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Science Moves to the 

Forefront

Updated July 24, 2001
STS-105

Table of Contents

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

Mission Objectives ...................................................................................................... 5

Crew Members ............................................................................................................. 7

Flight Day Summary Timeline .................................................................................. 13

Rendezvous ............................................................................................................... 14

Spacewalks

STS-105 EVAs ............................................................................................................ 16

Payloads 

Multipurpose Logistics Module (MPLM) Leonardo ....................................................... 19

Materials ISS Experiment (MISSE) .............................................................................. 21

Small Experiments ....................................................................................................... 22

DSO/DTO

DSO 498 Spaceflight and Immune Function ................................................................ 26

DSO 635 Spatial Reorientation Following Spaceflight ................................................. 27

DTO 700-14 Single-String Global Positioning System ................................................. 28

DTO 701 Space Vision Laser Camera System ............................................................ 29

DTO 805 Crosswind Landing Performance ................................................................. 30

Shuttle Reference Data

Shuttle Abort History .................................................................................................... 31

Shuttle Abort Modes .................................................................................................... 33

Shuttle Rendezvous Maneuvers .................................................................................. 37

Shuttle Solid Rocket Boosters ..................................................................................... 38

Shuttle Super-lightweight Tank .................................................................................... 45

Acronyms and Abbreviations ................................................................................... 46

Media Assistance ...................................................................................................... 57

Media Contacts .......................................................................................................... 59
STS-105

Mission Overview 

New Crew, New Lab Racks to be Launched to ISS 

Rotation of the International Space Station crew, the third flight of an Italian-built 

Multipurpose Logistics Module delivering additional scientific racks, equipment and supplies 

for the space station, and two spacewalks highlight the STS-105 mission of Discovery, 

scheduled for launch from Kennedy Space Center in Florida. 

The crew changeout is the second for the ISS, and the logistical module, named Leonardo, 

is making its second flight to the space station. An identical module named Raffaello has 

flown once. 

The STS-105 mission will involve three crews. They are the four-member crew of 

Discovery, the three members of the Expedition Three crew to be launched to the space 

station, and the three members of the Expedition Two crew returning to Earth aboard the 

shuttle. 

Commanding the Discovery crew will be Scott Horowitz, an Air Force colonel with a Ph.D. 

in aerospace engineering, making his fourth flight into space. Pilot will be Frederick W. 

"Rick" Sturckow, a Marine major, former test pilot and veteran of a previous flight to the 

space station. Patrick G. Forrester, an Army lieutenant colonel and former test pilot, is 

making his first flight to space as mission specialist 1. Daniel T. Barry, who holds a 

doctorate in electrical engineering/computer science and an M.D. degree, is mission 

specialist 2. This is his third mission to space. 

The Expedition Three crew of the space station launching aboard Discovery is made up of 

an astronaut and two cosmonauts. Its commander is Frank Culbertson, 52, a retired Navy 

captain and former test pilot making his third flight into space. Cosmonaut Vladimir 

Dezhurov, 39, a Russian Air Force lieutenant colonel who served as commander of a 115-

day mission aboard Mir in 1995, will be Soyuz pilot. Cosmonaut Mikhail Tyurin, 41, from 

RSC Energia and on his first space mission, will serve as a researcher and flight engineer. 

The Expedition Two crew returning to Earth aboard Discovery is cosmonaut Yury Usachev, 

its commander, and astronauts Jim Voss and Susan Helms. They were taken to the station 

aboard Discovery on a flight that launched March 8. Expedition Two began the major 

scientific investigations aboard Destiny that are the purpose of the orbiting laboratory, and 

paved the way for more to come. 

About 46 hours after its launch Discovery is scheduled to dock with the International Space 

Station. The shuttle will spend almost eight days attached to the ISS. Transfer of equipment 

from the orbiter's middeck begins less than three hours after docking, which occurs during 

the crew's flight day three. 

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Leonardo will be lifted out of Discovery's payload bay on flight day four and attached 

directly to the station's Unity node for the unloading of its cargo. Once Leonardo is attached 

to Unity, half a dozen power, data and fluid connecters will be hooked up. The following day 

the ISS crew will begin transferring equipment and supplies to the station. 

The pressurized moving van first flew on Discovery on the STS-102 mission to the space 

station in March 2001. Among items in Leonardo will be two EXPRESS Racks to be 

installed in the station's U.S. laboratory Destiny. EXPRESS stands for Expedite the 

Processing of Experiments to the Space Station. The racks will house a variety of scientific 

experiments, which can be changed out in space. 

Destiny is the scientific focus of the ISS, and the most advanced and most versatile 

scientific research facility ever launched into orbit. The space station eventually will have 

six laboratories. Destiny, installed on the STS-98 mission of Atlantis in February 2001, has 

slots for 24 of the interchangeable racks (six on the top, six on the bottom and six on each 

side). Eleven are systems racks, and one slot has Destiny's 20-inch-diameter, opticalquality window. Remaining slots are for scientific racks. 

Two spacewalks are planned while Discovery is docked to the International Space Station 

to deliver and install equipment and make repairs. The first spacewalk, to last about 61⁄2 

hours on flight day seven, will see Barry and Forrester install the Early Ammonia Servicer 

to the space station's P6 truss and the Materials ISS Experiment (MISSE) on handrails of 

the ISS airlock. The Early Ammonia Servicer and MISSE will be taken into space in two 

Passive Experiment Carriers on the Integrated Cargo Carrier in Discovery's cargo bay. 

During the second spacewalk, to last about 51⁄2 hours on Flight Day Nine, Barry and 

Forrester will install handrails and lay cables to provide temporary power to the S0 truss, to 

be launched on a future mission. 

Space station crew transfer is a carefully thought out process. As a member of the 

Expedition Three crew transfers from the shuttle to the ISS, that crewmember's customdesigned seat liner, called an Individual Equipment Liner Kit, is installed in the Soyuz 

spacecraft docked to the station. The seat liner of the replaced crewmember is removed 

from the Soyuz, and that individual then becomes a member of the shuttle crew. 

All three Expedition Three crewmembers complete the liner changeout with members of the 

Expedition Two crew on Discovery's Flight Day Four, though the formal beginning of 

Expedition Three occurs at final closing of the hatches between Discovery and the space 

station. 

Equipment and supply transfer operations are scheduled during flight days five through 

eight. 

The crew will leave Leonardo and deactivate the MPLM on flight day nine. Loaded with 

unneeded equipment and refuse from the ISS, it will be returned to Discovery's cargo bay 

to be taken back to Kennedy Space Center. 

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Discovery also will carry a number of small scientific payloads. Among them is Simplesat, a 

satellite which uses inexpensive commercial hardware to demonstrate Global Positioning 

System attitude control and payload-assisted fine pointing while free flying in low Earth 

orbit. It will be deployed from a Hitchhiker canister on Discovery. 

Discovery departs the space station on the crew's Flight Day 11. 

STS-105 is the 11th shuttle flight to the International Space Station. It is the fifth shuttle 

mission of the year and the 106th shuttle flight. The 11-day flight will end with Discovery's 

landing on the 3-mile runway at Kennedy Space Center. 

Here is a day-by-day summary of the mission: 

Day 1 - Launch

Discovery's crew will launch at the end of its day during a precisely timed, few-minuteslong launch window that begins the process of rendezvous with the International Space 

Station. Crewmembers begin a sleep period about seven hours after launch. 

Day 2 - Equipment Checkouts, Rendezvous Preparations

Discovery's crew will spend its first full day in space checking out equipment that will be 

used for upcoming major activities -- the shuttle's robotic arm; and the controls and tools 

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

prepare the shuttle's docking system and perform several engine firings to optimize the rate 

at which Discovery closes in on the station. 

Day 3 - Rendezvous and Docking

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

Day 4 - Berthing of the MPLM Leonardo

Leonardo will be attached to the station's Unity node, powered up and activated. The three 

Expedition Three crewmembers will install their Individual Equipment Liner Kits in the 

Soyuz capsule docked to the station. 

Day 5 - Equipment, Supplies Transfer

Both station and shuttle crewmembers will work at transferring equipment and supplies 

from Leonardo to the space station. Expedition Two and Expedition Three crewmembers 

will take some time for handover activities. 

Day 6 - Spacewalk Preparation

Astronauts will continue transfers from Leonardo, including moving the EXPRESS racks 

into the Destiny laboratory. They also will check out spacesuits and other spacewalking 

equipment. The station and shuttle arms will be prepared for the next day's activities. 

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Day 7 - The First Spacewalk

Barry and Forrester will install the Early Ammonia Servicer to the space station's P6 truss 

and the Materials ISS Experiment (MISSE) on handrails of the ISS airlock during a 

spacewalk of about 61⁄2 hours. 

Day 8 - Equipment, Supplies Transfer

Again station and shuttle crewmembers will transfer equipment and supplies from Leonardo 

to the space station. Shuttle crewmembers also will prepare for the subsequent day's 

spacewalk, while station crewmembers will continue handover activities. 

Day 9 - The Second Spacewalk

Barry and Forrester, in another spacewalk of about 51⁄2 hours, will install handrails and lay 

cables they will install to provide temporary power to the S0 truss, to be launched later. 

Day 10 – Unberthing of Leonardo

Leonardo will be unberthed from the space station and, loaded with unneeded equipment 

and trash from the station, returned to Discovery's cargo bay. Station crewmembers will 

continue their handover. 

Day 11 Shuttle-Station Hatch Closing, Undocking, Flyaround

The shuttle and station crews will close hatches between the spacecraft. Horowitz and 

Sturckow will undock Discovery from the station. With Sturckow at the controls, Discovery 

will do a flyaround of the complex before departing. 

Day 12- Pre-Landing Checkouts, Cabin Stow

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

Horowitz and Sturckow as well as the normal steering jet test firing. The crew will spend 

most of the day stowing away gear on board the shuttle and preparing for the return home. 

Day 13 - Entry and Landing

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

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Mission Objectives

Top priorities for the STS-105 (7A.1) mission of Discovery are rotation of the International 

Space Station crew, bringing water, equipment and supplies to the station and completion 

of a series of spacewalks and robotics tasks.

International Space Station Program priorities include the following tasks to be 

accomplished.

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

mission.

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

--Transfer critical cargo from the shuttle middeck to the station.

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

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

module to the cargo bay.

--Spacewalk and robotics activities, including installation of the Early Ammonia Servicer 

and preparation for future station assembly. Among the preparation activities are laying 

heater cables for a future station truss segment.

Crew

Commander: Scott J. Horowitz

Pilot: Frederick (Rick) W. Sturckow

Mission Specialist 1: Patrick G. Forrester

Mission Specialist 2: Daniel T. Barry

E3 Up: Frank L. Culbertson, Jr.

E3 Up: Vladimir N. Dezhurov

E3 Up: Mikhail Tyurin

E2 Down: Yury V. Usachev

E2 Down: James S. Voss

E2 Down: Susan J. Helms

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Launch

 

Orbiter: Discovery OV103

Launch Site: Kennedy Space Center Launch Pad 39A

Launch Window: 2.5 to 5 minutes

Altitude: Insertion 122 Nautical Miles; Rendezvous 240 Nautical 

Miles

Inclination: 51.6 Degrees

Duration: 11 Days 19 Hrs. 39 Min.

Vehicle Data

 

Shuttle Liftoff Weight: 4517989 lbs.

Orbiter/Payload Liftoff Weight: 257748 lbs.

Orbiter/Payload Landing Weight:

 

222275 lbs.

Software Version: OI-28

Space Shuttle Main Engines: (1 MB pdf)

SSME 1: 2052 SSME 2: 2044 SSME 3: 2045

External Tank: ET-110A ( Super Light Weight Tank) 

SRB Set: BI109PF 

Landing

 

Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

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Crew Members 

Commander: Scott J. Horowitz 

Scott Horowitz, 44, an Air Force colonel and former test pilot with a Ph.D. in 

aerospace engineering, will command Discovery's STS-105 mission and be 

responsible for its safety and success. He will fly Discovery through its 

rendezvous and docking with the International Space Station on the fifth 

shuttle flight of the year. He will operate the shuttle's robotic arm during the 

mission's two spacewalks and act as backup arm operator during the 

berthing and unberthing of the Multipurpose Logistics Module. He will assist 

pilot Rick Sturckow in Discovery's flyaround of the station after undocking. 

Finally, he will land Discovery at mission's end.

Previous Space Flights:

Horowitz flew as pilot on STS-75, the Tethered Satellite reflight launched in February 1996; on 

STS-82, the second Hubble Space Telescope maintenance mission in February 1997, and on STS101, the third shuttle mission to the space station. 

Ascent Seating: Flight Deck - Port Forward

Entry Seating: Flight Deck - Port Forward

RMS 

Pilot: Frederick (Rick) W. Sturckow 

A Marine major, a veteran of 41 Desert Storm combat missions and former 

test pilot, Rick Sturckow, 39, [40 on Aug. 11] will be responsible for 

monitoring critical shuttle systems during ascent and entry. He also will play 

a major role during rendezvous and docking operations, responsible for 

many of the shuttle's navigational tools. He will be responsible for operating 

still and video cameras. He will serve as the intravehicular crewmember 

during the mission's two spacewalks, monitoring and coordinating activities 

of the spacewalkers. Sturckow himself is the backup spacewalker. After 

participating in Discovery's undocking from the station, he will perform the 

flyaround of the orbiting laboratory.

Previous Space Flights:

Sturckow was pilot on STS-88 launched in December 1998, the first space station assembly 

mission. 

Ascent Seating: Flight Deck - Starboard Forward

Entry Seating: Flight Deck - Starboard Forward

IV1 

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STS-105

Mission Specialist 1: Patrick G. Forrester 

Patrick Forrester, 44, is an Army lieutenant colonel, former test pilot and 

Army Ranger with a master's in mechanical and aerospace engineering. 

He will do two spacewalks during STS-105. He also will be primary 

operator of the shuttle's robotic arm during berthing and unberthing of the 

Multipurpose Logistics Module. Among his other responsibilities will be 

opening and closing of Discovery's payload bay doors and the shuttle's 

communications equipment and instruments, as well as flight data file. He 

will serve as a backup in still photography and video.

Previous Space Flights:

Forrester is making his first spaceflight. 

Ascent Seating: Flight Deck - Starboard Aft

Entry Seating: Flight Deck - Starboard Aft 

EV2

Mission Specialist 2: Daniel T. Barry 

Daniel Barry, 47, a veteran of two space flights, earned a Ph.D. in electrical 

engineering/computer science and an M.D. degree. As EV1 he will be the 

lead for the two spacewalks during Discovery's flight to the space station. 

Barry will serve as Discovery's flight engineer during ascent and entry. He 

will have primary responsibility in post-insertion activities, converting the 

shuttle from a launch vehicle to an orbiting spacecraft, and in deorbit 

preparations. He will provide information to the commander and pilot 

during rendezvous with the station and after undocking. He will serve as 

loadmaster on the shuttle side for transfer of equipment and supplies to the 

space station and for items being returned to Earth from the station.

Previous Space Flights:

Barry was a mission specialist on STS-72, the Space Flyer Unit retrieval flight, launched in 

January 1996, and on STS-96, a logistics flight to the space station, launched in May 1999. 

Ascent Seating: Flight Deck - Center Aft

Entry Seating: Flight Deck - Center Aft

EV1 

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E3 UP: Frank L. Culbertson, Jr. 

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

manager of the ISS Phase One (Shuttle-Mir) Program, will command the 

Expedition Three mission to the space station. As commander, he will have 

overall responsibility for expedition safety and success as the station's size 

and scientific capabilities continue to increase. Culbertson also will have a 

number of responsibilities aboard Discovery during STS-105. Among them 

will be primary responsibility for shuttle communication with the station and 

with Mission Control Moscow during rendezvous and docking and for 

pressure and leak checks once docking is complete. He also will be 

responsible for water transfer from Discovery to the station and for MPLM commanding and 

vestibule preparation. 

Previous Space Flights:

Culbertson was pilot on STS-38, a five-day Defense Department mission in November 1990. He 

commanded STS-51, which launched the Advanced Communications Technology Satellite and 

the Shuttle Pallet Satellite in September 1993. 

Ascent Seating: Mid Deck - Port

E3 UP: Vladimir N. Dezhurov 

Vladimir Nikolaevich Dezhurov is a veteran of one long-duration 

spaceflight, having served as commander of a mission aboard the Russian 

space station Mir in 1995. That crew returned to Earth aboard the shuttle 

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

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

earning three Armed Forces Medals. He was first assigned to the 

Cosmonaut Training Center in 1987. Since 1989 he has trained with a 

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

Expedition One crew to the International Space Station.

Previous Space Flights:

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

Ascent Seating: Mid Deck - Center

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E3 UP: Mikhail Tyurin 

Mikhail Tyurin, 41, worked as an engineer at the RSC-Energia Corp. after 

his graduation from the Moscow Aviation Institute in 1984. At Energia he 

worked in dynamics, ballistics and software development. He continues 

graduate studies, and his personal scientific research relating to 

psychological aspects of cosmonauts' training for manual control of 

spacecraft. Tyurin himself was selected to begin cosmonaut training in 

1993. Since 1998 he has trained as an ISS flight engineer. He was a 

backup crewmember for Expedition One before being named an 

Expedition Three crewmember.

Previous Space Flights:

Tyurin is making his first spaceflight. 

Ascent Seating: Mid Deck - Starboard

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E2 DOWN: James S. Voss

Jim Voss, 52, a retired Army colonel, will return from his second visit to the 

space station after his months aboard the orbiting laboratory as part of the 

Expedition Two crew. Voss and commander Yury Usachev did an internal 

spacewalk, the first from the space station. They repositioned a docking 

cone in preparation for the arrival later this year of the Russian docking 

compartment. Voss was instrumental in the successful effort to recover from 

station computer problems that began during the STS-100 mission in April 

2001. Voss worked with Helms in the checkout and troubleshooting for the 

station's robotic arm, Canadarm2.

Previous Space Flights:

Voss flew on STS-44 that launched a military satellite in 1991, STS-53 with a classified military 

payload in 1992, STS-69, the second Wake Shield Facility flight, in 1995, and STS-101 to the 

space station in 2000.

Entry Seating: Mid Deck - Port

E2 DOWN: Yury V. Usachev

Yury Usachev, 43, is ending his fourth flight into space with his return to 

Earth on Discovery. He is the first Russian to command the International 

Space Station. During his Discovery flight, Usachev will be designated 

Mission Specialist 5. During his months on the ISS, Usachev was 

responsible for the safety of his crew and the success of the mission, 

which saw the beginning of substantial science aboard the International 

Space Station. He did a spacewalk with Voss in the Zvezda module and 

helped Voss and Helms in the checkout and troubleshooting of 

Canadarm2. 

Previous Space Flights:

Usachev flew as a flight engineer during two long-duration missions to the Mir space station in 

1994 and 1996. He was a mission specialist during the STS-101 mission of Atlantis to the space 

station in May 2000 along with crewmates Jim Voss and Susan Helms. Usachev has logged 386 

days in space and six spacewalks.

Entry Seating: Mid Deck - Starboard

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E2 DOWN: Susan J. Helms

Susan Helms, 43, is an Air Force colonel returning from her fifth 

spaceflight. She operated the station's Canadarm2 during checkout and 

troubleshooting operations. She and fellow Expedition Two crewmember 

Voss performed a spacewalk from Discovery after Expedition Two arrived 

at the space station in March 2000. She was choreographer for the second 

spacewalk, performed by Andy Thomas and Paul Richards, operating from 

Discovery's aft flight deck. She also was responsible for transfer of vital 

racks from the Multipurpose Logistics Module to the U.S. laboratory 

Destiny. With Usachev and Voss, she conducted and participated in a 

number of scientific experiments during the Expedition Two mission.

Previous Space Flights:

Helms flew on STS-54, which launched a Tracking and Data Relay Satellite in 1993; STS-64, the 

Lidar In-Space Technology Experiment flight, in 1994; STS-78, a Spacelab flight, in 1996, and 

STS-101 to the space station in 2000.

Entry Seating: Mid Deck - Center

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Flight Day Summary Timeline 

DATE TIME (EST) DAY MET EVENT

08/09/01 5:32:00 PM 1 000/00:00 Launch

08/11/01 1:08:00 PM 3 001/19:36 TI Burn

08/11/01 3:27:00 PM 3 001/21:55 Docking

08/11/01 5:17:00 PM 3 001/23:45 ISS Ingress

08/12/01 10:52:00 AM 4 002/17:20 MPLM Installation

08/15/01 10:37:00 AM 7 005/17:05 EVA 1 Start

08/17/01 10:37:00 AM 9 007/17:05 EVA 2 Start

08/18/01 4:22:00 PM 10 008/22:50 MPLM Berth

08/19/01 11:48:00 AM 11 009/18:16 Undocking

08/21/01 12:09:00 PM 13 011/18:37 Deorbit Burn

08/21/01 1:11:00 PM 13 011/19:39 Landing

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Rendezvous and Docking 

Overview 

Discovery'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 Discovery to the starting 

point for a final approach. 

About 21⁄2 hours before the scheduled docking on Flight Day Three, Discovery will reach 

that point about 50,000 feet -- 91⁄2 miles -- behind the ISS. There Discovery's jets will be 

fired in a Terminal Intercept (TI) burn to begin the final phase of the rendezvous. 

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

As Discovery closes in, the shuttle's rendezvous radar system will begin tracking the 

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

approach, the shuttle can make as many as four, small course corrections at regular 

intervals. Just after the last correction is completed, Discovery will reach a point about 

half a mile below the station. At that time, about an hour before the scheduled docking, 

Commander Scott Horowitz will take manual control of Discovery. 

Horowitz will slow Discovery's approach and fly to a point about 600 feet directly below 

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

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

During the rendezvous, Horowitz will be assisted by Pilot Rick Sturckow. Mission 

Specialists Dan Barry and Patrick Forrester also will play key roles in the rendezvous, 

with Barry operating a handheld laser-ranging device and a laptop computer navigation 

aid assisted by Forrester. Barry also will operate the shuttle's docking mechanism to 

latch the station and Discovery together after the two spacecraft make contact. 

Horowitz will slowly close on the station moving at a speed of about a tenth of a mile per 

hour. Using a view from a camera mounted in the center of Discovery's docking 

mechanism as a key alignment aid, Horowitz will precisely center the docking ports of 

the two spacecraft. Horowitz will fly to a point where the docking mechanisms are 30 

feet apart, and pause for about five minutes to check the alignment. 

For Discovery's docking, Horowitz will maintain the shuttle's speed relative to the station 

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

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

preliminary latches will automatically attach the two spacecraft together. Immediately 

after Discovery docks, the shuttle's steering jets will be deactivated to reduce the forces 

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

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

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

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

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

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Undocking, Separation and Flyaround 

Once Discovery is ready to undock, Barry will send a command that will release the 

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

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

station. Discovery's steering jets will be shut off to avoid any inadvertent firings during 

this initial separation. 

Once the docking mechanism's springs have pushed Discovery to a distance of about 

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

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

deck, Sturckow will manually control Discovery within a tight corridor as he separates 

from the ISS, essentially the reverse of the task performed by Horowitz when Discovery 

docked. 

Discovery will continue away to a distance of about 450 feet, where Sturckow will begin 

a close flyaround of the station, circling the complex 11⁄4 times. 

Sturckow will pass directly above the station, then behind, then underneath, then in front 

and then reach a point directly above it for a second time. At that point, passing above 

the station for a second time, Sturckow will fire Discovery's jets to separate from the 

area of the station. The flyaround is expected to be completed a little over an hour after 

undocking. 

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EVA 

Two Spacewalks to Lay Groundwork for Future ISS Construction 

Overview 

Astronauts Dan Barry and Patrick Forrester are to perform two spacewalks while Discovery 

is docked to the International Space Station during STS-105. 

Barry will be designated Extravehicular crewmember 1 (EV1) and wear red stripes on his 

spacesuit. Forrester, designated EV2, will wear an all-white spacesuit. 

Discovery Pilot Rick Sturckow will be the Intravehicular crewmember (IV), coordinating the 

spacewalk activities from within the shuttle's cabin. Discovery Commander Scott Horowitz 

will control the shuttle's robotic arm during the spacewalk. 

The spacewalkers will install equipment on the exterior of the station for future maintenance 

and construction work on the outpost. Both spacewalks will originate from Discovery's 

airlock, and the two astronauts will be tethered to the shuttle's robotic arm for much of the 

work. 

The primary objective of the first spacewalk, planned for Flight Day Seven and to last about 

61⁄2 hours, is to install an Early Ammonia Servicer on the station, a system that contains 

spare ammonia for the station's cooling system. Ammonia is the fluid used in the radiators 

that cool the station's electronics. The EAS will be installed on the truss, called the P6 truss 

that holds the station's giant U.S. solar arrays, associated batteries and the cooling 

radiators. 

During the first spacewalk, Barry and Forrester also will attach an experiment to the outside 

of the station's airlock that will collect information on how various materials weather the 

space environment. The experiment, called the Materials International Space Station 

Experiment (MISSE), is housed in two carriers that will be attached to the station's exterior 

for an extended duration. 

As Barry and Forrester exit Discovery's airlock, Horowitz will maneuver the shuttle's robotic 

arm into position to latch onto a grapple fixture on the EAS, bolted to a carrier in the 

shuttle's payload bay for launch. After Horowitz has latched the arm onto the EAS, Barry 

and Forrester will go to the pallet, called an Integrated Cargo Carrier, and begin loosening 

the six bolts that hold the unit in place. In addition, Barry will translate hand-over-hand up to 

the station's Destiny Lab, where he will pick up a foot platform to be used during installation 

of the EAS. With the bolts free, Horowitz will begin lifting the EAS, with Barry and Forrester 

holding on to handrails on the EAS as well, up to the station. 

Horowitz will maneuver the spacewalkers and EAS up to the position on the station's P6 

truss where the EAS will be installed. 

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STS-105

There, Barry will attach the foot platform and secure himself to it. Horowitz will release the 

arm's grip on the EAS, basically handing off the unit to Barry. Forrester will then help Barry 

align the unit over its attachment position and move it to a "soft dock," where it will be 

preliminarily held in place by a hook mechanism closed and locked with a pip pin inserted 

by Forrester. Forrester will then tighten a bolt to firmly attach the EAS in position on the 

truss. The two spacewalkers will then unfurl and attach cables to supply station electrical 

power to heaters on the EAS, completing the installation. 

That done, the spacewalkers will hold on to the station arm again as Horowitz lowers them 

back to Discovery's payload bay, pausing at the station's Z1 truss to allow Barry to put the 

foot restraint in a stowed location needed for upcoming mission STS-110/8a. In Discovery's 

cargo bay, Barry and Forrester will move to the carrier platform and release the two 

Passive Experiment Containers containing the MISSE investigations from their launch 

restraints. With each of the spacewalkers holding an experiment container, they will hold 

onto the arm while Horowitz maneuvers them up to the station's airlock. There they will let 

go of the arm and clamp the MISSE carriers to two separate airlock handrails. 

The second spacewalk, planned to last up to 51⁄2 hours, will be performed on Flight Day 

Nine of the mission and will focus on preparations for future station assembly, installing 

handrails on the Destiny lab and laying heater cables for a future station truss segment. 

Horowitz will again be operating the shuttle robotic arm to maneuver the spacewalkers, 

who will be hanging on to the arm at times. As the spacewalk begins, Barry and Forrester 

will take with them from Discovery's airlock two bags containing the heater cables they will 

install on the station. Called Launch to Activation heater cables, they will be used on shuttle 

mission STS-110 to power heaters on the station's S0 truss segment, the center segment 

of the station's truss structure, more than 300 feet long. In addition, they will take with them 

two bags holding 11 new handrails they will install on the Destiny Lab, called Orbit-Installed 

Handrails. 

Barry and Forrester will hold on to the shuttle arm, carrying the heater cable bags, as 

Horowitz lifts them to the station's Destiny lab. There, they will temporarily attach the bags 

to handrails, one on the port side of the lab and another on the starboard side. 

Barry will install six handrails on the lab's starboard side while Forrester installs five 

handrails on the port side. The spacewalkers also will relocate two existing lab handrails. 

With the handrails installed, the spacewalkers will then feed the heater cables along the 

rails on either side of the lab, connecting one end to the station and placing the other end in 

position for use when the S0 truss segment is delivered on STS-110. 

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EVA Timeline for 

Two Spacewalks to Lay Groundwork for Future ISS Construction 

Time Event 

005/17:05 EVA 1 Start 

005/17:35 EVA1 Early Ammonia Servicer Install PT 1 

005/18:35 EVA 1 Early Ammonia Servicer Install PT 2 

005/21:35 EVA 1 Materials International Space Station Experiment Install 

005/22:50 EVA 1 Clean Up 

005:23:20 EVA 1 Ingress 

005/23:35 EVA 1 End 

007/17:05 EVA 2 Start 

007/17:35 EVA 2 S0 Launch To Activation Cable Install 

007/21:05 EVA 2 Clean Up 

007/23:20 EVA 2 Ingress 

007/23:35 EVA 2 End 

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Payloads 

Leonardo - An Italian Space Veteran 

Overview 

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

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

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

orbiting laboratory. 

Leonardo is mounted in Discovery's payload bay for launch and remains there until after 

the shuttle docks with the space station. Discovery's astronauts will use the shuttle's robotic 

arm to remove Leonardo from the payload bay and attach it to the space station's Unity 

Node for unloading. 

Aboard Leonardo are six Resupply Stowage Racks, four Resupply Stowage Platforms, and 

two new scientific experiment racks for the station's U.S. laboratory Destiny. The two new 

science racks (EXPRESS Racks 4 and 5) will add science capability to the station. 

EXPRESS stands for Expedite the Processing of Experiments to the Space Station. 

EXPRESS Rack 4 weighs 1,175 pounds and EXPRESS Rack 5 weighs 1,200 pounds. The 

empty weight of each EXPRESS rack is about 785 pounds. EXPRESS Racks 1 and 2A 

were delivered aboard the Raffaello cargo module during STS-100/6A in April 2001. 

EXPRESS Rack 3 is scheduled to be brought to the station during STS-111/UF-2 in 2002. 

The Resuppy Stowage Racks and Resupply Stowage Platforms are filled with Cargo 

Transfer Bags that contain equipment and supplies for the station. The six Resuppply 

Stowage Racks contain almost 3,200 pounds of cargo and the four Resupply Stowage 

Platforms contain about 1,200 pounds of cargo, not including the weight of the Cargo 

Transfer Bags, the foam packing around the cargo or the straps and fences that hold the 

bags in place. 

The total weight of cargo, racks and packing material aboard Leonardo is just over 11,000 

pounds. Total cargo weight is about 6,775 pounds. 

Leonardo's cargo includes equipment required for activation of the two new science racks, 

a variety of spare parts for station systems, and food and other supplies to support the 

Expedition Three crew. After the cargo is removed, the Resupply Stowage Racks and 

Resupply Stowage Platforms, which remain aboard Leonardo, will be filled with any 

unneeded station equipment and trash. Empty Cargo Transfer Bags and packing foam 

also will be loaded. Once filled, Leonardo will be detached from the station and put back 

into the shuttle's payload bay for the trip home. 

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History/Background 

Construction of Leonardo began in April 1996 at the Alenia Aerospazio factory in Turin, 

Italy. Leonardo was flown from Italy to the Kennedy Space Center in Florida in August 1998 

aboard a special Beluga cargo aircraft. Although built in Italy, Leonardo and two additional 

MPLMs are owned by the U.S. The MPLMs were provided in exchange for Italian access to 

U.S. research time on the space station. 

The cylindrical Leonardo module is about 21 feet (6.4 meters) long and 15 feet (4.6 meters) 

in diameter. It weighs a little over 9,000 pounds (4.1 metric tons) empty and can carry up to 

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

racks or platforms. The reusable MPLM functions as both a cargo carrier and a space 

station module. 

Leonardo contains components that provide some life support, fire detection and 

suppression, electrical distribution and computer functions. When in the payload bay, 

Leonardo is independent of the space shuttle and there is no passageway for shuttle 

crewmembers to travel to and from the module. Eventually, the MPLMs also will carry 

refrigerator freezers for transporting experiment samples and food to and from the station. 

Leonardo first flew to the space station aboard Discovery on STS-102/5A.1 in March 2001. 

The second MPLM, Raffaello, flew to the station aboard Endeavour on STS-100/6A in April 

2001. 

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Payloads 

Materials International Space Station Experiments 

Overview 

The Materials International Space Station Experiments (MISSE) Project is a NASA/Langley 

Research Center-managed cooperative endeavor to fly materials and other types of space 

exposure experiments on the space station. The objective is to develop early, low-cost, 

non-intrusive opportunities to conduct critical space exposure tests of space materials and 

components planned for use on future spacecraft. 

Johnson Space Center, Marshall Space Flight Center, Glenn Research Center, the 

Materials Laboratory at the Air Force Research Laboratory and Boeing Phantom Works are 

participants with Langley in the project. 

The MISSE experiments will be the first externally mounted experiments conducted on the 

ISS. The experiments are in four Passive Experiment Containers (PECs) that were initially 

developed and used for an experiment on Mir in 1996 during the Shuttle-Mir Program. The 

PECs were transported to Mir on STS-76. After an 18-month exposure in space, they were 

retrieved on STS-86. 

PECs are suitcase-like containers for transporting experiments via the space shuttle to and 

from an orbiting spacecraft. Once on orbit and clamped to the host spacecraft, the PECs 

are opened and serve as racks to expose experiments to the space environment. 

The first two MISSE PECs will be launched to the ISS on STS-105. Two more will be 

launched to the ISS about 18 months later. 

Examples of tests to be performed in MISSE include: New generations of solar cells with 

longer expected lifetimes to power satellites; advanced optical components planned for 

future Earth observational satellites; new, longer-lasting coatings that better control heat 

absorption and emissions and thereby the temperature of satellites; new concepts for 

lightweight shields to protect crews from energetic cosmic rays found in interplanetary 

space; and the effects of micrometeoroid impacts on materials planned for use in the 

development of ultra-light membrane structures for solar sails, large inflatable mirrors and 

lenses. 

New affordable materials will enable the development of advanced reusable launch 

systems and advanced spacecraft systems. 

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Payloads 

Small Payloads Take Youth Science into Orbit 

Overview 

Goddard Space Flight Center's Wallops Flight Facility manages NASA's Shuttle Small 

Payloads Project. The SSPP designs, develops, tests, integrates and flies a group of small 

payload carrier systems aboard the space shuttle. These carriers -- the Hitchhiker, 

Getaway Specials, Space Experiment Module -- support payloads supplied by NASA, other 

U.S. government agencies, universities, high schools, domestic commercial customers and 

foreign nationals and governments. The following small payloads will be flown aboard 

Discovery during the STS-105 mission: 

Simplesat

Simplesat, a deployable satellite, is being developed as a prototype for a satellite that could 

be constructed at a college or university. It is designed to evaluate the use of inexpensive 

commercial hardware on spacecraft. Simplesat is expected to demonstrate Global 

Positioning System attitude control and payload-assisted fine pointing while free flying in 

low Earth orbit. It will be ejected from a Hitchhiker canister on the shuttle and deployed 

away from the sun to protect its optical equipment. It will not be retrieved. 

The shuttle crew will deploy Simplesat using switches to arm and activate pyrotechnic 

devices that release the satellite from the canister. Once the satellite leaves the shuttle, 

Simplesat's batteries will begin to charge and scientists will monitor Simplesat via radio 

frequency transmission. Simplesat GPS operates as a navigational tool that has both 

earthbound and spacebound applications because it provides scientists with a very precise 

reading of one's location in space. 

G-780 Cell Growth in Microgravity

The Get-Away Special canister G-780, Cell Growth in Microgravity experiment, is an 

educational project that encourages Minnesota high school students to observe root cell 

growth in microgravity by germinating Vicia Faba bean seeds in space. The primary 

objective of the experiment is to engage some 200 Mayo High School (Rochester, Minn.) 

students in an authentic investigation that requires collaboration with scientific 

professionals from the community. The students designed and prepared the experiment. 

For additional information about this experiment see stbrehmer@rochester.k12.mn.us. 

Microgravity Smoldering Combustion 

The Microgravity Smoldering Combustion experiments are designed to study smoldering 

combustion in an extremely low gravity (microgravity) environment and in normal gravity. 

The microgravity setting is essential because it permits scientists to study smoldering 

combustion mechanisms without the complications introduced by gravity and it provides 

insight into how smoldering combustion behaves in space. 

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Smoldering combustion is a complex, nonflaming form of burning that occurs in the interior 

of porous, combustible materials, both natural (piles of leaves and pine needles) and 

manmade (furniture stuffing and cable insulation). Smolder is a serious problem: 40 percent 

of all deaths caused by fire in the U.S. can be attributed to the smoldering of household 

furniture, which releases toxic byproducts. In space, the threat of smoldering combustion 

becomes an even greater risk. 

An earlier version of this experiment flew on USML-1 in 1992. The present version was first 

tested on Earth and flown aboard STS-69 and STS-77 in 1995-1996. 

Hitchhiker Experiments Advancing Technology 

The Hitchhiker Experiments Advancing Technology payload contains two experiments, 

Simplesat and Space Experiment Module-10. NASA's Goddard Space Flight Center, 

Greenbelt, Md., sponsors both experiments. 

Space Experiment Module-10

The Space Experiment Module-10 contains 11 experiments and flies in the space shuttle's 

payload bay. Experiments flying aboard the SEM-10 module are: 

· Space Travel's Affect on Roots (STARS): The STARS experiment examines the growing 

characteristics of roots subjected to the space environment. Once the roots return to Earth, 

they will be planted alongside control roots that were purchased at the same time. A 

difference in crop yield could aid in realizing the potential for growing food in space for longterm exploration. (Arizona State University, Tempe, Ariz.) 

· Flowers in Space: Students will examine the effects of space travel on two types of 

perennial flowers (coreopsis and columbine) and two types of vegetables (lettuce and 

cucumbers). Half of the seeds will fly aboard the mission and the other half will be held at 

Wallops. Upon return, the flower and lettuce seeds will be planted in the fall. The lettuce will 

mature in the fall, the perennial flowers will mature in the following spring, and the 

cucumber seeds will be started indoors during the spring and planted outdoors. Students 

will compare growth rates at different geographic locations to determine if the seeds that 

traveled in space grow differently. (GSFC/Wallops New 2000, Media, Pa.) 

· Food for Earth and Space: Students will determine whether the environment of space 

influences the growth of edible sprouts. Mass, volume and mean growth length will be 

compared for both the control and variable groups. This experiment should reveal if the 

environment of space could produce more or less food on the space station. (Corpus 

Christi School, Chambersburg, Pa.) 

· Corn: Tomorrow's Food on Earth and in Space and Rusting in Space: The first student 

experiment will explore if the environment of space impacts the embryo of the corn seed or 

affects its ability to grow and produce once planted on Earth. Preflight, control and variable 

seed groups will be measured for mass, volume and density and will be stored in similar 

environments. Upon return, all growing conditions (time, light, temperature and watering 

amounts) will be the same. The "Rusting in Space" experiment will observe if rust develops 

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differently on a variety of metals after exposure to the environment of space. The control 

and variable groups will be stored in similar environments and then they will be placed in a 

rust-promoting environment. Students will record data regarding mass and density 

changes, oxidation time and other physical changes. (Chambersburg Area Middle School, 

Chambersburg, Pa.) 

· Shirt and Shoes Required: The experiment will determine the effect of high-frequency 

radiation and microgravity on fabrics, both natural and synthetic. Results from this 

experiment may influence clothing manufacturing on Earth's changing environment. (Great 

Bridge Middle School, Chesapeake, Va.) 

· Agrilaser: This experiment will examine the effects of lasering various seeds and sending 

them into space. In space, outside the protective atmosphere, the molecules are subjected 

to cosmic particles. This may affect the seeds' growth cycle, germination period, growth 

timeline, edible plant taste, look and texture. A variety of seeds will be used and proper 

controls will be used for each seed group. (Arrowhead Union High School, Port 

Washington, Wis.) 

· Space Laser Comm 2001: This experiment will test the feasibility of using a laser to 

communicate in space. A semiconductor laser module will be carried into space to see if it 

can withstand a space environment of microgravity and radiation. The peak wavelength of 

the laser module will be characterized, along with the optical output power of the laser 

module and various electrical inputs before it goes into space and after it returns. Students 

will be looking for changes in the peak wavelength and optical output along with any 

differences in the transmissivity of the laser lens. (Mills Lawn Elementary School, Yellow 

Springs, Ohio) 

· Different Types of Seeds: Students will pack tubes with different types of seeds. Some of 

the seeds will be from the Cahokia Mounds Historical Site in Cahokia Mounds, Ill. Other 

types of seeds will include tomatoes, lettuce, beans, cucumbers, pumpkins and corn, some 

of them native to the Midwest area. The students will place the seeds in soil to see if they 

grow. They will also place them in the hydroponics lab to see if they will grow. They will 

also grow a control group of seeds that have not been up in space in soil and in the 

hydroponics lab. (Ellis School, Belleville, Ill.) 

· Stuck on Space: This team of experimenters consists of students in grades seven 

through nine from schools in three states. This experiment will explore how temperature 

extremes, radiation and microgravity will affect adhesives. Commonly used adhesivebacked materials will be used to determine how these items will react in a microgravity 

environment. Materials that may possibly be used on the International Space Station and 

on future space exploration missions will be used. (Suffield High School, Suffield, Conn.) 

· SCI-FIVE: Students from five schools will study the effects of the space environment on a 

variety of materials. Balls, Playdough©, gum, seeds, Alka-Seltzer©, exposed film, ink and 

teeth/braces will be tested after they have traveled in space to determine how radiation, 

temperature and microgravity may have affected them. (Anne Arundel County Schools, 

Anne Arundel County, Md.) 

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· Imaging Media and Radiation Shielding Experiment: Regina Science Club will conduct 

both of these experiments, which will be housed in one SEM module. The "Imaging Media" 

experiment will compare the ability of various consumer grade image storage media to 

withstand degradation due the SEM space flight environment. Several popular image 

storage media will be compared side-by-side, image-by-image comparisons with unflown 

control media and with each other. The "Radiation Shielding Experiment" will test the 

effectiveness of several radiation shielding strategies. At least 15 radiation dosimeters will 

be placed in the SEM module. A duplicate control set of dosimeters, both shielded and 

unshielded, will be kept on the ground for the duration of the experiment to allow for 

comparison of the levels of radiation in space to those on the ground. After the flight, all 

experiment dosimeters will be returned to the manufacturer for developing. The 

manufacturer will provide radiation exposure levels for each type of radiation measured for 

each dosimeter. (Regina Catholic Education Center, Iowa City, Iowa) 

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DTO/DSO/RME 

Spatial Reorientation Following Spaceflight 

DSO 635

Overview 

Spatial orientation is altered during and after spaceflight by a shift of central vestibular 

processing (from a gravitational frame-of-reference to an internal, head-centered frame-ofreference) that occurs during adaptation to microgravity and is reversed during the first few 

days after return to Earth. Discordant sensory stimuli during the postflight readaptive period 

will temporarily disorient/destabilize the subject by triggering a shift (state change) to the 

previously learned, internally referenced, microgravity-adapted pattern of spatial orientation 

and sensorimotor control. 

History/Background 

The purpose of this DSO is to examine both the adaptive changes in the spatial reference 

frame used for coding spatial orientation and sensorimotor control as well as the fragility of 

the adaptive process and the feasibility of driving state changes in central vestibular 

processing via discordant sensory stimuli using balance control tests and eye movement 

responses to pitch-axis rotation in a short-arm centrifuge. The findings are expected to 

demonstrate the degree to which challenging motion environments may affect postflight 

readaptation and lead to a better understanding of safe postflight activity regimens. The 

findings are also expected to demonstrate the feasibility of triggering state changes 

between sensorimotor control sets using a centrifuge device. 

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DTO/DSO/RME 

Spaceflight and Immune Function 

DSO 498 

Overview 

Astronauts face an increasing risk of contracting infectious diseases as they work and live 

for longer periods in the crowded conditions and closed environments of spacecraft such as 

the International Space Station. The effects of spaceflight on the human immune system, 

which plays a pivotal role in warding off infections, is not fully understood. Understanding 

the changes in immune functions caused by exposure to microgravity will allow researchers 

to develop countermeasures to minimize the risk of infection. 

History/Background 

The objective of this DSO is to characterize the effects of spaceflight on neutrophils, 

monocytes and cytotoxic cells, which play an important role in maintaining an effective 

defense against infectious agents. The premise of this study is that the space environment 

alters the essential functions of these elements of human immune response. 

Researchers will conduct a functional analysis of neutrophils and monocytes from blood 

samples taken from astronauts before and after the flight. They will also assess the 

subjects' pre- and postflight production of cytotoxic cells and cytokine. 

This study will complement previous and continuing immunology studies of astronauts' 

adaptation to space. 

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DTO/DSO/RME 

Single-String Global Positioning System 

DTO 700-14

Overview 

The purpose of the Single-String Global Positioning System (GPS) is to demonstrate the 

performance and operation of the GPS during orbiter ascent, on-orbit, entry and landing 

phases using a modified military GPS receiver processor and the existing orbiter GPS 

antennas. GPS data may be downlinked during all mission phases. 

History/Background 

This is the 18th flight of DTO 700-14. 

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DTO/DSO/RME 

Space Vision Laser Camera System 

DTO 701 

Overview 

DTO 701 will demonstrate the capability of the Space Vision Laser Camera System 

(SVLCS) to accurately measure the position and attitude of objects in harsh lighting 

conditions and the ability of the SVLCS to act as an input sensor to the Orbiter Space 

Vision System (OSVS). 

The SVLCS consists of the Laser Camera Head (LCH), which will be mounted in the 

payload bay, and the Laser Camera Controller (LCC), which will be in the aft flight deck. 

The LCH contains an eye-safe laser, projection and receiving optics, scanning optics, 

detectors and driver electronics. The scanning electronics in the LCH scan a 30- by 40-

degree field of view. It detects and tracks objects (satellites, payloads and structures) and 

provides position and attitude information to the OSVS. The LCC is based on a standard 

payload and general support computer. The LCH and LCC will be connected via Ethernet. 

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DTO/DSO/RME 

Crosswind Landing Performance 

DTO 805

Overview 

The purpose of this DTO is to demonstrate the capability to perform a manually controlled 

landing in the presence of a crosswind. The testing is done in two steps. 

1. Prelaunch: Ensure planning will allow selection of a runway with Microwave 

Scanning Beam Landing System support, which is a set of dual transmitters 

located beside the runway providing precision navigation vertically, 

horizontally and longitudinally with respect to the runway. This precision 

navigation subsystem helps provide a higher probability of a more precise 

landing with a crosswind of 10 to 15 knots as late in the flight as possible. 

2. Entry: This test requires that the crew perform a manually controlled landing 

in the presence of a 90-degree crosswind component of 10 to 15 knots steady 

state. 

During a crosswind landing, the drag chute will be deployed after nose gear touchdown 

when the vehicle is stable and tracking the runway centerline. 

History/Background 

This DTO has been manifested on 66 previous flights. 

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Shuttle Reference Data 

Shuttle Abort History 

RSLS Abort History:

(STS-41 D) June 26, 1984

The countdown for the second launch attempt for Discovery’s maiden flight ended at T4 seconds when the orbiter’s computers detected a sluggish valve in main engine #3. 

The main engine was replaced and Discovery was finally launched on August 30, 1984. 

(STS-51 F) July 12, 1985

The countdown for Challenger’s launch was halted at T-3 seconds when on-board 

computers detected a problem with a coolant valve on main engine #2. The valve was 

replaced and Challenger was launched on July 29, 1985. 

(STS-55) March 22, 1993

The countdown for Columbia’s launch was halted by on-board computers at T-3 

seconds following a problem with purge pressure readings in the oxidizer preburner on 

main engine #2 Columbia’s three main engines were replaced on the launch pad, and 

the flight was rescheduled behind Discovery’s launch on STS-56. Columbia finally 

launched on April 26, 1993. 

(STS-51) August 12, 1993

The countdown for Discovery’s third launch attempt ended at the T-3 second mark 

when on-board computers detected the failure of one of four sensors in main engine #2 

which monitor the flow of hydrogen fuel to the engine. All of Discovery’s main engines 

were ordered replaced on the launch pad, delaying the Shuttle’s fourth launch attempt 

until September 12, 1993. 

(STS-68) August 18, 1994

The countdown for Endeavour’s first launch attempt ended 1.9 seconds before liftoff 

when on-board computers detected higher than acceptable readings in one channel of a 

sensor monitoring the discharge temperature of the high pressure oxidizer turbopump in 

main engine #3. A test firing of the engine at the Stennis Space Center in Mississippi on 

September 2nd confirmed that a slight drift in a fuel flow meter in the engine caused a 

slight increase in the turbopump’s temperature. The test firing also confirmed a slightly 

slower start for main engine #3 during the pad abort, which could have contributed to 

the higher temperatures. After Endeavour was brought back to the Vehicle Assembly 

Building to be outfitted with three replacement engines, NASA managers set October 

2nd as the date for Endeavour’s second launch attempt. 

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Abort to Orbit History:

(STS-51 F) July 29, 1985

After an RSLS abort on July 12, 1985, Challenger was launched on July 29, 1985. Five 

minutes and 45 seconds after launch, a sensor problem resulted in the shutdown of 

center engine #1, resulting in a safe "abort to orbit" and successful completion of the 

mission.

Updated: 05/22/2001 

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Shuttle Reference Data 

Shuttle Abort Modes 

RSLS ABORTS 

These occur when the onboard shuttle computers detect a problem and command a halt in 

the launch sequence after taking over from the Ground Launch Sequencer and before Solid 

Rocket Booster ignition. 

ASCENT ABORTS 

Selection of an ascent abort mode may become necessary if there is a failure that affects 

vehicle performance, such as the failure of a space shuttle main engine or an orbital 

maneuvering system. Other failures requiring early termination of a flight, such as a cabin 

leak, might also require the selection of an abort mode. 

There are two basic types of ascent abort modes for space shuttle missions: intact aborts 

and contingency aborts. Intact aborts are designed to provide a safe return of the orbiter to 

a planned landing site. Contingency aborts are designed to permit flight crew survival 

following more severe failures when an intact abort is not possible. A contingency abort 

would generally result in a ditch operation. 

INTACT ABORTS 

There are four types of intact aborts: abort to orbit (ATO), abort once around (AOA), 

transoceanic abort landing (TAL) and return to launch site (RTLS). 

Return to Launch Site 

The RTLS abort mode is designed to allow the return of the orbiter, crew, and payload to 

the launch site, Kennedy Space Center, approximately 25 minutes after lift-off. 

The RTLS profile is designed to accommodate the loss of thrust from one space shuttle 

main engine between lift-off and approximately four minutes 20 seconds, at which time not 

enough main propulsion system propellant remains to return to the launch site. 

An RTLS can be considered to consist of three stages--a powered stage, during which the 

space shuttle main engines are still thrusting; an ET separation phase; and the glide phase, 

during which the orbiter glides to a landing at the Kennedy Space Center. The powered 

RTLS phase begins with the crew selection of the RTLS abort, which is done after solid 

rocket booster separation. The crew selects the abort mode by positioning the abort rotary 

switch to RTLS and depressing the abort push button. The time at which the RTLS is 

selected depends on the reason for the abort. For example, a three-engine RTLS is 

selected at the last moment, approximately three minutes 34 seconds into the mission; 

whereas an RTLS chosen due to an engine out at lift-off is selected at the earliest time, 

approximately two minutes 20 seconds into the mission (after solid rocket booster 

separation). 

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After RTLS is selected, the vehicle continues downrange to dissipate excess main 

propulsion system propellant. The goal is to leave only enough main propulsion system 

propellant to be able to turn the vehicle around, fly back towards the Kennedy Space 

Center and achieve the proper main engine cutoff conditions so the vehicle can glide to the 

Kennedy Space Center after external tank separation. During the downrange phase, a 

pitch-around maneuver is initiated (the time depends in part on the time of a space shuttle 

main engine failure) to orient the orbiter/external tank configuration to a heads up attitude, 

pointing toward the launch site. At this time, the vehicle is still moving away from the launch 

site, but the space shuttle main engines are now thrusting to null the downrange velocity. In 

addition, excess orbital maneuvering system and reaction control system propellants are 

dumped by continuous orbital maneuvering system and reaction control system engine 

thrustings to improve the orbiter weight and center of gravity for the glide phase and 

landing. 

The vehicle will reach the desired main engine cutoff point with less than 2 percent excess 

propellant remaining in the external tank. At main engine cutoff minus 20 seconds, a pitchdown maneuver (called powered pitch-down) takes the mated vehicle to the required 

external tank separation attitude and pitch rate. After main engine cutoff has been 

commanded, the external tank separation sequence begins, including a reaction control 

system translation that ensures that the orbiter does not recontact the external tank and 

that the orbiter has achieved the necessary pitch attitude to begin the glide phase of the 

RTLS. 

After the reaction control system translation maneuver has been completed, the glide 

phase of the RTLS begins. From then on, the RTLS is handled similarly to a normal entry. 

Transoceanic Abort Landing 

The TAL abort mode was developed to improve the options available when a space shuttle 

main engine fails after the last RTLS opportunity but before the first time that an AOA can 

be accomplished with only two space shuttle main engines or when a major orbiter system 

failure, for example, a large cabin pressure leak or cooling system failure, occurs after the 

last RTLS opportunity, making it imperative to land as quickly as possible. 

In a TAL abort, the vehicle continues on a ballistic trajectory across the Atlantic Ocean to 

land at a predetermined runway. Landing occurs approximately 45 minutes after launch. 

The landing site is selected near the nominal ascent ground track of the orbiter in order to 

make the most efficient use of space shuttle main engine propellant. The landing site also 

must have the necessary runway length, weather conditions and U.S. State Department 

approval. Currently, the three landing sites that have been identified for a due east launch 

are Moron, Spain; Dakar, Senegal; and Ben Guerur, Morocco (on the west coast of Africa). 

To select the TAL abort mode, the crew must place the abort rotary switch in the TAL/AOA 

position and depress the abort push button before main engine cutoff. (Depressing it after 

main engine cutoff selects the AOA abort mode.) The TAL abort mode begins sending 

commands to steer the vehicle toward the plane of the landing site. It also rolls the vehicle 

heads up before main engine cutoff and sends commands to begin an orbital maneuvering 

system propellant dump (by burning the propellants through the orbital maneuvering 

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system engines and the reaction control system engines). This dump is necessary to 

increase vehicle performance (by decreasing weight), to place the center of gravity in the 

proper place for vehicle control, and to decrease the vehicle's landing weight. 

TAL is handled like a nominal entry. 

Abort to Orbit 

An ATO is an abort mode used to boost the orbiter to a safe orbital altitude when 

performance has been lost and it is impossible to reach the planned orbital altitude. If a 

space shuttle main engine fails in a region that results in a main engine cutoff under speed, 

the Mission Control Center will determine that an abort mode is necessary and will inform 

the crew. The orbital maneuvering system engines would be used to place the orbiter in a 

circular orbit. 

Abort Once Around 

The AOA abort mode is used in cases in which vehicle performance has been lost to such 

an extent that either it is impossible to achieve a viable orbit or not enough orbital 

maneuvering system propellant is available to accomplish the orbital maneuvering system 

thrusting maneuver to place the orbiter on orbit and the deorbit thrusting maneuver. In 

addition, an AOA is used in cases in which a major systems problem (cabin leak, loss of 

cooling) makes it necessary to land quickly. In the AOA abort mode, one orbital 

maneuvering system thrusting sequence is made to adjust the post-main engine cutoff orbit 

so a second orbital maneuvering system thrusting sequence will result in the vehicle 

deorbiting and landing at the AOA landing site (White Sands, N.M.; Edwards Air Force 

Base; or the Kennedy Space Center). Thus, an AOA results in the orbiter circling the Earth 

once and landing approximately 90 minutes after lift-off. 

After the deorbit thrusting sequence has been executed, the flight crew flies to a landing at 

the planned site much as it would for a nominal entry. 

CONTINGENCY ABORTS 

Contingency aborts are caused by loss of more than one main engine or failures in other 

systems. Loss of one main engine while another is stuck at a low thrust setting may also 

necessitate a contingency abort. Such an abort would maintain orbiter integrity for in-flight 

crew escape if a landing cannot be achieved at a suitable landing field. 

Contingency aborts due to system failures other than those involving the main engines 

would normally result in an intact recovery of vehicle and crew. Loss of more than one main 

engine may, depending on engine failure times, result in a safe runway landing. However, 

in most three-engine-out cases during ascent, the orbiter would have to be ditched. The inflight crew escape system would be used before ditching the orbiter. 

35
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ABORT DECISIONS 

There is a definite order of preference for the various abort modes. The type of failure and 

the time of the failure determine which type of abort is selected. In cases where 

performance loss is the only factor, the preferred modes would be ATO, AOA, TAL and 

RTLS, in that order. The mode chosen is the highest one that can be completed with the 

remaining vehicle performance. 

In the case of some support system failures, such as cabin leaks or vehicle cooling 

problems, the preferred mode might be the one that will end the mission most quickly. In 

these cases, TAL or RTLS might be preferable to AOA or ATO. A contingency abort is 

never chosen if another abort option exists. 

The Mission Control Center-Houston is prime for calling these aborts because it has a more 

precise knowledge of the orbiter's position than the crew can obtain from onboard systems. 

Before main engine cutoff, Mission Control makes periodic calls to the crew to tell them 

which abort mode is (or is not) available. If ground communications are lost, the flight crew 

has onboard methods, such as cue cards, dedicated displays and display information, to 

determine the current abort region. 

Which abort mode is selected depends on the cause and timing of the failure causing the 

abort and which mode is safest or improves mission success. If the problem is a space 

shuttle main engine failure, the flight crew and Mission Control Center select the best 

option available at the time a space shuttle main engine fails. 

If the problem is a system failure that jeopardizes the vehicle, the fastest abort mode that 

results in the earliest vehicle landing is chosen. RTLS and TAL are the quickest options (35 

minutes), whereas an AOA requires approximately 90 minutes. Which of these is selected 

depends on the time of the failure with three good space shuttle main engines. 

The flight crew selects the abort mode by positioning an abort mode switch and depressing 

an abort push button. 

Updated: 05/22/2001 

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STS-105

Shuttle Reference Data 

Space Shuttle Rendezvous Maneuvers 

COMMON SHUTTLE RENDEZVOUS MANEUVERS

OMS-1 (Orbit insertion) - Rarely used ascent abort burn 

OMS-2 (Orbit insertion) - Typically used to circularize the initial orbit following ascent, 

completing orbital insertion. For ground-up rendezvous flights, also considered a 

rendezvous phasing burn 

NC (Rendezvous phasing) - Performed to hit a range relative to the target at a future 

time 

NH (Rendezvous height adjust) - Performed to hit a delta-height relative to the target 

at a future time 

NPC (Rendezvous plane change) - Performed to remove planar errors relative to the 

target at a future time 

NCC (Rendezvous corrective combination) - First on-board targeted burn in the 

rendezvous sequence. Using star tracker data, it is performed to remove phasing and 

height errors relative to the target at Ti 

Ti (Rendezvous terminal intercept) - Second on-board targeted burn in the 

rendezvous sequence. Using primarily rendezvous radar data, it places the Orbiter on a 

trajectory to intercept the target in one orbit 

MC-1, MC-2, MC-3, MC-4 (Rendezvous midcourse burns) - These on-board targeted 

burns use star tracker and rendezvous radar data to correct the post-Ti trajectory in 

preparation for the final, manual proximity operations phase 

Updated: 05/22/2001 

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STS-105

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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STS-105

Additionally, special structural tests were performed on the aft skirt. During this test 

program, an anomaly occurred in a critical weld between the hold-down post and skin of 

the skirt. A redesign was implemented to add reinforcement brackets and fittings in the aft 

ring of the skirt. 

These two modifications added approximately 450 pounds to the weight of each SRB. 

The propellant mixture in each SRB motor consists of an ammonium perchlorate (oxidizer, 

69.6 percent by weight), aluminum (fuel, 16 percent), iron oxide (a catalyst, 0.4 percent), a 

polymer (a binder that holds the mixture together, 12.04 percent), and an epoxy curing 

agent (1.96 percent). The propellant is an 11-point star-shaped perforation in the forward 

motor segment and a double-truncated-cone perforation in each of the aft segments and aft 

closure. This configuration provides high thrust at ignition and then reduces the thrust by 

approximately a third 50 seconds after lift-off to prevent overstressing the vehicle during 

maximum dynamic pressure. 

The SRBs are used as matched pairs and each is made up of four solid rocket motor 

segments. The pairs are matched by loading each of the four motor segments in pairs from 

the same batches of propellant ingredients to minimize any thrust imbalance. The 

segmented-casing design assures maximum flexibility in fabrication and ease of 

transportation and handling. Each segment is shipped to the launch site on a heavy-duty 

rail car with a specially built cover. 

The nozzle expansion ratio of each booster beginning with the STS-8 mission is 7-to-79. 

The nozzle is gimbaled for thrust vector (direction) control. Each SRB has its own 

redundant auxiliary power units and hydraulic pumps. The all-axis gimbaling capability is 8 

degrees. Each nozzle has a carbon cloth liner that erodes and chars during firing. The 

nozzle is a convergent-divergent, movable design in which an aft pivot-point flexible 

bearing is the gimbal mechanism. 

The cone- shaped aft skirt reacts the aft loads between the SRB and the mobile launcher 

platform. The four aft separation motors are mounted on the skirt. The aft section contains 

avionics, a thrust vector control system that consists of two auxiliary power units and 

hydraulic pumps, hydraulic systems and a nozzle extension jettison system. 

The forward section of each booster contains avionics, a sequencer, forward separation 

motors, a nose cone separation system, drogue and main parachutes, a recovery beacon, 

a recovery light, a parachute camera on selected flights and a range safety system. 

Each SRB has two integrated electronic assemblies, one forward and one aft. After 

burnout, the forward assembly initiates the release of the nose cap and frustum and turns 

on the recovery aids. The aft assembly, mounted in the external tank/SRB attach ring, 

connects with the forward assembly and the orbiter avionics systems for SRB ignition 

commands and nozzle thrust vector control. Each integrated electronic assembly has a 

multiplexer/ demultiplexer, which sends or receives more than one message, signal or unit 

of information on a single communication channel. 

39
STS-105

Eight booster separation motors (four in the nose frustum and four in the aft skirt) of each 

SRB thrust for 1.02 seconds at SRB separation from the external tank. Each solid rocket 

separation motor is 31.1 inches long and 12.8 inches in diameter. 

Location aids are provided for each SRB, frustum/drogue chutes and main parachutes. 

These include a transmitter, antenna, strobe/converter, battery and salt water switch 

electronics. The location aids are designed for a minimum operating life of 72 hours and 

when refurbished are considered usable up to 20 times. The flashing light is an exception. 

It has an operating life of 280 hours. The battery is used only once. 

The SRB nose caps and nozzle extensions are not recovered. 

The recovery crew retrieves the SRBs, frustum/drogue chutes, and main parachutes. The 

nozzles are plugged, the solid rocket motors are dewatered, and the SRBs are towed back 

to the launch site. Each booster is removed from the water, and its components are 

disassembled and washed with fresh and deionized water to limit salt water corrosion. The 

motor segments, igniter and nozzle are shipped back to Thiokol for refurbishment. 

Each SRB incorporates a range safety system that includes a battery power source, 

receiver/ decoder, antennas and ordnance. 

HOLD-DOWN POSTS 

Each solid rocket booster has four hold-down posts that fit into corresponding support posts 

on the mobile launcher platform. Hold-down bolts hold the SRB and launcher platform 

posts together. Each bolt has a nut at each end, but only the top nut is frangible. The top 

nut contains two NASA standard detonators, which are ignited at solid rocket motor ignition 

commands. 

When the two NSDs are ignited at each hold-down, the hold-down bolt travels downward 

because of the release of tension in the bolt (pretensioned before launch), NSD gas 

pressure and gravity. The bolt is stopped by the stud deceleration stand, which contains 

sand. The SRB bolt is 28 inches long and is 3.5 inches in diameter. The frangible nut is 

captured in a blast container. 

The solid rocket motor ignition commands are issued by the orbiter''s computers through 

the master events controllers to the hold-down pyrotechnic initiator controllers on the 

mobile launcher platform. They provide the ignition to the hold-down NSDs. The launch 

processing system monitors the SRB hold-down PICs for low voltage during the last 16 

seconds before launch. PIC low voltage will initiate a launch hold. 

SRB IGNITION 

SRB ignition can occur only when a manual lock pin from each SRB safe and arm device 

has been removed. The ground crew removes the pin during prelaunch activities. At T 

minus five minutes, the SRB safe and arm device is rotated to the arm position. The solid 

rocket motor ignition commands are issued when the three SSMEs are at or above 90-

percent rated thrust, no SSME fail and/or SRB ignition PIC low voltage is indicated and 

there are no holds from the LPS. 

40
STS-105

The solid rocket motor ignition commands are sent by the orbiter computers through the 

MECs to the safe and arm device NSDs in each SRB. A PIC single-channel capacitor 

discharge device controls the firing of each pyrotechnic device. Three signals must be 

present simultaneously for the PIC to generate the pyro firing output. These signals--arm, 

fire 1 and fire 2--originate in the orbiter general-purpose computers and are transmitted to 

the MECs. The MECs reformat them to 28-volt dc signals for the PICs. The arm signal 

charges the PIC capacitor to 40 volts dc (minimum of 20 volts dc). 

The fire 2 commands cause the redundant NSDs to fire through a thin barrier seal down a 

flame tunnel. This ignites a pyro booster charge, which is retained in the safe and arm device 

behind a perforated plate. The booster charge ignites the propellant in the igniter initiator; 

and combustion products of this propellant ignite the solid rocket motor initiator, which fires 

down the length of the solid rocket motor igniting the solid rocket motor propellant. 

The GPC launch sequence also controls certain critical main propulsion system valves and 

monitors the engine-ready indications from the SSMEs. The MPS start commands are 

issued by the onboard computers at T minus 6.6 seconds (staggered start--engine three, 

engine two, engine one--all approximately within 0.25 of a second), and the sequence 

monitors the thrust buildup of each engine. All three SSMEs must reach the required 90-

percent thrust within three seconds; otherwise, an orderly shutdown is commanded and 

safing functions are initiated. 

Normal thrust buildup to the required 90-percent thrust level will result in the SSMEs being 

commanded to the lift-off position at T minus three seconds as well as the fire 1 command 

being issued to arm the SRBs. At T minus three seconds, the vehicle base bending load 

modes are allowed to initialize (movement of approximately 25.5 inches measured at the tip 

of the external tank, with movement towards the external tank). 

At T minus zero, the two SRBs are ignited, under command of the four onboard computers; 

separation of the four explosive bolts on each SRB is initiated (each bolt is 28 inches long 

and 3.5 inches in diameter); the two T-0 umbilicals (one on each side of the spacecraft) are 

retracted; the onboard master timing unit, event timer and mission event timers are started; 

the three SSMEs are at 100 percent; and the ground launch sequence is terminated. 

The solid rocket motor thrust profile is tailored to reduce thrust during the maximum 

dynamic pressure region. 

ELECTRICAL POWER DISTRIBUTION 

Electrical power distribution in each SRB consists of orbiter-supplied main dc bus power to 

each SRB via SRB buses A, B and C. Orbiter main dc buses A, B and C supply main dc 

bus power to corresponding SRB buses A, B and C. In addition, orbiter main dc bus C 

supplies backup power to SRB buses A and B, and orbiter bus B supplies backup power to 

SRB bus C. This electrical power distribution arrangement allows all SRB buses to remain 

powered in the event one orbiter main bus fails. 

The nominal dc voltage is 28 volts dc, with an upper limit of 32 volts dc and a lower limit of 

24 volts dc. 

41
STS-105

HYDRAULIC POWER UNITS 

There are two self-contained, independent HPUs on each SRB. Each HPU consists of an 

auxiliary power unit, fuel supply module, hydraulic pump, hydraulic reservoir and hydraulic 

fluid manifold assembly. The APUs are fueled by hydrazine and generate mechanical shaft 

power to a hydraulic pump that produces hydraulic pressure for the SRB hydraulic system. 

The two separate HPUs and two hydraulic systems are located on the aft end of each SRB 

between the SRB nozzle and aft skirt. The HPU components are mounted on the aft skirt 

between the rock and tilt actuators. The two systems operate from T minus 28 seconds 

until SRB separation from the orbiter and external tank. The two independent hydraulic 

systems are connected to the rock and tilt servoactuators. 

The APU controller electronics are located in the SRB aft integrated electronic assemblies 

on the aft external tank attach rings. 

The APUs and their fuel systems are isolated from each other. Each fuel supply module 

(tank) contains 22 pounds of hydrazine. The fuel tank is pressurized with gaseous nitrogen 

at 400 psi, which provides the force to expel (positive expulsion) the fuel from the tank to 

the fuel distribution line, maintaining a positive fuel supply to the APU throughout its 

operation. 

The fuel isolation valve is opened at APU startup to allow fuel to flow to the APU fuel pump 

and control valves and then to the gas generator. The gas generator's catalytic action 

decomposes the fuel and creates a hot gas. It feeds the hot gas exhaust product to the 

APU two-stage gas turbine. Fuel flows primarily through the startup bypass line until the 

APU speed is such that the fuel pump outlet pressure is greater than the bypass line's. 

Then all the fuel is supplied to the fuel pump. 

The APU turbine assembly provides mechanical power to the APU gearbox. The gearbox 

drives the APU fuel pump, hydraulic pump and lube oil pump. The APU lube oil pump 

lubricates the gearbox. The turbine exhaust of each APU flows over the exterior of the gas 

generator, cooling it, and is then directed overboard through an exhaust duct. 

When the APU speed reaches 100 percent, the APU primary control valve closes, and the 

APU speed is controlled by the APU controller electronics. If the primary control valve logic 

fails to the open state, the secondary control valve assumes control of the APU at 112-

percent speed. 

Each HPU on an SRB is connected to both servoactuators on that SRB. One HPU serves 

as the primary hydraulic source for the servoactuator, and the other HPU serves as the 

secondary hydraulics for the servoactuator. Each sevoactuator has a switching valve that 

allows the secondary hydraulics to power the actuator if the primary hydraulic pressure 

drops below 2,050 psi. A switch contact on the switching valve will close when the valve is 

in the secondary position. When the valve is closed, a signal is sent to the APU controller 

that inhibits the 100-percent APU speed control logic and enables the 112-percent APU 

speed control logic. The 100-percent APU speed enables one APU/HPU to supply 

sufficient operating hydraulic pressure to both servoactuators of that SRB. 

42
STS-105

The APU 100-percent speed corresponds to 72,000 rpm, 110-percent to 79,200 rpm, and 

112-percent to 80,640 rpm. 

The hydraulic pump speed is 3,600 rpm and supplies hydraulic pressure of 3,050, plus or 

minus 50, psi. A high-pressure relief valve provides overpressure protection to the hydraulic 

system and relieves at 3,750 psi. 

The APUs/HPUs and hydraulic systems are reusable for 20 missions. 

THRUST VECTOR CONTROL 

Each SRB has two hydraulic gimbal servoactuators: one for rock and one for tilt. The 

servoactuators provide the force and control to gimbal the nozzle for thrust vector control. 

The space shuttle ascent thrust vector control portion of the flight control system directs the 

thrust of the three shuttle main engines and the two SRB nozzles to control shuttle attitude 

and trajectory during lift-off and ascent. Commands from the guidance system are 

transmitted to the ATVC drivers, which transmit signals proportional to the commands to 

each servoactuator of the main engines and SRBs. Four independent flight control system 

channels and four ATVC channels control six main engine and four SRB ATVC drivers, 

with each driver controlling one hydraulic port on each main and SRB servoactuator. 

Each SRB servoactuator consists of four independent, two-stage servovalves that receive 

signals from the drivers. Each servovalve controls one power spool in each actuator, which 

positions an actuator ram and the nozzle to control the direction of thrust. 

The four servovalves in each actuator provide a force-summed majority voting arrangement 

to position the power spool. With four identical commands to the four servovalves, the 

actuator force-sum action prevents a single erroneous command from affecting power ram 

motion. If the erroneous command persists for more than a predetermined time, differential 

pressure sensing activates a selector valve to isolate and remove the defective servovalve 

hydraulic pressure, permitting the remaining channels and servovalves to control the 

actuator ram spool. 

Failure monitors are provided for each channel to indicate which channel has been 

bypassed. An isolation valve on each channel provides the capability of resetting a failed or 

bypassed channel. 

Each actuator ram is equipped with transducers for position feedback to the thrust vector 

control system. Within each servoactuator ram is a splashdown load relief assembly to 

cushion the nozzle at water splashdown and prevent damage to the nozzle flexible bearing. 

SRB RATE GYRO ASSEMBLIES 

Each SRB contains two RGAs, with each RGA containing one pitch and one yaw gyro. 

These provide an output proportional to angular rates about the pitch and yaw axes to the 

orbiter computers and guidance, navigation and control system during first-stage ascent 

flight in conjunction with the orbiter roll rate gyros until SRB separation. At SRB separation, 

a switchover is made from the SRB RGAs to the orbiter RGAs. 

43
STS-105

The SRB RGA rates pass through the orbiter flight aft multiplexers/ demultiplexers to the 

orbiter GPCs. The RGA rates are then mid-value- selected in redundancy management to 

provide SRB pitch and yaw rates to the user software. The RGAs are designed for 20 

missions. 

SRB SEPARATION 

SRB separation is initiated when the three solid rocket motor chamber pressure 

transducers are processed in the redundancy management middle value select and the 

head-end chamber pressure of both SRBs is less than or equal to 50 psi. A backup cue is 

the time elapsed from booster ignition. 

The separation sequence is initiated, commanding the thrust vector control actuators to the 

null position and putting the main propulsion system into a second-stage configuration (0.8 

second from sequence initialization), which ensures the thrust of each SRB is less than 

100,000 pounds. Orbiter yaw attitude is held for four seconds, and SRB thrust drops to less 

than 60,000 pounds. 

The SRBs separate from the external tank within 30 milliseconds of the ordnance firing 

command. 

The forward attachment point consists of a ball (SRB) and socket (ET) held together by one 

bolt. The bolt contains one NSD pressure cartridge at each end. The forward attachment 

point also carries the range safety system cross-strap wiring connecting each SRB RSS 

and the ET RSS with each other. 

The aft attachment points consist of three separate struts: upper, diagonal and lower. Each 

strut contains one bolt with an NSD pressure cartridge at each end. The upper strut also 

carries the umbilical interface between its SRB and the external tank and on to the orbiter. 

There are four booster separation motors on each end of each SRB. The BSMs separate 

the SRBs from the external tank. The solid rocket motors in each cluster of four are ignited 

by firing redundant NSD pressure cartridges into redundant confined detonating fuse 

manifolds. 

The separation commands issued from the orbiter by the SRB separation sequence initiate 

the redundant NSD pressure cartridge in each bolt and ignite the BSMs to effect a clean 

separation. 

Updated: 05/22/2001

44
STS-105

Shuttle Reference Data 

Space Shuttle Super Light Weight Tank (SLWT) 

The super lightweight external tank (SLWT) made its first shuttle flight June 2, 1998, on 

mission STS-91. The SLWT is 7,500 pounds lighter than the standard external tank. The 

lighter weight tank will allow the shuttle to deliver International Space Station elements 

(such as the service module) into the proper orbit. 

The SLWT is the same size as the previous design. But the liquid hydrogen tank and the 

liquid oxygen tank are made of aluminum lithium, a lighter, stronger material than the metal 

alloy used for the shuttle's current tank. The tank's structural design has also been 

improved, making it 30% stronger and 5% less dense. 

The SLWT, like the standard tank, is manufactured at Michoud Assembly, near New 

Orleans, Louisiana, by Lockheed Martin. 

The 154-foot-long external tank is the largest single component of the space shuttle. It 

stands taller than a 15-story building and has a diameter of about 27 feet. The external tank 

holds over 530,000 gallons of liquid hydrogen and liquid oxygen in two separate tanks. The 

hydrogen (fuel) and liquid oxygen (oxidizer) are used as propellants for the shuttle's three 

main engines. 

Updated: 05/22/2001

45
STS-105 

ACRONYMS AND ABBREVIATIONS

A/L Airlock (ISS Joint Airlock) 

AAA Avionics Air Assembly 

AAC Aft Access Cone 

ABC Audio Bus Coupler 

ABOLT Acquire BOLT 

ACBM Active Common Berthing Mechanism 

ACLS Advanced Cardiac Life Support System 

ACO Assembly Checkout Officer 

ACS Assembly Contingency System 

Atmosphere Control and Supply 

Attitude Control System 

ACU Arm Computer Unit 

ADM Antenna Distribution Module 

AIO Analog Input/Output 

AL Airlock (ISS Joint Airlock) 

ALSP Advanced Life Support Pack 

AO Atomic Oxygen 

AOB Assembly Operations Book 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Attachment System 

APCF Advanced Protein Crystallization 

APCU Assembly Power Converter Unit 

APDS Androgynous Peripheral Docking System 

APFR Articulating Portable Foot Restraint 

APM Attached Pressurized Module 

APPCM Arm Pitch Plane Change Mode 

APS Automated Payload Switch 

ARIS Active Rack Isolation System 

AR Atmosphere Revitalization 

ARS Atmospheric Revitalization System 

ASCR Assured Safe Crew Return 

ASL Atmosphere Sampling Line 

ASV Air Selector Valve 

ATCS Active Thermal Control System 

Advanced Television Systems Committee 

ATU Audio Terminal Unit 

AUAI Assembly Contingency System UHF Audio Interface 

AVV Air Vent Valve 

BC Bus Controller 

BCDU Battery Charge/Discharge Units 

BCSS Biotechnology Cell Science Stowage 

BCU Backup Drive Control Unit 

BDU Backup Drive Unit 

46
STS-105 

BGA Beta Gimbal Assembly 

BMRRM Bearing Motor Roll Ring Module 

BMS Bristol Meyers Squibb Science Insert 

BP/ECG Blood Pressure/Electrocardiogram 

BSP Baseband Signal Processor 

BSTC Biotechnology Specimen Temperature Controller 

BTLS Basic Trauma Life Support System 

BTR Biotechnology Refrigerator 

BUS Bus Controller Unit 

C&C Command and Control 

C&DH Command and Data Handling 

C&T Communication and Tracking 

C&W Caution and Warning 

C/L Crew Lock 

CA Control Attitude 

CB Control Bus 

CBM Common Berthing Mechanism 

CCAA Common Cabin Air Assembly 

CCD Cursor Control Device 

CCTV Closed Circuit Television 

CDDT Common Display Development Team 

CDRA Carbon Dioxide Removal System 

CDS Command and Data Software 

CETA Crew Equipment Translation Aid 

CEU Control Electronics Unit 

CFA Cabin Fan Assembly 

CheCS Crew Health Care System 

CHX Condensing Heat Exchanger 

CMO Crew Medical Officer 

CMRS Crew Medical Restraint System 

Comm Communications 

COTS Commercial-Off-The-Shelf 

CPCG-H Commercial Protein Crystal Growth-High Density 

CPFSK Continuous Phase Frequency Shift Keying 

CPU Central Processing Unit 

CRT Cathode Ray Tube 

CSA-CP Compound Specific Analyzer-Combustion Products 

CSA-H CSA-Hydrazine 

CSCI Computer S/W Configuration Item 

CSM Cargo Systems Manual 

CSV CO2 Selector Valve 

CTB Cargo Transfer Bag 

CTV Crew Transfer Vehicle 

CVIU Common Video Interface Unit 

CVT Current Valve Table 

47
STS-105 

CVV Carbon dioxide Vent Valve 

CWC Contingency Water Container 

CWR Collapsible Water Reservoir 

DA Depressurization Assembly 

DAIU Docked Audio Interface Unit 

DAK Double-Aluminized Kapton 

DCP Display and Control Panel 

DCPCG-V Dynamically Controlled Protein Crystal Growth-Vapor 

DCSU Direct Current Switching Unit 

DIO Discrete input/output 

DMCU Docking Mechanism Control Unit 

DOF Degrees-of-Freedom 

DPA Data Processing Assembly 

DPS Data Processing System 

E/L Equipment Lock 

EACP EMU Audio Control Panel 

EAIU EMU Audio Interface Unit 

EAS Early Ammonia Servicer 

ECB Electronics Control Board 

ECG Electrocardiogram 

ECLSS Environmental Control and Life Support System 

ECS Early Communications Subsystem 

ECU Electronic Control Unit 

EDDA EMU Don/Doff Assembly 

EEATCS Early External Active Thermal Control System 

EELS Emergency Egress Lighting System 

EET Experiment Elapsed Time 

EETCS Early External Thermal Control System 

EFGF electrical flight grapple fixture 

ELPS Emergency Lighting Power Supply 

ELS Emergency Lighting Strip 

EMA Engagement Mechanism Assembly 

EMU Extravehicular Maneuvering Unit 

 EXPRESS Memory Unit 

EPLS Emergency Lighting Power Supply 

EPS Electrical Power System 

EV-CPDS Extravehicular-Charged Particle Directional Spectrometer 

EVA Extravehicular Activity 

EVR Extravehicular Robotics 

EXPRESS Expedite the Processing of Experiments to the Space Station 

FC Firmware Controller 

FCC Flat Collector Circuit 

Federal Communications Commission 

FCV Flow Control Valve 

48
STS-105 

FD Flight Day 

FDA Fault Detection Annunciation 

FDI Failure Detection and Isolation 

FDS Fire Detection and Suppression 

FGB Functional Cargo Block 

FPU Fluid Pumping Unit 

FRGF Flight Releasable Grapple Fixture 

FSE Flight Support Equipment 

FSEGF FSE Grapple Fixture 

GC Growth Cell 

GFE Government Furnished Equipment 

GLA General Lighting Assembly 

GLONASS Global Navigational Satellite System 

GMT Greenwich Mean Time 

GNC Guidance and Navigation Computer 

GPC General Purpose Computer 

GPS Global Positioning System 

GSE Ground Support Equipment 

GSFC Goddard Space Flight Center 

GSM Gas Supply Module 

GUI Graphical User Interface 

HCU Headset Control Unit 

HDR High Data Rate 

HDPCG High Density Protein Crystal Growth 

HDTV High Definition Television 

HEAT Hitchhiker Experiment Advancing Technology 

HEC Headset Extension Cable 

HEPA High-Efficiency Particulate Arrestor (a filter for the CCAA) 

HESE Hitchhiker Eject System Electronics 

HGA High Gain Antenna 

HLA High Level Analog 

HPGT High Pressure Gas Tank (see ONTO) 

HRF Human Research Facility 

HRFM High Rate Frame Multiplexer 

HRM High Rate Modem 

 Heart Rate Monitor 

I/O Input/Output 

IAA Internal Antenna Assembly 

IAC Internal Audio Controller 

IAS Internal Audio System 

ICC Integrated Cargo Carrier 

ICM Isothermal Containment Module 

IEA Integrated Equipment Assembly 

IELK Individual Equipment Liner Kit 

49
STS-105 

I/F Interface 

IFHX Interface Heat Exchanger 

IMS Inventory Management System 

IMV Intermodule Ventilation 

IOCU Input/Output Controller Unit 

IP International Partner 

IRU In-flight Refill Unit 

ISA International Sampling Adapter 

ISIS International Subrack Interface Standard 

ISPR International Standard Payload Rack 

ISS International Space Station 

ISSIS International Space Station Interface Standard 

ISSP International Space Station Program 

ISSSH International Space Station Systems Handbook 

ITCS Internal Thermal Control System 

IV-CPDS Intravehicular-Charged Particle Directional Spectrometer 

IVA Intervehicular Activity 

JEU Joint Electronics Unit 

JEUS Joint Expedited Undocking and Separation 

JSC Johnson Space Center 

KBAR Knee-Brace Assembly Replacement 

KSSL Krug Single-Stowage Lock 

KYA Keel Yoke Assembly 

LAN Local Area Network 

LaRC Langley Research Center 

LB Local Bus 

LCA Lab Cradle Assembly 

LCD Liquid Crystal Display 

LCP Lower Connector Panel 

LDA Launch Deployment Assembly 

LDR Low Data Rate 

LEE Latching End Effector (both SRMS and SSRMS) 

LED Light Emitting Diode 

LFDP Load Fault Detect/Protect 

LGA Low Gain Antenna 

LLA Low Level Analog 

LRU Line Replaceable Unit 

LTA Launch to Activiation 

LTL Low Temperature Loop 

MA Mechanical Assembly 

MAM Manual Augmented Mode 

Mb Megabytes 

MBM Manual Berthing Mechanism 

50
STS-105 

MBSU Main Bus Switching Unit 

MCA Major Constituent Analyzer 

MCC Mission Control Center 

MCC-H MCC-Houston 

MCC-M MCC-Moscow 

MCDS Multifunction CRT Display System 

MCS Motion Control System 

MDM Multiplexer/Demultiplexer 

MDPS Meteoroid and Debris Protection System 

MEEP Mir Environment Effects Payload 

METOX Metal Oxide (for CO2 removal) 

MIP Mission Integration Plan 

MISSE Materials ISS Experiment 

MLE Middeck Locker Equivalent 

MLI Multilayer Insulation 

MMOD Micrometeoroid Orbital Debris 

MOD Mission Operations Directorate 

MPEV Manual Pressure Equalization Valve 

MPLM Multi-Purpose Logistics Module 

MPMs/MRLs Manipulator Positioning Mechanisms/ 

Manipulator Retention Latches 

MPR Manual Pulmonary Resuscitator 

MR Medium Rate 

MSD Mass Storage Device 

MSFC Marshall Space Flight Center 

MSS Mobile Servicing System 

MT Mobile Transporter 

MTL Moderate Temperature Loop 

MUP Mission Unique Process 

N2 Nitrogen (DI-molecular) 

NCS Node Control Software 

NET No Earlier Than 

NiCD Nickel Cadmium 

NGTC Next Generation Thermal Control 

NIV Nitrogen Isolation Valve 

NMS Nitrogen Management System 

NPRA Negative Pressure Relief Assembly 

NST Near Saturation Threshold 

NPRV Negative Pressure Relief Valve 

NSTC National Television Systems Committee 

O2 Oxygen (DI-molecular) 

OCA Orbital Communication Adapter 

OCAD Operational Control Agreement Document 

OCJM Operator Commanded Joint Position Mode 

OCPM Operator Commanded POR Mode 

51
STS-105 

ODA Orbiter Disconnect Assembly 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

OIV Oxygen Isolation Valve 

ONS Off Nominal 

ONTO Oxygen Nitrogen Tank ORU (see HPGT) 

OPP OSVS Patch Panel 

OPS Operations (Operational) 

OPS LAN Operations Local Area Network 

ORCA Oxygen Recharge Compressor Assembly 

ORU Orbital Replacement Unit 

OSE Orbital Support Equipment 

OSVS Orbiter Space Vision System 

OSVU Orbiter Space Vision Unit 

PAV Process Air Valve 

PB Power Bus 

PBA Portable Breathing Apparatus (mask) 

PCA Pressure Control Assembly 

PCBA Portable Clinical Blood Analyzer 

PCBM Passive Common Berthing Mechanism 

PCMCIA Personal Computer Memory Card International Adapter 

PCMMM Pulse Code Master Modulation Unit 

PCP Pressure Control Panel 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PDB Power Distribution Box 

PDGF Power and Data Grapple Fixture 

PDI Payload Data Interface 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PEC Passive Experiment Container 

PEHB Payload Ethernet Hub Bridge 

PEHG Payload Ethernet Hub Gateway 

PEP Portable Emergency Provision 

PES Pallet Ejection System 

 Payload Ejection System 

PEV Pressure Equalization Valve 

PFCS Pump Flow Control Subassembly 

PFE Portable Fire Extinguisher 

PG Product Group 

PIHPC Permanent International Human Presence Capability 

PJAM Pre-Stored Joint Position Auto-sequence Mode 

PL Payload 

PMA Pressurized Mounting Panel 

Pressurized Mating Adapter 

52
STS-105 

PMP Payload Mounting Panel 

ppO2 partial pressure of Oxygen 

POIC Payload Operations Integration Center 

POR Points of Reference 

PPA Pump Package Assembly 

PPAM Pre-stored POR Auto-sequence Mode 

PPP Power Patch Panel 

PPRA Positive Pressure Relief Assembly 

PPRV Positive Pressure Relief Valve 

PRLA Payload Retention Latch Assembly 

PSA Power Supply Assembly 

psia pounds per square inch – absolute 

psid pounds per square inch – differential 

PSP Payload Signal Processor 

PTCS Passive Thermal Control System 

PTT Push To Talk 

PTU Pan/Tilt Units 

PUNT Peremptory Unilateral Network Tracking 

PV Photovoltaic 

PVM Photovoltaic Module 

PWP Power Work Platform 

QD Quick Disconnect 

QTCM Quad Tissue Culture Module 

QTCMA QTCM Assembly 

 

R&MA Restraint and Mobility Aids 

R-S Reed-Solomon 

R/F refrigerator/freezer 

RAIU Russian Audio Interface Unit 

RAM Random Access Memory 

RAMV Rheostat Air Mix Valve 

RAB Rack Attachment Block 

RCU Remote Control Unit 

RED Resistive Exercise Device 

RF Radio Frequency 

RFCA Rack Flow Control Assembly 

RFG Radio Frequency Group 

RGS Russian Ground Site 

RHC Rotational Hand Controller 

RHX Regenerative Heat Exchanger 

RIC Rack Interface Controller 

ROEU Remote Operated Electrical Umbilical 

ROFU Remote Operated Fluid Umbilical 

ROS Russian Orbital Segment 

RPC Remote Power Controller 

53
STS-105 

RPCM Remote Power Controller Module 

RPDA Remote Power Distribution Assembly 

RS Russian Segment 

RSA Russian Space Agency 

RSC-E Rocket Space Corporation – Energia 

RSP Resupply Support Platform 

RSR Resupply Stowage Rack 

RT Remote Terminal 

RTL Ready to Launch 

RWS Robotic Workstation 

SASA S-Band Antenna Support Assembly 

SAW Solar Array Wing 

SCA Switchgear Controller Assembly 

SCSI Serial Command and Monitoring Interface 

SCU Servicing and Cooling Umbilical 

Sync and Control Unit 

SD Smoke Detector 

SDO Solenoid Driver Output 

SDS Sample Delivery System 

SEM Space Experiment Module 

SGANT Space-to-Ground Antenna 

SJRM Single Joint Rate Mode 

SLDP Spacelab Logistics Double Pallet 

SOC State of Charge 

SM Service Module 

SPCE Servicing and Performance Checkout Equipment 

SPDA Secondary Power Distribution Assembly 

SPDM Special Purpose Dextrous Manipulator 

SPDU Secondary Power Distribution Unit 

SPP Science Power Platform 

SRMS Shuttle Remote Manipulator System 

SSC Station Support Computer 

Subsystem Computer 

SSCS Space-to-Space Communication System 

SSE Space Station Eyewash 

SSER Space-to-Space EMU Radio 

SSOR Space-to-Space Orbiter Radio 

SSOV Sample line Shut-off Valve 

SSP Space Shuttle Program 

Standard Switch Panel 

SSPC Solid State Power Controller 

SSPCM Solid State Power Control Module 

SSRMS Space Station Remote Manipulator System 

SSSR Space-to-Space Station Radio 

SSU Sequential Shunt Unit 

54
STS-105 

STIPL Standard Interface Plate 

STS Space Transportation System 

SW Software 

TA Thruster Assist 

TCCS Trace Contaminant Control Subassembly 

TCCV Temperature Control and Check Valve 

TCS Thermal Conditioning System 

Thermal Control System 

TDMA Time Division Multiple Access 

TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

TEPC Tissue Equivalent Proportional Counter 

TFL Telemetry Format Load 

THC Temperature and Humidity Control 

Translationall Hand Controller 

TOCA Total Organic Carbon Analyzer 

TRC Transmitter Receiver Controller 

TVIS Treadmill Vibration Isolation System 

UB User Bus 

UCP Unpressurized Cargo Pallet 

UIA Umbilical Interface Assembly 

UIP Utility Interface Panel 

UHF Ultrahigh Frequency 

UOP Utility Outlet Panel 

USOS United States Orbital Segment 

VAJ Vacuum Access Jumper 

VBSP Video Baseband Signal Processor 

Vdc Volts (direct current) 

VDS Video Distribution System 

VDU Video Distribution Unit 

VES Vacuum Exhaust System 

VES/VRS Vacuum Exhaust/Resource System 

VGS Video Graphics Software 

VMDS Valve Motor Drive Switch 

VOX Voice Operated Transmission 

VPMP Vented PMP 

VRCV Vent/Relief Control Valve 

VRIV Vent/Relief Isolation Valve 

VRS Vacuum Resource System 

VRV Vent/Relief Valve 

VSC Video Signal Converter 

VSU Video Switch Unit 

VTR Video Tape Recorder 

55
STS-105 

WAA Wireless Antenna Assembly 

WHS Workstation Host Software 

WIF Worksite Interface 

WIU Wireless Interface Unit 

WMV Water Modulating Valve 

WOV Water ON/OFF Valve 

WPP Water Pump Package 

WRM Water Recovery and Management 

WS Water Separator 

WVA Water Vent Assembly 

ZSR Zero-g Stowage Rack 

56
STS-105

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, FL; Marshall Space Flight Center, 

Huntsville, AL; Dryden Flight Research Center, Edwards, CA; Johnson Space Center, 

Houston, TX; 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 newscenter 

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

 

57
STS-105

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. 

58
STS-105

Media Contacts 

NASA PAO CONTACTS

Carlos Fontanot 256 961-6225

NASA Johnson Space Center

Houston, TX

NASA Moscow PAO

carlos.fontanot1@jsc.nasa.gov

Glen Golightly 714 372 4742

The Boeing Company

Huntington Beach, CA

Space Shuttle

robert.g.golightly@boeing.com

Bruce Buckingham 321 867-2468

NASA Kennedy Space Center

Kennedy Space Center, FL

Launch Operations

bruce.buckingham-1@kmail.ksc.nasa.gov

Dan Beck 818 586-4572

Boeing Rocketdyne

Canoga Park, CA

Space Shuttle Main Engines

daniel.c.beck@boeing.com

Debbie Rahn 202 358-1638

NASA Headquarters

Washington, DC

International Partners

debbie.rahn@hq.nasa.gov

Dwayne Brown 202 358-1726

NASA Headquarters

Washington, DC

Space Shuttle/Space Station 

Policy

dwayne.brown@hq.nasa.gov

59
STS-105

Eileen Hawley 281 483-5111

NASA Johnson Space Center

Houston, TX

Astronauts/Mission Operations

eileen.hawley1@jsc.nasa.gov

Jack King 321 861-4358

United Space Alliance

Kennedy Space Center, FL

Shuttle Processing

KingJW@usafoo.unitedspacealliance.com

Kari Kelley Allen 281 336-4844

The Boeing Company

Houston, TX

International Space Station

kari.k.allen@boeing.com

Kyle Herring 281 483-5111

NASA Johnson Space Center

Houston, TX

International Space Station 

Operations

kyle.j.herring1@jsc.nasa.gov

June Malone 256 544-0031

NASA Marshall Space Flight Center

Huntsville, AL

Space Station Science

June.Malone@msfc.nasa.gov

60
Table prepared by Richard W. Orloff, 06/02/2002 

SHUTTLE FLIGHTS AS AUGUST 2001 

105 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 80 SINCE RETURN TO FLIGHT 

STS-102 

03/08/01 – 03/21/01 

STS-92 

10/11/00 - 10/24/00 

STS-103 

12/19/99 - 12/27/99 

STS-93 

07/23/99 - 07/27/99 

STS-96 

05/27/99 - 06/06/99 

STS-90 

04/17/98 - 05/03/98 

STS-95 

10/29/98 - 11/07/98 

STS-87 

11/19/97 - 12/05/97 

STS-91 

06/02/09 - 06/12/98 

STS-104 

07/12/01 – 07/24/01 

STS-94 

07/01/97 - 07/17/97 

STS-85 

08/07/97 - 08/19/97 

STS-98 

02/07/01 - 02/20/01 

STS-83 

04/04/97 - 04/08/97 

STS-82 

02/11//97 - 02/21/97 

STS-106 

09/08/00 - 09/20/00 

STS-80 

11/19/96 - 12/07/96 

STS-70 

07/13/95 - 07/22/95 

STS-101 

05/19/00 - 05/29/00 

STS-78 

06/20/96 - 07/07/96 

STS-63 

02/03/95 - 02/11/95 

STS-86 

09/25/97 - 10/06/97 

STS-75 

02/22/96 - 03/09/96 

STS-64 

09/09/94 - 09/20/94 

STS-84 

05/15/97 - 05/24/97 

STS-73 

10/20/95 - 11/05/95 

STS-60 

02/03/94 - 02/11/94 

STS-81 

01/12/97 - 01/22/97 

STS-65 

07/08/94 - 07/23/94 

STS-51 

09/12/93 - 09/22/93 

STS-79 

09/16/96 - 09/26/96 

STS-62 

03/04/94 - 03/18/94 

STS-56 

04/08/83 - 04/17/93 

STS-76 

03/22/96 - 03/31/96 

STS-100 

04/19/01 – 05/01/01 

STS-58 

10/18/93 - 11/01/93 

STS-53 

12/02/92 - 12/09/92 

STS-74 

11/12/95 - 11/20/95 

STS-97 

11/30/00 - 12/11/00 

STS-55 

04/26/93 - 05/06/93 

STS-42 

01/22/92 - 01/30/92 

STS-71 

06/27/95 - 07/07/95 

STS-99 

02/11/00 - 02/22/00 

STS-52 

10/22/92 - 11/01/92 

STS-48 

09/12/91 - 09/18/91 

STS-66 

11/03/94 - 11/14/94 

STS-88 

12/04/98 - 12/15/98 

STS-50 

06/25/92 - 07/09/92 

STS-39 

04/28/91 - 05/06/91 

STS-46 

07/31/92 - 08/08/92 

STS-89 

01/22/98 - 01/31/98 

STS-40 

06/05/91 - 06/14/91 

STS-41 

10/06/90 - 10/10/90 

STS-45 

03/24/92 - 04/02/92 

STS-77 

05/19/96 - 05/29/96 

STS-35 

12/02/90 - 12/10/90 

STS-51L 

01/28/86 

STS-31 

04/24/90 - 04/29/90 

STS-44 

11/24/91 - 12/01/91 

STS-72 

01/11/96 - 11/20/96 

STS-32 

01/09/90 - 01/20/90 

STS-61A 

10/30/85 - 11/06/85 

STS-33 

11/22/89 - 11/27/89 

STS-43 

08/02/91 - 08/11/91 

STS-69 

09/07/95 - 09/18/95 

STS-28 

08/08/89 - 08/13/89 

STS-51F 

07/29/85 - 08/06/85 

STS-29 

03/13/89 - 03/18/89 

STS-37 

04/05/91 - 04/11/91 

STS-67 

03/02/95 - 03/18/95 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

STS-38 

11/15/90 - 11/20/90 

STS-68 

09/30/94 - 10/11/94 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-36 

02/28/90 - 03/04/90 

STS-59 

04/09/94 – 04/20/94 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-34 

10/18/89 - 10/23/89 

STS-61 

12/02/93 - 12/13/93 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-30 

05/04/89 - 05/08/89 

STS-57 

06/21/93 - 07/01/93 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-27 

12/02/88 - 12/06/88 

STS-54 

01/13/93 - 01/19/93 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-47 

09/12/92 - 09/20/92 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

STS-49 

05/07/92 - 05/16/92 

OV-102 

Columbia 

(26 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(29 flights) 

OV-104 

Atlantis 

(24 flights) 

OV-105 

Endeavour 

(16 flights)