and one-G test results are 

compromised by buoyancy and by gravity-affected fluid configuration within the electrolysis cells. A 

lower cell voltage operation may result from microgravity effects 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. 

Mission Description 

The EPICS experiment will examine the effects of microgravity on electrolyte distribution in the SFE 

electrolyte retention matrix. This will be accomplished by determining performance characteristics of 

electrode/matrix assemblies having different matrix thicknesses and electrode pore sizes, and operating at 

varying current densities. In one-G SFE operation, gravity produces an electrolyte distribution gradient and 

an electrolyte density gradient in the cell core. Such gradients result from the relative effects of gravity and 

capillary forces acting on the electrolyte solution within the cell core matrix. If a more uniform electrolyte 

distribution were to occur in microgravity, then a more efficient electrolysis process could result. 

Comparison of flight and ground test data collected under the same operating conditions will enable 

designers to determine if, and by how much, efficiency is enhanced in microgravity. This understanding 

can then be applied to the development of improved SFE designs. 

The experimental hardware consists of two primary hardware assemblies: 

a. Mechanical/Electrochemical Assembly (M/EA) 

b. b. Control/Monitor Instrumentation (C/MI) 

The M/EA contains the physical capability for conducting the EPICS experiment. It is composed of three 

separate, self-contained, Integrated Electrolysis Units (IEUs), ancillary components, and the enclosure. 

Each IEU is made up of an integrated electrolysis cell, a thermal control plate, an O2 accumulator, and a 

H2 accumulator. 

The C/MI controls the operation of the experiment, provides for monitoring and control of critical 

parameters, and stores experimental data. 

The experiment is designed to be self-contained, requiring only electrical energy and cabin air for cooling. 

The experiment is designed to be compatible with the weight, power, and heat rejection capability of two 

standard middeck locker spaces. The weight is approximately 93 lbs., and the required power is 

approximately 230 watts. The heat rejected to the cabin is essentially the power consumed. 

The flight of the EPICS is sponsored by the NASA’s Office of Space Access and Technology as part of the 

In-Space Technology Experiments Program. The EPICS payload is being developed by Life Systems, Inc., 

Cleveland, OH, and is managed by NASA’s Johnson Space Center, Houston, TX. 
Edited by Richard W. Orloff, 01/2001/Page 41 

COMMERCIAL MDA ITA EXPERIMENTS (CMIX-4) 

CMIX-4 is the fourth in a five-flight program to support commercially driven biomedical research 

involving NASA, the University of Alabama/Huntsville (UAH) Consortium for Materials Development in 

Space, and Instrumentation Technology Associates, Inc. (ITA), a small business located in Exton, PA. 

The Consortium’s research goals for this mission include an analysis of microgravity and its effects on cell 

change, as prior flight experiments indicate that microgravity slows cell growth. This alteration of cell 

growth in microgravity may provide important insight into cell changes on Earth and may lead to 

therapeutic measures to counter cell growth inhibition, loss of bone mass and impaired immune function. 

Research also will focus on neuro-muscular development disorders which are of interest to the industrial 

pharmaceutical and biotechnical research communities. 

A third set of experiments will be associated with plant cell growth. Pharmaceutical products from plants 

have been used for treatment of various types of cancer. Plant products include vinblastine and taxol. 

Cultured cells from soy bean plants will be flown during this mission to assess the effect of microgravity 

on growth, development and production of secondary metabolites. These cells, grown in ground-based 

tests, produce a product with anti-colon cancer activity. Preliminary research indicates that microgravity 

may foster higher production of this product. Other research experiments will be conducted using the flight 

hardware provided by ITA. 

ITA’s portion of the mission concentrates on three research activities: the growth of over a dozen types of 

protein crystals with emphasis on urokinase protein crystals; microencapsulation of drugs; and the ITA 

student space education program. 

The urokinase experiment is designed to grow protein crystals of urokinase for research linked to breast 

cancer inhibitors. If the structure of the urokinase protein crystal can be established, an inhibitor drug can 

be developed to combat breast cancer metastasis. To date, no ground-based research effort has provided 

urokinase crystals of sufficient size to effectively analyze. It is anticipated that the microgravity 

environment will enable urokinase protein crystals to be developed with sufficient size and uniformity of 

structure to be analyzed. 

ITA also is working with its partners to explore microencapsulation of drugs (a drug delivery system) to 

better target the intervention area of tumors without affecting surrounding healthy tissues. These research 

efforts have considerable potential for the pharmaceutical industry and medical provider community. 

A third major effort is ITA’s student space experiment outreach program which donates a percentage of the 

CMIX payload flight hardware and technical support to selected university and high school projects as a 

means of fostering an interest in the field of space technology. ITA also will have other experiments 

including an assessment of properties of collagen fibrils grown in space. 

This ambitious experiment activity is accomplished through an innovative exchange agreement between 

NASA and UAH, with a corresponding agreement between UAH and ITA. In exchange for the flight 

opportunities, ITA provides 50 percent of its privately developed Materials Dispersion Apparatus (MDA) 

flight hardware capacity to the UAH researchers. ITA markets half of its hardware commercially and 

provides a turn-key space processing, hardware and payload integration service to domestic and 

international users, including private sector companies, universities and research institutions. In addition, 

ITA conducts its own corporate biomedical research projects. This mission will also use Liquid Mixing 

Apparatus developed by ITA, and BioProcessing Modules provided by UAH. Some of these units will be 

contained within the Commercial Refrigerator Incubator Module. Others will be located in a separate 

storage pouch. This configuration of material and fluid mixing flight equipment enables hundreds of 

separate experiment samples to be flown within a single middeck locker. 
Edited by Richard W. Orloff, 01/2001/Page 42 

A number of researchers will take part in this mission for UAH experiments, including Dr. Millie HughesFulford, University of California at San Francisco; Dr. Mary Ann Priniapato, U.S. Food and Drug 

Administration; Dr. Edward Piepmeier, University of South Carolina; Dr. Raphael Gruener, University of 

Arizona; and Dr. Peter Kaufman, University of Michigan. These researchers are collaborating with Dr. 

Marian Lewis of UAH. ITA research projects and commercial users include two U.S. cancer centers, four 

U.S. corporations, a JSC researcher, four U.S. universities/research institutions, several international 

university research organizations including Canada and Germany (INTOSPACE) and one high school. 
Edited by Richard W. Orloff, 01/2001/Page 43 

STS-69 CREWMEMBERS 

STS069-S-002 -- These five NASA astronauts have been named as crew members for the STS-69 mission, 

scheduled onboard the Space Shuttle Endeavour in late July of 1995. David M. Walker (right front) is 

mission commander; with Kenneth D. Cockrell (left front) scheduled to serve as pilot. On the back row are 

(left to right) Michael L. Gernhardt and James H. Newman, both mission specialists; and James S. Voss, 

payload commander. 

No copyright is asserted for this photograph. If a recognizable person appears in the photo, use for 

commercial purposes may infringe a right of privacy or publicity. It may not be used to state or imply the 

endorsement by NASA or by any NASA employee of a commercial product, process or service, or used in 

any other manner that might mislead. Accordingly, it is requested that if this photograph is used in 

advertising and other commercial promotion, layout and copy be submitted to NASA prior to release. 

PHOTO CREDIT: NASA or National Aeronautics and Space Administration. 
Edited by Richard W. Orloff, 01/2001/Page 44 

BIOGRAPHICAL DATA 

DAVID M. WALKER , a three-time shuttle veteran will command Endeavour’s ninth mission. A captain in the 

United States Navy, Walker, 51, was born in Columbus, GA, but considers Eustis, FL., to be his hometown. He 

received a bachelor’s degree from the U.S. Naval Academy in 1966. After graduating from Annapolis, Walker 

received flight training from the Naval Aviation Training Command at bases in Florida, Mississippi and Texas. 

He was designated a naval aviator in December 1967 and proceeded to Naval Air Station Miramar, CA, for 

assignment to F-4 Phantoms aboard the carriers USS Enterprise and USS America. From December 1970 to 

1971, he attended the USAF Aerospace Research Pilot School at Edwards Air Force Base, CA. 

Selected as an astronaut in January 1978, Walker has logged a total of 464 hours in space. His first flight was as 

pilot of STS-51A in 1984. During that mission, crew members deployed Canada’s Anik D-2 satellite and 

Hughes’ LEASAT-1 satellite, and carried the first space salvage mission by retrieving the Palapa B-2 and Westar 

VI satellites for return to Earth. 

Walker’s second mission was STS-30 in May 1989. The highlight of the four-day mission was the deployment of 

the Magellan probe. Most recently, he commanded STS-53 in November/December 1992. The crew of five 

deployed a classified Department of Defense payload and then performed several Military-Man-In-Space and 

NASA experiments. 

KENNETH D. COCKRELL, a native of Austin, TX, will serve as the STS-69 pilot. Cockrell, 45, received a 

bachelor’s degree in mechanical engineering from the University of Texas in 1972, and a master’s degree in 

aeronautical systems from the University of West Florida in 1974. 

Cockrell received his commission through the Naval Aviation Reserve Officer Candidate Program at Naval Air 

Station at Pensacola, FL, in December 1972. He was designated a naval aviator in August 1974. Cockrell 

resigned his commission in 1987 to join the Johnson Space Center as an aerospace engineer and research pilot at 

Ellington Field, Houston, serving as an instructor pilot and functional check pilot in NASA T-38 aircraft. 

Selected as an astronaut candidate in January 1990, Cockrell has had a variety of technical assignments including 

serving in the Astronaut Office’s Operations Development Branch; working on landing, roll-out, tires and brake 

issues; and serving as CAPCOM in the Mission Control Center for ascent and entry. 

Cockrell’s first space flight in April 1993 was STS-56, the ATLAS-2 mission. During the nine-day flight, the 

crew conducted atmospheric and solar studies in order to better understand the effect of solar activity on the 

Earth’s climate and environment. 

JAMES S. VOSS, an Army Lieutenant Colonel will be Mission Specialist-1 and Payload Commander for the 

flight. 

Voss, 46, was born in Cordova, AL, but considers Opelika, AL, to be his hometown. He has a bachelor’s degree 

in aerospace engineering from Auburn University in 1972 and a master’s degree in aerospace engineering 

sciences from the University of Colorado in 1974. 

Upon graduation from Auburn and commissioning as a 2nd Lieutenant, Voss went directly to the University of 

Colorado to obtain his master’s degree under the Army Graduate Fellowship Program. After attending the U.S. 

Naval Test Pilot School at the Armed Forces Staff College, Voss was assigned to the U.S. Army Aviation 

Engineering Flight Activity as a Flight Test Engineer/Research and Development Coordinator. He was involved 

in several major flight test projects before being detailed to the Johnson Space Center. 

Voss began working at Johnson in 1984 as a Vehicle Integration Test Engineer. He participated in the STS 51-L 

accident investigation and supported the resulting reviews dedicated to returning the Space Shuttle safely to 

flight. He was selected as an astronaut in 1987, and is now a veteran of two Shuttle flights. His first mission, 

STS-44 in November 1991, included the deployment of a Defense Support Program satellite with an Inertial 

Upper Stage booster. His second mission was STS-52 in December 1992 during which a classified Department of 

Defense payload was deployed. He has logged more than 340 hours in space. 
Edited by Richard W. Orloff, 01/2001/Page 45 

JIM NEWMAN, Ph.D., 38, will serve as Mission Specialist 2. Born in the Trust Territory of the Pacific Islands, 

Newman considers San Diego, CA, to be his hometown. He graduated cum laude with a bachelor’s degree in 

physics from Dartmouth College in 1978. He received a master’s and a doctorate in physics from Rice University 

in 1982 and 1984, respectively. After graduating from Rice, Newman did an additional year of post-doctoral 

work at Rice before being appointed as an adjunct assistant professor in the Department of Space Physics and 

Astronomy at the university. That same year, he came to work at Johnson where he conducted flight crew and 

flight control team training for all mission phases in the areas of Orbiter propulsion, guidance and control. He 

was working as a simulation supervisor when selected for the astronaut program in 1990. 

STS-69 will be Newman’s second flight. His first mission was STS-51 in September 1993. During the 10-day 

flight, crew members deployed the advanced Communications Technology Satellite and the Orbiting and 

Retrievable Far and Extreme Ultraviolet Spectrometer on the Shuttle Pallet (SPAS) Satellite. Newman was 

responsible for SPAS operations and conducted a seven-hour spacewalk. He has logged 236 hours in space. 

MICHAEL L. GERNHARDT, Ph.D., 39, will serve as Mission Specialist 3 for the STS-69 crew. 

Born in Mansfield, OH, Gernhardt received a bachelor’s degree in physics from Vanderbilt University in 1978, 

and master’s and doctorate degrees in bioengineering from the University of Pennsylvania in 1983 and 1991, 

respectively. 

From 1977 to 1984, Gernhardt worked as a professional deep sea diver and project engineer on a variety of 

subsea oil field construction and repair projects around the world. He has logged more than 700 deep sea dives 

and has experience in air, mixed gas, bounce bell and saturation diving. 

In 1988, he founded Oceaneering Space Systems, a wholly- owned subsidiary of Oceaneering International. Until 

his selection by NASA in 1992, he worked on the development of new astronaut and robot-compatible tools for 

performing maintenance on the Space Station. He also worked on the development of new portable life support 

systems and decompression procedures for extravehicular activities. 

Since coming to NASA, Gernhardt has been detailed to the Shuttle Avionics Laboratory, supported training for 

the Hubble Space Telescope servicing mission and has worked on a variety of Space Station EVA developments. 

STS-69 will be his first space flight. 
Edited by Richard W. Orloff, 01/2001/Page 46 

SHUTTLE FLIGHTS AS OF AUGUST 1995 

70 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 45 SINCE RETURN TO FLIGHT 

STS-70 

07/13/95 - 07/22/95 

STS-63 

02/03/95 - 02/11/95 

STS-64 

09/09/94 - 09/20/94 

 STS-60 

02/03/94 - -2/11/94 

STS-65 

07/08/94 0 07/23/94 

STS-51 

09/12/93 - 09/22/93 

STS-62 

03/04/94 - 03/18/94 

STS-56 

04/08/83 - 04/17/93 

STS-58 

10/18/93 - 11/01/93 

STS-53 

12/02/92 - 12/09/92 

STS-55 

04/26/93 - 05/06/93 

STS-42 

01/22/92 - 01/30/92 

STS-71 

06/27/95 - 07/07/95 

STS-52 

10/22/92 - 11/01/92 

STS-48 

09/12/91 - 09/18/91 

STS-66 

11/03/94 - 11/14/94 

STS-50 

06/25/92 - 07/09/92 

STS-39 

04/28/91 - 05/06/91 

STS-46 

07/31/92 - 08/08/92 

STS-40 

06/05/91 - 06/14/91 

STS-41 

10/06/90 - 10/10/90 

STS-45 

03/24/92 - 04/02/92 

STS-35 

12/02/90 - 12/10/90 

STS-51L 

01/28/86 

STS-31 

04/24/90 - 04/29/90 

STS-44 

11/24/91 - 12/01/91 

STS-32 

01/09/90 - 01/20/90 

STS-61A 

10/30/85 - 11/06/85 

STS-33 

11/22/89 - 11/27/89 

STS-43 

08/02/91 - 08/11/91 

STS-28 

08/08/89 - 08/13/89 

STS-51F 

07/29/85 - 08/06/85 

STS-29 

03/13/89 - 03/18/89 

STS-37 

04/05/91 - 04/11/91 

STS-67 

03/02/95 - 03/18/95 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

STS-38 

11/15/90 - 11/20/90 

STS-68 

09/30/94 - 10/11/94 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-36 

02/28/90 - 03/04/90 

STS-59 

04/09/94 - 04/20/94 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-34 

10/18/89 - 10/23/89 

STS-61 

12/02/93 - 12/13/93 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-30 

05/04/89 - 05/08/89 

STS-57 

06/21/93 - 07/01/93 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-27 

12/02/88 - 12/06/88 

STS-54 

01/13/93 - 01/19/93 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-47 

09/12/92 - 09/20/92 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

STS-49 

05/07/92 - 05/16/92 

 

OV-102 

Columbia 

(17 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(21 flights) 

OV-104 

Atlantis 

(14 flights) 

OV-105 

Endeavour 

(8 flights)