Table 3–51. Space Shuttle Missions Summary (1989

databk7_collected.book Page 370 Monday, September 14, 2009 2:53 PM

Flt No. Mission/Orbiter Dates Crew 

73 STS-74/Atlantis November 12, 1995 – CDR: Kenneth D. Cameron 

November 20, 1995 PLT: James D. Halsell, Jr. 

MS: Chris A. Hadfield, Jerry L. Ross, William S. Mc

74 STS-72/Endeavour January 11, 1996 – CDR: Brian Duffy 

January 20, 1996 PLT: Brent W. Jett, Jr. 

MS: Leroy Chiao, Winston E. Scott, Koichi WaDaniel T. Barry

75 STS-75/Columbia February 22, 1996 – CDR: Andrew M. Allen 

March 9, 1996 PLT: Scott J. Horowitz 

MS: Jeffrey A. Hoffman, Maurizio Cheli, Claude NicollierPC: Franklin R. Chang-DiazPS: Umberto Guidoni

76 STS-76/Atlantis March 22, 1996 – CDR: Kevin P. Chilton 

March 31, 1996 PLT: Richard A. Searfoss 

MS: Ronald M. Sega, MichaClifford, Linda M. Godwin, Shannon W. Lucid (to Mir)

77 STS-77/Endeavour May 19, 1996 – CDR: John H. Casper 

May 29, 1996 PLT: Curtis L. Brown, Jr. 

MS: Andrew S.W. Thomas, Daniel W. Bursch, Mario RuMarc Garneau
Table 3–51. Space Shuttle Missions Summary (1989

databk7_collected.book Page 371 Monday, September 14, 2009 2:53 PM

Flt No. Mission/Orbiter Dates Crew 

78 STS-78/Columbia June 20, 1996 – CDR: Terence T. Henricks 

July 7, 1996 PLT: Kevin R. Kregel 

MS: Richard M. Linnehan, Charles E. Brady, Jr.PC: Susan J. HelmsPS: Jean-Jacques Favier, Robert Brent Thirsk

79 STS-79/Atlantis September 16, 1996 – CDR: William F. Readdy 

September 26, 1996 PLT: Terence W. Wilcutt 

MS: Jerome Apt, Thomas DCarl E. Walz, John E. Blaha Shannon W. Lucid (returned 

80 STS-80/Columbia November 19, 1996 – CDR: Kenneth D. Cockrell 

December 7, 1996 PLT: Kent V. Rominger 

MS: Thomas D. Jones, F. Story MusgravePC: Tamara E. Jernigan

81 STS-81/Atlantis January 12, 1997 – CDR: Michael A. Baker 

January 22, 1997 PLT: Brent W. Jett, Jr. 

MS: Peter J.K. Wisoff, John M. Grunsfeld, Marsha Jerry M. Linenger (to Mir), John E. Blaha (returned from 
Table 3–51. Space Shuttle Missions Summary (1989

databk7_collected.book Page 372 Monday, September 14, 2009 2:53 PM

Flt No. Mission/Orbiter Dates Crew 

82 STS-82/Discovery February 11, 1997 – CDR: Kenneth D. Bowersox 

February 21, 1997 PLT: Scott J. Horowitz 

MS: Joseph R. Tanner, Steven A. Hawley, Gregory JSteven L. Smith,PC: Mark C. Lee

83 STS-83/Columbia April 4, 1997 – CDR: James D. Halsell, Jr. 

April 8, 1997 PLT: Susan L. Still 

MS: Michael L. Gernhardt, Donald A. ThomasPC: Janice E. VossPS: Roger K. Crouch, Gregory T. Linteris

84 STS-84/Atlantis May 15, 1997 – CDR: Charles J. Precourt 

May 24, 1997 PLT: Eileen M. Collins 

MS: Carlos I. Noriega, Edward Tsang Lu, Elena V. KC. Michael Foale (to Mir), Jerry M. Linenger (returned 

PC: Jean-Francois Clervoy

85 STS-94/Columbia July 1, 1997 – CDR: James D. Halsell, Jr. 

July 17, 1997 PLT: Susan L. Still 

MS: Michael L. Gernhardt, Donald A. ThomasPC: Janice E. VossPS: Roger K. Crouch, Gregory T. Linteris
Table 3–51. Space Shuttle Missions Summary (1989

databk7_collected.book Page 373 Monday, September 14, 2009 2:53 PM

Flt No. Mission/Orbiter Dates Crew 

86 STS-85/Discovery August 7, 1997 – CDR: Curtis L. Brown, Jr. 

August 19, 1997 PLT: Kent V. Rominger. 

MS: Robert L. Curbeam, Jr., Stephen K. RobinsonPC: N. Jan DavisPS: Bjarni V. Tryggvason

87 STS-86/Atlantis September 25, 1997 – CDR: James D. Wetherbee 

October 6, 1997 PLT: Michael J. Bloomfield 

MS: Vladimir G. Titov, ScotParazynski, Jean-Loup J.M. Wendy B. Lawrence, David (to Mir), C. Michael Foale (return from Mir)

88 STS-87/Columbia November 19, 1997 – CDR: Kevin R. Kregel 

December 5, 1997 PLT: Steven W. Lindsey 

MS: Kalpana Chawla, Winston E. Scott, Takao DoiPS: Leonid K. Kadenyuk

89 STS-89/Endeavour January 22, 1998 – CDR: Terrence W. Wilcutt 

January 31, 1998 PLT: Joe Frank Edwards, Jr. 

MS: James F. Reilly, MichaeAnderson, Salizhan ShakirovSharipov, Andrew S.W. ThoDavid A. WolfPC: Bonnie J. Dunbar
Table 3–51. Space Shuttle Missions Summary (1989

databk7_collected.book Page 374 Monday, September 14, 2009 2:53 PM

Flt No. Mission/Orbiter Dates Crew 

90 STS-90/Columbia April 17, 1998 – CDR: Richard A. Searfoss 

May 3, 1998 PLT: Scott D. Altman 

MS: Kathryn P. Hire, Dafydd Rhys WilliamsPC: Richard M. LinnehanPS: Jay C. Buckey, James A. Pawelczyk

91 STS-91/Discovery June 2, 1998 – CDR: Charles J. Precourt 

June 12, 1998 PLT: Dominic L. Pudwill-Go

MS: Franklin R. Chang-Diaz

Wendy B. Lawrence, Janet LKavandi, Valery Victorovitch 

Andrew Thomas (returned fr

92 STS-95/Discovery October 29, 1998 – CDR: Curtis L. Brown, Jr. 

November 7, 1998 PLT: Steven W. Lindsey 

MS: Scott E. Parazynski, PePC: Stephen K. Robinson PS: Chiaki Mukai, Sen. John H. Glenn, Jr.

93 STS-88/Endeavour December 4, 1998 – CDR: Robert D. Cabana 

December 15, 1998 PLT: Frederick R. Sturckow 

MS: Jerry L. Ross, Nancy J. James H. Newman, Sergei K

a “USA 40,” NSSDC Master Catalog, Spacecraft, http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1989

Scientists lists this payload as USA 40 - SDS B1, http://www.fas.org/spp/military/program/list.htm (accessed 

b “USA 41,” http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1989-061C (accessed December 22, 2005
c No satellite was listed for this Shuttle launch in NSSDC Master Catalog. The Federation of American Scienti

48–Magnum 2 in the Launch Log of Jonathan’s Space Report, http://planet4589.org/space/log/launchlog.txt (

d “KH 11-10,” http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1990-019B (accessed November 30, 2

Jonathan’s Space Report.

e “USA 67,”http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1990-097B (accessed November 30, 2005

67 - SDS B-2. Listed as USA 67 QUASAR 2 in the Launch Log of Jonathan’s Space Report.

f “USA 75,” http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1991-080B (accessed November 30, 20

Launch Log of Jonathan’s Space Report.

g “USA 89,” http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1992-086B (accessed November 30, 2005

databk7_collected.book Page 375 Monday, September 14, 2009 2:53 PM
Table 3–52. STS-29 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Michael L. Coats

PLT: John E. Blaha

MS: James F. Buchli, Robert C. Springer, 

James P. Bagian

Launch March 13, 1989, 9:57:00 a.m., EST, Kennedy Spa

Center, Pad 39-B. Launch manifested for February 

was reassessed for late February/early March laun

replace suspect liquid oxygen turbopumps on 

Discovery’s three main engines and faulty master e

controller. Launch on March 13 was delayed 1 hou

minutes due to morning ground fog and upper win

Orbital Altitude & 

Inclination 

184 nmi (341 km), 28.45 deg

Launch Weight (lb/kg) 256,357 /116,282 

Landing & Postlanding 

Operations

March 18, 1989, 6:35:51 a.m., PST, Runway 22, 

Edwards Air Force Base. Orbiter returned to Kenn

Space Center March 24, 1989.

Rollout Distance (ft/m) 9,339/2,847 

Rollout Time (seconds) 51 

Mission Duration 119 hr, 38 min, 52 sec

Landed Revolution No. 79 

Mission Support Spaceflight Tracking and Data Network (STDN)

Primary Objective Launch of Tracking and Data Relay Satellite-D

Deployed Satellites Tracking and Data Relay Satellite-D (TDRS-D/IU

designated TDRS-4.

Experiments Orbiter Experiments Autonomous Supporting 

Instrumentation System (OASIS-I): Recorded 

environmental data for the Shuttle’s primary payl

It was configured to interface with TDRS-D (4). 

OASIS-I measured thermal, acoustic, vibration, s

and acceleration parameters of the satellite during 

ascent and other phases of the mission.
Table 3–52. STS-29 Mission Characteristics (Continued)

Experiments Space Station Heat Pipe Advanced Radiator Eleme

(SHARE): SHARE was an attached payload with th

TDRS-D/IUS satellite initiated by the Office of 

Aeronautics and Space Technology (OAST) and 

managed by the Office of Space Station. The OSSA 

performed mission implementation and integration

SHARE was a part of NASA’s Thermal Energy 

Management Processes (TEMP) program, supportin

development of various two-phase heat transport sy

for use on Space Station Freedom or other future sp

missions. SHARE was designed to test and measur

thermal performance of a single high-capacity heat 

radiator element in space and to demonstrate wheth

natural process could serve as a dependable, durabl

cooling system for Space Station Freedom. Althoug

faulty manifold design resulted in early termination 

the experiment, significant data with respect to the d

of spaceborne heat pipes was obtained. 

Air Force Maui Optical System (AMOS) Calibrat

Test: The tests allowed ground-based electro-opti

sensors located on Mt. Haleakala, Maui, Hawaii, 

collect imagery and signature data of the orbiter d

cooperative overflights. The scientific observation

made of the orbiter while performing reaction con

system thruster firings, water dumps, or payload b

light activation were used to support the calibratio

the AMOS sensors and the validation of spacecra

Chromosome and Plant Cell Division in Space 

Experiment (CHROMEX): Sponsored by the Stat

University of New York at Stony Brook. The 

CHROMEX was designed to determine whether t

roots of a plant developed similarly in microgravit

on Earth. One objective was to test whether the no

rate, frequency, and patterning of cell division in t

root tip could be sustained in microgravity. Anoth

objective was to determine whether the fidelity of 

chromosome partitioning was maintained during 

after flight. The CHROMEX used shoots of cell 

culture-derived daylily (Hemerocallis cv. Autumn 

Blaze) and both tissue cultured and seedling clone

haplopappus (Haplopappus gracilis).a
Table 3–52. STS-29 Mission Characteristics (Continued)

Experiments Protein Crystal Growth (PCG): A joint project of 

NASA’s Office of Commercial Programs (OCP) a

OSSA, in conjunction with the Center for 

Macromolecular Crystallography, a NASA OCPsponsored Center for the Commercial Developme

Space (CCDS) at the University of Alabama at 

Birmingham. Scientific methods and commercial 

potential were investigated for growing large, hig

quality protein crystals in microgravity. Proteins w

processed at a “cold” temperature.

IMAX Corporation Camera Experiment (IMAX): 

70-mm motion picture camera system photograph

Earth with particular emphasis on environmentall

threatened areas.

Shuttle Student Involvement Project (SSIP) 82-8—

Effects of Weightlessness in Spaceflight on the He

of Bone Fractures: The project was designed to 

determine if the environmental effects of spaceflig

inhibit bone healing. The subjects were four rats w

small piece of bone removed by a veterinarian fro

non-weight-bearing bone. A similar group of rats 

remained on Earth as a control group. The effects 

zero gravity on the origin, development, and 

differentiation of osteoblasts (bone cells) and thei

production of callus were studied.

SSIP 83-9—Chicken Embryo Development in Sp

This experiment studied the effects of the space 

environment on the development of chicken embr

In the experiment, 32 eggs—16 fertilized two day

before launch and 16 fertilized nine days before 

launch—were placed in an incubator to see if any 

changes in the developing embryo could be attribu

weightlessness. An identical group of 32 eggs rem

on Earth as a control group. On return to Earth, h

each group of eggs were opened and examined to 

identify any differences in cartilage, bone and dig

structures, muscle system, nervous system, facial 

structure, and internal organs. The second half (16 

spaceflight, 16 from control) were hatched 21 day

after fertilization. All embryos fertilized two days 

before being carried into orbit had died. 

Get Away Specials None

Mission Results Successful

a “CHROMEX-01/STS-29: Life Sciences Objectives,” http://lifesci.arc.nasa.gov/lis2/Chapter4_Pr

CHROMEX/CHROMEX_01.html (accessed December 1, 2005).
Table 3–53. STS-30 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: David M. Walker

PLT: Ronald J. Grabe

MS: Mark C. Lee, Norman E. Thagard, Mary L. Cle

Launch May 4, 1989, 2:46:59 p.m. EDT, Kennedy Space Cente

39-B. The April 28 launch was scrubbed at T-31 secon

because of a problem with the liquid hydrogen recircu

pump on the No. 1 main engine and a vapor leak in the 

(10-cm) liquid hydrogen recirculation line between the 

orbiter and the external tank. Repairs were made and la

reset for May 4. Liftoff was delayed until the last 5 mi

of a 64-minute window opening at 1:48 a.m. EDT due 

cloud cover and high winds at the Kennedy Space Cen

Shuttle runway, violating return-to-launch-site limits. 

Orbital Altitude & 

Inclination 

184 nmi (341 km), 28.85 deg

Launch Weight (lb/kg) 261,118/118,441 

Landing & Postlanding 

Operations

May 8, 1989, 12:43:26 p.m. PDT, Runway 22, Edw

Air Force Base. Orbiter returned to Kennedy Space 

Center May 15, 1989.

Rollout Distance (ft/m) 10,295/3,138

Rollout Time (seconds) 64

Mission Duration 96 hr, 57 min, 31 sec

Landed Revolution No. 64

Mission Support STDN

Primary Objective Launch Magellan

Deployed Satellites Magellan/IUS

Experiments FEA: This modular microgravity chemistry/physics 

laboratory was used to process samples of indium in 

float-zone mode. It examined the application of floa

zone processes and their effects on crystal quality. T

apparatus consisted of a heating element that moved 

along a track to melt and recrystallize the sample, w

was sealed in a Pyrex tube. The super 8-mm camera 

computer provided inflight monitoring and data for 

postflight analysis of each test.

MLE: This experiment was used to observe and rec

the visual characteristics of large-scale lightning as 

from space using the on-board cargo bay TV and 35

cameras. 

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful 
Table 3–54. STS-28 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Brewster H. Shaw, Jr.

PLT: Richard N. Richards

MS: James C. Adamson, David C. Leestma, 

Mark N. Brown

Launch August 8, 1989, 8:37:00 a.m., EDT, Kennedy Space 

Center, Pad 39-B. Liftoff occurred during a classifie

launch window within a launch period extending fro

7:30 a.m. to 11:30 a.m., EDT.

Orbital Altitude & 

Inclination 

191 statute mia (166 nmi/307 km), 57 deg

Launch Weight (lb/kg) Classified

Landing & Postlanding 

Operations

August 13, 1989, 6:37:08 a.m., PDT, Runway 17, 

Edwards Air Force Base. Orbiter returned to Kenn

Space Center August 21, 1989.

Rollout Distance (ft/m) 6,015/1,833

Rollout Time (seconds) 46

Mission Duration 121 hr, 0 min, 9 sec

Landed Revolution No. 80

Mission Support STDN

Primary Objective DOD mission

Deployed Satellites SDS 2 (USA 40) and USA 41 military satellitesb

Experimentsc Cosmic Ray Upset Experiment (CRUX)-B

Interim Operational Contamination Monitor (IOCM

The OCM was an automatic operation system for t

measurement of contamination in the payload bay 

the entire mission. The IOCM continuously measu

collected particulate and molecular mass at 

preprogrammed collection surface temperatures.

Multi-Purpose Experiment Canister (MPEC): MPE

was a modified GAS canister containing an ejectab

classified U.S. Air Force Space Systems Division 

experiment.

AMOS Calibration Test: See STS-29.

Cloud Logic to Optimize Use of Defense Systems 

(CLOUDS)-1A: This experiment involved photogra

sequences of cloud fields to correlate space data and 

ground data simultaneously and develop functions 

quantifying the relationship between apparent cloud 

cover and the viewing angle for various cloud forma

Radiation Monitoring Equipment (RME)–III: This 

experiment measured ionizing radiation in the orbi

during sequenced time intervals and digitally store

resulting data.
Table 3–54. STS-28 Mission Characteristics (Continued)

Experimentsd Shuttle Activation Monitor (SAM): The SAM mea

the amounts of gamma rays in the Shuttle’s crew c

Visual Function Tester (VFT)-2: This experiment w

biomedical study to determine the effects of microg

on human visual performance. The experiment exam

the vision of crew members exposed to microgravity 

regard to contrast thresholds, directional perception

pattern sensitivities.

Aerodynamic Coefficient Identification Package 

(ACIP): The package instrumentation included tria

sets of linear accelerometers, angular acceleromete

and angular rate gyros, which sensed the orbiter’s 

motions during flight. ACIP provided the vehicle m

data that was used in conjunction with the Shuttle 

Air Data System (SEADS) environmental informa

for determining aerodynamic characteristics below 

about 300,000 ft altitude.

Get Away Specialse G-0335 

Customer: Naval Postgraduate School

No information submitted on payload.

G-0341

Customer: DOD Space Test Program

No information submitted on payload. 

Mission Results Successful

Remarks DOD mission

a Jenkins, p. 294. Classified mission. No altitude given in NASA sources. b “USA 40,” NSSDC Master Catalog, Spacecraft, http://nssdc.gsfc.nasa.gov/database/MasterCat

=1989-061B (accessed December 1, 2005). The Federation of American Scientists lists this pa

USA 40–SDS B1, http://www.fas.org/spp/military/program/list.htm (accessed July 6, 2005); “U

http://nssdc.gsfc.nasa.gov/database/ScQuery (accessed December 22, 2005). c Experiments were “acknowledged payloads” by the U.S. Air Force according to Jenkins, p. 296

d Experiments were “acknowledged payloads” by the U.S. Air Force according to Jenkins, p. 296

e The First 100 GAS Payloads, NASA Goddard Space Flight Center, Shuttle Small Payloads Pro

108–109.
Table 3–55. STS-34 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Donald E. Williams

PLT: Michael J. McCulley

MS: Shannon W. Lucid, Franklin Chang-Diaz, El

Baker

Launch October 18, 1989, 12:53:40 p.m., EDT, Kennedy S

Center, Pad 39-B. Launch set for October 12 was 

rescheduled due to a faulty main engine controller o

No. 2 main engine. Launch set for October 17 was 

rescheduled due to weather constraints for a return

launch-site landing at the Kennedy Space Center S

Landing Facility.

Orbital Altitude & 

Inclination 

185 nmi (342 km), 34.3 deg

Launch Weight (lb/kg) 257,569/116,831

Landing & Postlanding 

Operations

October 23, 1989, 9:33:00 a.m., PDT, Runway 23

Edwards Air Force Base. The orbiter returned to 

Kennedy Space Center October 29, 1989.

Rollout Distance (ft/m) 9,677/2,950

Rollout Time (seconds) 61

Mission Duration 119 hr, 39 min, 24 sec

Landed Revolution No. 79 

Mission Support STDN

Primary Objective Launch of Galileo

Deployed Satellites Galileo/IUS

Experiments SSBUV Instrument: This experiment compared th

observations of several ozone-measuring instrume

aboard NOAA satellites and other Earth-monitori

spacecraft being flown. SSBUV data was used to 

the calibration of the ozone sounders on these 

spacecraft to ensure the most accurate readings po

for detecting atmospheric ozone trends and verify 

accuracy of the data set of atmospheric ozone and 

irradiance data. The SSBUV used the Space Shut

orbital flight path to assess instrument performan

directly comparing data from identical instrumen

aboard orbiting satellites as the Shuttle and the sa

passed over the same Earth location within a 1-ho

window. These orbital coincidences could occur 1

times per day.
Table 3–55. STS-34 Mission Characteristics (Continued)

Experiments Growth Hormone Concentration and Distribution 

(GHCD) in Plants: This experiment studied the ef

of microgravity on the concentration, turnover 

properties, and behavior of plant growth hormone 

(Auxin) in corn shoot tissue. There were four plan

canisters: two placed into a gaseous nitrogen free

and two were undisturbed.

IMAX Cargo-Bay Camera: This 70-mm motion p

camera system photographed Galileo deployment 

various Earth features.

Student Experiment (SE-82-15)—Zero Gravity G

of Ice Crystals from Supercooled Water With Rel

to Temperature: This student experiment observed 

formation of ice crystals at various supercooled 

temperatures below 0°C (32°F) in a gravity-free 

environment for high-altitude meteorology and 

researched the relationships between water vapor 

saturation and crystal geometry to better understan

absence of gravity.

Polymer Morphology (PM-1): This self-contained 

payload examined the effects of microgravity on 

processing of polymers.

MLE: See STS-30

Sensor Technology Experiment (STEX): This 

dosimetry experiment consisted of a self-containe

battery-powered, automated sensor with an intern

solid state memory. The STEX Investigated natur

background radiation and the radiation from the 

Radioisotope Thermoelectric Generators (RTG).

Experiments AMOS: See STS-29

Get Away Specials None

Mission Results Successful
Table 3–56. STS-33 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Frederick D. Gregory

PLT: John E. Blaha

MS: Manley L. Carter, Jr., F. Story Musgrave, Kat

C. Thornton

Launch November 22, 1989, 7:23:30 p.m. EST, Kennedy S

Center, Pad 39-B. Launch set for November 20 wa

rescheduled to allow the changeout of suspect integ

electronics assemblies on the solid rocket boosters

Orbital Altitude & 

Inclination 

302 nmi (559 km), 28.45 deg

Launch Weight (lb/kg) Classified

Landing & Postlanding 

Operations

November 27, 1989, 4:30:16 p.m. PST, Runway 4

Edwards Air Force Base. Orbiter returned to Kenn

Space Center December 4, 1989.

Rollout Distance (ft/m) 7,764/2,366

Rollout Time (seconds) 46

Mission Duration 120 hr, 6 min, 49 sec

Landed Revolution No. 79

Mission Support STDN

Primary Objective DOD mission

Deployed Satellites Classified military satellitea

Experiments AMOS: See STS-29

Auroral Photography Experiment (APE)-B: The A

experiment photographed the airglow aurora, auro

optical effects, Shuttle glow phenomenon, and thr

emissions.

CLOUDS-I: See STS-28

RME-III: See STS-28

VFT-1: The crew members executed a variety of h

movements with eyes both opened and closed, and 

reported on sensations of movement. The crew 

measured the sensory effects accompanying 

observation of shifting red lights (light-emitting di

on a visual target display.

Get Away Specials Reflight of SD-301, Cosmic Ray Induced Error R

Memory Chips (CRUX Cosmic Ray Upset Experi

Unofficial “classified” GAS.

Mission Results Successful

Remarks DOD mission

a No satellite listed for this Shuttle launch in NSSDC Master Catalog. The Federation of A

Scientists lists this payload as USA 48–Magnum 2. Also listed as USA 48–Magnum 2 in the “

Log of Jonathan’s Space Report,” http://planet4589.org/space/log/launchlog.txt (accessed No

30, 2005).
Table 3–57. STS-32 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Daniel C. Brandenstein

PLT: James D. Wetherbee

MS: Bonnie J. Dunbar, Marsha S. Ivins, G. David 

Launch January 9, 1990, 7:35:00 a.m., EST, Kennedy Spac

Center, Pad 39-A. Launch scheduled for December 

1989, was postponed to complete and verify 

modifications to Pad A, being used for the first tim

since January 1986. The January 8, 1990, launch w

scrubbed due to weather conditions. This was the f

use of Mobile Launch Platform for the Shuttle.

Orbital Altitude & 

Inclination 

178 nmi (330 km), 28.5 deg

Launch Weight (lb/kg) 255,994/116,117

Landing & Postlanding 

Operations

January 20, 1990, 1:35:37 a.m., PST, Runway 22, 

Edwards Air Force Base. Orbiter returned to Kenn

Space Center January 26, 1990.

Rollout Distance (ft/m) 10,731/3,271

Rollout Time (seconds) 64

Mission Duration 261 hr, 0 min, 37 sec

Landed Revolution No. 171

Mission Support STDN

Primary Objective Deployment of SYNCOM IV-F5 and retrieval of L

Deployed Satellites Defense communications satellite SYNCOM IV-F

(also known as LEASAT 5)

Experiments Characterization of Neurospora Circadian Rhythms 

(CNCR): This experiment, sponsored by NASA’s O

Life Sciences Division, determined if Neurospora (

pink bread mold) circadian rhythms persisted in 

microgravity by eliminating most of the exogenous

derived environment cues from Earth. The experim

provided data on endogenously-driven biological cl

that could be applied to other organisms. 

Interim Operational Contamination Monitor (IOCM

See STS-28.

PCG: These were a continuing series of approximate

120 different PCG experiments conducted simultane

using as many as 24 different proteins. See STS-29.

FEA: The apparatus was used to conduct the 

Microgravity Disturbances Experiment. See STS-3

American Flight Echocardiograph (AFE): The AFE 

obtained data on the inflight cardiovascular dynami

the space adaptation process to help develop optim

countermeasures to debilitating effects for reasons 

personal and operational safety.
Table 3–57. STS-32 Mission Characteristics (Continued)

Experiments Latitude/Longitude Locator (L3): The crew conduc

tests to determine the accuracy and usability of the 

system in finding the latitude and longitude of kno

ground sites. Consisted of a modified Hasselblad 

camera equipped with a wide-angle 40-mm lens, a 

camera-computer interface developed by Johnson S

Center engineers, and a Graphics Retrieval and 

Information Display (GRID) 1139 Compass Comp

The crew photographed the same target twice at an 

interval of approximately 15 seconds and fed 

information to the GRID computer, which compute

two possible locations. The crew, by knowing if th

target was north or south of the flight path, could 

determine which of the two locations was correct a

the target’s latitude and longitude.

MLE: See STS-30.

IMAX: This 70-mm motion picture camera system

mounted in the payload bay, was used to photograp

various Earth features.

AMOS Calibration Test: See STS-29.

Shuttle Infrared Leeside Temperature Sensing (SILTS

Mounted on Columbia’s vertical tail, SILTS consisted 

cylindrical housing of approximately 20 in (50.8 cm) 

diameter capped at the leading edge by a hemispheric

dome. Mounted inside the dome was an infrared cam

that obtained high-resolution infrared imagery of the u

(leeside) surfaces of Columbia’s port (left) wing and 

fuselage during entry. The images provided detailed 

temperature maps at the surface of the leeside therma

protection materials and indicated the degree of 

aerodynamic heating of the surface in flight. Columb

computer activated SILTS at about 400,000 ft (121,92

and terminated SILTS after the orbiter passed throug

period of significant aerodynamic heating.a

SEADS: The SEADS nosecap on the Columbia cont

14 penetration assemblies, each containing a small ho

sense the nosecap surface air pressure. Measuremen

the pressure levels and distribution allowed postfligh

determination of vehicle attitude and atmospheric de

during entry. SEADS operated at an altitude range o

280,000 ft (85,344 m) to landing.b

Get Away Specials None

Mission Results Successful

a “STS-32 Press Information, December 1989,” p. 54, http://www.jsc.nasa.gov/history/shuttle_p

FLIGHT_033-STS-032_MRK.pdf (accessed December 20, 2005). b “STS-32 Press Information, December 1989,” p. 56.
Table 3–58. STS-36 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: John O. Creighton

PLT: John H. Casper

MS: David C. Hilmers, Richard M. Mullane, 

Pierre J. Thuot

Launch February 28, 1990, 2:50:22 a.m., EST, Kennedy S

Center, Pad 39-A. Launch set for February 22 was 

postponed to February 23, February 24, and Februa

due to the illness of the crew commander and wea

conditions. Launch set for February 25 was scrubb

due to malfunction of the range safety computer. L

set for February 26 was scrubbed due to weather 

conditions (Note: the external tank was loaded onl

launch attempts on February 25, February 26, and 

launch on February 28). Launch February 28 was s

a classified window lying within a launch period f

midnight to 4 a.m. EST.

Orbital Altitude & 

Inclination 

132 nmi (244 km), 62 deg

Launch Weight (lb/kg) Classified

Landing & Postlanding 

Operations

March 4, 1990, 10:08:44 a.m., PST, Runway 23, 

Edwards Air Force Base. Orbiter returned to Kenn

Space Center on March 13, 1990.

Rollout Distance (ft/m) 7,900/2,408

Rollout Time (seconds) 53

Mission Duration 106 hr, 18 min, 23 sec

Landed Revolution No. 72

Mission Support STDN

Primary Objective DOD mission

Deployed Satellites KH-11-10 (AFP-731)a

Experiments RME-III-12: See STS-28.

VFT-1: See STS-33.

VFT-2: See STS-28.

Get Away Specials None

Mission Results Successful 

Remarks DOD mission

a “KH 11-10,” NSSDC Master Catalog Display: Spacecraft, http://nssdc.gsfc.nasa.gov/d

MasterCatalog?sc=1990-019B (accessed November 29, 2005). Listed as “USA 53, AFP-731 M

in the Launch Log of Jonathan’s Space Report.
Table 3–59. STS-31 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Loren J. Shriver

PLT: Charles F. Bolden, Jr.

MS: Steven A. Hawley, Kathryn D. Sullivan, 

Bruce McCandless, II

Launch April 24, 1990, 8:33:51 a.m. EDT, Kennedy Space 

Center, Pad 39-B. Launch scheduled for April 18, 

April 12, then moved back to April 10 following th

Flight Readiness Review. This was the first time th

date set at a Flight Readiness Review was before th

shown on previous planning schedules. April 10 la

was scrubbed at T-4 minutes due to a faulty valve i

auxiliary power unit (APU) No. 1. The APU was 

replaced and payload batteries were recharged. Th

countdown was briefly halted again at T-31 second

April 24, because computer software failed to shut 

a fuel valve line on ground support equipment. Eng

ordered the valve to shut and countdown continued

Orbital Altitude & 

Inclination 

330 nmi (611 km) at HST deployment, 28.45 deg

Launch Weight (lb/kg) 249,109/112,994

Landing & Postlanding 

Operations

April 29, 1990, 6:49:57 a.m. PDT, Runway 22, Ed

Air Force Base. Orbiter returned to Kennedy Spac

Center on May 7, 1990.

Rollout Distance (ft/m) 8,874/2,705

Rollout Time (seconds) 61

Mission Duration 121 hr, 16 min, 5 sec

Landed Revolution No. 79

Mission Support STDN

Primary Objective Deployment of Hubble Space Telescope 

Deployed Satellites Hubble Space Telescope 

Experiments IMAX Cargo Bay Camera (ICBC): The ICBC 

documented operations outside the crew cabin. Th

used the ICBC to film several Earth observation si

including the country of Botswana, the San Franc

Bay Area, the Andes Mountains in South America

Amazon Rainforest, and Japan.

IMAX Handheld Camera: The crew used the hand

camera for filming inside the crew cabin.
Table 3–59. STS-31 Mission Characteristics (Continued)

Experiments Ascent Particle Monitor (APM): An automatic sys

mounted in the payload bay measured particle 

contamination or particle detachment during the 

immediate prelaunch period and during ascent. It 

consisted of a small box with a fixed door and a m

door mounted in a clamshell arrangement atop an 

aluminum housing. 

PCG III: In a continuing series of experiments, the 

modified Vapor Diffusion Apparatus trays to allow 

hand seeding of the protein solution droplets. See S

RME-III: See STS-28.

Investigations into Polymer Membrane Processing 

(IPMP): The Batelle organization sponsored this 

experiment through the Advanced Materials Center 

Commercial Development of Space, partially funde

NASA. The experiment determined porosity contro

microgravity environment. The objective was to fla

evaporate mixed solvent systems in the absence of 

convection to control the porosity of a polymer mem

SSIP–Investigation of Arc and Ion Behavior in 

Microgravity: This experiment studied the effects 

weightlessness on electrical arcs and observed the 

effects of microgravity on an electric arc in a seale

a aluminum arc chamber box.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful

a Called the Student Science Investigation Project in the STS-31 Press Kit.
Table 3–60. STS-41 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Richard N. Richards

PLT: Robert D. Cabana

MS: Bruce E. Melnick, Thomas D. Akers, William 

Shepherd

Launch October 6, 1990, 7:47:15 a.m. EDT, Kennedy Spac

Center, Pad 39-B. Liftoff occurred 12 minutes after 

hour launch window opened at 7:35 a.m. EDT, Octo

a brief delay was due to weather concerns. An addi

11-second hold occurred at T-5 minutes due to a Gr

Launch Sequencer glitch, and at T-31 seconds, the 

halted for 22 seconds to correct an orbiter purge, ve

drain system glitch.

Orbital Altitude & 

Inclination 

160 nmi (296 km), 28.45 deg

Launch Weight (lb/kg) 259,593/117,749

Landing & Postlanding 

Operations

October 10, 1990, 6:57:18 a.m. PDT, Runway 22, 

Edwards Air Force Base. Orbiter returned to Kenn

Space Center October 16, 1990.

Rollout Distance (ft/m) 8,478/2,584

Rollout Time (seconds) 49

Mission Duration 98 hr, 10 min, 3 sec

Landed Revolution No. 65

Mission Support STDN

Primary Objective Launch of Ulysses

Deployed Satellites Ulysses/IUS/PAM-S

Experiments SSBUV: See STS-34

INTELSAT Solar Array Coupon (ISAC): The ISA

obtained data from the interaction of atomic oxyge

the solar array silver interconnects to assess the 

condition of the INTELSAT spacecraft stranded in 

Earth orbit (see STS-49). 

CHROMEX: See STS-29. 

Voice Command System (VCS): The VCS collecte

on voice command recognition accuracy and oper

the orbiter’s closed-circuit TV system.

Solid Surface Combustion Experiment (SSCE): Th

SSCE studied flame spread in microgravity and 

improved fire safety aspects of space travel.

IPMP: See STS-31.
Table 3–60. STS-41 Mission Characteristics (Continued)

Experiments PSE: The PSE studied the effects of a proprietary p

molecule on animal physiological systems in 

microgravity.

RME-III: See STS-28.

SSIP–Convection in Zero Gravity (SE 81-9): This 

experiment studied surface tension induced flows 

microgravity.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful
Table 3–61. STS-38 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Richard O. Covey

PLT: Frank L. Culbertson, Jr.

MS: Carle J. Meade, Robert C. Springer, Charles 

Gemar

Launch November 15, 1990, 6:48:15 p.m. EST, Kennedy 

Center, Pad 39-A. The launch was originally sche

for July 1990. However, a liquid hydrogen leak fo

on Columbia during the STS-35 countdown prom

three precautionary mini-tanking tests on Atlantis 

pad June 29, July 13, and July 25. Tests confirme

hydrogen fuel leak on the external tank side of the 

external tank/orbiter 17-in (43.1-cm) quick discon

umbilical. With a leak that could not be repaired a

pad; Atlantis was rolled back to the Vehicle Assem

Building (VAB) August 9, demated, and transferr

the Orbiter Processing Facility (OPF). During the 

rollback, the vehicle was parked outside the VAB 

a day while the Columbia/STS-35 stack transferre

the pad for launch. Outside, Atlantis suffered mino

damage to its tiles during a thunderstorm. After re

were made in the OPF, Atlantis transferred to the 

for mating on October 2. During hoisting operatio

platform beam that should have been removed fro

aft compartment fell and caused minor damage tha

repaired. The vehicle rolled out to Pad A on Octob

The fourth mini-tanking test was performed Octob

with no excessive hydrogen or oxygen leakage 

detected. At the Flight Readiness Review, the laun

date was set for November 9. The launch was rese

November 15 due to payload problems. Liftoff occ

during a classified launch window lying within a l

period extending from 6:30 p.m. to 10:30 p.m. ES

November 15.

Orbital Altitude & 142 nmi (262 km), 28.5 deg

Inclination 

Launch Weight (lb/kg) Classified 

Landing & Postlanding November 20, 1990, 4:42:42 p.m. EST, Runway 3

Operations Kennedy Space Center. Mission was extended on

due to unacceptable crosswinds at the original pla

landing site, Edwards Air Force Base. Continued 

adverse conditions led to a decision to shift landin

Kennedy Space Center. It was the first Kennedy S

Center landing for Atlantis and the first end-of-mi

landing at Kennedy Space Center since April 198

Rollout Distance (ft/m) 9,003/2,744
Table 3–61. STS-38 Mission Characteristics (Continued)

Rollout Time (seconds) 57

Mission Duration 117 hr, 54 min, 22 sec

Landed Revolution No. 78

Mission Support STDN

Primary Objective DOD mission

Deployed Satellites USA 67 electronics intelligence satellitea

Experiments None

Get Away Specials None

Mission Results Successful

a “USA 67,”http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1990-097B (accessed Novem

2005). The Federation of American Scientists lists this payload as USA 67–SDS B-2. It is listed 

67 QUASAR 2 in the Launch Log of Jonathan’s Space Report.
Table 3–62. STS-35 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Vance D. Brand

PLT: Guy S. Gardner

MS: John M. Lounge, Jeffrey A. Hoffman, Robert 

Parker

PS: Ronald A. Parise, Samuel T. Durrance

Launch December 2, 1990, 1:49:01 a.m. EST, Kennedy Sp

Center, Pad 39-B. Launch was first scheduled for 

16, 1990. Following the Flight Readiness Review, 

announcement of a firm launch date was delayed t

change out a faulty Freon coolant loop proportion

valve in the orbiter’s coolant system. At a subsequ

Flight Readiness Review, the date was set for May 

Launch on May 30 was scrubbed during tanking du

minor hydrogen leak in the tail service mast on th

mobile launcher platform and a major leak in the 

external tank/orbiter 17-in (43.1-cm) quick discon

assembly. Hydrogen also was detected in the orbite

compartment believed associated with a leak invo

the 17-in (43.1-cm) umbilical assembly.

A mini-tanking test on June 6 confirmed the leak 

17-in (43.1-cm) umbilical. The umbilical could no

repaired at the pad and the orbiter was returned to 

VAB June 12, demated, and transferred to the OPF

Changeout of the orbiter-side 17-in (43.1-cm) umb

assembly was made with one borrowed from 

Endeavour; the external tank was fitted with new 

umbilical hardware. The Astro-1 payload was rese

regularly and remained in Columbia’s cargo bay d

orbiter repairs and reprocessing.
Table 3–62. STS-35 Mission Characteristics (Continued)

Launch Columbia rolled out to Pad A a second time on Au

to support a September 1 launch date. Two days b

launch, the avionics box on the Broad Band X-Ra

Telescope portion of the Astro-1 payload malfunc

and had to be changed out and retested. Launch w

rescheduled for September 6. During tanking, high 

concentrations of hydrogen were detected in the or

aft compartment, forcing another postponement. N

managers concluded that Columbia had experienc

separate hydrogen leaks from the beginning: one o

umbilical assembly (now replaced) and one or mo

the aft compartment that had resurfaced. Suspicio

focused on a package of three hydrogen recirculat

pumps in the aft compartment. These were replace

retested. A damaged Teflon cover seal in the main 

engine No. 3 hydrogen prevalve was replaced. Lau

was rescheduled for September 18. A fuel leak in 

compartment resurfaced during tanking and the m

was scrubbed again. The STS-35 mission was put 

hold until problems were resolved by a special tig

team assigned by the Space Shuttle director.

Columbia transferred to Pad B October 8, to make 

for Atlantis on STS-36. Tropical Storm Klaus forc

rollback to the VAB on October 9. The vehicle 

transferred to Pad B again October 14. A mini-tank

test was conducted on October 30 using special sen

and video cameras and employing a see-through 

Plexiglas aft compartment door. No excessive hydr

leakage was detected. Liftoff December 2 was dela

21 minutes to allow Air Force range time to observ

level clouds that might impede tracking of Shuttle 

Orbital Altitude & 190 nmi (252 km), 28.45 deg

Inclination 

Launch Weight (lb/kg) 256,385/116,294

Landing & Postlanding December 10, 1990, 9:54:08 p.m. PST, Runway 2

Operations Edwards Air Force Base. Mission was cut short on

due to impending bad weather at the primary land

site, Edwards Air Force Base. The orbiter returned 

Kennedy Space Center on December 20, 1990.

Rollout Distance (ft/m) 10,450/3,185

Rollout Time (seconds) 58

Mission Duration 215 hr, 5 min, 8 sec

Landed Revolution No. 143

Mission Support STDN

Primary Objective Astrophysics observations using Astro-1

Deployed Satellites None
Table 3–62. STS-35 Mission Characteristics (Continued)

Experiments Astro-1: An observatory consisting of four telesco

Hopkins Ultraviolet Telescope (HUT), Wisconsin 

Ultraviolet Photo-Polarimeter Experiment (WUPP

Ultraviolet Imaging Telescope (UIT), and Broad B

X-Ray Telescope (BBXRT)—all designed for rou

the-clock observations of the celestial sphere in th

ultraviolet and x-ray ranges.a Ultraviolet telescope

mounted on the Spacelab instrument pointing syst

carried on pallets in the cargo bay. Loss of both da

display units (used for pointing telescopes and ope

experiments) during the mission impacted crew-ai

procedures and forced ground teams at Marshall S

Flight Center to aim the ultraviolet telescopes with 

tuning by the flight crew. 

• HUT: This telescope studied faint astronomical o

such as quasars, active galactic nuclei, and super

remnants in the little-explored ultraviolet range b

1200 angstroms. The telescope Observed the ou

planets of the solar system to investigate auroras 

gained insight into the interaction of each planet

magnetosphere with the solar wind.

• WUPPE: This experiment measured the polariza

of ultraviolet light from celestial objects such as 

stars, galactic nuclei, and quasars.

• UIT: This telescope investigated the present stel

content and history of star formation in galaxies

nature of spiral structure, and non-thermal sourc

galaxies.

• BBXRT: This telescope studied various targets, 

including active galaxies, clusters of galaxies, 

supernova remnants, and stars. The BBXRT dire

measured the amount of energy in electron volts 

each x-ray detected.

Orbiter Experiments Program (OEX): The OEX w

developed to perform flight experiments on a full-

lifting vehicle:

• SEADS. See STS-32.
Table 3–62. STS-35 Mission Characteristics (Continued)

Experiments • Shuttle Upper Atmosphere Mass Spectrometer (SU

The SUMS complemented SEADS by enabling 

measurement of atmospheric density above 300,0

(91,440 m). The SUMS sampled air through a sma

on the lower surface of the vehicle aft of the nosec

used a mass spectrometer operating as a pressuresensing device to measure atmospheric density in 

high altitude and rarefied flow regime where the 

pressure was too low to use ordinary pressure sen

The mass spectrometer, incorporated in the SUMS 

experiment, was spare equipment originally devel

for the Viking Mars Lander. 

• ACIP. See STS-28.

• High Resolution Accelerometer Package (HiRA

This instrument was a three-axis set of highly sen

accelerometers that measured vehicle motions d

the high altitude portion (above 300,000 ft) (91,4

of entry. This instrument provided the companio

vehicle motion data to be used with the SUMS r

HiRAP had flown on previous missions of the or

Columbia and Challenger.

• SILTS: This experiment used a scanning infrared 

radiometer located atop the vertical tail to collect 

infrared images of the orbiter’s leeside (upper) sur

during entry, for the purpose of measuring the 

temperature distribution and the aerodynamic hea

environment. On STS-32, the experiment obtained 

images of the left wing. For STS-35 and STS-40, 

experiment was configured to obtain images of the 

fuselage. SILTS had flown on four Columbia fligh

Shuttle Amateur Radio Experiment-2 (SAREX-2)

SAREX-2 communicated with amateur radio stati

within line-of-sight of the orbiter in voice mode o

mode. 

AMOS Calibration Test: See STS-29.

The Shuttle crew conducted a Space Classroom Pr

called “Assignment–The Stars,” to spark student in

in science, math, and technology.
Table 3–62. STS-35 Mission Characteristics (Continued)

Experiments • Aerothermal Instrumentation Package (AIP): The 

Comprised about 125 measurements of aerodyna

surface temperature and pressure at discrete locat

on the upper surface of the orbiter’s left wing, fus

and vertical tail. These sensors were originally pa

the development flight instrumentation system tha

aboard Columbia during its Orbital Flight Test mi

(STS-1 through STS-5). They were reactivated th

an AIP-unique data handling system. Among oth

applications, the AIP data provided “ground-truth

information for the SILTS experiment. The AIP h

flown on previous Columbia flights.

Get Away Specials None

Mission Results Marshall and Goddard Space Flight Centers estim

that 70 percent of the planned science data was acq

Other mission objectives were achieved.

The crew experienced trouble dumping waste wat

to a clogged drain, they were able to use spare 

containers.

a See chapter 4, Space Science, of this volume for further discussion of the Astro-1 mission.
Table 3–63. STS-37 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Steven R. Nagel

PLT: Kenneth D. Cameron

MS: Linda M. Godwin, Jerry L. Ross, Jay Apt

Launch April 5, 1991, 9:22:44 a.m. EST, Kennedy Space 

Center, Pad 39-B. Launch set for April 5, 9:18 a.m

briefly delayed due to low-level clouds in the area

Orbital Altitude & 

Inclination 

248 nmi (459 km), 28.453 deg

Launch Weight (lb/kg) 255,824/116,040

Landing & Postlanding 

Operations

April 11, 1991, 6:55:29 a.m. PDT, Runway 33, 

Edwards Air Force Base. Landing was originally 

scheduled for April 10 but was delayed one day d

weather conditions at Edwards Air Force Base an

Kennedy Space Center.

Rollout Distance (ft/m) 6,364/1,940

Rollout Time (seconds) 56

Mission Duration 143 hr, 32 min, 44 sec

Landed Revolution No. 93

Mission Support STDN

Primary Objective Deployment of the Gamma Ray Observatory

Deployed Satellites Gamma Ray Observatory

Experiments APM: See STS-31.

SAREX II: See STS-35. 

PCG: A continuing series of experiments, the STS

set of PCG experiments used the batch process an

flew in a new hardware configuration, the Protein 

Crystallization Facility, developed by the PCG 

investigators. See STS-29.

Bioserve/Instrumentation Technology Associates 

Materials Dispersion Apparatus (BIMDA): The 

BIMDA gathered data by mixing fluids in the 

microgravity of space.

RME-III: See STS-28.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful
Table 3–63. STS-37 Mission Characteristics (Continued)

Remarks Astronauts Ross and Apt performed an unschedul

contingency spacewalk to manually deploy the GR

high-gain antenna. Although the GRO was designe

servicing by the Shuttle, an early mishap with its 

propulsion system and the later failure of one of it

gyroscopes made this impossible. It was brought d

in a controlled reentry on June 4, 2000.

Crew and Equipment Translation Aids (CETA): R

and Apt performed a scheduled 6-hour spacewalk 

test a method for astronauts to move themselves a

equipment while maintaining Space Station Freed
Table 3–64. STS-39 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Michael L. Coats

PLT: L. Blaine Hammond, Jr.

MS: Gregory J. Harbaugh, Donald McMonagle, G

S. Bluford, Jr., Charles Lacy Veach, Richard J. Hi

Launch April 28, 1991, 7:33:14 a.m. EDT, Kennedy Spac

Center, Pad 39-A. The launch was originally sche

for March 9, but, during processing work at Pad A

significant cracks were found on all four lug hinge

the two external tank umbilical door drive mechan

NASA managers opted to roll back the vehicle to 

VAB on March 7 and then to the OPF for repair. H

were replaced and reinforced with units taken from 

orbiter Columbia. Discovery returned to the launc

April 1, and launch was reset for April 23. The mi

was again postponed when, during prelaunch exte

tank loading, a transducer on the high-pressure ox

turbopump for main engine No. 3 showed reading

of specification. The transducer and its cable harn

were replaced and tested. Launch was rescheduled 

April 28.

Orbital Altitude & 

Inclination

140 nmi (259 km), 57.007 deg

Launch Weight (lb/kg) 247,373

Landing & Postlanding 

Operations

May 6, 1991, 2:55:35 p.m. EDT, Runway 15, Ken

Space Center. Landing diverted to Kennedy Space 

Center because of unacceptably high winds at the 

planned landing site, Edwards Air Force Base.

Rollout Distance (ft/m) 9,234/2,815

Rollout Time (seconds) 56

Mission Duration 199 hr, 22 min, 22 sec

Landed Revolution No. 133

Mission Support STDN

Primary Objective Unclassified DOD mission with multiple payload

Deployment Satellites Released and retrieved the SPAS-II
Table 3–64. STS-39 Mission Characteristics (Continued)

Experiments Air Force Program-675 (AFP-675): AFP-675 was 

collection of scientific instruments observing targ

such as the atmosphere and the aurora and stars in 

infrared, far ultraviolet, ultraviolet, and x-ray 

wavelengths. AFP-675 instruments also analyzed 

spectrum of various targets and gases released fro

around the Shuttle. 

Cryogenic Infrared Radiance Instrumentation for 

Shuttle (CIRRIS): The CIRRUS measured infrare

characteristics of atmospheric emissions.

Critical Ionization Velocity (CIV): This experime

released four pressure vessels mounted in the pay

bay. Each vessel contained a non-hazardous gas. 

Instruments on SPAS-II observed the resultant gas 

plume effect.

Chemical Release Observation (CRO): The CRO 

deployed three subsatellites. Each subsatellite rele

different chemical. SPAS-II, ground, and airborne 

scientific instruments observed the resulting cloud

MPEC: See STS-28.a

RME-III: See STS-28.

CLOUDS-I: See STS-28.

Space Test Payload-1 (STP-1): This payload cons

of a varied collection of scientific instruments. On

instrument observed the luminous “airglow” effec

atomic oxygen on Discovery; a second instrument 

tested a new method of flowing rocket propellants 

weightlessness to assist in the design of future eng

and a third instrument observed the fringes of Ear

atmosphere at various times, including sunrise and 

sunset, in ultraviolet wavelengths.

Get Away Specials None

Mission Results Successful

Remarks Unclassified DOD mission. Work with payloads d

the flight involved extensive maneuvering, rendez

and proximity operations by Discovery. 

a The STS-39 Mission Chronology called this experiment the “Multi-Purpose Release Caniste

seems to be an error in that the STS-39 Press Kit and the biography of astronaut Guion Blufo

released the experiment, called it the “Multi-Purpose Experiment Canister.” MPEC also s

“Multi-Purpose Experiment Canister” in other missions where it was deployed. 
Table 3–65. STS-40 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Bryan D. O’Connor

PLT: Sidney M. Gutierrez

MS: James P. Bagian, Tamara E. Jernigan, Marga

Rhea Seddon 

PS: F. Drew Gaffney, Millie Hughes-Fulford

Launch June 5, 1991, 9:24:51 a.m. EDT, Kennedy Space 

Center, Pad 39-B. Launch was originally set for M

22, 1991. The mission was postponed less than 48 

before launch when it became known that a leakin

liquid hydrogen transducer in the orbiter main 

propulsion system, which had been removed and 

replaced during leak testing in 1990, had failed an 

analysis by the vendor. Engineers feared that one 

more of the nine liquid hydrogen and liquid oxyg

transducers protruding into fuel and oxidizer lines 

break off and be ingested by the engine turbopum

causing engine failure.

In addition, one of the orbiter’s five general purpo

computers failed completely, along with one of th

multiplexer demultiplexers that controlled orbiter 

hydraulics ordinance and orbiter maneuvering sys

reaction control system functions in the aft 

compartment.

A new general purpose computer and multiplexer 

demultiplexers were installed and tested. One liqu

hydrogen and two liquid oxygen transducers were 

replaced upstream in the propellant flow system n

the 17-in (43.1-cm) disconnect area, which was 

protected by an internal screen. Three liquid oxyg

transducers were replaced at the engine manifold 

while three liquid hydrogen transducers were rem

and the openings plugged. The launch was reset f

a.m. EDT, June 1, but it was postponed again afte

several failed attempts to calibrate inertial measur

unit No. 2. The unit was replaced and retested, an

launch was rescheduled for June 5. 

Orbital Altitude & 157 nmi (291 km), 39.0156 deg

Inclination

Launch Weight (lb/kg) 251,970/114,292

Landing & Postlanding June 14, 1991, 8:39:11 a.m. PDT, Runway 22, Ed

Operations Air Force Base. Orbiter returned to Kennedy Spa

Center June 21.

Rollout Distance (ft/m) 9,438/2,877

Rollout Time (seconds) 55
Table 3–65. STS-40 Mission Characteristics (Continued)

Mission Duration 218 hr, 14 min, 20 sec

Landed Revolution No. 145

Mission Support STDN

Primary Objective SLS-1 mission

Deployed Satellites None

Experiments SLS-1 using the Spacelab long module: The tests 

subjects were humans, 30 rodents, and thousands 

jellyfish. The primary SLS-1 experiments studied 

body systems. The body systems investigated wer

cardiovascular/ cardiopulmonary (heart, lungs and 

vessels); 2) renal/endocrine (kidneys and hormone

secreting organs and glands); 3) blood (blood plas

4) immune system (white blood cells); 5) 

musculoskeletal (muscles and bones); and 6) 

neurovestibular (brains and nerves, eyes, and inne

Of the 18 investigations, 10 involved humans, 7 inv

rodents, and 1 used jellyfish. The experiments wer

• Influence of Weightlessness Upon Human Auton

Cardiovascular Controls

• In-flight Study of Cardiovascular Deconditionin

• Vestibular Experiments in Spacelab

• Protein Metabolism During Spaceflight

• Fluid-Electrolyte Regulation During Spacefligh

• Pulmonary Function During Weightlessness

• Lymphocyte Proliferation in Weightlessness

• Influence of Spaceflight on Erythrokinetics in M

• Cardiovascular Adaptation to Microgravity

• Pathophysiology of Mineral Loss During Space

• Regulation of Erythropoiesis During Spacefligh

• Regulation of Blood Volume During Spacefligh

• Bone, Calcium, and Spaceflight

• A Study of the Effects of Space Travel on Mamm

Gravity Receptors

• Effects of Microgravity-Induced Weightlessnes

Aurelia Ephyra Differentiation and Statolith 

Synthesis

• Skeletal Myosin Isoenzymes in Rats Exposed to 

Microgravity

• Effects of Microgravity on Biochemical and 

Metabolic Properties of Skeletal Muscle in Rats

• The Effects of Microgravity on the Electron 

Microscopy, Histochemistry, and Protease Activ

of Rat Hind-limb Muscles
Table 3–65. STS-40 Mission Characteristics (Continued)

Experiments Orbital Acceleration Research Experiment (OAR

This experiment was designed to accurately meas

aerodynamic acceleration rates in zero gravity to 

expand the database of knowledge in predicting o

drag in the design of future space systems like Sp

Station Freedom.

Middeck Zero-Gravity Dynamics Experiment (MO

This experiment studied the behavior of space stru

and contained fluids in microgravity. Scale models 

truss beams for large space structures of the future 

attached to a vibrating device to analyze the stresse

developed. Fluid slosh forces, in a partially filled 

container, were measured during vibration. The re

yielded insight into developing efficient technique

fluid transfer in space.

OEX: The OEX program provided a mechanism f

flight research experiments to be developed and f

aboard a Space Shuttle orbiter. Since the program

inception, 13 experiments were developed for flig

Principal investigators for these experiments 

represented Langley and Ames Research Centers

Johnson Space Center, and Goddard Space Flight 

Center. Seven OEX experiments flew on STS-40. 

Included among this group were six experiments 

conceived by Langley researchers and one experi

developed by Johnson.

• SEADS: See STS-32.

• SUMS: See STS-35. 

Both SEADS and SUMS provided entry atmosp

environmental (density) information. This data, 

combined with vehicle motion data, was used to 

determine in-flight aerodynamic performance 

characteristics of the orbiter.

• ACIP: See STS-28.

• HiRAP: See STS-35.

• SILTS: This experiment used a scanning infrare

radiometer located atop the vertical tail to collec

infrared images of the orbiter’s leeside (upper) 

surfaces during entry, for the purpose of measur

the temperature distribution and the aerodynam

heating environment. On STS-32, the experime

obtained images of the left wing. For STS-35 an

STS-40, the experiment was configured to obtai

images of the upper fuselage. SILTS had flown 

four Columbia flights. 

• AIP: See STS-35.
Table 3–65. STS-40 Mission Characteristics (Continued)

Get Away Specials Twelve GAS canisters were installed on the GAS 

bridge in the cargo bay for experiments in materia

science, plant biology, and cosmic radiation.

G-021

Customer: ESA 

Solid State Microaccelerometer Experiment: This 

experiment tested a new kind of very sensitive, hi

miniaturized accelerometers intended for applicat

on a number of ESA space missions. 

G-052 

Customer: GTE Laboratories, Inc.

Experiment in Crystal Growth: This experiment gr

two crystals of gallium arsenide (GaAs). Growth o

two crystals in space was part of a comprehensive 

research program to systematically investigate the 

of gravity-driven fluid flow on GaA crystal growth

G-091

Customer: CSUN Aerospace Group

Orbital Ball Bearing Experiment: A team of resear

from California State University, Northridge (CSU

built an apparatus called the Orbital Ball Bearing 

Experiment (OBBEX) to test the effects of melting 

cylindrical metal pellets in microgravity. If success

this experiment might produce a new type of ball b

G-105 

Customer: Alabama Space & Rocket Center

In-Space Commercial Processing: Scientists at th

University of Alabama in Huntsville (UAH) used 

experiments to study possible commercial in-spac

processing opportunities.

Two experiment packages in the canister processed 

organic films and crystals that might be used in op

communications and computers. A third investigat

electroplated metals to study special catalytic or re

properties, or resistance to corrosion. A fourth 

experiment studied technology used to refine and p

organic materials such as medical samples. The fif

experiment collected cosmic ray interactions on fil

emulsion while helping scientists assess materials 

might be used in future massive cosmic ray detecto

be flown on the Shuttle or Space Station Freedom 

determine exposure to energetic particles on Earth

The U.S. Space and Rocket Center provided the si

experiment which studied the effects of cosmic rad

on the chromosomes and genes of a common yeas
Table 3–65. STS-40 Mission Characteristics (Continued)

Get Away Specials G-286

Customer: OMNI International, Ltd., and Duke 

University

Foamed Ultralight Metals: This experiment 

demonstrated the feasibility of producing, in orbi

foams of ultralight metals for possible application 

shock-absorbing panel-backing to improve the 

shielding of both crewed and uncrewed vehicles a

satellites, including Space Station Freedom, again

hypervelocity impacts either from micrometeroid

orbiting debris.

G-405 

Customer: Frontiers of Science Foundation

Chemical Precipitate Formation: This experiment 

returned data on the formation of six insoluble 

inorganic chemical precipitates. The experiment 

investigated the rate of formation and terminal siz

precipitate particles when the growth was unimpa

by settling due to gravity.

G-408 

Customer: The Mitre Corporation

Five Microgravity Experiments: One GAS can 

contained five student experiments from the Worc

Polytechnic Institute. One attempted to grow larg

zeolite crystals. Another studied the behavior of f

in microgravity. A third, the Environmental Data 

Acquisition System, recorded information about s

light, temperature, and pressure within the GAS c

The fourth measured Shuttle acceleration along th

axes with a high degree of precision. A fifth exper

studied the fogging of film in space.

G-451

Customer: Nissho Iwai American

Flower and Vegetable Seeds Exposure to Space: S

Seeds Corp. in Yokohama, Japan, and the Nissho 

American Corp. in New York, New York, jointly 

19 varieties of flower and vegetable seeds into sp

determine how the unknown variables of microgr

affected seed growth. After the Shuttle landed and 

seeds were recovered, the companies distributed t

seeds to amateur growers. 
Table 3–65. STS-40 Mission Characteristics (Continued)

Get Away Specials G-455 

Customer: Nissho Iwai American

Semiconductor Crystal Growth Experiment: 

Investigated the potential advantages of crystal gr

under microgravity. There were two experiments: 

PbSnTe crystal growth from vapor and GaAs crys

growth from metallic solution. This payload was 

sponsored by Fujitsu Ltd. in Kawasaki, Japan, an

Nissho Iwai Corp. in Tokyo, Japan. 

G-507 

Customer: Goddard Space Flight Center

Orbiter Stability Experiment: This experiment 

measured the Space Shuttle’s spectrum of small an

motions (or “jitter”) produced by the operation of 

mechanical systems, thruster firings, and human 

motions during normal crew activity. In addition t

vibration measurements made, Goddard’s GAS ca

carried a passive experiment to test the effects of 

radiation on photographic film. 

G-616

Customer: Thomas Hancock

The Effect of Cosmic Radiation on Floppy Disks 

Plant Seeds Exposure to Microgravity: This paylo

consisted of two experiments. The first investigat

static computer memory (floppy disks) to determi

cosmically charged particles produced changes in 

integrity or structure. The second looked for chan

the physiology or growth of 38 different types of 

seeds. Each cultivator was examined postflight an

compared with samples from the same seed lot th

remained on Earth for a wide variety of possible e

or changes.

Several of the floppy disks contained programs 

developed by elementary school students. In addit

large number of plant seeds were distributed to ev

elementary and junior high school student in the 

Redlands, California, Unified School District, the 

sponsor of the experiment. 

G-486

Sponsor: EDSYN, Inc., Van Nuys, California 

Six Active Soldering Experiments

Mission Results Successful

Remarks This was the first mission dedicated solely to life 

sciences using the Spacelab habitable module. 
Table 3–66. STS-43 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: John E. Blaha

PLT: Michael A. Baker

MS: Shannon W. Lucid, James C. Adamson, G. D

Low

Launch August 2, 1991, 11:01:59 a.m. EDT, Kennedy Spa

Center, Pad 39-A. Launch was originally set for Ju

but was moved to July 24 to allow time to replace 

faulty integrated electronics assembly that controll

orbiter/external tank separation. The mission was 

postponed again about 5 hours before liftoff on Ju

due to a faulty main engine controller on the No. 3 

engine. The controller was replaced and retested; l

was reset for August 1. Liftoff set for 11:01 a.m. w

delayed and postponed because of a cabin pressure 

valve reading at 12:28 p.m. due to unacceptable we

at the return-to-launch-site location. Launch was r

for August 2.

Orbital Altitude & 

Inclination

174 nmi (322 km), 28.45 deg

Launch Weight (lb/kg) 259,374/117,650

Landing & Postlanding 

Operations

August 11, 1991, 8:23:25 a.m. EDT, Runway 15, 

Kennedy Space Center.

Rollout Distance (ft/m) 9,890/3,014

Rollout Time (seconds) 60

Mission Duration 213 hr, 21 min, 22 sec

Landed Revolution No. 142

Mission Support STDN

Primary Objective Deployment of TDRS-E

Deployed Satellites TDRS-5/IUS

Experiments SHARE II: This experiment demonstrated microgr

thermal vacuum performance of a heat pipe radiato

heat rejection.

SSBUV Instrument: See STS-34.

Tank Pressure Control Equipment (TPCE): This 

experiment determined the effectiveness of jet mix

for controlling tank pressures and equilibrating flu

temperatures.

Optical Communications Through Windows (OCT

This experiment demonstrated the optical transmis

of data from the crew cabin to the payload bay.

APE-B: See STS-33.
Table 3–66. STS-43 Mission Characteristics (Continued)

Experiments PCG III: Part of a continuing series of experiment

mission’s experiments were conducted using bovin

insulin. See STS-29.

BIMDA: See STS-37.

IPMP: See STS-31.

Space Acceleration Measurement System (SAMS)

SAMS provided acceleration data to characterize t

middeck and/or middeck-mounted experiments 

acceleration environment.

SSCE: See STS-41.

Ultraviolet Plume Imager (UVPI): No flight hardw

the orbiter was used as a calibration target for spac

based ultraviolet sensors.

AMOS Calibration Test: See STS-29. 

Get Away Specials None

Mission Results Successful
Table 3–67. STS-48 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: John O. Creighton

PLT: Kenneth S. Reightler, Jr.

MS: James F. Buchli, Charles D. Gemar, Mark N

Brown

Launch September 12, 1991, 7:11:04 p.m. EDT, Kennedy 

Space Center, Pad 39-A. Launch was delayed 14 

minutes by a faulty communication link between 

Kennedy Space Center and Mission Control in 

Houston.

Orbital Altitude & 

Inclination

313 nmi (580 km), 57 deg

Launch Weight (lb/kg) 240,062/108,890

Landing & Postlanding 

Operations

September 18, 1991, 12:38:42 a.m. PDT, Runway 

Edwards Air Force Base. Landing was scheduled 

Kennedy Space Center but was diverted to Edwar

due to bad weather. Orbiter returned to Kennedy S

Center September 26, 1991.

Rollout Distance (ft/m) 9,384/2,860

Rollout Time (seconds) 50

Mission Duration 128 hr, 27 min, 34 sec

Landed Revolution No. 80

Mission Support STDN

Primary Objective Deployment of the UARS

Deployed Satellites UARS 

Experiments APM: See STS-31.

MODE: See STS-40.

SAM: See STS-28. 

Cosmic Ray Effects and Activation Monitor 

(CREAM): The monitor collected data on cosmic 

energy loss spectra, neutron fluxes, and induced 

radioactivity. The data was obtained from the sam

locations used to gather data for the SAM experim

in an attempt to correlate data between the two.
Table 3–67. STS-48 Mission Characteristics (Continued)

Experiments Physiological and Anatomical Rodent Experimen

(PARE): First in a series of planned experiments, 

physiological and developmental adaptation to 

microgravity, the PARE-01 experiment examined 

changes caused by exposure to microgravity in an

gravity muscles (used for movement) and in tissue

involved in movement. Eight young, healthy rats 

on the Shuttle. After flight, full ground studies ho

an identical group of animals under identical cond

(except for the presence of gravity) were conduct

Both groups were housed in self-contained anima

enclosure modules that provided food, water, and 

environmental control throughout the flight. The 

experiment’s design and intent received the review 

approval of the animal care and use committees at 

NASA and the University of Arizona. Laboratory 

animal veterinarians oversaw the selection, care, a

handling of the rats. Following the flight, the prin

investigator thoroughly evaluated the rat tissues. 

PCG II-2: A continuation of earlier studies, PCG 

investigated processes for growing large protein 

crystals in space. This experiment consisted of 60 

vapor diffusion crystal growth chambers. See STS

IPMP: See STS-31.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful
Table 3–68. STS-44 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Frederick D. Gregory

PLT: Terence T. Henricks

MS: F. Story Musgrave, Mario Runco, Jr., James S

PS: Thomas J. Hennen

Launch November 24, 1991, 6:44:00 p.m. EST, Kennedy 

Center, Pad 39-A. Launch set for November 19 w

delayed due to a malfunctioning redundant inertia

measurement unit on the IUS booster attached to t

DSP satellite. The unit was replaced and tested. L

was reset for November 24 but was delayed for 13 

minutes to allow an orbiting spacecraft to pass and 

allow external tank liquid oxygen replenishment a

minor repairs to the valve in the liquid oxygen 

replenishment system in the mobile launcher platf

Orbital Altitude & 

Inclination

197 nmi (365 km), 28.5 deg

Launch Weight (lb/kg) 259,629/117,766

Landing & Postlanding 

Operations

December 1, 1991, 2:34:44 p.m. PST, Runway 5, 

Edwards Air Force Base. Landing was originally 

scheduled for Kennedy Space Center on Decembe

but the 10-day mission was shortened and landing 

rescheduled following the November 30 on-orbit f

of one of the three orbiter inertial measurement un

Lengthy rollout was due to minimal braking for te

Rollout Distance (ft/m) 11,191/3,411

Rollout Time (seconds) 107

Mission Duration 166 hr, 50 min, 42 sec

Landed Revolution No. 109

Mission Support STDN

Primary Objective Unclassified DOD mission; deployment of DSP s

Deployed Satellites DSP F16/IUS (USA 75)a

Experiments IOCM: See STS-28.

Terra Scout: To evaluate the effectiveness of real-tim

visual observation of terrestrial and oceanic targets, 

observational and analytical skills of a photointerpre

specialist were compared with earthbound observat

technology of designated targets. Results aided in th

development of autonomous sensors.
Table 3–68. STS-44 Mission Characteristics (Continued)

Experiments Military Man in Space (M88-1): To evaluate the 

effectiveness of real-time visual observations of 

terrestrial and oceanic targets, a crew member use

optical camera systems to attempt to identify vario

military-related activities such as ship wakes; truc

convoys; armored formations; aircraft operations; 

clouds; and smoke.

AMOS Calibration Test: See STS-29.

CREAM: See STS-48.

SAM: See STS-28.

RME-III: See STS-28.

VFT-1: See STS-33.

Extended Duration Orbiter Medical Project: To 

investigate countermeasures to orthostatic intolera

problems, this experiment used fluid loading, in w

crew members ingested salt tablets and water and 

the Lower Body Negative Pressure (LBNP) device

LBNP created a partial vacuum around the lower 

returning some of the fluids to the legs.

UVPI: See STS-43.

Bioreactor Flow and Particle Trajectory (BFPT) in 

Microgravity: This fluid dynamics experiment val

Earth-based predictions for the action of cell cultu

the NASA-developed Slow-Turning Lateral Vesse

(STLV) bioreactor. Researchers were interested in 

benefits of flying a bioreactor in space because of 

expected increased capabilities for cell culturing. 

STLV bioreactor, developed as a tool for Space St

Freedom, grew cell cultures in a horizontal cylind

container that slowly rotated, emulating micrograv

and keeping the cells continuously suspended whi

bathing them in nutrients and oxygen. Component

the NASA bioreactor occupied two middeck locke

Get Away Specials None

Mission Results Successful

Remarks Unclassified DOD mission

Ten-day mission was shortened to seven days beca

the on-orbit failure of one of the three orbiter iner

measurement units. Despite the early return, most 

mission objectives were achieved.b

a “USA 75,” http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1991-080B (accessed Nove

2005). Also listed in the Federation of American Scientists list of military satellites and the Lau

of Jonathan’s Space Report. b “STS-44 Mission Summary,” Spacelink Cached Web site, http://spacelink.nasa.gov/NASA.

Human.Exploration.and.Development.of.Space/Human.Space.Flight/Shuttle/Shuttle.Missions/

Flight.044.STS-44/Mission.Summary (cached site accessed December 14, 2005).
Table 3–69. STS-42 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Ronald J. Grabe

PLT: Stephen S. Oswald

MS: Norman E. Thagard, David C. Hilmers, Willi

Readdy

PS: Roberta L. Bondar (Canadian Space Agency/C

Ulf D. Merbold (ESA)

Launch January 22, 1992, 9:52:33 a.m. EST, Kennedy Spa

Center, Pad 39-A. Launch was delayed 1 hour due 

weather conditions. 

Orbital Altitude & 

Inclination

163 nmi (302 km), 57 deg

Launch Weight 243,396/110,403

Landing & Postlanding 

Operations

January 30, 1992, 8:07:17 a.m. PST, Runway 22, 

Edwards Air Force Base. The mission was extende

day for continued scientific experimentation. Orbite

returned to Kennedy Space Center on February 16, 

Rollout Distance (ft/m) 9,841/3,000

Rollout Time (seconds) 58

Mission Duration 193 hr, 14 min, 44 sec

Landed Revolution No. 128

Mission Support STDN

Primary Objective Conduct life sciences research with the IML-1

Deployed Satellites None

Experiments IML-1: Working in a pressurized Spacelab long m

the international crew, divided into red and blue te

conducted experiments on the human nervous syst

adaptation to low gravity and the effects of microg

on other life forms such as shrimp eggs, lentil seed

fruit fly eggs, and bacteria. Low gravity materials 

processing experiments included crystal growth fr

variety of substances such as enzymes, mercury io

and a virus.

IML-1 Life Science Experiments

• Biorack 

– Leukemia Virus Transformed Cells to Microg

in the Presence of Dimethylsulfoxide (DMSO

– Proliferation and Performance of Hybridoma 

in Microgravity (HYBRID)

– Dynamic Cell Culture System (CULTURE)
Table 3–69. STS-42 Mission Characteristics (Continued)

Experiments – Chondrogenesis in Micromass Cultures of Mo

Limb Mesenchyme Exposed to Microgravity 

(CELLS) 

– Effects of Microgravity and Mechanical Stimu

on the In-Vitro Mineralization and Resorption 

Fetal Mouse Bones (BONES)

– Why Microgravity Might Interfere With Amp

Egg Fertilization and the Role of Gravity in 

Determination of the Dorsal/Ventral Axis in 

Developing Amphibian Embryos (EGGS)

– Effects of Space Environment on the Developm

Drosophila Melanogaster (FLY)

– Genetic and Molecular Dosimetry of HZE Rad

(RADIAT)

– Dosimetric Mapping Inside Biorack (DOSIMTR

– Embryogenesis and Organogenesis of Carausi

(MOROSUS)

– Gravity-Related Behavior of the Acellular Slim

Mold Physarum Polycephalum (SLIME)

– Microgravitational Effects on Chromosome 

Behavior (YEAST)

– Growth and Sporulation in Bacillus Subtilis U

Microgravity (SPORES)

– Studies on Penetration of Antibiotics in Bacteri

Cells in Space Conditions (ANTIBIO) 

– Transmission of the Gravity Stimulus in Statoc

the Lentil Root (ROOTS)

– Genotype Control of Graviresponse, Cell Pola

and Morphological Development of Arabidop

Thaliana in Microgravity (SHOOTS)

– Effects of Microgravity Environment on Cell 

Regeneration, Cell Divisions, Growth and 

Differentiation of Plants From Protoplasts (PR

• Gravitational Plant Physiology Facility Experim

– Gravity Threshold (GTHRES)

– Response to Light Stimulation: Phototropic 

Transients (FOTRAN)

• Microgravity Vestibular Investigations

• Mental Workload and Performance Experiment

• Space Physiology Experiments

– Space Adaptation Syndrome Experiments (SA

– Sled Experiment

– Rotation Experiment

– Visual Stimulator Experiment

– Proprioceptive Experiments

– Energy Expenditure in Spaceflight (EES)

– Position and Spontaneous Nystagmus (PSN)
Table 3–69. STS-42 Mission Characteristics (Continued)

Experiments – Measurement of Venous Compliance (MVC) 

Evaluation of an Experimental Anti-Gravity S

– Assessment of Back Pain in Astronauts (BPA)

– Phase Partitioning Experiment (PPE)

• Biostack (four packages)

• Radiation Monitoring Container Device (RMCD

IML-1 Materials Science Experiments

• PCG

• Cryostat

• Single Crystal Growth of Beta-Galactosidase an

Beta-Galactosidase/Inhibiter Complex

• Crystal Growth of the Electrogenic Membrane P

Bacteriorhodopsin

• Crystallization of Proteins and Viruses in Microg

by Liquid-Liquid Diffusion

– Fluids Experiment System

• Study of Solution Crystal Growth in Low G

(TGS)

• An Optical Study of Grain Formation: Castin

Solidification Technology (CAST)

– Vapor Crystal Growth System (VCGS)

• Vapor Crystal Growth Studies of Single Me

Iodide Crystals

– Mercury Iodide Crystal Growth (MICG) Syste

• Mercury Iodide Nucleations and Crystal Gr

in Vapor Phase

• Organic Crystal Growth Facility

• Critical Point Facility (CPF) 

– Study of Density Distribution in a Near-Critic

Simple Fluid

– Heat and Mass Transport in a Pure Fluid in th

Vicinity of a Critical Point

– Phase Separation of an Off-Critical Binary Mi

– Critical Fluid Thermal Equilibration Experimen

SAMS: See STS-43.

SSIP (SE 81-09): Convection in Zero Gravity: Thi

experiment studied surface-tension-induced flows 

microgravity.

SSIP (SE 83-02): Zero-G Capillary Rise of Liquid 

Through Granular Porous Media: This experiment s

the flow of liquid through granular porous media. 

Gelation of SOLS Applied Microgravity Research 

(GOSAMR): This experiment involved chemical ge

to form precursors for advanced ceramic materials. 

IPMP: See STS-31.

RME-III: See STS-28.
Table 3–69. STS-42 Mission Characteristics (Continued)

Get Away Specials G-086

Customer: Booker T. Washington Senior High Sch

Houston, Texas 

G-086 studied behavioral and physiological effect

microgravity on brine shrimp cysts hatched in spa

The experiment also studied thermal conductivity 

bubble velocity of air and water in microgravity.

G-140

Customer: German Space Agency (DARA)

G-140 studied the effect that a disturbance of the l

liquid interface (due to interfacial tension) had on 

transfer in a liquid-liquid extraction system in a flo

zone.

G-143

Customer: DARA

Gas Bubbles in Glass Melts: This experiment resea

the process of glass fining, the removal of all visib

gaseous inhomogeneities from glass melt.

G-329

Customer: Swedish Space Corporation

G-329 studied solidification phenomena in metal a

by looking at the dentrite growth in a cadmium-tin 

G-336

Customer: U.S. Air Force Geophysics Laboratory

G-336 measured the visible light reflected by 

intergalactic dust. Data from those measurements 

to be used to validate and update existing data coll

in earlier experiments and help provide backgroun

measurements of visible light for use in space 

surveillance.a

G-337

Customer: U.S. Naval Postgraduate School

G-337 measured the performance of a thermoacou

refrigerator under microgravity conditions.

G-456

Customer: Society of Japanese Aerospace Compa

G-456 separated three colored, biologically active 

enzymes by electrophoresis and compared them to 

Earth-based patterns.

G-457

Customer: Society of Japanese Aerospace Compa

G-457 cultivated cellular slime mold in micrograv

a preliminary study of a method of gas-liquid sepa

under conditions of microgravity.
Table 3–69. STS-42 Mission Characteristics (Continued)

Get Away Specials G-609/G-610

Customer: Australian Space Office 

Auspace Ltd. designed and built an Australian 

ultraviolet light telescope for the Australian Space 

Office. It obtained ultraviolet images of violent eve

nearby galaxies. Two interconnected GAS cans ho

the payload’s components. One contained the opti

elements, and the second contained a flight battery 

two tape recorders for recording detector data.

G-614

Customer: Chinese Society of Astronautics and Th

American Association for Promotion of Space in C

G-614 photographed the motion of simulated debr

the Shuttle under microgravity and remelted variou

melting point mixtures of paraffin and Wood’s me

while in orbit. 

Mission Results Successful

a The First 100 GAS Payloads, (Greenbelt, MD: NASA Goddard Space Flight Center, no date), p
Table 3–70. STS-45 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Charles F. Bolden, Jr.

PLT: Brian Duffy

MS: Kathryn D. Sullivan, David C. Leestma, C. M

Foale

PS: Byron K. Lichtenberg, Dirk D. Frimout (ESA)

Launch March 24, 1992, 8:13:40 a.m. EST, Kennedy Spac

Center, Pad 39-A. Launch was originally schedule

March 23, but was delayed one day because of hig

than allowable concentrations of liquid hydrogen a

liquid oxygen in the orbiter’s aft compartment dur

tanking operations. During troubleshooting, the le

could not be reproduced, leading engineers to beli

they were the result of plumbing in the main propu

system not thermally conditioned to the super cold 

propellants. Launch was rescheduled for March 24

Liftoff was delayed about 13 minutes due to low-l

clouds at the Kennedy Space Center Shuttle runwa

Orbital Altitude & 

Inclination

160 nmi (296 km), 57 deg

Launch Weight (lb/kg) 233,650/105,982

Landing & Postlanding 

Operations

April 2, 1992, 6:23:08 a.m. EST, Runway 33, Ken

Space Center. Mission extended one day to contin

science experiments.

Rollout Distance (ft/m) 9,227/2,812

Rollout Time (seconds) 60

Mission Duration 214 hr, 9 min, 28 sec

Landed Revolution No. 142

Mission Support STDN

Primary Objective Atmospheric research using the ATLAS-1

Deployed Satellites None

Experiments Atmospheric Laboratory for Applications and Scie

using the Spacelab pallet and igloo. ATLAS-1 

investigations in the areas of atmospheric science, 

plasma physics, and astrophysics.

• Atmospheric Science 

– Atmospheric Lyman-Alpha Emission (ALAE)

– Atmospheric Trace Molecule Spectroscopy 

(ATMOS)

– Grille Spectrometer

– Millimeter Wave Atmospheric Sounder (MAS

– Imaging Spectrometric Observatory (ISO)
Table 3–70. STS-45 Mission Characteristics (Continued)

Experiments • Solar Science

– Active Cavity Radiometer Irradiance Monitor 

(ACRIM)

– Measurement of Solar Constant (SOLCON) 

– Solar Spectrum (SOLSPEC)

– Solar Ultraviolet Spectral Irradiance Monitor 

(SUSIM)

– Plasma Physics

– Atmospheric Emissions Photometric Imager (

– Space Experiments with Particle Accelerators 

(SEPAC)

– Energetic Neutral Atom Precipitation (ENAP)

• Astrophysics

– Far Ultraviolet Space Telescope (FAUST)

SSBUV: The instrument is housed in two GAS can

See STS-34.

Space Tissue Loss (STL): This experiment was a 

cooperative effort between NASA’s OSSA and the W

Reed Army Institute of Research with hardware spon

by the U.S. Army Space Test Program and mission 

management provided by the U.S. Air Force Space 

Systems Division. The STL experiment studied the e

of the microgravity environment on the biochemistr

functional activity of muscle, bone, and blood cells. 

Appropriate cell lines were cultured to develop a ce

model for comparison with whole animal results. Th

muscle atrophy model, consisting of cultured human 

myocardial cells in a monitored environment, valida

skeletal and cardiac muscle atrophy, collected data o

catabolic pathways, and tested candidate pharmaceu

for efficacy in countering tissue loss.

IPMP: See STS-31.

RME-III: See STS-28.

VFT-2: See STS-28.

CLOUDS-1A: See STS-28

SAREX II-B: See STS-35.

Get Away Specials G-229 

Customer: GTE Laboratories

Experiment in Crystal Growth:

This experiment was designed to grow GaAs cryst

GaAs is a versatile electronic material used in high

speed electronics and optoelectronics. The crystal g

on this mission was 1 inch in diameter by 3.5 inche

and was grown using a gradient freeze growth tech

Mission Results Successful
Table 3–71. STS-49 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Daniel C. Brandenstein

PLT: Kevin P. Chilton

MS: Pierre J. Thuot, Kathryn C. Thornton, Richar

Hieb, Thomas D. Akers, Bruce E. Melnick

Launch May 7, 1992, 7:40:00 p.m. EDT, Kennedy Space 

Center, Pad 39-B. Following the Flight Readiness 

firing of Endeavour’s three main engines on Apri

1992, Shuttle managers decided to replace all thre

engines due to irregularities detected in two of th

high-pressure oxidizer turbopumps; no impact to 

launch date was expected. Launch was originally 

for May 4 at 8:34 p.m. EDT, but it was moved to M

for an earlier launch window opening at 7:06 p.m. 

to achieve better lighting conditions for photograp

documentation of vehicle behavior during the lau

phase. Liftoff was delayed 34 minutes due to 

transoceanic abort landing site weather condition

a technical glitch with one of the orbiter master e

controllers.

Orbital Altitude & 

Inclination

195 nmi (361 km), 28.34 deg

Launch Weight (lb/kg) 256,597/116,390

Landing & Postlanding 

Operations

May 16 1992, 1:57:38 p.m. PDT, Runway 22, Edw

Air Force Base. The flight was extended two days t

complete mission objectives. The first use of drag c

during landing, they deployed after nosegear touch

for data collection only. The orbiter returned to Ken

Space Center on May 30, 1992. 

Rollout Distance (ft/m) 9,490/2,893

Rollout Time (seconds) 58

Mission Duration 213 hr, 17 min, 38 sec

Landed Revolution No. 140

Mission Support STDN

Primary Objective Capture, repair, and redeploy INTELSAT VI

Deployed Satellites INTELSAT VI
Table 3–71. STS-49 Mission Characteristics (Continued)

Experiments Commercial PCG Experiment: For six years, a vari

hardware configurations were used to conduct PCG 

experiments aboard 12 Space Shuttle flights. These 

experiments involved minute quantities of sample 

materials to be processed. On STS-49, the Protein 

Crystallization Facility (PCF), developed by the Ce

for Macromolecular Crystallography (CMC), a NA

Center for the Commercial Development of Space 

University of Alabama-Birmingham, used much la

quantities of materials to grow crystals in batches, 

temperature as a means to initiate and control 

crystallization. The PCF was reconfigured to includ

cylinders with the same height but varying diamete

obtain different volumes (500 ml, 200 ml, 100 ml, a

ml). These cylinders allowed for a relatively minim

temperature gradient and required less protein solut

produce quality crystals. This industry-driven chan

was brought about by a need to reduce the cost and 

amount of protein sample needed to grow protein cr

in space, while at the same time increasing the qua

and quantity of crystals. The PCF served as the gro

chamber for significant quantities of protein crysta

Also flying as part of the CPCG payload complem

was a newly designed, state-of-the-art Commercia

Refrigerator Incubator Module (CRIM) that allow

a preprogrammed temperature profile. Developed 

Space Industries, Inc., for CMC, the CRIM also 

provided improved thermal capability and had a 

microprocessor that used “fuzzy logic” to control 

monitor the CRIM’s thermal environment. 

UVPI Experiment: See STS-43.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful
Table 3–71. STS-49 Mission Characteristics (Continued)

Remarks INTELSAT VI had been stranded in an unusable o

since its launch aboard a Titan rocket in March 19

The INTELSAT VI capture required three EVAs. 

first spacewalk was on flight day four by Thuot, w

was unable to attach a capture bar to INTELSAT f

his position on the remote manipulator system arm

second unscheduled but identical attempt by Thuo

failed on the following day. After resting on flight 

six, an unprecedented three-person EVA was perfo

on flight day seven. During the longest EVA so fa

U.S. space history (8 hours, 29 minutes), Hieb, Th

and Akers grasped the rotating INTELSAT by han

while Brandenstein maneuvered the orbiter, ultim

attaching the capture bar to the satellite and attach

INTELSAT to its new upper stage. The day after 

capture of the satellite, INTELSAT flight controlle

ignited the upper stage to send the satellite to its 

intended geosynchronous orbit. 

On flight day eight, Akers and Thornton performe

EVA as part of the Assembly of Station by EVA 

Methods (ASEM) experiment to demonstrate and v

maintenance and assembly capabilities for Space 

Station Freedom. 
Table 3–72. STS-50 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Richard N. Richards

PLT: Kenneth D. Bowersox

PC: Bonnie J. Dunbar

MS: Ellen S. Baker, Carl J. Meade

PS: Lawrence J. DeLucas, Eugene H. Trinh

Launch June 25, 1992, 12:12:23 p.m. EDT, Kennedy Spac

Center, Pad 39-A. Liftoff was delayed 5 minutes d

weather. This was the first flight of Columbia afte

scheduled checkout and extensive modification pe

Orbital Altitude & 

Inclination

160 nmi (296 km), 28.45 deg

Launch Weight (lb/kg) 257,265/116,693

Landing & Postlanding 

Operations

July 9, 1992, 7:42:27 a.m. EDT, Runway 33, Kenn

Space Center. Landing was delayed one day due to 

at the primary landing site, Edwards Air Force Base

was the first landing using new synthetic tread tires

Rollout Distance (ft/m) 10,674/3,253

Rollout Time (seconds) 59

Mission Duration 331 hr, 30 min, 04 sec

Landed Revolution No. 220

Mission Support STDN

Primary Objective Microgravity research using USML-1

Deployed Satellites None

Experiments USML-1: A pressurized Spacelab long module wi

connecting tunnel to the orbiter crew compartmen

USML-1 was a national effort to advance microgr

research in a broad array of disciplines. Experime

conducted were: 

• Crystal Growth Furnace (CGF)

• Drop Physics Module (DPM)

• Surface Tension Driven Convection Experiment 

(STDCE)

• Zeolite Crystal Growth (ZCG)

• PCG

• Glovebox Facility (GBX)

• SAMS

• Generic Bioprocessing Apparatus (GBA)

• ASTROCULTURE-1 (ASC)

• Extended Duration Orbiter Medical Project (EDO

• SSCE
Table 3–72. STS-50 Mission Characteristics (Continued)

Experiments IPMP: See STS-31.

SAREX II: See STS-35.

UVPI: See STS-43.

Get Away Specials

Mission Results

None

Successful
Table 3–73. STS-46 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Loren J. Shriver

PLT: Andrew M. Allen

PC: Jeffrey A. Hoffman

MS: Franklin R. Chang-Diaz, Claude Nicollier (E

Marsha S. Ivins

PS: Franco Malerba (Italian Space Agency Agenz

Spaziale Italiana/ASI)

Launch July 31, 1992, 9:56:48 a.m. EDT, Kennedy Space 

Center, Pad 39-A. Liftoff was delayed 48 seconds 

minutes to allow orbiter computers to verify that t

orbiter auxiliary power units were ready to start.

Orbital Altitude & 

Inclination

230 nmi (426 km), 28.45 deg

Launch Weight (lb/kg) 256,031/116,134

Landing & Postlanding 

Operations

August 8, 1992, 9:11:51 a.m. EDT, Runway 33, 

Kennedy Space Center. The mission was extended 

day to complete scientific objectives.

Rollout Distance (ft/m) 10,860/13,310

Rollout Time (seconds) 66

Mission Duration 191 hr, 15 min, 03 sec

Landed Revolution No. 126

Mission Support STDN

Primary Objective Operation and testing of the TSS and deployment 

ESA’s EURECA

Deployed Satellites EURECA

Joint NASA/Italian Space Agency TSS-1

Experiments Evaluation of Oxygen Integration with Materials/

Thermal Energy Management Processes (EOIM-I

TEMP 2A-3): This experiment gathered accurate 

on the reaction rate of atomic oxygen, present in l

orbit, on Space Shuttle materials. Collisions with a

oxygen in orbit cause erosion of many materials. T

experiment attempted to identify materials resistan

erosion to be used on future spacecraft.
Table 3–73. STS-46 Mission Characteristics (Continued)

Experiments Consortium for Materials Development in Space 

Complex Autonomous Payload (CONCAP II and 

CONCAP III): This experiment investigated react

occurring on the surface of materials when expose

the atomic oxygen flow in Earth orbit on hightemperature, super-conducting films, and on mate

degradation/reaction samples. The payloads were 

in 5-ft (1.5-m)-high cylindrical GAS canisters.

CONCAP-II studied the changes materials underw

low-Earth orbit. The payload experiments studied 

surface reactions resulting from exposing material

the atomic oxygen flow experienced by the Space 

Shuttle in orbit. CONCAP-III measured and recor

absolute accelerations (microgravity levels) in one 

experiment and electroplated pure nickel metal an

recorded the conditions (temperature, voltage, and 

current) during this process in another experiment

ICBC: The ICBC payload documented operations 

outside the crew cabin, including prerelease and 

postrelease of EURECA, TSS-1 flyaway, and TSS 

out and reel-in. The ICBC also observed Typhoon 

the Windward Islands; Java the Sahara desert; 

Madagascar; Brazil; the Andes mountains; the Tua

Archipelago; and the area from Indonesia to Austr

Limited Duration Space Environment Candidate 

Materials Exposure (LDCE): This experiment eva

candidate space structure composite materials for 

degradation due to exposure in low-Earth orbit (pa

systems).

AMOS: See STS-29.

Pituitary Growth Hormone Cell Function (PHCF)

experiment was a study to determine if the exposu

cultured rat pituitary cells to microgravity affected 

capacity to produce biologically active growth hor

UVPI: See STS-43.

Get Away Specials None

Mission Results During TSS deployment, the satellite reached a 

maximum distance of only 840 ft (256 m) from th

orbiter instead of the planned 12.5 mi (201 km) be

of a jammed tether line. After numerous attempts 

spanning several days to free the tether, TSS opera

were curtailed, and the satellite was stowed for ret

Earth. Other mission objectives were accomplishe
Table 3–74. STS-47 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Robert L. Gibson

PLT: Curtis L. Brown, Jr.

PC: Mark C. Lee

MS: Jerome Apt, N. Jan Davis, Mae C. Jemison

PS: Mamoru Mohri (Japanese Aerospace Explora

Agency/JAXA)

Launch September 12, 1992, 10:23:00 a.m. EDT, Kennedy S

Center, Pad 39-B. This launch was the first on-time S

launch since STS-61-B in November 1985.

Orbital Altitude & 

Inclination

166 nmi (307 km), 57.00 deg

Launch Weight (lb/kg) 258,679/117,335

Landing & Postlanding 

Operations

September 20, 1992, 8:53:23 a.m. EDT, Runway 3

Kennedy Space Center. The mission was extended 

day for further scientific experimentation. This mis

was the first time the drag chute was deployed in 

operational mode, before nosegear touchdown. 

Postlanding assessment showed that the orbiter vee

off the runway centerline, possibly due to the drag 

Rollout Distance (ft/m) 8,567/2,611

Rollout Time (seconds) 51

Mission Duration 190 hr, 31 min, 11 sec 

Landed Revolution No. 125

Mission Support STDN

Primary Objective Materials and life sciences research using Spacela

Deployed Satellites None
Table 3–74. STS-47 Mission Characteristics (Continued)

Experiments Spacelab-J: A joint NASA-National Space Develop

Agency of Japan (NASDA) mission using a Space

long module. The international crew was divided i

red and blue teams for round-the-clock operations

Spacelab-J included materials science and life scie

experiments, of which NASDA sponsored 37 and N

sponsored 8. Materials science investigations cove

such fields as biotechnology; electronic materials; 

dynamics and transport phenomena; glasses and 

ceramics; metals and alloys; and acceleration 

measurements. Life sciences investigations covere

human health; cell separation and biology; develop

biology; animal and human physiology and behavi

space radiation; and biological rhythms. Test subje

included crew members; Japanese koi fish; culture

animal and plant cells; chicken embryos; fruit flies

fungi and plant seeds; and frogs and frog eggs.

Sponsored by NASA

• Materials Science

– SAMS

– Inflight Demonstration of the Space Station 

Freedom Health Maintenance Facility Fluid 

Therapy System

• Life Science

– PCG

– Monitoring Astronauts’ Functional State

– Autogenic Responses to Microgravity

– Bone Cell Research

– Amphibian Development in Microgravity: Th

STS-47 Frog Embryology Experiment

– Lower Body Negative Pressure Countermeasu

Against Orthostatic Intolerance After Space F

– Plant Cell Research Experiment on Spacelab 

Mitotic Disturbances in Daylily (Hemerocalli

Somatic Embryos After an 8-Day Spaceflight

– Magnetic Resonance Imaging After Exposure 

Microgravity

From the National Space Development Agency of 

• Materials Science

– Growth Experiments of Narrow Band-Gap 

Semiconductor Pb-Sn-Te Single Crystal in Sp

– Growth of Pb-Sn-Te Single Crystal by Traveli

Zone Method 

– Growth of Semiconductor Compound Single 

Crystal InSb by Floating Zone Method
Table 3–74. STS-47 Mission Characteristics (Continued)

Experiments – Casting of Superconducting Composite Mater

– Formation Mechanism of Deoxidation Produc

Iron Ingot Deoxidized With Two or Three Ele

– Preparation of Particle Dispersion–Alloys

– Diffusion in Liquid State and Solidification o

Binary System

– High-Temperature Behavior of Glass

– Growth of Silicon Spherical Crystals and Surf

Oxidation

– Study of Solidification of Immiscible Alloy

– Fabrication of Ultra-Low-Density, High-Stiffn

Carbon Fiber/Aluminum Composites

– Study on Liquid Phase Sintering

– Fabrication of Si-As-Te: Semiconductor in 

Microgravity Environment

– Gas Evaporation in Low Gravity

– Drop Dynamics in an Acoustic Resonant Cha

and Interference with the Acoustic Field

– Bubble Behavior in Thermal Gradient and 

Stationery Acoustic Wave

– Preparation of Optical Materials Used in Non

Visible Region

– Marangoni Effort-Induced Convection in Mat

Processing Under Microgravity

– Solidification of Eutectic System Alloys in Sp

– Growth of Samarskite Crystal in Microgravity

– Crystal-Growth Experiment on Organic Meta

Low Gravity

– Crystal Growth of Compound Semiconductor

Low-Gravity Environment

• Life Science

– Endocrine and Metabolic Changes in Payload 

Specialist

– Neurophysiological Study of Visuo-Vestibula

Control of Posture and Movement in Fish Dur

Adaptation to Weightlessness

– Comparative Measurement of Visual Stability 

Earth and Cosmic Space

– Crystal Growth of Enzymes in Low Gravity

– Studies on the Effects of Microgravity on the 

Ultrastructure and Functions of Cultured 

Mammalian Cells

– Effect of Low Gravity on Calcium Metabolism 

Bone Formation in Chick Embryo

– Separation of Biogenic Materials by 

Electrophoresis Under Zero Gravity

– Genetic Effects of HZE and Cosmic Radiation
Table 3–74. STS-47 Mission Characteristics (Continued)

– Manual Control in Space Research on Percep

Motor Functions Under Microgravity Conditi

– Study on the Biological Effect of Cosmic Rad

and the Development of Radiation Protection 

Technology

– Circadian Rhythm of Conidiation in Neurospo

Crassa

– Electrophoretic Separation of Cellular Materi

Under Microgravity

– Study of the Effects of Microgravity on Cell 

Growth of Human Antibody-Producing Cells 

Their Secretions

– Organ Differentiation from Cultured Plant Ce

Under Microgravity

– Health Monitoring of Japanese Payload Speci

– Autonomic Nervous and Cardiovascular Resp

Under Reduced Gravity

Israeli Space Agency Investigation About Hornets 

(ISAIAH): This experiment attempted to gain great

insight into the ability of hornets to construct a com

the direction of the gravitational vector by observing 

comb-building in microgravity. It also investigated 

effects of microgravity on comb integrity, social 

interactions, hornet venom toxicity, and the 

semiconductive properties of hornet cuticle.

SSCE: See STS-41. 

SAREX II: See STS-35. 

AMOS Calibration Test: See STS-29.

UVPI: See STS-43.
Table 3–74. STS-47 Mission Characteristics (Continued)

Get Away Specials G-102 

Customer: TRW Defense and Space Systems Grou

Explorer Scouts

POSTAR: Consisted of seven experiments:

1. Capillary Pumping Experiment: This experimen

investigated pumping liquids using capillary fe

tubes.

2. Cosmic Ray Experiment: This experiment studi

direction and composition of cosmic rays.

3. Crystal Growth Experiment: This experiment 

examined high-quality, lattice-structure crystal

using nickel sulfate.

4. Emulsions Experiment: This experiment investi

the formation of oil/water emulsions. 

5. Fluid Droplet Experiment: This experiment stu

the shape of fluid droplets in microgravity.

6. Floppy Disk Experiment: This experiment 

investigated the effect of low-level radiation on 

floppy disks.

7. Fiber Optics Experiment: This experiment exam

the degradation of fiber optic cables under the s

radiation environment.

G-255

Customer: University of Kansas

Scientific studies contained four experiments:

Composite Materials: This experiment compared 

composites manufactured in microgravity with tho

made on Earth.

Cell Membrane: This experiment investigated the 

formation of biological membranes in microgravit

Crystal Growth: This experiment studied the effec

microgravity on bond angles and the structure of 

crystals.

Space Seeds: This experiment studied the effects o

space environment on germination rates and healt

seeds.

G-300

Customer: Matra Marconi Space

Thermal Conductivity of Liquids in Microgravity

experiment measured the thermal conductivity of 

liquids in microgravity. It was the first GAS paylo

from France.

G-330

Customer: Swedish Space Corporation

Material Science Experiments: Crystal Growth an

Electromigration: These experiments investigated 

breakdown of a solid/liquid interface.
Table 3–74. STS-47 Mission Characteristics (Continued)

Get Away Specials G-482

Customer: Space Aerospace, Ltd., Quebec, Canad

Baking Bread in Space: This experiment investiga

the behavior of bread yeast in the absence of gravit

in the presence of normal atmospheric pressure.

G-520 

Customer: The Independent Television News of 

England

Scientific Experiments for Educational Competiti

Consisted of two experiments:

Chemical Gardens Experiment: This experiment 

deposited cobalt nitrate crystals into a container o

sodium silicate solution. The ensuing crystal grow

was compared to crystals grown on Earth.

The Liesegang Rings Experiment: This experimen

deposited a silver nitrate solution on a compound 

containing potassium chromate. Silver nitrate diff

through potassium chromate and formed a precipit

the shape of rings. The investigation attempted to 

produce rings on a large scale to aid in determining 

they were produced.

This was the first British school experiment to fly 

space.

G-521

Customer: Canadian Space Agency

QUESTS: This experiment involved performing 

directional solidification and diffusion experimen

microgravity using 3 gradient furnaces and 12 

isothermal furnaces.

G-534

Customer: NASA Headquarters

Pool Boiling Experiment: This experiment investi

the effects of heat flux and liquid subcooling on 

nucleate pool boiling in a long-term, reduced-grav

environment.

G-613

Customer: University of Washington

Liquid Droplet Rotating-Collector Experiment: Th

was a proof-of-concept experiment testing the abil

a centrifugal collector to recover a free fluid strea

microgravity.

Mission Results Successful
Table 3–75. STS-52 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: James D. Wetherbee

PLT: Michael A. Baker

MS: Charles Lacy Veach, William M. Shepherd, 

Tamara E. Jernigan

PS: Steven G. MacLean (CSA)

Launch October 22, 1992, 1:09:39 p.m. EDT, Kennedy Sp

Center, Pad 39-B. The targeted launch date in mid

October slipped when managers decided to replac

No. 3 engine, prompted by concerns about possib

cracks in the liquid hydrogen coolant manifold on 

engine nozzle. Liftoff set for 11:16 a.m. was delay

about 2 hours due to crosswinds at the Kennedy S

Center landing strip, violating return-to-launch-sit

criteria, and clouds at the Banjul transoceanic abo

landing site.

Orbital Altitude & 

Inclination

163 nmi (302 km), 28.45 deg

Launch Weight (lb/kg) 250,130/113,457

Landing & Postlanding 

Operations

November 1, 1992, 9:05:52 a.m. EST, Runway 33

Kennedy Space Center. The drag chute was again 

deployed before nosegear touchdown to allow fur

study of deployment dynamics.

Rollout Distance (ft/m) 10,708/3,263

Rollout Time (seconds) 63

Mission Duration 236 hr, 56 min, 13 sec

Landed Revolution No. 158

Mission Support STDN

Primary Objective Deploy LAGEOS II and operation of USMP-1

Deployed Satellites LAGEOS II/IRIS
Table 3–75. STS-52 Mission Characteristics (Continued)

Experiments USMP-1: The payload included three experiment

mounted on two connected Multipurpose Experim

Support Structures mounted in the cargo bay. The 

USMP-1 experiments were: 

• Lambda Point Experiment (LPE): This experim

studied fluid behavior in microgravity.

• French-sponsored Material Pour l’Etude Des 

Phenomenes Interessant La Solidification Sur Te

Et En Orbite (Materials for the Study of Interest

Phenomena of Solidification on Earth and in Or

(MEPHISTO): This experiment studied metallur

processes in microgravity.

• SAMS: This was a study of the microgravity 

environment on board the Space Shuttle.

Canadian Experiments-2 (CANEX-2): These 

experiments were a complement of space technolo

space science, materials processing, and life scien

experiments located in both the cargo bay and mid

including: 

• Space Vision System (SVS)

• Materials Exposure in Low-Earth Orbit (MELE

• Queen’s University Experiment in Liquid-Metal 

Diffusion (QUELD)

• Phase Partitioning in Liquids (PARLIQ)

• Sun Orbiter Glow-2 

(OGLOW-2)

• Space Adaptation Tests and Observations (SATO

• Sun Photo Spectrometer Earth Atmosphere 

Measurement (SPEAM-2)

• Vestibular-Ocular Reflex Check

• Body Water Changes in Microgravity

• Assessment of Back Pain in Astronauts

• Illusions During Movement

Altitude Sensor Package (ASP): The ASP feature

three ESA independent sensors mounted on a 

Hitchhiker plate in the cargo bay: 

• Modular Star Sensor

• Yaw Earth Sensor and Low Altitude Conical Ea

Sensor

• Tank Pressure Control Experiment/Thermal 

Phenomena

Commercial Materials Dispersion Apparatus 

Instrument Technology Associates Experiments 

(CMIX): These experiments were designed to mix 

variety of sample fluids/solids in microgravity and 

processing modules designed to mix fluids to perf

immune cell response in microgravity.
Table 3–75. STS-52 Mission Characteristics (Continued)

Experiments CPCG: See STS-49.

Crystal Vapor Transport Experiment (CVTE): The 

CVTE consisted of two furnaces, which provided 

controlled environment for growth of selected 

materials.

• Heat Pipe Performance Experiment (HPP): The 

experiment developed the understanding of heat 

behavior in microgravity.

PSE-02: The PSE-02 determined the effects of a 

proprietary protein molecule on an animal’s 

physiological system.

Shuttle Plume Impingement Experiment (SPIE): T

SPIE consisted of sensing hardware mounted on t

remote manipulating system to measure the atomi

oxygen flux and contamination.

Tank Pressure Control Experiment/Thermal 

Phenomena (TPCE/TP): This experiment determi

the effectiveness of jet mixing as a means of contro

tank pressures and equilibrating fluid temperature

contained in a GAS canister.

Get Away Specials None

Mission Results Successful
Table 3–76. STS-53 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: David M. Walker

PLT: Robert D. Cabana

MS: Guion S. Bluford, Jr., James S. Voss, Michae

Clifford

Launch December 2, 1992, 8:24:00 a.m. EST, Kennedy Sp

Center, Pad 39-A. Liftoff was originally set for 6:

a.m. but was delayed to allow sunlight to melt ice 

the external tank that had formed after tanking du

overnight temperatures in the upper 40s°F and lig

wind. 

Orbital Altitude & 

Inclination

174 nmi (322 km), 57.00 deg

Launch Weight (lb/kg) 243,952/110,655

Landing & Postlanding 

Operations

December 9, 1992, 12:43:47 p.m. PST, Runway 2

Edwards Air Force Base. Landing was originally s

Kennedy Space Center but was diverted due to clo

in the landing strip vicinity. The drag chute was 

deployed before nosegear touchdown. After landi

small leak was detected in a forward thruster that 

delayed crew egress before a fan and winds dissip

the leaking gas. The orbiter returned to Kennedy S

Center on December 18, 1992.

Rollout Distance (ft/m) 10,165/3,098

Rollout Time (seconds) 73

Mission Duration 175 hr, 19 min, 47 sec

Landed Revolution No. 115

Mission Support STDN

Primary Objective Deploy a classified DOD payload

Deployed Satellites SDS-2 (USA 89)
Table 3–76. STS-53 Mission Characteristics (Continued)

Experiments Glow Experiment (GLO)/Cryogenic Heat Pipe 

Experiment (CRYOHP) Payload (GCP): These pay

were contained in or attached to GAS hardware. Th

GLO experiment observed orbiter and air glow, prim

reaction control system and vernier reaction contro

system burns, water dumps, and flash evaporator sy

operations. The CRYOHP experiment measured the 

performance of liquid oxygen heat pipes in microgr

Battlefield Laser Acquisition Sensor Test (BLAST

This test evaluated the use of a spaceborne laser 

receiver to detect laser energy and provide laser 

communication uplink for GPS information from 

specific ground sites.

CLOUDS: See STS-28.

CREAM: See STS-48.

Fluid Acquisition and Resupply Experiment (FAR

The FARE investigated the fill, refill, and expulsio

fluid tanks and liquid motion in microgravity.

Handheld, Earth-oriented, Real-time, Cooperative

User-friendly, Location-Targeting and Environme

System (HERCULES): The HERCULES perform

geolocating operations over selected ground sites.

Microcapsules in Space-1 (MIS-1): This experime

demonstrated the capability to produce 

microencapsulated ampicillin in microgravity to 

compare with Earth-produced ampicillin. 

RME-III: See STS-28.

STL: See STS-45.

VFT-2: See STS-28.

Orbital Debris Radar Calibration System (ODERAC

This system qas to release six calibration spheres fr

Discovery. The spheres—two with diameters of 6 

(15-cm), two with 4-in (10-cm) diameters, and two 

2-in (5-cm) diameters—were to be placed in a 175-

(377-km) orbit when they were ejected from the Shu

cargo bay. The primary objective of the experiment 

to provide a source for fine-tuning of the Haystack 

Radar, located in Tyngsboro, Massachusetts, and op

ated by the Lincoln Laboratory at the Massachusett

Institute of Technology for the U.S. Air Force.

Get Away Specials None

Mission Results The ODERACS was not deployed. After attempts t

communicate with the experiment without respons

was determined that a battery had been drained bef

launch. Other mission objectives were successfully 

Remarks This was the final Shuttle flight for the DOD.
Table 3–77. STS-54 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: John H. Casper

PLT: Donald R. McMonagle

MS: Mario Runco, Jr., Gregory J. Harbaugh, Susa

Helms

Launch January 13, 1993, 8:59:30 a.m. EST, Kennedy Spa

Center, Pad 39-B. Liftoff was delayed about 7 min

due to concerns associated with upper atmospheri

winds.

Orbital Altitude & 

Inclination

165 nmi (306 km), 29.45 deg

Launch Weight (lb/kg) 259,764a/117,827

Landing & Postlanding 

Operations

January 19, 1993, 8:37:49 a.m. EST, Runway 33, 

Kennedy Space Center. Landing was delayed one 

due to ground fog at Kennedy Space Center.

Rollout Distance (ft/m) 8,724/2,659

Rollout Time (seconds) 49

Mission Duration 143 hr, 38 min, 19 sec

Landed Revolution No. 95

Mission Support STDN

Primary Objective Deploy TDRS-6

Deployed Satellites TDRS-6/IUS

Experiments Diffuse X-ray Spectrometer (DXS): The DXS wa

Hitchhiker experiment sponsored by Goddard Spa

Flight Center. Data was collected on x-ray radiatio

from diffuse sources in deep space. The DXS 

determined the wavelength and intensity of the 

strongest x-ray lines emitted by the hot stellar gas

released by supernovas.b

Commercial General Bioprocessing Apparatus (CG

The CGBA performed two functions, biological sa

processing and stowage. The Generic Bioprocessin

Apparatus (GBA) module was a self-contained mix

and incubation module for samples. Temperaturecontrolled stowage was achieved in the CRIM.

CHROMEX: See STS-29.

PARE-02: See STS-48.

SAMS: See STS-43.

SSCE: See STS-41.

Get Away Specials None

Mission Results Successful

a Jenkins, p. 302. b See chapter 4, Space Science, for further discussion of the Diffuse X-ray Spectrometer experim
Table 3–78. STS-56 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Kenneth D. Cameron

PLT: Stephen S. Oswald

MS: C. Michael Foale, Kenneth D. Cockrell, Elle

Ochoa

Launch April 8, 1993, 1:29:00 a.m. EDT, Kennedy Space 

Center, Pad 39-B. The first launch attempt on Apr

was halted at T-11 seconds by orbiter computers w

instrumentation on the liquid hydrogen high point 

valve in the main propulsion system indicated “of

instead of “on.” Later analysis indicated that the v

was properly configured; 48-hour scrub turnaroun

procedures were implemented. The final countdow

April 8 proceeded smoothly.

Orbital Altitude & 

Inclination

160 nmi (296 km), 57.00 deg

Launch Weight (lb/kg) 236,659/107,347

Landing & Postlanding 

Operations

April 17, 1993, 7:37:19 a.m. EDT, Runway 33, 

Kennedy Space Center. Landing, originally set for 

April 16, at Kennedy Space Center was waved off 

to weather. A second reefing line was added to dr

chute for greater stability.

Rollout Distance (ft/m) 9,530/2,905

Rollout Time (seconds) 62

Mission Duration 222 hr, 8 min, 24 sec

Landed Revolution No. 147

Mission Support STDN

Primary Objective ATLAS-2

Deployed Satellites SPARTAN-201: Retrieved April 13a

Experiments ATLAS-2: This mission used Spacelab pallet and ig

collect data on the relationship between the Sun’s e

output and Earth’s middle atmosphere and their affe

the ozone layer. The atmospheric instruments were

• ATMOS experiment

• MAS

• SSBUV/A spectrometer: See STS-34.

The solar science instruments were: 

• SOLSPEC instrument

• SUSIM

• Active Cavity Radiometer (ACR)

• SOLCON experiments

SAREX II: See STS-35.
Table 3–78. STS-56 Mission Characteristics (Continued)

Experiments Commercial Materials Dispersion Apparatus 

Instrumentation Technology Associates Experime

(CMIX): This collection of experiments was hous

a CRIM, replacing a middeck locker. The CRIM 

contained four MDA mini-lab units designed to m

variety of fluids and/or fluids and solids in the 

microgravity environment. The CRIM also contai

10 Bioprocessing Modules (BPM) designed to mi

fluids to perform immune cell response experimen

microgravity. The experiments studied protein cry

growth, collagen polymerization, fibrin clot forma

liquid-solid diffusion, and the formation of thin fi

membranes. See STS-52.

Experiments developed by the University of Alab

Huntsville Consortium for Materials Developmen

Space and its affiliates included:

• Bone Cell Differentiation (MDA)

• Immune Cell Response (MDA)

• Diatoms (MDA)

• Mouse Bone Marrow Cells (MDA)

• Nerve/Muscle Cell Interactions 

• Phagocytosis (MDA)

• Other experiments evaluating fluids mixing, 

invertebrate and bone development, virus sub-un

assembly and collagen self-assembly, and forma

of drug encapsulated liposomes

• Live Cell Investigations (BPM)

Experiments developed by ITA, Inc. and its affilia

include:

• Collagen Reconstitution (MDA)

• Microencapsulation (MDA)

• Urokinase Protein Crystal Growth (MDA)

• Bacterial Aldolase and Rabbit Muscle Aldolase 

Protein Crystal Growth (MDA)

• HIV Reverse Transcriptase (MDA)

• RNA Protein Crystal Growth (MDA)

• Methylase Protein Crystal Growth (MDA)

• Lysozyme Protein Crystal Growth (MDA)

• DNA-Heme Protein Crystal Growth (MDA)

• Brine Shrimp Development (MDA)

• Cell Research (MDA)

• Other commercial MDA experiments included 

inorganic assembly (proprietary), myoglobin pro

crystal growth, dye and yeast cell diffusion, and 

engineering tests

• Mustard Seed Germination (MDA-student)
Table 3–78. STS-56 Mission Characteristics (Continued)

Experiments PARE-03: See STS-48.

STL-3: See STS-53.

CREAM: See STS-48.

HERCULES: See STS-53.

RME-III: See STS-28.

AMOS Calibration Test: See STS-29.

Get Away Specials Solar Ultraviolet Experiment (SUVE)

Customer: Colorado Space Grant Consortium

Measured extreme ultraviolet and far ultraviolet s

irradiance with two spectrometers.

Mission Results Successful

a See chapter 4, Space Science, for details of the SPARTAN satellites.
Table 3–79. STS-55 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Steven R. Nagel

PLT: Terence T. Henricks

MS: Jerry L. Ross, Charles J. Precourt, Bernard A

Harris, Jr.

PS: Ulrich Walter (Germany), Hans W. Schlegela

(Germany)

Launch April 26, 1993, 10:50:00 a.m. EDT, Kennedy Spac

Center, Pad 39-A. Launch first set for February sli

to early March after questions arose about turbine 

tip seal retainers in the high-pressure oxidizer 

turbopumps on the orbiter main engines. When 

engineers could not verify whether old or new reta

were on Columbia, NASA opted to replace all thre

turbopumps at the pad as a precaution.

The March 14 launch date slipped again after a 

hydraulic flex hose burst in the aft compartment d

a Flight Readiness Test. All 12 hydraulic lines in t

compartment were removed and inspected; 9 lines 

reinstalled, and 3 new lines were put in.

Launch set for March 21 was pushed back 24 hour

to range conflicts caused by a Delta II one-day lau

delay. Orbiter computers aborted a liftoff attempt 

March 22 at T-3 seconds because of incomplete ig

of the No. 3 main engine. The liquid oxygen prebu

check valve leaked internally, causing an overpres

ized purge system that, in turn, prevented full engi

ignition. This was the first on-the-pad main engine 

since return to flight, and the third in program hist

(51-F and 41-D were the other two). The valve lea

later traced to contamination during manufacturin

NASA decided to replace all three main engines o

Columbia with spares.

Launch was reset for April 24 but was scrubbed ea

launch morning when one of orbiter’s three inertia

measurement units (IMU) gave a possible faulty 

reading. Liftoff was postponed for 48 hours to allo

removal and replacement of the IMU. The final la

countdown on April 26 proceeded smoothly. 

Orbital Altitude & 163 nmi (302 km), 28.45 deg

Inclination

Launch Weight (lb/kg) 255,441b/115,866

Landing & Postlanding May 6, 1993, 7:29:59 a.m. PDT, Runway 22, Edw

Operations Air Force Base. Landing originally set for Kenned

Space Center moved to Edwards because of cloud 
Table 3–79. STS-55 Mission Characteristics (Continued)

Rollout Distance (ft/m) 10,125/3,086

Rollout Time (seconds) 61

Mission Duration 239 hr, 39 min, 59 sec

Landed Revolution No. 159

Mission Support STDN

Primary Objective Microgravity research using the German Spacelab 

Deployed Satellites None

Experiments Spacelab D-2: The D-2 mission augmented the Ge

microgravity research program started by the D-1 

Spacelab mission in 1985. The German Aerospace 

Research Establishment (DLR) had been tasked b

DARA to conduct the second mission. DLR, NAS

ESA, and agencies in France and Japan contribute

D-2’s scientific program. Eleven nations participa

the experiments. 

Of the 88 experiments conducted on the D-2 miss

four were NASA-sponsored. The crew worked in 

shifts around-the-clock to complete investigations 

areas of fluid physics; materials sciences; life scie

biological sciences; technology; Earth observation

atmospheric physics; and astronomy. 

The payloads were: 

Material Science Experiment Double Rack for 

Experiment Modules and Apparatus (MEDEA)

• Floating Zone Growth of GaAs

• Floating Zone Crystal Growth of Gallium-Dope

Germanium

• Hysteresis of the Specific Heat CV During Heat

and Cooling Through the Critical Point

• Diffusion of Nickel in Liquid Copper-Aluminum 

Copper-Gold Alloys

• Directional Solidification of Ge/GaAs Eutectic 

Composites

• Cellular-Dendritic Solidification with Quenchin

Aluminum-Lithium Alloys

• Thermoconvection at Dendritic-Eutectic Solidifi

of an Al-Si Alloy

• Growth of GaAs from Gallium Solutions

Werkstofflabor (WL) Material Sciences Laborator

• OSIRIS: Oxide Dispersion Strengthened Single 

Crystalline Alloys Improved by Resolidification 

Space

• Impurity Transport and Diffusion in InSb Melt U

Microgravity Environment

• Cellular-Dendritic Solidification at Low Rate of 

Aluminum-Lithium Alloys

• Directional Solidification of the LiF-LiBaF3-Eu

• Separation Behavior of Monotectic Alloys
Table 3–79. STS-55 Mission Characteristics (Continued)

Experiments • Liquid Columns’ Resonances

• Stability of Long Liquid Columns

• Higher Modes and Their Instabilities of Oscillat

Marangoni Convection in a Large Cylindrical Li

Column

• Marangoni-Benard Instability

• Onset of Oscillatory Marangoni Flows

• Marangoni Convection in a Rectangular Cavity

• Stationary Interdiffusion in a Non-Isothermal M

Salt Mixture

• Transport Kinetics and Structure of Metallic Me

• Nucleation and Phase Selection During Solidific

of Undercooled Alloys

• Heating and Remelting of an Allotropic Fe-C-Si 

in a Ceramic Skin and the Effect of the Volume 

Change on the Mold’s Stability

• Immiscible Liquid Metal Systems

• Convective Effects on the Growth of GaInSb Cr

• Vapor Growth of InP-Crystal with Halogen Tran

in a Closed Ampoule

• Solution Growth of GaAs Crystals Under 

Microgravity

• Crystallization of Nucleic Acids and Nucleic Ac

Protein Complexes

• Crystallization of Ribosomal Particles

Holographic Optics Laboratory (HOLOP)

• Marangoni Convection in a Rectangular Cavity

• Interferometric Determination of the Differentia

Interdiffusion Coefficient of Binary Molten Salt

• IDILE: Measurements of Diffusion Coefficients 

Aqueous Solution

• NUGRO: Phase Separation in Liquid Mixtures w

Miscibility Gap

Baroreflex (BA) 

• Residual Acceleration in Spacelab D2

• Transfer Function Experiment

• Robotics Experiment (ROTEX)

• Anthrorack (AR)

• Cardiovascular Regulation at Microgravity

• Central Venous Pressure During Microgravity

• Leg Fluid Distribution at Rest and Under Lower 

Negative Pressure

• Determination of Segmental Fluid Content and 

Perfusion

• Left Ventricular Function at Rest and Under 

Stimulation

• Peripheral and Central Hemodynamic Adaptatio

Microgravity During Rest, Exercise, and Lower 

Negative Pressure in Humans
Table 3–79. STS-55 Mission Characteristics (Continued)

Experiments • Tonometry–Intraocular Pressure in Microgravity

• Tissue Thickness and Tissue Compliance Along 

Axis Under Microgravity Conditions

• Changes in the Rate of Whole-Body Nitrogen 

Turnover, Protein Synthesis, and Protein Breakd

Under Conditions of Microgravity

• Regulation of Volume Homeostasis in Reduced 

Gravity Possible Involvement of Atrial Natriuret

Factor Urodilatin and Cyclic GMP

• Effects of Microgravity on Glucose Tolerance

• Effects of Spaceflight on Pituitary-Gonad-Adren

Function in the Human

• Adaptation to Microgravity and Readaptation to 

Terrestrial Conditions

• Pulmonary Perfusion and Ventilation in Microgr

Rest and Exercise

• Ventilation Distribution in Microgravity

• Effects of Microgravity on the Dynamics of Gas 

Exchange, Ventilation, and Heart Rate in Subma

Dynamic Exercise

• Cardiovascular Regulation in Microgravity

• Biolabor (BB)

• Development of Vestibulocular Reflexes in Amp

and Fishes with Microgravity Experience

• Comparative Investigations of Microgravity Effe

Structural Development and Function of the Gra

Perceiving Organ of Two Water-Living Vertebra

• Structure and Function-Related Neuronal Plastic

the Central Nervous System of Aquatic Vertebra

During Early Ontogenetic Development Under 

Microgravity Conditions

• Immunoelectron Microscopic Investigation of 

Cerebellar Development at Microgravity

• Gravisensitivity of Cress Roots

• Influence of Gravity on Fruiting Body Developm

Fungi

• Significance of Gravity and Calcium Ions on the 

Production of Secondary Metabolites in Cell 

Suspensions

• Influence of Conditions in Low-Earth Orbit on 

Expression and Stability of Genetic Information 

Bacteria

• Productivity of Bacteria

• Fluctuation Test on Bacterial Cultures

• Connective Tissue Biosynthesis in Space: Gravit

Effects on Collagen Synthesis and Cell Prolifera

of Cultured Mesenchymal Cells

• Antigen-Specific Activation of Regulatory 

T-Lymphocytes to Lymphokine Production

• Growth of Lymphocytes Under Microgravity 

Conditions
Table 3–79. STS-55 Mission Characteristics (Continued)

Experiments • Enhanced Hybridoma Production Under Microg

• Culture and Electrofusion of Plant Cell Protopla

Under Microgravity: Morphological/Biochemica

Characterization

• Yeast Experiment HB-L29/Yeast: Investigations 

Metabolism

Cosmic Radiation Experiments

• Biological Hze-Particle Dosimetry with Biostack

• Personal Dosimetry: Measurement of the Astron

Ionizing Radiation Exposure

• Measurement of the Radiation Environment Insi

Spacelab at Locations Which Differ in Shielding 

Against Cosmic Radiation

• Chromosome Aberration

• Biological Response to Extraterrestrial Solar UV 

Radiation and Space Vacuum

User Support Structure Payloads

• Module Optoelectronic Multispectral Stereo Sca

(MOMS)

• Galactic Ultrawide-Angle Schmidt System (GAU

• Atomic Oxygen Exposure Tray (AOET)

• Material Science Autonomous Payload (MAUS)

– Reaction Kinetics in Glass Melts Payload (RK

– Pool Boiling

– Gas Bubbles in Glass Melts

Crew Telesupport Experiment (CTE): Combined a

board computer-based multimedia documentation 

with a real-time, graphical communication betwee

on-orbit crew members and the ground station.

SAREX II: See STS-35.

Get Away Specials None

Mission Results Successful

Remarks Spacelab D-2 conducted the first telerobotic captur

free-floating object by flight controllers in Germa

The crew conducted the first intravenous saline so

injection in space as part of an experiment to study 

human body’s response to direct fluid replacemen

countermeasure for amounts lost during spacefligh

crew also successfully completed an in-flight 

maintenance procedure for collection of orbiter 

wastewater that allowed the mission to continue.

Spacelabs D1 and D2 were the only Spacelab mis

to date with payload operations controlled from a 

foreign country.

a Integrated into ESA’s single European astronaut corp in 1998. b Jenkins, p. 302.
Table 3–80. STS-57 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Ronald J. Grabe

PLT: Brian Duffy

MS: G. David Low, Nancy J. Sherlock (Currie), P

J.K. Wisoff, Janice E. Voss

Launch June 21, 1993, 9:07:22 a.m. EDT, Kennedy Space 

Center, Pad 39-B. The launch originally targeted f

mid-May was rescheduled to June to allow both li

and landing to occur in daylight. Liftoff set for Jun

slipped when managers decided to replace the hig

pressure oxidizer turbopump on main engine No. 2 

concerns arose over a misplaced inspection stamp 

spring in the pump. Additional time also allowed 

investigation of an inexplicable loud noise heard a

the Shuttle arrived at the launch pad, which was 

eventually attributed to the ball strut tie-rod assem

inside the 17-in (43-cm) liquid hydrogen line. The 

launch attempt on June 20 was scrubbed at T-5 mi

due to low clouds and rain at the return-to-launch 

Kennedy Space Center, and weather concerns at al

transoceanic abort landing sites. The launch count

was the longest since return to flight to allow serv

of payloads at the pad.

Orbital Altitude & 

Inclination

252 nmi (467 km), 28.45 deg

Launch Weight (lb/kg) 252,710a/114,627

Landing & Postlanding 

Operations

July 1, 1993, 8:52:16 a.m. EDT, Runway 33, Kenn

Space Center. Landing attempts on June 29 and Ju

were waved off due to unacceptable cloud cover an

showers at Kennedy Space Center. After landing, 

STS-57 crew on Endeavour talked with the STS-5

on Discovery at Pad 39-B. It was the first orbiter-t

orbiter crew conversation since the orbiting STS-5

crew talked with the STS 51-B crew at Kennedy S

Center in 1985.

Rollout Distance (ft/m) 9,954/3,034

Rollout Time (seconds) 65

Mission Duration 239 hr, 44, min, 54 sec

Landed Revolution No. 154

Mission Support STDN

Primary Objective Retrieval of EURECA and biomedical and materia

science experimentation using the SPACEHAB m

Deployed Satellites None
Table 3–80. STS-57 Mission Characteristics (Continued)

Experiments SPACEHAB 01 Experiments:

• Commercial Material Science Experiments

– Equipment for Controlled Liquid Phase Sinter

Experiment-SPACEHAB (ECLiPSE)

– GPPM

– IPMP

– Liquid Encapsulated Melt Zone (LEMZ)

– Support of Crystal Growth (SCG)

– Zeolite Crystal Growth (ZCG)

• Commercial Life Science Experiments

– ASTROCULTURETM

– BioServe Pilot Laboratory (BPL)

– CGBA

– Organic Separation (ORSEP)

– PCG 

– Vapor Diffusion Apparatus and Crystallization 

Facility Experiments

– Direct-Control Protein Crystal Growth

– PSE

• Johnson Space Center Experiments

– Application-Specific Pre-programmed Experi

Culture (ASPEC)

– Charged Particle Directional Spectrometer (C

– Human Factors Assessment (HFA)

– Neutral Body Posture (NBP)

– Tools and Diagnostics System (TDS)

• Space Station Experiment

– Environmental Control Life Support System 

(ECLSS) Flight Experiment

• Supporting Hardware Overview

– Three-Dimensional Microgravity Accelerome

(3-DMA)

– SAMS

FARE: See STS-53.

SAREX-II: See STS-35.

AMOS Calibration Test: See STS-29.

Consortium for Materials Development in Space 

Complex Autonomous Payload IV (CONCAP IV)

complex was designed to grow non-linear optical 

organic thin films and crystals through the physica

vapor transport process. The payload was carried o

GAS Bridge Assembly.

Superfluid Helium On-Orbit Transfer (SHOOT): 

SHOOT was designed to develop and demonstrate 

technology required to resupply liquid helium cont

in space. It was carried on the GAS Bridge Assem
Table 3–80. STS-57 Mission Characteristics (Continued)

Get Away Specials G-022

Customer: ESA, European Space Research and 

Technology Centre, Noordwijk, the Netherlands

Liquid Gauging Technology Experiment: This 

experiment demonstrated two on-orbit methods of 

gauging liquids in tanks.

G-324

Customer: Charleston County School District, 

Charleston, South Carolina

CAN-DO (GEOCAM): The CAN-DO consisted o

35-mm cameras for Earth photography to compare 

Skylab photographs. The canister also contained 3

small passive student experiments that allowed stu

to participate directly in research by testing the eff

space on various materials.

G-399 

Customer: Dr. Ronald S. Nelson, Inc., Fresno, Cal

Insulin/Artemia/Ion Experiments: These experime

studied Ferritin-tagged insulin, Artemia growth, an

ion transport across a permeable membrane.

G-450 

Customer: American Institute of Aeronautics and 

Astronautics, Vandenberg Air Force Base, Califor

Multiple Experiments: G-450 was a multidisciplin

package of six self-contained modules, each conta

multiple experiments designed and developed by 

California elementary, middle, and high school stu

G-452 

Customer: Society of Japanese Aerospace Compa

Tokyo, Japan

Crystal Growth of Gallium Arsenide: G-452 had t

small electric furnaces used to carry out the follow

experiments in low gravity.

Growth of a single gallium-arsenide crystal from t

liquid phase.

Growth of a gallium-arsenide-based mixed crystal

Addition of a heavy element to gallium-arsenide.

Addition of a heavy element to indium-antimony c

G-453 

Customer: Society of Japanese Aerospace Compa

Tokyo, Japan

Semiconductor/Superconductor Boiling Experime

G-453 consisted of three experiments on semiconductors and a superconductor and one experim

boiling an organic solvent under weightlessness.
Table 3–80. STS-57 Mission Characteristics (Continued)

Get Away Specials G-454 

Customer: Society of Japanese Aerospace Compa

Tokyo, Japan

Crystal Growth: This experiment studied the cryst

growth of indium-gallium-arsenic from vapor pha

under weightlessness, the crystal growth of 3-selen

niobium from vapor phase, the crystal growth of a

optoelectric crystal by the diffusion method, and t

formation of superferromagnetic alloy.

G-535 

Customer: NASA Headquarters, OSSA

Pool Boiling Experiment: This was a study of hea

vapor and bubble growth/collapse.

G-601 

Customer: San Diego Section, American Institute 

Aeronautics and Astronautics, San Diego, Californ

High Frequency Variations of the Sun: This experi

measured and analyzed high-frequency solar outpu

better determine the physics of the Sun and other s

G-647 

Customer: Canadian Space Agency, Ottawa, Onta

Canada 

Liquid Phase Electroepitaxy, Configurable Hardwa

Multidisciplinary Projects in Space (CHAMPS): G

provided a versatile payload for materials science 

experiments in space. The experiment examined a 

recently developed technique for crystal growth ca

Liquid Phase Electro-Epitaxy (LPEE) in a microg

environment.

GAS Ballast Payload

Customer: Goddard Space Flight Center, Greenbe

Maryland

Ballast payloads were flown for stability when a G

payload was dropped and no replacement was ava

A small accelerometer package recorded accelerat

during the mission.

Sample Return Experiment: This experiment sat on 

the ballast GAS cans. It quantified extraterrestrial 

particles and other orbital debris present in the orbit

Mission Results Successful

a Jenkins, p. 302.
Table 3–81. STS-51 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Frank L. Culbertson, Jr.

PLT: William F. Readdy

MS: James H. Newman, Daniel W. Bursch, Carl E

Walz

Launch September 12, 1993, 7:45:00 a.m. EDT, Kennedy S

Center, Pad 39-B. The first launch attempt on July 

was scrubbed during a hold at T-20 minutes due to 

premature and unexplained charging of pyrotechni

initiator controllers (PIC), located on the mobile 

launcher platform (MLP), for T-0 liquid hydrogen 

arm umbilical and solid rocket booster hold-down b

The problem was traced to a faulty circuit card in 

PIC rack on the MLP. 

An abbreviated countdown began July 23. A secon

liftoff attempt on July 24 was halted at T-19 secon

due to a problem with the auxiliary power unit (AP

turbine assembly for one of the two hydraulic pow

units on the right solid rocket booster. The APU w

removed and replaced at pad.

Launch was rescheduled for August 4 to August 1

because of concerns relating to the Perseid meteor 

shower, which was expected to peak on August 11

A liftoff attempt on August 12 was halted at the T-

second mark due to a faulty sensor monitoring fuel 

on main engine No. 2. This was the fourth pad abo

Shuttle program history that led to a changeout of 

three main engines at the pad. 

The launch was rescheduled for September 10 but 

slipped to September 12 to allow time to complete 

review of the ACTS design, production, and testin

history following the loss of contact with the Mars 

Observer and NOAA-13 satellite.

The countdown proceeded smoothly to an on-time 

liftoff on September 12.

Orbital Altitude & 160 nmi (296 km), 28.45 deg

Inclination

Launch Weight (lb/kg) 261,486a/118,608
Table 3–81. STS-51 Mission Characteristics (Continued)

Landing & Postlanding 

Operations

September 22, 1993, 3:56:11 a.m. EDT, Runway 1

Kennedy Space Center. A September 21 landing 

opportunity was waved off due to the possibility o

within 30 miles of the Shuttle Landing Facility. It 

the first end-of-mission night landing at Kennedy S

Center for the Shuttle program.

Rollout Distance (ft/m) 8,271/2,521

Rollout Time (seconds) 50

Mission Duration 236 hr, 11 min, 11 sec

Landed Revolution No. 156

Mission Support STDN

Primary Objective Deploy ACTS; deployment and retrieval of ORFE

SPAS

Deployed Satellites ACTS/TOS

ORFEUS-SPAS (See chapter 4, Space Science, fo

description of science objectives and payload.)

Experiments IMAX: The ORFEUS-SPAS payload was recorded 

the Shuttle using a handheld IMAX camera; the Sh

was recorded using the Remote IMAX Camera Sys

(RICS) mounted on the free-flying ORFEUS-SPAS

CPCG: See STS-49.

CHROMEX: See STS-29.

High Resolution Shuttle Glow Spectroscopy (HRS

A): This payload obtained high-resolution spectra i

visible and near visible wavelength range of the Sh

surface glow.

APE-B: See STS-33.

RME-III: See STS-28. 

IPMP: See STS-31.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful

a Jenkins, p. 302. b See chapter 4, Space Science, of this volume for further discussion of the ORFEUS-SPAS miss
Table 3–82. STS-58 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: John E. Blaha

PLT: Richard A. Searfoss

MS: Margaret Rhea Seddon, William S. McArthu

David A. Wolf, Shannon W. Lucid

PS: Martin J. Fettman

Launch October 18, 1993, 10:53:10 a.m. EDT, Kennedy S

Center, Pad 39-B. The first launch attempt on Oct

14 was scrubbed at T-31 seconds due to a failed R

Safety computer. The second launch attempt on O

15 was scrubbed at T-9 minutes due to failed a S-b

transponder on the orbiter. Launch was reset for O

18. Countdown proceeded smoothly to liftoff, del

only by several seconds because of an aircraft in t

launch zone.

Orbital Altitude & 

Inclination

155 nmi (287 km), 39.00 deg

Launch Weight (lb/kg) 256,097a/116,164

Landing & Postlanding 

Operations

November 1, 1993, 7:05:42 a.m. PST, Runway 22, 

Edwards Air Force Base. The orbiter returned to Ke

Space Center on November 9 after a two-day trip.

Rollout Distance (ft/m) 9,640/2,938

Rollout Time (seconds) 61 

Mission Duration 336 hr, 12 min, 32 sec

Landed Revolution No. 225

Mission Support STDN

Primary Objective Dedicated Spacelab Life Sciences research 

Deployed Satellites None
Table 3–82. STS-58 Mission Characteristics (Continued)

Experiments SLS-2 mission using the Spacelab long module: T

crew conducted 14 experiments in four areas: regu

physiology, cardiovascular/cardiopulmonary, 

musculoskeletal, and neurosciences. Eight of the 

experiments focused on the crew, six on 48 rodent

crew collected more than 650 different samples fr

themselves and the rodents, increasing the statistic

base for life sciences research.

Cardiovascular/cardiopulmonary experiments: Th

experiments focused on understanding and quanti

the changes occurring on orbit and on the acute fl

shift and long-term adaptation of the heart and lun

• Inflight Study of Cardiovascular Deconditioning

• Cardiovascular Adaptation to Zero Gravity

• Pulmonary Function During Weightlessness

Regulatory physiology experiments: These experi

investigated the theory that the kidneys and endoc

glands adjusted the body’s fluid-regulating hormo

stimulate an increase in fluid to be excreted. The 

experiments also investigated the mechanisms 

surrounding the decrease in red blood cells respon

for carrying oxygen to the tissues that occurred in 

spaceflight.

• Fluid-Electrolyte Regulation During Spaceflight

• Regulation of Blood Volume During Spacefligh

• Regulation of Erythropoiesis in Rats During 

Spaceflight

• Influence of Spaceflight on Erythrokinetics in M

Neuroscience investigations: These investigations 

documented both physical vestibular (balance) ch

and perception changes and investigated the 

mechanisms involved. The investigators also hope

identify countermeasures to alleviate the effects of 

motion sickness. The mission included an Astrona

Science Advisor (ASA), a computer-based intellig

assistant designed to help astronauts work more 

efficiently and improve the quality of space scienc

ASA supported the Rotating Dome Experiment, w

measured how the visual and vestibular systems in

and how this interaction was affected as humans a

to microgravity. The experiment included:

• Study of the Effects of Space Travel on Mamma

Gravity Receptors

• Vestibular Experiments in Spacelab
Table 3–82. STS-58 Mission Characteristics (Continued)

Experiments Musculoskeletal investigations: In microgravity, th

body’s bones and muscles were used less extensiv

than on Earth. As a result, researchers saw a decre

the mass of both during spaceflight. The SLS-2 st

provided more information about the complex 

musculoskeletal system, including:

• Protein Metabolism During Spaceflight

• Effects of Zero Gravity on the Functional and 

Biochemical Properties of Antigravity Skeletal 

Muscle

• Effects of Microgravity on the Electron Microsc

Histochemistry, and Protease Activities of Rat 

Hindlimb Muscles

• Pathophysiology of Mineral Loss During Space

• Bone, Calcium, and Spaceflight

OARE: See STS-40.

SAREX: See STS-35.

Pilot Inflight Landing Operations Trainer (PILOT

PILOT, a portable laptop computer simulator, allo

the pilot and commander to maintain proficiency f

approach and landing during longer missions.

Get Away Specials None

Mission Results Successful

a Jenkins, p. 302.
Table 3–83. STS-61 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Richard O. Covey

PLT: Kenneth D. Bowersox

PCF: Story Musgrave

MS: Kathryn C. Thornton, Claude Nicollier (ESA

Jeffrey A. Hoffman, F. Story Musgrave, Thomas D

Akers

Launch December 2, 1993, 4:27:00 a.m. EST, Kennedy Sp

Center, Pad 39-B. The launch was originally sche

to occur from Launch Pad 39-A, but after rollout 

October 28, contamination was found in the Pad 3

Payload Changeout Room, and a decision was ma

move the Shuttle and payloads to Pad 39-B. Rollar

occurred on November 15. The first launch attemp

December 1 was scrubbed due to out-of-limit wea

conditions at the Shuttle Landing Facility in the e

of a return-to-launch-site contingency. Launch on 

December 2 occurred on schedule.

Orbital Altitude & 

Inclination

321 nmi (594 km), 28.45 deg

Launch Weight (lb/kg) 250,314/113,541

Landing & Postlanding 

Operations

December 13, 1993, 12:25:37 a.m. EST, Runway 

Kennedy Space Center. Second night landing at 

Kennedy Space Center. The orbiter returned one o

earlier than originally planned to allow two landin

opportunities at Kennedy Space Center.

Rollout Distance (ft/m) 7,922/2,415

Rollout Time (seconds) 53

Mission Duration 259 hr, 58 min, 37 sec

Landed Revolution No. 162

Mission Support STDN

Primary Objective First Hubble Space Telescope Servicing Mission

Deployed Satellites Hubble Space Telescope retrieved and redeployed 

servicing

Experiments None

Get Away Specials None

Mission Results Successful
Table 3–83. STS-61 Mission Characteristics (Continued)

Remarks The record-setting five back-to-back spacewalks 

totaled 35 hours, 28 minutes.

EVA No.1, by Hoffman and Musgrave, lasted 7 h

54 minutes. The two spacewalkers replaced two s

remote sensing units, which contained gyroscopes 

helped the Hubble Space Telescope point in the co

direction. They also replaced two electronic contr

units and eight electrical fuse plugs protecting the 

telescope’s electrical circuits. This was the second 

longest spacewalk in U.S. history to date.

EVA No. 2, by Akers and Thornton, lasting 6 hou

minutes, replaced the telescope’s two solar arrays

EVA No. 3, by Hoffman and Musgrave, lasted 6 h

minutes. They replaced the original WF/PC with a 

WFPC-2 in about 40 minutes rather than the 4 ho

that had been anticipated. The new camera had a h

rating than the previous model, especially in the 

ultraviolet range, and included its own spherical 

aberration correction system. They also replaced t

magnetometers. 

EVA No. 4, by Akers and Thornton, lasting 6 hrs, 

minutes, replaced the Hubble Space Telescope’s H

Speed Photometer (HSP) with the COSTAR syste

COSTAR corrected the telescope’s spherical aberr

of the main mirror for all instruments except WFP

which had its own built-in corrective optics. Durin

spacewalk, Akers set a new individual U.S. 

spacewalking record of 29 hours, 14 minutes.

EVA No. 5, by Hoffman and Musgrave, lasted 7 h

minutes. This EVA replaced the solar array drive 

electronics and, after several unsuccessful comma

from the Space Telescope Operations Control Cen

the astronauts cranked the solar arrays’ deployme

mechanism by hand, successfully deploying them

They also installed the GHRS Redundancy Kit an

protective covers over the original magnetometers

covers, which were fabricated on board by astrona

Nicollier and Bowersox, would contain any debri

caused by the older magnetometers, which showe

some signs of ultraviolet decay.
Table 3–84. STS-60 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Charles F. Bolden, Jr.

PLT: Kenneth S. Reightler, Jr.

MS: N. Jan Davis, Ronald M. Sega, Franklin R. C

Diaz, Sergei K. Krikalev (Russian Space Agency/

Launch February 3, 1994, 7:10:00 a.m. EST, Kennedy Spa

Center, Pad 39-A. Launch was on time.

Orbital Altitude & 

Inclination

191 nmi (354 km), 57.00 deg

Launch Weight (lb/kg) 245,767a/111,478

Landing & Postlanding 

Operations

February 11, 1994, 2:19:22 p.m. EST, Runway 15

Kennedy Space Center. The first landing attempt w

waved off due to unfavorable weather in the Kenn

Space Center area.

Rollout Distance (ft/m) 7,771/2,368

Rollout Time (seconds) 50

Mission Duration 199 hr, 9 min, 22 sec

Landed Revolution No. 129

Mission Support STDN

Primary Objective Experimentation using WSF-1 and SPACEHAB 0

Deployed Satellites WSF-1: There were two unsuccessful attempts to d

the facility. The WSF-1 was instead operated at th

of the remote manipulator system arm.

Experiments SPACEHAB 02: SPACEHAB 02 carried 12 payloa

conducted under the Commercial Middeck 

Augmentation Module contract. The experiments 

represented a wide range of space experimentation 

including nine commercial-development-of-space 

experiments in materials processing and biotechno

sponsored by five NASA CCDS; three supporting 

hardware and technology development payloads, o

from a CCDS, one from Lewis Research Center; a

from Johnson Space Center. In addition, a Sample R

Experiment sat on the top of the SPACEHAB mod

SPACEHAB 02 Payloads:b

• SPACEHAB (ECLiPSE): This experiment used 

mounted, enclosed furnace assembly to investig

controlled liquid-phase sintering of metallic syst

microgravity.

• Space Experiment Furnace: This payload allowed 

three separate furnaces in one unit. This flight car

one transparent furnace and one opaque core furn
Table 3–84. STS-60 Mission Characteristics (Continued)

Experiments • ASTROCULTURETM: This payload validated th

performance of plant growth technologies in the 

microgravity environment of space.

• BPL: This experiment determined the response o

to various hormones and stimulating agents in 

microgravity.

• CGBA: The apparatus allowed a wide range of 

sophisticated biomaterials, life sciences, and 

biotechnology investigations to be performed in 

device in a microgravity environment. It process

biological fluids by mixing components in a 

microgravity environment. The CGBA also supp

32 separate commercial investigations in the are

biomedical testing and drug development, contr

ecological life support system development, and 

agricultural development and manufacture of 

biological-based materials.

• IMMUNE-1: This experiment was designed to r

or prevent changes seen in the immune system o

rats after spaceflight. The drug PEG-IL2 was use

attempt to alleviate the immunosuppression indu

the microgravity environment. The experiment m

provide a new therapy to treat the effects of spac

on the human immune system, as well as on phy

ical systems affected by the immune system.

• ORSEP: This experiment explored the use of ph

separation techniques in microgravity condition

separate cells, cell fragments, and heavy molecu

• CPCG: This experiment was designed to produce 

well-ordered crystals of various proteins. See STS

• Penn State Biomodule: This was a computer-cont

fluid-transfer mixing device used to test the hypo

that exposure to near-zero gravity can alter micro

gene expression in commercially useful ways.

• 3-DMA: The accelerometer helped chart the eff

deviations of zero gravity on experiments condu

space, allowing researchers to review experimen

results against deviations from zero gravity.

• SAMS: The SAMS measured and recorded low-

accelerations during experiment operations.

• Stirling Orbiter Refrigerator Freezer (SOR/F): T

experiment was a flight test and characterization 

relating to operation of advanced refrigerator/fre

technology in microgravity.

• Sample Return Experiment: This experiment sat 

of the SPACEHAB module to capture intact cos

dust particles as they came in contact with 160 c

cells. The capture cells consisted of transparent 

aerogel, the lowest density solid material known 

extremely fine structure.
Table 3–84. STS-60 Mission Characteristics (Continued)

Get Away Specials G-071

Customer: California State University, Northridge

OBBEX: This apparatus tested the effects of melt

cylindrical metal alloy pellets in microgravity to pr

a new kind of ball bearing never before built, a sea

hollow ball bearing.

G-514 

Customer: Goddard Space Flight Center

The Orbiter Stability Experiment: The objective w

measure the vibration spectrum of the orbiter stru

present during normal orbiter and crew operations 

evaluate fogging of photographic emissions due to 

energetic particles.

G-536 

Customer: NASA Headquarters, OSSA, Microgra

Sciences Division

The Pool Boiling Experiment: This experiment m

the 100th GAS payload to fly since the program’s 

inception. The experiment’s objective was to impr

understanding of the boiling process in micrograv

G-557 

Customer: ESA 

The Netherlands Capillary Pumped Loop (CPL) 

Experiment: This experiment demonstrated in-orb

working principle and performances of a two-pha

CPL, a two-phase Vapor Quality Sensor, and a tw

phase multichannel Condenser Profile. It also com

data on CPL behavior in a low-gravity environmen

analytical predictions resulting from modeling and 

Earth performance.

CAPL/ODERACS/BREMSAT/GAS Bridge Asse

• Capillary Pumped Loop (CAPL): This system 

investigated heat rejection in microgravity as a 

prototype of the two-phase thermal control syste

planned for use in the Earth Observing System (

platform. This flew as a Hitchhiker payload.

• ODERACS: This experiment deployed six spher

were observed, tracked, and recorded by ground

radars and optical telescopes. 
Table 3–84. STS-60 Mission Characteristics (Continued)

Get Away Specials • BREMEN Satellite (BREMSAT): The satellite 

conducted scientific activities at various mission 

phases. This German-built, ejectable satellite con

of six scientific experiments operated before and 

satellite deployment. The experiments measured 

conductivity; residual acceleration forces; densi

distribution and dynamics of micrometeorites an

particles in low-Earth orbit; atomic oxygen; exc

of momentum and energy between the molecula

and the rotating satellite; and pressure and tempe

during reentry.

Mission Results The WSF was not deployed but was operated at th

of the robot arm. Other mission objectives were 

successfully achieved.

a Jenkins, p. 302. b “Space Shuttle Mission STS-60 Press Kit” (February 1994, with Errata and Updates from Janu

1994, http://www.jsc.nasa.gov/history/shuttle_pk/pk/Flight_060_STS-060_Press_Kit.pdf (acce

December 2, 2005).
Table 3–85. STS-62 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: John H. Casper

PLT: Andrew M. Allen

MS: Pierre J. Thuot, Charles D. Gemar, Marsha S

Launch March 4, 1994, 8:53:00 a.m. EST, Kennedy Space C

Pad 39-B. Launch set for March 3 was postponed at 

T-11 hour mark due to predicted unfavorable weather 

Kennedy Space Center area. The countdown on Mar

proceeded smoothly. The only deviation to normal 

operating procedures was a delay in deploying the so

rocket booster recovery ships because of high seas. T

recovery ships left port on launch day and recovered 

boosters and their parachutes on March 6.

Orbital Altitude & 

Inclination

162 nmi (300 km) and 140 nmi (259 km), 39.00 d

Launch Weight (lb/kg) 256,584a/116,385

Landing & Postlanding 

Operations

March 18, 1994, 8:09:41 a.m. EST, Runway 33, 

Kennedy Space Center. 

Rollout Distance (ft/m) 10,151/3,094

Rollout Time (seconds) 55

Mission Duration 335 hr, 16 min, 41 sec

Landed Revolution No. 223

Mission Support STDN

Primary Objective Experimentation using USMP-2 and OAST-2

Deployed Satellites None

Experiments USMP-2: These experiments investigated materia

processing and crystal growth in microgravity. 

• Advanced Automated Directional Solidification 

Furnace (AADSF) 

• MEPHISTO 

• Isothermal Dendritic Growth Experiment (IDGE

• Critical Fluid Light Scattering Experiment (ZEN

• SAMS
Table 3–85. STS-62 Mission Characteristics (Continued)

Experiments OAST-2: The objective of this payload was to obt

technology data to support future needs for advan

satellites, sensors, microcircuits, and the ISS. Six 

In-Space Technology Program (INSTEP) experim

were mounted on a Hitchhiker carrier.

• Experimental Investigation of Spacecraft Glow 

(EISG) and Spacecraft Kinetic Infrared Test (SK

These experiments developed an understanding 

physical processes leading to the spacecraft glow 

phenomena by studying infrared, visible, and fa

ultraviolet light emissions as a function of surfa

temperature and orbital altitude.

• Cryogenic Two Phase (CRYOTP): This experim

determined the performance of microgravity nit

space heat pipe and cryogenically-cooled, vibra

free, phase-change-material thermal storage uni

thermal energy control technologies.

• Thermal Energy Storage (TES): This experimen

determined the microgravity behavior of two dif

thermal energy storage salts that underwent repe

melting and freezing.

• Emulsion Chamber Technology (ECT): This 

experiment measured background cosmic ray 

radiation as a function of shielding and radiation 

energy photographic films.

• Solar Array Module Plasma Interaction Experim

(SAMPIE): This experiment determined the arc

and current collection behavior of different type

sizes, and shapes of solar cells, solar modules, a

spacecraft materials.

Dexterous End Effector (DEE): The DEE worked 

the remote manipulator system and demonstrated 

Force Torque Sensor, Magnetic End Effector, Targ

and Reflective Alignment Concept (TRAC) grapp

alignment system, and Auto TRAC Vision System

SSBUV/A: See STS-34.

LDCE: This experiment exposed material sample

atomic oxygen in the space environment.

Advanced Protein Crystal Growth (APCG): This 

experiment produced high-quality, well-ordered cr

of selected proteins for analysis of molecular stru

through x-ray diffraction and computer modeling

PSE: See STS-52. 

CPCG: See STS-49.

CGBA: See STS-54.

MODE: See STS-40.
Table 3–85. STS-62 Mission Characteristics (Continued)

Experiments Bioreactor Demonstration Systems (BDS): This 

experiment attempted to determine the threshold m

for the transfer/diffusion of glucose and oxygen in

static cell culture in the microgravity environmen

APE-B: See STS-33.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful

a Jenkins, p. 302.
Table 3–86. STS-59 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Sidney M. Gutierrez

PLT: Kevin P. Chilton

PC: Linda M. Godwin

MS: Jerome Apt, Michael R. Clifford, Thomas D. 

Launch April 9, 1994, 7:05:00 a.m. EDT, Kennedy Space 

Center, Pad 39-A. Launch set for April 7 was 

postponed for one day at the T-27-hour mark to al

for additional inspections of the metallic vanes in 

SSME high-pressure oxidizer preburner pumps. 

Launch on April 8 was scrubbed due to weather, h

crosswinds, and low clouds at the Shuttle Landing 

Facility and clouds at the launch pad. The countdo

April 9 proceeded smoothly.

Orbital Altitude & 

Inclination

121 nmi (224 km), 57.00 deg

Launch Weight (lb/kg) 246,851a/111,970

Landing & Postlanding 

Operations

April 20, 1994, 9:54:30 a.m. PDT, Runway 22, 

Edwards Air Force Base. Landing was originally 

planned for Kennedy Space Center on April 19, bu

landing opportunities were waved off due to low c

and possible thunderstorms in the area. An early 

landing opportunity on April 20 was also waved o

favor of landing at Edwards Air Force Base. The o

returned to Kennedy Space Center from Edwards 

Shuttle Carrier Aircraft on May 2, 1994.

Rollout Distance (ft/m) 10,691/3,258

Rollout Time (seconds) 54

Mission Duration 269 hr, 49 min, 30 sec

Landed Revolution No. 182

Mission Support STDN

Primary Objective Study Earth’s global environment using SRL-1

Deployed Satellites None
Table 3–86. STS-59 Mission Characteristics (Continued)

Experiments SRL-1: This was the first simultaneous multifrequ

(C, L, and X bands), multipolarization phased-arr

imaging radar in space for geoscientific studies of 

in different seasons. Used to image sites for geolo

hydrology, vegetation science, and oceanography 

study vegetation type, extent, and deforestation; w

storage and flux; ocean dynamics; wave fields; wi

fields; volcanism; tectonic activity; soil erosion; 

desertification; and topography. The SRL payload 

consisted of: 

• SIR-C 

• X-SAR 

• MAPS

The DARA and the Italian Space Agency provide

X-SAR instrument.

CONCAP-IV: See STS-57.

STL/National Institutes of Health-Cells (NIH)-C: 

Configuration A and B–These experiments valida

models for muscle, bone, and endothelial cell 

biochemical and functional loss induced by 

microgravity stress; to evaluate cytoskeleton, 

metabolism, membrane integrity, and protease act

in target cells; and to test tissue loss pharmaceutic

for efficacy.

VFT-4: This test measured the near and far point o

clear vision, as well as the ability to change focus 

within the range of clear vision.

SAREX-II: See STS-35.

Get Away Specials G-203

Customer: New Mexico State University

G-203 observed the crystal forming characteristic

water using zeolite desorption-absorption process

G-300

Customer: Matre/Laboratoire de Genie Electrique 

Paris (L.G.E.P.)

G-300 performed conductivity measurements on t

silicon oils in microgravity.

G-458

Customer: The Society of Japanese Aerospace 

Companies, Inc.

G-458 cultivated cellular slime molds.

Mission Results Successful

a Jenkins, p. 302.
Table 3–87. STS-65 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Robert D. Cabana

PLT: James D. Halsell, Jr.

PC: Richard J. Hieb

MS: Carl E. Walz, Leroy Chiao, Donald A. Thom

PS: Chiaki Naito-Mukai (JAXA).

Launch July 8, 1994, 12:43:00 p.m. EDT, Kennedy Space 

Center, Pad 39-A. The launch occurred exactly on 

at the beginning of a 2 1/2-hour launch window. T

countdown progressed smoothly but was held at T

minutes due to a return-to-launch-site weather 

constraint. The weather constraint was cleared at 

p.m., leading to an on-time liftoff.

Orbital Altitude & 

Inclination

160 nmi (296 km), 28.45 deg

Launch Weight (lb/kg) 258,585a/117,292

Landing & Postlanding 

Operations

July 23, 1994, 6:38:00 a.m. EDT, Runway 33, Ken

Space Center. This was the longest Shuttle flight to 

The landing opportunity on July 22 was waved of

to the possibility of rain showers in the area.

Rollout Distance (ft/m) 10,211/3,112

Rollout Time (seconds) 68

Mission Duration 353 hr, 55 min, 1 sec

Landed Revolution No. 234

Mission Support STDN

Primary Objective IML-2

Deployed Satellites None
Table 3–87. STS-65 Mission Characteristics (Continued)

Experiments IML-2: Two teams performed around-the-clock 

research. The space agencies represented were: N

ESA; CSA; the Centre National d’Etudes spatiale

(CNES); DARA; and the NASDA. The activities w

divided into two groups: life sciences and microgr

sciences and used a number of facilities and appar

Life science apparatus included: 

• Biorack 

• Biostack 

• EDOMP 

• Spinal Changes in Microgravity (SCM) 

• NIZEMI 

• Aquatic Animal Experiment Unit (AAEU) 

• Free Flow Electrophoresis Unit (FFEU) 

• Real-time Radiation Monitoring Device (RRMD

• Thermoelectric Incubator (TEI)/Cell Culture Ki

(CCK)

• Performance Assessment Workstation (PAWS) 

Microgravity science apparatus included: 

• APCF 

• Bubble, Drop and Particle Unit (BDPU) 

• CPF 

• Large Isothermal Furnace (LIF) 

• Quasi-Steady Acceleration Measurement System 

(QSAMS)

• Applied Research on Separation Methods Using 

Electrophoresis (RAMSES) 

• SAMS

• TEMPUS

• Vibration Isolation Box Experiment System (VI

OARE: See STS-40.

CPCG: See STS-49.

Military Application of Ship Tracks (MAST): This 

experiment used Linhof and Hasselblad cameras to 

ship movement by detecting ship tracks formed in s

stratocumulus, and fog when ship-induced disturba

and emissions altered existing cloud structures.

SAREX: See STS-35.

AMOS Calibration Test: See STS-29.

Get Away Specials None

Mission Results Successful

Remarks The crew took time during the mission to honor th

anniversary of Apollo 11, noting that Apollo 11 al

featured a spacecraft named Columbia.

Columbia was outfitted with extended duration or

hardware for the flight.

a Jenkins, p. 302.
Table 3–88. STS-64 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Richard N. Richards

PLT: L. Blaine Hammond, Jr.

MS: Jerry M. Linenger, Susan J. Helms, Carl J. M

Mark C. Lee

Launch September 9, 1994, 6:22:55 p.m. EDT, Kennedy S

Center, Pad 39-B. A late afternoon launch was sc

uled to permit nighttime operation of the LITE la

early in the mission. The launch was delayed due 

launch weather violations near the launch comple

Orbital Altitude & 

Inclination

140 nmi (259 km), 57.00 deg

Launch Weight (lb/kg) 241,434/109,513

Landing & Postlanding 

Operations

September 20, 1994, 5:12:52 p.m. EDT, Runway 0

Edwards Air Force Base. Mission already extended 

day was extended again after first landing opportun

at Kennedy Space Center on September 19 were w

off due to stormy weather. Two additional opportun

at Kennedy Space Center on September 20 were al

waved off, and the orbiter was diverted to California

orbiter was transported to Kennedy Space Center o

September 27.

Rollout Distance (ft/m) 9,656/2,943

Rollout Time (seconds) 60

Mission Duration 262 hr, 49 min, 57 sec

Landed Revolution No. 175

Mission Support STDN

Primary Objective Experimentation using the LIDAR LITE: Deploy

and retrieval of SPARTAN-201

Deployed Satellites Deployed and retrieved SPARTAN-201

Experiments LITE: This experiment measured the vertical prof

certain atmospheric parameters (cloud top height, 

planetary boundary layer height, tropospheric aer

stratospheric aerosols, temperature, and density). T

measurements were obtained by emitting laser en

into the atmosphere and measuring the return sign

scattered from the atmospheric constituents. 

Unprecedented views were obtained of cloud 

structures, storm systems, dust clouds, pollutants, 

burning, and surface reflectance. Sites studied inc

the atmosphere above northern Europe, Indonesia 

the south Pacific, Russia, and Africa.
Table 3–88. STS-64 Mission Characteristics (Continued)

Experiments Shuttle Plume Impingement Flight Experiment 

(SPIFEX): The SPIFEX studied the characteristic

behavior of exhaust plumes from Discovery’s Rea

Control System thrusters during the mission. The 

SPIFEX, when picked up by Discovery’s mechan

arm, is a 33-ft (10-m)-long extension for the arm w

package of instruments to measure the near-field, 

transition, and far-field effects of thruster plumes

SPIFEX plume information gathered would assist 

planners in understanding the potential effects of 

thruster plumes on large space structures, such as 

Russian Mir space station and the ISS, during fut

Shuttle docking and rendezvous operations.

SAREX-II: See STS-35. 

SSCE: See STS-41.

Biological Research in Canister (BRIC): This 

experiment investigated the effects of spaceflight 

small arthropod animals and plant specimens.

RME-III: See STS-28.

MAST: See STS-59.

AMOS Calibration Test: See STS-29. 

Robot Operated Materials Processing Systems 

(ROMPS): These systems used the microgravity 

environment to develop commercially valuable 

methods of processing semiconductor materials. 

ROMPS also advanced automation and robotics f

material processing in ways that could lower the c

of developing and manufacturing semiconductors

ROMPS experiment investigated in-space process

semiconductor materials and consisted of a robot

furnace, samples, and control electronics. It used 

robot to transport a variety of semiconductors fro

storage racks to halogen lamp furnaces where the

crystal structures were reformed in heating and co

cycles. ROMPS flight hardware was contained in 

of GAS cans mounted on the Hitchhiker-G Carrie

ROMPS was the first robotics system operated in 

The NASA Office of Advanced Concepts and 

Technology sponsored ROMPS as part of their mi

to develop commercially relevant techniques for i

space materials processing. The project was being 

carried out by Goddard Space Flight Center and t

NASA-sponsored Centers for the Commercial 

Development of Space: the Consortium for 

Commercial Crystal Growth at Clarkson Universi

Potsdam, New York, and the Space Automation a

Robotics Center in Ann Arbor, Michigan. 
Table 3–88. STS-64 Mission Characteristics (Continued)

Get Away Specials GBA: This assembly held 10 GAS canisters conta

experiments to investigate different physical and 

biological phenomena and two ballast GAS cans 

containing accelerometers.

G-178 

Customer: Sierra College, Rocklin, California

Spectrometer Measurements of the Upper Atmosp

in the UV Range: G-178 took ozone measuremen

Earth’s upper atmosphere in the ultraviolet 200-

nanometer to 400-nanometer spectral range using 

Charge Coupled Device (CCD)-based spectromet

CCD photographic camera also flew as part of the 

experiment and provided target verification for th

spectrometer.

G-254 

Customer: The Kinkaid School and Utah State 

University

Four experiments were flown in individual spacep

including a new aluminum Isogrid construction. T

payload contained popcorn kernels and radish see

separate Ziploc bags as an experiment by Edith B

Elementary School located on the Utah State Univ

campus. After the flight, the students popped and 

the popcorn. The radishes were grown and compa

with a similar sample maintained in 1g. The expe

ments dealt with fluid distillation, flat zone instab

photosynthesis, and bubble interferometry.

G-0325 

Customer: Norfolk, Virginia Public Schools

NORSTAR experiment: Acoustic Wave Study an

minor experiments: This experiment recorded vis

how sound affected dust particles in near-zero gra

to advance understanding of acoustics.

G-417 

Customer: Beijing Institute of Environmental 

Engineering

Three experiments: Paramecium Reproduction, O

Water Mixing, Soldering Examples.
Table 3–88. STS-64 Mission Characteristics (Continued)

Experiments G-453

Customer: N. Tateyama, The Society of Japanese 

Aerospace Co., Inc. (SJAC) 

Reflight of G-453 on STS-57 due to incomplete r

following a battery failure. The experiments 

investigated the formation of superconducting ma

and the boiling phenomenon under microgravity a

the absence of convection. There were two 

experiments: 

1) Formation of Silicon-Lead (Si-Pb) Alloy: This 

experiment investigated the formation of 

superconducting alloy (not mixable on the ground

Each sample, in a platinum crucible located insid

quartz ampoule (small glass container), was heate

furnace up to 1,450°C (2,640°F) for 25 minutes. 

2) Boiling Experiment: This experiment observed 

bubble formation when an organic solvent (Freon 

boiled under microgravity and in the absence of 

convection. The organic solvent was heated and b

in a small sealed vessel. The behavior of bubbles 

formed while boiling was observed and recorded 

a video system. 

G-454 

Customer: Society of Japanese Aerospace Co.

Crystallization via a Temperature Gradient Furna

G-454 investigated the crystallization or the form

of materials under microgravity and in the absenc

convection. 

G-456 

Customer: Society of Japanese Aerospace Co.

Separation of Biologically Active Materials via 

Electrophoresis: G-456 observed electrophoresis 

movement of suspended particles through a fluid 

under the action of an electromotive force applied 

electrodes in contact with the suspension) with a 

camera above the separation chamber. The experi

was recorded on video cassette recorders. The 

separation results would be compared to results 

obtained on Earth.

G-485 

Customer: ESA

Material Evaporation/Exposure experiment via a 

motorized door assembly: This experiment tested 

feasibility of depositing different materials in a 

microgravity and vacuum environment by flying 

payload in a GAS canister with a motorized door 

assembly.
Table 3–88. STS-64 Mission Characteristics (Continued)

Experiments G-506 

Customers: Goddard Space Flight Center and Mo

State University

Three experiments:

Orbiter Stability Experiment: This experiment wa

designed to evaluate the Space Shuttle as a platfor

imaging the Sun in x-rays and extreme ultraviolet 

Radiation Effects on Photographic Film.

Radiation Effects on Seeds: This experiment stud

the effects of radiation and zero gravity on germin

and growth.

G-562

Customer: Canadian Space Agency 

QUESTS: Reflight of G-521: G-562 consisted of 

isothermal furnaces and three gradient furnaces fo

materials science, a computer control system, a d

acquisition system, and batteries. There were two 

of furnaces: temperature-gradient (for directional 

crystal growth studies) and constant-temperature 

metal diffusion studies).

Sample Return Experiment: The experiment sat o

of the GAS can in position 4. The primary scienc

objective was to quantify extraterrestrial particles 

other orbital debris in the orbiter bay. A secondar

objective was a realistic test for comet sample 

collection concepts.

Mission Results Successful

Remarks Astronauts Lee and Meade completed the first 

untethered EVA in a decade. During the 6-hour, 

15-minute EVA, they tested a new SAFER backp

designed for use in the event a crew member beca

untethered while conducting an EVA.
Table 3–89. STS-68 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Michael A. Baker

PLT: Terrence W. Wilcutt

PC: Thomas D. Jones

MS: Steven L. Smith, Daniel W. Bursch, Peter J.K

Wisoff

Launch September 30, 1994, 7:16:00 a.m. EDT, Kennedy 

Center, Pad 39-A. The first launch attempt Augus

was halted at T-1.9 seconds when orbiter compute

shut down all three main engines after detecting a

unacceptably high discharge temperature in the hi

pressure oxidizer turbopump turbine for main eng

No. 3. Endeavour returned to the VAB and all thr

engines were replaced. The countdown for the sec

launch attempt proceeded smoothly to an on-time 

September 30.

Orbital Altitude & 

Inclination

120 nmi (222 km), 57.00 deg

Launch Weight (lb/kg) 247,129/112,096

Landing & Postlanding 

Operations

October 11, 1994, 10:02:08 a.m. PDT, Runway 2

Edwards Air Force Base. The landing was diverte

Edwards Air Force Base because of unacceptable 

weather at Kennedy Space Center. The postlandin

video showed what appeared to be water dripping 

the area of the centerline latch for the orbiter/exte

tank doors. The source later was found to be a cra

valve in water spray boiler No. 3. The orbiter retur

Kennedy Space Center atop the 747 Shuttle Carri

Aircraft October 2.

Rollout Distance (ft/m) 8,495/2,589

Rollout Time (seconds) 60

Mission Duration 269 hr, 46 min, 8 sec

Landed Revolution No. 181

Mission Support STDN

Primary Objective Research using the SRL-2

Deployed Satellites None
Table 3–89. STS-68 Mission Characteristics (Continued)

Experiments SRL-2: The SRL-2 was the second simultaneous 

multfrequency (C, L, and X bands), multipolariza

phased array imaging radar in space for geoscient

studies of Earth’s different seasons. The crew use

SRL-2 to image sites for geology, hydrology, vege

science, and oceanography to study vegetation typ

extent, and deforestation; water storage and flux; 

dynamics; wave fields; wind fields; volcanism; te

activity; soil erosion; desertification; and topogra

Using SIR-C/X-SAR, the crew imaged a volcanic 

eruption in Russia and the islands of Japan after a

earthquake. The SRL-2 payload consisted of the 

following: 

• SIR-C 

• X-SAR 

• MAPS 

The DARA and Italian Space Agency provided th

SAR instrument.

CHROMEX: See STS-29.

CPCG: See STS-49.

BRIC: See STS-64.

CREAM: See STS-48.

MAST: See STS-65.

Get Away Specials G-316

Customer: North Carolina A&T State University

This experiment determined the effect of microgr

on arthropod development and crystal growth.

G-503

Customer: University of Alabama

This experiment determined the effect of microgr

on diatoms, the curing of concrete, root growth, a

pitting of metals.

G-541

Customer: Swedish Space Corporation 

This experiment studied the breakdown of a plana

solid/liquid interface in space.

GAS Postal Payloads: The U.S. Postal Service us

GAS hardware to fly 500,000 commemorative sta

to recognize the 25th anniversary of the Apollo 1

Moon Landing. The stamp was a $9.95 Express M

stamp. Father and son team Paul and Chris Calle, 

experienced stamp designers and NASA Art Prog

participants, created the artwork for the stamp.
Table 3–89. STS-68 Mission Characteristics (Continued)

Get Away Specials Sample Return Experiments 

Principal Investigator: Dr. Peter Tsou, Jet Propuls

Laboratory

Two Sample Return Experiments sat on top the po

payloads. The primary science objective was the 

quantification of extraterrestrial particles and othe

orbital debris present in the orbiter bay. A second

objective was a realistic test for comet sample coll

concepts. 

Mission Results Successful
Table 3–90. STS-66 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Donald R. McMonagle

PLT: Curtis L. Brown, Jr.

PC: Ellen Ochoa

MS: Joseph R. Tanner, Jean-Francois Clervoy (ES

Scott E. Parazynski

Launch November 3, 1994, 11:59:43 a.m. EST, Kennedy 

Center, Pad 39-B. The 11:56 a.m. launch was dela

slightly while Shuttle managers assessed the weat

the transoceanic abort landing sites. The liftoff wa

Atlantis’s first since an extended checkout and mo

tion period at the Rocketdyne Rockwell plant in 

Palmdale, California.

Orbital Altitude & 

Inclination

164 nmi (304 km), 57.00 deg

Launch Weight (lb/kg) 243,089a/110,263

Landing & Postlanding 

Operations

November 14, 1994, 7:33:45 a.m. PST, Runway 2

Edwards Air Force Base. The landing was diverte

California due to high winds, rain, and clouds in F

from Tropical Storm Gordon. 

Rollout Distance (ft/m) 7,642/2,329

Rollout Time (seconds) 49

Mission Duration 262 hr, 34 min, 2 sec

Landed Revolution No. 173

Mission Support STDN

Primary Objective Research using ATLAS-3; deployment and retriev

the CRISTA-SPAS

Deployed Satellites Deployed and retrieved CRISTA-SPAS: The spac

carried two instruments—the German CRISTA 

telescope and the U.S. Middle Atmosphere High 

Resolution Spectrograph Investigation (MAHRSI

instrument.
Table 3–90. STS-66 Mission Characteristics (Continued)

Experiments ATLAS-3: The ATLAS-3 collected data about the 

energy output and chemical makeup of Earth’s mi

atmosphere and how these factors affected global 

levels. The experiments included the following:

• ATMOS Experiment: This experiment collected 

on trace gases in the atmosphere. 

• SSBUV: The spectrometer took ozone measurem

to calibrate the NOAA-9 satellite ozone monitor

SSBUV also took cooperative measurements wi

other ATLAS-3 instruments. (See STS-34.)

• ACRIM: The ACRIM made extremely precise 

measurements of the Sun’s total radiation for 30 

as a calibration reference for a sister instrument 

UARS launched in 1991.

• SOLCON: Provided by Belgium, the SOLCON 

measured solar radiation as a reference point to 

changes over years.

• SOLSPEC: A French instrument. The SOLSPE

measured the Sun’s radiation as a function of 

wavelength. 

• SUSIM: The SUSIM measured the fluctuation o

Sun’s ultraviolet radiation and determined how 

the measured ultraviolet light degraded the accu

of the measuring instrument.

• MAS: The MAS collected 9 hours of observatio

measuring the distribution of water vapor, chlor

monoxide, and ozone at altitudes between 12 m

60 mi (20 km and 100 km) before a computer 

malfunction halted instrument operations.

Experiment of the Sun Complementing the ATLA

Payload and Education-II (ESCAPE-II): This 

experiment collected solar data with solar imaging 

ultraviolet solar irradiance experiments. The data 

correlated with the co-manifested ATLAS-3 solar 

experiments to understand upper atmosphere 

photochemistry.

Protein Crystal Growth-Thermal Enclosure System 

(PCG-TES): This experiment investigated the 

mechanisms of PCG and retrieved high-quality cr

grown during spaceflight using a double locker TE

Protein Crystal Growth-Single Locker Thermal 

Enclosure System (PCG-STES): This experiment 

investigated the mechanisms of PCG and retrieved 

quality crystals grown during spaceflight using a 

locker TES.

HPP Experiment-Reflight: See STS-52.

PARE/NIH-R: Both PARE and NIH-R studied the 

physiological and anatomical changes occurring i

mammals under weightless spaceflight conditions
Table 3–90. STS-66 Mission Characteristics (Continued)

Experiments SAMS: See STS-43.

STL-A: See STS-53.

Get Away Specials None

Mission Results Successful

Remarks This mission successfully tested a different metho

approaching a spacecraft to retrieve CRISTA-SPA

prelude to the upcoming U.S. Shuttle/Russian spa

station Mir docking flights. Called an R-Bar appr

it was expected to save propellant while reducing 

risk of contamination to Mir systems from orbiter 

thruster jet firings.

a Jenkins, p. 302.
Table 3–91. STS-63 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: James D. Wetherbee

PLT: Eileen M. Collins

PC: Bernard A. Harris, Jr.

MS: C. Michael Foale, Janice Voss, Vladimir G. T

(RSA)

Launch February 3, 1995, 12:22:04 a.m. EST, Kennedy Spa

Center, Pad 39-B. NASA adjusted the countdown 

sequence to accommodate a short 5-minute window 

required for rendezvous with Mir, including adding 

hold time at T-6 hours and T-9 minutes. The launch 

scheduled for February 2 was postponed on Februa

when one of the three inertial measurement units on 

orbiter failed. The countdown on February 3 procee

so smoothly that there was extra time left in the T-9

minute hold. The launch marked the first at a 51.6-d

inclination to the equator to put the orbiter into the 

orbital plane as Mir.

Orbital Altitude & 

Inclination

213 nmi (394 km), 51.60 deg

Launch Weight (lb/kg) 247,555a/112,289

Landing & Postlanding 

Operations

February 11, 1995, 6:50:19 a.m. EST, Runway 15, 

Kennedy Space Center. This was the first end-of-mis

landing since the runway was resurfaced in fall 1994 

decrease wear on orbiter tires and increase crosswind 

tolerances. After landing, cosmonauts aboard Mir rad

their congratulations to the Discovery crew. Discove

became the first orbiter in the U.S. fleet to complete 

missions. The orbiter transferred to the OPF later tha

Rollout Distance (ft/m) 11,002/3,353

Rollout Time (seconds) 80

Mission Duration 198 hr, 28 min, 15 sec

Landed Revolution No. 128

Mission Support STDN

Primary Objective Experimentation using SPACEHAB-3, deploymen

retrieval of SPARTAN-204

Deployed Satellites Deployed and retrieved SPARTAN-204 with Far 

Ultraviolet Imaging Spectrograph (FUVIS)
Table 3–91. STS-63 Mission Characteristics (Continued)

Experiments SPACEHAB-3: This commercially developed mod

carried experiments in biotechnology and advance

materials development, technology demonstration

two pieces of supporting hardware measuring on-o

accelerations. 

• Biotechnology experiments: 

– ASC-04

– BPL-03

– CGBA-06 

– Fluids Generic Bioprocessing Apparatus (FGB

01)

– IMMUNE-02

– Commercial Protein Crystal Growth-Vapor 

Diffusion Apparatus (CPCG-VDA)

– Protein Crystallization Facility-Light Scatterin

Temperature Controlled (PCFLS/T)

• Materials processing experiments were:

– ECLiPSE-Hab 

– Gas Permeable Polymer Membranes (GPPM-

Technology experiments:

– 3-DMA CharlotteTM Robotic Experiment Mon

• Life and biomedical sciences and applications 

experiments:

– BRIC-03

– CHROMEX-06 

– NIH-C-03

• Microgravity science and applications experime

– PCG-STES-03

– SAMS-03

• Johnson Space Center Space and Life Sciences 

Directorate experiment: 

– CPDS

• DOD, U.S. Air Force experiments:

– CREAM-06 

– RME-III 

– Window Experiment (WINDEX-01)

Cryo Systems Experiment (CSE): This experimen

tested cryogenic cooling system and oxygen diode 

pipes for use on future spacecraft designs.

GLO-2: See STS-53.

ODERACS-2: See STS-53.

SSCE: See STS-41.

AMOS Calibration Test: See STS-29.

IMAX: The crew used the IMAX handheld motio

picture camera to film inside the crew cabin.

Get Away Specials None

Mission Results Successful
Table 3–91. STS-63 Mission Characteristics (Continued)

Remarks Astronauts Foale and Harris began an EVA suspen

the end of the robot arm, away from the payload b

test modifications to their spacesuits to keep 

spacewalkers warmer in the extreme cold of space. 

were then scheduled to practice handling the 

approximately 2,500-lb (1,134-kg) SPARTAN-204 

rehearse Space Station assembly techniques. How

both astronauts reported they were becoming very 

this portion of EVA was performed during a night 

and mass-handling was curtailed. The EVA lasted 

hours, 38 minutes.

This was the first flight as part of Phase I of the IS

program. The Shuttle performed first approach an

around of Russian space station Mir. 

a Jenkins, p. 302.
Table 3–92. STS-67 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Stephen S. Oswald

PLT: William G. Gregory

MS: John M. Grunsfeld, Wendy B. Lawrence

PC: Tamara E. Jernigan

PS: Samuel T. Durrance, Ronald A. Parise

Launch March 2, 1995, 1:38:13 a.m. EST, Kennedy Space 

Center, Pad 39-A. After a smooth countdown, lifto

delayed for about a minute due to concerns about a 

heater system on the flash evaporator system. A ba

heater was used, and the countdown proceeded.

Orbital Altitude & 

Inclination

187 nmi (346 km), 28.45 deg

Launch Weight (lb/kg) 256,293a/116,253

Landing & Postlanding 

Operations

March 18, 1995, 1:47:01 p.m. PST, Runway 22, 

Edwards Air Force Base. The orbiter was diverted 

Edwards Air Force Base after landing opportunitie

Florida were waved off on March 17 and in the ear

on March 18. The orbiter returned to Florida on M

27 and was taken to the OPF on March 28.

Rollout Distance (ft/m) 9,975/3,040

Rollout Time (seconds) 59

Mission Duration 399 hr, 8 min, 48 sec

Landed Revolution No. 261

Mission Support STDN

Primary Objective Research using Astro-2

Deployed Satellites None

Experiments Astro-2: The Astro-2 made ultraviolet observation

stars, galaxies, magnetospheres, and quasars.b Thr

experiments were mounted to the SPACELAB 

instrument pointing system: 

• HUT: Considered a complement to the Hubble S

Telescope, the HUT completed more than 200 sep

observations of more than 100 celestial objects.

• WUPPE: The WUPPE greatly expanded the data

on ultraviolet spectropolarimetry.

• UIT: The UIT cameras imaged about two dozen 

spiral galaxies for inclusion in an atlas of such 

galaxies; it made the first ultraviolet images of th

entire Moon.
Table 3–92. STS-67 Mission Characteristics (Continued)

Experiments Middeck Active Control Experiment (MACE): Th

MACE measured and controlled the dynamics of 

complex systems in the microgravity environment

experiment developed a well verified set of Contro

Structure Integration/Controlled Structures Techno

(CSI/CST) methods and approaches, allowing desi

of future CST spacecraft, which cannot be dynami

tested on the ground in a sufficiently realistic zero

gravity simulation, to have confidence in the event

orbit of such spacecraft.

PCG-TES: See STS-66.

PCG-STES: See STS-63.

CMIX: See STS-56.

SAREX-II: See STS-35.

Get Away Specials G-387 and G-388

Customer: Australian Space Office and Auspace Li

G-387 and G-388 made ultraviolet observations of d

space to aid in the study of the structure of galactic 

supernova remnants, distribution of hot gas in the 

Magellanic Clouds, hot galactic halo emissions, and 

emissions associated with galactic cooling flows an

Mission Results One of the two cameras on the UIT malfunctioned 

undetected while on orbit, and only 80 percent of U

science objectives were met. Other mission objecti

were met successfully.

Remarks Endeavour was outfitted with extended duration or

hardware for the flight.

a Jenkins, p. 303. b See chapter 4, Space Science, of this volume for further discussion of the Astro-2 mission.
Table 3–93. STS-71 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Robert L. Gibson

PLT: Charles J. Precourt

PC: Ellen S. Baker

MS: Gregory J. Harbaugh, Bonnie J. Dunbar

Anatoly Solovyev (RSA)–Mir-19 crew upload

Nikolai Budarin (RSA)–Mir-19 crew upload

Norman E. Thagard–Mir-18 crew download

Vladimir Dezhurov (RSA)–Mir-18 crew download

Gennadiy Strekalov (RSA)–Mir-18 crew downloa

Launch June 27, 1995, 3:32:19 p.m. EDT, Kennedy Space 

Center, Pad 39-A. The launch was originally targe

for late May but slipped into June to accommodat

Russian space program activities necessary for the 

Space Shuttle–Mir–Space Station docking, includ

series of spacewalks to reconfigure the Station for 

docking and launch of the new Spektr module to M

containing U.S. research hardware. The launch se

June 23 was scrubbed when rainy weather and ligh

prevented loading of the external tank earlier that d

second try June 24 was scrubbed at T-9 minutes, a

due to persistent stormy weather in central Florida

coupled with a short 10-minute launch window. L

was reset for June 27, and final countdown procee

smoothly.

Orbital Altitude & 

Inclination

170 nmi (315 km)/216 nmi (400 km) when dockin

51.60 deg

Launch Weight (lb/kg) 248,857a/112,880

Landing & Postlanding 

Operations

July 7, 1995, 10:54:34 a.m. EDT, Runway 15, Ken

Space Center. The runway switched from 33 to 15 

20 minutes before touchdown due to concerns of C

Astronaut Robert Cabana, flying the Shuttle Train

Aircraft, about clouds blocking runway landing ai

from view.

Rollout Distance (ft/m) 8,364/2,549

Rollout Time (seconds) 51

Mission Duration 235 hr, 22 min, 17 sec

Landed Revolution No. 152

Mission Support STDN

Primary Objective First Shuttle-Mir docking

Deployed Satellites None
Table 3–93. STS-71 Mission Characteristics (Continued)

Experiments IMAX camera: This 70-mm motion picture camer

system photographed rendezvous and spacecraft 

operations from within the crew compartment.

SAREX-II: See STS-35.

Get Away Specials None

Mission Results Successful

Remarks Spacelab-Mir: This was a combined science and 

logistical transfer mission. Life and microgravity 

science investigations were performed jointly with 

to complement investigations on the Shuttle. The 

performed research into biomedical life sciences a

microgravity with an emphasis on the effects of lo

duration spaceflight on the human body. The logis

transfers included transporting the Mir-19 crew to 

returning the Mir-18 crew; transferring water to M

science specimens and hardware transferred to and 

Mir; food resupply sent to Mir; and Russian hardw

returned. The crews conducted fifteen separate 

biomedical and scientific investigations, covering 

different disciplines: 1) cardiovascular and pulmo

functions; 2) human metabolism; 3) neuroscience

hygiene, sanitation, and radiation; 5) behavioral 

performance and biology; 6) fundamental biology

7) microgravity research. The Mir-18 crew served 

test subjects for the investigations.

The joint Atlantis-Mir spacecraft was the largest e

orbit when the two were linked and the first on-or

changeout of a Shuttle crew. Astronaut Thagard lo

the longest U.S. spaceflight with his return from M

For the return flight, the crews made provisions on 

Atlantis to accommodate an eight-person crew.

President William J. Clinton called and congratula

the crews on the successful docking and invited th

visit the White House.

a Jenkins, p. 303.
Table 3–94. STS-70 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Terence T. Henricks

PLT: Kevin R. Kregel

MS: Nancy J. Currie (Sherlock), Donald A. Thom

Mary Ellen Weber

Launch July 13, 1995, 9:41:55 a.m. EDT, Kennedy Space 

Center, Pad 39-B. The count was held for 55 seco

T-31 seconds due to fluctuations seen on the exter

tank automatic gain control external tank range sa

system receiver. Launch Commit Criteria conting

procedures were worked and the count then proce

on schedule.

STS-70 had originally moved ahead of the launch 

STS-71 because of a delay in the launch of the Ru

Spektr laboratory module to the Russian space sta

Mir. However, on May 31, NASA Shuttle manage

assessed damage to the Discovery’s external tank 

caused by nesting flicker woodpeckers. The dama

consisted of about 71 holes (ranging in size from 

(1.3 cm) to 4 in (10 cm) in diameter) in the extern

tank’s thermal protection foam insulation. Technic

installed safeguards against additional damage. On 

2, NASA managers decided to delay the launch of 

Discovery on STS-70 to repair the foam insulation 

the vehicle’s external tank. STS-71 was moved ahe

STS-70 and Discovery was rolled back to the VAB

was the quickest turnaround landing (STS-71) to l

(STS-70).

Orbital Altitude & 160 nmi (296 km), 28.45 deg

Inclination

Launch Weight (lb/kg) 258,798a/117,389

Landing & Postlanding July 22, 1995, 8:02:00 a.m. EDT, Runway 33, Ken

Operations Space Center. The first landing opportunities on Ju

at Kennedy Space Center were waved off due to fo

low visibility. The first opportunity on July 22 at 

Kennedy Space Center was also waved off. 

Rollout Distance (ft/m) 8,465/2,580 
Table 3–94. STS-70 Mission Characteristics (Continued)

Rollout Time (seconds) 57

Mission Duration 214 hr, 20 min, 7 sec

Landed Revolution No. 143

Mission Support STDN

Primary Objective Deployment of TDRS-G

Deployed Satellites TDRS-G (7)/IUS

Experiments PARE/NIH-R: See STS-66.

Bioreactor Demonstration System (BDS): The BD

developed the capability and demonstrated the abi

grow mammalian cells in fluid growth medium in 

microgravity. 

CPCG: See STS-49.

STL/NIH-C: See STS-59.

BRIC: See STS-64.

SAREX-II: See STS-35.

VFT-4: See STS-59.

HERCULES: This system provided an on-orbit 

capability to geolocate a ground target.

MIS-B: See STS-53. 

WINDEX: The WINDEX obtained spectrally isol

images of the Shuttle surface glow, thruster plume

water dumps, aurora, and airglow.

RME-III: See STS-28.

MAST: See STS-65.

Get Away Specials None

Mission Results Successful. It was the most trouble-free mission to 

b date.

Remarks This was the first mission in which ground suppor

the new Mission Control Center at Johnson Space 

Center.c

a Jenkins, p. 303. b “STS-70/Flight 70 Mission Report,” http://members.aol.com/WSNTWOYOU/STS70MR.HTM (a

December 6, 2005). c “STS-70 Flight Brings New Tools On-Line,” Space News Roundup, Johnson Space Center 34, no. 2

(July 14, 1995): 1, http://www.jsc.nasa.gov/history/roundups/issues/95-07-14.pdf (accessed Dece

2005).
Table 3–95. STS-69 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: David M. Walker

PLT: Kenneth D. Cockrell

PC: James S. Voss

MS: James H. Newman, Michael L. Gernhardt

Launch September 7, 1995, 11:09:00 a.m. EDT, Kennedy S

Center, Pad 39-A. The launch originally set for Au

5 was postponed indefinitely to allow further revie

solid rocket motor nozzle joint hardware from STS

and STS-71. An inspection team was formed to as

the significance of the gas path in nozzle internal j

No. 3, extending from insulation in the motor cham

to, but not past, the primary O-ring seal. The team 

concluded that the nozzle joint design was sound a

that gas paths were being created when insulation 

material, known as Room Temperature Vulcanizin

was applied. Small air pockets were forming in the 

thermal insulation that could later become pathway

hot gas during motor operation. Attention then foc

on developing procedures to allow Non-Destructiv

Evaluation (NDE) inspection of insulation at the p

and a new launch date of August 31 was set. The 

August 31 launch was scrubbed about 5.5 hours be

liftoff due to the failure of one of the orbiter’s three 

cells. Fuel cell No. 2 indicated higher than allowab

temperatures during activation as countdown 

proceeded. The fuel cell was removed and replace

Liftoff on September 7 was preceded by a smooth 

countdown.

Orbital Altitude & 

Inclination

165 nmi (306 km), 28.45 deg

Launch Weight (lb/kg) 256,645a/116,412

Landing & Postlanding 

Operations

September 18, 1995, 7:37:56 a.m. EDT, Runway 3

Kennedy Space Center. The landing occurred at the 

opportunity.

Rollout Distance (ft/m) 10,230/3,118

Rollout Time (seconds) 56

Mission Duration 260 hr, 28 min, 26 sec

Landed Revolution No. 170

Mission Support STDN

Primary Objective Deployment and retrieval of SPARTAN 201-03 an

WSF-2

Deployed Satellites Deployed and retrieved SPARTAN 201-03 and WS
Table 3–95. STS-69 Mission Characteristics (Continued)

Experiments International Extreme Ultraviolet Hitchhiker-1 (IE

The IEH consisted of a Hitchhiker carrier with fou

experiments: 

• Solar Extreme Ultraviolet Hitchhiker (SEH): Th

SEH was contained in an extended GAS canister 

a Hitchhiker Motorized Door Assembly. The SE

used rare gas ionization cells, photodiodes, and a 

spectrometer for solar viewing.

• Ultraviolet Spectrograph Telescope for Astronom

Research (UVSTAR): This was a spectrograph w

internal gimbals, allowing for stellar observation

• GLO-3: This spectrograph measured Shuttle glo

phenomena in the 115 nm to 1150 nm spectral ra

• CONCAP IV-03: See STS-57. 

STL/NIH-C: See STS-59.

Electrolysis Performance Improvement Concept S

(EPICS): This study was a characterization in 

microgravity of the water electrolysis concepts to 

used for metabolic oxygen generation in Space Sta

Freedom and other life support, propulsion, EVA, 

space power applications.

Commercial Materials Dispersion Apparatus (MD

CMIX: See STS-56.

CGBA Configuration A: See STS-54.

BRIC Block 2: See STS-64.

Get Away Specials Capillary Pumped Loop (CAPL)/Gas Bridge Asse

(GBA): The combined CAPL-2/GBA payload cons

of the CAPL-2 Hitchhiker payload, the TES-2 pay

four GAS payloads, and the Sample Return 

Experiment. 

CAPL-2: CAPL-2 was a reflight of the CAPL-1 

Hitchhiker payload flown on STS-60 with 

modifications to enhance the startup of its capillar

system. This flight verified the heat transport 

requirements of the thermal control system under 

design for the EOS. See STS-60.

TES-2: The TES-2 was designed to provide data f

understanding the long-duration behavior of TES 

fluoride salts that undergo repeated melting and 

freezing in microgravity. It developed a melt/freez

behavior database for TES phase change materials

leading to performance enhancements for solardynamic power system heat receivers.
Table 3–95. STS-69 Mission Characteristics (Continued)

Get Away Specials G-645 

Customer: Millcreek Township School District

Investigation of Electroheological Fluids: This 

experiment investigated the performance of 

electroheological fluid-filled beams used as structu

dampers in space.

G-702

Customer: Lewis Research Center

Microgravity Smoldering Combustion: This experi

increased the understanding of smoldering combu

in long-term microgravity.

G-726 

Customer: Langley Research Center

Joint Damping Experiment: The experiment meas

influence of gravity on the structural damping of a 

three-bay truss.

G-515

Customer: ESA

G-515 studied active damping control loops using 

flexible plate and two piezo (pressure) actuators.

Sample Return Experiment: The Sample Return 

Experiment sat on top the ballast GAS can. The pri

science objective was the quantification of extrater

trial particles and other orbital debris present in th

orbiter bay. A secondary objective was a realistic t

for comet sample collection concepts.

Mission Results Successful

Remarks This was the first time that two different payloads 

retrieved and deployed during the same mission.

a Jenkins, p. 303.
Table 3–96. STS-73 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Kenneth D. Bowersox

PLT: Kent V. Rominger

MS: Catherine G. Coleman, Michael E. Lopez-Al

PC: Kathryn C. Thornton

PS: Fred W. Leslie, Albert Sacco, Jr.

Launch October 20, 1995, 9:53:00 a.m. EDT, Kennedy Sp

Center, Pad 39-B. The launch was after Columbia

return to the fleet following its scheduled modific

and refurbishment. A successful launch took place 

six scrubs, which tied STS-61-C for the greatest 

number of launch scrubs. Liftoff originally set for 

September 25 was scrubbed shortly after tanking b

when a hydrogen leak was detected in the main en

No. 1 main fuel valve. The valve was replaced at t

pad. The launch was reset for October 5, but Hurr

Opal led to an L-1 day decision to postpone launc

day to October 6. 

The October 6 launch attempt was scrubbed befor

external tank loading when it was determined that 

hydraulic fluid had been inadvertently drained fro

hydraulic system 1 following the main engine No

fuel valve replacement. A compressibility test 

demonstrated that the system was satisfactory for 

launch, and liftoff was reset to occur October 7. T

launch attempt October 7 was scrubbed at T-20 sec

when master events controller 1 failed to operate 

properly and mission managers determined that it 

needed to be replaced. The launch was reset for Oc

14, and then rescheduled for October 15 to allow 

additional time to inspect the main engine oxidize

ducts because of crack in a test engine oxidizer du

found at Stennis Space Center. A launch attempt 

October 15 was postponed at T-5 minutes due to l

clouds and rain. The launch was tentatively reset t

October 19, pending a successful Atlas launch Oc

18. However, the Atlas launch was delayed, and ST

launch was moved to October 20. Countdown to l

on October 20 was delayed 3 minutes due to a ran

computer glitch.

Orbital Altitude & 150 nmi (277 km), 39.00 deg

Inclination

Launch Weight (lb/kg) 257,017a/116,581

Landing & Postlanding November 5, 1995, 6:45:21 a.m. EST, Runway 33

Operations Kennedy Space Center. The landing occurred on t

first opportunity.
Table 3–96. STS-73 Mission Characteristics (Continued)

Rollout Distance (ft/m) 9,117/2,779

Rollout Time (seconds) 55

Mission Duration 381 hr, 52 min, 22, sec

Landed Revolution No. 255

Mission Support STDN

Primary Objective Research using the USML-2

Deployed Satellites None

Experiments USML-2: This was the second U.S. Spacelab mis

dedicated to microgravity research. It consisted of 

facilities performing 18 experiments and 7 investi

tions. The research was dedicated to fluid dynami

crystal growth, combustion science, biological sci

and technology demonstrations. Government, coll

and private industry were involved in all facets of 

research. 

• Primary experiments: 

– CGF 

– DPM 

– Geophysical Fluid Flow Cell (GFFC) 

– STDCE

– GBX

• Small Middeck Experiment Rack (SMIDEX) 

– APCF

– LBNP

– CGBA

ASTROCULTURETM facility and experiment

The Glovebox-enclosed cabinet offered a clean wo

space and minimized contamination risks for thes

experiments: 

• Interface Configuration Experiment (ICE) 

• Oscillatory Thermocapillary Flow Experiment 

(OTFE) 

• Fiber Supported Droplet Combustion (FSDC) 

• Protein Crystal Growth–Glovebox (PCGG) 

• Zeolite Crystal Growth–Glovebox (ZCGG) 

• Colloidal Disorder-Order Transitions (CDOT) 

• Particle Dispersion Experiment (PDE) 

OARE: Provided near real-time data for character

the low frequency microgravity in the orbiter in su

of USML-2. See STS-40.

Get Away Specials None

Mission Results Successful

Remarks Columbia was outfitted with extended duration or

hardware for the flight.

a Jenkins, p. 303.
Table 3–97. STS-74 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Kenneth D. Cameron

PLT: James D. Halsell, Jr.

MS: Chris A. Hadfield (CSA), Jerry L. Ross, Willi

McArthur, Jr.

Launch November 12, 1995, 7:30:43 a.m. EST, Kennedy S

Center, Pad 39-A. The planned rendezvous with M

necessitated a brief launch window of about 7 min

Liftoff originally set for November 11, was scrubb

due to unacceptable weather at the TAL sites.a

Countdown the following day proceeded smoothly 

on-time liftoff.

Orbital Altitude & 

Inclination

213 nmi (394 km), 51.60 deg

Launch Weight (lb/kg) 274,560b/124,538

Landing & Postlanding 

Operations

November 20, 1995, 12:01:27 p.m. EST, Runway 

Kennedy Space Center 

Rollout Distance (ft/m) 8,607/2,623

Rollout Time (seconds) 57

Mission Duration 196 hr, 30 min, 46 sec

Landed Revolution No. 128

Mission Support STDN

Primary Objective Second Shuttle-Mir docking

Deployed Satellites None

Experiments ICBC: A 65-mm color camera mounted in the pay

bay documented DM installation, the Mir rendezv

docking, flyaround, and separation.

GLO Experiment/Photogrammetric Appendage 

Structural Dynamics Experiment (PASDE) Payloa

(GPP): The GLO experiment obtained data from t

Shuttle and Mir glow emissions for various condit

Three PASDE canisters, located throughout the ca

bay, photogrammetrically recorded structural resp

data of the Mir solar arrays during the docked pha

the mission.

SAREX-II: See STS-35.

Get Away Specials None

Mission Results Successful
Table 3–97. STS-74 Mission Characteristics (Continued)

Remarks Shuttle-Mir Mission 2 (S/MM-2): This mission 

delivered the Russian-built DM with two solar arra

attached. The DM was installed on the ODS to be 

docked to the Mir Kristall module. The DM remai

attached the Mir to provide for future Shuttle and 

Soyuz-TM dockings. The port solar array was a 

Russian-built Reusable Solar Array (RSA) while L

Research Center built the starboard Cooperative S

Array (CSA). The crews retrieved and resupplied 

microgravity and life science experiments on board 

performed ISS Risk Mitigation Experiments (RME

and resupplied Mir.

a NASA used the term “transoceanic abort landing” in Section 6.4 of the 1997 Shuttle Flight Op

Manual rather than “transatlantic landing,” which it used in the 1988 NSTS Shuttle Reference 

Although some references to the older abort term continued to appear in mission docume

Mission Chronology for STS-74 in 1995 specifically used “transoceanic abort landing” in its 

description. See “Space Station Mission Chronology: STS-74,” http://www-pao.ksc.nasa.gov/

chron/sts-74.htm (accessed November 28, 2005); E-mail from Kyle Herring, November 30, 200

b Jenkins, p. 303.
Table 3–98. STS-72 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Brian Duffy

PLT: Brent W. Jett, Jr.

MS: Leroy Chiao, Winston E. Scott, Koichi Waka

(JAXA), Daniel T. Barry

Launch January 11, 1996, 4:41:00 a.m. EST, Kennedy Spa

Center, Pad 39-B. The countdown to the first Shut

launch of the year proceeded smoothly except for 

23-minute delay due to communication glitches 

between various sites on the ground and to reduce 

the risk of colliding with space debris.

Orbital Altitude & 

Inclination

250 nmi (463 km), 28.45 deg

Launch Weight (lb/kg) 258,391a/117,204

Landing & Postlanding 

Operations

January 20, 1996, 2:41:41 a.m. EST, Runway 15, 

Kennedy Space Center. Endeavour landed on its f

opportunity.

Rollout Distance (ft/m) 8,770/2,673

Rollout Time (seconds) 66

Mission Duration 218 hr, 0 min, 45 sec

Landed Revolution No. 142

Mission Support STDN

Primary Objective Deployment and retrieval of SPARTAN OAST-Fly

retrieval of Space Flyer Unit

Deployed Satellites Deployed and retrieved SPARTAN OAST-Flyer

Retrieved Japanese Space Flyer Unit

Experiments SSBUV-A: See STS-34.

PARE/NIH-R-03: See STS-66.

STL/NIH-C-05: See STS-59.

PCG-STES-04: See STS-63.

CPCG-08: See STS-49.

EDFT-03: This test evaluated and demonstrated 

mission-critical EVA hardware for its planned use 

support the scheduled EVAs for the Space Station

Shuttle Laser Altimeter-01: This experiment was t

first of four planned remote sensing flights to prec

measure the distance between Earth’s surface and 

Space Shuttle. The experiment acquired samples o

topology and vegetation data to demonstrate laser 

altimeter operation in low Earth orbit and measure 

top height, structure, and aerosol layering. The 

experiment also provided an in-space engineering 

testbed for future spaceflight laser sensors.
Table 3–98. STS-72 Mission Characteristics (Continued)

Get Away Specials G-342

Customer: U.S. Air Force, Space and Missile Syst

Center

Flexible Beam Experiment 2 (FLEXBEAM 2): Th

FLEXBEAM 2 investigated vibrations in space by 

exciting two Aluminum 6061 T-6 cantilevered bea

Each beam was subjected to different initial condi

resulting in exciting different modes. Electromagn

sensors measured the vibrations while a recorder s

the data.

G-459

Customer: Society of Japanese Aerospace Co.’s, In

(SJAC)

PCG

This experiment reexamined the effect of the 

microgravity environment on protein-crystal nucle

Crystal form and size were recorded on photograp

film and analyzed after recovery of the payload. T

adapt to a GAS payload canister, researchers deve

a hardware system using 16 independent crystalliz

units. Each of the units could carry out crystallizat

experiments by one of three crystallization method

i.e., batch, vapor diffusion, and free-interface diffu

G-740

Customer: Lewis Research Center

Pool Boiling Experiment: This experiment was an 

extension of the study of the fundamentals of nucl

pool boiling heat transfer under the microgravity 

conditions of space. An improved understanding o

basic processes that constitute boiling was sought 

removing the buoyancy effects that mask other 

phenomena.

Mission Results Successful

Remarks Two EVAs were conducted as part of the continuin

series to prepare for on-orbit construction of the IS

During the first EVA, lasting 6 hours, 9 minutes, C

and Barry evaluated a new portable work platform 

structure known as the rigid umbilical, which mig

eventually be used to hold various fluid and electr

lines. During the second EVA, conducted by Chia

Scott, lasting 6 hours, 53 minutes, a portable work 

platform was again evaluated. Also tested were a S

Station utility box designed to hold avionics and f

line connects. Scott also tested a spacesuit’s therm

control in severe cold up to -104°F (-75°C).

a Jenkins, p. 303.
Table 3–99. STS-75 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Andrew M. Allen

PLT: Scott J. Horowitz

MS: Jeffrey A. Hoffman, Maurizio Cheli (ESA), 

Claude Nicollier (ESA)

PC: Franklin R. Chang-Diaz

PS: Umberto Guidoni (ESA)

Launch February 22, 1996, 3:18:00 p.m. EST, Kennedy Sp

Center, Pad 39-B. The liftoff occurred on-time 

following a smooth countdown. Six seconds after 

liftoff, the crew reported that the left main engine 

chamber pressure meter was showing only 40 perc

thrust instead of 104 percent thrust that was neces

prior to throttle-down. Mission controllers in Hou

reported that telemetry showed all three engines w

performing nominally, and there was no effect on 

ascent phase.

Orbital Altitude & 

Inclination

160 nmi (296 km), 28.45 deg

Launch Weight (lb/kg) 261,927a/118,808

Landing & Postlanding 

Operations

March 9, 1996, 8:58:21 a.m. EST, Runway 33, 

Kennedy Space Center. A March 8 landing was w

off due to unfavorable weather conditions. 

Rollout Distance (ft/m) 8,459/2,578

Rollout Time (seconds) 64

Mission Duration 377 hr, 40 min, 21 sec

Landed Revolution No. 251

Mission Support STDN

Primary Objective Flight of TSS-1R; experimentation using USMP-3

Deployed Satellites U.S./Italian TSS-1R—The satellite was lost durin

mission (see Remarks below).

Experiments USMP-3: The crew performed microgravity resear

advance understanding of materials science and 

condensed matter physics. 

• Supporting hardware included: 

– SAMS 

– OARE

• USMP-3 experiments were: 

– AADSF 

– ZENO 

– IDGE 

– MEPHISTO
Table 3–99. STS-75 Mission Characteristics (Continued)

Experiments Middeck Glovebox Facility (MGBX): This facilit

provided a safe laboratory workbench for three 

combustion experiments: 

• Forced-Flow Flamespreading Test (FFFT) 

• Radiative Ignition and Transition to Spread 

Investigation (RITSI) 

• Comparative Soot Diagnostics (CSD)

CPCG: See STS-49.

Get Away Specials None

Mission Results The tether snapped on flight day three as TSS-1R 

was just short of full deployment at about 12.8 mi 

(20.6 km). The satellite immediately began speedi

away from the orbiter because of orbital forces; th

crew was never in danger. Other mission objective

were successfully achieved.

a Jenkins, p. 303.
Table 3–100. STS-76 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Kevin P. Chilton

PLT: Richard A. Searfoss

MS: Ronald M. Sega, Michael R. Clifford, Linda 

Godwin, Shannon W. Lucid (remained on Mir)

Launch March 22, 1996, 3:13:04 a.m. EST, Kennedy Spac

Center, Pad 39-B. The first launch attempt set for M

21 was scrubbed before beginning tanking operati

March 20 due to concerns about high winds. The la

reset for March 22 proceeded smoothly to an on-ti

liftoff. During ascent, a leak occurred in the hydra

system powered by APU No. 3. The leak stopped 

hydraulic system shutdown on orbit. Mission man

concluded that the system would remain stable an

proceeded with plans for a full-duration mission.

Orbital Altitude & 

Inclination

160 nmi (296 km), 51.60 deg

Launch Weight (lb/kg) 246,337a/111,737

Landing & Postlanding 

Operations

March 31, 1996, 5:28:57 a.m. PST, Runway 22, 

Edwards Air Force Base. Mission managers 

rescheduled the landing from March 31 to March 

anticipation of rain and clouds at the Kennedy Spa

Center landing site, but landing attempts at Kenne

Space Center on both March 30 and March 31 we

waved off due to weather. The orbiter was finally 

diverted to California. More conservative weather 

criteria were employed for landing due to the leak 

APU No. 3 hydraulic system and special measures 

taken during reentry to minimize use of this APU. 

During landing preparations, 3 of 38 reaction cont

system thrusters failed, but backup thrusters were 

available to perform the same functions. It was no

considered a night landing because landing occurr

minutes before sunrise. Flight rules define night la

landing as one occurring at least 15 minutes after s

and at least 15 minutes before sunrise.

Rollout Distance (ft/m) 8,357/2,547

Rollout Time (seconds) 55

Mission Duration 221 hr, 15 min, 33 sec

Landed Revolution No. 145

Mission Support STDN

Primary Objective Third Shuttle-Mir docking; research and transfer o

supplies using SPACEHAB-Single Module

Deployed Satellites None
Table 3–100. STS-76 Mission Characteristics (Continued)

Experiments SPACEHAB-SM: A single module configuration 

carried a mix of supplies and scientific equipment 

and from Mir. 

• Equipment in this module: 

– Russian logistics

– EVA tools

– ISS Risk Mitigation Experiment 

– American logistics

– Science and technology experiments

• RME:

– Mir Electric Field Characterization (MEFC) 

hardware 

– Mir Environmental Effects Payload (MEEP)

• Science and Technology Experiments: 

– ESA’s Biorack 

– Life Sciences Laboratory Equipment Refriger

Freezer (LSLE R/F) 

– Mir Glovebox Stowage 

– QUELD 

– High Temperature Liquid Phase Sintering (LP

• Mir Environmental Effects Payload (MEEP):

– Polished Plate Micrometeoroid Debris (PPMD

experiment 

– Orbital Debris Collector (ODC) experiment 

– Passive Optical Samples (POSA) I and II

• Mir Glovebox Stowage: 

– Combustion Experiments Parts Box 

– FFFT

– Passive Accelerometer 

– PCG

– PCG-TES Ancillary 

Kidsat: This project gave middle school students t

opportunity to participate in space exploration by 

configuring their own payload of digital video and 

camera for flight on the Shuttle. They could comm

the camera from their classrooms and download th

images of Earth in near real-time.

SAREX: See STS-35.

Get Away Specials G-312

Customer: U.S. Air Force Space Test Program

Naval Research Laboratory’s Trapped Ions In Spa

(TRIS) Experiment: This experiment measured a 

recently discovered belt of energetic cosmic ray nu

trapped in Earth’s magnetic field to quantify radia

hazards in space to develop a better theoretical 

understanding of how these cosmic ray nuclei bec

trapped in Earth’s magnetic field. TRIS flew previ

on a Space Shuttle mission in 1984.

Mission Results Successful
Table 3–100. STS-76 Mission Characteristics (Continued)

Remarks During this Shuttle-Mir docking, astronauts Linda 

Godwin and Michael Clifford conducted the first U

EVA around two mated spacecraft. During the 6-h

2-minute EVA, they attached four MEEP experime

Mir’s DM that would characterize the environmen

around Mir over an 18-month period. The two wo

SAFER propulsive devices.

a Jenkins, p. 310.
Table 3–101. STS-77 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: John H. Casper

PLT: Curtis L. Brown, Jr.

MS: Andrew S.W. Thomas, Daniel W. Bursch, Ma

Runco, Jr., Marc Garneau (CSA)

Launch May 19, 1996, 6:30:00 a.m. EDT, Kennedy Space 

Center, Pad 39-B. The original launch date of May 

was changed to May 19 due to Eastern Range sche

conflicts. The countdown proceeded smoothly to a

time liftoff on May 19.

Orbital Altitude & 

Inclination

153 nmi (283 km), 39.00 deg

Launch Weight (lb/kg) 254,891a/115,617

Landing & Postlanding 

Operations

May 29, 1996, 7:09:18 a.m. EDT, Runway 33, Ken

Space Center. Favorable weather allowed for a lan

at the first opportunity.

Rollout Distance (ft/m) 9,291/2,832

Rollout Time (seconds) 42

Mission Duration 240 hr, 39 min, 24 sec

Landed Revolution No. 160

Mission Support STDN

Primary Objective Deployment and retrieval of SPARTAN 207 IAE; 

experimentation using SPACEHAB-04 and TEAM

Deployed Satellites Deployed and retrieved SPARTAN 207 carrying th

IAE. The PAMS and Satellite Test Unit (STU) we

deployed but not retrieved; however, Endeavour d

rendezvous three times with the satellite.

Experiments SPACEHAB 04: This mission carried 12 experime

primarily involved in the materials and life science

• Advanced Separations (ADSEP)

• Commercial Float Zone Furnace (CFZF)

• CGBA

• Commercial Vapor Diffusion Apparatus (CVDA

• FGBA

• Hand Held-Diffusion Test Cells (HH-DTC)

• IMMUNE

• PCF

• Protein Crystal Facility-Light Scattering and 

Temperature Controlled (PCF-LST)

• Plant Growth Bioprocessing Apparatus (PGBA)

• Space Experiment Facility (SEF)

• GPPM
Table 3–101. STS-77 Mission Characteristics (Continued)

Experiments TEAMS: Hitchhiker carrier had four experiments: 

• GPS Attitude and Navigation Experiment (GAN

• Vented Tank Resupply Experiment (VTRE)

• Liquid Metal Thermal Experiment (LMTE) 

• PAMS

Brilliant Eyes Ten-Kelvin Sorption Cryocooler 

Experiment (BETSCE): This experiment tested 

advanced sorption cooler techniques using hydrog

a coolant.

Aquatic Research Facility-01 (ARF-01): This faci

supported life science research using a broad rang

small aquatic species.

BRIC-07: See STS-64.

TPCE/RFL: This experiment obtained data require

develop the technology for pressure control of cryo

tankage.

Get Away Specials G-056

Customer: California Institute of Technology, Pasa

California

Gamma-ray Astrophysics Mission (GAMCIT): Th

GAMCIT studied gamma-ray bursts, an enigmatic 

source of cosmic radiation.

G-142 and G-144

Customer: DARA

Heat Transfer Phenomena (G-142) and Reaction 

Kinetics in Glass Melts (G-144): Autonomous Ma

Science Experiments Under Microgravity (MAUS

Germany offered scientists from disciplines of ma

research and processing the opportunity to perform 

material science investigations under microgravity 

conditions.

G-063

Customer: Pennsylvania State University

G-063 gave students first-hand experience at desig

a self-contained space experiment. Once the paylo

returned from its flight, the students observed its re

The experiments included an accelerometer to me

the impact of orbital debris and a magnetometer to 

measure the magnetic fields. There was also an 

experiment to test the effect of a single event upse

to effects of cosmic radiation on semiconductors.

G-163

Customer: Johnson Space Center

Diffusion Coefficient Measurement Facility (DCM

This facility measured the speed at which mercuri

iodide (solid) evaporated and then was transported 

vapor under microgravity conditions.
Table 3–101. STS-77 Mission Characteristics (Continued)

Get Away Specials G-200

Customer: Utah State University

Three experiments were flown in the canister. The 

payload also contained popcorn kernels in ziplock 

as part of an experiment by elementary school stud

After return to Earth, students popped the popcorn 

compared it to a similar sample maintained in Ear

gravity.

G-490

Customer: British Sugar PLC

The experiment was designed and constructed by the 

School of Electronics and Electrical Engineering at t

Robert Gordon University, Aberdeen, Scotland. Briti

Sugar PLC sponsored the launch services. The first 

experiment was to verify a proposal that a low-level 

gravitational field could be measured by observing it

effect on the convection currents present in a heated l

The second project was devised by a group of childre

from Elrick Primary School near Aberdeen, Scotland

series of controlled experiments were carried out on 

selected samples of seeds, oats, wheat, barley, and na

to quantify the effects of spaceflight on growth patte

G-564 and G-565

Customer: CSA

Nanocrystal Get Away Special (NANO-GAS) and 

Atlantic Canada Thin Organic Semiconductors 

(ACTORS): The results of these experiments 

contributed to the development of new materials w

applications in high-performance laser, electronic 

equipment, and components.

G-703

Customer: Lewis Research Center

Microgravity Smoldering Combustion (MSC): Th

experiment studied the smolder characteristics of p

combustible materials in a microgravity environm

G-741

Customer: Lewis Research Center

Pool Boiling Experiment: This experiment was an 

extension of the study of the fundamentals of nucl

pool boiling heat transfer under the microgravity 

conditions of space. 

Mission Results Successful

a Jenkins, p. 310.
Table 3–102. STS-78 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Terence T. Henricks

PLT: Kevin R. Kregel

MS: Richard M. Linnehan, Charles E. Brady, Jr.

PC: Susan J. Helms

PS: Jean-Jacques Favier (CNES), Robert Brent Th

(CSA)

Launch June 20, 1996, 10:49:00 a.m. EDT, Kennedy Spac

Center, Pad 39-B. The liftoff proceeded on time. A

cabin camera provided the first video images from 

flight deck, beginning with crew ingress and conti

through main engine cutoff. Postlaunch assessmen

spent solid rocket boosters revealed a hot gas path 

motor field joints to, not past, the capture feature O

This marked the first occurrence of combustion pr

penetration into the J-joint of the redesigned solid r

motor. Flight safety was not compromised, and m

performance met design specification requirement

probable cause was a new, more environmentally 

friendly adhesive and cleaning fluid.

Orbital Altitude & 

Inclination

150 nmi (278 km), 39.00 deg

Launch Weight (lb/kg) 256,145a/116,185

Landing & Postlanding 

Operations

July 7, 1996, 8:36:45 a.m. EDT, Runway 33, Kenn

Space Center. This mission had the first live down

video during an orbiter’s descent. After landing, 

Henricks and Kregel participated in the Olympic T

Ceremony at Kennedy Space Center Visitors Cent

Rollout Distance (ft/m) 9,339/2,847

Rollout Time (seconds) 45

Mission Duration 405 hr, 47 min, 36 sec

Landed Revolution No. 271

Mission Support STDN

Primary Objective Experimentation using the LMS

Deployed Satellites None
Table 3–102. STS-78 Mission Characteristics (Continued)

Experiments LMS using the Spacelab long module: Five space 

agencies represented a complement of multination

experiments representing microgravity science an

applications with emphasis on material and life sc

processing. These space agencies were: NASA, E

the French Space Agency, CSA, and the Italian Sp

Agency. Research scientists from 10 countries wo

together on this payload, which made use of the 

Spacelab long module. 

• Human Physiology Experiments: Musculoskelet

Investigations

– Effects of Weightlessness on Human Single M

Fiber Function

– Relationship of Long-Term Electromyographi

Activity and Hormonal Function to Muscle At

and Performance

– Effects of Microgravity on Skeletal Muscle 

Contractile Properties

– Effects of Microgravity on the Biomechanical 

Bioenergetic Characteristics of Human Skelet

Muscle

– Magnetic Resonance Imaging After Exposure 

Microgravity (Ground Study)

– An Approach to Counteract Impairment of 

Musculoskeletal Function in Space (Ground S

• Human Physiology Experiments: Metabolic 

Investigations

– Direct Measurement of the Initial Bone Respo

Spaceflight in Humans

– Measurement of Energy Expenditures During 

Spaceflight Using the Doubly Labeled Water 

Method

• Human Physiology Experiments: Pulmonary 

Investigations

– Extended Studies of Pulmonary Function in 

Weightlessness

• Human Physiology Experiments: Human Behav

and Performance Investigations

– Human Sleep, Circadian Rhythms, and 

Performance in Space

– Microgravity Effects on Standardized Cogniti

Performance Measures 

• Human Physiology Experiments: Neuroscience 

Investigations

– Torso Rotation Experiment 

– Canal and Otolith Integration Studies (COIS)
Table 3–102. STS-78 Mission Characteristics (Continued)

Experiments • Microgravity Science: BDPU

– Bubbles and Drop Interaction with Solidificat

Front

– Boiling on Small Plate Heaters Under Microg

and a Comparison with Earth Gravity 

– A Liquid Electrohydrodynamics Experiment

– Thermocapillary Convection in Multilayer Sy

– Nonlinear Surface Tension-Driven Bubble 

Migration

– Oscillatory Thermocapillary Instability

– Thermocapillary Migration and Interactions o

Bubbles and Drops

• Microgravity Science: Advanced Gradient Heati

Facility (AGHF)–Materials Processing

– Directional Solidification of Refined Al–4 wt. 

Alloys

– Coupled Growth in Hypermonotectics

– Effects of Convection on Interface Curvature 

During Growth of Concentrated Tenary Comp

– Directional Solidification of Refined Al–1.5 w

Ni Alloys

– Interactive Response of Advancing Phase 

Boundaries to Particles

– Particle Engulfment and Pushing by Solidifyi

Interfaces

• Microgravity Science: APCF–Medical Research

– Crystallization of EGFR-EGF

– Crystallization of Apocrustacyanin Cl

– Crystallization and X-ray Analysis of 5S rRN

the 5S rRNA Domain A

– Growth of Lysozyme Crystals at Low Nucleat

Density

– Comparative Analysis of Aspartyl tRA-Synth

and Thaumatin Crystals Grown on Earth and i

Microgravity

– Crystallization of the Nucleosome Core Partic

– Crystallization of Photosystem I

– Mechanism of Membrane Protein Crystal Gro

Bacteriorhodopsin-Mixed Micelle Packing at 

Consolution Boundary, Stabilized in Microgra

– Crystallization in a Microgravity Environmen

CcdB, a Protein Involved in the Control of Ce

Death

– Crystallization of Sulfolobus Solfataricus 

– Lysosome Crystal Growth in the Advanced Pr

Crystallization Facility Monitored via MachZehdner Interferometry and CCD Video

– Analysis of Thaumatin Crystals Grown on Ea

and in Microgravity
Table 3–102. STS-78 Mission Characteristics (Continued)

Experiments • Microgravity Science: Accelerometers–Characte

the Microgravity Environment

– OARE

– Microgravity Measurement Assembly (MMA

– SAMS

• Space Biology:

– Compression Wood Formation in a Micrograv

Environment 

– Development of the Fish Medaka in Microgra

– Role of Corticosteroids in Bone Loss During 

Spaceflight

SAREX-II: See STS-35.

BRIC-07: See STS-64.

Get Away Specials None

Mission Results Successful

Remarks Columbia was outfitted with Extended Duration O

hardware for this mission.

a Jenkins, p. 310.
Table 3–103. STS-79 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: William F. Readdy

PLT: Terence W. Wilcutt

MS: Jerome Apt, Thomas D. Akers, Carl E. Walz, 

E. Blaha (remained on Mir), Shannon W. Lucid 

(departed Mir for return to Earth)

Launch September 16, 1996, 4:54:49 a.m. EDT, Kennedy 

Center, Pad 39-A. The launch, originally set for Ju

slipped when mission managers decided to switch 

Atlantis’s twin solid rocket boosters. The new laun

date of September 12 was targeted and Atlantis ret

to the launch pad. The launch date was delayed to 

September 16 when the Shuttle was returned to the 

due to the threat from Hurricane Fran. The countd

proceeded smoothly to an on-time liftoff Septemb

Approximately 13 minutes into flight, auxiliary po

unit No. 2 shut down prematurely. After review an

analysis, the Mission Management Team conclude

mission could proceed to its nominal end-of-missi

planned.

Orbital Altitude & 

Inclination

170-213 nmi (315-394 km), 51.60 deg

Launch Weight (lb/kg) 249,328a/113,093

Landing & Postlanding 

Operations

September 26, 1996, 8:13:15 a.m. EDT, Runway 1

Kennedy Space Center. The landing went smoothl

first opportunity.

Rollout Distance (ft/m) 10,981/3,347

Rollout Time (seconds) 62

Mission Duration 243 hr, 18 min, 24 sec

Landed Revolution No. 159

Mission Support STDN

Primary Objective S/MM-04; experimentation using SPACEHAB-05

Deployed Satellites None
Table 3–103. STS-79 Mission Characteristics (Continued)

Experiments SPACEHAB-05: A double SPACEHAB module ca

experiments in its forward portion that were conduc

the crew before, during, and after Atlantis’s dockin

Mir. The aft portion of the module housed primarily 

logistics equipment to be transferred to Mir.

• Experiments returning from Mir:

– Environmental Radiation Measurements

– Greenhouse-Integrated Plant Experiments

– Human Life Sciences

– Assessment of Humoral Immune Function Du

Long Duration Space Flight 

• Experiments remaining on Mir for later retrieval

– BTS

– MIDAS

– CGBA

• Roundtrip experiments on Atlantis:

– Extreme Temperature Translation Furnace (ET

– CPCG experiments

– Mechanics of Granular Materials (MGM)

• Risk Mitigation Experiments:

– Mated Shuttle and Mir Structural Dynamics T

(1301)

– Mir Electric Field Characterization (1302)

– Shuttle/Mir Experiment Kit Transport (1303)

– Shuttle/Mir Alignment Stability Experiment (

– Real-Time Radiation Monitoring Device (RRM

1312)

– Active Rack Isolation System (ARIS: 1313)

– Inventory Management System (1319)

IMAX: Large format motion picture system photogr

Mir during undocking and flyaround. The crews also 

the camera to photograph Mir interior scenes.

Midcourse Space Experiment (MSX): The MSX 

obtained ultraviolet, infrared, and visible data of th

Shuttle and Shuttle thrusters from an independent

space-based sensor satellite in a 99-degree orbit.

SAREX-II: See STS-35. 

Get Away Specials None

Mission Results Successful

a Jenkins, p. 310.
Table 3–104. STS-80 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Kenneth D. Cockrell

PLT: Kent V. Rominger

PC: Tamara E. Jernigan

MS: Thomas D. Jones, F. Story Musgrave

Launch November 19, 1996, 2:55:47 p.m. EST, Kennedy Sp

Center, Pad 39-B. Launch date of October 31 was fi

threatened by the changeout of the STS-79 boosters 

those slated to fly on STS-80 and the delay of the ST

liftoff. Hurricane preparations because of Hurricane 

in early September halted the STS-80 booster stack

operations in the VAB, prompting mission manager

reschedule the launch date to November 8. At the F

Readiness Review (FRR) on October 28, mission 

managers declined to formalize the launch date pen

an analysis of erosion in the STS-79 booster nozzle

the FRR on November 4, the launch date was chang

no earlier than November 15 to allow engineers mo

time to complete their study of nozzle erosion. At th

follow-up FRR on November 11, November 15 was 

the official launch date, pending a commercial Atla

launch on November 13, and the launch count began

launch was postponed to November 19, due to the s

of the Atlas launch and predicted bad weather in the 

Kennedy Space Center vicinity for a period of sever

days, and the count remained in an extended hold. T

launch on November 19 occurred about 3 minutes a

the scheduled opening of the launch window due to a 

at T-31 seconds to assess hydrogen concentrations i

aft engine compartment.

Orbital Altitude & 

Inclination

189 nmi (350 km), 28.45 deg

Launch Weight (lb/kg) 260,935a/118,358

Landing & Postlanding 

Operations

December 7, 1996, 6:49:05 a.m. EST, Runway 33, 

Kennedy Space Center. Landing was originally 

scheduled for December 5, but Columbia was wave

two days in a row due to weather conditions in Flo

Rollout Distance (ft/m) 8,721/2,658

Rollout Time (seconds) 62

Mission Duration 423 hr, 53 min, 19 sec

Landed Revolution No. 277

Mission Support STDN
Table 3–104. STS-80 Mission Characteristics (Continued)

Primary Objective Deployment and retrieval of ORFEUS-SPAS-2 and 

WSF-3

Deployed Satellites Deployed and retrieved ORFEUS-SPAS-2 and WS

Experiments NIH-R4: This experiment studied blood pressure 

regulation and function in rats fed either a high-cal

or a low-calcium diet before and during spacefligh

CCM-A (formerly STL/NIH-C-05): This experime

continued the investigation into how microgravity 

affected bones at the cellular level.

BRIC-09: See STS-64.

CMIX-5: See STS-52.

Visualization in an Experimental Water Capillary 

Pumped Loop (VIEW-CPL): This experiment colle

and transported excess heat generated by spacecraf

instruments to a spacecraft radiator for ejection int

space. The experiment was used to develop a more 

complete understanding of CPL physics in a 

microgravity environment by viewing the fluid flow 

inside the evaporator.

Get Away Specials None

SEM SEM-01 experiments were:

• Charleston, South Carolina, school district 

(CAN-DO):

– Gravity and Acceleration Readings

– Bacteria-Agar Research Instrument

– Crystal Research in Space

– Magnetic Attraction Viewed in Space

• Purdue University, West Lafayette, Indiana:

– Fluid Thermal Convection

– NADH Oxidase Absorbance in Shrimp

– Passive Particle Detector Experiment

• Hampton Elementary School, Lutherville, Maryl

– Experimented with seeds; soil; chalk; crayon; 

calcite; Silly Putty; bubble solution; popcorn; 

mosquito eggs; and other organic compounds

• Glenbrook North High School, Northbrook, Illin

– Surface Tension Experiment

• Albion Jr. High, Strongville, Ohio:

– Heat Transfer Experiment–studied heating 

properties of copper tubes and pennies

• Poquoson Middle School, Poquoson, Virginia:

– Bacteria Inoculation in Space Experiment

• Norfolk Public Schools Science and Technology 

Advanced Research (NORSTAR):

– Observed the behavior of immiscible fluids
Table 3–104. STS-80 Mission Characteristics (Continued)

Mission Results Two EVAs by Jernigan and Jones planned to evalu

equipment and procedures to be used during 

construction and maintenance of the ISS were canc

because the crew could not open the outer airlock h

Crew and mission troubleshooting did not reveal th

cause, so mission managers concluded it would be 

unwise to attempt the two EVAs and risk unnecess

damage to the hatch or seals. Postlanding assessme

the hatch indicated that a small screw had become 

from an internal assembly and lodged in an actuato

gearbox mechanism that operated linkages securin

hatch, preventing the crew from opening the hatch

Other mission objectives were achieved.

Remarks At age 61, Musgrave became the oldest human to f

space. He set a new record for the most Shuttle flig

(six) and tied astronaut John Young’s record for the 

total spaceflights.

a Jenkins, p. 310.
Table 3–105. STS-81 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Michael A. Baker

PLT: Brent W. Jett, Jr.

MS: Peter J.K. Wisoff, John M. Grunsfeld, Marsh

Ivins, Jerry M. Linenger (remained on Mir), John 

Blaha (departed Mir for return to Earth)

Launch January 12, 1997, 4:27:23 a.m. EST, Kennedy Spa

Center, Pad 39-B. The liftoff occurred on time 

following a smooth countdown.

Orbital Altitude & 

Inclination

160 nmi (296 km), 51.60 deg

Launch Weight (lb/kg) 249,936a/113,369

Landing & Postlanding 

Operations

January 22, 1997, 9:22:44 a.m. EST, Runway 33, 

Kennedy Space Center. The first landing opportun

was waved off due to weather.

Rollout Distance (ft/m) 9,350/2,850

Rollout Time (seconds) 69

Mission Duration 244 hr, 55 min, 23 sec

Landed Revolution No. 160

Mission Support STDN

Primary Objective S/MM-05; experimentation using SPACEHAB Do

Module

Deployed Satellites None

Experiments SPACEHAB Double Module: The double module 

carried the following experiments:

• Environmental Radiation Measurements

• Greenhouse-Integrated Plant Experiments

• Human Life Sciences

• Assessment of Humoral Immune Function Durin

Long Duration Space Flight

• Diffusion-Controlled Crystallization Apparatus 

Microgravity 

• Gaseous Nitrogen Dewar

• Liquid Metal Diffusion 

• Optical Properties Monitor

CREAM: See STS-48.

KidSat: Provided students access to real-time imag

Earth by uplinking commands to the Electronic St

Camera to photograph specific land areas. The im

were downlinked in real time via the Ku-band 

Communication Adapter.
Table 3–105. STS-81 Mission Characteristics (Continued)

Experiments SAMS: The SAMS provided acceleration data to 

characterize the experiments acceleration environm

on Mir. See STS-43.

MSX: The objective of the MSX was to fire the or

thrusters (orbital maneuvering and primary reactio

control systems) in space and use the sophisticated 

sensors of the orbiting MSX satellite to collect 

ultraviolet, infrared, and visible light data of the ev

Get Away Specials None

Mission Results Successful

Remarks This mission was the largest transfer to date of log

between the two spacecraft.

a Jenkins, p. 310.
Table 3–106. STS-82 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Kenneth D. Bowersox

PLT: Scott J. Horowitz

MS: Joseph R. Tanner, Steven A. Hawley, Gregor

Harbaugh, Steven L. Smith

PC: Mark C. Lee

Launch February 11, 1997, 3:55:17 a.m. EST, Kennedy 

Space Center, Pad 39-A. The launch originally 

targeted for February 13 was moved up to Febr

11 to provide more range opportunities. Countd

proceeded smoothly to an on-time liftoff on Feb

11. This was the first flight after Discovery’s OM

Orbital Altitude & 

Inclination

313 nmi (579 km), 28.45 deg

Launch Weight (lb/kg) 251,238a/113,960

Landing & Postlanding 

Operations

February 21, 1997, 3:32:26 a.m. EST, Runway 15

Kennedy Space Center. The orbiter landed on the 

second opportunity after the first was waved off d

low clouds.

Rollout Distance (ft/m) 7,066/2,154

Rollout Time (seconds) 60

Mission Duration 239 hr, 37 min, 7 sec

Landed Revolution No. 149

Mission Support STDN

Primary Objective Second Hubble Space Telescope Servicing Missio

Deployed Satellites Retrieved, serviced, and redeployed the Hubble S

Telescope

Experiments MSX: See STS-81.

Get Away Specials None

Mission Results Successful

Remarks There were five EVAs: four scheduled and one 

unscheduled.

EVA No. 1: Performed by Lee and Smith, the first 

lasted 6 hours, 42 minutes. Lee and Smith remove

GHRS and FOS from the telescope and replaced 

with the STIS and NICMOS.
Table 3–106. STS-82 Mission Characteristics (Continued)

Remarks EVA No. 2: Performed by Harbaugh and Tanner, 

second EVA lasted 7 hours, 27 minutes. Harbaugh 

Tanner replaced a degraded fine guidance sensor 

failed Engineering and Science Tape Recorder wi

new spares. They also installed a new unit called 

Optical Control Electronics Enhancement Kit, wh

increased the capability of the fine guidance senso

astronauts noted cracking and wear on thermal 

insulation on the side of the telescope facing the S

and in the direction of travel.

EVA No. 3: Performed by Lee and Smith, the third 

lasted 7 hours, 11 minutes. Lee and Smith remove

replaced a Data Interface Unit on the Hubble Spa

Telescope as well as an old reel-to-reel Engineerin

Science Tape Recorder with a new digital solid st

recorder (SSR) that allowed simultaneous recordi

and playback of data. The astronauts also changed 

one of four reaction wheel assembly units that use

momentum to move the telescope toward a target 

maintain it in a stable position.

EVA No. 4: Performed by Harbaugh and Tanner, 

fourth EVA lasted 6 hours, 34 minutes. Harbaugh 

Tanner replaced a solar array drive electronics pac

which controlled the positioning of the Hubble Sp

Telescope’s solar arrays. The astronauts also repla

covers over the telescope’s magnetometers and pl

thermal blankets of multilayer material over two a

of degraded insulation around the light shield port

the telescope just below the top of the observatory

EVA No. 5: Performed by Lee and Smith, the fifth 

lasted 5 hours, 17 minutes. Lee and Smith attache

several thermal insulation blankets to three equipm

compartments at the top of the Support Systems 

Module section of the telescope that contained key 

processing, electronics, and scientific instrument 

telemetry packages. 

a Jenkins, p. 310.
Table 3–107. STS-83 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: James D. Halsell, Jr.

PLT: Susan L. Still

PC: Janice E. Voss

MS: Michael L. Gernhardt, Donald A. Thomas

PS: Roger K. Crouch, Gregory T. Linteris

Launch April 4, 1997, 2:20:32 p.m. EST, Kennedy Space 

Center, Pad 39-A. The launch originally was set fo

April 3. It was initially delayed 24 hours on April 

to a requirement to add additional thermal insulati

a water coolant line in the orbiter’s payload bay. M

managers determined that the coolant line, which c

various electronics on the orbiter, was not properly 

insulated and could possibly freeze on-orbit. On A

liftoff was delayed 20 minutes, 32 seconds due to 

orbiter access hatch seal that had to be replaced.

Orbital Altitude & 160 nmi (296 km), 28.45 deg

Inclination

Launch Weight (lb/kg) 259,144a/117,546

Landing & Postlanding April 8, 1997, 2:33:11 p.m. EDT, Runway 33, Ken

Operations Space Center. The landing was originally schedule

April 19, but the mission was cut short due to prob

with Columbia’s fuel cell No. 2.

Rollout Distance (ft/m) 8,602/2,622

Rollout Time (seconds) 59

Mission Duration 95 hr, 12 min, 39 sec

Landed Revolution No. 63

Mission Support STDN

Primary Objective Research using the MSL-1

Deployed Satellites None

Experiments MSL-1: The MSL-1 housed a collection of microg

experiments inside a Spacelab long module. The 

laboratory featured facilities for material science 

investigations. Due to an early return because of 

problems with fuel cell No. 2, only a few experim

were conducted. 

• TEMPUS:

– Thermophysical Properties of Undercooled M

Melts

• Large Isothermal Furnace:

– Liquid-Phase Sintering II

• Combustion Module-1 (CM-1):

– Laminar Soot Processes

– Structure of Flame Balls at Low Lewis-numbe

(SOFBALL)
Table 3–107. STS-83 Mission Characteristics (Continued)

Get Away Specials None

Mission Results The MSL-1 mission was cut short due to concerns 

one of the three fuel cells. Fuel cell No. 2 had sho

some erratic readings during prelaunch startup but 

cleared to fly after additional checkout and test. S

after on-orbit operations began, the differential vo

in the No. 3 substack of fuel cell No. 2 began to ri

Shuttle flight rules required all three to be function

properly to ensure crew safety and provide sufficie

backup capability during reentry and landing. A 

decision was made after landing to refly the entire 

mission on STS-94. It was the first mission to end 

since STS-44 in 1991. 

Remarks Columbia was outfitted with extended duration or

hardware for the flight.

a Jenkins, p. 310.
Table 3–108. STS-84 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: Charles J. Precourt

PLT: Eileen M. Collins

PC: Jean-Francois Clervoy (ESA)

MS: Carlos I. Noriega, Edward Tsang Lu, Elena V

Kondakova (RSA), C. Michael Foale (remained o

Mir), Jerry M. Linenger (departed Mir for return t

Earth)

Launch May 15, 1997, 4:07:48 a.m. EDT, Kennedy Space 

Center, Pad 39-A. The liftoff occurred on time 

following a smooth countdown.

Orbital Altitude & 

Inclination

160 nmi (296 km), 51.60 deg

Launch Weight (lb/kg) 249,462a/113,154

Landing & Postlanding 

Operations

May 24, 1997, 9:27:44 a.m. EDT, Runway 33, Ken

Space Center. The orbiter landed on the second 

opportunity after being waved off from the first du

low clouds in the vicinity.

Rollout Distance (ft/m) 8,384/2,555

Rollout Time (seconds) 51

Mission Duration 221 hr, 19 min, 56 sec

Landed Revolution No. 143

Mission Support STDN

Primary Objective S/MM-06; experimentation using SPACEHAB

Deployed Satellites None

Experiments SPACEHAB Double Module: Double module car

the following experiments:

• Environmental Radiation Measurements

• Greenhouse-Integrated Plant Experiments

• Human Life Sciences Project

• Protein Crystal Growth Experiments

• Diffusion-Controlled Crystallization Apparatus 

Microgravity (DCAM)

• Gaseous Nitrogen Dewar (GND)

• VDA-2

• Morphological Transition and Model Substance

(MOMO)
Table 3–108. STS-84 Mission Characteristics (Continued)

Experiments • Biorack: This multipurpose unit contained these 

experiments:

– Cytoskeleton of the Lentil Root Statocyte

– Morphology and Physiology of Loxodes Afte

Cultivation in Space

– Lymphocyte and Monocyte Intra-Cellular Sig

Transduction in Microgravity

– Microgravity Effects on Bone Cell Gene 

Expression

– Microgravity and Signal Transduction Pathwa

Sea Urchin Sperm

– Graviperception in Starch-Deficient Plants

PCG-STES: See STS-67.

Liquid Motion Experiment (LME): The LME 

investigated inertia wave oscillations of liquids in 

spinning around an exterior axis that was nutating 

microgravity conditions.

CREAM: See STS-48.

EPICS: See STS-69.

RME-III: See STS-28.

Shuttle Ionospheric Modification with Pulsed Loca

Exhaust (SIMPLEX): The orbiter orbital maneuver

system thruster firings were used to create ionosphe

disturbances for observation by the SIMPLEX radar 

MSX: See STS-79.

Get Away Specials None

Mission Results Successful

Remarks Linenger’s 123-day stay on Mir and 132 days in sp

placed him second behind Shannon Lucid for the m

time spent on-orbit by an American. Another miles

reached during his stay was the one-year anniversar

continuous U.S. presence in space that began with 

Lucid’s arrival at Mir on March 22, 1996.

a Jenkins, p. 310.
Table 3–109. STS-94 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: James D. Halsell, Jr.

PLT: Susan L. Still

PC: Janice E. Voss

MS: Michael L. Gernhardt, Donald A. Thomas

PS: Roger K. Crouch, Gregory T. Linteris

Launch July 1, 1997, 2:02:00 p.m. EDT, Kennedy Space Ce

Pad 39-A. The liftoff was delayed about 12 minute

because of unacceptable weather conditions in the la

area in the event a return-to-launch site abort was 

necessary. The launch window originally was targe

open at 2:37 p.m., July 1. On June 20, NASA mana

decided to move the launch back 47 minutes to 1:50 

to avoid forecasted afternoon thundershowers.

Orbital Altitude & 

Inclination

160 nmi (296 km), 28.45 deg

Launch Weight (lb/kg) 260,249a/118,047

Landing & Postlanding 

Operations

July 17, 1997, 6:46:34 a.m. EDT, Runway 33, Ken

Space Center. The landing occurred at the first 

opportunity.

Rollout Distance (ft/m) 8,892/2,710

Rollout Time (seconds) 55

Mission Duration 370 hr, 44 min, 36 sec

Landed Revolution No. 250

Mission Support STDN

Primary Objective Reflight of the MSL-1

Deployed Satellites None

Experiments Reflight of STS-83 MSL-1: MSL-1 housed a collec

of microgravity experiments inside a Spacelab long 

module. The laboratory featured material science 

investigations. The facilities and their experiments 

• LIF:

– Measurement of Diffusion Coefficient by She

Cell Method

– Diffusion of Liquid Metals

– Diffusion in Liquid Lead-Tin-Telluride

– Impurity Diffusion in Ionic Metals

– Liquid Phase Sintering II

– Diffusion Processes in Molten Semiconductor
Table 3–109. STS-94 Mission Characteristics (Continued)

Experiments • Expedite the Processing of Experiments to the S

Station Rack (EXPRESS):

– Physics of Hard Sphere Experiment

– Astro/Plant Generic Bioprocessing Apparatus 

(AstroPGBA)

• TEMPUS:

– Thermophysical Properties of Undercooled 

Metallic Melts

– Thermophysical Properties of Advance Materi

the Undercooled Liquid State

– Measurement of the Surface Tension of Liqui

Undercooled Metallic Melts by Oscillating Dr

Technique

– Study of the Morphological Stability of Grow

Dendrites by Comparative Dendrite Velocity 

Measurements on Pure Ni and a Dilute Ni-C A

in the Earth and Space Laboratory

– Undercooled Melts of Alloys with Polytetrahe

Short-Range Order

– Thermal Expansion of Glass Forming Metalli

Alloys in the Undercooled State

– Experiments on Nucleation in Different Flow 

Regimes

– Alloy Undercooling Experiments

– Measurement of Surface Tension and Viscosit

Undercooled Liquid Metals

– AC Calorimetry and Thermophysical Properti

Bulk Glass-Forming Metallic Liquids

• CM-1:

– Laminar Soot Processes

– SOFBALL

• Droplet Combustion Apparatus:

– Droplet Combustion Experiment

– Fiber-Supported Droplet Combustion

• Middeck Glove Box:

– Coarsening in Solid-Liquid Mixtures

– Bubble and Drop Nonlinear Dynamics

– A Study of Fundamental Operation of a Capil

Driven Heat Transfer (CHT) Device in 

Microgravity

– Internal Flows in a Free Drop

• Protein Crystallization Apparatus: 

– Protein Crystallization Apparatus for Microgr

– Second Generation Vapor Diffusion Apparatu

– Handheld Diffusion Test Cells

• Measuring Microgravity:

– SAMS

– QSAMS 

– OARE

– MMA
Table 3–109. STS-94 Mission Characteristics (Continued)

Experiments Cryogenic Flexible Diode Experiment (CRYOFD

This experiment determined the behavior of cryog

two-phase thermal control components in microgr

demonstrated oxygen and methane heat pipe startu

from a super-critical condition, demonstrated 

operations; verified analytical performance models

established the correlation between 1g and microgr

thermal performance. A secondary objective was t

validate the performance of an American Loop He

Pipe with Ammonia (ALPHA).

SAREX-II: See STS-35. 

MSX: See STS-79.

Get Away Specials None

Mission Results Successful

Remarks Columbia was outfitted with extended duration or

hardware for the flight.

The mission was the first reflight of the same vehi

crew, and payloads. It also was the first reservicing 

primary payload, MSL-1, in the orbiter.

a Jenkins, p. 310.
Table 3–110. STS-85 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Curtis L. Brown, Jr.

PLT: Kent V. Rominger

PC: N. Jan Davis

MS: Robert L. Curbeam, Jr., Stephen K. Robinso

PS: Bjarni V. Tryggvason (CSA)

Launch August 7, 1997, 10:41:00 a.m. EDT, Kennedy Sp

Center, Pad 39-A. The liftoff was on time followi

smooth countdown.

Orbital Altitude & 

Inclination

173 nmi (320 km), 51.6 deg

Launch Weight (lb/kg) 249,696a/113,260 

Landing & Postlanding 

Operations

August 19, 1997, 7:07:59 a.m. EDT, Runway 33, 

Kennedy Space Center. A landing opportunity on 

August 18 was waved off due to threat of ground f

the local area.

Rollout Distance (ft/m) 8,792/2,680

Rollout Time (seconds) 68

Mission Duration 284 hr, 27 min, 00 sec

Landed Revolution No. 189

Mission Support STDN

Primary Objective Deployment and retrieval of CRISTA-SPAS-2

Deployed Satellites Deployed and retrieved CRISTA-SPAS-2

Experiments Technology Applications and Science (TAS-1): T

overall objective was to fly more science experim

using better, faster, and cheaper avionics and proc

This Hitchhiker payload carried the following 

experiments: 

• SOLCON

• Infrared Spectral Imaging Radiometer (ISIR)

• Shuttle Laser Altimeter (SLA)

• Critical Viscosity of Xenon (CVX)

• SEM

• Two Phase Flow (TPF)

• Cryogenic Flight Experiment (CFE)

• Stand Alone Acceleration Measurement Device 

the Wide Band Stand Alone Acceleration 

Measurement Device (SAAMD/WBSAAMD)
Table 3–110. STS-85 Mission Characteristics (Continued)

Experiments Manipulator Flight Demonstration (MFD): Spons

by NASDA, this experiment evaluated the use of 

Small Fine Arm planned to be part of the Japanes

Experiment Module’s remote manipulator system 

the ISS. It also included two other experiments:

• Two-Phase Fluid Loop Experiment (TPFLEX)

• Evaluation of Space Environment and Effects o

Materials (ESEM)

EH-2: The IEH-2 consisted of four experiments w

the common objective of investigating the uncerta

and long-term variation in the absolute solar extre

ultraviolet (EUV) flux and EUV emissions of the 

Jupiter Io plasma torus system. The experiments w

• SEH-2

• UVSTAR

• Distribution and Automation Technology 

Advancement–Colorado Hitchhiker and Studen

Experiment of Solar Radiation (DATA-CHASE

• GLO-5 and GLO-6

BDS-3: See STS-70.

PCG-STES: See STS-67. 

MSX: See STS-79.

SIMPLEX: See STS-84.

Southwest Ultraviolet Imaging System (SWUIS): 

imaging system was used primarily to view the H

Bopp comet. The SWUIS also performed ultravio

astronomy; planetary and cometary imaging; terre

airglow and atmospheric background imaging; au

imaging; and studied Shuttle glow and vehicle plu

evaluations.

BRIC-10: See STS-64. 

SSCE: See STS-41.

Get Away Specials G-572

Customer: Bellarmine College, University of Uta

Utah State University

Hearts in Space: This experiment investigated the 

of weightlessness on physical factors contributing 

cardiac function.

G-745

Customer: Students and Teachers of Mayo High S

in Rochester, Minnesota

This experiment investigated root growth during a 

Shuttle mission.
Table 3–110. STS-85 Mission Characteristics (Continued)

Space Experiment Module CAN-DO, Charleston, South Carolina

Several active experiments flew within CAN-DO

single module, including the following: a study of 

revival of a Polypodium Polypodioides plant; the 

measurement of radiation of the internal environm

of the module; the recording of “sounds” within t

module with a cassette recorder and vibration sen

and the observation of the dispersion of paint in 

microgravity. Also, the module included passive a

active experiments from other school districts.

Mission Results Successful

a Jenkins, p. 310.
Table 3–111. STS-86 Mission Characteristics 

Vehicle OV-104

Atlantis

Crew CDR: James D. Wetherbee

PLT: Michael J. Bloomfield

MS: Vladimir G. Titov (RSA), Scott E. Parazynsk

Jean-Loup J.M. Chretien (French Air Force), Wen

Lawrence, David A. Wolf (remained on Mir), C. 

Michael Foale (departed Mir for return to Earth)

Launch September 25, 1997, 10:34:19 p.m. EDT, Kenned

Space Center, Pad 39-A. On-time liftoff occurred 

final approval for flight to Mir given earlier in day 

NASA Administrator Goldin following his review 

independent and internal safety assessments regar

safety of Mir and Shuttle-Mir docking and two 

independent studies that were prompted by numer

problems on the station, including a fire and a col

(see discussion of the Mir program later in this ch

Orbital Altitude & 

Inclination

160 nmi (296 km), 51.60 deg

Launch Weight (lb/kg) 252,035a/114,321

Landing & Postlanding 

Operations

October 6, 1997, 5:55:09 p.m. EDT, Runway 15, 

Kennedy Space Center. The Shuttle landed on the 

opportunity after two opportunities on October 5 

waved off due to low clouds.

Rollout Distance (ft/m) 11,947/3,641

Rollout Time (seconds) 82

Mission Duration 259 hr, 20 min, 53 sec

Landed Revolution No. 169

Mission Support STDN

Primary Objective Seventh Shuttle-Mir docking; experimentation usi

SPACEHAB

Deployed Satellites None

Experiments SPACEHAB: This double module carried the foll

experiments:

• Human Life Sciences

• ISS Risk Mitigation

• Interferometer To Study Protein Crystal Growth 

(IPCG)

• Canadian Protein Crystallization Experiment (C

MEEP: This Mir payload gathered data on human

and natural space debris, capturing some debris fo

study.
Table 3–111. STS-86 Mission Characteristics (Continued)

Experiments SEEDS-II: This experiment passively exposed a g

of tomato seeds in hand-sewn Dacron bags to the 

vacuum of space. Seeds flown in the payload wer

compared with a control group of seeds and an 

experimental group of seeds in an underwater hab

Key Largo, Florida. After completion of the missio

seeds were distributed to schools for education an

outreach purposes. 

Kidsat: The Kidsat used an electronic still camera 

aboard the Shuttle to bring the frontiers of space 

exploration to a growing number of U.S. middle s

classrooms via the Internet.

CPCG: See STS-49.

CREAM: See STS-48.

CCM-A: See STS-80.

SIMPLEX: See STS-84.

ESA’s European Laser Docking System: This syst

monitored the Shuttle’s approach and departure fr

Mir using GPS receivers and optical rendezvous 

sensors.

Get Away Specials None

Mission Results Successful

a Jenkins, p. 310.
Table 3–112. STS-87 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Kevin R. Kregel

PLT: Steven W. Lindsey

MS: Kalpana Chawla, Winston E. Scott, Takao D

(JAXA)

PS: Leonid K. Kadenyuk (National Space Agency 

Ukraine)

Launch November 19, 1997, 2:46:00 p.m. EST, Kennedy 

Center, Pad 39-B. The liftoff proceeded on time. T

was the first use of Pad 39-B since January follow

extensive modifications to the pad structure.

Orbital Altitude & 

Inclination

150 nmi (278 km), 28.45 deg

Launch Weight (lb/kg) 260,799a/118,296

Landing & Postlanding 

Operations

December 5, 1997, 7:20:04 a.m. EST, Runway 33

Kennedy Space Center. The Shuttle landed on the 

landing opportunity.

Rollout Distance (ft/m) 8,004/2,440

Rollout Time (seconds) 57

Mission Duration 376 hr, 34 min, 2 sec

Landed Revolution No. 251

Mission Support STDN

Primary Objective Deployment and retrieval of SPARTAN 201-04; 

experimentation using the USMP-4

Deployed Satellites Deployed and retrieved SPARTAN 201-04

Experiments USMP-4: This payload conducted research in the 

of materials science, combustion science, and 

fundamental physics. 

USMP experiments operating without crew involv

included:

• AADSF

• Confined Helium Experiment (CheX)

• IDGE

• MEPHISTO

• SAMS

• OARE

Experiments housed in the MGBX requiring crew 

involvement:

• Enclosed Laminar Flames (ELF)

• Wetting Characteristics of Immiscibles (WCI)

• Particle Engulfment and Pushing by a Solid/Liq

Interface (PEP)
Table 3–112. STS-87 Mission Characteristics (Continued)

Experiments Collaborative Ukrainian Experiment (CUE): The 

was a collection of 10 plant space biology experim

that evaluated the effects of microgravity on pollin

and fertilization of Brassica rapa (Wisconsin Fast 

Plants). The experiment also compared change in 

ultrastructure, biochemical composition, and func

induced by the spaceflight environment on the 

photosynthetic apparatus of Brassica rapa seedlin

different stages of vegetative development. 

Teachers and Students Investigating Plants in Space 

(CUE-TSIPS): High school students in the United S

and Ukraine performed special plant biology scienc

experiments while viewing interactive downlinks o

Payload Specialist Kadenyuk and U.S. astronauts 

conducting the same experiments in microgravity.

Shuttle Ozone Limb Sounding Experiment/Limb O

Retrieval Experiment (SOLSE/LORE): A Hitchhi

payload, this experiment generated overall ozone 

coverage images and cross sections of the atmosp

showing ozone concentrations at different altitude

Loop Heat Pipe/Sodium Sulfur Battery Experime

(LHP/NaSBE): A Hitchhiker payload, this experim

investigated a unique thermal energy managemen

system using a loop heat pipe and studied the 

microgravity operation of sodium and sulfur liqui

electrodes. 

Turbulent Gas-Jet Diffusion Flames (TGDF): A 

Hitchhiker payload, this experiment used a GAS 

canister to gain further knowledge of the characte

of transitional turbulent gas-jet diffusion flames.

Get Away Specials G-036

Customer: El Paso (Texas) Community College a

Goddard Space Flight Center

G-036 contained four experiments:

• Cement Mixing Experiment (CME): Cement sa

were mixed with water and then compared with 

produced on Earth to analyze the effects of 

microgravity on the combination of cement and 

• Configuration Stability of Fluid Experiment (CS

The CSFE investigated the effects of micrograv

the configuration stability of a two-phase fluid s

• Computer (Compact) Disc Evaluation Experime

(CDEE): The CDEE investigated the effects of t

exosphere, the outer fringe region of the atmosp

of a planet, on the ability of discs to retain their 

information.

• Asphalt Evaluation Experiment (AEE): The AE

explored the effects of exposure to the exospher

asphalt.
Table 3–112. STS-87 Mission Characteristics (Continued)

Mission Results A malfunction of SPARTAN’s attitude control sys

caused the rotational spin of about two degrees pe

second after attempts to regrapple the satellite. Pl

research on SPARTAN was not performed. Other 

mission objectives were successfully achieved.

Remarks To retrieve SPARTAN, Winston Scott and Takao D

began a 7-hour, 43-minute EVA. They captured 

SPARTAN by hand and then completed a series o

activities continuing preparations for on-orbit asse

of the ISS. Doi became the first Japanese citizen to 

in space.

a Jenkins, p. 310.
Table 3–113. STS-89 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Terrence W. Wilcutt

PLT: Joe Frank Edwards, Jr.

MS: James F. Reilly, Michael P. Anderson, Salizh

Shakirovich Sharipov (RSA), Andrew S.W. Thom

(remained on Mir), David A. Wolf (departed Mir 

return to Earth)

PC: Bonnie J. Dunbar

Launch January 22, 1998, 9:48:15 p.m. EST, Kennedy Sp

Center, Pad 39-A. The launch originally targeted 

January 15, 1998, was changed first to no earlier t

January 20 and then to January 22 per request fro

Russian Space Agency (RSA) to allow completio

activities on Mir. Endeavour returned to the Shuttl

after completing its first OMDP. Endeavour was t

second orbiter to dock with Mir.

Orbital Altitude & 

Inclination

150 nmi (279 km), 51.60 deg

Launch Weight (lb/kg) 252,316a/114,449

Landing & Postlanding 

Operations

January 31, 1998, 5:35:09 p.m. EST, Runway 15, 

Kennedy Space Center. The Shuttle landed on the 

opportunity.

Rollout Distance (ft/m) 9,790/2,983

Rollout Time (seconds) 70

Mission Duration 211 hr, 46 min, 55 sec

Landed Revolution No. 138

Mission Support STDN

Primary Objective S/MM-08; experimentation using SPACEHAB

Deployed Satellites None

Experiments The SPACEHAB double module carried the follo

experiments:

• Mechanics of Granular Materials

• ASTROCULTURETM

• X-Ray Detector Test

• DCAM

• Gaseous Nitrogen Dewar

Closed Equilibrated Biological Aquatic System 

(CEBAS): The CEBAS mini-module was a habita

aquatic organisms. The CEBAS conducted variou

gravity-related experiments in zoology, botany, an

developmental biology, and interdisciplinary area

as scientific research on artificial ecosystems.
Table 3–113. STS-89 Mission Characteristics (Continued)

Experiments Microgravity Plant Nutrient Experiment (MPNE)

experiment tested nutrient delivery technology tha

would support plant growth in space.

EarthKAM: Students from 51 middle schools in t

nations operated a digital camera mounted in the 

overhead window of the Shuttle, selecting sites ar

the world to photograph during the Shuttle flight.

Get Away Specials G-093

Customer: University of Michigan

Vortex Ring Transit Experiment (VORTEX): The 

VORTEX investigated the propagation of a vortex 

through a liquid-gas interface in microgravity.

G-141

Customer: German Aerospace Center and the 

University of Giessen, Germany

Structure of Marangoni Convection in Floating Zo

Marangoni convection was studied without disturb

in microgravity.

G-145

Customer: German Aerospace Center and Technic

University of Clausthal, Germany

Glass Fining: G-145 studied the process of glass f

or the removal of all visible gaseous bubbles from 

glass melt.

G-432

Customer: Chinese Academy of Sciences, Beijing

China

G-432 consisted of five experiments:

• Super Cooling

• Processing of High Critical Test

• Growth of Gallium Antimony Experiment

• Liquid Phase Epitaxy

• Wetability Test

Mission Results Successful

a Jenkins, p. 310.
Table 3–114. STS-90 Mission Characteristics 

Vehicle OV-102

Columbia

Crew CDR: Richard A. Searfoss

PLT: Scott D. Altman

PC: Richard M. Linnehan

MS: Kathryn P. Hire, Dafydd (Dave) Rhys Willia

(CSA)

PS: Jay C. Buckey, James A. Pawelczyk

Launch April 17, 1998, 2:19:00 p.m. EDT, Kennedy Spac

Center, Pad 39-B. The launch was postponed on A

16 for 24 hours due to difficulty with one of Colum

two network signal processors that format data an

voice communications between the ground and th

Space Shuttle. Network signal processor No. 2 wa

replaced, and the liftoff on April 17 occurred on t

Orbital Altitude & 

Inclination

150 nmi (279 km), 39.00 deg

Launch Weight (lb/kg) 262,357a/119,003

Landing & Postlanding 

Operations

May 3, 1998, 12:08:59 p.m. EDT, Runway 33, Ke

Space Center. The Shuttle landed on the first 

opportunity.

Rollout Distance (ft/m) 9,998/3,047

Rollout Time (seconds) 58

Mission Duration 381 hr, 49 min, 58 sec

Landed Revolution No. 255

Mission Support STDN

Primary Objective Conduct final Spacelab mission: Neurolab

Deployed Satellites None

Experiments Neurolab: The Neurolab, dedicated to study of lif

sciences, focused on the most complex and least 

understood part of the human body: the nervous sy

The crew served as both experiment subjects and 

operators. Other subjects included rats, mice, cric

snails, and two kinds of fish. The Neurolab teams 

performed the following experiments:

• Autonomic Nervous System Team:

– Artificial Neural Networks and Cardiovascula

Regulation

– Integration of Neural Cardiovascular Control 

Space

– Autonomic Neuroplasticity in Weightlessness

– Autonomic Neurophysiology in Microgravity
Table 3–114. STS-90 Mission Characteristics (Continued)

Experiments • Sensory Motor Performance Team:

– Frames of Reference and Internal Models

– Visuo-Motor Coordination During Spacefligh

– Role of Visual Cues in Spatial Orientation

• Vestibular Team:

– Visual-Otolithic Interactions in Microgravity

– Spatial Orientation of the Vestibulo-Ocular R

• Sleep Team:

– Sleep and Respiration in Microgravity

– Clinical Trial of Melatonin as Hypnotic for 

Neurolab Crew

• Mammalian Development Team:

– Neuro-Thyroid Interaction on Skeletal Isomy

Expression in Zero Gravity

– Neuronal Development Under Conditions of 

Spaceflight

– Reduced Gravity: Effects in the Developing 

Nervous System

– Microgravity and Development of Vestibular 

Circuits

– Effects of Microgravity on Neuromuscular 

Development

– Postnatal Development of Aortic Nerves in S

– Effects of Gravity on Postnatal Motor Develo

• Adult Neuronal Plasticity Team:

– Central Nervous System Control of Rhythms 

Homeostasis During Spaceflight

– Anatomical Studies of Central Vestibular 

Adaptation

– Multidisciplinary Studies of Neural Plasticity 

Space

– Ensemble Neural Coding of Place and Direct

Zero-G

– Effects of Microgravity on Gene Expression i

Brain

• Aquatic Team:

– Chronic Recording of Otolith Nerves in 

Microgravity

– Development of Vestibular Organs in Microg

• Neurobiology Team: 

– Development of an Insect Gravity Sensory Sy

in Space
Table 3–114. STS-90 Mission Characteristics (Continued)

Experiments Shuttle Vibration Forces (SVF): Measured dynam

forces acting between the Space Shuttle and a can

attached to the Shuttle sidewall during the mission

BDS-04: The crew performed the following two c

biology experiments under controlled conditions o

small samples of material:

• Human Renal Cell Experiment

• Microgravity Induced Differentiation of HL-60 

Promyelocytic Leukemia Cell

Get Away Specials G-197

Customer: Lockheed Martin Astronautics, Denver

National Institute of Standards and Technology (N

and Ames Research Center, Mountain View, Calif

This experiment demonstrated pulse tube cooling 

technology in the zero gravity environment of spa

gain operational experience with the smallest such 

cryocooler yet built.

G-772

Customer: University of Colorado, Boulder

Collisions into Dust Experiment (COLLIDE): Th

COLLIDE analyzed the gentle collisions of dust 

particles in space to learn more about the sources o

in planetary rings.

G-744

Customer: Sierra College, Rocklin, California

This experiment took ozone measurements of Ear

upper atmosphere in the ultraviolet 200-nanomete

400-nanometer spectral range using a charge coup

device-based spectrometer.

Mission Results The mission was successful except for the results f

the Mammalian Development Team, which had to 

reprioritize its science activities because of the 

unexpected high mortality rate of neonatal rats on b

Remarks Columbia was outfitted with extended duration or

hardware for the flight.

Astronaut Kathryn Hires was the first Kennedy Sp

Center employee to be chosen as an astronaut can

a Jenkins, p. 310.
Table 3–115. STS-91 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Charles J. Precourt

PLT: Dominic L. Pudwill-Gorie

MS: Franklin R. Chang-Diaz, Wendy B. Lawrence

Lynn Kavandi, Valery Victorovitch Ryumin (RSA)

Launch June 2, 1998, 6:06:24 p.m. EDT, Kennedy Space Ce

Pad 39-A. The countdown proceeded smoothly exce

a slight delay in operations to load the external tank 

cryogenic propellant to evaluate a few technical issu

planned, launch managers determined the exact orbi

location of the Mir space station during the countdow

T-9-minute built-in hold. The decision was then mad

launch Discovery at 6:06 p.m. to achieve optimum S

system performance and to accommodate Shuttle-M

rendezvous activities.

Orbital Altitude & 

Inclination

204 nmia (379 km), 51.60 deg

Launch Weight (lb/kg) 259,653b/117,777

Landing & Postlanding 

Operations

June 12, 1998, 2:00:18 p.m. EDT, Runway 15, Ke

Space Center. The Shuttle landed on the first land

opportunity.

Rollout Distance (ft/m) 11,730/3,575

Rollout Time (seconds) 64

Mission Duration 235 hr, 54 min, 00 sec

Landed Revolution No. 154

Mission Support STDN

Primary Objective S/MM-09; experimentation using SPACEHAB

Deployed Satellites None

Experiments AMS: This experiment was a collaboration betwe

NASA and the U.S. Department of Energy. This w

first time a high-energy particle magnetic spectrom

was placed in orbit. The spectrometer was design

detect and catalogue, with a high degree of precis

high-energy charged particles (including antimatt

outside Earth’s atmosphere. During its time aboar

Shuttle, a complete system check was performed 

ensure it would function properly on the Space St

The spectrometer also carried out a search for ant

helium and anti-carbon nuclei and measured the 

spectrum of antiprotons.
Table 3–115. STS-91 Mission Characteristics (Continued)

Experiments Shuttle-Mir Science:

• Advanced Technology–Commercially initiated 

research to evaluate new technologies and techn

using the Mir space station and the Shuttle as a 

testbed.

– ASTROCULTURETM

– X-Ray Detector Test (XDT)

– Optizon Liquid Phase Sintering Experiment 

(OLiPSE)

• Earth Sciences–Visual observations and photogr

of sites of interest,

• Human Life Sciences–Investigations focusing on 

members’ adaptation to weightlessness in terms 

skeletal muscle and bone changes, cardiovascul

acclimatization, and psychological interactions. 

investigations continued to characterize the integ

human response to a prolonged presence in spac

– Crew member and Crew-Ground Interactions 

During NASA-Mir

– Magnetic Resonance Imaging (MRI)

– Autonomic Investigations (Cardio)

– Bone Mineral Loss and Recovery After Shuttl

Flights (Bone)

– Assessment of Humoral Immune Function Du

Long-Duration Spaceflight (Immunity)

– Renal Stone Risk Assessment During LongDuration Spaceflight (Renal-2)

• ISS Risk Mitigation

– CREAM

– Space Portable Spectroreflectometer (SPSR)

– Test of Portable Computer System (TCPS) 

Hardware

– RME

• Microgravity–Materials science research

– Microgravity Isolation Mount (MIM) Facility 

Operations PCG-Dewar

– SAMS

– QUELD

– Biotechnology System Diagnostic Experimen

(BTSDE) Reflight 

– Biotechnology System Coculture (COCULT)

– DCAM

CPCG: See STS-49.

SSCE: See STS-41.

Growth and Morphology, Boiling and Critical 

Fluctuations in Phase Separating Supercritical Flu

(GMSF): This experiment increased knowledge in 

fundamental science of critical fluids.

SIMPLEX: See STS-84.
Table 3–115. STS-91 Mission Characteristics (Continued)

Get Away Specials G-648

Customer: Canadian Space Agency’s Microgravit

Sciences Program and University of Moncton, Ne

Brunswick

ACTORS: The ACTORS processed organic mater

space where the gravitational forces were minima

compare thin films.

G-765

Customer: Canadian Space Agency and several ot

partners

• Microgravity Industry Related Research for Oil 

Recovery (MIRROR): The MIRROR conducted 

research to develop new technologies to extract 

from Earth and clean up accidental oil spills.

G-090

Customer: Utah State University designed this GA

payload to carry the following four experiments fo

school students:

• Chemical Unit Process (CUP)–Shoshone-Ba Ju

Senior High School, Fort Hall Reservation, Idah

• Nucleic Boiling–Box Elder High School, Brigh

City, Utah

• Crystal Growth Experiment–Moscow (Idaho) H

School and Moscow University, Idaho

• Popcorn/Radish Experiment–St. Vincent Eleme

School, Salt Lake City, Utah

G-743

Customer: Broward (Davie, Florida) and Brevard 

(Cocoa, Florida) Community Colleges and Belen 

Preparatory School (Miami, Florida)

A genotoxicology experiment determined the deg

which DNA was damaged by exposure to cosmic 

radiation in a space environment.
Table 3–115. STS-91 Mission Characteristics (Continued)

Space Experiment Module SEM-03: 

• Effect of Microgravity on Crossing-Over in Sor

Fimicola–Shoreham, New York Wading River H

School

• Crystal Growth in Microgravity–Tomasita Youn

Astronauts Club, Albuquerque, New Mexico

• Norfolk, Virginia Public Schools Science and 

Technology Advanced Research (NORSTAR) 

experiments:

– Effect of microgravity on development of Dap

Eubranchipus, and Triops eggs

– Separation of immiscible fluids in microgravi

• Boy Scouts Troop 177 and Four Rivers District, 

Gambrills, Maryland–Merit Badge Madness

• CAN-DO Project, Charleston, South Carolina, 

experiments:

• MAVIS–Magnetic Attraction Viewed In Space

• BEST–Big Experiment in Small Tubes

• Cosmic Radiation Effects on Programmable Lo

Devices (CREPLD)–Purdue University, West 

Lafayette, Indiana

• Woodmore Elementary School, Mitchellville, 

Maryland (WESTAR)

SEM-05:

• Effect of Spaceflight on Food Yield–Chesapeak

Girl Scout Council, Salisbury, Maryland

• Exposure of the Space Experiment Module to th

Space Environment–Excel Interactive Science 

Museum, Salisbury, Maryland

• Comparative Microgravity Response of Fungi a

Mold–Grand Coulee, Washington Elementary S

• Effect of Microgravity on Plant Seeds–Olin-San

Ruby Union Institute, Ocononmowoc, Wisconsi

• Flower Garden in Space–Virginia Parent Teache

Students Association, Accomac, Virginia

• Effects of Microgravity on Sordaria Fimicola–

Wicomico High School, Salisbury, Maryland

Mission Results Successful

Remarks After undocking of Discovery from Mir, the crew 

carried out a gas release procedure consisting of t

release of a tracer gas composed of acetone and bi

into the depressurized Spektr module on Mir. The 

procedure was designed to enable Shuttle astrona

document the ionization glow from the gas throug

hole in Spektr’s hull before sunrise and any fluore

glow from the gas after sunrise.

a Altitude not found in NASA Mission Archives. Source of altitude is Jenkins, p. 311. b Jenkins, p. 311.
Table 3–116. STS-95 Mission Characteristics 

Vehicle OV-103

Discovery

Crew CDR: Curtis L. Brown, Jr.

PLT: Steven W. Lindsey

PC: Stephen K. Robinson

MS: Scott E. Parazynski, Pedro Duque (ESA)

PS: Chiaki Mukai (JAXA), Senator John H. Glen

Launch October 29, 1998, 2:19:34 p.m. EST, Kennedy Sp

Center, Pad 39-B. The countdown proceeded to T

minutes but was held an additional 8.5 minutes w

the launch team discussed the status of a master a

heard during cabin leak checks after hatch closure

When the count picked up and the Orbiter Access 

was retracted, the Range Safety Officer (RSO) 

requested a hold at T-5 minutes due to an aircraft 

restricted air space around Kennedy Space Center

When the aircraft cleared the area, the RSO gave 

clear signal and the countdown proceeded. Follow

main engine start, but before booster ignition, the 

chute compartment door fell off but, according to 

NASA Space Shuttle Mission Chronology for ST

“posed no problem for the mission.”a Managers de

not to deploy the chute upon landing. This was th

flight of the Space Shuttle Main Engine–Block II

Orbital Altitude & 

Inclination

310 nmi (574 km), 28.45 deg

Launch Weight (lb/kg) 263,987b/119,743

Landing & Postlanding 

Operations

November 7, 1998, 12:04:00 p.m. EST, Runway 3

Kennedy Space Center. Landed on first opportuni

Rollout Distance (ft/m) 9,508/2,898

Rollout Time (seconds) 59

Mission Duration 213 hr, 14 min, 57 sec

Landed Revolution No. 134

Mission Support STDN

Primary Objective Experimentation using SPACEHAB; deployment 

retrieval of SPARTAN 201; operation of HOST: r

of John Glenn to flight

Deployed Satellites Deployed and retrieved SPARTAN 201
Table 3–116. STS-95 Mission Characteristics (Continued)

Experiments The SPACEHAB Single Module experiments inc

• Vestibular Function Experiment Unit (VFEU)

• BRIC

• Oceaneering SPACEHAB Refrigerator Freezer 

(OSRF)

• OCC 3-DMA

• AGHF

• Facility for Adsorption and Surface Tension (FA

• APCF 3-DMA

• BIOBOX

• Self-Standing Drawer-Morphological Transition 

Model Substances (SSD-MOMO)

• Osteoporosis Experiment in Orbit (OSTEO)

• NIH-C8

• Clinical Trial of Melatonin as Hypnotic for Spa

Crew (SLEEP-2)

• Protein Turnover During Space Flight (PTO)

• CPCG-PCF

• CPCG-CVDA

• MGBX 

• MGBX–Colloidal Disorder Order Transition (M

CDOT)

• MGBX–Colloidal Gelation Experiment Transit

(MGBX-CGEL)

• Commercial Instrumentation Technology Assoc

(ITA) Biomedical Experiments (CIBX)

• CGBA 1

• ASC-8

• ADSEP

• Protein Crystallization Apparatus for Micrograv

(PCAM-1)

• Biotechnology Dynamics-A (BIODYN-A)

• Aerogel

• MBGX-Internal Flows in a Free Drop (MGBX-

• Microencapsulation Electrostatic Processing Sy

(MEPS)

The HOST Platform experiments: 

• Tested flight of NICMOS cooler, planned for 

installation into the Hubble Space Telescope

• Verified the zero-gravity operation of the Rever

Turbo Brayton Cycle Cooler/CPL system 

• Tested flight of the Hubble Space Telescope 48

computer, planned for installation into the Hubb

Space Telescope 

• Tested flight of the solid state recorder and corr

to known Hubble Space Telescope flight perform

• Verified the operation of the Fiber-Optic Flight 

Experiment, a fiber-optic data link between the 

cabin and the payload bay
Table 3–116. STS-95 Mission Characteristics (Continued)

Experiments The IEH-03 experiments consisted of:

• SEH

• UVSTAR

• STAR-LITE

• CONCAP IV (see STS-57)

• Petite Amateur Navy Satellite (PANSAT)

• SOLCON

Cryogenic Thermal Storage Unit Flight Experime

(CRYOTSU): Fifth in a series of Cryogenic Test B

flights. These experiments consisted of:

• 60 K Thermal Storage Unity (TSU)

• Cryogenic Capillary Pump Loop (CCPL)

• Cryogenic Thermal Switch (CTSW)

• Phase Change Upper End Plate (PCUEP)

E-Nose: The E-Nose was an environmental moni

instrument that detected and identified a wide ran

organic and inorganic molecules down to the part

million level.

PCG-STES: See STS-49.

BRIC: See STS-64.

Get Away Specials G-467

Customer: ESA

This experiment investigated the performance of 

phase CPL with two advanced evaporators, a two

Vapor Quality Sensor (VQS), and a control reserv

G-779

Customer: Bellarmine College Louisville, Kentuc

This experiment examined the role of gravitationa

dependent hydrostatic pressure effects on the adap

of the cardiovascular system to the microgravity 

environment of spaceflight.

GAS canisters that were carried on the IEH-03 

Hitchhiker:

G-764

Customer: University of Bremen, Germany and 

Zentrum fur Angewandte Raumfahrttechnologie u

Mikrogravitation (ZARM)

Cosmic Dust Aggregation (CODAG): The CODA

experiment simulated the aggregation of dust part

and dynamics of dust clouds that occurred in the 

stages of the formation of our solar system.

G-238

Customer: American Institute of Aeronautics and 

Astronautics and DuVal High School, Lanham, 

Maryland

Roach Experiment: This experiment studied the e

of space on the life cycle of the American cockro
Table 3–116. STS-95 Mission Characteristics (Continued)

Space Experiment Module SEM-04: This canister contained the following ei

student experiment modules, part of an education

initiative to increase student access to space.

• The Effect of Microgravity and Temperature on 

Human Tissue and Human Used and Consumed 

Items–Blue Mountain School, Floyd, Virginia.

• Effects of Microgravity on an Object’s Physical 

Characteristics–Dowell Elementary School, Ma

Georgia

• The Effect of Cosmic Radiation on Wisconsin F

Plants and the Development of Brine Shrimp Eg

Chia Seeds–Fort Couch Middle School, Upper 

Clair, Pennsylvania Monrovia Elementary Scho

Madison, Alabama

• The Effects of Microgravity on Surface Tension

Glenbrook North High School, Northbrook, Illi

• Growing “Montello” Transglobally–Montello H

School, Montello, Wisconsin; Istituto Technico 

Commerciale Riccatl, Treviso, Italy

• Analysis of Three-Dimensional Sprag Performa

a Microgravity Environment–University of Mar

College Park, Maryland

• The Effect of Microgravity and Temperature on 

Growth–West Richland Elementary School, No

Illinois

• Woodmore Elementary School, Teaching And 

Researching–2 (WESTAR-2)/ GERMINAcion 

ARgentina (GERMINAR)–The Effect of 

Microgravity on Seed Growth and Survival 

Woodmore Elementary School, Mitchellville, 

Maryland; Colegio Santa Hilda, Buenos Aires, 

Argentina

Mission Results Successful

Remarks This was the first time a U.S. President (Presiden

William J. Clinton) attended a Shuttle launch.c

a “Space Shuttle Mission Chronology: STS-95,” http://www-pao.ksc.nasa.gov/kscpao/chron/st

(accessed November 30, 2005). b Jenkins, p. 311. c “The First U.S. Launch for the International Space Station: Wrapping Up a Successful Year 

Shuttle Missions,” Spaceport News 37, no. 25 (December 18, 1998): 1, 4.
Table 3–117. STS-88 Mission Characteristics 

Vehicle OV-105

Endeavour

Crew CDR: Robert D. Cabana

PLT: Frederick R. Sturckow

MS: Jerry L. Ross, Nancy J. Currie, James H. New

Sergei K. Krikalev (RSA)

Launch December 4, 1998, 3:35:34 a.m. EST, Kennedy Sp

Center, Pad 39-A. The originally scheduled launch 

Endeavour on December 3 was postponed for 24 

when time ran out on the launch window. About T

minutes in the launch countdown, after orbiter 

hydraulic systems were powered on, a master alar

associated with hydraulic system No. 1 in the crew 

cabin was noted. The countdown was held at T-31 

seconds to further assess the situation. Shuttle sys

engineers attempted to quickly complete an assess

of the suspect hydraulic system and eventually ga

initial “go” to resume the countdown. With only 

seconds to respond, launch controllers were unabl

resume the countdown in time to launch within th

remaining window. The launch was completed on 

on December 4.

Orbital Altitude & 

Inclination

173 nmi (320 km), 51.60/31.363 deg

Launch Weight (lb/kg) 239,059a/108,435

Landing & Postlanding 

Operations

December 15, 1998, 10:53:29 p.m. EST, Runway 

Kennedy Space Center. Landing made on the first 

opportunity.

Rollout Distance (ft/m) 8,343/2,543

Rollout Time (seconds) 44

Mission Duration 283 hr, 17 min, 3 sec

Landed Revolution No. 185

Mission Support STDN

Primary Objective To deliver the first U.S. ISS module Unity and asse

with the first Russian ISS module Zarya, already i

space

Deployed Satellites Argentinean National Commission of Space Activ

Satelite de Aplicaciones/Cientifico-A (SAC-A)
Table 3–117. STS-88 Mission Characteristics (Continued)

Experiments MightySat 1: The MightySat 1 was a non-recover

all-composite spacecraft structure and experiment

integrated with a Hitchhiker Ejection System. The 

program was dedicated to providing frequent, 

inexpensive, on-orbit demonstrations of space sys

technologies. The experiments were:

• Advanced Composite Structure

• Advanced Solar Cell

• Microsystem and Packaging for Low Power 

Electronics

Assessment of Human Factors Configuration A: Th

experiment analyzed human-machine, humanenvironment, and human-human interfaces.

Effects of Microgravity on Cell-Mediated Immunit

Reactivation of Latent Viral Infections: This experi

assessed the immune system function using the imm

cells from the standard Flight Medicine blood draw

objective was to examine the mechanisms of space

induced alterations in the human immune function 

latent virus shedding.

Individual Susceptibility to Post-Spaceflight Ortho

Intolerance: This experiment investigated mechani

responsible for differences in post-spaceflight ortho

intolerance to customize countermeasure protocols

Interaction of the Space Shuttle Launch and Entry 

and Sustained Weightlessness on Egress: This 

experiment identified the impact of the Launch En

Suit/Advanced Crew Escape Suit (LES/ACES) an

sustained weightlessness on egress locomotion 

mechanical efficiency as measured by oxygen 

consumption and gait change.

Low Iodine Residual System: This system used a n

developed technology that replaced the Galley Iod

Removal Assembly (GIRA) to reduce the concentr

of iodine in the Shuttle potable water system, 

demonstrating that iodine concentrations in Shuttl

drinking water can be reduced to medically accep

levels while maintaining microbial control in the w

distribution system.

Single String Global Positioning System: This sys

demonstrated GPS performance and operation dur

orbiter ascent, on-orbit operations, entry, and land

phases using a modified military GPS receiver 

processor and existing orbiter GPS antennas.
Table 3–117. STS-88 Mission Characteristics (Continued)

Experiments Space Integrated Global Positioning System/Inert

Navigation System (SIGI): The SIGI mitigated th

technical and schedule risks of applying this new 

technology to the Shuttle navigation systems by 

evaluating the systems’ performance in spacefligh

Structural Dynamics Model Validation: This test 

excited the structural dynamics of the joined Shut

and ISS to acquire several critical natural frequenc

and their corresponding structural damping to allo

confirmation of the acceptability of the Shuttle pri

jet control algorithm tuning before attitude contro

using the algorithm.

USA SAFER Flight Demonstration: This 

demonstration showed, through an end-to-end on-

functional checkout, that the USA SAFER design 

performed as expected.

ICBC: The ICBC was a 65-mm color motion pictu

camera system used to film the Unity installation 

the orbiter docking system; the Zarya rendezvous

docking; EVA tasks; separation burn; and flyaroun

Get Away Specials G-093R

Customer: University of Michigan (Ann Arbor) 

Students for the Exploration and Development of 

Vortex Ring Transit Experiment: Investigated the 

propagation of a vortex ring through a liquid-gas 

interface in microgravity.

Space Experiment Module SEM-07: This module contained 11 experiments a

of an educational initiative to increase student acc

space.

Mission Results Successful

a Jenkins, p. 311.
s 

Table 3–118. Space Station Freedom Prime 

Prime Contractor/ Work Package Description Phase I Value 

NASA Center

Boeing Aerospace/ Work Package 1: Laboratory and habitation $1.6 billion $

Marshall Space Flight modules; resource node structures; airlock Center systems; environmental control/life support; 

thermal/video/ audio systems; logistics elements

McDonnell Douglas Work Package 2: Truss structure; mobile $2.6 billion $

Astronautics/Johnson servicing transporter; airlocks; resource (Space Center node outfitting; data management; s

communications and tracking; guidance; navigation and control; EVA systems; propulsion; thermal control

General Electric Astro- Work Package 3: Polar platform; two attach $895 million $

Space/ Goddard Space points on crewed base; integrated telerobotic (Flight Center servicer; defined satellite servicing facility p

mps

Rockwell International Photovoltaic power generation system $1.6 billion $Rocketdyne Division/ (Lewis Research Center p

databk7_collected.book Page 552 Monday, September 14, 2009 2:53 PM

a “Space Station Freedom Contract Negotiations Concluded,” NASA News Release 88-132, September 28, 1988

(September 1988): 18.
Table 3–119. Space Station Freedom Characteristics 

(May 1992a) 

Element Shape Characteristic

Station end-to-end length 108 m (353 ft)

Station total weight 281,430 kg (309.6 tons)

Truss assembly and Hexagonal Length: 65.9 m (216.0 ft)

equipment size Width: 3.7 m by 4.9 m (12 ft by 

Truss assembly and 146,000 kg (160.6 tons)

equipment weight

U.S. laboratory size Cylindrical 8.4 m by 4.4 m (27.4 ft by 14.5 f

U.S. laboratory weight 15,545 kg (17.1 tons)

U.S. habitation module size Cylindrical 8.4 m by 4.4 m (27.4 ft by 14.5 f

U.S. habitation module 16,182 kg (17.8 tons)

weight

Japanese laboratory Cylindrical 10.6 m by 4.0 m (34.8 ft by 13.1 

Japanese Exposed Facility Cylindrical 5.0 m by 5.6 m (16.4 ft by 18.4 f

Japanese module weight 32,818 kg (36.1 tons) (both labor

and exposed facility)

International standard 1 m (3.5 ft) wide

payload racks

U.S. resource nodes size Cylindrical Three each 5.2 m by 4.4 m (17 ft 

14.5 ft); centrifuge in third resou

node

U.S. resource node weight Two nodes and cupola: 23,545 k

(25.9 tons)

Canadian Mobile Servicing 

System

Space System Remote 55 ft (16.8 m)

Manipulator

Space System Remote 113,398 kg (250,000 lb)

Manipulator capacity

Special Purpose Dexterous 12 ft (3.6 m) (two 6-ft (1.8-m) ar

Manipulator

ESA Columbus Free-Flying Cylindrical 11.8 m (38.7 ft) by 4.5 m (14.7 f

laboratory

Solar arrays size Rectangular 12 m (39 ft) and 34 m (112 ft)

Solar arrays weight 7,909 kg (8.7 tons) 

(does not include truss)

Number of cells per array 32,800

wing

Number of solar cells for 196,800

six array wings
Table 3–119. Space Station Freedom Characteristics 

(May 1992a) (Continued)

Element Shape Characteristic

Power generation 120 volts DC, 18.75 kW at mantended capability with at least 11 

available to researchers. Would g

to 56.25 kW in the follow-on pha

(permanently tended capability), 

nominal 30 kW available for use

26.25 kW available for housekee

Crew Four persons (two dedicated for 

payload operations and two 

researchers), growing to eight cre

the follow-on phase

Altitude 335 km–460 km (208 nmi–285 n

Inclination 28.5 degrees 

a “Space Station Freedom, Gateway to the Future,” National Aeronautics and Space Administrati

1992 (NASA History Office Folder 009554). Also Space Station Freedom Media Handbook, 199

b Space Station Freedom User’s Guide, August 1992, p. 3-3 (NASA History Office Folder 00955

Launius, p. 234. Power was reduced to 56.25 kW from 75 kW for permanently tended capabi

1992 redesign.
Table 3–120. Shuttle-Mir Flight

Mission Dates Orbiter Type of Mission 

STS-63 February 3 – February 11, 1995 Discovery RendezvousSTS-71 June 27 – July 6, 1995 Atlantis Docked Returned 

(Thagard 

STS-74 November 12 – November 20, 1995 Atlantis Docked No astroSTS-76 March 22 – March 30, 1996 Atlantis Docked Delivere

STS-79 September 19 – September 26, 1996 Atlantis Docked Returned 

STS-81 January 12 – January 22, 1997 Atlantis Docked Returned 

Linenger

STS-84 May 15 – May 24, 1997 Atlantis Docked Returned 

Foale.

STS-86 September 25 – October 6, 1997 Atlantis Docked Returned STS-89 January 22 – January 31, 1998 Endeavour Docked Returned 

Thomas

STS-91 June 2 – June 12, 1998 Discovery Docked Returned 

databk7_collected.book Page 555 Monday, September 14, 2009 2:53 PM
s

Table 3–121. ISS Contributora

Country/Space Agency Component

Canada Mobile servicing system

European Space Agency Columbus laboratory module

Japan Experiment module with centrifuge 

facility

Exposed facility

Russia Power platform

Service module

Functional cargo block (FGB)b

Two research modules

United States Integrated truss

Habitation module

Laboratory module

Docking modules and passageway (N

Joint airlock 

Italy Nodes 2 and 3 built for NASA

a “International Space Station Builds on ‘Freedom,’” HQ Bulletin (April 4, 1994): 1 (NASA 

Office Folder 009577); Press Information Book, The Boeing Company (NASA History Offic

16482). b The first Russian module is referred to in NASA and Russian documents and Web sites as 

Functional Energy Block and the Functional Cargo Block. For uniformity, it is called Function

Block in this document. The acronym FGB comes from the Russian translation written in the 

alphabet.
Table 3–122. ISS Major Milestones (as of April 1994a) 

Date Event

November 1997 Russian FGB vehicle launch

December 1997 First U.S. launch

January 1998 Russian service module added, follo

by the addition of the universal dock

module and science power platform

May 1998 U.S. laboratory module attached (ma

the beginning of human-tended scien

operations)

June 1998 Canadian-built robotic arm added

August 1998 Addition of the Soyuz transfer vehic

Early 2000 ESA laboratory module added

June 2002 Assembly complete

a “International Space Station Builds on ‘Freedom,’” HQ Bulletin (April 4, 1994): 1 (NASA 

Office Folder 009577).

Table 3–123. ISS Assembly Schedule (June 1994a)

Schedule Date Payload

First Russian element November 1997 FGB

launch

First U.S. element launch December 1997 Node 1 (with four rack

Human-tended capability June 1998 U.S. lab outfitting

Three-person on-orbit August 1998 Soyuz crew transfer v

capability

Japanese lab launch March 2000 Japanese Experiment 

Module pressurized la

European Space Agency lab March 2001 Attached pressurized 

launch module

Habitation module launch February 2002 U.S. habitation modul

Permanent human June 2002 Soyuz crew transfer v

capability

a International Space Station Fact Book, National Aeronautics and Space Administration, June 1
Table 3–124. Columbus Characteristics a

Item Description

Total module length 687 cm (22.5 ft)

Largest diameter 448 cm (14.7 ft)

Total internal volume 75 cu meters (2,649 cu ft)

Total volume of payload racks 25 cu meters (883 cu ft)

Mass without payload 10,300 kg (22,708 lb)

Launch mass 12,800 kg, including 2,500-kg paylo

(28,219 lb, including 5,512-lb paylo

Maximum payload mass 8,000 kg (17,637 lb)

Maximum on-orbit mass 19,300 kg (42,549 lb)

Communications Downlink via Artemis; downlink an

uplink via TDRS

Crew size Three

Cabin temperature Between 16°C and 30°C (61°F and 8

Air pressure Between 959 and 1013 hPa

Total electrical power 20 kW provided by the Station

Payload power 13.5 kW

Main contractor Daimler Benz Aerospace leading a 

consortium of subcontractorsb

a “Columbus: European Laboratory,” ESA, http://www.esa.int/esaHS/ESAFRG0VMOC_iss

(accessed June 14, 2005). b Daimler Benz Aerospace merged with Matra Marconi Space in May 2000 to form Astrium Gm
Table 3–125. Partial Revised Manifest, Revision C, 

Through 1999 (as of May 15, 1997a) 

Date Flight Element

June 1998

July 1998

December 1998

December 1998

January 1999

January 1999

March 1999

May 1999

June 1999

August 1999

1A/R

2A

1R

2A.1

3A

2R

4A

5A

6A

7A

Functional Cargo Block

STS-88/U.S. Node 1 and two pressu

mating adapters (PMA)

Service module

Either service module logistics or th

Interim Control Module

Integrated truss structure Z1, PMA-

Ku-band communications system, co

moment gyros

Three-person crew begins permanen

presence on ISS: Soyuz provides ass

crew return capability

Integrated truss structure Port 6, 

photovoltaic module, S-band antenn

system

Lab provides initial U.S. user capab

Adds U.S. multipurpose logistics mo

ultra-high frequency antenna, ISS re

manipulating system; carries second 

crew

Joint airlock provides U.S. and Russ

EVA capability, high pressure gas 

assembly

Phase II Complete

October 1999

December 1999

7A.1

4R

Multipurpose logistics module, addit

battery sets

Docking compartment 1 provides eg

ingress for Russia-based EVA and a 

Soyuz docking port

a “Assembly Sequence, 5/15/97 Rev C,” National Aeronautics and Space Administration, Inter

Space Station (NASA History Office Folder 11613). Also “Station Buildup Sequence Co

Complex Hardware,” Aviation Week & Space Technology (December 8, 1997): pp. 52–53 (

Office Folder 16949).
Table 3–126. ISS Assembly Sequence Revision D, Through 

Date Flight Launch Vehicle 

November 1998 1A/R Proton Control Module (Function

December 1998 2A Space Shuttle (STS-88) Unity node, two PMAs April 1999 1R Proton Service module May 1999 2A.1 Space Shuttle (STS-96) SPACEHAB Double Carg

June 1999 3A Space Shuttle (STS-92) Integrated Truss Structure July 1999 2R Soyuz Soyuz. Station begins perAugust 1999 4A Space Shuttle (STS-97) Integrated Truss Structure 

October 1999 5A Space Shuttle (STS-98) U.S. Laboratory Module December 1999 6A Space Shuttle (STS-99) Multipurpose Logistics M

databk7_collected.book Page 560 Monday, September 14, 2009 2:53 PM
s

Table 3–127. Functional Cargo Block (Zarya) Specificationsa

Item Specification

Length (end-to-end) 12.6 m (41.2 ft)

Diameter at widest point 4.10 m (13.5 ft)

Solar arrays 10.7 m (35 ft) by 3.4 m (11 ft)

Gross launching mass 23,500 kg (53,020 lb)

Orbital mass 19,323 kg (42,600 lb)

Orbital operation No less than 15 years

lifetime

Orbital inclination 51.6 degrees to the equator

Preliminary orbit 220.4 km (137 mi) by 339.6 km (211 mi)

Docking orbit altitude 386.2 km (240 mi)b

Propellant 16 tanks together holding more than 5.4 metric tons (6 

Power supply Two solar arrays and six nickel-cadmium batteries

Power to be supplied to Can supply an average of 3 kW

the U.S. segment Daily average before docking with service module: 0

Daily average after docking with service module: 1.2 

a “Functional Energy Block,” Khrunichev State Research and Production Space Center (Histor

Folder 17083). Also “Zarya,” ISS Element, http://www.shuttlepresskit.com/ISS_OVR/eleme

(accessed June 13, 2005); “Space Station Assembly: Elements: Zarya Control Module,” N

Aeronautics and Space Administration, http://spaceflight.nasa.gov/station/assembly/elem

index.html (accessed June 17, 2005). b The docking orbit altitude is the altitude at which Endeavour made rendezvous and captured the sp

to attach it to the U.S.-built Unity module. “Space Station Assembly: Elements: Zarya Control M

http://spaceflight.nasa.gov/station/assembly/elements/fgb/index.html (accessed December 2, 2005

Table 3–128. Unity Characteristicsa

Item Characteristic

Module length 18 ft (5.5 m)

Module diameter 15 ft (4.6 m)

Shape Six-sided

Pressurized mating adapters 8 ft (2.4 m)

length

Launch weight 25,600 lb (11,612 kg)

Ports Six 50-in (127-cm) ports (4 radial and 2 axia

Material Aluminum

Lines 216 lines to carry fluids and gases

Cables 121 internal/external electrical cables using 

(9.7 km) of wire

Stowage space Four 27-cu-ft (9.8-cu-m) racks

a Press Information Book, Mission Modules, Station Overview, NASA, Boeing, pp. 5–6, 12.
Table 3–129. Zarya-Unity Orbital Events Summarya

Day Date Event

1 November 20, 1998 Proton launch, ascent, and orbit insertion of Zar

Begin multi-axis spin for thermal control and to 

reduce fuel consumption.

2 November 21, 1998 Engine test burn (10 seconds duration, single en

Television camera test.

Perform perigee raising burn (single engine).

Resulting orbit is 153 statute mi (246 km) by 21

statute mi (346 km).

4 November 23, 1998 Perform two burns to raise orbit; resulting orbit

mi (306 km) by 238 mi (383 km).

5 November 24, 1998 Russian flight controllers place the module in it

orbit to achieve Endeavour rendezvous. Resulti

orbit is 240 miles (386.2 km) circular.b

6 November 25, 1998 Perform on-board computer system test. Maneu

test Endeavour capture, docking orientation. 

Maneuver to assess solar array performance.

8 November 27, 1998 Maneuver to test Endeavour capture, docking 

orientation. Assess solar array, battery charging 

performance. Begin multi-axis spin.

14 December 3, 1998 Endeavour launches on STS-88. Astronauts act

Shuttle Orbiter Docking System.

15 December 4, 1998 Perform Shuttle remote manipulator system, Or

Space Vision System, spacesuit checkout.

16 December 5, 1998 Attach Unity PMAs to the Orbiter Docking Sys

using the Shuttle remote manipulator system.

17 December 6, 1998 Rendezvous with and capture Zarya with Endea

remote manipulator system. Zarya berths to Un

PMA-1.

18 December 7, 1998 First spacewalk to connect utilities between PM

Unity PMA-1, and Zarya. Activate Unity 

computerized control units and PMA shell heat

19 December 8, 1998 Pressurize PMA-1 via Zarya.

20 December 9, 1998 Second spacewalk to install early communicatio

system antennas and cable, install computerized 

control sunshade, EVA aids, and remove comm

berthing mechanism hatch launch restraint pins

21 December 10, 1998 ISS entered for the first time. Install and activat

communications system; remove shear panels; 

transfer spare equipment to ISS.

22 December 11, 1998 ISS entered; complete remaining tasks; doors cl

to ISS at end of day.

23 December 12, 1998 Third spacewalk to install EVA node stowage b

perform photo documentation survey, and other 

ISS first element completed.
Table 3–129. Zarya-Unity Orbital Events Summarya (Continue

Day Date Event

24 December 13, 1998 Endeavour/ISS undock, flyaround.

25 December 14, 1998 Perform Endeavour secondary payload operatio

25–34 December 14–23, Systems checkout by ground controllers throug

1998 S-band communications system installed on Un

26 December 15, 1998 Endeavour returns home.

a “Summary Flight Plan, The International Space Station,” http://www.shuttlepresskit.com/IS

assembly1_summary_timeline.htm (NASA, Boeing, and United Space Alliance Web site) (acces

13, 2005). Also Press Information Book, Mission Modules, Station Overview, NASA, Boeing, p

b “Space Station Assembly: Elements: Zarya Control Module,” http://spaceflight.nasa.gov

assembly/elements/fgb/index.html (accessed June 17, 2005).

Table 3–130. Science Laboratories Accommodationsa

Type of Feature

Accommodation

Overall • 30 kW average power available for payloads

• 75 Mb/sec data downlink

• Teleoperations

• Multipayload modular environment

• Standardized service interfaces for payloads

Internal payload • 37 rack locations

• Vibration-free environments

• Microgravity environment: 10 locations at 1g level

• 3 kW, 6 kW, and 12 kW power options

• Vacuum, nitrogen, argon, helium, and carbon dioxi

service options

• Ethernet, video, high-rate data download

• Payload volumes: more than 40 cu ft (1.1 cu m) pe

• Many racks support multiple modular sub-rack pay

• One location with an Earth-facing science-quality 

window

External payload • 14 payload sites

• 10 locations with active thermal control

• 3 kW and 6 kW power options

• Video, high-rate data downlink

• Earth and stellar viewing sites

• Robotic payload manipulation

a Press Information Book, p. 53.
Table 3–131. Space Station Chronology 

Date Event

January 25, 1984 President Ronald Reagan delivers State of the Union add

calling for a “permanently manned space station” to be b

within a decade.

February 20, 1986 Mir space station core sent into space on a Proton booste

rocket.

March 1986 First Russian crew arrives on Mir.

1987 Space Station development split into two phases: the revi

baseline configuration and the enhanced configuration.

1987 NASA Administrator Fletcher requests $3 million to stud

crew emergency return vehicles.

July 1988 President Ronald Reagan names the Space Station “Freed

September 28, 1988 Negotiations concluded for four 10-year contracts with B

Aerospace, McDonnell Douglas Astronautics, GE Astro-

Division, and Rocketdyne Division of Rockwell Internati

to correspond with four work packages.

June 1989 Assembly sequence is revised to allow only the Shuttle fo

lifting and assembling components.

July 1989 NASA forms Configuration Budget Review team headed 

Ray Hook to develop preliminary options for ways for th

program to exist within severe budget constraints threaten

Congress.

October 1989 Congress funds program at $1.8 billion, $250 million les

the administration’s request.

October 1989 NASA releases a request for proposal for the Assured Cr

Return Vehicle.

Late 1989 “Rephasing” of program announced to reduce risk and m

anticipated budget cut of nearly $300 million for FY 1990

element launch remains at March 1995.

January 1990 NASA forms the External Maintenance Task Team to add

EVAs needed for Station maintenance.

June 1990 NASA forms the External Maintenance Solutions Team t

address problems raised by the External Maintenance Tas

Team and to recommend ways to reduce the number of 

spacewalks.

Fall 1990 White House forms the Advisory Committee on the Futu

the U.S. Space Program, chaired by Norman Augustine, 

assess alternative approaches and make recommendation

future civil space goals. Committee recommends reducin

Station’s size and complexity.

March 1991 NASA delivers restructuring report to Congress for a sma

and simpler Station with a $30 billion price tag. Work Pa

2 with GE is eliminated. A rephased assembly sequence m

first element launch to early 1996, human-tended capabil

mid-1997, and permanent occupation to 2000. 
Table 3–131. Space Station Chronology (Continued)

Date Event

March 21, 1991 Vice President Dan Quayle and the National Space Coun

endorse report and redesign.

July 1991 Vice President Dan Quayle meets with Oleg Shishkin, mi

of General Machine Building in the Soviet Union, to disc

cooperative effort using the Mir space station for human 

missions.

July 31, 1991 President George H. W. Bush and Soviet President Mikh

Gorbachev sign an agreement for an astronaut to visit Mir 

cosmonaut to fly on the Space Shuttle.

September 27, 1991 The House Appropriations Committee recommends cutti

all funds to the Station, but the Senate agrees to a House 

funding bill and grants NASA its full FY 1992 funding re

of $2,028,900,000 for the Space Station.

December 9, 1991 President George H. W. Bush signs NASA’s funding bill.

April 1, 1992 Daniel Goldin replaces Richard Truly as NASA Adminis

April 1992 Russian President Boris Yeltsin creates the civilian Russi

Space Agency, headed by Yuri Koptev. Goldin and Kopte

meet informally in Washington, DC to discuss possibiliti

cooperation.

June 17, 1992 President George H. W. Bush and Russian President Yelt

hold a summit in which the two agree to consider a joint 

mission. They sign the “Agreement Between the United S

of America and the Russian Federation Concerning 

Cooperation in the Exploration and Use of Outer Space f

Peaceful Purposes” that includes a Shuttle-Mir mission.

June 19, 1992 Russia and the United States formally sign a new U.S.-Ru

Space Cooperation Agreement and ratify a $1 million co

between NASA and Russian aerospace firm, NPO-Energ

October 5, 1992 NASA and the Russian Space Agency sign an “Implemen

Agreement Between the National Aeronautics and Space 

Administration of the United States of America and the 

Russian Space Agency of the Russian Federation on Hum

Space Flight Cooperation” that details cooperation called 

the June 1992 agreement. 

March 9, 1993 President William J. Clinton orders NASA to undertake a 

redesign of the Station to reduce costs and complexity. T

administration goal was $9 billion.

March 10, 1993 First meeting of the Station Redesign Team, led by Dr. Jo

Shea.

April 1993 An Advisory Committee, also known as the Vest Panel, i

formed to assess redesign options.

April 3–4, 1993 President William J. Clinton and Vice President Albert A

meet with Russian leaders at a summit in Vancouver, Can

on further cooperation in space. President William J. Clin

invites Russia to participate in the new Station, and Russ

President Yeltsin agrees.
Table 3–131. Space Station Chronology (Continued)

Date Event

June 10, 1993 Advisory Committee presents final report to President W

J. Clinton.

June 17, 1993 President William J. Clinton announces his selection of a 

reduced cost, scaled-down version of the original Space S

Freedom, called Alpha, with a $10.5 billion cost spannin

years. The President also directs NASA to develop an 

implementation plan by September 1993.

August 17, 1993 Goldin names Johnson Space Center as the host Center fo

new Space Station program and Boeing as the single prim

contractor.

September 1–2, 1993 United States-Russian Commission on technological coope

in the areas of energy and space, headed by Vice President A

A. Gore and Russian Prime Minister Viktor Chernomyrdin

meets and agrees on a three-phase structure to complete th

Space Station.

September 7, 1993 President William J. Clinton formally chooses the small, 

person Alpha Station, a merger of Space Station Freedom 

the Russian Mir. Congress and the administration agree t

total cost cap of $17.4 billion and a fixed annual budget o

billion. NASA slips the date for permanent habitability to 

September 2003.

October 16, 1993 The United States meets with international partners in Pa

France to formally inform them of the intent to invite Rus

join the Space Station program.

November 1, 1993 Goldin and Koptev sign an “Addendum to Program 

Implementation Plan” for Space Station Alpha describing 

overall concept of the relationship between NASA and th

Russian Space Agency.

November 7, 1993 Space Station partners jointly meet with the Russian Spa

Agency to review details of the November 1 addendum.

November 15, 1993 NASA signs a letter contract with Boeing making the com

the Space Station prime contractor.

November 29, 1993 An agreement is reached for Russia to be “the primary pa

in the Space Station program, which would be designated 

International Space Station. Russia agrees to cancel the pl

sale of missile technology to India and would receive $10

million annually from NASA as compensation.

December 6, 1993 Space Station partners decide to formally invite Russia to 

the partnership.
Table 3–131. Space Station Chronology (Continued)

Date Event

December 16–17, The Gore-Chernomyrdin Commission meets in Moscow. 

1993 Russia to announce the Commission’s acceptance of the 

invitation to join the Space Station program. Goldin and 

Koptev sign a protocol expanding the terms of the 1992 H

Cooperation agreement and agree on Shuttle-Mir flights d

1995–1997. Albert A. Gore and Chernomyrdin sign a “Jo

Statement on Space Station Cooperation” describing the 

needed to formally bring Russia into the Station partners

The two parties note that NASA and the Russian Space A

have agreed to a $400 million contract through 1997 for t

Shuttle-Mir program and other Station development.

February 1, 1994 Space Station Freedom is formally terminated when cont

ending the work package contracts are ended and respons

is consolidated in a contract with Boeing.

February 3, 1994 Phase I of the ISS begins when Cosmonaut Sergei Krikal

becomes the first Russian to fly on a U.S. spacecraft on t

STS-63 Shuttle mission, inaugurating the Shuttle-Mir pro

March 1994 The ISS assembly schedule is revised with the first Shutt

launch moved from July 1997 to December 1997, and the 

completion date slipped from October 2001 to June 2002

March 1994 The successful System Design Review marks a major tech

milestone; it confirms the validity of the baseline configur

schedule, and cost. Planned assembly is scheduled to beg

November 1997 with the Russian FGB. Assembly planne

be complete in 2002. 

April 1994 Heads of the Space Station agencies meet in Washington

to endorse the successful review and reaffirm Russia’s pa

the program.

 June 23, 1994 The U.S.-Russian Joint Commission on Economic and 

Technological Cooperation signs a new “Joint Statement 

Space Station Cooperation” reiterating the two governme

commitment to develop an integrated Space Station and t

expedite Russia’s involvement as a full partner in the pro

June 29, 1994 A bipartisan House coalition defeats a motion to cancel t

Station.

July 1994 The Space Station Control Board approves a revised asse

sequence moving launch of Russia’s service module from 

January to May 1998. The Board also agrees to purchase 

FGB from Khrunichev to assure its availability when Sta

assembly begins.

August 3, 1994 The Senate rejects motion to cancel the Station.

August 31, 1994 NASA and Boeing agree on the key elements of the ISS p

contract.

September 1994 Space Station managers release another updated assembly 

incorporating a centrifuge to augment the Station’s scienc

capabilities and provide more power.
Table 3–131. Space Station Chronology (Continued)

Date Event

1995 X-38 project begins at Johnson Space Center.

January 13, 1995 NASA and Boeing sign a $5.63 billion contract to manag

building of the core Station, including two nodes, an airlo

and laboratory and habitation modules and their integrati

The contract also calls for the design and development of 

Station.

February 5, 1995 NASA and the Russian Space Agency sign a protocol refl

the contract negotiated between Boeing subcontractor 

Lockheed Missiles & Space and Khrunichev for the FGB

May 1995 ISS completes tests to evaluate the Water Recovery Syste

May 20, 1995 Spektr module is launched toward Mir.

July 1995 The orbiter Atlantis permanently attaches a new docking 

module to the Mir Kristall androgynous docking unit.

July 1995 The House defeats an attempt to cut off Station funding.

September 1995 The Senate defeats a motion to cut off Station funding.

Mid-September 1995 By this date, the United States has produced 54,000 poun

ISS hardware; international partners have manufactured a 

of more than 60,000 pounds of hardware. Boeing complet

main structure, Node 2, of the U.S. laboratory module.

October 18, 1995 The ESA Council meets in Toulouse, France, and approv

program “European Participation in the International Spa

Station Alpha,” providing for the Columbus laboratory m

ATV, and studies of a European CTV.

December 1995 The Russian Space Agency announces that the Russian 

government owes Khrunichev money for work performed 

1995 and, if the government does not release the funds ne

for the FGB and service module, it would be unable to me

FGB’s launch date and unable to build the service modul

January 1996 Exterior of the U.S. Station’s modules is completed.

March 27, 1996 NASA Administrator Goldin states that he is giving Russ

month or six weeks to “get [the] Station moving again” an

he is “cautiously optimistic” that Russia will be able to “

its commitment to deliver the critical service module on 

time...”a

May 1996 The ISS air purification system passes a major test of abi

control carbon dioxide, oxygen, and air pressure inside th

Station’s living and laboratory quarters.

November 1996 Node 1, the U.S. module, successfully completes the mod

final pressure test.

December 1996 Russian FGB is assembled and ready for testing. The Ru

Space Agency acknowledges that the service module wil

to be delayed until December 1998 because of lack of fun

January 1997 NASA allocates $100 million to Lockheed to develop the 

Interim Control Module as a backup to Russia’s service 

module.
Table 3–131. Space Station Chronology (Continued)

Date Event

February 24, 1997 A fire on Mir endangers the crew.

April 1997 NASA and the Russian Space Agency formally agree to 

launch of the FGB from November 1997 to mid-1998.

April 9, 1997 NASA announces a slip in the Station’s on-orbit assembl

“no later than” October 1998.

April 11,1997 Russia arranges for bank loans to Energia by the end of M

allowing work to resume on the service module.

May 15, 1997 The Space Station Control Board releases a new assembl

schedule, Revision C. The FGB is scheduled to launch in 

1998, the U.S. node in July 1998, and the service module 

December 1998.

May 31, 1997 The heads of space agencies accept Revision C at a meet

Tokyo. Japan.

June 25, 1997 Collision between Progress cargo ship and Mir causes air 

and extensive damage.

June 1997 Node 1 (Unity) is shipped to Kennedy Space Center from 

Boeing plant in Alabama.

July 1997 Unpiloted, captive-carry flight tests of X-38 test airframe

attached to B-52 aircraft begin at Dryden Flight Research 

Center.

September 1997 NASA and Boeing reveal that Boeing’s prime contract w

have at least a $600 million overrun at completion and th

NASA needs $430 million more than expected for FY 19

September 1997 Goldin requests that the NASA Advisory Council establi

cost control task force.

September 1997 Revision C of the assembly and launch schedule is forma

approved by all partners. The first U.S.-built element, No

is scheduled to launch in July 1998, the Russian service m

in December 1998, and the ESA’s Columbus is scheduled 

launch in October 2002.

September 18, 1997 The GAO releases a report describing worsening cost ove

October 14, 1997 NASA and the Brazilian Space Agency sign an implemen

arrangement providing for the design, development, oper

and use of Brazilian-developed flight equipment and pay

for the ISS in exchange for Brazil’s access to ISS facilitie

orbit and a flight opportunity for a Brazilian astronaut.

November 1997 Boeing admits to a House panel that its costs are millions 

dollars over its contract amount.

January 29, 1998 The United States and international partners sign a multil

agreement formalizing the framework for cooperation am

the ISS partners. Goldin also signs bilateral agreements w

the heads of the ESA, the Canadian Space Agency, and th

Russian Space Agency describing their roles and 

responsibilities. A similar agreement with the governmen

Japan is signed on February 24, 1998.
Table 3–131. Space Station Chronology (Continued)

Date Event

March 12, 1998 First free-flight X-38 drop tests take place at Dryden Flig

Research Center.

April 15, 1998 The Cost Control Task Force, chaired by Jay Chabrow, de

its report to the Advisory Council. The report states that N

will need an estimated $7 billion extra and up to three 

additional years to complete the program.

May 31, 1998 NASA’s partners agree to officially target a November 19

launch for the first Station component and to revise rema

launch dates. The partners set an April 1999 launch date f

service module and a summer 1999 date for transport of t

first crew by Soyuz to the ISS.

June 15, 1998 The NASA response to the Cost Control Task Force repo

released. NASA identifies $1.4 billion in additional costs

schedule has been changed to accommodate a four-month 

service module schedule slip. The first element launch w

moved to November 1998, and the ISS assembly complet

is scheduled for January 2004.

November 20, 1998 Launch of Zarya (FGB) takes place from the Baikonur 

Cosmodrome in Kazakhstan.

December 3, 1998 First U.S. component, Unity, is launched on STS-88.

December 6, 1998 Unity and Zarya dock.

a “Goldin Gives Russia Six Weeks To Get Station Moving Again,” Aerospace Daily (March 27

Article 28066 (NASA History Office Folder 17083).