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

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-34 

PRESS KIT 

OCTOBER 1989 

PROJECT GALILEO 
Edited by Richard W. Orloff, 01/2001/Page 2 

STS-34 INSIGNIA 

S89-29077 -- The triangular shape of the STS-34 crew insignia represents forward motion and the entering 

into new frontiers of science, engineering and technology. The Galileo spacecraft overlaying the orbiter 

symbolizes the joining together of both manned and unmanned space programs in order to maximize the 

capabilities of each. The crew members, who designed the insignia, use a sunrise stretching across Earth's 

horizon to depict expansion of our knowledge of the solar system and other worlds, leading to a better 

understanding of our own planet. In the distance, Jupiter, a unique world with many unknowns, awaits the 

arrival of Galileo to help unlock its secrets. Meanwhile, the space shuttle remains in Earth orbit, 

continuing to explore the near-Earth environment. 

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

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

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

not anticipate, it will be publicly announced. 

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

PUBLIC AFFAIRS CONTACTS 

Sarah Keegan/Barbara Selby 

Office of Space Flight 

NASA Headquarters, Washington, D.C. 

(Phone: 202/453-8536) 

Charles Redmond/Paula Cleggett-Haleim 

Office of Space Science and Applications 

NASA Headquarters, Washington, D.C. 

(Phone: 202/453-1548) 

Jim Ball 

Office of Commercial Programs 

NASA Headquarters, Washington, D.C. 

(Phone: 202/453-2927) 

Lisa Malone 

Kennedy Space Center, Fla. 

(Phone: 407/867-2468) 

Kyle Herring 

Johnson Space Center, Houston, Texas 

(Phone: 713/483-5111) 

Jerry Berg 

Marshall Space Flight Center, Huntsville, Ala. 

(Phone: 205/544-0034) 

Mack Herring 

Stennis Space Center, Bay St. Louis, Miss. 

(Phone: 601/688-3341) 

Nancy Lovato 

Ames-Dryden Flight Research Facility, Edwards, Calif. 

(Phone: 805/258-8381) 

Robert J. MacMillin 

Jet Propulsion Laboratory, Pasadena, Calif. 

(Phone: 818/354-5011) 

Jim Elliott 

Goddard Space Flight Center, Greenbelt, Md. 

(Phone: 301/286-6256) 

Peter W. Waller 

Ames Research Center, Mountain View, Calif. 

(Phone: 415/694-5091) 
Edited by Richard W. Orloff, 01/2001/Page 4 

CONTENTS 

GENERAL RELEASE 5 

GENERAL INFORMATION 7 

STS-34 QUICK LOOK 8 

LAUNCH PREPARATIONS, COUNTDOWN & LIFTOFF 9 

MAJOR COUNTDOWN MILESTONES 11 

TRAJECTORY SEQUENCE OF EVENTS 13 

SPACE SHUTTLE ABORT MODES 14 

SUMMARY OF MAJOR ACTIVITIES 15 

LANDING AND POST LANDING OPERATIONS 16 

GALILEO 18 

GALILEO MISSION EVENTS 18 

EARTH TO JUPITER 19 

VENUS 19 

FIRST EARTH PASS 19 

FIRST ASTEROID 19 

SECOND EARTH PASS 20 

SECOND ASTEROID 20 

APPROACHING JUPITER 20 

AT JUPITER 20 

 The probe at Jupiter 20 

 The orbiter at Jupiter 21 

SCIENTIFIC ACTIVITIES 22 

 Spacecraft scientific activities 22 

 Probe scientific activities 22 

 Orbiter scientific activities 23 

GROUND SYSTEMS 28 

SPACECRAFT CHARACTERISTICS 30 

JUPITER'S SYSTEM 31 

WHY JUPITER INVESTIGATIONS ARE IMPORTANT 31 

GALILEO MANAGEMENT 34 

GALILEO ORBITER AND PROBE SCIENTIFIC INVESTIGATIONS 34 

STS-34 INERTIAL UPPER STAGE (IUS-19) 36 

 Specifications 36 

 Airborne Support Equipment 36 

 IUS Structure 36 

 Equipment Support Section 36 

 IUS Avionics Subsystems 37 

 IUS Solid Rocket Motors 37 

 Reaction Control System 37 

 IUS to Spacecraft Interfaces 37 

 Flight Sequence 38 

SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT (SSBUV) 39 

GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS 41 

POLYMER MORPHOLOGY 42 

STUDENT EXPERIMENT 43 

MESOSCALE LIGHTNING EXPERIMENT 44 

IMAX 45 

AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST 46 

SENSOR TECHNOLOGY EXPERIMENT 47 

SPACEFLIGHT TRACKING AND DATA NETWORK 48 

PAYLOAD AND VEHICLE WEIGHTS 49 

STS-34 CARGO CONFIGURATION 50 

CREW BIOGRAPHIES 51 

NASA PROGRAM MANAGEMENT 54 
Edited by Richard W. Orloff, 01/2001/Page 5 

RELEASE: 89-151 October 1989 

SHUTTLE ATLANTIS TO DEPLOY GALILEO PROBE TOWARD JUPITER 

Space Shuttle mission STS-34 will deploy the Galileo planetary exploration spacecraft into low-Earth orbit 

starting Galileo on its journey to explore Jupiter. Galileo will be the second planetary probe deployed from 

the Shuttle this year following Atlantis' successful launch of Magellan toward Venus exploration in May. 

Following deployment about 6 hours after launch, Galileo will be propelled on a trajectory, known as 

Venus-Earth-Earth Gravity Assist (VEEGA) by an Air Force-developed, inertial upper stage (IUS). 

Galileo's trajectory will swing around Venus, the sun and Earth before Galileo makes it's way toward 

Jupiter. 

Flying the VEEGA track, Galileo will arrive at Venus in February 1990. During the flyby, Galileo will 

make measurements to determine the presence of lightning on Venus and take time-lapse photography of 

Venus' cloud circulation patterns. Accelerated by Venus' gravity, the spacecraft will head back to Earth. 

Enroute, Galileo will activate onboard remote-sensing equipment to gather near-infrared data on the 

composition and characteristics of the far side of Earth's moon. Galileo also will map the hydrogen 

distribution of the Earth's atmosphere. 

Acquiring additional energy from the Earth's gravitational forces, Galileo will travel on a 2-year journey 

around the sun spending 10 months inside an asteroid belt. On Oct. 29, 1991, Galileo will pass within 600 

miles of the asteroid Gaspra. 

On the second Earth flyby in December 1992, Galileo will photograph the north pole of the moon in an 

effort to determine if ice exists. Outbound, Galileo will activate the time-lapse photography system to 

produce a "movie" of the moon orbiting Earth. 

Racing toward Jupiter, Galileo will make a second trek through the asteroid belt passing within 600 miles 

of asteroid Ida on Aug. 29, 1993. Science data gathered from both asteroid encounters will focus on surface 

geology and composition. 

Five months prior to the Dec. 7, 1995, arrival at Jupiter, Galileo's atmospheric probe, encased in an oval 

heat shield, will spin away from the orbiter at a rate of 5 revolutions per minute (rpm) and follow a ballistic 

trajectory aimed at a spot 6 degrees north of Jupiter's equator. The probe will enter Jupiter's atmosphere at a 

shallow angle to avoid burning up like a meteor or ricocheting off the atmosphere back into space. 

At approximately Mach 1 speed, the probe's pilot parachute will deploy, removing the deceleration module 

aft cover. Deployment of the main parachute will follow, pulling the descent module out of the aeroshell to 

expose the instrument-sensing elements. During the 75-minute descent into the Jovian atmosphere, the 

probe will use the orbiter to transmit data back to Earth. After 75 minutes, the probe will be crushed under 

the heavy atmospheric pressure. 

The Galileo orbiter will continue its primary mission, orbiting around Jupiter and four of its satellites, 

returning science data for the next 22 months. 

Galileo's scientific goals include the study of the chemical composition, state and dynamics of the Jovian 

atmosphere and satellites, and the investigation of the structure and physical dynamics of the powerful 

Jovian magnetosphere. 

Overall responsibility for management of the project, including orbiter development, resides at NASA's Jet 

Propulsion Laboratory, Pasadena, Calif. The NASA Ames Research Center, Mountain View, Calif., 

manages the probe system. JPL built the 2,500-lb. spacecraft and Hughes Aircraft Co. built the 740-lb. 

probe. 
Edited by Richard W. Orloff, 01/2001/Page 6 

Modifications made to Galileo since flight postponement in 1986 include the addition of sunshields to the 

base and top of the antenna, new thermal control surfaces, blankets and heaters. Because of the extended 

length of the mission, the electrical circuitry of the thermoelectric generator has been revised to reduce 

power demand throughout the mission to assure adequate power supply for mission completion. 

Joining Galileo in the payload bay of Atlantis will be the Shuttle Solar Backscatter Ultraviolet (SSBUV) 

instrument. The SSBUV is designed to provide calibration of backscatter ultraviolet instruments currently 

being flown on free-flying satellites. SSBUV's primary objective is to check the calibration of the ozone 

sounders on satellites to verify the accuracy of the data set of atmospheric ozone and solar irradiance data. 

The SSBUV is contained in two Get Away Special canisters in the payload bay and weighs about 1219 lbs . 

One canister contains the SSBUV spectrometer and five supporting optical sensors. The second canister 

houses data, command and power systems. An interconnecting cable provides the communication link 

between the two canisters. 

Atlantis also will carry several secondary payloads involving radiation measurements, polymer 

morphology, lightning research, microgravity effects on plants and a student experiment on ice crystal 

growth in space. 

Commander of the 31st Shuttle mission is Donald E. Williams, Captain, USN. Michael J. McCulley, 

Commander, USN, is Pilot. Williams flew as Pilot of mission STS 51-D in April 1985. McCulley will be 

making his first Shuttle flight. 

Mission Specialists are Shannon W. Lucid, Ph.D.; Franklin R. Chang-Diaz, Ph.D.; and Ellen S. Baker, 

M.D. Lucid previously flew as a Mission Specialist on STS 51-G in June 1985. Chang-Diaz flew as a 

Mission Specialist on STS 61-C in January 1986. Baker is making her first Shuttle flight. 

Liftoff of the fifth flight of orbiter Atlantis is scheduled for 1:29 p.m. EDT on Oct. 12 from Kennedy Space 

Center, Fla., launch pad 39-B, into a 160-nautical-mile, 34.3-degree orbit. Nominal mission duration is 5 

days, 2 hours, 45 minutes. Deorbit is planned on orbit 81, with landing scheduled for 4:14 p.m. EDT on 

Oct. 17 at Edwards Air Force Base, Calif. 

Liftoff on Oct. 12 could occur during a 10-minute period. The launch window grows each day reaching a 

maximum of 47 minutes on Nov. 2. The window then decreases each day through the remainder of the 

launch opportunity which ends Nov. 21. The window is dictated by the need for a daylight landing 

opportunity at the trans-Atlantic landing abort sites and the performance constraint of Galileo's inertial 

upper stage. 

After landing at Edwards AFB, Atlantis will be towed to the NASA Ames-Dryden Flight Research Facility, 

hoisted atop the Shuttle Carrier Aircraft and ferried back to the Kennedy Space Center to begin processing 

for its next flight. 

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS.) 
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GENERAL INFORMATION 

NASA Select Television Transmission 

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

longitude, frequency 3960.0 MHz, vertical polarization, audio monaural 6.8 MHz. 

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

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

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

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

TV schedules also may be obtained by calling COMSTOR, 713/483-5817. COMSTOR is a computer data 

base service requiring the use of a telephone modem. Voice updates of the TV schedule may be obtained by 

dialing 202/755-1788. This service is updated daily at noon EDT. 

Special Note to Broadcasters 

In the 5 workdays before launch, short sound bites of astronaut interviews with the STS-34 crew will be 

available to broadcasters by calling 202/755-1788 between 8 a.m. and noon EDT. 

Status Reports 

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

produced by the appropriate NASA news center. 

Briefings 

An STS-34 mission press briefing schedule will be issued prior to launch. During the mission, flight control 

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

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

STS-34 QUICK LOOK 

Launch Date: Oct. 12, 1989 

Launch Site: Kennedy Space Center, FL, Pad 39B 

Launch Window: 1:29 p.m. - 1:39 p.m. EDT 

Orbiter: Atlantis (OV-104) 

Orbit: 160 nm 

Inclination: 34.30 degrees 

Duration: 5 flight days 

Landing Date: October 17, 1989 

Landing Time: 4:14 p.m. EDT 

 

Primary Landing Site: Edwards AFB, CA 

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

 Transoceanic Abort Landing - Ben Guerir, Morocco 

 Abort Once Around - Edwards AFB, CA 

 

Crew: Donald E. Williams, Commander 

 Michael J. McCulley, Pilot 

 Shannon W. Lucid, Mission Specialist 

 Ellen S. Baker, Mission Specialist 

 Franklin R. Chang-Diaz, Mission Specialist 

 

Cargo Bay Payloads: Galileo spacecraft to Jupiter 

 Shuttle Solar Backscatter Ultraviolet (SSBUV) 

 

Middeck Payloads: Growth Hormone Concentration & Distribution in Plants (GHCD) 

 Mesoscale Lightning Experiment (MLR) 

 Polymer Morphology (PM) 

 Sensor Technology Experiment (STEX) 
Edited by Richard W. Orloff, 01/2001/Page 9 

LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF 

Processing activities began on Atlantis for the STS-34 mission on May 16 when Atlantis was towed to 

Orbiter Processing Facility (OPF) bay 2 after arrival from NASA's Ames-Dryden Flight Research Facility 

in California. STS-30 post-flight deconfiguration and inspections were conducted in the processing hangar. 

As planned, the three main engines were removed the last week of May and taken to the main engine shop 

in the Vehicle Assembly Building (VAB) for the replacement of several components including the high 

pressure oxidizer turbopumps. The engines were reinstalled the first week of July, while the ship was in the 

OPF. Engine 2027 is installed in the number one position, engine 2030 is in the number two position and 

engine 2029 is in the number three position. 

The right hand Orbital Maneuvering System (OMS) pod was removed in mid-June for repairs. A propellant 

tank needed for Atlantis' pod was scheduled for delivery too late to support integrated testing. As a result, 

Discovery's right pod was installed on Atlantis about 2 weeks later. The left OMS pod was removed July 9 

and reinstalled 2 1/2 weeks later. Both pods had dynatubes and helium isolation valve repairs in the 

Hypergolic Maintenance Facility. 

About 34 modifications have been implemented since the STS-30 mission. One significant modification is 

a cooling system for the radioisotope thermoelectric generators (RTG). The RTG fuel is plutonium dioxide 

which generates heat as a result of its normal decay. The heat is converted to energy and used to provide 

electrical power for the Galileo spacecraft. A mixture of alcohol and water flows in the special cooling 

system to lower the RTG case temperature and maintain a desired temperature to the payload 

instrumentation in the vicinity of the RTGs. These cooling lines are mounted on the port side of the orbiter 

from the aft compartment to a control panel in bay 4. 

Another modification, called "flutter buffet," features special instrumentation on the vertical tail and right 

and left outboard elevons. Ten accelerometers were added to the vertical tail and one on each of the 

elevons. These instruments are designed to measure in-flight loads on the orbiter's structure. Atlantis is the 

only vehicle that will be equipped with this instrumentation. 

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

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

propulsion system and avionics system. 

Stacking of solid rocket motor (SRM) segments for flight began with the left aft booster on Mobile 

Launcher Platform 1 in the VAB on June 15. Booster stacking operations were completed by July 22 and 

the external tank was mated to the two boosters on July 30. 

Flight crew members performed the Crew Equipment Interface Test on July 29 to become familiar with 

Atlantis' crew compartment, vehicle configuration and equipment associated with the mission. 

The Galileo probe arrived at the Spacecraft Assembly and Encapsulation Facility (SAEF) 2 on April 17 and 

the spacecraft arrived on May 16. While at SAEF-2, the spacecraft and probe were joined and tested 

together to verify critical connections. Galileo was delivered to the Vertical Processing Facility (VPF) on 

Aug. 1. The Inertial Upper Stage (IUS) was delivered to the VPF on July 30. The Galileo/IUS were joined 

together on Aug. 3 and all integrated testing was performed during the second week of August. 

The Shuttle Solar Backscatter Ultraviolet (SSBUV) experiment, contained in two Get Away Special (GAS) 

canisters, was mounted on a special GAS beam in Atlantis' payload bay on July 24. Interface verification 

tests were performed the next day. 
Edited by Richard W. Orloff, 01/2001/Page 10 

Atlantis was transferred from the OPF to the VAB on Aug. 21, where it was mated to the external tank and 

SRBs. A Shuttle Interface Test was conducted in the VAB to check the mechanical and electrical 

connections between the various elements of the Shuttle vehicle and onboard flight systems. 

The assembled Space Shuttle vehicle was rolled out of the VAB aboard its mobile launcher platform for the 

4.2 mile trip to Launch Pad 39-B on Aug. 29. Galileo and its IUS upper stage were transferred from the 

VPF to Launch Pad 39-B on Aug. 25. The payload was installed in Atlantis' payload bay on Aug. 30. 

The payload interface verification test was planned for Sept. 7 to verify connections between the Shuttle 

and the payload. An end-to-end test was planned for Sept. 8 to verify communications between the 

spacecraft and ground controllers. Testing of the IUS was planned about 2 weeks prior to launch in parallel 

with Shuttle launch preparations. 

A Countdown Demonstration Test, a dress rehearsal for the STS-34 flight crew and KSC launch team, is 

designed as a practice countdown for the launch. At press time, it was planned for Sept. 14 and 15. 

One of the unique STS-34 processing milestones planned was a simulation exercise for the installation of 

the RTGs. Simulated RTGs were to be used in the 2-day event scheduled within the first week after 

Atlantis arrives at the launch pad. The test is designed to give workers experience for the installation of the 

RTGs, a first in the Shuttle program. In addition, access requirements will be identified and procedures will 

be verified. 

Another test scheduled at the pad is installation of the flight RTGs and an associated test and checkout of 

the RTG cooling system planned for the third week of September. This test will verify the total RTG 

cooling system and connections. The RTGs will be removed at the completion of the 3-day cooling system 

test and returned to the RTG facility. The two flight RTGs will be reinstalled on the spacecraft 6 days 

before launch. The flight RTGs were not required for the RTG cooling system test. 

Launch preparations scheduled the last 2 weeks prior to launch countdown include final vehicle ordnance 

activities, such as power-on stray-voltage checks and resistance checks of firing circuits; loading the fuel 

cell storage tanks; pressurizing the hypergolic propellant tanks aboard the vehicle; final payload closeouts; 

and a final functional check of the range safety and SRB ignition, safe and arm devices. 

The launch countdown is scheduled to pick up at the T-minus 43-hour mark, leading up to the STS-34 

launch. Atlantis' fifth launch will be conducted by a joint NASA/industry team from Firing Room 1 in the 

Launch Control Center. 
Edited by Richard W. Orloff, 01/2001/Page 11 

MAJOR COUNTDOWN MILESTONES 

T-43 Hours Power up Space Shuttle vehicle. 

T-34 Hours Begin orbiter and ground support equipment closeouts for launch. 

T-30 Hours Activate orbiter's navigation aids. 

T-27 Hours (holding) Enter first built-in hold for 8 hours. 

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

and liquid hydrogen reactants. 

T-25 Hours Load orbiter's fuel cell tanks with liquid oxygen. 

T-22 Hours, 30 minutes Load orbiter's fuel cell tanks with liquid hydrogen. 

T-22 Hours Perform interface check between Houston Mission Control and Merritt 

Island 

Launch Area (MILA) tracking station. 

T-20 Hours Activate and warm up inertial measurement units (IMU). 

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

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

closeouts and preparations to move the Rotating Service Structure (RSS). 

T-11 Hours (holding) Start 14-hour, 40 minute built-in hold orbiter flight and middecks. 

T-11 Hours (counting) Retract RSS from vehicle to launch position. 

T-9 Hours Activate orbiter's fuel cells. 

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

danger area. 

T-6 Hours, 30 minutes Perform Eastern Test Range open loop command test. 

T-6 Hours (holding) Enter 1-hour built-in hold. Receive management "go" for tanking. 

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

T-5 Hours Start IMU pre-flight calibration. 

T-4 Hours Perform MILA antenna alignment. 

T-3 Hours (holding) 2-hour built-in hold begins. Loading of external tank is complete and in a 

stable replenish mode. Ice team goes to pad for inspections. Closeout crew 

goes to white room to begin preparing oriter’s cabin for f light crew’s entry. 

Wake flight crew (launch minus 4 hours 55 minutes). 
Edited by Richard W. Orloff, 01/2001/Page 12 

MAJOR COUNTDOWN MILESTONES 

T-3 Hours (counting) Resume countdown. 

T-2 Hours, 55 minutes Flight crew departs O&C Building for Launch Pad 39-B (Launch minus 3 

hours,15 minutes). 

T-2 Hours, 30 minutes Crew enters orbiter vehicle (Launch minus 2 Hours, 50 minutes). 

T-60 minutes Start pre-flight alignment of IMUs. 

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

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

T-10 minutes White room closeout crew cleared through launch danger are a roadblocks. 

T-9 minutes (holding) 40-minute built-in hold begins. Perform status check and receive Launch 

Director and Mission Management Team “go.” 

T-9 minutes (counting) Start ground launch sequencer. 

T-7 minutes, 30 seconds Retract orbiter access arm. 

T-5 minutes Pilot starts auxiliary power units. Arm range safety, solid rocket booster 

(SRB) 

ignition systems. 

T-3 minutes, 30 seconds Orbiter goes on internal power. 

T-2 minutes, 55 seconds Pressurize liquid oxygen tank for flight and retract gaseous oxygen vent 

hood. 

T-1 minute, 57 seconds Pressurize liquid hydrogen tank. 

T-31 seconds "Go" from ground computer for orbiter computers to start the automatic 

launch sequence. 

T-28 seconds Start SRB hydraulic power units. 

T-21 seconds Start SRB gimbal profile test. 

T-6.6 seconds Main engine start. 

T-3 seconds Main engines at 90 percent thrust. 

T-0 SRB ignition, holddown post release and liftoff. 

T+7 seconds Shuttle clears launch tower and control switches to JSC. 

Note: This countdown timeline may be adjusted in real time as necessary. 
Edited by Richard W. Orloff, 01/2001/Page 13 

TRAJECTORY SEQUENCE OF EVENTS 

Event 

MET 

(d/h:m:s) 

Relative 

Velocity 

(fps) Mach 

Altitude 

(ft) 

 

Launch 00/00:00:00 

Begin Roll Maneuver 00/00:00:09 165 0.15 627 

End Roll Maneuver 00/00:00:17 374 0.33 2,898 

SSME Throttle Down to 65% 00/00:00:34 833 0.75 11,854 

Max. Dyn. Pressure (Max Q) 00/00:00:52 1,260 1.2 28,037 

SSME Throttle Up to 104% 00/00:01:01 1,499 1.49 38,681 

SRB Staging 00/00:02:04 4,316 3.91 153,873 

Negative Return 00/00:03:54 6,975 7.48 317,096 

Main Engine Cutoff (MECO) 00/00:08:27 24,580 22.41 366,474 

Zero Thrust 00/00:08:33 24,596 22.17 368,460 

ET Separation 00/00:08:45 

OMS 2 Burn 00/00:39:48 

Galileo/IUS Deploy (orbit 5) 00/06:21:36 

Deorbit Burn (orbit 81) 05/01:45:00 

Landing (orbit 82) 05/02:45:00 

Apogee, Perigee at MECO: 157 x 39 nm 

Apogee, Perigee post-OMS 2: 161 x 161 nm 

Apogee, Perigee post deploy: 177 x 161 nm 
Edited by Richard W. Orloff, 01/2001/Page 14 

SPACE SHUTTLE ABORT MODES 

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

its payload. Abort modes include: 

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

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

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

around before landing at Edwards Air Force Base, Calif.; White Sands Space Harbor (Northrup 

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

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

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

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

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

within gliding distance of the SLF. 

STS-34 contingency landing sites are Edwards AFB, White Sands, KSC, Ben Guerir, Moron and Banjul. 
Edited by Richard W. Orloff, 01/2001/Page 15 

SUMMARY OF MAJOR ACTIVITIES 

Flight Day 1 

Ascent 

Post-insertion checkout 

Pre-deploy checkout 

Galileo/Inertial Upper Stage (IUS) deploy 

Detailed Secondary Objective (DSO) 

Polymer Morphology (PM) 

Sensor Technology Experiment (STEX) activation 

Flight Day 2 

Galileo/IUS backup deploy opportunity 

DSO 

IMAX 

PM 

Shuttle Solar Backscatter Ultraviolet (SSBUV) activation 

Shuttle Student Involvement Program (SSIP) 

Landing preparations 

Flight Day 3 

DSO 

IMAX 

Mesoscale Lightning Experiment (MLE) 

PM 

Flight Day 4 

DSO 

IMAX 

MLE 

PM 

SSBUV deactivation 

Flight Day 5 

DTO/DSO 

GHCD operations 

PM 

STEX deactivation 

FCS checkout 

Cabin stow 

Flight Day 6 

PM stow 

Deorbit preparation 

Deorbit burn 

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

LANDING AND POST LANDING OPERATIONS 

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

on the runway at Edwards Air Force Base, Calif. Those operations include preparing the Shuttle for the 

return trip to Kennedy. 

After landing, the flight crew aboard Atlantis begins "safing" vehicle systems. Immediately after wheel 

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

significant levels for other safing operations to proceed. 

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

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

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

the vehicle safing activity. 

Once the initial aft safety assessment is made, access vehicles are positioned around the rear of the orbiter 

so that lines from the ground purge and cooling vehicles can be connected to the umbilical panels on the aft 

end of Atlantis. 

Freon line connections are completed and coolant begins circulating through the umbilicals to aid in heat 

rejection and protect the orbiter's electronic equipment. Other lines provide cooled, humidified air to the 

payload bay and other cavities to remove any residual fumes and provide a safe environment inside 

Atlantis. 

A tow tractor will be connected to Atlantis and the vehicle will be pulled off the runway at Edwards and 

positioned inside the Mate/Demate Device (MDD) at nearby Ames-Dryden Flight Research Facility. After 

the Shuttle has been jacked and leveled, residual fuel cell cryogenics are drained and unused pyrotechnic 

devices are disconnected prior to returning the orbiter to Kennedy. 

The aerodynamic tail cone is installed over the three main engines, and the orbiter is bolted on top of the 

747 Shuttle Carrier Aircraft for the ferry flight back to Florida. Pending completion of planned work and 

favorable weather conditions, the 747 would depart California about 6 days after landing for the crosscountry ferry flight back to Florida. A refueling stop is necessary to complete the journey. 

Once back at Kennedy, Atlantis will be pulled inside the hangar-like facility for post-flight inspections and 

in-flight anomaly troubleshooting. These operations are conducted in parallel with the start of routine 

systems reverification to prepare Atlantis for its next mission. 
Edited by Richard W. Orloff, 01/2001/Page 17 
Edited by Richard W. Orloff, 01/2001/Page 18 

GALILEO 

Galileo is a NASA spacecraft mission to Jupiter to study the planet's atmosphere, satellites and surrounding 

magnetosphere. It was named for the Italian renaissance scientist who discovered Jupiter's major moons by 

using the first astronomical telescope. 

This mission will be the first to make direct measurements from an instrumented probe within Jupiter's 

atmosphere and the first to conduct long-term observations of the planet and its magnetosphere and 

satellites from orbit around Jupiter. It will be the first orbiter and atmospheric probe for any of the outer 

planets. On the way to Jupiter, Galileo also will observe Venus, the Earth-moon system, one or two 

asteroids and various phenomena in interplanetary space. 

Galileo will be boosted into low-Earth orbit by the Shuttle Atlantis and then boosted out of Earth orbit by a 

solid rocket Inertial Upper Stage. The spacecraft will fly past Venus and twice by the Earth, using gravity 

assists from the planets to pick up enough speed to reach Jupiter. Travel time from launch to Jupiter is a 

little more than 6 years. 

In December 1995, the Galileo atmospheric probe will conduct a brief, direct examination of Jupiter's 

atmosphere, while the larger part of the craft, the orbiter, begins a 22-month, 10-orbit tour of major 

satellites and the magnetosphere, including long-term observations of Jupiter throughout this phase. 

The 2-ton Galileo orbiter spacecraft carries 9 scientific instruments. There are another six experiments on 

the 750-pound probe. The spacecraft radio link to Earth serves as an additional instrument for scientific 

measurements. The probe's scientific data will be relayed to Earth by the orbiter during the 75-minute 

period while the probe is descending into Jupiter's atmosphere. Galileo will communicate with its 

controllers and scientists through NASA's Deep Space Network, using tracking stations in California, Spain 

and Australia. 

GALILEO MISSION EVENTS 

(Note: for both asteroids, closes in mid-October) Oct. 12 to Nov. 21, 1989 

Venus flyby ( 9,300 mi) Feb. 9, 1990* 

Venus data playback Oct. 1990 

Earth 1 flyby ( about 600 mi) Dec. 8, 1990* 

Asteroid Gaspra flyby (600 mi) Oct. 29, 1991* 

Earth 2 flyby (200 mi) Dec. 8, 1992* 

Asteroid Ida flyby (600 mi) Aug. 28, 1993* 

Probe release July 1995 

(includes Io flyby, probe entry and relay, Jupiter 

orbit insertion) 

Dec. 7, 1995 

Orbital tour of Galilean satellites Dec '95-Oct '97 

*Exact dates may vary according to actual launch date 
Edited by Richard W. Orloff, 01/2001/Page 19 

EARTH TO JUPITER 

Galileo will make three planetary encounters in the course of its gravity-assisted flight to Jupiter. These 

provide opportunities for scientific observation and measurement of Venus and the Earth-moon system. 

The mission also has a chance to fly close to one or two asteroids, bodies which have never been observed 

close up, and obtain data on other phenomena of interplanetary space. 

Scientists are currently studying how to use the Galileo scientific instruments and the limited ability to 

collect, store and transmit data during the early phase of flight to make the best use of these opportunities. 

Instruments designed to observe Jupiter's atmosphere from afar can improve our knowledge of the 

atmosphere of Venus and sensors designed for the study of Jupiter's moons can add to our information 

about our own moon. 

VENUS 

The Galileo spacecraft will approach Venus early in 1990 from the night side and pass across the sunlit 

hemisphere, allowing observation of the clouds and atmosphere. Both infrared and ultraviolet spectral 

observations are planned, as well as several camera images and other remote measurements. The search for 

deep cloud patterns and for lightning storms will be limited by the fact that all the Venus data must be taperecorded on the spacecraft for playback 8 months later. 

The spacecraft was originally designed to operate between Earth and Jupiter, where sunlight is 25 times 

weaker than at Earth and temperatures are much lower. The VEEGA mission will expose the spacecraft to 

a hotter environment from Earth to Venus and back. Spacecraft engineers devised a set of sunshades to 

protect the craft. For this system to work, the front end of the spacecraft must be aimed precisely at the Sun, 

with the main antenna furled for protection from the Sun's rays until after the first Earth flyby in December 

1990. This precludes the use of the Galileo high-gain antenna and therefore, scientists must wait until the 

spacecraft is close to Earth to receive the recorded Venus data, transmitted through a low-gain antenna. 

FIRST EARTH PASS 

Approaching Earth for the first time about 14 months after launch, the Galileo spacecraft will observe, from 

a distance, the nightside of Earth and parts of both the sunlit and unlit sides of the moon. After passing 

Earth, Galileo will observe Earth's sunlit side. At this short range, scientific data are transmitted at the high 

rate using only the spacecraft's low-gain antennas. The high-gain antenna is to be unfurled like an umbrella, 

and its high-power transmitter turned on and checked out, about 5 months after the first Earth encounter. 

FIRST ASTEROID 

Nine months after the Earth passage and still in an elliptical solar orbit, Galileo will enter the asteroid belt, 

and two months later, will have its first asteroid encounter. Gaspra is believed to be a fairly representative 

main-belt asteroid, about 10 miles across and probably similar in composition to stony meteorites. 

The spacecraft will pass within about 600 miles at a relative speed of about 18,000 miles per hour. It will 

collect several pictures of Gaspra and make spectral measurements to indicate its composition and physical 

properties. 

SECOND EARTH PASS 

Thirteen months after the Gaspra encounter, the spacecraft will have completed its 2-year elliptical orbit 

around the Sun and will arrive back at Earth. It will need a much larger ellipse (with a 6-year period) to 

reach as far as Jupiter. The second flyby of Earth will pump the orbit up to that size, acting as a natural 

apogee kick motor for the Galileo spacecraft. 
Edited by Richard W. Orloff, 01/2001/Page 20 

Passing about 185 miles above the surface, near the altitude at which it had been deployed from the Space 

Shuttle almost three years earlier, Galileo will use Earth's gravitation to change the spacecraft's flight 

direction and pick up about 8,000 miles per hour in speed. 

Each gravity-assist flyby requires about three rocket-thrusting sessions, using Galileo's onboard 

retropropulsion module, to fine-tune the flight path. The asteroid encounters require similar maneuvers to 

obtain the best observing conditions. 

Passing the Earth for the last time, the spacecraft's scientific equipment will make thorough observations of 

the planet, both for comparison with Venus and Jupiter and to aid in Earth studies. If all goes well, there is 

a good chance that Galileo will enable scientists to record the motion of the moon about the Earth while the 

Earth itself rotates. 

SECOND ASTEROID 

Nine months after the final Earth flyby, Galileo may have a second asteroid-observing opportunity. Ida is 

about 20 miles across. Like Gaspra, Ida is believed to represent the majority of main-belt asteroids in 

composition, though there are believed to be differences between the two. Relative velocity for this flyby 

will be nearly 28,000 miles per hour, with a planned closest approach of about 600 miles. 

APPROACHING JUPITER 

Some 2 years after leaving Earth for the third time and 5 months before reaching Jupiter, Galileo's probe 

must separate from the orbiter. The spacecraft turns to aim the probe precisely for its entry point in the 

Jupiter atmosphere, spins up to 10 revolutions per minute and releases the spin-stabilized probe. Then the 

Galileo orbiter maneuvers again to aim for its own Jupiter encounter and resumes its scientific 

measurements of the interplanetary environment underway since the launch more than 5 years before. 

While the probe is still approaching Jupiter, the orbiter will have its first two satellite encounters. After 

passing within 20,000 miles of Europa, it will fly about 600 miles above Io's volcano-torn surface, twenty 

times closer than the closest flyby altitude of Voyager in 1979. 

AT JUPITER 

The Probe at Jupiter 

The probe mission has four phases: launch, cruise, coast and entry-descent. During launch and cruise, the 

probe will be carried by the orbiter and serviced by a common umbilical. The probe will be dormant during 

cruise except for annual checkouts of spacecraft systems and instruments. During this period, the orbiter 

will provide the probe with electric power, commands, data transmission and some thermal control. 

Six hours before entering the atmosphere, the probe will be shooting through space at about 40,000 mph. 

At this time, its command unit signals "wake up" and instruments begin collecting data on lightning, radio 

emissions and energetic particles. 

A few hours later, the probe will slam into Jupiter's atmosphere at 115,000 mph, fast enough to jet from 

Los Angeles to New York in 90 seconds. Deceleration to about Mach 1 -- the speed of sound -- should take 

just a few minutes. At maximum deceleration as the craft slows from 115,000 mph to 100 mph, it will be 

hurtling against a force 350 times Earth's gravity. The incandescent shock wave ahead of the probe will be 

as bright as the sun and reach searing temperatures of up to 28,000 degrees Fahrenheit. After the 

aerodynamic braking has slowed the probe, it will drop its heat shields and deploy its parachute. This will 

allow the probe to float down about 125 miles through the clouds, passing from a pressure of 1/10th that on 

Earth's surface to about 25 Earth atmospheres. 
Edited by Richard W. Orloff, 01/2001/Page 21 

About 4 minutes after probe entry into Jupiter's atmosphere, a pilot chute deploys and explosive nuts shoot 

off the top section of the probe's protective shell. As the cover whips away, it pulls out and opens the main 

parachute attached to the inner capsule. What remains of the probe's outer shell, with its massive heat 

shield, falls away as the parachute slows the instrument module. 

From there on, suspended from the main parachute, the probe's capsule with its activated instruments floats 

downward toward the bright clouds below. 

The probe will pass through the white cirrus clouds of ammonia crystals - the highest cloud deck. Beneath 

this ammonia layer probably lie reddish-brown clouds of ammonium hydrosulfides. Once past this layer, 

the probe is expected to reach thick water clouds. This lowest cloud layer may act as a buffer between the 

uniformly mixed regions below and the turbulent swirl of gases above. 

Jupiter's atmosphere is primarily hydrogen and helium. For most of its descent through Jupiter's three main 

cloud layers, the probe will be immersed in gases at or below room temperature. However, it may 

encounter hurricane winds up to 200 mph and lightning and heavy rain at the base of the water clouds 

believed to exist on the planet. Eventually, the probe will sink below these clouds, where rising pressure 

and temperature will destroy it. The probe's active life in Jupiter's atmosphere is expected to be about 75 

minutes in length. The probe batteries are not expected to last beyond this point, and the relaying orbiter 

will move out of reach. 

To understand this huge gas planet, scientists must find out about its chemical components and the 

dynamics of its atmosphere. So far, scientific data are limited to a two-dimensional view (pictures of the 

planet's cloud tops) of a three-dimensional process (Jupiter's weather). But to explore such phenomena as 

the planet's incredible coloring, the Great Red Spot and the swirling shapes and high-speed motion of its 

topmost clouds, scientists must penetrate Jupiter's visible surface and investigate the atmosphere concealed 

in the deep-lying layers below. 

A set of six scientific instruments on the probe will measure, among other things, the radiation field near 

Jupiter, the temperature, pressure, density and composition of the planet's atmosphere from its first faint 

outer traces to the hot, murky hydrogen atmosphere 100 miles below the cloud tops. All of the information 

will be gathered during the probe's descent on an 8-foot parachute. Probe data will be sent to the Galileo 

Orbiter 133,000 miles overhead then relayed across the half billion miles to Deep Space Network stations 

on Earth. 

To return its science, the probe relay radio aboard the orbiter must automatically acquire the probe signal 

below within 50 seconds, with a success probability of 99.5 percent. It must reacquire the signal 

immediately should it become lost. 

To survive the heat and pressure of entry, the probe spacecraft is composed of two separate units: an inner 

capsule containing the scientific instruments, encased in a virtually impenetrable outer shell. The probe 

weighs 750 pounds. The outer shell is almost all heat shield material. 

The Orbiter at Jupiter 

After releasing the probe, the orbiter will use its main engine to go into orbit around Jupiter. This orbit, the 

first of 10 planned, will have a period of about 8 months. A close flyby of Ganymede in July 1996 will 

shorten the orbit, and each time the Galileo orbiter returns to the inner zone of satellites, it will make a 

gravity-assist close pass over one or another of the satellites, changing Galileo's orbit while making close 

observations. These satellite encounters will be at altitudes as close as 125 miles above their surfaces. 

Throughout the 22-month orbital phase, Galileo will continue observing the planet and the satellites and 

continue gathering data on the magnetospheric environment. 
Edited by Richard W. Orloff, 01/2001/Page 22 

SPACECRAFT SCIENTIFIC ACTIVITIES 

Galileo's scientific experiments will be carried out by more than 100 scientists from six nations. Except for 

the radio science investigation, these are supported by dedicated instruments on the Galileo orbiter and 

probe. NASA has appointed 15 interdisciplinary scientists whose studies include data from more than one 

Galileo instrument. 

The instruments aboard the probe will measure the temperatures and pressure of Jupiter's atmosphere at 

varying altitudes and determine its chemical composition including major and minor constituents (such as 

hydrogen, helium, ammonia, methane, and water) and the ratio of hydrogen to helium. Jupiter is thought to 

have a bulk composition similar to that of the primitive solar nebula from which it was formed. Precise 

determination of the ratio of hydrogen to helium would provide an important factual check of the Big Bang 

theory of the genesis of the universe. 

Other probe experiments will determine the location and structure of Jupiter's clouds, the existence and 

nature of its lightning, and the amount of heat radiating from the planet compared to the heat absorbed from 

sunlight. 

In addition, measurements will be made of Jupiter's numerous radio emissions and of the high-energy 

particles trapped in the planet's innermost magnetic field. These measurements for Galileo will be made 

within a distance of 26,000 miles from Jupiter's cloud tops, far closer than the previous closest approach to 

Jupiter by Pioneer 11. The probe also will determine vertical wind shears using Doppler radio 

measurements made of probe motions from the radio receiver aboard the orbiter. 

Jupiter appears to radiate about twice as much energy as it receives from the sun and the resulting 

convection currents from Jupiter's internal heat source towards its cooler polar regions could explain some 

of the planet's unusual weather patterns. 

Jupiter is over 11 times the diameter of Earth and spins about two and one-half times faster -- a Jovian day 

is only 10 hours long. A point on the equator of Jupiter's visible surface races along at 28,000 mph. This 

rapid spin may account for many of the bizarre circulation patterns observed on the planet. 

Spacecraft Scientific Activities 

The Galileo mission and systems were designed to investigate three broad aspects of the Jupiter system: the 

planet's atmosphere, the satellites and the magnetosphere. The spacecraft is in three segments to focus on 

these areas: the atmospheric probe; a non-spinning section of the orbiter carrying cameras and other remote 

sensors; and the spinning main section of the orbiter spacecraft which includes the propulsion module, the 

communications antennas, main computers and most support systems as well as the fields and particles 

instruments, which sense and measure the environment directly as the spacecraft flies through it. 

Probe Scientific Activities 

The probe will enter the atmosphere about 6 degrees north of the equator. The probe weighs just under 750 

pounds and includes a deceleration module to slow and protect the descent module, which carries out the 

scientific mission. 

The deceleration module consists of an aeroshell and an aft cover designed to block the heat generated by 

slowing from the probe's arrival speed of about 115,000 miles per hour to subsonic speed in less than 2 

minutes. After the covers are released, the descent module deploys its 8-foot parachute and its instruments, 

the control and data system, and the radio-relay transmitter go to work. 
Edited by Richard W. Orloff, 01/2001/Page 23 

Operating at 128 bits per second, the dual L-band transmitters send nearly identical streams of scientific 

data to the orbiter. The probe's relay radio aboard the orbiter will have two redundant receivers that process 

probe science data, plus radio science and engineering data for transmission to the orbiter communications 

system. Minimum received signal strength is 31 dbm. The receivers also measure signal strength and 

Doppler shift as part of the experiments for measuring wind speeds and atmospheric absorption of radio 

signals. 

Probe electronics are powered by long-life, high-discharge-rate 34-volt lithium batteries, which remain 

dormant for more than 5 years during the journey to Jupiter. The batteries have an estimated capacity of 

about 18 amp-hours on arrival at Jupiter. 

Orbiter Scientific Activities 

The orbiter, in addition to delivering the probe to Jupiter and relaying probe data to Earth, will support all 

the scientific investigations of Venus, the Earth and moon, asteroids and the interplanetary medium, 

Jupiter's satellites and magnetosphere, and observation of the giant planet itself. 

The orbiter weighs about 5,200 pounds including about 2,400 pounds of rocket propellant to be expended 

in some 30 relatively small maneuvers during the long gravity-assisted flight to Jupiter, the large thrust 

maneuver which puts the craft into its Jupiter orbit, and the 30 or so trim maneuvers planned for the 

satellite tour phase. 

The retropropulsion module consists of 12 10-newton thrusters, a single 400-newton engine, and the fuel, 

oxidizer, and pressurizing-gas tanks, tubing, valves and control equipment. (A thrust of 10 newtons would 

support a weight of about 2.2 pounds at Earth's surface). The propulsion system was developed and built by 

Messerschmitt-Bolkow-Blohm and provided by the Federal Republic of Germany. 

The orbiter's maximum communications rate is 134 kilobits per second (the equivalent of about one blackand-white image per minute); there are other data rates, down to 10 bits per second, for transmitting 

engineering data under poor conditions. The spacecraft transmitters operate at S-band and X-band (2295 

and 8415 megahertz) frequencies between Earth and on L-band between the probe. 

The high-gain antenna is a 16-foot umbrella-like reflector unfurled after the first Earth flyby. Two low-gain 

antennas (one pointed forward and one aft, both mounted on the spinning section) are provided to support 

communications during the Earth-Venus-Earth leg of the flight and whenever the main antenna is not 

deployed and pointed at Earth. The despun section of the orbiter carries a radio relay antenna for receiving 

the probe's data transmissions. 

Electrical power is provided to Galileo's equipment by two radioisotope thermoelectric generators. Heat 

produced by natural radioactive decay of plutonium 238 dioxide is converted to approximately 500 watts of 

electricity (570 watts at launch, 480 at the end of the mission) to operate the orbiter equipment for its 8-

year active period. This is the same type of power source used by the Voyager and Pioneer Jupiter 

spacecraft in their long outer-planet missions, by the Viking lander spacecraft on Mars and the lunar 

scientific packages left on the Moon. 

Most spacecraft are stabilized in flight either by spinning around a major axis or by maintaining a fixed 

orientation in space, referenced to the sun and another star. Galileo represents a hybrid of these techniques, 

with a spinning section rotating ordinarily at 3 rpm and a "despun" section which is counter-rotated to 

provide a fixed orientation for cameras and other remote sensors. 

Instruments that measure fields and particles, together with the main antenna, the power supply, the 

propulsion module, most of the computers and control electronics, are mounted on the spinning section. 

The instruments include magnetometer sensors mounted on a 36-foot boom to escape interference from the 

spacecraft; a plasma instrument detecting low-energy charged particles and a plasma-wave detector to 
Edited by Richard W. Orloff, 01/2001/Page 24 

study waves generated in planetary magnetospheres and by lightning discharges; a high-energy particle 

detector; and a detector of cosmic and Jovian dust. 

The despun section carries instruments and other equipment whose operation depends on a fixed 

orientation in space. The instruments include the camera system; the near-infrared mapping spectrometer to 

make multispectral images for atmosphere and surface chemical analysis; the ultraviolet spectrometer to 

study gases and ionized gases; and the photopolarimeter radiometer to measure radiant and reflected 

energy. The camera system is expected to obtain images of Jupiter's satellites at resolutions from 20 to 

1,000 times better than Voyager's best. 

This section also carries a dish antenna to track the probe in Jupiter's atmosphere and pick up its signals for 

relay to Earth. The probe is carried on the despun section, and before it is released, the whole spacecraft is 

spun up briefly to 10 rpm in order to spin-stabilize the probe. 

The Galileo spacecraft will carry out its complex operations, including maneuvers, scientific observations 

and communications, in response to stored sequences which are interpreted and executed by various onboard computers. These sequences are sent up to the orbiter periodically through the Deep Space Network 

in the form of command loads. 
Edited by Richard W. Orloff, 01/2001/Page 25 
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Edited by Richard W. Orloff, 01/2001/Page 28 

GROUND SYSTEMS 

Galileo communicates with Earth via NASA's Deep Space Network (DSN), which has a complex of large 

antennas with receivers and transmitters located in the California desert, another in Australia and a third in 

Spain, linked to a network control center at NASA's Jet Propulsion Laboratory in Pasadena, Calif. The 

spacecraft receives commands, sends science and engineering data, and is tracked by Doppler and ranging 

measurements through this network. 

At JPL, about 275 scientists, engineers and technicians, will be supporting the mission at launch, increasing 

to nearly 400 for Jupiter operations including support from the German retropropulsion team at their 

control center in the FGR. Their responsibilities include spacecraft command, interpreting engineering and 

scientific data from Galileo to understand its performance, and analyzing navigation data from the DSN. 

The controllers use a set of complex computer programs to help them control the spacecraft and interpret 

the data. 

Because the time delay in radio signals from Earth to Jupiter and back is more than an hour, the Galileo 

spacecraft was designed to operate from programs sent to it in advance and stored in spacecraft memory. A 

single master sequence program can cover 4 weeks of quiet operations between planetary and satellite 

encounters. During busy Jupiter operations, one program covers only a few days. Actual spacecraft tasks 

are carried out by several subsystems and scientific instruments, many of which work from their own 

computers controlled by the main sequence. 

Designing these sequences is a complex process balancing the desire to make certain scientific observations 

with the need to safeguard the spacecraft and mission. The sequence design process itself is supported by 

software programs, for example, which display to the scientist maps of the instrument coverage on the 

surface of an approaching satellite for a given spacecraft orientation and trajectory. Notwithstanding these 

aids, a typical 3-day satellite encounter may take efforts spread over many months to design, check and 

recheck. The controllers also use software designed to check the command sequence further against flight 

rules and constraints. 

The spacecraft regularly reports its status and health through an extensive set of engineering measurements. 

Interpreting these data into trends and averting or working around equipment failures is a major task for the 

mission operations team. Conclusions from this activity become an important input, along with scientific 

plans, to the sequence design process. This too is supported by computer programs written and used in the 

mission support area. 

Navigation is the process of estimating, from radio range and Doppler measurements, the position and 

velocity of the spacecraft to predict its flight path and design course-correcting maneuvers. These 

calculations must be done with computer support. The Galileo mission, with its complex gravity-assist 

flight to Jupiter and 10 gravity-assist satellite encounters in the Jovian system, is extremely dependent on 

consistently accurate navigation. 

In addition to the programs that directly operate the spacecraft and are periodically transmitted to it, the 

mission operations team uses software amounting to 650,000 lines of programming code in the sequence 

design process; 1,615,000 lines in the telemetry interpretation; and 550,000 lines of code in navigation. 

These must all be written, checked, tested, used in mission simulations and, in many cases, revised before 

the mission can begin. 

Science investigators are located at JPL or other university laboratories and linked by computers. From any 

of these locations, the scientists can be involved in developing the sequences affecting their experiments 

and, in some cases, in helping to change preplanned sequences to follow up on unexpected discoveries with 

second looks and confirming observations. 
Edited by Richard W. Orloff, 01/2001/Page 29 
Edited by Richard W. Orloff, 01/2001/Page 30 

SPACECRAFT CHARACTERISTICS 

 Orbiter Probe 

 

Mass, lbs. 5,242 744 

Propellant, lbs 2,400 none 

Height (in-flight) 15 feet 34 inches 

Inflight span (w/o boom) 30 feet 

Instrument payload 10 instruments 6 instruments 

Payload mass, lbs 260 66 

Electric power, watts 570-480 (RTGs) 730 (Lithium-sulfur battery) 
Edited by Richard W. Orloff, 01/2001/Page 31 

JUPITER'S SYSTEM 

Jupiter is the largest and fastest-spinning planet in the solar system. Its radius is more than 11 times Earth's, 

and its mass is 318 times that of our planet. Named for the chief of the Roman gods, Jupiter contains more 

mass than all the other planets combined. It is made mostly of light elements, principally hydrogen and 

helium. Its atmosphere and clouds are deep and dense, and a significant amount of energy is emitted from 

its interior. 

The earliest Earth-based telescopic observations showed bands and spots in Jupiter's atmosphere. One 

storm system, the Red Spot, has been seen to persist over three centuries. 

Atmospheric forms and dynamics were observed in increasing detail with the Pioneer and Voyager flyby 

spacecraft, and Earth-based infrared astronomers have recently studied the nature and vertical dynamics of 

deeper clouds. 

Sixteen satellites are known. The four largest, discovered by the Italian scientist Galileo Galilei in 1610, are 

the size of small planets. The innermost of these, Io, has active sulfurous volcanoes, discovered by Voyager 

1 and further observed by Voyager 2 and Earth-based infrared astronomy. Io and Europa are about the size 

and density of Earth's moon (3 to 4 times the density of water) and probably rocky inside. Ganymede and 

Callisto, further out from Jupiter, are the size of Mercury but less than twice as dense as water. Their 

cratered surfaces look icy in Voyager images, and they may be composed partly of ice or water. 

Of the other satellites, eight (probably captured asteroids) orbit irregularly far from the planet, and four 

(three discovered by the Voyager mission in 1979) are close to the planet. Voyager also discovered a thin 

ring system at Jupiter in 1979. 

Jupiter has the strongest planetary magnetic field known. The resulting magnetosphere is a huge teardropshaped, plasma-filled cavity in the solar wind pointing away from the sun. Jupiter's magnetosphere is the 

largest single entity in our solar system, measuring more than 14 times the diameter of the sun. The inner 

part of the magnetic field is doughnut- shaped, but farther out it flattens into a disk. The magnetic poles are 

offset and tilted relative to Jupiter's axis of rotation, so the field appears to wobble with Jupiter's rotation 

(just under 10 hours), sweeping up and down across the inner satellites and making waves throughout the 

magnetosphere. 

WHY JUPITER INVESTIGATIONS ARE IMPORTANT 

With a thin skin of turbulent winds and brilliant, swift-moving clouds, the huge sphere of Jupiter is a vast 

sea of liquid hydrogen and helium. Jupiter's composition (about 88 percent hydrogen and 11 percent helium 

with small amounts of methane, ammonia and water) is thought to resemble the makeup of the solar nebula, 

the cloud of gas and dust from which the sun and planets formed. Scientists believe Jupiter holds important 

clues to conditions in the early solar system and the process of planet formation. 

Jupiter may also provide insights into the formation of the universe itself. Since it resembles the interstellar 

gas and dust that are thought to have been created in the "Big Bang," studies of Jupiter may help scientists 

calibrate models of the beginning of the universe. 

Though starlike in composition, Jupiter is too small to generate temperatures high enough to ignite nuclear 

fusion, the process that powers the stars. Some scientists believe that the sun and Jupiter began as unequal 

partners in a binary star system. (If a double star system had developed, it is unlikely life could have arisen 

in the solar system.) While in a sense a "failed star," Jupiter is almost as large as a planet can be. If it 

contained more mass, it would not have grown larger, but would have shrunk from compression by its own 

gravity. If it were 100 times more massive, thermonuclear reactions would ignite, and Jupiter would be a 

star. 
Edited by Richard W. Orloff, 01/2001/Page 32 

For a brief period after its formation, Jupiter was much hotter, more luminous, and about 10 times larger 

than it is now, scientists believe. Soon after accretion (the condensation of a gas and dust cloud into a 

planet), its brightness dropped from about one percent of the Sun's to about one billionth -- a decline of ten 

million times. 

In its present state Jupiter emits about twice as much heat as it receives from the Sun. The loss of this heat -

- residual energy left over from the compressive heat of accretion -- means that Jupiter is cooling and losing 

energy at a tremendously rapid rate. Temperatures in Jupiter's core, which were about 90,000 degrees 

Fahrenheit in the planet's hot, early phase, are now about 54,000 degrees Fahrenheit, 100 times hotter than 

any terrestrial surface, but 500 times cooler than the temperature at the center of the sun. Temperatures on 

Jupiter now range from 54,000 degrees Fahrenheit at the core to minus 248 degrees Fahrenheit at the top of 

the cloud banks. 

Mainly uniform in composition, Jupiter's structure is determined by gradations in temperature and pressure. 

Deep in Jupiter's interior there is thought to be a small rocky core, comprising about four percent of the 

planet's mass. This "small" core (about the size of 10 Earths) is surrounded by a 25,000-mile-thick layer of 

liquid metallic hydrogen. (Metallic hydrogen is liquid, but sufficiently compressed to behave as metal.) 

Motions of this liquid "metal" are the source of the planet's enormous magnetic field. This field is created 

by the same dynamo effect found in the metallic cores of Earth and other planets. 

At the outer limit of the metallic hydrogen layer, pressures equal three million times that of Earth's 

atmosphere and the temperature has cooled to 19,000 degrees Fahrenheit. 

Surrounding the central metallic hydrogen region is an outer shell of "liquid" molecular hydrogen. Huge 

pressures compress Jupiter's gaseous hydrogen until, at this level, it behaves like a liquid. The liquid 

hydrogen layer extends upward for about 15,000 miles. Then it gradually becomes gaseous. This transition 

region between liquid and gas marks, in a sense, where the solid and liquid planet ends and its atmosphere 

begins. 

From here, Jupiter's atmosphere extends up for 600 more miles, but only in the top 50 miles are found the 

brilliant bands of clouds for which Jupiter is known. The tops of these bands are colored bright yellow, red 

and orange from traces of phosphorous and sulfur. Five or six of these bands, counterflowing east and west, 

encircle the planet in each hemisphere. At one point near Jupiter's equator, east winds of 220 mph blow 

right next to west winds of 110 mph. At boundaries of these bands, rapid changes in wind speed and 

direction create large areas of turbulence and shear. These are the same forces that create tornados here on 

Earth. On Jupiter, these "baroclinic instabilities" are major phenomena, creating chaotic, swirling winds 

and spiral features such as White Ovals. 

The brightest cloud banks, known as zones, are believed to be higher, cooler areas where gases are 

ascending. The darker bands, called belts, are thought to be warmer, cloudier regions of descent. 

The top cloud layer consists of white cirrus clouds of ammonia crystals, at a pressure six-tenths that of 

Earth's atmosphere at sea level (.6 bar). Beneath this layer, at a pressure of about two Earth atmospheres (2 

bars) and a temperature of near minus 160 degrees Fahrenheit, a reddish-brown cloud of ammonium 

hydrosulfide is predicted. 

At a pressure of about 6 bars, there are believed to be clouds of water and ice. However, recent Earth-based 

spectroscopic studies suggest that there may be less water on Jupiter than expected. While scientists 

previously believed Jupiter and the sun would have similar proportions of water, recent work indicates 

there may be 100 times less water on Jupiter than if it had a solar mixture of elements. If this is the case, 

there may be only a thin layer of water-ice at the 6 bar level. 

However, Jupiter's cloud structure, except for the highest layer of ammonia crystals, remains uncertain. The 

height of the lower clouds is still theoretical -- clouds are predicted to lie at the temperature levels where 

their assumed constituents are expected to condense. The Galileo probe will make the first direct 

observations of Jupiter's lower atmosphere and clouds, providing crucial information. 
Edited by Richard W. Orloff, 01/2001/Page 33 

The forces driving Jupiter's fast-moving winds are not well understood yet. The classical explanation holds 

that strong currents are created by convection of heat from Jupiter's hot interior to the cooler polar regions, 

much as winds and ocean currents are driven on Earth, from equator to poles. But temperature differences 

do not fully explain wind velocities that can reach 265 mph. An alternative theory is that pressure 

differences, due to changes in the thermodynamic state of hydrogen at high and low temperatures, set up 

the wind jets. 

Jupiter's rapid rotation rate is thought to have effects on wind velocity and to produce some of Jupiter's 

bizarre circulation patterns, including many spiral features. These rotational effects are known as 

manifestations of the Coriolis force. Coriolis force is what determines the spin direction of weather 

systems. It basically means that on the surface of a sphere (a planet), a parcel of gas farther from the poles 

has a higher rotational velocity around the planet than a parcel closer to the poles. As gases then move 

north or south, interacting parcels with different velocities produce vortices (whirlpools). This may account 

for some of Jupiter's circular surface features. 

Jupiter spins faster than any planet in the solar system. Though 11 times Earth's diameter, Jupiter spins 

more than twice as fast (once in 10 hours), giving gases on the surface extremely high rates of travel -- 

22,000 mph at the equator, compared with 1000 mph for air at Earth's equator. Jupiter's rapid spin also 

causes this gas and liquid planet to flatten markedly at the poles and bulge at the equator. 

Visible at the top of Jupiter's atmosphere are eye-catching features such as the famous Great Red Spot and 

the exotic White Ovals, Brown Barges and White Plumes. The Great Red Spot, which is 25,000 miles wide 

and large enough to swallow three Earths, is an enormous oval eddy of swirling gases. It is driven by two 

counter-flowing jet streams, which pass, one on each side of it, moving in opposite directions, each with 

speeds of 100-200 mph. The Great Red Spot was first discovered in 1664, by the British scientist Roger 

Hook, using Galileo's telescope. In the three centuries since, the huge vortex has remained constant in 

latitude in Jupiter's southern equatorial belt. Because of its stable position, astronomers once thought it 

might be a volcano. 

Another past theory compared the Great Red Spot to a gigantic hurricane. However, the GRS rotates anticyclonically while hurricanes are cyclonic features (counterclockwise in the northern hemisphere, 

clockwise in the southern) -- and the dynamics of the Great Red Spot appear unrelated to moisture. 

The Great Red Spot most closely resembles an enormous tornado, a huge vortex that sucks in smaller 

vortices. The Coriolis effect created by Jupiter's fast spin, appears to be the key to the dynamics that drive 

the spot. 

The source of the Great Red Spot's color remains a mystery. Many scientists now believe it to be caused by 

phosphorus, but its spectral line does not quite match that of phosphorus. The GRS may be the largest in a 

whole array of spiral phenomena with similar dynamics. About a dozen white ovals, circulation patterns 

resembling the GRS, exist in the southern latitudes of Jupiter and appear to be driven by the same forces. 

Scientists do not know why these ovals are white. 

Scientists believe the brown barges, which appear like dark patches on the planet, are holes in the upper 

clouds, through which the reddish-brown lower cloud layer may be glimpsed. The equatorial plumes, or 

white plumes, may be a type of wispy cirrus anvil cloud. 
Edited by Richard W. Orloff, 01/2001/Page 34 

GALILEO MANAGEMENT 

The Galileo Project is managed for NASA's Office of Space Science and Applications by the NASA Jet 

Propulsion Laboratory, Pasadena, Calif. This responsibility includes designing, building, testing, operating 

and tracking Galileo. NASA's Ames Research Center, Moffett Field, Calif. is responsible for the 

atmosphere probe, which was built by Hughes Aircraft Company, El Segundo, Calif. 

The probe project and science teams will be stationed at Ames during pre-mission, mission operations, and 

data reduction periods. Team members will be at Jet Propulsion Laboratory for probe entry. 

The Federal Republic of Germany has furnished the orbiter's retropropulsion module and is participating in 

the scientific investigations. The radioisotope thermoelectric generators were designed and built for the 

U.S. Department of Energy by the General Electric Company. 

GALILEO ORBITER AND PROBE SCIENTIFIC INVESTIGATIONS 

Listed by experiment/instrument and including the Principal Investigator and scientific objectives of that 

investigation: 

PROBE 

Atmospheric Structure A. Seiff NASA Ames Research 

Center 

Temperature, pressure, 

density, molecular 

weight profiles 

Neutral Mass 

Spectrometer 

H. Neimann NASA Goddard Space 

Flight Center 

chemical composition 

Helium Abundance U. von Zahn Bonn University, FRG helium/hydrogen ratio 

Nephelometer B. Ragent NASA Ames Research 

Center 

clouds, solid/liquid 

particles 

Net Flux Radiometer L. Sromovsky University of 

Wisconsin-Madison 

thermal/solar energy 

profiles 

Lightning/Energetic 

Particles 

L. Lanzerotti Bell Laboratories detect lightning, 

measuring energetic 

particles 

ORBITER (DESPUN PLATFORM 

Solid-State Imaging 

Camera 

M. Belton National Optical 

Astronomy 

Observatories (team 

leader) 

Galilean satellites at 1-

km resolution or better 

Near-Infrared Mapping 

Spectrometer 

R. Carlson NASA Jet Propulsion 

Laboratory 

surface/atmospheric 

composition, thermal 

mapping 

Ultraviolet 

Spectrometer 

C. Hord University of Colorado atmospheric gases, 

aerosols 

Photopolarimeter 

Radiometer 

J. Hansen Goddard Institute for 

Space Studies 

atmospheric particles, 

thermal/reflected 

radiation 
Edited by Richard W. Orloff, 01/2001/Page 35 

ORBITER (SPINNING SPACECRAFT SECTION) 

Magnetometer; M. Kivelson. University of California at Los Angeles; strength and fluctuations of magnetic 

fluids 

Energetic Particles; D. Williams, Johns Hopkins Applied Physics Laboratory; electrons, protons, heavy 

ions in magnetosphere and interplanetary space 

Plasma; L. Frank, University of Iowa; composition, energy, distribution of magnetospheric ions 

Plasma Wave; D. Gurnett, University of Iowa; electromagnetic waves and wave-particle interactions 

Dust; E. Grun, Max Planck Institute; mass, velocity, charge of submicron particles 

Radio Science - Celestial Mechanics; J. Anderson, NASA Jet Propulsion Laboratory (team leader); masses 

and motions of bodies from spacecraft tracking 

Radio Science – Propagation; H. T. Howard, Stanford University; satellite radii, atmospheric structure both 

from radio propagation.

INTERDISCIPLINARY INVESTIGATIONS 

F. P. Fanale University of Hawaii 

P. Gierasch Cornell University 

D. M. Hunten University of Arizona 

A. P. Ingersoll California Institute of Technology 

H. Masursky U.S. Geological Survey 

D. Morrison Ames Research Center 

M. McElroy Harvard University 

G. S. Orton NASA Jet Propulsion Laboratory 

T. Owen State University of New York at Stony Brook 

J. B. Pollack NASA Ames Research Center 

C. T. Russell University of California at Los Angeles 

C. Cagan Cornell University 

G. Schubert University of California at Los Angeles 

J. Van Allen University of Iowa 
Edited by Richard W. Orloff, 01/2001/Page 36 

STS-34 INERTIAL UPPER STAGE (IUS-19) 

The Inertial Upper Stage (IUS) will again be used with the Space Shuttle, this time to transport NASA's 

Galileo spacecraft out of Earth's orbit to Jupiter, a 2.5-billion-mile journey. 

The IUS has been used previously to place three Tracking and Data Relay Satellites in geostationary orbit 

as well as to inject the Magellan spacecraft into its interplanetary trajectory to Venus. In addition, the IUS 

has been selected by the agency for the Ulysses solar polar orbit mission. 

After 2 1/2 years of competition, Boeing Aerospace Co., Seattle, was selected in August 1976 to begin 

preliminary design of the IUS. The IUS was developed and built under contract to the Air Force Systems 

Command's Space Systems Division. The Space Systems Division is executive agent for all Department of 

Defense activities pertaining to the Space Shuttle system. NASA, through the Marshall Space Flight 

Center, Huntsville, Ala., purchases the IUS through the Air Force and manages the integration activities of 

the upper stage to NASA spacecraft. 

Specifications 

IUS-19, to be used on mission STS-34, is a two-stage vehicle weighing approximately 32,500 lbs. Each 

stage has a solid rocket motor (SRM), preferred over liquid-fueled engines because of SRM's relative 

simplicity, high reliability, low cost and safety. 

The IUS is 17 ft. long and 9.25 ft. in diameter. It consists of an aft skirt, an aft stage SRM generating 

approximately 42,000 lbs. of thrust, an interstage, a forward-stage SRM generating approximately 18,000 

lbs. of thrust, and an equipment support section. 

Airborne Support Equipment 

The IUS Airborne Support Equipment (ASE) is the mechanical, avionics and structural equipment located 

in the orbiter. The ASE supports the IUS and the Galileo in the orbiter payload bay and elevates the 

combination for final checkout and deployment from the orbiter. 

The IUS ASE consists of the structure, electromechanical mechanisms, batteries, electronics and cabling to 

support the Galileo/IUS. These ASE subsystems enable the deployment of the combined vehicle; provide, 

distribute and/or control electrical power to the IUS and spacecraft; provide plumbing to cool the 

radioisotope thermoelectric generator (RTG) aboard Galileo; and serve as communication paths between 

the IUS and/or spacecraft and the orbiter. 

IUS Structure 

The IUS structure is capable of supporting loads generated internally and also by the cantilevered 

spacecraft during orbiter operations and the IUS free flight. It is made of aluminum skin-stringer 

construction, with longerons and ring frames. 

Equipment Support Section 

The top of the equipment support section contains the spacecraft interface mounting ring and electrical 

interface connector segment for mating and integrating the spacecraft with the IUS. Thermal isolation is 

provided by a multilayer insulation blanket across the interface between the IUS and Galileo. 
Edited by Richard W. Orloff, 01/2001/Page 37 

The equipment support section also contains the avionics which provide guidance, navigation, control, 

telemetry, command and data management, reaction control and electrical power. All mission-critical 

components of the avionics system, along with thrust vector actuators, reaction control thrusters, motor 

igniter and pyrotechnic stage separation equipment are redundant to assure reliability of better than 98 

percent. 

IUS Avionics Subsystems 

The avionics subsystems consist of the telemetry, tracking and command subsystems; guidance and 

navigation subsystem; data management; thrust vector control; and electrical power subsystems. These 

subsystems include all the electronic and electrical hardware used to perform all computations, signal 

conditioning, data processing and formatting associated with navigation, guidance, control, data and 

redundancy management. The IUS avionics subsystems also provide the equipment for communications 

between the orbiter and ground stations as well as electrical power distribution. 

Attitude control in response to guidance commands is provided by thrust vectoring during powered flight 

and by reaction control thrusters while coasting. Attitude is compared with guidance commands to generate 

error signals. During solid motor firing, these commands gimbal the IUS's movable nozzle to provide the 

desired pitch and yaw control. The IUS's roll axis thrusters maintain roll control. While coasting, the error 

signals are processed in the computer to generate thruster commands to maintain the vehicle's altitude or to 

maneuver the vehicle. 

The IUS electrical power subsystem consists of avionics batteries, IUS power distribution units, a power 

transfer unit, utility batteries, a pyrotechnic switching unit, an IUS wiring harness and umbilical and 

staging connectors. The IUS avionics system provides 5-volt electrical power to the Galileo/IUS interface 

connector for use by the spacecraft telemetry system. 

IUS Solid Rocket Motors 

The IUS two-stage vehicle uses a large solid rocket motor and a small solid rocket motor. These motors 

employ movable nozzles for thrust vector control. The nozzles provide up to 4 degrees of steering on the 

large motor and 7 degrees on the small motor. The large motor is the longest-thrusting duration SRM ever 

developed for space, with the capability to thrust as long as 150 seconds. Mission requirements and 

constraints (such as weight) can be met by tailoring the amount of propellant carried. The IUS-19 firststage motor will carry 21,488 lb. of propellant; the second stage 6,067 lb. 

Reaction Control System 

The reaction control system controls the Galileo/IUS spacecraft attitude during coasting, roll control during 

SRM thrustings, velocity impulses for accurate orbit injection and the final collision-avoidance maneuver 

after separation from the Galileo spacecraft. 

As a minimum, the IUS includes one reaction control fuel tank with a capacity of 120 lb. of hydrazine. 

Production options are available to add a second or third tank. However, IUS-19 will require only one tank. 

IUS To Spacecraft Interfaces 

Galileo is physically attached to the IUS at eight attachment points, providing substantial load-carrying 

capability while minimizing the transfer of heat across the connecting points. Power, command and data 

transmission between the two are provided by several IUS interface connectors. In addition, the IUS 

provides a multilayer insulation blanket of aluminized Kapton with polyester net spacers across the 

Galileo/IUS interface, along with an aluminized Beta cloth outer layer. All IUS thermal blankets are vented 
Edited by Richard W. Orloff, 01/2001/Page 38 

toward and into the IUS cavity, which in turn is vented to the orbiter payload bay. There is no gas flow 

between the spacecraft and the IUS. The thermal blankets are grounded to the IUS structure to prevent 

electrostatic charge buildup. 

Flight Sequence 

After the orbiter payload bay doors are opened in orbit, the orbiter will maintain a preselected attitude to 

keep the payload within thermal requirements and constraints. 

On-orbit predeployment checkout begins, followed by an IUS command link check and spacecraft 

communications command check. Orbiter trim maneuvers are normally performed at this time. 

Forward payload restraints will be released and the aft frame of the airborne-support equipment will tilt the 

Galileo/IUS to 29 degrees. This will extend the payload into space just outside the orbiter payload bay, 

allowing direct communication with Earth during systems checkout. The orbiter then will be maneuvered to 

the deployment attitude. If a problem has developed within the spacecraft or IUS, the IUS and its payload 

can be restowed. 

Prior to deployment, the spacecraft electrical power source will be switched from orbiter power to IUS 

internal power by the orbiter flight crew. After verifying that the spacecraft is on IUS internal power and 

that all Galileo/IUS predeployment operations have been successfully completed, a GO/NO-GO decision 

for deployment will be sent to the crew from ground support. 

When the orbiter flight crew is given a "Go" decision, they will activate the ordnance that separates the 

spacecraft's umbilical cables. The crew then will command the electromechanical tilt actuator to raise the 

tilt table to a 58-degree deployment position. The orbiter's RCS thrusters will be inhibited and an ordnanceseparation device initiated to physically separate the IUS/spacecraft combination from the tilt table. 

Six hours, 20 minutes into the mission, compressed springs provide the force to jettison the IUS/Galileo 

from the orbiter payload bay at approximately 6 inches per second. The deployment is normally performed 

in the shadow of the orbiter or in Earth eclipse. 

The tilt table then will be lowered to minus 6 degrees after IUS and its spacecraft are deployed. A small 

orbiter maneuver is made to back away from IUS/Galileo. Approximately 15 minutes after deployment, the 

orbiter's OMS engines will be ignited to move the orbiter away from its released payload. 

After deployment, the IUS/Galileo is controlled by the IUS onboard computers. Approximately 10 minutes 

after IUS/Galileo deployment from the orbiter, the IUS onboard computer will send out signals used by the 

IUS and/or Galileo to begin mission sequence events. This signal will also enable the IUS reaction control 

system. All subsequent operations will be sequenced by the IUS computer, from transfer orbit injection 

through spacecraft separation and IUS deactivation. 

After the RCS has been activated, the IUS will maneuver to the required thermal attitude and perform any 

required spacecraft thermal control maneuvers. 

At approximately 45 minutes after deployment from the orbiter, the ordnance inhibits for the first SRM will 

be removed. The belly of the orbiter already will have been oriented towards the IUS/Galileo to protect 

orbiter windows from the IUS's plume. The IUS will recompute the first ignition time and maneuvers 

necessary to attain the proper attitude for the first thrusting period. When the proper transfer orbit 

opportunity is reached, the IUS computer will send the signal to ignite the first stage motor 60 minutes after 

deployment. After firing approximately 150 seconds, the IUS first stage will have expended its propellant 

and will be separated from the IUS second stage. 

Approximately 140 seconds after first-stage burnout, the second- stage motor will be ignited, thrusting 

about 108 seconds. The IUS second stage then will separate and perform a final collision/contamination 

avoidance maneuver before deactivating. 
Edited by Richard W. Orloff, 01/2001/Page 39 

SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT 

The Shuttle Solar Backscatter Ultraviolet (SSBUV) instrument was developed by NASA to calibrate 

similar ozone measuring space-based instruments on the National Oceanic and Atmospheric 

Administration's TIROS satellites (NOAA-9 and -11). 

The SSBUV will help scientists solve the problem of data reliability caused by calibration drift of solar 

backscatter ultraviolet (SBUV) instruments on orbiting spacecraft. The SSBUV uses the Space Shuttle's 

orbital flight path to assess instrument performance by directly comparing data from identical instruments 

aboard the TIROS spacecraft, as the Shuttle and the satellite pass over the same Earth location within a 1-

hour window. These orbital coincidences can occur 17 times per day. 

The SBUV measures the amount and height distribution of ozone in the upper atmosphere. It does this by 

measuring incident solar ultraviolet radiation and ultraviolet radiation backscattered from the Earth's 

atmosphere. The SBUV measures these parameters in 12 discrete wavelength channels in the ultraviolet. 

Because ozone absorbs in the ultraviolet, an ozone measurement can be derived from the ratio of 

backscatter radiation at different wavelengths, providing an index of the vertical distribution of ozone in the 

atmosphere. 

Global concern over the depletion of the ozone layer has sparked increased emphasis on developing and 

improving ozone measurement methods and instruments. Accurate, reliable measurements from space are 

critical to the detection of ozone trends and for assessing the potential effects and development of 

corrective measures. 

The SSBUV missions are so important to the support of Earth science that six additional missions have 

been added to the Shuttle manifest for calibrating ozone instruments on future TIROS satellites. In addition, 

the dates of the four previously manifested SSBUV flights have been accelerated. 

The SSBUV instrument and its dedicated electronics, power, data and command systems are mounted in 

the Shuttle's payload bay in two Get Away Special canisters, an instrument canister and a support canister. 

Together, they weigh approximately 1200 lb. The instrument canister holds the SSBUV, its specially 

designed aspect sensors and in-flight calibration system. A motorized door assembly opens the canister to 

allow the SSBUV to view the sun and Earth and closes during the in-flight calibration sequence. 

The support canister contains the power system, data storage and command decoders. The dedicated power 

system can operate the SSBUV for a total of approximately 40 hours. 

The SSBUV is managed by NASA's Goddard Space Flight Center, Greenbelt, Md. Ernest Hilsenrath is the 

principal investigator. 
Edited by Richard W. Orloff, 01/2001/Page 40 
Edited by Richard W. Orloff, 01/2001/Page 41 

GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS 

The Growth Hormone Concentration and Distribution in Plants (GHCD) experiment is designed to 

determine the effects of microgravity on the concentration, turnover properties, and behavior of the plant 

growth hormone, Auxin, in corn shoot tissue (Zea Mays). 

Mounted in foam blocks inside two standard middeck lockers, the equipment consists of four plant 

canisters, two gaseous nitrogen freezers and two temperature recorders. Equipment for the experiment, 

excluding the lockers, weighs 97.5 pounds. 

A total of 228 specimens (Zea Mays seeds) are "planted" in special filter, paper-Teflon tube holders no 

more than 56 hours prior to flight. The seeds remain in total darkness throughout the mission. 

The GHCD experiment equipment and specimens will be prepared in a Payload Processing Facility at KSC 

and placed in the middeck lockers. The GHCD lockers will be installed in the orbiter middeck within the 

last 14 hours before launch. 

No sooner than 72 hours after launch, mission specialist Ellen Baker will place two of the plant canisters 

into the gaseous nitrogen freezers to arrest the plant growth and preserve the specimens. The payload will 

be restowed in the lockers for the remainder of the mission. 

After landing, the payload must be removed from the orbiter within 2 hours and will be returned to 

customer representatives at the landing site. The specimens will be examined post flight for microgravity 

effects. 

The GHCD experiment is sponsored by NASA Headquarters, the Johnson Space Center and Michigan 

State University. 
Edited by Richard W. Orloff, 01/2001/Page 42 

POLYMER MORPHOLOGY 

The Polymer Morphology (PM) experiment is a 3M-developed organic materials processing experiment 

designed to explore the effects of microgravity on polymeric materials as they are processed in space. 

Since melt processing is one of the more industrially significant methods for making products from 

polymers, it has been chosen for study in the PM experiment. Key aspects of melt processing include 

polymerization, crystallization and phase separation. Each aspect will be examined in the experiment. The 

polymeric systems for the first flight of PM include polyethylene, nylon-6 and polymer blends. 

The apparatus for the experiment includes a Fournier transform infrared (FTIR) spectrometer, an automatic 

sample manipulating system and a process control and data acquisition computer known as the Generic 

Electronics Module (GEM). The experiment is contained in two separate, hermetically sealed containers 

that are mounted in the middeck of the orbiter. Each container includes an integral heat exchanger that 

transfers heat from the interior of the containers to the orbiter's environment. All sample materials are kept 

in triple containers for the safety of the astronauts. 

The PM experiment weighs approximately 200 lb., occupies three standard middeck locker spaces (6 cubic 

ft., total) in the orbiter and requires 240 watts to operate. 

Mission specialists Franklin R. Chang-Diaz and Shannon W. Lucid are responsible for the operation of the 

PM experiment on orbit. Their interface with the PM experiment is through a small, NASA-supplied laptop 

computer that is used as an input and output device for the main PM computer. This interface has been 

programmed by 3M engineers to manage and display the large quantity of data that is available to the crew. 

The astronauts will have an active role in the operation of the experiment. 

In the PM experiment, infrared spectra (400 to 5000 cm-1) will be acquired from the FTIR by the GEM 

computer once every 3.2 seconds as the materials are processed on orbit. During the 100 hours of 

processing time, approximately 2 gigabytes of data will be collected. Post flight, 3M scientists will process 

the data to reveal the effects of microgravity on the samples processed in space. 

The PM experiment is unique among material processing experiments in that measurements characterizing 

the effects of microgravity will be made in real time, as the materials are processed in space. 

In most materials processing space experiments, the materials have been processed in space with little or no 

measurements made during on-orbit processing and the effects of microgravity determined post facto. 

The samples of polymeric materials being studied in the PM experiment are thin films (25 microns or less) 

approximately 25 mm in diameter. The samples are mounted between two infrared transparent windows in 

a specially designed infrared cell that provides the capability of thermally processing the samples to 200 

degrees Celsius with a high degree of thermal control. The samples are mounted on a carousel that allows 

them to be positioned, one at a time, in the infrared beam where spectra may be acquired. The GEM 

provides all carousel and sample cell control. The first flight of PM will contain 17 samples. 

The PM experiment is being conducted by 3M's Space Research and Applications Laboratory. Dr. Earl L. 

Cook is 3M's Payload Representative and Mission Coordinator. Dr. Debra L. Wilfong is PM's Science 

Coordinator, and James E. Steffen is the Hardware Coordinator. 

The PM experiment, a commercial development payload, is sponsored by NASA's Office of Commercial 

Programs. The PM experiment will be 3M's fifth space experiment and the first under the company's 10-

year Joint Endeavor Agreement with NASA for 62 flight experiment opportunities. Previous 3M space 

experiments have studied organic crystal growth from solution (DMOS/1 on mission STS 51-A and 

DMOS/2 on STS 61-B) and organic thin film growth by physical vapor treatment (PVTOS/1 on STS 51-I 

and PVTOS/2 on mission STS-26). 
Edited by Richard W. Orloff, 01/2001/Page 43 

STUDENT EXPERIMENT 

Zero Gravity Growth of Ice Crystals From Supercooled Water 

With Relation To Temperature (SE82-15) 

This experiment, proposed by Tracy L. Peters, formerly of Ygnacio High School, Concord, Calif., will 

observe the geometric ice crystal shapes formed at supercooled temperatures, below 0 degrees Celsius, 

without the influence of gravity. 

Liquid water has been discovered at temperatures far below water's freezing point. This phenomenon 

occurs because liquid water does not have a nucleus, or core, around which to form the crystal. When the 

ice freezes at supercold temperatures, the ice takes on many geometric shapes based on the hexagon. The 

shape of the crystal primarily depends on the supercooled temperature and saturation of water vapor. The 

shapes of crystals vary from simple plates to complex prismatic crystals. 

Many scientists have tried to determine the relation between temperature and geometry, but gravity has 

deformed crystals, caused convection currents in temperature-controlled apparatus, and caused faults in the 

crystalline structure. These all affect crystal growth by either rapid fluctuations of temperature or 

gravitational influence of the crystal geometry. 

The results of this experiment could aid in the design of radiator cooling and cryogenic systems and in the 

understanding of high-altitude meteorology and planetary ring structure theories. 

Peters is now studying physics at the University of California at Berkeley. His teacher advisor is James R. 

Cobb, Ygnacio High School; his sponsor is Boeing Aerospace Corp., Seattle. 

Peters also was honored as the first four-time NASA award winner at the International Science and 

Engineering Fair (ISEF), which recognizes student's creative scientific endeavors in aerospace research. At 

the 1982 ISEF, Peters was one of two recipients of the Glen T. Seaborg Nobel Prize Visit Award, an allexpense-paid visit to Stockholm to attend the Nobel Prize ceremonies, for his project "Penetration and 

Diffusion of Supersonic Fluid." 
Edited by Richard W. Orloff, 01/2001/Page 44 

MESOSCALE LIGHTNING EXPERIMENT 

The Space Shuttle will again carry the Mesoscale Lightning Experiment (MLE), designed to obtain 

nighttime images of lightning in order to better understand the global distribution of lightning, the 

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

convective storms and precipitation. 

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

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

lightning threats to life and property. 

In recent years, NASA has used both Space Shuttle missions and high-altitude U-2 aircraft to observe 

lightning from above convective storms. The objectives of these observations have been to determine some 

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

optical and electrical characteristics of lightning as viewed from above the cloudtop; and investigate the 

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

thunderstorms and thunderstorm systems. 

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

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

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

sensors. 

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

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

experiment also will be helpful for designing procedures for using the Lightning Mapper Sensor (LMS), 

planned for several geostationary platforms. 

In this experiment, Atlantis' payload bay camera will be pointed directly below the orbiter to observe 

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

observed from Shuttle altitudes. Scientists on the ground will analyze the imagery for the frequency of 

lightning flashes in active storm clouds within the camera's field of view, the length of lightning discharges, 

and cloud brightness when illuminated by the lightning discharge within the cloud. 

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

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

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

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

Kennedy Space Center, Fla.; and the NOAA Severe Storms Laboratory, Norman, Okla. Other groundbased lightning detection systems in Australia, South America and Africa will be integrated when possible. 

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

experiment. Dr. Hugh Christian is the project scientist, and Dr. James Arnold is the project manager. 
Edited by Richard W. Orloff, 01/2001/Page 45 

IMAX 

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

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

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

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

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

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

space and Earth. 

Film from those missions form the basis for the IMAX production, "The Dream is Alive." On STS 61-B, an 

IMAX camera mounted in the payload bay recorded extravehicular activities in the EAS/ACCESS space 

construction demonstrations. 

The IMAX camera, most recently carried aboard STS-29, will be used on this mission to cover the 

deployment of the Galileo spacecraft and to gather material on the use of observations of the Earth from 

space for future IMAX films. 
Edited by Richard W. Orloff, 01/2001/Page 46 

AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST 

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

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

overflights. Scientific observations made of the orbiter while performing Reaction Control System thruster 

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

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

hardware and only require that the orbiter be in predefined attitude operations and lighting conditions. 

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

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

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

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

investigator is from AVCO. 

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

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

conducted at JSC Mission Control Center in coordination with the AMOS facilities located in Hawaii. 
Edited by Richard W. Orloff, 01/2001/Page 47 

SENSOR TECHNOLOGY EXPERIMENT 

The Sensor Technology Experiment (STEX) is a radiation detection experiment designed to measure the 

natural radiation background. The STEX is a self-contained experiment with its own power, sensor, 

computer control and data storage. A calibration pack, composed of a small number of passive threshold 

reaction monitors, is attached to the outside of the STEX package. 

Sponsored by the Strategic Defense Initiative Organization, the STEX package weighs approximately 50 

pounds and is stowed in a standard middeck locker throughout the flight. 
Edited by Richard W. Orloff, 01/2001/Page 48 

SPACEFLIGHT TRACKING AND DATA NETWORK 

Primary communications for most activities on STS-34 will be conducted through the orbiting Tracking 

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

geosynchronous orbit 22,300 miles above the Earth. In addition, three NASA Spaceflight Tracking and 

Data Network (STDN) ground stations and the NASA Communications Network (NASCOM), both 

managed by Goddard Space Flight Center, Greenbelt, Md., will play key roles in the mission. 

Three stations -- Merritt Island and Ponce de Leon, Florida and the Bermuda -- serve as the primary 

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

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

Kennedy and Johnson Space Centers by way of the Merritt Island facility. 

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

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

communications between the Shuttle and the centers for 70 seconds, or until 150 seconds into the mission. 

This is during a critical period when exhaust from the solid rocket motors "blocks out" the Merritt Island 

antennas. 

The Merritt Island facility resumes communications to and from the Shuttle after those 70 seconds and 

maintains them until 6 minutes, 30 seconds after launch when communications are "switched over" to 

Bermuda. Bermuda then provides the communications until 11 minutes after liftoff when the TDRS-East 

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

The TDRS-East and -West satellites will provide communications with the Shuttle during 85 percent or 

better of each orbit. The TDRS-West satellite will handle communications with the Shuttle during its 

descent and landing phases. 
Edited by Richard W. Orloff, 01/2001/Page 49 

PAYLOAD AND VEHICLE WEIGHTS 

 (Pounds)

Orbiter (Atlantis) Empty 172,018 

 

Galileo/IUS (payload bay) 43,980 

Galileo support hardware (middeck) 59 

SSBUV (payload bay) 637 

SSBUV support 578 

DSO 49 

DTO 170 

GHCD 130 

IMAX 269 

MLE 15 

PM 219 

SSIP 70 

STEX 52 

Orbiter and Cargo at SRB Ignition 264,775 

Total Vehicle at SRB Ignition 4,523,810 

Orbiter Landing Weight 195,283 
Edited by Richard W. Orloff, 01/2001/Page 50 
Edited by Richard W. Orloff, 01/2001/Page 51 

STS-34 CREWMEMBERS 

S89-39803 -- The STS-34 Atlantis, OV-104, official crew portrait includes mission commander Donald E. 

Williams, pilot Michael J. McCulley, mission specialists Shannon W. Lucid, Ellen S. Baker, and Franklin R. 

Chang-Diaz wearing red mission t-shirts. Seated (left to right) are Lucid, Chang-Diaz, and Baker with 

Williams (left) and McCulley standing. Crew insignia is displayed in the background. 

No copyright is asserted for this photograph. If a recognizable person appears in the photo, use for 

commercial purposes may infringe a right of privacy or publicity. It may not be used to state or imply the 

endorsement by NASA or by any NASA employee of a commercial product, process or service, or used in 

any other manner that might mislead. Accordingly, it is requested that if this photograph is used in 

advertising and other commercial promotion, layout and copy be submitted to NASA prior to release. 

PHOTO CREDIT: NASA or National Aeronautics and Space Administration. 
Edited by Richard W. Orloff, 01/2001/Page 52 

BIOGRAPHICAL DATA 

DONALD E. WILLIAMS, 47, Capt., USN, will serve as commander. Selected as an astronaut in January 

1978, he was born in Lafayette, Ind. 

Williams was pilot for STS-51D, the fourth flight of Discovery, launched April 12, 1985. During the 

mission, the seven-member crew deployed the Anik-C communications satellite for Telesat of Canada and 

the Syncom IV-3 satellite for the U.S. Navy. A malfunction in the Syncom spacecraft resulted in the first 

unscheduled extravehicular, rendezvous and proximity operation for the Space Shuttle in an attempt to 

activate the satellite. 

He graduated from Otterbein High School, Otterbein, Ind., in 1960 and received his B.S. degree in 

mechanical engineering from Purdue University in 1964. Williams completed his flight training at 

Pensacola, Fla., Meridian, Miss., and Kingsville, Texas, and earned his wings in 1966. 

During the Vietnam Conflict, Williams completed 330 combat missions. He has logged more than 5,400 

hours flying time, including 5,100 in jets, and 745 aircraft carrier landings. 

MICHAEL J. MCCULLEY, 46, Cdr., USN, will be pilot on this flight. Born in San Diego, McCulley 

considers Livingston, Tenn., his hometown. He was selected as a NASA astronaut in 1984. He is making 

his first Space Shuttle flight. 

McCulley graduated from Livingston Academy in 1961. He received B.S. and M.S. degrees in 

metallurgical engineering from Purdue University in 1970. 

After graduating from high school, McCulley enlisted in the U.S. Navy and subsequently served on one 

diesel-powered and two nuclear-powered submarines. Following flight training, he served tours of duty in 

A-4 and A-65 aircraft and was selected to attend the Empire Test Pilots School in Great Britain. He served 

in a variety of test pilot billets at the Naval Air Test Center, Patuxent River, Md., before returning to sea 

duty on the USS Saratoga and USS Nimitz. 

He has flown more than 50 types of aircraft, logging more than 4,760 hours, and has almost 400 carrier 

landings on six aircraft carriers. 

SHANNON W. LUCID, 46, will serve as mission specialist (MS-1) on this, her second Shuttle flight. 

Born in Shanghai, China, she considers Bethany, Okla., her hometown. Lucid is a member of the astronaut 

class of 1978. 

Lucid's first Shuttle mission was during STS 51-G, launched from the Kennedy Space Center on June 17, 

1985. During that flight, the crew deployed communications satellites for Mexico, the Arab League and the 

United States. 

Lucid graduated from Bethany High School in 1960. She then attended the University of Oklahoma where 

she received a B.S. degree in chemistry in 1963, an M.S. degree in biochemistry in 1970 and a Ph.D. in 

biochemistry in 1973. 

Before joining NASA, Lucid held a variety of academic assignments such as teaching assistant at the 

University of Oklahoma's department of chemistry; senior laboratory technician at the Oklahoma Medical 

Research Foundation; chemist at Kerr-McGee in Oklahoma City; graduate assistant in the University of 

Oklahoma Health Science Center's department of biochemistry; and molecular biology and research 

associate with the Oklahoma Medical Research Foundation in Oklahoma City. Lucid also is a commercial, 

instrument and multi-engine rated pilot. 
Edited by Richard W. Orloff, 01/2001/Page 53 

BIOGRAPHICAL DATA 

FRANKLIN CHANG-DIAZ, 39, will serve as MS-2. Born in San Jose, Costa Rica, Chang-Diaz also will 

be making his second flight since being selected as an astronaut in 1980. 

Chang-Diaz made his first flight aboard Columbia on mission STS 61-C, launched from KSC Jan. 12, 

1986. During the 6-day flight he participated in the deployment of the SATCOM KU satellite, conducted 

experiments in astrophysics and operated the materials science laboratory, MSL-2. 

Chang-Diaz graduated from Colegio De La Salle, San Jose, Costa Rica, in 1967, and from Hartford High 

School, Hartford, Conn., in 1969. He received a B.S. degree in mechanical engineering from the University 

of Connecticut in 1973 and a Ph.D. in applied plasma physics from the Massachusetts Institute of 

Technology in 1977. 

While attending the University of Connecticut, Chang-Diaz also worked as a research assistant in the 

physics department and participated in the design and construction of high-energy atomic collision 

experiments. Upon entering graduate school at MIT, he became heavily involved in the United State's 

controlled fusion program and conducted intensive research in the design and operation of fusion reactors. 

In 1979, he developed a novel concept to guide and target fuel pellets in an inertial fusion reactor chamber. 

In 1983, he was appointed as visiting scientist with the MIT Plasma Fusion Center which he visits 

periodically to continue his research on advanced plasma rockets. 

Chang-Diaz has logged more than 1,500 hours of flight time, including 1,300 hours in jet aircraft. 

ELLEN S. BAKER, 36, will serve as MS-3. She will be making her first Shuttle flight. Baker was born in 

Fayetteville, N.C., and was selected as an astronaut in 1984. 

Baker graduated from Bayside High School, New York, N.Y., in 1970. She received a B.A. degree in 

geology from the State University of New York at Buffalo in 1974, and an M.D. from Cornell University in 

1978. 

After medical school, Baker trained in internal medicine at the University of Texas Health Science Center 

in San Antonio, Texas. In 1981, she was certified by the American Board of Internal Medicine. 

Baker joined NASA as a medical officer at the Johnson Space Center in 1981 after completing her 

residency. That same year, she graduated with honors from the Air Force Aerospace Medicine Primary 

Course at Brooks Air Force Base in San Antonio. Prior to her selection as an astronaut, she served as a 

physician in the Flight Medicine Clinic at JSC. 
Edited by Richard W. Orloff, 01/2001/Page 54 

NASA PROGRAM MANAGEMENT 

NASA HEADQUARTERS, WASHINGTON, DC 

Richard H. Truly NASA Administrator 

James R. Thompson Jr. NASA Deputy Administrator 

William B. Lenoir Acting Associate Administrator for Space Flight 

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

Arnold D. Aldrich Director, National Space Transportation Program 

Leonard S. Nicholson Deputy Director, NSTS Program (Johnson Space Center) 

Robert L. Crippen Deputy Director, NSTS Operations (Kennedy Space Center) 

David L. Winterhalter Director, Systems Engineering and Analyses 

Gary E. Krier Director, Operations Utilization 

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

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

George A. Rodney Associate Administrator for Safety Reliability Maintainability and 

 Quality Assurance 

Charles T. Force Associate Administrator for Operations 

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

Samuel Keller Assistant Deputy Associate Administrator NASA Headquarters 

Al Diaz Deputy Associate Administrator for Space Science and Applications 

Dr. Geoffrey A. Briggs Director, Solar System Exploration Division 

Robert F. Murray Manager, Galileo Program 

Dr. William Quade Galileo Program Scientist 

JOHNSON SPACE CENTER, HOUSTON, TX 

Aaron Cohen Director 

Paul J. Weitz Deputy Director 

Richard A. Colonna Manager, Orbiter and GFE Projects 

Donald R. Puddy Director, Flight Crew Operations 

Eugene F. Kranz Director, Mission Operations 

Henry O. Pohl Director, Engineering 

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

KENNEDY SPACE CENTER, FL 

Forrest S. McCartney Director 

Thomas E. Utsman Deputy Director 

Jay F. Honeycutt Director, Shuttle Management and Operations 

Robert B. Sieck Launch Director 

George T. Sasseen Shuttle Engineering Director 

Conrad G. Nagel Atlantis Flow Director 

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

John T. Conway Director, Payload Management and Operations 
Edited by Richard W. Orloff, 01/2001/Page 55 

MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, AL 

Thomas J. Lee Director 

Dr. J. Wayne Littles Deputy Director 

G. Porter Bridwell Manager, Shuttle Projects Office 

Dr. George F. 

McDonough Director, Science and Engineering 

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

Royce E. Mitchell Manager, Solid Rocket Motor Project 

Cary H. Rutland Manager, Solid Rocket Booster Project 

Jerry W. Smelser Manager, Space Shuttle Main Engine Project 

G. Porter Bridwell Acting Manager, External Tank Project 

Sidney P. Saucier Manager, Space Systems Projects Office [for IUS] 

STENNIS SPACE CENTER, BAY ST. LOUIS, MS 

Roy S. Estess Director 

Gerald W. Smith Deputy Director 

William F. Taylor Associate Director 

J. Harry Guin Director, Propulsion Test Operations 

Edward L. Tilton III Director, Science and Technology Laboratory 

John L. Gasery Jr. Chief, Safety/Quality Assurance and Occupational Health 

JET PROPULSION LABORATORY, PASADENA, CA 

Dr. Lew Allen Director 

Dr. Peter T. Lyman Deputy Director 

Gene Giberson Laboratory Director for Flight Projects 

John Casani Assistant Laboratory Director for Flight Projects 

Richard J. Spehalski Manager, Galileo Project 

William J. O'Neil Manager, Science and Mission Design, Galileo Project 

Dr. Clayne M. Yeates Deputy Manager, Science and Mission Design, Galileo Project 

Dr. Torrence V Johnson Galileo Project Scientist 

Neal E. Ausman Jr. Mission Operations and Engineering Manager, Galileo Project 

A. Earl Cherniack Orbiter Spacecraft Manager, Galileo Project 

Matthew R. Landano Deputy Orbiter Spacecraft Manager, Galileo Project 

William G. Fawcett Orbiter Science Payload Manager, Galileo Project 

AMES RESEARCH CENTER, MOUNTAIN VIEW, CA 

Dr. Dale L. Compton Acting Director 

Dr. Joseph C. Sharp Acting Director, Space Research Directorate 

Joel Sperans Chief, Space Exploration Projects Office 

Benny Chin Probe Manager, Galileo Project 

Dr. Lawrence Colin Probe Scientist, Galileo Project 

Dr. Richard E. Young Probe Scientist, Galileo Project 
Edited by Richard W. Orloff, 01/2001/Page 56 

AMES-DRYDEN FLIGHT RESEARCH FACILITY, EDWARDS, CA 

Martin A. Knutson Site Manager 

Theodore G. Ayers Deputy Site Manager 

Thomas C. McMurtry Chief, Research Aircraft Operations Division 

Larry C. Barnett Chief, Shuttle Support Office 

GODDARD SPACE FLIGHT CENTER, GREENBELT, MD 

Dr. John W. Townsend Director 

Peter Burr Director, Flight Projects 

Dale L. Fahnestock Director, Mission Operations and Data Systems 

Daniel A. Spintman Chief, Networks Division 

Gary A. Morse Network Director 

Dr. Robert D. Hudson Head, Atmospheric Chemistry and Dynamics 

Ernest Hilsenrath SSBUV Principal Investigator 

Jon R. Busse Director, Engineering Directorate 

Robert C. Weaver Jr. Chief, Special Payloads Division 

Neal F. Barthelme SSBUV Mission Manager 
Edited by Richard W. Orloff, 01/2001/Page 57 

SHUTTLE FLIGHTS AS OF OCTOBER 1989 

30 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 5 SINCE RETURN TO FLIGHT 

STS-51L 

01/28/86 

STS-61A 

10/30/85 - 11/06/85 

STS-28 

08/08/89 - 08/13/89 

STS-51F 

07/29/85 - 08/06/85 

STS-29 

03/13/89 - 03/18/89 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-30 

05/04/89 - 05/08/89 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-27 

12/02/88 - 12/06/88 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

 

OV-102 

Columbia 

(8 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(8 flights) 

OV-104 

Atlantis 

(4 flights)