NASA Space Shuttle STS-105 Press Kit

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Science Moves to theScience Moves to the

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Updated July 24, 2001


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Table of Contents

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

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

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

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

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

Spacewalks

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

PayloadsMultipurpose Logistics Module (MPLM) Leonardo ....................................................... 19Materials ISS Experiment (MISSE) .............................................................................. 21Small Experiments....................................................................................................... 22

DSO/DTO

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

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

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

DTO 701 Space Vision Laser Camera System ............................................................ 29DTO 805 Crosswind Landing Performance ................................................................. 30

Shuttle Reference Data

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

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

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

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

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

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

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

Media Contacts .......................................................................................................... 59


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Mission Overview

New Crew, New Lab Racks to be Launched to ISS

Rotation of the International Space Station crew, the third flight of an Italian-builtMultipurpose Logistics Module delivering additional scientific racks, equipment and suppliesfor the space station, and two spacewalks highlight the STS-105 mission of Discovery,scheduled for launch from Kennedy Space Center in Florida.

The crew changeout is the second for the ISS, and the logistical module, named Leonardo,is making its second flight to the space station. An identical module named Raffaello hasflown once.

The STS-105 mission will involve three crews. They are the four-member crew ofDiscovery, the three members of the Expedition Three crew to be launched to the spacestation, and the three members of the Expedition Two crew returning to Earth aboard theshuttle.

Commanding the Discovery crew will be Scott Horowitz, an Air Force colonel with a Ph.D.in aerospace engineering, making his fourth flight into space. Pilot will be Frederick W."Rick" Sturckow, a Marine major, former test pilot and veteran of a previous flight to thespace station. Patrick G. Forrester, an Army lieutenant colonel and former test pilot, ismaking his first flight to space as mission specialist 1. Daniel T. Barry, who holds adoctorate in electrical engineering/computer science and an M.D. degree, is missionspecialist 2. This is his third mission to space.

The Expedition Three crew of the space station launching aboard Discovery is made up ofan astronaut and two cosmonauts. Its commander is Frank Culbertson, 52, a retired Navycaptain and former test pilot making his third flight into space. Cosmonaut VladimirDezhurov, 39, a Russian Air Force lieutenant colonel who served as commander of a 115-day mission aboard Mir in 1995, will be Soyuz pilot. Cosmonaut Mikhail Tyurin, 41, fromRSC Energia and on his first space mission, will serve as a researcher and flight engineer.

The Expedition Two crew returning to Earth aboard Discovery is cosmonaut Yury Usachev,its commander, and astronauts Jim Voss and Susan Helms. They were taken to the stationaboard Discovery on a flight that launched March 8. Expedition Two began the majorscientific investigations aboard Destiny that are the purpose of the orbiting laboratory, and

paved the way for more to come.

About 46 hours after its launch Discovery is scheduled to dock with the International SpaceStation. The shuttle will spend almost eight days attached to the ISS. Transfer of equipmentfrom the orbiter's middeck begins less than three hours after docking, which occurs duringthe crew's flight day three.

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Leonardo will be lifted out of Discovery's payload bay on flight day four and attacheddirectly to the station's Unity node for the unloading of its cargo. Once Leonardo is attachedto Unity, half a dozen power, data and fluid connecters will be hooked up. The following daythe ISS crew will begin transferring equipment and supplies to the station.

The pressurized moving van first flew on Discovery on the STS-102 mission to the spacestation in March 2001. Among items in Leonardo will be two EXPRESS Racks to beinstalled in the station's U.S. laboratory Destiny. EXPRESS stands for Expedite theProcessing of Experiments to the Space Station. The racks will house a variety of scientificexperiments, which can be changed out in space.

Destiny is the scientific focus of the ISS, and the most advanced and most versatilescientific research facility ever launched into orbit. The space station eventually will havesix laboratories. Destiny, installed on the STS-98 mission of Atlantis in February 2001, hasslots for 24 of the interchangeable racks (six on the top, six on the bottom and six on eachside). Eleven are systems racks, and one slot has Destiny's 20-inch-diameter, optical-

quality window. Remaining slots are for scientific racks.

Two spacewalks are planned while Discovery is docked to the International Space Stationto deliver and install equipment and make repairs. The first spacewalk, to last about 6hours on flight day seven, will see Barry and Forrester install the Early Ammonia Servicerto the space station's P6 truss and the Materials ISS Experiment (MISSE) on handrails ofthe ISS airlock. The Early Ammonia Servicer and MISSE will be taken into space in twoPassive Experiment Carriers on the Integrated Cargo Carrier in Discovery's cargo bay.

During the second spacewalk, to last about 5 hours on Flight Day Nine, Barry andForrester will install handrails and lay cables to provide temporary power to the S0 truss, to

be launched on a future mission.

Space station crew transfer is a carefully thought out process. As a member of theExpedition Three crew transfers from the shuttle to the ISS, that crewmember's custom-designed seat liner, called an Individual Equipment Liner Kit, is installed in the Soyuzspacecraft docked to the station. The seat liner of the replaced crewmember is removedfrom the Soyuz, and that individual then becomes a member of the shuttle crew.

All three Expedition Three crewmembers complete the liner changeout with members of theExpedition Two crew on Discovery's Flight Day Four, though the formal beginning ofExpedition Three occurs at final closing of the hatches between Discovery and the space

station.

Equipment and supply transfer operations are scheduled during flight days five througheight.

The crew will leave Leonardo and deactivate the MPLM on flight day nine. Loaded withunneeded equipment and refuse from the ISS, it will be returned to Discovery's cargo bayto be taken back to Kennedy Space Center.

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Discovery also will carry a number of small scientific payloads. Among them is Simplesat, asatellite which uses inexpensive commercial hardware to demonstrate Global PositioningSystem attitude control and payload-assisted fine pointing while free flying in low Earthorbit. It will be deployed from a Hitchhiker canister on Discovery.

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

STS-105 is the 11th shuttle flight to the International Space Station. It is the fifth shuttlemission of the year and the 106th shuttle flight. The 11-day flight will end with Discovery'slanding on the 3-mile runway at Kennedy Space Center.

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

Day 1 - Launch

Discovery's crew will launch at the end of its day during a precisely timed, few-minutes-

long launch window that begins the process of rendezvous with the International SpaceStation. Crewmembers begin a sleep period about seven hours after launch.

Day 2 - Equipment Checkouts, Rendezvous Preparations

Discovery's crew will spend its first full day in space checking out equipment that will beused for upcoming major activities -- the shuttle's robotic arm; and the controls and toolsused for the final rendezvous and docking with the station. The crew also will power up andprepare the shuttle's docking system and perform several engine firings to optimize the rateat which Discovery closes in on the station.

Day 3 - Rendezvous and Docking

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

Day 4 - Berthing of the MPLM Leonardo

Leonardo will be attached to the station's Unity node, powered up and activated. The threeExpedition Three crewmembers will install their Individual Equipment Liner Kits in theSoyuz capsule docked to the station.

Day 5 - Equipment, Supplies Transfer

Both station and shuttle crewmembers will work at transferring equipment and suppliesfrom Leonardo to the space station. Expedition Two and Expedition Three crewmemberswill take some time for handover activities.

Day 6 - Spacewalk Preparation

Astronauts will continue transfers from Leonardo, including moving the EXPRESS racksinto the Destiny laboratory. They also will check out spacesuits and other spacewalkingequipment. The station and shuttle arms will be prepared for the next day's activities.

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Day 7 - The First Spacewalk

Barry and Forrester will install the Early Ammonia Servicer to the space station's P6 trussand the Materials ISS Experiment (MISSE) on handrails of the ISS airlock during aspacewalk of about 6 hours.

Day 8 - Equipment, Supplies Transfer

Again station and shuttle crewmembers will transfer equipment and supplies from Leonardoto the space station. Shuttle crewmembers also will prepare for the subsequent day'sspacewalk, while station crewmembers will continue handover activities.

Day 9 - The Second Spacewalk

Barry and Forrester, in another spacewalk of about 5 hours, will install handrails and laycables they will install to provide temporary power to the S0 truss, to be launched later.

Day 10 Unberthing of Leonardo

Leonardo will be unberthed from the space station and, loaded with unneeded equipmentand trash from the station, returned to Discovery's cargo bay. Station crewmembers willcontinue their handover.

Day 11 Shuttle-Station Hatch Closing, Undocking, Flyaround

The shuttle and station crews will close hatches between the spacecraft. Horowitz andSturckow will undock Discovery from the station. With Sturckow at the controls, Discoverywill do a flyaround of the complex before departing.

Day 12- Pre-Landing Checkouts, Cabin Stow

Activities include the standard day-before-landing flight control checks of Discovery byHorowitz and Sturckow as well as the normal steering jet test firing. The crew will spendmost of the day stowing away gear on board the shuttle and preparing for the return home.

Day 13 - Entry and Landing

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

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Mission Objectives

Top priorities for the STS-105 (7A.1) mission of Discovery are rotation of the InternationalSpace Station crew, bringing water, equipment and supplies to the station and completionof a series of spacewalks and robotics tasks.

International Space Station Program priorities include the following tasks to beaccomplished.

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

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

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

--Berth the Multipurpose Logistics Module to the station, check it out and transfer criticalcargo to the space station, transfer and stow return cargo in the module and return themodule to the cargo bay.

--Spacewalk and robotics activities, including installation of the Early Ammonia Servicerand preparation for future station assembly. Among the preparation activities are layingheater cables for a future station truss segment.

Crew

Commander:

Scott J. HorowitzPilot: Frederick (Rick) W. Sturckow

Mission Specialist 1: Patrick G. Forrester

Mission Specialist 2: Daniel T. Barry

E3 Up: Frank L. Culbertson, Jr.

E3 Up: Vladimir N. Dezhurov

E3 Up: Mikhail Tyurin

E2 Down: Yury V. Usachev

E2 Down: James S. Voss

E2 Down: Susan J. Helms

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Launch

Orbiter: Discovery OV103

Launch Site: Kennedy Space Center Launch Pad 39A

Launch Window: 2.5 to 5 minutes

Altitude: Insertion 122 Nautical Miles; Rendezvous 240 NauticalMiles

Inclination: 51.6 Degrees

Duration: 11 Days 19 Hrs. 39 Min.

Vehicle Data

Shuttle Liftoff Weight: 4517989 lbs.

Orbiter/Payload Liftoff Weight: 257748 lbs.

Orbiter/Payload Landing Weight:222275 lbs.

Software Version: OI-28

Space Shuttle Main Engines:(1 MB pdf)

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

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

SRB Set: BI109PF

Landing

Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

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Crew Members

Commander: Scott J. Horowitz

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

aerospace engineering, will command Discovery's STS-105 mission and beresponsible for its safety and success. He will fly Discovery through itsrendezvous and docking with the International Space Station on the fifthshuttle flight of the year. He will operate the shuttle's robotic arm during themission's two spacewalks and act as backup arm operator during theberthing and unberthing of the Multipurpose Logistics Module. He will assistpilot Rick Sturckow in Discovery's flyaround of the station after undocking.Finally, he will land Discovery at mission's end.

Previous Space Flights:Horowitz flew as pilot on STS-75, the Tethered Satellite reflight launched in February 1996; onSTS-82, the second Hubble Space Telescope maintenance mission in February 1997, and on STS-101, the third shuttle mission to the space station.

Ascent Seating: Flight Deck - Port ForwardEntry Seating: Flight Deck - Port ForwardRMS

Pilot: Frederick (Rick) W. Sturckow

A Marine major, a veteran of 41 Desert Storm combat missions and formertest pilot, Rick Sturckow, 39, [40 on Aug. 11] will be responsible formonitoring critical shuttle systems during ascent and entry. He also will playa major role during rendezvous and docking operations, responsible formany of the shuttle's navigational tools. He will be responsible for operating

still and video cameras. He will serve as the intravehicular crewmemberduring the mission's two spacewalks, monitoring and coordinating activitiesof the spacewalkers. Sturckow himself is the backup spacewalker. Afterparticipating in Discovery's undocking from the station, he will perform the

flyaround of the orbiting laboratory.

Previous Space Flights:Sturckow was pilot on STS-88 launched in December 1998, the first space station assemblymission.

Ascent Seating: Flight Deck - Starboard ForwardEntry Seating: Flight Deck - Starboard ForwardIV1

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Mission Specialist 1: Patrick G. Forrester

Patrick Forrester, 44, is an Army lieutenant colonel, former test pilot andArmy Ranger with a master's in mechanical and aerospace engineering.He will do two spacewalks during STS-105. He also will be primaryoperator of the shuttle's robotic arm during berthing and unberthing of the

Multipurpose Logistics Module. Among his other responsibilities will beopening and closing of Discovery's payload bay doors and the shuttle'scommunications equipment and instruments, as well as flight data file. Hewill serve as a backup in still photography and video.

Previous Space Flights:Forrester is making his first spaceflight.

Ascent Seating: Flight Deck - Starboard AftEntry Seating: Flight Deck - Starboard AftEV2

Mission Specialist 2: Daniel T. Barry

Daniel Barry, 47, a veteran of two space flights, earned a Ph.D. in electricalengineering/computer science and an M.D. degree. As EV1 he will be thelead for the two spacewalks during Discovery's flight to the space station.Barry will serve as Discovery's flight engineer during ascent and entry. Hewill have primary responsibility in post-insertion activities, converting theshuttle from a launch vehicle to an orbiting spacecraft, and in deorbitpreparations. He will provide information to the commander and pilotduring rendezvous with the station and after undocking. He will serve asloadmaster on the shuttle side for transfer of equipment and supplies to the

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

Previous Space Flights:Barry was a mission specialist on STS-72, the Space Flyer Unit retrieval flight, launched inJanuary 1996, and on STS-96, a logistics flight to the space station, launched in May 1999.

Ascent Seating: Flight Deck - Center AftEntry Seating: Flight Deck - Center AftEV1

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E3 UP: Frank L. Culbertson, Jr.

Frank Culbertson, 52, a retired Navy captain, former test pilot, and formermanager of the ISS Phase One (Shuttle-Mir) Program, will command theExpedition Three mission to the space station. As commander, he will have

overall responsibility for expedition safety and success as the station's sizeand scientific capabilities continue to increase. Culbertson also will have anumber of responsibilities aboard Discovery during STS-105. Among themwill be primary responsibility for shuttle communication with the station andwith Mission Control Moscow during rendezvous and docking and forpressure and leak checks once docking is complete. He also will be

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

Previous Space Flights:Culbertson was pilot on STS-38, a five-day Defense Department mission in November 1990. Hecommanded STS-51, which launched the Advanced Communications Technology Satellite andthe Shuttle Pallet Satellite in September 1993.

Ascent Seating: Mid Deck - Port

E3 UP: Vladimir N. Dezhurov

Vladimir Nikolaevich Dezhurov is a veteran of one long-durationspaceflight, having served as commander of a mission aboard the Russianspace station Mir in 1995. That crew returned to Earth aboard the shuttleAtlantis July 7, 1995, after 115 days in orbit. Dezhurov is a lieutenantcolonel in his country's air force and served as a pilot and senior pilot,earning three Armed Forces Medals. He was first assigned to theCosmonaut Training Center in 1987. Since 1989 he has trained with agroup of test cosmonauts. He served as a backup member of theExpedition One crew to the International Space Station.

Previous Space Flights:Dezhurov commanded the Mir-18 mission, a 115-day flight in 1995.

Ascent Seating: Mid Deck - Center

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E3 UP: Mikhail Tyurin

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

his graduation from the Moscow Aviation Institute in 1984. At Energia heworked in dynamics, ballistics and software development. He continuesgraduate studies, and his personal scientific research relating topsychological aspects of cosmonauts' training for manual control ofspacecraft. Tyurin himself was selected to begin cosmonaut training in1993. Since 1998 he has trained as an ISS flight engineer. He was abackup crewmember for Expedition One before being named anExpedition Three crewmember.

Previous Space Flights:Tyurin is making his first spaceflight.

Ascent Seating: Mid Deck - Starboard

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E2 DOWN: James S. Voss

Jim Voss, 52, a retired Army colonel, will return from his second visit to thespace station after his months aboard the orbiting laboratory as part of theExpedition Two crew. Voss and commander Yury Usachev did an internalspacewalk, the first from the space station. They repositioned a dockingcone in preparation for the arrival later this year of the Russian dockingcompartment. Voss was instrumental in the successful effort to recover fromstation computer problems that began during the STS-100 mission in April2001. Voss worked with Helms in the checkout and troubleshooting for the

station's robotic arm, Canadarm2.

Previous Space Flights:Voss flew on STS-44 that launched a military satellite in 1991, STS-53 with a classified militarypayload in 1992, STS-69, the second Wake Shield Facility flight, in 1995, and STS-101 to thespace station in 2000.

Entry Seating: Mid Deck - Port

E2 DOWN: Yury V. Usachev

Yury Usachev, 43, is ending his fourth flight into space with his return toEarth on Discovery. He is the first Russian to command the InternationalSpace Station. During his Discovery flight, Usachev will be designated

Mission Specialist 5. During his months on the ISS, Usachev wasresponsible for the safety of his crew and the success of the mission,which saw the beginning of substantial science aboard the InternationalSpace Station. He did a spacewalk with Voss in the Zvezda module andhelped Voss and Helms in the checkout and troubleshooting ofCanadarm2.

Previous Space Flights:Usachev flew as a flight engineer during two long-duration missions to the Mir space station in1994 and 1996. He was a mission specialist during the STS-101 mission of Atlantis to the spacestation in May 2000 along with crewmates Jim Voss and Susan Helms. Usachev has logged 386days in space and six spacewalks.

Entry Seating: Mid Deck - Starboard

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E2 DOWN: Susan J. Helms

Susan Helms, 43, is an Air Force colonel returning from her fifthspaceflight. She operated the station's Canadarm2 during checkout andtroubleshooting operations. She and fellow Expedition Two crewmember

Voss performed a spacewalk from Discovery after Expedition Two arrivedat the space station in March 2000. She was choreographer for the secondspacewalk, performed by Andy Thomas and Paul Richards, operating fromDiscovery's aft flight deck. She also was responsible for transfer of vitalracks from the Multipurpose Logistics Module to the U.S. laboratoryDestiny. With Usachev and Voss, she conducted and participated in a

number of scientific experiments during the Expedition Two mission.

Previous Space Flights:Helms flew on STS-54, which launched a Tracking and Data Relay Satellite in 1993; STS-64, theLidar In-Space Technology Experiment flight, in 1994; STS-78, a Spacelab flight, in 1996, andSTS-101 to the space station in 2000.

Entry Seating: Mid Deck - Center

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Flight Day Summary Timeline

DATE TIME (EST) DAY MET EVENT

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

08/11/01 1:08:00 PM 3 001/19:36 TI Burn08/11/01 3:27:00 PM 3 001/21:55 Docking

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

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

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

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

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

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

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

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

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Rendezvous and Docking

Overview

Discovery's rendezvous and docking with the International Space Station begins withthe precisely timed launch of the shuttle on a course for the station. During the first twodays of the mission, periodic engine firings will gradually bring Discovery to the startingpoint for a final approach.

About 2 hours before the scheduled docking on Flight Day Three, Discovery will reachthat point about 50,000 feet -- 9 miles -- behind the ISS. There Discovery's jets will befired in a Terminal Intercept (TI) burn to begin the final phase of the rendezvous.Discovery will close the final miles to the station during the next orbit of the Earth.

As Discovery closes in, the shuttle's rendezvous radar system will begin tracking thestation and providing range and closing rate information to the crew. During theapproach, the shuttle can make as many as four, small course corrections at regular

intervals. Just after the last correction is completed, Discovery will reach a point abouthalf a mile below the station. At that time, about an hour before the scheduled docking,Commander Scott Horowitz will take manual control of Discovery.

Horowitz will slow Discovery's approach and fly to a point about 600 feet directly belowthe station. There he will begin a quarter-circle of the station, slowly moving to a positionin front of the complex, in line with its direction of travel.

During the rendezvous, Horowitz will be assisted by Pilot Rick Sturckow. MissionSpecialists Dan Barry and Patrick Forrester also will play key roles in the rendezvous,with Barry operating a handheld laser-ranging device and a laptop computer navigation

aid assisted by Forrester. Barry also will operate the shuttle's docking mechanism tolatch the station and Discovery together after the two spacecraft make contact.

Horowitz will slowly close on the station moving at a speed of about a tenth of a mile perhour. Using a view from a camera mounted in the center of Discovery's dockingmechanism as a key alignment aid, Horowitz will precisely center the docking ports ofthe two spacecraft. Horowitz will fly to a point where the docking mechanisms are 30feet apart, and pause for about five minutes to check the alignment.

For Discovery's docking, Horowitz will maintain the shuttle's speed relative to the stationat about one-tenth of a foot per second, and keep the docking mechanisms aligned towithin three inches of one another. When Discovery makes contact with the station,preliminary latches will automatically attach the two spacecraft together. Immediatelyafter Discovery docks, the shuttle's steering jets will be deactivated to reduce the forcesacting at the docking interface. Shock absorber-type springs in the docking mechanismwill dampen any relative motion between the shuttle and the station.

Once relative motion between the spacecraft has been stopped, Barry will secure thedocking mechanism, sending commands for Discovery's mechanism to retract andclose a final set of latches between the shuttle and station.

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Undocking, Separation and Flyaround

Once Discovery is ready to undock, Barry will send a command that will release thedocking mechanism. The initial separation of the spacecraft will be performed bysprings in the docking mechanism that will gently push the shuttle away from thestation. Discovery's steering jets will be shut off to avoid any inadvertent firings during

this initial separation.

Once the docking mechanism's springs have pushed Discovery to a distance of abouttwo feet, when the docking devices will be clear of one another, Sturckow will turn thesteering jets back on and fire them to begin very slowly moving away. From the aft flightdeck, Sturckow will manually control Discovery within a tight corridor as he separatesfrom the ISS, essentially the reverse of the task performed by Horowitz when Discoverydocked.

Discovery will continue away to a distance of about 450 feet, where Sturckow will begina close flyaround of the station, circling the complex 1 times.

Sturckow will pass directly above the station, then behind, then underneath, then in frontand then reach a point directly above it for a second time. At that point, passing abovethe station for a second time, Sturckow will fire Discovery's jets to separate from thearea of the station. The flyaround is expected to be completed a little over an hour afterundocking.

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EVA

Two Spacewalks to Lay Groundwork for Future ISS Construction

OverviewAstronauts Dan Barry and Patrick Forrester are to perform two spacewalks while Discoveryis docked to the International Space Station during STS-105.

Barry will be designated Extravehicular crewmember 1 (EV1) and wear red stripes on hisspacesuit. Forrester, designated EV2, will wear an all-white spacesuit.

Discovery Pilot Rick Sturckow will be the Intravehicular crewmember (IV), coordinating thespacewalk activities from within the shuttle's cabin. Discovery Commander Scott Horowitzwill control the shuttle's robotic arm during the spacewalk.

The spacewalkers will install equipment on the exterior of the station for future maintenanceand construction work on the outpost. Both spacewalks will originate from Discovery'sairlock, and the two astronauts will be tethered to the shuttle's robotic arm for much of thework.

The primary objective of the first spacewalk, planned for Flight Day Seven and to last about6 hours, is to install an Early Ammonia Servicer on the station, a system that containsspare ammonia for the station's cooling system. Ammonia is the fluid used in the radiatorsthat cool the station's electronics. The EAS will be installed on the truss, called the P6 trussthat holds the station's giant U.S. solar arrays, associated batteries and the coolingradiators.

During the first spacewalk, Barry and Forrester also will attach an experiment to the outsideof the station's airlock that will collect information on how various materials weather thespace environment. The experiment, called the Materials International Space StationExperiment (MISSE), is housed in two carriers that will be attached to the station's exteriorfor an extended duration.

As Barry and Forrester exit Discovery's airlock, Horowitz will maneuver the shuttle's roboticarm into position to latch onto a grapple fixture on the EAS, bolted to a carrier in theshuttle's payload bay for launch. After Horowitz has latched the arm onto the EAS, Barryand Forrester will go to the pallet, called an Integrated Cargo Carrier, and begin looseningthe six bolts that hold the unit in place. In addition, Barry will translate hand-over-hand up to

the station's Destiny Lab, where he will pick up a foot platform to be used during installationof the EAS. With the bolts free, Horowitz will begin lifting the EAS, with Barry and Forresterholding on to handrails on the EAS as well, up to the station.

Horowitz will maneuver the spacewalkers and EAS up to the position on the station's P6truss where the EAS will be installed.

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There, Barry will attach the foot platform and secure himself to it. Horowitz will release thearm's grip on the EAS, basically handing off the unit to Barry. Forrester will then help Barryalign the unit over its attachment position and move it to a "soft dock," where it will bepreliminarily held in place by a hook mechanism closed and locked with a pip pin insertedby Forrester. Forrester will then tighten a bolt to firmly attach the EAS in position on the

truss. The two spacewalkers will then unfurl and attach cables to supply station electricalpower to heaters on the EAS, completing the installation.

That done, the spacewalkers will hold on to the station arm again as Horowitz lowers themback to Discovery's payload bay, pausing at the station's Z1 truss to allow Barry to put thefoot restraint in a stowed location needed for upcoming mission STS-110/8a. In Discovery'scargo bay, Barry and Forrester will move to the carrier platform and release the twoPassive Experiment Containers containing the MISSE investigations from their launchrestraints. With each of the spacewalkers holding an experiment container, they will holdonto the arm while Horowitz maneuvers them up to the station's airlock. There they will letgo of the arm and clamp the MISSE carriers to two separate airlock handrails.

The second spacewalk, planned to last up to 5 hours, will be performed on Flight DayNine of the mission and will focus on preparations for future station assembly, installinghandrails on the Destiny lab and laying heater cables for a future station truss segment.

Horowitz will again be operating the shuttle robotic arm to maneuver the spacewalkers,who will be hanging on to the arm at times. As the spacewalk begins, Barry and Forresterwill take with them from Discovery's airlock two bags containing the heater cables they willinstall on the station. Called Launch to Activation heater cables, they will be used on shuttlemission STS-110 to power heaters on the station's S0 truss segment, the center segmentof the station's truss structure, more than 300 feet long. In addition, they will take with themtwo bags holding 11 new handrails they will install on the Destiny Lab, called Orbit-Installed

Handrails.

Barry and Forrester will hold on to the shuttle arm, carrying the heater cable bags, asHorowitz lifts them to the station's Destiny lab. There, they will temporarily attach the bagsto handrails, one on the port side of the lab and another on the starboard side.

Barry will install six handrails on the lab's starboard side while Forrester installs fivehandrails on the port side. The spacewalkers also will relocate two existing lab handrails.With the handrails installed, the spacewalkers will then feed the heater cables along therails on either side of the lab, connecting one end to the station and placing the other end inposition for use when the S0 truss segment is delivered on STS-110.

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EVA Timeline forTwo Spacewalks to Lay Groundwork for Future ISS Construction

Time Event

005/17:05 EVA 1 Start

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

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

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

005/22:50 EVA 1 Clean Up

005:23:20 EVA 1 Ingress

005/23:35 EVA 1 End

007/17:05 EVA 2 Start

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

007/21:05 EVA 2 Clean Up

007/23:20 EVA 2 Ingress

007/23:35 EVA 2 End

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History/Background

Construction of Leonardo began in April 1996 at the Alenia Aerospazio factory in Turin,Italy. Leonardo was flown from Italy to the Kennedy Space Center in Florida in August 1998aboard a special Beluga cargo aircraft. Although built in Italy, Leonardo and two additionalMPLMs are owned by the U.S. The MPLMs were provided in exchange for Italian access toU.S. research time on the space station.

The cylindrical Leonardo module is about 21 feet (6.4 meters) long and 15 feet (4.6 meters)in diameter. It weighs a little over 9,000 pounds (4.1 metric tons) empty and can carry up to20,000 pounds (9.1 metric tons) of cargo packed into 16 standard space station equipmentracks or platforms. The reusable MPLM functions as both a cargo carrier and a spacestation module.

Leonardo contains components that provide some life support, fire detection andsuppression, electrical distribution and computer functions. When in the payload bay,Leonardo is independent of the space shuttle and there is no passageway for shuttle

crewmembers to travel to and from the module. Eventually, the MPLMs also will carryrefrigerator freezers for transporting experiment samples and food to and from the station.

Leonardo first flew to the space station aboard Discovery on STS-102/5A.1 in March 2001.The second MPLM, Raffaello, flew to the station aboard Endeavour on STS-100/6A in April2001.

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Payloads

Materials International Space Station Experiments

OverviewThe Materials International Space Station Experiments (MISSE) Project is a NASA/LangleyResearch Center-managed cooperative endeavor to fly materials and other types of spaceexposure experiments on the space station. The objective is to develop early, low-cost,non-intrusive opportunities to conduct critical space exposure tests of space materials andcomponents planned for use on future spacecraft.

Johnson Space Center, Marshall Space Flight Center, Glenn Research Center, theMaterials Laboratory at the Air Force Research Laboratory and Boeing Phantom Works areparticipants with Langley in the project.

The MISSE experiments will be the first externally mounted experiments conducted on theISS. The experiments are in four Passive Experiment Containers (PECs) that were initiallydeveloped and used for an experiment on Mir in 1996 during the Shuttle-Mir Program. ThePECs were transported to Mir on STS-76. After an 18-month exposure in space, they wereretrieved on STS-86.

PECs are suitcase-like containers for transporting experiments via the space shuttle to andfrom an orbiting spacecraft. Once on orbit and clamped to the host spacecraft, the PECsare opened and serve as racks to expose experiments to the space environment.

The first two MISSE PECs will be launched to the ISS on STS-105. Two more will belaunched to the ISS about 18 months later.

Examples of tests to be performed in MISSE include: New generations of solar cells withlonger expected lifetimes to power satellites; advanced optical components planned forfuture Earth observational satellites; new, longer-lasting coatings that better control heatabsorption and emissions and thereby the temperature of satellites; new concepts forlightweight shields to protect crews from energetic cosmic rays found in interplanetaryspace; and the effects of micrometeoroid impacts on materials planned for use in thedevelopment of ultra-light membrane structures for solar sails, large inflatable mirrors andlenses.

New affordable materials will enable the development of advanced reusable launch

systems and advanced spacecraft systems.

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Payloads

Small Payloads Take Youth Science into Orbit

OverviewGoddard Space Flight Center's Wallops Flight Facility manages NASA's Shuttle SmallPayloads Project. The SSPP designs, develops, tests, integrates and flies a group of smallpayload carrier systems aboard the space shuttle. These carriers -- the Hitchhiker,Getaway Specials, Space Experiment Module -- support payloads supplied by NASA, otherU.S. government agencies, universities, high schools, domestic commercial customers andforeign nationals and governments. The following small payloads will be flown aboardDiscovery during the STS-105 mission:

Simplesat

Simplesat, a deployable satellite, is being developed as a prototype for a satellite that couldbe constructed at a college or university. It is designed to evaluate the use of inexpensivecommercial hardware on spacecraft. Simplesat is expected to demonstrate GlobalPositioning System attitude control and payload-assisted fine pointing while free flying inlow Earth orbit. It will be ejected from a Hitchhiker canister on the shuttle and deployedaway from the sun to protect its optical equipment. It will not be retrieved.

The shuttle crew will deploy Simplesat using switches to arm and activate pyrotechnicdevices that release the satellite from the canister. Once the satellite leaves the shuttle,Simplesat's batteries will begin to charge and scientists will monitor Simplesat via radiofrequency transmission. Simplesat GPS operates as a navigational tool that has both

earthbound and spacebound applications because it provides scientists with a very precisereading of one's location in space.

G-780 Cell Growth in Microgravity

The Get-Away Special canister G-780, Cell Growth in Microgravity experiment, is aneducational project that encourages Minnesota high school students to observe root cellgrowth in microgravity by germinating Vicia Faba bean seeds in space. The primaryobjective of the experiment is to engage some 200 Mayo High School (Rochester, Minn.)students in an authentic investigation that requires collaboration with scientificprofessionals from the community. The students designed and prepared the experiment.For additional information about this experiment see [email protected].

Microgravity Smoldering Combustion

The Microgravity Smoldering Combustion experiments are designed to study smolderingcombustion in an extremely low gravity (microgravity) environment and in normal gravity.The microgravity setting is essential because it permits scientists to study smolderingcombustion mechanisms without the complications introduced by gravity and it providesinsight into how smoldering combustion behaves in space.

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Smoldering combustion is a complex, nonflaming form of burning that occurs in the interiorof porous, combustible materials, both natural (piles of leaves and pine needles) andmanmade (furniture stuffing and cable insulation). Smolder is a serious problem: 40 percentof all deaths caused by fire in the U.S. can be attributed to the smoldering of householdfurniture, which releases toxic byproducts. In space, the threat of smoldering combustion

becomes an even greater risk.

An earlier version of this experiment flew on USML-1 in 1992. The present version was firsttested on Earth and flown aboard STS-69 and STS-77 in 1995-1996.

Hitchhiker Experiments Advancing Technology

The Hitchhiker Experiments Advancing Technology payload contains two experiments,Simplesat and Space Experiment Module-10. NASA's Goddard Space Flight Center,Greenbelt, Md., sponsors both experiments.

Space Experiment Module-10

The Space Experiment Module-10 contains 11 experiments and flies in the space shuttle'spayload bay. Experiments flying aboard the SEM-10 module are:

Space Travel's Affect on Roots (STARS): The STARS experiment examines the growingcharacteristics of roots subjected to the space environment. Once the roots return to Earth,they will be planted alongside control roots that were purchased at the same time. Adifference in crop yield could aid in realizing the potential for growing food in space for long-term exploration. (Arizona State University, Tempe, Ariz.)

Flowers in Space: Students will examine the effects of space travel on two types ofperennial flowers (coreopsis and columbine) and two types of vegetables (lettuce andcucumbers). Half of the seeds will fly aboard the mission and the other half will be held atWallops. Upon return, the flower and lettuce seeds will be planted in the fall. The lettuce willmature in the fall, the perennial flowers will mature in the following spring, and thecucumber seeds will be started indoors during the spring and planted outdoors. Studentswill compare growth rates at different geographic locations to determine if the seeds thattraveled in space grow differently. (GSFC/Wallops New 2000, Media, Pa.)

Food for Earth and Space: Students will determine whether the environment of spaceinfluences the growth of edible sprouts. Mass, volume and mean growth length will becompared for both the control and variable groups. This experiment should reveal if theenvironment of space could produce more or less food on the space station. (Corpus

Christi School, Chambersburg, Pa.)

Corn:Tomorrow's Food on Earth and in Space and Rusting in Space: The first studentexperiment will explore if the environment of space impacts the embryo of the corn seed oraffects its ability to grow and produce once planted on Earth. Preflight, control and variableseed groups will be measured for mass, volume and density and will be stored in similarenvironments. Upon return, all growing conditions (time, light, temperature and wateringamounts) will be the same. The "Rusting in Space" experiment will observe if rust develops

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differently on a variety of metals after exposure to the environment of space. The controland variable groups will be stored in similar environments and then they will be placed in arust-promoting environment. Students will record data regarding mass and densitychanges, oxidation time and other physical changes. (Chambersburg Area Middle School,Chambersburg, Pa.)

Shirt and Shoes Required: The experiment will determine the effect of high-frequencyradiation and microgravity on fabrics, both natural and synthetic. Results from thisexperiment may influence clothing manufacturing on Earth's changing environment. (GreatBridge Middle School, Chesapeake, Va.)

Agrilaser: This experiment will examine the effects of lasering various seeds and sendingthem into space. In space, outside the protective atmosphere, the molecules are subjectedto cosmic particles. This may affect the seeds' growth cycle, germination period, growthtimeline, edible plant taste, look and texture. A variety of seeds will be used and propercontrols will be used for each seed group. (Arrowhead Union High School, PortWashington, Wis.)

Space Laser Comm 2001: This experiment will test the feasibility of using a laser tocommunicate in space. A semiconductor laser module will be carried into space to see if itcan withstand a space environment of microgravity and radiation. The peak wavelength ofthe laser module will be characterized, along with the optical output power of the lasermodule and various electrical inputs before it goes into space and after it returns. Studentswill be looking for changes in the peak wavelength and optical output along with anydifferences in the transmissivity of the laser lens. (Mills Lawn Elementary School, YellowSprings, Ohio)

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

the seeds will be from the Cahokia Mounds Historical Site in Cahokia Mounds, Ill. Othertypes of seeds will include tomatoes, lettuce, beans, cucumbers, pumpkins and corn, someof them native to the Midwest area. The students will place the seeds in soil to see if theygrow. They will also place them in the hydroponics lab to see if they will grow. They willalso grow a control group of seeds that have not been up in space in soil and in thehydroponics lab. (Ellis School, Belleville, Ill.)

Stuck on Space: This team of experimenters consists of students in grades seventhrough nine from schools in three states. This experiment will explore how temperatureextremes, radiation and microgravity will affect adhesives. Commonly used adhesive-backed materials will be used to determine how these items will react in a microgravity

environment. Materials that may possibly be used on the International Space Station andon future space exploration missions will be used. (Suffield High School, Suffield, Conn.)

SCI-FIVE: Students from five schools will study the effects of the space environment on avariety of materials. Balls, Playdough, gum, seeds, Alka-Seltzer, exposed film, ink andteeth/braces will be tested after they have traveled in space to determine how radiation,temperature and microgravity may have affected them. (Anne Arundel County Schools,Anne Arundel County, Md.)

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Imaging Media and Radiation Shielding Experiment: Regina Science Club will conductboth of these experiments, which will be housed in one SEM module. The "Imaging Media"experiment will compare the ability of various consumer grade image storage media towithstand degradation due the SEM space flight environment. Several popular imagestorage media will be compared side-by-side, image-by-image comparisons with unflown

control media and with each other. The "Radiation Shielding Experiment" will test theeffectiveness of several radiation shielding strategies. At least 15 radiation dosimeters willbe placed in the SEM module. A duplicate control set of dosimeters, both shielded andunshielded, will be kept on the ground for the duration of the experiment to allow forcomparison of the levels of radiation in space to those on the ground. After the flight, allexperiment dosimeters will be returned to the manufacturer for developing. Themanufacturer will provide radiation exposure levels for each type of radiation measured foreach dosimeter. (Regina Catholic Education Center, Iowa City, Iowa)

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DTO/DSO/RME

Spatial Reorientation Following SpaceflightDSO 635

Overview

Spatial orientation is altered during and after spaceflight by a shift of central vestibularprocessing (from a gravitational frame-of-reference to an internal, head-centered frame-of-reference) that occurs during adaptation to microgravity and is reversed during the first fewdays after return to Earth. Discordant sensory stimuli during the postflight readaptive periodwill temporarily disorient/destabilize the subject by triggering a shift (state change) to thepreviously learned, internally referenced, microgravity-adapted pattern of spatial orientationand sensorimotor control.

History/Background

The purpose of this DSO is to examine both the adaptive changes in the spatial referenceframe used for coding spatial orientation and sensorimotor control as well as the fragility ofthe adaptive process and the feasibility of driving state changes in central vestibularprocessing via discordant sensory stimuli using balance control tests and eye movementresponses to pitch-axis rotation in a short-arm centrifuge. The findings are expected todemonstrate the degree to which challenging motion environments may affect postflightreadaptation and lead to a better understanding of safe postflight activity regimens. Thefindings are also expected to demonstrate the feasibility of triggering state changesbetween sensorimotor control sets using a centrifuge device.

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DTO/DSO/RME

Spaceflight and Immune FunctionDSO 498

Overview

Astronauts face an increasing risk of contracting infectious diseases as they work and livefor longer periods in the crowded conditions and closed environments of spacecraft such asthe International Space Station. The effects of spaceflight on the human immune system,which plays a pivotal role in warding off infections, is not fully understood. Understandingthe changes in immune functions caused by exposure to microgravity will allow researchersto develop countermeasures to minimize the risk of infection.

History/Background

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

monocytes and cytotoxic cells, which play an important role in maintaining an effectivedefense against infectious agents. The premise of this study is that the space environmentalters the essential functions of these elements of human immune response.

Researchers will conduct a functional analysis of neutrophils and monocytes from bloodsamples taken from astronauts before and after the flight. They will also assess thesubjects' pre- and postflight production of cytotoxic cells and cytokine.

This study will complement previous and continuing immunology studies of astronauts'adaptation to space.

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DTO/DSO/RME

Single-String Global Positioning SystemDTO 700-14

Overview

The purpose of the Single-String Global Positioning System (GPS) is to demonstrate theperformance and operation of the GPS during orbiter ascent, on-orbit, entry and landingphases using a modified military GPS receiver processor and the existing orbiter GPSantennas. GPS data may be downlinked during all mission phases.

History/Background

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

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DTO/DSO/RME

Space Vision Laser Camera SystemDTO 701

Overview

DTO 701 will demonstrate the capability of the Space Vision Laser Camera System(SVLCS) to accurately measure the position and attitude of objects in harsh lightingconditions and the ability of the SVLCS to act as an input sensor to the Orbiter SpaceVision System (OSVS).

The SVLCS consists of the Laser Camera Head (LCH), which will be mounted in thepayload bay, and the Laser Camera Controller (LCC), which will be in the aft flight deck.The LCH contains an eye-safe laser, projection and receiving optics, scanning optics,detectors and driver electronics. The scanning electronics in the LCH scan a 30- by 40-

degree field of view. It detects and tracks objects (satellites, payloads and structures) andprovides position and attitude information to the OSVS. The LCC is based on a standardpayload and general support computer. The LCH and LCC will be connected via Ethernet.

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DTO/DSO/RME

Crosswind Landing PerformanceDTO 805

Overview

The purpose of this DTO is to demonstrate the capability to perform a manually controlledlanding in the presence of a crosswind. The testing is done in two steps.

1. Prelaunch: Ensure planning will allow selection of a runway with MicrowaveScanning Beam Landing System support, which is a set of dual transmitterslocated beside the runway providing precision navigation vertically,horizontally and longitudinally with respect to the runway. This precisionnavigation subsystem helps provide a higher probability of a more preciselanding with a crosswind of 10 to 15 knots as late in the flight as possible.

2. Entry: This test requires that the crew perform a manually controlled landingin the presence of a 90-degree crosswind component of 10 to 15 knots steadystate.

During a crosswind landing, the drag chute will be deployed after nose gear touchdownwhen the vehicle is stable and tracking the runway centerline.

History/Background

This DTO has been manifested on 66 previous flights.

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STS-105Shuttle Reference Data

Shuttle Abort History

RSLS Abort History:(STS-41 D) June 26, 1984

The countdown for the second launch attempt for Discoverys maiden flight ended at T-4 seconds when the orbiters computers detected a sluggish valve in main engine #3.The main engine was replaced and Discovery was finally launched on August 30, 1984.

(STS-51 F) July 12, 1985

The countdown for Challengers launch was halted at T-3 seconds when on-boardcomputers detected a problem with a coolant valve on main engine #2. The valve wasreplaced and Challenger was launched on July 29, 1985.

(STS-55) March 22, 1993

The countdown for Columbias launch was halted by on-board computers at T-3seconds following a problem with purge pressure readings in the oxidizer preburner onmain engine #2 Columbias three main engines were replaced on the launch pad, andthe flight was rescheduled behind Discoverys launch on STS-56. Columbia finallylaunched on April 26, 1993.

(STS-51) August 12, 1993

The countdown for Discoverys third launch attempt ended at the T-3 second markwhen on-board computers detected the failure of one of four sensors in main engine #2

which monitor the flow of hydrogen fuel to the engine. All of Discoverys main engineswere ordered replaced on the launch pad, delaying the Shuttles fourth launch attemptuntil September 12, 1993.

(STS-68) August 18, 1994

The countdown for Endeavours first launch attempt ended 1.9 seconds before liftoffwhen on-board computers detected higher than acceptable readings in one channel of asensor monitoring the discharge temperature of the high pressure oxidizer turbopump inmain engine #3. A test firing of the engine at the Stennis Space Center in Mississippi onSeptember 2nd confirmed that a slight drift in a fuel flow meter in the engine caused a

slight increase in the turbopumps temperature. The test firing also confirmed a slightlyslower start for main engine #3 during the pad abort, which could have contributed tothe higher temperatures. After Endeavour was brought back to the Vehicle AssemblyBuilding to be outfitted with three replacement engines, NASA managers set October2nd as the date for Endeavours second launch attempt.

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STS-105Abort to Orbit History:

(STS-51 F) July 29, 1985

After an RSLS abort on July 12, 1985, Challenger was launched on July 29, 1985. Fiveminutes and 45 seconds after launch, a sensor problem resulted in the shutdown ofcenter engine #1, resulting in a safe "abort to orbit" and successful completion of themission.

Updated: 05/22/2001

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Shuttle Abort Modes

RSLS ABORTSThese occur when the onboard shuttle computers detect a problem and command a halt inthe launch sequence after taking over from the Ground Launch Sequencer and before SolidRocket Booster ignition.

ASCENT ABORTS

Selection of an ascent abort mode may become necessary if there is a failure that affectsvehicle performance, such as the failure of a space shuttle main engine or an orbitalmaneuvering system. Other failures requiring early termination of a flight, such as a cabinleak, might also require the selection of an abort mode.

There are two basic types of ascent abort modes for space shuttle missions: intact abortsand contingency aborts. Intact aborts are designed to provide a safe return of the orbiter toa planned landing site. Contingency aborts are designed to permit flight crew survivalfollowing more severe failures when an intact abort is not possible. A contingency abortwould generally result in a ditch operation.

INTACT ABORTS

There are four types of intact aborts: abort to orbit (ATO), abort once around (AOA),transoceanic abort landing (TAL) and return to launch site (RTLS).

Return to Launch Site

The RTLS abort mode is designed to allow the return of the orbiter, crew, and payload tothe launch site, Kennedy Space Center, approximately 25 minutes after lift-off.

The RTLS profile is designed to accommodate the loss of thrust from one space shuttlemain engine between lift-off and approximately four minutes 20 seconds, at which time notenough 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 thespace 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 poweredRTLS 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 rotaryswitch to RTLS and depressing the abort push button. The time at which the RTLS isselected depends on the reason for the abort. For example, a three-engine RTLS isselected 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 boosterseparation).

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STS-105After RTLS is selected, the vehicle continues downrange to dissipate excess mainpropulsion system propellant. The goal is to leave only enough main propulsion systempropellant to be able to turn the vehicle around, fly back towards the Kennedy SpaceCenter and achieve the proper main engine cutoff conditions so the vehicle can glide to theKennedy 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 shuttlemain 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 launchsite, but the space shuttle main engines are now thrusting to null the downrange velocity. Inaddition, excess orbital maneuvering system and reaction control system propellants aredumped by continuous orbital maneuvering system and reaction control system enginethrustings to improve the orbiter weight and center of gravity for the glide phase andlanding.

The vehicle will reach the desired main engine cutoff point with less than 2 percent excesspropellant 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 requiredexternal tank separation attitude and pitch rate. After main engine cutoff has beencommanded, the external tank separation sequence begins, including a reaction controlsystem translation that ensures that the orbiter does not recontact the external tank andthat the orbiter has achieved the necessary pitch attitude to begin the glide phase of theRTLS.

After the reaction control system translation maneuver has been completed, the glidephase of the RTLS begins. From then on, the RTLS is handled similarly to a normal entry.

Transoceanic Abort Landing

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

main engine fails after the last RTLS opportunity but before the first time that an AOA canbe accomplished with only two space shuttle main engines or when a major orbiter systemfailure, for example, a large cabin pressure leak or cooling system failure, occurs after thelast 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 toland 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 tomake the most efficient use of space shuttle main engine propellant. The landing site alsomust have the necessary runway length, weather conditions and U.S. State Departmentapproval. 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/AOAposition and depress the abort push button before main engine cutoff. (Depressing it aftermain engine cutoff selects the AOA abort mode.) The TAL abort mode begins sendingcommands to steer the vehicle toward the plane of the landing site. It also rolls the vehicleheads up before main engine cutoff and sends commands to begin an orbital maneuveringsystem propellant dump (by burning the propellants through the orbital maneuvering

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STS-105system engines and the reaction control system engines). This dump is necessary toincrease vehicle performance (by decreasing weight), to place the center of gravity in theproper place for vehicle control, and to decrease the vehicle's landing weight.

TAL is handled like a nominal entry.

Abort to Orbit

An ATO is an abort mode used to boost the orbiter to a safe orbital altitude whenperformance has been lost and it is impossible to reach the planned orbital altitude. If aspace 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 informthe crew. The orbital maneuvering system engines would be used to place the orbiter in acircular orbit.

Abort Once Around

The AOA abort mode is used in cases in which vehicle performance has been lost to suchan extent that either it is impossible to achieve a viable orbit or not enough orbitalmaneuvering system propellant is available to accomplish the orbital maneuvering systemthrusting maneuver to place the orbiter on orbit and the deorbit thrusting maneuver. Inaddition, an AOA is used in cases in which a major systems problem (cabin leak, loss ofcooling) makes it necessary to land quickly. In the AOA abort mode, one orbitalmaneuvering system thrusting sequence is made to adjust the post-main engine cutoff orbitso a second orbital maneuvering system thrusting sequence will result in the vehicledeorbiting and landing at the AOA landing site (White Sands, N.M.; Edwards Air ForceBase; or the Kennedy Space Center). Thus, an AOA results in the orbiter circling the Earthonce and landing approximately 90 minutes after lift-off.

After the deorbit thrusting sequence has been executed, the flight crew flies to a landing atthe planned site much as it would for a nominal entry.

CONTINGENCY ABORTS

Contingency aborts are caused by loss of more than one main engine or failures in othersystems. Loss of one main engine while another is stuck at a low thrust setting may alsonecessitate a contingency abort. Such an abort would maintain orbiter integrity for in-flightcrew escape if a landing cannot be achieved at a suitable landing field.

Contingency aborts due to system failures other than those involving the main engineswould normally result in an intact recovery of vehicle and crew. Loss of more than one mainengine 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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STS-105ABORT DECISIONS

There is a definite order of preference for the various abort modes. The type of failure andthe time of the failure determine which type of abort is selected. In cases whereperformance loss is the only factor, the preferred modes would be ATO, AOA, TAL andRTLS, 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 coolingproblems, the preferred mode might be the one that will end the mission most quickly. Inthese cases, TAL or RTLS might be preferable to AOA or ATO. A contingency abort isnever chosen if another abort option exists.

The Mission Control Center-Houston is prime for calling these aborts because it has a moreprecise 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 themwhich abort mode is (or is not) available. If ground communications are lost, the flight crewhas onboard methods, such as cue cards, dedicated displays and display information, todetermine the current abort region.

Which abort mode is selected depends on the cause and timing of the failure causing theabort and which mode is safest or improves mission success. If the problem is a spaceshuttle main engine failure, the flight crew and Mission Control Center select the bestoption 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 thatresults in the earliest vehicle landing is chosen. RTLS and TAL are the quickest options (35minutes), whereas an AOA requires approximately 90 minutes. Which of these is selecteddepends 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 depressingan abort push button.

Updated: 05/22/2001

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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 arendezvous phasing burn

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

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 thetarget at a future time

NCC (Rendezvous corrective combination) - First on-board targeted burn in therendezvous sequence. Using star tracker data, it is performed to remove phasing andheight errors relative to the target at Ti

Ti (Rendezvous terminal intercept) - Second on-board targeted burn in therendezvous 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 targetedburns use star tracker and rendezvous radar data to correct the post-Ti trajectory inpreparation for the final, manual proximity operations phase

Updated: 05/22/2001

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Space Shuttle Solid Rocket Boosters

The two SRBs provide the main thrust to lift the space shuttle off the pad and up to analtitude of about 150,000 feet, or 24 nautical miles (28 statute miles). In addition, the twoSRBs carry the entire weight of the external tank and orbiter and transmit the weight loadthrough their structure to the mobile launcher platform.

Each booster has a thrust (sea level) of approximately 3,300,000 pounds at launch. Theyare ignited after the three space shuttle main engines' thrust level is verified. The two SRBsprovide 71.4 percent of the thrust at lift- off and during first-stage ascent. Seventy- fiveseconds after SRB separation, SRB apogee occurs at an altitude of approximately 220,000feet, or 35 nautical miles (40 statute miles). SRB impact occurs in the ocean approximately122 nautical miles (140 statute miles) downrange.

The SRBs are the largest solid-propellant motors ever flown and the first designed forreuse. 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 solidrocket motor weighs approximately 1,100,000 pounds. The inert weight of each SRB isapproximately 192,000 pounds.

Primary elements of each booster are the motor (including case, propellant, igniter andnozzle), structure, separation systems, operational flight instrumentation, recovery avionics,pyrotechnics, deceleration system, thrust vector control system and range safety destructsystem.

Each booster is attached to the external tank at the SRBs aft frame by two lateral swaybraces and a diagonal attachment. The forward end of each SRB is attached to theexternal tank at the forward end of the SRBs forward skirt. On the launch pad, eachbooster also is attached to the mobile launcher platform at the aft skirt by four bolts andnuts that are severed by small explosives at lift-off.

During the downtime following the Challenger accident, detailed structural analyses wereperformed on critical structural elements of the SRB. Analyses were primarily focused inareas 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 SRBmotor case. This situation was attributed to the high loads encountered during waterimpact. To correct the situation and ensure higher strength margins during ascent, theattach 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-105Additionally, special structural tests were performed on the aft skirt. During this testprogram, an anomaly occurred in a critical weld between the hold-down post and skin ofthe skirt. A redesign was implemented to add reinforcement brackets and fittings in the aftring 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), apolymer (a binder that holds the mixture together, 12.04 percent), and an epoxy curingagent (1.96 percent). The propellant is an 11-point star-shaped perforation in the forwardmotor segment and a double-truncated-cone perforation in each of the aft segments and aftclosure. This configuration provides high thrust at ignition and then reduces the thrust byapproximately a third 50 seconds after lift-off to prevent overstressing the vehicle duringmaximum 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 fromthe same batches of propellant ingredients to minimize any thrust imbalance. Thesegmented-casing design assures maximum flexibility in fabrication and ease oftransportation and handling. Each segment is shipped to the launch site on a heavy-dutyrail 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 ownredundant auxiliary power units and hydraulic pumps. The all-axis gimbaling capability is 8degrees. Each nozzle has a carbon cloth liner that erodes and chars during firing. Thenozzle 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 launcherplatform. The four aft separation motors are mounted on the skirt. The aft section containsavionics, a thrust vector control system that consists of two auxiliary power units andhydraulic pumps, hydraulic systems and a nozzle extension jettison system.

The forward section of each booster contains avionics, a sequencer, forward separationmotors, a nose cone separation system, drogue and main parachutes, a recovery beacon,a recovery light, a parachute camera on selected flights and a range safety system.

Each SRB has two integrated electronic assemblies, one forward and one aft. Afterburnout, the forward assembly initiates the release of the nose cap and frustum and turnson 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 ignitioncommands and nozzle thrust vector control. Each integrated electronic assembly has amultiplexer/ demultiplexer, which sends or receives more than one message, signal or unitof information on a single communication channel.

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STS-105Eight booster separation motors (four in the nose frustum and four in the aft skirt) of eachSRB thrust for 1.02 seconds at SRB separation from the external tank. Each solid rocketseparation motor is 31.1 inches long and 12.8 inches in diameter.

Location aids are provided for each SRB, frustum/drogue chutes and main parachutes.These include a transmitter, antenna, strobe/converter, battery and salt water switchelectronics. The location aids are designed for a minimum operating life of 72 hours andwhen 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. Thenozzles are plugged, the solid rocket motors are dewatered, and the SRBs are towed backto the launch site. Each booster is removed from the water, and its components aredisassembled and washed with fresh and deionized water to limit salt water corrosion. Themotor 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 postson the mobile launcher platform. Hold-down bolts hold the SRB and launcher platformposts together. Each bolt has a nut at each end, but only the top nut is frangible. The topnut contains two NASA standard detonators, which are ignited at solid rocket motor ignitioncommands.

When the two NSDs are ignited at each hold-down, the hold-down bolt travels downwardbecause of the release of tension in the bolt (pretensioned before launch), NSD gaspressure and gravity. The bolt is stopped by the stud deceleration stand, which containssand. The SRB bolt is 28 inches long and is 3.5 inches in diameter. The frangible nut iscaptured in a blast container.

The solid rocket motor ignition commands are issued by the orbiter''s computers throughthe master events controllers to the hold-down pyrotechnic initiator controllers on themobile launcher platform. They provide the ignition to the hold-down NSDs. The launchprocessing system monitors the SRB hold-down PICs for low voltage during the last 16seconds 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 devicehas been removed. The ground crew removes the pin during prelaunch activities. At Tminus five minutes, the SRB safe and arm device is rotated to the arm position. The solidrocket 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 andthere are no holds from the LPS.

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STS-105The solid rocket motor ignition commands are sent by the orbiter computers through theMECs to the safe and arm device NSDs in each SRB. A PIC single-channel capacitordischarge device controls the firing of each pyrotechnic device. Three signals must bepresent simultaneously for the PIC to generate the pyro firing output. These signals--arm,fire 1 and fire 2--originate in the orbiter general-purpose computers and are transmitted to

the MECs. The MECs reformat them to 28-volt dc signals for the PICs. The arm signalcharges 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 aflame tunnel. This ignites a pyro booster charge, which is retained in the safe and arm devicebehind 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 firesdown 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 andmonitors the engine-ready indications from the SSMEs. The MPS start commands areissued 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 sequencemonitors 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 andsafing functions are initiated.

Normal thrust buildup to the required 90-percent thrust level will result in the SSMEs beingcommanded to the lift-off position at T minus three seconds as well as the fire 1 commandbeing issued to arm the SRBs. At T minus three seconds, the vehicle base bending loadmodes are allowed to initialize (movement of approximately 25.5 inches measured at the tipof the external tank, with movement towards the external tank).

At T minus zero, the two SRBs are ignited, under command of the four onboard computers;separation of the four explosive bolts on each SRB is initiated (each bolt is 28 inches longand 3.5 inches in diameter); the two T-0 umbilicals (one on each side of the spacecraft) areretracted; 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 maximumdynamic 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 dcbus power to corresponding SRB buses A, B and C. In addition, orbiter main dc bus Csupplies backup power to SRB buses A and B, and orbiter bus B supplies backup power toSRB bus C. This electrical power distribution arrangement allows all SRB buses to remainpowered 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 of24 volts dc.

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STS-105HYDRAULIC POWER UNITS

There are two self-contained, independent HPUs on each SRB. Each HPU consists of anauxiliary power unit, fuel supply module, hydraulic pump, hydraulic reservoir and hydraulicfluid manifold assembly. The APUs are fueled by hydrazine and generate mechanical shaftpower 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 SRBbetween the SRB nozzle and aft skirt. The HPU components are mounted on the aft skirtbetween the rock and tilt actuators. The two systems operate from T minus 28 secondsuntil SRB separation from the orbiter and external tank. The two independent hydraulicsystems are connected to the rock and tilt servoactuators.

The APU controller electronics are located in the SRB aft integrated electronic assemblieson 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 nitrogenat 400 psi, which provides the force to expel (positive expulsion) the fuel from the tank tothe fuel distribution line, maintaining a positive fuel supply to the APU throughout itsoperation.

The fuel isolation valve is opened at APU startup to allow fuel to flow to the APU fuel pumpand control valves and then to the gas generator. The gas generator's catalytic actiondecomposes the fuel and creates a hot gas. It feeds the hot gas exhaust product to theAPU two-stage gas turbine. Fuel flows primarily through the startup bypass line until theAPU 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 pumplubricates the gearbox. The turbine exhaust of each APU flows over the exterior of the gasgenerator, 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 theAPU speed is controlled by the APU controller electronics. If the primary control valve logicfails 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 servesas 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 thatallows the secondary hydraulics to power the actuator if the primary hydraulic pressuredrops below 2,050 psi. A switch contact on the switching valve will close when the valve isin the secondary position. When the valve is closed, a signal is sent to the APU controllerthat inhibits the 100-percent APU speed control logic and enables the 112-percent APUspeed control logic. The 100-percent APU speed enables one APU/HPU to supplysufficient operating hydraulic pressure to both servoactuators of that SRB.

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STS-105The APU 100-percent speed corresponds to 72,000 rpm, 110-percent to 79,200 rpm, and112-percent to 80,640 rpm.

The hydraulic pump speed is 3,600 rpm and supplies hydraulic pressure of 3,050, plus orminus 50, psi. A high-pressure relief valve provides overpressure protection to the hydraulicsystem 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. Theservoactuators provide the force and control to gimbal the nozzle for thrust vector control.

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NASA Space Shuttle STS-105 Press Kit

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