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

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-39 

PRESS KIT 

MARCH 1991 

DEPARTMENT OF DEFENSE AIR FORCE PROGRAM-675 
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STS-39 INSIGNIA 

STS039-S-001 -- The arrowhead shape of the STS-39 crew insignia represents a skyward aim to learn more about 

our planet's atmosphere and space environment in support of the Department of Defense. Our national symbol is 

represented by the star constellation Aquila (the eagle) as its brightest star, Altair, lifts a protective canopy above 

Earth. The space shuttle encircles the spectrum which represents X-Ray, ultraviolet, visible and infrared 

electromagnetic radiation to be measured by a variety of scientific instruments. Experiments will be operated within 

the payload bay and aboard a free-flying satellite which will be deployed and retrieved during the mission. The 

insignia was designed by the STS-39 crew. 

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 

NASA PUBLIC AFFAIRS CONTACTS 

Mark Hess/Jim Cast/Ed Campion 

Office of Space Flight 

NASA Headquarters, Washington, DC 

(Phone: 202/453-8536) 

Lisa Malone 

Kennedy Space Center, FL 

(Phone: 407/867-2468) 

Jerry Berg 

Marshall Space Flight Center, Huntsville, AL 

(Phone: 205/544-0034) 

James Hartsfield 

Johnson Space Center, Houston, TX 

(Phone: 713/483-5111) 

Dolores Beasley 

Goddard Space Flight Center, Greenbelt, MD 

(Phone: 301/286-7277) 

Myron Webb 

Stennis Space Center, Bay St. Louis, MS 

(Phone: 601/688-2241) 

Nancy Lovato 

Ames-Dryden Flight Research Facility, Edwards, CA 

(Phone: 805/258-3448) 

DOD PUBLIC AFFAIRS CONTACTS 

Captain Marty Hauser 

Secretary of the Air Force Public Affairs 

The Pentagon 

(Phone: 703/695-5766) 

Betty Ciotti 

USAF Space Systems Division 

Los Angeles AFB, CA 

(Phone: 213/363-6836 

Major Carolyn Channave 

DOD/SDIO External Affairs 

The Pentagon 

(Phone: 703/693-1777 

Robert McKinney 

SDIO External Affairs 

The Pentagon 

(Phone: 703/693-1778 

Lt. Colonel Jim Jannette 

Eastern Space and Missile Center, FL 

(Phone: 407/494-7731) 
Edited by Richard W. Orloff, 01/2001/Page 4 

TABLE OF CONTENTS 

GENERAL INFORMATION 5 

GENERAL RELEASE 6 

STS-39 QUICK LOOK 8 

SUMMARY OF MAJOR ACTIVITIES 9 

SPACE SHUTTLE ABORT MODES 10 

TRAJECTORY SEQUENCE OF EVENTS 11 

VEHICLE AND PAYLOAD WEIGHTS 12 

STS-39 PRELAUNCH PROCESSING 13 

SHUTTLE ADVANCED GENERAL PURPOSE COMPUTER 14 

STS-39 MISSION OVERVIEW 15 

AIR FORCE PAYLOAD-675 (AFP-675): 17 

 CIRRIS-1A 17 

 AURORA DETAILS 18 

 FAR UV 18 

 URA 21 

 HUP 21 

 QINMS 23 

INFRARED BACKGROUND SIGNATURE SURVEY (IBSS) 24 

 IBSS OVERVIEW 24 

 SPAS-II 24 

 CRO 24 

 CRO MANAGEMENT 27 

 CIV 27 

 CIV MANAGEMENT 27 

 IBSS OBJECTIVES 29 

 IBSS PLUME OBSERVATIONS 30 

 EARTH BACKGROUND EXPERIMENTS 30 

 ORBITER ENVIRONMENT EXPERIMENT 30 

 IBSS PARTICIPANTS 31 

 STS-39 SPAS/IBSS RENDEZVOUS & TRACKING OPERATIONS 32 

SECONDARY PAYLOADS 

 STP-1 35 

 OVERVIEW 35 

 HITCHHIKER PROJECT 36 

 ULTRAVIOLET LIMB IMAGING (UVLIM) EXPERIMENT 36 

 ADVANCED LIQUID FEED EXPERIMENT (ALFE) 36 

 SPACECRAFT KINETIC INFRARED TEST (SKIRT) 37 

 ASCENT PARTICLE MONITOR (APM) 38 

 DATA SYSTEM EXPERIMENT (DSE) 38 

 STP-1 PARTICIPANTS 39 

 MULTI-PURPOSE EXPERIMENT CANISTER (MPEC) 40 

 CLOUDS 1A 41 

 RADIATION MONITORING EQUIPMENT-III 42 

STS-39 CREW BIOGRAPHIES 43 

SPACE SHUTTLE MANAGEMENT 47 
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GENERAL INFORMATION 

NASA Select Television Transmission 

NASA Select television is available on Satcom F-2R, Transponder 13, located at 72 degrees west 

longitude; frequency 3960.0 MHz, audio 6.8 MHz. 

The schedule for television transmissions from the orbiter and for the change-of-shift briefings from 

Johnson Space Center, Houston, will be available during the mission at Kennedy Space Center, FL; 

Marshall Space Flight Center, Huntsville, AL.; Johnson Space Center; and NASA Headquarters, 

Washington, DC. The TV schedule will be updated daily 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 TV schedule 

may be obtained by dialing 202/755-1788. This service is updated daily at noon EST. 

Status Reports 

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

produced by the appropriate NASA news center. 

Briefings 

An STS-39 mission press briefing schedule will be issued prior to launch. During the mission, flight 

control personnel will be on 8-hour shifts. Change-of-shift briefings by the off-going flight director will 

occur at approximately 8-hour intervals. 
Edited by Richard W. Orloff, 01/2001/Page 6 

RELEASE: 91-25 March 1991 

STRATEGIC DEFENSE SYSTEM TESTS HIGHLIGHT 

Mission STS-39 is the first unclassified Department of Defense-dedicated Space Shuttle mission, 

highlighted by around-the-clock observations of the atmosphere, gas releases, Shuttle engine firings, 

subsatellite gas releases and the Shuttle's orbital environment in wavelengths ranging from infrared to the 

far ultraviolet. 

Carried aboard Discovery on its 12th flight, the 39th Shuttle mission, will be Air Force Program-675 

(AFP-675); the Infrared Background Signature Survey (IBSS) mounted on the Shuttle Pallet Satellite-II 

(SPAS-II); the Critical Ionization Velocity (CIV) experiment; three Chemical Release Observation (CRO) 

subsatellites; the Space Test Payload (STP-1) and a classified payload in a Multi-Purpose Experiment 

Canister (MPEC). 

Inside Discovery's crew cabin will be the Cloud Logic to Optimize the Use of Defense Systems-1A 

(CLOUDS-1A) experiment and the Radiation Monitoring Equipment-III (RME-III). 

Work with these payloads during the flight will involve extensive maneuvering, rendezvous and close 

proximity operations by Discovery. STS-39 is currently working toward a 3:49 a.m. EST launch on March 

9, 1991. Landing is set for Edwards Air Force Base, CA, at 11:14 a.m. EST on March 17, giving the flight 

a planned length of 8 days, 7 hours and 26 minutes. 

AFP-675 is a collection of scientific instruments to observe targets such as the atmosphere, the aurora and 

stars in infrared, far ultraviolet, ultraviolet and X-ray wavelengths. AFP-675 instruments also will analyze 

the spectrum of various targets and gases released from or around the Shuttle. AFP-675 is sponsored by the 

U.S. Air Force's Space Systems Division and may provide a better understanding of the difficulties in 

identifying spacecraft with remote sensors and distinguishing those spacecraft from naturally occurring 

phenomena. The AFP-675 instruments also are to study several astronomical targets of interest. 

The Strategic Defense Initiative Organization's IBSS experiment, mounted on the SPAS-II platform, will 

be deployed and retrieved by Discovery so that SPAS-II can observe the Shuttle's engine firings from afar. 

IBSS will observe and record the infrared signature of these firings and also will perform infrared 

observations of other targets, including three CRO subsatellites to be released from Discovery. IBSS will 

observe common rocket fuels nitrogen tetroxide, monomethyl hydrazine and dimethyl hydrazine released 

from the three CRO subsatellites after they are deployed by Discovery. 

IBSS also will observe releases of the gases xenon, neon, carbon dioxide and nitric oxide from canisters in 

Discovery's payload bay. These gases are part of the CIV experiment, which, with instruments in the 

payload bay, will observe the releases simultaneously with IBSS. IBSS is sponsored by SDIO and 

information from its studies may assist in developing remote sensors that can identify missiles. 

The STP-1 experiment is a varied collection of scientific instruments, including one that will observe the 

luminous "airglow" effect of atomic oxygen on Discovery; one that will test a new method of flowing 

rocket propellants in weightlessness to assist in the design of future engines; and another to observe the 

fringes of Earth's atmosphere at various times, including sunrise and sunset, in ultraviolet wavelengths. 

STP-1 is sponsored by the Air Force's Space Systems Division. 

Inside the crew cabin, the CLOUDS-1A experiment is a camera the crew will use to photograph various 

cloud formations on the Earth to better understand cloud movements and structures. The RME-III 

experiment is designed to monitor radiation levels inside the cabin during the flight. 
Edited by Richard W. Orloff, 01/2001/Page 7 

Commanding Discovery will be Navy Capt. Michael L. Coats. Air Force Major L. Blaine Hammond will 

serve as pilot. Mission specialists include Gregory J. Harbaugh; USAF Lt. Col. Don McMonagle; USAF 

Col. Guion Bluford; C. Lacy Veach; and Richard J. Hieb. 

The flight crew will operate in two teams to accommodate 24-hour a day observations aboard Discovery, with each 

team working a 12-hour shift. On the Red Team will be Hammond, Veach and Hieb. On the Blue Team will be 

Harbaugh, McMonagle and Bluford. Coats will keep his own hours, independent of any assigned shift. 

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS.) 
Edited by Richard W. Orloff, 01/2001/Page 8 

STS-39 QUICK LOOK 

Launch Date: Mar. 9, 1991 

 

Landing Site: Kennedy Space Center, FL, Pad 39-A 

 

Launch Window: 3:49 a.m. - 6:51 a.m. EST 

 

Orbiter: Discovery (OV-103) 

 

Orbit: 140 x 140 nautical miles 

 

Inclination: 57 degrees 

 

Landing Date/Time: Mar. 17, 1991, 11:14 a.m. EST 

 

Primary Landing Site: Edwards Air Force Base, CA 

 

Abort Landing Sites: Return to Launch Site - Kennedy Space Center, FL 

 Transoceanic Abort Landing - Zaragoza and Moron, Spain 

 Abort Once Around - Northrup Strip, White Sands, NM 

 

Crew: Michael L. Coats, Commander 

 Blaine Hammond Jr., Pilot 

 Gregory L. Harbaugh, Mission Specialist 1 

 Donald R. McMonagle, Mission Specialist 2 

 Guion S. Bluford, Mission Specialist 3 

 C. Lacy Veach, Mission Specialist 4 

 Richard J. Hieb, Mission Specialist 5 

 

Cargo Bay Payloads: IBSS/SPAS-II 

 CIV 

 CRO 

 STP-1 

 MPEC 

 

Middeck Payloads: Cloud Logic to Optimize the Use of Defense Systems (CLOUDS-1A) 

 Radiation Monitoring Experiment (RME-III) 
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SUMMARY OF MAJOR ACTIVITIES 

Flight Day One 

Ascent 

OMS 2 

IBSS on-orbit checkout 

AFP-675 activation 

RME-III activation 

DSO 

Flight Day Two 

AFP-675 operations 

SPAS pre-deploy checkout 

IBSS/SPAS-II unberth; deploy 

IBSS/SPAS-II far-field observations 

Flight Day Three 

IBSS/SPAS-II far-field observations 

IBSS/SPAS-II near-field observations 

CRO-C deploy 

Flight Day Four 

IBSS/SPAS-II near-field observations 

IBSS/SPAS-II rendezvous 

CRO-B deploy 

IBSS/SPAS-II retrieval; berthing 

DSO 

Flight Day Five 

AFP-675 operations 

CRO-A deploy 

Flight Day Six 

SPAS-II pre-deploy checkout 

IBSS/SPAS-II unberthing; RMS operations 

Flight Day Seven 

IBSS/SPAS-II berthing 

AFP-675 operations 

Flight Day Eight 

AFP-675 operations 

STP-I operations 

Flight Control Systems checkout 

MPEC deploy 

Payload deactivation 

Cabin stow 

Flight Day Nine 

RME-III deactivation; stow 

Deorbit; landing 
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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 include: 

• Abort-To-Orbit (ATO) -- Partial loss of main engine thrust late enough to permit reaching a minimal 105-

nautical mile orbit with orbital maneuvering system engines. 

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

before landing at either Edwards Air Force Base, CA; White Sands Space Harbor (Northrup Strip), NM; or the 

Shuttle Landing Facility (SLF) at Kennedy Space Center, FL. 

• Trans-Atlantic Abort Landing (TAL) -- Loss of two main engines midway through powered flight would force 

a landing at either Zaragoza or Moron, Spain. 

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

Zaragoza, would result in a pitch around and thrust back toward KSC until within gliding distance of the SLF. 

STS-39 contingency landing sites are Edwards AFB, White Sands, Kennedy Space Center, Zaragoza and Moron. 
Edited by Richard W. Orloff, 01/2001/Page 11 

TRAJECTORY SEQUENCE OF EVENTS 

Event 

MET 

(d/h:m:s) 

Relative 

Velocity 

(fps) Mach 

Altitude 

(ft) 

 

Launch 00/00:00:00 

Begin Roll Maneuver 00/00:00:09 160 0.14 600 

End Roll Maneuver 00/00:00:19 410 0.37 3,500 

Throttle Down to 70% 00/00:00:28 630 0.56 7,170 

Throttle Up to 104% 00/00:00:58 1,320 1.28 33,230 

Max. Dynamic Pressure 00/00:01:03 1,460 1.45 38,540 

SRB Staging 00/00:02:06 4,190 3.80 154,810 

Main Engine Cutoff 00/00:08:30 24,900 21.94 375,830 

Zero Thrust 00/00:08:40 24,974 21.68 375,830 

ET Separation 00/00:08:50 

OMS 2 Burn 00/00:38:00 

IBSS/SPAS-II Deploy 01/21:10:00 

IBSS/SPAS-II Retrieval 03/11:18:00 

Deorbit Burn 08/06:31:00 

Landing 08/07:26:00 

Apogee, Perigee at MECO: 136 x 23 nautical miles 

Apogee, Perigee post-OMS 2: 140 x 140 nautical miles 
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VEHICLE AND PAYLOAD WEIGHTS 

Pounds

Orbiter (Discovery) empty, and 3 SSMEs 72,517 

Remote Manipulator System (payload bay) 1,258 

IBSS/SPAS-II (payload bay) 4,197 

AFP-675 (payload bay) 203 

Chemical Release Observation (CRO) (payload bay) 1,307 

Critical Ionization Velocity (CIV) (payload bay) 1,215 

Space Test Program (STP-I) (payload bay) 4,288 

Radiation Monitoring Experiment-III (RME-III) 8 

Cloud Logic to Optimize the Use of Defense Systems (CLOUDS) 8 

Total Vehicle at SRB Ignition 4,512,245 

Orbiter Landing Weight 211,300 
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STS-39 PRELAUNCH PROCESSING 

Kennedy Space Center workers began preparing Discovery for its 12th flight into space when the vehicle was towed 

into the Orbiter Processing Facility on Oct. 18 following its previous mission, STS-33. 

Discovery spent about 15 weeks in the processing facility undergoing about 22 modifications and routine testing. 

One of the significant changes made was the installation of the five new general purpose computers. 

Space Shuttle main engine locations for this flight are as follows: engine 2026 in the No. 1 position, engine 2030 in 

the No. 2 position, and engine 2029 in the No. 3 position. 

Booster stacking operations on mobile launcher platform 2 began Nov. 7 and were completed Dec. 13. The external 

tank was mated to the boosters Dec. 18 and the Orbiter Discovery was bolted to the tank on Jan. 30. 

STS-39 primary payloads were installed in Discovery's payload bay in the OPF and at the launch pad. Payloads 

installed in the OPF include the Critical Ionization Velocity payload and the Chemical Release Observatory. The 

U.S. Air Force payload 675 and the Shuttle Pallet Satellite-II were installed at the launch pad Feb. 5. The vehicle 

was rolled out to Launch Pad 39-A on Feb. 4. A dress rehearsal launch countdown was held Feb. 7-8 at KSC. 

The launch countdown will begin about 3 days prior to the launch. During the countdown, the orbiter's onboard fuel 

and oxidizer storage tanks will be loaded and all orbiter systems will be prepared for flight. About 9 hours before 

launch, the external tank will be filled with its flight load of a half a million gallons of liquid oxygen and liquid 

hydrogen propellants. About 2 1/2 hours before liftoff, the flight crew will begin taking their assigned seats in the 

crew cabin. 

KSC's recovery teams will prepare the orbiter Discovery for the return trip to Florida following the end-of-mission 

landing at Edwards AFB, CA. Orbiter turnaround operations at Dryden Flight Research Facility typically take about 

5 days. 
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SHUTTLE ADVANCED GENERAL PURPOSE COMPUTER 

On STS-39, Discovery's avionics system will feature the first set of five upgraded general purpose computers 

(GPCs), plus a spare, to fly aboard the Shuttle. 

The updated computers have more than twice the memory and three times the processing speed of their 

predecessors. Officially designated the IBM AP-101S, built by IBM, Inc., they are half the size, about half the 

weight and require less electricity than the first-generation GPCs. The central processor unit and input/output 

processor, previously installed as two separate boxes, are now a single unit. 

The new GPCs use the existing Shuttle software with only subtle changes. However, the increases in memory and 

processing speed allow for future innovations in the Shuttle's data processing system. 

Although there is no real difference in the way the crew will operate with the new computers, the upgrade increases 

the reliability and efficiency in commanding the Shuttle systems. The predicted "mean time between failures" 

(MTBF) for the advanced GPCs is 6,000 hours. The MTBF for the original GPCs is 5,200 hours. 

Specifications 

Dimensions: 19.55" x 7.62" x 10.2" 

Weight: 64 lbs. 

Memory capacity: 262,000 words (32-bits each) 

Processing rate: 1 million instructions per second 

Power requirements: 550 watts 
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STS-39 MISSION OVERVIEW 

The STS-39 mission is comprised of two primary payloads: Air Force Program 675 (AFP-675) and the Strategic 

Defense Initiative's (SDIO) Infrared Background Signature Survey (IBSS). 

There also are two secondary payloads; Space Test Payload (STP-1) and a Multi-Purpose Experiment Canister 

(MPEC). Two mid-deck experiments, CLOUDS-1A and RME III, are included on the STS-39 mission. IBSS and 

AFP-675 have scheduled observing time throughout the mission with a small amount of dedicated time for both 

STP-1 and MPEC on the last day of the mission. 

The AFP-675 payload is sponsored by SDIO and Air Force Systems Command's Space Systems Division (SSD). It 

contains three experiments sponsored by the Phillips Laboratory's Geophysics Directorate, by the Naval Research 

Laboratory, and by the Los Alamos National Laboratory, respectively. The prime integration contractor for the 

payload is Lockheed Missiles and Space Company, Inc. AFP-675 is a unique demonstration of the ability to 

command, control and evaluate a system of experiments without ground commands or telemetry data. 

Voice (although not necessary) will be included on this mission for communication between the crew and the 

ground to discuss the experiments. 

The AFP-675 payload will remain in the payload bay during the mission, and commanding of the experiments will 

be accomplished by the crew from a panel in the aft flight deck. The experiments will be measuring infrared, 

ultraviolet, visible and X-ray emissions. One of the important observations for the mission is the aurora. The launch 

date and time were chosen to assure visibility of the aurora. 

SDIO's IBSS payload is composed of three separate systems, the Shuttle Pallet Satellite (SPAS-II), the Critical 

Ionization Velocity (CIV) system and the Chemical Release Observation (CRO) experiment. SDIO has program 

management responsibility. The SPAS-II was developed by Messerschmitt-Bolkow-Blohm (MBB). 

The CIV portion is managed by the Geophysics Directorate, and the CRO portion is managed by the Western Space 

Technology Center. Mission operations are managed by SSD. 

The SPAS-II structure supports a cryogenically cooled infrared sensor, an ultraviolet multispectral sensor and low 

light level television cameras. The SPAS-II will be deployed and maneuvered to observe various targets and can be 

commanded by the on-board crew or by the ground. 

The CRO is composed of three separate subsatellite structures that will be deployed and will release chemicals upon 

ground command to be observed by the SPAS infrared sensors. Each subsatellite is loaded with a different 

chemical. 

The CIV structure is composed of four separate gas canisters which remain attached to the orbiter and will release 

gas upon command to be observed by the SPAS sensors. Each cylinder is loaded with a different gas; xenon, neon, 

carbon dioxide and nitrous oxide. 

SSD sponsors the STP-1 payload which is a standard Goddard Space Flight Center (GSFC) Hitchhiker structure 

supporting five experiments. Experiments are sponsored by the Naval Research Laboratory, the Rocket Propulsion 

Directorate of the Phillips Laboratory, the Geophysics Directorate, GSFC, and SSD. 

STP-1 remains in the cargo bay and is commanded from a control center at Goddard Space Flight Center. The 

UVLIM experiment will collect airglow measurements, ALFE will evaluate advanced propellant management 

systems, and SKIRT will collect infrared, visible and ultraviolet data on Shuttle glow. DSE will test advanced data 

management concepts, and APM will collect particles to study particulate contamination in the Shuttle bay. 

MPEC is a multipurpose experiment canister sponsored by SSD. The MPEC will deploy a classified experiment on 

the last day of the mission. 

There are two mid-deck experiments on the STS-39 mission. The CLOUDS-1A experiment will study cloud cover, 

and the RME-III experiment will measure ionizing radiation exposure in the orbiter cabin. 
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Edited by Richard W. Orloff, 01/2001/Page 17 

AIR FORCE PAYLOAD-675 

Cryogenic Infrared Radiance Instrumentation For Shuttle (CIRRIS-1A) 

The CIRRIS instrument is sponsored by the Strategic Defense Initiative Organization (SDIO), and program 

responsibility is under the Phillips Laboratory's Geophysics Directorate at Hanscom Air Force Base, MD. The 

sensor prime contractor is Utah State University with major subcontractors Space Data Corporation, Sensor System 

Group and Boston College. 

CIRRIS-1A is the highest priority experiment being flown on the AFP-675 space vehicle. The experiment is 

designed to be operated by Discovery's crew from a command panel in the aft flight deck. 

The experiment operates in the infrared portion of the electromagnetic spectrum (wavelength between 2.5 to 25 

micro-meters). The experiment will obtain simultaneous spectral and spatial measurements of airglow and auroral 

emissions. 

The data obtained from the mission should help answer questions regarding the optimum atmospheric windows for 

detecting cold body targets, the background radiance levels in various regions, the spatial structure (clutter) of the 

background, and the variability of Earth limb emissions during day/night airglow and auroral events. This 

information will help DOD design surveillance systems. 

There is a low light level television co-aligned on the sensor telescope which can be used by the crew to acquire and 

track the auroral displays and celestial calibration targets. 

One primary mission objective is to measure the spectral and spatial characteristics of auroral emissions. The premidnight/midnight sector of the Northern and Southern auroral oval is expected to exhibit the most intense infrared 

emissions and therefore, is of particular interest. An auroral watch will be maintained by a network of ground 

personnel to monitor the level of auroral activity. In the event of an intense auroral display, this team would alert 

Discovery's crew of the location and intensity of the aurora. 

Earth limb emissions will be collected covering a range of altitudes, latitudes, day/night and geomagnetic 

conditions. 

To provide a radiometric calibration of the infrared sensors, certain known celestial sources will be measured during 

the mission. 

Discovery will be maneuvered to provide the proper attitude for observations and to provide the required scanning 

and pointing capability. The sensor is mounted on a two-axis gimbal. 

Gravity gradient is the primary attitude for CIRRIS-1A data collection. It is the only attitude maintainable by the 

orbiter without the use of the reaction control system which produces unacceptable contaminates. 
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Edited by Richard W. Orloff, 01/2001/Page 20 

Aurora Details 

Aurora are created by solar activity. When a solar flare, sun spot or coronal hole occurs within a particular area of 

the sun's disk, an increased number of energetic particles is directed towards the Earth. As the solar wind accelerates 

with the Earth's magnetosphere, a generator effect is produced which accelerates electrons down the Earth's 

magnetic field lines. As these electrons impinge upon the Earth's atmosphere, oxygen and nitrogen are excited and 

ionized to produce aurorae. The aurorae emit visible, ultraviolet, infrared and radio frequencies. Because the 

electrons precipitate down the geomagnetic field lines, aurorae are produced in an oval shaped zone roughly 

centered around the magnetic pole regions of the North and South poles. 

The shape and size of the oval is dependent on the intensity of the solar wind. The intensity of the aurora within the 

oval is variable. The objective of the mission is to observe an extremely active aurora. The two primary indicators 

for predicting when an active aurora might appear are solar activity and geomagnetic disturbance. These events will 

both be monitored during the mission. 

A ground station magnetometer network and Defense Meteorological Satellite Program (DMSP) satellite coverage 

will be utilized to detect whether an active aurora is in progress. This network is located in the Northern 

Hemisphere and will collect simultaneous scientific measurements as well as provide a near real-time detection 

capability. The southern aurora is a mirror image of the northern aurora. If there is an active northern aurora then 

the southern aurora also will be active. 

FAR Ultraviolet Cameras (FAR UV) 

The FAR Ultraviolet Cameras experiment is sponsored by the Naval Research Laboratory. The hardware is a part of 

the AFP-675 payload. The instrumentation consists of two electrographic Schmidt cameras. A course-pointing two 

axis gimbal platform and a low light level TV camera for finding the objects and guiding the instrument. The 

instrument also has a stabilization system for long exposures on celestial objects. The instrument weighs 

approximately 550 pounds and the dimensions are approximately 60" x 32" x 20". 

The cameras will record naturally-occurring and man-made emission phenomena in near-Earth space in the 1050-

1600 angstroms (A) and 1230-2000A wavelength ranges. The phenomena of interest include day and night airglow, 

diffuse aurorae and the orbiter environment. Of particular interest is the orbiter thruster and surface glow effects. 

The experiment also will make observations of interplanetary and interstellar media, stars, extragalactic objects, 

effects of chemical deposition and atmospheric density measurements by stellar occultation. 

Each camera has a film transport loaded with 150 feet of film yielding up to 900 frames of data. The gimbaled 

platform allows pointing of FAR UV to be somewhat independent of orbiter attitude. The outer gimbal can travel 

between +/- 80 degrees and the inner gimbal can travel between +/- 22 degrees. 

The experiment is commanded by a crew member who views the TV monitor to determine where the camera is 

pointing as he moves the camera into position. 

The sun sensor is an array of silicon solar cells which outputs a voltage of 5 volts in full sunlight. As the output 

from the sun sensor in excess of 3 volts indicates the sun is shining into the payload bay and hence, the FAR UV 

high voltage must be turned off and the doors closed. 

The terrestrial atmospheric observations include northern and southern diffuse aurora, snapshot views of discrete 

aurora, night airglow with attention to the tropical arcs and twilight airglow. Stellar occultation observations will 

occur concurrent with airglow observations. Any unique phenomena such as meteor showers should be noted if they 

occur in airglow or aurora viewing periods. 
Edited by Richard W. Orloff, 01/2001/Page 21 

The celestial target observations include the diffuse nebulae, diffuse galactic background, star fields at high and low 

galactic latitudes, and also nearby external galaxies. 

The primary Shuttle environment events are the primary RCS and OMS thruster firings (in daylight and dark) and 

Shuttle glow. Secondary interests are Shuttle contamination effects such as fuel cell purges, flash evaporator events 

and water dumps. 

Uniformly Redundant Array (URA) 

The URA experiment is sponsored by the Department of Energy and Los Alamos National Laboratory. 

The URA is designed to conduct studies of astrophysical sources of X-ray radiation. The instrument, a part of the 

AFP-675 payload, is an assembly consisting of a detector, a 35 mm camera and an electronics package. The 

aperture plate of the detector contains over 26,000 hexagonal holes to collect the X-ray photons. Objects will be 

selected to test the capability of the URA to image point sources, complex collections of point sources and extended 

objects. The instrument will be operated both in a staring and slow scan mode. The URA experiment will be 

controlled by a mission specialist via the CMP (Command and Monitor Panel). 

The URA must not only detect X-rays of interest but must also suppress detection of particles that are present as 

background. The backgrounds of concern are mainly cosmic rays (relativistic protons and alpha particles) and 

charged particles (electrons above a 50 keV energy) trapped by the Earth's magnetic field. Because such particles 

penetrate the detector walls or window, the backgrounds are rejected by anti-coincidence, second moment and rise 

time discrimination techniques. 

The extended charge distribution from an energetic charged particle, as opposed to an X-ray photon, produces a 

slower amplifier pulse because it is collected over a finite period of time. Rise time discrimination is thus an 

independent means of background rejection. 

Despite the background rejection provisions, URA will not operate usefully at high levels of background. Cosmic 

ray background is less at low latitude and altitude because of the shielding effect of the Earth's magnetic field. X-ray 

experiments are not successful in high background regions, which are found at high altitude, and high magnetic 

latitude, and in the South Atlantic Anomaly. 

Low altitude, low latitude will increase the success of the URA observations. 

Horizon Ultraviolet Program (HUP) 

The HUP is an AF Geophysics Laboratory experiment to demonstrate a capability to measure the spatial and 

spectral characteristics of the Earth's horizon as observed in the ultraviolet wavelength region and to analyze Shuttle 

contamination. 

The instrument weighs less than 40 pounds and is approximately 15" x 21" x 9". 

The ultraviolet instrument is smaller and does not require cooling like the infrared instruments. The experiment runs 

continuously during the mission. The line of sight of the instrument is in the -Z direction, vertically out of the 

Shuttle bay. 

The telescope assembly is pivoted about an axis which enables the field of view to vary from local horizontal to a 

few degrees below the hard Earth horizon. Data will be collected using continuous angle scans at a series of 

wavelengths in the range of 1100-1900 A, continuous wavelength scans in a fixed direction and a fixed wavelength 

fixed direction. 
Edited by Richard W. Orloff, 01/2001/Page 22 

To prevent damage from the sun, a solar protection sensor closes the spectrometer shutter when the sun is 

within 3 degrees of the line of sight. The spectrometer then automatically starts a calibration cycle and 

resumes data taking when the sun is no longer in the field of view. 

The HUP instrument will measure the atmospheric radiance as a function of tangent altitude. The horizon 

limb profiles are necessary to develop attitude sensors for spacecraft and to obtain backgrounds for above 

the horizon missile detection techniques. The radiance is due to solar scattering, airglow and auroral 

excitation. Contamination of the orbiter environment also will be measured. 

The experiment should yield data radiation backgrounds from the airglow and aurora Earth limb 

measurements, and information on variability and clutter in the atmosphere. 
Edited by Richard W. Orloff, 01/2001/Page 23 

Quadrupole Ion-Neutral Mass Spectrometer (QINMS) 

The QINMS experiment is sponsored by the Phillips Laboratory's Geophysics Directorate. The mass spectrometer 

instrument weighs approximately 28 pounds. 

The hardware, part of the AFP-675 payload, is mounted to the ESS and does not gimbal. 

The primary role of QINMS is to support CIRRIS by measuring the amount and nature of orbiter bay 

contamination, particularly water concentration. CIRRIS will not be operated until contamination levels are low. 

QINMS will collect data continuously throughout the flight with operations controlled by a Mission Specialist via 

the CMP. 

Data also will be collected while passing through the auroral zone and polar latitude. Levels of hydrogen, oxygen, 

water vapor and other gases will be measured. 
Edited by Richard W. Orloff, 01/2001/Page 24 

INFRARED BACKGROUND SIGNATURE SURVEY (IBSS) 

IBSS Overview 

Infrared Background Signature Survey is a Strategic Defense Initiative Organization sponsored program for the 

purpose of obtaining scientific data for use in the development of ballistic missile defense sensor systems. 

IBSS is composed of three separate elements: the Shuttle Pallet Satellite II (SPAS -II), the Critical Ionization 

Velocity (CIV) package, and the Chemical Release Observation (CRO) experiment. In addition to sponsoring the 

program, SDIO also manages the overall program. Supporting SDIO in program management are several systems 

engineering and technical analysis firms, including: Stears, Kiya and Wright of Arlington, Va.; Orbital Systems 

Limited of Lanham, Md.; Nichols Research Corp. of Vienna, VA., and Hernandez Engineering Inc. of Houston, 

TX. The SPAS-II hardware is developed and manufactured by Messerschmitt-Bolkow-Blohm GmbH of Munich, 

Germany. Mounted on the SPAS-II are two sensor systems: an infrared spectrometer/radiometer built by KayserThrede of Germany housed in cryostat (cryogenically cooled instrument chamber) built by Linde of Germany and a 

multispectral Arizona Imager/Spectrograph (AIS) built by the University of Arizona at Tucson, AZ. 

Shuttle Pallet Satellite II (SPAS-II) 

The SPAS-II element incorporates a liquid helium cooled infrared sensor, the Arizona Imager/Spectrograph (AIS) 

multispectral sensor, two low light level television cameras and various support subsystems on a modular graphiteepoxy structure. SPAS-II will be deployed from the orbiter using the Remote Manipulator System (RMS) and will 

maneuver at ranges of up to 20 km from the orbiter to gather spectral and spatial data during several experiments. 

Chemical Release Observation (CRO) 

The Chemical Release Observation (CRO) portion of the Infrared Background Signature Survey (IBSS) mission is 

an experiment designed to collect infrared, visible and ultraviolet time-resolved radiometric data associated with the 

release of liquid rocket propellants in near Earth orbit. The experiment is composed of three separate subsatellites 

containing chemicals and their launchers. 

Since the three chemical releases will produce short-lived clouds of vapor and frozen particles in orbit near the 

Shuttle, it is possible that a faint glow of visible light may occur due to the interaction of the vapor cloud with 

oxygen atoms in the upper atmosphere. It is not expected, however, that the vapor glow from any of the releases 

will be bright enough to be detected by the unaided eye on the ground. The chances of observers near Vandenberg 

seeing the first and only nighttime scheduled release experiment are very remote. 

The cloud of frozen particles, however, can scatter sunlight producing visible light with much greater intensity. The 

sunlight scattered from the particle cloud will not be as intense as the daytime sky, however, so it is unlikely that 

either the second or third release can be viewed from the ground for the scheduled launch and mission time line. If 

the launch is delayed a couple of hours, however, the first scheduled release could occur under pre-dawn twilight 

conditions on the west coast. This situation would provide optimal viewing conditions as the release would occur in 

sunlight while a west coast observer would be in darkness. Under these conditions, the release would initially 

appear as a disk of white light approximately the size of the full moon (though somewhat dimmer). The cloud will 

continue to grow and gradually dim after the flow of liquid ends. The remnants of the bright cloud will only persist 

for a few minutes. 
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CRO Management 

The CRO element is managed by the Air Force Space Technology Center from their West Coast (Los Angeles) 

office. The CRO subsatellites and launcher mechanisms are designed and manufactured by Defense Systems Inc.,. 

of McLean, Va., while the launcher cylinders and support beams are provided by NASA/Goddard Space Flight 

Center at Greenbelt, MD. Subsatellite ground control and telemetry is provided by USAF 6595th Test & Evaluation 

Group and the Western Test Range at Vandenberg AFB, CA, supported by Federal Electric Corp. Aircraft sensor 

platform operations for collecting CRO data in the VAFB area are provided by the HALO aircraft, operated by 

Phillips Laboratory's Weapons Directorate and 4950th Test Group at Kirtland AFB, N.M., supported by BDM Corp. 

of Albuquerque, N.M. 

IBSS mission integration, launch site operations and payload flight operations are managed by the Space Systems 

Division, Air Force Systems Command, supported by The Aerospace Corporation and Rockwell International Space 

Division. 

Critical Ionization Velocity (CIV) 

The Critical Ionization Velocity experiment will investigate the interaction of neutral gases with the ambient 

weakly-magnetized plasma. 

The CIV element includes four compressed gas canisters (xenon, neon, carbon dioxide and nitrous oxide) which 

release plumes of the gas out of the orbiter bay upon crew command. The plumes are then observed by the SPAS-II 

sensors at different orientations to the orbiter's direction of travel and the local geomagnetic lines of force. The CIV 

hardware weighs about 500 lbs. 

Kinetic energy of the gas will exceed its ionization potential due to its relative velocity with the ambient plasma. 

The resulting plasma instability is expected to enhance ionization. Charge exchange between the gases released and 

ambient ions (mainly oxygen) is expected to produce other ions. 

Both mechanisms can lead to the release of radiation. Therefore, radiation in the infrared, visible and ultraviolet 

bands will be collected by the sensors from the deployed SPAS-II. The CIV experiment also has a data acquisition 

package, its radiometers will measure both visible and ultraviolet radiation from the payload bay. The CIV 

experiment, in the payload bay, has a Langmuir probe which will measure the ambient electron density and 

temperature. 

Four different gases have been selected, and the release mechanism was designed such that the critical ionization 

velocity should be reached for three of the four gases when they are released in the RAM direction. Because the 

orientation and strength of the local magnetic field is expected to affect the intensity of the ionization phenomenon, 

the gas releases will be observed both when the local magnetic field is approximately parallel to RAM and when it 

is perpendicular to RAM. The effect of ambient electron density on the phenomenon will be observed by repeating 

the observations in both the daylight and darkness. 

Four observations are planned with the SPAS-II deployed at a location near the Orbiter. Lighting and magnetic field 

orientation will be varied to produce four unique observations. 

CIV Management 

The CIV element is managed by Geophysics Laboratory/Space Physics Division at Hanscom AFB, Mass. 

Supporting contractors include: 

Physical Sciences Inc., Andover, MA Gas Release System & System Integration 

Northeastern University, Boston, MA Payload Support System Manufacturer 

Wentworth Inst. of Tech, Boston, MA General Mechanical Mfg. 

John Hopkins University, Baltimore, MD Pressure Gauge Subsystems 

Research Science Inc., Washington, DC Radiometer Subsystem 

University of Iowa, Iowa City, IA Langmuir Probe 
Edited by Richard W. Orloff, 01/2001/Page 28 
Edited by Richard W. Orloff, 01/2001/Page 29 

IBSS OBJECTIVES 

The Infrared Background Signature Survey is a Strategic Defense Initiative Organization sponsored program for the 

purpose of obtaining scientific data for use in the development of ballistic missile defense sensor systems. The IBSS 

mission will involve the collection of infrared, ultraviolet and visible measurements of natural and induced 

geophysical phenomena. 

Using the SPAS-II sensors at various ranges from the orbiter, spectral, spatial and temporal radiometric 

observations will be made of the exhaust plumes when the orbiter's orbital maneuvering systems (OMS) fires and 

creates replications of ICBM booster and midcourse engine firings. Interaction of the outer plume regions with the 

atmosphere will be characterized, as well as the region near the exit nozzle. The single engine OMS firings for these 

observations represent the first time such firings have been attempted in space by the orbiter. 

The Chemical Release Observations (CRO) will be carried out by deploying each of the three CRO subsatellites 

from the cargo bay at about 3.5 feet per second, allowing them to separate until the subsatellite trails the SPAS-II by 

50 to 200 km in orbit. Release will be timed such that, at that range, the CRO subsatellite will pass over Vandenberg 

AFB (VAFB) in Southern California. A signal from VAFB will cause the subsatellite to send telemetry 

measurements of its health and status. Then another signal (moments later on the same pass or on the next pass) will 

cause the subsatellite to expel a stream of chemical which will quickly vaporize into a cloud, while being observed 

from SPAS-II sensors, ground sensors at VAFB and airborne sensors on the ARGUS aircraft, simultaneously. 

Spectral information will permit characterization of the chemical interactions with the atmosphere and solar energy, 

as well as determine the aerosol distribution of the chemicals with respect to particle size and expansion rate. The 

chemicals released are 15 pounds of nitrogen tetroxide, 52 pounds of unsymmetrical dimethyl hydrazine and 60 

pounds of monomethyl hydrazine, released in that order. These observations will assist the SDIO in characterizing 

the signature from liquid fuel clouds escaping from damaged ICBM boosters. 

The subsatellites will be tracked and commanded by personnel from the USAF 659th Test and Evaluation Group, 

supported by Federal Electric Corporation, using assets of the Western Test Range at VAFB. Aircraft sensor 

platform operations for collecting CRO data in the VAFB area are provided by the Strategic Defense Initiative 

Organization's High Altitude Observatory (HALO) aircraft operated by Aeromet Inc., Tulsa, Okla., with instrument 

support by Automated Sciences Group, Inc., Huntsville, AL. for the U.S. Army Strategic Defense Command. 

The CIV experiment is intended to provide on-orbit spectral data to examine a theory which holds that many gases 

(including rocket combustion products) can be ionized if they are passed through a magnetized plasma and their 

kinetic energy is caused to exceed their ionization potential. Ions so created would then flow along the local 

magnetic lines of force and generate emissions which can be detected by space-borne sensors, thereby permitting 

tracking of the vehicle releasing the gases. In the CIV experiment, gases under pressure will be ejected at different 

angles to the orbiter velocity (such that collisions with the thin orbital atmosphere will enhance ionization) and to 

the local magnetic field lines. The SPAS-II will be "parked" about 2 km away, taking spectral data on the gas 

plumes, and other instruments in the CIV package (radiometers and a Langmuir probe) will take data as well. The 

gases used will be xenon (low ionization potential - should definitely ionize), neon (very high potential - should not 

ionize), carbon dioxide and nitric oxide (typical exhaust products form hypergolic fueled rockets). 

SPAS-II also will be used to take spatial and spectral measurements of the Earth's atmosphere as viewed at the 

horizon (called the "Earth's limb" at various altitudes above the surface. Such data is necessary to establish the 

background against which an approaching ICBM would be viewed by a sensor system as the ICBM came over the 

horizon. For the same reason, measurements will be taken of the Earth's surface under many conditions of light and 

darkness, hard earth and water, clouds and cloudlessness. Yet another geophysical type of data which will be 

measured for the same reasons will be auroral emissions (Northern and Southern Lights) as available. 

Finally, to characterize the effects of contaminating materials coming from a sensor platform itself, the environment 

around the orbiter will be measured by the SPAS-II "parked" nearby. These measurements will be taken with the 

orbiter in a "quiet" state, as well as during fuel cell purges, water dumps, thruster firings and other contaminating 

events. Measurements also will be taken of the "orbiter glow" phenomenon. This phenomenon occurs where the 

rarefied atmosphere strikes orbiter surfaces, especially the tail, causing visible and infrared radiance. Theories on 

the mechanism, including reactions with atomic oxygen, chemiluminescence and gas phase collisions, will be 
Edited by Richard W. Orloff, 01/2001/Page 30 

investigated and hopefully better understood. This phenomenon also may occur on orbiting SDI sensor platforms or 

target ICBM vehicles. 

IBSS Plume Observations 

The objective of the plume experiment is to gather data on the optical signature of rocket plumes. The experiment 

should permit the characterization of the plumes through spectral, spatial and temporal radiometric measurements in 

the infrared, ultraviolet and visible bands. 

Observations will be made of the plumes generated by the orbiter engine firings. The outer regions of the plumes 

will be examined to determine the interaction with the atmosphere. Observations also will be made to measure the 

radiative properties near the exit nozzle. 

Earth Background Experiments 

The Earth Background experiments will use the IBSS Infrared Sensor and the AIS sensors to characterize the Earth 

background from the Earth's limb to the hard earth and in areas around the solar specular point. Measurements will 

consist of Earth's limb and Earth scan observations with SPAS deployed, auroral observations with SPAS on the 

RMS, and AIS Earth's limb observations from in the bay. 

The Earth's limb observations will include day, night and terminator views. The Earth scan observations are directed 

at the Earth rather than the limb. These include observations of spatial clutter in CO2 bands, observations of areas 

around the solar specular point, the terminator and limb to Earth scans. 

Orbiter Environment Experiment 

The Orbiter Environment Experiment is an experiment to be performed by the IBSS payload. The orbiter 

environment observation will use the IBSS infrared sensor and the AIS sensors to characterize the contaminant 

environment in and around the orbiter payload bay. Observations will be in the infrared, visible, and ultraviolet 

regions of the spectrum. Observations also will be made of the orbiter glow phenomenon. 

During orbital operations, water dumps are made and thrusters are fired. Gases are released when materials are 

exposed to the vacuum environment of space. This experiment will observe these and other contaminants in the 

payload bay. 

A diffuse near-field glow phenomenon has been observed above spacecraft surfaces subjected to the impact of 

atmospheric species as the spacecraft travels through the low-Earth orbital atmosphere. It is thought that this 

phenomenon results from some type of interaction between the ambient atmosphere and the spacecraft surface. 

Sufficient data does not exist to fully understand the process. A number of mechanisms have been proposed which 

could give rise to the glow. These include: (1) gas phase collisions, (2) surface-aided chemiluminescence reactions 

with adsorbates on orbiter surfaces, and (3) surface reactions with the atomic oxygen environment leading to 

material loss or compositional changes. 

The spectrum of the glow is relatively diffuse and based primarily in the red-infrared region. The glow intensity is 

dependent upon the surface orientation to the velocity vector. The glow intensity seems to vary as a function of the 

atomic oxygen density. The glow intensity seems to vary depending upon the type of material. 
Edited by Richard W. Orloff, 01/2001/Page 31 

IBSS Participants 

Program Management

Strategic Defense Initiative Organization., Washington, DC 

Integration of Payload and Operations with Shuttle

HQ Space Systems Division, Los Angeles Air Force Base, CA 

The Aerospace Corporation, Los Angeles, Calif. 

Federal Electric Corporation 

Vandenberg Air Force Base, CA 

Rockwell International, Downey, CA 

6595th TEG/DTR and Western Test Range, Vandenberg Air Force Base, CA 

Develop Payload

Strategic Defense Initiative Organization, Washington, DC 

Messerschmidt-Bolkow-Blohm, Germany 

Defense Systems, Inc., McLean, VA 

Physical Sciences, Inc., Andover, MA 

Orbital Systems, Ltd., Lanham, MD. 

SKW Corporation, Arlington, VA 

Nichol Research Corp., McLean, VA 

Geophysics Directorate of Phillips Laboratory 

Hanscom Air Force Base, MA 

Phillips Laboratory's West Coast Office, Los Angeles Air Force Base, CA 

University of Arizona, Tucson, AZ 

Training

Hernandez Engineering Corp., Houston, TX 
Edited by Richard W. Orloff, 01/2001/Page 32 

STS-39 SPAS/IBSS RENDEZVOUS & TRACKING OPERATIONS 

Rendezvous and tracking maneuvers in support of IBSS operations during STS-39 present many significant 

challenges to Space Shuttle mission operations. More than 60 orbiter maneuvers are planned to support the various 

phases of SPAS/IBSS rendezvous, including IBSS calibrations, deployment, separation, far-field observations, nearfield observations, CRO subsatellite deployments and observations, and SPAS retrieval and berthing. 

Separation to Far-field 

Following the deployment of the SPAS/IBSS imaging platform, the crew will perform an acceleration, or posigrade 

burn, firing Discovery's reaction control system (RCS) thrusters to raise Discovery's orbit about 1 statute mile above 

the SPAS. The effect of this maneuver will drift Discovery to a point about 6 1/2 statute miles behind the SPAS, the 

required distance for far-field observations. Arriving at that point one orbit after the separation burn, the crew will 

fire the RCS to brake Discovery and place it again in the same orbit with the SPAS. Deployment and separation are 

scheduled to occur while both crew shifts are awake. 

Far-field Operations 

Following a crew shift handover at the far-field position, the Red Team will maneuver Discovery to point its nose 

north, with the payload bay pointed in the direction of orbital travel -- toward SPAS, 6 1/2 miles ahead. 

OMS Plume Observation 

From this position, the crew will remotely command the SPAS/IBSS to point its imaging systems at Discovery for 

the first plume observation. Once the experiments are properly trained on Discovery, one orbital maneuvering 

system (OMS) engine will be fired for 20 seconds. The result of the burn will be to propel Discovery north, off of 

its previous orbital groundtrack, without changing the spacecraft's altitude. A burn with this lateral effect is known 

as "out-of-plane." Immediately following the burn, the crew will perform a "fast-flip" yaw maneuver, using RCS 

jets to turn Discovery's nose around 180 degrees to the south. A single-engine OMS braking burn then will be 

performed to stop Discovery's travel at a point less than a mile north of its previous groundtrack. Using RCS jets, 

the crew will return Discovery to its starting position, on its original groundtrack behind the SPAS. As Discovery 

drifts back to the starting point, a "fast-flip" reversal will turn the spacecrafts nose back to the north. Throughout 

this sequence, the crew will point the SPAS/IBSS by remote control to observe each burn. 

Far-field observations will continue following the Blue Team's sleep shift. Due to the complexities involved, all 

OMS burns will be conducted only when both crew shifts are awake and able to participate. 

Discovery will remain at the far-field position during the Blue Team's sleep, and the Red Team will continue 

SPAS/IBSS operations, conducting Earth's limb observations by remote control. 

Following the Blue Team's sleep shift, while both teams are awake, the same sequence of maneuvers will be 

repeated twice in support of two additional plume observations. 

PRCS Plume Observation 

The final IBSS objective at the far-field position will be an observation of Discovery's primary RCS jets firing. In 

the same attitude used for OMS plume observations, the crew again will align SPAS/IBSS to train it's optics on the 

vehicle and then ignite one of the primary thrusters for 25 seconds. 
Edited by Richard W. Orloff, 01/2001/Page 33 

Far-field CRO Release 

After the far-field plume observations have been completed and while the Red Team sleeps, the Blue Team will 

eject the first CRO canister from the payload bay at a rate of 3.5 feet per second (fps) to an altitude just above that 

of Discovery and SPAS. 

Just after it is ejected from the payload bay, antennae on the canister will deploy, providing a remote command link 

to investigators at Vandenberg Air Force Base (VAFB). The canister will drift during several orbits to the desired 

distance for IBSS imaging, where VAFB investigators will remotely command the canister to release its gaseous 

contents. CRO gas releases and observations will begin after near-field operations have been completed. 

Transition to Near-field 

To reach the near-field observations position, the crew will perform a slowing, or retrograde, RCS burn to slightly 

lower Discovery's orbit. The effect of the burn, over the next orbit, will move Discovery to within 1 5 statute miles 

behind the SPAS. As Discovery approaches that point, another RCS burn will brake the orbiter, placing it directly 

behind SPAS on the same orbital path, less than 1.5 miles behind. 

Near-field Operations: OMS Plume Observations 

At the near-field position with both crew teams awake, Discovery again will be maneuvered to the "nose-north" 

start attitude which was used for far-field observations. The same out-of-plane OMS burn sequence will be repeated 

twice for near-field plume observations. The crew will continue to point the SPAS/IBSS imaging systems by remote 

control to set up and record each observation. 

Near-field Operations: CIV Observations 

Before leaving the near-field position, the crew will train SPAS/IBSS imaging systems on Discovery's payload bay 

to observe and document a sequence of gas releases from CIV canisters mounted in the bay. 

CRO Observations 

Following completion of near-field operations while the Blue Team sleeps, the Red Team will conduct a series of 

maneuvers to set up IBSS imaging and tracking of the CRO gas-release canisters ejected from Discovery's payload 

bay. 

A combination burn, both posigrade and out-of-plane, will be made to further separate Discovery from the SPAS 

and avoid obscuring it's view of the already deployed canister. The posigrade component of the RCS burn will 

provide for a slow separation from the SPAS, over 7.5 hours and five orbits, to a distance of 9 miles behind SPAS 

for the start of retrieval operations. The lateral component will move Discovery off of the direct track between 

SPAS and the CRO canister so it will not block the line of sight of the SPAS imaging experiments. 

During this five-orbit separation phase, the crew will remotely command the SPAS/IBSS to track and observe the 

first CRO canister as VAFB ground controllers remotely command the gas release. 

Following completion of the first CRO observation, the crew will perform an RCS burn to move Discovery back 

into alignment with the flight path of the SPAS, but continuing to separate. The crew will then eject a second 

canister and command the SPAS/IBSS to track and observe another ground-commanded gas release. 
Edited by Richard W. Orloff, 01/2001/Page 34 

SPAS/IBSS Retrieval 

After separating to more than 9 statute miles and with both crew shifts awake again, a retrograde burn will slightly 

lower Discovery's orbit to overtake the SPAS/IBSS. Several course adjustment burns may be conducted as 

Discovery nears it's target, in order to arrive directly in front of the SPAS on the same flight path. The crew then 

will manually maneuver Discovery to within range of the remote manipulator system for capture. 
Edited by Richard W. Orloff, 01/2001/Page 35 

STP-1 

Overview 

The STP-1 payload is sponsored by the USAF Space Systems Division. It is a complex secondary payload with 

experiments that are monitored and controlled by the Hitchhiker avionics. The Hitchhiker equipment for the payload 

consists of the support structure, the avionics and the experiment containers. This equipment is managed by NASA's 

Goddard Space Flight Center (GSFC). GSFC also provides a carrier, power and communications to the various 

experiments aboard. The experiments are contained in Get Away Special (GAS) canisters which are already 

certified for space. GSFC also completes the integration and testing for the experiments. 

STP-1 is composed of five separate experiments: the Ultraviolet Limb Imaging (UVLIM) experiment, the Advanced 

Liquid Feed Experiment (ALFE), the Spacecraft Kinetic Infrared Test (SKIRT), the Data System Experiment (DSE) 

and the Ascent Particle Monitor (APM). 

STP-1 is considered a secondary payload which means it may not interfere with the two primary payloads. Only a 

short portion of dedicated time is allocated to the payload, and at other times the experiments are conducted on a 

non-interference basis. 

After the Shuttle is in orbit and the payload bay doors are open, the crew will power on the payload. The payload 

then will be commanded from the ground by a control center located at GSFC. The control center will be operated 

24 hours a day to coincide with the 24-hour operations of the Shuttle crew. The control centers for the two primary 

payloads are located at NASA's Johnson Space Center. There will be constant coordination between the control 

centers during the flight to execute the mission and to replan should the need arise. 
Edited by Richard W. Orloff, 01/2001/Page 36 

Hitchhiker Project 

The Hitchhiker Project, operated by Goddard Space Flight Center (GSFC) in Greenbelt, MD, provides for 

accommodation of small payloads in the Shuttle payload bay. The Hitchhiker payload for STS-39 is called Space 

Test Payload-1 (STP-1) and consists of a Hitchhiker cross-bay carrier with five experiments. The carrier hardware 

includes the cross-bay structure, carrier avionics unit, mounting plates, canisters and a motorized canister door. 

STP-1 is sponsored by the U.S. Air Force Space Systems Division. 

Hitchhiker was designed and built at Goddard and will be operated from a control center at GSFC during the 

mission. The five experiments on STP-1 are: The Hitchhiker Project is operated by GSFC for the NASA Office of 

Space Flight. Payloads are provided thermally controlled mounting surfaces or sealed pressurizable canisters, 

orbiter power, command and data interfaces. 

The last Hitchhiker mission was in 1986, and the next after STS-39 will be in August 1992, followed by another in 

October of that year. 

GSFC Project Manager and Deputy Project Manager are Theodore Goldsmith and Steven Dunker. Chuck Chidekel, 

also of Goddard, is Integration Manager. The USAF STP-1 Program Manager is Capt. Hau Tran, and NASA 

Headquarters Program Manager is Edward James. 

Ultraviolet Limb Imaging (UVLIM) Experiment 

The objective of the Ultraviolet Limb Imaging experiment, sponsored by the Naval Research Laboratory in 

Washington D .C., is to measure the vertical and geographic distribution of the ultraviolet airglow in the wavelength 

region from 575 angstroms to 1900 angstroms. 

These measurements will be used to determine the daily and seasonal variation of the composition of the ionosphere 

and neutral atmosphere between the altitudes of 100 and 500 kilometers. The UVLIM experiment requires a 5 cubic 

foot canister with a motorized door and a mounting plate to house a 35 mm aspect camera. The camera will be 

aligned with the experiment aperture plate to provide simultaneous data which will be correlated with post flight 

data in determining point location. 

The experiment uses an extreme ultraviolet imaging spectrometer with a two dimensional detector to make images 

of the horizon from the airglow emissions which characterize the composition of the ionosphere. The far ultraviolet 

spectrometer measures emissions indicative of the temperature and composition of the neutral atmosphere. 

Advanced Liquid Feed Experiment (ALFE) 

The next generation of spacecraft and space tugs may be one step closer to autonomous operation and longer life 

due to the technology to be demonstrated in space by the Advanced Liquid Feed Experiment (ALFE). The space 

flight experiment is designed to evaluate the performance of key components of an advanced spacecraft propulsion 

system designed and built by the McDonnell Douglas Astronautics Company (MDAC) under contract to the Phillips 

Laboratory's Astronautics Directorate. 

ALFE will provide the first space flight demonstration of an electronic pressure regulator and a series of ultrasonic 

propellant level and flow sensing systems. These components will provide the capability to remotely and 

electronically control the pressurization schedule of spacecraft propellant tanks to accurately gauge the available onboard propellants and to reliably track the propellant usage throughout the mission. The experiment also will 

demonstrate the capability to integrate all storable propellant on-board the spacecraft by transferring attitude control 

system propellants into the main engine tanks and vice versa. 

The experiment is designed to use commercially available components to build two hardware modules weighing 

approximately 250 pounds each. The first module is an electronic package which will function as the remote test 
Edited by Richard W. Orloff, 01/2001/Page 37 

conductor aboard the Shuttle. It contains an on-board computer and associated electronics necessary for performing 

the experiment and recording the data. 

The module will provide the command and control for the experiment. It also will provide the communication link 

to transfer experiment telemetry and video signals to the ground based operator located at NASA's Goddard Space 

Flight Center (GSFC). 

The second module is the fluid system module. It contains two test tanks, an electronic pressure regulator, an 

ultrasonic liquid gauging system and the associated instrumentation, pumps and valves. The items of interest are the 

test tanks, the electronic pressure regulator and the ultrasonic liquid gauging system. 

The test tanks are made of Plexiglas and are scaled to represent a 1/4 scale of the actual system. Internally, each of 

these tanks is fitted with a liquid acquisition device for liquid positioning in the low gravity environment of space, 

and a screen device to preclude the ingestion of gas bubble into the lines. During the experiment, various quantities 

of fluid will be transferred between two tanks to simulate a hypothetical resupply scenario in space. 

The electronic pressure regulator, built by Parker Hannifin of Irvine, CA, will control the pressure of the test tank 

during flight. It has a unique capability to provide a smooth ramp-up of tank pressure when commanded in contrast 

with the typical burst disk system. The regulator also has the capability to control the downstream pressure to 

different pressure settings. 

This will enable better management of the limited quantity of the precious pressurized gas carried by the spacecraft. 

The ultrasonic liquid gauging system, supplied by Panametrics in Waltham, Mass., will provide an advanced 

approach to measure and track the liquid propellant usage. The system consists of a group of six ultrasonic point 

sensors and an ultrasonic flow cell. The point sensors, using the pulse-echo effect, measure the time delays for the 

ultrasonic pulses and their echoes to transit through the fluid to the gas-liquid interface. From these time 

measurements, the amount of the liquid contained within the tank can be calculated. Using a similar approach, the 

ultrasonic flow cell measures the time delay between two simultaneous ultrasonic pulses along a fluid line to 

calculate the propellant flow. 

When flown, the ALFE on-board computer will accept commands from the ground based operator located at 

NASA's GSFC and will configure the payload for the desired test sequence. An internal wide angle television 

camera will record the fluid settling characteristics under various acceleration loads. 

Experiment data will be both stored on-board in the electronic module and transmitted to the ground based operator. 

The results will be used in further updating the design of the advanced spacecraft feed system. 

Spacecraft Kinetic Infrared Test (SKIRT) 

The Spacecraft Kinetic Infrared Test (SKIRT), sponsored by Phillips Laboratory's Geophysics Directorate, consists 

of two separate and independent components. 

The Gaseous Luminosity of Optical Surface (GLOS) consists of infrared, visible and ultraviolet radiometers 

combined into one package weighing 50 pounds. The Circular Variable Filter (CVF) is a solid nitrogen cooled 

infrared spectrometer/radiometer mounted in a sealed canister with an aperture in the top plate. A motor driven 

cover is commanded open and closed on-orbit to cover the aperture as needed. A "glow plate" attached to the top 

plate provides a surface for impingement of the residual atmosphere to produce the glow which is then observed by 

the spectrometer. CVF weighs approximately 150 pounds with cryogen. 

The experiment objective is to obtain infrared spectral measurements of the Shuttle glow at resolutions and 

sensitivity that will allow identification of the chemical species associated with this phenomenon. Since the Shuttle 

glow effect is thought to be caused by the impact of atomic oxygen on the orbiter surfaces, it is only necessary that 

surfaces near the SKIRT field-of-view be exposed to ram (direction) at various times during the mission. 
Edited by Richard W. Orloff, 01/2001/Page 38 

Ascent Particle Monitor (APM) 

The Ascent Particle Monitor (APM), sponsored by USAF Space Systems Division's Operating Location detachment 

in Houston Texas, consists of a small box with a fixed door and a movable door mounted in a clamshell 

arrangement atop an aluminum housing. Each door contains six coupon holders into which selected passive witness 

samples are installed. The door is closed preflight to protect the coupons from the environment. It is opened after 

ground operations are completed and the payload bay doors are about to be closed in preparation for launch. A 

motor/gearbox assembly, two battery packs, launch detection circuitry and door opening circuitry are contained 

within the aluminum housing of the unit. The electric motor is used to open and close the door so that particles can 

be collected at specific times during Shuttle ascent. An internal timing circuit set prior to installation of the APM 

into the orbiter payload bay to control the door movement. The timer circuit is acoustically actuated by orbiter main 

engine start. 

The concept of the APM experiment evolved as a direct response to concerns by the spacecraft community about 

the fallout of particles in the Shuttle orbiter payload bay during the ascent portion of the missions. Particulate 

contaminants on Shuttle bay surfaces and on surfaces of payloads in the cargo bay may be released during launch 

and ascent by vibroacoustic, gravitational and aerodynamic forces. These particles can be deposited on surfaces 

from which they were released or on other surfaces depending on location acceleration and velocity vectors with 

respect to such surfaces. 

Many analytical models of particle redistribution have been made using assumed ascent forces during launch, but 

most models are based on uniform redistribution of particles. Insufficient experiment data exist on particle fallout 

and deposition during Shuttle ascent to verify current models. The understanding of particle redistribution on 

surfaces and releases of particles into the field of view of instruments incorporating critical sensors is important in 

view of the influence the particles may have on the properties of the surfaces on which they are deposited and on the 

optical degradation of the environment into which they may escape. Some of the effects of particles on surfaces and 

in the environment are physical obscuration of the surface, scattering of radiation which changes the transmitting or 

reflecting properties, increased diffuse reflection of the surface, and emission of radiation by the particles which 

may be detrimental to certain sensors. 

The first APM flew on the STS-28 mission and the flight coupons were analyzed in the Materials Science 

Laboratory of the Aerospace Corporation in Los Angeles, Calif. Various analytical techniques were used to evaluate 

the contaminants, including optical and scanning electron microscopy, infrared spectroscopy and energy dispersive 

X-ray spectroscopy. The coupons also were examined at NASA's Goddard Space Flight Center at Greenbelt, MD., 

using bidirectional reflectance distribution function scatter measurements. The APM also flew on STS-31 (Hubble 

Space Telescope), and is manifested on STS-37 (Gamma Ray Observatory payload). 

Data System Experiment (DSE) 

The Data System Experiment (DSE), sponsored by NASA's Goddard Space Flight Center in Greenbelt, MD., 

consists of a MILVAX computer, Erasable Optical Disk, and associated simulators and interfaces. The simulators 

would generate data to be used to exercise the computer and the optical disk. 

The objective of the DSE is to evaluate the performance of the computer and disk in a micro gravity environment. 

The optical disk system stem consists of an erasable optical disk drive unit and a removable cartridge media. Both 

are designed for reliable use under a variety of environmental conditions. 
Edited by Richard W. Orloff, 01/2001/Page 39 

STP-1 PARTICIPANTS 

Overall Project Management 

 Space Systems Division, Los Angeles AFB, Calif. 

Responsible for integration of flight hardware, production of flight and ground safety packages, and performance of 

all integrated systems testing: NASA's Goddard Space Flight Center, Greenbelt, MD. 

Organizations Responsible for the Experiments 

Naval Research Laboratory 

Washington, D.C. 

Ultraviolet Limb Imaging Experiment (UVLIM) 

Phillips Laboratory's Astronautics Directorate 

Edwards Air Force Base, Calif. 

Advanced Liquid Feed Experiment (ALFE) 

Hanscom Air Force Base, Mass. 

Spacecraft Kinetic Infrared Test (SKIRT) 

USAF Space Systems Division 

Detachment OL-AW, Houston, TX. 

Ascent Particle Monitor (APM) 

NASA's Goddard Space Flight Center 

Greenbelt, MD 

Data System Experiment (DSE) 
Edited by Richard W. Orloff, 01/2001/Page 40 

MULTI-PURPOSE EXPERIMENT CANISTER (MPEC) 

The Multi-Purpose Experiment Canister (MPEC) carries a classified experiment sponsored by the USAF Space 

Systems Division (SSD). The canister, a modified Get Away Special (GAS) container, is mounted on a beam 

attached to the starboard sidewall of orbiter cargo bay 6. The modified canister includes a 9-inch extension 

containing an ejection kit, electronics and a full diameter motorized door assembly. 

The experiment is scheduled to be deployed from the cargo bay on the last day of the mission. However, 

deployment can occur earlier on a contingency basis. 

The crew provides power to the MPEC via the standard switch panel located in the crew compartment. The crew 

will send a command to open the canister door and, after verifying that the door is open, will arm the ejection 

mechanism and send the deployment command. The experiment is ejected with a relative velocity of about 2.7 ft/sec 

by a spring mechanism. After ejection, the canister door will be closed and power removed from the canister. 
Edited by Richard W. Orloff, 01/2001/Page 41 

CLOUDS 1A 

The overall objective of the CLOUDS-1A program is to quantify the variation in apparent cloud cover as a function 

of the angle at which clouds of various types are viewed. 

The CLOUDS-1A experiment is stowed in a middeck locker and consists of a Nikon F3/T camera assembly and 

film. On-orbit, a crew member will take a series of high resolution photographs of individual cloud scenes, 

preferably high "wispy" cirrus clouds, over a wide range of viewing angles. 
Edited by Richard W. Orloff, 01/2001/Page 42 

RADIATION MONITORING EQUIPMENT-III 

Radiation Monitoring Equipment-III (RME-III) measures the rate and dosage of ionizing radiation to the crew at 

different locations throughout the orbiter cabin. The hand-held instrument measures gamma ray, electron, neutron 

and proton radiation and calculates the amount of exposure. The information is stored in memory modules for postflight analysis. 

RME-III will be stored in a middeck locker during flight except for when it is turned on and when memory modules 

are replaced every 2 days. It will be activated as soon as possible after achieving orbit and will operate throughout 

the flight. To activate the instrument, a crew member will enter the correct mission elapsed time. 

The instrument contains a liquid crystal display for real-time data readings and a keyboard for function control. It 

has four zinc-air batteries and five AA batteries in each replaceable memory module and two zinc-air batteries in the 

main module. 

RME-III, which has flown on STS-31 and STS-41, is the current configuration, replacing the earlier RME-I and 

RME-II units. 

The Department of Defense, in cooperation with NASA, sponsors the data gathering instrument. 
Edited by Richard W. Orloff, 01/2001/Page 43 

STS-39 CREWMEMBERS 

S90-52756 – The crewmembers for the STS-39 mission, in their launch and entry suits (LESs), are, left to right, 

mission specialists Charles L. Veach, Donald R. McMonagle, and Gregory J. Harbaugh; mission commander 

Michael L. Coats; pilot L. Blaine Hammond; and mission specialists Richard J. Hieb and Guion S. Bluford. The 

double exposure utilized an actual Earth-limb photograph and man-made ground "fog." 

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 

Michael L. Coats, 45, Capt., USN, will serve as commander. Selected as an astronaut in 1978, he considers 

Riverside, CA, his hometown. STS-39 will be Coats' third space flight. 

Coats was pilot on STS-41D, launched Aug. 30, 1984, the maiden flight of Discovery. Coats next commanded 

mission STS-29 aboard Discovery, launched March 13, 1989, to deploy a Tracking and Data Relay Satellite. 

Coats graduated from Ramona High School, Riverside, in 1964, received a bachelor of science from the U.S. Naval 

Academy in 1968; a master of science in the administration of science and technology from George Washington 

University in 1977; and a master of science in aeronautical engineering from the U.S. Naval Postgraduate School in 

1979. 

He was designated a naval aviator upon graduation from Annapolis in 1969 and was assigned to Attack Squadron 

192 aboard the USS Kitty Hawk for 2 years, flying 315 combat missions in Southeast Asia. He then served as a 

flight instructor with the A-7E Readiness Training Squadron at the Naval Air Station in Lemoore, CA, for a year 

before attending the Naval Test Pilot School. Afterward, he was project officer and test pilot for the A-7 and A-4 

aircraft for 2 years before becoming a flight instructor at the Test Pilot School in 1976. 

Coats has logged more than 5,000 hours of flying time in more than 28 different aircraft and 264 hours in space. 

L. Blaine Hammond Jr., 38, Major, USAF, will serve as Pilot. Selected as an astronaut in 1984, Hammond was 

born in Savannah, Ga., and will make his first space flight. 

Hammond graduated from Kirkwood High School, Kirkwood, Mo., in 1969; received a bachelor of science in 

engineering science and mechanics from the U.S. Air Force Academy in 1973; and received a master of science in 

engineering science and mechanics from the Georgia Institute of Technology in 1974. 

Hammond earned his wings at Reese Air Force Base, Texas, in 1975 and was assigned to the 496th Tactical Fighter 

Squadron, Hahn Air Base, Germany, flying the F-4E. In 1979, he spent a year at Williams Air Force Base, Ariz., 

flying the F-5B/E/F and training foreign students. Hammond then attended the Empire Test Pilot School at A&AEE 

Boscombe Down, England. He returned to Edwards Air Force Base in 1982 and was assigned as an instructor at the 

Air Force Test Pilot School, a position he held at the time of his selection by NASA. 

Hammond has logged more than 3,100 hours flying 15 different American and 10 different English aircraft. 

Gregory J. Harbaugh, 34, will serve as Mission Specialist 1 (MS1). Harbaugh, selected as an astronaut in 1987, 

considers Willoughby, Ohio, to be his hometown and will make his first space flight. 

Harbaugh graduated from Willoughby South High School in 1974; received a bachelor of science in aeronautical 

engineering from Purdue University in 1978; and received a master of science in physical sciences from the 

University of Houston-Clear Lake in 1986. 

Harbaugh came to NASA upon his graduation from Purdue and served in engineering and management positions at 

JSC until his selection as an astronaut. Harbaugh supported Shuttle operations in Mission Control for most flights 

from STS-1 through STS-51L, working as a Data Processing Systems (DPS) flight controller and later as a Shuttle 

Planning and Analysis Manager, the senior flight controller interface with the engineering community. He also has a 

commercial pilot's license and has logged more than 1,000 hours flying time. 
Edited by Richard W. Orloff, 01/2001/Page 45 

BIOGRAPHICAL DATA 

Donald R. McMonagle, 38, Lt. Col., USAF, will serve as Mission Specialist 2 (MS2). Selected as an astronaut in 

1987, he was born in Flint, Mich., and will make his first space flight. 

McMonagle graduated from Hamady High School, Flint, Mich., in 1970; received a bachelor of science in 

astronautical engineering from the Air Force Academy in 1974; and a master of science in mechanical engineering 

from California State University-Fresno in 1985. 

He completed pilot training on the F-4 in 1975 and was assigned a year-long tour of duty at Kunsan Air Base, South 

Korea. He returned to Holloman AFB, N.M., in 1977 for training on the F-15, and, in 1979, was assigned as an F-15 

instructor at Luke AFB, Ariz. In 1981, he attended the Air Force Test Pilot School and graduated as the outstanding 

pilot of his class. From 1982-1985, he was the operations officer and test pilot for the Advanced Fighter Technology 

Integration (AFTI) F-16. He then attended the Air Command and Staff College at Maxwell AFB, AL., for 1 year 

before being assigned as operations officer for the 6513th Test Squadron at Edwards AFB, CA, where he was 

stationed at the time of his selection by NASA. 

McMonagle has logged more than 3,400 hours flying time in a variety of aircraft. 

Guion S. Bluford, 48, Col., USAF, will serve as Mission Specialist 3 (MS3). Selected as an astronaut in 1979, 

Bluford was born in Philadelphia, Pa., and will make his third space flight. 

Bluford graduated from Overbrook High School, Philadelphia, in 1960; received a bachelor of science in aerospace 

engineering from Pennsylvania State University in 1964; received a master of science in the same subject from the 

Air Force Institute of Technology in 1974; received a doctorate in aerospace engineering with a minor in laser 

physics from the Air Force Institute of Technology in 1978; and received a master of business administration from 

the University of Houston-Clear Lake in 1987. 

He served as a mission specialist on STS-8, launched Aug. 30, 1983, the third flight of Challenger and first mission 

with a night launch and landing. During the flight, the crew deployed the Indian National Satellite (INSAT-1B) and 

operated the remote manipulator system with a test article. His next flight was as a mission specialist aboard 

Challenger on STS 61-A, launched Oct. 30, 1985, with the German D-1 Spacelab. 

Bluford has logged more than 314 hours in space. 

C. Lacy Veach, 46, will serve as Mission Specialist 4 (MS4). Selected as an astronaut in 1984, Veach considers 

Honolulu his hometown and will make his first space flight. 

Veach graduated from Punahou School in 1962 and received a bachelor of science in engineering management from 

the Air Force Academy in 1966. 

Veach was commissioned in the Air Force upon graduation from the Academy and received his pilot wings in 1967. 

For 14 years, he served as a fighter pilot with a variety of assignments in the United States and overseas, including a 

275-mission combat tour in Southeast Asia and 2 years with the Air Force Demonstration Squadron, the 

Thunderbirds. Veach left active duty in 1981, but continues to fly with the Texas Air National Guard. 

He began work at NASA in 1982 as an engineer and research pilot, serving as an instructor pilot in the Shuttle 

Training Aircraft until his selection as an astronaut. 

He has logged more than 4,500 flying hours. 
Edited by Richard W. Orloff, 01/2001/Page 46 

BIOGRAPHICAL DATA 

Richard J. Hieb, 35, will serve as Mission Specialist 5 (MS5). Selected as an astronaut in 1986, he considers 

Jamestown, N. D., his hometown and will make his first space flight. 

Hieb graduated from Jamestown High School in 1973; received a bachelor of arts in math and physics from 

Northwest Nazarene College in 1977; and received a master of science in aerospace engineering from the University 

of Colorado in 1979. 

Hieb began work for NASA after graduating from the University of Colorado, serving in the crew procedures 

development and crew activity planning areas. He worked in Mission Control for ascent during STS-1 and 

specialized in rendezvous and proximity operations for numerous subsequent flights. 
Edited by Richard W. Orloff, 01/2001/Page 47 

NASA SPACE SHUTTLE MANAGEMENT 

NASA HEADQUARTERS, OFFICE OF SPACE FLIGHT , WASHINGTON, DC 

Dr. William B. Lenoir Associate Administrator 

Robert L. Crippen Director, Space Shuttle 

Leonard S. Nicholson Deputy Director, Space Shuttle (Program) 

Brewster Shaw Deputy Director, Space Shuttle (Operations) 

KENNEDY SPACE CENTER, FL 

Forrest S. McCartney Director 

Jay Honeycutt Director, Shuttle Management & Operations 

Robert B. Sieck Launch Director 

John T. Conway Director, Payload Management & Operations 

Joanne H. Morgan Director, Payload Project Management 

Roelf Schuiling STS-39 Payload Manager 

MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, AL 

Thomas J. Lee Director 

Dr. J. Wayne Littles Deputy Director 

G. Porter Bridwell Manager, Shuttle Projects Office 

Dr. George F. McDonough Director, Science and Engineering 

Alexander A. McCool Director, Safety and Mission Assurance 

Victor Keith Henson Manager, Solid Rocket Motor Project 

Cary H. Rutland Manager, Solid Rocket Booster Project 

Jerry W. Smelser Manager, Space Shuttle Main Engine Project 

Gerald C. Ladner Manager, External Tank Project 

JOHNSON SPACE CENTER , HOUSTON, TX 

Aaron Cohen Director 

Eugene F. Kranz Director, Mission Operations 

Franklin Brizzolara Payload Integration Manger 

STENNIS SPACE CENTER, BAY ST. LOUIS, MS 

John S. Estess Director 

Gerald W. Smith Deputy Director 

J. Harry Guin Director, Propulsion Test Operations 

AMES-DRYDEN FLIGHT RESEARCH FACILITY, EDWARDS, CA 

Kenneth J. Szalai Director 

T. G. Ayers Deputy Director 

James R. Phelps Chief, Shuttle Support Office 
Edited by Richard W. Orloff, 01/2001/Page 48 

DEPARTMENT OF DEFENSE PAYLOAD MANAGEMENT 

Key Management Participants 

Martin C. Faga Assistant Secretary of the Air Force for Space 

Mission Directors

Lt. Gen. Donald L. Cromer Commander, Space Systems Division 

Col. John E. Armstrong Program Manager, Space Test and Transportation System Office 

CARGO Operations Officers

Maj. Robert Crombie SSD/CLPC 

Capt. Linda Wolters SSD/CLPC 

IBSS Program Directors

Mike Harrison SDIO/TNS 

Howard Stears SKW Corp. 

AFP-675 Program Directors

Capt. Lindley Johnson SSD/CLPC 

Capt. Lloyd Johnson SSD/CLPC 

STP-1 Program Directors

Ted Goldsmith GSFC 

Capt. Hau Tran SSD/CLPC 

Key Operations Participants 

IBSS Operations Directors

Capt. Al Locker GL 

1Lt. Ross Balestreri SSD/CLPC 

IBSS Test Conductors

Jim Covington Aerospace 

Scott Bartell SKW Corp. 

IBSS Replanners

Howard R. Pedolsky Orbital Systems, Ltd. 

Larry Sharp Aerospace 

AFP-675 Operations Directors

Capt. Mike Spencer SSD/CLPC 

Capt. Pete Clarke SSD/CLPC 

STP-1 Operations Directors

Debbie Knapp GSFC 

Vic Gehr GSFC 
Edited by Richard W. Orloff, 01/2001/Page 49 

SHUTTLE FLIGHTS AS OF MARCH 1991 

39 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 14 SINCE RETURN TO FLIGHT 

STS-41 

10/06/90 - 10/10/90 

STS-35 

12/02/90 - 12/10/90 

STS-51L 

01/28/86 

STS-31 

04/24/90 - 04/29/90 

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-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-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-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-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-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-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-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-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 

 

OV-102 

Columbia 

(10 flights)

OV-099 

Challenger 

(10 flights)

OV-103 

Discovery 

(11 flights)

OV-104 

Atlantis 

(8 flights)