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

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-32 

PRESS KIT 

DECEMBER 1989 

SYNCOM IV-F5 DEPLOYMENT 

LONG DURATION EXPOSURE FACILITY (LDEF) RETRIEVAL 
Edited by Richard W. Orloff, 01/2001/Page 2 

STS-32 INSIGNIA 

S89-44076 -- The STS-32 insignia, designed by the five crewmembers for the scheduled December 1989 

space mission, depicts the space shuttle orbiter rendezvousing with the Long Duration Exposure Facility 

(LDEF) satellite from above. The Syncom satellite is successfully deployed and on its way to 

geosynchronous orbit. Five stars have been arranged so that three are one side of the orbiter and two on 

the other to form the number 32. The seven major rays of the sun are in remembrance of the crewmembers 

for STS 51-L. In preparation for the first Extended Duration Orbiter (EDO) missions, STS-32 will conduct 

a number of medical and mid-deck scientific experiments. The caduceus on the left represents the medical 

experiments, and the crystalline structure on the right represents the materials science. The crew is 

comprised of astronauts Daniel C. Brandenstein, James D. Wetherbee, Bonnie J. Dunbar, Marsha S. Ivins, 

and G. David Low. 

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 

NASA Headquarters, Washington, D.C. 

Mark Hess/Ed Campion 202/453-8536 

Office of Space Flight 

Mary Sandy 202/453-2754 

Office of Aeronautics and Space Technology 

Barbara Selby 202/453-2927 

Office of Commercial Programs 

Langley Research Center, Hampton, Va. 

Jean Drummond Clough 804/864-6122 

Kennedy Space Center, Fla. 

Lisa Malone 407/867-2468 

Johnson Space Center, Houston, Texas 

Kyle Herring 713/483-5111 

Marshall Space Flight Center, Huntsville, Ala. 

Jerry Berg 205/544-0034 

Stennis Space Center, Bay St. Louis, Miss. 

Mack Herring 601/688-3341 

Ames-Dryden Research Facility, Edwards, Calif. 

Nancy Lovato 805/258-8381 

Goddard Spaceflight Center, Greenbelt, Md. 

Jim Elliott 301/286-6256 
Edited by Richard W. Orloff, 01/2001/Page 4 

CONTENTS 

Press Release 5 

Quick Look 7 

General Information 8 

Launch Preparations, Countdown and Liftoff 9 

Space Shuttle Abort Modes 10 

Major Countdown Milestones 11 

Trajectory Sequence of Events 13 

Vehicle and Payload Weights 14 

Summary of Major Activities 15 

STS-32 Payload Diagram 16 

Landing and Post-Landing Operations 17 

STS-32 Payloads 18 

 Syncom IV-F5 18 

 LDEF 20 

 AFE 25 

 CNCR 26 

 PCG 27 

 FEA 29 

 MLE 32 

 IMAX 33 

 AMOS 35 

 L3 36 

Space Flight Tracking and Data Network 38 

Crew Biographies 39 

NASA Program Management 42 
Edited by Richard W. Orloff, 01/2001/Page 5 

RELEASE: 89-180 December 1989 

SYNCOM IV DEPLOY, LDEF RETRIEVAL 

HIGHLIGHT 10-DAY COLUMBIA FLIGHT 

Highlights of Space Shuttle mission STS-32, the 33rd flight of the National Space Transportation System, 

will be deployment of a Navy synchronous communications satellite (Syncom IV) and retrieval of the 

Long Duration Exposure Facility (LDEF) launched aboard Challenger on mission STS-41C in April 1984. 

Syncom IV-F5 is the last in a series of five Navy satellites built by Hughes Communications Services Inc. 

It is designed to provide worldwide, high-priority communications between aircraft, ships, submarines and 

land- based stations for the U.S. military services and the Presidential Command Network. Syncom 

measures 15 feet long and 13 feet in diameter. 

After Syncom deployment using the "Frisbee" method, the crew will do a Shuttle separation burn 

maneuver away from the satellite. A solid rocket perigee kick motor along with several liquid apogee 

motor firings will boost the satellite to geosynchronous orbit. 

The LDEF, a 12-sided, open-grid structure made of aluminum rings and longerons, is 30 feet long, 14 feet 

in diameter and weighs 8,000 pounds. Retrieval of the LDEF will be accomplished by the orbiter's remote 

manipulator system (RMS) arm. Once the rendezvous portion of the mission is completed, Mission 

Specialist Bonnie Dunbar will grapple the LDEF with the end effector of the RMS and maneuver LDEF 

into the five support trunnion latches in the payload bay of Columbia. 

The LDEF experiments range in research interest from materials to medicine to astrophysics. All required 

free-flying exposure in space without extensive electrical power, data handling or attitude control systems. 

Many of the experiments are relatively simple with some being completely passive while in orbit. The 

structure was designed for reloading and reuse once returned to Earth. 

Orbital data on the LDEF is provided to NASA by the North American Aerospace Defense Command 

(NORAD). Intensive C-band radar tracking will begin approximately 72 hours before launch to provide the 

accurate data required for orbiter and LDEF rendezvous. 

Joining Syncom IV and later LDEF in the payload bay of Columbia will be the Interim Operational 

Contamination Monitor (IOCM). This is an automatic operation system for the measurement of 

contamination that may be present in the payload bay for the entire mission duration. It is designed to 

provide continuous measurement of collected particulate and molecular mass at preprogrammed collection 

surface temperatures. 

Columbia also will carry several secondary payloads involving material crystal growth, microgravity 

protein crystal growth, lightning research, in- flight cardiovascular changes and effects of microgravity and 

light on the cellular processes that determine circadian rhythms and metabolic rates. 

Commander of the mission is Daniel C. Brandenstein, Captain, USN. James D. Wetherbee, Lieutenant 

Commander, USN, is pilot. Brandenstein was pilot on mission STS-8 in August 1983 and commander of 

STS-51G in June 1985. Wetherbee will be making his first Shuttle flight. 

Mission specialists are Bonnie J. Dunbar, Ph.D.; Marsha S. Ivins and G. David Low. Dunbar previously 

flew as a mission specialist on STS-61A in October 1985. Ivins and Low will be making their first Shuttle 

flights. 

Liftoff of the ninth flight of Columbia is scheduled for 6:46 p.m. EST on December 18 from Kennedy 

Space Center, Fla., launch pad 39-A, into a 190- nautical mile, 28.5 degree orbit. 
Edited by Richard W. Orloff, 01/2001/Page 6 

A final decision on launch time will be made approximately 12 hours prior to launch. The decision will be 

based on the latest tracking data for the LDEF and allow for appropriate adjustment of Orbiter inflight 

computers. 

Nominal mission duration is expected to be 9 days, 21 hours 35 minutes. Deorbit is planned on orbit 158, 

with landing scheduled for 4:21 p.m. EST, depending on actual launch time, on December 28 at Edwards 

Air Force Base, Calif. 

The launch window for this mission is dictated by vehicle performance, real-time LDEF rendezvous data 

and the reentry track of the external tank. 

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

STS-32 QUICK LOOK 

Launch Date: Dec. 18, 1989 

Launch Site: Kennedy Space Center, FL, Pad 39A. 

Launch Window: 6:46 p.m. - 7:48 p.m. EST 

Orbiter: Columbia (OV-102) 

Orbit: 190 n.m. altitude 

Inclination: 28.5 degrees 

Landing Date: Dec. 28, 1989 

Landing Time: 4:21 p.m. EST 

Primary Landing Site: Edwards AFB, CA 

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

 Transoceanic Abort Landing - Ben Guerir, Morocco 

 Abort Once Around - Edwards AFB, CA 

Crew: Daniel C. Brandenstein, Commander 

 James D. Wetherbee, Pilot 

 Bonnie J. Dunbar, Mission Specialist 

 Marsha S. Ivins, Mission Specialist 

 G. David Low, Mission Specialist 

Cargo Bay Payloads: Syncom IV-F5 (primary payload) 

 RMS for LDEF Retrieval 

Middeck Payloads: Characterization of Neurospora Circadian Rhythms (CNCR) 

 Protein Crystal Growth (PCG) 

 Fluid Experiment Apparatus (FEA) 

 American Flight Echocardiograph (AFE) 

 Latitude/Longitude Locator (L3) 

 IMAX 
Edited by Richard W. Orloff, 01/2001/Page 8 

GENERAL INFORMATION 

NASA Select Television Transmission 

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

longitude. The schedule for orbiter transmissions and change-of-shift briefings from Johnson Space Center, 

Houston, will be available during the mission at Kennedy Space Center, Fla.; Marshall Space Flight 

Center, Huntsville, Ala.; Johnson Space Center; and NASA Headquarters, Washington, D.C. The schedule 

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

Special Note to Broadcasters 

In the five workdays before launch, short sound bites of STS-32 crew interviews will be available by 

calling 202/755-1788 between 8 a.m. and noon. 

Status Reports 

 Status reports on countdown, mission progress and landing operations will be produced by the appropriate 

NASA news center. 

Briefings

A press-briefing schedule will be issued before 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 9 

LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF 

Processing of Columbia for the STS-32 mission began on Aug. 21, when the spacecraft was towed to 

Orbiter Processing Facility (OPF) Bay 2 after arrival from Dryden Flight Research Facility. Post-flight 

deconfiguration of STS-28, Challenger's previous mission, and inspections were conducted in the hangar. 

Approximately 26 modifications have been implemented since the STS-28 mission. One of the more 

significant added a fifth tank set for the orbiter's power reactant storage and distribution system. This will 

provide additional liquid hydrogen and liquid oxygen, which combine in the fuel cells to produce 

electricity for the Shuttle and water as a by-product. With the addition of the fifth tank, the mission 

duration has been planned for 10 days. 

Improved controllers for the water spray boilers and auxiliary power units were also installed. Other 

improvements were made to the orbiter's structure and thermal protection system, mechanical systems, 

propulsion system and avionics system. 

Columbia was transferred from the OPF to the Vehicle Assembly Building (VAB) on Nov. 16 for mating 

to the external tank and SRBs. The assembled Space Shuttle was rolled out of the VAB aboard its mobile 

launcher platform (MLP) for the 3.4-mile trip to Launch Pad 39-A on Nov. 28. STS-32 will mark the first 

use of MLP-3 in the Shuttle program and the first use of Pad A since mission 61-C in January 1986. 

The countdown for Columbia's ninth launch will pick up at T-minus 43- hours. The launch will be 

conducted by a NASA-and-industry team from Firing Room 1 in the Launch Control Center. 
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SPACE SHUTTLE ABORT MODES 

Space Shuttle launch abort philosophy aims for safe and intact recovery of the flight crew, the 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 Edwards Air Force Base, Calif.; White Sands Space Harbor (Northrup Strip), 

N.M.; or the Shuttle Landing Facility (SLF) at Kennedy Space Center, Fla. 

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

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

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

to reach Ben Guerir, would result in a pitch around and thrust back toward KSC until within gliding 

distance of the SLF. 

STS-32 contingency landing sites are Edwards AFB, White Sands, Kennedy Space Center, Ben Guerir, 

Moron and Banjul. 
Edited by Richard W. Orloff, 01/2001/Page 11 

MAJOR COUNTDOWN MILESTONES 

T-43 Hours (43:00:00) Verify that the Space Shuttle is powered up. 

T-34:00:00 Continue orbiter and ground support equipment close-outs for launch. 

T-30:00:00 Activate orbiter's navigation aids. 

T-27:00:00 (holding) Enter the first built-in hold for eight hours. 

T-27:00:00 (counting) Begin preparations for loading fuel cell storage tanks with liquid oxygen and 

 liquid hydrogen reactants. 

T-25:00:00 Load the orbiter's fuel cell tanks with liquid oxygen. 

T-22:30:00 Load the orbiter's fuel cell tanks with liquid hydrogen. 

T-22:00:00 Perform interface check between Houston Mission Control and the Merritt 

 Island Launch Area (MILA) tracking station. 

T-20:00:00 Activate inertial measurement units (IMUs). 

T-19:00:00 (holding) Enter the 8-hour built-in hold. Activate orbiter communications system. 

T-19:00:00 (counting) Resume countdown. Continue preparations to load the external tank, orbiter 

 close-outs and preparations to move the Rotating Service Structure. 

T-11:00:00 (holding) Start built-in hold, duration dependent on launch time. Perform orbiter ascent 

 switch list in the orbiter flight and middecks. 

T-11:00:00 (counting) Retract Rotating Service Structure from vehicle to launch position. (Could 

 occur several hours earlier if weather is favorable.) 

T-9:00:00 Activate orbiter's fuel cells. 

T-8:00:00 Configure Mission Control communications for launch. Start clearing blast 

 danger area. 

T-6:30:00 Perform Eastern Test Range open loop command test. 

T-6:00:00 (holding) Enter one-hour built-in hold. Receive mission management "go" for tanking. 

T-6:00:00 (counting) Start external tank chilldown and propellant loading. 

T-5:00:00 Start IMU pre-flight calibration. 

T-4:00:00 Perform MILA antenna alignment. 

T-3:00:00 (holding) Begin two-hour built-in hold. Complete external tank loading and ensure tank 

 is in a stable replenish mode. Ice team goes to pad for inspections. Closeout 

 crew goes to white room to begin preparing orbiter's cabin for flight crew's 

 entry. Wake flight crew (actual time launch minus 4:55:00). 
Edited by Richard W. Orloff, 01/2001/Page 12 

MAJOR COUNTDOWN MILESTONES 

T-3:00:00 (counting) Resume countdown. 

T-2:55:00 Flight crew departs O&C Building for Launch Pad 39-A (Launch minus 

 3:15:00). 

T-2:30:00 Crew enters orbiter vehicle (Launch minus 3:15:00). 

T-00:60:00 Start pre-flight alignment of IMUs. 

T-00:20:00 (holding) 10-minute built-in-hold begins. 

T-00:20:00 (counting) Configure orbiter computers for launch. 

T-00:10:00 White room closeout crew cleared through the launch danger area roadblocks. 

T-00:09:00 (holding) Begin 10-minute built-in-hold. Perform status check and receive Launch 

 Director and Mission Management Team "go." 

T-00:09:00 (counting) Start ground launch sequencer. 

T-00:07:30 Retract orbiter access arm. 

T-00:05:00 Pilot starts auxiliary power units. Arm range safety, SRB ignition systems. 

T-00:03:30 Place orbiter on internal power. 

T-00:02:55 Pressurize liquid oxygen tank for flight and retract gaseous oxygen vent hood. 

T-00:01:57 Pressurize liquid hydrogen tank. 

T-00:00:31 "Go" from ground computer for orbiter computers to start the automatic launch 

 sequence. 

T-00:00:28 Start solid rocket booster hydraulic power units. 

T-00:00:21 Start SRB gimbal profile test. 

T-00:00:06.6 Main engine start. 

T-00:00:03 Main engines at 90 percent thrust. 

T-00:00:00 SRB ignition, aft skirt holddown post release and liftoff. Flight begins and 

 control switches to Houston. 
Edited by Richard W. Orloff, 01/2001/Page 13 

STS-32 TRAJECTORY SEQUENCE OF EVENTS 

Event 

MET 

(d/h:m:s) 

Relative 

Velocity 

(fps) Mach 

Altitude 

(ft) 

 

Launch 00/00:00:00 

Begin Roll Maneuver 00/00:00:09 159 .14 604 

End Roll Maneuver 00/00:00:15 311 .28 2,165 

SSME Throttle Down to 65 % 00/00:00:28 663 .61 8,313 

Max. Dyn. Pressure (Max Q) 00/00:00:52 1,171 1.10 26,751 

SSME Throttle Up to 104 % 00/00:00:59 1,323 1.27 33,602 

SRB Staging 00/00:02:06 4,138 3.75 157,422 

Negative Return 00/00:04:05 7,100 7.61 339,500 

Main Engine Cutoff (MECO) 00/00:08:34 24,543 22.88 362,696 

Zero Thrust 00/00:08:40 24,557 22.59 364,991 

ET Separation 00/00:08:52 

OMS 2 Burn 00/00:40:27 

Syncom IV-F5 Deploy (or 17) 01/00:44:00 

Deorbit Burn (orbit 158) 09/20:38:17 

Landing (orbit 159) 09/21:34:44 

Apogee, Perigee at MECO: 186 x 34 

Apogee, Perigee at post-OMS 2: 190 x 160* 

Apogee, Perigee at post-deploy: 190 x 166* 

*These numbers are highly variable depending on real-time LDEF altitude at time of launch. 
Edited by Richard W. Orloff, 01/2001/Page 14 

VEHICLE AND PAYLOAD WEIGHTS 

Pounds

Orbiter (Columbia) Empty 185,363 

Remote Manipulator System (payload bay) 858 

Syncom IV-5 (payload bay) 5,286 

Syncom ASE 1801 

Long Duration Exposure Facility (LDEF) 21,393 

Interim Operational Contamination Monitor (IOCM)) 137 

American Flight Echocardiograph (AFE) 111 

Characterization of Neurospora Circadian Rhythms (CNCR) 43 

Detailed Secondary Objectives (DSO) 163 

Detailed Technical Objectives (DTO) 36 

Fluids Experiment Apparatus (FEA) 148 

IMAX Camera 274 

Latitude-Longitude Locator (L3) 56 

Mesoscale Lightning Experiment (MLE) 15 

Protein Crystal Growth Experiment (PCG) 154 

Orbiter and Cargo at SRB Ignition 256,670 

Total Vehicle at SRB Ignition 4,523,534 

Orbiter Landing Weight 229,526 
Edited by Richard W. Orloff, 01/2001/Page 15 

SUMMARY OF MAJOR ACTIVITIES 

Flight Day 1 Flight Day 5 

Ascent AFE 

Post-insertion checkout DSO 

Unstow cabin FEA 

RMS checkout L3 setup 

AFE IMAX 

CNCR 

DSO Flight Day 6 

FEA unstow AFE 

PCG activation DSO/DTO 

 FEA 

Flight Day 2 IMAX 

Syncom IV deploy 

AFE Flight Day 7 

DSO/DTO AFE 

FEA DSO/DTO 

IMAX FEA 

 IMAX 

Flight Day 3 

Syncom backup deploy/injection Flight Day 8 

AFE AFE 

DSO/DTO DSO/DTO 

FEA FEA stow 

IMAX IMAX 

 

Flight Day 4 Flight Day 9 

LDEF rendezvous AFE stow 

LDEF grapple DSO/DTO 

LDEF photo survey FCS checkout 

LDEF berthing IMAX stow 

LDEF deactivation L3 stow 

AFE PCG deactivation 

DTO Cabin stow 

FEA Landing preparations 

IMAX 

Flight Day 10 

Deorbit preparations and 

burn 

 Landing at Edwards AFB 
Edited by Richard W. Orloff, 01/2001/Page 16 
Edited by Richard W. Orloff, 01/2001/Page 17 

LANDING AND POST-LANDING OPERATIONS 

The Kennedy Space Center is responsible for ground operations of the orbiter once it has rolled to a stop 

on the runway at Edwards Air Force Base. Those operations include preparing Columbia for the return trip 

to Kennedy. 

After landing, the flight crew aboard Columbia begins "safing" vehicle systems. Immediately after wheels 

stop, specially garbed technicians will first determine that any residual hazardous vapors are below 

significant levels in order for other safing operations to proceed. 

A mobile white room is moved into place around the crew hatch once it is verified that there are no 

concentrations of toxic gases around the forward part of the vehicle. The flight crew is expected to leave 

Columbia about 45 to 50 minutes after landing. As the crew exits, technicians will enter the orbiter to 

complete the vehicle safing activity. 

Pending completion of planned work and favorable weather conditions, the 747 Shuttle Carrier Aircraft 

would depart California about 6 days after landing for the cross-country ferry flight back to Florida. 

Several refueling stops will be necessary to complete the journey because of the weight of the LDEF 

payload. 

Once back at Kennedy, Columbia will be pulled inside the hangar like processing facility where the 

retrieved Long Duration Exposure Facility (LDEF) will be removed from the payload bay. Orbiter 

post-flight inspections, in- flight anomaly trouble-shooting and routine systems reverification will 

commence to prepare Columbia for its next mission. 
Edited by Richard W. Orloff, 01/2001/Page 18 

STS-32 PAYLOADS 

Syncom IV-F5 

Syncom IV-F5, also known as LEASAT 5, will be the fourth operational satellite in the LEASAT system. 

It will be leased by the Department of Defense to replace the older FleetSatCom spacecraft for worldwide 

UHF communications between ships, planes and fixed facilities. A Hughes HS381 design, the LEASAT 

spacecraft is designed expressly for launch from the Space Shuttle and uses the unique "Frisbee," or 

rollout, method of deployment. 

The first two spacecraft were deployed during the 1984 41-D and 51-A Shuttle missions. LEASAT 3 was 

deployed successfully in 1985 during mission 51-D but failed to activate. The satellite drifted in low-Earth 

orbit until a salvage and rescue mission was performed by the crew of mission 51-I in September 1985. 

Following a series of modifications by the Shuttle crew, LEASAT 3 was successfully deployed into its 

operational orbit. Also as part of mission 51-I, LEASAT 4 was successfully deployed from the orbiter. 

However, it did not go into operational service due to a spacecraft failure shortly after arrival at 

geosynchronous orbit. 

Interface between the spacecraft and the payload bay is accomplished with a cradle structure. The cradle 

holds the spacecraft with its forward end toward the nose of the orbiter. Mounting the antennas on 

deployable structures allows them to be stowed for launch. 

Five trunnions (four longeron and one keel) attach the cradle to the orbiter. Five similarly located internal 

attach points attach the spacecraft to the cradle. Another unique feature of the Syncom IV series of 

satellites is the lack of requirement for a separately purchased upper stage, as have all other 

communications satellites launched to date from the Shuttle. 

The Syncom IV satellites contain their own unique upper stage to transfer them from the Shuttle deploy 

orbit of about 160 n.m. to a circular orbit 19,300 n.m. over the equator. 

Each satellite is 20 feet long with UHF and omnidirectional antennas deployed. Total payload weight in the 

orbiter is 17,000 pounds. The satellite's weight on station, at the beginning of its life, will be nearly 3,060 

pounds. Hughes' Space and Communications Group builds the satellites. 

Ejection of the spacecraft from the Shuttle is initiated when locking pins at the four contact points are 

retracted. An explosive device then releases a spring that ejects the spacecraft in a "Frisbee" motion. This 

gives the satellite its separation velocity and gyroscopic stability. The satellite separates from the Shuttle at 

a velocity of about 1.5 feet per second and a spin rate of about 2 rpm. 

As part of this mission, Columbia must rendezvous with the Long Duration Exposure Facility (LDEF). As 

a result, the normal Syncom IV launch condition constraints were relaxed so that Columbia could launch at 

any time of day, any day of the year. This change resulted in modifications to the spacecraft to permit three 

different mission scenarios required to meet the spacecraft operational constraints for different launch 

windows. 

The first mission scenario is the standard Syncom IV sequence controlled by the Post Ejection Sequencer 

(PES). In the PES mode, a series of maneuvers, performed over a period of several days, will be required 

to place Syncom IV into its geosynchronous orbit over the equator. The process starts 80 seconds after the 

spacecraft separates from Columbia with the automatic deployment of the omnidirectional antenna. 

Forty-five minutes after deployment, the solid perigee kick motor, identical to that used as the third stage 

of the Minuteman missile, is ignited, raising the high point of the satellite's orbit to approximately 8,200 

n.m. 

Two liquid fuel engines that burn hypergolic propellants, monomethyl hydrazine and nitrogen tetroxide, 

are used to augment the velocity on successive perigee transits, to circularize the orbit and to align the 

flight path with the equator. 
Edited by Richard W. Orloff, 01/2001/Page 19 

The first of three such maneuvers raises the apogee to 10,500 n.m., the second to 13,800 n.m. and the third 

to geosynchronous orbital altitude. At this point, the satellite is in a transfer orbit with a 160 n.m. perigee 

and a 19,300 n.m. apogee. The final maneuver circularizes the orbit at the apogee altitude. 

In the second mission scenario, called the Sub Transfer Earth Orbit or SEO Mode, the post-ejection 

sequencer fires the perigee kick motor 45 minutes after ejection from the cargo bay, as in the PES mode. 

However, in the SEO mode, the perigee augmentation maneuvers are delayed for up to 20 days to optimize 

spacecraft performance. After this delay, the mission is identical to the PES mission. 

In the third mission scenario, called Low Earth Orbit or LEO mode, the post-ejection sequencer does not 

fire the perigee kick motor. Instead, the spacecraft is stored in low-Earth orbit for up to 15 days, until the 

PKM firing constraints are met. The perigee kick motor is then fired by ground command. The subsequent 

mission is identical to the PES mission. 

The selection of the optimal mission scenario for Syncom IV-F5 will depend on the launch day and 

window selected for LDEF retrieval. This should be known several weeks before launch, but can be 

changed as late as 11 hours before launch. 

Hughes Communications, Inc. operates the worldwide LEASAT satellite communications system under a 

contract with the Department of Defense, with the U.S. Navy acting as the executive agent. The system 

includes four LEASAT satellites and the associated ground facilities. Users include mobile air, surface, 

subsurface and fixed ground stations of the Navy, Marine Corps, Air Force and Army. The satellites are 

positioned for coverage of the continental United States and the Atlantic, Pacific and Indian oceans. 

LEASAT 1, 2 and 3 occupy geostationary positions at 15 degrees West, 73 degrees East and 105 degrees 

West, respectively. LEAST 5 will be positioned at 177 degrees W. 
Edited by Richard W. Orloff, 01/2001/Page 20 

LONG DURATION EXPOSURE FACILITY RENDEZVOUS AND RETRIEVAL 

LDEF was delivered to Earth orbit by STS-41C (STS-13) on April 6, 1984. The orbiter Columbia will 

rendezvous and retrieve LDEF using a -R BAR approach and the remote manipulator system (RMS) for 

berthing of the spacecraft in the payload bay on flight day four. 

LDEF Rendezvous and Grapple 

As the orbiter nears LDEF, the -R BAR approach will be initiated. The orbiter will first pass below the 

spacecraft and circle up and over it. The - R BAR approach is a new technique that does not require 

close-in fly-around. This maneuver will face the payload bay toward Earth and LDEF will now be 

between, as well as perpendicular, to both the Earth and the orbiter. 

At this point, Columbia is approximately 400 feet from LDEF with the RMS arm extended and the wrist 

camera pointing toward the orbiter's starboard side. The wrist camera will provide the primary field of view 

for grapple. A yaw maneuver then will be performed to place the wrist camera in the same x,y plane as 

grapple fixture 2 (GF2) aboard LDEF, so that the camera can eventually view GF2 head on. 

LDEF is then directly "above" the crew compartment (the arm is still in its same position; unattached to the 

LDEF). This allows Commander Dan Brandenstein and Pilot Jim Wetherbee to make necessary flight 

instrument changes to "fly in formation" with the same speed and direction as the free- flying LDEF. 

Next, the orbiter will move forward (+ZLV) very slowly. The crew will be watching their onboard monitor 

for the LDEF to appear in the wrist camera's field of view. As soon as GF2 is spotted, orbiter movement 

will cease. The wrist camera then will rotate 180 degrees to be properly positioned for the grapple of GF2. 

Mission specialist Bonnie Dunbar then will direct the RMS toward GF2 and make the connection for 

grapple completion. LDEF will be approximately 35 feet above the bay during this procedure. 

LDEF Berthing 

The onboard computer then commands the arm to align LDEF with the berthing guides on the payload bay 

sides. The final RMS maneuvering now will be commanded manually to set LDEF in the bay (if there are 

no failures, this process should take approximately 15 minutes). 

The crew also will utilize the black and white camera positioned at keel station 3 aiming it at a docking 

target. The crew will be watching the on- board monitor with an overlay for precision berthing. Three 

orange Styrofoam balls called "berthing whiskers" will extend horizontally inward from the forward 

payload bay side walls. The berthing whiskers will act as "curb feelers" to detect forward movement of 

LDEF. 

LDEF Post-Berthing 

The arm will now detach from GF2 and move to GF1, looking for the six Experiment Initiator System 

(EIS) indicators. If the EIS's are black, the experiments power supply is already off. If they are white, the 

arm will move into GF1 and turn off the experiments. Finally, the arm will be stowed. 

LDEF Post-Flight 

STS-32 is a unique mission for payloads operations, as specialists must perform not only "up-processing" 

(i.e. pre-flight operations to prepare the Syncom IV payload for integration into the orbiter) but also a 
Edited by Richard W. Orloff, 01/2001/Page 21 

"down- processing" for 57 experiments that have been exposed to the harsh space environment for more 

than 5 years aboard the Long Duration Exposure Facility. 

In supporting the return of LDEF, the KSC payload team, working closely with Langley Research Center, 

has planned a post-flight flow that accentuates the preservation of the scientific data. In addition, special 

research teams from Langley, which sponsored the project, will be at KSC when LDEF returns. 

LDEF will remain in Columbia's payload bay during routine post-flight servicing at Edwards Air Force 

Base, Calif. and during the ferry-flight back to KSC. 

To assist in maintaining experiment integrity, an air-conditioned purge system will be hooked up to the 

orbiter during its stay at EAFB and any overnight stops. This system will keep air-conditioned air 

circulating through the payload bay. 

Once Columbia is in the Orbiter Processing Facility (OPF), LDEF will be removed from the cargo bay and 

placed in a payload canister and transported to the Operations and Checkout Building (O&C). There, 

LDEF will be loaded from the canister to the LATS (LDEF Assembly and Transportation System). This 

special "cradle" is 55 feet long, l7 feet wide, and 21 feet high. LATS also was used during the pre-launch 

processing of LDEF. 

LDEF is expected to be in the O&C from about Jan. 8-12. Then, supported by the LATS, it will be 

transferred to the Spacecraft Assembly and Encapsulation Facility, where the experiments will be taken off 

the frame and turned over to researchers. 

Post-Mission Operations 

At KSC, LDEF will be turned over to Langley personnel for off-line facility and experiment operations. 

Before any experiment activities or operations begin, there will be an initial inspection of LDEF and its 

experiments to check the general condition of the spacecraft and to look for any unexpected changes. 

Once the initial inspection is completed, all of the principal investigators (PI) and the Special Investigation 

Groups (SIG) will conduct detailed visual inspections of the entire LDEF and all of the visible experiment 

hardware. 

Experiment trays will be removed from the LDEF and taken on ground support equipment transporters to 

an experiment operations area. After batteries are removed from once-active experiments, trays will go to a 

work bench where the PIs will perform closer inspections and take basic measurements. After the PIs have 

completed their procedures, the experiment hardware will be properly configured, packaged and shipped to 

the PIs' laboratories. 

An accessible LDEF database will be developed to document all of the information resulting from the 

LDEF mission. It is anticipated that this unique body of data on space experiments and the effects of 

long-term exposure in space on typical spacecraft hardware will become a valued resource to future 

spacecraft designers. Structures like the LDEF provide a relatively inexpensive way to conduct 

experiments and may be reusable. Requirements for the use of the LDEF or similar facilities for follow-on 

flights will be evaluated at a later date. 

Structure 

LDEF is a 12-sided, open grid structure made of aluminum rings and longerons (fore-and-aft framing 

members). The structure is 30 feet long, 14 feet in diameter and weighs 8,000 pounds. 
Edited by Richard W. Orloff, 01/2001/Page 22 

LDEF's center ring frame and end frames are of welded and bolted construction. The longerons are bolted 

to both frames, and intercostals (crosspieces between longerons) are bolted to the longerons to form 

intermediate rings. The main load of LDEF was transmitted to the orbiter through two side-support 

trunnions on the center ring. 

LDEF holds 86 experiment trays, 72 around the circumference, six on the Earth-pointing end and eight on 

the space-pointing end. A typical tray measures 50 inches by 34 inches and investigators could choose one 

of three depths: 3, 6 or 12 inches. The trays are made of aluminum and hold experiments that weigh up to 

200 pounds. Some experiments fill more than one tray; some fill only part of a tray. All trays and their 

experiments weigh only 13,400 pounds. Total weight of the structure, trays and experiments is 21,393 

pounds. 

Experiments 

The LDEF experiments are divided into four groups: materials and structures, power and propulsion, 

science and electronics and optics. The 57 experiments on LDEF involve 200 investigators, who represent 

21 universities, 33 private companies, seven NASA centers, nine Department of Defense laboratories and 

eight foreign countries. 

LDEF science experiments include an interstellar gas experiment that may provide insight into the 

formation of the Milky Way galaxy by capturing and analyzing its interstellar gas atoms. 

LDEF cosmic radiation experiments are designed to investigate the evolution of the heavier elements in our 

galaxy. 

LDEF micrometeoroid experiments could increase understanding of the processes involved in the 

evolution of our Solar System. The impact of space radiation on living organisms is another area 

investigated. LDEF science experiments gathered data on the radiation intensity and its effect on living 

organisms such as shrimp eggs and plant seeds. 

Other LDEF experiments collected data on the behavior of a multitude of materials used to manufacture 

spacecraft and space experiment systems exposed to space, including radiation, vacuum, extreme 

temperature variations, atomic oxygen and collision with space matter. The LDEF mission has provided 

important information for the design of future spacecraft that will require extended lifetimes in space, such 

as Space Station Freedom. 

Several LDEF experiments were designed to investigate the effects of prolonged exposure to the space 

environment on optical system components, which include optical filters, coatings, glasses, detectors and 

optical fiber transmission links. LDEF provided an opportunity to study the effects of long-term space 

exposure on the design of solar array power systems by investigating the effects of exposure to the space 

environment on a wide variety of solar cells and associated components. 

A unique process for growing crystals in solutions, which took advantage of the microgravity conditions 

provided by LDEF, was used to grow high purity crystals with unique electrical properties applicable to 

electronic circuits. 

The Space Exposed Experiment Developed for Students (SEEDS) offers a wide variety of opportunities for 

student experiments. Investigators will provide a total of 12.5 million tomato seeds, packaged in kits, to 

students from the upper elementary through the university level. Students will have the unprecedented 

opportunity to study the effects of long-term space exposure on tomato seeds. The program encourages 

active student involvement and a multidisciplinary approach, allowing students to design their own 

experiments and to be involved in decision making, data gathering and reporting of final results. 
Edited by Richard W. Orloff, 01/2001/Page 23 

The low cost of an LDEF experiment encouraged high-risk/high-return investigations and made 

experiments particularly attractive to students and research groups with no experience in space 

experimentation. Investigators could take advantage of NASA and private industry expertise to develop 

relatively inexpensive investigations. 

The LDEF structure was designed and built at the Langley Research Center in Hampton, Va. Experiment 

trays were provided to investigators, who built their own experiments, installed them in trays and tested 

them. To help reduce costs, each investigator established the amount of reliability, quality control and 

testing required to insure proper operation of his experiment. 

The LDEF project is managed by Langley for NASA's Office of Aeronautics and Space Technology in 

Washington, D.C. E. Burton Lightner is Manager of the LDEF Project Office. William H. Kinard is LDEF 

Chief Scientist and Head of the Data Analysis Team. 
Edited by Richard W. Orloff, 01/2001/Page 24 
Edited by Richard W. Orloff, 01/2001/Page 25 

AMERICAN FLIGHT ECHOCARDIOGRAPH 

The American Flight Echocardiograph is an off-the-shelf medical ultrasonic imaging system modified for 

Space Shuttle compatibility. The AFE noninvasively generates a two-dimensional, cross-sectional image of 

the heart or other soft tissues and displays it on a cathode-ray tube (CRT) at 30 frames per second. 

AFE has flown before on STS-51D and is designed to provide inflight measurements of the size and 

functioning of the heart and record heart volume and cardiovascular responses to space flight. Results from 

the AFE will be used in the development of optimal countermeasures to crew cardiovascular changes. 

Operated by STS-32 Mission Specialist Marsha Ivins, the AFE hardware will be stored in an orbiter 

middeck locker. All five crew members will participate in the experiment as subjects as time allows. Crew 

members also will use the AFE to support Detailed Secondary Objective 478, the first flight of a 

collapsible Lower Body Negative Pressure unit. 

In echocardiography, a probe next to the skin sends high frequency sound waves (ultrasound) through the 

skin and into the body, then detects reflections or echoes from the surfaces of the organs, producing 

pictures. 

The Life Sciences Division of NASA's Office of Space Science and Applications is sponsoring the AFE 

which was developed at the Johnson Space Center. Dr. Michael Bungo, the Director of JSC's Space 

Biomedical Research Institute, is the Principal Investigator. 
Edited by Richard W. Orloff, 01/2001/Page 26 

CHARACTERIZATION OF NEUROSPORA CIRCADIAN RHYTHMS 

Characterization of Neurospora Circadian Rhythms (CNCR) in Space is a middeck payload sponsored by 

the Office of Space Science and Applications, Life Sciences Division. The objective of the CNCR 

experiment is to determine if neurospora (pink bread mold) circadian rhythm (diurnal cycles) persists in the 

microgravity environment of space. 

This experiment is intended to provide information about endogenously driven biological clocks, which 

might then be applied to other organisms. Endogenous indicates the activity occurs within a single cell's 

outer membrane. 

Neurospora grows in two forms, a smooth confluence of silky threads (mycelia) and cottony tufts of 

upright stalks tipped with tiny ball-shaped spores (conidia). When growing in a constant, completely 

uniform external environment, the neurospora mold cycles rhythmically from one growth form to the other. 

This cycle causes the mold to produce the ball-shaped spores on approximately 21-hour intervals. This 

interval is believed to be controlled by an internal cell clock. 

However, under typical circumstances, alterations in the external environment, particularly day-night 

cycles with a period of 24 hours, are capable of readjusting the neurospora internal clock. The fundamental 

question addressed by this Shuttle experiment is whether the conditions of space flight, especially the 

absence of Earth's strong gravitational field, affect the neurospora's circadian rhythms. Because these 

rhythmic phenomena also are found in all plants and animals, including humans, this experiment addresses 

a broad and important biological question. 

The Principal Investigator is Dr. James S. Ferraro, Southern Illinois University, Carbondale, Ill. Project 

Manager is Dr. Randall Berthold at NASA's Ames Research Center, Mountain View, Calif. Project 

Scientist is Dr. Charles Winget, also at Ames. Program Scientist/Manager is Dr. Thora Halstead, NASA 

Headquarters Life Sciences Division. Mission Manager is Willie Beckham of NASA's Johnson Space 

Center, Houston. 
Edited by Richard W. Orloff, 01/2001/Page 27 

PROTEIN CRYSTAL GROWTH EXPERIMENT 

The Protein Crystal Growth (PCG) payload aboard STS-32 is a continuing series of experiments that may 

prove a major benefit to medical technology. These experiments could improve food production and lead 

to innovative new drugs to combat cancer, AIDS, high blood pressure, organ transplant rejection, 

rheumatoid arthritis and many other diseases. 

Protein crystals, like inorganic crystals such as snowflakes, are structured in a regular pattern. With a good 

crystal, roughly the size of a grain of table salt, scientists are able to study the protein's molecular 

architecture. 

Determining a protein crystal's molecular shape is an essential step in several phases of medical research. 

Once the three-dimensional structure of a protein is known, it may be possible to design drugs that will 

either block or enhance the protein's normal function within the body. Though crystallographic techniques 

can be used to determine a protein's structure, this powerful technique has been limited by problems 

encountered in obtaining high-quality crystals well-ordered and large enough to yield precise structural 

information. 

Protein crystals grown on Earth are often small and flawed. The problem associated with growing these 

crystals is analogous to filling a sports stadium with fans who all have reserved seats. Once the gate opens, 

people flock to their seats and in the confusion, often sit in someone else's place. On Earth, gravity-driven 

convection keeps the molecules crowded around the "seats" as they attempt to order themselves. 

Unfortunately, protein molecules are not as particular as many of the smaller molecules and are often 

content to take the wrong places in the structure. 

As would happen if you let the fans into the stands slowly, microgravity allows the scientist to slow the 

rate at which molecules arrive at their seats. Since the molecules have more time to find their spot, fewer 

mistakes are made, creating better and larger crystals. 

During the STS-32 mission, 120 different PCG experiments will be conducted simultaneously using as 

many as 24 different proteins. Though there are three processes used to grow crystals on Earth, vapor 

diffusion, liquid diffusion and dialysis, only vapor diffusion will be used in this set of experiments. 

Shortly after achieving orbit, either Mission Specialist Marsha Ivins or Mission Specialist David Low will 

combine each of the protein solutions with other solutions containing a precipitation agent to form small 

droplets on the ends of double-barreled syringes positioned in small chambers. Water vapor will diffuse 

from each droplet to a solution absorbed in a porous reservoir that lines each chamber. The loss of water by 

this vapor diffusion process will produce conditions in the droplets that cause protein crystals to grow. 

In three of the 20-chambered, 15-by-10-by-1.5-inch trays, crystals will be grown at room temperature (22 

degrees Centigrade); the other three trays will be refrigerated (4 degrees C) during crystal growth. STS-32 

will be the first mission during which PCG experiments will be run at 4 degrees C, making it possible to 

crystallize a wider selection of proteins. The 9-day flight also provides a longer time period for crystals to 

grow. 

A seventh tray will be flown without temperature control. The crew will videotape droplets in the tray to 

study the effects of orbiter maneuvers and crew activity on droplet stability and crystal formation. 

Just prior to descent, the mission specialist will photograph the droplets in the room temperature trays. 

Then all the droplets and any protein crystals grown will be drawn back into the syringes. The syringes 

then will be resealed for reentry. Upon landing, the hardware will be turned over to the investigating team 

for analysis. 

Protein crystal growth experiments were first carried out by the investigating team during Spacelab 2 in 

April 1985. These experiments have flown six times. The first four flights were primarily designed to 
Edited by Richard W. Orloff, 01/2001/Page 28 

develop space crystal growing techniques and hardware. 

The STS-26 and STS-29 experiments were the first scientific attempts to grow useful crystals by vapor 

diffusion in microgravity. The main differences between the STS-26 and STS-29 payloads and those on 

previous flights were the introduction of temperature control and the automation of some of the processes 

to improve accuracy and reduce the crew time required. 

To further develop the scientific and technological foundation for protein crystal growth in space, NASA's 

Office of Commercial Programs and the Microgravity Science and Applications Division are 

co-sponsoring the STS-32 experiments with management provided through Marshall Space Flight Center, 

Huntsville, Ala. Blair Herren is the Marshall experiment manager and Richard E. Valentine is the mission 

manager for the PCG experiment at Marshall. 

Dr. Charles E. Bugg, director of the Center for Macromolecular Crystallography, a NASA-sponsored 

Center for the Development of Space located at the University of Alabama-Birmingham, is lead 

investigator for the PCG research team. 

The STS-32 industry, university and government PCG research investigators include CNRS, Marseilles, 

France; Eli Lilly & Co.; U.S. Naval Research Laboratory; E.I. du Pont de Nemours & Co.; Merck Sharp & 

Dohme Laboratories; Texas A&M University; University of Alabama-Birmingham/Schering Corp.; Yale 

University; University of Pennsylvania; University of California at Riverside; The Weizmann Institute of 

Science; Marshall Space Flight Center; Australian National University/BioCryst, Ltd.; University of 

Alabama-Birmingham/BioCryst; Smith Kline & French Labs.; The Upjohn Co.; Eastman Kodak Co.; 

Wellcome Research Labs. and Georgia Institute of Technology. 
Edited by Richard W. Orloff, 01/2001/Page 29 

MICROGRAVITY RESEARCH WITH THE 

FLUIDS EXPERIMENT APPARATUS 

Fluids Experiment Apparatus 

The Fluids Experiment Apparatus (FEA) is designed to perform materials processing research in the 

microgravity environment of spaceflight. Its design and operational characteristics are based on actual 

industrial requirements and have been coordinated with industrial scientists, NASA materials processing 

specialists and Space Shuttle operations personnel. The FEA offers experimenters convenient, low-cost 

access to space for basic and applied research in a variety of product and process technologies. 

The FEA is a modular microgravity chemistry and physics laboratory for use on the Shuttle and supports 

materials processing research in crystal growth, general liquid chemistry, fluid physics and 

thermodynamics. It has the functional capability to heat, cool, mix, stir or centrifuge gaseous, liquid or 

solid experiment samples. Samples may be processed in a variety of containers or in a semicontainerless 

floating zone mode. Multiple samples can be installed, removed or exchanged through a 14.1-by-10-inch 

door in the FEA's cover. 

Instrumentation can measure sample temperature, pressure, viscosity, etc. A camcorder or super-8 mm 

movie camera may be used to record sample behavior. Experiment data can be displayed and recorded 

through the use of a portable computer that also is capable of controlling experiments. 

The interior of the FEA is approximately 18.6-by-14.5-by-7.4 inches and can accommodate about 40 

pounds of experiment-unique hardware and subsystems. The FEA mounts in place of a standard stowage 

locker in the middeck of the Shuttle crew compartment, where FEA is operated by the flight crew. 

Modular design permits the FEA to be easily configured for almost any experiment. Configurations may be 

changed in orbit, permitting experiments of different types to be performed on a single Shuttle mission. 

Optional subsystems may include custom furnace and oven designs, special sample containers, 

low-temperature air heaters, specimen centrifuge, special instrumentation and other systems specified by 

the user. Up to 100 watts of 120-volt, 400-Hertz power is available from the Shuttle orbiter for FEA 

experiments. The FEA was successfully flown on two previous missions, as a student experiment on STS41D and as the first flight of the JEA on STS-30. 

Rockwell International, through its Space Transportation Systems Division, Downey, Calif., is engaged in 

a joint endeavor agreement (JEA) with NASA's Office Commercial Programs in the field of floating zone 

crystal growth and purification research. The 1989 agreement provides for microgravity experiments to be 

performed on two Space Shuttle missions. 

Under the sponsorship of NASA's Office of Commercial Programs, the FEA will fly aboard Columbia on 

STS-32. Rockwell is responsible for developing the FEA hardware and for integrating the experiment 

payload. Johnson Space Center, Houston, has responsibility for developing the materials science 

experiments and for analyzing their results. 

The Indium Corporation of America, Utica, N.Y., is collaborating with NASA on the experiments and is 

providing seven indium samples to be processed during this mission. NASA provides standard Shuttle 

flight services under the JEA. 

Floating Zone Crystal Growth and Purification 

The floating zone process is one of many techniques used to grow single crystal materials. The process 

involves an annular heater that melts a length of sample material and then moves along the sample. As the 

heater moves (translates), more of the polycrystalline material in front of it melts. The molten material 

behind the heater will cool and solidify into a single crystal. 
Edited by Richard W. Orloff, 01/2001/Page 30 

The presence of a "seed" crystal at the initial solidification interface will establish the crystallographic 

lattice structure and orientation of the single crystal that results. Impurities in the polycrystalline material 

will tend to stay in the melt as it passes along the sample and will be deposited at the end when the heater is 

turned off and the melt finally solidifies. 

Under the influence of Earth's gravity, the length of the melt is dependent upon the density and surface 

tension of the material being processed. Many industrially important materials cannot be successfully 

processed on Earth because of their properties. In the microgravity environment of spaceflight, there is a 

maximum theoretical molten zone length which can be achieved. 

Materials of industrial interest include selenium, cadmium telluride, gallium arsenide and others. Potential 

applications for those materials include advanced electronic electro-optical devices and high-purity feed 

stock. Zone refining to produce ultra-high purity indium also is of interest for the production of advanced 

electronic devices from indium antimonide and indium arsenide. 

FEA-3 Experiment Plan 

The FEA-3 microgravity disturbances experiment involves seven samples (plus one spare) of commercial 

purity indium (99.97 percent purity). Indium was chosen for this experiment because it is a 

well-characterized material and has a relatively low melting point (156 degrees Celsius). The samples each 

will be 1 centimeter in diameter and 18 centimeters long and will be processed in an inert argon 

atmosphere. The sample seeding heater translation rates and process durations are provided in the 

following table: 

Experiment Samples and Parameters 

Sample Seeded 

Heater 

Rate 

(cm/hr) 

Duration 

(hours) 

1 No 0 2.00 

2 Yes 24 4.50 

3 Yes 12 9.00 

4 Yes 24 4.50 

5 Yes 48 2.25 

6 Yes 12 9.00 

7 Yes 96 1.10 

At 5.25 hours mission elapsed time (MET), the flight crew will unstow the FEA and connect its computer 

and support equipment. The samples will be sequentially installed at 20, 26, 44, 66, 97, 114 and 144 hours 

MET and processed. 

The experiment parameters (heater power and translation rate) will be controlled by the operator through 

the FEA control panel. Sample behavior (primarily melt-zone length and zone stability) will be observed 

by the operator and recorded using the on-board camcorder. Experiment data (heater power, translation rate 

and position, experiment time, and various experiment and FEA temperatures) will be formatted, displayed 

to the operator and recorded by the computer. The operator will record the MET at the start of each 

experiment and significant orbiter maneuvers and other disturbances that occur during FEA operations. In 

addition, accelerometer measurements during the induced disturbances will be recorded for postflight 

analysis. 

In general, the experiment process involves installing a sample in the FEA, positioning the heater at a 

designated point along the sample, turning on the heater to melt a length of the sample, starting the heater 

translation at a fixed rate and maintaining a constant melt-zone length. When the heater reaches the end of 
Edited by Richard W. Orloff, 01/2001/Page 31 

the sample, it is turned off, allowing the sample to completely solidify, and the heater's translation is 

reversed until it reaches the starting end of the sample. The sample 8 mm camcorder cassette and computer 

disk with the experiment data then can be changed and the next experiment started. 

FEA-3 Experiment Description 

Most materials are processed in space to take advantage of the low gravity levels achievable in low-Earth 

orbit, which has been demonstrated to produce superior quality crystals over those grown on the ground. 

The focus of the FEA-3 experiment entitled "Microgravity Disturbances Experiment," is to investigate the 

effects of both orbiter and crew-induced disturbances in the microgravity environment on the resulting 

microstructure of float-zone-grown indium crystals. 

The FEA-3 experiment is one of the first designed specifically to grow crystals during known disturbances 

to investigate their effects on crystal growth processes. The disturbances to be investigated in this 

experiment will focus on orbiter engine firings and crew exercise on the treadmill, but will include several 

other disturbances typical of orbiter operations. This research should provide information useful in 

establishing the microgravity- level requirements for processing materials aboard Space Station Freedom 

and also provide a greater understanding of the role of residual gravity in materials processing. 

This experiment will also investigate the effects of disturbances on the stability of a freely suspended 

molten zone and provide information on the impurity refining capability of float zone processing in space. 
Edited by Richard W. Orloff, 01/2001/Page 32 

MESOSCALE LIGHTNING EXPERIMENT 

Space Shuttle mission STS-32 will again carry the Mesoscale Lightning Experiment (MLE), designed to 

obtain nighttime images of lightning to better understand the global distribution of lightning, the 

relationships between lightning events in nearby storms and relationships between lightning, convective 

storms and precipitation. 

A better understanding of the relationships between lightning and thunderstorm characteristics can lead to 

the development of applications in severe storm warning and forecasting and in early warning systems for 

lightning threats to life and property. 

In recent years, NASA has used the Space Shuttle and high-altitude U-2 aircraft to observe lightning from 

above convective storms. The objectives of these observations have been to determine some of the baseline 

design requirements for a satellite-borne optical lightning mapper sensor; study the overall optical and 

electrical characteristics of lightning as viewed from above the cloud top and to investigate the relationship 

between storm electrical development and the structure, dynamics and evolution of thunderstorms and 

thunderstorm systems. 

The MLE began as an experiment to demonstrate that meaningful, qualitative observations of lightning 

could be made from the Shuttle. Having accomplished this, the experiment is now focusing on quantitative 

measurements of lightning characteristics and observation simulations for future space- borne lightning 

sensors. 

Data from the MLE will provide information for the development of observation simulations for an 

upcoming polar platform and Space Station instrument, the Lightning Imaging Sensor. The lightning 

experiment also will be helpful for designing procedures for using the Lightning Mapper Sensor, planned 

for several geostationary platforms. 

The Experiment 

The Space Shuttle payload bay camera will be pointed directly below the orbiter to observe nighttime 

lightning in large, or mesoscale, storm systems to gather global estimates of lightning as observed from 

Shuttle altitudes. Scientists on the ground will analyze the imagery for the frequency of lightning flashes in 

active storm clouds within the camera's field of view, the length of lightning discharges and cloud 

brightness when illuminated by the lightning discharge within the cloud. 

If time permits during missions, astronauts also will use a handheld 35 mm camera to photograph lightning 

activity in storm systems not directly below the Shuttle's orbital track. 

Data from the MLE will be associated with ongoing observations of lightning made at several locations on 

the ground, including observations made at facilities at the Marshall Space Flight Center, Huntsville, Ala.; 

Kennedy Space Center, Fla.; and the NOAA Severe Storms Laboratory, Norman, Okla. Other 

ground-based lightning detection systems in Australia, South America and Africa will be integrated when 

possible. 

The MLE is managed by NASA's Marshall Space Flight Center. Otha H. Vaughan Jr., is coordinating the 

experiment. Dr. Hugh Christian is the project scientist and Dr. James Arnold is the project manager. 
Edited by Richard W. Orloff, 01/2001/Page 33 

IMAX 

The IMAX project is a collaboration between NASA and the Smithsonian Institution's National Air and 

Space Museum to document significant space activities using the IMAX film medium. This system, 

developed by the IMAX Systems Corp., Toronto, Canada, uses specially designed 70 mm film cameras and 

projectors to record and display very high definition large-screen color motion pictures. 

IMAX cameras previously have flown on Space Shuttle missions 41-C, 41-D and 41-G to document crew 

operations in the payload bay and the orbiter's middeck and flight deck along with spectacular views of 

Earth. Film from those missions form the basis for the IMAX production, The Dream is Alive. 

In 1985, during Shuttle Mission STS-61-B, an IMAX camera mounted in the payload bay recorded 

extravehicular activities in the EASE/ACCESS space construction demonstrations. 

So far in 1989, the IMAX camera has flown twice, during Shuttle missions STS-29 in March and STS-34 

in October. During those missions, the camera was used to gather material for an upcoming IMAX 

production entitled The Blue Planet. 

During STS-32, IMAX will film the retrieval of the Long Duration Exposure Facility and collect additional 

material for upcoming IMAX productions. 
Edited by Richard W. Orloff, 01/2001/Page 34 
Edited by Richard W. Orloff, 01/2001/Page 35 

AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST (AMOS) 

The Air Force Maui Optical Site (AMOS) tests allow ground-based electro- optical sensors located on 

Mount Haleakala, Maui, Hawaii, to collect imagery and signature data of the orbiter during overflights of 

that location. The scientific observations made of the orbiter while performing reaction control system 

thruster firings, water dumps or payload bay light activation, are used to support calibration of the AMOS 

sensors and the validation of spacecraft contamination models. The AMOS tests have no payload-unique 

flight hardware and only require that the orbiter be in a pre-defined attitude operations and lighting 

conditions. 

The AMOS facility was developed by the Air Force Systems Command (AFSC) through its Rome Air 

Development Center, Griffiss Air Force Base, N.Y., and is administered and operated by the AVCO 

Everett Research Laboratory in Maui. The principal investigator for the AMOS tests on the Space Shuttle 

is from AFSC's Air Force Geophysics Laboratory, Hanscom Air Force Base, Mass. A co- principal 

investigator is from AVCO. 

Flight planning and mission support activities for the AMOS test opportunities are provided by a 

detachment of AFSC's Space Systems Division at Johnson Space Center. Flight operations are conducted 

at JSC Mission Control Center in coordination with the AMOS facilities located in Hawaii. 
Edited by Richard W. Orloff, 01/2001/Page 36 

LATITUDE-LONGITUDE LOCATOR EXPERIMENT 

On Shuttle mission 41-G, Payload Specialist and oceanographer Scully Power observed numerous unusual 

oceanographic features from orbit but was unable to determine their exact locations for subsequent study. 

NASA, in conjunction with the Department of Defense, began work on an instrument that would be able to 

determine the precise latitude and longitude of objects observed from space. 

The Latitude-Longitude Locator (L3) was developed and flown on a previous Space Shuttle mission. This 

flight will continue tests to determine the accuracy and usability of the system in finding the latitude and 

longitude of known ground sites. 

L3 consists of a modified Hasselblad camera equipped with a wide-angle 40 mm lens, a camera computer 

interface developed by JSC engineers and a Graphics Retrieval and Information Display (GRID) 1139 

Compass Computer. 

Crew members will take two photographs of the same target at an interval of approximately 15 seconds. 

Information will be fed to the GRID computer, which will compute two possible locations. The crew, by 

knowing whether the target is north or south of the flight path, will be able to determine which of the two 

locations is correct and the target's latitude and longitude. 

Andy Saulietis of NASA's Johnson Space Center is the Principle Investigator for the experiment. 
Edited by Richard W. Orloff, 01/2001/Page 37 
Edited by Richard W. Orloff, 01/2001/Page 38 

SPACEFLIGHT TRACKING AND DATA NETWORK 

Primary communications for most activities on STS-32 will be conducted through the orbiting Tracking 

and Data Relay Satellite System (TDRSS), a constellation of three communications satellites, two 

operational and one spare, in geosynchronous orbit 22,300 miles above the Earth. In addition, three NASA 

Spaceflight Tracking and Data Network (STDN) ground stations and the NASA Communications Network 

(NASCOM), both managed by Goddard Space Flight Center, Greenbelt, Md., will play key roles in the 

mission. 

Three stations Merritt Island and Ponce de Leon, Fla., and Bermuda serve as the primary communications 

facilities during the launch and ascent phases of the mission. For the first 80 seconds, all voice, telemetry 

and other communications from the Space Shuttle are relayed to the mission managers at Kennedy and 

Johnson Space Centers by Merritt Island. 

At 80 seconds, the communications are picked up from the Shuttle and relayed to the two NASA centers 

from Ponce de Leon, 30 miles north of the launch pad. This facility provides the communications between 

the Shuttle and the centers for 70 seconds, or until 150 seconds into the mission. This is during a critical 

period when exhaust from the solid rocket motors "blocks out" the Merritt Island antennas. 

Merritt Island resumes communications with the Shuttle after those 70 seconds and maintains 

communications until 6:30 after launch, when communications are "switched over" to Bermuda. Bermuda 

then provides the communications until 11 minutes after lift off when the TDRS-East satellite acquires the 

Shuttle. TDRS-West acquires the orbiter at launch plus 50 minutes. 

Communications will alternate between the TDRS-East and TRDS-West satellites as the Shuttle orbits the 

Earth. The two satellites will provide communications with the Shuttle during 85 percent or more of each 

orbit. The TDRS-West satellite will handle communication with the Shuttle during its descent and landing 

phases. 
Edited by Richard W. Orloff, 01/2001/Page 39 

STS-32 CREWMEMBERS 

S89-48342 – The official crew portrait for STS-34 includes, seated, mission commander Daniel C. 

Brandenstein and pilot James D. Wetherbee. Standing are mission specialists Bonnie J. Dunbar, G. David 

Low, and Marsha S. Ivins. Low is holding the mission insignia. 

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 40 

BIOGRAPHICAL DATA 

DANIEL C. BRANDENSTEIN, 46, Capt. USN, will serve as commander. Selected as an astronaut in 

January 1978, he was born in Watertown, Wisc., and will be making his third Shuttle flight. 

Brandenstein was pilot for STS-8, the third flight of Challenger, launched on Aug. 30, 1983. During the 

6-day mission, the five-member crew deployed the Indian National Satellite (INSAT-1B) and tested the 

orbiter's remote manipulator system (RMS) with the Payload Test Article. 

On his second flight, Brandenstein served as commander for STS-51G, launched June 17, 1985. During the 

7-day mission, the 18th Space Shuttle flight, the seven-member crew deployed the Morelos satellite for 

Mexico; the Arabsat satellite for the Arab League; and the AT&T Telstar satellite. Also, the RMS was used 

to deploy and later retrieve the SPARTAN satellite. 

Following STS-51G, Brandenstein became deputy director of flight crew operations at JSC and later 

assumed his current post, chief of the Astronaut Office. 

He graduated from Watertown High School in 1961 and received a B.S. degree in mathematics and physics 

from the University of Wisconsin in 1965. Brandenstein was designated a naval aviator in 1967. During 

the Vietnam War and later as a test pilot, he logged more than 5,200 hours of flying time in 24 types of 

aircraft and has more than 400 carrier landings. 

JAMES D. WETHERBEE, 37, Lt. Cmdr., USN, will serve as pilot. Selected as an astronaut in May 1984, 

he was born in Flushing, N.Y., and will be making his first Shuttle flight. 

Wetherbee graduated from Holy Family Diocesan High School, South Huntington, N.Y., in 1970 and 

received a B.S. in aerospace engineering from Notre Dame in 1974. 

Wetherbee was designated a naval aviator in December 1976. After serving aboard the aircraft carrier USS 

John F. Kennedy, he attended the Naval Test Pilot School and completed training there in 1981. He then 

worked with testing of, and later flew, the F/A-18 aircraft until his selection by NASA. 

Wetherbee has logged more than 2,500 hours flying in 20 types of aircraft and completed more than 345 

carrier landings. 

BONNIE J. DUNBAR, 40, will serve as mission specialist 1 (MS1). Selected as an astronaut in August 

1981, she was born in Sunnyside, Wash., and will be making her second Shuttle flight. 

Dunbar served as a mission specialist on STS-61A, the West German D-1 Spacelab mission and the first 

Shuttle flight to carry eight crew members. During the 7-day mission, Dunbar was responsible for 

operating the Spacelab and its subsystems as well as performing a variety of experiments. 

Dunbar graduated from Sunnyside High School in 1967; received a B.S. degree and an M.S. degree in 

ceramic engineering from the University of Washington in 1971 and 1975, respectively; and received a 

doctorate in biomedical engineering from the University of Houston in 1983. 

Dunbar joined NASA as a payload officer/flight controller at JSC in 1978. She served as a guidance and 

navigation officer/flight controller for the Skylab reentry mission in 1979, among other tasks, prior to her 

selection as an astronaut. She is a private pilot with more than 200 hours in single- engine aircraft and more 

than 700 hours in T-38 jets as a co-pilot. 
Edited by Richard W. Orloff, 01/2001/Page 41 

BIOGRAPHICAL DATA 

MARSHA S. IVINS, 38, will serve as mission specialist 2 (MS2). Selected as an astronaut in May 1984, 

she was born in Baltimore, Md., and will be making her first Shuttle flight. 

Ivins graduated from Nether Providence High School, Wallingford, Pa., in 1969 and received a B.S. degree 

in aerospace engineering from the University of Colorado in 1973. 

She began her career with NASA as an engineer in the Crew Station Design Branch at JSC in July 1974. 

Her work involved Space Shuttle displays and controls and development of the orbiter head-up display. In 

1980, Ivins became a flight simulation engineer on the Shuttle Training Aircraft and also served as a 

co-pilot on the NASA administrative aircraft, a Gulfstream I. 

Ivins has logged more than 4,500 hours flying time in NASA and private aircraft and holds a multi-engine 

airline transport pilot license with a Gulfstream I rating; single-engine airplane, land, sea and commercial 

licenses; a commercial glider license; and instrument, multi-engine and glider flight instructor ratings. 

G. DAVID LOW, 33, will serve as mission specialist 3 (MS3). Selected as an astronaut in May 1984, he 

was born in Cleveland and will be making his first Shuttle flight. 

Low graduated from Langley High School, McLean, Va., in 1974; received a B.S. degree in 

physics-engineering from Washington and Lee University in 1978; received a B.S. degree in mechanical 

engineering from Cornell University in 1980; and received a M.S. degree in aeronautics and astronautics 

from Stanford University in 1983. 

Low began his career with NASA in 1980 in the Spacecraft Systems Engineering Section of the NASA Jet 

Propulsion Laboratory (JPL), Pasadena, Calif., where he participated in the preliminary planning of several 

planetary missions and the systems engineering design of the Galileo spacecraft. Following a 1-year leave 

of absence from JPL to pursue graduate studies, he returned and worked as the principal spacecraft systems 

engineer for the Mars Geoscience/Climatology Observer Project until his selection as an astronaut. 

As an astronaut, his technical assignments have included work with the RMS and extravehicular systems. 

He also served as a spacecraft communicator during STS-26, STS-27 and STS-29. 
Edited by Richard W. Orloff, 01/2001/Page 42 

NASA PROGRAM MANAGEMENT 

NASA HEADQUARTERS, WASHINGTON, DC 

Richard H. Truly NASA Administrator 

James R. Thompson Jr. NASA Deputy Administrator 

William B. Lenoir Associate Administrator for Space Flight 

George W.S. Abbey Deputy Associate Administrator for Space Flight 

Robert L. Crippen Acting Director, Space Shuttle Program 

 Deputy Director, Space Shuttle Operations 

Leonard S. Nicholson Deputy Director, Space Shuttle Program (located at Johnson Space Center) 

David L. Winterhalter Director, Systems Engineering and Analyses 

Gary E. Krier Director, Operations Utilization 

Joseph B. Mahon Deputy Associate Administrator for Space Flight (Flight Systems) 

Charles R. Gunn Director, Unmanned Launch Vehicles and Upper Stages 

George A. Rodney Associate Administrator for Safety, Reliability, Maintainability and Quality 

 Assurance 

Arnold Aldrich Associate Administrator for Office of Aeronautics and Space Technology 

Lana Couch Director for Space 

Jack Levine Director, Flight Projects Division 

John Loria LDEF Program Manager 

Sam Venneri Director, Materials and Structures Division 

James T. Rose Assistant Administrator for Commercial Programs 

Charles T. Force Associate Administrator for Operations 

Dr. Lennard A. Fisk Associate Administrator for Space Science and Applications 

A. V. Diaz Deputy Associate Administrator for Space Science and Applications 

JOHNSON SPACE CENTER, HOUSTON, TX 

Aaron Cohen Director 

Paul J. Weitz Deputy Director 

Daniel M. Germany Acting Manager, Orbiter and GFE Projects 

Donald R. Puddy Director, Flight Crew Operations 

Eugene F. Kranz Director, Mission Operations 

Henry O. Pohl Director, Engineering 

Charles S. Harlan Director, Safety, Reliability and Quality Assurance 

KENNEDY SPACE CENTER, FL 

Forrest S. McCartney Director 

Thomas E. Utsman Deputy Director 

Jay F. Honeycutt Director, Shuttle Management and Operations 

Robert B. Sieck Launch Director 

George T. Sasseen Shuttle Engineering Director 

Larry Ellis (Acting) Columbia Flow Director 

James A. Thomas Director, Safety, Reliability and Quality Assurance 

John T. Conway Director, Payload Management and Operations 
Edited by Richard W. Orloff, 01/2001/Page 43 

MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, AL 

Thomas J. Lee Director 

Dr. J. Wayne Littles Deputy Director 

G. Porter Bridwell Manager, Shuttle Projects Office Acting Manager, External Tank 

 Project 

Dr. George F. 

McDonough Director, Science and Engineering 

Alexander A. McCool Director, Safety, Reliability and Quality Assurance 

Royce E. Mitchell Manager, Solid Rocket Motor Project 

Cary H. Rutland Manager, Solid Rocket Booster Project 

Jerry W. Smelser Manager, Space Shuttle Main Engine Project 

LANGLEY RESEARCH CENTER, HAMPTON, VA 

Richard H. Petersen Director 

Frank Allario Director for Electronics 

Leon Taylor Chief, Projects Division 

E. Burton Lightner LDEF Project Manager 

William H. Kinard LDEF Chief Scientist 

Charles Blankenship Director for Structures 

Darrel Tenney Chief, Materials Division 

STENNIS SPACE CENTER, BAY ST. LOUIS, MS 

Roy S. Estess Director 

Gerald W. Smith Deputy Director 

AMES RESEARCH CENTER, MOUNTAIN VIEW, CA 

Dr. Dale L. Compton Acting Director 

AMES-DRYDEN FLIGHT RESEARCH FACILITY, EDWARDS, CA 

Martin A. Knutson Site Manager 

Theodore G. Ayers Deputy Site Manager 

Thomas C. McMurtry Chief, Research Aircraft Operations Division 

Larry C. Barnett Chief, Shuttle Support Office 

GODDARD SPACE FLIGHT CENTER, GREENBELT, MD 

Dr. John W. Townsend Director 

Peter Burr Director, Flight Projects 

Dale L. Fahnestock Director, Mission Operations and Data Systems 

Daniel A. Spintman Chief, Networks Division 

Wesley J. Bodin Associate Chief, Ground Network 

Gary A. Morse Network Director 
Edited by Richard W. Orloff, 01/2001/Page 44 

SHUTTLE FLIGHTS AS OF DECEMBER 1989 

32 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 7 SINCE RETURN TO FLIGHT 

STS-51L 

01/28/86 

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-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

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-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

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 

(9 flights)

OV-099 

Challenger 

(10 flights)

OV-103 

Discovery 

(9 flights)

OV-104 

Atlantis 

(4 flights)