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Updated November 10, 2000

ENDEAVOUR:

DELIVERING 

SOLAR ARRAYS

TO THE

INTERNATIONAL

SPACE STATION

STS-97
STS-97 

Table of Contents

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

Crew ...............................................................................................................................4 

Mission Profile ..............................................................................................................7 

Flight Day Summary Timeline ......................................................................................9 

Rendezvous .................................................................................................................10 

EVAs 

STS-97 EVA ................................................................................................................12 

Payloads 

Payload Overview ........................................................................................................18 

Photovoltaic Array Assembly (PVAA) ..........................................................................20 

Integrated Equipment Assembly ..................................................................................22 

The Long Spacer .........................................................................................................24 

Experiments 

JASON On Board Seed Experiments ..........................................................................25 

DTO/DSO/RME 

DTO 257 Structural Dynamics Model Validation ..........................................................27 

DTO 261 International Space Station On-Orbit Loads Validation ................................28 

DTO 700-14 Single-String Global Positioning System .................................................29 

DTO 700-22 Crew Return Vehicle (CRV) Space Integrated Global Positioning 

System/Inertial Navigation System (SIGI) ....................................................................30 

DTO 805 Crosswind Landing Performance .................................................................31 

DTO HTD 1403 Micro-Wireless Instrumentation System (Micro-WIS) .........................32 

DTO HTD 1404 Laser Dynamic Range Imager (LDRI) ................................................33 

DSO 802 Educational Activities ...................................................................................34 
STS-97 

Mission Benefits ........................................................................................................35 

Shuttle Reference and Data 

Shuttle Abort Modes ....................................................................................................39 

Shuttle External Tank ..................................................................................................44 

Space Shuttle Rendezvous Maneuvers .......................................................................47 

Space Shuttle Solid Rocket Boosters ..........................................................................48 

Space Shuttle Super-Lightweight Tank (SLWT) ..........................................................56 

Acronyms and Abbreviations ...................................................................................57 

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

Media Contacts ..........................................................................................................70 
STS-97

Mission Overview 

ENDEAVOUR'S FLIGHT HELPS THE STATION SPREAD ITS 

WINGS 

During 10 days punctuated by space flight firsts, the Space Shuttle Endeavour on mission 

STS-97 will see the International Space Station spread its wings -- giant solar arrays that 

will quintuple the station's electrical power, enabling future unparalleled research. 

The 240-foot solar arrays to be attached and unfolded by Endeavour’s international 

crew of five – Commander Brent Jett, Pilot Mike Bloomfield and Mission Specialists Joe 

Tanner, Carlos Noriega and Canadian Space Agency astronaut Marc Garneau – will be 

the longest structure to ever fly in space. Endeavour will carry aloft the United Statesdeveloped solar arrays, associated electronics, batteries, cooling radiator, and support 

structure. The entire 17-ton package is called the P6 Integrated Truss Segment, and it 

will be the heaviest and largest element yet delivered to the station aboard a Shuttle. 

The addition of the huge solar arrays – only the first of three identical such sets that will 

be attached to the station in coming years -- will clearly distinguish the International 

Space Station from any predecessor spacecraft. They will provide the station with more 

electrical power, a key to successful modern research, than anything that has flown 

before. Endeavour also will be the first Space Shuttle to visit an inhabited International 

Space Station, although the Shuttle crew and station crew of Commander Bill Shepherd, 

Pilot Yuri Gidzenko and Flight Engineer Sergei Krikalev will not greet one another until the 

hatches are fully opened between the spacecraft on the seventh day of the mission. 

Endeavour is targeted for launch on STS-97 at 10:05 p.m. EST from the Kennedy 

Space Center, Florida, at the opening of a launch window that extends for between two 

to five minutes. After two days spent slowly closing in on the complex and checking out 

equipment, Jett will maneuver Endeavour to dock with the International Space Station 

just before 2 p.m. on Dec. 2, given an on-time launch. 

Immediately after docking, Garneau will use the shuttle's 50-foot, Canadian-built robotic 

arm to initially lift the truss segment a few feet out of the shuttle cargo bay, holding it in 

position there overnight to control its temperature. Also, the Shuttle crew will open the 

station's outermost hatch and stow some early supplies in an outer compartment of the 

station to await retrieval later in the mission by the Expedition One crew. 

On the following day, the crew will begin installing the solar arrays on the station, with 

Tanner and Noriega conducting the first of two planned six and a half hour space walks. 

With Tanner and Noriega assisting from outside, Garneau will use the robotic arm to 

attach the truss segment package, including the folded arrays and electronics, atop a 

smaller exterior framework already on the station. Tanner and Noriega will visually 

assist Garneau to properly align the new segment. The two space walkers will tighten 

attachment bolts to ensure the P6 truss is mechanically secure. Next, they will connect 

umbilicals for power and data between the new equipment and the rest of the station, as 

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well as release various restraints that were in place to protect equipment during the 

Shuttle’s launch. Near the end of the first space walk, the crew will send commands to 

begin deploying the solar arrays, folded for launch into a box only 20 inches thick, to 

their full outstretched length. 

A second space walk by Tanner and Noriega on the sixth day of the mission will move a 

communications antenna to a location high on the new truss segment. During the last half 

of the space walk, they will prepare the station for the next shuttle visit that will deliver the 

first laboratory, the United States' Destiny lab, in January 2001. The capability exists to 

add a third space walk by Tanner and Noriega to the mission if needed. 

The Shuttle and station crews will greet one another for the first time on the seventh day 

of the mission as they fully open the hatches between the two spacecraft. The crews will 

spend two days working together, transferring supplies and equipment back and forth. 

Endeavour's visit and the power from the new solar arrays will allow the station crew to 

begin conducting some of the first experiments aboard the station after Endeavour 

departs. Those experiments will include: student experiments conducted in conjunction 

with the national JASON education project that will study the effects of space on 

soybean and corn seeds; an experiment developed by the Air Force and the 

Massachusetts Institute of Science and Technology that will study new control 

mechanisms for satellites; and several medical evaluations that will study the 

effectiveness of exercise on the station's treadmill and other exercise equipment. 

Based an on-time launch on Nov. 30, Bloomfield is scheduled to undock Endeavour 

from the station just after noon CST on Dec. 8, performing a full-circle flyaround of the 

complex before departing the vicinity. The day after the undocking will be spent 

preparing Endeavour for landing, and the Shuttle's touchdown would occur at the 

Kennedy Space Center about 5:46 p.m. CST on Dec. 10, nine days, 20 hours and 41 

minutes after launch. 

STS-97 will be the 15th flight of Endeavour and the 101st Space Shuttle mission. 

An Overview of STS-92

Flight Day 1: On Flight Day 1, Endeavour and its five-member crew will launch from the 

Kennedy Space Center. Once on orbit, they will climb out of their launch and entry suits, 

open the payload bay doors, reconfigure computers and other equipment on board, and 

activate a three-dimensional IMAX camera. The astronauts will go to sleep 

approximately five hours after launch. 

Flight Day 2: Flight Day 2 is a day of preparation for Endeavour’s crew as the 

astronauts activate and check out the Shuttle’s robotic arm using it to conduct a survey 

of the cargo latched into the payload bay; check out the Space Vision System that will 

provide Marc Garneau with visual cues as he unberths the P6 truss from the payload 

bay on Flight Day 3; inspect the space suits that will be worn by Astronauts Joe Tanner 

and Carlos Noriega on Flight Days 4 and 6; and begin activating wireless 

instrumentation systems that provide temperature data on the cargo mounted in 

Endeavour’s payload bay. 

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Flight Day 3: With an on-time launch on November 30, Flight Day 3 will see Endeavour 

dock to a port on the Unity module of the International Space Station shortly before 2 

p.m. CST. After docking, the P6 integrated truss – containing the large solar arrays – 

will be lifted out of Endeavour’s payload bay and moved into an overnight ‘parking’ 

position. The astronauts will also begin preparing the docking port for their later entry 

into the ISS. 

Flight Day 4: Astronauts Joe Tanner and Carlos Noriega will take the first of their two 

scheduled space walks to install the solar arrays that will provide increased power to the 

U.S. portions of the space station. 

Flight Day 5: The astronauts will get some rest following the first of their two scheduled 

space walks, and begin preparing for their entry into the space station on Flight Day 7. 

Flight Day 6: Tanner and Noriega will take their second space walk on Flight Day 6, 

relocating a communications antenna to the top of the P6 truss that was installed on 

Flight Day 4. They will also begin preparing the Station for the arrival of the U.S. 

laboratory Destiny, by relocating some foot restraints and power cables that will be used 

by the STS-98 crew early next year. 

Flight Day 7: After spending six days attached to the International Space Station, the 

STS-97 and Expedition One (resident) crew will swing open the hatches between 

Endeavour and the ISS to greet one another and transfer equipment and supplies. 

Flight Day 8: With Pilot Mike Bloomfield at the controls, Endeavour will undock from the 

ISS, flying one full circle around it before firing the Shuttle’s engines to begin its final 

departure from the station. The rest of the day will be spent preparing Endeavour for its 

return to Earth on Flight Day 10. 

Flight Day 9: Endeavour’s astronauts begin the process of heading home on Flight Day 

9 as they put away the tools, hardware, checklists, cameras and other materials they 

have used while in space. In addition, Brent Jett, Mike Bloomfield and Marc Garneau 

will conduct the routine day-before-landing checks of the Shuttle’s small reaction control 

system jets and aero surfaces to ensure their health prior to landing. 

Flight Day 10: Flight Day 10 should see Endeavour return to the Kennedy Space Center 

and conclude its mission to help the growing space station spread its wings. On board, 

the astronauts will finish putting away last-minute items, climb into their orange launch 

and entry suits and close the payload bay doors. When they receive a "go" decision from 

the Flight Control Team in Houston, they will fire Endeavour’s engines in a deorbit burn to 

bring the Shuttle and its five-member crew out of orbit and back to Earth. 

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Crew Profile Menu

Commander: Brent W. Jett 

Brent Jett (Cdr., USN), 42, leads an all-veteran crew on 

Endeavour’s flight to install the sprawling U.S. solar arrays on the 

International Space Station (ISS) during the STS-97 mission. 

Jett is responsible for the overall success of the flight and the 

safety of his crew. He will fly Endeavour to its linkup with a new 

docking port on the ISS and supervise the deployment of the 

arrays, which when unfurled, will span 240 feet wingtip to wingtip. 

After his last flight, Jett spent almost a year as the Director of 

Operations for NASA at the Gagarin Cosmonaut Training Center in Star City, Russia, 

overseeing the training of U.S. astronauts involved in preparations for flights to the ISS. 

Jett is making his third trip into space, having flown as Pilot on the STS-72 mission in 1996 

and the STS-81 mission in 1997 to the Mir Space Station. 

Ascent Seating: Flight Deck - Port Forward

Entry Seating: Flight Deck - Port Forward

Pilot: Michael J. Bloomfield 

Mike Bloomfield (Lt. Col., USAF), 41, is making his second flight 

into space as Pilot on the STS-97 mission. 

On Endeavour’s flight to the ISS, Bloomfield will assist Jett during 

the rendezvous and approach to the ISS and will be at the controls 

for Endeavour’s undocking from the Station and a subsequent 

flyaround of the new facility. He will operate Endeavour’s robot arm 

during two space walks planned for the mission, maneuvering a 

pair of astronauts around the ISS as they conduct their assembly 

work. 

Bloomfield first flew as Pilot of the STS-86 mission to the Mir Space Station in 1997 which 

delivered Astronaut David Wolf to the Russian outpost and brought Mike Foale home after a 

four-month stay. 

Ascent Seating: Flight Deck - Starboard Forward

Entry Seating: Flight Deck - Starboard Forward

RMS 

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Mission Specialist 1: Joseph R. Tanner 

Joe Tanner, 50, is making his third flight into space and is 

designated as Mission Specialist 1 (MS 1). For the flight, he will be 

seated on the flight deck for Endeavour’s launch and the middeck 

for entry and landing. 

He will be responsible for the operation of Endeavour’s docking 

system and will join Noriega for two ISS assembly space walks 

during this flight. Tanner will work with Noriega to install the 

photovoltaic arrays on the ISS, hook up electrical and data cables, 

relocate the Station’s S-band communications system and conduct 

other tasks to prepare the ISS for the arrival of the U.S. Laboratory Destiny early next year. 

Tanner will be designated as EV 1 during the two space walks, and will wear the spacesuit 

bearing the red stripes. Tanner will assist Marc Garneau in the transfer and stowage of 

logistical items and hardware for the Expedition One crew, aboard the ISS. The former 

Navy pilot will also share prime responsibility for the systems of the solar arrays and will 

operate an IMAX camera during the flight to document the crew’s activities. 

Tanner flew on the STS-66 mission in 1994 and conducted a pair of space walks on the 

STS-82 mission in 1997 to refurbish the Hubble Space Telescope. 

Ascent Seating: Flight Deck - Starboard Aft

Entry Seating: Mid Deck - Port

EV1 

Mission Specialist 2: Marc Garneau 

Dr. Marc Garneau, 51, of the Canadian Space Agency, is making 

his third flight into space on the STS-97 mission, having earned the 

distinction of becoming the first Canadian to fly in space 16 years 

ago. As Mission Specialist 2 (MS 2), Garneau will serve as flight 

engineer during Endeavour’s launch and landing. 

Garneau will assist crewmate Noriega in using a variety of 

navigational tools to assist Jett in the rendezvous and docking with 

the International Space Station. 

During docked operations, Garneau will use the Canadian-built robot arm to install the large 

U.S. solar arrays on the ISS. Garneau also will serve as onboard choreographer during the 

two space walks planned for the flight. 

Once aboard the ISS, Garneau will oversee the transfer of cargo to the Expedition One 

crew and will help ISS Commander Bill Shepherd, Soyuz Commander Yuri Gidzenko and 

Flight Engineer Sergei Krikalev in the stowage of equipment and other supplies. 

He first flew on the STS-41G mission in 1984 and returned to space in 1996 on the STS-77 

mission. 

Ascent Seating: Flight Deck - Center Aft

Entry Seating: Flight Deck - Center Aft

RMS 

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Mission Specialist 3: Carlos I. Noriega 

Carlos Noriega (Lt. Col., USMC), 41, is making his second flight 

into space aboard Endeavour. Noriega serves as Mission 

Specialist 3 (MS 3) on STS-97, responsible for the onboard 

computers and the navigational tools which will be used to assist 

Jett in his rendezvous with the ISS. 

Noriega shares responsibility for all of the systems of the large 

solar arrays that will be installed on the ISS to provide the most 

powerful source of electricity of any orbiting spacecraft. During the 

two space walks in which he and Tanner will supervise the solar 

array installation and other Station assembly work, Noriega will be designated EV 2, and 

will wear the pure white spacesuit. 

Noriega will be seated in Endeavour’s middeck for launch and will take a seat on the 

Shuttle’s flight deck for entry and landing. 

Noriega previously flew on the STS-84 mission in 1997, visiting the Mir Space Station as 

part of the Shuttle/Mir Program.

Ascent Seating: Mid Deck - Port

Entry Seating: Flight Deck - Starboard Aft

EV2 

Updated: 11/09/2000 

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Mission Profile 

Endeavour OV105 

Launch: Thursday, November 30, 2000 

 10:05 PM (eastern time)

Crew

 

Commander: Brent W. Jett

Pilot: Michael J. Bloomfield

Mission Specialist 1: Joseph R. Tanner

Mission Specialist 2: Marc Garneau

Mission Specialist 3: Carlos I. Noriega

Launch

 

Orbiter: Endeavour OV105

Launch Site: Kennedy Space Center Launch Pad 39B

Launch Window: 2.5 Minutes

Altitude: 173 Nautical Miles

Inclination: 51.6 Degrees

Duration: 9 Days 20 Hrs. 41 Min.

Vehicle Data

 

Shuttle Liftoff Weight: 4524410 lbs.

Orbiter/Payload Liftoff Weight: 266185 lbs.

Orbiter/Payload Landing Weight:

 

197879 lbs.

Payload Weights

PVAA 185 pounds

IEA 17,000 pounds

LS 245 pounds

Software Version: OI-27

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Space Shuttle Main Engines

SSME 1: 2043 SSME 2: 2054 SSME 3: 2049

External Tank: ET-105A ( Super Light Weight Tank)

SRB Set: BI103PF/R074-99 

Shuttle Aborts

Abort Landing Sites

 RTLS: Kennedy Space Center Shuttle Landing Facility

 TAL: Zaragoza

 AOA: Edwards Air Force Base, California

Landing

 

Landing Date: 12/10/00

Landing Time: 6:46 PM (eastern time)

Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

Payloads

Cargo Bay

PHOTOVOLTAIC ARRAY ASSEMBLY (PVAA):

INTEGRATED EQUIPMENT ASSEMBLY 

THE LONG SPACER 

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Mission Summary 

Flight Day Summary 

DATE TIME (EST) DAY MET EVENT

11/30/00 10:05:30 PM 1 000/00:00 Launch

11/30/00 10:55:30 PM 1 000/00:50 OMS2 Burn

12/01/00 1:49:30 AM 1 000/03:44 NC1 Burn

12/01/00 1:42:30 PM 2 000/15:37 NC2 Burn

12/01/00 5:51:30 PM 2 000/19:46 NPC Burn

12/01/00 10:41:30 PM 2 001/00:36 NC3 Burn

12/02/00 10:21:30 AM 3 001/12:16 NH Burn

12/02/00 10:51:30 AM 3 001/12:46 NC4 Burn

12/02/00 12:22:30 PM 3 001/14:17 TI Burn

12/02/00 2:53:30 PM 3 001/16:48 Docking

12/02/00 6:10:30 PM 3 001/20:05 ISS Early Egress

12/03/00 2:00:30 PM 4 002/15:55 EVA 1 Start

12/03/00 8:05:30 PM 4 002/22:00 EVA 1 End

12/05/00 2:00:30 PM 6 004/15:55 EVA 2 Start

12/05/00 8:05:30 PM 6 004/22:00 EVA 2 End

12/06/00 1:00:30 PM 7 005/14:55 Joint PMA 3 Ingress

12/07/00 8:35:30 PM 8 006/22:30 ISS Hatch Close

12/08/00 1:18:30 PM 9 007/15:13 ISS Undock

12/08/00 2:25:30 PM 9 007/16:20 Final Sep

12/10/00 5:41:30 PM 11 009/19:36 Deorbit Burn

12/10/00 6:46:30 PM 11 009/20:41 Landing

Updated: 11/09/2000 

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Rendezvous

Endeavour Docks with the Station 

Endeavour’s rendezvous with the International Space Station actually begins with its 

precisely timed launch from the Kennedy Space Center in Florida. The Shuttle will 

rendezvous with the Station either on Flight Day 3 or 4, based on the time and date of 

launch, and at a time based on ISS-orbiter phasing. 

The primary pre-rendezvous activities include a check-out of the orbiter's remote 

manipulator system, or robot arm, (RMS), the extravehicular mobility units (EMUs), the 

Ku-band antenna, the orbiter docking system (ODS), and the ground command system. 

Final rendezvous operations begin about three hours prior to Endeavour’s docking with 

the ISS. Endeavour will approach the ISS from below, in what is referred to as a plus-R 

bar approach, to minimize the effects of jet thruster firings on the station and its solar 

arrays. About 40 minutes prior to the terminal initiation burn (Ti burn) when Endeavour 

moves within 135,000 feet of the station, the Shuttle’s rendezvous radar system is 

activated to provide supplemental navigation information. Prior to initiating the Ti burn, 

the crew will power on the ODS and activate Endeavour’s docking lights. 

A series of course correction burns will bring Endeavour to a point almost directly below 

and behind the International Space Station, at which point Commander Brent Jett 

initiates the manual portion of his approach to the ISS. 

Endeavour will intercept the R-bar at a distance of about 600 feet below the station. Jett 

will slowly move Endeavour to a point about 500 feet below the station before 

performing a 180 degree yaw maneuver to position Endeavour in a “tail forward” attitude 

for the final approach and docking. As Jett gently moves Endeavour toward the station, 

the Shuttle will stationkeep at distances of 170 feet and 30 feet before initiating the final 

approach and docking. Solar arrays on the Zarya and Zvezda modules will be feathered 

(or positioned) and locked during the 170 foot stationkeeping phase. Feathering is 

initiated by a command to reposition and hold each beta (and alpha) joint at a 

predetermined angle, which will limit the induced loads. 

Endeavour will dock with Pressurized Mating Adapter (PMA) 3 located on the nadir port 

of the Unity module. This new docking port was installed during the STS-92 mission in 

October. 

At initial contact and capture, the ISS will automatically switch to free drift, and 

Endeavour will go to free drift to avoid imposing excessive loads on the orbiter docking 

system (ODS). 

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After capture, light-emitting diodes (LEDs) on PMA-3 will blink confirming the ISS is in 

free drift. The crew will be able to see the red indicators through the overhead window 

on Endeavour’s aft flight deck and verify that the ISS is in the free-drift mode before 

beginning the automatic rigidization and retraction process and closure of the capture 

latches between the two docking hatches. 

Once a “hard dock” is confirmed, the ODS will be deactivated, Zvezda and Zarya solar 

arrays will resume sun tracking, and the Endeavour-ISS complex will maneuver to the 

mated attitude. 

Docked Operations

After the orbiter docks with the ISS, the crew will enter PMA-3 to install ground straps, 

and perform a pressure leak check and center disk removal to prepare for their later 

entry into the Unity module of the ISS for supply transfer. 

Mission Specialists Joe Tanner and Carlos Noriega will perform two scheduled space 

walks, or EVAs, during docked operations to install the P6 photovoltaic solar array for 

power distribution to the Station, relocate the S-band antenna installed during the STS92 mission in October, peform early external thermal control system connections, and 

complete some “get ahead” tasks for the STS-98/5A mission in February. 

Undocking and Flyaround

Before Endeavour undocks and departs on Flight Day 8, ground personnel will update the 

ISS vector and mass data. These data include attitude departure maneuver data, attitude 

hold data, post-departure mass properties, and post-departure attitude maneuver data. A 

navigation platform alignment will be performed. Zvezda and Zarya solar arrays will be 

commanded to stop sun tracking and will be feathered to the edge-on position. 

In preparation for undocking from the ISS, the STS-97 crew will once again power-up 

the orbiter docking system, turn on the Shuttle's docking lights, terminate all OIU 

operations, and enable the Shuttle’s navigational aids. 

Following its undocking from the ISS, Pilot Mike Bloomfield will slowly back Endeavour 

away from the ISS at the rate of about 1/10th of a foot-per-second before beginning a 

flyaround of ISS. Endeavour will move to a point about 450 feet below the station before 

beginning a tail-forward circuit of the station, arriving once again at a position 

approximately 600 feet below the ISS. At that point, Bloomfield will perform a final 

separation burn to move Endeavour away from the station. 

Once Endeavour is about 30 feet away from the station, the Expedition One crew will 

activate the station’s attitude control systems. The Zvezda module will then maneuver 

station to is normal orientation for orbital operations, the solar arrays will be commanded 

to resume sun tracking, and the station docking system and lights will be deactivated. 

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EVAs 

A Pair of Space Walks Brings New Power to the Station 

Overview 

STS-97 will carry a crew of five on a 10-day mission that includes two space walks or 

EVAs designed to install the P6 Integrated Truss Segment and its associated solar 

arrays that will generate power for the U.S. segments of the International Space Station. 

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Currently, two space walks are scheduled on Flight Days 4 and 6, assuming an on-time 

launch on Nov. 30, and a Flight Day 3 docking. Mission Specialist Joe Tanner is 

designated EVA crew member 1 (EV1) and will wear the spacesuit with red stripes on 

the legs. His space walking partner, Carlos Noriega is designated as EV2 and will be 

identifiable with his pure white space suit. Inside Endeavour’s cabin, Canadian Space 

Agency astronaut Marc Garneau will be the Intra-vehicular crew member (IV), acting as 

the on-orbit choreographer of the mission. Garneau also will use Endeavour’s robotic 

arm to attach the P6 truss segment to the International Space Station. Pilot Mike 

Bloomfield will then take over robotic arm operations for the remaining space walk 

tasks, freeing Garneau to devote his attention to assisting the two space walkers. 

History/Background 

EVA 1 

After Endeavour docks to the International Space Station, Marc Garneau will use the 

Shuttle’s robot arm to lift the P6 structure out of the payload bay where it will remain 

attached overnight. Prior to the start of the first space walk, he will use the arm to move the 

35,000 pound assembly to the “low hover” position adjacent to Endeavour’s payload bay. 

Once the P6 is in its low hover position, the EVA crew will exit Endeavour’s air lock and 

begin assembling the tools and hardware they will use during the planned 6 1⁄2 hour 

space walk. 

EV1 Joe Tanner and EV2 Carlos Noriega will take positions on the forward and aft sides 

of the Z1 truss, respectively, to provide robot arm operator Marc Garneau with visual 

cues as he unberths the P6 structure. Garneau’s primary cues will come from the Space 

Vision System that provides him with a closed circuit television view of targets located 

on the P6 and the ISS, but Tanner and Noriega will provide verbal confirmation and 

additional visual cues throughout the unberthing process. 

Once Garneau moves the P6 within its capture envelope, Tanner and Noriega will verify 

the ready-to-latch position and activate the capture latches on the Z1 truss, initiating a 

coarse alignment between the P6 and Z1 truss. Noriega will then drive the capture latch 

assembly to bring the P6 into fine alignment. After the structure is secured in place – by 

127 turns of the Capture Latch Assembly (CLA) – Tanner and Noriega will begin 

securing bolts on each of the four corners of the P6 before releasing the capture latch to 

allow loads to be carried through the primary bolts. 

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At that point, Garneau will release the robot arm’s grip on the P6 structure and 

maneuver it into position to allow Noriega to attach an articulating portable foot restraint. 

At this point in the space walk, Pilot Mike Bloomfield assumes responsibility for 

operating the robot arm using it to maneuver Noriega as he connects the nine power, 

command and data umbilicals from Z1 to the forward face of the P6 that will provide 

power to the Orbital Replacement Units in anticipation of the deployment of the large 

solar arrays. Garneau, the back-up EVA crew member, then turns his full attention to 

acting as the on-board choreographer for the remainder of EVA 1 and all of EVA 2. 

As Noriega connects the umbilicals, Tanner sets to work releasing first the starboard 

and then the port Solar Array Blanket Boxes (SABB) by releasing a series of 5/8” bolts – 

two on the nadir and six on the zenith ends of each SABB. 

Noriega’s next task is to release the starboard Solar Array Wing (SAW) Beta Gimbal 

launch restraint (BGA) by releasing a pair of retention bolts and allowing the BGA to 

swing outward and upward or downward into its deployed position. Following the 

release of the starboard SAW BGA, Tanner will perform a similar function on the port 

side of the structure. 

Both Tanner and Noriega then begin deploying the SABBs by releasing a pip pin on the 

mast canister and then rotating the boxes 90 degrees from their launch position to their 

deployable position. Once in the deploy position, a locking arm holds each box in 

position. The space walkers then release three bolts that hold the mast tip fitting 

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releasing it from the top of the mast canister. At that point, Jett commands the mast to 

deploy, beginning the unfolding of the large solar arrays. 

Noriega’s final scheduled EVA task is to remove six “cinches” around the PV Radiator 

that hold it in its launch configuration by releasing two winch bar mechanisms and pip 

pins – one at each end of the radiator. 

Noriega and Tanner will then clean up the payload bay and head back in to 

Endeavour’s airlock concluding the first of two scheduled space walks. 

EVA 2

The second space walk, scheduled for Flight Day 6, is designed to reconfigure electrical 

connections so that power from the newly-installed P6 solar arrays can be distributed to 

the U.S. elements of the ISS. 

Noriega will work on the port side of the truss structure reconfiguring cables and moving 

them from one connector to the other to support the transfer of power and then 

removing a thermal shroud from a DC to DC Conversion Unit (DDCU). Tanner will 

remove a similar shroud from a baseband signal processor (BSP) and prepare to 

relocate the S-Band Antenna Subassembly (SASA) from its location on the Z1 truss 

where it was temporarily stowed by the STS-92 crew in October. 

The thermal shrouds are removed to allow the DDCU and BSP to dissipate heat as they 

begin operating off of power generated by the P6 arrays. 

One of the major elements of this second EVA is the relocation of the SASA as Tanner 

and Noriega move it from a temporary stowage location on the starboard side of the Z1 

truss to its new location on the top of the P6 array. Tanner will remove the power 

connections that provide maintenance power to the Z1 truss as he unbolts the SASA. 

Mike Bloomfield will maneuver the arm to Noriega’s location tethered to the Integrated 

Equipment Assembly (IEA) where, in a series of “leap frog” like exchanges, Tanner and 

Noriega will alternate possession of the SASA until the antenna assembly is installed in 

its operating position on the IEA. They will remove its thermal shroud and gimbal locks, 

readying the SASA for operation. 

Tanner will then descend from the truss assembly to connect thermal system umbilicals 

between the Z1 and P6 truss assemblies, while Noriega resumes work mating umbilical 

cables to the Z1 patch panel. 

The remaining EVA tasks are designed to pave the way for the arrival of the U.S. 

Laboratory Destiny early next year. Tanner will mount the robotic arm to mate a prerouted cable for the centerline berthing camera to the early communications system 

antenna to provide the STS-98/5A crew with camera views to aid them in attaching the 

large lab module. Tanner and Noriega then will remove umbilicals from Pressurized 

Mating Adapter–2 (PMA2) connecting them to a dummy panel located on that docking 

port preparing it for relocation to the aft end of the Destiny module during the STS98/5A mission. 

15
STS-97

Noriega will then release cinches on the aft radiator of the early thermal control system 

in much the same procedure he followed for the PV Radiator task, and then relocate 

foot restraints to assist the astronauts who will perform a space walk during the STS102/5A mission. At the same time, Tanner will begin connecting two electrical jumpers, 

called H-Jumpers, that will provide increased power capacity to the Zvezda and Zarya 

modules. 

Tanner and Noriega will gather up their tools and hardware before heading back into 

Endeavour’s airlock concluding the second scheduled space walk of the mission. 

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EVA Timeline for “A Pair of Space Walks Brings New Power to the Station” 

Time Event

2/15:55 EVA 1 Airlock Egress

2/16:00 EVA 1 Sortie Setup

2/16:30 EVA 1 Attach P6 to Z1 Truss

2/18:00 EVA 1 RMS Ungrapple P6

2/18:00 EVA 1 Release Starboard Solar Array Blanket Boxes (SABB) Restraints

2/18:00 EVA 1 Connect Z1 to P6 Power, Command and Data Umbilical Cables

2/19:00 EVA 1 Release Port Solar Array Blanket Boxes (SABB) Restraints

2/19:10 EVA 1 Release Starboard Solar Array Wing (SAW) Beta Gimbal Launch 

Restraint

2/19:55 EVA 1 Rotate Integrated Electronics Assembly Keel Pin

2/20:00 EVA 1 Release Port Solar Array Wing (SAW) Beta Gimbal Launch Restraint

2/20:15 EVA 1 Unstow Starboard Blanket Boxes

2/20:35 EVA 1 Release Photo Voltaic Radiator Cinch and Winch

2/20:45 EVA 1 Unstow Port Blanket Boxes

2/21:30 EVA 1 Sortie Cleanup

2/22:00 EVA 1 Airlock Ingress 

4/15:55 EVA 2 Airlock Egress

4/16:00 EVA 2 Sortie Setup

4/16:30 EVA 2 Remove AC Base Band Signal Processor Coldplate Thermal Shroud

4/16:30 EVA 2 Z1 Patch Panel Reconfiguration

4/16:40 EVA 2 Remove DC to DC Conversion Unit (DDCU) Coldplate Thermal Shroud

4/16:42 EVA 2 S-Band Antenna Subassembly (SASA) Relocation

4/17:50 EVA 2 Attach Z1 to P6 QD

4/17:50 EVA 2 Z1 Patch Panel Reconfiguration

4/18:00 EVA 2 Pressurized Mating Adapter-2 (PMA2) Relocation Preparations

4/18:30 EVA 2 Centerline Berthing Camera Cable Connection

4/20:00 EVA 2 Release EETCS Station Aft Radiator Cinches and Winches

4/20:15 EVA 2 Electrical Power System (EPS) Jumper Stow

4/20:40 EVA 2 5a Preparation Tasks - APFR Relocate and Deploy MBM Capture Latch

4/21:15 EVA 2 Sortie Cleanup

4:22:00 EVA 2 Airlock Ingress

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Payloads 

Payload Overview 

Prime:

Backup:

Overview

STS-97 will build on and enhance the capabilities of the International Space Station 

(ISS), delivering the first set of U.S.-provided solar arrays and batteries, called the P6 

photovoltaic module (PVM) and temporarily install the P6 Integrated truss structure 

(ITS) on the Z1 truss until it is relocated to its permanent location on the P5 truss during 

a later assembly mission. 

The P6 Integrated Truss Structure is the primary payload for the STS-97 mission and 

contains three discrete elements: the Photovoltaic Array Assembly (PVAA), the 

Integrated Equipment Assembly (IEA) and the Long Spacer (LS). 

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STS-97

The P6 Integrated Truss Structure

Electrical power is the most critical resource for the ISS because it allows astronauts to 

live comfortably, safely operate the station, and perform complex scientific experiments. 

Whether used to power the life support system, run a furnace that makes crystals, 

manage a computerized data network, or operate a centrifuge, electricity is essential. 

Since the only readily available source of energy for spacecraft is sunlight, technologies 

were developed to efficiently convert solar energy to electrical power. One way to do 

this is by using large numbers of solar cells assembled into arrays to produce high 

power levels. The cells are made from purified crystal ingots of silicon that directly 

convert light to electricity through a process called photovoltaics. 

Solar cells do the job, but a spacecraft orbiting the Earth is not always in direct sunlight 

so energy has to be stored. Storing power in rechargeable batteries provides a 

continuous source of electricity while the spacecraft is in the Earth's shadow. 

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Payloads 

Photovoltaic Array Assembly (PVAA): 

Prime:

Backup:

Overview

The STS-97 crew will bring the first of eight sets of solar arrays that – at the completion 

of Space Station construction in 2006 – will comprise the Station’s electrical power 

system, converting sunlight to electricity. 

The ISS derives its power from the conversion of solar energy into electrical power. The 

Photovoltaic Power Module – or “P6” – performs this energy conversion. 

The P6 has four primary functions: the conversion or generation, storage, regulation 

and distribution of electrical power for the ISS. 

The Solar Arrays Unfurl to their Full Length

The P6 has two identical PVAAs which themselves consist of two major elements: 

The Solar Array Assembly (SAA) containing two Solar Array Wings (SAW) connected to 

a mast which is folded into a Mast Canister before deployment. 

The Beta Gimbal Assembly (BGA) consists of: a) Mast Canister which houses the 

folded mast, b) “Bearing, Motor and Roll Ring module” (BMRRM) used to rotate the 

SAW and transfer power, c) Electronic Control Unit (ECU) used to control the BGA 

motor and mast rotation, and d) Sequential Shunt Unit (SSU) used to coarsely regulate 

the SAW output voltage. Power generated by the PVAA is routed via the SSU to the 

IEA. 

There are two solar array wings on the P6 module, each deployed in the opposite 

direction from each other. Each SAW is made up of two solar panels mounted to a 

common mast. Prior to deployment, each panel is folded into a Solar Array Blanket Box 

(SABB) measuring 20 inches high and 15 feet in length. 

The mast is housed in a Mast Canister Orbital Replacement Unit (ORU). The mast ORU 

is comprised of the following items: the canister, the Folding Articulated Square Truss 

(FAST), upper and lower pivot fittings, tip fitting, a Motor Drive Assembly (MDA), wire 

harness and beta gimbal platform assembly. 

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STS-97

When fully deployed, the SAW extends 115 feet and spans 38 feet across. Since the 

second SAW is deployed in the opposite direction the total wing span is over 240 feet. 

Each Solar Array Wing is the largest ever deployed in space, weighing over 2,400 

pounds and using nearly 33,000 solar arrays, each measuring 8-cm square with 4,100 

diodes. Each SAW is capable of generating nearly 31 Kilowatts (kW) of direct current 

power. There are two SAWs on the P6 module yielding a total power generation 

capability approaches 64 kW, enough power to meet the needs of 30 average homes – 

without air conditioning (based on an average 2kW of power.) 

BGA measures 8 x 8 x 2 feet and provides a structural link between the Integrated 

Electronics Assembly (IEA.) 

The BGA’s most visual functions are to deploy and retract the SAW and rotate it about 

its longitudinal axis. The BGA consist of three major components: the Bearing, Motor 

and Roll Ring Module (BMRRM), the Electronic Control Unit (ECU) and the Sequential 

Shunt Unit (SSU). 

The motor used to rotate, deploy and retract the solar arrays is a three-phase, 200W 

DC stepper motor. The system has a rotational pointing accuracy of +/- 1 degree and a 

maximum rotational rate of +/- 200 degrees per minute. Rotational rate is obtained by 

pulse width modulation of the input DC power. The motor has a maximum operating 

torque of 380 in-lb. and a maximum stationary torque of 1,700 in-lb. 

The Roll Rings allow the transfer of power from the rotating (Mast Canister) side of the 

BGA to the stationary (IEA) side of the BGA. These rings can transfer up to 35kW. 

The ECU controls the motor that rotates,deploys and retracts the SAW. The ECU 

operates off of 120 VDc and receives its power from the DDCU located within the IEA. 

Commanding of the ECU is from a computer also located within the IEA. The ECU 

measures 23 x 12 x 14 inches. 

The SSU is designed to coarsely regulate the solar power collected during periods of 

insolation – when the arrays collect power during sun-pointing periods . A sequence of 

82 separate strings, or power lines, leads from the solar array to the SSU. Shunting, or 

controlling, the output of each string regulates the amount of power transferred. The 

regulated voltage setpoint is controlled by a computer located on the IEA and is 

normally set to around 140 volts. The SSU has an overvoltage protection feature to 

maintain the output voltage below 200 V DC maximum for all operating conditions. This 

power is then passed through the BMRRM to the DCSU located in the IEA. The SSU 

measures 32” by 20” by 12” and weighs 185 pounds.

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Payloads 

Integrated Equipment Assembly 

Payload Bay 

17,000 lbs. 

Prime:

Backup:

Overview

The Integrated Equipment Assembly measures 16 x 16 x 16 feet, weighs nearly 17,000 

pounds and is designed to condition and store the electrical power collected by the 

photovoltaic arrays for use on board the Station. 

The IEA integrates the energy storage subsystem, the electrical equipment, the thermal 

control system, structural framework and the Solar Array Rotary Joint (SARJ). The IEA 

consist of three major elements: 

1. The power system electronics consisting of the Direct Current Switching Unit 

(DCSU) used for primary power distribution; the Direct Current to Direct Current 

Control Unit (DDCU) used to produce regulated secondary power; the Battery 

Charge/Discharge Unit (BCDU) used to control the charging and discharging of 

the storage batteries; and the batteries used to store power. 

2. The Photovoltaic Thermal Control System consisting of: the coldplate 

subassembly used to transfer heat from an electronic box to the coolant; the 

Pump Flow Control System (PFCS) used to pump and control the ammonia 

coolant; and the Photovoltaic Radiator (PVR) used to dissipate the heat into deep 

space. 

3. The computers used to control the P6 module. 

The IEA power system is divided into two independent and nearly identical channels. Each 

channel is capable of control (fine regulation), storage and distribution of power to the ISS. 

The PVAA is attached to one end of the IEA and the LS to the other. 

Power received from each PVAA is fed directly into the appropriate Direct Current 

Switching Unit (DCSU). The DCSU is a high-power, multi-path remotely controlled unit that 

is used for primary and secondary power distribution, protection and fault isolation within 

the IEA. It also distributes primary power to the ISS. During periods of insolation, the DCSU 

routes primary power directly to the ISS from its PVAA and also routes power to the power 

storage system for battery charging. During periods of eclipse the DCSU routes power from 

the power storage system to the ISS. The DCSU measures 28” by 40” by 12” and weighs 

235 pounds. 

22
STS-97

Primary power from the DCSU is also distributed to the Direct Current to Direct Current 

Converter Unit (DDCU). The DDCU is a power processing system that conditions the 

coarsely regulated power from the PVAA to 123 +/- 2 VDC. It has a maximum power output 

of 6.25 kW. This power is used for all P6 operations employing secondary power. 

Primary power from the DCSU is also distributed to the three power storage systems 

located within each channel of the IEA. The power storage system consists of a Battery 

Charge/Discharge Unit (BCDU) and two battery assemblies. 

The BCDU serves a dual function of charging the batteries during solar collection periods, 

and providing conditioned battery power to the primary power busses (via the DCSU) 

during eclipse periods. The BCDU has a battery charging capability of 8.4 kW and a 

discharge capability of 6.6 kW. The BCDU also includes provisions for battery status 

monitoring and protection from power circuit faults. Commanding of the BCDU is from the 

IEA computer. 

Each battery assembly consist of 38 lightweight Nickel Hydrogen cells and associated 

electrical and mechanical equipment. Two battery assemblies connected in series are 

capable of storing a total of 8 kW of electrical power. This power is fed to the ISS via the 

BCDU and DCSU respectively. The batteries have a design life of 6.5 years and can 

exceed 38,000 charge/discharge cycles at 35% depth of discharge. Each battery measures 

40” by 36” by 18” and weighs 375 pounds. 

In order to maintain the IEA electronics at safe operating temperatures in the harsh space 

environments, they are conditioned by the Photovoltaic Thermal Control System (PVTCS). 

The PVTCS consist of ammonia coolant, eight coldplates, two Pump Flow Control Systems 

(PFCS) and one Photovoltaic Radiator (PVR). 

The coldplate subassemblies are an integral part of IEA structural framework. Heat is 

transferred from the IEA orbital replacement unit (ORU) electronic boxes to the coldplates 

via fine interweaving fins located on both the coldplate and the electronic boxes. The fins 

add lateral structural stiffness to the coldplates in addition to increasing the available heat 

transfer area. 

The PFCS is the heart of the thermal system. It consists of all the pumping capacity, valves 

and controls required to pump the heat transfer fluid to the heat exchanges and radiator, 

and regulate the temperature of the thermal control system ammonia coolant. The PVTCS 

is designed to dissipate 6,000 Watts of heat per orbit on average and is commanded by the 

IEA computer. 

Each PFCS consumes 275 Watts during normal operations and measures approximately 

40 x 29 x 19 inches, weighing 235 pounds. 

The PVR – the radiator – is deployable on orbit and comprised of two separate flow paths 

through seven panels. Each flow path is independent and is connected to one of the two 

PFCSs on the IEA. In total, the PVR can reject up to 14 kW of heat into deep space. 

The PVR weighs 1,600 pounds and when deployed measures 4 x 12 x 7 inches. 

23
STS-97

Payloads 

The Long Spacer 

Payload Bay 

245 lbs. 

Prime:

Backup:

Overview

The P6 Long Spacer measures 28 x 16 x 16 feet and performs two basic functions: to 

physically separate the P6 solar arrays from the P4 solar arrays when the P6 is relocated 

on a later assembly mission; and to provide temporary cooling for the U.S. Laboratory 

“Destiny” when it arrives on STS-102/5A early next year. Ultimately, Destiny will be 

cooled by the main Heat Rejection System (HRS) when it is activated on a later assembly 

flight. 

The long spacer thermal system is called the Early External Active Thermal Control 

System (EEATCS) and is similar to the IEA’s PVTCS with a few exceptions. The 

EEATCS employs two separate cooling system loops and has two high-power PFCSs 

each feeding into its own PVR. It also has external ammonia accumulators used for 

pressure control and heaters to preclude freezing. 

The PFCS’s flow control valve regulates the ammonia flow through the PVR in response 

to the Laboratory heat exchanger temperature. The EEATCS is designed to reject 14,000 

Watts of heat per orbit and is commanded by the PFCS is under the control of the IEA 

computer. Each PFCS consumes 350 Watts during normal operations and the heaters 

consume 115 Watts. It measures 40 x 29 x 19 inches, and weighs 245 pounds. 

24
STS-97

Experiments 

JASON On Board Seed Experiments 

Prime:

Backup:

Overview

Seed Morphology Experiment

This student experiment will be transferred to the ISS during docked operations 

between Endeavour and the ISS. The study supports the education objectives of the 

JASON Project. 

The experiment utilizes digital photography as a means of documenting the growth of 

germinating soybean and corn seeds under extreme conditions (spaceflight and, 

elsewhere under water). The spaceflight images obtained are downlinked and posted to 

a web site for dissemination to students for their evaluation. Parallel classroom 

investigations are conducted by the students. 

Eight seed pouches will be flown and germinated either under dark or lighted conditions. 

Each seed pouch contains a grid along its side to provide a scale for data extraction. 

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STS-97

Seed Metabolite Experiment 

This study explores potential new roles of flavonoids and isoflavonoids in the processes 

associated with adaptation of plants in general (and soybeans in particular) to 

microgravity. These compounds have been proposed to play many diverse roles in plants, 

including protection against insects, pathogens and UV light damage. This class of 

compounds may play a significant role in plant adaptation to the microgravity 

environment. The experiment consists of wetting three soybean seed pouches each day, 

starting at 7 days prior to scheduled landing (R-7) and continuing until R-1. Temperature 

and light intensity recorders will be used to document environmental conditions in the 

vicinity of the seed pouches. 

After landing, the plants will be frozen to stabilize them for analysis. A delayed ground 

control experiment will be scheduled post-flight utilizing the KSC Orbiter Environmental 

Simulator Chamber. 

26
STS-97

DTO/DSO/RMEs 

Structural Dynamics Model Validation 

DTO 257 

Prime:

Backup:

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. 

27
STS-97

DTO/DSO/RMEs 

International Space Station On-Orbit Loads Validation 

DTO 261 

Prime:

Backup:

Overview

This DTO will use the Shuttle’s aft primary RCS 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. 

28
STS-97

DTO/DSO/RMEs 

Single-String Global Positioning System 

DTO 700-14 

Prime:

Backup:

Overview

The purpose of this DTO is to demonstrate the performance and operation of the Global 

Positioning System (GPS) during ascent, orbital, and entry phases of the flight. It uses a 

modified military GPS receiver/processor and the existing orbiter GPS antennas, and 

records data on a payload and general support computer (PGSC) hard drive. 

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STS-97

DTO/DSO/RMEs 

Crew Return Vehicle (CRV) Space Integrated Global 

Positioning System/Inertial Navigation System (SIGI) 

DTO 700-22 

Prime:

Backup:

Overview

This is the first flight of DTO 700-22, which will measure both GPS only and GPS/INS 

blended position, velocity, time, and attitude performance during on-orbit and entry 

operations and will also measure the time to first GPS fix (position, velocity, time) during 

on-orbit operations after warm or cold starts of the SIGI. 

30
STS-97

DTO/DSO/RMEs 

Crosswind Landing Performance 

DTO 805 

Prime:

Backup:

Overview

This DTO will continue to gather data to demonstrate the capability to perform a manually 

controlled landing with a 90-degree, 10- to 15-knot steady crosswind. This DTO can be 

performed regardless of landing site or vehicle mass properties. During a crosswind 

landing, the drag chute will be deployed after nose gear touchdown when the vehicle is 

stable and tracking the runway centerline. 

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STS-97

DTO/DSO/RMEs 

Micro-Wireless Instrumentation System (Micro-WIS) 

(Objective 3 Only)

DTO HTD 1403 

Prime:

Backup:

Overview

Human Exploration and Development of Space (HEDS) Technology Demonstration 

(HTDs) 

This HTD will demonstrate the operational utility and functionality of Micro-WIS on orbit, 

initially in the crew cabin of the orbiter and then in the ISS. The Micro-WIS 

sensor/transmitter will provide important real-time temperature measurements. 

32
STS-97

DTO/DSO/RMEs 

Laser Dynamic Range Imager (LDRI) 

DTO HTD 1404 

Prime:

Backup:

Overview

Human Exploration and Development of Space (HEDS) Technology Demonstration 

(HTD) 

The purpose of this HTD is to demonstrate the LDRI as an instrument for obtaining static 

and dynamic range imagery and measurements of space structures for use in validating 

structural models and for determining position and orientation in real time. 

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STS-97

DTO/DSO/RMEs 

Educational Activities 

DSO 802 

Prime:

Backup:

Overview

This DSO will provide live television of the mission to classrooms in hopes of attracting 

students to careers in science, engineering, and mathematics. The addition of this DSO to 

a particular flight is coordinated through the JSC Educational Working Group (EWG). The 

tasks required by this DSO have three objectives: 

1. Produce educational products, such as 20-minute video lessons, with scenes recorded 

both in space and on the ground. The video from space should be about one-third of 

the finished video product. This objective requires the videotaping of educational 

activities performed by astronauts in space, and other educational activities deemed 

appropriate by the EWG and the flight crew. 

2. Support the live television of educational activities performed by astronauts for, or 

involving participation by, students and teachers. Typically, these downlinks are limited 

to one or two 30-minute live sessions. 

3. Explain the live or videotaped television of educational activities by astronauts to a 

general audience. Typically, these activities are limited to 5 or 10 minutes per 

demonstration/narration to explain the science and/or principles of the experiments 

performed by the astronauts. 

This educational DSO supports the NASA Administrator's educational initiative and 

complies with his direction to use live and recorded lessons from astronauts on Space 

Shuttle missions in NASA's educational programs. 

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STS-97

Mission Benefits 

Why build the International Space Station? 

When studying sound, you go into a quiet room. When studying light, you go into a dark 

room. When studying the effects of gravity, you’d like to go into an “anti-gravity” room. 

Since there’s no such thing on Earth, we have the International Space Station. 

By flying around the Earth at about 17,500 mph, the station and everything in it remain 

in orbit, a continuous free fall around the planet. In orbit, forces are balanced and the 

effects of gravity are essentially removed. The result is microgravity, one of the unique 

aspects of the ISS environment that holds the hope of new discovery. The ISS thus 

allows long-term exposure to a world nearly unexplored. 

Gravity affects everything. From our bodies, to the materials we use to build cars and 

buildings, to the flames we use to heat our homes, our world is controlled by gravity. 

For as long as we have curiously investigated our surroundings, we have been limited, 

until recently, to accepting gravity as a given in all our studies. History shows that 

changing what once were constants can lead to revolutionary discoveries. 

The 19th Century saw temperature and pressure controlled in new ways to harness 

steam power and revolutionize the way we live. The 21st Century offers the hope of 

controlling gravity’s effects to understand why things behave the way they do. 

Observing and understanding this behavior is key to new discoveries in many scientific 

disciplines and using that knowledge is key to the betterment of life on Earth. 

The Space Station Mir gave us a platform for long-term microgravity research, and 

important knowledge about how to live and work in space. Like all research, we must 

proceed one step at a time. As we open one door, answering one question, we are 

faced with the opportunity of more doors, more questions. 

The ISS is the next step in that journey of discovery, and represents a quantum leap in 

our capability to conduct research on orbit. In space, electrical power is key to the 

quantity and quality of research. When complete, the ISS’s enormous solar arrays will 

supply 60 times more power for science than did Mir. This, coupled with the large space 

available for experiments, will provide scientists with unprecedented access to this 

unique environment. 

Aboard the ISS, and through interaction from the ground, scientists will explore basic 

questions in the fields of biotechnology, biomedical research and countermeasures, 

fluid physics, fundamental biology, materials science, combustion science, fundamental 

physics, Earth science and space science. Space-based research will be supported by 

research on the ground, with selection of only those experiments requiring the 

microgravity environment selected for flight on the ISS. 

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STS-97

In addition to serving as a research laboratory, the ISS will sustain and strengthen U.S. 

leadership in other areas. It will provide opportunity to enhance U.S. economic 

competitiveness and create new commercial enterprises. Companies can use ISS 

research to build profit-based businesses. 

The ISS will maintain the U.S. leadership in space exploration that has inspired a 

generation of Americans and people throughout the world. Tied in with other NASA 

assets, the ISS will serve as a virtual classroom in space to the benefit of educators and 

students alike. Live educational events and programs like EarthKAM ( with students 

operating a camera on the ISS beginning next fall to investigate changes on Earth, will 

motivate students to understand their world. 

Education and inspiration will couple to maintain U.S. economic leadership by raising a 

new generation of science, math, and technology savvy children that will invent 21st

century products and services. Finally, the ISS will serves as a testbed and springboard 

for further exploration of space. We will learn how the human body responds to the 

long-term exposure to space, and how to best prepare for the next major human steps 

into the solar system. 

Research on the International Space Station 

Early Research Disciplines: 

Biomedical Research and Countermeasures: Researchers seek to understand and 

control the effects of the space environment on space travelers (e.g. muscle atrophy, 

bone loss, fluid shifts, etc.). 

• Long term Benefits: enhance the safety of space travel; develop methods to keep 

humans healthy in low-gravity environments; advance new fields of research in the 

treatment of diseases. 

Fundamental Biology: Scientists study gravity’s influence on the evolution, 

development, growth, and internal processes of plants and animals. Their results 

expand fundamental knowledge that will benefit medical, agricultural, and other 

industries. 

• Long term Benefits: advance understanding of cell, tissue, and animal behavior; 

use of plants as sources of food and oxygen for exploration; improved plants for 

agricultural and forestry. 

Biotechnology: Microgravity allows researchers to grow three-dimensional tissues that 

have characteristics more similar to tissues in the body than has ever been previously 

available and to produce superior protein crystals for drug development. 

• Long term Benefits: culture realistic tissue for use in research (cancerous tumors, 

organ pieces); provide information to design a new class of drugs to target specific 

proteins and cure specific diseases. 

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STS-97

Fluid Physics: The behavior of fluids is profoundly influenced by gravity. Researchers 

use gravity as an experimental variable to explain and model fluid behavior in systems 

on Earth and in space. 

• Long term Benefits: improved spacecraft systems designs for safety and 

efficiency; better understanding of soil behavior in Earthquake conditions; improved 

mathematical models for designing fluid handling systems for, powerplants, 

refineries and innumerable other industrial applications. 

Additional Research Disciplines (later in the life of ISS): 

Advanced Human Support Technology: Researchers develop technologies, systems, 

and procedures to enable safe and efficient human exploration and development of space. 

• Long term Benefits: reduce the cost of space travel while enhancing safety; 

develop small, low power monitoring and sensing technologies with applications in 

environmental monitoring in space and on Earth; develop advanced waste 

processing and agricultural technologies with applications in space and on Earth. 

Materials Science: Researchers use low gravity to advance our understanding of the 

relationships among the structure, processing and properties of materials. In low gravity, 

differences in weight of liquids used to form materials do not interfere with the ability to mix 

these materials opening the door to a whole new world of composite materials. 

• Long term Benefits: advance understanding of processes for manufacturing 

semiconductors, metals, ceramics, polymers, and other materials; determine 

fundamental physical properties of molten metal, semiconductors, and other 

materials with precision impossible on Earth. 

Combustion Science: The removal of gravity allows scientists to simplify the study of 

complex combustion (burning) processes. Since combustion is used to produce 85 

percent of Earth’s energy, even small improvements in efficiency and reduction of soot 

production (a major source of pollution on earth) will have large environmental and 

economic benefits. 

• Long term Benefits: enhance efficiency of combustion processes; enhance fire 

detection and safety on Earth and in Space; improve control of combustion 

emissions and pollutants. 

Fundamental Physics: Scientists use the low gravity and low temperature 

environment to slow down reactions allowing them to test fundamental theories of 

physics with degrees of accuracy that far exceed the capacity of Earthbound science. 

• Long term Benefits: challenge and expand theories of how matter organizes as it 

changes state (important in understanding superconductivity); test fundamental 

theories in physics with precision beyond the capacity of Earth-bound science; 

potential for improved magnetic materials. 

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Earth Science and Space Science: Space Station will be a unique platform with 

multiple exterior attach points from which to observe the Earth and the Universe. 

• Long term Benefits: Space Scientists will use the location above the atmosphere 

to collect and search for cosmic rays, cosmic dust, antimatter and “dark” matter. 

Earth Scientists can obtain global profiles of aerosols, ozone, water vapor, and 

oxides in order to determine their role in climatological processes and take 

advantage of the longevity of ISS to observe global changes over many years. 

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Shuttle Reference Data 

Shuttle Abort Modes 

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). 

ABORT TO ORBIT (ATO)

The ATO mode is designed to allow the vehicle to achieve a temporary orbit that is 

lower than the nominal orbit. This mode requires less performance and allows time to 

evaluate problems and then choose either an early deorbit maneuver or an orbital 

maneuvering system thrusting maneuver to raise the orbit and continue the mission. 

ABORT ONCE AROUND (AOA)

The AOA is designed to allow the vehicle to fly once around the Earth and make a 

normal entry and landing. This mode generally involves two orbital maneuvering system 

thrusting sequences, with the second sequence being a deorbit maneuver. The entry 

sequence would be similar to a normal entry. 

TRANSOCEANIC ABORT LANDING (TAL)

The TAL mode is designed to permit an intact landing on the other side of the Atlantic 

Ocean. This mode results in a ballistic trajectory, which does not require an orbital 

maneuvering system maneuver. 

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RETURN TO LAUNCH SITE (RTLS)

The RTLS mode involves flying downrange to dissipate propellant and then turning 

around under power to return directly to a landing at or near the launch site. 

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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RETURN TO LAUNCH SITE OVERVIEW

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 threeengine 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). 

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 pitch-down 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. 

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TRANSATLANTIC LANDING ABORT OVERVIEW

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 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 OVERVIEW

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. 

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ABORT ONCE AROUND OVERVIEW 

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 ABORT OVERVIEW

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 in-flight crew escape system would be used before ditching the orbiter.

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Space Shuttle External Tank

The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and 

supplies them under pressure to the three space shuttle main engines in the orbiter 

during lift-off and ascent. When the SSMEs are shut down, the ET is jettisoned, enters 

the Earth's atmosphere, breaks up, and impacts in a remote ocean area. It is not 

recovered. 

The largest and heaviest (when loaded) element of the space shuttle, the ET has three 

major components: the forward liquid oxygen tank, an unpressurized intertank that 

contains most of the electrical components, and the aft liquid hydrogen tank. The ET is 

153.8 feet long and has a diameter of 27.6 feet. 

The ET is attached to the orbiter at one forward attachment point and two aft points. In 

the aft attachment area, there are also umbilicals that carry fluids, gases, electrical 

signals and electrical power between the tank and the orbiter. Electrical signals and 

controls between the orbiter and the two solid rocket boosters also are routed through 

those umbilicals. 

Liquid Oxygen Tank 

The liquid oxygen tank is an aluminum monocoque structure composed of a fusionwelded assembly of preformed, chem-milled gores, panels, machined fittings and ring 

chords. It operates in a pressure range of 20 to 22 psig. The tank contains anti-slosh 

and anti-vortex provisions to minimize liquid residuals and damp fluid motion. The tank 

feeds into a 17-inch-diameter feed line that conveys the liquid oxygen through the 

intertank, then outside the ET to the aft right-hand ET/orbiter disconnect umbilical. The 

17-inch-diameter feed line permits liquid oxygen to flow at approximately 2,787 pounds 

per second with the SSMEs operating at 104 percent or permits a maximum flow of 

17,592 gallons per minute. The liquid oxygen tank's double-wedge nose cone reduces 

drag and heating, contains the vehicle's ascent air data system (for nine tanks only) and 

serves as a lightning rod. The liquid oxygen tank's volume is 19,563 cubic feet. It is 331 

inches in diameter, 592 inches long and weighs 12,000 pounds empty. 

Intertank

The intertank is a steel/aluminum semimonocoque cylindrical structure with flanges on 

each end for joining the liquid oxygen and liquid hydrogen tanks. The intertank houses 

ET instrumentation components and provides an umbilical plate that interfaces with the 

ground facility arm for purge gas supply, hazardous gas detection and hydrogen gas 

boiloff during ground operations. It consists of mechanically joined skin, stringers and 

machined panels of aluminum alloy. The intertank is vented during flight. The intertank 

contains the forward SRB/ET attach thrust beam and fittings that distribute the SRB 

loads to the liquid oxygen and liquid hydrogen tanks. The intertank is 270 inches long, 

331 inches in diameter and weighs 12,100 pounds. 

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Liquid Hydrogen Tank

The liquid hydrogen tank is an aluminum semimonocoque structure of fusion-welded 

barrel sections, five major ring frames, and forward and aft ellipsoidal domes. Its 

operating pressure range is 32 to 34 psia. The tank contains an anti-vortex baffle and 

siphon outlet to transmit the liquid hydrogen from the tank through a 17-inch line to the 

left aft umbilical. The liquid hydrogen feed line flow rate is 465 pounds per second with 

the SSMEs at 104 percent or a maximum flow of 47,365 gallons per minute. At the 

forward end of the liquid hydrogen tank is the ET/orbiter forward attachment pod strut, 

and at its aft end are the two ET/orbiter aft attachment ball fittings as well as the aft 

SRB/ET stabilizing strut attachments. The liquid hydrogen tank is 331 inches in 

diameter, 1,160 inches long, and has a volume of 53,518 cubic feet and a dry weight of 

29,000 pounds. 

ET Thermal Protection System

The ET thermal protection system consists of sprayed-on foam insulation and 

premolded ablator materials. The system also includes the use of phenolic thermal 

insulators to preclude air liquefaction. Thermal isolators are required for liquid hydrogen 

tank attachments to preclude the liquefaction of air-exposed metallic attachments and 

to reduce heat flow into the liquid hydrogen. 

ET Hardware

Each propellant tank has a vent and relief valve at its forward end. This dual-function 

valve can be opened by ground support equipment for the vent function during 

prelaunch and can open during flight when the ullage (empty space) pressure of the 

liquid hydrogen tank reaches 38 psig or the ullage pressure of the liquid oxygen tank 

reaches 25 psig. 

The liquid oxygen tank contains a separate, pyrotechnically operated, propulsive tumble 

vent valve at its forward end. At separation, the liquid oxygen tumble vent valve is 

opened, providing impulse to assist in the separation maneuver and more positive 

control of the entry aerodynamics of the ET. 

There are eight propellant-depletion sensors, four each for fuel and oxidizer. The fueldepletion sensors are located in the bottom of the fuel tank. The oxidizer sensors are 

mounted in the orbiter liquid oxygen feed line manifold downstream of the feed line 

disconnect. During SSME thrusting, the orbiter general-purpose computers constantly 

compute the instantaneous mass of the vehicle due to the usage of the propellants. 

Normally, main engine cutoff is based on a predetermined velocity; however, if any two 

of the fuel or oxidizer sensors sense a dry condition, the engines will be shut down. 

The locations of the liquid oxygen sensors allow the maximum amount of oxidizer to be 

consumed in the engines, while allowing sufficient time to shut down the engines before 

the oxidizer pumps cavitate (run dry). In addition, 1,100 pounds of liquid hydrogen are 

loaded over and above that required by the 6:1 oxidizer/fuel engine mixture ratio. This 

assures that MECO from the depletion sensors is fuel-rich; oxidizer-rich engine 

shutdowns can cause burning and severe erosion of engine components. 

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STS-97

Four pressure transducers located at the top of the liquid oxygen and liquid hydrogen 

tanks monitor the ullage pressures. 

Each of the two aft external tank umbilical plates mate with a corresponding plate on 

the orbiter. The plates help maintain alignment among the umbilicals. Physical strength 

at the umbilical plates is provided by bolting corresponding umbilical plates together. 

When the orbiter GPCs command external tank separation, the bolts are severed by 

pyrotechnic devices. 

The ET has five propellant umbilical valves that interface with orbiter umbilicals: two for 

the liquid oxygen tank and three for the liquid hydrogen tank. One of the liquid oxygen 

tank umbilical valves is for liquid oxygen, the other for gaseous oxygen. The liquid 

hydrogen tank umbilical has two valves for liquid and one for gas. The intermediatediameter liquid hydrogen umbilical is a recirculation umbilical used only during the liquid 

hydrogen chill-down sequence during prelaunch. 

The ET also has two electrical umbilicals that carry electrical power from the orbiter to 

the tank and the two SRBs and provide information from the SRBs and ET to the 

orbiter. 

A swing-arm-mounted cap to the fixed service structure covers the oxygen tank vent on 

top of the ET during the countdown and is retracted about two minutes before lift-off. 

The cap siphons off oxygen vapor that threatens to form large ice on the ET, thus 

protecting the orbiter's thermal protection system during launch. 

ET Range Safety System

A range safety system provides for dispersing tank propellants if necessary. It includes 

a battery power source, a receiver/decoder, antennas and ordnance. 

Various parameters are monitored and displayed on the flight deck display and control 

panel and are transmitted to the ground. 

The contractor for the external tank is Martin Marietta Aero space, New Orleans, La. 

The tank is manufactured at Michoud, La. Motorola, Inc., Scottsdale, Ariz., is the 

contractor for range safety receivers. 

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STS-97

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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STS-97

Space Shuttle Solid Rocket Boosters

The two SRBs provide the main thrust to lift the space shuttle off the pad and up to an 

altitude of about 150,000 feet, or 24 nautical miles (28 statute miles). In addition, the 

two SRBs carry the entire weight of the external tank and orbiter and transmit the weight 

load through their structure to the mobile launcher platform. 

Each booster has a thrust (sea level) of approximately 3,300,000 pounds at launch. 

They are ignited after the three space shuttle main engines'' thrust level is verified. The 

two SRBs provide 71.4 percent of the thrust at lift- off and during first-stage ascent. 

Seventy- five seconds after SRB separation, SRB apogee occurs at an altitude of 

approximately 220,000 feet, or 35 nautical miles (41 statute miles). SRB impact occurs 

in the ocean approximately 122 nautical miles (141 statute miles) downrange. 

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

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

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

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

SRB is approximately 192,000 pounds. 

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

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

avionics, pyrotechnics, deceleration system, thrust vector control system and range 

safety destruct system. 

Each booster is attached to the external tank at the SRB''s aft frame by two lateral sway 

braces and a diagonal attachment. The forward end of each SRB is attached to the 

external tank at the forward end of the SRB''s forward skirt. On the launch pad, each 

booster also is attached to the mobile launcher platform at the aft skirt by four bolts and 

nuts that are severed by small explosives at lift-off. 

During the downtime following the Challenger accident, detailed structural analyses 

were performed on critical structural elements of the SRB. Analyses were primarily 

focused in areas where anomalies had been noted during postflight inspection of 

recovered hardware. 

One of the areas was the attach ring where the SRBs are connected to the external 

tank. Areas of distress were noted in some of the fasteners where the ring attaches to 

the SRB motor case. This situation was attributed to the high loads encountered during 

water impact. To correct the situation and ensure higher strength margins during 

ascent, the attach ring was redesigned to encircle the motor case completely (360 

degrees). Previously, the attach ring formed a C and encircled the motor case 270 

degrees. 

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STS-97

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 heavyduty 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. 

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STS-97

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. 

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. 

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STS-97

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. 

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 signalsarm, 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). 

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STS-97

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. 

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. 

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STS-97

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. 

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. 

53
STS-97

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. 

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. 

54
STS-97

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.

55
STS-97

Space Shuttle Super Light Weight Tank (SLWT)

The super lightweight external tank (SLWT) made its first Shuttle flight June 2, 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. 

56
STS-97

Acronyms and Abbreviations 

A/D Analog to Digital 

ACBM Active Common Berthing Mechanism 

ACBSP Assembly Contingency Baseboard Signal Processor 

ACLS Advanced Cardiac Life Support 

ACS Attitude Control System 

AD Active Device 

AFD Aft Flight Deck 

AGIT Antenna Group Immediate Frequency Tube 

Ah Ampere Hour 

ALSP Advance Life Support Pack 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Assembly System 

APCU Assembly Power Converter Unit 

APDS Androgynous Peripheral Docking System 

APFR Articulating Portable Foot Restraint 

APM Ambulatory Medical Pack 

 Attached Pressurized Module 

AR Atmosphere Revitalization 

ARCU American-to-Russian Converter Unit 

ASCR Assured Safe Crew Return 

ATV Automated Transfer Vehicle 

AUIAU ASC/UHF Audio Interface Unit 

BC Bus Controller 

BCDU Battery Charge/Discharge Unit 

BDT Binary Data Transfer 

BGA Beta Gimbal Assembly 

BGDTS Beta Gimbal Deployment/Transition Set 

BGHS Beta Gimbal Housing Subassembly 

BG/PVAA Beta Gimbal/Photovoltaic Array Assembly 

BIA Bus Interface Adapter 

BIT Built-In Test 

BITE Built-In Test Equipment 

BIU Bus Interface Unit 

BMR Body-Mounted Radiator 

BMRRM Bearing, Motor, and Roll Ring Module 

BOL Beginning of Life 

BRS Blanket Restraint System 

BSCCM Battery Signal Conditioning and Control Module 

BSP Baseband Signal Processor 

BTLS Basic Trauma Life Support 

C&C Command and Control 

C&DH Command and Data Handling 

C&T Communications and Tracking 

57
STS-97

C&W Caution and Warning 

CADU Channel Access Data Unit 

CB Command Bus 

CBCS Centerline Berthing Camera System 

CBM Common Berthing Mechanism 

CC Central Computer 

CCPK Crew Contamination Protection Kit 

CCSDS Consultative Committee for Space Data Systems 

CCTV Closed-Circuit Television 

CDR Critical Design Review 

CDRA Carbon Dioxide Removal Assembly 

CETA Crew and Equipment Translation Aid 

CHeCS Crew Health Care System 

CHIA Cargo Handling Interface Adapter 

CIL Critical Items List 

CMG Control Moment Gyro 

CMO Crew Medical Officer 

COTS Commercial Off-the-Shelf 

CPDS Crew Passive Dosimeter 

CPP Connector Patch Panel 

CRT Cathode-Ray Tube 

CSA-CP Compound Specific Analyzer-Combustion Product 

CSCI Computer Software Configuration Item 

CT 2 Communication and Tracking 2 

CTP Command and Telemetry Processor 

CTV Crew Transfer Vehicle 

CWC Contingency Waste Collection 

DC Docking Compartment 

DDCU DC to DC Converter Unit 

 Direct Current-to-Direct Current Converter Unit 

DDCUE DC to DC Converter Unit External 

DDCU-HP DDCU with Heat Pipe Radiators 

DDCUI DC to DC Converter Unit Internal 

DCSU Direct Current Switching Unit 

DIA Diagnostic 

DIO Discrete Input/Output 

DMCU Docking Mechanism Control Unit 

DMS Data Management System 

DSCU Docking System Control Unit 

DTO Detailed Test Objective 

Early Comm Early Communications System 

EATC External Active Thermal Control 

EATCS External Active Thermal Control System 

ECLSS Environmental Control and Life Support System/Subsystem 

ECOMM Early Communications System 

58
STS-97

ECU Electronic Control/Coupling Unit 

 Electronic Control Unit 

EDAC Error Detection and Correction 

EDP Electronic Document Project 

EE End Effector 

EEATCS Early External Active Thermal Control System/Subsystem 

EEPROM Electronically Erasable Programmable Read-Only Memory 

EETCS Early External Thermal Control System 

EMI Electromagnetic Interference 

EMI/EMC Electromagnetic Interference/Electromagnetic Compatibility 

EMU Extravehicular Mobility Unit 

EOL End of Life 

EPCS Early Portable Computer System 

EPS Electrical Power System/Subsystem 

ERSU External RSU 

ESA European Space Agency 

ESSMDM Enhanced Space Station MDM 

ESSU Energy Storage Subsystem Upgrade 

ETCS External Thermal Control System 

ETE End-to-End 

ETI Elapsed Time Indicator 

ETSD External Tool Stowage Device 

EV Extravehicular 

EVA Extravehicular Activity 

EVAS EVA System 

FAST Folding Articulated Square Truss 

FCC Flat Collector Circuit 

FCV Flow Control Valve 

FD Flight Day 

FDF Flight Data File 

FDIR Fault Detection, Isolation, and Recovery 

FDS Fire Detection and Suppression 

FGB Functional Cargo Block 

FQDC Fluid Quick Disconnect Coupling 

FRGF Flight Releasable Grapple Fixture 

FRR Flight Readiness Review 

FS File Server 

FSE Flight Support Equipment 

GFE Government-Furnished Equipment 

GLONASS Global Navigational Satellite System 

GNC Guidance, Navigation, and Control 

GPC General Purpose Computer 

GSE Ground Support Equipment 

GSFC Goddard Space Flight Center 

59
STS-97

H&S Health and Safety 

H/W Hardware 

HCA Hollow Cathode Assembly 

HDL High-Rate Data Link 

HEDS Human Exploration and Development of Space 

HEI Hernandez Engineering, Inc. 

HGA High Gain Antenna 

HP Heat Pipe 

HPR Heat Pipe Radiator 

HRD High Rate Data 

 High Rate Dosimeter 

HRM Heart Rate Monitor 

 High-Rate Mode 

HRW Heart Rate Watch 

HTD Human Exploration and Development of Space Technology 

Demonstration 

I/F Interface 

 Intermediate Frequency 

I/O Input/Output 

IACO Installation, Assembly, and Checkout 

IAPFR 

IATC Internal Active Thermal Control 

ICC Instrumentation Cargo Compartment 

ICD Interface Control Document 

ID Inside Diameter 

IDA Initialization Diode Assembly 

IEA Integrated Electronics Assembly 

IEE Integrated Equipment Assembly 

IF Interface 

IMS Inventory Management System 

IMV Intermodule Ventilation 

IOCC Input/Output Card Controller 

IP International Partner 

IRD Interface Requirement Document 

IRED Interim Resistive Exercise Device 

ISS International Space Station 

ISSP International Space Station Program 

ITS Integrated Truss Segment 

IV Intravehicular 

IVA Intravehicular Activity 

IWIS Internal WIS 

JOP Joint Operating Panel 

JSC Johnson Space Center 

60
STS-97

kbps kilobits per second 

kg kilogram 

km kilometer 

KSC Kennedy Space Center 

LAN Local Area Network 

LCU LED Control Unit 

LDI Local Data Interface 

LDRI Laser Dynamic Range Imager 

LED Light Emitting Diode 

LFDP Load Fault Detect/Protect 

LGA Low Gain Antenna 

LSAR Logistics Support Analysis Report 

LSE Launch Support Equipment 

LSM Life Support Module 

LSS Life Support System 

LTA Launch to Activation 

LV/LH Local Vertical/Local Horizontal 

MBM Manual Berthing Mechanism 

mbps megabytes per second 

MBSU Main Bus Switching Unit 

MCC Mission Control Center 

MCC-H Mission Control Center-Houston 

MCC-M Mission Control Center-Moscow 

MCDS Management Communication and Data System 

 Multipurpose Crew Display System 

MCS Motion Control System 

MDA Motor Drive Assembly 

MDM Multiplexer/Demultiplexer 

MIL-STD Military Standard 

MIP Mission Integration Plan 

MLI Multilayer Insulation 

mm millimeter 

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 

MRL Manipulator Retention Latch 

ms milliseconds 

MSC Mobile Servicing Center 

MSID Measurement Stimulus Identification 

MSS Mobile Servicing System 

MT Mobile Transporter 

MU Match Unit 

61
STS-97

μs microseconds 

N/A Not Applicable 

n. mi. nautical mile 

NASA National Aeronautics and Space Administration 

NCS Node Control Software 

NCU Network Control Unit 

NIU Network Interface Unit 

NPRV Negative Pressure Relief Valve 

NRZ-M Non-Return-to-Zero Mark 

OCA Orbiter Communications Adapter 

OCC Onboard Complex Control 

OCCS Onboard Complex Control System 

OCS Onboard Computer System 

OD Outside Diameter 

ODF Operations Data File 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

OMS Onboard Measuring Subsystem 

OPP OSVS Patch Panel 

ORU Orbital Replacement Unit 

OS On-Orbit Segment 

OSD Operations Support Department 

OSE Orbital Support Equipment 

OSHF Onboard S-Band High Frequency 

OSVS Orbiter Space Vision System 

OSVU Orbiter Space Vision Unit 

OTD ORU Transfer Device 

P6 Port 6 

PA Pressurized Adapter 

PBA Portable Breathing Apparatus 

PCBA Portable Clinical Blood Analyzer 

PCBM Passive Common Berthing Mechanism 

PCIA Portable Computer Interface Adapter 

PCMCIA Portable Computer Memory Card International Adapter 

PCMMU Pulse Code Modulation Master Unit 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PCU Plasma Contactor Unit 

PD Physical Device 

PDI Payload Data Interface 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PDS Passive Dosimetry System 

PEV Pressure Equalization Valve 

62
STS-97

PFCS Pump and Flow Control Subassembly 

PFE Periodic Fitness Evaluation 

 Portable Fire Extinguisher 

PFR Portable Foot Restraint 

PG Product Group 

PGSC Payload General Support Computer 

PGT Pistol Grip Tool 

PIT Preintegrated Truss 

PLB Payload Bay 

PM Pressurized Module 

PMA Pressurized Mating Adapter 

PMAD Power Management and Distribution 

PMCA Power Management Controller Application 

PMCU Power Management Controller Unit 

PN Pseudorandom Noise 

POR Point of Resolution 

POST Power-On Self-Test 

PPCO2 Partial Pressure of Carbon Dioxide 

PPRV Positive Pressure Relief Valve 

PRCS Primary Reaction Control System 

PRI Primary 

PRLA Payload Retention Latch Assembly 

PSI Parameter Status Indication 

psid pounds per square inch differential 

psig pounds per square inch gauge 

PSP Payload Signal Processor 

PSS Power Supply System 

PTB Payload Timing Buffer 

PTCS Passive Thermal Control Subsystem 

PUI Program-Unique Identifier 

PV Photovoltaic 

PVAA Photovoltaic Array Assembly 

PVCA Photovoltaic Controller Application 

PVCU Photovoltaic Control Unit 

PVM Photovoltaic Module 

PVR PV Radiator 

QD Quick Disconnect 

RACU Russian-to-American Converter Unit 

RAMS Radiation Area Monitoring System 

RBI Remote Bus Isolator 

RCS Reaction Control System 

RF Radio Frequency 

RFG Radio Frequency Group 

RFHX Radiant Fin Heat Exchanger 

RFPDB RF/Power Distribution Box 

63
STS-97

RFX Radiant Fin Heat Exchanger 

RHC Rotational Hand Controller 

RIRS Reflector Interface Ring Structure 

RMS Remote Manipulator System 

ROEU Remotely Operated Electrical Umbilical 

ROS Russian On-Orbit Segment 

RPC Remote Power Controller 

RPCM Remote Power Controller Mode 

RPDA Remote Power Distribution Assembly 

RS Russian Segment 

RSA Russian Space Agency 

RSU Remote Sensing Unit 

RT Remote Terminal 

RTAS Rocketdyne Truss Attachment System 

RTD Resistive Temperature Device 

 Resistive Thermal Device 

RTE Run Time Environment 

RTL Ready to Latch 

RTS Radio Telemetry System 

S/W Software 

S0 Starboard-zero 

S1 Starboard-one 

SABB Solar Array Blanket Box 

SAFER Simplified Aid for EVA Rescue 

SARJ Solar Array Rotary Joint 

SASA S-Band Antenna Subassembly 

 S-Band Antenna Support Assembly 

SAW Solar Array Wing 

SBS Series Bungee System 

SCA Switchgear Controller Assembly 

SDO Solenoid Driver Output 

SDP Standard Data Processor 

SGANT Space-to-Ground Antenna 

SGTRC Space-to-Ground Transmit/Receive Controller 

SHF S-Band High Frequency 

SLD Subject Load Device 

SM Service Module 

SMCC Service Module Central Computer 

SO Standard Out 

SODF Station Operations Data File 

SPD Serial Parallel Digital 

 Subject Positioning Device 

SPDA Secondary Power Distribution Assembly 

SPM Solar Power Module 

SRMS Shuttle Remote Manipulator System 

SSA S-Band Single Access 

64
STS-97

SSAF S-Band Single Access Forward 

SSAS Segment-to-Segment Attachment System 

SSC Station Support Computer 

 System Support Computer 

SSE Space Station Eyewash 

SSEC Secondary 

SSMDM Space Station Multiplexer/Demultiplexer 

SSOR Space-to-Space Orbiter Radio 

SSP Standard Switch Panel 

 Space Station Program 

SSRMS Space Station Remote Manipulator System 

SSSH Space Shuttle Systems Handbook 

SSU Sequential Shunt Unit 

STS Space Transportation System 

SVS Space Vision System 

SWIS Shuttle-Based WIS 

 

tb talkback 

TBD To be Determined 

TC Terminal Computer 

TCS Thermal Control System 

TDRS Tracking and Data Relay Satellite 

TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

TEPC Tissue Equivalent Proportional Counter 

THC Temperature and Humidity Control 

 Translational Hand Controller 

TORU Teleoperator Control System 

TRA Transmit/Receive Amplifier 

TRC Transmit/Receive/Controller 

TTCS Telephone-Telegraph Communication Subsystem 

TTL Transfer Tracking Log 

TUS Trailing Umbilical System 

TVIS Treadmill Vibration and Isolation System 

UAS User Application Software 

U.S. United States 

UDM Universal Docking Module 

UHF Ultrahigh Frequency 

USA United Space Alliance 

USOS United States On-Orbit Segment 

VBSP Video Baseband Signal Processor 

VIU Video Interface Unit 

VPU Video Processing Unit 

VSU Video Switching Unit 

VTR Video Tape Recorder 

65
STS-97

VTS Video Teleconferencing System 

WIF Worksite Interface 

WIS Wireless Instrumentation System 

WM Waste Management 

WRM Water Recovery and Management 

XPDR Transponder 

ZSR Zero-g Stowage Rack 

 

Russian Acronyms 

Blood Pressure 

 Navigation Satellite Instrumentation 

 Message Acquisition System 

 Toilet 

 Antenna Feeder Unit 

 

	 Vozdukh Automatic Control Unit 


 Onboard Computer System 

Secondary Purification Unit 

 Liquid Unit 


-12 Onboard Measurement Telemetry Subsystem 

 Gas Analysis Calibration Assembly 

 Gas Analyzer Monitoring Unit 

 

	 Vozdukh Valve Panel 

 Pump Unit 

 Nitrogen Purge Assembly 

	 Preliminary Drying Unit 

 Signal Conversion Unit 

 


 Heat Exchanger Unit 

 


 Vacuum Pump 

 


 Gas-Liquid Heat Exchanger Assembly 

 

Pressure Sensors 


 Temperature Sensors 

 

-
 Flush Water Container 

 


 Liquid-Liquid Heat Exchanger 

 

66
STS-97

	 Calf Measurement Device 

 Rodnik Status Panel 

 Mass Measurement Device 

 Integrated Control Panel 

 Liquid Carryover Indicator 

 

 Local Group Commutator 



 Non-Potable Container 

 Compressor 

 Central Post Computer 

 

 Local Analog Commutator 

 

- Air-Water Separator 

 


- Condensate Water Processor Control Panel 

	 Transfer Compartment 

 

 Rheoplethsysmography 

Pressure Differential Regulator 

 

 Onboard Measurement System 


	- Simvol-Ts 


 Air Conditioning System 

	 Oxygen Generation Hardware 

	
 Thermal Control System 

- Urine Collection Assembly 


-2 Condensate Water Processor 


-64 Current Regulator 



 SM Audio subsystem 


 Onboard Equipment Control System 

 Motion Control and Navigation System 

 



 Television Subsystem 


	 Teleoperator Control System 

 

 

 

 

 

 

67
STS-97

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

 

68
STS-97

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.

69
STS-97

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 256 961-6225 

(Moscow)

NASA Johnson Space Center

Houston, TX

NASA Moscow PAO

carlos.fontanot1@jsc.nasa.gov

Bruce Buckingham 321 867-2468

NASA Kennedy Space Center

Kennedy Space Center, FL

Launch Operations

bruce.buckingham-1@kmail.ksc.nasa.gov

Jack King 321 861-4358

United Space Alliance

Kennedy Space Center, FL

Shuttle Processing

KingJW@usafoo.unitedspacealliance.com

70
STS-97

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 Engines

daniel.c.beck@boeing.com

71
Table prepared by Richard W. Orloff, 02/2001 

SHUTTLE FLIGHTS AS OF NOVEMBER 2000 

100 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 75 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-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-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 

(22 flights) 

OV-105 

Endeavour 

(14 flights)