NASA
SPACE SHUTTLE MISSION STS-26
PRESS KIT

SEPTEMBER 1988

                            CONTACTS

                   Sarah Keegan/Barbara Selby
                     Office of Space Flight
                 Headquarters, Washington, D.C.
                     (Phone:  202/453-2352)

                        Geoffrey Vincent
                   Office of Space Operations
                 Headquarters, Washington, D.C.
                     (Phone:  202/453-2754)

                           Lisa Malone
                   Kennedy Space Center, Fla.
                     (Phone:  407/867-2468)

                          Kyle Herring
                  Johnson Space Center, Houston
                     (Phone:  703/483-5111)

                            Ed Medal
         Marshall Space Flight Center, Huntsville, Ala.
                     (Phone:  205/544-0034)

                          Mack Herring
           Stennis Space Center, Bay St. Louis, Miss.
                     (Phone:  601/688-3341)

                          Nancy Lovato
      Ames-Dryden Flight Research Facility, Edwards, Calif.
                     (Phone:  805/258-8381)

                           Jim Elliott
           Goddard Space Flight Center, Greenbelt, Md.
                     (Phone:  301/286-6256)


                            CONTENTS

GENERAL RELEASE...........................................      1
GENERAL INFORMATION.......................................      3
STS-26 -- QUICK LOOK......................................      4
LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF................      5
MAJOR COUNTDOWN MILESTONES................................      9
SUMMARY OF MAJOR ACTIVITIES...............................     11
STS-26 TRAJECTORY SEQUENCE OF EVENTS......................     12
SPACE SHUTTLE ABORT MODES.................................     13
LANDING AND POST-LANDING OPERATIONS.......................     14
TRACKING AND DATA RELAY SATELLITE SYSTEM..................     15
INERTIAL UPPER STAGE......................................     20
SECONDARY PAYLOADS........................................     22
     Physical Vapor Transport of Organic Solids...........     22
     Protein Crystal Growth Experiment....................     24
     Infrared Communications Flight Experiment............     27
     Automated Directional Solidification Furnace.........     29
     Aggregation of Red Blood Cells.......................     31
     Isoelectric Focusing Experiment......................     33
     Mesoscale Lightning Experiment.......................     35
     Phase Partitioning Experiment........................     36
     Earth-Limb Radiance Experiment.......................     38
     Space Shuttle Student Program........................     39
     Weightlessness Effects On Grain And Metal............     40
OASIS INSTRUMENTATION.....................................     41
STS-26 PAYLOAD AND VEHICLE WEIGHTS........................     43
MAJOR ORBITER MODIFICATIONS...............................     44
SOLID ROCKET MOTOR REDESIGN...............................     45
SPACE SHUTTLE MAIN ENGINE IMPROVEMENTS....................     49
SPACEFLIGHT TRACKING AND DATA NETWORK.....................     50
NASA-CONTROLLED TRACKING STATIONS.........................     52
HUNTSVILLE OPERATIONS SUPPORT CENTER......................     53
STS-26 MENU...............................................     54
CREW BIOGRAPHIES..........................................     60
SPACE SHUTTLE PROGRAM MANAGEMENT..........................     63
ACRONYMS AND ABBREVIATIONS................................     67


GENERAL RELEASE

RELEASE:  88-121

STS-26 -- THE RETURN TO FLIGHT                    September, 1988

     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, 
Calif., 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.

     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.)


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


                      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, Fla.

Launch Date/Time:  Late September, 1988, (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, Calif.
  Weather Alternate:  White Sands Space Harbor, N.M.
  Trans-Atlantic Abort:  Ben Guerir, Morocco
  Abort-Once-Around:  Edwards AFB

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.


           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, Calif., 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.

     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 electrial 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 manuevering 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 borescope, 
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 Aug. 
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 Aug. 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.

     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 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 Jan. 
28, 1986.  The STS-26 launch will be conducted by a joint 
NASA/industry team from Firing Room 1 in the Launch Control 
Center.


                      MAJOR COUNTDOWN MILESTONES

Count Event             Event

T-43 Hrs                Power up the Space Shuttle

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

T-30 Hrs                Activate Discovery's navigation aids

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

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

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

T-19 Hrs                Perform interface check between Houston-
                        Mission Control and the Merritt Island 
                        Launch Area (MILA) tracking station

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

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

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

T-9 Hrs                 Activate orbiter's fuel cells

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

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

T-6 Hrs                 Start external tank chilldown and 
                        propellant loading

T-5 Hrs                 Start IMU pre-flight calibration

T-4 Hrs                 Perform MILA antenna alignment

T-3 Hrs                 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 Hrs (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 Hrs, 30 Min         Flight crew departs O&C Building for 
                        Launch Pad 39-B (launch minus 2 hours, 50 
                        minutes)

T-2 Hrs                 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


                   SUMMARY OF MAJOR ACTIVITIES

DAY 1

Ascent
Post-insertion checkout
TDRS-C/IUS deploy
ADSF, PCG, PVTOS, ARC activation

DAY2

Backup TDRS-C/IUS deploy opportunity
PPE

DAY 3

ELRAD
SSIP
Deorbit prep rehearsal

DAY 4

PPE
Flight control systems checkout
Cabin stowage
Landing preparations

DAY 5

Deorbit preparations
Deorbit burn
Landing at EAFB


               STS-26 TRAJECTORY SEQUENCE OF EVENTS


-------------------------------------------------------------------------

EVENT                                      MET                INERTIAL
                                        (d:h:m:s)             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


                      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, Fla.

     * Trans-Atlantic Abort Landing (TAL) -- Loss of two main 
       engines midway through powered flight would force a 
       landing at Ben Guerir, Morocco; Moron, Spain; or Banjul, 
       The Gambia.

     * Return to Launch Site (RTLS) -- Early shutdown of one or 
       more engines and without enough energy to reach Ben 
       Guerir, would result in a pitch around and thrust back 
       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.


              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 umbilicials 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.


           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, Calif.  

     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, N.M., 
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.

     The TDRSS satellites are the largest, privately-owned tele
communications 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 molyb
denum 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 telecom
munications 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, Calif., and 
the Harris Government Communications System Division, Melbourne, 
Fla., 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.


                  TDRS Spacecraft Configuration


                           TDRS System


                      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 equip
ment, 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 con
tract 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.


                      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 ampule 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.


PVTOS art


Protein Crystal Growth Experiment

     Protein Crystal Growth (PCG) experiments to be conducted 
during STS-26 are expected to help advance a technology attract
ing intense interest from major pharmaceutical houses, the bio
tech industry and agrichemical 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 
crystalized 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 founda
tion for protein crystal growth in space, NASA's Office of Com
mercial 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, 
Ala.

     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 pro
tein 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, N.C., 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.

     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. 
Upjohns principal investigator is Dr. Howard Einspahr.


PCG art


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.


IRCFE art


     While the IRCFE calls for a minimum of 2 hours of experimenta
tion, 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 inves
tigator for the experiment is Joseph L. Prather, of the Engineering 
Directorate's Tracking and Communications Division at JSC.


Automated Directional Solidification Furnace

     The Automated Directional Solidification Furance (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.


ADSF art


     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 exper
iment 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.


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 main
tained 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.  


ARC art


     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.


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 
isolectric 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.


IEF art


     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.


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, Okla.

     The Shuttle payload bay camera system provides camera orien
tation 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 bio
medical technology involves separation processes.  Cell types 
producing important compounds must be separated from other cell 
types.  Cells with important biomedical characteristics must be iso
lated 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 par
titioning 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.

     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 35-70mm 
macrozoom 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.


PPE art


     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.


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 ultaviolet 
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.


                 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 aparatus 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.


                        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.


STS-26 Cargo Configuration


               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


                  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.


                   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.

     Longer field joint case mating pins, with a 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 "Stato-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 
stuctural 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 in
sulation.  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.


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.


            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.


              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, Calif.; at White Sands Missile Range, N.M.; 
and at Eastern Space and Missile Center (ESMC), Cape Canaveral Air 
Force Station, Fla.  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, Calif.,
provide highly-critical tracking, telemetry, command and air-ground 
support to the orbiter and send appropriate data to the Johnson and 
Kennedy control centers.


               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


               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.


                              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- Thermostablized
** Day 5 consists of Meal A only                 NF- Natural Form
                                                 B - Beverage
                                                 R - Rehydratable
                                                IM - Intermediate Moisture

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

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

Day 1*, 5**                   Day 2,9                        

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

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)

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

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


                      STS 26 CONTINGENCY/PANTRY

REHYDRATABLE BEVERAGES         QTY       REHYDRATABLE FOOD           QTY
Apple Cider                      5       Soup Kit                       
Cocoa                            5        Chicken Consomee             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
Tea                              5       THERMOSTABILIZED FOOD
Tea w/Lemon & A/S                5       Beef & Gravy (8 oz)           5
Tropical Punch                   5       Chicken Salad Spread          2
TOTAL                          105       Frankfurters                  3
                                         Ham Salad Spread              3
SNACKS                                   Peaches, diced                4
Almonds (NF)                    15       Tuna Salad Spread             2
Butter Cookies (NF)              5       Turkey & Gravy (8 oz)         5
Candy Coated Chocolates (NF)    20       TOTAL                        23
Candy Coated Peanuts (NF)       20
Cashews (NF)                    10
Dried Beef (IM)                 15
Granola Bars (NF)                5       FRESH FOOD
Macadamia Nuts (NF)             10       Apples, Red Delicious         2
Peanut Butter, Crunchy (Jar) (1M)1       Apples, Granny Smith          3
Soda Crackers                   10       Bread, Whole Wheat            2
Trail Mix (IM)                   5       Breakfast Rolls, Menu plus    6
TOTAL                          116       Carrot Sticks                 2
                                         Celery Sticks                 2
                                         Cheddar Cheese, 2 oz          5
                                         Crackers, Goldfish, Plain     1
                                         Crackers, Wheat Thins         1
                                         Tortillas                     2

Drinking Water Containers       20       Life Savers - 5 fruit flavor
In-Suit Food Bars                2
Reentry Kit
  5 Salt Tablets (8)
 20 Long Straws
 20 Drinking Water Containers

A/S - Artificial Sweetner
NF  - Natural Form
IM  - Intermediate Moisture


                        CREW BIOGRAPHIES

     FREDERICK H. (RICK) HAUCK, 47, captain, USN, is mission 
commander.  Born in Rochester, N.Y., he considers Winchester, 
Mass., 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, Colo., 
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.


     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, 
Calif., 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, 
Minn., 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, N.M.; the 
Astronomical Institute at Utrecht, The Netherlands; the 
University of Gottingen Observatory, West Germany; and at the 
Joint Institute for Laboratory Astrophysics in Boulder, Colo.


                SPACE SHUTTLE PROGRAM MANAGEMENT

NASA HEADQUARTERS

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 Dirctor, 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

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

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

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


STENNIS SPACE CENTER

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

Dr. Dale L. Compton           Acting Director

Victor L Peterson             Acting Deputy Director


AMES-DRYDEN FLIGHT RESEARCH FACILITY

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

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


             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 Televison
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 Compution 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
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
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

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 Dissassembly 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

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