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Updated Mar. 6, 2001

STS-98

DISCOVERY: 

OUTFITTING DESTINY
STS-102 

Table of Contents

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

Mission Objectives ....................................................................................................... 6 

Crew Members ............................................................................................................ 11 

Flight Day Summary Timeline ................................................................................... 16 

Rendezvous ................................................................................................................ 17 

EVAs 

STS-102 EVA ............................................................................................................. 19 

Payloads 

Leonardo – A Space Age Moving Van.......................................................................... 22 

Integrated Cargo Carrier............................................................................................... 24 

Passive Dosimeter System........................................................................................... 26 

Space Experiment Module Carrier System................................................................... 28 

Wide-Band Shuttle Vibration Force Measurement........................................................ 30 

Get-Away Special ......................................................................................................... 31 

DTO/DSO/RME 

DSO 493 Monitoring Latent Virus Reactivation and Shedding in Astronauts................ 32 

DSO 496 Individual Susceptibility to Post-Space Flight Orthostatic Intolerance........... 33 

DSO 498 Space Flight and Immune Function (pre-/postflight only).............................. 34 

DTO 805 Crosswind Landing Performance .................................................................. 35 

DTO 261 International Space Station On-Orbit Loads Validation ................................. 36 

DTO 263 Shuttle Automatic Reboost Tuning................................................................ 37 

DTO 700-14 Single-String Global Positioning System.................................................. 38 

DTO 257 Structural Dynamics Model Validation........................................................... 39 
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Shuttle Reference and Data 

Shuttle Abort History ................................................................................................... 40 

Shuttle Abort Modes ................................................................................................... 42 

Space Shuttle Rendezvous Maneuvers ...................................................................... 46 

Space Shuttle Solid Rocket Boosters ......................................................................... 47 

Space Shuttle Super-Lightweight Tank (SLWT) ......................................................... 54 

Acronyms and Abbreviations .................................................................................. 55 

Media Assistance ...................................................................................................... 66 

Media Contacts ......................................................................................................... 68
STS-102

Mission Overview 

New Crew, New Lab Racks to be Launched to ISS 

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

Logistics Module and the first scientific rack for the U.S. laboratory Destiny highlight the 

STS-102 mission of Discovery, scheduled for launch no earlier than March 8 from Kennedy 

Space Center in Florida. The crew changeout is the first for the ISS, and the logistical 

module, named Leonardo, is the first of three that will serve as pressurized moving vans, 

bringing equipment and supplies to the space station. 

Aboard Leonardo will be the Human Research Facility scientific rack to be installed aboard 

Destiny, the scientific cornerstone of the ISS. Destiny is the most advanced and most 

versatile scientific research facility ever launched into space, and the Human Research 

Facility enables the U.S. laboratory to begin to fulfill the purpose and the promise for which 

it - and the entire International Space Station - is being created. The space station 

eventually will have six laboratories. 

Leonardo will be lifted out of Discovery's payload bay and attached directly to Destiny for 

the unloading of its cargo, which includes half a dozen systems racks and the Human 

Research Facility experiment rack. The systems racks will provide electrical power and 

control of the station's robotic arm supplied by Canada, which will arrive on the next 

assembly mission. One rack will contain emergency crew health care equipment. Near the 

end of the shuttle's mission, the MPLM will be returned to the cargo bay and returned to 

Earth for refurbishment and reuse on a mission this summer. The MPLM is valued at $150 

million. 

James D. Wetherbee, commanding his fourth mission and making his fifth flight into space, 

leads the shuttle crew. He brings a unique management perspective to this operational role 

on this flight. He served as deputy director of the Johnson Space Center, and now is chief 

of Flight Crew Operations. Pilot James M. Kelly, a former Air Force test pilot, is making his 

first space flight. Australian-born Mission Specialist Andrew S.W. Thomas spent 141 days 

and 2,250 orbits aboard the Russian Mir space station. Mission Specialist Paul W. 

Richards, also making his first space flight, worked as a NASA engineer at the Goddard 

Space Flight Center, developing tools for space walkers for the Hubble Space Telescope 

Servicing Project before being selected as an astronaut in 1996. 

Because of the space station crew replacement, three crews will be involved in the flight of 

Discovery. The orbiter will carry Expedition Two Commander Yury Vladimirovich Usachev, 

and Flight Engineers James S. Voss and Susan J. Helms to the ISS to replace the 

Expedition One crew, Commander William M. Shepherd and cosmonauts Soyuz 

Commander Yuri Pavlovich Gidzenko and Flight Engineer Sergei Konstantinovich Krikalev, 

who arrived aboard the station on Nov. 2, 2000. Expedition One crewmembers will come 

home in Discovery. 

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About 41 hours after its launch Discovery is scheduled to dock with the International Space 

Station. In addition to the new crew and the Multipurpose Logistics Module, Discovery also 

brings to the ISS the Integrated Cargo Carrier and two Assembly Power Converter Units 

(APCU's) in the orbiter's cargo bay, and ISS equipment and supplies in the Orbiter crew 

compartment. The Integrated Cargo Carrier carries the Pump and Flow Control 

Subassembly, the Lab Cradle Assembly, the External Stowage Platform, and the Rigid 

Umbilical which are attached or installed on the ISS during the two scheduled space walks. 

A Quick Look at the STS-102 Mission 

Discovery will spend almost eight days attached to the ISS. Transfer of equipment begins 

less than three hours after docking, which occurs during the crew's flight day three. Later in 

flight day three, hatches will be closed so pressure in Discovery's cabin can be lowered in 

preparation for a space walk. 

The first of two space walks scheduled for flight day four will see Voss and Helms prepare 

for the relocation of one of the docking ports attached to the ISS Unity module to prepare 

for MPLM docking. Leonardo must be attached to the lower port of Unity to facilitate its 

unloading. The space walkers also will install a cradle keel mechanism on the roof of 

Destiny, which will be used later in the ISS assembly sequence to mount additional 

hardware. Voss and Helms also will install an umbilical cable tray on Destiny in preparation 

for the delivery of the ISS' robotic arm in April. 

A highlight of flight day five will be installation of Leonardo to Unity using the orbiter's 

robotic arm. 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 

systems racks from Leonardo to the U.S. lab Destiny, while Discovery crewmembers focus 

on the mission's second space walk. During this space walk, Thomas and Richards will 

install a stowage bin to the truss and deliver a replacement pump system that would be 

used to help ammonia flow to critical avionics on the ISS, if required. 

Italian-built Leonardo brings to the new U.S. laboratory Destiny six system racks. Two are 

DC-to-DC Converter Unit (DDCU) racks to convert power into a suitable form for ISS 

experiments and other station activities. Two are robotic workstation racks for control of the 

station's Canadian robotic arm and its four cameras, starting on Mission 6A. The Avionics 

No. 3 Rack has the hardware to activate the Ku-Band and some orbital replacement units 

for other systems. The Temporary Crew Health System Rack contains emergency medical 

equipment, including a defibrillator. Leonardo also is bringing equipment and supplies to 

the ISS in three resupply stowage racks and four resupply stowage platforms. Leonardo 

can transport as many as 16 racks in its 2,698 cubic feet. 

The arrival aboard Leonardo of the first scientific rack for the U.S. laboratory is significant in 

that it is a major step toward the beginning of scientific research aboard the space station. 

The Human Research Facility is a milestone, which will mark the beginning of major 

scientific research capability aboard the space station. 

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

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

systems racks, and one slot has Destiny's 20-inch-diameter, optical-quality window. 

Remaining slots are available for scientific racks. 

Flight day seven will focus on transfer of equipment and supplies to the station from 

Discovery and from Leonardo, as well as stowage of equipment from the station to 

Leonardo. Several hours are allotted for handover sessions with the Expedition One and 

Expedition Two crews. 

Crew transfer is a carefully thought out and choreographed process carried out one 

replacement at a time. As a member of the Expedition Two crew formally transfers from the 

shuttle to the ISS, that crewmember’s custom-designed 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. Usachev and Gidzenko make the switch on flight 

day three, Krikalev and Voss on flight day five and Shepherd and Helms on flight day 

seven. 

Equipment and supply transfer operations are scheduled during flight day eight. Transfer 

activities continue on flight day nine. 

The crew will leave Leonardo and deactivate the MPLM on flight day 10. Loaded with 

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

to be taken back to the Kennedy Space Center. 

Discovery departs the space station on the crew's flight day 11 and is scheduled to land at 

Kennedy Space Center a little more than two days later, no earlier than March 20. 

STS-102 is the eighth space shuttle mission in support of space station assembly, the 29th 

mission of Discovery and the 103rd flight in shuttle program history. 

Expedition One Crew Return Plans

Concluding a four-month stay in space, the first resident crew of the International Space 

Station will feel the effects of gravity for the first time as Discovery touches down at the 

Kennedy Space Center. 

In space, many of the body's systems, which were designed for the one-gravity 

environment of Earth, are subjected to fewer demands than normal. The heart is not 

required to work as hard to pump blood through the body; bones and muscles are not used 

as intensively; and the brain must learn to adapt to altered input as the inner ear, eyes, 

muscles and joints no longer have the constant of gravity as an indicator of position and 

orientation. Living in a microgravity environment, astronauts learn to modify the way they 

eat, move, and operate equipment, and how to respond to the internal changes 

experienced by their bodies. 

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Living in such an environment since their Oct. 31 launch from the Baikonur Cosmodrome, 

Expedition One Commander Bill Shepherd, Pilot Yuri Gidzenko and Flight Engineer Sergei 

Krikalev observed a strict regimen of exercise designed to maintain both cardiovascular 

health and muscle and bone strength. Exercise is an effective countermeasure to the 

physiological effects of microgravity and can reduce the amount of time required for an 

astronaut to readapt. 

When the Expedition One crew returns on board Discovery, they will spend several weeks 

readjusting to life on Earth. Just as they had to respond to altered sensory inputs in space, 

they will need to readjust their bodies back to the sensation of gravity. The time required to 

readapt is related to the duration of the mission. 

American and Russian flight surgeons, and strength, conditioning and rehabilitation 

specialists, will work with the crewmembers to ensure their adaptation and begin a period 

of rehabilitation to restore bone and muscle strength. Researchers also will gather data on 

the three crewmembers to expand the existing knowledge of the effects of long-term flight 

on the human body. 

Shepherd, Gidzenko and Krikalev will be seated in specially-designed recumbent seats on 

Discovery's middeck for entry and landing. Returning to Earth in this reclined position, 

allows the g-forces experienced during re-entry and landing to be distributed more evenly 

through the astronaut's body, allowing them to adapt more gradually to the presence of 

gravity. 

Returning astronauts, including Shepherd, Gidzenko and Krikalev, may experience 

orthostatic intolerance, a feeling of light headedness or fainting when standing in an upright 

posture, as they return to Earth. Returning to Earth in these recumbent seats, rather than 

sitting in an upright position, reduces the effects of orthostatic intolerance. The light 

headedness occurs when gravity pulls fluids downward, away from the heart and head. 

Recovery is generally rapid and there are no requirements for the Expedition One crew to 

be removed from Discovery in a reclining position. 

The crew will not be medically monitored during the re-entry, but will undergo routine postflight evaluations by flight surgeons shortly after landing. Shepherd, Gidzenko and Krikalev 

then will join their STS-102 crew mates in the crew quarters building at the Kennedy Space 

Center for a brief reunion with their families before undergoing more extensive physical 

exams. 

One day after landing, the combined STS-102 and Expedition One crews will return to 

Houston. 

The Expedition One crewmembers will begin a rehabilitation and medical observation 

period of approximately 45 days, as flight surgeons and rehabilitation specialists work with 

them to assist in their readaptation to life on Earth. Gidzenko and Krikalev will continue 

their rehabilitation program following their return to Russia, within a few weeks after 

landing. 

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The rehabilitation program is highly individualized for each crew member. The length, 

duration and intensity of the rehabilitation sessions will be influenced by feedback from 

each crewmember, the rehabilitation specialist and the attending crew surgeon. In general, 

the program begins with massage, assisted walking, stretching and mild resistance 

exercise, water exercise and manual resistance exercise. 

The following table outlines the basic rehabilitation plan for the first seven days: 

R+1 Assisted Walking 0-100 steps 

Total Body PNF (hold/relax/stretch) 1 set: 2 seconds concentric 

 4 seconds eccentric 

Massage/Sauna/Whirlpool 

R+2 Crew Day Off 

Suggest assisted walking & flexibility 

R+3 Assisted or Unassisted Walking 100 steps - 1 mile 

Total Body PNF (hold/relax/stretch 2 sets: 2 seconds concentric 

 4 seconds eccentric 

Massage/Sauna/Whirlpool 

R+4 Water Exercise Therapy Warmup/Flexibility 

Cardio Workout 

Strength Training 

Cool Down/Flexibility 

R+5 Cardio Workout: 12-15 minutes 

(recumbent bike, orbiter treadmill, etc) 

Flexibility Total Body 

Strength Training 1-3 sets x 12-15 reps 

Massage/Flexibility 

R+6 Water Exercise Therapy Warmup/Flexibility 

Cardio Workout 

Strength Training 

Cool Down/Flexibility 

R+7 Cardio Workout: 15-20 minutes 

Flexibility Total Body 

Strength Training 1-3 sets x 12-15 reps 

Massage/Flexibility 

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Mission Objectives 

Discovery OV103

Launch: Thursday, March 08, 2001 

 6:42 AM (eastern time) 

Discovery's STS-102 (5A.1) flight is focused on outfitting the International Space Station 

(ISS), particularly the new U.S. laboratory, Destiny. It also will bring to the station the 

new Expedition Two crew, to replace the Expedition One crew which will come home on 

Discovery. 

The crew transfer, the first for the station, is among the mission's top priorities. 

Expedition One Commander Bill Shepherd, Soyuz Commander Yuri Gidzenko and 

Flight Engineer Sergei Krikalev will be replaced by Expedition Two Commander Yury 

Usachev and Expedition Two flight engineers Susan Helms and Jim Voss. 

The transfer will take place in a carefully orchestrated, one-at-a-time process that ensures 

three current members of the station crew will be able to come home, at any time during 

the switch, aboard the Soyuz spacecraft attached to the station. Expedition Two 

crewmembers officially join the station when they install their seat liners in the Soyuz. 

Equipment transfer to the ISS and outfitting Destiny for the arrival of the Space Station 

Remote Manipulator System (SSRMS), the space station's robotic arm scheduled to be 

launched on STS-100 (6A) no earlier than April, also is among the major priorities of 

Discovery's flight. Much of that equipment will be transferred from the Multi-Purpose 

Logistics Module (MPLM), a pressurized moving van module designed to be taken into 

orbit, attached to the space station, and then, after unloading, brought back to the 

orbiter's cargo bay for return to Earth. 

The Italian-built MPLM, named Leonardo, will be attached to the nadir, or Earth-facing, 

berthing port of the Unity node. Before that can happen a docking port, Pressurized 

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Mating Adaptor 3 (PMA 3), must be removed from that berthing port. It will be attached 

to an adjacent berthing port on Unity's left side. 

Leonardo brings six systems racks to the station. Among them are two robotic 

workstation racks for control of the station's robotic arm and the four cameras mounted 

on it. Two are DC-to-DC Converter Units (DDCUs) which convert electrical power from 

the station's solar arrays to a form usable by station systems and experiments. One is 

the U.S. Lab Avionics 3 rack with components supporting both the Ku-Band 

communications system and the command and control system. The sixth is a Crew 

Health Care System rack. 

The Ku-Band is used for high data rate communications, including downlink of television 

pictures. The command and control system is operated from the U.S. laboratory and 

controls the attitude or orientation in space of the station, using four 800-pound 

gyroscopes mounted in the Z-1 Truss of the ISS. 

The PMA 3 move will be made during a space walk by Voss and Helms on Flight Day 4. 

The space walk will be preceded by transfer of a spacesuit and two Simplified Aids for 

EVA Rescue (SAFER) devices from the station to the shuttle shortly after docking on 

Flight Day 3. 

Once outside Discovery's airlock, Voss and Helms will disconnect PMA 3 cables and 

then Mission Specialist Andy Thomas, operating the shuttle's robotic arm, will move it to 

its new location. 

The space walkers subsequently will take the Lab Cradle Assembly from Discovery's 

cargo bay and install it atop Destiny. Its first application will be to support the Launch 

Deployment Assembly of the SSRMS. Later in the space walk they will take the Rigid 

Umbilical from the cargo bay and install it onto Destiny. It is designed to provide power, 

data and video links between the SSRMS and Destiny. 

Leonardo is to be attached to the station on Flight Day 5 and the ISS crew will begin 

unloading it the following day. Hatches will be closed between the shuttle and the 

station in preparation for the mission's second space walk by Thomas and Mission 

Specialist Paul Richards. During that space walk they will take an External Stowage 

Platform from the cargo bay and install it onto Destiny, then hook up power cables for 

the orbital replacement units, spares, to be stowed on it. They will stow the first of those 

spares, a Pump and Flow Control Subassembly for ammonia coolant. 

Among racks to be transferred by the ISS crew will be the Human Research Facility, the 

first scientific rack to be brought to the station. While it is significant in that it marks the 

beginning of major research capability on the station, its transfer is a lower priority than 

transfer of the six systems racks, the three resupply stowage racks and the four 

resupply stowage platforms from Leonardo -- indeed it will be the last of the racks to be 

transferred. While the experiment rack will be activated and checked out, the Ku-Band 

and a communications outage recorder must be working to support data recording and 

downlink. 

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After transfer of the Human Research Facility, transfer of materials into Leonardo will 

begin. Such materials -- batteries at the end of their designed lives, used filters, packing 

materials and garbage are examples -- will be returned to Earth. 

Other priorities include activation and checkout of transferred racks, operation of the 

IMAX camera by the station crew, a series of tests supporting station assembly, ISS 

reboost if adequate propellant is available and a fly-around of the ISS by the orbiter 

after undocking to photograph and videotape the station. 

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Crew

 

Commander: James D. Wetherbee

Pilot: James M. Kelly

Mission Specialist 1: Andrew S.W. Thomas

Mission Specialist 2: Paul W. Richards

Mission Specialist 3: Sergei Krikalev (down)

Mission Specialist 3: James S. Voss (up)

Mission Specialist 4: William M. Shepherd (down)

Mission Specialist 4: Susan J. Helms (up)

Mission Specialist 5: Yuri P. Gidzenko (down)

Mission Specialist 5: Yury V. Usachev (up)

Launch

 

Orbiter: Discovery OV103

Launch Site: Kennedy Space Center Launch Pad 39B

Launch Window: 2.5 to 5 Minutes

Altitude: 122 Nautical Miles

Inclination: 51.6 Degrees

Duration: 11 Days 19 Hrs. 20 Min.

Vehicle Data

 

Shuttle Liftoff Weight: 4,522,944 lbs.

Orbiter/Payload Liftoff Weight: 198,507 lbs.

Orbiter/Payload Landing Weight:

 

219,363 lbs.

Payload Weights

Leonardo 9,000 pounds (almost 4.1 metric tons)

Software Version: OI-28

Space Shuttle Main Engines: (1 MB pdf)

SSME 1: 2048 SSME 2: 2053 SSME 3: 2045

External Tank: 107 ( Super Light Weight Tank) 

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SRB Set: BI-106PF

Shuttle Aborts

Abort Landing Sites

 RTLS: Kennedy Space Center Shuttle Landing Facility

 TAL: Zaragoza

 AOA: Edwards Air Force Base, California 

Shuttle Abort History

Landing

 

Landing Date: 03/20/01

Landing Time: 2:02 AM (eastern time)

Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

Payloads 

Cargo Bay

Leonardo -- A Space Age Moving Van

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Crew Members 

Commander: James D. Wetherbee 

Jim Wetherbee (Capt., USN), 48, makes his fifth flight into space as commander 

of Discovery. Wetherbee, who brought Discovery to within 37 feet of the Russian 

Mir space station in 1995 in the first rendezvous of the Shuttle-Mir Phase One 

program, and who commanded a mission which docked to the Mir in 1997, will 

be responsible for linking Discovery to the International Space Station (ISS) on 

the second shuttle mission of the year. Wetherbee will be in charge of the overall 

safety and success of the mission, and will help in the activation of the Leonardo 

Multi-Purpose Logistics Module, which is carrying supplies and racks of 

experiments to the station. Once docked to the ISS, Wetherbee will also transfer bags of water to the 

orbital outpost for use by its resident crewmembers. After serving a stint as Deputy Director of the 

Johnson Space Center, Wetherbee currently serves as the Director of Flight Crew Operations.

Previous Space Flights:

Wetherby is making his fifth flight into space. STS-102 is Wetherbee's fourth command. He previously 

flew as pilot on STS-32 in 1990, and as commander on STS-52 in 1992, STS-63 in 1995 and STS-86 in 

1997.

Ascent Seating: Flight Deck - Port Forward

Entry Seating: Flight Deck - Port Forward

Pilot: James M. Kelly 

Jim Kelly (Lt. Col., USAF), 36, will be in charge of monitoring critical Shuttle 

systems during Discovery's ascent to orbit and its reentry for landing. Kelly will 

be responsible for the operation of many of Discovery's navigational tools during 

its rendezvous with the International Space Station (ISS) and will serve as one of 

the two robot arm operators during the mission's space walks and the movement 

of the Leonardo module from Discovery's cargo bay to the ISS for cargo transfer. 

Kelly will also be at the controls for Discovery's flyaround of the ISS following its 

undocking. 

Previous Space Flights:

Making his first flight into space, Kelly is a former Air Force test pilot.

Ascent Seating: Flight Deck - Starboard Forward

Entry Seating: Flight Deck - Starboard Forward

RMS 

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Mission Specialist 1: Andrew S.W. Thomas 

Andy Thomas, Ph.D., 49, is Mission Specialist 1 (MS 1) on STS-102. Thomas, 

who will ride on Discovery's flight deck during launch and on the middeck for 

landing to assist the returning Expedition One crewmembers, will serve as one of 

two space walkers on the second space walk of the flight along with Paul 

Richards to install new equipment on the International Space Station (ISS). Born 

in Australia, Thomas will be the prime robotic arm operator during the mission for 

the first space walk of the flight by Jim Voss and Susan Helms and the movement 

of the Leonardo module from Discovery's cargo bay for attachment to the Unity 

module of the ISS. He will also be in charge of cargo transfer from Leonardo to 

the ISS as well as Earth observation photography during the mission. 

Previous Space Flights:

Thomas is making his third trip into space. He was the last American to live and work aboard the 

Russian Mir Space Station in 1998, launching on STS-89 and landing on STS-91 for a total of 141 days 

in orbit. His first flight was STS-77 in 1996.

Ascent Seating: Flight Deck - Starboard Aft

Entry Seating: Mid Deck - Port

EV3 

Mission Specialist 2: Paul W. Richards 

Paul Richards, 36, is Mission Specialist 2 (MS 2) on STS-102. He will serve as 

flight engineer on the flight deck of Discovery during launch and landing and will 

accompany Andy Thomas on the second space walk of the flight. Richards will be 

responsible for the operation of all of Discovery's computers, and will be the 

choreographer for the first space walk of the flight by Jim Voss and Susan Helms, 

operating from Discovery's aft flight deck.

Previous Space Flights:

Richards is making his first flight into space. Before being selected as an 

astronaut, Richards was the lead engineer for the design and development of space-walking tools which 

were used during the Hubble Space Telescope servicing missions.

Ascent Seating: Flight Deck - Center Aft

Entry Seating: Flight Deck - Center Aft

EV4 

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Mission Specialist 3: Sergei Krikalev (down)

Sergei Krikalev, 42, Krikalev served as flight engineer on Expedition One, 

responsible for activating and testing ISS module systems and the in-flight 

maintenance of station hardware. 

Previous Space Flights:

Krikalev is wrapping up his fifth flight into space after completing his second trip 

to the International Space Station as a member of the Expedition One crew. By 

the time he lands while seated on Discovery's middeck, Krikalev will have 

accumulated more than 600 days in space, making him the fourth most 

experienced space traveler in human spaceflight history. Krikalev previously flew on two long-duration 

missions to Mir and two space shuttle flights, STS-60 in 1994 and STS-88 in 1998, the first flight to 

begin assembly of the International Space Station.

Entry Seating: Mid Deck - Port

Mission Specialist 3: James S. Voss (up)

Jim Voss (Col., USA, Ret.), 52, will return to the International Space Station (ISS) 

for a second time as both Mission Specialist 3 (MS 3) on the STS-102 crew and 

as Flight Engineer-1 for the second long-duration, or Expedition Two, crew, which 

will spend four months on the orbital complex. He will be seated on the middeck 

during Discovery's climb to orbit. Voss will join Susan Helms, another Expedition 

Two crewmember, for the first space walk of the STS-102 mission, and is 

scheduled to conduct at least one space walk during his stay on the ISS. Voss will 

be among those responsible for transferring cargo from the Leonardo MultiPurpose Logistics Module to the ISS, and will trade places with Expedition One 

Flight Engineer Sergei Krikalev during crew transfer operations while Discovery is docked to the station. 

During his four months on the ISS, Voss will work with Helms in the operation of the new Canadian-built 

Space Station Remote Manipulator System (SSRMS), conduct checkouts of the soon-to-be installed 

U.S. Airlock and perform experiments on the first science racks in the U.S. Laboratory Destiny.

Previous Space Flights:

Voss is making his fifth flight into space. He previously flew on STS-44 in 1991, STS-53 in 1992, STS69 in 1995 and STS-101 (his previous mission to the space station) in 2000.

Ascent Seating: Mid Deck - Port

EV1 

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Mission Specialist 4: William M. Shepherd (down)

Bill Shepherd (Capt., USN), 51, has served as the first commander of the 

International Space Station since he and his Expedition One crewmates were 

launched on a Soyuz rocket from the Baikonur Cosmodrome in Kazakhstan on 

Oct. 31, 2000. Shepherd will return to Earth on Discovery's middeck. During 

Expedition One, Shepherd led his colleagues in the setup and activation of key 

systems in the Zvezda living quarters and the Destiny laboratory and the 

checkout of the large U.S. solar arrays. He was also responsible for the operation 

of computer systems and hardware maintenance and replacement on board the 

orbital outpost. Shepherd will have played host to three visiting crews during his 

historic tenure as Commander. Before being assigned to lead the first resident crew on the ISS, 

Shepherd served as Deputy Space Station Program Manager in charge of the redesign of the project. 

Previous Space Flights:

Shepherd will have spent 160 days in space on his four flights at the time he lands. 

He previously flew on STS-27 in 1988, STS-41 in 1990 and STS-52 in 1992.

Entry Seating: Mid Deck - Starboard

Mission Specialist 4: Susan J. Helms (up)

Susan Helms (Col., USAF), 43, is one of three crewmembers to return to the 

International Space Station on Discovery's flight. She will be seated on the 

middeck for launch. During STS-102, Helms will serve as Mission Specialist 4 

(MS 4) and will join Jim Voss for the flight's first space walk. She will also act as 

the choreographer for the mission's second space walk, to be performed by Andy 

Thomas and Paul Richards, operating from Discovery's aft flight deck. Helms will 

be the last Expedition Two crewmember to swap orbiting homes with an 

Expedition One crewmember, moving over to the ISS to trade places with 

Expedition One Commander Bill Shepherd. In addition, Helms will be responsible 

for the transfer of vital systems racks from the Leonardo module to the ISS for installation in the U.S. 

Laboratory Destiny. During her four-month stay on the ISS, Helms will serve as Flight Engineer-2. She'll 

conduct checkouts with and the operation of the new Canadian-built Space Station Remote Manipulator 

System (SSRMS), use the SSRMS to move the U.S. Airlock from the shuttle's cargo bay to the ISS and 

will perform experiments on the first science racks in Destiny. 

Previous Space Flights:

Helms is making her fifth flight into space. She previously flew on STS-54 in 1993, STS-64 in 1994, 

STS-78 in 1996 and STS-101 to the space station in 2000.

Ascent Seating: Mid Deck - Center

EV2 

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Mission Specialist 5: Yuri P. Gidzenko (down)

Yuri Gidzenko (Lt. Col., Russian Air Force) will turn 39 a few days after he 

returns to Earth aboard Discovery to wrap up his second flight into space. 

Gidzenko has served as the Expedition One pilot, guiding his Soyuz capsule to a 

docking to the International Space Station on Nov. 2, 2000, two days after he 

and his crewmates were launched to the ISS from the Baikonur Cosmodrome in 

Kazakhstan. Gidzenko was also responsible for the manual docking of a 

Progress resupply vehicle to the ISS in November and its redocking in 

December. He flew the Soyuz from the aft docking port of the Zvezda module to 

the nadir docking port of Zarya in February to clear the way for the arrival of a 

new Progress ship. Gidzenko will return to Earth on Discovery's middeck. During more than four months 

onboard the ISS, Gidzenko was primarily responsible for the maintenance and operation of systems in 

the Zvezda and Zarya modules. 

Previous Space Flights:

Gidzenko's return to Earth will complete a mission which will bring his total time in space to 320 days. 

He previously flew as commander of a long-duration mission to the Mir space station in 1995-1996.

Entry Seating: Mid Deck - Center

Mission Specialist 5: Yury V. Usachev (up)

Yury Usachev, 43, will be the first Russian commander of the International Space 

Station during the four-month increment of the Expedition Two crew. During STS102, Usachev will be designated Mission Specialist 5 (MS 5). Usachev has 

logged 386 days in space and six space walks. Usachev, who will be seated on 

Discovery's middeck for launch, will be the first Expedition Two crewmember to 

move into the ISS, a few hours after docking. He will trade places with Expedition 

One Pilot Yuri Gidzenko to insure that a Soyuz vehicle expert will be available to 

fly the craft home in the event of a contingency. He will officially become 

Expedition Two commander of the ISS at the end of docked operations. During 

his four months on the ISS, Usachev will be responsible for the safety of his crew and the success of 

the mission, is scheduled to conduct at least one space walk with Voss and will assist Voss and Helms 

in the checkout and operation of the Canadian-built Space Station Remote Manipulator System after it 

is delivered to the ISS this spring.

Previous Space Flights:

Usachev is making his fourth flight into space on the STS-102 mission. He flew as a flight engineer 

during two long-duration missions to the Mir space station in 1994 and 1996 and was a mission 

specialist during the STS-101 mission of Atlantis in 2000 along with crewmates Jim Voss and Susan 

Helms.

Ascent Seating: Mid Deck - Starboard

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Flight Plan 

Flight Day Summary 

DATE TIME (EST) DAY MET EVENT

03/08/01 6:42:00 AM 1 000/00:00 Launch

03/08/01 8:07:00 AM 1 000/01:25 Payload Bay Door Opening

03/09/01 10:16:00 PM 3 001/15:34 TI Burn

03/10/01 12:32:00 AM 3 001/17:50 Docking

03/10/01 2:42:00 AM 3 001/20:00 ISS Hatch Open

03/10/01 11:37:00 PM 4 002/16:55 EVA 1 Start

03/11/01 5:47:00 AM 4 002/23:05 EVA 1 End

03/11/01 9:42:00 PM 5 003/15:00 MPLM Grapple

03/11/01 10:32:00 PM 5 003/15:50 MPLM Installation

03/12/01 2:42:00 AM 5 003/20:00 MPLM Vestibule Outfitting

03/12/01 3:57:00 AM 5 003/21:15 MPLM Activation

03/12/01 11:37:00 PM 6 004/16:55 EVA 2 Start

03/13/01 3:47:00 AM 6 004/21:05 EVA 2 End

03/16/01 11:47:00 PM 10 008/17:05 MPLM Grapple/Separation from 

ISS

03/17/01 1:57:00 AM 10 008/19:15 MPLM/Discovery Berthing

03/17/01 8:27:00 PM 11 009/13:45 ISS Hatch Close

03/17/01 10:57:00 PM 11 009/16:15 ISS Undock

03/17/01 11:07:00 PM 11 009/16:25 Flyaround Begins

03/20/01 12:59:00 AM 13 011/18:17 Deorbit Burn

03/20/01 2:02:00 AM 13 011/19:20 Landing

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Rendezvous 

Rendezvous and Docking Overview 

Rendezvous and Docking

Discovery's rendezvous and docking with the International Space Station actually 

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 

a point about nine statute miles behind the station, the starting point for a final approach 

to the station. 

About two and a half hours before the scheduled docking time on Flight Day Three, 

Discovery will reach the point about nine statute miles -- 48,600 feet -- behind the ISS. 

At that time, Discovery's engines 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 Earth. As Discovery closes in, the shuttle's rendezvous radar 

system will continue to track the station and provide range and closing rate information 

to the crew. During the approach toward the station, the shuttle will have an opportunity 

to conduct four, small mid-course corrections at regular intervals. Just after the fourth 

correction is completed, Discovery will reach a point about a half-mile below the station. 

At that time, about an hour before the scheduled docking, Commander Jim Wetherbee 

will take over manual control of the approach. 

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

below the station, from which 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, Wetherbee will be assisted by Pilot James Kelly in controlling Discovery's 

approach. Mission Specialists Andy Thomas and Paul Richards also will play key roles 

in the rendezvous, with Thomas operating the shuttle's docking mechanism and 

Richards assisting with the rendezvous navigation. Thomas and Richards will use a 

handheld laser pointed through the shuttle windows to provide supplemental information 

on the station's range and the shuttle's closing rate. 

Wetherbee will fly the quarter-circle of the station, starting at a point 600 feet below, 

while slowly closing in on the complex, stopping at a point a little over 300 feet directly 

in front of the station. From that point, he will begin slowly closing in on the station -- 

moving at a relative speed of about a tenth of a foot per second. Using a view from a 

camera mounted in the center of Discovery's docking mechanism as a key alignment 

aid, Wetherbee will precisely center the docking ports of the two spacecraft. Wetherbee 

will fly to a point where the docking mechanisms are 30 feet apart, and pause briefly to 

check the alignment. 

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

station, and keep the docking mechanisms aligned to within three inches of one 

another. When Discovery makes contact with the station, latches will automatically 

17
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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, Thomas will command 

the docking ring on Discovery's mechanism to retract, closing latches in the mechanism 

to firmly secure the shuttle to the station. 

Undocking, Separation and Fly-Around

Once Discovery is ready to undock, Thomas 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. Both Discovery's and the station'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 away to a distance of 

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

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

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

the ISS, essentially the reverse of the task performed by Wetherbee when Discovery 

docked. 

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

close flyaround of the station, circling the complex one and a half times. Kelly will first 

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

when he reaches a point directly above the station for the second time, Kelly will fire 

Discovery's jets to separate from the Station. The flyaround is expected to be completed 

a little over an hour after undocking. 

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STS-102

EVA 

Space Walks Continue to Grow the Space Station 

Overview 

Astronauts Jim Voss and Susan Helms will make the first of two space walks on 

Discovery's flight day four to help relocate a Pressurized Mating Adaptor and install an 

attachment fixture atop the U.S. laboratory Destiny. Voss is designated EV1 and will wear 

the spacesuit with the solid red stripes. Helms is EV2 and will wear the solid white 

spacesuit. 

A second space walk, by astronauts Andy Thomas, EV3, and Paul Richards, EV4, will 

follow on flight day six. They will install a stowage platform outside Destiny and hook up 

power cables to power devices that will be stowed there. They also will place a pump on 

the stowage platform. Finally they will test latches on the attachment fixture installed by 

Voss and Helms. Thomas will wear the spacesuit with broken stripes, while Richards will 

wear the suit with diagonal stripes. Both space walks are scheduled to last about six hours. 

Flight Day Four: The First Space walk 

Voss and Helms will help relocate Pressurized Mating Adaptor 3 (PMA-3) from the lower 

berthing port on the Unity node to an adjacent berthing port on Unity's left side. That is 

being done so the Multipurpose Logistics Module (MPLM) can be docked to the common 

berthing mechanism of the lower port. 

Voss and Helms will start their space walk jobs by preparing for the PMA-3 move. This 

includes moving a gap spanner tether and disconnecting eight cables. Next, Voss removes 

the port Early Communications System antenna from the port side of the Unity Node and 

takes it to the airlock. 

Voss, on the end of Discovery's robotic arm being operated by Thomas (who shares arm 

duties with Pilot Jim Kelly), and Helms then remove the Lab Cradle Assembly (LCA) from 

the Integrated Cargo Carrier in Discovery's cargo bay and install it on the U.S. laboratory 

Destiny's aft zenith trunnion. During STS-100 (6A) later this year, the 300-pound, four-footsquare LCA will be used to secure the Launch Deployment Assembly of the station's 

robotic arm. On STS-110 (8A) it will be used to permanently secure the S0 truss segment 

to Destiny, and will become the structural interface between the station and the main truss. 

The space walkers run cables to Destiny for power and data and remove a thermal cover 

from the LCA. 

They then swap places, with Helms moving to the foot support on the arm and Voss 

becoming the free-floater. They return to the Integrated Cargo Carrier pallet and remove 

the Rigid Umbilical, a wiring harness to take power, data and video between Destiny and 

the station's robotic arm. They transfer and install the RU to the forward, lower side of 

Destiny near the Power & Data Grapple Fixture, an attachment point on Destiny for the 

station arm. There they remove a protective shield and connect cables. 

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Finally, they will do standard post-space walk cleanup. They will wait in the airlock, to see if 

they are needed to help with the PMA-3 move. 

Flight Day Six: Second Space Walk

Thomas and Richards will remove the External Stowage Platform (ESP) from the 

Integrated Cargo Carrier pallet in the cargo bay and install it on the port aft trunnion on 

Destiny. With Kelly on the arm, they hook up cables that provide heater power to orbital 

replacement units - spares stowed on the ESP and available to replace vital equipment. 

Thomas then maneuvers back to the pallet and removes the Pump and Flow Control 

Subassembly, the first of such spares to be left on the ESP. He transfers it to the ESP and 

installs it there. The Pump and Flow Control Subassembly is a 250-pound device that 

pumps and controls valves for ammonia coolant flow. 

Meanwhile, Richards turns his attention to the LCA installed on the first space walk. He 

performs a ready-to-latch indicator test on each of the four indicators on the LCA. Richards 

then closes two circuit interrupt devices to bring power to the DC-to-DC Conversion Units 

inside Destiny. 

Richards then begins a photo-documentation survey of the worksite, before he and Thomas 

do the post-space walk cleanup and go back into the airlock. 

Additional tasks were being considered for the second space walk.

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STS-102

EVA Timeline for Space Walks Continue to Grow the Space Station 

Time Event

2/16:55 EVA 1 Start

2/17:20 EVA 1 Setup

2/17:45 EVA 1 PMA 3 Umbilicals

2/18:45 EVA 1 Remove ECOMM

2/18:45 EVA 1 LCA Prep

2/19:15 EVA 1 LCA Transfer

2/20:15 EVA 1 TTHR

2/20:25 EVA 1 RU Remove Inst

2/21:05 EVA 1 RU Connect

2/21:55 EVA 1 Cleanup

2/23:05 EVA 1 End

4/16:55 EVA 2 Start

4/17:25 EVA 2 Setup

4/18:05 EVA 2 ESP Remove & Install

4/19:00 EVA 2 PFCS Remove & Install

4/19:30 EVA 2 Cleanup

4/20:45 EVA 2 End

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STS-102

Payloads 

Leonardo -- A Space Age Moving Van

Payload Bay

9,000 pounds (almost 4.1 metric tons) 

Overview

The Leonardo Multi-Purpose Logistics Module (MPLM), which was built by the Italian 

Space Agency (ASI), is the first of three such pressurized modules that will serve as the 

International Space Station's "moving vans," carrying laboratory racks filled with equipment, 

experiments and supplies to and from the International Space Station aboard the space 

shuttle. 

Construction of ASI's Leonardo module began in April 1996 at the Alenia Aerospazio 

factory in Turin, Italy. Leonardo was delivered to Kennedy from Italy in August 1998 by a 

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

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

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

station equipment racks. 

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

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

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

station module when it is flown. In order to function as an attached station module as well 

as a cargo transport, Leonardo contains components that provide some life support, fire 

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

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

to and from the station. 

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

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

robotic arm will remove Leonardo from the payload bay and berth it to the Unity Module on 

the ISS. During its berthed period to the station, system racks and individual components 

will be transferred to the ISS. 

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

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

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

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

crewmembers to travel from the shuttle cabin to the module. 

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

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

16 racks the module can carry, this mission brings six ISS system racks, three resupply 

stowage racks, four resupply stowage platforms, and the first scientific experiment rack. 

Of the six systems racks, two racks contain power distribution equipment to support 

laboratory payloads. This equipment includes DC-to-DC Conversion Units (DDCU) and 

Remote Power Control Modules (RPCM). Two of the racks contain the Robotic Work 

Station (RWS) required for controlling the space station robotic arm which is scheduled to 

arrive on Flight 6A. One rack contains the remaining hardware required to activate the KuBand Communication system and additional avionics to support the computer system. The 

sixth rack contains crew health care equipment including a defibrillator and a respirator 

support pack. 

The first experiment rack called HRF#1 (Human Research Facility #1) is also contained 

within Leonardo. This rack contains the first experiments to be performed on the ISS. The 

HRF rack will be used to conduct human life science investigations. Although the rack will 

be mounted in its permanent location during the mission, it will remain inactive until after 

the shuttle leaves. 

There are also 7 Resupply Stowage Racks (RSR) and Resupply Stowage Platforms (RSP) 

within the MPLM. These 7 racks contain equipment required for crew rotation, components 

to augment existing ISS systems, spare parts for systems already on the station, in addition 

to food and supplies to support the crew. Resupply Stowage Racks, and Resupply 

Stowage Platforms use Cargo Transfer Bags (CTB) to carry components to the ISS but the 

racks, platforms, and bags themselves remain in the Leonardo module and are returned to 

Earth with the shuttle. 

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STS-102

Payloads 

Integrated Cargo Carrier 

Overview

The Integrated Cargo Carrier is a two-part structure consisting of a waffle-like aluminum 

box-beam pallet and keel-yoke assembly. It is installed in the cargo bay of the space 

shuttle orbiter, to expand the shuttle's capacity to transport unpressurized cargo. 

SPACEHAB's Integrated Cargo Carrier is 8 feet long, 15 feet wide and 10 inches thick. 

It has a capacity of up to 6,000 pounds of attached payload. Cargo can be attached to 

both the top and bottom of the pallet. 

Participating Contractors are RSC-Energia, maker of the Unpressurized Cargo Pallet. 

Astrium GmbH is the maker of the Keel Yoke Assembly (KYA) that anchors the UCP in 

the Shuttle cargo bay and is SPACEHAB's mission integration and operations support 

prime contractor. 

STS-102 Specifics: 

Launch Weight of the Integrated Cargo Carrier on STS-102 is 3,438 pounds. Both sides 

of the Unpressurized Cargo Pallet (UCP) are being used to transport cargo to the 

International Space Station. 

ISS Cargo Compliment: Lab Cradle Assembly with Module Truss Structure Attach 

System installed; Pump Flow Control Subassembly with attached Flight Support 

Equipment; External Stowage Platform; and the Rigid Umbilical. 

The Lab Cradle Assembly will be installed on the U.S. laboratory Destiny's aft zenith 

trunnion on the mission's first space walk. During STS-100 (6A) later this year, the 300-

pound, four-foot-square LCA will be used to secure the Launch Deployment Assembly 

of the station's robotic arm. On STS-110 (8A) it will be used to permanently secure the 

S0 truss segment to Destiny. It will become the structural interface between the station 

and the main truss. 

The External Stowage Platform will be installed during the second space walk on the 

port aft trunnion on Destiny. It is a temporary home for orbital replacement units - 

spares stowed on the ESP and available to replace vital equipment. Space walking 

astronauts also will hook up cables to provide power to the orbital replacement units 

stowed there. 

The Pump Flow Control Subassembly will be the first of those orbital replacement units 

on the External Stowage Platform. It is a 250-pound device that pumps and controls 

valves for ammonia coolant flow. 

24
STS-102

The Rigid Umbilical is a wiring harness to take power, data and video between Destiny 

and the Space Station Remote Manipulator System, the station's robotic arm. During 

the first space walk, it will be installed on the forward, lower side of Destiny near the 

Power & Data Grapple Fixture, an attachment point on Destiny for the station arm. 

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STS-102

Payloads 

Passive Dosimeter System 

Overview

Monitoring radiation exposure in space is important both to crew health and to future 

scientific research on the International Space Station. 

The STS-102 mission will transport the Passive Dosimeter System (PDS) to the ISS, 

where it will serve as a flexible and easy-to-use radiation monitor that will be available 

for use by any experimenter. 

The PDS hardware consists of two kinds of radiation dosimeters and an electronic 

"reader." The dosimeters can be placed anywhere in the ISS to provide an accurate 

point measurement of the radiation at their locations. 

One of the radiation dosimeters is a thermoluminescent detector, or TLD. Each TLD, 

which resembles a fat fountain pen, contains calcium sulfate crystals inside an 

evacuated glass bulb. These crystals absorb energy from incident ionizing radiation 

(protons, neutrons, electrons, heavy charged particles, gamma and x-rays) as the 

radiation passes through them. This process results in a steady increase in the energy 

level of the electrons in the crystal. 

To read the accumulated radiation dose, an astronaut aboard the ISS removes the 

crystal-containing dosimeter from its measurement location and places it into the 

electronic reader. A component inside the reader heats the crystals. As the crystals are 

heated they emit a glow of light that is proportional to the amount of radiation they have 

been exposed to. This glow is measured by a photomultiplier tube in the reader. The 

reader stores the measured dose on a memory card that can be returned to Earth for 

further analysis. After the crystals have emitted all their stored energy, they are ready to 

begin accumulating a dose again and the TLD is ready to be reused. 

The other dosimeter is a set of Plastic Nuclear Track Detectors (PNTDs). The PNTDs 

are thin sheets of plastic, similar to the material used for some eyeglass lenses. As 

heavy charged ions pass through the PNTDs, the surface becomes pitted with tiny 

craters. When the PNTDs are subsequently returned to Earth, the plastic is etched to 

enlarge the craters. Then the craters are counted and their shapes and sizes are 

analyzed using a microscope. This information is used to improve the accuracy of the 

radiation dose the TLDs have recorded and to improve the estimate of the biological 

effects of the radiation. 

26
STS-102

The complete set of 48 TLDs and the reader will be carried into orbit on STS-102. They 

will remain on the ISS indefinitely to support a variety of future scientific experiments. A 

set of 12 PNTDs will be carried to the ISS on STS-100 later this year. The combined 

dosimeters will be used to measure radiation as part of the DOSMAP experiment, which 

is being conducted by the NASA Human Research Facility on the ISS. The exposed 

PNTDs will be returned to Earth for analysis by the STS-105 mission. 

Understanding the radiation environment on the ISS will be useful in helping scientists 

explain experimental results that otherwise might be unaccounted for. The radiation 

measurements can help scientists determine whether a given effect is due to 

microgravity, radiation or something else. 

The Passive Dosimeter System is the first ISS hardware from NASA's Ames Research 

Center, Moffett Field, Calif. The Hungarian Space Office provided the 

thermoluminescent detectors, which are a third-generation version of dosimeters that 

flew previously on the Russian space stations Salyut 7 and Mir, and on the Space 

Shuttle. The Hungarian Space Office also provided the compact radiation reader, which 

is smaller than a typical shoebox. The Plastic Nuclear Track Detectors are provided and 

analyzed by ERIL Research Company in San Rafael, CA. 

Ames' role has led efforts to verify and certify the dosimeters for safety, and to package 

them in one of four transport containers, which resemble insulated lunch bags. One 

container holds a reader and 12 TLDs with associated power and data cables. Two 

additional kits each hold 18 TLDs. The final kit holds 12 PNTDs and two memory cards 

for the reader. 

27
STS-102

Payloads 

Space Experiment Module Carrier System 

Overview 

The Space Experiment Module (SEM) 09 Carrier System in Discovery's cargo bay contains 

educational experiments. 

--The "Microgravity Rainbow" of Beaver Run Elementary, Salisbury, Md., involved 45 first 

and second grade students who mixed 44 vials of Kool-aid. Twenty two will be flown and 

colors will be compared with samples and with paint color swatches after the flight. 

--The "Ponds" experiment of Woodland Middle School, East Meadow, N.Y., involved two 

teachers and 210 sixth graders from two schools. They will fly samples from natural and 

manmade ponds, other water and related samples. 

--The "Sunflower Seeds in Space" experiment of Coyote Valley Elementary School, 

Middletown, Calif., is an effort by fourth graders to determine effects of space travel on 

sunflower seeds. Flown and control samples will be planted and compared after the flight. 

--"Operation Cheese Mold" is an experiment of Rostraver Middle School, Belle Vernon, Pa. 

Various cheese samples will be flown and later compared for mold growth with control 

samples. 

--"The Effect of Cosmic Radiation on Lichens" experiment of the Delta Cyber School in 

Delta Junction, Alaska, contains two sets of eleven space capsules containing lichens. 

One set will be exposed to cosmic radiation and the other shielded. When the lichens 

return, the sets will be compared for structure or growth changes. 

--"Coco for Coconauts" is an experiment of the Congress Math/Science/Technology Middle 

School Magnet Team, Boynton Beach, Fla. Pupils in grades six to eight will place coconut 

samples in vials for the flight. They will be exposed to radiation and after return examined 

for changes. 

--"A Seed for a Larger Service" experiment of the Country Center 4-H Space Science 

Project, Sacramento, Calif., will use a hybrid grass material to look at how spaceflight 

affects it at a molecular level. They will compare results to an experiment flown on STS101. 

--"The Ultra Fluffy Outcome" experiment of Virginia Space Academy 2000 in Newport 

News, Va. compares effects of radiation and temperature on cotton candy samples flown 

in space to control samples. 

28
STS-102

--"MISE" (Materials in Space Experiments) of the Young Valley Scientists in Santa Ynez, 

Calif., will test how the space environment affects various materials, including natural 

materials and materials made using old and new technologies. Also, the experiment will 

explain how microgravity and radiation affect materials made by old and new 

technologies. 

--SSM -- Anne Arundel County Schools, Anne Arundel County, Md., students from five 

schools will investigate effects of the space environment on a variety of commonly used 

materials, including common school supplies, food samples, fabrics, shampoos, 

perfumes, and soaps. 

History/Background

The Space Experiment Module (SEM) Carrier System is a self-contained assembly of 

subsystems that function together to provide structural support, power, experiment, 

command and data storage capabilities. The SEM-09 carrier system is a five-foot 'canister' 

that contains 10 experiment modules. 

The SEM software is required for active experimentation. The software application helps 

the experimenter describe the experiment, enter power consumption, parts, materials, 

timeline, control and command data. Also, the software is used to analyze the data for SEM 

compatibility and post-flight reports. 

The active modules are powered by one 12-Volt battery independent of the shuttle power 

supply. Each powered module has an integrated programmable control circuit board or 

Module Electronic Unit (MEU) for data sampling and storage. The MEU processes the 

student-devised flight operations timeline. A Ground Module Electronic Unit is provided to 

selected active experimenters for development and testing of their active experiment. 

The SEM canister is generally installed three months before launch in the Space Shuttle 

cargo bay. During the early state of the shuttle flight, astronauts activate the SEM canister 

via the Payload and General Support Computer. For active experiments (using battery 

power) the MEU's carry out the programmed timeline defined by the experimenters. 

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STS-102

Payloads 

Wide-band Shuttle Vibration Force Measurement 

Overview 

The Wide-band Shuttle Vibration Force Measurement (WSVFM) experiment is a part of 

the payload-to- Space Shuttle Program and is managed by the Jet Propulsion 

Laboratory. WSVFM is a standard secondary payload that will be integrated using the 

Get-Away Special (GAS) Carrier Payload Integrated Plan. 

The WSVFM experiment will obtain flight measurements of the vibration forces acting 

between a space vehicle payload and its mounting structure and complementary 

acceleration data at high and low frequencies. Also, the project will provide 

measurements of the vibration forces generated by the shuttle engines and transmitted 

to the onboard equipment. These measurements will enable the future evaluation of 

models used to derive force limits for a new, more realistic vibration test method that is 

used to qualify flight hardware. 

The WSVFM payload is self-supporting (the payload is battery powered and the data is 

recorded within the payload) and does not require crew interface. The payload will be 

activated automatically by the shuttle's main engine ignition vibration and will operate for 

about 270 seconds. After landing, the data will be retrieved from the recorders using a 

personal computer. 

History/Background

The primary purpose of the WSVFM and precursor SVF experiments is to validate a 

new, cost-effective method of conducting laboratory vibration tests, which are routinely 

performed to qualify aerospace equipment for flight. 

The WSVFM payload will be in a sealed, standard 5-cubic-foot GAS canister. The 

payload weighs 260 pounds -- 160 pounds for the canister and 100 pounds for the 

experiment and ballast structure. 

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STS-102

Payloads 

Get-Away Special Canister 783 

Overview

The GAS (Get-Away Special) canister G-783, also known as Aria-2, is an educational 

project that encourages K-12 St. Louis area students to use hands-on science 

experimentation in an exciting environment. Students for the Aria-2 project design, build, 

and fly experiments in space. The Aria-2 project introduces students to science, 

engineering and technology, and fosters their involvement in hands-on space science 

before they make long-term career decisions. Aria-2 carries 124 passive science 

experiments from more than 1,700 kindergarten through 12th-grade students from 19 St. 

Louis area schools, one school in Washington, D.C., and one school in Palo Alto, Calif. 

Individual teachers provided instruction in the following areas: preparing hypotheses, 

designing experiments, collecting materials, creating flight articles, and analyzing the 

results after flight. All of the Aria-2 experiments are "fly and compare" experiments that 

contain two samples. Both samples are packaged identically. One sample is flown on board 

STS-102 and the other is kept on the ground. After the mission samples will be compared 

and the differences are noted. 

Students will look at effects of microgravity, radiation, magnetism, and other possible 

circumstances experienced in a low-Earth-orbit environment. Each school is responsible for 

its own student organization and participation. Some organized clubs and others integrated 

the experiments into their curriculum. 

History/Background 

The Washington University St. Louis School of Engineering and Applied Science 

sponsored the Aria-2 project. Twenty undergraduate Washington University students 

designed, built, and tested the primary GAS structure and packaging systems. Keith 

Bennett, Department of Computer Science, and Dr. Michael Swartwout, Department of 

Mechanical Engineering, provided instruction to the undergraduate students. The project is 

co-sponsored by the St. Louis Area Junior Achievement which aided in contacting area 

schools, communicating the project opportunity, and linking interested schools with 

Washington University and the Aria-2 project. 

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STS-102

DTO/DSO/RME 

Monitoring Latent Virus Reactivation and Shedding in Astronauts 

DSO 493

Overview 

The premise of this DSO is that the incidence and duration of latent virus reactivation in 

saliva and urine will increase during space flight. The objective is to determine the 

frequency of induced reactivation of latent viruses, latent virus shedding, and clinical 

disease after exposure to the physical, physiological, and psychological stressors 

associated with space flight. 

History/Background 

Spaceflight-induced alterations in the immune response become increasingly important 

on long missions, particularly the potential for reactivation and dissemination (shedding) 

of latent viruses. An example of a latent virus is Herpes Simplex Type 1 (HSV-1), which 

infects 70 to 80% of all adults. Its classic manifestations are cold sores, pharyngitis, and 

tonsillitis; and it usually is acquired through contact with the saliva, skin, or mucous 

membranes of an infected individual. However, many recurrences are asymptomatic, 

resulting in shedding of the virus. Twenty subjects have been studied for Epstein-Barr 

virus. Three additional viruses will be examined in an expanded subject group. 

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DTO/DSO/RME 

Individual Susceptibility to Post-Spaceflight Orthostatic Intolerance 

DSO 496

Overview 

Susceptibility to postflight orthostatic intolerance - lightheadedness or fainting upon 

return to Earth - is highly individual. Some astronauts are little affected, while others 

have severe symptoms. Women are more often affected than men. The goal of this 

DSO is to discover the mechanisms responsible for these differences in order to 

customize countermeasure protocols. 

History/Background 

It has been well documented that spaceflight significantly alters cardiovascular function. 

One of the most important changes from a crew safety standpoint is postflight loss of 

orthostatic tolerance, which causes astronauts to have difficulty walking independently 

and induces lightheadedness or fainting. These may impair their ability to leave the 

orbiter after it lands. 

This DSO will perform a flight-related study, designed to clarify preflight and postflight 

differences in susceptible and nonsusceptible astronauts. There are no on-orbit 

activities associated with this DSO. 

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DTO/DSO/RME 

Spaceflight and Immune Functions 

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 function 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 

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 63 previous flights. 

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DTO/DSO/RME 

International Space Station On-Orbit Loads Validation 

DTO 261

Overview 

This DTO will use the shuttle's aft primary reaction control system jets to measure the 

structural dynamics (natural frequencies, modal amplitudes, and structural dampening) 

of the ISS and use the results to validate critical areas of the on-orbit loads prediction 

models. Tests will obtain photogrammetric measurements of the radiator. 

History/Background 

This is the third flight of DTO 261. 

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DTO/DSO/RME 

Shuttle Automatic Reboost Tuning 

DTO 263

Overview 

Shuttle reboost of the space station using the automatic reboost software requires jetfiring separation to avoid excitation of the joined shuttle/ISS structural natural 

frequencies. Accurate specification of this jet-firing separation requires measurement of 

the on-orbit joined structure natural frequencies. A brief execution of the reboost 

software using benign parameters, such as burn length, will allow acquisition of 

structural dynamics data to validate the preflight estimate of the structural natural 

frequencies and damping and, thus, the jet-firing separation time. 

The structural natural frequencies can be measured using the shuttle inertial 

measurement unit downlinked data, and the jet-firing separation time can be 

implemented by display inputs by the crew. This DTO is appropriate for shuttle flights to 

the ISS between availability of OI-28 reboost software and availability of the vernier jet 

reboost capability and which have a significant structural configuration difference from 

previous flights. 

History/Background 

This is the second flight of DTO 263. 

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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 15th flight of DTO 700-14. 

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DTO/DSO/RME 

Structural Dynamics Model Validation 

DTO 257

Overview 

This DTO will fire a sequence of primary reaction control system (RCS) jets and 

observe the effects on the structural dynamics of the mated Shuttle and International 

Space Station complex. The test is designed to confirm that primary reaction control 

system jet firings are acceptable for use if vernier reaction control system jets are not 

available. 

History/Background 

This is the fifth flight of DTO 257. 

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Shuttle Reference and Data 

Shuttle Abort History 

RSLS Abort History: 

(STS-41 D) June 26, 1984 

The countdown for the second launch attempt for Discovery’s maiden flight ended at T-4 

seconds when the orbiter’s computers detected a sluggish valve in main engine #3. The 

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

(STS-51 F) July 12, 1985 

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

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Shuttle Reference and Data 

Shuttle Abort Modes 

RSLS ABORTS 

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

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

Rocket Booster ignition. 

ASCENT ABORTS 

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

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

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

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

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

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

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

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

would generally result in a ditch operation. 

INTACT ABORTS 

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

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

Return to Launch Site 

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

separation). 

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

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

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

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

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

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

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

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

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

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

dumped by continuous orbital maneuvering system and reaction control system engine 

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

landing. 

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

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

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

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

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

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

RTLS. 

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

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

Transoceanic Abort Landing 

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

TAL is handled like a nominal entry. 

Abort to Orbit 

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

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

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

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

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

circular orbit. 

Abort Once Around 

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

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

maneuvering system propellant is available to accomplish the orbital maneuvering system 

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

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

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

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

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

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

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

once and landing approximately 90 minutes after lift-off. 

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

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

CONTINGENCY ABORTS 

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

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

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

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

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

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

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

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

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ABORT DECISIONS 

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

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

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

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

remaining vehicle performance. 

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

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

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

never chosen if another abort option exists. 

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

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

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

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

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

determine the current abort region. 

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

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

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

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

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

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

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

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

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

an abort push button. 

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Shuttle Reference and Data 

Space Shuttle Rendezvous Maneuvers 

COMMON SHUTTLE RENDEZVOUS MANEUVERS 

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

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

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

rendezvous phasing burn 

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

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

future time 

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

target at a future time 

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

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

height errors relative to the target at Ti 

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

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

intercept the target in one orbit 

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

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

preparation for the final, manual proximity operations phase 

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Shuttle Reference and 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. Seventyfive seconds after SRB separation, SRB apogee occurs at an altitude of approximately 

220,000 feet, or 35 nautical miles (40 statute miles). SRB impact occurs in the ocean 

approximately 122 nautical miles (140 statute miles) downrange. 

The SRBs are the largest solid- propellant motors ever flown and the first designed for 

reuse. Each is 149.16 feet long and 12.17 feet in diameter. 

Each SRB weighs approximately 1,300,000 pounds at launch. The propellant for each solid 

rocket motor weighs approximately 1,100,000 pounds. The inert weight of each SRB is 

approximately 192,000 pounds. 

Primary elements of each booster are the motor (including case, propellant, igniter and 

nozzle), structure, separation systems, operational flight instrumentation, recovery avionics, 

pyrotechnics, deceleration system, thrust vector control system and range safety destruct 

system. 

Each booster is attached to the external tank at the SRB''s aft frame by two lateral sway 

braces and a diagonal attachment. The forward end of each SRB is attached to the 

external tank at the forward end of the SRB''s forward skirt. On the launch pad, each 

booster also is attached to the mobile launcher platform at the aft skirt by four bolts and 

nuts that are severed by small explosives at lift-off. 

During the downtime following the Challenger accident, detailed structural analyses were 

performed on critical structural elements of the SRB. Analyses were primarily focused in 

areas where anomalies had been noted during postflight inspection of recovered hardware. 

One of the areas was the attach ring where the SRBs are connected to the external tank. 

Areas of distress were noted in some of the fasteners where the ring attaches to the SRB 

motor case. This situation was attributed to the high loads encountered during water 

impact. To correct the situation and ensure higher strength margins during ascent, the 

attach ring was redesigned to encircle the motor case completely (360 degrees). 

Previously, the attach ring formed a C and encircled the motor case 270 degrees. 

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

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

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

ring of the skirt. 

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

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

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

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

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

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

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

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

maximum dynamic pressure. 

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

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

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

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

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

rail car with a specially built cover. 

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

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

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

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

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

bearing is the gimbal mechanism. 

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

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

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

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

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

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

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

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

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

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

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

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

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

of information on a single communication channel. 

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

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

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

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

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

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

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

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

The SRB nose caps and nozzle extensions are not recovered. 

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

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

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

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

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

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

receiver/ decoder, antennas and ordnance. 

HOLD-DOWN POSTS 

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

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

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

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

ignition commands. 

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

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

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

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

captured in a blast container. 

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

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

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

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

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

SRB IGNITION 

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

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

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

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

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

there are no holds from the LPS. 

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

safing functions are initiated. 

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

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

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

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

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

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

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

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

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

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

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

dynamic pressure region. 

ELECTRICAL POWER DISTRIBUTION 

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

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

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

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

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

powered in the event one orbiter main bus fails. 

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

24 volts dc. 

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HYDRAULIC POWER UNITS 

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

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

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

power to a hydraulic pump that produces hydraulic pressure for the SRB hydraulic system. 

The two separate HPUs and two hydraulic systems are located on the aft end of each SRB 

between the SRB nozzle and aft skirt. The HPU components are mounted on the aft skirt 

between the rock and tilt actuators. The two systems operate from T minus 28 seconds 

until SRB separation from the orbiter and external tank. The two independent hydraulic 

systems are connected to the rock and tilt servoactuators. 

The APU controller electronics are located in the SRB aft integrated electronic assemblies 

on the aft external tank attach rings. 

The APUs and their fuel systems are isolated from each other. Each fuel supply module 

(tank) contains 22 pounds of hydrazine. The fuel tank is pressurized with gaseous nitrogen 

at 400 psi, which provides the force to expel (positive expulsion) the fuel from the tank to 

the fuel distribution line, maintaining a positive fuel supply to the APU throughout its 

operation. 

The fuel isolation valve is opened at APU startup to allow fuel to flow to the APU fuel pump 

and control valves and then to the gas generator. The gas generator''s catalytic action 

decomposes the fuel and creates a hot gas. It feeds the hot gas exhaust product to the 

APU two- stage gas turbine. Fuel flows primarily through the startup bypass line until the 

APU speed is such that the fuel pump outlet pressure is greater than the bypass line''s. 

Then all the fuel is supplied to the fuel pump. 

The APU turbine assembly provides mechanical power to the APU gearbox. The gearbox 

drives the APU fuel pump, hydraulic pump and lube oil pump. The APU lube oil pump 

lubricates the gearbox. The turbine exhaust of each APU flows over the exterior of the gas 

generator, cooling it, and is then directed overboard through an exhaust duct. 

When the APU speed reaches 100 percent, the APU primary control valve closes, and the 

APU speed is controlled by the APU controller electronics. If the primary control valve logic 

fails to the open state, the secondary control valve assumes control of the APU at 112-

percent speed. 

Each HPU on an SRB is connected to both servoactuators on that SRB. One HPU serves 

as the primary hydraulic source for the servoactuator, and the other HPU serves as the 

secondary hydraulics for the servoactuator. Each sevoactuator has a switching valve that 

allows the secondary hydraulics to power the actuator if the primary hydraulic pressure 

drops below 2,050 psi. A switch contact on the switching valve will close when the valve is 

in the secondary position. When the valve is closed, a signal is sent to the APU controller 

that inhibits the 100-percent APU speed control logic and enables the 112-percent APU 

speed control logic. The 100-percent APU speed enables one APU/HPU to supply 

sufficient operating hydraulic pressure to both servoactuators of that SRB. 

51
STS-102

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. 

52
STS-102

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. 

53
STS-102

Shuttle Reference and 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. 

54
STS-102 

A ACRONYMS AND ABBREVIATIONS 

A/A Air-to-Air 

A/G Air-to-Ground 

AAA Avionics Air Assembly 

AAC Aft Access Closure 

ABC Audio Bus Controller 

ABOLT Acquire Bolt Load 

AC Assembly Complete 

ACBM Active Common Berthing Mechanism 

ACC Antenna Controller Card 

ACO Assembly Checkout Officer 

ACS Assembly Contingency System 

 Atmosphere Control and Supply 

 Atmosphere Control Supply 

 Attitude Control System 

ADF Air Diffuser 

AFD Aft Flight Deck 

AIO Analog Input/Output 

ALS Advanced Life Support 

ALSP Advance Life Support Pack 

AMP Ambulatory Medical Pack 

AOH Assembly Operations Handbook 

AOS Acquisition of Signal 

APAS Androgynous Peripheral Attachment System 

APCU Assembly Power Converter Unit 

 Auxiliary Power Converter Unit 

APFR Articulating Portable Foot Restraint 

APS Automated Payload Switch 

 Auxiliary Power Supply 

ARIS Active Rack Isolation System 

ARS Air Revitalization System 

 Atmosphere Revitalization System 

ASC Aisle Stowage Container 

ASCR Assured Safe Crew Return 

ASL Atmosphere Sampling Line 

ASV Air Selector Valve 

ATCS Active Thermal Control System 

ATU Audio Terminal Unit 

AVU Artificial Vision Unit 

AUAI ACD/UHF Audio Interface 

AVV Accumulator Vent Valve 

 Air Vent Valve 

BBOLTCK Berthing Bolt Check 

BC Bolt Controller 

 Bus Controller 

55
STS-102 

BCDU Battery Charge/Discharge Unit 

BCU Backup Control Unit 

BDT Binary Data Transfer 

BG Beta Gimbal 

BGA Beta Gimbal Assembly 

BGDTS Beta Gimbal Deployment Transition Structure 

BGHS Beta Gimbal Housing Subassembly 

BIC Bus Interface Card 

BIT Built-In Test 

BMRRM Bearing Motor and Roll Ring Module 

BP/ECG Blood Pressure/Electrocardiogram 

BSP Baseband Signal Processor 

C&C Command and Control 

C&DH Command and Data Handling 

C&M Control and Monitor 

C&T Communications and Tracking 

C&W Caution and Warning 

CADU Channel Access Data Units 

CAM Centrifuge Accommodations Module 

CBM Common Berthing Mechanism 

CCAA Common Cabin Air Assembly 

CCC CTP Controller Card 

CCH Crew Communications Headset 

CCHA Crew Communications Headset Assembly 

CCPK Crew Contamination Protection Kit 

CCS Command and Control Software 

CCSDS Consultative Committee for Space Data Systems 

CCT Cold Cathode Transducer 

CCTV Closed-Circuit Television 

CDDT ???6-1 

CDMK Carbon Dioxide Monitoring Kit 

CDRA Carbon Dioxide Removal Assembly 

CDS Command and Data Software 

CEVIS Cycle Ergometer with Vibration Isolation and Stabilization 

CHeCS Crew Health Care System 

CHX Condensing Heat Exchanger 

CID Circuit Interrupt Device 

CIR Cargo Integration Review 

CLA Capture Latch Assembly 

CMG Control Moment Gyro 

CMO Crew Medical Officer 

CMRS Crew Medical Restraint System 

COAS Crew Optical Alignment System 

COTS Commercial-Off-The-Shelf 

CPA Controller Panel Assembly 

CPDS Crew Passive Dosimetery System 

56
STS-102 

CPS Cabin Pressure Sensor 

CSA-CP Compound Specific Analyzer-Combustion Products 

CSCI Computer Software Configuration Item 

CSI Common Structural Interface 

CSV CO2 Selector Valve 

CTP Command and Telemetry Processor 

CVIU Common Video Interface Unit 

CVT Current Value Table 

CVV CO2 Vent Valve 

CWC Contingency Water Collection 

DA Depressurization Assembly 

DAIU Docked Audio Interface Unit 

DAK Double-Aluminized Kapton 

DBBOLTCK Deberthing Bolt Check 

DCP Display and Control Panel 

DCSU Direct Current Switching Unit 

DDCU DC-to-DC Converter Unit 

DIO Discrete Input/Output 

DMCU Docking Mechanism Control Unit 

DSP Digital Signal Processor 

EA Electronics Assembly 

EAS Early Ammonia Servicer 

ECG Not called out 

ECLSS Environmental Control and Life Support System 

ECM Embedded Control Module 

ECS Early Comm Subsystem 

 Early Communications Subsystem 

ECU Electronics Control Unit 

EELS Emergency Egress Lighting System 

EETCS Early External Thermal Control System 

EIA Electrical Interface Assembly 

EIB Electronic Interface Box 

ELS Emergency Lighting Strip 

EMA Engagement Mechanism Assembly 

EMI Electromagnetic Interference 

EMU Extravehicular Mobility Unit 

EPS Electrical Power System 

ESA External Sampling Adapter 

ESP External Stowage Platform 

ETI Elapsed Time Indicator 

EUE Experiment Unique Equipment 

EVA Extravehicular Activity 

EXPRESS EXpedite the PRocessing of Experiments to the Space Station 

57
STS-102 

FBOLT Final Bolt Load 

FC Fuel Cell 

FCC Flat Collector Circuit 

FCT Flight Control Team 

FCV Flow Control Valve 

FDI Fault Detection and Isolation 

FDIR Fault Detection, Isolation and Recovery 

FDS Fire Detection and Suppression 

FET Field Effect Transistors 

FGB Functional Cargo Block 

FMC Fan Motor Controller 

FMK Formaldehyde Monitor Kit 

FO Fiber Optic 

FQDC Fluid Quick Disconnect Coupling 

FRGF Flight Releasable Grapple Fixture 

FSE Flight Support Equipment 

FSS Fluid Servicer System 

GFE Government-Furnished Equipment 

GFI Ground Fault Interrupter 

 Ground Fault Interruption 

GLA General Lighting Assembly 

GLONASS Global Navigational Satellite System 

GNC Guidance Navigation and Control 

GPC General Purpose Computer 

GPS Global Positioning System 

GSE Ground Support Equipment 

HAB Habitation 

HCA Hollow Cathode Assembly 

HCU Headset Control Unit 

 Heater Control Unit 

HDR High Data Rate 

HEC Headset Extension Cable 

HEPA High Efficiency Particulate Air 

HGA High Gain Antenna 

HIC Headset Interface Cable 

HLA High Level Analog 

HRD High Rate Dosimeter 

HRDL High Rate Data Lines 

HRF Human Research Facility 

HRFM High-Rate Frame Multiplexer 

HRM Heart Rate Monitor 

 High Rate Modem 

I/O Input/Output 

IAC Internal Audio Controller 

58
STS-102 

IAS Internal Audio Subsystem 

IBOLT Initial Bolt Load 

 Intermediate Bolt 

ICC Integrated Cargo Carrier 

ICD Interface Control Document 

IDA Integrated Diode Assembly 

IEA Integrated Equipment Assembly 

IELK Individual Equipment Liner Kits 

IFHX Interface Heat Exchanger 

IMCA Integrated Motor Controller Assembly 

IMS Inventory Management System 

IMV Intermodule Ventilation 

IOCU Input/Output Control Unit 

 Input/Output Controller Unit 

iRED Interim Resistive Exercise Device 

IRED Isolated Resistive Exercise Device 

ISA Internal Sampling Adapter 

ISOV Intermodule Ventilation Shutoff Valve 

ISPR International Standard Payload Rack 

ISS International Space Station 

ISSP International Space Station Program 

ISSSH International Space Station System Handbook 

ITCS Internal Thermal Control System 

IVA Intravehicular Activity 

IV-CPDS Intravehicular-Charged Particle Directional Spectrometer 

IVSU Internal Video Switch Unit 

JOP Joint Operations Panel 

KBAR Knee Brace Assembly Replacement 

KYA Keel Yoke Assembly 

LAN Local Area Network 

LB Local Bus 

LBOLT Loosen Bolt Load 

LC Latch Controller 

LCA Lab Cradle Assembly 

 Load Control Assembly 

 Loop Crossover Assembly 

LDA Launch Deployment Assembly 

LDI Local Data Interface 

LDR Low Data Rate 

LED Light Emitting Diode 

LFDP Load Fault Detection Protection 

LGA Low Gain Antenna 

LiOH Lithium Hydroxide 

LLA Low Level Analog 

59
STS-102 

LNS Lab Nitrogen System 

LON Launch On Need 

LOS Loss of Signal 

LRU Line Replaceable Unit 

LT Low Temperature 

LTL Low Temperature Loop 

LVLH Local Vertical/Local Horizontal 

MA Mechanical Assembly 

MAS Microbial Air Sampler 

MBE Metal Bellows Expander 

MBM Manual Berthing Mechanism 

MC Mid Course Correction 

MCA Major Constituent Analyzer 

MCC Mission Control Center 

MCC-H Mission Control Center-Houston 

MCDS Multifunction CRT Display System 

MCOR Medium Rate Comm Outage Recorder 

MCS Motion Control System 

MDA Motor Drive Assembly 

MDM Multiplexer/Demultiplexer 

MDPS Meteoroid and Debris Protection System 

MEC Medical Equipment Computer 

MFCV Manual Flow Control Valve 

MIL-STD Military Standard 

MIP Mission Integration Plan 

MLE Middeck Locker Equivalent 

MLI Multi-Layer Insulation 

MM/OD Micrometeoroid Orbital Debris 

MOD Mission Operations Directorate 

MPEV Manual Pressure Equalization Valve 

MPLM Mini Pressurized Logistics Module 

 Multipurpose Logistics Module 

MPM Manipulator Positioning Mechanism 

MPR Manual Pulmonary Resuscitator 

MPSD Multipurpose Support Drive 

MPV Manual Procedures Viewer 

MRDL Medium Rate Data Lines 

MRL Manipulator Retention Latch 

MSD Mass Storage Device 

MSFC Marshall Space Flight Center 

MT Moderate Temperature 

MTL Moderate Temperature Loop 

MTSAS Module-to-Truss Segment Attach System 

MTSAS-A Module-to-Truss Segment Attach System-Active 

MTSAS-P Module-to-Truss Segment Attach System-Passive 

60
STS-102 

NASA National Aeronautics and Space Administration 

NATC NASA Threaded Coupling 

NBLC NASA Breech Lock Coupling 

NCC Nominal Corrective Combination 

NCG Non-Condensable Gas 

NCS Node Control Software 

 Node Control Software 

NIA Nitrogen Interface Assembly 

NIV Nitrogen Introduction Valve 

NPRA Negative Pressure Relief Assembly 

NPRV Negative Pressure Relief Valve 

NZGL NASA Zero-G Lever 

NZGW NASA Zero-G Wing 

OCA Orbiter Communications Adapter 

ODA Orbiter Disconnect Assembly 

ODF Operations Data File 

ODM Orbiter Drive Mechanism 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

 On-Orbit Replaceable Unit 

OMS Orbital Maneuvering System 

OP Overhead Port 

OPS LAN Operations Local Area Network 

ORU Orbital Replacement Unit 

 Orbiter Replaceable Unit 

OS Overhead Starboard 

OSE Orbital Support Equipment 

OSO Operations Support Officer 

OSTP Onboard Short-Term Plan 

OSVS Orbiter Space Video System 

OTD ORU Transfer Device 

P&S Pointing and Support 

P/T Pressure/Temperature 

PA Pressurized Adapter 

PAV Process Air Valve 

PBA Portable Breathing Apparatus 

PBIT Passive Built-In-Test 

PCA Pressure Control Assembly 

PCBM Passive Common Berthing Mechanism 

PCC Power Converter Controller 

PCMCIA Personal Computer Memory Card International Association 

PCP Pressure Control Panel 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PCT Post Contact Thrust 

61
STS-102 

PCU Plasma Contactor Unit 

PD Port Deck 

PDA Payload Disconnect Assembly 

PDB Power Distribution Box 

PDGF Power Data Grapple Fixture 

PDI Payload Data Interface 

PDS Passive Dosimetery System 

PDU Power Distribution Unit 

 Power Drive Unit 

PEHG Payload Ethernet Hub Gateway 

PEV Pressure Equalization Valve 

PFCS Pump and Flow Control Subassembly 

PFE Portable Fire Extinguisher 

PFMC Pump/Fan Motor Controller 

PGSC Payload General Support Computer 

PGT Pirini Gage Transducer 

PHP Perimeter Hole Pattern 

PL Payload 

PL PRI Primary Payload 

PMA Pressurized Mating Adapter 

PMC Pump Motor Controller 

PMCU Power Management Control Unit 

POIC Payload Operations Integration Center 

PPA Pump Package Assembly 

PPL Pre-Positioned Load 

PPRA Positive Pressure Relief Assembly 

PPRV Positive Pressure Relief Valve 

PRC PORTCOM Receiver Card 

PRLA Payload Retention Latch Assembly 

PSP Payload Signal Processor 

PT Pressure Transducer 

PTC PORTCOM Transmit Card 

PTCS Passive Thermal Control System 

PUI Program Unique Identifiers 

PV Photovoltaic 

PVCA Photovoltaic Controller Application 

PVCE Photovoltaic Controller Elements 

PVCU Photovoltaic Controller Unit 

PVM Photovoltaic Module 

PVR Photovoltaic Radiator 

PVTCS Photovoltaic Thermal Control System 

QD Quick Disconnect 

R&MA Restraint and Mobility Aid 

R&R Removal and Replacement 

R-S Reed-Solomon 

62
STS-102 

R/F Refrigerator/Freezer 

RAB Rack Attachment Block 

RAC Remote Antenna Controller 

RAIU Russian Audio Interface Unit 

RAM Radiation Area Monitor 

 Random Access Memory 

RAMV Rheostat Air Mix Valve 

RBI Remote Bus Isolator 

RBOLT Remove Bolt Load 

RCU Remote Control Unit 

REMA Restraint and Mobility Aids 

RF Radio Frequency 

RFCA Rack Flow Control Assembly 

RFG Radio Frequency Group 

RFPDB Radio Frequency Power Distribution Box 

RGA Rate Gyro Assembly 

RHC Rotational Hand Controller 

RHX Regenerative Heat Exchanger 

RM Research Module 

RMS Remote Manipulator System 

ROEU Remotely Operated Electrical Umbilical 

ROFU Remotely Operated Fluid Umbilical 

ROS Russian On-orbit Segment 

RPC Remote Power Controller 

RPCM Remote Power Controller Module 

RPDA Remote Power Distribution Assembly 

RPS Rack Power Switch 

RSA Russian Space Agency 

RSP Respiratory Support Pack 

 Resupply Stowage Platform 

RSR Resupply Storage Rack 

RSTS Rack Standalone Temperature Sensor 

RT Remote Terminal 

RTAS Rocketdyne Truss Attachment System 

RTD Resistive Thermal Device 

RTL Ready-to-Latch 

RU Rigid Umbilical 

RWS Remote Workstation 

 Robotic Workstations 

S&M Structures and Mechanisms 

SAFER Simplified Aid for EVA Rescue 

SASA S-band Antenna Support Assembly 

SAW Solar Array Wing 

SCA Switchgear Controller Assembly 

SCI Signal Conditioning Interface 

SCSI Serial Command and Monitoring Interface 

63
STS-102 

SD Starboard Deck 

SDS Sample Delivery System 

 Sample Distribution System 

SEM Shunt Electronics Module 

SFCA System Flow Control Assembly 

SGANT Space-to-Ground Antenna 

SGI Square Grid Interface 

SGTRC Space-to-Ground Transmitter/Receiver Controller 

SLP Spacelab Pallet 

SM Service Module 

 System Monitoring 

SMA Sensor Module Assembly 

SMCC Service Module Central Computers 

SOC State of Charge 

SOV Shutoff Valve 

SPD Serial Parallel Digital 

SPDA Secondary Power Distribution Assembly 

SPEC Specialist Function 

SPG Single Point Ground 

SPP Science Power Platform 

SRMS Shuttle Remote Manipulator System 

SSA S-band Single Access 

SSAF S-band Single Access Forward 

SSAR S-band Single Access Return 

SSC Station Support Computer 

SSK Surface Sampler Kit 

SSOV Sample Line Shutoff Valve 

SSP Standard Switch Panel 

SSRMS Space Station Remote Manipulator System 

SSSR S-band Single Access Return 

SSU Sequential Shunt Unit 

STCR Starboard Thermal Control Radiator 

STIPL Standard Interface Plate 

SW Software 

TA Thruster Assist 

TB Talkbacks 

TC Terminal Computer 

TCCS Trace Contaminant Control Subassembly 

TCCV Temperature Control and Check Valve 

TCS Thermal Control Subsystem 

 Thermal Control System 

TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

TEPC Tissue Equivalent Proportional Counter 

TERA Temporary Equipment Restraint Aid 

TFL Telemetry Format List 

64
STS-102 

THA Thermostat Housing Assembly 

THC Temperature and Humidity Control 

 Translational Hand Controller 

TI Transition Initiation 

TMA Torque Motor Assembly 

TOCA Total Organic Carbon Analyzer 

TPS Total Pressure Sensors 

TTCR Trailing Thermal Control Radiator 

TTL Transfer Tracking Log 

TVIS Treadmill with Vibration Isolation System 

TWMV Three-Way Mixing Valve 

UCP Unpressurized Cargo Pallet 

UDG User Data Generation 

UDM Universal Docking Module 

UDMH Unsymmetrical Dimethylhydrazine 

UIP Utility Interface Panel 

UOP Utility Outlet Panel 

USOS United States On-orbit Segment 

UTAS Universal Trunnion Attach System 

VAJ Vacuum Access Jumper 

VAP Vacuum Access Port 

VBSP Video Baseband Signal Processor 

VDS Video Distribution Subsystem 

VES/VRS Vacuum Exhaust/Resource System 

VIS Vibration Isolation System 

VMDS Valve Motor Drive Switch 

VRA Vent Relief Assembly 

VRCV Vent and Relief Control Valve 

VRIV Vent and Relief Isolation Valve 

VSC Video Signal Conditioner 

VSU Video Switching Unit 

VTR Video Tape Recorder 

VTS Video Teleconferencing System 

WIF Worksite Interface 

WMK Water Microbiology Kit 

WOV Water ON/OFF Valve 

WPP Water Pump Package 

WRM Water Recovery and Management 

WS Water Separator 

WSA Water Sampler and Archiver 

WVA Water Vent Assembly 

XPDR Standard TDRSS Transponder 

XPOP X-Axis Perpendicular to Orbital Plane 

ZSR Zero-G Stowage Rack 

65
STS-102

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

 

66
STS-102

General information on NASA and its programs is available through the NASA Home 

Page and the NASA Public Affairs Home Page: 

http://www.nasa.gov

 

or 

http://www.nasa.gov/newsinfo/index.html

 

Shuttle Pre-Launch Status Reports

http://www-pao.ksc.nasa.gov/kscpao/status/stsstat/current.htm

 

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.

67
STS-102

Media Contacts 

NASA PAO Contacts 

Dwayne Brown 202 358-1726

NASA Headquarters

Washington , DC

Space Shuttle/Space Station 

Policy

dwayne.brown@hq.nasa.gov

Debbie Rahn 202 358-1638

NASA Headquarters

Washington, DC

International Partners

debbie.rahn@hq.nasa.gov

Eileen Hawley 281 483-5111

NASA Johnson Space Center

Houston, TX

Astronauts/Mission Operations

eileen.hawley1@jsc.nasa.gov

Kyle Herring 281 483-5111

NASA Johnson Space Center

Houston, TX

International Space Station 

Operations

kyle.j.herring1@jsc.nasa.gov

Carlos Fontanot 256 961-6226

Moscow, 

NASA Moscow PAO

carlos.fontanot1@jsc.nasa.gov

Bruce Buckingham 312 867-2468

NASA Kennedy Space Center

Kennedy Space Center, FL

Launch Operations

bruce.buckingham-1@kmail.ksc.nasa.gov

Dave Drachlis 256 544-0034

NASA Marshall Space Flight Center

Huntsville, AL

Space Station Science

Dave.Drachlis@msfc.nasa.gov

68
STS-102

Jack King 321 861-4358

United Space Alliance

Kennedy Space Center, FL

Shuttle Processing

KingJW@usafoo.unitedpsacealliance.com

Kari Kelley-Allen 281 336-4844

The Boeing Company

Houston, TX

International Space Station

kari.k.allen@boeing.com

Beth Hill 714 372-4736

The Boeing Company

Huntington Beach, CA

Space Shuttle

sara.b.hill@boeing.com

Dan Beck 818 586-4572

Boeing Rocketdyne

Canoga Park, CA

Space Shuttle Main Engiens

daniel.c.beck@boeing.com

69
Table prepared by Richard W. Orloff, 06/15/2001 

SHUTTLE FLIGHTS AS OF MARCH 2001 

102 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 77 SINCE RETURN TO FLIGHT 

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-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-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 

(28 flights) 

OV-104 

Atlantis 

(23 flights) 

OV-105 

Endeavour 

(15 flights)