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Updated November 9, 2001

STS-108

New Station Crew, Supplies and 

Spacewalk

STS-108

New Station Crew, Supplies and 

Spacewalk
STS-108

Table of Contents 

Mission Overview ..................................................................................................... 1 

Mission Objectives .................................................................................................. 8 

Crewmembers .......................................................................................................... 9 

Flight Day Summary Timeline ............................................................................... 15 

Rendezvous ............................................................................................................ 16 

Spacewalk 

STS-108 EVA ........................................................................................................... 20 

Payloads 

Multipurpose Logistics Module (MPLM) Raffaello .................................................... 22 

Avian Development Facility ...................................................................................... 24 

Commercial Biomedical Testing Module .................................................................. 26 

Starshine 2 ............................................................................................................... 27

Small Experiments ................................................................................................... 29 

Experiments 

DSOs and DTOs ...................................................................................................... 42 

Shuttle Reference Data 

Shuttle Abort History ................................................................................................ 45 

Shuttle Abort Modes ................................................................................................ 47 

Shuttle Rendezvous Maneuvers .............................................................................. 51 

Shuttle Solid Rocket Boosters .................................................................................. 52 

Shuttle Super-lightweight Tank ................................................................................ 59 

Acronyms and Abbreviations ............................................................................... 60 

Media Assistance ................................................................................................... 68 

Media Contacts ...................................................................................................... 70 
STS-108

Mission Overview 

New Station Crew, Logistics Ops., Spacewalk on Tap for STS-108 

A new International Space Station crew, the fourth flight of an Italian-built Multipurpose 

Logistics Module and a spacewalk to install thermal blankets over two pieces of 

equipment at the bases of the space station’s solar wings are major elements of the 

STS-108 flight of Endeavour. 

The Expedition Four crew consists of Russian Commander Yury Onufrienko and 

Astronauts Carl Walz and Dan Bursch. They will replace the Expedition Three crew, 

Commander Frank Culbertson and Cosmonauts Mikhail Tyurin and Vladimir Dezhurov. 

Expedition Three crewmembers were launched to the station aboard Discovery on STS105 on Aug. 10, 2001, and will return to Earth aboard Endeavour. 

The Italian Multipurpose Logistics Module named Raffaello is making its second visit to 

the space station. It first flew aboard Endeavour on STS-100 in April 2001. It is one of 

three virtually identical modules that serve as pressurized moving vans, bringing 

equipment and supplies to the space station. A sister module named Leonardo has 

visited the station twice, on STS-102 in March 2001 and on STS-105 in August 2001. 

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Raffaello will be lifted out of Endeavour’s payload bay and attached directly to the 

station’s Unity node for the unloading of its cargo, which consists of the contents of 

eight resupply stowage racks and four resupply stowage platforms. Much of the material 

will be transferred to the station’s U.S. laboratory Destiny. 

Destiny, installed on the STS-98 mission of Atlantis in February 2001, has slots for 24 of 

the interchangeable racks (six on the top, six on the bottom and six on each side). 

Eleven are systems racks, and one slot has Destiny’s 20-inch-diameter, optical-quality 

window. Remaining slots are available for scientific racks. 

The MPLM will be put back into the cargo bay and returned to Earth for refurbishment 

and reuse on a subsequent mission. The MPLM is valued at $150 million. 

Dominic Gorie, a Navy captain and former test pilot, is commanding his first shuttle flight 

on STS-108. He has flown twice before as pilot, on STS-91, the final shuttle flight to the 

Russian space station Mir in 1998, and on STS-99, the Shuttle Radar Topography 

mission in 2000. Pilot Mark E. Kelly, a Navy lieutenant commander, an honors graduate 

of the U.S. Merchant Marine Academy and a former test pilot, is making his first 

spaceflight. Mission Specialist Linda M. Godwin, who holds a Ph.D. in physics, is a 

veteran of three space flights – STS-37, the Gamma Ray Observatory mission in 1991; 

STS-59, the Space Radar Laboratory flight in 1994; and the STS-76, a flight to the 

Russian space station Mir in 1996. Mission Specialist Daniel M. Tani, who holds an 

M.S. in mechanical engineering from Massachusetts Institute of Technology and was 

selected as an astronaut in 1996, is making his first space flight. 

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About 46 hours after its launch, Endeavour is scheduled to dock with the International 

Space Station. After hatches are opened a welcoming ceremony and a safety briefing 

will be held for the new arrivals. Transfer operations begin about 21⁄2 hours after 

docking. Spacesuit transfer from the station to Endeavour in preparation for the 

mission’s four-hour spacewalk by Godwin and Tani is among the first activities on the 

logistics schedule. 

The purpose of the spacewalk is to install thermal blankets over the Beta Gimbal 

Assemblies (BGAs) at the bases of the station’s two large solar wings. Together the 

wings have a span of 240 feet. The BGAs, atop the station’s P6 Truss, control the wings 

so that they are at an optimal angle to take power from the sun. The blanket installation 

is a sort of preventative maintenance. The BGAs to be covered continue to function; 

elements of them have shown some unexplained spikes in power consumption. 

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Godwin and Tani will take the blankets out of the airlock with them. The shuttle’s robotic 

arm, controlled by Kelly, will take them as far up the P6 Truss as it can reach, perhaps 

30 feet below the work site. They’ll move the rest of the way to the top of the truss, 

taking the blankets with them. 

The blanket installation is relatively straightforward. After it is completed, Godwin and 

Tani are likely to have some time to perform “get-ahead” tasks relating to future station 

assembly work. 

After the spacewalk, attention again turns to logistics. 

In addition to the new crew and the Multipurpose Logistics Module, the shuttle also 

brings to the ISS in its cargo bay the Lightweight Mission Peculiar Support Structure 

Carrier with four Get Away Special (GAS) experiments. Another cargo-bay payload is 

the Multiple Application Customized Hitchhiker-1 (MACH-1), situated between 

Endeavour’s airlock and Raffaello. Among its payloads is the Starshine satellite. 

Starshine is an 85-pound, 19-inch-diameter ball with a surface covered with 845 

aluminum mirrors and 31 laser retro reflectors. More than 25,000 students from 26 

countries polished the mirrors. 

Starshine (the name is an acronym for Student Tracked Atmospheric Research Satellite 

for Heuristic International Networking Experiment) will be deployed by a spring 

mechanism from Endeavour’s cargo bay the day before landing. It is among several 

small, optically reflective spherical Starshine student satellites, built by the U.S. Naval 

Research Laboratory, that are being deployed by NASA. The first was placed in orbit 

from Discovery on STS-96 in June 1999. A second was launched Sept. 29, 2001, from 

the Kodiak launch complex in Alaska. Students and other observers around the world 

precisely observe its position, calculate its orbital decay and use the information to 

study the density of the atmosphere. 

Also aboard the Hitchhiker will be the Capillary Pumped Loop Experiment-3, the 

Prototype Synchrotron Radiation Detector, two Space Experiment Modules containing 

multiple small experiments and a GAS can containing seven experiments. 

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Just forward of the Hitchhiker, on the right payload bay wall, will be two GAS containers, 

one housing seven experiments from Utah State University and the other with an 

experiment looking at smoldering combustion in microgravity. 

Behind Raffaello, at the rear of the cargo bay, is the Lightweight Multipurpose 

Experiment Support Structure Carrier (LMC), with four more GAS cans. One has three 

Penn State University experiments and another contains 10 student experiments. A 

third houses a Swedish Space Corp. experiment focusing on weak Marangoni flows and 

the fourth, from Ames Research Center, is a test of a prototype instrument cooler for 

planetary missions. 

In Endeavour’s middeck area will be the Avian Development Facility and the 

Commercial Biomedical Testing Module – Animal Enclosure Module. The Avian 

Development Facility is flown to validate subsystems and will contain two experiments 

on development in space of Japanese quail eggs. The Animal Enclosure Module is a 

commercial experiment using mice and seeking information that could lead to better 

treatment of osteoporosis in humans. 

STS-108 is the 12th space shuttle mission in support of the space station, the 17th 

mission of Endeavour and the 107th flight in shuttle program history. 

Endeavour 

Endeavour, the newest addition to the four-orbiter fleet, is named after the first ship 

commanded by James Cook, the 18th-Century British explorer, navigator and 

astronomer. 

On Endeavour’s maiden voyage in August 1768, Cook sailed to the South Pacific (to 

observe and record the infrequent event of the planet Venus passing between the Earth 

and the sun). Determining the transit of Venus enabled early astronomers to find the 

distance of the sun from the Earth, which then could be used as a unit of measurement 

in calculating the parameters of the universe. 

In 1769, Cook was the first person to fully chart New Zealand (which was previously 

visited in 1642 by the Dutchman Abel Tasman from the Dutch province of Zeeland). 

Cook also surveyed the eastern coast of Australia, navigated the Great Barrier Reef and 

traveled to Hawaii. 

Cook's voyage on the Endeavour also established the usefulness of sending scientists 

on voyages of exploration. While sailing with Cook, naturalist Joseph Banks and Carl 

Solander collected many new families and species of plants, and encountered 

numerous new species of animals. 

Endeavour and her crew reportedly made the first long-distance voyage on which no 

crewman died from scurvy, the dietary disease caused by lack of ascorbic acids. Cook 

is credited with being the first captain to use diet as a cure for scurvy, when he made his 

crew eat cress, sauerkraut and an orange extract. 

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The Endeavour was small at about 368 tons, 100 feet in length and 20 feet in width. In 

contrast, its modern day namesake is 78 tons, 122 feet in length and 78 feet wide. The 

Endeavour of Captain Cook's day had a round bluff bow and a flat bottom. The ship's 

career ended on a reef along Rhode Island. 

For the first time, a national competition involving students in elementary and secondary 

schools produced the name of the new orbiter; it was announced by President George 

Bush in 1989. The space shuttle orbiter Endeavour was delivered to Kennedy Space 

Center in May 1991, and flew its first mission, highlighted by the dramatic rescue of a 

stranded communications satellite, a year later in May 1992. 

Endeavour is called OV-105, for Orbiter Vehicle-105. 

Day-by-day summary of the mission: 

Day 1 – Launch 

Endeavour’s crew will launch in the afternoon of its day during a precisely timed, fewminutes-long launch window that begins the process of rendezvous with the 

International Space Station. Crewmembers begin a sleep period about seven hours 

after launch. 

Day 2 – Equipment Checkouts, Rendezvous Preparations 

Endeavour’s crew will spend its first full day in space checking out equipment that will 

be used for upcoming major activities -- the shuttle’s robotic arm and the controls and 

tools used for the final rendezvous and docking with the station. The crew also will 

power up and prepare the shuttle’s docking system and perform several engine firings 

to optimize the rate at which Endeavour closes in on the station. 

Day 3 – Rendezvous and Docking 

Plans call for Endeavour to dock with the International Space Station on Flight Day 3. 

Expedition Four crewmembers’ Individual Equipment Liner Kits are transferred to the 

station and stowed temporarily. 

Day 4 – Berthing of the MPLM Raffaello 

Raffaello will be attached to the station’s Unity node, powered up and activated. The 

three Expedition Four crewmembers will install their Individual Equipment Liner Kits in 

the Soyuz capsule docked to the station, thus becoming members of the station crew. 

Day 5 –Spacewalk Preparation 

Astronauts will check out spacesuits and other spacewalking equipment. The station 

and shuttle arms will be prepared for the next day’s activities. 

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Day 6 – The Spacewalk 

Goodwin and Tani will install thermal blankets over the Beta Gimbal Assemblies, atop 

the P6 Truss at the bases of the station’s two large solar wings. The spacewalk is 

expected to last about four hours. Transfer of equipment and supplies to the station 

continues, as do handover talks between the Expedition Three and Expedition Four 

crews. 

Day 7 – Transfer and Handover 

Transfer operations, including moving powered station payloads to the shuttle, continue. 

Biotechnology Refrigerator samples also will be transferred to Endeavour. 

Day 8 – Equipment, Supplies Transfer 

Again station and shuttle crewmembers will transfer equipment and supplies between 

Raffaello and the station. Raffaello will be loaded with unneeded equipment and 

supplies from the station for return to earth. Station crewmembers will continue 

handover activities. 

Day 9 – Raffaello Returns to Endeavour 

Raffaello will be unberthed from the space station and, loaded with its new cargo of 

unneeded equipment and supplies from the station, returned to Endeavour’s cargo bay. 

Station and shuttle crewmembers will review undocking procedures. 

Day 10 -- Shuttle-Station Hatch Closing, Undocking, Flyaround 

The Endeavour and station crews will close hatches between the spacecraft. Gorie and 

Kelly will undock Endeavour from the station. With Kelly at the controls, Endeavour will 

do a flyaround of the complex before departing. 

Day 11– Pre-Landing Checkouts, Cabin Stow 

Activities include the standard day-before-landing flight control checks of Endeavour by 

Gorie and Kelly and the normal steering jet test firing. The crew will spend most of the 

day stowing gear on board the shuttle and preparing for the return home. The Starshine 

satellite will be deployed. 

Day 12 – Entry and Landing 

Kennedy Space Center, Fla., is the preferred landing site. 

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Mission Objectives 

Endeavour (OV-105) 

Top priorities for the STS-108 (UF-1) mission of Endeavour are rotation of the International 

Space Station Expedition Three and Expedition Four crews, bringing water, equipment and 

supplies to the station and completion of spacewalk and robotics tasks. 

International Space Station Program priorities include the following tasks to be 

accomplished. 

--Rotation of the Expedition Three and Expedition Four crews. 

--Water transfer from the shuttle to the station. The quantity will be determined during the 

mission. 

--Berth the Multipurpose Logistics Module to the station, check it out and transfer critical 

cargo to the space station, transfer and stow return cargo in the module and return the 

module to the cargo bay. 

--Transfer and activate powered experiments hardware and other cargo on Endeavour’s 

middeck, the space station’s U.S. laboratory Destiny, and transfer and activate powered 

experiments from the station to Endeavour’s middeck for return to Earth. 

--Conduct spacewalk and robotics activities, including installation of blanket over Beta 

Gimbal Assemblies at the base of the solar wings. 

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Crew Members 

Commander: Dom Gorie 

Dom Gorie, 44, a Navy captain, combat veteran of Desert 

Storm, former test pilot and veteran of two spaceflights, will 

command Endeavour’s STS-108 flight to the International 

Space Station and be responsible for its safety and success. 

He will fly Endeavour through its rendezvous and docking with 

the International Space Station on the 107th flight of the Space 

Shuttle Program. He will be the intravehicular crewmember 

during the spacewalk, helping keep the astronauts on task and 

on time. Gorie will have primary responsibility for water transfer 

from the shuttle to the station, a mission priority. He will assist 

pilot Mark Kelly in Endeavour’s flyaround of the station after 

undocking. Finally, he will land Endeavour at the end of the 

mission. 

Gorie flew as pilot on STS-91, the last shuttle flight to Mir, in June 1998, and on STS-99, 

the Shuttle Radar Topography Mission to map much of the Earth, in February 2000. 

Pilot: Mark Kelly 

A Navy lieutenant commander and, like his commander, former 

test pilot and Desert Storm combat veteran, pilot Mark E. Kelly, 

37, was selected as an astronaut in April 1996. Kelly will be 

responsible for monitoring critical shuttle systems and assisting 

Gorie during ascent and entry. He also will play a major role 

during rendezvous and docking operations, responsible for many 

of the shuttle’s navigational tools. He will be responsible for 

operating still and video cameras. Kelly will be primary arm 

operator during the mission’s single spacewalk. After 

participating in Endeavour’s undocking from the station, he will 

perform the flyaround of the orbiting laboratory. 

Kelly is making his first spaceflight. 

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Mission Specialist 1: Linda Godwin 

Linda M. Godwin, 49, holds a Ph.D. in physics and is a veteran of 

three spaceflights. She will do the spacewalk planned for the 

STS-108 flight of Endeavour. She will have primary responsibility 

for opening and closing of the shuttle’s payload bay doors after 

Endeavour reaches orbit and during deorbit preparations. 

Godwin will be shuttle loadmaster during logistics transfer 

operations. She will have primary responsibility for the 

Androgynous Peripheral Docking System on docking and 

undocking, and for shuttle pressure and leak checks on docking. 

She will be primary operator of the shuttle’s robotic arm during 

berthing and unberthing of the Multipurpose Logistics Module, 

and be responsible for a number of scientific payloads. 

Godwin was a mission specialist on STS-37, the Gamma Ray Observatory flight, in April 

1991. She also flew on STS-59, the Space Radar Laboratory Mission in April 1994, and on 

STS-76, the third shuttle docking mission to the Russian space station Mir in March 1996. 

Mission Specialist 2: Daniel Tani 

Daniel M. Tani, 40, who holds bachelor’s and master’s degrees 

in mechanical engineering from Massachusetts Institute of 

Technology, was selected as an astronaut in April 1996 after 

working for about 10 years for space-related companies, 

primarily with Orbital Sciences Corp. There assignments included 

a period as launch operations manager of the Pegasus program. 

Tani will participate with Godwin in the flight’s spacewalk. Tani 

will serve as Endeavour’s flight engineer during ascent and entry. 

He will have primary responsibility in post-insertion activities, 

converting the shuttle from a launch vehicle to an orbiting 

spacecraft. He will provide information to the commander and 

pilot during rendezvous with the station and after undocking, and 

be responsible for shuttle laptop and payload support computers. 

He has primary responsibility for deploying the Starshine 2 satellite. 

Tani is making his first spaceflight. 

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Expedition Four (Up only) 

Commander: Yury Onufrienko 

Col. Yury Ivanovich Onufrienko, 40, a test cosmonaut and former 

senior pilot in his country’s air force, commanded the Mir 21 

expedition in 1996. Fellow crewmembers included Astronaut 

Shannon Lucid and ISS Expedition Two Commander Yury 

Usachev. As ISS commander, he will have overall responsibility 

for expedition safety and success of the space station and the 

Expedition Four crew. He also will have duties aboard 

Endeavour. During rendezvous he will have backup 

responsibilities for communication with the station and with 

Mission Control-Moscow and for shuttle pressure and leak 

checks. He is backup shuttle robotic arm operator for the 

spacewalk. He has primary responsibility for transfer of the 

culture growth experiment and the contents of the biotechnology 

refrigerator from Endeavour to the station. 

Onufrienko has made one previous spaceflight, as commander of the Mir 21 expedition 

from Feb. 21 to Sept. 2, 1996. 

Flight Engineer: Daniel Bursch 

Daniel W. Bursch, 44, is a Navy captain, a former test pilot and 

test pilot school instructor, and a veteran of three spaceflights. 

He is a Naval Academy graduate and holds an M.S. in 

engineering science from the Naval Postgraduate School. He 

has more than 3,100 flight hours in 35 aircraft types. He became 

an astronaut in 1991. On Endeavour he will be one of two crew 

medics. He will have primary responsibility for contact with the 

station and with Mission Control-Moscow during rendezvous 

operations. Secondary responsibilities include ISS pressure and 

leak checks and initial operations. 

Bursch flew on STS-51, the Advanced Communications 

Technology Satellite and Shuttle Pallet Satellite flight, in 

September 1993. He also flew on STS-68, the Space Radar Lab-2 flight launched in 

September 1994 and on STS-77, with the fourth Spacehab module, in May 1996. 

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Flight Engineer: Carl Walz 

Air Force Col. Carl E. Walz, 46, a former flight test engineer and 

flight test manager, was selected as an astronaut in 1990 and is a 

veteran of three spaceflights. He holds B.S. and M.S. degrees in 

physics and enjoys sports and music – he is lead singer for MAXQ, the astronaut rock-n-roll band. On Endeavour, Walz will have 

primary responsibility for external tank photography, the handheld 

laser rangefinder on rendezvous, pressure and leak checks on 

docking and for moving two scientific experiments from Endeavour 

to the station. He will serve as backup for post-insertion activities 

and as backup for intravehicular spacewalk activities. 

Walz flew as a mission specialist with Bursch on STS-51, the 

Advanced Communications Technology Satellite and Shuttle Pallet Satellite flight, in 

September 1993. He also flew on STS-65, the second International Microgravity Laboratory 

Spacelab module, in July 1994 and on STS-79, a mission to the Russian space station Mir 

in September 1997. 

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Expedition Three (Down only) 

Commander: Frank Culbertson 

Frank Culbertson, 52, a retired Navy captain, former test pilot, and 

former manager of the ISS Phase One (Shuttle-Mir) Program, is 

commander of the Expedition Three mission to the space station. 

Culbertson also will have a number of responsibilities aboard 

Endeavour during STS-108. Among them will be primary 

responsibility for return of three experiments from the station to the 

shuttle, for crew equipment and stowage, for shuttle 

communications with the station and with Mission Control-Moscow 

and as a medic on the shuttle’s trip home. He will have secondary 

responsibility for Endeavour’s deorbit preparations. 

Culbertson was pilot on STS-38, a five-day Defense Department mission in November 

1990. He commanded STS-51, which launched the Advanced Communications 

Technology Satellite and the Shuttle Pallet Satellite in September 1993 and whose crew 

included Expedition Four’s Walz and Bursch. 

Flight Engineer: Vladimir Dezhurov 

Vladimir Nikoaevich Dezhurov, 39, is a veteran of one previous 

long-duration spaceflight, having served as commander of a 

mission aboard the Russian space station Mir in 1995. That crew 

returned to Earth aboard the shuttle Endeavour’s STS-71 mission 

on July 7, 1995, after 115 days in orbit. Dezhurov is a lieutenant 

colonel in his country’s air force and served as a pilot and senior 

pilot, earning three Armed Forces Medals. He was first assigned to 

the Cosmonaut Training Center in 1987. Since 1989 he has trained 

with a group of test cosmonauts. He served as a backup member of 

the Expedition One crew to the International Space Station. 

Dezhurov commanded the Mir-18 mission, a 115-day flight in 1995. 

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Flight Engineer: Mikhail Tyurin 

Mikhail Tyurin, 41, worked as an engineer at RSC Energia after his 

graduation from the Moscow Aviation Institute in 1984. At Energia 

he worked in dynamics, ballistics and software development. He 

continues graduate studies, and his personal scientific research 

relating to psychological aspects of cosmonauts’ training for 

manual control of spacecraft. Tyurin himself was selected to begin 

cosmonaut training in 1993. Since 1998 he has trained as an ISS 

flight engineer. He was a backup crewmember for Expedition One 

before being named an Expedition Three crewmember. 

Tyurin is returning from his first spaceflight. 

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Flight Day Summary Timeline 

EVENT FD MET LOCAL 

Launch 01 00/00:00 11/29/01 

OMS-2 01 00/00:38 11/29/01 

NC1 01 00/03:34 11/29/01 

NC2 02 00/18:24 11/30/01 

NPC 02 00/21:49 11/30/01 

NC3 02 01/02:36 11/30/01 

NH 03 01/16:20 12/01/01 

NC4 03 01/17:07 12/01/01 

TI 03 01/18:40 12/01/01 

ISS docking 03 01/21:00 12/01/01 

Ingress 1 03 01/22:45 12/01/01 

MPLM Berth to ISS 04 02/18:00 12/02/01 

MPLM Hatch Open 04 03/02:50 12/02/01 

Reboost 1 05 03/17:33 12/03/01 

EVA (4 hrs) 06 04/19:30 12/04/01 

Reboost 2 07 05/17:11 12/05/01 

Reboost 3 08 06/17:49 12/06/01 

MPLM Hatch Close 08 07/16:00 12/07/01 

MPLM Berth to STS 09 07/22:25 12/07/01 

Undock 10 08/17:48 12/08/01 

Sep 10 08/19:17 12/08/01 

Starshine DPLY 11 09/16:52 12/09/01 

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Rendezvous and Docking 

Endeavour's rendezvous and docking with the International Space Station begins with the 

precisely timed launch of the shuttle on a course for the station. During the first two days 

of the mission, periodic engine firings will gradually bring Endeavour to a point about 91⁄2 

statute miles behind the station, the starting point for a final approach to the station. 

Endeavour will reach that point about 21⁄2 hours before the scheduled docking time on 

Flight Day Three. There Endeavour’s jets will be fired in a Terminal Intercept (TI) burn to 

begin the final phase of the rendezvous. 

Endeavour will close the final miles to the station during the next orbit of the Earth. As 

Endeavour closes in, the shuttle’s rendezvous radar system will begin tracking the 

station and providing range and closing rate information to the crew. During the 

approach, the shuttle will have an opportunity to make four, small mid-course 

corrections at regular intervals. 

Just after the fourth correction, Endeavour will be about half a mile below the station. 

There, about an hour before the scheduled docking, Commander Dom Gorie will take 

over manual control of the approach. 

Gorie will slow Endeavour’s approach and fly to a point about 600 feet directly below the 

station. There he will begin a quarter-circle of the station, slowly moving to a position in 

front of the complex, in line with its direction of travel. 

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During the rendezvous, Gorie will be assisted by Pilot Mark Kelly in controlling 

Endeavour's approach. Mission Specialists Linda Godwin and Dan Tani also will play 

key roles in the rendezvous, with Godwin operating a handheld laser-ranging device 

and the shuttle's docking system that will latch the spacecraft together. Tani will be 

coordinating checklists and procedures on board the spacecraft. 

Gorie will fly the quarter-circle of the station, while slowly closing in on the complex. He 

will stop Endeavour a little more than 300 feet directly in front of it. From that point, he 

will begin slowly moving directly toward the station's shuttle docking port – moving at a 

speed of about a tenth of a mile per hour. 

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Using a view from a camera mounted in the center of Endeavour’s docking mechanism 

as a key alignment aid, Gorie will precisely center the docking ports of the two 

spacecraft. Gorie will fly to a point where the docking mechanisms are 30 feet apart, 

and pause for a few minutes to check the alignment. 

For Endeavour's docking, Gorie will maintain the shuttle's speed relative to the station at 

about one-tenth of a foot per second, and keep the docking mechanisms aligned to 

within three inches of one another. When Endeavour makes contact with the station, 

preliminary latches will automatically engage, attaching the spacecraft to one another. 

Immediately after Endeavour docks, the shuttle's steering jets will be deactivated to 

reduce the forces acting at the docking interface. Shock absorber-type springs in the 

docking mechanism will dampen any relative motion between the shuttle and the station. 

Once relative motion between the spacecraft has been stopped, Godwin will secure the 

docking mechanism, sending commands for Endeavour's mechanism to retract and 

close a final set of latches between the shuttle and station. 

Undocking, Separation and Fly Around 

Once Endeavour is ready to undock, Godwin will send a command that will release the 

docking mechanism. The initial separation of the spacecraft will be performed by 

springs in the docking mechanism that will gently push the shuttle away from the 

station. Endeavour’s steering jets will be shut off to avoid any inadvertent firings during 

this initial separation. 

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Once the docking mechanism’s springs have pushed Endeavour away to a distance of 

about two feet, when the docking devices will be clear of one another, Kelly will turn the 

steering jets back on and fire them to begin very slowly moving away. From the aft flight 

deck, Kelly will manually control Endeavour within a tight corridor as he separates from 

the ISS, essentially the reverse of the task performed by Gorie when Endeavour docked. 

Endeavour will continue away to a distance of about 450 feet, where Kelly will begin a 

close fly around of the station, circling the complex 11⁄4 times. Kelly will pass directly 

above the station, then behind, then underneath, then in front and then reach a point 

directly above it for a second time. At that point, passing above the station for a second 

time, Kelly will fire Endeavour’s jets to separate the vicinity of the station. The fly around 

is expected to be completed about 90 minutes after undocking. 

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Extravehicular Activity 

Astronauts Linda Godwin and Dan Tani will do a four-hour spacewalk on the sixth day of 

STS-108 to install insulating blankets around two cylindrical mechanisms that rotate the 

International Space Station's large United States solar array wings. Godwin and Tani also 

will perform some "get-ahead tasks” for station assembly work planned during STS-110 

next year. 

For the spacewalk, Godwin will be designated the Extravehicular 1 (EV1) crewmember, 

distinguishable by red stripes on her spacesuit, and Tani will be designated EV2, wearing 

an all white spacesuit. Commander Dom Gorie will serve as the Intravehicular (IV) 

crewmember, choreographing the spacewalk work from inside the shuttle cabin. Pilot Mark 

Kelly will operate the shuttle's robotic arm, maneuvering the spacewalkers during part of 

their work. 

The spacewalk will originate from Endeavour's airlock. Two blankets will be installed, one 

on the mechanism that rotates the port side solar array wing, technically labeled the 4B 

array, and another on the mechanism that rotates the starboard side solar array wing, 

labeled the 2B array. The blankets are designed to moderate the extremes of heat and cold 

that the mechanisms experience in space, safeguarding their future operation. Godwin and 

Tani will carry the blankets out of the airlock with them, each carrying one up to the work 

site, located at the top of the station's P6 truss, about five stories above the station's 

modules. 

After they have left the shuttle airlock, positioned each blanket for translation and gathered 

tools stowed in Endeavour's bay, Godwin and Tani will attach tethers to the end of the 

shuttle's robotic arm. As they hold on, Kelly will maneuver the arm to lift the spacewalkers 

to a point part way up the five-story truss structure, as high as the shuttle arm is able to 

reach. At that point, Godwin and Tani will leave the arm and climb the rest of the way up to 

the top of the truss to the starboard and port rotating mechanisms, called Beta Gimbal 

Assemblies. 

The two spacewalkers will work together to install each custom-designed blanket, turning 

the first on portside mechanism. Tani will be carrying the port blanket and begin to unpack 

it, first attaching straps that will anchor it to handrails. Then, Tani will begin unrolling the 

blanket, wrapping around the barrel-shaped mechanism, passing it underneath the 

assembly and handing the blanket off to Godwin. 

Godwin will continue to wrap the blanket around the mechanism and hand it back over the 

assembly to Tani, where it will be secured to its starting edge using Velcro straps to tighten 

it in place. A hood will unfurl as the blanket is unrolled that will be positioned to insulate 

connectors attached to the mechanism. 

The spacewalkers will then reposition themselves and repeat the procedure to install the 

blanket carried by Godwin around the starboard mechanism. Then, crewmembers will turn 

their attention to several miscellaneous "get-ahead" tasks. 

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STS-108

For the first such task, the crew will remain at the top of the station's truss and Godwin will 

use vice grips to help rotate a latch in place for one brace on the starboard, or 2B, solar 

array wing. The wing has four braces. The brace in question did not latch properly when the 

P6 truss and solar arrays were installed during shuttle mission STS-97 in 2000. The array 

is secure with three braces latched, but the spacewalkers will take advantage of their 

position atop the truss to latch the final brace as well. An analysis by engineers determined 

that the open latch can be engaged by using vice grips to slightly rotate the center shaft, an 

activity that should take only a few minutes. 

Next Godwin and Tani will climb back down the five-story truss, stopping about midway to 

retrieve a protective cover that had been launched on an S-Band Antenna Assembly 

installed on the station last year. After being removed from the antenna, the cover was 

stowed in a storage bin on the truss exterior. Godwin and Tani will bring the cover inside 

Endeavour's cabin for return to Earth. It may be reused. 

Several additional tasks will help with future spacewalks to be performed on shuttle mission 

STS-110 next year that will install a central truss segment on the station. As part of early 

preparations for that work, Godwin and Tani will retrieve several tools that will be needed 

on that flight from kits on the station's exterior and bring them aboard Endeavour. 

The tools will be stowed aboard the station, saving time during that future spacewalk by 

allowing the needed tools to be taken outside with the spacewalkers rather than having to 

be retrieved from various outside toolboxes. Godwin and Tani also will take outside with 

them two Circuit Interrupt Devices, switches that will be temporarily secured to hand rails 

on the station's Z1 truss. The devices will be installed during mission STS-110. 

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Payloads 

Raffaello – Second Round-trip 

Overview 

The Raffaello Multi-Purpose Logistics Module (MPLM) acts as a moving van for the 

International Space Station Program, carrying laboratory racks with science equipment as 

well as racks and platforms filled with bags of experiments and supplies to and from the 

orbiting laboratory. 

On this mission, Raffaello will be mounted in the space shuttle's payload bay for launch and 

remain there until after docking. Once the shuttle is docked to the station, the shuttle's 

robotic arm will remove Raffaello from the payload bay and attach it with common berthing 

mechanisms to the Unity Node on the station. During its berthed period to the station 

individual components will be transferred to the station. 

After Raffaello is unloaded, used equipment and trash will be transferred to it from the 

station for return to Earth. The Raffaello logistics module will then be detached from the 

station and positioned back into the shuttle's cargo bay for the trip home. When in the cargo 

bay, Raffaello is independent of the shuttle cabin, and there is no passageway for shuttle 

crewmembers to travel from the shuttle cabin to the module. 

Raffaello will be filled with equipment and supplies to outfit the U.S. laboratory Destiny, 

which was carried to the International Space Station on STS-98 in February 2001. Of the 

16 racks the module can carry, this mission brings eight Resupply Stowage Racks (RSRs) 

and four Resupply Stowage Platforms (RSPs). 

The RSRs and RSPs within the MPLM contain components to augment existing station 

systems, spare parts for systems already on the station, in addition to food and supplies to 

support the crew. RSRs and RSPs use Cargo Transfer Bags to carry components to the 

station but the racks, platforms, and bags themselves remain in the Raffaello module and 

are returned to Earth aboard the shuttle. 

History/Background 

Raffaello, built by the Italian Space Agency (ASI), is the second of three such pressurized 

modules that serve as the International Space Station’s "moving vans," carrying laboratory 

racks filled with equipment, experiments and supplies to and from the International Space 

Station aboard the space shuttle. 

Construction of ASI's Raffaello module was the responsibility of Alenia Aerospazio in Turin, 

Italy. Raffaello was delivered to Kennedy Space Center from Italy in July 1999 by a special 

Beluga cargo aircraft. The cylindrical module is about 6.4 meters (21 feet) long and 4.6 

meters (15 feet) in diameter. It weighs about 9,000 pounds (almost 4.1 metric tons). It can 

carry up to 20,000 pounds (9.1 metric tons) of cargo packed into 16 standard space station 

equipment racks. 

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Although built in Italy, Raffaello and two additional MPLMs are owned by the U.S. They 

were provided in exchange for Italian access to U.S. research time on the station. 

The unpiloted, reusable logistics module functions as both a cargo carrier and a space 

station module when it is flown. To function as an attached station module as well as a 

cargo transport, Raffaello contains components that provide some life support, fire 

detection and suppression, electrical distribution and computer functions. Eventually, the 

modules also will carry refrigerator freezers for transporting experiment samples and food 

to and from the station. 

Raffaello first flew to the station aboard Endeavour on STS-100/6A in April 2001. 

Common Berthing Mechanism 

The Common Berthing Mechanism (CBM) connects one pressurized module to another on 

the U.S. segment of the International Space Station. The active half weighs 583 pounds 

and is made up of an 80-inch-diameter structural ring, four capture latches, eight alignment 

guides, four powered bolts and actuators, four ready-to-latch indicators, four controller 

panel assemblies, and striker plates. 

Only the active half of the CBM connects to power and data. The passive half weighs 360 

pounds and has a structural ring, four capture latch fittings, eight alignment guides, 16 

power bolt nuts and four ready-to-latch indicators. 

During installation of a module that uses the CBM, the robotic arm of the shuttle or the 

space station moves the module with the passive half into the capture envelope of the 

active half. The latching process begins as the active CBM extends four capture latches to 

catch the passive CBM. The 16 power bolts then extend from the active CBM and are 

inserted into the bolt nuts of the passive CBM, completing the connection. 

There are more than 25 CBMs on the space station. 

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Payloads 

Avian Development Hardware Set for Flight 

Overview 

The second generation of avian development hardware, the Avian Development 

Facility, is designed for space experiments that use Japanese quail eggs. The main 

ADF objective on the STS-108 mission is to validate its subsystems and reduce the risk 

in developing the next generation of avian development hardware, the Egg Incubator. 

The ADF provides optimal incubation conditions for embryo development during flight. It 

also minimizes crew time and improves the science return by using advanced 

telerobotics and teleoperations. NASA’s Ames Research Center, Moffett Field, Calif., 

manages the ADF project. 

Secondary objectives will be support of two experiments studying how the lack of 

gravity affects the development of avian embryos. Stephen Doty, Ph.D., of the Hospital 

for Special Surgery in New York City, will study the effects of spaceflight on embryonic 

skeletal development. The development and function of the avian vestibular system will 

be the focus of a study by David Dickman, Ph.D., of the Central Institute of the Deaf, 

Washington University, St. Louis, Mo. 

The ADF is an automated avian egg incubator that requires no crew interaction with the 

eggs. It provides a snapshot of embryogenesis in space using the avian embryos as a 

biological model. Avian eggs are ideally suited for microgravity research because they 

are self-contained and self-sustaining. 

The ADF will house 36 Japanese quail eggs in holders designed to isolate the eggs 

from vibration and to minimize any effects of launch and re-entry on the developing 

embryos. The egg holders are mounted on two rotating centrifuges that will provide 

either exposure to microgravity or to a gravity force equivalent to that found on Earth. 

Interior environmental temperature, humidity, carbon dioxide and oxygen concentration 

can be pre-programmed to provide optimal incubation conditions. The ADF also has an 

automated fixative-injection system that can be programmed to fix or preserve the 

embryos at specific times during incubation. The egg holder is designed with a 

secondary containment system to prevent leaking of injected fixative into the incubator. 

The ADF rotates the eggs 180 degrees every hour, similar to turning in a natural 

environment. The facility fits into a space shuttle middeck locker. 

The ADF is the first of several research habitats to fly on board the International Space 

Station that are being developed as part of the Space Station Biological Research 

Project (SSBRP) at NASA Ames. The SSBRP is responsible for managing the 

development of several habitats that provide life support, environmental control, and 

monitoring systems for various research subjects and specimens. The habitats are 

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being developed to operate with three major host systems: the variable-gravity, 2.5-

meter centrifuge; the microgravity-holding racks; and the Life Sciences Glovebox. In 

addition, SSBRP will manage the development of various laboratory equipment items 

needed for science operations. 

Space Hardware Optimization Technology, Inc. (SHOT), of Greenville, Ind., developed 

the ADF for NASA Ames. The ADF is the second generation of avian development 

hardware from SHOT. The first-generation hardware flew on the space shuttle in 1986 

and 1989. The third-generation Egg Incubator will be capable of supporting long-term 

egg incubation experiments on the International Space Station. Possible future studies 

will examine embryo orientation and mortality, embryogenesis, and development of 

bone and muscular tissue. 

The two ADF experiments are supported by NASA’s Office of Biological and Physical 

Research, which promotes basic and applied research to support human exploration of 

space and to take advantage of the space environment as a laboratory. More 

information is available at: http://spaceresearch.nasa.gov/. 

The information collected from this mission is expected to help Earth-based 

biotechnology and health care research leap forward toward cures or treatments that 

may otherwise not have been realized. 

More information about Ames’ life sciences research and the Space Station Biological 

Research Project is available at http://lifesci.arc.nasa.gov/ and at 

http://brp.arc.nasa.gov/. 

Details about SHOT are available at http://www.shot.com. 

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Payloads 

Commercial Biomedical Testing Module Experiment 

Principal Investigators: Dr. Paul Kostenuik, Amgen Thousand Oaks, Calif. 

Overview 

Osteoporosis is a debilitating disease that can lead to bone fractures and result in reduced 

quality of life for the elderly population it generally afflicts. With 80 percent of the incidence 

of osteoporosis in females, more than 30 million women in America are at risk of 

developing osteoporosis and subsequently have an increased risk of serious bone 

fractures. 

A promising treatment for this brittle bone condition is being tested during STS-108 by 

Amgen Inc., a biotechnology firm in Thousand Oaks, Calif. This treatment is the protein 

osteoprotegerin (OPG), a potent regulator of bone metabolism. The experiment is made 

possible by Amgen’s work with one of NASA’s 17 Commercial Space Centers: BioServe 

Space Technologies at the University of Colorado, Boulder and Kansas State University, 

Manhattan. 

Before launch, Amgen scientists will treat 12 lab mice with OPG; 12 similar lab mice will 

receive a placebo. During the flight, the rodents will reside in an Animal Enclosure Module. 

Similarly treated mice will remain on Earth to control for the effects of gravity. Periodically, 

crewmembers will monitor the status of the mice and their habitat. After the shuttle lands, 

the mice will be returned to Amgen and BioServe scientists who will examine the effects of 

spaceflight and the ability of OPG to mitigate the effects of spaceflight on osteoclast/ 

osteoblast signaling using various analysis methods. 

This space experiment will contribute to Amgen’s ground-based studies of OPG. Since 

spaceflight induces a complete, more systematic, accelerated bone loss, it is expected to 

provide a good model for osteoporosis and potential treatments. Potentially, it could provide 

scientists with further insight into the relationship between skeletal loss from microgravity 

and the role of OPG and OPG-ligand (or OPGL, a protein that OPG binds with) in the 

determination of bone composition, morphology and mechanical properties. This data may 

assist Amgen in its development of OPG as a treatment for osteoporosis. 

NASA also is interested in treatments that prevent bone loss in astronauts. Microgravityinduced bone loss is a significant barrier for long-term human spaceflight. For various 

reasons, current medications for osteoporosis are not appropriate or ideal 

countermeasures for most astronauts. In addition to this study, NASA is studying bone loss 

in space station crewmembers. 

This is the first time OPG will be studied in space. This payload is Amgen’s first space 

experiment. 

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Payloads 

Students to Track Starshine 2, Atmospheric Research Satellite 

Overview 

About 25,000 students from 26 countries are awaiting the deployment of Starshine 2 

during the STS-108 mission. The students helped polish nearly 900 mirrors that cover 

the surface of the beach ball-sized hollow aluminum sphere that will orbit the earth for 

almost a year. During the satellite's mission, sunlight reflecting from the mirrors will be 

visible to the naked eye during morning and evening twilight hours. Teams of 

elementary, middle and high school students will visually track the satellite and note the 

times that it passes between selected pairs of targeted stars. 

The students will enter their observations on the STARSHINE project's Internet site at 

http://www.azinet.com/starshine, and the U.S. Naval Research Laboratory and the U.S. 

Space Command will use the measurements to calculate the satellite's orbit. The orbital 

data will be used to post sighting predictions on a link from the web site so the students 

will know where and when to look for Starshine 2's next appearance over their 

observation sites. As the project progresses, high school students will be taught how to 

calculate the orbits on their personal computers. 

Throughout the mission, students will measure the daily change in the time it takes 

Starshine 2 to circle the Earth. The students will use this information to calculate the 

density of the Earth's upper atmosphere. During its eight-month lifetime, Starshine 2 will 

gradually lose altitude because of the aerodynamic drag caused by the atmosphere's 

density and eventually will burn up like a flaming meteor approximately 50 miles (80 

kilometers) above the Earth. 

Students will also look at daily extreme ultraviolet radiation from the sun on the 

STARSHINE web site and count the sunspots on the solar surface. They will plot this 

radiation against the rate of change of Starshine 2's orbital period to learn how solar 

storms heat and expand the Earth's upper atmosphere, causing variations in its density 

and producing aerodynamic drag. 

The spacecraft contains a special cold gas spin system that will rotate the satellite five 

degrees per second to enhance the rate at which sunlight will flash from its mirrors. In 

addition, the satellite carries twenty laser retro-reflectors, distributed evenly across its 

surface, to permit tracking by the International Satellite Laser Ranging Network. 

The mirrors covering the entire spacecraft were machined by Utah high school 

technology students and were shipped to students around the world to be polished. 

They were then coated with a scratch-resistant, anti-oxidizing layer of Silicon Dioxide at 

the Hill Air Force Base and then installed by engineers at the NRL in Washington, D.C. 

Starshine 2 will fly into space in a Hitchhiker canister in the payload bay of Endeavour 

and will be deployed 240 miles (387 kilometers) above the Earth while inclined to the 

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Earth's equator by 51.6 degrees toward the end of the mission. The spacecraft weighs 

86 pounds (39 kilograms) and is almost 20 inches (one half meter) in diameter. 

Background 

Starshine 2 is the third satellite of Project STARSHINE to be deployed. Project 

STARSHINE originally planned to launch one satellite per year over an 11-year solar 

cycle, but changes in launch schedules have resulted in two being launched in one 

year. Starshine 1 was launched aboard Space Shuttle Discovery in May 1999 and 

provided eight months of data for students around the world. Starshine 3 was launched 

from the Kodiak Launch Complex, Alaska, in September 2001 and is orbiting 470 

kilometers above the Earth. By the end of this year, mirror-polishing kits will be sent to 

applying schools so they can begin work on the mirrors for Starshine 4 and 5. 

Benefits 

The principal objectives of Project STARSHINE are educational and motivational. If 

students help "build" the spacecraft (by polishing its mirrors), they should be more 

excited about tracking it and using it to measure upper atmospheric density and the 

response of that region of the atmosphere to solar storms. 

Project STARSHINE is giving pre-college students a chance to work with real space 

hardware and learn how to do precision work on elements of that hardware. They also 

learn about satellite orbits and the earth's upper atmosphere and the interaction 

between the Earth's and sun's atmospheres and magnetospheres. The participants use 

the Internet to obtain knowledge, report their measurements, and communicate as team 

members with students in other countries. They are taught how to make precision 

optical measurements and use precision timing systems to make those measurements, 

and they learn something about observational astronomy and orbit dynamics. In short, 

they learn that science and engineering and technology can be fun and still produce 

useful results. 

Through observations of STARSHINE satellites, students will learn the basic principles 

of solar-terrestrial physics. To further this end, the project posts daily satellite images of 

the sun on its web site. 

Besides educating and motivating students, Project STARSHINE may have scientific 

benefits. If enough students do serious tracking of the spacecraft to get good orbits, 

especially during the terminal phase of flight, the project might be able to contribute to 

the pool of knowledge of the average density of the atmosphere in the 50- to 291-mile 

(80- to 470-kilometer) altitude regime. Since STARSHINE satellites are spherical, they 

have a much more uniform drag coefficient than spacecraft with solar arrays and helical 

antennas and other structures protruding from them, so the density measurements that 

will be made from tracking STARSHINE satellites will be more precise than those from 

tracking other re-entering spacecraft. 

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Payloads 

Small Payloads Provide Worldwide Research Opportunities 

Overview 

Researchers worldwide will fly experiments on STS-108 through NASA’s Shuttle Small 

Payloads Project (SSPP), managed at the Goddard Space Flight Center in Greenbelt, Md., 

and its Wallops Flight Facility, Wallops Island, Va. The SSPP designs, develops, tests, 

integrates and flies a group of carrier systems in the shuttle’s cargo bay. These carriers – 

the Hitchhiker, Hitchhiker Jr., Get Away Specials and Space Experiment Module – support 

payloads supplied by NASA, other U.S. government agencies, domestic and foreign 

commercial customers, foreign governments, and schools from kindergarten through 

universities. The following small payloads will be flown aboard Endeavour during the STS108 mission. 

Hitchhikers 

Hitchhiker payloads fly in mounted canisters attached to mounting plates of various sizes. 

For STS-108, the Hitchhikers, Hitchhiker Jr. and two SEMs will fly on a cross-bay platform. 

The Hitchhiker carrier provides electrical power, command signals, and “downlink” data 

interfaces. Hitchhiker customers may operate their payloads from the Hitchhiker Control 

Center at the Goddard Space Flight Center or from a remote site. 

Hitchhiker web site: http://sspp.gsfc.nasa.gov/hh/index.html

Capillary Pumped Loop Experiment (CAPL-3) 

NASA Goddard Space Flight Center/Naval Research Laboratory/Swales Corp. 

Capillary Pumped Loops are two-phase heat transfer devices that use capillary forces for 

heat acquisition and fluid pumping with no moving parts. A single system can cool multiple 

components and reject heat to multiple radiators. The system can transfer high heat loads 

over long distances with reliable, vibration-free operation and passive control. The design 

provides versatility and lower weight compared to heat pipe systems. It uses heat load 

sharing. It can automatically use waste heat from operating components to warm nonoperational components. 

Earlier experiments flew on STS-60 and STS-69. The main objective of CAPL-3 is to 

demonstrate in space a multiple evaporator capillary pumped loop system, capable of 

reliable start-up, reliable continuous operation and at least 50 percent heat load sharing 

with hardware for a deployable radiator. It is a two-phase ammonia thermal control system 

consisting of a capillary pumped loop with multiple capillary evaporators and parallel direct 

condensation radiators.

Experiment Manager – Laura Ottenstein, GSFC 

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Hitchhiker Jr. (1) 

The Hitchhiker Jr. carrier provides mechanical and electrical interfaces similar to a Get 

Away Special, but has avionics to monitor carrier and payload functions and power 

services. 

Hitchhiker Jr. web site: http://sspp.gsfc.nasa.gov/hhjr/index.html

Collisions into Dust Experiment (COLLIDE-2) 

NASA Glenn Research Center/University of Colorado 

COLLIDE-2 is an investigation into planetary dust rings. A follow-on to COLLIDE-1, which 

flew on STS-90, COLLIDE-2 performs low-velocity impact experiments into simulated dusty 

regoliths in microgravity. These impacts simulate the conditions in planetary rings and early 

protoplanetary disks. The experiment will give scientists a look at the dynamics, origin and 

evolution of planetary ring systems. Rings are collisonally evolved systems. Collisions 

sculpt the ring, leading to spreading, transfer of anular momentum, release of dust particles 

and damping of waves and wakes. The rate of evolution depends on dissipation of energy 

in collisions. COLLIDE-2 results also can be applied to the lifecycles of planetary dust rings. 

Principal Investigator: Joshua Colwell, University of Colorado 

Project Manager: Monica Hoffmann, NASA Glenn Research Center 

Web site: http://lasp.colorado.edu/collide

Get Away Special (GAS) 

The Get Away Specials carrier provides limited mechanical and electrical interfaces for selfcontained experiments. Simple crew control functions may be performed, but the user 

addresses internal system requirements. The GAS carriers flown will be about the size of a 

55-gallon drum or half that size. The customer equipment can weigh up to 200 pounds 

(91.32 kilograms). 

Get Away Special web site: http://www.wff.nasa.gov/gas

G-761 

Argentine Experiments Package (Paquete Argentino de Experimentos – PADE) 

The Argentine Association of Space Technology is flying seven experiments designed by 

personnel at Argentine universities and scientific institutions. 

1. Transport Fluids in Non-Circular Tubing 

This experiment looks at the flow of fluids in microgravity through various 

geometric shaped tubes to determine the most efficient way to transport fluids in 

space. 

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2. Surface Vibration of Water Drops 

Scientists will measure the surface vibration generated by surface tension in 

water drops in microgravity. Similar tests on Earth are influenced by gravity. The 

results may have applications in the petrochemical industry as well as space 

applications. 

3. Migration of Drops and Bubbles in Microgravity 

Scientists will study the convection of water drops and bubbles in microgravity to 

determine the feasibility for future development of a detector of drop and bubble 

movement based on thermal changes. 

4. Exposure of Seeds to Space 

This experiment is designed to examine cell mutation and modifications in 

several types of seeds exposed to the space environment. The retrieved samples 

will be compared with samples maintained on Earth. The experiment will be used 

to interest Argentine high school students in biological experiments. 

5. Crystal Formation and Growth in a Microgravity Environment 

The objective of this experiment is to determine the differences in crystal growth 

between Earth and space. The results may be applicable to the pharmaceutical 

and electronics industries. 

6. Maximum Accelerations Register 

To aid in the development of an acceleration recorder that does not require 

electrical energy, the experiment will record maximum acceleration of the orbiter 

during flight. The experiment consists of two systems to record acceleration: a 

mechanical device which turns springs and a device activated by the change of 

shape of strings from one stable equilibrium position to another. 

7. Geophysical Fluids Movement 

This experiment simulates a small “planet” in its container. Its goal is to use 

microgravity to simulate atmospheric and sea movement in spherical bodies to 

better understand the Earth’s atmosphere and oceans. 

Payload Manager: Pablo De León 

PADE web site: http://www.aate.org/g761.htm

G-775 

Microgravity Smoldering Combustion (MSC) 

NASA Glenn Research Center 

Smoldering combustion is a serious problem: 40 percent of all fire deaths in the U.S. can 

be attributed to the smoldering of household furniture, which releases toxic byproducts. 

Smolder is potentially an even greater problem in space. By increasing our fundamental 

understanding of smoldering combustion, the MSC experiment will improve our ability to 

predict and prevent smolder-originated fires on Earth and in space. 

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The experiment consists, essentially, of heat, fuel, and air. The hardware includes a 

cylindrical sample holder, whose major parts are a flow inlet for the introduction of air; an 

igniter to start the smoldering process; thermocouples to measure temperature and 

determine speed; and polyurethane foam which functions as the fuel. The sample holder is 

placed inside a sealed combustion chamber, which in turn is placed in the MSC flight 

assembly (which holds two combustion chambers). This assembly, which is placed inside 

the Get Away Special canister in the cargo bay of the space shuttle, includes an ultrasonic 

imaging system similar to those found in medical clinics and hospitals. This imaging system 

can “see” into the foam to measure the extent of smolder. 

An earlier version of the MSC experiment flew on USML-1 in 1992. The present version 

was flown aboard STS-69 (1995), STS-77 (1996) and STS-105 (2001). 

Principal Investigator: Prof. A. Carlos Fernandez-Pello, University of California-Berkeley 

Project Scientist: Dr. David Urban, NASA Glenn Research Center, Cleveland, Ohio 

Project Manager: Frank Vergilli, NASA Glenn Research Center 

Web site: http://microgravity.grc.nasa.gov/combustion/index.htm#top. 

G-221 

Utah State University 

Three high schools from Utah and Idaho designed and built experiments. Utah State 

University sponsored the GAS container and provided assistance to the students. G-221 

also contains popcorn that will be used in science outreach programs by the university with 

local elementary school students. 

Nucleic Boiling 

We all know that when water boils, the bubbles go up. In space, because of the lack 

gravity, there is no up. So, where do the bubbles go? That is the question this experiment is 

trying to answer. The experiment boils water inside a chamber and videotapes the action of 

the bubbles. Small thermometers placed in different locations in the chamber record the 

temperature. The collected data will allow students at Box Elder High School, Brigham City, 

Utah, to see how the bubbles move in the chamber while it is being heated. 

Chemical Unit Process 

On a long journey in space, all you have is what you brought with you. That includes water. 

For the water to continue to be useful, a method of purifying the water needs to be 

developed for space applications. This experiment takes a solution of urea (a major 

component of urine) and purifies it through a process developed by students at Shoshone 

Bannock Jr./Sr. High School, Ft. Hall, Idaho, with the help of engineers at INEEL. Once the 

experiment returns, the students will analyze the water to identify any contamination. 

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Crystal Growth 

Some crystals form differently in the microgravity of space than they do on Earth. This 

experiment is going to grow crystals from chemicals commonly found in the human body. 

During long-duration space flight it will be important to know how these crystals form 

differently in space. The results will be examined by students from Moscow High School, 

Moscow, Idaho. 

Popcorn and Seeds 

Elementary school students will be given a package of earthbound microwave popcorn and 

a package that flies on G-221. The students will determine which bag went to space. The 

students will characterize the two samples after popping. Each group will decide what 

properties of the popcorn to measure. 

Principal Investigator: Jan Sojka 

Web site: http://gas.physics.usu.edu

G-730 

Weak Convection Influencing Radial Segregation 

Swedish Space Corp. 

The electrical properties of a semiconductor are strongly influenced by the addition of small 

amounts of a so-called dopant and its spatial distribution within the semiconductor crystal. 

In this experiment the influence of weak convection, caused by surface tension forces on 

radial dopant segregation, is studied under microgravity conditions in seven mirror 

furnaces. The method used is the floating zone technique, and antimony has been chosen 

as sample material. 

Varying the geometry of the free surfaces among the seven flight samples offers the 

possibility to obtain different levels of the thermocapillary convection. The experiment 

sequence and furnace processing is controlled by a PC104 computer system with a CPU 

and a data acquisition board. 

The payload is powered from two 44-volt batteries of sealed lead-acid cells with a nominal 

capacity of 1060 watts. During the experiment phase measured experiment data, housekeeping data and data from accelerometers are stored in a non-volatile memory. 

Principal Investigator: Professor Dr. Torbjorn Carlberg, Mid Sweden University 

Experiment system design and manufacturing: Swedish Space Corporation’s Space 

Systems Division under contract from the European Space Agency (ESA) and the Swedish 

National Space Board (SNSB). 

Project Manager: Per Holm, Swedish Space Corp. e-mail: per.holm@ssc.se , 

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For more information on the Swedish Space Corporation see http://www.ssc.se. 

For more information on ESA, see http://www.esa.int. 

For more information on SNSB, see http://www.snsb.se. 

For more information on Mid Sweden University, see http://www.mh.se

G-064 

Penn State University 

This GAS project provides an opportunity for about 50 Penn State University students to 

experience “hands-on” design and fabrication of hardware and to learn teamwork and 

project management. Three experiments have been prepared to investigate plant growth in 

space, the magnetic field environment in the shuttle, and the acoustic signature for 

collisions on the shuttle by space debris. Support for this project also is provided by 

Lockheed Martin Corp. 

1. “PSU Germinator I” is a low-cost and reusable experimental plant growth 

chamber for seed germination and early seedling development. The experiment 

is designed to answer questions related to sustained plant life in space and 

provide an affordable space-rated test chamber for microgravity and life science 

researchers. 

2. The “Magnetometer” will record a three-dimensional model of magnetic moment 

of the space shuttle and measure distortions of the uniform background signal 

from currents that produce a part of the Earth’s magnetic field. The experiment 

will be activated at 50,000 feet during ascent of the shuttle and collect data for 

five hours. 

3. The “Orbital Debris Experiment” will measure the acoustical signature from hits 

on the shuttle by micro-meteors or space junk to test a concept for a future space 

station monitoring sensor. The experiment will operate for seven days. 

G-785 

NASA Ames Research Center

This experiment is designed to determine zero-g performance of a miniature two-stage 

pulse tube cryocooler, a small refrigerator that uses oscillating gaseous helium to achieve a 

very cold temperature (-315° F, or -193° C) without using cold moving parts. A secondary 

objective is to measure the thermal conductance of the cryocooler stages (the cold head) 

over a wide temperature range in zero-g. A third objective is to demonstrate the launch 

survivability and performance of a cryocooler that uses mostly commercial components. On 

STS-90, the last two objectives were largely achieved and have been reported. However, 

the primary objective was not fully achieved due to low voltage on some of the batteries 

that supply power to the small compressor that produces the oscillating helium in the cold 

head. The re-flight payload incorporates a significantly improved battery system. 

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Miniature cryocoolers are required to cool infrared (IR) sensors in space-based instruments 

such as imagers and spectrometers. Remote IR sensing is used to measure the 

temperature and chemical composition of the earth’s surface and atmosphere. 

G-785 was developed as a collaboration among Lockheed Martin Corporation (LMC), 

Denver, Colo.; the National Institute of Standards and Technology (NIST), Boulder, Colo.; 

and NASA Ames Research Center (ARC), Moffett Field, Calif. 

Primary and co-investigators: Dr. Peter Kittel (ARC) 

 Dr. Daniel Ladner (LMC) 

 Dr. Ray Radebaugh (NIST) 

Space Experiment Module (SEM) (3) 

The Space Experiment Module is a self-contained assembly of structure, power, command 

and data storage capabilities for microgravity experiments. SEM is open to students in 

grades K-12 and university level. Selected student experiments are flown in NASAprovided modules. The SEM carrier accommodates 10 modules in a standard Get Away 

Special canister. 

For more information see: http://www.wff.nasa.gov/sem

SEM-11 

This module has both active (power required) and passive (no power required) experiments 

from the United States, Argentina, Portugal and Morocco. It also includes winning entries 

from the 2000 and 2001 NASA Student Involvement Program. 

RESUME (Restrain Release Using Melting-Wire Experiment) (Active) 

Universidad Tecnológica Nacional, Argentina 

The goal of RESUME is to perform design, analysis test and flight qualification of a 

multipurpose original restrain-release mechanism for fastening deployable systems in 

spacecraft. The mechanism is based on a melting wire triggered system. It is being flown 

through an agreement between NASA and the Argentine National Space Agency. 

ARIA-3 (Passive) 

Washington University, St. Louis, Mo. 

The Aria-3 project is a joint Australian/U.S. K-12 education project that will carry 22 

experiments focusing on the effects of space on Australian flora/fauna. Schools in Australia 

will select local flora/fauna that meet the long-duration storage requirement of the SEM 

program, prepare two samples, keep one on the ground, and fly the second one in space. 

Once the flight experiments are returned to earth, students will compare the flight and earth 

samples to detect differences. The Aria-3 involves schools in Australia teamed with schools 

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in the United States. The Australian schools work via email with a “sister” school in 

Missouri. 

Effect of Weightlessness on the Developmental Cycle in Gypsy Moth (Passive) 

Mohamed V University, Morocco 

This experiment will include several batches of gypsy moth eggs, in a state of diapause, to 

study the effects of weightlessness on development. Upon their return to Earth, 

development will be compared to that of control eggs maintained in the laboratory as 

measured by the degree of absorption of the extra-embryonic yolk, time to hatching, and 

survival rate. Histological organ data will also be compared. 

PULS R – Portugal – Unified Learning through Space & Research (Passive) 

Ciência Viva - National Agency for Scientific and Technological Culture, Portugal 

The experiments include testing for possible modifications in the seeds of plants, including 

some Portuguese endemic species and Mediterranean species. 

Collaborative International SEM (Passive) 

GADGET - Glenbrook North High School, Northbrook, Ill. 

This experiment is part of a collaborative international SEM project. Students from the U.S., 

Portugal, Morocco and possibly other countries will be involved. The experiments will 

investigate the effects of the space environment on different types of seeds. Others will test 

plant products of Portugal and the U.S.

CRISTANAR (Active) 

Argentina 

This experiment studies microgravity’s effect on the growth and electro-optical properties of 

KDP crystals (potassium dihydrogen phosphate, KH2PO4) and compares them with crystals 

grown on Earth. Crystal growth uses the super saturation method with a slow temperature 

decrease. After the flight, the crystals remain in thermal equilibrium with the KDP aqueous 

solution that acts as a means of preservation. 

Three-Dimensional Resonance Modes in Microgravity (Active) 

GADGET - NSIP 2000 - Glenbrook North High School, Northbrook, Ill. 

This experiment will study how Faraday resonance will affect a wax-like substance 

suspended in a sodium silicate solution in microgravity. It uses a tone-generated sound 

system with a speaker attached directly to the acrylic box containing the wax and sodium 

silicate, applying a sequence of tones. The results will be videotaped for further analysis in 

both constant and strobe lighting. Information gained from this experiment may some day 

help in understanding the resonance modes of structures made for microgravity. 

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Electro-Deposition of CUSO4 (Active) 

NSIP 2000 - The Northwest School, Seattle, Wash. 

The experiment uses electrodeposition to determine the effects of microgravity and cosmic 

radiation on the flow of electrons. The experiment will analyze the fractal patterns formed 

by the deposition of copper when an electric current is passed through a solution of cupric 

sulfate. Results will help determine how electrical currents flow in the space environment. 

SISTEM (Passive) 

Kingswood Regional Middle School, Wolfeboro, N.H. 

This experiment examines whether the space environment will affect subsequent 

generations of various seeds flown in space. This experiment may include thousands of 

participants by the end of the fifth year. 

Artemia Space Launch Experiment (Active) 

NSIP 2001 - DuVal High School, Lanham, Md. 

The purpose of the experiment is to see how microgravity affects the rate of hatching, 

growth, size and mobility of brine shrimp. Students from the two ISA classes have 

constructed a device to inject dehydrated brine shrimp eggs into a culture solution at a 

predetermined time during the mission. A micro video camera will film the eggs in the 

solution about every three hours. 

SEM-12 

SEM-12 will be mounted on the LMC. SEM-12 will carry only passive experiments. 

Space FIZ-ics 

Athol-Royalston Middle School, Athol, Mass., and Schaumburg High School, 

Schaumburg, Ill. 

This experiment studies effects of microgravity, radiation, and temperature fluctuation on 

the production of carbon dioxide and the growth rate of yeast cells in a closed fermentation 

chamber. A secondary experiment is to test the ability of a launch-activated passive 

mechanical device to initiate the experiment. 

Blast-Off 

Anne Arundel County Schools, Anne Arundel County, Md. 

This experiment is an extension of the fourth-grade curriculum Space and Space 

Technology. The value of the experiment is to see how the space environment will affect 

materials, and if they would be useful on the space station. The effect of space travel on 

dental gum will be investigated to determine the feasibility of using it to replace brushing 

teeth in space. The second experiment will determine the effect of the space environment 

on tardigrades, and how they will behave when reconstituted after spaceflight. 

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A Study on the Role of Adhesives in Entombed Hybrid Patches 

Old Dominion University, Norfolk, Va. 

An advanced repair concept with possible future applications for damaged space structures 

is the subject of this experiment. The repair patch uses weld bonding which is an advanced 

hybrid technology that has the advantages of laser welding and adhesive bonding 

combined. Also, third grade students at Hilton Elementary School in Newport News, Va., 

and Ghent Elementary School in Norfolk, Va., will send corn seeds into space to determine 

if the space journey affects their growth cycle. 

The Effect of the Space Environment on Shape Memory Alloy 

The Harker School, San Jose, Calif. 

Nitinol is a material that exhibits shape memory properties. In one-g conditions, Nitinol 

devices that are deformed revert to their original shape when heated. This investigation 

looks at whether Nitinol devices deformed in microgravity can revert to their original shape 

when heated after return to Earth. 

Medium Movement 

Mechanicsburg School District, Mechanicsburg, Pa. 

This experiment looks at movement of half-inch-diameter wooden spheres in closed 

containers of various media (balsa wood, cork, caulking material, play-dough, potting soil, 

pink fiberglass insulation, talcum powder, or Styrofoam insulation) during space flight. 

Results will be compared with a control experiment on the ground. 

The Florida-Mars Connection 

Palm Beach County Middle Schools, Boyton Beach, Fla. 

The experiment looks for food plants that can grow in Martian soil. Students will plant seeds 

of a variety of plants, including soybeans, in simulated Martian soil in hydroponics grow 

pots. The same day they will prepare vials with simulated Martian soil and soybean seeds 

for flight, to see if they will grow when exposed to radiation, temperature extremes and 

microgravity. 

Sprouting Seeds 

Creekside Intermediate School, League City, Texas 

The experiment team will investigate the effect of the space environment on sprouting 

seeds. A passive watering system, to be activated by the launch environment, will also be 

tested. 

Neurospora Cresse on Bread in Space 

Cranston High School, Cranston, R.I. 

The experiment looks at how the space environment affects Neurospora cresse on different 

types of bread. This study could help determine how the space environment affects 

organisms harmful to food. 

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SEM Endeavour Program 

Pennsylvania Middle Schools, Archbald, Pa. 

Experiment participants are from Pennsylvania middle schools that have participated in the 

NASA Endeavour program for the past two years. Adhesives, plant seeds, tree seeds, 

spores, and bacterial samples will be tested to find the effects from spaceflight. 

Space Soy, Generation GappED 

New Oxford Elementary School, Brethren Home Retirement Community, Hanover, 

Pa. 

Students will use the greenhouse at the retirement community and will work with the senior 

citizens on all aspects of the project. The investigation will determine how soy will grow 

after the seeds have been subjected to the space environment on a shuttle flight. 

SEM-15 

SEM-15 will be part of the MACH-1 Hitchhiker Bridge and contain only passive 

experiments. 

Invertabraes in Microgravity 

NORSTAR, Norfolk, Va. 

The experiment will test the effects of microgravity on Edith's Checkerspot Butterflies. 

Butterfly eggs will be sent in a state of diapause, so there are no time limitations. After the 

shuttle flight the butterflies will be observed to see if they can still pollinate flowers, 

reproduce, and perform everyday functions. The Edith's Checkerspot Butterflies were 

chosen because they live in high mountain ranges, as well as coastal regions, and are 

known to be able to withstand both extreme cold and heat. As a secondary project, 

retesting a previous experiment, artemia eggs in diapause also will be flown. 

MEDLAB 

Guardian Lutheran School, Dearborn Heights, Mich. 

The experiment studies the effects on animal tissue in space. By studying animal tissues, 

the students will hopefully gain insight as to the effects of space travel on mankind, as well 

as his traditional food sources. 

Magnetic Stars 

Henry E. Harris School, Bayonne, N.J. 

This experiment investigates how magnets react during space travel. Students will 

construct structures using magnetic star/moon shapes. One structure will be packed for 

launch and the other five will have one variable added to each (suspended upside-down, 

submerged in water, placed into a freezer, placed sideways, etc.). When the structure 

returns from space, all six will be compared and measured to detect any movement in the 

structure. 

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Magnets and the Magnetosphere 

Woodland Middle School, East Meadow, N.Y. 

The purpose of the experiment is to study how the shuttle’s passage through the Earth’s 

magnetic field lines affects magnetic items. Magnets, security strips, nails, lodestone, and 

magnetic marbles are the primary objects under investigation. The experiment is a followup investigation on a previous SEM project. 

Folger McKinsey Space Owls 

Folger McKinsey Elementary, Severna Park, Md. 

Students will study effects of the space environment on a variety of materials. Several 

student teams will share the available volume of the module. Flight materials will include 

balloons, electronic components, magnets, detergents, oils, sponges, rubber bands, and 

various fluids for pH testing. Students will determine how radiation, temperature, and 

microgravity of the space environment affect these materials. 

Aria-4: Space, Man and Biology 

Washington University, St. Louis, Mo. 

The Aria-4 project is a St. Louis education project involving the effects of space on biology. 

The project involves students from the Central Institute for the Deaf and the Good Hope 

School in partnership with Washington University's School of Engineering and Applied 

Science. The project will have 22 experiments and controls. It compares effects of the 

space environment on biological samples such as vegetable seeds, flower seeds, yeast, 

brine shrimp, pond water samples, and human hair samples with the controls. 

Soothing, Minty, and Fresh on ISS 

Broadneck Elementary, Arnold, Md. 

This experiment is an extension of the fourth-grade curriculum Space and Space 

Technology. It looks at how everyday materials are affected by the space environment, and 

if they would be useful on the International Space Station. Experiment materials will 

include dental gum, elastic, cough drops, and air freshener material. 

The Effects of Environmental Conditions on Soil and Water 

Northeastern Pennsylvania GLOBE Project 

The experiment will test the effects of microgravity, radiation, and magnetism on samples of 

soil and water from throughout northeastern Pennsylvania. Characteristics tested will 

include pH, electric conductivity, nitrates, and NPK. These characteristics will then be 

compared to those materials that flew aboard the space shuttle. Consideration will be given 

as to how these effects would enhance the growth of seeds that were nurtured using this 

soil and water. 

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From Anthracite to Space Flight 

Forest City Regional, Hazleton Area, Riverside, Scranton School Districts and 

Northeastern Educational Intermediate Unit 19, Northeastern Pennsylvania 

The experiment lets students measure effects of microgravity, radiation, extreme 

temperature changes, and intense vibration on physical and chemical properties of various 

materials related to anthracite. 

 

Countdown to Wildflowers 

TODTWD 2001, Eastern Shore, Va. 

The purpose of this experiment is to determine the effects of microgravity and space travel 

on wildflower seeds. Students also are keeping a control group on Earth. After the space 

shuttle returns, both sets of seeds will then be planted to compare their germination rates 

and their plants, flowers and seeds. Partner Fulton Elementary School of Howard County, 

Md., will share the module, flying vegetable seeds, flower seeds, brine shrimp, and a yeast 

sample. 

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Experiments 

DSOs and DTOs 

Detailed Supplementary Objectives (DSOs) are space and life sciences investigations. 

Their purpose is to determine the extent of physiological deconditioning resulting from 

spaceflight, to test countermeasures to those changes and to characterize the environment 

of the space shuttle and/or space station relative to crew health. 

Detailed Test Objectives (DTOs) are aimed at testing, evaluating or documenting space 

shuttle systems or hardware, or proposed improvements to space shuttle or space station 

hardware, systems and operations. 

Such experiments aboard Endeavour are: 

DSO 490 

Bioavailability and Performance Effects of Promethazine During Space Flight 

Promethazine (PMZ) is the anti-motion sickness medication of choice for treating space 

motion sickness (SMS) during shuttle missions. Usual side effects include dizziness, 

drowsiness, sedation and impaired psychomotor performance, which could impact crew 

performance of mission operations. Early reports from crewmembers indicate that these 

central nervous system side effects of PMZ are absent or greatly reduced in microgravity. 

DSO 490 will evaluate PMZ’s performance, side effects, and efficacy in microgravity. Tests 

on Endeavour will test responses to various doses and effectiveness of administering it 

using intramuscular, oral and suppository methods of administration. Results will then be 

compared with preflight evaluations. This is the first flight of DSO 490. 

DSO 498 

Space Flight and Immune Function 

Astronauts face an increasing risk of contracting infectious diseases as they work and live 

for longer periods in the crowded conditions and closed environments of spacecraft such as 

the International Space Station. The effect of spaceflight on the human immune system, 

which plays a pivotal role in warding off infections, is not fully understood. Understanding 

the changes in immune functions caused by microgravity will enable researchers to 

develop countermeasures to minimize infection risk. DSO 498 will look at effects of space 

flight on neutrophils, monocytes and cytotoxic cells, which play an important role in 

maintaining an effective defense against infectious agents. Scientists believe space 

changes the way these cells function. Researchers will analyze neutrophils and monocytes 

from astronaut blood samples taken before and after the flight. They will also assess the 

subjects’ pre- and postflight production of cytotoxic cells and cytokine. This study will 

complement previous and continuing immunology studies of astronauts’ adaptation to 

space. 

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DSO 500 

Space Flight-Induced Reactivation of Latent Epstein-Barr Virus 

The effects of microgravity, along with associated physical and psychological stress, 

decrease Epstein-Barr virus (EBV)-specific T-cell immunity and reactivate latent EBV in 

infected B-lymphocytes. DSO 500 will examine the mechanisms of spaceflight-induced 

alterations in human immune function and latent virus reactivation. Specifically, it will 

determine the magnitude of immunosuppression as a result of spaceflight by analyzing 

stress hormones, performing quantitative analysis of EBV replication using molecular and 

serological methods, and determining virus-specific T-cell immune function. This is the first 

flight of DSO 500. 

DSO 503S 

Test of Midodrine as a Countermeasure Against Postflight Orthostatic 

Hypotension 

After spaceflight, astronauts returning to upright posture may experience the inability to 

maintain adequate arterial pressure and cerebral perfusion (orthostatic or postural 

hypotension). This may result in lightheadedness or loss of consciousness during re-entry 

or egress. DSO 503S will evaluate the efficacy of midodrine, a medicine commonly used to 

treat low blood pressure. It works by stimulating nerve endings in blood vessels, causing 

the blood vessels to tighten, which increases blood pressure. The experiment will assess 

midodrine’s effectiveness in reducing the incidence and/or severity of orthostatic 

hypotension in returning astronauts. This is the first flight of DSO 503S. 

DSO 632 

Pharmacokinetics and Contributing Physiologic Changes During Space Flight 

The physical, environmental and physiologic conditions of spaceflight alter gastrointestinal 

(GI) function and physiology. These changes affect the pharmacokinetics of oral 

medications. Previous tests indicated absorption and bioavailability of oral liquid dosages 

may be better and more reliable than that of an equivalent solid dosage form. DSO 632 will 

determine changes in the GI function and physiology in microgravity and continue to 

examine the pharmacokinetics of orally administered acetaminophen. This is the first flight 

of DSO 632. 

DTO 262 

On-Orbit Bicycle Ergometer Loads Measurement 

This DTO studies the possibility of reducing engineering conservatism by measuring the 

joined shuttle/space station natural frequencies, using the bicycle ergometer as the natural 

frequency excitation source. Reduction of conservatism would allow more operational 

flexibility by reducing preflight load predictions and, thus, operational constraints. This is the 

second of seven planned flights of DTO 262. 

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DTO 700-14 

Single-String Global Positioning System 

The purpose of the Single-String Global Positioning System (GPS) is to demonstrate the 

performance and operation of the GPS during orbiter ascent, on-orbit, entry and landing 

phases. It uses a modified military GPS receiver processor and the existing orbiter GPS 

antennas. GPS data may be downlinked during all mission phases. This is the 20th flight of 

DTO 700-14. 

DTO-700-22 

Crew Return Vehicle (CRV) Space Integrated 

Global Positioning System/Inertial Navigation System (SIGI) 

The CRV SIGI is intended to be the primary navigation source for the space station CRV. 

DTO 700-22 will measure Global Positioning System (GPS) only and GPS/Inertial 

Navigation System (INS) blended position, velocity, time, and attitude performance during 

on orbit and re-entry, and will measure the time to first GPS fix (position, velocity, time) 

during on-orbit operations after warm or cold starts of the SIGI. This is the second flight of 

DTO 700-22. 

DTO 805 

Crosswind Landing Performance 

DTO 805 is to demonstrate the capability to perform a manually controlled landing in a 

crosswind. The testing is done in two steps. 1) Prelaunch: Ensure planning will allow 

selection of a runway with Microwave Scanning Beam Landing System support, which is a 

set of dual transmitters located beside the runway providing precision navigation vertically, 

horizontally and longitudinally with respect to the runway. This precision navigation 

subsystem helps provide a higher probability of a more precise landing with a crosswind of 

10 to 15 knots as late in the flight as possible. 2) Entry: This test requires that the crew 

perform a manually controlled landing in a 90-degree crosswind component of 10 to 15 

knots steady state. During a crosswind landing, the drag chute will be deployed after nose 

gear touchdown when the vehicle is stable and tracking the runway centerline. This DTO 

has been on 67 flights. 

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Shuttle Reference Data 

Shuttle Abort History 

RSLS Abort History:

(STS-41 D) June 26, 1984

The countdown for the second launch attempt for Discovery’s maiden flight ended at T4 seconds when the orbiter’s computers detected a sluggish valve in main engine #3. 

The main engine was replaced and Discovery was finally launched on August 30, 1984. 

(STS-51 F) July 12, 1985

The countdown for Challenger’s launch was halted at T-3 seconds when on-board 

computers detected a problem with a coolant valve on main engine #2. The valve was 

replaced and Challenger was launched on July 29, 1985. 

(STS-55) March 22, 1993

The countdown for Columbia’s launch was halted by on-board computers at T-3 

seconds following a problem with purge pressure readings in the oxidizer preburner on 

main engine #2 Columbia’s three main engines were replaced on the launch pad, and 

the flight was rescheduled behind Discovery’s launch on STS-56. Columbia finally 

launched on April 26, 1993. 

(STS-51) August 12, 1993

The countdown for Discovery’s third launch attempt ended at the T-3 second mark 

when on-board computers detected the failure of one of four sensors in main engine #2 

which monitor the flow of hydrogen fuel to the engine. All of Discovery’s main engines 

were ordered replaced on the launch pad, delaying the Shuttle’s fourth launch attempt 

until September 12, 1993. 

(STS-68) August 18, 1994

The countdown for Endeavour’s first launch attempt ended 1.9 seconds before liftoff 

when on-board computers detected higher than acceptable readings in one channel of a 

sensor monitoring the discharge temperature of the high pressure oxidizer turbopump in 

main engine #3. A test firing of the engine at the Stennis Space Center in Mississippi on 

September 2nd confirmed that a slight drift in a fuel flow meter in the engine caused a 

slight increase in the turbopump’s temperature. The test firing also confirmed a slightly 

slower start for main engine #3 during the pad abort, which could have contributed to 

the higher temperatures. After Endeavour was brought back to the Vehicle Assembly 

Building to be outfitted with three replacement engines, NASA managers set October 

2nd as the date for Endeavour’s second launch attempt. 

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Abort to Orbit History:

(STS-51 F) July 29, 1985

After an RSLS abort on July 12, 1985, Challenger was launched on July 29, 1985. Five 

minutes and 45 seconds after launch, a sensor problem resulted in the shutdown of 

center engine #1, resulting in a safe "abort to orbit" and successful completion of the 

mission.

Updated: 05/22/2001 

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Shuttle Reference Data 

Shuttle Abort Modes 

RSLS ABORTS 

These occur when the onboard shuttle computers detect a problem and command a halt in 

the launch sequence after taking over from the Ground Launch Sequencer and before Solid 

Rocket Booster ignition. 

ASCENT ABORTS 

Selection of an ascent abort mode may become necessary if there is a failure that affects 

vehicle performance, such as the failure of a space shuttle main engine or an orbital 

maneuvering system. Other failures requiring early termination of a flight, such as a cabin 

leak, might also require the selection of an abort mode. 

There are two basic types of ascent abort modes for space shuttle missions: intact aborts 

and contingency aborts. Intact aborts are designed to provide a safe return of the orbiter to 

a planned landing site. Contingency aborts are designed to permit flight crew survival 

following more severe failures when an intact abort is not possible. A contingency abort 

would generally result in a ditch operation. 

INTACT ABORTS 

There are four types of intact aborts: abort to orbit (ATO), abort once around (AOA), 

transoceanic abort landing (TAL) and return to launch site (RTLS). 

Return to Launch Site 

The RTLS abort mode is designed to allow the return of the orbiter, crew, and payload to 

the launch site, Kennedy Space Center, approximately 25 minutes after lift-off. 

The RTLS profile is designed to accommodate the loss of thrust from one space shuttle 

main engine between lift-off and approximately four minutes 20 seconds, at which time not 

enough main propulsion system propellant remains to return to the launch site. 

An RTLS can be considered to consist of three stages--a powered stage, during which the 

space shuttle main engines are still thrusting; an ET separation phase; and the glide phase, 

during which the orbiter glides to a landing at the Kennedy Space Center. The powered 

RTLS phase begins with the crew selection of the RTLS abort, which is done after solid 

rocket booster separation. The crew selects the abort mode by positioning the abort rotary 

switch to RTLS and depressing the abort push button. The time at which the RTLS is 

selected depends on the reason for the abort. For example, a three-engine RTLS is 

selected at the last moment, approximately three minutes 34 seconds into the mission; 

whereas an RTLS chosen due to an engine out at lift-off is selected at the earliest time, 

approximately two minutes 20 seconds into the mission (after solid rocket booster 

separation). 

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After RTLS is selected, the vehicle continues downrange to dissipate excess main 

propulsion system propellant. The goal is to leave only enough main propulsion system 

propellant to be able to turn the vehicle around, fly back towards the Kennedy Space 

Center and achieve the proper main engine cutoff conditions so the vehicle can glide to the 

Kennedy Space Center after external tank separation. During the downrange phase, a 

pitch-around maneuver is initiated (the time depends in part on the time of a space shuttle 

main engine failure) to orient the orbiter/external tank configuration to a heads up attitude, 

pointing toward the launch site. At this time, the vehicle is still moving away from the launch 

site, but the space shuttle main engines are now thrusting to null the downrange velocity. In 

addition, excess orbital maneuvering system and reaction control system propellants are 

dumped by continuous orbital maneuvering system and reaction control system engine 

thrustings to improve the orbiter weight and center of gravity for the glide phase and 

landing. 

The vehicle will reach the desired main engine cutoff point with less than 2 percent excess 

propellant remaining in the external tank. At main engine cutoff minus 20 seconds, a pitchdown maneuver (called powered pitch-down) takes the mated vehicle to the required 

external tank separation attitude and pitch rate. After main engine cutoff has been 

commanded, the external tank separation sequence begins, including a reaction control 

system translation that ensures that the orbiter does not recontact the external tank and 

that the orbiter has achieved the necessary pitch attitude to begin the glide phase of the 

RTLS. 

After the reaction control system translation maneuver has been completed, the glide 

phase of the RTLS begins. From then on, the RTLS is handled similarly to a normal entry. 

Transoceanic Abort Landing 

The TAL abort mode was developed to improve the options available when a space shuttle 

main engine fails after the last RTLS opportunity but before the first time that an AOA can 

be accomplished with only two space shuttle main engines or when a major orbiter system 

failure, for example, a large cabin pressure leak or cooling system failure, occurs after the 

last RTLS opportunity, making it imperative to land as quickly as possible. 

In a TAL abort, the vehicle continues on a ballistic trajectory across the Atlantic Ocean to 

land at a predetermined runway. Landing occurs approximately 45 minutes after launch. 

The landing site is selected near the nominal ascent ground track of the orbiter in order to 

make the most efficient use of space shuttle main engine propellant. The landing site also 

must have the necessary runway length, weather conditions and U.S. State Department 

approval. Currently, the three landing sites that have been identified for a due east launch 

are Moron, Spain; Dakar, Senegal; and Ben Guerur, Morocco (on the west coast of Africa). 

To select the TAL abort mode, the crew must place the abort rotary switch in the TAL/AOA 

position and depress the abort push button before main engine cutoff. (Depressing it after 

main engine cutoff selects the AOA abort mode.) The TAL abort mode begins sending 

commands to steer the vehicle toward the plane of the landing site. It also rolls the vehicle 

heads up before main engine cutoff and sends commands to begin an orbital maneuvering 

system propellant dump (by burning the propellants through the orbital maneuvering 

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system engines and the reaction control system engines). This dump is necessary to 

increase vehicle performance (by decreasing weight), to place the center of gravity in the 

proper place for vehicle control, and to decrease the vehicle's landing weight. 

TAL is handled like a nominal entry. 

Abort to Orbit 

An ATO is an abort mode used to boost the orbiter to a safe orbital altitude when 

performance has been lost and it is impossible to reach the planned orbital altitude. If a 

space shuttle main engine fails in a region that results in a main engine cutoff under speed, 

the Mission Control Center will determine that an abort mode is necessary and will inform 

the crew. The orbital maneuvering system engines would be used to place the orbiter in a 

circular orbit. 

Abort Once Around 

The AOA abort mode is used in cases in which vehicle performance has been lost to such 

an extent that either it is impossible to achieve a viable orbit or not enough orbital 

maneuvering system propellant is available to accomplish the orbital maneuvering system 

thrusting maneuver to place the orbiter on orbit and the deorbit thrusting maneuver. In 

addition, an AOA is used in cases in which a major systems problem (cabin leak, loss of 

cooling) makes it necessary to land quickly. In the AOA abort mode, one orbital 

maneuvering system thrusting sequence is made to adjust the post-main engine cutoff orbit 

so a second orbital maneuvering system thrusting sequence will result in the vehicle 

deorbiting and landing at the AOA landing site (White Sands, N.M.; Edwards Air Force 

Base; or the Kennedy Space Center). Thus, an AOA results in the orbiter circling the Earth 

once and landing approximately 90 minutes after lift-off. 

After the deorbit thrusting sequence has been executed, the flight crew flies to a landing at 

the planned site much as it would for a nominal entry. 

CONTINGENCY ABORTS 

Contingency aborts are caused by loss of more than one main engine or failures in other 

systems. Loss of one main engine while another is stuck at a low thrust setting may also 

necessitate a contingency abort. Such an abort would maintain orbiter integrity for in-flight 

crew escape if a landing cannot be achieved at a suitable landing field. 

Contingency aborts due to system failures other than those involving the main engines 

would normally result in an intact recovery of vehicle and crew. Loss of more than one main 

engine may, depending on engine failure times, result in a safe runway landing. However, 

in most three-engine-out cases during ascent, the orbiter would have to be ditched. The inflight crew escape system would be used before ditching the orbiter. 

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ABORT DECISIONS 

There is a definite order of preference for the various abort modes. The type of failure and 

the time of the failure determine which type of abort is selected. In cases where 

performance loss is the only factor, the preferred modes would be ATO, AOA, TAL and 

RTLS, in that order. The mode chosen is the highest one that can be completed with the 

remaining vehicle performance. 

In the case of some support system failures, such as cabin leaks or vehicle cooling 

problems, the preferred mode might be the one that will end the mission most quickly. In 

these cases, TAL or RTLS might be preferable to AOA or ATO. A contingency abort is 

never chosen if another abort option exists. 

The Mission Control Center-Houston is prime for calling these aborts because it has a more 

precise knowledge of the orbiter's position than the crew can obtain from onboard systems. 

Before main engine cutoff, Mission Control makes periodic calls to the crew to tell them 

which abort mode is (or is not) available. If ground communications are lost, the flight crew 

has onboard methods, such as cue cards, dedicated displays and display information, to 

determine the current abort region. 

Which abort mode is selected depends on the cause and timing of the failure causing the 

abort and which mode is safest or improves mission success. If the problem is a space 

shuttle main engine failure, the flight crew and Mission Control Center select the best 

option available at the time a space shuttle main engine fails. 

If the problem is a system failure that jeopardizes the vehicle, the fastest abort mode that 

results in the earliest vehicle landing is chosen. RTLS and TAL are the quickest options (35 

minutes), whereas an AOA requires approximately 90 minutes. Which of these is selected 

depends on the time of the failure with three good space shuttle main engines. 

The flight crew selects the abort mode by positioning an abort mode switch and depressing 

an abort push button. 

Updated: 05/22/2001 

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Shuttle Reference Data 

Space Shuttle Rendezvous Maneuvers 

COMMON SHUTTLE RENDEZVOUS MANEUVERS

OMS-1 (Orbit insertion) - Rarely used ascent abort burn 

OMS-2 (Orbit insertion) - Typically used to circularize the initial orbit following ascent, 

completing orbital insertion. For ground-up rendezvous flights, also considered a 

rendezvous phasing burn 

NC (Rendezvous phasing) - Performed to hit a range relative to the target at a future 

time 

NH (Rendezvous height adjust) - Performed to hit a delta-height relative to the target 

at a future time 

NPC (Rendezvous plane change) - Performed to remove planar errors relative to the 

target at a future time 

NCC (Rendezvous corrective combination) - First on-board targeted burn in the 

rendezvous sequence. Using star tracker data, it is performed to remove phasing and 

height errors relative to the target at Ti 

Ti (Rendezvous terminal intercept) - Second on-board targeted burn in the 

rendezvous sequence. Using primarily rendezvous radar data, it places the Orbiter on a 

trajectory to intercept the target in one orbit 

MC-1, MC-2, MC-3, MC-4 (Rendezvous midcourse burns) - These on-board targeted 

burns use star tracker and rendezvous radar data to correct the post-Ti trajectory in 

preparation for the final, manual proximity operations phase 

Updated: 05/22/2001 

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Shuttle Reference Data 

Space Shuttle Solid Rocket Boosters 

The two SRBs provide the main thrust to lift the space shuttle off the pad and up to an 

altitude of about 150,000 feet, or 24 nautical miles (28 statute miles). In addition, the two 

SRBs carry the entire weight of the external tank and orbiter and transmit the weight load 

through their structure to the mobile launcher platform. 

Each booster has a thrust (sea level) of approximately 3,300,000 pounds at launch. They 

are ignited after the three space shuttle main engines' thrust level is verified. The two SRBs 

provide 71.4 percent of the thrust at lift- off and during first-stage ascent. Seventy- five 

seconds after SRB separation, SRB apogee occurs at an altitude of approximately 220,000 

feet, or 35 nautical miles (40 statute miles). SRB impact occurs in the ocean approximately 

122 nautical miles (140 statute miles) downrange. 

The SRBs are the largest solid-propellant motors ever flown and the first designed for 

reuse. Each is 149.16 feet long and 12.17 feet in diameter. 

Each SRB weighs approximately 1,300,000 pounds at launch. The propellant for each solid 

rocket motor weighs approximately 1,100,000 pounds. The inert weight of each SRB is 

approximately 192,000 pounds. 

Primary elements of each booster are the motor (including case, propellant, igniter and 

nozzle), structure, separation systems, operational flight instrumentation, recovery avionics, 

pyrotechnics, deceleration system, thrust vector control system and range safety destruct 

system. 

Each booster is attached to the external tank at the SRB’s aft frame by two lateral sway 

braces and a diagonal attachment. The forward end of each SRB is attached to the 

external tank at the forward end of the SRB’s forward skirt. On the launch pad, each 

booster also is attached to the mobile launcher platform at the aft skirt by four bolts and 

nuts that are severed by small explosives at lift-off. 

During the downtime following the Challenger accident, detailed structural analyses were 

performed on critical structural elements of the SRB. Analyses were primarily focused in 

areas where anomalies had been noted during postflight inspection of recovered hardware. 

One of the areas was the attach ring where the SRBs are connected to the external tank. 

Areas of distress were noted in some of the fasteners where the ring attaches to the SRB 

motor case. This situation was attributed to the high loads encountered during water 

impact. To correct the situation and ensure higher strength margins during ascent, the 

attach ring was redesigned to encircle the motor case completely (360 degrees). 

Previously, the attach ring formed a C and encircled the motor case 270 degrees. 

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Additionally, special structural tests were performed on the aft skirt. During this test 

program, an anomaly occurred in a critical weld between the hold-down post and skin of 

the skirt. A redesign was implemented to add reinforcement brackets and fittings in the aft 

ring of the skirt. 

These two modifications added approximately 450 pounds to the weight of each SRB. 

The propellant mixture in each SRB motor consists of an ammonium perchlorate (oxidizer, 

69.6 percent by weight), aluminum (fuel, 16 percent), iron oxide (a catalyst, 0.4 percent), a 

polymer (a binder that holds the mixture together, 12.04 percent), and an epoxy curing 

agent (1.96 percent). The propellant is an 11-point star-shaped perforation in the forward 

motor segment and a double-truncated-cone perforation in each of the aft segments and aft 

closure. This configuration provides high thrust at ignition and then reduces the thrust by 

approximately a third 50 seconds after lift-off to prevent overstressing the vehicle during 

maximum dynamic pressure. 

The SRBs are used as matched pairs and each is made up of four solid rocket motor 

segments. The pairs are matched by loading each of the four motor segments in pairs from 

the same batches of propellant ingredients to minimize any thrust imbalance. The 

segmented-casing design assures maximum flexibility in fabrication and ease of 

transportation and handling. Each segment is shipped to the launch site on a heavy-duty 

rail car with a specially built cover. 

The nozzle expansion ratio of each booster beginning with the STS-8 mission is 7-to-79. 

The nozzle is gimbaled for thrust vector (direction) control. Each SRB has its own 

redundant auxiliary power units and hydraulic pumps. The all-axis gimbaling capability is 8 

degrees. Each nozzle has a carbon cloth liner that erodes and chars during firing. The 

nozzle is a convergent-divergent, movable design in which an aft pivot-point flexible 

bearing is the gimbal mechanism. 

The cone- shaped aft skirt reacts the aft loads between the SRB and the mobile launcher 

platform. The four aft separation motors are mounted on the skirt. The aft section contains 

avionics, a thrust vector control system that consists of two auxiliary power units and 

hydraulic pumps, hydraulic systems and a nozzle extension jettison system. 

The forward section of each booster contains avionics, a sequencer, forward separation 

motors, a nose cone separation system, drogue and main parachutes, a recovery beacon, 

a recovery light, a parachute camera on selected flights and a range safety system. 

Each SRB has two integrated electronic assemblies, one forward and one aft. After 

burnout, the forward assembly initiates the release of the nose cap and frustum and turns 

on the recovery aids. The aft assembly, mounted in the external tank/SRB attach ring, 

connects with the forward assembly and the orbiter avionics systems for SRB ignition 

commands and nozzle thrust vector control. Each integrated electronic assembly has a 

multiplexer/ demultiplexer, which sends or receives more than one message, signal or unit 

of information on a single communication channel. 

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Eight booster separation motors (four in the nose frustum and four in the aft skirt) of each 

SRB thrust for 1.02 seconds at SRB separation from the external tank. Each solid rocket 

separation motor is 31.1 inches long and 12.8 inches in diameter. 

Location aids are provided for each SRB, frustum/drogue chutes and main parachutes. 

These include a transmitter, antenna, strobe/converter, battery and salt water switch 

electronics. The location aids are designed for a minimum operating life of 72 hours and 

when refurbished are considered usable up to 20 times. The flashing light is an exception. 

It has an operating life of 280 hours. The battery is used only once. 

The SRB nose caps and nozzle extensions are not recovered. 

The recovery crew retrieves the SRBs, frustum/drogue chutes, and main parachutes. The 

nozzles are plugged, the solid rocket motors are dewatered, and the SRBs are towed back 

to the launch site. Each booster is removed from the water, and its components are 

disassembled and washed with fresh and deionized water to limit salt water corrosion. The 

motor segments, igniter and nozzle are shipped back to Thiokol for refurbishment. 

Each SRB incorporates a range safety system that includes a battery power source, 

receiver/ decoder, antennas and ordnance. 

HOLD-DOWN POSTS 

Each solid rocket booster has four hold-down posts that fit into corresponding support posts 

on the mobile launcher platform. Hold-down bolts hold the SRB and launcher platform 

posts together. Each bolt has a nut at each end, but only the top nut is frangible. The top 

nut contains two NASA standard detonators, which are ignited at solid rocket motor ignition 

commands. 

When the two NSDs are ignited at each hold-down, the hold-down bolt travels downward 

because of the release of tension in the bolt (pretensioned before launch), NSD gas 

pressure and gravity. The bolt is stopped by the stud deceleration stand, which contains 

sand. The SRB bolt is 28 inches long and is 3.5 inches in diameter. The frangible nut is 

captured in a blast container. 

The solid rocket motor ignition commands are issued by the orbiter''s computers through 

the master events controllers to the hold-down pyrotechnic initiator controllers on the 

mobile launcher platform. They provide the ignition to the hold-down NSDs. The launch 

processing system monitors the SRB hold-down PICs for low voltage during the last 16 

seconds before launch. PIC low voltage will initiate a launch hold. 

SRB IGNITION 

SRB ignition can occur only when a manual lock pin from each SRB safe and arm device 

has been removed. The ground crew removes the pin during prelaunch activities. At T 

minus five minutes, the SRB safe and arm device is rotated to the arm position. The solid 

rocket motor ignition commands are issued when the three SSMEs are at or above 90-

percent rated thrust, no SSME fail and/or SRB ignition PIC low voltage is indicated and 

there are no holds from the LPS. 

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The solid rocket motor ignition commands are sent by the orbiter computers through the 

MECs to the safe and arm device NSDs in each SRB. A PIC single-channel capacitor 

discharge device controls the firing of each pyrotechnic device. Three signals must be 

present simultaneously for the PIC to generate the pyro firing output. These signals--arm, 

fire 1 and fire 2--originate in the orbiter general-purpose computers and are transmitted to 

the MECs. The MECs reformat them to 28-volt dc signals for the PICs. The arm signal 

charges the PIC capacitor to 40 volts dc (minimum of 20 volts dc). 

The fire 2 commands cause the redundant NSDs to fire through a thin barrier seal down a 

flame tunnel. This ignites a pyro booster charge, which is retained in the safe and arm device 

behind a perforated plate. The booster charge ignites the propellant in the igniter initiator; 

and combustion products of this propellant ignite the solid rocket motor initiator, which fires 

down the length of the solid rocket motor igniting the solid rocket motor propellant. 

The GPC launch sequence also controls certain critical main propulsion system valves and 

monitors the engine-ready indications from the SSMEs. The MPS start commands are 

issued by the onboard computers at T minus 6.6 seconds (staggered start--engine three, 

engine two, engine one--all approximately within 0.25 of a second), and the sequence 

monitors the thrust buildup of each engine. All three SSMEs must reach the required 90-

percent thrust within three seconds; otherwise, an orderly shutdown is commanded and 

safing functions are initiated. 

Normal thrust buildup to the required 90-percent thrust level will result in the SSMEs being 

commanded to the lift-off position at T minus three seconds as well as the fire 1 command 

being issued to arm the SRBs. At T minus three seconds, the vehicle base bending load 

modes are allowed to initialize (movement of approximately 25.5 inches measured at the tip 

of the external tank, with movement towards the external tank). 

At T minus zero, the two SRBs are ignited, under command of the four onboard computers; 

separation of the four explosive bolts on each SRB is initiated (each bolt is 28 inches long 

and 3.5 inches in diameter); the two T-0 umbilicals (one on each side of the spacecraft) are 

retracted; the onboard master timing unit, event timer and mission event timers are started; 

the three SSMEs are at 100 percent; and the ground launch sequence is terminated. 

The solid rocket motor thrust profile is tailored to reduce thrust during the maximum 

dynamic pressure region. 

ELECTRICAL POWER DISTRIBUTION 

Electrical power distribution in each SRB consists of orbiter-supplied main dc bus power to 

each SRB via SRB buses A, B and C. Orbiter main dc buses A, B and C supply main dc 

bus power to corresponding SRB buses A, B and C. In addition, orbiter main dc bus C 

supplies backup power to SRB buses A and B, and orbiter bus B supplies backup power to 

SRB bus C. This electrical power distribution arrangement allows all SRB buses to remain 

powered in the event one orbiter main bus fails. 

The nominal dc voltage is 28 volts dc, with an upper limit of 32 volts dc and a lower limit of 

24 volts dc. 

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HYDRAULIC POWER UNITS 

There are two self-contained, independent HPUs on each SRB. Each HPU consists of an 

auxiliary power unit, fuel supply module, hydraulic pump, hydraulic reservoir and hydraulic 

fluid manifold assembly. The APUs are fueled by hydrazine and generate mechanical shaft 

power to a hydraulic pump that produces hydraulic pressure for the SRB hydraulic system. 

The two separate HPUs and two hydraulic systems are located on the aft end of each SRB 

between the SRB nozzle and aft skirt. The HPU components are mounted on the aft skirt 

between the rock and tilt actuators. The two systems operate from T minus 28 seconds 

until SRB separation from the orbiter and external tank. The two independent hydraulic 

systems are connected to the rock and tilt servoactuators. 

The APU controller electronics are located in the SRB aft integrated electronic assemblies 

on the aft external tank attach rings. 

The APUs and their fuel systems are isolated from each other. Each fuel supply module 

(tank) contains 22 pounds of hydrazine. The fuel tank is pressurized with gaseous nitrogen 

at 400 psi, which provides the force to expel (positive expulsion) the fuel from the tank to 

the fuel distribution line, maintaining a positive fuel supply to the APU throughout its 

operation. 

The fuel isolation valve is opened at APU startup to allow fuel to flow to the APU fuel pump 

and control valves and then to the gas generator. The gas generator's catalytic action 

decomposes the fuel and creates a hot gas. It feeds the hot gas exhaust product to the 

APU two-stage gas turbine. Fuel flows primarily through the startup bypass line until the 

APU speed is such that the fuel pump outlet pressure is greater than the bypass line's. 

Then all the fuel is supplied to the fuel pump. 

The APU turbine assembly provides mechanical power to the APU gearbox. The gearbox 

drives the APU fuel pump, hydraulic pump and lube oil pump. The APU lube oil pump 

lubricates the gearbox. The turbine exhaust of each APU flows over the exterior of the gas 

generator, cooling it, and is then directed overboard through an exhaust duct. 

When the APU speed reaches 100 percent, the APU primary control valve closes, and the 

APU speed is controlled by the APU controller electronics. If the primary control valve logic 

fails to the open state, the secondary control valve assumes control of the APU at 112-

percent speed. 

Each HPU on an SRB is connected to both servoactuators on that SRB. One HPU serves 

as the primary hydraulic source for the servoactuator, and the other HPU serves as the 

secondary hydraulics for the servoactuator. Each sevoactuator has a switching valve that 

allows the secondary hydraulics to power the actuator if the primary hydraulic pressure 

drops below 2,050 psi. A switch contact on the switching valve will close when the valve is 

in the secondary position. When the valve is closed, a signal is sent to the APU controller 

that inhibits the 100-percent APU speed control logic and enables the 112-percent APU 

speed control logic. The 100-percent APU speed enables one APU/HPU to supply 

sufficient operating hydraulic pressure to both servoactuators of that SRB. 

56
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The APU 100-percent speed corresponds to 72,000 rpm, 110-percent to 79,200 rpm, and 

112-percent to 80,640 rpm. 

The hydraulic pump speed is 3,600 rpm and supplies hydraulic pressure of 3,050, plus or 

minus 50, psi. A high-pressure relief valve provides overpressure protection to the hydraulic 

system and relieves at 3,750 psi. 

The APUs/HPUs and hydraulic systems are reusable for 20 missions. 

THRUST VECTOR CONTROL 

Each SRB has two hydraulic gimbal servoactuators: one for rock and one for tilt. The 

servoactuators provide the force and control to gimbal the nozzle for thrust vector control. 

The space shuttle ascent thrust vector control portion of the flight control system directs the 

thrust of the three shuttle main engines and the two SRB nozzles to control shuttle attitude 

and trajectory during lift-off and ascent. Commands from the guidance system are 

transmitted to the ATVC drivers, which transmit signals proportional to the commands to 

each servoactuator of the main engines and SRBs. Four independent flight control system 

channels and four ATVC channels control six main engine and four SRB ATVC drivers, 

with each driver controlling one hydraulic port on each main and SRB servoactuator. 

Each SRB servoactuator consists of four independent, two-stage servovalves that receive 

signals from the drivers. Each servovalve controls one power spool in each actuator, which 

positions an actuator ram and the nozzle to control the direction of thrust. 

The four servovalves in each actuator provide a force-summed majority voting arrangement 

to position the power spool. With four identical commands to the four servovalves, the 

actuator force-sum action prevents a single erroneous command from affecting power ram 

motion. If the erroneous command persists for more than a predetermined time, differential 

pressure sensing activates a selector valve to isolate and remove the defective servovalve 

hydraulic pressure, permitting the remaining channels and servovalves to control the 

actuator ram spool. 

Failure monitors are provided for each channel to indicate which channel has been 

bypassed. An isolation valve on each channel provides the capability of resetting a failed or 

bypassed channel. 

Each actuator ram is equipped with transducers for position feedback to the thrust vector 

control system. Within each servoactuator ram is a splashdown load relief assembly to 

cushion the nozzle at water splashdown and prevent damage to the nozzle flexible bearing. 

SRB RATE GYRO ASSEMBLIES 

Each SRB contains two RGAs, with each RGA containing one pitch and one yaw gyro. 

These provide an output proportional to angular rates about the pitch and yaw axes to the 

orbiter computers and guidance, navigation and control system during first-stage ascent 

flight in conjunction with the orbiter roll rate gyros until SRB separation. At SRB separation, 

a switchover is made from the SRB RGAs to the orbiter RGAs. 

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The SRB RGA rates pass through the orbiter flight aft multiplexers/ demultiplexers to the 

orbiter GPCs. The RGA rates are then mid-value- selected in redundancy management to 

provide SRB pitch and yaw rates to the user software. The RGAs are designed for 20 

missions. 

SRB SEPARATION 

SRB separation is initiated when the three solid rocket motor chamber pressure 

transducers are processed in the redundancy management middle value select and the 

head-end chamber pressure of both SRBs is less than or equal to 50 psi. A backup cue is 

the time elapsed from booster ignition. 

The separation sequence is initiated, commanding the thrust vector control actuators to the 

null position and putting the main propulsion system into a second-stage configuration (0.8 

second from sequence initialization), which ensures the thrust of each SRB is less than 

100,000 pounds. Orbiter yaw attitude is held for four seconds, and SRB thrust drops to less 

than 60,000 pounds. 

The SRBs separate from the external tank within 30 milliseconds of the ordnance firing 

command. 

The forward attachment point consists of a ball (SRB) and socket (ET) held together by one 

bolt. The bolt contains one NSD pressure cartridge at each end. The forward attachment 

point also carries the range safety system cross-strap wiring connecting each SRB RSS 

and the ET RSS with each other. 

The aft attachment points consist of three separate struts: upper, diagonal and lower. Each 

strut contains one bolt with an NSD pressure cartridge at each end. The upper strut also 

carries the umbilical interface between its SRB and the external tank and on to the orbiter. 

There are four booster separation motors on each end of each SRB. The BSMs separate 

the SRBs from the external tank. The solid rocket motors in each cluster of four are ignited 

by firing redundant NSD pressure cartridges into redundant confined detonating fuse 

manifolds. 

The separation commands issued from the orbiter by the SRB separation sequence initiate 

the redundant NSD pressure cartridge in each bolt and ignite the BSMs to effect a clean 

separation. 

Updated: 05/22/2001

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Shuttle Reference Data 

Space Shuttle Super Light Weight Tank (SLWT) 

The super lightweight external tank (SLWT) made its first shuttle flight June 2, 1998, on 

mission STS-91. The SLWT is 7,500 pounds lighter than the standard external tank. The 

lighter weight tank will allow the shuttle to deliver International Space Station elements 

(such as the service module) into the proper orbit. 

The SLWT is the same size as the previous design. But the liquid hydrogen tank and the 

liquid oxygen tank are made of aluminum lithium, a lighter, stronger material than the metal 

alloy used for the shuttle's current tank. The tank's structural design has also been 

improved, making it 30% stronger and 5% less dense. 

The SLWT, like the standard tank, is manufactured at Michoud Assembly, near New 

Orleans, Louisiana, by Lockheed Martin. 

The 154-foot-long external tank is the largest single component of the space shuttle. It 

stands taller than a 15-story building and has a diameter of about 27 feet. The external tank 

holds over 530,000 gallons of liquid hydrogen and liquid oxygen in two separate tanks. The 

hydrogen (fuel) and liquid oxygen (oxidizer) are used as propellants for the shuttle's three 

main engines. 

Updated: 05/22/2001

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ACRONYMS AND ABBREVIATIONS 

A/L Airlock 

AA Antenna Assembly 

ACBM Active Common Berthing Mechanism 

ACH Assembly Console Handbook 

ACS Attitude Control System 

ACSM Attitude Control System Moding 

ACU Arm Computer Unit 

AEA Antenna Electronics Assembly 

AFD Aft Flight Deck 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Attachment System 

APCU Assembly Power Converter Unit 

APDS Androgynous Peripheral Docking System 

APFR Articulating Portable Foot Restraint 

APPCM Arm Pitch Plane Change Mode 

APS Automated Payload Switch 

ASCR Assured Safe Crew Return 

ATA Ammonia Tank Assembly 

ATCS Active Thermal Control System 

ATU Audio Thermal Unit 

AVU Artificial Vision Unit 

BC Bus Controller 

BCDU Battery Charge/Discharge Unit 

BCU Bus Controller Unit 

BDU Backup Drive Unit 

BGA Beta Gimbal Assembly 

BIT Built-In Test 

BITE Built-In Test Equipment 

BMRRM Bearing Motor Roll Ring Module 

C&C Command and Control 

C&DH Command and Data Handling 

C&M Control and Monitor 

C&W Caution and Warning 

C/A-code Coarse/Acquisition-code 

C/L Crew Lock 

CA Control Attitude 

CAM Centrifuge Accommodations Module 

CAS Common Attach Assembly 

CBC Common Booster Core 

CBM Common Berthing Mechanism 

CCAA Common Cabin Air Assembly 

CCD Cursor Control Device 

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CCTV Closed-Circuit Television 

CDS Command and Data Software 

CETA Crew and Equipment Translation Aid 

CEU Control Electronics Unit 

CheCS Crew Health Care System 

CID Circuit Interrupt Device 

CIOB Cargo Integration and Operations Branch 

CIR Cargo Integration Review 

CMB Common Berthing Mechanism 

CMG Control Moment Gyro 

COTS Commercial-Off-the-Shelf 

CO2 Carbon Dioxide (di-molecular) 

CRV Crew Return Vehicle 

CSA Computer Systems Architecture 

CSC Computer Software Component 

CVT Current Value Table 

DC Direct Current 

Docking Compartment 

DCP Display and Control Panel 

DCSU Direct Current Switching Unit 

DDCU DC-to-DC Converter Unit 

DMCU Docking Mechanism Control Unit 

DMS-R Data Management System-Russian 

DOF Degrees of Freedom 

DPA Digital Pre-Assembly 

DPS Data Processing System 

DSM Docking and Stowage Module 

E/D Electrodynamics 

E/L Equipment Lock 

EACP Extravehicular Audio Control Panel 

EAIU EMU Audio Interface Unit 

EAS Early Ammonia Servicer 

EATCS External Active Thermal Control System 

ECLSS Environmental Control and Life Support System 

ECU Electronics Control Unit 

EDDA EMU Don/Doff Assembly 

EEATCS Early External Active Thermal Control System 

EETCS Early External Thermal Control System 

EF Exposed Facility 

EFGF Electrical Flight Grapple Fixture 

ELM Experimental Logistics Module 

EMU External Maneuvering Unit 

EPS Electrical Power System 

ERA Electrical Replaceable Assembly 

ES Escape System 

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ESP External Stowage Platform 

ESSMDM Enhanced Space Station Multiplexer/Demultiplexer 

E-stop Emergency Stop 

ETCS External Thermal Control System 

ETI Elapsed Time Indicator 

ETSD EVA Tool Storage Device 

EV Extravehicular 

EVA Extravehicular Activity 

EVCPDS Extravehicular Charged Particle Detection System 

EVR Extravehicular Robotics 

EVSWS Extravehicular Support Work Station 

EXPRESS Expediting the Process of Experiments to the Space Station 

EXT Experimental Terminal 

FCC Flat Collector Circuit 

FCV Flow Control Valve 

FD Flight Day 

FDIR Failure, Detection, Isolation, and Recovery 

FGB Functional Cargo Block 

FPU Fluid Pumping Unit 

FRGF Flight Releasable Grapple Fixture 

FSEGF Flight Support Equipment Grapple Fixture 

GFE Government Furnished Equipment 

GLONASS Russian Global Navigation Satellite System 

GNC Guidance, Navigation, and Control 

GPC General Purpose Computer 

GPS Global Positioning System 

GUI Graphical User Interface 

HC Hand Controller 

HP Heat Pipe 

I/O Input/Output 

IAS Internal Audio System 

ICC Integrated Cargo Carrier 

ICS Intersatellite Communication System 

IDA Integrated Diode Assembly 

IEA Integrated Equipment Apparatus 

IFHX Interface Heat Exchanger 

IFM In-Flight Maintenance 

IMCA Integrated Motor Controller Assembly 

IMCS Integrated Mission Control System 

INCO Instrumentation and Communications Officer 

INS Inertial Navigation System 

IOCU Input/Output Controller Unit 

IP International Partner 

IRU In-Flight Refill Unit 

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ISPR International Standard Payload Rack 

ISS International Space Station 

ISSSH International Space Station Handbook 

ITCS Internal Thermal Control System 

ITS Integrated Truss Segment 

IV Intravehicular 

IVA Intravehicular Activity 

IVCPDS Intravehicular Charged Particle Detection System 

JEM Japanese Experiment Module 

JEU Joint Electronic Unit 

KBAR Knee-Brace Assembly Replacement 

km Kilometer 

LA Lab Assembly 

Lab US Laboratory Module 

LAN Local Area Network 

LB Local Bus 

LCA Lab Cradle Assembly 

 Loop Crossover Assembly 

LCD Liquid Crystal Display 

LDA Launch Deployment Assembly 

LDU Linear Drive Unit 

LED Light Emitting Diode 

LEE Latching End Effector 

LFDP Load Fault Detect/Protect 

LLA Low-Level Analog 

LTL Low Temperature Loop 

LVLH Local Vertical/Local Horizontal 

m Meter 

MA Mechanical Assembly 

MAM Manual Augmented Mode 

MBM Manual Berthing Mechanism 

MBS Mobile Base System 

 Mobile Remote Servicer Base System 

MBSU Main Bus Switching Unit 

MCC Mission Control Center 

MCC-H Mission Control Center-Houston 

MCC-M Mission Control Center-Moscow 

MCDS Multifunction Cathode Ray Tube Display System 

MCS Motion Control System 

MDM Multiplexer/Demultiplexer 

MELF Metal Electrical Face 

METOX Metal Oxide 

MFCV Manual Flow Control Valve 

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MILA Moding Indicator Light Assembly 

MLI Multilayer Insulation 

Mm Millimeter 

MM/OD Micrometeoroid/Orbital Debris 

MOD Mission Operations Directorate 

MPLM Multipurpose Logistics Module 

MPM/MRL Manipulator Positioning Mechanism/Manipulator Retention Latch 

ms millisecond 

MSD Mass Storage Device 

MSFC Marshall Space Flight Center 

MSS Mobile Servicing System 

MT Mobile Transporter 

MTL Moderate Temperature Loop 

MTS Mobile Tracking Station 

 Module-to-Truss Structure 

MTSAS Module-to-Truss Segment Attach System 

N2 Nitrogen (di-molecular) 

NASA National Aeronautics and Space Administration 

NTA Nitrogen Tank Assembly 

O2 Oxygen (di-molecular) 

OCA Orbital Communications Adapter 

OCAD Operational Control Agreement Document 

OCJM Operator Commanded Joint Position Mode 

OCPM Operator Commanded Point of Reference Mode 

OCS Operations and Control Software 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

OPP Orbiter Space Vision System Patch Panel 

OPS Operations 

ORU Orbital Replacement Unit 

OSE Orbital Support Equipment 

OSO Operation Support Officer 

OSVS Orbiter Space Vision System 

OSVU Orbiter Space Vision Unit 

OTD Orbital Replacement Unit Transfer Device 

P&S Pointing and Support 

P/L Payload 

PB Power Bus 

PC Personal Computer 

PCMCIA Personal Computer Memory Card International Adapter 

PCN Page Change Notice 

P-Code Precision Code 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

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PDGF Power and Data Grapple Fixture 

PDI Payload Data Interface 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PEHG Payload Ethernet Hub Gateway 

PFCS Pump and Flow Control Subassembly 

PGSC Payload General Support Computer 

PGT Pistol Grip Tool 

PIHPC Permanent International Human Presence Capability 

PJAM Prestored Joint Position Autosequence Mode 

PL Payload 

PLB Payload Bay 

PMA Pressurized Mating Adapter 

PMCU Power Management Controller Unit 

POR Point of Reference 

 Point of Resolution 

POST Power On Self-Test 

PPA Pump Package Assembly 

PPAM Pre-Stored Point of Reference Autosequence Mode 

PRLA Payload Retention Latch Assembly 

PS Power Supply 

PSP Payload Signal Processor 

PSRP Payload Safety Review Panel 

PTCS Passive Thermal Control System 

PTU Pan/Tilt Unit 

PV Photovoltaic 

PVCU Photovoltaic Control Unit 

PVM Photovoltaic Module 

PVRGF Photovoltaic Radiator Grapple Fixture 

PWP Portable Work Platform 

R&R Remove and Replace 

R/P Receiver/Processor 

RAM Random Access Memory 

RBI Remote Bus Isolation 

RF Radio Frequency 

RFCA Rack Flow Control Assembly 

RGA Rate Gyro Assembly 

RHC Rotational Hand Controller 

RHX Regenerative Heat Exchanger 

RJAM Prestored Joint Position Autosequence Mode 

RM Research Module 

RMS Remote Manipulator System 

ROS Russian On-Orbit Segment 

RPC Remote Power Controller 

RPCM Remote Power Control Module 

RPDA Remote Power Distribution Assembly 

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RS Russian Segment 

RSP Resupply Stowage Platform 

RSR Resupply Stowage Rack 

RT Remote Terminal 

RU Rigid Umbilical 

RWS Robotic Workstation 

S0 Starboard Zero 

SA Solar Array 

SAW Solar Array Wing 

SCA Switchgear Controller Assembly 

SCU Service and Cooling Umbilical 

 Signal Conditioning Unit 

SDMS Structural Dynamics Measurement System 

SFA Sunfinder Assembly 

SFCA System Flow Control Assembly 

SHOSS SpaceHab Oceaneering Space System 

SIGI Space Integrated Global Positioning System/Inertial Navigation System 

SJRM Single Joint Rate Mode 

SLP Spacelab Pallet 

SM Service Module 

SMCC Shuttle Mission Control Center 

SMTC Service Module Terminal Computer 

SOC State of Charge 

SPCE Servicing Performance and Checkout Equipment 

SPD Serial Parallel Digital 

SPDA Secondary Power Distribution Assembly 

SPDC Secondary Power Distribution Control 

SPDM Special Purpose Dexterous Manipulator 

SPP Science Power Platform 

SRMS Shuttle Remote Manipulator System 

SSAS Segment-to-Segment Attachment System 

SSC Station Support Computer 

 Subsystem Computer 

SSMDM Space Station Multiplexer/Demultiplexer 

SSOR Space-to-Space Orbiter Radio 

SSP Space Shuttle Program 

 Standard Switch Panel 

SSRMS Space Station Remote Manipulator System 

SSSR Space-to-Space Station Radio 

SSU Sequential Shunt Unit 

SVS Synthetic Vision System 

 

TA Thruster Assist 

TC Terminal Computer 

TCS Thermal Control System 

TDRS Tracking and Data Relay Satellite 

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TDRSS Tracking and Data Relay Satellite System 

TEPC Tissue Equivalent Proportional Counter 

THC Translational Hand Controller 

TORU Teleoperator Control Mode 

TRRJ Thermal Radiator Rotary Joint 

TSA Tool Storage Assembly 

TUS Trailing Umbilical System 

TV Television 

TVIS Treadmill Vibration Isolation and Stabilization 

UB User Bus 

UDG User Data Generation 

UDM Universal Docking Module 

UF Utilization Flight 

UHF Ultra High Frequency 

UIA Umbilical Interface Assembly 

UIP Utility Interface Panel 

ULC Unpressurized Logistic Carrier 

ULCAS Unpressurized Logistic Carrier Attach System 

UMA Umbilical Mechanism Assembly 

UOP Utility Outlet Panel 

URL Uniform Resource Locator 

USA United Space Alliance 

USOS United States On-Orbit Segment 

USS United States Segment 

VDS Video Distribution System 

VDU Video Distribution Unit 

VGS Video Graphics Software 

VRCS Vernier Reaction Control System 

VSW Video Switches 

VTR Video Tape Recorder 

WHS Workstation Host Software 

WVS Wireless Video System 

ZSR Zero-g Stowage Rack 

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Media Assistance 

NASA Television Transmission 

NASA Television is available through the GE2 satellite system which is located on 

Transponder 9C, at 85 degrees west longitude, frequency 3880.0 MHz, audio 6.8 MHz. 

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

available during the mission at Kennedy Space Center, Fla.; Marshall Space Flight Center, 

Huntsville, Ala.; Dryden Flight Research Center, Edwards, Calif.; Johnson Space Center, 

Houston, Texas; and NASA Headquarters, Washington, DC. The television schedule will be 

updated to reflect changes dictated by mission operations. 

Status Reports 

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

operations will be produced by the appropriate NASA news center. 

Briefings 

A mission press briefing schedule will be issued before launch. During the mission, status 

briefings by a flight director or mission operations representative and when appropriate, 

representatives from the payload team, will occur at least once each day. The updated 

NASA television schedule will indicate when mission briefings are planned. 

Internet Information 

Information is available through several sources on the Internet. The primary source for 

mission information is the NASA Human Space Flight Web, part of the World Wide Web. 

This site contains information on the crew and its mission and will be updated regularly with 

status reports, photos and video clips throughout the flight. The NASA Shuttle Web's 

address is: 

http://spaceflight.nasa.gov

General information on NASA and its programs is available through the NASA Home Page 

and the NASA Public Affairs Home Page: 

http://www.nasa.gov

or 

http://www.nasa.gov/newsinfo/index.html

Shuttle Pre-Launch Status Reports 

http://www-pao.ksc.nasa.gov/kscpao/status/stsstat/current.htm

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Information on other current NASA activities is available through the Today@NASA page: 

http://www.nasa.gov/today/index.html

The NASA TV schedule is available from the NTV Home Page: 

http://spaceflight.nasa.gov/realdata/nasatv/schedule.html

Resources for educators can be found at the following address: 

http://education.nasa.gov

Access by CompuServe 

Users with CompuServe accounts can access NASA press releases by typing "GO NASA" 

(no quotes) and making a selection from the categories offered. 

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Media Contacts 

NASA PAO CONTACTS

Glen Golightly 714 372 4742

The Boeing Company

Huntington Beach, CA

Space Shuttle

robert.g.golightly@boeing.com

Bruce Buckingham 321 867-2468

NASA Kennedy Space Center

Kennedy Space Center, FL

Launch Operations

bruce.buckingham-1@kmail.ksc.nasa.gov

Dan Beck 818 586-4572

Boeing Rocketdyne

Canoga Park, CA

Space Shuttle Main Engines

daniel.c.beck@boeing.com

Debbie Rahn 202 358-1638

NASA Headquarters

Washington, DC

International Partners

debbie.rahn@hq.nasa.gov

Dwayne Brown 202 358-1726

NASA Headquarters

Washington, DC

Space Shuttle/Space Station 

Policy

dwayne.brown@hq.nasa.gov

Eileen Hawley 281 483-5111

NASA Johnson Space Center

Houston, TX

Astronauts/Mission Operations

eileen.hawley1@jsc.nasa.gov

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Jack King 321 861-4358

United Space Alliance

Kennedy Space Center, FL

Shuttle Processing

KingJW@usafoo.unitedspacealliance.com

Kari Kelley Allen 281 336-4844

The Boeing Company

Houston, TX

International Space Station

kari.k.allen@boeing.com

Kyle Herring 281 483-5111

NASA Johnson Space Center

Houston, TX

International Space Station 

Operations

kyle.j.herring1@jsc.nasa.gov

June Malone 256 544-0031

NASA Marshall Space Flight Center

Huntsville, AL

Space Station Science

June.Malone@msfc.nasa.gov

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