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

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-46 

PRESS KIT 

JULY 1992 

TETHERED SATELLITE SYSTEM (TSS-1) 
Edited by Richard W. Orloff, 01/2001/Page 2 

STS-46 INSIGNIA 

STS046-S-001 -- Designed by the crewmembers assigned to the flight, the STS-46 crew insignia depicts the 

space shuttle Atlantis in orbit around Earth, accompanied by major payloads: the European Retrievable 

Carrier (EURECA) and the Tethered Satellite System (TSS-1). In the depiction, EURECA has been 

activated and released, its antennae and solar arrays deployed, and it is about to start its ten-month 

scientific mission. The Tethered Satellite is linked to the orbiter by a 20-km tether. The purple beam 

emanating from an electron generator in the payload by spirals around Earth's magnetic field. The TSS 

mission studied the dynamics and electrodynamics of tethered systems in space and the physics of Earth's 

ionosphere. Visible on Earth's surface are the United States of America and the thirteen member countries 

of the European Space Agency (ESA), in particular, Italy -- partner with the U.S. in the TSS program. The 

American and Italian flags, as well as the ESA logo, further serve to illustrate the international character 

of STS-46. 

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

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

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

do not anticipate, it will be publicly announced. 

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

PUBLIC AFFAIRS CONTACTS 

NASA Headquarters 

Office of Space Flight/Office of Space Systems Development 

Mark Hess/Jim Cast/Ed Campion 

(Phone: 202/453-8536) 

Office of Space Science and Applications 

Paula Cleggett-Haleim/Mike Braukus/Brian Dunbar 

(Phone: 202/453-1547) 

Office of Commercial Programs 

Barbara Selby 

(Phone: 703/557-5609) 

Office of Aeronautics and Space Technology 

Drucella Andersen/Les Dorr 

(Phone: 202/453-2754) 

Office of Safety & Mission Quality/Office of Space Communications 

Dwayne Brown 

(Phone: 202/453-8596) 

Ames Research Center Langley Research Center 

Jane Hutchison Jean Drummond Clough 

(Phone: 415/604-4968) (Phone: 804/864-6122) 

 

Ames-Dryden Flight Research Facility Lewis Research Center 

Nancy Lovato Mary Ann Peto 

(Phone: 805/258-3448) (Phone: 216/433-2899) 

 

Goddard Space Flight Center Marshall Space Flight Center 

Dolores Beasley Mike Simmons 

(Phone: 301/286-2806) (Phone: 205/544-6537) 

 

Jet Propulsion Laboratory Stennis Space Center 

James Wilson Myron Webb 

(Phone: 818/354-5011) (Phone: 601/688-3341) 

 

Johnson Space Center Wallops Flight Center 

James Hartsfield Keith Koehler 

(Phone: 713/483-5111) (Phone: 804/824-1579) 

Kennedy Space Center 

Lisa Malone 

(Phone: 407/867-2468) 
Edited by Richard W. Orloff, 01/2001/Page 4 

CONTENTS 

GENERAL RELEASE 5 

MEDIA SERVICES INFORMATION 7 

QUICK-LOOK-FACTS 8 

SUMMARY OF MAJOR ACTIVITIES 9 

PAYLOAD AND VEHICLE WEIGHTS 10 

TRAJECTORY SEQUENCE OF EVENTS 12 

SPACE SHUTTLE ABORT MODES 13 

PRELAUNCH PROCESSING 14 

TETHERED SATELLITE SYSTEM (TSS-1) 15 

 Deployer 16 

 Flight Operations 24 

 Science Operations 27 

 Science Investigations 29 

 TSS-1 Team 33 

 TSS-1 Science Investigations 34 

EUROPEAN RETRIEVABLE CARRIER (EURECA) 35 

 EURECA Science 38 

EVALUATION OF OXYGEN INTERACTION WITH MATERIALS/EOIM)/ 

 TWO PHASE MOUNTING PLATE EXPERIMENT (TEMP) 

45 

CONSORTIUM FOR MATERIALS DEVELOPMENT IN SPACE (COMPLEX 

AUTONOMOUS PAYLOAD) 

47 

LIMITED DURATION SPACE ENVIRONMENT CANDIDATE MATERIALS 

EXPOSURE (LDCE) 

48 

PITUITARY GROWTH HORMONE CELL FUNCTION (PHCF) 50 

IMAX CARGO BAY CAMERA (ICBC) 50 

AIR FORCE MAUI OPTICAL STATION (AMOS) 53 

ULTRAVIOLET PLUME IMAGER (UVPI) 53 

STS-46 CREW BIOGRAPHIES 54 

MISSION MANAGEMENT FOR STS-46 57 
Edited by Richard W. Orloff, 01/2001/Page 5 

RELEASE: 92-95 July 1992 

49th SHUTTLE FLIGHT TO DEPLOY TETHERED SATELLITE SYSTEM 

Highlighting Shuttle mission STS-46 will be experiments involving a 12.5-mile-long tether connecting a 

satellite to the orbiter Atlantis, to demonstrate the feasibility of the technology for a variety of uses ranging 

from generating electrical power to researching the upper atmosphere. 

During the mission the crew will also deploy the European Retrievable carrier (EURECA-1) platform, 

which contains a series of experiments dealing with materials sciences, life sciences and radiobiology. The 

platform will remain in orbit for about 9 months before being retrieved during a later Shuttle mission. 

"First and foremost, this is a mission of discovery," Thomas Stuart, Tethered Satellite System Program 

Manager said. 

"It's the first time we've ever deployed a satellite on a long tether in space. This system is at the leading 

edge of scientific discovery and will give us a glimpse of space technologies of the future," he said. 

STS-46 is scheduled for launch in late July. It will be the 12th flight for Atlantis, and is scheduled to last 6 

days, 22 hours and 11 minutes, with a planned landing at Kennedy Space Center, Fla. 

TETHERED SATELLITE SYSTEM 

The Tethered Satellite System-1 (TSS-1) -- a joint project of the United States and Italy under an 

agreement signed in 1984 -- consists of a satellite, a 1/10th inch diameter tether and a deployer in the 

Shuttle's cargo bay. 

The 1,139 pound satellite was developed by the Italian Space Agency (ASI) and the tether and deployer 

system were developed by the U.S. The 12 main experiments were selected jointly by NASA and ASI. 

"During this mission we're going to learn a great deal about how to safely operate a tether system," Stuart 

said. "We're going to demonstrate the feasibility of using a tether to generate electricity, as a propulsion 

system to power spacecraft and for studying the earth's magnetic field and ionosphere." 

When the tether is fully extended to its 12.5 mile length, the combination of the orbiter, tether and satellite 

combined will be the longest structure ever flown in space. 

EURECA 

The crew will deploy the European Space Agency's (ESA) EURECA-1 which will then ascend to its 

operational orbit of 515 km using its own propulsion system. After 9 months it will be moved to a lower 

orbit for retrieval by another Shuttle in late April 1993. After its return to Earth it will be refurbished and 

equipped for its next mission. 

Aboard EURECA-1 are 15 experiments devoted to researching the fields of material science, life sciences 

and radiobiology, all of which require a controlled microgravity environment. The experiments include: 
Edited by Richard W. Orloff, 01/2001/Page 6 

• Protein crystallization 

• Biological effects of space radiation 

• Measurements of fluids' critical points in microgravity 

• Measurements of solar irradiation 

• Solar/terrestrial relationship in aeronomy and climatology 

• electric propulsion in space. 

Scientists participating in the investigations are from Belgium, Germany, Denmark, France, Italy, United 

Kingdom and The Netherlands. 

EURECA-1 was built by the ESA and designed to be maintained during its long-term mission by ground 

controllers at ESA's Space Operations Centre (ESOC), Darmstadt, Germany. 

ADDITIONAL PAYLOADS 

Additional payloads carried in Atlantis' cargo bay include the: 

Evaluation of Oxygen Interaction with Materials III (EOIM) experiment to study how oxygen molecules in 

low-earth orbit affect materials that will be used to construct Space Station Freedom; 

Thermal Energy Management (TEMP 2A) experiment to test a new cooling method that may be used in 

future spacecraft; 

Consortium for Material Development in Space Complex Autonomous Payload experiment to study 

materials processing; 

Limited Duration Space Environment Candidate materials Exposure experiments will explore materials 

processing methods in weightlessness; 

An IMAX camera will be in the payload bay to film various aspects of the mission for later IMAX 

productions. 

Atlantis will be commanded by USAF Col. Loren Shriver, making his third Shuttle flight. Marine Corps 

Major Andy Allen will serve as Pilot, making his first flight. Mission specialists will include Claude 

Nicollier, a European Space Agency astronaut making his first Shuttle flight; Marsha Ivins, making her 

second Shuttle flight; Jeff Hoffman, making his third space flight; and Franklin Chang-Diaz, making his 

third space flight. Franco Malerba from the Italian Space Agency will be a payload specialist aboard 

Atlantis. 

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

MEDIA SERVICES INFORMATION 

NASA Select Television Transmission 

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

longitude; frequency 3960.0 MHz, audio 6.8 MHz. 

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

during the mission at Kennedy Space Center, Fla.; Marshall Space Flight Center, Huntsville; Ames-Dryden 

Flight Research Facility, Edwards, Calif.; Johnson Space Center, Houston, and NASA Headquarters, 

Washington, DC. The television schedule will be updated to reflect changes dictated by mission 

operations. 

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

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

schedule is updated daily at noon Eastern time. 

Status Reports 

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

produced by the appropriate NASA news center. 

Briefings 

A mission press briefing schedule will be issued prior to launch. During the mission, change-of-shift 

briefings by the off-going flight director and the science team will occur at least once per day. The updated 

NASA Select television schedule will indicate when mission briefings are planned. 
Edited by Richard W. Orloff, 01/2001/Page 8 

STS-46 QUICK LOOK (revised) 

Launch Date/Site: July 31, 1992 - Kennedy Space Center, FL, Pad 39B 

 

Launch Time: 9:56 a.m. - 12:26 p.m. EDT 

 

Orbiter: Atlantis (OV-104) 

Altitude: 230 n.m. x 230 n.m. (EURECA deploy) 

160 n.m. x 160 n.m. (TSS operations) 

128 n.m. x 128 n.m. (EOIM operations) 

 

Inclination: 28.5 degrees 

 

Landing Date: August 7, 1992 

 

Landing Time: 8:05 a.m. EDT 

 

Primary Landing Site: Kennedy Space Center, FL. 

 

Return to Launch Site: Return to Launch Site - Kennedy Space Center, Fla. 

Transoceanic Abort Landing -- Banjul, The Gambia 

Alternates: Ben Guerir, Morocco; Moron, Spain 

 Abort Once Around: Edwards Air Force Base, Calif. 

 

Crew: Loren Shriver, Commander 

 Andy Allen, Pilot 

 Claude Nicollier, Mission Specialist 1 

 Marsha Ivins, Mission Specialist 2 

 Jeff Hoffman, Mission Specialist 3 

 Franklin Chang-Diaz, Mission Specialist 4 

 Franco Malerba, Payload Specialist 1 

 

Operational shifts: Red team -- Ivins, Hoffman, Chang-Diaz 

 Blue team -- Nicollier, Allen, Malerba 

 

Cargo Bay Payloads: TSS-1 (Tethered Satellite System-1) 

 EURECA-1L (European Retrievable Carrier-1L) 

 EOIM-III/TEMP 2A (Evaluation of Oxygen Integration with Materials/Thermal 

Management Processes) 

 CONCAP II (Consortium for Materials Development in Space Complex 

Autonomous Payload 

 CONCAP III 

 ICBC (IMAX Cargo Bay Camera) 

 LDCE (Limited Duration Space 

 Environment Candidate Materials Exposure) 

 

Middeck Payloads: AMOS (Air Force Maui Optical Site) 

 PHCF (Pituitary Growth Hormone Cell Function) 

 UVPI (Ultraviolet Plume Instrument) 
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STS-46 SUMMARY OF MAJOR ACTIVITIES 

Blue Team Flight Day One: Red Team Flight Day One: 

 Launch 

 Orbit insertion (230 x 230 n.m.) 

 TSS activation 

 RMS checkout 

 TSS deployer checkout 

 EOIM/TEMP-2A activation 

Blue Flight Day Two: Red Flight Day Two: 

EURECA deploy TEMP-2A operations 

EURECA stationkeeping checkout Tether Optical Phenomenon (TOP) 

 

Blue Flight Day Three: Red Flight Day Three: 

TOP checkout TSS checkout/in-bay operations 

Supply water dump nozzle DTO 

TEMP-2A operations 

OMS-3 burn 

OMS-4 burn (160 x 160 n.m.) 

 

Blue Flight Day Four: Red Flight Day Four: 

TSS in-bay operations TSS deploy 

TEMP-2A operations 

 

Blue Flight Day Five: Red Flight Day Five: 

TSS on station 1 (12.5 miles) TSS retrieval to 1.5 miles 

TSS final retrieval 

 TSS dock 

 

Blue Flight Day Six: Red Flight Day Six: 

TSS safing EOIM/TEMP-2A operations 

TSS in-bay operations 

OMS-5 burn 

OMS-6 burn (128 x 128 n.m.) 

 

Blue Flight Day Seven: Red Flight Day Seven: 

TSS science deactivation EOIM/TEMP-2A operations 

EOIM/TEMP-2A operations Flight Control Systems checkout 

Reaction Control System hot-fire 

 

Blue Flight Day Eight: Red Flight Day Eight: 

 Cabin stow 

 Deorbit preparations 

 Entry and landing 
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VEHICLE AND PAYLOAD WEIGHTS 

Pounds

Orbiter (Atlantis) empty, and 3 SSMEs 151,377 

 

Tethered Satellite -- pallet, support equipment 10,567 

Tethered Satellite -- satellite, tether 1,476 

European Retrievable Carrier 9,901 

EURECA Support Equipment 414 

Evaluation of Oxygen Interaction with Materials 2,485 

CONCAP-II 590 

CONCAP-III 368 

LDCE 1,125 

PHDF 69 

Detailed Supplementary Objectives 56 

Detailed Test Objectives 42 

Total Vehicle at SRB Ignition 4,522,270 

Orbiter Landing Weight 208,721 
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STS-46 TRAJECTORY SEQUENCE OF EVENTS 

Event 

MET 

(d/h:m:s 

Relative 

Velocity

(fps) Mach 

Altitude 

(ft) 

 

Launch 00/00:00:00 

Begin Roll Maneuver 00/00:00:10 189 0.16 797 

End Roll Maneuver 00/00:00:15 325 0.29 2,260 

SSME Throttle Down to 80% 00/00:00:26 620 0.55 6,937 

SSME Throttle Down to 67% 00/00:00:53 1,236 1.20 28,748 

SSME Throttle Up to 104% 00/00:01:02 1,481 1.52 37,307 

Maximum Dynamic Press. 00/00:01:04 1,548 1.61 41,635 

SRB Separation 00/00:02:04 4,221 4.04 152,519 

Main Engine Cutoff (MECO) 00/00:08:29 24,625 22.74 364,351 

Zero Thrust 00/00:08:35 24,624 N/A 363,730 

ET Separation 00/00:08:48 

OMS-2 Burn 00/00:41:24 

Landing 06/22:11:00 

Apogee, Perigee at MECO: 226 x 32 nautical miles 

Apogee, Perigee post-OMS 2: 230 x 230 nautical miles 
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SPACE SHUTTLE ABORT MODES

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

its payload. Abort modes include: 

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

105-nautical mile orbit with orbital maneuvering system engines. 

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

around before landing at either Edwards Air Force Base, Calif., White Sands Space Harbor, NM, or 

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

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

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

• Return-To-Launch-Site (RTLS) -- Early shutdown of one or more engines, 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-46 contingency landing sites are Edwards Air Force Base, the Kennedy Space Center, White Sands 

Space Harbor, Banjul, Ben Guerir and Moron. 
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STS-46 PRE-LAUNCH PROCESSING 

KSC's processing team began readying the orbiter Atlantis for its 12th flight into space following its STS45 flight which ended with a landing at KSC on April 2. Atlantis was in the Orbiter Processing Facility 

from April 2 to June 4, undergoing post-flight inspections and pre-flight testing and inspections. While in 

the OPF, technicians installed the three main engines. Engine 2024 is in the No. 1 position, engine 2012 is 

in the No. 2 position and engine 2028 is in the No. 3 position. 

The remote manipulator system was installed on Apr. 28. Members of the STS-46 flight crew participated 

in the Crew Equipment Interface Test on May 16. 

Atlantis was towed from the Orbiter Processing Facility (OPF) on June 4 to the Vehicle Assembly Building 

where it was mated to its external tank and solid rocket boosters on the same day. Rollout to Launch Pad 

39-B occurred on June 11, 1992. On June 15-16, the Terminal Countdown Demonstration Test with the 

STS-46 flight crew was conducted. 

The Tethered Satellite System (TSS) was processed for flight in the Operations and Checkout Building 

high bay and the EURECA payload was processed at the commercial Astrotech facility in Titusville, FL. 

The two primary payloads were installed in the payload canister at the Vertical Processing Facility before 

they were transferred to the launch pad. 

Payload installation into Atlantis' payload bay was scheduled for late June. Several interface verification 

tests were scheduled between the orbiter and the payload elements. A standard 43-hour launch countdown 

is scheduled to begin 3 days prior to launch. During the countdown, the orbiter's fuel cell storage tanks will 

be loaded with fuel and oxidizer and all orbiter systems will be prepared for flight. 

About 9 hours before launch, the external tank will be filled with its flight load of a half million gallons of 

liquid oxygen and liquid hydrogen propellants. About 2 and one-half hours before liftoff, the flight crew 

will begin taking their assigned seats in the crew cabin. 

Atlantis's end-of-mission landing is planned at Kennedy Space Center. Several hours after landing, the 

vehicle will be towed to the Vehicle Assembly Building for a few weeks until an OPF bay becomes 

available. Atlantis will be taken out of flight status for several months for a planned modification period. 

Atlantis' systems will be inspected and improved to bring the orbiter up to par with the rest of the Shuttle 

fleet. 

Atlantis's next flight, STS-57, is planned next year with the first flight of the Spacehab payload and the 

retrieval of the EURECA payload deployed on the STS-46 mission. 
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TETHERED SATELLITE SYSTEM (TSS-1) 

An exciting new capability for probing the space environment and conducting experiments will be 

demonstrated for the first time when the NASA/Italian Space Agency Tethered Satellite System (TSS-1) is 

deployed during the STS-46 Space Shuttle flight. The reusable Tethered Satellite System is made up of a 

satellite attached to the Shuttle orbiter by a super strong cord which will be reeled into space from the 

Shuttle's cargo bay. When the satellite on its cord, or tether, is deployed to about 12 miles above the 

orbiter, TSS-1 will be the longest structure ever flown in space. 

Operating the tethered system is a bit like trolling for fish in a lake or the ocean. But the potential "catch" is 

valuable data that may yield scientific insights from the vast sea of space. For the TSS-1 mission, the tether 

-- which looks like a 12-mile-long white bootlace -- will have electrically-conducting metal strands in its 

core. The conducting tether will generate electrical currents at a high voltage by the same basic principle as 

a standard electrical generator -- by converting mechanical energy (the Shuttle's more than 17,000-mile-anhour orbital motion) into electrical energy by passing a conductor through a magnetic field (the Earth's 

magnetic field lines). 

TSS-1 scientific instruments, mounted in the Shuttle cargo bay, the middeck and on the satellite, will allow 

scientists to examine the electrodynamics of the conducting tether system, as well as clarify their 

understanding of physical processes in the ionized plasma of the near-Earth space environment. 

Once the investigations are concluded, it is planned to reel the satellite back into the cargo bay and stow it 

until after the Shuttle lands. 

The TSS-1 mission will be the first step toward several potential future uses for tethers in space now being 

evaluated by scientists and engineers. One possible application is using long conducting tethers to generate 

electrical power for Space Station Freedom or other orbiting bodies. Conversely, by expending electrical 

power to reverse the current flow into a tether, the system can be placed in an "electric motor" mode to 

generate thrust for orbit maintenance. Tethers also may be used to raise or lower spacecraft orbits. This 

could be achieved by releasing a tethered body from a primary spacecraft, thereby transferring momentum 

(and imparting motion) to the spacecraft. Another potential application is the creation of artificial gravity 

by rotating two or more masses on a tether, much like a set of bolas. 

Downward deployment (toward Earth) could place a satellite in regions of the atmosphere that have been 

difficult to study because they lie above the range of high-altitude balloons and below the minimum 

altitude of free-flying satellites. Deploying a tethered satellite downward from the Shuttle also could make 

possible aerodynamic and wind tunnel type testing in the region 50 to 75 nautical miles above the Earth. 

Mission Objectives 

Space-based tethers have been studied theoretically since early in this century. More recently, the projected 

performance of such systems has been modeled extensively on computers. In 1984, the growing interest in 

tethered system experiments resulted in the signing of an agreement between NASA and the Italian Space 

Agency (Agenzia Spaziale Italiana - ASI) to jointly pursue the definition and development of a Tethered 

Satellite System to fly aboard the Space Shuttle. Scientific investigations (including hardware experiments) 

were selected in 1985 in response to a joint NASA/ASI announcement of opportunity. 

The TSS-1 mission will be the first time such a large, electrodynamic tethered system has ever been flown. 

In many respects, the mission is like the first test flight of a new airplane: the lessons learned will improve 

both scientific theory and operations for future tether missions. 
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Edited by Richard W. Orloff, 01/2001/Page 17 

The primary objectives of the first tethered satellite mission are to evaluate the capability to safely deploy, 

control and retrieve a tethered satellite, to validate predictions of the dynamic forces at work in a tethered 

satellite system and to conduct exploratory electrodynamic science investigations and demonstrate the 

capability of the system to serve as a facility for research in geophysical and space physics. 

Since the dynamics of the Tethered Satellite System are complex and only can be tested fully in orbit, it is 

impossible to predict before the mission exactly how the system will perform in the space environment. 

Though tether system dynamics have been extensively tested and simulated, it could be that actual 

dynamics will differ somewhat from predictions. The complexity of a widely separated, multi-component 

system and the forces created by the flow of current through the system are other variables that will affect 

the system's performance. 

Responsibilities 

Responsibility for Tethered Satellite System activities within NASA is divided between the Marshall Space 

Flight Center, Huntsville, AL, and the Johnson Space Center, Houston. Marshall has the development and 

integration responsibility. Marshall also is responsible for developing and executing the TSS-1 science 

mission, and science teams for each of the 12 experiments work under that center's direction. During the 

mission, Johnson will be responsible for the operation of the TSS-1 payload. This includes deployment and 

retrieval of the satellite by the crew as well as controlling Spacelab pallet, the deployer and the satellite. 

Marshall will furnish real-time engineering support for the TSS-1 system components and tether dynamics. 

ASI is furnishing satellite engineering and management support. All remote commanding of science 

instruments aboard the satellite and deployer will be executed by a Marshall payload operations control 

cadre stationed at Johnson for the mission. 

Tethered Satellite System Hardware 

The Tethered Satellite System has five major components: the deployer system, the tether, the satellite, the 

carriers on which the system is mounted and the science instruments. Under the 1984 memorandum of 

understanding, the Italian Space Agency agreed to provide the satellite and NASA agreed to furnish the 

deployer system and tether. The carriers are specially adapted Spacelab equipment, and the science 

instruments were developed by various universities, government agencies and companies in the United 

States and Italy. 

Carriers 

TSS-1 hardware rides on two carriers in the Shuttle cargo bay. The deployer is mounted on a Spacelab 

Enhanced Multiplexer-Demultiplexer pallet, a general-purpose unpressurized platform equipped to provide 

structural support to the deployer, as well as temperature control, power distribution and command and 

data transmission capabilities. The second carrier is the Mission Peculiar Equipment Support Structure, an 

inverted A-frame truss located immediately aft of the enhanced pallet. The support structure, also 

Spacelab-provided, holds science support equipment and two of the TSS-1 science experiments. 
Edited by Richard W. Orloff, 01/2001/Page 18 
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Edited by Richard W. Orloff, 01/2001/Page 20 

DEPLOYER 

The deployer system includes the structure supporting the satellite, the deployment boom, which initially 

lifts the satellite away from the orbiter, the tether reel, a system that distributes power to the satellite before 

deployment and a data acquisition and control assembly. 

Cables woven through the structure provide power and data links to the satellite until it is readied for 

release. When the cables are disconnected after checkout, the satellite operates on its internal battery 

power. If the safety of the orbiter becomes a concern, the tether can be cut and the satellite released or the 

satellite and boom jettisoned. 

The boom, with the satellite resting atop it, is housed in a canister in the lower section of the satellite 

support structure. As deployment begins, the boom will unfold and extend slowly out of the turning 

canister, like a bolt being forced upward by a rotating nut. As the upward part of the canister rotates, 

horizontal cross members (fiberglass battens similar to those that give strength to sails) are unfolded from 

their bent-in-half positions to hold the vertical members (longerons) erect. Additional strength is provided 

by diagonal tension cables. The process is reversed for retrieval. When it is fully extended, the 40-foot 

boom resembles a short broadcasting tower. 

The tether reel mechanism regulates the tether's length, tension and rate of deployment -- critical factors for 

tether control. Designed to hold up to 68 miles of tether, the reel is 3.3 feet in diameter and 3.9 feet long. 

The reel is equipped with a "level-wind" mechanism to assure uniform winding on the reel, a brake 

assembly for control of the tether and a drive motor. The mechanism is capable of letting out the tether at 

up to about 10 miles per hour. However, for the TSS-1 mission, the tether will be released at a much 

slower rate, about 2.5 miles per hour. 

Tether 

The tether's length and electrical properties affect all aspects of tethered operations. For the TSS-1 mission, 

the tether will be reeled out to an altitude about 12 miles above the Shuttle, making the TSS-1/orbiter 

combination 100 times longer than any previous spacecraft. It will create a large current system in the 

ionosphere, similar to natural currents in the Earth's polar regions associated with the aurora borealis. 

When the tether's current is pulsed by electron accelerators, it becomes the longest and lowest frequency 

antenna ever placed in orbit. Also, for the first time, scientists can measure the level of charge or electric 

potential acquired by a spacecraft as a result of its motion through the Earth's magnetic field lines. All these 

capabilities are directly related to the structure of the bootlace-thick tether, a conducting cord designed to 

anchor a satellite miles above the orbiter. 

The TSS-1 tether is 13.6 miles long. When deployed, it is expected to develop a 5,000-volt electrical 

potential and carry a maximum current of 1 ampere. At its center is the conductor, a 10-strand copper 

bundle wrapped around a Nomex (nylon fiber) core. The wire is insulated with a layer of Teflon, then 

strength is provided with a layer of braided Kevlar -- a tough, light synthetic fiber also used for making 

bulletproof vests. An outer braid of Nomex protects the tether from atomic oxygen. The cable is about 0.1 

inch in diameter. 

Satellite 

Developed by the Italian Space Agency, the spherical satellite is a little more than 5 feet in diameter and is 

latched atop the deployer's satellite support structure. The six latches are released when boom extension is 

initiated. After the satellite is extended some 40 feet above the orbiter atop the boom, tether unreeling will 

begin. 
Edited by Richard W. Orloff, 01/2001/Page 21 

The satellite is divided into two hemispheres. The payload module (the upper half of the sphere opposite 

the tether) houses satellite-based science instruments. Support systems for power distribution, data 

handling, telemetry and navigational equipment are housed in the service module or lower half. Eight 

aluminum-alloy panels, covered with electrically conductive paint, developed at the Marshall Space Flight 

Center, form the outer skin of the satellite. Doors in the panels provide access for servicing batteries; 

windows for sun, Earth and charged-particle sensors; and connectors for cables from the deployer. 

A fixed boom for mounting science instruments extends some 39 inches from the equator of the satellite 

sphere. A short mast opposite the boom carries an S-band antenna for sending data and receiving 

commands. For the TSS-1 mission, the satellite is outfitted with two additional instrument-mounting 

booms on opposite sides of the sphere. The booms may be extended up to 8 feet from the body of the 

satellite, allowing instruments to sample the surrounding environment, then be pulled back inside before 

the satellite is reeled back to the Shuttle. 

Motion of the tethered satellite is controlled by its auxiliary propulsion module, in conjunction with the 

deployer's tether reel and motor. The module also initiates, maintains and controls satellite spin at up to 0.7 

revolution per minute on command from the Shuttle. One set of thrusters near the tether attachment can 

provide extra tension on the tether, another can be used to reduce or eliminate pendulum-type motions in 

the satellite, and a third will be used to spin and de-spin the satellite. A pressurized tank containing gaseous 

nitrogen for the thrusters is located in the center of the sphere. 
Edited by Richard W. Orloff, 01/2001/Page 22 
Edited by Richard W. Orloff, 01/2001/Page 23 
Edited by Richard W. Orloff, 01/2001/Page 24 

TETHERED SATELLITE SYSTEM-1 FLIGHT OPERATIONS 

The responsibility for flying the tethered satellite, controlling the stability of the satellite, tether and 

Atlantis, lies with the flight controllers in the Mission Control Center at the Johnson Space Center, 

Houston. 

The primary flight control positions contributing to the flight of the Tethered Satellite System (TSS) are the 

Guidance and Procedures (GPO) area and the Payloads area. GPO officers will oversee the dynamic phases 

of deployment and retrieval of the satellite and are responsible for determining the correct course of action 

to manage any tether dynamics. To compute corrective actions, the GPO officers will combine data from 

their workstations with inputs from several investigative teams. 

The Payloads area will oversee control of the satellite systems, the operation of the tether deployer and all 

other TSS systems. Payloads also serves as the liaison between Mission Control Center and the science 

investigators, sending all real-time commands for science operations to the satellite. Atlantis' crew will 

control the deployer reel and the satellite thrusters from onboard the spacecraft. 

Deploy Operations 

The satellite will be deployed from Atlantis when the cargo bay is facing away from Earth, with the tail 

slanted upward and nose pitched down. A 39-foot long boom, with the satellite at its end, is raised out of 

the cargo bay to provide clearance between the satellite and Shuttle during deploy and retrieval operations. 

The orientation of the payload bay will result in the tethered satellite initially deployed upward but at an 

angle of about 40 degrees behind Atlantis' path. 

Using the tether reel's electric motors to unwind the tether, an electric motor at the end of the boom to pull 

the tether off of the reel and a thruster on the satellite that pushes the satellite away from Atlantis, the 

satellite will be moved away from the Shuttle. The deploy will begin extremely slowly, with the satellite, 

after 1 hour has elapsed since the tether was first unwound, moving away from Atlantis at about one-half 

mile per hour. The initial movement of the satellite away from the boom will be at less than twohundredths of 1 mile per hour. The speed of deploy will continue to increase, peaking after 1 and a half 

hours from the initial movement to almost 4 miles per hour. 

At this point, when the satellite is slightly less than 1 mile from Atlantis, the rate of deployment will begin 

slowing briefly, a maneuver that is planned to reduce the 40-degree angle to 5 degrees and put the satellite 

in the same plane almost directly overhead of Atlantis by the time that about 3 miles of tether has been 

unwound. 

When the satellite is 3.7 miles from Atlantis, 2 and one-half hours after the start of deployment, a onequarter of a revolution-per-minute spin will be imparted to it via its attitude control system thrusters. The 

slight spin is needed for science operations with the satellite. 

After this, the speed of deployment will again be increased gradually, climbing to a peak separation from 

Atlantis of almost 5 mph about 4 hours into the deployment when the satellite is about 9 miles distant. 

From this point, the speed with which the tether is fed out will gradually decrease through the rest of the 

procedure, coming to a stop almost 5 and half hours after the initial movement, when the satellite is almost 

12.5 miles from Atlantis. Just prior to the satellite arriving on station at 12.5 miles distant, the quarterrevolution spin will be stopped briefly to measure tether dynamics and then, a seven-tenths of a revolutionper-minute spin will be imparted to it. At full deploy, the tension on the tether or the pull from the satellite 

is predicted to be equivalent to about 10 pounds of force. 
Edited by Richard W. Orloff, 01/2001/Page 25 

The tether, in total, is 13.7 miles long, allowing an extra 1.2 miles of spare tether that is not planned to be 

unwound during the mission. 

Dynamics Functional Objectives 

During the deploy of TSS, several tests will be conducted to explore control and dynamics of a tethered 

satellite. Models of deployment have shown that the longer the tether becomes, the more stable the system 

becomes. The dynamics and control tests to be conducted during deploy also will aid in preparing for 

retrieval of the satellite and serve to verify the ability to control the satellite during that operation. During 

retrieval, it is expected that the stability of the system will decrease as the tether is shortened, just opposite 

the way stability increased as the tether was lengthened during deploy. 

The dynamics tests involve maintaining a constant tension on the tether and correcting any of several 

possible disturbances to it. Possible disturbances include: a bobbing motion, also called a plumb bob, 

where the satellite bounces slightly on the tether causing it to alternately slacken and tighten; a vibration of 

the tether, called a libration, resulting in a clock-pendulum type movement of tether and satellite; a 

pendulous motion of the satellite or a rolling and pitching action by the satellite at the end of the tether; and 

a lateral string mode disturbance, a motion where the satellite and Shuttle are stable, but the tether is 

moving back and forth in a "skip rope" motion. All of these disturbances may occur naturally and are not 

unexpected. However, some disturbances will be induced intentionally. 

The first test objectives will be performed before the satellite reaches 200 yards from Atlantis and will 

involve small firings of Atlantis' steering jets to test the disturbances these may impart to the tether and 

satellite. The crew will test three different methods of damping the libration (clock pendulum) motion 

expected to be created in the tether and the pendulous (rolling and pitching) motion expected in the 

satellite. First, using visual contact with the satellite, to manually stabilize it from onboard the Shuttle by 

remotely firing TSS's attitude thrusters. Second, using the telemetry information from the satellite to 

manually fire the satellite's attitude thrusters. Third, using an automatic attitude control system for the 

satellite via the Shuttle's flight control computers to automatically fire the TSS thrusters and stabilize the 

system. 

Another test will be performed when the satellite is about 2.5 miles from Atlantis. Atlantis' autopilot will 

be adjusted to allow the Shuttle to wobble by as much as 10 degrees in any direction before steering jets 

automatically fire to maintain Atlantis' orientation. The 10-degree deadband will be used to judge any 

disturbances that may be imparted to the satellite if a looser attitude control is maintained by Atlantis. The 

standard deadband, or degree of wobble, set in Shuttle autopilot for the tethered satellite operations is 2 

degrees of wobble. Tests using the wider deadband will allow the crew and flight controllers to measure 

the amount of motion the satellite and tether impart to Atlantis. 

When the satellite is fully deployed and on station at 12.5 miles, Atlantis will perform jet firings to judge 

disturbances imparted to the tether and satellite at that distance. 

Dampening of the various motions expected to occur in the tether and satellite will be accomplished while 

at 12.5 miles using electrical current flow through the tether. During retrieval, test objectives will be met 

using a combination of the Shuttle's steering jets, a built-in dampening system at the end of the deploy 

boom and the satellite's steering jets. 

Tether Retrieval Operations 

Satellite retrieval will occur more slowly than deployment. The rate of tether retrieval, the closing rate 

between Atlantis and the satellite, will build after 5 hours since first movement to a peak rate of about 3 

miles per hour. At that point, when the satellite is about 4 and a half miles from Atlantis, the rate of 

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

will gradually decrease, coming to a halt 10 hours after start of retrieval operations when the satellite is 1.5 

miles from Atlantis. 

The satellite will remain at 1.5 miles from Atlantis for about 5 hours of science operations before the final 

retrieval begins. Final retrieval of the satellite is expected to take about 2 hours. A peak rate of closing 

between Atlantis and the satellite of about 1.5 miles per hour will be attained just after the final retrieval 

begins, and the closing rate will decrease gradually through the remainder of the operation. The closing 

rate at the time the satellite is docked to the cradle at the end of the deployer boom is planned to be less 

than one-tenth of 1 mile per hour. 

If the safety of the orbiter becomes a concern, the tether will be cut and the satellite released or the satellite 

and boom jettisoned. 
Edited by Richard W. Orloff, 01/2001/Page 27 

TSS-1 SCIENCE OPERATIONS 

Speeding through the magnetized ionospheric plasma at almost 5 miles per second, a 12-mile-long 

conducting tethered system should create a variety of very interesting plasma-electrodynamic phenomena. 

These are expected to provide unique experimental capabilities, including the ability to collect an electrical 

charge and drive a large current system within the ionosphere; generate high voltages (on the order of 5 

kilovolts) across the tether at full deployment; control the satellite's electrical potential and its plasma 

sheath (the layer of charged particles created around the satellite); and generate low-frequency electrostatic 

and electromagnetic waves. It is believed that these capabilities can be used to conduct controlled 

experimental studies of phenomena and processes that occur naturally in plasmas throughout the solar 

system, including Earth's magnetosphere. 

A necessary first step toward these studies -- and the primary science goal of the TSS-1 mission -- is to 

characterize the electrodynamic behavior of the satellite-tether-orbiter system. Of particular interest is the 

interaction of the system with the charged particles and electric and magnetic fields in the ionosphere. 

A circuit must be closed to produce an electrical current. For example, in a simple circuit involving a 

battery and a light bulb, current travels down one wire from the battery to the bulb, through the bulb and 

back to the battery via another wire completing the circuit. Only when the circuit is complete will the bulb 

illuminate. The conductive outer skin of the satellite collects free electrons from the space plasma, and the 

induced voltage causes the electrons to flow down the conductive tether to the Shuttle. Then, they will be 

ejected back into space with electron guns. 

Scientists expect the electrons to travel along magnetic field lines in the ionosphere to complete the loop. 

TSS-1 investigators will use a series of interdependent experiments conducted with the electron guns and 

tether current-control hardware, along with a set of diagnostic instruments, to assess the nature of the 

external current loop within the ionosphere and the processes by which current closure occurs at the 

satellite and the orbiter. 

Science Operations 

The TSS-1 mission is comprised of 11 scientific investigations selected jointly by NASA and the Italian 

Space Agency. In addition, the U.S. Air Force's Phillips Laboratory, by agreement, is providing an 

experimental investigation. Seven investigations provide equipment that either stimulates or monitors the 

tether system and its environment. Two investigations will use ground-based instruments to measure 

electromagnetic emissions from the Tethered Satellite System as it passes overhead, and three 

investigations were selected to provide theoretical support in the areas of dynamics and electrodynamics. 

Most of the TSS-1 experiments require measurements of essentially the same set of physical parameters, 

with instrumentation from each investigation providing different parts of the total set. While some 

instruments measure magnetic fields, others record particle energies and densities, and still others map 

electric fields. A complete set of data on plasma and field conditions is required to provide an accurate 

understanding of the space environment and its interaction with the tether system. TSS-1 science 

investigations, therefore, are interdependent. They must share information and operations to achieve their 

objectives. In fact, these investigations may be considered to be different parts of a single complex 

experiment. 

The TSS-1 principal and associate investigators and their support teams will be located in a special Science 

Operations Center at the Mission Control Center in Houston. During the tethered satellite portion of the 

STS-46 flight, all 12 team leaders will be positioned at a conference table in the operations center. Science 

data will be available to the entire group, giving them an integrated "picture" of conditions observed by all 

the instruments. Together, they will assess performance of the experiment objectives. Commands to change 

any instrument mode that affects the overall data set must be approved by the group, because such a change 
Edited by Richard W. Orloff, 01/2001/Page 28 

could impact the overall science return from the mission. Requests for adjustments will be relayed by the 

mission scientist, the group's leader, to the science operations director for implementation. 

The primary scientific data will be taken during the approximately 10.5-hour phase (called "on-station 1") 

when the satellite is extended to the maximum distance above the Shuttle. Secondary science 

measurements will be taken prior to and during deployment, during "on-station 1," and as the satellite is 

reeled back to the orbiter. However, during the latter phase, satellite recovery has a higher priority than 

continued science data gathering. 

Science activities during the TSS-1 mission will be directed by the science principal investigator team and 

implemented by a payload cadre made up primarily of Marshall Space Flight Center employees and their 

contractors. Science support teams for each of the 12 experiments will monitor the science hardware status. 

From the Science Operations Center at Mission Control, the principal investigator team will be able to 

evaluate the quality of data obtained, replan science activities as needed and direct adjustments to the 

instruments. The cadre will be led by a science operations director, who will work closely with the mission 

scientist, the mission manager and Mission Control's payloads officer to coordinate science activities. 

During the mission, most activities not carried out by the crew will be controlled by command sequences, 

or timeline files, written prior to the mission and stored in an onboard computer. For maximum flexibility, 

however, during all TSS phases, modifications to these timeline files may be uplinked, or commands may 

be sent in real-time from the Science Operations Center to the on-board instruments. 
Edited by Richard W. Orloff, 01/2001/Page 29 

SCIENCE INVESTIGATIONS 

TSS Deployer Core Equipment and Satellite Core Equipment (DCORE/SCORE) 

Principal Investigator: 

Dr. Carlo Bonifazi 

Italian Space Agency, Rome, Italy 

The Tethered Satellite System Core Equipment controls the electrical current flowing between the satellite 

and the orbiter. It also makes a number of basic electrical and physical measurements of the system. 

Mounted on the aft support structure in the Shuttle cargo bay, the Deployer Core Equipment features an 

electron accelerator with two electron beam emitters that can each eject up to 500 milli-amperes (one-half 

amp) of current from the system. A master switch, power distribution and electronic control unit, and 

command and data interfaces also are included in the deployer core package. A voltmeter measures tether 

potential with respect to the orbiter structure, and a vacuum gauge measures ambient gas pressure to 

prevent operations if pressure conditions might cause electrical arcing. 

Core equipment located on the satellite itself includes an accelerometer to measure satellite movements and 

an ammeter to measure tether current collected on the skin of the TSS-1 satellite. 

Research on Orbital Plasma Electrodynamics (ROPE) 

Principal Investigator: 

Dr. Nobie Stone 

NASA Marshall Space Flight Center, Huntsville, AL 

This experiment studies behavior of ambient charged particles in the ionosphere and ionized neutral 

particles around the satellite under a variety of conditions. Comparisons of readings from its instruments 

should allow scientists to determine where the particles come from that make up the tether current as well 

as the distribution and flow of charged particles in the space immediately surrounding the satellite. 

The Differential Ion Flux Probe, mounted on the end of the satellite's fixed boom, measures the energy, 

temperature, density and direction of ambient ions that flow around the satellite as well as neutral particles 

that have been ionized in its plasma sheath and accelerated outward by the sheath's electric field. 

The Soft Particle Energy Spectrometer is actually five electrostatic analyzers -- three mounted at different 

locations on the surface of the satellite itself, and the other two mounted with the Differential Ion Flux 

Probe on the boom. Taken together, measurements from the two boom-mounted sensors can be used to 

determine the electrical potential of the sheath of ionized plasma surrounding the satellite. The three 

satellite-mounted sensors will measure geometric distribution of the current to the satellite's surface. 

Research on Electrodynamic Tether Effects (RETE) 

Principal Investigator: 

Dr. Marino Dobrowolny 

Italian National Research Council, Rome, Italy 

This experiment measures the electrical potential in the plasma sheath around the satellite and identifies 

waves excited by the satellite and tether system. The instruments are located in two canisters at the end of 

the satellite's extendible booms. As the satellite spins, the booms are extended, and the sensors sweep the 

plasma around the entire circumference of the spacecraft. To produce a profile of the plasma sheath, 

measurements of direct-current potential and electron currents are made both while the boom is fully 

extended and as it is being extended or retracted. The same measurements, taken at a fixed distance from 

the spinning satellite, produce a map of the angular structure of the sheath. 
Edited by Richard W. Orloff, 01/2001/Page 30 

Magnetic Field Experiment for TSS Missions (TEMAG) 

Principal Investigator: 

Prof. Franco Mariani 

Second University of Rome, Italy 

The primary goal of this investigation is to map the levels and fluctuations in magnetic fields around the 

satellite. Two magnetometers -- very accurate devices for measuring such fields -- are located on the fixed 

boom of the satellite, one at its end and the other at its midpoint. Comparing measurements from the two 

magnetometers allows real-time estimates to be made of unwanted disturbances to the magnetic fields 

produced by the presence of satellite batteries, power systems, gyros, motors, relays and other magnetic 

material. After the mission, the variable effects of switching satellite subsystems on and off, of thruster 

firings and of other operations that introduce magnetic disturbances will be modeled on the ground, so 

these satellite effects can be subtracted from measurements of the ambient magnetic fields in space. 

Shuttle Electrodynamic Tether System (SETS) 

Principal Investigator: 

Dr. Peter Banks 

University of Michigan, Ann Arbor 

This investigation studies the ability of the tethered satellite to collect electrons by determining current and 

voltage of the tethered system and measuring the resistance to current flow in the tether itself. It also 

explores how tether current can be controlled by the emission of electrons at the orbiter end of the system 

and characterizes the charge the orbiter acquires as the tether system produces power, broadcasts lowfrequency radio waves and creates instabilities in the surrounding plasma. 

The hardware is located on the support structure in the orbiter cargo bay. In addition to three instruments to 

characterize the orbiter's charge, the experiment includes a fast-pulse electron accelerator used to help 

neutralize the orbiter's charge. It is located close to the core electron gun and aligned so beams from both 

are parallel. The fast-pulse accelerator acts as a current modulator, emitting electron beams in recognizable 

patterns to stimulate wave activity over a wide range of frequencies. The beams can be pulsed with on/off 

times on the order of 100 nanoseconds. 

Shuttle Potential and Return Electron Experiment (SPREE) 

Associate Investigators: 

Dr. Dave Hardy and Capt. Marilyn Oberhardt 

Dept. of the Air Force, Phillips Laboratory, Bedford, Mass. 

Also located on the support structure, this experiment will measure populations of charged particles around 

the orbiter. Measurements will be made prior to deployment to assess ambient space conditions as well as 

during active TSS-1 operations. The measurements will determine the level of orbiter charging with respect 

to the ambient space plasma, characterize the particles returning to the orbiter as a result of TSS-1 electron 

beam ejections and investigate local wave-particle interactions produced by TSS-1 operations. Such 

information is important in determining how the Tethered Satellite System current is generated, and how it 

is affected by return currents to the orbiter. The experiment uses two sets of two nested electrostatic 

analyzers each, which rotate at approximately 1 revolution per minute, sampling the electrons and ions in 

and around the Shuttle's cargo bay. 
Edited by Richard W. Orloff, 01/2001/Page 31 

Tether Optical Phenomena Experiment (TOP) 

Associate Investigator: 

Dr. Stephen Mende 

Lockheed, Palo Alto Research Laboratory, Palo Alto, Calif. 

This experiment uses a hand-held, low-light-level TV camera system operated by the crew, to provide 

visual data to allow scientists to answer a variety of questions about tether dynamics and optical effects 

generated by TSS-1. The imaging system will operate in four configurations: filtered, interferometer, 

spectrographic and filtered with a telephoto lens. In particular, the experiment will image the high voltage 

plasma sheath surrounding the satellite when it is reeled back toward the orbiter near the end of the 

retrieval stage of the mission. 

Investigation of Electromagnetic Emissions for Electrodynamic Tether (EMET) 

Principal Investigator: 

Dr. Robert Estes 

Smithsonian Astrophysical Observatory, Cambridge, Mass. 

Observations at the Earth's Surface of Electromagnetic Emission by TSS (OESEE) 

Principal Investigator: 

Dr. Giorgio Tacconi 

University of Genoa, Italy 

The main goal of these experiments is to determine how well the Tethered Satellite System can broadcast 

from space. Ground-based radio transmissions, especially below 15 kilohertz, are inefficient since most of 

the power supplied to the antenna -- large portions of which are buried -- is absorbed by the ground. Since 

the Tethered Satellite System operates in the ionosphere, it should radiate waves more efficiently. 

Magnetometers at several locations in a chain of worldwide geomagnetic observatories and extremely lowfrequency receivers at the Arecibo Radio Telescope facility, Puerto Rico, and other sites around the world, 

will try to measure the emissions produced and track direction of the waves when electron accelerators 

pulse tether current over specific land reference points. An Italian ocean surface and ocean bottom 

observational facility also provides remote measurements for TSS-1 emissions. 

The Investigation and Measurement of Dynamic Noise in the TSS (IMDN) 

Principal Investigator: 

Dr. Gordon Gullahorn 

Smithsonian Astrophysical Observatory, Cambridge, Mass. 

Theoretical and Experimental Investigation of TSS Dynamics (TEID) 

Principal Investigator: 

Prof. Silvio Bergamaschi 

Institute of Applied Mechanics, Padua University, Padua, Italy 

These two investigations will analyze data from a variety of instruments to examine Tethered Satellite 

System dynamics or oscillations over a wide range of frequencies. Primary instruments will be 

accelerometers and gyros on board the satellite, but tether tension and length measurements and magnetic 

field measurements also will be used. The dynamics will be observed in real-time at the Science Operations 

Center and later, subjected to detailed post-flight analysis. Basic theoretical models and simulations of 

tether movement will be verified, extended or corrected as required. Then they can be used confidently in 

the design of future systems. 
Edited by Richard W. Orloff, 01/2001/Page 32 

Theory and Modeling in Support of Tethered Satellite Applications (TMST) 

Principal Investigator: 

Dr. Adam Drobot 

Science Applications International Corp., McLean, VA 

This investigation provides theoretical electro-dynamic support for the mission. Numerical models were 

developed of anticipated current and voltage characteristics, plasma sheaths around the satellite and the 

orbiter and of the system's response to the operation of the electron accelerators. These models tell 

investigators monitoring the experiments from the ground what patterns they should expect to see in the 

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

THE TSS-1 TEAM 

Within NASA, the Tethered Satellite System program is directed by the Office of Space Flight and the 

Office of Space Science and Applications. The Space Systems Projects Office at the Marshall Space Flight 

Center, Huntsville, AL, has responsibility for project management and overall systems engineering. 

Experiment hardware systems were designed and developed by the U.S. and Italy. Responsibility for 

integration of all hardware, including experiment systems, is assigned to the project manager at the 

Marshall center. The Kennedy Space Center, Florida, is responsible for launch-processing and launch of 

the TSS-1 payload. The Johnson Space Center, Houston, has responsibility for TSS-1/STS integration and 

mission operations. 

R. J. Howard of the Office of Space Science and Applications, NASA Headquarters, Washington, DC, is 

the TSS-1 Science Payload Program Manager. The TSS Program Manager is Tom Stuart of the Office of 

Space Flight, NASA Headquarters. Billy Nunley is NASA Project Manager and TSS-1 Mission Manager at 

the Marshall Space Flight Center. Dr. Nobie Stone, also of Marshall, is the NASA TSS-1 Mission 

Scientist, the TSS Project Scientist and Co-chairman of the Investigator Working Group. 

For the Italian Space Agency, Dr. Gianfranco Manarini is Program Manager for TSS-1, while the Program 

Scientist is Dr. F. Mariani. Dr. Marino Dobrowolny is the Project Scientist for the Italian Space Agency, 

and Co-chairman of the investigator group. Dr. Maurizio Candidi is the Mission Scientist for the Italian 

Space Agency. 

Martin Marietta, Denver, Colo., developed the tether and control system deployer for NASA. Alenia in 

Turin, Italy, developed the satellite for the Italian Space Agency. 
Edited by Richard W. Orloff, 01/2001/Page 34 

TSS-1 SCIENCE INVESTIGATIONS 

Title Institution (Nation) 

 

Research on Electrodynamic Tether Effects CNR or Italian National Research 

Council (Italy) 

 

Research on Orbital Plasma Electrodynamics NASA/MSFC (U.S.) 

Shuttle Electrodynamic Tether System University of Michigan 

(U.S.) 

Magnetic Field Experiments for TSS Missions Second University of Rome (Italy) 

Theoretical & Experimental Investigations of TSS Dynamics Univ. of Padua (Italy) 

Theory & Modeling in Support of Tethered Satellite SAIC (U.S.) 

Investigation of Electromagnetic Emissions for Electrodynamic 

Tether 

Smithsonian Astrophysical 

Observatory (U.S.) 

Investigation and Measurement of Dynamic Noise of TSS 

Smithsonian Astrophysical Observatory (U.S.) 

Observation on Earth's Surface of Electromagnetic Emissions by 

TSS 

Univ. of Genoa (Italy) 

Deployer Core Equipment and Satellite Core Equipment ASI (Italy) 

Tether Optical Phenomena Experiment Lockheed (U.S.) 

Shuttle Potential & Return Dept. of the Air Force 

Electron Experiment Phillips Laboratory (U.S.) 
Edited by Richard W. Orloff, 01/2001/Page 35 

EUROPEAN RETRIEVABLE CARRIER (EURECA) 

The European Space Agency's (ESA) EURECA will be launched by the Space Shuttle and deployed at an 

altitude of 425 km. It will ascend, using its own propulsion, to its operational orbit of 515 km. After 6 to 9 

months in orbit, it will descend to the lower orbit where it will be retrieved by another orbiter and brought 

back to Earth. It will refurbished and equipped for the next mission. 

The first mission (EURECA-1) primarily will be devoted to research in the fields of material and life 

sciences and radiobiology, all of which require a controlled microgravity environment. The selected 

microgravity experiments will be carried out in seven facilities. The remaining payload comprises space 

science and technology. 

During the first mission, EURECA's residual carrier accelerations will not exceed 10-5g. The platform's 

altitude and orbit control system makes use of magnetic torquers augmented by cold gas thrusters to keep 

disturbance levels below 0.3 Nm during the operational phase. 

Physical characteristics 

Launch mass 4491 kg 

Electrical power solar array 5000w 

Continuous power to EURECA 

experiments 

1000w 

Launch configuration dia: 4.5m, length: 

2.54m 

Volume 40.3m 

Solar array extended 20m x 3.5 

User friendly 

Considerable efforts have been made during the design and development phases to ensure that EURECA is 

a "user friendly" system. As is the case for Spacelab, EURECA has standardized structural attachments, 

power and data interfaces. Unlike Spacelab, however, EURECA has a decentralized payload control 

concept. Most of the onboard facilities have their own data handling device so that investigators can 

control the internal operations of their equipment directly. This approach provides more flexibility as well 

as economical advantages. 

Operations 

EURECA is directly attached to the Shuttle cargo bay by means of a three-point latching system. The 

spacecraft has been designed with a minimum length and a close-to-optimum length-to-mass ratio, thus 

helping to keep down launch and retrieval costs. 

All EURECA operations will be controlled by ESA's Space Operations Centre (ESOC) in Darmstadt, 

Germany. During the deployment and retrieval operations, ESOC will function as a Remote Payload 

Operations Control Centre to NASA's Mission Control Center, Houston, and the orbiter will be used as a 

relay station for all the commands. In case of unexpected communication gaps during this period, the 

orbiter crew has a back-up command capability for essential functions. 

Throughout the operational phase, ESOC will control EURECA through two ground stations at 

Maspalomas and Kourou. EURECA will be in contact with its ground stations for a relatively short period 
Edited by Richard W. Orloff, 01/2001/Page 36 

each day. When it is out of contact, or "invisible", its systems operate with a high degree of autonomy, 

performing failure detection, isolation and recovery activities to safeguard ongoing experimental processes. 

An experimental advanced data relay system, the Inter-orbit Communication package, is included in the 

first payload. This package will communicate with the European Olympus Communication Satellite to 

demonstrate the possible improvements for future communications with data relay satellites. As such a 

system will significantly enhance real-time data coverage, it is planned for use on subsequent EURECA 

missions to provide an operational service via future European data relay satellites. 
Edited by Richard W. Orloff, 01/2001/Page 37 

Structure 

The EURECA structure is made of high strength carbon-fiber struts and titanium nodal points joined 

together to form a framework of cubic elements. This provides relatively low thermal distortions, allows 

high alignment accuracy and simple analytical verification, and is easy to assemble and maintain. Larger 

assemblies are attached to the nodal points. Instruments weighing less than 100 kg are assembled on 

standard equipment support panels similar to those on a Spacelab pallet. 

Thermal Control 

Thermal control for EURECA combines active and passive heat transfer and radiation systems. Active 

transfer, required for payload facilities which generated more heat, is achieve by means of a Freon cooling 

loop which dissipates the thermal load through two radiators into space. The passive system makes use of 

multi-layer insulation blankets combined with electrical heaters. During nominal operations, the thermal 

control subsystem rejects a maximum heat load of about 2300 w. 

Electrical Power 

The electrical power subsystem generates, stores, conditions and distributes power to all the spacecraft 

subsystems and to the payload. The deployable and retractable solar arrays, with a combined raw power 

output of some 5000 w together with four 40 amp-hour (Ah) nickel-cadmium batteries, provide the payload 

with a continuous power of 1000 w, nominally at 28 volts, with peak power capabilities of up to 1500 w 

for several minutes. While EURECA is in the cargo bay, electric power is provided by the Shuttle to ensure 

that mission critical equipment is maintained within its temperature limits. 

Attitude and Orbit Control 

A modular attitude and orbit control subsystem (AOCS) is used for attitude determination and spacecraft 

orientation and stabilization during all flight operations and orbit control maneuvers. The AOCS has been 

designed for maximum autonomy. It will ensure that all mission requirements are met even in case of 

severe on-board failures, including non-availability of the on-board data handling subsystem for up to 48 

hours. 

An orbit transfer assembly, consisting of two redundant sets of four thrusters, is used to boost EURECA to 

its operation attitude at 515 km and to return it to its retrieval orbit at about 300 km. The amount of 

onboard propellant hydrazine is sufficient for the spacecraft to fly different mission profiles depending on 

its nominal mission duration which may be anywhere between 6 and 9 months. 

EURECA is three-axis stabilized by means of a magnetic torque assembly together with a nitrogen reaction 

control assembly (RCA). This specific combination of actuators was selected because its' control 

accelerations are well below the microgravity constraints of the spacecraft. The RCA cold gas system can 

be used during deployment and retrieval operations without creating any hazards for the Shuttle. 

Communications and Data Handling 

EURECA remote control and autonomous operations are carried out by means of the data handling 

subsystem (DHS) supported by the telemetry and telecommand subsystems which provide the link to and 

from the ground segment. Through the DHS, instructions are stored and executed, telemetry data is stored 

and transmitted, and the spacecraft and its payload are controlled when EURECA is no longer "visible" 

from the ground station. 
Edited by Richard W. Orloff, 01/2001/Page 38 

EURECA SCIENCE 

Solution Growth Facility (SGF) 

Principal Investigator: 

J. C. Legros 

Universite Libre de Bruxelles, Brussels, Belgium 

The Solution Growth Facility (SGF) is a multi-user facility dedicated to the growth of monocrystals from 

solution, consisting of a set of four reactors and their associated control system. 

Three of the reactors will be used for the solution growth of crystals. These reactors have a central buffer 

chamber containing solvent and two reservoirs containing reactant solutions. The reservoirs are connected 

to the buffer chamber by valves which allow the solutions to diffuse into the solvent and hence, to 

crystallize. 

The fourth reactor is divided into twenty individual sample tubes which contain different samples of binary 

organic mixtures and aqueous electrolyte solutions. This reactor is devoted to the measurement of the Soret 

coefficient, that is, the ratio of thermal to isothermal diffusion coefficient. 

The SGF has been developed under ESA contract by Laben and their subcontractors Contraves and Terma. 

Protein Crystallization Facility (PCF) 

Principal Investigator: 

W. Littke 

Chemisches Laboratorium, Universitat Freiburg, Freiburg, Germany 

The Protein Crystallization Facility (PCF) is a multi-user solution growth facility for protein crystallization 

in space. The object of the experiments is the growth of single, defect-free protein crystals of high purity 

and of a size sufficient to determine their molecular structure by x-ray diffraction. 

This typically requires crystal sizes in the order of a few tenths of a millimeter. 

The PCF contains twelve reactor vessels, one for each experiment. Each reactor, which is provided with an 

individually controlled temperature environment, has four chambers -- one containing the protein, one 

containing a buffer solution and two filled with salt solutions. When the reactors have reached their 

operating temperatures, one of the salt solution chambers, the protein chamber and the buffer solution 

chamber are opened. Salt molecules diffuse into the buffer chamber causing the protein solution to 

crystallize. At the end of the mission the second salt solution chamber is activated to increase the salt 

concentration. This stabilizes the crystals and prevents them from dissolving when individual temperature 

control for the experiments ceases and the reactors are maintained at a common storage temperature. 

One particular feature of the PCF is that the crystallization process can be observed from the ground by 

means of a video system. 

The PCF has been developed under ESA contract by MBB Deutsche Aerospace and their subcontractors 

Officine Galileo and Reusser. 
Edited by Richard W. Orloff, 01/2001/Page 39 

Exobiology And Radiation Assembly (ERA) 

Principal Investigator: 

H. Bucker 

Institut fur Flugmedizin Abt. Biophysik, DLR, Cologne, Germany 

The Exobiology and Radiation Assembly (ERA) is a multi-user life science facility for experiments on the 

biological effects of space radiation. Our knowledge of the interaction of cosmic ray particles with 

biological matter, the synergism of space vacuum and solar UV, and the spectral effectiveness of solar UV 

on viability should be improved as a result of experiments carried out in the ERA. 

The ERA consists of deployable and fixed experiment trays and a number of cylindrical stacks, known as 

Biostacks, containing biological objects such as spores, seeds or eggs alternated with radiation and track 

detectors. An electronic service module also is included in the facility. The deployable trays carry 

biological specimens which are exposed to the different components of the space radiation environment for 

predetermined periods of time. The duration of exposure is controlled by means of shutters and the type of 

radiation is selected by the use of optical bandpass filters. 

The ERA has been developed under ESA contract by Sira Ltd. 

Multi-Furnace Assembly (MFA) 

Principal Investigator: 

A. Passerone 

Ist. di Chimica Fisica Applicata dei Materiali, National Research Council (CNR), Genova, Italy 

The Multi-Furnace Assembly (MFA) is a multi-user facility dedicated to material science experiments. It is 

a modular facility with a set of common system interfaces which incorporates twelve furnaces of three 

different types, giving temperatures of up to 1400 degrees C. Some of the furnaces are provided by the 

investigators on the basis of design recommendations made by ESA. The remainder are derived from 

furnaces flown on other missions, including some from sounding rocket flights. These are being used on 

EURECA after the necessary modifications and additional qualification. The experiments are performed 

sequentially with only one furnace operating at any one time. 

The MFA has been developed under ESA contract by Deutsche Aerospace, ERNO Raumfahrttechnik and 

their subcontractors SAAB, Aeritalia, INTA and Bell Telephone. 

Automatic Mirror Furnace (AMF) 

Principal Investigator: 

K. W. Benz 

Kristallographisches Institut, Universitat Freiburg, Freiburg, Germany 

The Automatic Mirror Furnace (AMF) is an optical radiation furnace designed for the growth of single, 

uniform crystals from the liquid or vapor phases, using the traveling heater or Bridgman methods. 

The principal component of the furnace is an ellipsoidal mirror. The experimental material is placed at the 

lower ring focus of the mirror and heated by radiation from a 300 w halogen lamp positioned at the upper 

focus. Temperatures of up to 1200 degrees C can be achieved, depending on the requirements of individual 

samples. Seven lamps are available and up to 23 samples can be processed in the furnace. 

As the crystal grows, the sample holder is withdrawn from the mirror assembly at crystallization speed, 

typically 2 mm/day, to keep the growth site aligned with the furnace focus. The sample also is rotated 

while in the furnace. 
Edited by Richard W. Orloff, 01/2001/Page 40 

The AMF is the first of a new generation of crystal growth facilities equipped with sample and lamp 

exchange mechanisms. Fully automatic operations can be conducted in space during long microgravity 

missions on free flying carriers. During a 6 month mission, about 20 different crystal growth experiments 

can be performed. 

The AMF has been developed under ESA contract by Dornier Deutsche Aerospace and their 

subcontractors Laben, ORS and SEP. 

Surface Forces Adhesion Instrument (SFA) 

Principal Investigator: 

G. Poletti 

Universita di Milano, Milan, Italy 

The Surface Forces Adhesion instrument (SFA) has been designed to study the dependence of surface 

forces and interface energies on physical and chemical-physical parameters such as surface topography, 

surface cleanliness, temperature and the deformation properties of the contacting bodies. 

The SFA experiment aims at refining current understanding of adhesion-related phenomena, such as 

friction and wear, cold welding techniques in a microgravity environment and solid body positioning by 

means of adhesion. 

Very high vacuum dynamic measurements must be performed in microgravity conditions because of the 

extreme difficulty experienced on Earth in controlling the physical parameters involved. As a typical 

example, the interface energy of a metallic sphere of 1 g mass contacting a pane target would be of the 

order of 10-3 erg. corresponding to a potential gravitational energy related to a displacement of 10-5 mm. 

In the same experiment performed on the EURECA platform, in a 10 to 100,000 times lower gravity 

environment, this energy corresponds to a displacement of 1 mm, thus considerably improving 

measurements and reducing error margins. 

The SFA instrument has been funded by the Scientific Committee of the Italian Space Agency (ASI) and 

developed by the University of Milan and their subcontractors Centrotechnica, Control Systems and Rial. 

High Precision Thermostat Instrument (HPT) 

Principal Investigator: 

G. Findenegg 

Ruhr Universitat Bochum, Bochum, Germany 

Basic physics phenomena around the critical point of fluids are not, as yet, fully understood. Measurements 

in a microgravity environment, made during the German mission D-1, seem to be at variance with the 

expected results. Further investigations of critical phenomena under microgravity conditions are of very 

high scientific value. 

The High Precision Thermostat (HPT) is an instrument designed for long term experiments requiring 

microgravity conditions and high precision temperature measurement and control. Typical experiments are 

"caloric", "critical point" or "phase transition" experiments, such as the "Adsorption" experiment designed 

for the EURECA mission. 

This experiment will study the adsorption of Sulphur Hexafluoride (SF6), close to its critical point 

(Tc=45.55 degrees C, pc=0.737 g/cm3) on graphitized carbon. A new volumetric technique will be used 

for the measurements of the adsorption coefficient at various temperatures along the critical isochore 

starting from the reference temperature in the one-phase region (60x) and approaching the critical 

temperature. The results will be compared with 1g measurements and theoretical predictions. 
Edited by Richard W. Orloff, 01/2001/Page 41 

The HPT has been developed under DLR contract by Deutsche Aerospace ERNO Raumfahrttechnik and 

their subcontractor Kayser-Threde GmbH. 

Solar Constant And Variability Instrument (SOVA) 

Principal Investigator: 

D. Crommelynck IRMB 

Brussels, Belgium 

The Solar Constant and Variability Instrument (SOVA) is designed to investigate the solar constant, its 

variability and its spectral distribution, and measure: 

• fluctuations of the total and spectral solar irradiance within periods of a few minutes 

up to several hours and with a resolution of 10-6 to determine the pressure and 

gravity modes of the solar oscillations which carry information on the internal 

structure of the sun; 

• short term variations of the total and spectral solar irradiance within time scales 

ranging from hours to few months and with a resolution of 10-5 for the study of 

energy redistribution in the solar convection zone. These variations appear to be 

associated with solar activities (sun spots); 

• long term variations of the solar luminosity in the time scale of years (solar cycles) 

by measuring the absolute solar irradiance with an accuracy of better than 0.1 

percent and by comparing it with previous and future measurements on board 

Spacelab and other space vehicles. This is of importance for the understanding of 

solar cycles and is a basic reference for climatic research. 

The SOVA instrument has been developed by the Institut Royal Meteorologique de Belgique of Brussels, 

by the Physikalisch-Meteorologishces Observatorium World Radiation Center (PMOD/WRC) Davos and 

by the Space Science Department (SSD) of the European Space Agency (ESA-ESTEC), Noordwijk. 

Solar Spectrum Instrument (SOSP) 

Principal Investigator: 

G. Thuillier 

Service d'Aeronomie du CNRS, Verrieres le Buisson, France 

The Solar Spectrum Instrument (SOSP) has been designed for the study of solar physics and the solarterrestrial relationship in aeronomy and climatology. It measures the absolute solar irradiance and its 

variations in the spectral range from 170 to 3200 n.m., with an expected accuracy of 1 percent in the visible 

and infrared ranges and 5 percent in the ultraviolet range. 

Changes in the solar irradiance mainly relate to the short-term solar variations that have been observed 

since 1981 by the Solar Maximum spacecraft, the variations related to the 27-day solar rotation period and 

the long-term variations related to the 11-year sun cycles. While the short term variations can be measured 

during one single EURECA flight mission, two or three missions are needed to assess the long term 

variations. 

SOSP has been developed by the Service d'Aeronomie of the Centre National de Recherche Scientifique 

(CNRS), the Institut d'Aeronomie Spatiale de Belgique (IASB), the Landassternwarte Koenigstuhl and the 

Hamburger Sternwarte. 
Edited by Richard W. Orloff, 01/2001/Page 42 

Occultation Radiometer Instrument (ORA) 

Principal Investigator: 

E. Arijs 

Belgisch Instituut voor Ruimte Aeronomie (BIRA), Brussels, Belgium 

The Occultation Radiometer instrument (ORA) is designed to measure aerosols and trace gas densities in 

the Earth's mesosphere and stratosphere. The attenuation of the various spectral components of the solar 

radiation as it passes through the Earth's atmosphere enables vertical abundance profiles for ozone, 

nitrogen dioxide, water vapor, carbon dioxide and background and volcanic aerosols to be determined for 

altitudes between 20 and 100 km. 

The ORA instrument has been developed by the Institut d'Aeronomie Spatiale, and the Clarendon 

Laboratory of the University of Oxford. 

Wide Angle Telescope (WATCH) 

Principal Investigator: 

N. Lund 

Danish Space Research Institute, Lyngby, Denmark 

The Wide Angle Telescope (WATCH) is designed to detect celestial gamma and x-ray sources with photon 

energies in the range 5 to 200 keV and determine the position of the source. 

The major objective of WATCH is the detection and localization of gamma-ray bursts and hard x-ray 

transients. Persistent x-ray sources also can be observed. 

Cosmic gamma-ray bursts are one of the most extreme examples of the variability of the appearance of the 

x-ray sky. They rise and decay within seconds, but during their life they outshine the combined flux from 

all other sources of celestial x-and gamma rays by factors of up to a thousand. 

Less conspicuous, but more predictable are the x-ray novae which flare regularly, typically with intervals 

of a few years. In the extragalactic sky, the "active galactic nuclei" show apparently are random 

fluctuations in their x-ray luminosity over periods of days or weeks. 

WATCH will detect and locate these events. The data from the experiment can be used to provide light 

curves and energy for the sources. The data also may be searched for regularities in the time variations 

related to orbital movement or rotation or for spectral features that yield information about the source. 

Additionally, other, more powerful sky observation instruments can be alerted to the presence of objects 

that WATCH has detected as being in an unusual state of activity. 

WATCH has been developed by the Danish Space Research Institute. 

Timeband Capture Cell Experiment (TICCE) 

Principal Investigator: 

J. A. M. McDonnell 

Unit for Space Science, Physics Laboratory University of Kent, Great Britain 

The Timeband Capture Cell Experiment (TICCE) is an instrument designed for the study of the 

microparticle population in near-Earth space -- typically Earth debris, meteoroids and cometary dust. The 

TICCE will capture micron dimensioned particles with velocities in excess of 3 km/s and store the debris 

for retrieval and post-mission analysis. 
Edited by Richard W. Orloff, 01/2001/Page 43 

Particles detected by the instrument pass through a front foil and into a debris collection substrate 

positioned 100 n.m. behind the foil. Each perforation in the foil will have a corresponding debris site on the 

substrate. The foil will be moved in 50 discrete steps during the six month mission, and the phase shift 

between the debris site and the perforation will enable the arrival timeband of the particle to be determined. 

Between 200 and 300 particles are expected to impact the instrument during the mission. Ambiguities in 

the correlation of foil perforations and debris sites will probably occur for only a few of the impacts. 

Elemental analysis of the impact sites will be performed, using dispersive x-ray techniques, once the 

instrument has returned to Earth. 

TICCE has been developed by the University of Kent. Its structural support has been sponsored by ESA 

and subcontracted to SABCA under a Deutsche Aerospace ERNO Raumfahrttechnik contract. 

Radio Frequency Ionization Thruster Assembly (RITA) 

Principal Investigator: 

H. Bassner 

MBB Deutsche Aerospace, Munich, Germany 

The Radio Frequency Ionization Thruster Assembly (RITA) is designed to evaluate the use of electric 

propulsion in space and to gain operational experience before endorsing its use for advanced spacecraft 

technologies. 

The space missions now being planned - which are both more complex and of longer duration - call for 

increased amounts of propellant for their propulsion systems which, in turn, leads to an increase in the 

overall spacecraft mass to the detriment of the scientific or applications payload. Considerable savings can 

be made in this respect by the use of ion propulsion systems, wherein a gas is ionized and the positive ions 

are them accelerated by an electric field. In order to avoid spacecraft charging, the resulting ion beam is 

then neutralized by an electron emitting device, the neutralizer. The exhaust velocities obtained in this way 

are about an order of magnitude higher than those of chemical propulsion systems. 

RITA has been developed under ESA and BMFT contract by Deutsche Aerospace ERNO 

Raumfahrttechnik. 

Inter-Orbit Communication (IOC) 

R. Tribes 

CNES Project Manager, CNES-IOC Toulouse, France 

N. Neale 

ESA Project Manager, ESTEC-CD Noordwijk, The Netherlands 

The Inter-Orbit Communication (IOC) instrument is a technological experiment designed to provide a preoperational inflight test and demonstration of the main functions, services and equipment typical of those 

required for a data relay system, namely: 

• bi-directional, end-to-end data transmission between the user spacecraft and a dedicated ground station 

via a relay satellite in the 20/30 GHz frequency band; 

• tracking of a data relay satellite; 

• tracking of a user spacecraft; 

• ranging services for orbit determination of a user spacecraft via a relay satellite. 
Edited by Richard W. Orloff, 01/2001/Page 44 

In this case, the EURECA platform is the user spacecraft and the ESA communications satellite Olympus 

the relay satellite. One of the Olympus steerable spot beam antennas will be pointed towards the IOC on 

EURECA and the other towards the IOC ground station. The IOC instrument is provided with a mobile 

directional antenna to track Olympus. 

The IOC has been developed under ESA contract by CNES and their subcontractors Alocatel Espace, 

Marconi Space Systems, Laben, Matra Espace, Sener, Alcatel Bel, AEG-Telefunken, ETCA, TEX, MDS 

and COMDEV. 

Advanced Solar Gallium Arsenide Array (ASGA) 

Principal Investigator: 

C. Flores 

CISE SPA, Segrate, Italy 

The Advanced Solar Gallium Arsenide Array (ASGA) will provide valuable information on the 

performance of gallium arsenide (GaAs) solar arrays and on the effects of the low Earth orbit environment 

on their components. These solar cells, already being used in a trial form to power the Soviet MIR space 

station, are expected to form the backbone of the next generation of compact, high power-to-weight ratio 

European solar energy generators. 

The most significant environmental hazards encountered arise from isotopic proton bombardment in the 

South Atlantic Anomaly, high frequency thermal cycling fatigue of solar cell interconnections and the 

recently discovered atomic oxygen erosion of solar array materials. Although a certain amount of 

knowledge may be gained from laboratory experiments, the crucial confirmation of the fidelity of the GaAs 

solar array designs awaits the results of flight experiments. 

The project has been sponsored by the Italian Space Agency (ASI) and developed by CISE with its 

subcontractor, Carlo Gavazzi Space. The planar solar module has been assembled by FIAR. The miniature 

Cassegranian concentrator components have been developed in collaboration with the Royal Aircraft 

Establishments and Pilkington Space Technology. 

EURECA has been developed under ESA contract by Deutsche Aerospace, ERNO Raumfahrttechnik, 

(Germany), and their subcontractors Sener, (England), AIT, (Italy), SABCA, (Belgium), AEG, (Germany), 

Fokker, (The Netherlands), Matra, (France), Deutsche Aerospace, ERNO Raumfahrttechnik, (Germany), 

SNIA-BPD, (Italy), BTM, (Belgium), and Laben, (Italy). F. Schwan - Industrial Project Manager Deutsche 

Aerospace, ERNO Raumfahrttechnik, Bremen, Germany W. Nellessen - ESA Project Manager ESTEC 

MR, Noordwijk, The Netherlands 
Edited by Richard W. Orloff, 01/2001/Page 45 

EVALUATION OF OXYGEN INTERACTION WITH MATERIALS/ 

TWO PHASE MOUNTING PLATE EXPERIMENT (EOIM-III/TEMP 2A-3) 

EOIM 

The Evaluation of Atomic Oxygen Interactions with Materials (EOIM) payload will obtain accurate 

reaction rate measurements of the interaction of space station materials with atomic oxygen. It also will 

measure the local Space Shuttle environment, ambient atmosphere and interactions between the two. This 

will improve the understanding of the effect of the Shuttle environment on Shuttle and payload operations 

and will update current models of atmospheric composition. EOIM also will assess the effects of 

environmental and material parameters on reaction rates. 

To make these measurements, EOIM will use an ion-neutral mass spectrometer to obtain aeronomy 

measurements and to study atom-surface interaction products. The package also provides a mass 

spectrometer rotating carousel system containing "modeled" polymers for mechanistic studies. EOIM also 

will study the effects of mechanical stress on erosion rates of advanced composites and the effects of 

temperature on reaction rates of disk specimens and thin films. Energy accommodations on surfaces and 

surface-atom emission characteristics concerning surface recession will be measured using passive 

scatterometers. The payload also will assess solar ultraviolet radiation reaction rates. 

The environment monitor package will be activated pre-launch, while the remainder of the payload will be 

activated after payload bay door opening. Experiment measurements will be made throughout the flight, 

and the package will be powered down during de-orbit preparations. 

TEMP 

The Two Phase Mounting Plate Experiment (TEMP 2A-3) has two-phase mounting plates, an ammonia 

reservoir, mechanical pumps, a flowmeter, radiator and valves, and avionics subsystems. The TEMP is a 

two-phase thermal control system that utilizes vaporization to transport large amounts of heat over large 

distances. The technology being tested by TEMP is needed to meet the increased thermal control 

requirements of space station. The TEMP experiment will be the first demonstration of a mechanically 

pumped two-phase ammonia thermal control system in microgravity. It also will evaluate a propulsion-type 

fluid management reservoir in a two-phase ammonia system, measure pressure drops in a two-phase fluid 

line, evaluate the performance of a two-phase cold plate design and measure heat transfer coefficients in a 

two-phase boiler experiment. EOIM-III/TEMP 2A-3 are integrated together on a MPESS payload carrier in 

the payload bay. 
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CONSORTIUM FOR MATERIALS DEVELOPMENT IN SPACE COMPLEX 

AUTONOMOUS PAYLOAD (CONCAP) 

The Consortium for Materials Development in Space Complex Autonomous Payload (CONCAP) is 

sponsored by NASA's Office of Commercial Programs (OCP). On STS-46, two CONCAP payloads 

(CONCAP-II and -III) will be flown in 5-foot cylindrical GAS (Get Away Special) canisters. 

CONCAP-II is designed to study the changes that materials undergo in low-Earth orbit. This payload 

involves two types of experiments to study the surface reactions resulting from exposing materials to the 

atomic oxygen flow experienced by the Space Shuttle in orbit. The atomic oxygen flux level also will be 

measured and recorded. The first experiment will expose different types of high temperature 

superconducting thin films to the 5 electron volt atomic oxygen flux to achieve improved properties. 

Additional novel aspects of this experiment are that a subset of the materials samples will be heated to 320 

degrees Celsius (the highest temperature used in space), and that the material resistance change of 24 

samples will be measured on-orbit. 

For the second CONCAP-II experiment, the surface of different passive materials will be exposed (at 

ambient and elevated temperatures) to hyperthermal oxygen flow. This experiment will enable enhanced 

prediction of materials degradation on spacecraft and solar power systems. In addition, this experiment will 

test oxidation-resistant coatings and the production of surfaces for commercial use, development of new 

materials based on energetic molecular beam processing and development of an accurate data base on 

materials reaction rates in orbit. 

CONCAP-III is designed to measure and record absolute accelerations (microgravity levels) in one 

experiment and to electroplate pure nickel metal and record the conditions (temperature, voltage and 

current) during this process in another experiment. Items inside the orbiter experience changes in 

acceleration when various forces are applied to the orbiter, including thruster firing, crew motion and for 

STS-46, tethered satellite operations. By measuring absolute accelerations, CONCAP-III can compare the 

measured force that the orbiter undergoes during satellite operations with theoretical calculations. Also, 

during accelerations measurements, CONCAP-III can gather accurate acceleration data during the 

electroplating experiments. 

The second CONCAP-III experiment is an electroplating experiment using pure nickel metal. This 

experiment will obtain samples for analysis as part of a study of microgravity effects on electroplating. 

Materials electroplated in low gravity tend to have different structures than materials electroplated on 

Earth. Electroplating will be performed before and during the tethered satellite deployment to study the 

differences that occur for different levels of accelerations. 

The CONCAP-II and -III experiments are managed and developed by the Consortium for Materials 

Development in Space, a NASA Center for the Commercial Development of Space at the University of 

Alabama in Huntsville (UAH). Payload integration and flight hardware management is handled by NASA's 

Goddard Space Flight Center, Greenbelt, MD. 

Dr. John C. Gregory and Jan A. Bijvoet of UAH are Principal investigator and payload manager, 

respectively, for CONCAP-II. For CONCAP-III, principal investigator for the acceleration experiment is 

Bijvoet, principal investigator for the electrodeposition (electroplating) is Dr. Clyde Riley, also of UAH, 

and payload manager is George W. Maybee of McDonnell Douglas Space Systems Co., Huntsville, AL. 
Edited by Richard W. Orloff, 01/2001/Page 48 

LIMITED DURATION SPACE ENVIRONMENT CANDIDATE 

MATERIALS EXPOSURE (LDCE) 

The first of the Limited Duration Space Environment Candidate Materials Exposure (LDCE) payload 

series is sponsored by NASA's Office of Commercial Programs (OCP). The LDCE project on STS-46 

represents an opportunity to evaluate candidate space structure materials in low-Earth orbit. 

The objective of the project is to provide engineering and scientific information to those involved in 

materials selection and development for space systems and structures. By exposing such materials to 

representative space environments, an analytical model of the performance of these materials in a space 

environment can be obtained. 

The LDCE payload consists of three separate experiments, LDCE-1, -2 and -3, which will examine the 

reaction of 356 candidate materials to at least 40 hours exposure in low-Earth orbit. LDCE-1 and -2 will be 

housed in GAS (Get Away Special) canisters with motorized door assemblies. LDCE-3 will be located on 

the top of the GAS canister used for CONCAP-III. Each experiment has a 19.65-inch diameter support disc 

with a 15.34-inch diameter section which contains the candidate materials. The support disc for LDCE-3 

will be continually exposed during the mission, whereas LDCE-1 and -2 will be exposed only when the 

GAS canisters' doors are opened by a crew member. Other than opening and closing the doors, LDCE 

payload operations are completely passive. The doors will be open once the Shuttle achieves orbit and will 

be closed periodically during Shuttle operations, such as water dumps, jet firings and changes in attitude. 

Two primary commercial goals of the flight project are to identify environmentally-stable structural 

materials to support continued humanization and commercialization of the space frontier and to establish a 

technology base to service growing interest in space materials environmental stability. 

The LDCE payload is managed and developed by the Center for Materials on Space Structures, a NASA 

Center for the Commercial Development of Space at Case Western Reserve University (CWRU) in 

Cleveland. Dr. John F. Wallace, Director of Space Flight Programs at CWRU, is lead Investigator. Dawn 

Davis, also of CWRU, is program manager. 
Edited by Richard W. Orloff, 01/2001/Page 49 
Edited by Richard W. Orloff, 01/2001/Page 50 

PITUITARY GROWTH HORMONE CELL FUNCTION (PHCF) 

Principal Investigator: 

Dr. W. C. Hymer 

The Pennsylvania State University, University Park, Pa. 

The Pituitary Growth Hormone Cell Function (PHCF) experiment is a middeck-locker rodent cell culture 

experiment. It continues the study of the influence of microgravity on growth hormone secreted by cells 

isolated from the brain's anterior pituitary gland. 

PHCF is designed to study whether the growth hormone-producing cells of the pituitary gland have an 

internal gravity sensor responsible for the decreased hormone release observed following space flight. This 

hormone plays an important role in muscle metabolism and immune-cell function as well as in the growth 

of children. Growth hormone production decreases with age. The decline is thought to play an important 

role in the aging process. 

The decreased production of biologically active growth hormone seen during space flight could be a factor 

in the loss of muscle and bone strength and the decreased immune response observed in astronauts 

following space flight. If the two are linked, PHCF might identify mechanisms for providing 

countermeasures for astronauts on long space missions. It also may lead to increased understanding of the 

processes underlying human muscle degeneration as people age on Earth. 

The PHCF experiment uses cultures of living rat pituitary cells. These preparations will be placed in 165 

culture vials carried on the Shuttle's middeck in an incubator. After the flight, the cells will be cultured and 

their growth hormone output assayed. 

IMAX CARGO BAY CAMERA (ICBC) 

The IMAX Cargo Bay Camera (ICBC) is aboard STS-46 as part of NASA's continuing collaboration with 

the Smithsonian Institution in the production of films using the IMAX system. This system, developed by 

IMAX Corp., Toronto, Canada, uses specially-designed 70 mm film cameras and projectors to produce 

very high definition motion picture images which, accompanied by six channel high fidelity sound, are 

displayed on screens up to ten times the size used in conventional motion picture theaters. 

"The Dream is Alive" and "Blue Planet," earlier products of this collaboration, have been enjoyed by 

millions of people around the world. On this flight, the camera will be used primarily to cover the 

EURECA and Tether Satellite operations, plus Earth scenes as circumstances permit. The footage will be 

used in a new film dealing with our use of space to gain new knowledge of the universe and the future of 

mankind in space. Production of these films is sponsored by the Lockheed Corporation. 
Edited by Richard W. Orloff, 01/2001/Page 51 
Edited by Richard W. Orloff, 01/2001/Page 52 
Edited by Richard W. Orloff, 01/2001/Page 53 

AIR FORCE MAUI OPTICAL SYSTEM (AMOS) 

The Air Force Maui Optical System (AMOS) is an electrical-optical facility located on the Hawaiian island 

of Maui. The facility tracks the orbiter as it flies over the area and records signatures from thruster firings, 

water dumps or the phenomena of shuttle glow, a well-documented glowing effect around the shuttle 

caused by the interaction of atomic oxygen with the spacecraft. 

The information obtained is used to calibrate the infrared and optical sensors at the facility. No hardware 

onboard the shuttle is needed for the system. 

ULTRAVIOLET PLUME EXPERIMENT 

The Ultraviolet Plume Experiment (UVPI) is an instrument on the Low-Power Atmospheric Compensation 

Experiment (LACE) satellite launched by the Strategic Defense Initiative Organization in February 1990. 

LACE is in a 43-degree inclination orbit of 290 n.m. Imagery of Columbia's engine firings or attitude 

control system firings will be taken on a non-interference basis by the UVPI whenever an opportunity is 

available during the STS-46 mission. 
Edited by Richard W. Orloff, 01/2001/Page 54 

STS-46 CREWMEMBERS 

STS046-S-002 -- The crewmembers assigned to NASA's STS-46 mission pose with seven flags that represent 

participation on the flight. Mission commander Loren J. Shriver (right), holding launch and entry helmet (LEH), 

and pilot Andrew M. Allen (left), also holding LEH, are seated in the front. Standing behind them and wearing 

launch and entry suits (LESs) are (left to right) mission specialists(MS) Marsha S. Ivins, Claude Nicollier 

(representing the European Space Agency (ESA)), mission specialist and payload commander Jeffrey A. Hoffman, 

mission specialist Franklin R. Chang-Diaz, and payload specialist Franco Malerba (flying for the Italian Space 

Agency (ASI)). The flags (left to right) represent the United States of America (USA), Costa Rica (Chang-Diaz's 

native country), Italy, Switzerland (Nicollier's homeland), NASA, ESA, and ASI. Portrait made by NASA JSC 

photographer Robert L. Walck. 

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 55 

BIOGRAPHICAL DATA 

LOREN J. SHRIVER, 47, Col., USAF, will serve as commander of STS-46. Selected as an astronaut in 

January 1978, Shriver considers Paton, IA, his hometown and will be making his third space flight. 

Shriver graduated from Paton Consolidated High School, received a bachelor's in aeronautical engineering 

from the Air Force Academy and received a master's in aeronautical engineering from Purdue University. 

Shriver was pilot of STS-51C in January 1985, a Department of Defense-dedicated shuttle flight. He next 

flew as commander of STS-31 in April 1990, the mission that deployed the Hubble Space Telescope. 

Shriver has logged more than 194 hours in space. 

ANDREW M. ALLEN, 36, Major, USMC, will serve as pilot. Selected as an astronaut in June 1987, 

Allen was born in Philadelphia, PA, and will be making his first space flight. 

Allen graduated from Archbishop Wood High School in Warminster, PA, in 1973 and received a 

bachelor's in mechanical engineering from Villanova University in 1977. 

Allen was commissioned in the Marine Corps in 1977. Following flight school, he was assigned to fly the 

F-4 Phantom at the Marine Corps Air Station in Beaufort, SC. He graduated from the Navy Test Pilot 

School in 1987 and was a test pilot under instruction at the time of his selection by NASA. He has logged 

more than 3,000 flying hours in more than 30 different types of aircraft. 

CLAUDE NICOLLIER, 47, will be Mission Specialist 1 (MS1). Under an agreement between the 

European Space Agency and NASA, he was selected as an astronaut in 1980. Nicollier was born in Vevey, 

Switzerland, and will be making his first space flight. 

Nicollier graduated from Gymnase de Lausanne, Lausanne, Switzerland, received a bachelor's in physics 

from the University of Lausanne and received a master's in astrophysics from the University of Geneva. 

In 1976, he accepted a fellowship at ESA's Space Science Dept., working as a research scientist in various 

airborne infrared astronomy programs. In 1978, he was selected by ESA as one of three payload specialist 

candidates for the Spacelab-1 shuttle mission, training at NASA for 2 years as an alternate. In 1980, he 

began mission specialist training. Nicollier graduated from the Empire Test Pilot School, Boscombe Down, 

England, in 1988, and holds a commission as Captain in the Swiss Air Force. He has logged more than 

4,300 hours flying time, 2,700 in jet aircraft. 

MARSHA S. IVINS, 41, will be Mission Specialist 2 (MS2). Selected as an astronaut in 1984, Ivins was 

born in Baltimore, MD, and will be making her second space flight. 

Ivins graduated from Nether Providence High School, Wallingford, PA, and received a bachelor's in 

aerospace engineering from the University of Colorado. 

Ivins joined NASA shortly after graduation and was employed at the Johnson Space Center as an engineer 

in the Crew Station Design Branch until 1980. she was assigned as a flight simulation engineer aboard the 

Shuttle Training Aircraft and served as co-pilot of the NASA administrative aircraft. 

She first flew on STS-32 in January 1990, a mission that retrieved the Long Duration Exposure Facility 

(LDEF). She has logged more than 261 hours in space. 
Edited by Richard W. Orloff, 01/2001/Page 56 

BIOGRAPHICAL DATA 

JEFFREY A. HOFFMAN, 47, will be Mission Specialist 3 (MS3) and serve as Payload Commander. 

Selected as an astronaut in January 1978, Hoffman considers Scarsdale, NY, his hometown and will be 

making his third space flight. 

Hoffman graduated from Scarsdale High School, received a bachelor's in astronomy from Amherst 

College, received a doctorate in astrophysics from Harvard University and received a master's in materials 

science from Rice University. 

Hoffman first flew on STS-51D in April 1985, a mission during which he performed a spacewalk in an 

attempt to rescue a malfunctioning satellite. He next flew on STS-35 in December 1990, a mission carrying 

the ASTRO-1 astronomy laboratory. 

FRANKLIN R. CHANG-DIAZ will be Mission Specialist 4 (MS4). Selected as an astronaut in May 

1980, Chang-Diaz was born in San Jose, Costa Rica, and will be making his third space flight. 

Chang-Diaz graduated from Colegio De La Salle in San Jose and from Hartford High School, Hartford, 

CT; received a bachelor's in mechanical engineering from the University of Connecticut and received a 

doctorate in applied physics from the Massachusetts Institute of Technology. 

Chang-Diaz first flew on STS-61C in January 1986, a mission that deployed the SATCOM KU satellite. 

He next flew on STS-34 in October 1989, the mission that deployed the Galileo spacecraft to explore 

Jupiter. Chang-Diaz has logged more than 265 hours in space. 

FRANCO MALERBA, 46, will serve as Payload Specialist 1 (PS1). An Italian Space Agency payload 

specialist candidate, Malerba was born in Genova, Italy, and will be making his first space flight. 

Malerba graduated from Maturita classica in 1965, received a bachelor's degree in electrical engineering 

from the University of Genova in 1970 and received a doctorate in physics from the University of Genova 

in 1974. 

From 1978-1980, he was a staff member of the ESA Space Science Dept., working on the development and 

testing of an experiment in space plasma physics carried aboard the first shuttle Spacelab flight. From 

1980-1989, he has held various technical and management positions with Digital Equipment Corp. in 

Europe, most recently as senior telecommunications consultant at the European Technical Center in 

France. Malerba is a founding member of the Italian Space Society. 
Edited by Richard W. Orloff, 01/2001/Page 57 

MISSION MANAGEMENT FOR STS-46 

NASA HEADQUARTERS, WASHINGTON, DC 

Office of Space Flight 

Jeremiah W. Pearson III Associate Administrator 

Brian O'Connor Deputy Associate Administrator 

Tom Utsman Director, Space Shuttle 

Office of Space Science 

Dr. Lennard A. Fisk Associate Administrator, Office of Space Science and Applications 

Alphonso V. Diaz Deputy Associate Administrator, Office of Space Science and Applications 

George Withbroe Director, Space Physics Division 

R. J. Howard TSS-1 Science Payload Program Manager 

Office of Commercial Programs 

John G. Mannix Assistant Administrator 

Richard H. Ott Director - Commercial Development Division 

Garland C. Misener Chief, Flight Requirements and Accommodations 

Ana M. Villamil Program Manager, Centers for the Commercial Development of Space 

Office of Safety and Mission Quality 

Col. Federick Gregory Associate Administrator 

Dr. Charles Pellerin Jr. Deputy Associate Administrator 

Richard Perry Director, Programs Assurance 

KENNEDY SPACE CENTER, FL 

Robert L. Crippen Director 

James A. "Gene" Thomas Deputy Director 

Jay F. Honeycutt Director, Shuttle Management and Operations 

Robert B. Sieck Launch Director 

Conrad G. Nagel Atlantis Flow Director 

J. Robert Lang Director, Vehicle Engineering 

Al J. Parrish Director of Safety Reliability and Quality Assurance 

John T. Conway Director, Payload Management and Operations 

P. Thomas Breakfield Director, Shuttle Payload Operations 

Joanne H. Morgan Director, Payload Project Management 

Robert W. Webster STS-46 Payload Processing Manager 
Edited by Richard W. Orloff, 01/2001/Page 58 

MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, AL 

Thomas J. Lee Director 

Dr. J. Wayne Littles Deputy Director 

Harry G. Craft Manager, Payload Projects Office 

Billy Nunley TSS-1 Mission Manager 

Dr. Nobie Stone TSS-1 Mission Scientist 

Alexander A. McCool Manager, Shuttle Projects Office 

Dr. George McDonough Director, Science and Engineering 

James H. Ehl Director, Safety and Mission Assurance 

Otto Goetz Manager, Space Shuttle Main Engine Project 

Victor Keith Henson Manager, Solid Rocket Booster Project 

Gerald C. Ladner Manager, External Tank Project 

JOHNSON SPACE CENTER, HOUSTON, TX 

Paul J. Weitz Director (Acting) 

Paul J. Weitz Deputy Director 

Daniel Germany 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 

STENNIS SPACE CENTER, BAY ST. LOUIS, MS 

Roy S. Estess Director 

Gerald Smith Deputy Director 

J. Harry Guin Director, Propulsion Test Operations 

AMES-DRYDEN FLIGHT RESEARCH FACILITY, EDWARDS, CA 

Kenneth J. Szalai Director 

T. G. Ayers Deputy Director 

James R. Phelps Chief, Space Support Office 

AMES RESEARCH CENTER, MOUNTAIN VIEW, CA

Dr. Dale L. Compton Director 

Victor L. Peterson Deputy Director 

Dr. Steven A. Hawley Associate Director 

Dr. Joseph C. Sharp Director, Space Research 
Edited by Richard W. Orloff, 01/2001/Page 59 

SHUTTLE FLIGHTS AS OF JUNE 1992 

48 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 23 SINCE RETURN TO FLIGHT 

STS-42 

01/22/92 - 01/30/92 

STS-48 

09/12/91 - 09/18/91 

STS-50 

06/25/92 - 07/09/92 

STS-39 

04/28/91 - 05/06/91 

STS-40 

06/05/91 - 06/14/91 

 STS-41 

10/06/90 - 10/10/90 

STS-45 

03/24/92 - 04/02/92 

STS-35 

12/02/90 - 12/10/90 

STS-51L 

01/28/86 

STS-31 

04/24/90 - 04/29/90 

STS-44 

11/24/91 - 12/01/91 

STS-32 

01/09/90 - 01/20/90 

STS-61A 

10/30/85 - 11/06/85 

STS-33 

11/22/89 - 11/27/89 

STS-43 

08/02/91 - 08/11/91 

STS-28 

08/08/89 - 08/13/89 

STS-51F 

07/29/85 - 08/06/85 

STS-29 

03/13/89 - 03/18/89 

STS-37 

04/05/91 - 04/11/91 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

STS-38 

11/15/90 - 11/20/90 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-36 

02/28/90 - 03/04/90 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-34 

10/18/89 - 10/23/89 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-30 

05/04/89 - 05/08/89 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-27 

12/02/88 - 12/06/88 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

STS-49 

05/07/92 - 05/16/92 

 

OV-102 

Columbia 

(12 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(14 flights) 

OV-104 

Atlantis 

(11 flights) 

OV-105 

Endeavour 

(1 flight)