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Updated October 25, 2002

Station Crew Exchange,

Port Truss Segment

Installation Highlight

Endeavour's Mission

STS-113 Shuttle Press Kit
 STS-113 Shuttle Press Kit 

National Aeronautics and 

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Table of Contents 

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

Timeline Overview ................................................................................................... 9 

Mission Objectives ................................................................................................ 13 

Mission Factoids .................................................................................................... 14 

Mission Profile ....................................................................................................... 17 

Crewmembers ........................................................................................................ 19 

Rendezvous and Docking ..................................................................................... 45 

Spacewalks 

STS-113 Extravehicular Activities ............................................................................ 49 

Payloads 

Payload Overview..................................................................................................... 56 

P1 Truss .................................................................................................................. 59

International Space Station S1 and P1 Truss Summary .......................................... 61 

Crew and Equipment Translation Aid Cart 2 ............................................................ 65 

MEMS-based Pico Satellite (PICOSTAT) Inspector (MEPSI) ................................... 68 

Experiments 

Science Overview .................................................................................................... 70 

DSOs and DTOs ...................................................................................................... 72 
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Shuttle Reference Data 

Shuttle Abort History ................................................................................................ 76 

Shuttle Abort Modes ................................................................................................ 78 

Shuttle Rendezvous Maneuvers .............................................................................. 82 

Space Shuttle Main Engines .................................................................................... 83 

Shuttle Solid Rocket Boosters .................................................................................. 85 

Shuttle Super-lightweight Tank ................................................................................ 93 

Acronyms and Abbreviations ............................................................................... 94 

Media Assistance ................................................................................................. 105 

Media Contacts .................................................................................................... 107 
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Mission Overview 

STS-113 will be the 16th American (11A) assembly flight to the International Space Station 

(ISS). The primary mission will be to bring the Expedition 6 crew to the ISS and return the 

Expedition 5 crew to the Earth. In addition to the crew exchange, STS-113 will be the next 

flight in the assembly sequence to install a major component, the Port 1 (P1) Integrated 

Truss Assembly. 

If one held a giant mirror in front of the ISS during space shuttle Atlantis’ mission in 

October, that image could be replayed to demonstrate the primary assembly task of 

Endeavour’s crew to mount the next truss segment onto the station. The P1 Truss is 

virtually identical to the S1, which now is attached to the opposite side of the central truss 

piece. 

Space shuttle Endeavour is rolled to the Kennedy Space Center Launch Pad 39A on 

top of the Mobile Launch Platform, moved by the crawler-transporter underneath. 

Endeavour is set to depart for the station from Launch Complex 39-A no earlier than Nov. 

10 to install that P1 Truss element to the station and deliver the Expedition 6 crew to 

replace the Expedition 5 crew, which will return home after more than five months in space. 

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Known as STS-113 (station assembly flight 11A), Endeavour’s mission is the fifth providing 

expedition crew rotation services. 

The P1 Truss, highlighted in blue, will be attached to the 

International Space Station during STS-113/11A. 

The major objective of the planned 11-day mission is delivery of the 45-foot-long, 14-ton P1 

to the ISS. The segment, identical to the one delivered on the recent STS-112/9A flight, will 

be attached to the port side of the centerpiece truss, the S-Zero (S0), which is home to the 

Mobile Transporter (MT), Mobile Base System (MBS) and the Canadarm2 robotic arm. P1 

continues the outboard expansion of the station’s rail system in preparation for the addition 

of new power and international science modules in the years to come. With the addition of 

P1, the station’s truss spans 134 feet. 

P1 contains the Active Thermal Control System (ATCS) for the station that will be activated 

next year. This system serves a similar purpose to an automobile’s radiator except this 

system uses 99.9 percent pure ammonia. Additionally, the P1 houses a second Ultra High 

Frequency (UHF) communications system to provide enhanced and extended voice and 

data capability, and a second mobile work platform for spacewalkers called the Crew and 

Equipment Translation Aid (CETA) cart. Like the S1, the P1 includes a Thermal Radiator 

Rotary Joint (TRRJ), which will provide the mechanical and electrical energy for rotating the 

station’s heat-rejecting radiators. 

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Three spacewalks will be carried out to install and activate the truss and its associated 

equipment. 

Inside the KSC Space Station Processing Facility, the P1 Truss segment is 

moved by overhead crane through the highbay toward the payload canister. 

P1 is the fourth of 11 truss structures that ultimately will expand the ISS to the length of a 

football field and increase its power through the addition of new photovoltaic modules and 

solar arrays. 

Future assembly missions will include additional truss elements and relocation in late 2003 

of the P6 Truss with the first set of U.S. solar arrays, which was delivered to the ISS as part 

of the STS-97/4A mission in December 2000. 

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The STS-113 and Expedition 6 crews exit the Operations and Checkout Building on 

their way to Launch Pad 39A for a simulated launch countdown. On the left, front to 

back, are Ken Bowersox, commander of Expedition 6, Mission Specialist John 

Herrington, astronaut Donald Pettit, and Mission Specialist Michael Lopez-Alegria. 

On the right, front to back, are STS-113 Commander James Wetherbee, Pilot Paul 

Lockhart, and cosmonaut Nikolai Budarin. The countdown is part of Terminal 

Countdown Demonstration Test activities prior to launch. 

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Endeavour will be commanded by veteran Astronaut Jim Wetherbee (Capt., USN), who will 

be making his sixth flight into space, most recently on STS-102 in 2001 – the first station 

crew rotation mission. He will be joined on the flight deck by Pilot Paul Lockhart (Lt. Col., 

USAF), making his second flight to the ISS this year after piloting the STS-111 mission that 

delivered the station’s Mobile Base System along with the Expedition 5 crew and returned 

Expedition 4 home. 

First-time shuttle crewmember John Herrington (Cmdr., USN) will serve as Endeavour’s 

flight engineer and will be one of the two astronauts conducting three spacewalks during 

the docked phase of the mission to connect power and data cables between truss sections 

along with other external hardware. 

Joining Herrington on the spacewalks (known as Extravehicular Activity, or EVA) is veteran 

Astronaut Mike Lopez-Alegria (Capt., USN) who conducted spacewalks during his last 

mission to the station on the STS-92 flight to install the Z1 Truss and huge gyroscopes to 

the station two years ago. In addition to his outside work, Lopez-Alegria will oversee the 

transfer of equipment and supplies inside the station. 

The Expedition 6 crew of Commander Ken Bowersox and Flight Engineers Nikolai Budarin 

and Don Pettit will join Endeavour’s four astronauts heading to the station for about a fourmonth stay. They will replace the Expedition 5 crew of Commander Valery Korzun and 

Flight Engineers Sergei Treschev and Peggy Whitson, also serving as the first NASA ISS 

Science Officer. That crew returns after more than five months on the station that included 

the conduct of some 25 science experiments. Pettit will serve as ISS Science Officer for 

Expedition 6. 

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The International Space Station, photographed by Atlantis crewmembers after 

undocking, clearly shows the newly installed S1 Truss (illuminated in center). 

Two days after Endeavour is launched, Wetherbee will guide the shuttle to a gentle linkup 

with a docking port on the U.S. Destiny laboratory, setting the stage for the opening of the 

hatches and the start of seven days of joint operations, including the fifth transition of one 

station crew to another. 

The following day, Lopez-Alegria and Herrington will begin spacewalk preparations while 

Wetherbee uses the shuttle’s robotic arm to lift the huge P1 Truss out of Endeavour’s 

payload bay to hand it to the station’s Canadarm2 under control of Whitson inside Destiny. 

She then will carefully install it on the port side of the S0 Truss. Capture bolts will 

structurally mate the two trusses after a claw-like device on the S0 grabs a fixture on the P1 

segment. The procedure will be timed so that the two spacewalkers do not exit the station’s 

Quest Airlock until the mating process is complete. 

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As part of Crew Equipment Interface Test activities, STS-113 Mission Specialists 

Michael Lopez-Alegria (left) and John Herrington (right) practice working with flight 

equipment in Endeavour’s payload bay. 

Once outside, Lopez-Alegria and Herrington begin the connection of power, data and fluid 

umbilicals between the newly attached trusses. They also will release launch restraints on 

the truss’ crew platform cart and install a wireless video system transceiver on the Unity 

module. 

The next day – Flight Day 5 – is highlighted by the formal handover of station command 

from Expedition 5 to Expedition 6. The day includes inside transfer work and some off duty 

time before the second spacewalk begins on Flight Day 6 to continue the connection of 

fluid lines between the P1 and the S0 segments, the installation of another wireless video 

system transceiver on the P1, and the relocation of the CETA cart in preparation for the 

relocation of the Mobile Transporter. Also in preparation for the MT relocation, the station’s 

Canadarm2 will be temporarily moved to a grapple fixture on the outside of Destiny. 

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Another day of transfer work will take place on the seventh day followed by the third and 

final spacewalk of the mission during which Lopez-Alegria and Herrington will focus on 

the installation of small devices called Spool Positioning Devices, which are being 

retrofitted on all of the quick disconnect fluid line fittings between modules and truss 

sections on the outside of the station. They are being installed as a precautionary step 

to ensure the lines can be disconnected even if pressure builds up due to an internal 

leak. Fifty-one SPDs are being installed during this mission – more than 40 during the 

third EVA. Additionally, Lopez-Alegria and Herrington will install a pump used to 

transfer ammonia through the P1 and also connect ammonia and nitrogen lines to its 

Ammonia Tank Assembly. 

All three spacewalks are budgeted to last about 61⁄2 hours and will be conducted from the 

station’s Quest Airlock. 

The next day, Flight Day 9, the shuttle and station crews will complete transfer work and 

get-ahead tasks for future assembly flights. The Expedition 5 Crew bids farewell to its home 

for five months and the shuttle crew bids its Expedition 6 replacements bon voyage as the 

hatches are closed on Flight Day 10. 

Lockhart will be at the controls as Endeavour undocks from the ISS and conducts a 400-

foot radial fly around of the complex for photo and television documentation of the newly 

expanded facility. 

After a day devoted to packing up gear, Endeavour’s six crewmembers will glide to a 

landing at the Kennedy Space Center to wrap up the orbiter’s 19th mission and the 112th in 

shuttle program history 

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Timeline Overview 

Flight Day 1—Ascent: 

• Standard Flight Day 1 activities will be completed [Aft Controller C/O, Elevon Park, 

Auxiliary Power Unit (APU) Heater reconfiguration]. 

Flight Day 2—Prep for Mission: 

• The ergometer will be set up early in the day to support exercise for International 

Space Station crewmembers. 

• Checkout of two suits on shuttle to be used by STS-113 spacewalkers and other 

spacewalk setup and reconfiguration tasks will be performed in support of 11A. 

• The Shuttle Remote Manipulator System (SRMS) and Orbital Space Vision System 

(OSVS) will be checked out. 

• Rendezvous activities including rendezvous tools setup and checkout, handheld 

laser checkout, centerline camera installation and Orbiter Docking System ring 

extension will be performed before docking with the ISS. 

• Rendezvous burns will be performed. 

• Sequential Still Video will be set up, if not already from Flight Day 1. 

• Status of powered payloads will be verified. 

Flight Day 3—Rendezvous and Docking: 

• The ISS crew will set up the ISS Wireless Information System (IWIS) to observe 

loads caused by orbiter docking. After docking, the ISS crew will terminate the IWIS 

operations and will later downlink the data. 

• The ISS crew will perform an initial reading of the EVA Radiation Monitoring 

equipment to establish a baseline for future readings performed after EVAs. 

• The spacewalkers’ spacesuits will be removed from the shuttle airlock to facilitate 

hatch opening and transfers after docking. 

• The orbiter will rendezvous and dock with the ISS. 

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• After docking, leak checks will be performed on the PMA and ODS; the ODS will be 

prepared for ingress and hatches will be opened. A short ISS safety briefing will be 

given to the arriving shuttle crewmembers. 

• The SRMS will be powered and uncradled. A P1 install prep will check camera 

connectivity and views. 

• Spacewalkers’ spacesuits (Extravehicular Mobility Units or EMUs) and EVA 

equipment will be transferred to the ISS. The EMUs will be checked out with airlock 

interfaces. Rechargeable EVA Battery Assembly (REBA) batteries will be installed 

into the EMUs and REBA-powered equipment will be verified operational on both 

EMUs. EVA tools will be transferred to the ISS and prepared for EVA 1 the next day. 

The Pistol Grip Tool (PGT) will be checked out. All crewmembers involved in the first 

spacewalk will participate in an EVA 1 Procedure Review. 

• Large items in the shuttle middeck will be transferred to the ISS to clear space in the 

middeck. 

Flight Day 4—First Spacewalk: 

• The crew will grapple the P1 with the SRMS and remove it from the Orbiter Payload 

Bay. A 10-hour thermal clock begins when the truss clears the payload bay sill and 

ends when the survival heaters are activated. The P1 Truss will then be handed over 

to the SSRMS and installed on the Segment-to-Segment Attach System using an 

auto sequence. 

• Once bolting is completed, the SSRMS is no longer needed until EVA 2, so it will be 

maneuvered to the lab PDGF. Following this, the SSRMS will maneuver to the 

Mobile Base System and be powered down in preparation for EVA 2. Once the 

SRMS has completed Photo/TV Ops, it will be stowed and powered down. It will not 

be needed again for the docked phase. 

• The ISS Exercise EVA protocol will be used to support the EVA. The two EVA 

crewmembers will perform the required 10-minute Cycle/Ergometer Vibration 

Isolation System (CVIS) exercise while breathing pure oxygen to purge nitrogen 

from the EVA crewmembers’ blood. IV crewmembers will ingress the ISS airlock with 

the two EVA crewmembers and close the Node hatch. The EVA crewmembers will 

continue to pre-breathe pure oxygen for a total of 80 minutes. 

• Once Crew Lock depress is complete, EVA crewmembers will egress the Crew lock 

and begin EVA setup. 

• EVA 1 takes place. (See the section on spacewalks for details.) 

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• When EVA cleanup is complete, EVA crewmembers will enter the ISS Crew Lock 

and perform pre-repress, close the EVA hatch, and repress the Crew Lock. PostEVA procedures and EVA preparation activities for the next EVA will be performed. 

EMUs will be transferred to STS airlock for recharging overnight. 

Flight Day 5—Transfer: 

• Transfer of nitrogen from the orbiter to the Airlock High-Pressure Gas Tanks will be 

initiated. Nitrogen transfer is performed by equalizing the higher pressure orbiter 

nitrogen tanks with the ISS nitrogen tanks. 

• Reboost No. 1 will be performed. 

• A shuttle supply water will be performed. 

• Equipment Lock preparation, EVA tool configuration and preparation of spacesuits 

and equipment for the second spacewalk will be performed. 

• Logistics stowed in the shuttle middeck will be transferred to the ISS. 

• All shuttle crewmembers will participate in a joint PAO event. 

Flight Day 6—Second Spacewalk: 

• EVA 2 will be conducted. (See the section on spacewalks for details.) 

• The SSRMS will be stowed after the EVA is complete. 

Flight Day 7—Transfer: 

• Reboost No. 2 will be performed. 

• Preparation and configuration of suits and tools for the third spacewalk will be the 

order of the day. 

• A joint crew news conference will be conducted and a joint crew photo will be taken. 

• Remaining transfer items in the shuttle middeck will be delivered to the ISS. Return 

items in ISS will be taken to the orbiter and stowed. 

Flight Day 8—Third Spacewalk: 

• The Mobile Transporter will translate from worksite No. 4 to No. 7. The SSRMS will 

then walk off the lab onto the MT. 

• The third EVA will be conducted. (See the section on spacewalks for details.) 

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Flight Day 9—Undock Preparations: 

• Oxygen transfer will be terminated and equipment will be disassembled. 

• Reboost No. 3 takes place. 

• Final still imagery photos of the final 11A configuration will be taken. 

• Oxygen and nitrogen transfer will be terminated and transfer equipment will be 

disassembled. 

• Remaining logistics will be transferred between the ISS and shuttle. EMU and EVA 

equipment is transferred. An inventory check will be performed to verify that all 

equipment transferred between vehicles is returned to the correct vehicle. 

• Change of command ceremony takes place. 

• Off duty time for shuttle crewmembers is scheduled in the afternoon. 

Flight Day 10—Undock/MEPSI: 

• ISS and shuttle crews will bid farewell, close the hatch between vehicles, and 

perform an ODS leak check and Centerline Camera Setup. 

• Undocking, flyaround and final departure from the ISS takes place. 

• MEPSI will be deployed at a safe distance from ISS out of plane. 

• Any remaining crew time will be used to begin stowing the cabin. 

Flight Day 11—Entry Preparations: 

• Standard day before entry shuttle activities will be performed (Flight Control System 

checkout, Reaction Control System hot-fire, Deorbit Briefing, Landing -1 

communications check, cabin stow, pilot ops, entry video setup, ergometer stowed, 

and Ku stow). 

• SRMS will be powered down. 

• Any remaining crew time will be used to finish stowing the cabin. 

• Recumbent seats will be set up in the middeck. 

Flight Day 12—Entry and Landing: 

• Standard activities before de-orbit prep will be performed. 

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

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Mission Objectives 

International Space Station Program list of major tasks in order of priority 

1. Rotate the Expedition 5 crew with Expedition 6 crew. 

2. Install and safe the Integrated Truss Structure P1 to the existing central truss using 

both the shuttle and station robotic arms. 

3. Transfer critical items per Flight 11A Transfer Priority List. 

4. Perform mandatory crew activities to support powered payload maintenance 

operations. 

5. Complete P1 activation and check out, including connection of the remaining 

P1/S0 nadir and zenith tray umbilicals. 

6. Install and check out two Wireless Video System External Transceiver Assemblies 

(WETA). 

7. Deploy P1 central radiator. 

8. Disconnect the Squib Firing Unit harness, reposition it to the radiator beam line 

heaters and activate the P1 fluid line secondary heaters. 

9. Configure Mobile Transporter/Crew and Equipment Translation Aid (CETA) cart to 

starboard side of the MT. 

10. Release P1/P3 utility line clamps. 

11. Checkout P1/P3 Segment-to-Segment Attach System (SSAS). 

12. Perform Thermal Radiator Rotary Joint check out. 

13. Connect S0 to P1 ammonia lines. 

14. Connect Ammonia Tank Assembly nitrogen and ammonia lines. 

15. Deploy P1 Ultra High Frequency (UHF) antenna. 

16. Transfer oxygen and nitrogen to the Quest Airlock’s High-Pressure Gas Tanks. 

17. Activate and check out the P1 UHF antenna. 

18. Perform ISS reboost to maintain altitude and rendezvous requirements. 

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Mission Factoids 

Just over two years ago the International Space Station consisted of three modules and 

one small supporting truss structure upon which the station’s first solar arrays were 

mounted. In the fall of 2000, the ISS weighed 62 tons, was about 120 feet long and had an 

equivalent habitable volume to fill the average home garage. 

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Today, the fifth resident crew aboard the ISS is wrapping up a 41⁄2-month stay aboard an 

orbiting outpost with habitable volume equal to that of a three-bedroom house. It consists 

of six modules, two airlocks for spacewalk activity, the world’s most complex robotic arm for 

assembly and a railcar system which soon will span the 360-foot length of the station’s 

truss system in the years to come. 

The fifth crew rotation occurs during Endeavour’s week of docked operations at the station, 

providing a near seamless transition from one crew to the next since Expedition 1’s 

pathfinding flight that began in October 2000. 

As the International Space Station enters its third year of continuous occupancy and fifth 

since the first segment was launched Nov. 20, 1998, it features the following: 

• With the addition of the P1 Truss and the second of two small translation carts to 

help with moving spacewalkers and equipment to worksites, 19 different elements 

will have been delivered to the station, representing contributions from all of the 

International Partners involved in the global project. 

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• The ISS is 171 feet long, 240 feet wide and 90 feet high. 

• With the addition of the P1 Truss and the Crew and Equipment Translation Aid 

(CETA) cart, the ISS will weigh more than 197 tons. 

• Five scientific experiment racks are housed in the Destiny laboratory of the ISS. 

• Eleven experiments representing life sciences, material sciences and Earth 

observation studies are currently yielding reams of data for researchers back on 

Earth. 

• The three spacewalks on STS-113 are designed to install and activate the P1 Truss, 

and will bring to 49 the number of spacewalks conducted for ISS assembly and 

maintenance. 

• More than 300 hours in spacewalking time will have been devoted to ISS assembly 

and maintenance by the time STS-113 is completed. 

Acknowledged as the most complex engineering project in history, the ISS is rapidly 

expanding to accommodate new scientific modules and solar arrays to provide the power 

needed to run tens of thousands of systems and scientific research from every corner of 

the Earth. 

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Mission Profile 

Crew 

Commander: Jim Wetherbee 

Pilot: Paul Lockhart 

Mission Specialist 1: Michael Lopez-Alegria

Mission Specialist 2: John Herrington 

ISS Expedition 6 (Up): Ken Bowersox 

ISS Expedition 6 (Up): Nikolai Budarin 

ISS Expedition 6 (Up): Donald Pettit

ISS Expedition 5 (Down): Valery Korzun

ISS Expedition 5 (Down): Peggy Whitson

ISS Expedition 5 (Down): Sergei Treschev

Launch 

Orbiter: Endeavour (OV-105) 

Launch Site: Kennedy Space Center Launch Pad 39A 

Launch Date: Nov. 10, 2002 

Launch Window: 5 Minutes 

Altitude: 122 Nautical Miles (Orbital Insertion); 

210 NM (Rendezvous) 

Inclination: 51.6 Degrees 

Duration: 10 Days 19 Hrs. 10 Min. 

Vehicle Data 

Shuttle Liftoff Weight: 4,521,127 lbs. 

Orbiter/Payload Liftoff Weight: 256,747 lbs. 

Orbiter/Payload Landing Weight: 201,715 lbs. 

Software Version: OI-29 

Space Shuttle Main Engines: 

SSME 1: 2050 SSME 2: 2044 SSME 3: 2045 

External Tank: ET-116A (Super Light Weight Tank) 

SRB Set: BI114PF 

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Shuttle Aborts 

Abort Landing Sites 

RTLS: Kennedy Space Center Shuttle Landing Facility 

TAL: Primary – Zaragoza; Alternates Ben Guerir, Moron 

AOA: Kennedy Space Center Shuttle Landing Facility 

 

Landing 

Landing Date: 11/20/02 

Primary Landing Site: Kennedy Space Center 

Shuttle Landing Facility 

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Crewmembers 

Jim Wetherbee, Commander, 49 (Capt., USN) 

Seating: Flight deck for launch and landing. 

Responsibilities: Wetherbee is responsible for the overall safety and success of the 

mission and will oversee orbiter operations for the rendezvous and docking of Endeavour to 

the International Space Station. He will be the prime operator of the shuttle’s robotic arm 

during the removal of the P1 Truss from Endeavour’s payload bay. He then will hand it off 

to the station’s robotic arm under control of Expedition Five Flight Engineer Peggy Whitson. 

Wetherbee then serves as the backup to Pilot Paul Lockhart throughout the fly around of 

the station after undocking and will act as ‘camera operator’ during the three spacewalks 

conducted by Michael Lopez-Alegria and John Herrington. 

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PERSONAL DATA 

Born Nov. 27, 1952, in Flushing, N.Y. Considers his hometown to be Huntington Station, 

N.Y. Married to the former Robin DeVore Platt of Jacksonville, Fla. They have two children. 

He enjoys tennis, skiing, softball, running, and music. His parents, Mr. and Mrs. Dana A. 

Wetherbee, reside in Huntington Station, N.Y. Her parents, Mr. and Mrs. Harry T. Platt, Jr., 

reside in Jacksonville, Fla. 

EDUCATION 

Graduated from Holy Family Diocesan High School, South Huntington, N.Y., in 1970; 

received a bachelor of science degree in aerospace engineering from the University of 

Notre Dame in 1974. 

ORGANIZATIONS 

Member of the Society of Experimental Test Pilots. 

SPECIAL HONORS 

Distinguished Flying Cross; Navy Achievement Medal; two Meritorious Unit 

Commendations. 

EXPERIENCE 

Wetherbee received his commission in the United States Navy in 1975 and was designated 

a naval aviator in December 1976. After training in the A-7E, he was assigned to Attack 

Squadron 72 (VA-72) from August 1977 to November 1980 aboard the USS John F. 

Kennedy and logged 125 night carrier landings. After attending the U.S. Naval Test Pilot 

School, Patuxent River, Md., in 1981 he was assigned to the Systems Engineering Test 

Directorate. He was a project officer and test pilot for the weapons delivery system and 

avionics integration for the F/A-18 aircraft. Subsequently assigned to Strike Fighter 

Squadron 132 (VFA-132), he flew operationally in the F/A-18 from January 1984 until his 

selection for the astronaut candidate program. He has logged over 5,000 hours flying time 

and 345 carrier landings in 20 different types of aircraft. 

NASA EXPERIENCE 

Selected by NASA in May 1984, Wetherbee became an astronaut in June 1985. Most 

recently, he served as director of the Flight Crew Operations Directorate. A veteran of five 

spaceflights, Wetherbee has logged over 1,262 hours in space. He was the pilot on STS-32 

in 1990, and was the mission commander on STS-52 in 1992, STS-63 in 1995, STS-86 in 

1997, and STS-102 in 2001. Wetherbee will serve as commander of STS-113. 

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SPACEFLIGHT EXPERIENCE 

STS-32 Columbia (Jan. 9-20, 1990) included the successful deployment of the Syncom 

IV-F5 satellite, and retrieval of the 21,400-pound Long Duration Exposure Facility 

(LDEF) using the remote manipulator system (RMS). The crew also operated a 

variety of middeck experiments and conducted numerous medical test objectives, 

including in-flight aerobic exercise and muscle performance to evaluate human 

adaptation to extended duration missions. Mission duration was 173 orbits in 

261 hours and 1 minute. 

STS-52 Columbia (Oct. 22 to Nov. 1, 1992) successfully deployed the Laser Geodynamic 

Satellite (LAGEOS), a joint Italian-American project. The crew also operated the first 

U.S. Microgravity Payload (USMP) with French and American experiments, and 

successfully completed the initial flight tests of the Canadian-built Space Vision System 

(SVS). Mission duration was 236 hours and 56 minutes. 

STS-63 Discovery (Feb. 2-11, 1995), was the first joint flight of the new Russian-American 

Space Program. Mission highlights included the rendezvous with the Russian Space 

Station, Mir, operation of Spacehab, and the deployment and retrieval of Spartan 204. 

The mission was accomplished in 129 orbits in 198 hours and 29 minutes. 

STS-86 Atlantis (Sept. 25 to Oct. 6, 1997) was the seventh mission to rendezvous and 

dock with the Russian Space Station Mir. Highlights included the delivery of a Mir 

attitude control computer, the exchange of U.S. crew members Mike Foale and David 

Wolf, a spacewalk by Scott Parazynski and Vladimir Titov to retrieve four experiments 

first deployed on Mir during the STS-76 docking mission, the transfer to Mir of 10,400 

pounds of science and logistics, and the return of experiment hardware and results to 

Earth. Mission duration was 169 orbits in 259 hours and 21 minutes. 

STS-102 Discovery (March 8-21, 2001) was the eighth shuttle mission to visit the 

International Space Station. Mission accomplishments included the delivery of the 

Expedition 2 crew and the contents of the Leonardo Multi-Purpose Logistics Module, 

the completion of two successful space walks, the return to earth of the Expedition 1 

crew, as well as the return of Leonardo, the reusable cargo carrier built by the Italian 

Space Agency. Mission duration was 307 hours and 49 minutes. 

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Paul Lockhart, Pilot, 46 (Lt. Col., USAF) 

Seating: Flight deck for launch and landing. 

Responsibilities: Lockhart is the in-cabin choreographer throughout the three planned 

spacewalks by Lopez-Alegria and Herrington and will be in charge of undocking Endeavour 

from the ISS and conducting a fly around of the station for photo and television 

documentation. 

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PERSONAL DATA

Born April 28, 1956, in Amarillo, Texas, to Mr. and Mrs. Charles W. Lockhart. Married to the 

former Mary Theresa Germaine of Boston, Mass., where her parents, Mr. and Mrs. Joseph 

R. Germaine, still reside. His mother and stepfather, Joy and Leo Wiley, continue to reside 

in Amarillo. He enjoys all outdoor sports, including hunting and camping. 

EDUCATION

Graduated from Tascosa High School, Amarillo, Texas, in 1974; received a bachelor of arts 

degree in mathematics from Texas Tech University in 1978, and a master of science 

degree in aerospace engineering from the University of Texas in 1981. Studied at the 

University of Innsbruck and the University of Vienna Summer School from 1978-79 on a 

Rotarian Fellowship. Has also completed aerospace-related courses from Syracuse 

University and the University of Florida. 

ORGANIZATIONS

Society of Experimental Test Pilots, Order of Daedalians (Fraternal Order of Military Pilots). 

AWARDS

Recipient of Air Force Aerial Achievement Medal, Commendation Medal, Outstanding Unit 

Award with Valor, National Defense Service Medal, Achievement Medal, and numerous 

other service recognitions and ribbons. A distinguished graduate of both ROTC and the Air 

Force Squadron Officer School, Lockhart is also a member of Outstanding Young Men of 

America and Who's Who in American Colleges. 

EXPERIENCE

Lockhart was commissioned a 2nd Lieutenant in the USAF in 1981. Upon graduation from 

pilot training in 1983, he was assigned to the 49th Fighter Interceptor Squadron flying T33s. In 1986, he transitioned to the F-4 and flew operationally with U.S. Air Forces, Europe 

(in Germany) from 1987-1990 as an instructor pilot for F-4 and F-16 aircrew in the tactics of 

surface-to-air missile suppression. In 1991 he reported to Edwards Air Force Base for yearlong training as a test pilot in high-performance military aircraft. Upon graduation, he was 

assigned to the Test Wing at the Air Force Developmental Test Center at Eglin Air Force 

Base, Fla., performing weapons testing for the F-16 aircraft. During his 4-1/2 year tour at 

Eglin, he was selected as the Operations Officer for the 39th Flight Test Squadron. Much of 

America's state-of-the-art weaponry was first tested under his guidance at the 39th Flight 

Test Squadron. 

He has logged over 4,000 hours in more than 30 different aircraft. 

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NASA EXPERIENCE

Selected by NASA in April 1996, Lockhart reported to the Johnson Space Center in August 

1996. After completion of initial astronaut training, Lockhart was assigned to the Astronaut 

Office Spacecraft Systems/Operations Branch where he worked various technical issues 

including the Space Shuttle Main Engine (SSME) and redesign of the orbiter's flight display. 

Lockhart served as pilot on STS-111 (2002) and has logged over 332 hours in space. 

SPACEFLIGHT EXPERIENCE

STS-111 Endeavour (June 5-19, 2002). The STS-111 mission delivered a new ISS resident 

crew and a Canadian-built mobile base for the orbiting outpost's robotic arm. The crew 

also performed late-notice repair of the station's robot arm by replacing one of the arm's 

joints. It was the second space shuttle mission dedicated to delivering research 

equipment to the space platform. STS-111 also brought home the Expedition 4 crew 

from their 6-1/2 month stay aboard the station. Mission duration was 13 days, 20 hours 

and 35 minutes. Unacceptable weather conditions in Florida necessitated a landing at 

Edwards Air Force Base, Calif. 

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Michael Lopez-Alegria, Mission Specialist 1, 44 (Capt., USN) 

Seating: Flight deck for launch, middeck for landing. 

Responsibilities: Lopez-Alegria will serve as extravehicular crewmember 1 (EV1) for the 

three spacewalks and will wear the spacesuit bearing red stripes. He will assist in handling 

rendezvous tools during Endeavour’s approach for docking to the ISS and oversee the 

operation of the orbiter docking system and will direct the transfer of equipment and 

supplies to the station from the shuttle. 

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PERSONAL DATA 

Born May 30, 1958, in Madrid, Spain, and grew up in Mission Viejo, Calif. Married to the 

former Daria Robinson of Geneva, Switzerland. They have one son. Michael enjoys 

sports, traveling and cooking, and is interested in national and international political, 

economic and security affairs. His father, Eladio Lopez-Alegria, resides in Madrid. His 

mother, Louise Lopez-Alegria, is deceased. Daria’s parents, Professor Stuart and 

Margareta Robinson, reside in Geneva. 

EDUCATION 

Graduated from Mission Viejo High School, Mission Viejo, Calif., in 1976; received a 

bachelor of science degree in systems engineering from the U.S. Naval Academy in 

1980; and a master of science degree in aeronautical engineering from the U.S. Naval 

Postgraduate School in 1988. Graduate of Harvard University’s Kennedy School of 

Government Program for Senior Executives in National and International Security. 

ORGANIZATIONS 

Member, Society of Experimental Test Pilots; Association of Naval Aviation and 

Association of Space Explorers. 

EXPERIENCE 

Following flight training, Lopez-Alegria was designated a Naval Aviator on Sept. 4, 1981. 

He served as a flight instructor in Pensacola, Fla., until March 1983 and then as a pilot 

and mission commander of EP-3E aircraft, flying electronic reconnaissance missions in 

the Mediterranean Sea, North Atlantic, Baltic Sea and Central America. In 1986 he was 

assigned to a two-year cooperative program between the Naval Postgraduate School in 

Monterey, Calif., and the U.S. Naval Test Pilot School in Patuxent River, Md. His final tour 

before being assigned to NASA was at the Naval Air Test Center as an engineering test 

pilot and program manager. He has accumulated more than 4,500 pilot hours in over 30 

different aircraft types. 

NASA EXPERIENCE 

Selected by NASA in March 1992, Lopez-Alegria reported for training to the Johnson 

Space Center in August 1992. Following one year of training and designation as an 

astronaut, he was assigned to be the Astronaut Office technical point of contact to various 

space shuttle project elements. He was subsequently assigned to the Kennedy Space 

Center where he provided crew representation on orbiter processing issues and provided 

direct crew support during launches and landings. Following his first spaceflight he served 

as NASA Director of Operations at the Yuri Gagarin Cosmonaut Training Center, Star 

City, Russia. After his second mission, he led the newly formed ISS Crew Operations 

branch of the Astronaut Office. 

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SPACEFLIGHT EXPERIENCE 

STS-73 Columbia (Oct. 20 to Nov. 5, 1995) was launched from and returned to land at the 

Kennedy Space Center, Fla. STS-73 was the second United States Microgravity 

Laboratory mission and focused on materials science, biotechnology, combustion 

science, the physics of fluids, and numerous scientific experiments housed in the 

pressurized Spacelab module. Lopez-Alegria served as the flight engineer during the 

ascent and entry phases of flight, and was responsible for all operations of the “blue” 

shift on orbit. The STS-73 mission was completed in 15 days, 21 hours, 52 minutes and 

21 seconds and traveled over 6 million miles in 256 Earth orbits. 

STS-92 Discovery (Oct. 11-24, 2000) was launched from the Kennedy Space Center, Fla., 

and returned to land at Edwards Air Force Base, Calif. During the 13-day flight, the 

seven-member crew attached the Z1 Truss and Pressurized Mating Adapter 3 to the 

International Space Station using Discovery’s robotic arm and performed four 

spacewalks to configure these elements. This expansion of the ISS opened the door for 

future assembly missions and prepared the station for its first resident crew. LopezAlegria totaled 14 hours and 3 minutes of EVA time in two spacewalks. The STS-92 

mission was accomplished in 202 orbits of the Earth, traveling 5.3 million miles in 12 

days, 21 hours, 40 minutes and 25 seconds. 

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John Bennett Herrington, Mission Specialist 2, 44 (Cmdr., USN) 

Seating: Flight deck for launch and landing. 

Responsibilities: Herrington will serve as flight engineer during Endeavour’s launch and 

landing, assisting Wetherbee and Lockhart. He also will serve as extravehicular activity 

crewmember 2 (EV2) for the three spacewalks and will wear a suit with no markings. 

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PERSONAL DATA

Born Sept. 14, 1958, in Wetumka, Okla. He grew up in Colorado Springs, Colo., Riverton, 

Wyo., and Plano, Texas. Married to the former Debra Ann Farmer of Colorado Springs, 

Colo. They have two children. He enjoys rock climbing, snow skiing, running, cycling. His 

parents, Mr. and Mrs. James E. Herrington, reside in Spicewood, Texas. His brother, 

James E. Herrington, Jr., resides in Sandy Spring, Md. His sister, Jennifer D. Monshaugen, 

resides in Spicewood, Texas. 

EDUCATION

Graduated from Plano Senior High School, Plano, Texas, in 1976; received a bachelor of 

science degree in applied mathematics from the University of Colorado at Colorado 

Springs, in 1983, and a master of science degree in aeronautical engineering from the U.S. 

Naval Postgraduate School in 1995. 

ORGANIZATIONS

Life member of the Association of Naval Aviation, University of Colorado at Colorado 

Springs Alumni Association. Sequoyah Fellow, American Indian Science and Engineering 

Society. 

SPECIAL HONORS

Distinguished Naval Graduate from Aviation Officer Candidate School, Pensacola, Fla., in 

1984. Awarded Navy Commendation Medal, Navy Meritorious Unit Commendation, Coast 

Guard Meritorious Unit Commendation, Coast Guard Special Operations Service Ribbon, 

National Defense Medal, Sea Service Deployment Ribbons (3), and various other service 

awards. 

EXPERIENCE

Herrington received his commission from Aviation Officer Candidate School in March 1984 

and was designated a Naval Aviator in March 1985. He reported to Patrol Squadron ThirtyOne (VP-31) at the Moffett Field Naval Air Station, Mountain View, Calif., for initial training 

in the P-3C Orion. His first operational assignment was with Patrol Squadron Forty-Eight 

(VP-48) where he made three operational deployments, two to the Northern Pacific based 

from Naval Air Station Adak, Alaska, and one to the Western Pacific based from the Naval 

Air Station Cubi Point, Republic of the Philippines. While assigned to VP-48, Herrington 

was designated a Patrol Plane Commander, Mission Commander, and Patrol Plane 

Instructor Pilot. Following completion of his first operational tour, Herrington then returned 

to VP-31 as a Fleet Replacement Squadron Instructor Pilot. While assigned to VP-31 he 

was selected to attend the U.S. Naval Test Pilot School in Patuxent River, Md., in January 

1990. After graduation in December 1990, he reported to the Force Warfare Aircraft Test 

Directorate as a project test pilot for the Joint Primary Aircraft Training System. Herrington 

conducted additional flight test assignments flying numerous variants of the P-3 Orion as 

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well as the T-34C and the DeHavilland Dash 7. Following his selection as an Aeronautical 

Engineering Duty Officer, Herrington reported to the U.S. Naval Postgraduate School 

where he completed a master of science degree in aeronautical engineering in June 1995. 

Herrington was assigned as a special projects officer to the Bureau of Naval Personnel Sea 

Duty Component when selected for the astronaut program. 

He has logged over 3,000 flight hours in over 30 different types of aircraft. 

NASA EXPERIENCE

Selected by NASA in April 1996, Herrington reported to the Johnson Space Center in 

August 1996. Having completed two years of training and evaluation, he is qualified for 

flight assignment as a mission specialist. Initially, Herrington was assigned to the Flight 

Support Branch of the Astronaut Office where he served as a member of the Astronaut 

Support Personnel team responsible for shuttle launch preparations and post-landing 

operations. 

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Ken Bowersox, Mission Specialist 3 (Up), 45 (Capt., USN) 

Seating: Middeck for launch. 

Responsibilities: Bowersox will serve as commander of the Expedition 6 crew aboard 

the International Space Station. In that role, he will oversee the day-to-day operations 

aboard the complex, taking the reins from current commander Valery Korzun. During the 

docked phase of Endeavour’s mission, Bowersox will serve as the prime operator of the 

station’s robotic arm (Canadarm2) on spacewalks two and three and back up station Flight 

Engineer Peggy Whitson on the first. 

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PERSONAL DATA

Born Nov. 14, 1956, in Portsmouth, Va., but considers Bedford, Ind., to be his hometown. 

EDUCATION

Graduated from Bedford High School, Bedford, Ind., in 1974; received a bachelor of 

science degree in aerospace engineering from the United States Naval Academy in 1978, 

and a master of science degree in mechanical engineering from Columbia University in 

1979. 

EXPERIENCE

Bowersox received his commission in the United States Navy in 1978 and was designated 

a Naval Aviator in 1981. He was then assigned to Attack Squadron 22, aboard the USS 

Enterprise, where he served as a Fleet A-7E pilot, logging over 300 carrier arrested 

landings. Following graduation from the United States Air Force Test Pilot School at 

Edwards Air Force Base, Calif., in 1985, he moved to the Naval Weapon Center at China 

Lake, Calif., where he spent the next year and a half as a test pilot flying A-7E and F/A-18 

aircraft until advised of his selection to the astronaut program. 

NASA EXPERIENCE

Selected as an astronaut candidate by NASA in June 1987, Bowersox completed a oneyear training and evaluation program in August 1988. He has held a variety of assignments 

since then including: flight software testing in the Shuttle Avionics Integration Laboratory 

(SAIL); Technical Assistant to the Director of Flight Crew Operations; Astronaut Office 

representative for orbiter landing and rollout issues; Chief of the Astronaut Office Safety 

Branch; Chairman of the Spaceflight Safety Panel; during several shuttle missions he 

served as a spacecraft communicator (CAPCOM) in the Houston Mission Control Center. 

He also served as backup to the first International Space Station crew. A four-flight veteran, 

Bowersox has logged over 50 days in space. He flew as pilot on STS-50 in 1992 and STS61 in 1993, and was the spacecraft commander on STS-73 in 1995 and STS-82 in 1997. 

SPACEFLIGHT EXPERIENCE

STS-50, June 25-July 9, 1992, was the first flight of the United States Microgravity 

Laboratory and the first Extended Duration Orbiter flight. Over a two-week period, the 

STS-50 flight crew aboard space shuttle Columbia conducted a wide variety of 

experiments relating to materials processing and fluid physics in a microgravity 

environment. 

STS-61, Dec. 2-13, 1993, was the Hubble Space Telescope (HST) servicing and repair 

mission. During the 11-day flight, the HST was captured and restored to full capacity 

through a record five spacewalks by four astronauts. 

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STS-73, Oct. 20 to Nov. 5, 1995, was the second flight of the United States Microgravity 

Laboratory. The mission focused on materials science, biotechnology, combustion 

science, the physics of fluids, and numerous scientific experiments housed in the 

pressurized Spacelab module. 

STS-82, Feb. 11-21, 1997, was the second Hubble Space Telescope (HST) maintenance 

mission. During the flight, the crew retrieved and secured the HST in Discovery's 

payload bay. In five spacewalks, two teams installed two new spectrometers and eight 

replacement instruments, as well as replacing insulation patches over three 

compartments containing key data processing, electronics and scientific instrument 

telemetry packages. Following completion of upgrades and repairs, HST was boosted 

to a higher orbit and redeployed. 

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Nikolai Budarin, Mission Specialist 4 (Up), 49 (RSC-Energia) 

Seating: Middeck for launch. 

Responsibilities: Budarin will serve as flight engineer 1 (FE1) of Expedition 6 and initially 

oversee the transfer and installation of the seat liners in the Soyuz spacecraft, which serves 

as the emergency rescue vehicle when the shuttle is not present. Budarin would pilot the 

Soyuz, if needed, and manages the equipment and operation of the Russian segment. 

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PERSONAL DATA 

Born April 29, 1953, in Kirya, Chuvashia (Russia). Married to Marina Lvovna Budarina (nee 

Sidorenko). There are two sons in the family, Dmitry and Vladislav. His hobbies include 

fishing, skiing, picking mushrooms. His father, Mikhail Romanovich Budarin, died in 1984. 

His mother, Alexandra Mikhailovna Budarina, died in 1986. 

EDUCATION

Graduated from the S.Ordzhonikidze Moscow Aviation Institute in 1979 with a mechanical 

engineering diploma. 

SPECIAL HONORS 

Awarded the titles of Hero of Russia, and a Pilot-Cosmonaut of the Russian Federation 

EXPERIENCE 

Since 1976 Budarin has occupied the positions of engineer and leading engineer at the 

RSC ENERGIA. In February 1989 he was enrolled in the ENERGIA cosmonaut 

detachment as a candidate test cosmonaut. 

From September 1989 to January 1991, he underwent a complete basic space training 

course at the Gagarin Cosmonaut Training Center and passed a State examination. 

Budarin is qualified as a Test Cosmonaut. 

From February 1991 to December 1993, he took an advanced training course for the 

Soyuz-TM transport vehicle and the Mir Station flight. 

From June 27 to Sept. 11, 1995, Budarin participated in a space mission as a board 

engineer of the 19th long-term expedition launched by the space shuttle and landed by the 

Soyuz TM-21 transport vehicle. 

From Jan. 28 to Aug. 25, 1998, he participated in a space mission as a board engineer of 

the 25th long-term expedition aboard the Mir Orbital Station. 

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Don Pettit, Mission Specialist 5 (Up), 47 (Ph.D.) 

Seating: Middeck for launch. 

Responsibilities: Pettit serves as flight engineer 2 (FE2) of Expedition 6 and will back up 

Whitson, if needed, during station robotic arm operations during the early stages of the P1 

Truss’ handoff from the shuttle’s robot arm to the station’s. During his four-month stay on 

the ISS, Pettit will serve as NASA ISS Science Officer and prime operator of the ISS robotic 

arm. 

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PERSONAL DATA

Born April 20, 1955, in Silverton, Ore. Married. Two children. 

EDUCATION

Graduated from Silverton Union High School, Silverton, Ore., in 1973; received a bachelor 

of science degree in chemical engineering from Oregon State University in 1978 and a 

doctorate in chemical engineering from the University of Arizona in 1983. 

EXPERIENCE

Staff scientist at Los Alamos National Laboratory, Los Alamos, N.M., from 1984-1996. 

Projects included reduced gravity fluid flow and materials processing experiments on board 

the NASA KC-135 airplane, atmospheric spectroscopy measurements on noctolucent 

clouds seeded from sounding rocket payloads, volcano fumarole gas sampling on active 

volcanos, and problems in detonation physics applied to weapon systems. He was a 

member of the Synthesis Group, slated with assembling the technology to return to the 

moon and explore Mars (1990), and the Space Station Freedom Redesign Team (1993). 

NASA EXPERIENCE

Selected by NASA in April 1996, Pettit reported to the Johnson Space Center in August 

1996. Having completed two years of training and evaluation, he is qualified for flight 

selection as a mission specialist. Initially, he was assigned technical duties in the Astronaut 

Office Computer Support Branch. 

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Sergei Treschev, Mission Specialist 3 (Down), 44 (RSC-Energia) 

Seating: Middeck for landing. 

Responsibilities: Treschev served as the Expedition 5 Flight Engineer 2 during his fivemonth stay on the International Space Station. 

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PERSONAL DATA

Born Aug. 18, 1958, in Volynsky District, Lipetsk Region (Russia). Married to Elvira 

Victorovna Trescheva. They have two sons, Dmitry and Alexy. His father is Yevgeny 

Georgievich Treschev, and his mother is Nina Davydovna Trescheva. His hobbies include 

soccer, volleyball, ice hockey, hiking, tennis, music, photography, and video. 

EDUCATION

Graduated from the Moscow Energy Institute in 1982. 

EXPERIENCE

From 1982 to 1984, Treschev served as a group leader in an Air Force regiment. He 

worked as a foreman and as an engineer at the RSC ENERGIA from 1984 to 1986. His 

responsibilities included the analysis and planning of cosmonaut activities aboard the Mir 

and their in-flight technical training. He also developed technical documentation and, 

together with the Yuri Gagarin Cosmonaut Training Center, coordinated all facets of 

cosmonaut training. His duties also included crew support and training for descent and 

emergency escape scenarios aboard the Mir. He also participated as a test operator during 

tests of the ground-based complex (transport vehicle/Mir core module/KVANT-2 module 

docked configuration) to optimize the Life Support System of ЭУ367/734. 

In 1992, he enrolled in the RSC ENERGIA cosmonaut detachment, and from 1992 to 1994 

he completed the basic cosmonaut training course. Treschev spent the next three years 

(1994 to 1996) in advanced test cosmonaut training. 

From June 1997 to February 1998, Treschev trained as a flight engineer for the Mir station 

backup Exp-25 crew. 

From June 1999 to July 2000 he trained as a flight engineer for the Soyuz-TM backup ISS 

contingency crew. 

Initially, he trained as backup to the ISS Expedition 3 crew. 

Since June 7, 2002, Treschev has served as International Space Station (ISS) Increment 5 

flight engineer. 

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Valery Korzun, Mission Specialist 4 (Down), 

49 (Col., Russian Air Force) 

Seating: Middeck for landing. 

Responsibilities: Korzun served as the Expedition 5 commander during his five-month 

stay on the International Space Station. He will oversee the leak checks and hatch 

operations after Endeavour’s docking. Korzun also will serve as the backup choreographer 

during the first of the three spacewalks by Lopez-Alegria and Herrington. 

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PERSONAL DATA

Born March 5, 1953, in Krasny Sulin. Korzun and his wife Elana have one son, Nikita. His 

father is Korzun Grigori Andreevich, and his mother, Korzun Maria Arsentievna. 

EDUCATION

1974 graduate of the Kachin Military Aviation College; Commander Department of the 

Gagarin Air Force Academy, 1987. 

SPECIAL HONORS

Awarded six Air Force Medals. 

EXPERIENCE

After graduation from the Military College in 1974, he served as pilot, senior pilot, flight 

section leader, and ultimately commander of a Russian Air Force squadron. In 1987, after a 

successful tour as commander of the Gagarin Military Air-Force Academy, he was selected 

as a cosmonaut for training at the Gagarin Cosmonaut Training Center. 

In December 1987 he began cosmonaut training and was certified as a test-cosmonaut in 

June 1989. 

From September 1989 through September 1992, he trained for spaceflight as part of the 

test-cosmonauts group and from October 1992 to March 1994 he underwent extensive 

training as commander of the "Soyuz TM" rescue spacecraft. He also trained as a group 

member for flight on board the orbital complex Mir from March 1994 to June 1995. 

Korzun also served as deputy director of the 27KC crew flight training complex as crew 

communication supervisor from March 1994 to January 1995. 

Korzun is a 1st class military pilot and has logged 1,473 hours, primarily in four aircraft 

types. He is also an instructor of parachute training, and has completed 377 parachute 

jumps. 

In August 1996 Korzun completed training as commander for the Mir-22/ NASA-3 and 

"Cassiopia" (sponsored by CNES) programs. 

On March 2, 1997 Korzun returned to Earth after completing a 197-day flight on board the 

Mir. The program included joint flights with NASA/Mir 2, 3 and 4 astronauts, as well as 

astronauts from France and Germany. During the mission, Korzun performed two 

spacewalks totaling 12 hours and 33 minutes. 

Since June 7, 2002, Korzun has served as International Space Station Increment 5 

commander. 

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Peggy Whitson, Mission Specialist 5 (Down), 42 (Ph.D.) 

Seating: Middeck for landing. 

Responsibilities: Whitson served as the Expedition 5 Flight Engineer 1 and NASA ISS 

Science Officer during her five-month stay on the International Space Station. She is the 

primary station robotic arm operator throughout the installation of the P1 Truss onto the 

station and the first spacewalk, and will back up Bowersox throughout the second and third 

spacewalks. 

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PERSONAL DATA

Born Feb. 9, 1960, in Mt. Ayr, Iowa. Hometown is Beaconsfield, Iowa. Married to Clarence 

F. Sams, Ph.D. She enjoys windsurfing, biking, basketball, water skiing. 

EDUCATION

Graduated from Mt. Ayr Community High School in 1978; received a bachelor of science 

degree in biology/chemistry from Iowa Wesleyan College in 1981, and a doctorate in 

biochemistry from Rice University in 1985. 

AWARDS/HONORS

Two patents approved (1997, 1998); Group Achievement Award for Shuttle-Mir Program 

(1996); American Astronautical Society Randolph Lovelace II Award (1995); NASA Tech 

Brief Award (1995); NASA Space Act Board Award (1995, 1998); NASA Silver Snoopy 

Award (1995); NASA Exceptional Service Medal (1995); NASA Space Act Award for Patent 

Application; NASA Certificate of Commendation (1994); Submission of Patent Disclosure 

for "Method and Apparatus for the Collection, Storage, and Real Time Analysis of Blood 

and Other Bodily Fluids” (1993); Selected for Space Station Redesign Team (March-June 

1993); NASA Sustained Superior Performance Award (1990); Krug International Merit 

Award (1989); NASA-JSC National Research Council Resident Research Associate (1986-

1988); Robert A. Welch Postdoctoral Fellowship (1985-1986); Robert A. Welch Predoctoral 

Fellowship (1982-1985), Summa Cum Laude from Iowa Wesleyan College (1981); 

President's Honor Roll ( 1978-81); Orange van Calhoun Scholarship (1980); State of Iowa 

Scholar (1979); Academic Excellence Award (1978). 

EXPERIENCE

From 1981 to 1985, Whitson conducted her graduate work in biochemistry at Rice 

University as a Robert A. Welch Predoctoral Fellow. Following completion of her graduate 

work she continued at Rice as a Robert A. Welch Postdoctoral Fellow until October 1986. 

Following this position, she began her studies at NASA Johnson Space Center as a 

National Research Council Resident Research Associate. From April 1988 until September 

1989, Whitson served as the Supervisor for the Biochemistry Research Group at KRUG 

International, a medical sciences contractor at NASA-JSC. In 1991-1997, Whitson was also 

invited to be an Adjunct Assistant Professor in the Department of Internal Medicine and 

Department of Human Biological Chemistry and Genetics at University of Texas Medical 

Branch, Galveston, Texas. In 1997, Whitson began a position as Adjunct Assistant 

Professor at Rice University in the Maybee Laboratory for Biochemical and Genetic 

Engineering. 

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NASA EXPERIENCE

From 1989 to 1993, Whitson worked as a research biochemist in the Biomedical 

Operations and Research Branch at NASA-JSC. In 1990, she gained the additional duties 

of research advisor for the National Research Council Resident Research Associate. From 

1991-1993, she served as technical monitor of the Biochemistry Research Laboratories in 

the Biomedical Operations and Research Branch. From 1991-1992 she was the payload 

element developer for Bone Cell Research Experiment (E10) aboard SL-J (STS-47), and 

was a member of the US-USSR Joint Working Group in Space Medicine and Biology. In 

1992, she was named the project scientist of the Shuttle-Mir Program (STS-60, STS-63, 

STS-71, Mir 18, Mir 19) and served in this capacity until the conclusion of the Phase 1A 

Program in 1995. From 1993-1996 Whitson held the additional responsibilities of the 

deputy division chief of the Medical Sciences Division at NASA-JSC. From 1995-1996 she 

served as co-chair of the U.S.-Russian Mission Science Working Group. In April 1996, she 

was selected as an astronaut candidate and started training, in August 1996. Upon 

completing two years of training and evaluation, she was assigned technical duties in the 

Astronaut Office Operations Planning Branch and served as the lead for the Crew Test 

Support Team in Russia from 1998-99. 

Since June 7, 2002, Whitson has been living and working aboard the International Space 

Station. 

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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. 

About 21⁄2 hours before the scheduled docking time on Flight Day 3, Endeavour will reach 

that point, about 50,000 feet behind the ISS. 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. 

This view of the space shuttle Atlantis was photographed by an Expedition 5 

crewmember on board the International Space Station (ISS) during STS-112 

rendezvous and docking operations. The S-One (S1) Truss, similar to this mission’s 

P-One (P1) Truss, can be seen in Atlantis’ cargo bay. 

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 final 

approach, Endeavour can do as many as four small mid-course corrections at regular 

intervals. Just after the fourth correction is completed, Endeavour will reach a point about 

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half a mile below the station. There, about an hour before the scheduled docking, 

Commander Jim Wetherbee will take over manual control of the approach. 

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

station, from which he will begin a quarter-circle of the ISS, slowly moving to a position in 

front of the complex, in line with its direction of travel. Pilot Paul Lockhart will help 

Wetherbee in controlling Endeavour’s approach. Mission Specialist John Herrington also 

will play key roles in the rendezvous, using a handheld laser ranging device and acting as a 

backup in operation of the docking mechanism to latch the station and Endeavour together 

after the two spacecraft make contact. Mission Specialist Michael Lopez-Alegria will 

operate the docking system and back up Herrington on the handheld laser. 

Wetherbee will fly the quarter-circle of the station while slowly closing in on the complex, 

stopping at a point a little more than 300 feet directly in front of the station. From there, he 

will begin slowly moving Endeavour toward the station at about a tenth of a mile per hour. 

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

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

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

pause to check the alignment. 

A close-up view of the ISS docking adapter 

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For Endeavour’s docking, Wetherbee will maintain the shuttle’s speed relative to the station 

at about one-tenth of a foot per second (while both Endeavour and the space station are 

traveling at about five miles a second), and keep the docking mechanisms aligned to within 

a tolerance of three inches. When Endeavour makes contact with the station, preliminary 

latches will automatically attach the two spacecraft. Immediately after Endeavour docks, 

the shuttle’s steering jets will be deactivated to reduce the forces acting at the docking 

interface. Shock absorber-like springs in the docking mechanism will dampen any relative 

motion between the shuttle and the station. 

Once that motion between the spacecraft has been stopped, Lopez-Alegria will secure the 

docking mechanism, sending commands for Endeavour’s docking ring to retract and to 

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

Undocking, Separation and Flyaround 

Once Endeavour is ready to undock, Lopez-Alegria will send a command to release the 

docking mechanism. At initial separation of the spacecraft, springs in the docking 

mechanism will push the shuttle away from the station. Endeavour’s steering jets will be 

shut off to avoid any inadvertent firings during this initial separation. 

Once Endeavour is about two feet from the station, with the docking devices clear of one 

another, Lockhart will turn the steering jets back on and fire them to very slowly move 

away. From the aft flight deck, Lockhart will manually control Endeavour within a tight 

corridor as she separates from the ISS, essentially the reverse of the task performed by 

Wetherbee just before Endeavour docked. 

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

close flyaround of the station, much like the one he did on STS-111 in June, circling the 

complex about one and a quarter times. Lockhart will pass a point directly above the 

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

the station for a second time. At that point, passing above the orbiting laboratory, Lockhart 

will fire Endeavour’s jets for final separation from the station. The flyaround should take 

about an hour and 20 minutes after undocking. 

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Spacewalks 

STS-113 Extravehicular Activity 

Three spacewalks are scheduled for the STS-113 (11A) mission of Endeavour to the 

International Space Station. The spacewalks will be performed on alternate days, on the 

crew’s flight days four, six and eight. Endeavour Mission Specialists Michael Lopez-Alegria 

and John Herrington will perform all three. 

STS-113 Spacewalkers Michael Lopez-Alegria (left) and John Herrington (right) 

Lopez-Alegria, EV1 (EV stands for Extravehicular Activity) will wear the spacesuit marked 

with solid red stripes, while Herrington, EV2, will wear an all-white spacesuit. Each 

spacewalk will last about 61⁄2 hours. Lopez-Alegria has conducted two previous 

spacewalks. This will mark the first spacewalks for Herrington. 

The spacewalks focus on installation and hookup of the Port 1 (P1) Truss, the 45-foot-long 

third part of the station’s Integrated Truss Structure (ITS) to the Starboard 0 (S0) Truss, the 

center of the ITS. The ITS eventually will have 11 segments and stretch 356 feet from end 

to end. It will support four virtually identical solar array assemblies, including the one now 

atop the P6 Truss of the ISS, and radiators to cool the station. The truss, the backbone of 

the station, also will support experiments. It already boasts a railroad track with a mobile 

base for the station’s robotic arm, Canadarm2. 

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Astronaut John B. Herrington, STS-113 mission specialist, participates in an 

Extravehicular Mobility Unit (EMU) fit check in a Space Station Airlock Test Article 

(SSATA) in the Crew Systems Laboratory at the Johnson Space Center (JSC). 

All the spacewalks will be conducted from the station’s Joint Airlock Quest. Before each, 

Lopez-Alegria and Herrington will use the ISS Exercise EVA Protocol. Designed to purge 

nitrogen from the body, the protocol involves breathing pure oxygen while exercising 

vigorously. It eliminates the need to spend many hours at reduced cabin pressure and 

allows hatches between the shuttle and the station to remain open. The protocol was first 

used during STS-104 during the first spacewalk from the Joint Airlock installed earlier 

during that mission. 

Endeavour Pilot Paul Lockhart will be the Intravehicular (IV) crewmember, offering advice 

and coordinating spacewalk activities. Primary Canadarm2 operator during the spacewalks 

will be Expedition 5 crewmember Peggy Whitson, with help from Expedition 6 Commander 

Ken Bowersox and Expedition 6 Flight Engineer Don Pettit. Endeavour Commander Jim 

Wetherbee will operate the shuttle’s robotic arm, providing video and documentation. 

Lockhart and Expedition 5 Commander Valery Korzun will help with spacewalk preparation 

and be with Lopez-Alegria and Herrington in the Joint Airlock during depressurization to 

10.2 psi. 

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Spacewalk No. 1, Flight Day Four: Connect power, data and fluid umbilicals 

between S0 and P1, release Crew and Equipment Translation Aid (CETA) launch 

locks, install Spool Positioning Devices (SPDs), drag link removal, and install 

Node Wireless video system External Transceiver Assemblies (WETA). 

Before Lopez-Alegria and Herrington emerge from the airlock, Wetherbee will use the 

shuttle’s robotic arm to grapple P1 and lift it from the payload bay, then hand it off to the 

station’s Canadarm2, operated by Whitson and Bowersox. They will move P1 to the end of 

S0. After a claw attaches itself to P1 and draws it into position and bolts secure ends of the 

two segments, Lopez-Alegria and Herrington will emerge from the Joint Airlock and begin 

setting up for the first spacewalk. 

Once he is clear of the airlock, Herrington will move to the rail lines along P1, where he will 

release CETA cart launch latches, a two-hour and 20-minute job. The task involves 

releasing a total of 24 bolts. First among them are the cart’s brake system bolts; their 

removal enables the CETA’s brakes to be used. 

Meanwhile, Lopez-Alegria will maneuver to the cable tray on the bottom of P1. Working 

from a portable foot restraint, he will open covers of cable trays on the lower sides of S0 

and P1, then demate connectors on the S0 side from temporary attachment points and 

connect their free ends to receptacles on P1. 

Astronauts Michael E. Lopez-Alegria (left) and John B. Herrington, both STS-113 

mission specialists, use the virtual reality lab at the Johnson Space Center (JSC) to 

train for their duties aboard the space shuttle Endeavour.

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After that 45-minute task, Lopez-Alegria will begin installation of four 11⁄2-inch SPD on Flex 

Hose Rotary Coupler (FHRC) Quick Disconnects (QDs). He then will move inboard along 

P1 to the truss’ bay 12 and install two more 11⁄2-inch SPDs. 

SPDs are devices that maintain the QDs, in ammonia lines that are part of the station’s 

cooling system, in a position to enable them to function optimally. The installation of the 

11⁄2-inch SPDs involves installing the aft part of the SPD, then moving a bail (QD valve) 

back about 1⁄4-in and installing the forward part of the SPD. This keeps the QD valve in a 

fixed position. 

Back together again, Herrington and Lopez-Alegria move on to P1’s starboard drag link, 

located on the forward face of the truss. 

They will work together to release that drag link, a large metal rod used as a launch 

restraint. Lopez-Alegria will release a bolt attaching the drag link to P1, while Herrington 

releases a similar bolt attaching the drag link to the keel. Lopez-Alegria takes the drag link 

to its stowage location on the P1 framework and attaches it with Herrington’s assistance. 

The processes are repeated on the P1 port drag link. 

That 30-minute task completed, Lopez-Alegria moves to the cable tray atop P1. There he 

will make additional connections, opening thermal covers over cable trays atop S0 and P1, 

then demating connectors on the S0 side from temporary attachment points and connecting 

their free ends to receptacles on P1. 

After that task, Lopez-Alegria and Herrington, who has done some additional work on the 

CETA, will combine on the final major task of the spacewalk, a two-hour installation on the 

Unity Node of the first WETA, designed to support spacewalkers’ helmet cameras. 

Lopez-Alegria moves to the P1’s starboard keel pin, retrieves the WETA stanchion and 

takes it to the Joint Airlock. There he and Herrington will spend about 15 minutes attaching 

the WETA to the stanchion. Herrington retrieves the WETA from its temporary airlock 

stowage position. While Lopez-Alegria holds the WETA in place, Herrington uses a pistolgrip tool to secure a center jacking bolt and then two outer bolts. 

Lopez-Alegria, with the WETA, and Herrington move to the installation location on the 

node. With help from Herrington, Lopez-Alegria secures it by driving a stanchion bolt. 

Subsequently he mates three stanchion power and data connectors to the node. 

After about half an hour of EVA cleanup the spacewalkers will re-enter the airlock. 

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Spacewalk No. 2, Flight Day Six: Fluid Jumper Installation, keel pin removal, P1 

WETA installation and CETA relocation. 

Once they are out of the airlock and setup is complete, Lopez-Alegria and Herrington move 

to a point at the junction of S0 and P1 for a two-hour installation of fluid jumpers to move 

ammonia between the two. The two release two jumpers on S0, then move to the jumper 

install position. 

Lopez-Alegria will mate and install SPDs on two jumper connections on the S0 side, while 

Herrington performs a similar task on the P1 side. Each connection will involve a threeminute leak check. Lopez-Alegria and Herrington reinstall the thermal booties and together 

they close their respective ends of the P1 and S0 utility tray shrouds. Then Herrington and 

Lopez-Alegria, the latter on the CETA cart, move on to P1’s starboard keel pin. 

Lopez-Alegria sets the CETA brakes, and at the worksite releases the top keel pin bolt, 

rotates the keel pin, then reinstalls the bolt. He then removes the lower keel pin bolt, frees 

the keel pin and reinstalls the bolt. Herrington moves the CETA along with Lopez-Alegria 

and the keel pin, a few feet down the tracks. From the new location, Lopez-Alegria installs 

the keel pin in stowage brackets inside the P1 framework, completing the half-hour task. 

As part of Crew Equipment Interface Test activities, STS-113 Spacewalkers Michael 

Lopez-Alegria (left) and John Herrington look over tools that will be carried on the 

mission.

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Working together, the spacewalkers move on to installation of the second WETA, on the P1 

itself. This installation should take about an hour, and is completed in a manner similar to 

the Node WETA installation. 

While Lopez-Alegria completes the connections to the P1 WETA, Herrington will perform a 

test of the Segment-to-Segment Attachment System on the outboard end of P1. LopezAlegria and Herrington then move on to release of the port keel pin, repeating the tasks 

performed during release of the starboard keel pin. 

Finally, they will spend a little more than an hour moving the CETA launched on P1 to S1. 

Herrington will be on the end of Canadarm2, operated by Pettit, for this activity. The two 

spacewalkers will release the CETA from its tracks, move it around the Mobile Transporter 

(which supports the Mobile Base System for the Canadarm2), attach it to the tracks again 

and couple it to its sister CETA. 

Spacewalkers will re-enter the airlock after about half an hour of cleanup operations. 

Spacewalk No. 3, Flight Day Eight: SPD installation, Circuit Interrupt Device (CID) 

Main Bus Switching Unit (MBSU) reconfiguration and connect Ammonia Tank 

Assembly (ATA) umbilicals. 

The third spacewalk is devoted almost entirely to installation of SPDs. 

After setup, Herrington will enter a bay in the SO Truss and operate two CIDs allowing 

ground controllers to begin work on the MBSU reconfiguration. From there, Herrington will 

move to the top center of the P1 Truss and attach a foot restraint at the end of the 

Canadarm2. Herrington will then ingress the foot restraint and Pettit, at the arm’s controls, 

will maneuver him to the starboard end of the P1. There Herrington will begin the 

installation of a dozen 1-inch SPDs on lines linking the Radiator Beam Valve Modules 

(RBVMs) and the radiator junction box. 

He then gets off the arm and continues with the 1-inch SPD installations, moving out 

toward the outboard end of the P1. During this three-hour-plus phase of the spacewalk, 

Herrington will install a total of 18 SPDs. 

Meanwhile Lopez-Alegria installs two 1-inch SPDs at the Z1 to P6 interface, and then 

moves to the bottom of the Z1 Truss at its junction with the U.S. laboratory Destiny. There 

he will install two 1-inch SPDs. Next he moves to the Moderate Temperature Loop Heat 

Exchanger on the lab’s exterior, removes a Micro Meteoroid Orbital Debris shield and 

installs two 1-inch SPDs, and finally reinstalls the shield. 

His next task is at the pump module on P1. There he will install three 11⁄2-inch SPDs and a 

half-inch SPD. 

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Lopez-Alegria will take a break from SPD installation with his next activity, reconfiguration 

of electrical harnesses that route through Main Bus Switching Units. 

That 40-minute task, involving relocating two dustcaps and changing four cable 

connections from two foot restraint positions in the interior of the S0 Truss in bay 4, is 

completed by Lopez-Alegria about four hours into the spacewalk. Following the RBVM SPD 

installation, Herrington will focus his attention on the Ammonia Tank Assembly (ATA) 

umbilicals. The P1 ATA is on the starboard-most bay of P1 on the aft face. That 40-minute 

job, linking the ATA to ammonia lines in the station’s cooling system and the Nitrogen Tank 

Assembly lines to the ATA, involves relocation of four quick disconnect caps and hookup of 

four connections. Herrington also will install one 1⁄2-inch SPD during that process. 

Herrington’s final task of spacewalk No. 3 is installation of three 11⁄2-inch and one 1⁄2-inch 

SPDs on S1 Pump Module connector lines. Lopez-Alegria also will move to S1, to install 

four 11⁄2-inch SPDs on Flex Hose Rotary Coupler (FHRC) QDs. Those tasks accomplished, 

both spacewalkers will begin an EVA cleanup period and then move into the airlock. 

Lopez-Alegria and Herrington install more than 40 SPDs during STS-113 spacewalks. 

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Payloads 

Payload Overview 

The primary cargo element to be delivered on Mission 11A is the first port truss segment, 

Port 1 (P1), of the main International Space Station (ISS) Integrated Truss Structure (ITS). 

The ITS will eventually be used to support the four power-generating Photo-Voltaic 

Modules (PVMs) of the ISS, the permanent External Active Thermal Control Subsystem 

(EATCS) and will also provide a translation path for the Mobile Servicing System (MSS) 

along specially designed truss rails. The truss rails allow the Space Station Remote 

Manipulator System (SSRMS) to be positioned at various locations along the truss for 

performing maintenance tasks, element installations, and providing EVA assistance. 

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At Launch Complex 39A, the payload canister doors are open to reveal the P1 Truss 

before transfer to the Payload Changeout Room. 

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Integrated within the P1 Truss segment are various hardware components and their 

associated cabling for powering and controlling the port side systems of the ITS. P1 is preintegrated with Ultra-High Frequency (UHF) communication equipment, Thermal Radiator 

Rotary Joint (TRRJ), three EATCS radiators, DC-to-DC Converter Unit (DDCU), Remote 

Power Controller Module (RPCM), Nitrogen Tank Assembly (NTA), Ammonia Tank 

Assembly (ATA), Pump Module Assembly (PMA) and the second Crew Equipment and 

Translation Aid (CETA) cart, CETA Cart 2. 

The middeck of Endeavour will be filled with Extravehicular Activity (EVA) tools and 

equipment, crew rotation equipment, Operations Data File (ODF), Crew Health Care 

System (CheCS), crew provisions, ISS Utilization payloads, which includes Human 

Research Facility (HRF) resupply and three Payload Mounting Panels (PMPs) to be 

replaced by returning powered payloads, Portable Computer System (PCS) items, and 

photo/TV equipment. 

The Return Complement (RC) consists of crew rotation hardware, CheCS resupply, excess 

integration hardware, Russian hardware, and returning utilization complement, which 

consists of HRF passive stowage, Commercial Generic Bioprocessing Apparatus (CGBA), 

Single Thermal Enclosure System (STES), and the Plant Growth Bioprocessing Apparatus 

(PGBA). 

Secondary Payloads 

The MEMS-based Pico Satellite (PICOSAT) Inspector (MEPSI) payload consists of a 

launcher, or garage, which houses a set of two small deployable satellites, referred to as 

PICOSATs. Each PICOSAT weighs about 1 kilogram (2.2046 pounds). The two miniature 

satellites will be attached to each other with a tether on early flights. The launcher is 

mounted to a standard space shuttle-provided Adaptive Payload Carrier (APC). The total 

assembly, including launcher, firing circuit and PICOSATs, is referred to as the PICOSAT 

Launcher Assembly (PLA). The total weight, including the PLA and the attachment bracket, 

is about 8 kilograms (18 pounds). 

After release, the PICOSATs operate on battery power for several days to complete 

mission objectives. 

Payloads of Opportunity 

None. 

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Payloads 

P1 Truss to Join Mirror Image S1 in Space 

The Port One (P1) Truss is slated for launch to the International Space Station aboard 

space shuttle Endeavour no earlier than Nov. 10, 2002, from Kennedy Space Center, Fla. 

The truss is the next major addition to the space station’s 11-segment Integrated Truss 

Structure that will eventually span more than 300 feet to carry power, data and temperature 

control for the orbital outpost’s electronics. When completed, the ends of the truss structure 

will also house the station’s solar arrays. 

During Endeavour’s mission, spacewalkers assisted by the ISS robotic arm, will attach P1 

to the Starboard Zero (S0) Truss already in place aboard the U.S. laboratory module 

Destiny. Astronauts will make three spacewalks to complete installation and assembly of 

the P1. Space shuttle Atlantis delivered S1 to the ISS in October 2002 and it is attached to 

the other side of the S0 Truss. 

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The 27,506 lb. P1 Truss is primarily an aluminum structure that is 45 feet long, 13 feet high 

and 15 feet wide. The structure, along with one CETA (Crew and Equipment Translation 

Aid) cart, costs about $390 million. 

Boeing designed the P1 Truss in Huntington Beach, Calif., and began construction there in 

January 1997. Work on P1 was completed in Huntsville, Ala., in June 2000. The P1 moved 

to Kennedy Space Center, Fla., in July 2000 for flight processing. Boeing delivered the P1 

to NASA in November 2001 for final preparations and preflight checks. 

Both P1 and S1 trusses will provide structural support for the Active Thermal Control 

System (ATCS), the Mobile Transporter, a CETA cart and antennas. The S1 has an S-band 

system; the P1 a UHF system. Both trusses also have mounts for cameras and lights. P1 

also has a port for an S-band antenna. The S-band system is located on the P6 Truss and 

will be installed by spacewalkers on an upcoming mission. 

Additionally, both S1 and P1 carry three radiators each containing eight panels as part of 

the ATCS or cooling system for the space station’s electronics. The radiators are deployed 

in orbit and use 99.9 percent pure ammonia as compared to 1 percent strength found in the 

household variety. Ammonia rather than water is used because of its low freezing point and 

ability to transfer heat. 

The radiator assembly also rotates to keep itself in the shade and away from the sun. Each 

radiator has 18 launch locks securing the assembly during launch which will be 

deployed/stowed during a spacewalk. The Thermal Radiator Rotary Joint (TRRJ) rotates 

the three radiator structures in a 105-degree span either way. The TRRJ also transfers 

power and ammonia to the radiators. 

The addition of P1 also extends the Mobile Transporter (MT) rail line. The MT car travels 

along the length of the truss structure and carries spacewalkers, tools, construction items 

and the space station robotic arm. Flying aboard P1 is one of two CETA carts that move 

spacewalkers along the MT rails to worksites along the truss structure. The cart is manually 

operated by a spacewalker and can also be used as a work platform. S1 and P1 carry one 

cart each. 

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Payloads 

International Space Station S1 and P1 Truss Summary 

The Starboard One (S1) and Port One (P1) trusses will be attached to the S0 Truss aboard 

the International Space Station. The trusses provide structural support for the Active 

Thermal Control System, Mobile Transporter (MT), Crew and Equipment Translation Aid 

(CETA) cart, camera/light operations, and S-band and UHF communications. Once in orbit, 

the S1 and P1 end bulkheads will be used as attachment points for the S0, P3 and S3 truss 

segments. 

The CETA cart moves spacewalkers along the MT rails to worksites along the truss 

structure. The cart is manually operated by a spacewalker and can also be used as a work 

platform. S1 and P1 carry one cart each. 

The Thermal Radiator Rotary Joint (TRRJ) rotates the three radiator structures in a 105-

degree span either way. The TRRJ also transfers power and ammonia to the radiators. 

Differences between S1 and P1 

There are very few differences between the S1 and P1 elements. The primary structure 

(bulkheads and longerons) of S1 and P1 are mirror images of each other. All parts are all 

coated with an optical anodized surface preparation. 

Another unique attribute of the two elements is their communication capability. The S1 was 

launched with an S-band antenna system, whereas P1 has a UHF capability. P1 also has a 

port for an S-band antenna. The S-band system is currently located on the P6 Truss and 

will be installed by spacewalkers on an upcoming mission. 

Both trusses house the Active Thermal Control System. This system acts like the cooling 

system on a car radiator except this system uses 99.9 percent pure ammonia (compared to 

1 percent in household products). The system will provide temperature control for the 

space station’s electronics. 

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Boeing technicians install a radiator on 

the Port One (P1) Truss inside the 

Kennedy Space Center, Fla., Space 

Station Processing Facility during 

summer 2002. The radiator will be used 

to control the temperature of the 

International Space Station’s 

electronics. 

Facts in brief: 

• Manufacturer: Boeing 

• Dimensions: 45 ft. x 15 ft. x 13 ft. 

• Weight: 27,717 lbs. (S1); 27,506 lbs. (P1) 

• Cost: $390 million each (one CETA cart launched on each truss element) 

• Structure: Primarily aluminum 

• Major components: Primary structure is made of anodized aluminum and includes 

seven bulkheads per segment, eight longerons per segment, heat transport 

subsystem, radiator support beam, on-orbit video camera, electrical equipment, Sband antenna system; UHF antenna system for P1 and the Thermal Radiator Rotary 

Joint (TRRJ). 

• Purpose: To carry power and data along the integrated truss structure to space 

station components. Also to provide active thermal protection to electrical 

components throughout the station. 

• Construction: P1: Boeing designed the P1 Truss in Huntington Beach, Calif., and 

began construction there in January 1997. Work on P1 was completed in Huntsville, 

Ala., in June 2000. The P1 moved to Kennedy Space Center, Fla., in July 2000 for 

flight processing. Boeing delivered the P1 to NASA in November 2001 for final 

preparations and preflight checks. S1: Started assembly at Boeing plant in 

Huntington Beach in May 1997; moved to Boeing facility in Huntsville in February 

1999 for completion and then to Boeing Florida Operations at Kennedy Space 

Center in October 1999 for flight processing. S1 handed off to NASA in November 

2001. 

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• Major subcontractors: Lockheed Martin, Honeywell, L3 Communications, Hamilton 

Sundstrand and Parker Symetrics. 

• Installation: S1 installed during mission STS-112/9A October 2002, P1 to be 

installed during STS-113/11A, November 2002. 

• Radiator assembly: The entire radiator beam assembly (upper portion of the 

elements) rotates to keep the radiators in the shade. There are 18 launch locks that 

keep this radiator beam assembly together during launch – all deployed/stowed by 

EVA. 

The Port One (P1) Truss for the International Space Station sits inside the Kennedy 

Space Center, Fla., Space Station Processing Facility during June 2002. The radiator 

assembly (covered by white thermal blankets) can be seen on top of the truss. Space 

shuttle Endeavour will deliver P1 during mission STS-113. 

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P1 Truss placement aboard ISS 

More info at: 

Space shuttle schedule -- http://www-pao.ksc.nasa.gov/kscpao/schedule/schedule.htm 

Mission info – http://spaceflight.nasa.gov 

Boeing ISS site – http://www.boeing.com/defense-space/space/spacestation/flash.html 

Truss photos – http://www.boeingmedia.com 

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Payloads 

Crew and Equipment Translation Aid (CETA) Cart 

What happens when Lockheed Martin and NASA CTSD team members engineer a solid, 

roughly 2,500-pound block of aluminum and transform it into a 142-pound frame assembled 

with more than 1,100 parts? You get the Crew and Equipment Translation Aid (CETA), a 

complex, dynamic mechanical translation device – NASA’s equivalent of a flatbed truck. 

The second of two CETAs, CETA 2, will launch this fall on STS-113, station assembly flight 

11A. 

CETA, one of the largest pieces of extravehicular activity (EVA) equipment built for the 

International Space Station (ISS), will accompany the first portside truss, called Port One 

(P1), to orbit. This truss will become the backbone of the four solar wing assemblies and 

will incorporate many orbital replaceable units (ORU). Installation and maintenance of 

these ORUs – for example batteries, the DC-to-DC converter, the Remote Power Controller 

Module, and the multiplexer/demultiplexer – is critical. At this time, NASA uses spacewalking crewmembers or robotics to repair or replace those units. The need for a work 

platform that could also provide the crew with a means of transporting themselves, the 

necessary tools and ORUs safely and easily along the truss became crucial. The SEATengineered CETA fulfills those requirements. 

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Crew and Equipment Translation Aid (CETA) Cart 2 

The CETA is launched as an integrated part of the P1 Truss segment. Once deployed on 

orbit, crewmembers can propel themselves and accompanying hardware manually along 

the Mobile Transporter (MT) rails. On orbit, the two CETA carts will be located one on each 

side of the MT for usage flexibility. If required, a cart may be moved to the other side of the 

MT to complement the other cart. The CETA has attachment points for other EVA 

hardware such as the ORU Transfer Device (OTD), also known as the Space Crane; 

Articulating Portable Foot Restraint (APFR); EVA Tool Stowage Device (ETSD); and a host 

of other small crew and equipment restraining tools. During ISS assembly operations, 

crewmembers will also use CETA as a work platform to reach 90 percent of the worksites 

safely. When not in use the CETAs will attach to the MT for stowage and become part of a 

“train” that allows the SSRMS to move freely along the truss. 

CETA is made of many components, including the following major subassemblies: 

• A main frame; 

• Launch restraints to ensure CETA is secured to the truss segment; 

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• A wheel/brake subsystem to move along the truss; 

• A dynamic brake for speed control and a parking brake for use at worksites; 

• Energy absorbers to reduce the impact of a hard stop; 

• Three swing arms to provide access to structures along side the truss; and 

• An ORU transfer flat bed for attaching ORUs. 

The first CETA cart, CETA 1, was launched with the Starboard One (S1) Truss on STS-112 

(9A) in October 2002. 

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Payloads 

MEPSI Pre-flight Clears Way for Rapid Space Access of 

Miniature Platforms on Space Shuttle 

The MEMS-based PICOSAT Inspector (MEPSI) experiment series will conduct its third 

space test mission as two miniature satellites are released on orbit from NASA’s STS-113 

shuttle mission. The tethered satellite pair, each measuring 4” x 4” x 5”, will be released 

from a specialized spring-loaded launcher assembly mounted on the sidewall of the space 

shuttle Endeavour en-route from the International Space Station (ISS). 

Funded by the Defense Advanced Research Projects Agency (DARPA), this “PICOSAT” 

mission represents a significant step forward in the development of an on-board 

autonomous inspection capability being directed by the Air Force Research Laboratory 

(AFRL) Information Directorate located in Rome, N.Y. Researchers at the Information 

Directorate envision MEPSI enhancing satellite command and control operations by 

providing active on-board imaging capability to assess spacecraft damage, monitor launch 

and deployment sequences, and augment servicing operations. This will provide the 

foundation for a rapid feedback capability for spacecraft operators to detect and respond to 

anomalies while maintaining continual service to their users, and enable ultimate spacecraft 

longevity. 

MEPSI is integrated and flown under the direction of the Department of Defense Space 

Test Program. Third in a series of incremental flight experiments (two previous flights, one 

in February 2000 and the other in September 2001, were deployed from the Air Force’s 

new OSP-Minotaur launch vehicle), the success of this mission also demonstrates a new 

capability for NASA’s shuttle program that allows for PICOSAT type payloads to be flown 

on virtually any shuttle mission. 

The two PICOSATs, built by The Aerospace Corporation and the NASA Jet Propulsion 

Laboratory (JPL), are adjoined by a 50-foot non-conducting tether to facilitate detection by 

Earth-based radar and keep them in radio range of each other. The objectives of the 

minimum three-day mission include: 

• Demonstration of a “new” 4-inch form factor launcher assembly approved for use in 

the shuttle cargo bay; 

• Establish communications and data exchange between the two PICOSATs and the 

ground station; 

• Exercise on-board Microelectromechanical Systems (MEMS) inertial measurement 

system; 

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• Implementation of MEMS RF switches in transmit/receive operation along the 

communications critical path; 

• Improved RF transmit power. 

Among the major challenges of this mission are to implement the greatest amount of 

science within a fairly minimal power budget. 

In addition to the primary mission of realizing the MEPSI concept, the PICOSATs serve as 

a low-cost test bed for progressive development and insertion of micro- and nanotechnologies into radically different space systems. The PICOSAT platform serves as an 

ideal means for proving revolutionary technologies and concepts without breaking the bank.

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Experiments 

Science Overview 

The STS-113 mission will mark the beginning of a new expedition aboard the International 

Space Station, with a new crew and a combination of new and continuing scientific 

exploration. 

The crew of Expedition 6 – the sixth crew to live and work on the orbiting outpost -- will be 

launched to the space station in November aboard space shuttle Endeavour. Endeavour 

will return the Expedition 5 crew to Earth. Expedition 6 is scheduled to end in March 2003. 

Several new experiments will be ferried to the orbiting outpost during Expedition 6. The 

Expedition will feature a total of 19 new or continuing investigations. New experiments are 

expected to lead to insights in the fields of medicine, materials, plant science, commercial 

biotechnology, and manufacturing. Several experiments begun on earlier expeditions will 

return to Earth, while several others will continue operating during Expedition 6. 

NASA’s Marshall Space Flight Center in Huntsville, Ala., manages all science research 

experiment operations aboard the Station, coordination of the science mission planning 

work of a variety of international sources, as well as payload training for the station crew 

and payload operations ground personnel. 

Experiments headed for the space station on STS-113 are: 

Microgravity Science Glovebox-Coarsening in Solid Liquid Mixture (CSLM), an experiment 

to investigate the interaction of small and large particles in a mixture that can have an effect 

on the strength of materials ranging from turbine blades to dental fillings and porcelain. 

This experiment will be the third conducted in the Glovebox. Space shuttle Endeavour 

ferried the Glovebox to the station in June. Built by the European Space Agency, the 

Glovebox features a sealed work area with windows and attached rubber gloves that allow 

crewmembers to work safely with experiments involving chemicals, fluids and burning or 

molten samples. 

Microgravity Science Glovebox-InSPACE, an experiment to obtain basic data on 

magnetorheological fluids -- a new class of "smart materials" that can be used to improve 

or develop new brake systems, seat suspensions, robotics, clutches, airplane landing gear, 

and vibration damper systems. 

Foot/Ground Reaction Forces During Spaceflight, an experiment to characterize the load 

on the lower body and muscle activity in crewmembers while working on the Station. The 

human life science experiment is expected to provide data that could help maintain crew 

health on long duration space missions. 

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Protein Crystal Growth Single-locker Thermal Enclosure System (PCG-STES): Proteins to 

be grown in the microgravity environment of the space station will arrive on the STS-113 

mission. A payload on two earlier station expeditions, the PCG-STES experiment facility 

will again provide a temperature-controlled environment for growing a new set of highquality crystals of selected proteins in microgravity for later analyses on the ground to 

determine the proteins’ molecular structure. Research may contribute to advances in 

medicine, agriculture and other fields. 

Zeolite Crystal Growth Furnace (ZCG): This experiment is sponsored by a commercial firm 

attempting to grow larger crystals in microgravity, with possible applications in chemical 

processes, electronic device manufacturing and other applications on Earth. New samples 

will be ferried up for processing in the ZCG furnace, which was first installed and used 

during Expedition Four. 

Experiments returning to Earth on STS-113 are: 

Protein Crystal Growth Single-locker Thermal Enclosure System (PCG-STES): Protein 

samples, ferried to the station aboard the STS-112 mission in October and crystallized 

during Expedition 5, will be carefully loaded aboard the shuttle for analysis soon after the 

shuttle lands. 

Zeolite Crystal Growth Furnace (ZCG): Samples processed during Expedition 5 will be 

stowed aboard the shuttle for return to Earth on STS-113. 

Solidification Using a Baffle in Sealed Ampoules (SUBSA): This Microgravity Science 

Glovebox experiment was designed to process crystals of indium antimonide, used to make 

semiconductors on Earth. The science objectives of this investigation were to test an 

automatically moving baffle, or barrier, designed to reduce movement of the melted 

material, to see if it could further reduce residual flow of the molten material caused by nonconvective forces. 

Microencapsulation Electrostatic Processing System (MEPS): Improvements in the 

manufacturing processes for enclosing liquids – including drugs – in microscopic capsules 

in microgravity conditions also were investigated. Samples processed during Expedition 5 

will be returned to Earth, while experiment hardware remains on board to support future 

experiments. 

On the Internet: 

For fact sheets, imagery and more on Expedition Six experiments and payload operations, 

click on http://www.scipoc.msfc.nasa.gov

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Experiments 

DSOs and DTOs 

Detailed Supplementary Objectives (DSOs) are space and life science investigations. Their 

purpose is to: 

• Determine the extent of physiological deconditioning resulting from spaceflight 

• Test countermeasures to those changes 

• 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 the space shuttle or space 

station hardware, systems and operations. 

Such experiments aboard during STS-113 are: 

DSO 490B 

Bioavailability and Performance Effects of Promethazine During Spaceflight, 

Protocol B 

Promethazine (PMZ) is the anti-motion sickness medication of choice for treating Space 

Motion Sickness (SMS) during shuttle missions. The side effects associated with PMZ 

include dizziness, drowsiness, sedation, and impaired psychomotor performance, which 

could impact crew performance of mission operations. Early anecdotal reports from 

crewmembers indicate that these central nervous system side effects of PMZ are absent or 

greatly attenuated in microgravity. 

The objectives are to: 

• Evaluate the effects of microgravity on PMZ bioavailability, performance, side effects 

and efficacy in the treatment of SMS 

• Establish dose-response relationship of PMZ and the bioavailability of PMZ through 

intramuscular (IM), oral, suppository routes of administration 

• Compare these results with preflight evaluations 

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DSO 493 

Monitoring Latent Virus Reactivation and Shedding in Astronauts 

The premise of this DSO is to determine the frequency of induced reactivation of herpes 

viruses, herpes virus shedding and clinical disease after exposure to the physical, 

physiological and psychological stressors associated with spaceflight. 

DSO 498 

Spaceflight and Immune Function 

The premise of this DSO is to characterize the effects of spaceflight on selected immune 

elements that are important in maintaining an effective defense against infectious agents. 

The roles of neutrophils, monocytes, and cytotoxic cells – important elements of the 

immune response – have not been studied adequately in the U.S. space program. These 

studies will complement ongoing and previous investigations in space immunology. 

This investigation is designed to determine the functional status of important elements of 

the immune response providing valuable data to help in the assessment of infectious 

disease risks associated with long-duration spaceflight. 

DSO 499 

Eye Movements and Motion Perception Induced by Off-Vertical Axis Rotation 

(OVAR) at Small Angles of Tilt After Spaceflight 

Sensorimotor adaptation to the absence of gravity during orbital flight leads to perceptual 

and motor coordination problems upon return to Earth. The hypothesis is that there are 

adaptive changes in how the central nervous system processes gravitational tilt information 

from the vestibular (otolith) system. Eye movements and perceptual responses during 

constant velocity off-vertical axis rotation (OVAR) will reflect changes in otolith function as 

crewmembers readapt to Earth’s gravity. The time course of recovery will be a function of 

flight duration (i.e., slower recovery for long-duration crewmembers). 

This DSO will examine changes in spatial neural processing of gravitational tilt information 

following adaptation to microgravity. Postflight oculomotor and perceptual responses 

during off-vertical axis rotation will be compared with preflight baselines to track the time 

course of recovery. Comparison of data from short-duration and long-duration (ISS) 

crewmembers will allow assessment of the effect of flight duration. 

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DSO 500 

Spaceflight-induced Reactivation of Latent Epstein-Barr Virus 

The combined effects of microgravity along with associated physical and psychological 

stress will decrease Epstein-Barr virus (EBV)-specific T-cell immunity and reactivate latent 

EBV in infected B-lymphocytes. 

This investigation will examine the mechanisms of spaceflight-induced alterations in human 

immune function and latent virus reactivation. Specifically, this study will determine the 

magnitude of immunosuppression as a result of spaceflight by: 

• Analysis of stress hormones 

• Quantitative analysis of EBV replication using molecular and serological methods 

• Determining virus-specific T-cell immune function 

DSO 503S 

Test of Midodrine as a Countermeasure Against Postflight Orthostatic 

Hypotension

Following exposure to spaceflight, upright posture can result in the inability to maintain 

adequate arterial pressure and cerebral perfusion (orthostatic or postural hypotension). 

This may result in presyncope (lightheadedness) or syncope (loss of consciousness) during 

re-entry or egress. 

The objective of this DSO is to evaluate a new pharmacological countermeasure for 

protection from postflight orthostatic hypotension. This experiment will measure the 

efficacy of midodrine in reducing the incidence and/or severity of orthostatic hypotension in 

returning astronauts. Efficacy will be evaluated with an expanded tilt test. 

DSO 632B 

Pharmacokinetics and Contributing Physiologic Changes During Spaceflight, 

Protocol B 

Physical, environmental and physiologic conditions of spaceflight will alter gastrointestinal 

(GI) function and physiology; these alterations will affect the pharmacokinetics of oral 

medications. 

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The objective of this DSO is to determine changes in the GI function and physiology in 

microgravity and examine the pharmacokinetics of orally administered pharmaceutical 

probe acetaminophen. 

Results from salivary pharmacokinetics of acetaminophen indicate absorption and 

bioavailability of oral liquid dosages may be better and more reliable than that of an 

equivalent solid dosage form. The comparisons were based on DSO 458, 

“Pharmacokinetics of Acetaminophen,” which had seven subjects taking Tylenol tablets, 

and DSO 622, “Gastrointestinal Function During Extended Duration Spaceflight,” which had 

four subjects taking Tylenol syrup. 

DSO 634 

Sleep-Wake Actigraphy and Light Exposure During Spaceflight 

Disruption of sleep during spaceflight, both short- and long-duration, is associated with 

inappropriately timed (non-24 hour) or insufficiently intense light exposure. Sleep 

disruption and circadian misalignment will lead to subjective dissatisfaction with selfreported sleep quality and daytime alertness. Both of these conditions are associated with 

insomnia and associated impairment of alertness and cognitive performance that could 

impair mission success. 

This experiment will use state-of-the-art ambulatory technology to monitor sleep-wake 

activity and light exposure patterns obtained in flight. This data should help better 

understand the effects of spaceflight on sleep as well as aid in the development of effective 

countermeasures for both short- and long-duration spaceflight. 

DTO 805 

Crosswind Landing Performance 

DTO 805 is to demonstrate the capability to perform a manually controlled landing in the 

presence of a 90-degree, 10-15 knots steady state crosswind. This DTO has been 

previously manifested on 73 flights and last flown on STS-112. 

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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 T-4 

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 onboardcomputers detected a problem with a coolant valve on main engine #2. The valve 

wasreplaced 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-3seconds 

following a problem with purge pressure readings in the oxidizer preburner onmain engine 

#2 Columbia’s three main engines were replaced on the launch pad, andthe flight was 

rescheduled behind Discovery’s launch on STS-56. Columbia finallylaunched on April 26, 

1993. 

(STS-51) August 12, 1993 

The countdown for Discovery’s third launch attempt ended at the T-3 second markwhen onboard computers detected the failure of one of four sensors in main engine #2which 

monitor the flow of hydrogen fuel to the engine. All of Discovery’s main engineswere 

ordered replaced on the launch pad, delaying the Shuttle’s fourth launch attemptuntil 

September 12, 1993. 

(STS-68) August 18, 1994 

The countdown for Endeavour’s first launch attempt ended 1.9 seconds before liftoffwhen 

on-board computers detected higher than acceptable readings in one channel of asensor 

monitoring the discharge temperature of the high pressure oxidizer turbopump inmain 

engine #3. A test firing of the engine at the Stennis Space Center in Mississippi 

onSeptember 2nd confirmed that a slight drift in a fuel flow meter in the engine caused 

aslight increase in the turbopump’s temperature. The test firing also confirmed a 

slightlyslower start for main engine #3 during the pad abort, which could have contributed 

tothe higher temperatures. After Endeavour was brought back to the Vehicle 

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AssemblyBuilding to be outfitted with three replacement engines, NASA managers set 

October2nd as the date for Endeavour’s second launch attempt. 

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. 

Fiveminutes and 45 seconds after launch, a sensor problem resulted in the shutdown 

ofcenter engine #1, resulting in a safe "abort to orbit" and successful completion of 

themission. 

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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 

inthe launch sequence after taking over from the Ground Launch Sequencer and before 

SolidRocket Booster ignition. 

ASCENT ABORTS 

Selection of an ascent abort mode may become necessary if there is a failure that 

affectsvehicle performance, such as the failure of a space shuttle main engine or an 

orbitalmaneuvering system. Other failures requiring early termination of a flight, such as a 

cabinleak, 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 

toa planned landing site. Contingency aborts are designed to permit flight crew 

survivalfollowing 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 

tothe 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 

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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). 

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). 

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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 maneuveringsystem 

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. 

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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. 

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. 

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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 

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Shuttle Reference Data 

Space Shuttle Main Engines 

Developed in the 1970s by NASA's Marshall Space Flight Center in Huntsville, Ala., the 

Space Shuttle Main Engine is the most advanced liquid-fueled rocket engine ever built. Its 

main features include variable thrust, high performance, reusability, high redundancy, and a 

fully integrated engine controller. 

The shuttle’s three main engines are mounted on the Orbiter aft fuselage in a triangular 

pattern. Spaced so that they are movable during launch, the engines are used – in 

conjunction with the Solid Rocket Boosters – to steer the shuttle vehicle. 

Each of these powerful main engines is 14 feet (4.2 meters) long, weighs approximately 

7,000 pounds (3,150 kilograms) and is 7.5 feet (2.25 meters) in diameter at the end of its 

nozzle. 

The engines operate for about eight-and-one-half minutes during liftoff and ascent -- 

burning more than 500,000 gallons (1.9 million liters) of super-cold liquid hydrogen and 

liquid oxygen propellants stored in the huge external tank attached to the underside of the 

shuttle. The engines shut down just before the shuttle, traveling at about 17,000 mph 

(28,000 kilometers per hour), reaches orbit. 

The Main Engine operates at greater temperature extremes than any mechanical system in 

common use today. The fuel, liquefied hydrogen at -423 degrees Fahrenheit (-

253 degrees Celsius) is the second coldest liquid on Earth. When it and the liquid oxygen 

are combusted, the temperature in the main combustion chamber is 6,000 degrees 

Fahrenheit (3,316 degrees Celsius), hotter than the boiling point of iron. 

The main engines use a staged combustion cycle so that all propellants entering the 

engines are used to produce thrust or power -- more efficiently than any previous rocket 

engine. In a staged combustion cycle, propellants are first burned partially at high pressure 

and relatively low temperature -- then burned completely at high temperature and pressure 

in the main combustion chamber. The rapid mixing of the propellants under these 

conditions is so complete that 99 percent of the fuel is burned. 

At normal operating level, the engines generate 490,847 pounds of thrust (measured in a 

vacuum). Full power is 512,900 pounds of thrust; minimum power is at 316,100 pounds of 

thrust. 

The engine can be throttled by varying the output of the pre-burners, thus varying the 

speed of the high-pressure turbopumps and, therefore, the flow of the propellant. 

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At approximately 26 seconds into launch the main engines are throttled down to 316,000 

pounds of thrust to keep the dynamic pressure on the vehicle below a specified level -- 

about 580 pounds per square foot or max q. Then, the engines are throttled back up to 

normal operating level at approximately 60 seconds. This reduces stress on the vehicle. 

The main engines are throttled down again at approximately seven minutes 40 seconds 

into the mission to maintain 3 g’s – three times the Earth’s gravitational pull – again 

reducing stress on the crew and the vehicle. This acceleration level is about one-third the 

acceleration experienced on previous crewed space flights. 

Approximately 10 seconds before Main Engine Cutoff or MECO, the cutoff sequence 

begins; about three seconds later the main engines are commanded to begin throttling at 

10-percent thrust per second to 65-percent thrust. This is held for approximately 

6.7seconds, and the engines are shut down. 

The engine performance has the highest thrust for its weight of any engine yet developed. 

In fact, one Space Shuttle Main Engine generates sufficient thrust to maintain the flight of 

two-and-one-half 747 airplanes. 

The Space Shuttle Main Engine is also the first rocket engine to use a built-in electronic 

digital controller, or computer. The controller will accept commands from the Orbiter for 

engine start, change in throttle, shutdown, and monitor engine operation. In the event of a 

failure, the controller automatically corrects the problem or safely shuts down the engine. 

NASA continues to increase the reliability and safety of shuttle flights through a series of 

enhancements to the Space Shuttle Main Engines. The engines were modified in 1988, 

1995, 1998 and 2001. Modifications include new high-pressure fuel and oxidizer 

turbopumps that reduce maintenance and operating costs of the engine, a two-duct 

powerhead that reduces pressure and turbulence in the engine, a single-coil heat 

exchanger that lowers the number of post flight inspections required. Another modification 

incorporates a large-throat main combustion chamber that improves the engine’s reliability 

by reducing pressure and temperature in the chamber. 

NASA projects an upcoming enhancement – the Advanced Health Management System – 

will further improve safety, reliability and performance. The Advanced Health Management 

System is a high tech system that couples optical and vibration sensors with advanced 

processing and computing technology. It will monitor the main engines and “see” any 

problems. After the orbiter lands, the engines are removed and returned to a processing 

facility at Kennedy Space Center, Fla., where they are rechecked and readied for the next 

flight. Some components are returned to the main engine’s prime contractor, Rocketdyne 

Propulsion & Power unit of the Boeing Company, Canoga Park, Calif., for regular 

maintenance. The main engines are designed to operate for 7.5 accumulated hours. 

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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 

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multiplexer/ demultiplexer, which sends or receives more than one message, signal or unit 

of information on a single communication channel. 

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 

switchelectronics. 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. 

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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. 

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. 

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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. 

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 

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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. 

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. 

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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. 

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. 

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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. 

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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.

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Acronyms and Abbreviations 

A/L Airlock 

AA Antenna Assembly 

AAA Avionics Air Assembly 

ABC Audio Bus Coupler 

AC Assembly Complete 

ACBM Active Common Berthing System 

ACS Assembly Contingency System 

ACS Atmosphere Control and Supply 

ACS Attitude Control System 

ACSM Attitude Control System Moding 

ACU Arm Computer Unit 

AEA Antenna Electronics Assembly 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Attach System 

APAS Androgynous Peripheral Attachment System 

APCU Assembly Power Converter Unit 

APDS Androgynous Peripheral Docking System 

APM Attached Pressurized Module 

APPCM Arm Pitch Plane Change Mode 

AR Atmosphere Revitalization 

ARCU American-to-Russian Converter Units 

ARIS Active Rack Isolation System 

ARS Air Revitalization System 

ARS Atmosphere Revitalization Subsystem 

ASCR Assured Safe Crew Return 

ATA Ammonia Tank Assembly 

ATCS Active Thermal Control System 

ATU Audio Terminal units 

AUAI Assembly Contingency System/UHF Audio Interface 

AVU Advanced Vision Unit 

AVU Artificial Vision Unit 

AVV Accumulator Vent Valve 

BBC Bolt Bus Controller 

BC Bus Controller 

BCDU Battery Charge/Discharge Unit 

BCU Bus Controller Unit 

BDU Backup Drive Unit 

BG Beta Gimbal 

BGA Beta Gimbal Assembly 

BGDTS Beta Gimbal Deployment Transition Structure 

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BGHS Beta Gimbal Housing Subassembly 

BIT/BITE Built-In Test/Built-In Test Equipment 

BMRRM Bearing Motor and Roll Ring Module 

BSP Baseband Signal Processor 

C&C Command and Control 

C&DH Command and Data Handling 

C&M Control and Monitor 

C&T Communications and Tracking 

C&W Caution and Warning 

C/A Coarse/Acquisition 

C/L Crew Lock 

CA Control Attitude 

CAS Common Attach System 

CBM Common Berthing Mechanism 

CCAA Common Cabin Air Assembly 

CCD Cursor Control Device 

CCMS Concentric Cable Management System 

CCTV Closed Circuit TV 

CDRA Carbon Dioxide Removal Assembly 

CDRS Carbon Dioxide Removal System 

CDS Command and Data Software 

CETA Crew and Equipment Translation Aid 

CEU Control Electronics Unit 

CGBA Commercial Generic Bioprocessing Apparatus 

CHeCS Crew Health Care System 

CHX Condensing Heat Exchanger 

CMG Control Moment Gyroscopes 

COAS Crew Optical Alignment Sight 

COTS Commercial Off The Shelf 

CR Change Request 

CSA Canadian Space Agency 

CSA Computer Systems Architecture 

CSCI Computer Software Configuration Item 

CVIU Common Video Interface Unit 

CVT Current Value Table 

CVV Carbon dioxide Vent Valve 

CWC Contingency Water Collection 

CWC Contingency Water Container 

DAIU Docked Audio Interface Unit 

DC Docking Compartment 

DCP Display and Control Panel 

DCSU Direct Current Switching Unit 

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DDCU DC-to-DC Converter Unit 

DDCU-E DC-to-DC Converter Unit – External 

DDCU-I DC-to-DC Converter – Internal 

DLA Drive Locking Assembly 

DMS-R Data Management System-Russian 

DPA Digital Pre-Assembly 

DPS Data Processing System 

E/L Equipment Lock 

EACP EMU Audio Control Panel 

EACP EV Audio Control Panel 

EAIU EMU Audio Interface Unit 

EATCS External Active Thermal Control Subsystem 

ECLSS Environmental Control and Life Support System 

ECU Electronic Control Unit 

ED Engagement Drive 

EDDA EMU Don/Doff Assembly 

EEATCS Early External Active Thermal Control Subsystem 

EFGF Electrical Flight Grapple Fixture 

EIA Electrical Interface Assembly 

EMU Extravehicular Mobility Unit 

EPS Electrical Power System 

ESA External Sampling Adapter 

ESSMDM Enhanced Space Station Multiplexer/Demultiplexer 

ESU End Stop Unit 

ETVCG Pg 3-4 

EVA Extra Vehicular Activity 

EV-CPDS Extra-Vehicular – Charged Particle Directional Spectrometer 

EVR Extravehicular Robotics 

EVSU External Video Switching Units 

EXPRESS EXpedite the PRocessing of Experiments to the Space Station 

EXT External 

FC Firmware Controller 

FCC Flat Collector Circuit 

FCV Flow Control Valve 

FD Flight Day 

FDIR Failure, Detection, Isolation, and Recovery 

FDS Fire Detection Suppression 

FET Field Effect Transistors 

FGB Functional Cargo Block 

FPU Fluid Pumping Unit 

FQDC Fluid Quick Disconnect Coupling 

FRD Flight Requirements Document 

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FRGF Flight Releasable Grapple Feature 

FWCI Firmware Configuration Items 

GFE Government Furnished Equipment 

GFI Ground Fault Interrupter 

GLONASS Global Navigational Satellite System 

GNC Guidance, Navigation, and Control 

GPS Global Positioning System 

GUI Graphical User Interface 

HC Hand Controller 

HCA Hollow Cathode Assembly 

HDR High Data Rate 

HEPA High Efficiency Particulate Air 

HGA High Gain Antenna 

HHL Hand Held Lidar 

HPGT High Pressure Gas Tank 

HRF Human Research Facility 

HRFM High Rate Frame Multiplexer 

HRM High Rate Modem 

I/O Input/Output 

IAC Internal Audio Controller 

IAS Internal Audio Subsystem 

IAS Internal Audio System 

IATCS Internal Active Thermal Control Subsystem 

IATCS Internal Active Thermal Control System 

IDA Integrated Diode Assembly 

IDRD Increment Definition and Requirements Document 

IEA Integrated Equipment Assembly 

IELK Individual Equipment Liner Kit 

IFHX Interface Heat Exchanger 

IMCS Integrated Mission Control System 

IMV Intermodule Ventilation 

INT Internal 

IOC Input/Output Controller 

IOCU Input/Output Controller Unit 

IP International Partner 

IRU Inflight Refill Unit 

ISA Internal Sampling Adapter 

ISPR International Standard Payload Racks 

ISS International Space Station 

ISSPO International Space Station Program Office 

ISSSH International Space Station Systems Handbook 

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ITCS Internal Thermal Control System 

ITS Integrated Truss Structure 

IUA Interface Umbilical Assembly 

IVA Intra-Vehicular Activity 

IVSU Internal Video Switch Unit 

JEU Joint Electronic Units 

Lab Laboratory 

LAN Local Area Network 

LCA Lab Cradle Assembly 

LCA Loop Crossover Assembly 

LCD Liquid Crystal Display 

LDI Local Data Interface 

LDR Low Data Rate 

LDU Linear Drive Unit 

LED Light Emitting Diode 

LEE Latching End Effector 

LFDP Load Fault Detect Protect 

LFDP Load Fault Detection Protection 

LGA Low Gain Antenna 

LLA Low Level Analog 

LT Low Temperature 

LTA Launch-To-Activation 

LTL Low Temperature Loop 

LTU Load Transfer Unit 

LVLH Local Vertical Local Horizontal 

MA Mechanical Assembly 

MAM Manual Augmented Mode 

MBM Manual Berthing Mechanism 

MBS Mobile remote servicer Base System 

MBSU Main Bus Switching Units 

MC Midcourse Correction 

MCA Major Constituent Analyzer 

MCAS MBS Common Attach System 

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 

MCU MBS Computer Unit 

MDM Multiplexer/Demultiplexer 

METOX Metal Oxide 

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MFCV Manual Flow Control Valve 

MFSC Marshall Spaceflight Center 

MHS MCU Host Software 

MIP Mission Integration Plan 

MLI Multi-Layer Insulation 

MMT Mission Management Team 

MPEV Manual Pressure Equalization Valve 

MPLM Multi-Purpose Logistics Module 

MPM Manipulator Positioning Mechanism 

MRL Manipulator Retention Latch 

MRS Mobile Remote Servicer 

MSD Mass Storage Device 

MSG Microgravity Science Glovebox 

MSS Mobile Servicing System 

MT Mobile Transporter 

MT Moderate Temperature 

MTCL MT Capture Latch 

MTL Moderate Temperature Loop 

MTS Module to Truss Segment 

MTSAS Module to Truss Segment Attachment System 

MTWsN Move To Worksite number N 

NASA National Aeronautics and Space Administration 

NCC Nominal Corrective Combination 

NCG Non-Condensable Gas 

NET No Earlier 

NIA Nitrogen Interface Assembly 

NIV Nitrogen Isolation Valve 

NTA Nitrogen Tank Assembly 

OCA Orbital Communications Adapter 

OCJM Operator Commanded Joint Position Mode 

OCPM Operator Commanded POR Mode 

OCS Operations and Control Software 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

OIV Oxygen Isolation Valve 

OMI On-Orbit Maintainable Items 

OMS Orbital Maneuvering System 

OPP OSVS Patch Panel 

OPS Operations 

Ops Operations 

ORBT Optimized RBar Targeting 

ORCA Oxygen Recharge Compressor Assembly 

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ORU Orbital Replacement Units 

OSVS Orbiter Space Vision System 

OTD ORU Transfer Device 

P&S Pointing and Support 

P/L Payload 

P1 Port 1 

PAS Payload Attach System 

PBA Portable Breathing Apparatus 

PC Personal Computer 

PCA Pressure Control Assembly 

PCBM Passive Common Berthing System 

PCC Power Converter Controller 

PCG Protein Crystal Growth 

PCMCIA Personal Computer Memory Card International Adapter 

P-Code Precision Code 

PCP Pressure Control Panel 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PCT Post-Contact Thrusting 

PCU Plasma Contactor Unit 

PDGF Power and Data Grapple Fixture 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PDU Power Drive Unit 

PEHG Payload Ethernet Hub Gateways 

PFCS Pump and Flow Control Subassembly 

PFE Portable Fire Extinguisher 

PGBA Plant Generic Bioprocessing Apparatus 

PGSC Portable General Support Computer 

PJAM Prestored Joint Position Autosequence Mode 

PM Pump Module 

PMCU Power Management Control Unit 

POA Payload/ORU Accommodation 

POR Points of Reference 

POST Power On Self-Test 

PP Planning Period 

PPA Pump Package Assembly 

PPAM Prestored POR Autosequence Mode 

PPRV Positive Pressure Relief Valve 

PRLA Payload Retention Latch Assemblies 

Prox-Ops Proximity Operations 

PRPV Positive Pressure Release Valves 

PTCS Passive Thermal Control System 

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PTU Pan/Tilt Unit 

PVCA Photovoltaic Controller Application 

PVCE Photovoltaic Controller Element 

PVM Photovoltaic Module 

PVR Photovoltaic Radiator 

PVTCS Photovoltaic Thermal Control System 

PWR Payload Water Reservoir 

QD Quick Disconnect 

R/P Receiver/Processors 

RACU Russian-to-American Converter Units 

RAIU Russian Audio Interface Unit 

RAM Random Access Memory 

RAMV Rheostat Air Mix Valve 

RBI Remote Bus Isolators 

RBVM Radiator Beam Valve Module 

RF Radio Frequency 

RFCA Rack Flow Control Assembly 

RFG Radio Frequency Group 

RGA Rate Gyros Assembly 

RHC Rotational Hand Controller 

RHX Regenerative Heat Exchanger 

RJMC Rotary Joint Motor Controller 

RMS Remote Manipulator System 

RPC Remote Power Controller 

RPCM Remote Power Controller Module 

RPDA Remote Power Distribution Assembly 

RPOP Rendezvous and Prox-Ops Program 

RS Russian Segment 

RSP Resupply Stowage Platforms 

RSR Resupply Stowage Rack 

RSTS Rack Standalone Temperature Sensor 

RSU Roller Suspension Unit 

RT Remote Terminal 

RTD Resistive Thermal Devices 

RWS Robotic Workstation 

S&M Structures and Mechanisms 

SARJ Solar Alpha Rotary Joint 

SASA S-band Antenna Support Assembly 

SAW Solar Array Wing 

SCA Switchgear Controller Assembly 

SCI Signal Conditioning Interface 

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SCU Service and Cooling Umbilical 

SCU Sync and Control Unit 

SD Smoke Detector 

SDO Solenoid Driver Output 

SDS Sample Delivery System 

SEM Shunt Electronics Module 

SFCA System Flow Control Assembly 

SFU Squib Firing Unit 

SGANT Space-to-Ground Antenna 

SIGI Space Integrated Global Positioning System/Inertial Navigation 

System 

SJRM Single Joint Rate Mode 

SM Service Module 

SMCC Shuttle Mission Control Center 

SOC State of Charge 

SPCE Servicing Performance and Checkout Equipment 

SPDA Secondary Power Distribution Assembly 

SPDM Special Purpose Dexterous Manipulator 

SPG Single Point Ground 

SSAS Segment-to-Segment Attach System 

SSC Station Support Computer 

SSC Subsystem Computer 

SSMDM Space Station Multiplexer/Demultiplexer 

SSOR Space-to-Space Orbiter Radio 

SSP Space Shuttle Program 

SSP Standard Switch Panel 

SSRMS Space Station Remote Manipulator System 

SSSR Space-to-Space Station Radio 

SSU Sequential Shunt Unit 

STCR Starboard Thermal Control Radiator 

STES Single Locker Thermal Enclosure 

STS Space Transportation System 

SVS Synthetic Vision System 

TA Thruster Assist 

TBD To Be Determined 

TC Terminal Computers 

TCCS Trace Contaminant Control Subassembly 

TCCV Temperature Check Control Valve 

TCS Thermal Control System 

TCS Trajectory Control Sensor 

TCTV Temperature Control and Check Valve 

TD Translation Drive 

TDRS Tracking and Data Relay Satellite 

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TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

TFR Translation Foot Restraints 

THC Temperature and Humidity Control 

THC Translational Hand Controller 

TI Transition Initiation 

TORU Teleoperator Control Mode 

TORVA Twice Orbital rate +Rbar to +Vbar Approach 

TRC Transmitter Receiver Controller 

TRRJ Thermal Radiator Rotary Joint 

TSP Twisted Shielded Pairs 

TTCR Trailing Thermal Control Radiator 

TUS Training Umbilical System 

TV Television 

TVIS Treadmill Vibration Isolation System 

TWMV Three-Way Mixing Valve 

UDG User Data Generation 

UHF Ultra-High Frequency 

UIA Umbilical Interface Assembly 

UIP Utility Interface Panel 

ULCAS Unpressurized Logistics Carrier Attach System 

UMA Umbilical Mechanism Assembly 

UOP Utility Outlet Panel 

USOS United States Orbital Segment 

VAJ Vacuum Access Jumper 

VBSP Video Baseband Signal Processor 

VCP Video Camera Port 

VCSA Video Camera Support Assembly 

VDS Video Distribution Subsystem 

VDS Video Distribution System 

VDU Video Distribution Unit 

VES Vacuum Exhaust System 

VGS Video Graphics Software 

VRCV Vent/Relief Control Valve 

VRIV Vent/Relief Isolation Valve 

VRS Vacuum Resource System 

VRV Vent/Relief Valve 

VSC Video Signal Converter 

VTR Video Tape Recorders 

WETA Wireless video system External Transceiver Assemblies 

WHS Workstation Host Software 

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WRM Water Recovery and Management 

WS Water Separator 

WVA Water Vent Assembly 

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

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Shuttle Pre-Launch Status Reports 

http://www-pao.ksc.nasa.gov/kscpao/status/stsstat/current.htm

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 

Dwayne Brown 

NASA Headquarters 

Washington 

Dwayne.brown@hq.nasa.gov

Space Shuttle/Space Station Policy 

202-358-1726 

Debbie Rahn 

NASA Headquarters 

Washington 

Debbie.rahn@hq.nasa.gov

International Partners 

202-358-1638 

Donald Savage 

NASA Headquarters 

Washington 

donald.savage@hq.nasa.gov

Space Science Policy, Budget 

202-358-1727 

Eileen Hawley 

Johnson Space Center 

Houston 

Eileen.hawley1@jsc.nasa.gov

Astronauts/Mission Operations 

281-483-5111 

George Diller 

Kennedy Space Center 

Kennedy Space Center, Fla. 

George.Diller-1@ksc.nasa.gov

Space Shuttle Launch Operations 

321-867-2468 

Bruce Buckingham 

Kennedy Space Center 

Kennedy Space Center, Fla. 

Bruce.Buckingham-1@kmail.ksc.nasa.gov

Launch Operations 

321-867-2468 

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Kari Kelley Allen 

The Boeing Company 

Houston 

Kari.k.allen@boeing.com

International Space Station 

281-226-4844 

Glen Golightly 

The Boeing Company 

Huntington Beach, Calif. 

Robert.g.golightly@boeing.com 

Space Shuttle 

714-372-4742 

Dan Beck 

Boeing Rocketdyne 

Canoga Park, Calif. 

Daniel.c.beck@boeing.com

Space Shuttle Main Engines 

818-586-4572 

Kari Fluegel 

United Space Alliance 

Kennedy Space Center, Fla. 

FluegeKL@usano.ksc.nasa.gov

Shuttle Processing 

321-861-3805 

Dave Drachlis 

Marshall Space Flight Center 

Huntsville, Ala. 

Dave.Drachlis@msfc.nasa.gov

Space Shuttle 

256-544-0034 

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