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

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

SPACE SHUTTLE 

MISSION 

STS-26 

PRESS KIT 

SEPTEMBER 1988 

RETURN TO FLIGHT 

TRACKING AND DATA RELAY SATELLITE (TDRS C) 
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STS-26 INSIGNIA 

S87-39136 -- The predominant themes of the STS-26 insignia are: a new beginning (sunrise), a safe 

mission (stylized launch and plume), the building upon the traditional strengths of NASA (the red vector 

which symbolizes aeronautics on the original NASA insignia), and a remembrance of the crewmembers' 

seven colleagues who died aboard Challenger (the seven-starred Big Dipper). The insignia was designed 

by artist Stephen R. Hustvedt of Annapolis, Maryland. 

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

RELEASE 88-121 September, 1988 

PUBLIC AFFAIRS CONTACTS 

Sarah Keegan/Barbara Selby 

Office of Space Flight 

NASA Headquarters, Washington, DC 

(Phone: 202/453-2352) 

Geoffrey Vincent 

Office of Space Operations 

NASA Headquarters, Washington, DC 

(Phone: 202/453-2754) 

Lisa Malone 

Kennedy Space Center, FL 

(Phone: 407/867-2468) 

Kyle Herring 

Johnson Space Center, Houston, TX 

(Phone: 703/483-5111) 

Ed Medal 

Marshall Space Flight Center, Huntsville, AL 

(Phone: 205/544-0034) 

Mack Herring 

Stennis Space Center, Bay St. Louis, MS 

(Phone: 601/688-3341) 

Nancy Lovato 

Ames-Dryden Flight Research Center, Edwards, CA 

(Phone: 805/258-8381) 

Jim Elliott 

Goddard Space Flight Center, Greenbelt, MD 

(Phone: 301/286-6256) 
Edited by Richard W. Orloff, 01/2001/Page 4

CONTENTS 

GENERAL RELEASE 5 

GENERAL INFORMATION 7 

STS-26 QUICK LOOK 8 

LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF 9 

MAJOR COUNTDOWN MILESTONES 12 

SUMMARY OF MAJOR ACTIVITIES 13 

STS-26 TRAJECTORY SEQUENCE OF EVENTS 14 

SPACE SHUTTLE ABOARD MODES 15 

LANDING AND POST-LANDING OPERATIONS 16 

TRACKING AND DATA RELAY SATELLITE SYSTEM 17 

INERTIAL UPPER STAGE 21 

SECONDARY PAYLOADS 22 

 Physical Vapor Transport of Organic Solids (PVTOS) 22 

 Protein Crystal Growth Experiment (PCG) 24 

 Infrared Communications Flight Experiment (IRCFE) 27 

 Automated Directional Solidification Furnace (ADSF) 29 

 Aggregation of Red Blood Cells (ARC) 31 

 Isoelectric Focusing Experiment (IFE) 33 

 Mesoscale Lightning Experiment (MLE) 35 

 Phase Partitioning Experiment (PPE) 35 

 Earth-Limb Radiance Experiment (ELRAD) 38 

 Space Shuttle Student Involvement Program (SSIP) 39 

 Semi-Permeable Membrane to Direct Crystal Growth 39 

 Weightlessness Effects on Grain and Metal 39 

OASIS INSTRUMENTATION 40 

STS-26 PAYLOAD AND VEHICLE WEIGHTS 42 

MAJOR ORBITER MODIFICATIONS 43 

SOLID ROCKET MOTOR REDESIGN 44 

SPACE SHUTTLE MAIN ENGINE IMPROVEMENTS 47 

SPACEFLIGHT TRACKING AND DATA NETWORK 48 

NASA-CONTROLLED TRACKING STATIONS 49 

HUNTSVILLE OPERATIONS SUPPORT CENTER 50 

STS-26 MENU 51 

CREW BIOGRAPHIES 57 

SPACE SHUTTLE PROGRAM MANAGEMENT 60 

ACRONYMS AND ABBREVIATIONS 62 
Edited by Richard W. Orloff, 01/2001/Page 5

RELEASE: 88-121 September, 1988 

STS-26 -- THE RETURN TO FLIGHT 

The Space Shuttle will return to flight when the orbiter Discovery is launched on its seventh flight now 

scheduled for no earlier than late September, 1988. 

STS-26 will have as its primary payload the Tracking and Data Relay Satellite (TDRS-C) that will 

complete the constellation needed to communicate with spacecraft in low-Earth orbit. TDRS-B was lost in 

the 51-L Challenger accident. A third TDRS will be launched on a later Shuttle mission to replace the first 

TDRS, which then will be used as an on-orbit spare in the event that one of the two operational satellites 

fails. 

Commander of the five-man crew is Frederick H. (Rick) Hauck, captain, USN, a veteran of two Shuttle 

missions -- 51-A and STS-7. Pilot for the mission is Richard O. (Dick) Covey, a colonel in the USAF and 

veteran of the 51-I Shuttle mission. 

Three mission specialists are assigned to the crew: John M. (Mike) Lounge, David C. Hilmers, lt. colonel, 

USMC, and George D. (Pinky) Nelson. STS-26 will be the second flight for Lounge and Hilmers who 

previously flew on missions 51-I and 51-J, respectively. Nelson has flown two previous Shuttle missions -- 

41-C and 61-C. 

Discovery is scheduled to be launched from the Kennedy Space Center, Fla., Launch Pad 39-B, into a 

160-nautical-mile, 28.5 degree orbit. Liftoff is planned for (TBD) a.m. EDT. Nominal mission duration is 4 

days and 1 hour, with landing at Edwards Air Force Base, Calif., on Sept. (TBD), 1988, at (TBD) a.m. 

EDT. 

TDRS-C will be deployed 6 hours, 13 minutes into the mission on flight day one. There are two additional 

deploy times available on that day and one the following day. The 5,000-pound satellite will join the first 

TDRS, deployed on STS-6 in April 1983, to provide communications and data links between Earth and 

the Shuttle, as well as other spacecraft. 

TDRS-A is now in geosynchronous orbit (22,300 mi.) over the Atlantic Ocean east of Brazil (41 degrees 

west longitude). Following deployment from Discovery, TDRS-C will undergo testing and will be moved 

to its operational position over the Pacific Ocean south of Hawaii (171 degrees W. longitude). 

An Air Force-developed inertial upper stage (IUS) will boost the TDRS to geosynchronous orbit. The IUS 

is mated to the TDRS-C and the combination spacecraft and upper stage will be spring ejected from the 

orbiter payload bay. 

Following deployment, Discovery will maneuver to a position 36 nautical mi. behind and 16 nautical mi. 

above the TDRS-C/IUS before the two-stage motor ignites about 60 minutes after deployment. The 

three-axis, stabilized upper stage will maneuver the TDRS to the desired attitude. TDRS then will be 

configured for operation by the White Sands Ground Terminal, N.M. 

CONTEL, Atlanta, Ga., owns and operates the TDRS system for NASA. TRW's Defense and Space 

Systems Group, Redondo Beach, CA, built the satellites. 

The Orbiter Experiments Program Autonomous Supporting Instrumentation System (OASIS) will be flown 

on STS-26 to record environmental data in the orbiter payload bay during STS flight phases. OASIS will 

measure TDRS vibration, strain, acoustics and temperature during orbiter ascent, using transducers affixed 

directly to the payload. 

OASIS flight hardware consists of signal conditioning, multiplexing and recording equipment mounted on 

a Shuttle adaptive payload carrier behind the TDRS. Command and status interface is achieved through the 

standard mixed cargo harness and the general purpose computers. 
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In addition to TDRS-C and OASIS, Discovery will carry 11 secondary payloads, including two student 

experiments, involving microgravity research, materials processing and electrical storm studies. 

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

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

for its next flight. 

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

NASA Select Television Transmission 

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

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

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

Washington, DC 

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

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

Special Note to Broadcasters 

Beginning in September and continuing throughout the mission, approximately 7 minutes of audio 

interview material with the crew of STS-26 will be available to broadcasters by calling 202/269-6572. 

Status Reports 

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

produced by the appropriate NASA news center. 

Briefings 

An STS-26 mission press briefing schedule will be issued prior to launch. During the mission, flight 

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

occur at approximately 8-hour intervals. 
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STS-26 -- QUICK LOOK 

Crew: Frederick H. (Rick) Hauck, commander 

 Richard O. Covey, pilot 

 John M. (Mike) Lounge, mission specialist (MS-1) 

 David C. Hilmers, mission specialist (MS-2) 

 George D. (Pinky) Nelson, mission specialist (MS-3) 

Orbiter: Discovery (OV-103) 

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

Launch Date: Late September, 1988 

Launch Time: (TBD) a.m. EDT 

Launch Window: 3 hours 

Orbital Inclination: 28.45 degrees 

Altitude: 160 nautical miles 

Mission Duration: 4 days, 1 hour 

Landing Date/Time: Sept. (TBD), 1988, (TBD) a.m. EDT 

Primary Landing Site: Edwards AFB, CA 

Weather Alternate: White Sands Space Harbor, NM 

Trans-Atlantic Abort: Ben Guerir, Morocco 

Abort-Once-Around: Edwards AFB, CA 

Primary Payload: Tracking and Data Relay Satellite (TDRS-C) 

Secondary Payloads: Automatic Directional Solidification Furnace (ADSF) 

 Physical Vapor Transport of Organic Solids (PVTOS) 

 Infrared Communications Flight Experiment (IRCFE) 

 Protein Crystal Growth Experiment (PCG) 

 Isoelectric Focusing Experiment (IEF) 

 Phase Partitioning Experiment (PPE) 

 Aggregation of Red Blood Cells (ARC) 

 Mesoscale Lightning Experiment (MLE) 

 Earth-Limb Radiance Experiment (ELRAD) 

 2 Shuttle Student Involvement Program (SSIP) Experiments 

STS-26 MISSION OBJECTIVES 

The primary objective of STS-26 is to deliver NASA's second Tracking and Data Relay Satellite to orbit. 

The TDRS-C deployment will occur 6 hours, 6 minutes into the flight on Orbit 5. Day 2 is reserved for 

backup deployment opportunities. Experiments will be activated and performed throughout the flight. 
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LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF 

Discovery was selected as the Space Shuttle for the STS-26 mission in 1986. At the time of the 51-L 

accident, Discovery was in temporary storage in the KSC Vehicle Assembly Building (VAB) awaiting 

transfer to the Orbiter Processing Facility (OPF) for preparation for the first Shuttle flight from 

Vandenberg Air Force Base, CA, scheduled for later that year. Discovery last flew in August 1985 on 

Shuttle mission 51-I, the orbiter's sixth flight since it joined the fleet in November 1983. 

In January 1986, the Shuttle Atlantis was in the OPF, prepared for the Galileo mission and ready to be 

mated to the boosters and tank in the VAB. The orbiter Columbia had just completed the 61-C mission a 

few weeks prior to the accident and was also in the OPF undergoing post-flight deconfiguration. 

Various Shuttle manifest options were being considered, and it was determined that Atlantis would be 

rolled out to Launch Pad 39-B for fit checks of new weather protection modifications and for an 

emergency egress exercise and a countdown demonstration test. During that year it also was decided that 

Columbia would be flown to Vandenberg for fit checks. Discovery was then selected for the STS-26 

mission. 

Discovery was moved from the VAB High Bay 2, where it was in temporary storage, into the OPF the last 

week of June 1986. Power up modifications were active on the orbiter's systems until mid-September 1986 

when Discovery was transferred to the VAB while facility modifications were performed in Bay 1 of the 

OPF. 

Discovery was moved back into the OPF bay 1 on Oct. 30, 1987, a milestone that initiated an extensive 

modification and processing flow to ready the vehicle for flight. The hiatus in launching offered an 

opportunity to "tune-up" and fully check out all of the orbiter's systems and treat the orbiter as if it was a 

new vehicle. Most of the orbiter's major systems and components were removed and sent to the respective 

vendors for modifications or to be rebuilt. 

After an extensive powered-down period of 6 months, which began in February 1987, Discovery's systems 

were awakened when power surged through its electrical systems on Aug. 3, 1987. 

Discovery remained in the OPF while workers implemented over 200 modifications and outfitted the 

payload bay for the Tracking and Data Relay Satellite. 

Flight processing began in mid-September during which the major components of the vehicle were 

reinstalled and checked out, including the main engines, the right and left hand orbital maneuvering system 

pods and the forward reaction control system. 

In January 1988, Discovery's three main engines arrived at KSC and were installed. Engine 2019 arrived 

Jan. 6, 1988, and was installed in the number one position Jan. 10. Engine 2022 arrived Jan. 15 and was 

installed in the number 2 position Jan. 24. Engine 2028 arrived Jan. 21 and was installed in the number 3 

position also on Jan. 24. 

The redesigned solid rocket motor segments began arriving at KSC March 1, and the first segment, the left 

aft booster, was stacked on Mobile Launcher 2 in VAB High Bay 3 on March 29. Technicians started with 

the left aft booster and continued stacking the four left hand segments before beginning the right 

hand segments on May 5. The forward assemblies/nose cones were attached May 27 and 28. The SRB field 

joints were closed out prior to mating the external tank to the boosters on June 10. An interface test 

between the boosters and tank was conducted a few days later to verify the connections. 

The OASIS payload was installed in Discovery's payload bay on April 19. 

The TDRS arrived at the Vertical Processing Facility on May 16, and its Inertial Upper Stage (IUS) arrived 

May 24. The TDRS/IUS mechanical mating was accomplished on May 31. 
Edited by Richard W. Orloff, 01/2001/Page 10

Discovery was moved from the OPF to the VAB June 21, where it was mated to the external tank and solid 

rocket boosters. A Shuttle Interface Test was conducted shortly after the mate to check out the mechanical 

and electrical connections between the various elements of the Shuttle vehicle and the function of the 

onboard flight systems. 

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

July 4, 4.2 miles to Launch Pad 39-B for a few major tests and final launch preparations. 

A few days after Discovery's orbital maneuvering system pods were loaded with hypergolic propellants, a 

tiny leak was detected in the left pod (June 14). Through the use of a small, snake-like, fiber optics 

television camera, called a Cobra boroscope, workers pinpointed the leak to a dynatube fitting in the vent 

line for the reaction control system nitrogen tetroxide storage tank, located in the top of the OMS pod. 

The tiny leak was stabilized and controlled by "pulse-purging" the tank with helium - an inert gas. 

Pulse-purge is an automatic method of maintaining a certain amount of helium in the tank. In addition, 

console operators in the Launch Control Center firing room monitored the tank for any change that may 

have required immediate attention. It was determined that the leak would not affect the scheduled Wet 

Countdown Demonstration Test (WCDDT) and the Flight Readiness Firing (FRF) and repair was delayed 

until after these important tests. 

The WCDDT, in which the external tank was loaded with liquid oxygen and liquid hydrogen, was 

conducted August 1. A few problems with ground support equipment resulted in unplanned holds during 

the course of the countdown. 

A leak in the hydrogen umbilical connection at the Shuttle tail service mast developed while liquid 

hydrogen was being loaded into the external tank. Engineers traced the leak to a pressure monitoring 

connector. During the WCDDT, the leak developed again. The test was completed with the liquid 

hydrogen tank partially full and the special tanking tests were deleted. Seals in the 8-inch fill line in the tail 

service mast were replaced and leak checked prior to the FRF. 

In addition, the loading pumps in the liquid oxygen storage farm were not functioning properly. The pumps 

and their associated motors were repaired. 

After an aborted first attempt, the 22-second flight readiness firing of Discovery's main engines was 

conducted August 10. The first FRF attempt was halted inside the T-10 second mark due to a sluggish fuel 

bleed valve on the number 2 main engine. This valve was replaced prior to the FRF. This firing verified 

that the entire Shuttle system - including launch equipment, flight hardware and the launch team - were 

ready for flight. With over 700 pieces of instrumentation installed on the vehicle elements and launch pad, 

the test provided engineers with valuable data, including characteristics of the redesigned solid rocket 

boosters. 

After the test, a team of Rockwell technicians began repairs to the OMS pod leak. Four holes were cut into 

two bulkheads with an air powered router on Aug. 17. A metal "clamshell" device was bolted around the 

leaking dynatube fitting. The clamshell was filled with Furmanite - a dark thick material which consists of 

graphite, silicon and heavy grease and glass fiber. After an initial leak check was successfully performed, 

covers were bolted over the holes August 19, and the tank was pressurized to monitor any decay. No 

leakage or decay in pressure was noted and the fix was deemed a success. 

TDRS-C and its IUS upper stage were transferred from the VPF to Launch Pad 39-B on August 15. The 

payload was installed into Discovery's payload bay August 29. 

A Countdown Demonstration Test, a dress rehearsal for the STS-26 flight crew and KSC launch team, is 

designed as a practice countdown for the launch. At press time, it was planned for September 8. 
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Launch preparations scheduled the last two weeks prior to launch countdown include final vehicle 

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

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

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

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

liftoff since January 28, 1986. The STS-26 launch will be conducted by a joint NASA/industry team from 

Firing Room 1 in the Launch Control Center. 
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MAJOR COUNTDOWN MILESTONES 

T-43 Hours Power up the Space Shuttle 

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

T-30 Hours Activate Discovery's navigation aids 

T-25 Hours Load the power reactant storage and distribution system with liquid oxygen 

T-22 Hours Load liquid hydrogen into the power reactant storage and distribution system 

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

T-19 Hours Perform interface check between Houston-Mission Control and the Merritt Island 

Launch Area (MILA) tracking station 

T-13 Hours Perform pre-ingress switch list in the flight and middecks 

T-11 Hours Start 8 hour, 40 minute built-in hold (This time could be adjusted based on day of 

launch) 

T-11 Hours (counting) Retract Rotating Service Structure away from vehicle to launch position 

T-9 Hours Activate orbiter's fuel cells 

T-8 Hours Configure Mission Control communications for launch; clear blast danger area 

T-7 Hours Perform Eastern Test Range open loop command test 

T-6 Hours Start external tank chilldown and propellant loading 

T-5 Hours Start IMU pre-flight calibration 

T-4 Hours Perform MILA antenna alignment 

T-3 Hours Begin 2-hour built-in hold; external tank loading complete; ice team goes to pad for 

inspections; wake flight crew (launch minus 4 hours, 20 minutes) 

T-3 Hours (counting) Weather briefing; closeout crew has "go" to proceed to the White Room to begin 

preparing Discovery's cockpit for the flight crew's entry 

T-2 Hours, 30 Min Flight crew departs O&C Building for Launch Pad 39-B (launch minus 2 hours, 50 

minutes) 

T-2 Hours Crew enters orbiter vehicle (launch minus 2 hours, 20 minutes) 

T-61 Min Start pre-flight alignment of IMUs 

T-20 Min Begin 10-minute, built-in hold 

T-20 Min (counting) Configure orbiter computers for launch 

T-9 Min Begin 10-minute, built-in hold; perform status check and receive launch director "go" 

T-9 Min (counting) Start ground launch sequencer 

T-7 Min, 30 Sec Retract orbiter access arm 

T-5 Min Pilot starts auxiliary power units; arm range safety, SRB ignition systems 

T-3 Min, 30 Sec Orbiter goes on internal power 

T-2 Min, 55 Sec Pressurize liquid oxygen tank for flight and retract gaseous oxygen vent hood 

T-1 Min, 57 Sec Pressurize liquid hydrogen tank 

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

sequence 

T-6.6 Sec "Go" for main engine start 

T-3 Sec Main engines at 90 percent thrust 

T-0 SRB ignition, holddown post release and liftoff 

T+7 Sec Shuttle clears launch tower and control switches to Johnson Space Center 
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SUMMARY OF MAJOR ACTIVITIES 

Flight Day 1 

Ascent 

Post-insertion checkout 

TDRS-C/IUS deploy 

ADSF, PCG, PVTOS, ARC activation 

Flight Day 2 

Backup TDRS-C/IUS deploy opportunity 

PPE 

Flight Day 3 

ELRAD 

SSIP 

Deorbit prep rehearsal 

Flight Day 4 

PPE 

Flight control systems checkout 

Cabin stowage 

Landing preparations 

Flight Day 5 

Deorbit preparations 

Deorbit burn 

Landing at EAFB 
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STS-26 TRAJECTORY SEQUENCE OF EVENTS 

Event 

MET 

(d/h:m:s) 

Inertial 

Velocity 

(fps) 

 

Launch 00/00:00:00 

Begin roll maneuver 00/00:00:07 1,346 

End roll maneuver 00/00:00:14 1,418 

Begin SSME throttle down to 65% 00/00:00:27 1,728 

Begin SSME throttle up to 104% 00/00:00:59 2,404 

Maximum dynamic pressure (Max Q) 00/00:01:04 2.551 

SRB staging 00/00:02:04 5,326 

Negative return 00/00:04:04 8,275 

Main engine cutoff (MECO)* 00/00:08:31 25,783 

Zero thrust 00/00:08:38 25,871 

OMS-2 burn** 00/00:39:55 

TDRS/IUS deploy 00/06:13:00 

Deorbit burn 03/23:56:00 

Landing 04/00:56:00 

* Apogee, perigee at MECO: 156 x 35 nautical miles 

** Direct insertion ascent: no OMS-1 required 

Apogee, perigee post-OMS-2: 161 x 160 nm 
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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 Edwards Air Force Base, Calif.; White Sands Space Harbor, N.M.; 

or the Shuttle Landing Facility at Kennedy Space Center, FL 

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

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

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

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

within gliding distance of the KSC Shuttle Landing Facility. 

STS-26 contingency landing sites are Edwards AFB, White Sands Space Harbor, Kennedy Space Center, 

Ben Guerir, Moron and Banjul. 
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LANDING AND POST-LANDING OPERATIONS 

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

runway at Edwards Air Force Base. Those operations include preparing the Shuttle for the return trip to 

Kennedy. 

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

stop, specially garbed technicians will determine that any residual hazardous vapors around the orbiter are 

below significant levels, before proceeding to other safing operations. 

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

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

end of Discovery. 

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

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

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

Discovery. 

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

toxic gases around the forward part of the vehicle. The crew is expected to leave Discovery about 30 to 40 

minutes after landing. As the crew exits, technicians enter the orbiter to complete the vehicle safing 

activity. 

A tow tractor will be connected to Discovery to pull it off the runway at Edwards and position it inside the 

Mate/Demate Device (MDD) at the nearby Dryden Flight Research Facility. After the Shuttle has been 

jacked and leveled, residual fuel cell cryogenics are drained and unused pyrotechnic devices are 

disconnected prior to returning the orbiter to Kennedy. 

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

747 Shuttle Carrier Aircraft for the ferry flight back to Florida. The 747 is scheduled to leave California 

about 6 days after landing. An overnight stop is scheduled for refueling and the ferry flight continues the 

next day. 

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

and in-flight anomaly trouble shooting. These operations are conducted in parallel with the start of routine 

systems reverification to prepare Discovery for its next mission. 
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TRACKING AND DATA RELAY SATELLITE SYSTEM 

The Tracking and Data Relay Satellite (TDRS-C) is the third TDRS advanced communications spacecraft 

to be launched aboard the Space Shuttle. TDRS-1 was launched during Challenger's maiden flight in April 

1983. The second, TDRS-B, was lost during the Challenger accident of January 1986. 

TDRS-1 is now in geosynchronous orbit over the Atlantic Ocean just east of Brazil (41 degrees west 

longitude). It initially failed to reach its desired orbit, following successful Shuttle deployment, because of 

booster rocket failure. A NASA-industry team conducted a series of delicate spacecraft maneuvers over a 

2-month period to place TDRS-1 into the desired 22,300 mile altitude. 

Following arrival at geosynchronous altitude, TDRS-C (TDRS-3 in orbit) will undergo a series of tests 

prior to being moved to its operational geosynchronous position over the Pacific Ocean south of Hawaii 

(171 degrees W. longitude). 

TDRS-3 and its identical sister satellite will support up to 23 user spacecraft simultaneously, providing two 

basic types of service -- a multiple access service which can simultaneously relay data from as many as 19 

low-data-rate user spacecraft, and a single access service which will provide two high-data-rate 

communication relays from each satellite. 

TDRS-3 will be deployed from the orbiter approximately 6 hours after launch. Transfer to geosynchronous 

orbit will be provided by the solid propellant Boeing/U.S. Air Force Inertial Upper Stage (IUS). Separation 

from the IUS occurs approximately 13 hours after launch. 

The next TDRS spacecraft, currently targeted for launch in January 1989, will replace the 

partially-degraded TDRS-1 over the Atlantic. TDRS-1 will be moved to a location between the two 

operational TDRS spacecraft and serve as an on-orbit spare. 

The concept of using advanced communications satellites was developed following studies in the early 

1970s which showed that a system of communication satellites operated, from a single ground terminal, 

could support Space Shuttle and other low Earth-orbit space missions more effectively than a worldwide 

network of ground stations. 

NASA's Space Tracking and Data Network ground stations will be significantly reduced in number. Three 

of the network's present ground stations -- Madrid, Spain; Canberra, Australia; and Goldstone, Calif. -- 

already have been transferred to the Deep Space Network managed by NASA's Jet Propulsion Laboratory 

in Pasadena, CA. 

The remaining ground stations, except those necessary for launch operations, will be closed or transferred 

to other agencies after the successful launch and checkout of the next two TDRS satellites. 

The ground station network, managed by the Goddard Space Flight Center, Greenbelt, Md., provides 

communications support for only a small fraction (typically 15-20 percent) of a space craft's orbital period. 

The TDRSS network, when established, will provide coverage for almost the entire orbital period of 

user spacecraft (about 85 percent). 

A TDRSS ground terminal has been built at White Sands, NM, a location that provides a clear view to the 

TDRSS satellites and weather conditions generally good for communications. 

The NASA ground terminal at White Sands provides the inter face between the TDRSS and its network 

elements, which have their primary tracking and communication facilities at Goddard. Also located at 

Goddard is the Network Control Center, which provides system scheduling and is the focal point for 

NASA communications with the TDRSS satellites and network elements. 
Edited by Richard W. Orloff, 01/2001/Page 19

The TDRSS satellites are the largest, privately-owned telecommunications spacecraft ever built, each 

weighing about 5,000 lbs. Each satellite spans more than 57 ft., measured across its solar panels. The 

single-access antennas, fabricated of molybdenum and plated with 14K gold, each measure 16 ft. in 

diameter and, when deployed, span more than 42 ft. from tip to tip. 

The satellite consists of two modules. The equipment module houses the subsystems that operate the 

satellite. The telecommunications payload module has electronic equipment for linking the user spacecraft 

with the ground terminal. The TDRS has 7 antennas and is the first designed to handle communications 

through S, Ku and C frequency bands. 

Under contract, NASA has leased the TDRSS service from CONTEL, Atlanta, Ga., the owner, operator 

and prime contractor for the system. 

TRW Space and Technology Group, Redondo Beach, CA, and the Harris Government Communications 

System Division, Melbourne, FL, are the two primary subcontractors to CONTEL for spacecraft and 

ground terminal equipment, respectively. TRW also provided the software for the ground segment 

operation and integration and testing for the ground terminal and the TDRSS, as well as the systems 

engineering. 

Primary users of the TDRSS satellite have been the Space Shuttle, Landsat Earth resources satellites, the 

Solar Mesosphere Explorer, the Earth Radiation Budget Satellite, the Solar Maximum Mission satellite and 

Spacelab. 

Future users include the Hubble Space Telescope, scheduled for launch in mid-1989, the Gamma Ray 

Observatory and the Upper Atmosphere Research Satellite. 
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INERTIAL UPPER STAGE 

The Inertial Upper Stage (IUS) will be used to place NASA's Tracking and Data Relay Satellite (TDRS-C) 

into geosynchronous orbit during the STS-26 Space Shuttle mission. 

The STS-26 crew will deploy the combined IUS/TDRS-C payload approximately 6 hours, 13 minutes after 

liftoff, at a low-Earth orbit of 160 nautical miles. Upper stage airborne support equipment, located in the 

orbiter payload bay, positions the combined IUS/TDRS-C into its proper deployment attitude -- an angle of 

58 degrees -- and ejects it into low-Earth orbit. Deployment from the orbiter will be by a spring-ejection 

system. 

Following the deployment, the orbiter will move away from the IUS/TDRS-C to a safe distance. The IUS 

first stage will fire about 1 hour after deployment. 

After the first stage burn of 145 seconds, the solid fuel motor will shut down. After coasting for about 5 

hours, 15 minutes, the first stage will separate and the second stage motor will ignite at 12 hours, 29 

minutes after launch to place the spacecraft in its desired orbit. Following a 103-second burn, the second 

stage will shut down as the IUS/TDRS-C reaches the predetermined, geosynchronous orbit position. 

Thirteen hours, 7 minutes after liftoff, the second stage will separate from TDRS-C and perform an 

anti-collision maneuver with its onboard reaction control system. 

After the IUS reaches a safe distance from TDRS-C, the second stage will relay performance data to a 

NASA tracking station and then shut itself down 13 hours, 17 minutes after launch. 

The IUS has a number of features which distinguish it from previous upper stages. It has the first 

completely redundant avionics system developed for an unmanned space vehicle. It can correct in-flight 

features within milliseconds. 

Other advanced features include a carbon composite nozzle throat that makes possible the 

high-temperature, long-duration firing of the IUS motors and a redundant computer system in which the 

second computer is capable of taking over functions from the primary computer, if necessary. 

The IUS is 17 ft. long, 9 ft. in diameter and weighs more than 32,000 lbs., including 27,000 lbs. of solid 

fuel propellant. 

The IUS consists of an aft skirt, an aft stage containing 21,000 lbs. of solid propellant which generates 

45,000 lbs. of thrust, an interstage, a forward stage containing 6,000 lbs. of propellant generating 18,500 

lbs. of thrust and an equipment support section. The equipment support section contains the avionics which 

provide guidance, navigation, telemetry, command and data management, reaction control and electrical 

power. 

The IUS is built by Boeing Aerospace, Seattle, under contract to the U.S. Air Force Systems Command. 

Marshall Space Flight Center, Huntsville, Ala., is NASA's lead center for IUS development and program 

management of NASA-configured IUSs procured from the Air Force. 

TDRS-A was placed into an elliptical Earth orbit by an IUS in April 1983 during mission STS-6. TDRS-B 

and its IUS were lost in the Challenger accident in January 1986. 
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SECONDARY PAYLOADS 

Physical Vapor Transport of Organic Solids 

3M Company scientists will fly an experiment on STS-26 to produce organic thin films with ordered 

crystalline structures and to study their optical, electrical and chemical properties. 

They call the experiment the Physical Vapor Transport of Organic Solids (PVTOS), a name derived from 

the method which is employed to produce organic crystals -- vapor transport. 

Engaged in a long-term space research program that will extend into the Space Station era, 3M's primary 

objective with the STS-26 experiment is to build upon the knowledge gained from an earlier flight of the 

apparatus aboard Discovery in 1985. 

For more than a decade, 3M scientists have conducted research into ordered organic thin films with an 

emphasis on controlling the film's physical structure properties so as to affect the film's optical, electrical 

and chemical behavior. 

Using the physical vapor transport technique in the micro gravity environment of low-Earth orbit allows 

3M scientists a unique opportunity to investigate certain materials of interest. The results could eventually 

be applied to production of specialized thin films on Earth or in space. 

The PVTOS experiment consists of nine independent cells 12 inches long and 3 inches in diameter. Each 

cell contains a test tube-like ampoule containing organic material. During space flight, the organic material 

is vaporized. Migrating through a buffer gas, the vaporized material forms a highly ordered thin film on a 

flat surface. After the samples are returned to Earth, 3M scientists will study the films produced in space. 

The PVTOS experiment, sponsored by NASA's Office of Commercial Programs, is being conducted by 

3M's Space Research and Applications Laboratory, headed by Dr. Christopher N. Chow. Dr. Mark Debe is 

principal investigator with Dr. Earl Cook as co-investigator. 
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Protein Crystal Growth Experiment 

Protein Crystal Growth (PCG) experiments to be conducted during STS-26 are expected to help advance a 

technology attracting intense interest from major pharmaceutical houses, the biotech industry and 

agrochemical companies. 

A team of industry, university and government research investigators will explore the potential advantages 

of using protein crystals grown in space to determine the complex, three-dimensional structure of specific 

protein molecules. 

Knowing the precise structure of these complex molecules provides the key to understanding their 

biological function and could lead to methods of altering or controlling the function in ways that may result 

in new drugs. 

It is through sophisticated analysis of a protein in crystallized form that scientists are able to construct a 

model of the molecular structure. The problem is that protein crystals grown on Earth are often small and 

flawed. Protein crystal growth experiments flown on four previous Space Shuttle missions already have 

shown promising evidence that superior crystals can be obtained in the microgravity environment of space 

flight. 

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

Office of Commercial Programs and Microgravity Science and Applications Division are co-sponsoring 

the STS 26 experiments which are being managed through the Marshall Space Flight Center, Huntsville, 

AL. 

During the flight, 60 different crystal growth experiments, including as many as ten distinct proteins, will 

be attempted in an experiment apparatus that fits into one of the Shuttle orbiter's middeck lockers. 

Shortly after achieving orbit, astronauts will initiate the crystal growing process, which will continue for 

several days. The experiment apparatus, being flown for the first time on STS-26, differs from previous 

protein crystal payloads in that it provides temperature control and automation of some processes. 

After Discovery's landing, the experiment hardware and protein crystals will be turned over to the 

investigating team for analysis. Lead investigator for the research team is Dr. Charles E. Bugg of the 

University of Alabama-Birmingham (UAB). Dr. Bugg is director of the Center for Macromolecular 

Crystallography, a NASA-sponsored Center for the Commercial Development of Space located at UAB. 

Five industrial affiliates of the Center will provide samples to investigate the quality of protein crystals 

grown in space. Following post-flight analysis, crystals produced on the flight will be used by the 

participating industrial scientists for applied research. 

The industrial participants and their experiments are: 

Burroughs Wellcome Co., Research Triangle Park, NC, is experimenting with the enzyme reverse 

transcriptase. The enzyme is a chemical key to the replication of the AIDS virus. More detailed knowledge 

of its three-dimensional structure could lead to new drug treatments for AIDS. The investigators are Dr. 

Tom Krenitsky, Burroughs Wellcome Co. and Dr. David Stammers, Wellcome Research Laboratories. 

The Du Pont Company, Wilmington, Del., is conducting two experiments aimed at growing crystals of 

proteins important to life science research. One is isocystrate lyase, a target enzyme for fungicides. Better 

understanding of this enzyme should lead to more potent fungicides to treat serious crop diseases such as 

rice blast. The other protein is alpha 1-B, the first totally synthetic peptide which was recently synthesized 

by Du Pont to mimic ion channels in cell membranes. Research on alpha 1-B will lead to a better 

understanding of the manner in which cells selectively regulate the flow of ions such as potassium, sodium, 

and calcium in and out of the cell. It has important potential in therapeutics and diagnostics. Du Pont's 

principal investigator is Dr. Ray Salemme. 
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Merck, Rahway, N.J., will fly a sample of elastace, an enzyme associated with the degradation of lung 

tissue in people suffering from emphysema. A more detailed knowledge of this enzyme's structure will be 

useful in studying the causes of this debilitating disease. The company's principal investigator is Dr. 

Manuel Navia. 

Schering-Plough, Madison, N.J., will experiment to grow crystals of alpha interferon. Interferon, a protein, 

stimulates the body's immune system. Marketed as "Intron A," the company's alpha interferon is approved 

in the U.S. for treating a cancer, hairy cell leukemia, and a viral infection, genital warts. It is also approved 

overseas for treating these and a number of other cancers and ailments. The principal investigator is Dr. 

T.J. Nagabhushan. 

Upjohn, Kalamazoo, Mich., is flying two protein samples: genetically-engineered human renin and 

phospholipase A2, found in the venom of the cottonmouth snake. Human renin is produced by the kidneys 

and plays a major role in the chemical reaction that controls blood pressure. Phospholipase performs 

functions associated with cell membranes, and a better understanding of it could lead to improved 

medications for pain and inflammation. Upjohn's principal investigator is Dr. Howard Einspahr. 
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Infrared Communications Flight Experiment 

Using the same kind of invisible light that remotely controls our home TV sets and VCRs, mission 

specialist George "Pinky" Nelson is to conduct experimental voice communications with his STS-26 

crewmates via infrared, rather than standard radio frequency waves. 

On a non-interfering basis and during non-critical normal crew activities requiring voice operations, 

Nelson will unstow the Infrared Communications Flight Experiment (IRCFE) from the middeck locker and 

begin a minimum of 2 hours of experimentation from both flight- and middeck locations. 

Six small infrared transmitters and receivers (three each) will be attached by Velcro to Discovery's walls: 

two each on the flight deck and one each on the middeck. The transmitters and receivers are connected by 

cable to a base unit which also will be attached by Velcro to a middeck wall. Nelson will plug his standard 

lightweight headset into a belt-mounted unit which will transmit his voice via infrared lightwaves through 

the receivers to the base unit. There, the signal will be relayed to other crew members using the standard 

Orbiter audio distribution system. Communications back to Nelson from the other astronauts will travel by 

the reverse path. 

One major objective of the experiment is to demonstrate the feasibility of the secure transmission of 

information via infrared light. Unlike radio frequency (RF) signals, infrared waves will not pass through 

the orbiter's windows; thus, a secure voice environment would be created if infrared waves were used as 

the sole means of communications within the orbiter. Infrared waves also can carry data as well as voice 

(e.g., biomedical information). Future infrared systems are expected to be smaller, lighter weight and 

produce better voice quality than their RF counterparts. 

A clear line-of-sight path is not required between transmitter and receiver to insure voice transmission. 

Infrared light will reflect from most surfaces and therefore, quality voice can be transmitted even after 

multiple bounces. As Nelson moves around the vehicle, another major objective is to demonstrate a 

"flooded volume approach," that is, to see if the wall-mounted transmitters/receivers will pick up and 

deliver infrared signals without the need for him to precisely align his transmitter with a target receiver. 

The amount of coverage and/or blockage which occurs during the experiment under microgravity 

conditions is a critical objective of the experiment. Comments by Nelson and his crewmates on the 

effectiveness and quality of the system will be relied on heavily. Post-flight analysis of the infrared 

system's voice quality also will be made through tape comparisons. 

While the IRCFE calls for a minimum of 2 hours of experimentation, there are no constraints on continuing 

use of the system beyond that time. However, the experiment must be restowed in its locker prior to 

descent. The 20-lb. IRCFE package, which includes a complete back-up unit, fits in less than 1/2 of a 

2-cubic-ft. middeck locker. 

If proven effective, the technique of using infrared light as a voice and information carrier could have 

widespread application including incorporation in the Shuttle, Spacelab and the Space Station as well as 

potential non-NASA uses in military aircraft, naval ships and Army combat vehicles. 

The IRCFE was developed at a cost of approximately $500,000 by Johnson Space Center, Houston, and its 

contractor, Wilton Industries, Danbury, Conn. Project manager and principal investigator for the 

experiment is Joseph L. Prather, of the Engineering Directorate's Tracking and Communications Division 

at JSC. 
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Automated Directional Solidification Furnace 

The Automated Directional Solidification Furnace (ADSF) is a special space furnace developed and 

managed by Marshall Space Flight Center. It is designed to demonstrate the possibility of producing 

lighter, stronger and better-performing magnetic composite materials in a microgravity environment. 

Four furnace modules are included in the ADSF, each processing a single sample. The samples being used 

during the STS-26 mission are manganese and bismuth composites. They will be processed at a constant 

melting and resolidification speed of one about a third of an inch an hour. The total process times will be 

10.5 hours per sample. 

Material processed during the mission will be compared with samples of the same metallic alloys processed 

in laboratories on Earth, as well as from previous Shuttle and sounding rocket flights. Thermal, X-ray, 

chemical, structural and magnetic analysis will be made following the flight to determine differences in the 

various samples. 

The furnace is specially designed to melt along a plane in a long, slim, magnetic composite sample and 

then cool the molten metal behind the melt. The furnace module traverses the sample in a single direction, 

melting and then resolidifying the material as it goes. 

The ADSF flight hardware is housed in three separate containers connected by power and data cables. The 

four furnaces are housed in one container; another container has the electronic assembly which controls 

furnace operations and yet another houses the control switches, status indicators and a system which 

records data produced during the operation of the furnaces. 

The total flight package weighs about 250 lbs. and occupies the space of five crew lockers in the orbiter 

middeck. The equipment is highly automated and requires crew interaction only to initiate the operation of 

the furnaces. 

All the ADSF hardware is reusable. The furnace apparatus was first flown aboard sounding rockets. It has 

been modified to be compatible with the orbiter and crew interface requirements and to increase the 

furnace operating time. 

Each furnace can now operate up to 20 hours, compared to a total of 5 minutes during the sounding rocket 

flights. The experiment most recently flew aboard STS 51-G. 

Principal investigator for this experiment is Dr. David Larson, Grumman Aerospace Corp. MSFC manages 

the development of the hardware and provides mission integration management for NASA. Project 

manager is Fred Reeves, MSFC, and mission manager is Richard E. Valentine, also MSFC. 
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Aggregation of Red Blood Cells 

Blood samples from donors with such medical conditions as heart disease, hypertension, diabetes and 

cancer will fly in an experiment called Aggregation of Red Blood Cells (ARC) developed by Australia and 

managed by MSFC. 

The experiment is designed to provide information on the formation rate, structure and organization of red 

cell clumps, as well as on the thickness of whole blood cell aggregates at high and low flow rates. It will 

help determine if microgravity can play a beneficial role in new and existing clinical research and medical 

diagnostic tests. 

The first ARC experiment flew aboard STS 51-C in January 1985. The STS-26 experiment differs from its 

predecessor only in the samples tested. The experiment hardware is unchanged. 

The flight hardware weighs about 165 lbs. and is installed in three middeck lockers in the crew cabin. The 

experiment consists of a blood pump and storage subsystem, thermal control system, pressure transducer 

and an electronics equipment package to provide automated control and data acquisition. 

The ARC experiment uses eight experiment blood samples maintained at about 40 degrees F. Each flows 

one sample at a time, into a viscometer, two optically transparent polished glass plates separated by a 

spacer of platinum foil. 

Two 35mm cameras, located on either side of the viscometer, photograph the samples through 10x and 

300x power microscopes. The 10x power microscope uses black and white film and the 300x power uses 

color. 

After taking the photographic and low-rate data, the sample is discarded in a waste container. A saline 

solution, stored in syringes identical to those containing the blood samples, is then used to flush the system 

prior to running the next sample. 

All procedures are operated by the electronic equipment package except activation which is performed by 

one of the crew. Running time is about 8 hours. 

Results obtained in the Shuttle microgravity environment will be compared with results from a 

ground-based experiment to determine what effects gravity has on the kinetics and morphology of the 

sampled blood. The ground-based experiment will be conducted simultaneously with the flight experiment 

using samples identical in origin to the flight samples and functionally identical hardware. 

The experiment and hardware were developed by Dr. Leopold Dintenfass of the Kanematsu Institute, 

Department of Medical Research, Sydney, Australia. Richard E. Valentine, MSFC, is mission manager. 
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Isoelectric Focusing 

Isoelectric Focusing (IEF) is a type of electrophoresis experiment which separates proteins in an electric 

field according to their surface electrical charge. 

Three other electrophoresis experiments have flown before on Shuttle missions. They were the McDonnell 

Douglas Continuous Flow Electrophoresis System, NASA's Electrophoresis Equipment Verification Test 

and an earlier version of the IEF. 

The isoelectric focusing technique applies an electric field to a column of conducting liquid containing 

certain molecules which create a pH gradient in the column (alkalinity at one end, acidity at the other end). 

This pH gradient causes the biological sample to move to a location in the column where it has a zero 

charge - its isoelectric point. 

Protein and fluid-filled experiment columns are provided by the University of Arizona. The remainder of 

the flight hardware was designed and built by laboratory personnel at MSFC, which is providing mission 

management. 

The 65-pound experiment consists of eight glass columns containing protein, hemoglobin and albumen, 

with solutions which form the pH gradient column of conducting liquid. 

The columns are arranged in a row in the field of view of a 35 mm camera. The experiment is housed in a 

9-inch-high, 19 by 21-inch rectangular metal container and is installed in place of a middeck locker in the 

crew cabin. 

A crewmember will activate the equipment 23 hours into the flight. The experiment will operate for 90 

minutes with pictures of the separations being taken every 2 or 3 minutes. The crew member will return to 

the experiment hardware at the end of the running time to verify that it has successfully turned itself off. 

The film from the experiment camera will be removed for processing upon orbiter landing. The samples 

themselves are not required for post-mission analysis. 

Principal investigator on the experiment is professor Milan Bier of the University of Arizona. 

Co-investigator is Dr. Robert Snyder of the Separation Processes Branch at MSFC's Space Science 

Laboratory. Richard E. Valentine, MSFC, is the mission manager and Brian Barnett, MSFC, is the 

experiment coordinator. 
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Mesoscale Lightning Experiment 

Mesoscale Lightning Experiment (MLE) is an experiment designed to obtain night time images of 

lightning in an attempt to better understand the effects of lightning discharges on each other, on nearby 

storm systems and on storm microbursts and wind patterns and to determine interrelationships over an 

extremely large geographical area. 

The experiment will use Shuttle payload bay cameras to observe lightning discharges at night from active 

storms. The experiment uses color video cameras and a 35mm hand-held film camera and will provide 

synoptic coverage of an area roughly 200 by 150 miles directly below the Shuttle. 

Shuttle crewmembers also will document mesoscale storm systems that are oblique to the Shuttle but near 

NASA ground-based lightning detection systems at Marshall Space Flight Center, Kennedy Space Center, 

Stennis Space Center (formerly National Space Technology Laboratories), and the National Oceanic and 

Atmosphere Administration Severe Storms Laboratory, Norman, OK. 

The Shuttle payload bay camera system provides camera orientation data so that the locations and 

dimensions of the lightning discharges recorded can be easily determined from the video and film images. 

The imagery will be analyzed for the frequency of flashes, the size of the lightning and its brightness. 

Three co-investigators will analyze the lightning data taken from the Shuttle as well as corroborate 

information received from the ground-based lightning monitoring network. They are Dr. Bernard 

Vonnegut, State University of New York, Albany; Dr. Max Brook, New Mexico Institute of Mining and 

Technology, Socorro; and Otha H. Vaughan Jr., MSFC. Richard E. Valentine, MSFC, is the mission 

manager. 

Phase Partitioning Experiment 

One of the most important aspects of biotechnical and biomedical technology involves separation 

processes. Cell types producing important compounds must be separated from other cell types. Cells with 

important biomedical characteristics must be isolated to study those characteristics. This experiment 

involves a separation method termed two-phase partitioning. 

The Phase Partitioning Experiment (PPE) is designed to fine tune understanding of the role gravity and 

other physical forces play in separating, i.e., partitioning biological substances between two unmixable 

liquid phases. 

Most people are use to the two-phase systems formed by mixing oil and water. In PPE, the systems are 

simple saline solutions containing two different polymers. When the polymers are dissolved in solution, 

they separate. On Earth this results in the lighter phase floating on top of the heavier one. In space the 

demixed phases exhibit more complex behavior, looking somewhat like an egg which has a yolk floating 

inside of the egg white. 

Phase partitioning has been shown on Earth to yield more effective, large-scale cell separations than any 

other method, differentiating cells on the basis of their surface properties. Space experiments should 

improve efficiency of Earth-bound partitioning and may allow scientists to carryout cell separations 

unobtainable on Earth. 

The experiment is part of a category of handheld microgravity experiments designed to study the effects of 

the low gravity of spaceflight on selected physical processes. 

The experiment consists of an 18-chambered experimental module filled with small quantities of two-phase 

systems, each differing in various physical parameters (e.g. viscosity). The module will be shaken to mix 

the phases and the separation of the phases will be photographed periodically by a mission specialist. 
Edited by Richard W. Orloff, 01/2001/Page 37

The experiment will last approximately 2 hours. The 0.7 kilogram module is completely self-contained and 

will be stored in one of the middeck storage lockers. 

Photos of the separation will be taken with a 35mm Nikon camera equipped with an hour/minute/second 

time-tag using a 35-70 mm macro zoom lens. The photos will be studied when they are returned to Earth 

and analyzed by computer-aided densitometry for demixing-versus-time-kinetic information. 

A 15-chamber version of the PPE was successfully flown on STS 51-D, and the experiment is being 

considered for at least two more flights. 

The experiment was developed and is being managed by the Marshall Space Flight Center, Huntsville, Ala. 

The project is sponsored by NASA's Microgravity Science and Applications Division. 

The PPE scientific team includes Drs. Donald E. Brooks, principal investigator, University of British 

Columbia; J. Milton Harris, University of Alabama-Huntsville; James M. Van Alstine, Universities Space 

Research Associates at Marshall; Stephen Bamberger, National Research Council; and Robert S. Snyder, 

Marshall. Richard E. Valentine is the mission manager for PPE at Marshall. 
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Earth-Limb Radiance Experiment 

Earth Limb Radiance Experiment (ELRAD) is an experiment developed by the Barnes Engineering Co., 

designed to photograph the Earth's "horizon twilight glow" near sunrise and sunset. 

The experiment is expected to provide photographs of the Earth's horizon that will allow scientists to 

measure the radiance of the twilight sky as a function of the sun's position below the horizon. This 

information should allow designers to develop better, more accurate horizon sensors for geosynchronous 

communications satellites. 

Communications satellites routinely use the Earth's horizon or "limb" as a reference for attitude control. 

Barnes Engineering is developing an advanced horizon sensor that uses visible light to sense the Earth's 

limb. Near the spring and fall equinoxes, however, the Earth eclipses the sun once a day (as seen from the 

satellites' orbit), often for as long as 70 minutes. 

During these eclipses, the Earth's horizon is invisible to a visible light horizon sensor. However, the Earth's 

upper atmosphere scatters sunlight to produce a thin ring of blue and ultraviolet light that would still be 

visible even during an eclipse. This ring of light is what ELRAD will photograph. 

ELRAD consists of a 35mm Nikon camera, an 85mm lens, a blue lens filter and a timing device known as 

a intervalometer. Astronauts onboard the Space Shuttle will mount ELRAD in one of the Shuttle's windows 

and point it toward the Earth's horizon. The intervalometer will be set to take one photograph every 10 

seconds. Three sequences of photographs will be taken, one just before sunrise and two just after sunset. 

After the mission, the exposed film will be developed by NASA and provided to Barnes Engineering, 

along with a sensitivity curve. Barnes Engineering will then compute the radiance of the scattered light as 

recorded on the film. 

Principal investigator for ELRAD is William Surette, Barnes Engineering. Johnson Space Center manages 

the mission integration for NASA. The payload integration manager is Ed Jung and the mission manager is 

Willie Beckham, both from Johnson. 
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SHUTTLE STUDENT INVOLVEMENT PROGRAM 

Utilizing a Semi-Permeable Membrane to Direct Crystal Growth 

This is an experiment proposed by Richard S. Cavoli, formerly of Marlboro Central High School, 

Marlboro, N.Y. Cavoli is now enrolled at State University of New York, Buffalo School of Medicine, 

Buffalo, N.Y. 

The experiment will attempt to control crystal growth through the use of a semi-permeable membrane. 

Lead iodide crystals will be formed as a result of a double replacement reaction. Lead acetate and 

potassium iodide will react to form insoluble lead iodide crystals, potassium ions and acetate ions. As the 

ions travel across a semi-permeable membrane, the lead and iodide ions will collide, forming the lead 

iodide crystal. 

Cavoli's hypothesis states that the shape of the semi-permeable membrane and the concentrations of the 

two precursor compounds will determine the growth rate and shape of the resultant crystal without regard 

to other factors experienced in Earth-bound crystal growing experiments. 

Following return of the experiment apparatus to Cavoli, an analysis will be performed on the crystal color, 

density, hardness, morphology, refractive index and electrical and thermal characteristics. Crystals of this 

type are useful in imaging systems for detecting gamma and X-rays and could be used in spacecraft sensors 

for astrophysical research purposes. 

Cavoli's high school advisor is Annette M. Saturnelli of Marlboro Central High School, and his college 

advisor and experiment sponsor is Dr. Charles Scaife of Union College. 

Effects of Weightlessness on Grain Formation and Strength in Metals 

This experiment was proposed by Lloyd C. Bruce formerly of Sumner High School, St. Louis. Bruce is 

now a senior at the University of Missouri. 

The experiment proposes to heat a titanium alloy metal filament to near the melting point to observe the 

effect that weightlessness has on crystal reorganization within the metal. It is expected that heating in 

microgravity will produce larger crystal grains and thereby, increase the inherent strength of the metal 

filament. The experiment uses a battery supply, a timer and thermostat to heat a titanium alloy filament to 

1,000 degrees Celsius. 

At a temperature of 882 degrees C, the titanium-aluminum alloy crystal lattice network undergoes a 

metamorphosis from closely packed hexagonal crystals to centered cubic crystals. 

Following return of the experiment gear to Bruce, he will compare the space-tested alloy sample with one 

heated on Earth to analyze any changes in strength, size and shape of the crystal grains and any change in 

the homogeneity of the alloy. If necessary microscopic examination, stress testing and X-ray diffraction 

analysis also will be used. Any changes between the two samples could lead to variations on this 

experiment to be proposed for future Shuttle flights. A positive test might lead to a new, lightweight and 

stronger titanium-aluminum alloy or a new type of industrial process. 

Bruce's student advisor is Vaughan Morrill of Sumner High School. His sponsor is McDonnell Douglas 

Corp., St. Louis, and his experiment advisor is Dr. Diane Chong of McDonnell Douglas. 
Edited by Richard W. Orloff, 01/2001/Page 41

OASIS INSTRUMENTATION 

Special instrumentation to record the environment experienced by Discovery during the STS-26 mission is 

aboard the orbiter mounted in the payload bay. 

The Orbiter Experiments Autonomous Supporting Instrumentation System (OASIS) is designed to collect 

and record a variety of environmental measurements during various in-flight phases of the orbiter. The 

primary device is a large tape recorder which is mounted on the aft, port side of the orbiter. The OASIS 

recorder can be commanded from the ground to store information at a low, medium or high data rate. After 

Discovery's mission is over, the tapes will be removed for analysis. 

The information will be used to study the effects on the orbiter of temperature, pressure, vibration, sound, 

acceleration, stress and strain. It also will be used to assist in the design of future payloads and upper 

stages. 

OASIS is about desk-top size, approximately 4 ft. long, 1 ft. wide, 3 ft. deep and weighs 230 lbs. It was 

installed for flight in the payload bay on April 18. 

The OASIS data is collected from 101 sensors mounted on three primary elements. The sensors are located 

along the sills on either side of the payload bay, on the airborne support equipment of the Inertial Upper 

Stage and on the tape recorder itself. These sensors are connected to accelerometers, strain gauges, 

microphones, pressure gauges and various thermal devices on the orbiter. 

OASIS was exercised during the flight readiness firing of the Space Shuttle Discovery in August and data 

was collected for analysis. 

On STS-26 launch day, the system will be turned on 9 minutes before Discovery's liftoff to begin recording 

at high speed and recover high fidelity data. Following the first burn of the orbital maneuvering system, it 

will be switched to the low data rate. It will be commanded again to high speed for subsequent Shuttle 

OMS burns. 

Different data rates are to be commanded from the ground to OASIS at various times during the on-orbit 

operations. If tape remains, the recorder will operate during descent. 

NASA is flying OASIS aboard Discovery in support of the IUS program office of the Air Force Space 

Division. The system was developed by Lockheed Engineering and Management Services Co. under a 

NASA contract. Development was sponsored by the Air Force Space Division. 
Edited by Richard W. Orloff, 01/2001/Page 42
Edited by Richard W. Orloff, 01/2001/Page 43

STS-26 PAYLOAD AND VEHICLE WEIGHTS 

Pounds

Orbiter Empty 176, 019 

IUS 32,618 

TDRS-C 4,905 

OASIS I 223 

ADSF 266 

ARC 168 

ELRAD 3 

IEF 66 

IRCFE 9 

IUS Support Equipment 176 

MLE 15 

PCG 97 

PPE 2 

PVTOS 184 

SSIP (2) 42 

Orbiter Including Cargo at SRB Ignition 253,693 

Total Vehicle at SRB Ignition 4,521,762 

Orbiter Landing Weight 194,800 
Edited by Richard W. Orloff, 01/2001/Page 44

MAJOR ORBITER MODIFICATIONS 

More than 100 mandatory modifications to the orbiter Discovery were completed before returning to flight. 

Major modifications include: 

• Brake Improvements -- This included changes to eliminate mechanical and thermally-induced 

brake damage, improve steering margin and reduce the effects of tire damage or failure. 

Modifications for first flight are the thicker stators, stiffened main landing gear axles, tire pressure 

monitoring and anti-skid avionics. 

• 17-Inch Disconnect -- A positive hold-open latch design feature for the main propulsion system 

disconnect valves between the orbiter and the external tank (ET) was developed to ensure that the 

valve remains open during powered flight until nominal ET separation is initiated. 

• Reaction Control System Engines -- The RCS engines provide on-orbit attitude control and have 

been modified to turn off automatically in the event any combustion instability were to cause 

chamber wall burnthrough. 

• Thermal Protection System -- The TPS was improved in areas on the orbiter in the wing elevon 

cove region, nose landing gear door, lower wing surface trailing edge and elevon leading edge. 

• Auxiliary Power Unit -- An electrical interlock has been added to the APU tank shutoff valves to 

preclude electrical failures that could overheat the valves and cause decomposition of the fuel 

(hydrazine). 

• Orbital Maneuvering System -- To prevent development of leaks as a result of improper 

manufacturing processes, bellows in critical OMS propellant line valves have been replaced. 

• Crew Escape System -- A pyrotechnically jettisoned side hatch, crew parachutes and survival gear 

and a curved telescoping pole to aid the crew in clearing the wing, have been added to give a 

bail-out capability in the event of a problem where runway landing is not possible. An egress slide 

has been added to facilitate rapid post-landing egress from the vehicle under emergency 

conditions. 
Edited by Richard W. Orloff, 01/2001/Page 45

SOLID ROCKET MOTOR REDESIGN 

On June 13, 1986, the President directed NASA to implement the recommendations of the Presidential 

Commission on the Space Shuttle Challenger Accident. As part of satisfying those recommendations, 

NASA developed a plan to provide a redesigned solid rocket motor (SRM). 

The primary objective of the redesign effort was to provide an SRM that is safe to fly. A secondary 

objective was to minimize the impact on the launch schedule by using existing hardware, to the extent 

practical, without compromising safety. 

A redesign team was established which included participation from Marshall Space Flight Center; Morton 

Thiokol, NASA's prime contractor for the SRM; other NASA centers; contractors and experts from outside 

NASA. 

All aspects of the existing SRM were assessed. Design changes were deemed necessary in the field joint, 

case-to-nozzle joint, nozzle, factory joint, local propellant grain contour, ignition system and ground 

support equipment. Design criteria were established for each component to ensure a safe design with an 

adequate margin of safety. 

Design 

Field Joint -- The field joint metal parts, internal case insulation and seals were redesigned and a weather 

protection system was added. 

In the STS 51-L design, the application of actuating pressure to the upstream face of the o-ring was 

essential for proper joint sealing performance because large sealing gaps were created by pressure-induced 

deflections, compounded by significantly reduced o-ring sealing performance at low temperature. 

The major motor case change is the new tang capture feature which provides a positive metal-to-metal 

interference fit around the circumference of the tang and clevis ends of the mating segments. The 

interference fit limits the deflection between the tang and clevis o-ring sealing surfaces due to motor 

pressure and structural loads. The joints are designed so the seals will not leak under twice the expected 

structural deflection and rate. 

External heaters with integral weather seals were incorporated to maintain the joint and o-ring temperature 

at a minimum of 75 degrees F. The weather seal also prevents water intrusion into the joint. 

The new design, with the tang capture feature, the interference fit and the use of custom shims between the 

outer surface of the tang and inner surface of the outer clevis leg, controls the o-ring sealing gap 

dimension. 

The sealing gap and the o-ring seals are designed so there is always a positive compression (squeeze) on 

the o-rings. The minimum and maximum squeeze requirements include the effects of temperature, o-ring 

resiliency and compression set and pressure. The clevis o-ring groove dimension has been increased so the 

o-ring never fills more than 90 percent of the o-ring groove, enhancing pressure actuation. 

The new field joint design also includes a new o-ring in the capture feature and an additional leak check 

port to assure that the primary o-ring is positioned in the proper sealing direction at ignition. This new or 

third o-ring also serves as a thermal barrier should the sealed insulation be breached. Although not 

demanded by the specification, it has proved to be an excellent hot gas seal. 

The field joint internal case insulation was modified to be sealed with a pressure actuated flap called a 

J-seal, rather than with putty as in the STS 51-L configuration. 
Edited by Richard W. Orloff, 01/2001/Page 46

Longer field joint case mating pins, with a reconfigured retainer band, were added to improve the shear 

strength of the pins and increase the margin of safety in the metal parts of the joint. 

Case-to-Nozzle Joint -- The SRM case-to-nozzle joint, which experienced several instances of o-ring 

erosion in flight, has been redesigned to the same criteria imposed upon the case field joint. 

Similar to the field joint, case-to-nozzle joint modifications have been made in the metal parts, internal 

insulation and o-rings. Radial bolts with "Stat-O-Seals" were added to minimize the joint sealing gap 

opening. 

The internal insulation was modified to be sealed adhesively and a third o-ring included. The third o-ring 

serves as a dam or wiper in front of the primary o-ring to prevent the polysulfide adhesive from being 

extruded into the primary o-ring groove. It also serves as a thermal barrier should the polysulfide adhesive 

be breached. Like the third o-ring in the field joint, it has proven to be an effective hot gas seal. 

The polysulfide adhesive replaces the putty used in the 51-L joint. Also, an additional leak check port was 

added to reduce the amount of trapped air in the joint during the nozzle installation process and aid in the 

leak check procedure. 

Nozzle -- The internal joints of the nozzle metal parts have been redesigned to incorporate redundant and 

verifiable o-rings at each joint. The nozzle steel fixed housing part has been redesigned to permit 

incorporation of 100 radial bolts that attach the fixed housing to the case aft dome. 

Improved bonding techniques are used for the nozzle nose inlet, cowl/boot and aft exit cone assemblies. 

The nose inlet assembly metal part to ablative parts bondline distortion has been eliminated by increasing 

the thickness of the aluminum nose inlet housing and improving the bonding process. The tape wrap angle 

of the carbon cloth fabric in the areas of the nose inlet and throat assembly parts were changed to improve 

the ablative insulation erosion tolerance. 

Some of these ply angle changes were in progress prior to the STS 51-L accident. The cowl and outer boot 

ring has additional structural support with increased thickness and contour changes to increase their 

margins of safety. Additionally, the outer boot ring ply configuration was altered. 

Factory Joint -- Minor modifications were made in the case factory joints by increasing the insulation 

thickness and altering the lay-up to increase the margin of safety on the internal insulation. Longer pins 

also were added, along with a reconfigured retainer band and new weather seal to improve the factory joint 

performance and increase the margin of safety. The o-ring and o-ring groove size also were changed 

consistent with the field joint. 

Propellant -- The motor propellant forward transition region was recontoured to reduce the stress fields 

between the star and cylindrical portions of the propellant grain. 

Ignition System -- Several minor modifications were incorporated into the ignition system. The aft end of 

the igniter steel case, which contains the igniter nozzle insert, was thickened to eliminate a localized 

weakness. The igniter internal case insulation was tapered to improve the manufacturing process. 

Ground Support Equipment -- The Ground Support Equipment (GSE) has been redesigned to minimize 

the case distortion during handling at the launch site; to improve the segment tang and clevis joint 

measurement system for more accurate reading of case diameters to facilitate stacking; to minimize the risk 

of o-ring damage during joint mating; and to improve leak testing of the igniter, case and nozzle field 

joints. 

Other GSE modifications include transportation monitoring equipment and lifting beam. 
Edited by Richard W. Orloff, 01/2001/Page 47

Test Program 

An extensive test program was conducted to certify the redesigned motor for flight. Test activities included 

laboratory and component tests, subscale tests, simulator tests and full scale tests. 

Laboratory and component tests were used to determine component properties and characteristics. Subscale 

tests were used to simulate gas dynamics and thermal conditions for components and subsystem design. 

Simulator tests, consisting of motors using full size flight type segments, were used to verify joint design 

under full flight loads, pressure and temperature. Full scale tests were used to verify analytical models; 

determine hardware assembly characteristics; determine joint deflection characteristics; determine joint 

performance under full duration, hot gas tests including joint flaws and flight loads; and determine 

redesigned hardware structural characteristics. 

Five full scale, full duration motor static firing tests were conducted prior to STS-26 to verify the 

redesigned solid rocket motor performance. These included two development motor tests, two qualification 

motor (QM) tests, and a production verification motor test. Additionally, one post-STS-26 QM test is 

scheduled in late December to certify the redesigned motor for cold weather operation. 
Edited by Richard W. Orloff, 01/2001/Page 48

SPACE SHUTTLE MAIN ENGINE IMPROVEMENTS 

The main engines for Space Shuttle flight STS-26 incorporate numerous improvements over those on 

previous flights. Through an extensive, ongoing engine test program, NASA has identified, developed, 

certified and implemented dozens of modifications to the Space Shuttle main engine. 

In terms of hardware, areas of improvement include the electronic engine controller, valve actuators, 

temperature sensors, main combustion chamber and the turbopumps. 

In the high pressure turbomachinery, improvements have focused on the turbine blades and bearings to 

increase margin and durability. The main combustion chamber has been strengthened by nickel-plating a 

welded outlet manifold to give it extended life. 

Margin improvements also have been made to the five hydraulic actuators to preclude a loss in redundancy 

-- a situation which occurred twice on the launch pad. To address several instances of flight anomalies 

involving a temperature sensor in the critical engine cutoff logic, the sensor has been redesigned and 

extensively tested without problems. 

Along with hardware improvements, several major reviews were conducted on requirements and 

procedures. These reviews dealt with topics such as possible failure modes and effects, and the associated 

critical items list. Another review involved having a launch/abort reassessment team examine all 

launch-commit criteria, engine redlines and software logic. A design certification review also was 

performed. In combination, these reviews have maximized confidence for successful engine operation. 

A related effort saw Marshall engineers, working with their counterparts at the Kennedy Space Center, 

accomplish a comprehensive launch operations and maintenance review. This ensured that engine 

processing activities at the launch site are consistent with the latest operational requirements. 

In parallel with the various reviews, the most aggressive ground testing program in the history of the main 

engine was conducted. Its primary purposes were to certify the improvements and demonstrate the engine's 

reliability and operating margin. It was carried out at NASA's Stennis Space Center (formerly National 

Space Technology Laboratories) in Mississippi and at Rocketdyne's Santa Susana Field Laboratory in 

California. 

The other vital area of ground testing activity was checkout and acceptance of the three main engines for 

the STS-26 mission. Those tests, also at Stennis, began in August 1987 and all three STS-26 engines were 

delivered to Kennedy by January 1988. 
Edited by Richard W. Orloff, 01/2001/Page 49

SPACEFLIGHT TRACKING AND DATA NETWORK 

One of the key elements in the Space Shuttle mission is the capability to track the spacecraft, communicate 

with the astronauts and obtain the telemetry data that informs ground controllers of the condition of the 

spacecraft and the crew. 

The hub of this network is NASA's Goddard Space Flight Center, Greenbelt, Md., where the Spaceflight 

Tracking and Data Network (STDN) and the NASA Communications Network (NASCOM) are located. 

The STDN is a complex NASA worldwide system that provides realtime communications with the Space 

Shuttle orbiter and crew. The network is operated by Goddard. Approximately 2,500 personnel are 

required to operate the system. 

The NASA-controlled network consists of 14 ground stations equipped with 14-, 30- and 85-ft. S-band 

antenna systems and C-band radar systems, augmented by numerous Department of Defense (DOD) 

stations which provide C-band support and several DOD 60-ft. S-band antenna systems. S-band systems 

carry telemetry radio frequency transmissions. C-band stations conduct radar tracking. 

In addition, there are several major computing interfaces located at the Network Control Center and at the 

Flight Dynamics Facility, both at Goddard; at Western Space and Missile Center (WSMC), Vandenberg 

AFB, CA; at White Sands Missile Range, NM; and at Eastern Space and Missile Center (ESMC), Cape 

Canaveral Air Force Station, FL. They provide realtime network computational support for the generation 

of data necessary to point antennas at the Shuttle. 

The network has agreements with the governments of Australia, (Canberra and Yarragadee); Spain 

(Madrid); Senegal (Dakar); Chile (Santiago); United Kingdom (Ascension Island); and Bermuda to provide 

NASA tracking station support to the National Space Transportation System program. 

Should the Mission Control Center in Houston be seriously impaired for an extended period of time, the 

NASA Ground Terminal (NGT) at White Sands becomes an emergency Mission Control Center, manned 

by Johnson Space Center personnel, with the responsibility of safely returning the orbiter to a landing site. 

During the transition of the flight control team from Johnson to the White Sands NASA Ground Terminal, 

Goddard would assume operational control of the flight. 

The Merritt Island, Fla., S-band station provides the appropriate data to the Launch Control Center at 

Kennedy and the Mission Control Center at Johnson during pre-launch testing and the terminal countdown. 

During the first minutes of launch and during the ascent phase, the Merritt Island and Ponce de Leon, Fla., 

S-band and Bermuda S-band stations, as well as the C-band stations located at Bermuda; Wallops Island, 

Va.; Antigua; Cape Canaveral; and Patrick Air Force Base, Fla., provide appropriate tracking data, both 

high speed and low speed, to the Kennedy and Johnson control centers. 

During the orbital phase, all the S-band and some of the C-band stations, which acquire the Space Shuttle 

at 3 degrees above the horizon, support and provide appropriate tracking, telemetry, air-ground and 

command support to the Mission Control Center at Johnson through Goddard. 

During the nominal entry and landing phase planned for Edwards Air Force Base, Calif., the 

NASA/Goldstone and Dryden Flight Research Facility, Calif., sites, and the S-band and C-band stations at 

the WSMC and Edwards Air Force Base, CA, provide highly-critical tracking, telemetry, command and 

air-ground support to the orbiter and send appropriate data to the Johnson and Kennedy control centers. 
Edited by Richard W. Orloff, 01/2001/Page 50

NASA-CONTROLLED TRACKING STATIONS 

Location Equipment 

 

Ascension Island (ACN) (Atlantic Ocean) S-band, UHF A/G 

Bermuda (BDA) (Atlantic Ocean) S- and C-band, UHF A/G 

Goldstone (GDS) (California) S-band, UHF A/G, TV 

Guam (GWM) (Pacific Ocean) S-band, UHF A/G 

Hawaii (HAW) (Pacific Ocean) S-band, UHF A/G, TV 

Merritt Island (MIL) (Florida) S-band, UHF A/G, TV 

Santiago (AGO) (Chile) S-band 

Ponce de Leon (PDL) (Florida) S-band 

Madrid (RID) (Spain) S-band 

Canberra (CAN) (Australia) S-band 

Dakar (DKR) (Senegal, Africa) S-band, UHF A/G 

Wallops (WFF) (Virginia) C-band 

Yarragadee (YAR) (Australia) UHF A/G 

Dryden (DFRF) (California) S-band, UHF A/G, C-band 

The Canberra, Goldstone and Madrid stations are part of the Deep Space Network (DSN) and come under 

the management of NASA's Jet Propulsion Laboratory, Pasadena, Calif. 

Personnel: Tracking Stations; 1,100 (500+ are local residents) Goddard Space Flight Center; 1,400 
Edited by Richard W. Orloff, 01/2001/Page 51

HUNTSVILLE OPERATIONS SUPPORT CENTER 

The Huntsville Operations Support Center (HOSC) is a facility at NASA's Marshall Space Flight Center 

which supports launch activities at Kennedy Space Center, Fla. The operations center also supports 

powered flight and payload operations at the Johnson Space Center. 

During pre-mission testing, countdown, launch and powered flight toward orbit, Marshall and contractor 

engineers and scientists man consoles in the support center to monitor realtime data being transmitted from 

the Shuttle. Their purpose is to evaluate and help solve problems that might occur with Space Shuttle 

propulsion system elements, including the Space Shuttle main engines, external tank and solid rocket 

boosters. They also will work problems with the range safety system. 

The data, providing information on the "health" of these systems, are gathered by sensors aboard the 

Shuttle and are instantaneously transmitted from the launch site to the 2-story HOSC. There the 

information is processed by computers and displayed on screens and other instruments at 15 stations in the 

Engineering Console Room. More than 3,000 temperature, pressure, electrical voltage and other 

measurements are made every second. During the 10 hours of peak activity before and during launch, more 

that 11 million measurements are assessed by teams of experts in the support center. 

Approximately 150 Marshall support center personnel have access to more than 25 direct communications 

lines that link them with the launch site at Kennedy Space Center, Mission Control at Johnson Space 

Center and with Shuttle propulsion system contractor plants. 

If a problem is detected by the experts at one of the stations in the support center console room, engineers 

on the consoles immediately alert appropriate individuals at the Kennedy and Johnson centers, and 

operations center managers in the Shuttle action center, a conference room adjacent to the console room. 

They also pass the information to the appropriate teams of specialists in the nearby operations center 

working area. There are separate teams to work Space Shuttle main engine, external tank, solid rocket 

booster, main propulsion system and Range Safety System difficulties. 

In addition to launch support, payload services are provided by teams of scientists operating out of 

specially equipped payload support rooms. 
Edited by Richard W. Orloff, 01/2001/Page 52

STS-26 MENU 

FREDRICK H. (RICK) HAUCK, CDR - (RED) 

Day 1*, 5** Day 2 

Meal A Meal A 

Pears, Dried (IM) Peaches, Dried (IM) 

Sausage Patty (R) Granola (R) 

Scrambled Eggs (R) Mexican Scrambled Eggs (R) 

Bran Flakes (R) Cocoa (B) Orange-Grapefruit Drink (B) 

Orange-Pineapple Drink (B) 

Meal B Meal B 

Ham (T) Dried Beef (IM) 

Bread (NF) Bread (NF) 

Peaches, Diced (T) Pears, Diced (T) 

Shortbread Cookies (NF) Butter Cookies (NF) 

Lemonade w/A/S (2X) (B) Lemonade (2X) (B) 

Meal C Meal C 

Teriyaki Chicken (R) Beef w/BBQ Sauce 8 oz (T) 

Rice & Chicken (R) Potatoes au Gratin (R) 

Asparagus (R) Green Beans w/Mushrooms (R) 

Fruit Cocktail (T) Pears, Diced (T) 

Orange Mango (B) Citrus Drink (B) 

Day 3 Day 4 

Meal A Meal A 

Apricots, Dried (IM) Pears, Dried (IM) 

Seasoned Scrambled Eggs (R) Beef Patty (R) 

Bran Flakes (R) Bran Flakes (R) 

Cocoa (B) Grapefruit Drink (B) 

Orange-Grapefruit Drink (B) 

Meal B Meal B 

Peanut Butter (IM) Ham (T) 

Jelly (IM) Bread (NF) 

Bread (NF) Pineapple (T) 

Fruit Cocktail (T) Cashews (NF) 

Fruitcake (T) Tea w/Lemon & A/S (2X) (B) 

Tea w/Lemon & A/S (2X) (B) 

Meal C Meal C 

Shrimp Cocktail (R) Meatballs w/BBQ Sauce 8 oz (T) 

Beef & Gravy 8 oz (T) Rice Pilaf (R) 

Macaroni & Cheese (R) Italian Vegetables (R) 

Green Beans w/Mushrooms (R) Peaches, Diced (T) 

Peach Ambrosia (R) Apple Drink (B) 

Lemonade (B) 

* Day 1 consists of meals B and C T- Thermostabilized 

** Day 5 consists of Meal A only NF- Natural Form 

B - Beverage 

R - Rehydratable 

IM - Intermediate Moisture 
Edited by Richard W. Orloff, 01/2001/Page 53

RICHARD O. COVEY, PLT (YELLOW) 

Day 1*, 5** Day 2 

Meal A Meal A 

Peaches, Diced (T) Peaches, Diced (T) 

Sausage Patty (R) Granola (R) 

Seasoned Scrambled Eggs (R) Granola Bar (NF) 

Breakfast Roll (NF) Breakfast Roll (NF) 

Orange-Mango Drink (B) Orange-Grapefruit Drink (B) 

Meal B Meal B 

Tuna Salad Spread (T) Shrimp Creole (R) 

Bread (NF) Pears, Diced (T) 

Peaches, Diced (T) Butter Cookies (NF) 

Shortbread Cookies (NF) Lemonade (2X) (B) 

Lemonade (2X) (B) 

Meal C Meal C 

Chicken ala King 8 oz (T) Turkey & Gravy 8 oz (T) 

Rice & Chicken (R) Potatoes au Gratin (R) 

Asparagus (R) Green Beans w/Mushrooms (R) 

Chocolate Pudding (T) Butterscotch Pudding (T) 

Tea (B) Tea (B) 

Day 3 Day 4 

Meal A Meal A 

Dried Beef (IM) Pears, Diced (T) 

Seasoned Scrambled Eggs (R) Beef Patty (R) 

Bran Flakes (R) Bran Flakes (R) 

Breakfast Roll (NF) Breakfast Roll (NF) 

Orange-Mango Drink (B) Grapefruit Drink (B) 

Meal B Meal B 

Chicken Salad Spread (T) Beef Almondine (T) 

Bread (NF) Pineapple (T) 

Fruit Cocktail (T) Macadamia Nuts (NF) 

Almonds (NF) Lemonade (2X) (B) 

Lemonade (2X) (B) 

Meal C Meal C 

Teriyaki Chicken (R) Beef w/BBQ Sauce 8 oz (T) 

Potato Patty (R) Rice Pilaf (R) 

Creamed Spinach (R) Italian Vegetables (R) 

Candy Coated Peanuts (NF) Chocolate Pudding (T) 

Vanilla Pudding (T) Tea (B) 

Tea (B) 

* Day 1 consists of Meals B and C T - Thermostabilized 

** Day 5 consists of Meal A only NF - Natural Form 

B - Beverage 

R - Rehydratable 
Edited by Richard W. Orloff, 01/2001/Page 54

JOHN M. (MIKE) LOUNGE, MS-1- (BLUE) 

Day 1*, 5** Day 2 

Meal A Meal A 

Pears Peaches, Dried (IM) 

Beef Patty (R) Granola w/Blueberries (R) 

Seasoned Scrambled Eggs (R) Breakfast Roll (NF) 

Granola w/Raisins (R) Vanilla Instant Breakfast (B) 

Cocoa (B) Grapefruit Drink (B) 

Orange-Mango Drink (B) 

Meal B Meal B 

Peanut Butter (IM) Tuna Salad Spread (T) 

Bread (NF) Bread (NF) 

Peaches, Diced (T) Pears, Diced (T) 

Shortbread Cookies (NF) Butter Cookies (NF) 

Apple Drink (2X) 9B) Lemonade w/A/S (2X) (B) 

Meal C Meal C 

Meatballs w/BBQ Sce 8 oz (T) Beef w/BBQ Sauce 8 oz. (T) 

Rice & Chicken (R) Potatoes au Gratin (R) 

Asparagus (R) Green Bean w/Mushrooms (R) 

Chocolate Pudding (T) Butterscotch Pudding (T) 

Grape Drink (B) Orange Drink (B) 

Day 3 Day 4 

Meal A Meal A 

Apricots, Dried (IM) Fruit Cocktail (T) 

Seasoned Scrambled Eggs (R) Beef Patty (R) 

Bran Flakes (R) Oatmeal w/Raisins & Space (R) 

Cocoa (B) Breakfast Roll (NF) 

Orange Drink Mix (B) Grapefruit Drink (B) 

Meal B Meal B 

Salmon (T) Ham (T) 

Bread (NF) Cheddar Cheese Spread (T) 

Fruit Cocktail (T) Bread (NF) 

Fruitcake (T) Pineapple (T) 

Tea w/Lemon & A/S (2X) (B) Cashews (NF) 

 Lemonade w/A/S (2X) (B) 

Meal C Meal C 

Grd Beef w/Spice Sce 8 oz (T) Meatballs w/BBQ Sauce 8 oz (T) 

Potato Patty (R) Rice Pilaf (R) 

Green Beans & Broccoli (R) Italian Vegetables (R) 

Strawberries (R) Chocolate Pudding (T) 

Vanilla Pudding (T) Apple Drink (B) 

Tropical Punch w/A/S (B) 

* Day 1 consists of Meals B and C IM - Intermediate Moisture 

** Day 5 consists of Meal A only R - Rehydratable 

B - Beverage 

NF - Natural Form 

T - Thermostabilized 

A/S - Artificial Sweetener 
Edited by Richard W. Orloff, 01/2001/Page 55

DAVID C. HILMERS, MS-2 - (GREEN) 

Day 1*, 5** Day 2 

Meal A Meal A 

Applesauce (T) Peaches, Diced (T) 

Bran Flakes (R) Scrambled Eggs (R) 

Granola Bar (NF) Granola (R) 

Orange-Mango Drink (B) Granola Bar (NF) 

 Orange-Grapefruit Drink (B) 

Meal B Meal B 

Tuna Salad Spread (T) Turkey Salad Spread (T) 

Bread (NF) Bread (NF) 

Peaches, Diced (T) Pears, Diced (T) 

Shortbread Cookies (NF) Trail Mix (NF) 

Grapefruit Drink (2X) (B) Grapefruit Drink (2X) (B) 

Meal C Meal C 

Chicken ala King 8 oz (T) Turkey Tetrazzini (R) 

Corn, Grn Bean & Pasta (R) Potatoes au Gratin (R) 

Creamed Spinach (R) Green Bean w/Mushrooms (R) 

Fruit Cocktail (T) Fruit Cocktail (T) 

Chocolate Pudding (T) Apricots (IM) 

Orange-Grapefruit Drink Orange Drink (B) 

Day 3 Day 4 

Meal A Meal A 

Applesauce (T) Peaches, Diced (T) 

Scrambled Eggs (R) Scrambled Eggs (R) 

Granola Bar (NF) Oatmeal w/Brown Sugar (R) 

Orange Drink Mix (B) Granola Bar (NF) 

 Grapefruit Drink (B) 

Meal B Meal B 

Turkey Salad Spread (T) Cheddar Cheese Spread (T) 

Bread (NF) Bread (NF) 

Fruit Cocktail (T) Applesauce (T) 

Shortbread Cookies (NF) Granola Bar (NF) 

Dried Peaches (IM) Apricots (IM) 

Grapefruit Drink (2X) (B) Orange Drink (2X) (B) 

Meal C Meal C 

Teriyaki Chicken (R) Turkey & Gravy 8 oz (T) 

Potato Patty (R) Rice Pilaf (R) 

Green Beans & Broccoli (R) Italian Vegetables (R) 

Strawberries (R) Fruit Cocktail (T) 

Pineapple (T) Almonds (NF) 

Grapefruit Drink (B) Grapefruit Drink (B) 

* Day 1 consists of Meals B and C T - Thermostabilized 

** Day 5 consists of Meal A only NF - Natural Form 

B - Beverage 

R - Rehydratable 
Edited by Richard W. Orloff, 01/2001/Page 56

GEORGE D. (PINKY) NELSON, MS-3 (ORANGE) 

Day 1*, 5** Day 2 

Meal A Meal A 

Pineapple (T) Fruit Cocktail (T) 

Sausage Patty (R) Sausage Patty (R) 

Mexican Scrambled Eggs (R) Mexican Scrambled Eggs (R) 

Granola w/Raisins (R) Orange Drink (B) 

Cocoa (B) Kona Coffee (B) 

Orange-Pineapple Drink (B) 

Kona Coffee (B) 

Meal B Meal B 

Ham Salad Spread (T) Frankfurters (T) 

Tortillas (NF) Tortillas (NF) 

Chocolate Pudding (T) Chocolate Pudding (T) 

Candy Coated Chocolates (NF) Life Savers (NF) 

Apple Cider (2X) (B) Apple Cider (2X) (B) 

Meal C Meal C 

Shrimp Cocktail (R) Shrimp Cocktail (R) 

Sweet & Sour Chicken (R) Beef w/BBQ Sauce 8 oz (T) 

Rice Pilaf (R) Potato Patty (R) 

Green Beans & Broccoli (R) Italian Vegetables (R) 

Strawberries (R) Peaches, Diced (T) 

Orange Drink Mix (B) Vanilla Pudding (T) 

Kona Coffee (B) Peach Drink (B), Kona Coffee (B) 

Day 3 Day 4 

Meal A Meal A 

Pineapple (T) Fruit Cocktail (T) 

Sausage Patty (R) Beef Patty (R) 

Mexican Scrambled Eggs (R) Mexican Scrambled Eggs (R) 

Orange Drink Mix (B) Breakfast Roll (NF) 

Kona Coffee (B) Grapefruit Drink (B), Kona Coffee (B) 

Meal B Meal B 

Chicken Salad Spread (T) Frankfurters (T) 

Bread (NF) Bread (NF) 

Fruit Cocktail (T) Applesauce (T) 

Chocolate Covered Cookies (NF) Cashews (NF) 

Orange-Mango Drink (B) Apple Drink (2X) (B) 

Kona Coffee (B) 

Meal C Meal C 

Shrimp Cocktail (R) Shrimp Cocktail (R) 

Ham (T) Meatballs w/BBQ Sauce 8 oz (T) 

Potato Patty (R) Italian Vegetables (R) 

Green Beans & Broccoli (R) Chocolate Pudding (T) 

Strawberries (R) Apple Drink (B) 

Vanilla Pudding (T) Kona Coffee (B) 

Tropical Punch (B) 

Kona Coffee (B) 

* Day 1 consists of Meals B and C T - Thermostabilized 

** Day 2 consists of Meal A only R - Rehydratable 

B - Beverage 

NF - Natural Form 
Edited by Richard W. Orloff, 01/2001/Page 57

STS 26 CONTINGENCY/PANTRY 

Rehydratable Beverages Qty Rehydratable Food Qty 

 

Apple Cider 5 Soup Kit 

Cocoa 5 Chicken Consommé 8 

Coffee, Black 15 Rice & Chicken Soup 8 

Kona Coffee, Black 10 Broccoli au Gratin 3 

Grapefruit Drink 15 Shrimp Cocktail 10 

Lemonade 10 Turkey Tetrazzini 7 

Lemonade w/A/S 10 TOTAL 36 

Orange-Grapefruit Drink 5 

Orange-Mango Drink 15 Thermostabilized Food 

Tea 5 Beef & Gravy (8 oz) 5 

Tea w/Lemon & A/S 5 Chicken Salad Spread 2 

Tropical Punch 5 Frankfurters 3 

TOTAL 105 Ham Salad Spread 3 

 Peaches, diced 4 

Snacks Tuna Salad Spread 2 

Almonds (NF) 15 Turkey & Gravy (8 oz) 5 

Butter Cookies (NF) 5 TOTAL 23 

Candy Coated Chocolates (NF) 20 

Candy Coated Peanuts (NF) 20 Fresh Food 

Cashews (NF) 10 Apples, Red Delicious 2 

Dried Beef (IM) 15 Apples, Granny Smith 3 

Granola Bars (NF) 5 Brea, Whole Wheat 2 

Macadamia Nuts (NF) 10 Breakfast Rolls, Menu 

plus 

6 

Peanut Butter, Crunchy (JAR) 

(IM) 

1 Carrot Sticks 2 

Soda Crackers 10 Celery Sticks 2 

Trail Mix (IM) 5 Cheddar Cheese, 2 oz 5 

TOTAL 116 Crackers, Goldfish, Plain 1 

 Crackers, Wheat Thins 1 

 Tortillas 2 

 TOTAL 26 

 

Drinking Water Containers 20 Life Savers - 5 fruit 

flavors 

In-Suit Food Bars 2 

 

Reentry Kit 

Salt Tablets (8) 5 

Long Straws 20 

Drinking Water Containers 20 

A/S - Artificial Sweetener 

NF - Natural Form 

IM - Intermediate Moisture 
Edited by Richard W. Orloff, 01/2001/Page 58

STS-26 CREWMEMBERS 

S87-40673 – The official portrait of the STS-26 crewmembers includes, seated on either side of the space 

shuttle orbiter model, pilot Richard O. Covey (left) and mission commander Frederick H. Hauck with 

mission specialists (left to right) David C. Hilmers, George D. "Pinky" Nelson, and John M. Lounge 

standing behind them. The mission insignia and flag are displayed in background. 

No copyright is asserted for this photograph. If a recognizable person appears in the photo, use for 

commercial purposes may infringe a right of privacy or publicity. It may not be used to state or imply the 

endorsement by NASA or by any NASA employee of a commercial product, process or service, or used in 

any other manner that might mislead. Accordingly, it is requested that if this photograph is used in 

advertising and other commercial promotion, layout and copy be submitted to NASA prior to release. 

PHOTO CREDIT: NASA or National Aeronautics and Space Administration. 
Edited by Richard W. Orloff, 01/2001/Page 59

BIOGRAPHICAL DATA 

FREDERICK H. (RICK) HAUCK, 47, captain, USN, is mission commander. Born in Rochester, NY, he 

considers Winchester, MA, and Washington, D.C., as his hometowns. Hauck was selected as an astronaut 

in January 1978. 

He was Shuttle pilot for the seventh Space Shuttle mission (STS-7) aboard the orbiter Challenger in June 

1983. During the flight, Hauck operated the Canadian-built remote manipulator system (RMS) arm, 

performing the first deployment and retrieval exercise with the Shuttle Pallet Satellite. 

He also served as commander of Shuttle Discovery's second mission, STS 51-A, in November 1984, the 

first mission to retrieve satellites and return them to Earth. Hauck has logged more than 339 hours in space. 

Hauck received a B.S. degree in physics from Tufts University in 1962 and an M.S. degree in nuclear 

engineering from the Massachusetts Institute of Technology in 1966. 

A Navy ROTC student at Tufts, Hauck was commissioned in 1962 and served 20 months as a 

communications officer aboard the USS Warrington. He received his wings in 1968 and has since logged 

almost 5,000 hours flying time. Hauck flew 114 combat and combat support missions in Southeast Asia. 

RICHARD O. (DICK) COVEY, 42, colonel, USAF, is the STS-26 pilot. He was born in Fayetteville, 

AR, but considers Fort Walton Beach, Fla., his hometown. Covey was selected as an astronaut in January 

1978. 

He served as pilot on Shuttle mission 51-I aboard Discovery in August/September 1985. During that 

mission, the crew deployed three satellites and retrieved, repaired and re-deployed the ailing 

Leasat/Syncom IV-F3 satellite that failed to activate following deployment on STS 51-D earlier that year. 

Covey has 

logged more than 170 hours in space. 

Covey received a B.S. degree in engineering sciences from the U.S. Air Force Academy in 1968 and an 

M.S. degree in aeronautics and astronautics from Purdue University in 1969. 

A fighter pilot from 1970 to 1974, Covey flew 339 combat missions during two tours in Southeast Asia, 

was director and pilot for electronic warfare testing of the F-15 Eagle, and has flown more than 4,000 

hours in more than 25 types of aircraft. 

JOHN M. (MIKE) LOUNGE, 38, is mission specialist 1 (MS-1) on STS-26. Born in Denver, Colo., he 

considers Burlington, CO, his hometown. Lounge was selected as an astronaut in 1980. 

He was a mission specialist on Shuttle Discovery's last flight, STS 51-I, in August/September 1985. During 

this mission, Lounge's duties included deployment of the Australian AUSSAT communications satellite 

and operation of the remote manipulator system (RMS) arm. He has logged more than 170 hours in space. 

Lounge received a B.S. degree in physics and mathematics from the U.S. Naval Academy in 1969 and an 

M.S. degree in astrogeophysics from the University of Colorado in 1970. 

Following graduation from the Naval Academy, Lounge completed naval flight officer training at 

Pensacola, Fla., and took advanced training as radar intercept officer in the F-4J Phantom; completed a 

9-month Southeast Asia cruise aboard the USS Enterprise, participating in 99 combat missions; then 

transferred to the Navy Space Project Office in Washington, D.C., for a 2-year tour as staff project officer. 
Edited by Richard W. Orloff, 01/2001/Page 60

BIOGRAPHICAL DATA 

DAVID C. HILMERS, 38, Lt. Colonel, USMC, is mission specialist 2 (MS-2) on STS-26. He was born in 

Clinton, Iowa, but considers DeWitt, Iowa, as his hometown. Hilmers was selected as an astronaut in July 

1980. 

He served as a mission specialist on orbiter Atlantis' first flight, STS 51-J, a dedicated Department of 

Defense mission, in October 1985. Hilmers has logged more than 98 hours in space. 

Hilmers received a B.S. degree in mathematics from Cornell College in 1972, an M.S. degree in electrical 

engineering (with distinction) in 1977, and the degree of electrical engineer from the Naval Postgraduate 

School in 1978. 

Following basic training and flight school, he was assigned to Marine Corps Air Station, Cherry Point, 

N.C., flying the A-6 Intruder. Hilmers then served as an air liaison officer with the 1st Battalion, 2nd 

Marines, 6th Fleet in the Mediterranean. He was stationed with the 3rd Marine Aircraft Wing in El Toro, 

CA, at the time of his selection by NASA. Hilmers has logged more than 1,500 hours flying time in 16 

different types of aircraft. 

GEORGE D. (PINKY) NELSON, 38, is mission specialist 3 (MS-3) on STS-26. Born in Charles City, 

Iowa, he considers Willmar, MN, his hometown. He was selected as an astronaut in January 1978. 

Nelson was a mission specialist on STS 41-C in April 1984, the fourth flight of orbiter Challenger. During 

that flight, the crew deployed the Long Duration Exposure Facility (LDEF) and retrieved, repaired and 

re-deployed the Solar Maximum Mission (SMM) satellite. Nelson logged 9 hours of extravehicular activity 

(EVA) during the SMM repair. 

He also flew as a mission specialist on Columbia's seventh flight, STS 61-C in January 1986. During that 

mission, the crew deployed the Satcom KU satellite and conducted experiments in astrophysics and 

materials processing. With the completion of that flight, Nelson has logged more than 314 hours in space. 

Nelson received a B.S. degree in physics from Harvey Mudd College in 1972 and M.S. and Ph.D. degrees 

in astronomy from the University of Washington in 1974 and 1978, respectively. 

He was involved in astronomical research projects at the Sacramento Peak Solar Observatory, Sunspot, 

NM; the Astronomical Institute at Utrecht, The Netherlands; the University of Gottingen Observatory, 

West Germany; and at the Joint Institute for Laboratory Astrophysics in Boulder, CO. 
Edited by Richard W. Orloff, 01/2001/Page 61

SPACE SHUTTLE PROGRAM MANAGEMENT 

NASA Headquarters, Washington, DC 

Dr. James C. Fletcher Administrator 

Dale D. Myers Deputy Administrator 

RADM Richard H. Truly Associate Administrator for Space Flight 

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

Arnold D. Aldrich Director, National Space Transportation System 

Richard H. Kohrs Deputy Director, NSTS Program (located at Johnson Space Center) 

Robert L. Crippen Deputy Director, NSTS Operations (located at Kennedy Space Center) 

David L. Winterhalter Director, Systems Engineering and Analysis 

Gary E. Krier Acting Director, Operations Utilization 

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

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

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

 Quality Assurance 

Robert O. Aller Associate Administrator for Operations 

Eugene Ferrick Director, Tracking and Data Relay Satellite System 

Robert M. Hornstein Acting Director, Ground Networks Division 

Johnson Space Center, Houston, TX 

Aaron Cohen Director 

Paul J. Weitz Deputy Director 

Richard A. Colonna Manager, Orbiter and GFE Projects 

Donald R. Puddy Director, Flight Crew Operations 

Eugene F. Kranz Director, Mission Operations 

Henry O. Pohl Director, Engineering 

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

Kennedy Space Center, FL 

Forrest McCartney Director 

Thomas E. Utsman Deputy Director; Director, Shuttle Management and Operations 

Robert B. Sieck Launch Director 

George T. Sasseen Shuttle Engineering Director 

John J. Talone STS-26 Flow Director 

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

John T. Conway Director, Payload Management and Operations 

Marshall Space Flight Center, Huntsville, AL 

James R. Thompson Jr. Director 

Thomas J. Lee Deputy Director 

William R. Marshall Manager, Shuttle Projects Office 

Dr. J. Wayne Littles Director, Science and Engineering 

Gerald W. Smith Manager, Solid Rocket Booster Project 

Joseph A. Lombardo Manager, Space Shuttle Main Engine Project 

G.P. Bridwell Manager, External Tank Project 
Edited by Richard W. Orloff, 01/2001/Page 62

Stennis Space Center, Bay St. Louis, MS 

I. Jerry Hlass Director 

Roy Estess Deputy Director 

A.J. Rogers Jr. Manager, Engineering & Propulsion Test Support 

John L. Glasery Jr. Manager, Safety/Quality & Health 

Ames Research Center, Mountain View, CA 

Dr. Dale L. Compton Acting Director 

Victor L Peterson Acting Deputy Director 

Ames-Dryden Flight Research Facility, Edwards, CA 

Martin A. Knutson Site Manager 

Theodore G. Ayers Deputy Site Manager 

Thomas C. McMurtry Chief, Research Aircraft Operations Division 

Larry C. Barnett Chief, Shuttle Support Office 

Goddard Space Flight Center, Greenbelt, MD 

Dr. John W. Townsend Jr. Director 

Gerald W. Longanecker Director, Flight Projects 

Robert E. Spearing Director, Operations and Data Systems 

Daniel A. Spintman Chief, Networks Division 

Paul E. Brumberg Chief, Communications Division 

Dr. Dale W. Harris TDRS Project Manager 

Charles M. Hunter TDRS Deputy Project Manager 

Gary A. Morse Network Director 
Edited by Richard W. Orloff, 01/2001/Page 63

GLOSSARY OF ACRONYMS AND ABBREVIATIONS 

ADSF Automated Directional Solidification Furnace 

AFSCN Air Force Satellite Control Network 

A/L Approach and Landing 

ALT Approach and Landing Test (Program) 

AMU Astronaut Maneuvering Unit 

AOA Abort Once Around 

APS Alternate Payload Specialist 

APU Auxiliary Power Unit 

ARC Aggregation of Red Blood Cells 

ASE Airborne Support Equipment 

ATE Automatic Test Equipment 

ATO Abort to Orbit 

BFC Backup Flight Control (System) 

BOC Base Operations Contract 

CAPCOM Capsule Communicator 

CCAFS Cape Canaveral Air Force Station 

CCMS Checkout, Control and Monitor Subsystem 

CCTV Closed Circuit Television 

CDR Commander 

CDMS Command & Data Management Systems Officer 

CDS Central Data System 

CFES Continuous Flow Electrophoresis System 

CIC Crew Interface Coordinator 

CIE Communications Interface Equipment 

CITE Cargo Integration Test Equipment 

CTS Call to Stations 

DCC Data Computation Complex 

DCR Design Certification Review 

DCS Display Control System 

DIG Digital Image Generation 

DFI Development Flight Instrumentation 

DFRF Hugh L. Dryden Flight Research Facility 

DMC Data Management Coordinator 

DMOS Diffusive Mixing of Organic Solutions 

DOD Department of Defense 

DOP Diver Operated Plug 

DPS Data Processing System 

EAFB Edwards Air Force Base 

ECLSS Environmental Control & Life Support System 

EECOMP Electrical, Environmental & Consumables Systems Engineer 

EI Entry Interface 

ELRAD Earth Limb Radiance 

EMU Extravehicular Mobility Unit 

ESA European Space Agency 

ESMC Eastern Space and Missile Center 

ET External Tank 

EVA Extravehicular Activity 

FAO Flight Activities Officer 

FAWG Flight Assignment Working Group 

FBSC Fixed Base Crew Stations 
Edited by Richard W. Orloff, 01/2001/Page 64

F/C Flight Controller 

FCT Flight Crew Trainer 

FCTS Flight Crew Trainer Simulator 

FD Flight Director 

FDF Flight Data File 

FDO Flight Dynamics Officer 

FOD Flight Operations Directorate 

FOE Flight Operations Engineer 

FOPG Flight Operations Planning Group 

FOSO Flight Operations Scheduling Officer 

FR Firing Room 

FRC Flight Control Room 

FRCS Forward Reaction Control System 

FRF Flight Readiness Firing 

FRR Flight Readiness Review 

FSE Flight Simulation Engineer 

FSS Fixed Service Structure 

GAS Getaway Special 

GC Ground Control 

GDO Guidance Officer 

GLS Ground Launch Sequencer 

GN Ground Network 

GNC Guidance, Navigation & Control Systems Engineer 

GPC General Purpose Computer 

GSE Ground Support Equipment 

GSFC Goddard Space Flight Center 

HAC Heading Alignment Circle 

HB High Bay 

HMF Hypergolic Maintenance Facility 

HPPF Horizontal Payloads Processing Facility 

HUS Hypergolic Umbilical System 

IECM Induced Environment Contamination Monitor 

IEF Isoelectric Focusing Experiment 

IG Inertial Guidance 

ILS Instrument Landing System 

IMF In Flight Maintenance 

IMU Inertial Measurement Unit 

INCO Instrumentation & Communications Officer 

IRCFE Infrared Communications Flight Experiment 

IRIG Interrange Instrumentation Group 

ISP Integrated Support Plan 

IUS Inertial Upper Stage 

IVA Intravehicular Activity 

JPL Jet Propulsion Laboratory 

JSC Lyndon B. Johnson Space Center 

KSC John F. Kennedy Space Center 

LC Launch Complex 

LCC Launch Control Center 

LCS Launch Control System 

LDEF Long Duration Exposure Facility 

LETF Launch Equipment Test Facility 
Edited by Richard W. Orloff, 01/2001/Page 65

LOX Liquid Oxygen 

LPS Launch Processing System 

LSA Launch Services Agreement 

LWG Logistics Working Group 

MBCS Motion Base Crew Station 

MCC Mission Control Center 

MD Mission Director 

MDD Mate/Demate Device 

ME Main Engine 

MECO Main Engine Cutoff 

MET Mission Elapsed Time 

MLE Mesoscale Lightning Experiment 

MLP Mobile Launch Platform 

MLR Monodisperse Latex Reactor 

MLS Microwave Landing System 

MMACS Maintenance, Mechanical Arm & Crew Systems Engineer 

MMPSE Multiuse Mission Payload Support Equipment 

MMSE Multiuse Mission Support Equipment 

MMU Manned Maneuvering Unit 

MOD Mission Operations Directorate 

MOP Mission Operations Plan 

MPGHM Mobile Payload Ground Handling Mechanism 

MPPSE Multipurpose Payload Support Equipment 

MPS Main Propulsion System 

MS Mission Specialist 

MSBLS Microwave Scanning Beam Landing System 

MSCI Mission Scientist 

MSFC George C. Marshall Space Flight Center 

MSS Mobile Service Structure 

MST Mobile Service Tower 

MUM Mass Memory Unit Manager 

NASCOM NASA Communications Network 

NBT Neutral Buoyancy Facility 

NIP Network Interface Processor 

NOCC Network Operations Control Center 

NSRS NASA Safety Reporting System 

NSTL National Space Technology Laboratories 

NSTS National Space Transportation System 

OAA Orbiter Access Arm 

OC Operations Coordinator 

O&C Operations and Checkout (Building) 

OAST Office of Aeronautics & Space Technology 

OFI Operational Flight Instrumentation 

OFT Orbiter Flight Test 

OMBUU Orbiter Midbody Umbilical Unit 

OMRF Orbiter Maintenance & Refurbishment Facility 

OMS Orbital Maneuvering System 

OPF Orbiter Processing Facility 

OSF Office of Space Flight 

OSS Office of Space Science 

OSSA Office of Space Science and Applications 

OSTA Office of Space and Terrestrial Applications 

OV Orbiter Vehicle 
Edited by Richard W. Orloff, 01/2001/Page 66

PACE Prelaunch Automatic Checkout Equipment 

PAM Payload Assist Module 

PAYCOM Payload Command Coordinator 

PCG Protein Crystal Growth Experiment 

PCR Payload Changeout Room 

PDRS Payload Deployment & Retrieval System 

PGHM Payload Ground Handling Mechanism 

PHF Payload Handling Fixture 

PIP Payload Integration Plan 

PLSS Portable Life-Support Subsystem 

PLT Pilot 

POCC Payload Operations Control Center 

POD Payload Operations Director 

PPE Phase Partitioning Experiment 

PRC Payload Changeout Room 

PRF Parachute Refurbishment Facility 

PRSD Power Reactant Storage & Distribution 

PS Payload Specialist 

PVTOS Physical Vapor Transport of Organic Solids 

R&D Research Development 

RCS Reaction Control System 

RMS Remote Manipulator System 

RPS Record Playback Subsystem 

RSS Rotating Service Structure 

RTLS Return to Launch Site 

SAEF Spacecraft Assembly & Encapsulation Facility 

SAIL Shuttle Avionics Integration Laboratory 

SCA Shuttle Carrier Aircraft 

SCAMMA Station Conferencing & Monitoring Arrangement 

SCAPE Self-Contained Atmospheric Protection Ensemble 

SID Simulation Interface Device 

SIP Standard Interface Panel 

SIT Shuttle Interface Test 

SL Spacelab 

SLF Shuttle Landing Facility 

SMAB Solid Motor Assembly Building 

SMCH Standard Mixed Cargo Harness 

SMS Shuttle Mission Simulator 

SN Space Network 

SPIF Shuttle Payload Integration Facility 

SPOC Shuttle Portable On-Board Computer 

SRB Solid Rocket Booster 

SRBDF Solid Rocket Booster Disassembly Facility 

SRM Solid Rocket Motor 

SRM&QA Safety, Reliability, Maintainability & Quality Assurance 

SSC John C. Stennis Space Center 

SSCP Small Self-Contained Payload 

SSIP Shuttle Student Involvement Program 

SSP Standard Switch Panel 

SSME Space Shuttle Main Engines 

SST Single System Trainer 

STA Shuttle Training Aircraft 

STS Space Transportation System 
Edited by Richard W. Orloff, 01/2001/Page 67

T Time 

TACAN Tactical Air Navigation 

TAEM Terminal Area Energy Management 

TAL Trans-Atlantic Abort Landing 

TDRS Tracking and Data Relay Satellite 

TPAD Trunnion Pin Acquisition Device 

TPS Thermal Protection System 

TSM Tail Service Mast 

UHF Ultra-high Frequency 

UV Ultra-violet 

VAB Vehicle Assembly Building 

VLF Very Low Frequency 

VPF Vertical Processing Facility 

WCS Waste Collection System 

WSMC Western Space & Missile Center 

WSMR White Sands Missile Range 

WSSH White Sands Space Harbor 
Edited by Richard W. Orloff, 01/2001/Page 68

SHUTTLE FLIGHTS AS OF SEPTEMBER 1988 

25 TOTAL FLIGHTS OF THE SHUTTLE 

STS-51L 

01/28/86 

STS-61A 

10/30/85 - 11/06/85 

STS-51F 

07/29/85 - 08/06/85 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

 

OV-102 

Columbia 

(7 flights)

OV-099 

Challenger 

(10 flights)

OV-103 

Discovery 

(6 flights)

OV-104 

Atlantis 

(2 flights)