nasa space shuttle sts-106 press kit

8/14/2019 NASA Space Shuttle STS-106 Press Kit

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A T L A N T I S

R E T U R N ST O T H E

S P A C E S T A T I O N

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Table of Contents

Mission Index ................................................................................................................1

Mission Overview .........................................................................................................4

Mission Objectives .....................................................................................................11

Crew .............................................................................................................................14

Flight Day Summary Timeline ...................................................................................17

EVAs

STS-106 EVA ..............................................................................................................18

Payloads

Spacehab Logistics Double Module ............................................................................21

Integrated Cargo Carrier ..............................................................................................22

Commercial Generic Bioprocessing Apparatus ...........................................................23

Getaway Special G-782 ...............................................................................................26

Space Experiment Module 8 ........................................................................................29

Experiments

HTD 1403 Micro Wireless Instrumentation System (Micro WIS)

HEDS Technology Demonstration .............................................................32Protein Crystal Growth (PCG) Enhanced Gaseous Nitrogen (EGN) Dewar ................ 34

DTO/DSO/RME

DTO 700-14 Single-String Global Positioning System .................................................36

DTO 700-21 SIGI Orbital Attitude Readiness ..............................................................37

DTO 805 Crosswind Landing Performance .................................................................38

DSO 493 Monitoring Latent Virus Reactivation and Shedding in Astronauts

Using Saliva Kits ..........................................................................................39DSO 496 Individual Susceptibility to Postflight Orthostatic Intolerance (Tilt Test) ....... 40

DSO 498 Space Flight and Immune Function .............................................................41

DSO 499 Eye Movements and Motion Perception Induced by Off-Vertical-AxisRotation (OVAR) at Small Angles of Tilt After Space Flight .........................42


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Shuttle Reference and Data

Shuttle Abort Modes ....................................................................................................43

Space Shuttle Rendezvous Maneuvers .......................................................................48

Space Shuttle Solid Rocket Boosters ..........................................................................49

Space Shuttle Super-Lightweight Tank (SLWT) ..........................................................57

Mission Benefits ........................................................................................................58

Media Assistance ......................................................................................................61

Contacts .....................................................................................................................63


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Atlantis OV104Launch: Friday, September 08, 2000

8:45 AM (eastern time)

CrewCommander: Terrence WilcuttPilot: Scott D. AltmanMission Specialist 1: Edward T. LuMission Specialist 2: Richard A. MastracchioMission Specialist 3: Daniel C. BurbankMission Specialist 4: Yuri I. MalenchenkoMission Specialist 5: Boris V. MorukovLaunchOrbiter: Atlantis OV104Launch Site: Kennedy Space Center Launch Pad 39BLaunch Window: 2.5 MinutesAltitude: 173 Nautical Miles, 199 Statute MilesInclination: 51.6 DegreesDuration: 10 Days 19 Hrs. 9 Min.

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Vehicle DataShuttle Liftoff Weight: 4519645 lbs.Orbiter/Payload Liftoff Weight: 254099 lbs.Orbiter/Payload Landing Weight: 221271 lbs.Payload WeightsICC 4,528 pounds (ICC plus cargo)LDM 18,000 pounds

Software Version: OI-27Space Shuttle Main Engines:(1 MB pdf)SSME 1: 2052 SSME 2: 2044 SSME 3: 2047External Tank: ET-103ASRB Set: BI-102PF/RSRM-75

Shuttle AbortsAbort Landing Sites

RTLS: Kennedy Space Center Shuttle Landing FacilityTAL: ZaragozaAOA: Edwards Air Force Base, California

LandingLanding Date: 09/19/00Landing Time: 3:54 AM (eastern time)Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

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PayloadsCargo BaySpace Experiment Module 8Getaway Special G-782Spacehab Logistics Double ModuleIn-CabinCommercial Generic Bioprocessing Apparatus (CGBA)

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Mission Overview

Atlantis Returns to the International Space Station

Atlantis returns to the International Space Station (ISS) for the second time in fourmonths on NASAs third Shuttle flight of the year to complete outfitting of the firsthome in space for the first crew of the rapidly expanding facility.

Five American astronauts and two Russian cosmonauts are set to launch on the STS-106 mission no earlier than September 8 at 8:45 a.m. EDT from Launch Pad 39-B atthe Kennedy Space Center, Florida. It will be Atlantis 22nd mission and the 99thflight in Shuttle program history.

Veteran Astronaut Terry Wilcutt (Col., USMC) leads the seven-man crew,commanding his second Shuttle flight and making his fourth trip into space. Duringthe planned 11-day mission, Wilcutt and his crewmates will spend a week inside theISS unloading supplies from both a double Spacehab cargo module in the rear ofAtlantis cargo bay and from a Russian Progress M-1 resupply craft docked to the aftend of the Zvezda Service Module. Zvezda, which linked up to the ISS on July 26,will serve as the early living quarters for the station and is the cornerstone of theRussian contribution to the ISS.

The goal of the flight is to prepare Zvezda for the arrival of the first resident, orExpedition, crew later this fall and the start of a permanent human presence on thenew outpost. That crew, Expedition Commander Bill Shepherd, Soyuz CommanderYuri Gidzenko and Flight Engineer Sergei Krikalev, is due to launch in a Soyuzcapsule from the Baikonur Cosmodrome in Kazakhstan in late October for a four-month "shakedown" mission aboard the ISS.

In addition, Dr. Ed Lu and Yuri Malenchenko (Col., Russian Air Force), both makingtheir second flights into space, will conduct a 6 -hour space walk on the fourth day ofthe flight to hook up electrical, communications and telemetry cables between Zvezdaand the Zarya Control Module, whose computers handed over commanding functionsto the Service Modules computers in a smooth transition in late July. Lu andMalenchenko will also install a magnetometer to the exterior of Zvezda. Themagnetometer will serve as a three-dimensional compass designed to minimizeZvezda propellant usage by relaying information to the modules computers regarding

its orientation relative to the Earth.

It will be the second joint U.S.-Russian space walk outside a Space Shuttle, followingon the work conducted by Astronaut Scott Parazynski and Cosmonaut Vladimir Titovoutside Atlantis while docked to the Mir Space Station during the STS-86 mission inOctober 1997. Lu, designated EV 1, will wear the space suit marked by red stripes,while Malenchenko, EV 2, will wear the pure white suit.

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This will be Lus first space walk, while Malenchenkoconducted a pair of space walks totaling 12 hours duringhis four-month stay aboard Mir in 1994. Dan Burbank (Lt.Cmdr, USCG), who is a space rookie, will serve as thespace walk choreographer.

Mission Specialist Rick Mastracchio, also a space novice,will be the prime robot arm operator for the mission, using

the Canadian-built arm to move Lu and Malenchenko around the ISS as they conducttheir assembly work. Mastracchio is backed up on arm operations by Pilot ScottAltman (Cmdr., USN), making his second flight into space.

The final member of the crew is Russian Cosmonaut Dr. Boris Morukov, making hisfirst flight into space. Morukov will be responsible for unloading supplies from theProgress vehicle during the docked phase of the flight.

When Wilcutt guides Atlantis in for its docking with the ISS on the third day of themission, he will find the new station a much larger facility than the one left by theSTS-101 crew during its flight in May. With the addition of the Zvezda and theProgress resupply ship, the ISS will measure 143 feet in length, roughly the height ofa 13-story building, and will weigh 67 tons, twice the size of the ISS back in May. The

joining of Zvezda to the ISS and the arrival of the Progress provides about 8,800cubic feet of habitable volume for Station crew members, roughly the size of acomfortable apartment. By the time the U.S. Laboratory Destiny is installed on theISS in January, the Station will have surpassed both Skylab and Mir in total livablespace.

On the fifth day of the flight, Atlantis crew will enter the ISS, opening the hatch for thefirst time to Zvezda and to the Progress to begin unloading 1,300 pounds of goodsfrom the Russian craft for the first resident crew, including items ranging from clothingto medical kits, personal hygiene kits, laptop computers, a color printer, vacuumcleaners, food warmers for Zvezdas galley, trash bags and critical life supporthardware, including an Elektron oxygen generation unit and a Vozdukh carbondioxide removal unit. Elektron and Vozdukh will be unstowed from the Progress andmoved into Zvezda, but will not be installed and activated until the Expedition Onecrew arrives on board. The first toilet for the ISS will be delivered to Zvezda on thelast day of the crews work inside the Station for installation this fall once theExpedition 1 crew is on board.

Among the first tasks facing Atlantis crew will be the installation of three batteries andassociated electronic components in Zvezda and replacement of two of the sixbatteries in the Zarya module, completing the work begun by the STS-101 crew inMay. Zvezda was launched from Baikonur on July 12 with five of its eight battery setsalready installed. Lu and Malenchenko will be in charge of the installation work inZvezda. Also earmarked for Zvezda is the activation of two gas masks, which willserve as standard emergency equipment for ISS crews and three fire extinguishers.

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In addition, American-Russian power conversion units will be installed in Zvezda onthis flight to route electricity from huge solar arrays which will be installed on the STS-97 mission to the Russian modules. Electrical components to charge the batteries ofSoyuz or Progress vehicles visiting the ISS will be installed in Zvezda as well.

While Morukov spends most of his time unloading supplies from the Progress,Mastracchio will be in charge of unloading 2 tons of equipment from the Spacehabmodule, including medical equipment for the ISS Crew Health Care System, orCheCS, which will serve as the heart of the stations clinic for orbiting crews, and atreadmill device and bicycle ergometer which will serve as the first exercise gear forcrews on board the ISS. Associated hardware for the treadmill which will prevent itsuse from disturbing sensitive microgravity experiments, will be installed by thecrewmembers near the end of their stay on board.

On the tenth day of the flight, Atlantis will undock from the ISS and Altman willconduct a flyaround of the newly expanded station to enable his crewmates to

conduct photo documentation of the outpost.

Two days later, Wilcutt will fly Atlantis to a predawn landing at the Kennedy SpaceCenter, setting the stage a few days later for the launch of a second RussianProgress ship to the Station and a plethora of Shuttle assembly flights to turn thecomplex into a working research facility.

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International Space Station Assembly Sequence:Revision F (August 2000)Date Flight LaunchVehicle Element(s)Nov. 20, 1998 1A/R Russian Proton Zarya Control Module

(Functional Cargo Block - FGB)

Dec. 4, 1998 2A U.S. OrbiterSTS-88

Unity Node (1 Stowage Rack) 2 Pressurized Mating Adapters attached to Unity

May 27, 1999 2A.1 U.S. OrbiterSTS-96

SPACEHAB - Logistics Flight

May 19, 2000 2A.2a U.S. OrbiterSTS-101 SPACEHAB - Maintenance Flight

July 12, 2000 1R Russian Proton Zvezda Service ModuleSept. 8, 2000 2A.2b U.S. Orbiter

STS-106 SPACEHAB - Logistics Flight

Oct. 5, 2000 3A U.S. OrbiterSTS-92

Integrated Truss Structure (ITS) Z1

Pressurized Mating Adapter - 3

Ku-band Communications System Control Moment Gyros (CMGs)

Oct. 30, 2000 2R Russian Soyuz Soyuz Expedition 1 Crew

Nov. 30, 2000 4A U.S. OrbiterSTS-97 Integrated Truss Structure P6 Photovoltaic Module

Radiators

Jan. 18, 2001 5A U.S. OrbiterSTS-98

Destiny Laboratory Module

Feb. 15, 2001 5A.1 U.S. OrbiterSTS-102

Logistics and Resupply; Lab Outfitting

Leonardo Multi-Purpose Logistics Module (MPLM)carries equipment racks

March 2001 4R Russian Soyuz Docking Compartment 1 (DC-1) Strela Boom

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Date Flight LaunchVehicle Element(s)April 19, 2001 6A U.S. Orbiter

STS-100 Rafaello Multi-Purpose Logistics Module (MPLM)(Lab outfitting) Ultra High Frequency (UHF) antenna

Space Station Remote Manipulator System(SSRMS)

May 17, 2001 7A U.S. OrbiterSTS-104

Joint Airlock High Pressure Gas Assembly

June 21, 2001 7A.1 U.S. OrbiterSTS-105 Donatello Multi-Purpose Logistics Module (MPLM)

Oct. 4, 2001 UF-1 U.S. OrbiterSTS-109

Multi-Purpose Logistics Module (MPLM)

Photovoltaic Module batteries

Spares Pallet (spares warehouse)

Jan. 2002 8A U.S. Orbiter Central Truss Segment (ITS S0)

Mobile Transporter (MT)

Feb. 2002 UF-2 U.S. Orbiter Multi-Purpose Logistics Module (MPLM) withpayload racks

Mobile Base System (MBS)

May 2002 9A U.S. Orbiter First right-side truss segment (ITS S1) withradiators

Crew & Equipment Translation Aid (CETA) Cart A

June 2002 ULF1 U.S. Orbiter Utilization and Logistics FlightOct. 2002 11A U.S. Orbiter First left-side truss segment (ITS P1)

Crew & Equipment Translation Aid (CETA) Cart B

Oct. 2002 9A.1 U.S. Orbiter Russian provided Science Power Platform (SPP)with four solar arrays

Dec. 2002 12A U.S. Orbiter Second left-side truss segment (ITS P3/P4) Solar array and batteries

Feb. 2003 12A.1 U.S. Orbiter Third left-side truss segment (ITS P5) Logistics and Supplies

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Date Flight LaunchVehicle Element(s)April 2003 13A U.S. Orbiter Second right-side truss segment (ITS S3/S4)

Solar array set and batteries (Photovoltaic Module)

June 2003 13A.1 U.S. Orbiter Logistics and SuppliesAug. 2003 3R Russian Proton Universal Docking Module (UDM)Aug. 2003 5R Russian Soyuz Docking Compartment 2 (DC2)Oct. 2003 UF-4 U.S. Orbiter Express Pallet

Spacelab Pallet carrying "Canada Hand" (SpecialPurpose Dexterous Manipulator)

Nov. 2003 10A U.S. Orbiter US Node 2Feb. 2004 1J/A U.S. Orbiter Japanese Experiment Module Experiment

Logistics Module (JEM ELM PS)

Science Power Platform (SSP) solar arrays withtruss

April 2004 ATV European Automated Transfer VehicleMay 2004 1J U.S. Orbiter Kibo Japanese Experiment Module (JEM)

Japanese Remote Manipulator System (JEM RMS)

June 2004 10A.1 U.S. Orbiter Propulsion ModuleSept. 2004 UF-3 U.S. Orbiter Multi-Purpose Logistics Module (MPLM)

Express Pallet

Oct. 2004 1E U.S. Orbiter European Laboratory - Columbus ModuleJan. 2005 2J/A U.S. Orbiter Japanese Experiment Module Exposed Facility

(JEM EF)

Solar Array Batteries Cupola

Feb. 2005 UF-5 U.S. Orbiter Multi-Purpose Logistics Module (MPLM) Express Pallet

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Date Flight LaunchVehicle Element(s)TBD 9R Russian Proton Docking and Stowage Module (DSM)May 2005 14A U.S. Orbiter Science Power Platform (SPP) Solar Arrays

Zvezda Micrometeroid and Orbital Debris (MMOD)Shields

June 2005 UF-6 U.S. Orbiter Multi-Purpose Logistics Module (MPLM) Batteries

July 2005 20A U.S. Orbiter US Node 3Aug. 2005 8R Russian Soyuz Research Module 1Sept. 2005 16A U.S. Orbiter Habitation ModuleOct. 2005 17A U.S. Orbiter Multi-Purpose Logistics Module (MPLM)

Destiny racks

Dec. 2005 18A U.S. Orbiter Crew Return Vehicle (CRV)Jan. 2006 19A U.S. Orbiter Multi-Purpose Logistics Module (MPLM)March 2006 15A U.S. Orbiter Solar Arrays and Batteries (Photovoltaic Module

S6)

March 2006 10R Russian Soyuz Research Module 2April 2006 UF-7 U.S. Orbiter Centrifuge Accommodation Module (CAM)

Notes: Additional Progress, Soyuz, H-II Transfer Vehicle and Automated Transfer Vehicle flights for

crew transport, logistics and resupply are not listed.

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Mission Objectives

Primary ObjectiveAmong priority tasks to be completed during the STS-106 mission of Atlantis tothe International Space Station are:

--Changing Zvezda, the Service Module, from launch to flight configuration byinstalling six ground repressurization inlet caps, removing fire extinguisherlaunch restraint bolts and activating gas masks in the module for the Expedition1 crew.

--Logistics activities, including unloading the Progress cargo vessel into the ISSand transferring equipment, supplies and water from the shuttle to the ISS.

--Removing the TORU docking unit and the aft docking probe from the Zaryamodule.

--Replacing two batteries on Zarya and installing three batteries and associatedelectronic equipment on the Zvezda, installing voltage converters in the Zvezdaand performing other electrical system work in that module.

--A spacewalk to connect power, data and communications cables between theZvezda and Zarya, and install a magnetometer.

--Installation of a treadmill and related equipment.

--Air monitoring tasks, formaldehyde monitoring, replace and return threepassive dosimeters in Unity and install four others in the Zvezda, as well asperforming acoustic measurements in the Zvezda.

--Testing of the Space Integrated Global Positioning System/Internal NavigationSystem (SIGI).

--Installation of the toilet in the Zvezda.

--Performing ISS reboost with Atlantis and a shuttle flyaround of the ISS, both if

propellant is available.

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Progress Overview

During STS-106, the astronauts will transfer logistical material from the Progress supplyvehicle to the ISS.

The Progress is an automated version of the Soyuz, and was developed to carrypropellant and cargo to the Salyut and Mir space station. It will serve the same purposefor the ISS. Although ISS has its own propulsion system, generally it is the Progressvehicle that will perform periodic reboost maneuvers to maintain the ISS orbital altitude.

The Progress is approximately the same size as the Soyuz, but it has a slightly highermass at launch of approximately 7150 kg. The Progress spacecraft docks automaticallyto the ISS, and the TORU system acts as a backup remote control docking system.

The Progress is composed of three modules: the Cargo Module, the Refueling Module,

and the Instrument/Propulsion Module.

A modified version of the Progress M, called the Progress M1, is planned for operationwith the ISS. This version will have more propellant tanks for refueling, as the entireRefueling Module is devoted to fuel. Water will be carried in the Cargo Module.

The Progress payload includes cargo in the pressurized Cargo Module and propellant inthe Refueling Module. Excess propellant that is usually in the propulsion system tanksin the Instrumentation/ Propulsion Module can also be used by the ISS.

The table below summarizes the approximate payload capacity of the Progress vehicle.

Category Progress M Progress M1

Total payload limit (kg) 2350 2230 - 3200

Maximum pressurized cargo (kg) 1800 1800

Maximum water (kg) 420 In Cargo Module

Maximum air or oxygen (kg) 50 40

Maximum Refueling Module propellant (kg) 850 1700

Propellant surplus available to ISS (kg) 250 185 - 250

Trash disposal in Cargo Module (kg) 1000 - 1600 1000 - 1600

Wastewater (kg) 400 In Cargo Module

Cargo volume (m 3 ) 6.6 6.6

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The relative amounts of pressurized cargo, refueling propellant, air, and water will varywithin the constraints of the total payload limit. For example, if the maximum amount ofpropellant is carried, the amount of pressurized cargo will be less than the maximumamount. The payload masses for Progress M1 will increase within the ranges shown asimprovements are made to the Soyuz launch vehicle. The lowest value corresponds to

the capability with the current Soyuz launcher.

Cargo Module

The Progress Cargo Module is similar in construction to the Soyuz Orbital Module. TheCargo Module carries pressurized cargo that the crew transfers into the ISS through thedocking hatch. After the Cargo Module is unloaded, trash, unwanted equipment, andwastewater can be loaded into the Progress for disposal when the spacecraft leaves theISS.

Refueling Module

In place of the Soyuz Descent Module, the Progress has a module containing propellanttanks. The Progress is able to transfer propellant into the ISS propulsion systemthrough fluid connectors in the docking ring. The propellant in the Refueling Module canalso be used by the thrusters on the Progress vehicle for controlling and reboosting theISS. The Progress M has four propellant tanks (two each for fuel and oxidizer) and twowater tanks. The Progress M1 will have eight propellant tanks and no water tanks. Inthe Progress M1, water will be delivered in separate containers carried in the CargoModule.

Instrumentation/Propulsion Module

The Progress Instrumentation/Propulsion Module is similar to the module on Soyuz, buton Progress it is twice as long and contains additional avionics equipment. The largerInstrumentation Compartment carries avionics that would be contained in the DescentModule in the Soyuz.

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Crew Profile MenuCommander: Terrence WilcuttAs Commander, Wilcutt is responsible for mission success and crewsafety and is the ultimate authority for all mission decisions. He will bethe prime crew member for the rendezvous and docking with theInternational Space Station.Previous Space Flights:Wilcutt flew as the Shuttle pilot on two missions, STS-68 in 1994 andSTS-79 in 1996. He previously commanded STS-89 in 1998, the

mission that flew Andy Thomas to Mir and returned David Wolf from his 128-day stay on Mir.Ascent Seating: Flight Deck - Port ForwardEntry Seating: Flight Deck - Port Forward

Pilot: Scott D. AltmanAltman is responsible for many orbiter systems during launch andlanding and will back up Commander Terry Wilcutt during therendezvous and docking with the International Space Station. He willalso back up his crewmates on preparations for the space walk andoperation of the remote manipulator system.

Previous Space Flights:Altman previously piloted Columbia during the 1998 STS-90 Neurolab flight.Ascent Seating: Flight Deck - Starboard ForwardEntry Seating: Flight Deck - Starboard Forward

Mission Specialist 1: Edward T. LuLu will be teamed with Yuri Malenchenko to perform the spacewalk.During that EVA, the crew will install FBG/SM power cables, install thefoot restraint and magnetometer extension pole on the ServiceModule, re-install the Magnetometer unit on the pole and dispose thecover on the Shuttle.Previous Space Flights:Lu previously served as a mission specialist on STS-84 in 1997.

Ascent Seating: Flight Deck - Starboard AftEntry Seating: Mid Deck - StarboardEV1

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Mission Specialist 2: Richard A. MastracchioAs the Flight Engineer during Atlantis' launch and landing, Mastracchiowill be seated behind Commander Terry Wilcutt and Pilot Scott Altmanon the flight deck, monitoring key Shuttle systems. Mastracchio willuse the 50-foot long robot arm to aid his EVA crewmates.Previous Space Flights:This will be Mastracchio's first flight.

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

Mission Specialist 3: Daniel C. BurbankBurbank will serve as a backup spacewalker, and will back up"intravehicular" crew member Boris Morukov during the spacewalk.

Previous Space Flights:This will be Burbank's first flight.Ascent Seating: Mid Deck - PortEntry Seating: Flight Deck - Starboard AftMission Specialist 4: Yuri I. MalenchenkoMalenchenko will be teamed with Edward Lu to perform the

spacewalk. During that EVA, the crew will install FBG/SM powercables, install the foot restraint and magnetometer extension pole onthe Service Module, re-install the Magnetometer unit on the pole anddispose the cover on the Shuttle.Previous Space Flights:In 1994, Malenchenko served as Commander of Mir 16. He has

logged 126 days in space, including 2 EVA's totaling 12 hours.Ascent Seating: Mid Deck - CenterEntry Seating: Mid Deck - CenterEV2

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Mission Specialist 5: Boris V. MorukovMorukov will serve as the "intravehicular" crew member during thespacewalk, responsible for the choreography of the astronauts' workon the ISS.Previous Space Flights:This will be Morukov's first flight.Ascent Seating: Mid Deck - Starboard

Entry Seating: Mid Deck - StarboardIV1

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Flight Day SummaryDATE TIME (EST) DAY MET EVENT

09/08/00 8:45:00 AM 1 000/00:00 Launch09/08/00 9:29:00 AM 1 000/00:44 OMS2 Burn09/08/00 12:30:00 PM 1 000/03:45 NC1 Burn09/09/00 12:57:00 AM 2 000/16:12 NC2 Burn09/09/00 4:07:00 AM 2 000/19:22 NPC Burn09/09/00 7:46:00 AM 2 000/23:01 NC3 Burn09/09/00 8:45:00 PM 3 001/12:00 NH Burn09/09/00 9:31:00 PM 3 001/12:46 NC4 Burn09/09/00 11:02:00 PM 3 001/14:17 TI Burn09/10/00 1:54:00 AM 3 001/17:09 Docking09/11/00 1:05:00 AM 4 002/16:20 EVA Start09/11/00 11:00:00 PM 5 003/14:15 ISS Ingress09/16/00 3:15:00 AM 9 007/18:30 ISS Egress09/16/00 11:44:00 PM 10 008/14:59 Undock09/17/00 1:33:00 AM 10 008/16:48 Final Separation09/19/00 2:50:00 AM 12 010/18:05 Deorbit TIG09/19/00 3:54:00 AM 12 010/19:09 KSC Landing

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EVAs

STATION ASSEMBLY CONTINUES DURING SPACEWALKOverviewOn the fourth day of Atlantis' flight, Mission Specialists Ed Lu and Yuri Malenchenko willventure outside into the Shuttle's cargo bay to begin the sixth space walk in support ofthe assembly of the International Space Station (ISS) and the 50th space walk inShuttle history.

Lu, designated EV 1, will be making his first space walk and will wear the space suitmarked by red stripes. Malenchenko, who conducted two space walks totaling 12 hoursduring his 1994 flight aboard the Russian Mir Space Station, is designated EV 2 and willwear the pure white suit.

The main objective of the planned 6 hour space walk by Lu and Malenchenko is toattach a 6-foot long magnetometer and boom to a port on the newly arrived RussianZvezda Service Module. The magnetometer will serve as a type of navigation tool, orcompass, using data acquired from the Earth's magnetic field to "tell" Zvezda'scomputers how it is oriented in relation to the Earth. In doing so, Zvezda's propellentusage will be minimized in maintaining the orientation of the ISS until the arrival inJanuary of the U.S. Laboratory Destiny, which will take over attitude control, ororientation, of the ISS through the Station's Control Moment Gyroscopes.

With Mission Specialist Rick Mastracchio operating the Shuttle's robot arm and underthe watchful eye of space walk choreographer Dan Burbank, who will both work at

Atlantis' aft flight deck, Lu and Malenchenko will ride the Canadian-built arm as far as itwill take them, about 50 feet above Atlantis' cargo bay. Then they will use tethers andhandrails along the ISS' modules to make their way to a point more than 100 feet abovethe cargo bay for the magnetometer installation, the farthest any tethered space walkerhas ventured outside a Shuttle. This portion of the space walk should take about anhour and a half. Lu and Malenchenko will be twice as high above the bay as were StoryMusgrave and Jeff Hoffman during the STS-61 mission when they mounted the top ofthe Hubble Space Telescope to replace its magnetometers.

Once the magnetometer hook up is complete, electrical, data and television cablesbetween the newly arrived Zvezda Service Module and the Zarya Control Module to

which Zvezda is docked will be connected. In all, nine cables will be rigged between thetwo spacecraft in a procedure expected to last almost three hours.

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Four of the cables are critical power connections required before the end of the STS-97mission to the ISS to deliver the sprawling U.S. solar arrays. These cables will enablepower to flow from the arrays to the Russian modules to augment the solar arrays onboth Zarya and Zvezda since the U.S. arrays will shade portions of the Russians arraysonce they are installed on the top of the Z-1 truss framework.

Two of the cables will provide an internal closed circuit video feed for crew members inZvezda so they can monitor the docking of the second Russian Progress resupplymission to the ISS in late September which will linkup to the bottom, or nadir, dockingport to Zarya.

Two additional cables will link data from Zvezda to Zarya for, among other things, thecommanding of Zarya solar array pointing from Zvezda now that the Zarya's motioncontrol system has been deactivated.

A final fiber optic cable will be strung between Zvezda and Zarya to enable data to flowfrom the suits worn by Russian space walkers once the ISS airlock is installed at thestarboard port of the Unity connecting node to accommodate joint U.S.-Russian spacewalks. Until then, ISS space walks must be conducted from Zvezda's transfercompartment.

This will be the second joint U.S.-Russian space walk outside a Space Shuttle. OnOctober 1, 1997 on the STS-86 mission, Astronaut Scott Parazynski and CosmonautVladimir Titov performed a five-hour space walk while Atlantis was docked to Mir. Threeother space walks have been jointly conducted by astronauts and cosmonauts outsideMir without a Shuttle present:

Jerry Linenger / Vasily Tsibliev April 29, 1997

Mike Foale / Anatoly Solovyev September 6, 1997

Dave Wolf / Anatoly Solovyev January 14-15, 1998

There have been five previous space walks conducted for the assembly of theInternational Space Station:

STS-88(Endeavour)

Jerry Ross and Jim Newman conducted three space walks totaling 21hours, 22 minutes on Dec. 7, 9 and 12, 1998.

STS-96(Discovery)

Tammy Jernigan and Dan Barry conducted one space walk lasting 7hours, 55 minutes on May 29, 1999.

STS-101(Atlantis)

Jeff Williams and Jim Voss conducted one space walk lasting 6 hours,44 minutes on May 21-22, 2000.

In all, the five space walks performed to date have totaled 36 hours, 1 minute of ISSassembly time.

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EVA Timeline for STATION ASSEMBLY CONTINUES DURINGSPACEWALK

Time Event2/16:20

Egress

2/16:35EVA Sortie Setup2/17:50Magnetometer2/19:05FGB-SM Cable Install2/21:05EVA Sortie Cleanup2/22:35 Ingress

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Spacehab Logistics Double ModulePayload Bay

18,000 poundsOverviewSPACEHAB's Logistics Double Module is a 20-foot long, 14-foot wide, 11.2-foot highpressurized aluminum module carried in Atlantis' payload bay and connected to themiddeck area of the orbiter by an access tunnel.

For STS-106, the LDM will carry approximately 8,100 pounds of hardware, equipmentand logistical supplies to outfit the International Space Station.

Designed to augment the Shuttle's middeck, the double module has a total cargocapacity of up to 10,000 pounds and contains the systems necessary to support thecrewmembers, such as ventilation, lighting and limited power.

History/BackgroundBoeing-Huntsville developed the Logistics Double Module for SPACEHAB and servesas the mission integration contractor.

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Integrated Cargo Carrier4,528 pounds (ICC plus cargo)

OverviewThe Integrated Cargo Carrier is an externally mounted, unpressurized, aluminum flat-bed pallet, coupled with a keel-yoke assembly, that expands the Shuttle's capability totransport cargo.

On STS-106, it will carry 2,865 pounds of cargo to orbit. The ICC is 8 feet long, 15 feetwide and 10 inches thick, with a capacity to carry up to 6,000 pounds of cargo.

The ICC also carries the SPACEHAB-Oceaneering Space System (SHOSS) Box.SHOSS is an unpressurized "tool box" attached to the top of the ICC with the capacity to

carry up to 400 pounds of tools and other flight equipment.

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Commercial Generic Bioprocessing Apparatus (CGBA)In-Cabin

Principal Investigator: Dr. Haig Keshishian, Yale University, andDr. Timothy Hammond, Tulane University

Project Scientist: Debra Reiss-Bubenheim, NASA Ames Research CenterOverviewCGBA experiments that explore the ways biological processes are affected bymicrogravitythe near-weightlessness of spacemay allow researchers to betterunderstand the nervous system. Scientists also plan to use the CGBA to investigategrowing human tissue for use in surgical procedures such as skin grafts and organtransplants and in developing medicines.

Two experiments will be conducted on STS-106.

Synaptogenesis in Microgravity

This primary experiment will examine how space flight affects the developing nervoussystem of the fruit fly (Drosophila melanogastor). Researchers are particularlyinterested in learning how nerves that control movement navigate through theembryonic central nervous system and attach to the muscle fibers they will control andhow synapses, which are the communication junctures between nerves where signalsare transferred from one nerve to another, differentiate and develop to their mature formduring embryonic and postembryonic life.

The fruit fly is an ideal model for studying the effects of microgravity on normaldevelopmental processes because its development on Earth is well characterized and ithas a small set of genes. A better understanding of these effects could haveimplications not only for long-term space travel, but also for processes related to variousdiseases and the disorders of aging.

Kidney Cell Gene Expression

The second experiment is a follow-up to an STS-90 investigation. In that earlierexperiment, microgravity caused large-scale alterations in kidney cell genes. The

follow-up experiment will examine how microgravity alters the gene expression in kidneycells that ultimately enables kidneys to develop and function normally.

The ultimate goal of this experiment is to manipulate the kidney cells to produce specifictissues for use in humans or as models in developing medicines. Cells grown insuspension in space can join together and form three-dimensional tissues similar to theircounterparts in an intact organ. These tissues are difficult to produce in Earth's gravity.

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History/BackgroundThe Commercial Generic Bioprocessing Apparatus allows automated in-flightprocessing of a variety of biological experiments contained in eight individuallyprogrammable, temperature-controlled devices. The CGBA payload hardware consistsof the generic bioprocessing apparatus (GBA), which occupies a single middeck locker,and the isothermal containment module (ICM), a middeck locker apparatus for storingbiological samples in a temperature-controlled environment.

The GBA is a self-contained mixing and heating module for processing biological fluidsamples. Up to 120 triple-contained glass syringe fluid samples (in Lexan sheaths) arestored in either the ICM or a middeck locker. These fluids are manually mixed in thesyringes and transferred to containment vials that are heated and incubated. At the endof the incubation period, the fluid vials are returned to the ICM or stowage locker.

The ICM maintains a preset temperature environment, controls the activation andtermination of the experiment samples, and serves as an interface for crew interaction,control, and data transfer.

The fruit fly experiment will occupy seven sample containers, and the kidney cell gene

expression experiment will occupy the eighth.

The Commercial Generic Bioprocessing Apparatus is a cooperative commercialexperiment facility sponsored by NASA's Space Product Development Program at theMarshall Space Flight Center in Huntsville, Ala. BioServe Space Technologies designed,built, and manages the apparatus. BioServe is a NASA Commercial Space Center withfacilities at the University of Colorado in Boulder and Kansas State University.

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Yale University and NASA's Ames Research Center at Moffett Field, Calif., areconducting the fruit fly research, which is cosponsored by the National Institutes ofHealth. The Fundamental Biology Program at Ames is sponsoring the kidney cellexperiment.

Various configurations of CGBA have flown on 13 previous Space Shuttle missions and2 Mir missions. The CGBA technology is being advanced and refined for future use onthe International Space Station.

BenefitsThe interdisciplinary nature of this research offers unique educational opportunities forundergraduate and graduate students. Improving applications and developing newproducts will benefit U.S. industry, enhance the quality of life, and propel the field ofbiotechnology toward new frontiers.

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Getaway Special G-782Payload Bay

Principal Investigator: Keith Bennett, Washington University, St. LouisOverviewThe G-782 payload, or Aria-1 as it is known to its sponsors, is an educational project togive elementary and high school students in the St. Louis area an opportunity to beinvolved in hands-on space science and perhaps steer them toward science,engineering and technology careers. Aria-1 is a joint project of the School ofEngineering and Applied Science of Washington University in St. Louis and theCooperating School Districts, an educational consortium of 47 school districts in thegreater St. Louis metropolitan area.

More than 300 students from eight St. Louis schools prepared hypotheses, designed

experiments, collected materials, and prepared flight articles under the guidance of theirteachers. After the flight, the students will compare flight samples with ground controlsto determine the effects of microgravity, radiation, magnetism, and other possiblephenomena experienced in the low Earth orbit environment of the Shuttle mission.

The student experiments are housed in a standard 5-cubic-foot getaway specialcanister that is attached to the sidewall of Atlantis' payload bay. The payload iscompletely passive and requires no crew action.

Aria-1 Schools and Experiments

Bristol Elementary School

For this experiment, 50 first graders each drew pictures on two pieces Shrinky Dinkplastic that are about 5 inches square. This plastic shrinks about 50% when it isexposed to high heat. One set of 50 plastic pieces will be heated in a toaster oven onEarth so the students can see the effects of heat in gravity. After the mission, thestudents will examine their Shrinky Dinks that flew on Aria-1 to determine if they wereexposed to high temperatures. Each student will also get a souvenira piece of plasticthat has flown on the Space Shuttle.

Marissa Junior/Senior High School

Fourteen Marissa High School students are sending 18 different kinds of garden, flower,and crop seeds into space on Aria-1. They want to find out if the increased ultravioletradiation and extreme temperature changes found in space will change how the seedsgrow and the appearance of the plants. The experimenters will plant the seedsexposed to space alongside control seeds that remained on Earth and observe anydifferences in the plants.

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Glenridge Elementary School

Eight Glenridge students are investigating the reactions of everyday objects to theunique environment of space. They are studying the chewability of Bubblacious BubbleGum, the spin patterns and the rate of germination of maple seeds, the ability of mold

on bread to survive in space, the effects on dry cement mix and its hardening rate, andthe ability of active dry yeast to rise.

Ladue Junior High School

Twelve students have devised experiments whose results may have practicalapplications in space travel. One experiment will gauge the effect of space on thecleaning power of moist towelettes. Another will study whether space causestoothpaste to become hard and lose its flavor and color. One group of students wouldlike to find out whether microgravity, air pressure, and temperature changes will causesticky tack to lose its stickiness. In a related experiment, a student will test his

hypothesis that glue exposed to microgravity will become thinner and less sticky. Anexperiment labeled rubberball physics by its developers will try to determine whetherspace has any lasting effects on a rubber ball. Finally, a student is sending a floppydisk into space to see if the data encoded on it will be affected by zero gravity.Hazelwood West High School

Hazelwood West High School students have several experiments on Aria-1. One willexamine the effects of space flight on the ability of copper and superglue to withstandchanges in gravity, temperature, and radiation. Bacteria spores will be studied todetermine whether space exposure alters microorganisms. Finally, the experimenterswill investigate crystal growth in frozen red beet cells. They want to know if changingthe concentration of salt in a solution containing these cells will affect the growth ofcrystals and cell damage.

Mary Institute Country Day School

The MICDS Middle School Science Club is sending brine shrimp, dry yeast, and twofloppy disks into space to determine how the microgravity, temperature extremes, andvarious atmospheric pressures of space affect them. If the organisms withstand theseconditions and "reanimate" when they return to Earth, it may suggest that simple lifeforms might exist elsewhere in the universe. If the disks retain their ability to read andwrite data, it may mean that personal computers could be used on the InternationalSpace Station and Shuttle missions, which would help make space exploration moreeconomical.

Center for Creative Learning

Fourth and fifth graders designed 13 experiments to answer questions about howdifferent types of materials and organisms react to exposure to space because theyrealize the importance of these answers as humans move into space to live and build.Their experiments include studying human blood for mutations, observing changes in

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the growth patterns of bulbs, examining carrot slices infected with agrobacteriumtumefacians for any changes in their nuclei, and studying material reactive to airborneparticles for changes.

Sacred Heart Elementary School of Florissant

Students from Sacred Heart School will study the effects of space on the decompositionof various items, specifically the rate of decomposition. Samples of seeds, toothpaste,moldy bread, rotting hamburger, hair, soil, water from the Meramec River, and brineshrimp will be sent into space in sealed vials. After the mission, the students willcompare the amount of decomposition of the samples exposed to space with that ofcontrol samples that remained on Earth. The results of this experiment could lead to abetter system of waste reduction than traditional landfills and ultimately promote betterstewardship of our environment.

More information on Aria-1, including a list of participating schools and experiment

descriptions, is available at http://www.aria.cec.wustl.edu/Aria1.

History/Background

STS-106 is the 36th Shuttle mission to participate in NASA's Getaway Special program.The GAS program was designed as an inexpensive way for educational, international,commercial, and U.S. government users to place a payload on the Space Shuttle.Since the program began, 157 payloads have been flown.

Each payload must meet specific safety criteria and be screened for its propriety as wellas its educational, scientific, and technical objectives. These guidelines precludecommemorative items that are intended for sale as objects that have flown in space.

The Goddard Space Flight Center's Wallops Flight Facility, Wallops Island, Va.,manages the program. More information on the Getaway Special program can befound at http://www.wff.nasa.gov/~sspp/gas/gas.html.

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Space Experiment Module 8Payload Bay

Overview

Eye lenses, seeds, water, DNA, and steel are just some of the materials that will be thesubjects of student research on the eighth flight of the Space Experiment Module (SEM)project, NASA's educational initiative to increase access to space for students fromkindergarten to college. All together, 13 passive experiments will be flown on STS-106.

Since the first SEM flight in 1996, tens of thousands of students have flown experimentsin space that they have created, designed, and built with the help of teachers ormentors. NASA provides the experiment modules, or containers, which are placed instandard 5-cubic-foot getaway special canisters that are mounted in the orbiter'spayload bay.

SEM-08 Experiments

Water, Water EverywhereTown of Tonawanda School District, Buffalo, N.Y.; Edgemont Union Free SchoolDistrict, Scarsdale, N.Y.; Auxiliary Services for High Schools, New York City Board ofEducation

Students will observe the effects of space on samples taken from natural bodies ofwater. The students assume that changes in radiation, gravity, and temperature willhave no effect on the abiotic and biotic levels in the samples.

Houston, We Have an Eye ProblemIrwin Altman School 172, Floral Park, N.Y.

The purpose of this experiment is to determine if the high radiation of space will causethe layers of eye lenses to become cloudy and transmit less light. Lenses from sheepand cows will be used in this investigation. Contact lenses also will be tested todetermine the effects of radiation on the amount of light they transmit.

Investigation of Antibiotic-Resistant Mutations in a Microgravity EnvironmentShoreham-Wading River High School Science Research Program, Shoreham, N.Y.

This experiment will analyze differences in the mutation rates of antibiotic-resistantplasmid DNA exposed to microgravity and controls exposed to Earth's gravity.

R.S.V.P. (Rams Space Variety Package)Parkside High School, Salisbury, Md.

Students will study the effect of space on seeds, film, minicassettes, and a radiationdosimeter.

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The Pittsburgh Steelers in SpaceThe DePaul Institute for the Deaf, Pittsburgh, Penn.

Students will determine the effects of microgravity and radiation on the oxidation ofvarious types of steel and the minerals involved in the manufacture of steel.

Medicine Cabinet in SpaceNorth Kingstown High School, North Kingstown, R.I.; Cannon School, Concord, N.C.;Williston Northampton School, Easthampton, Mass.; South Middle School, St. Peters,Mo.; Holy Family School, Harrisburg, Pa.; Ramstein American High School, RamsteinAir Base, Germany

The experiment is designed to determine how common items from the medicinecabinet, items that could potentially be found on a long space mission, are altered bythe space environment.

Mars Lunch BoxTrinity Lutheran School, Cedar Rapids, Iowa, partnered with students from Wales;Washington Junior High School, Rock Island, Ill., partnered with students in Australia;Northside Middle School, Hampton, Va., partnered with students in Iceland

This experiment will study the effects of space travel on the growth of vegetable seeds.

SINBAD (Scientific and Instructional Ballast Alternative Device)Florida Institute of Technology, Geospace Physics Laboratory, Melbourne, Fla.

This experiment will study the frequencies of the orbiter during launch, orbit, andlanding; examine the effects of space flight on palm tree seeds; and study the reactionof acrylic latex caulking and its outgassing of water vapor.

PEESOILGates Chili High School, Rochester, N.Y.; Mynderse Academy, Seneca Falls, N.Y.;Northampton High School, Northampton, Mass.

The students are studying whether microgravity and radiation have an effect on thefertility of soil samples as determined by the soil's biodiversity. The experimenters willdetermine the average number of different organisms found before and after the soil isexposed to space.

Process of Germination and Plant GrowthFrank Elementary School, Guadalupe, Ariz.

This experiment will determine how the space environment affects seed germinationand plant growth. Kentucky Wonder and Quest seeds will be used in this investigation.

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Spaced Popped PopcornSouth Shore Elementary School, Crownsville, Md.

The students predict that unpopped popcorn exposed to microgravity and radiation willpop at a different rate and volume than the control group, which will remain on Earth.

Bounce and StretchSouth Shore Elementary School, Crownsville, Md.

The students predict that microgravity and radiation will affect the physicalcharacteristics of elastic materials, including balls and rubber bands.

Germ Killers in SpaceWalter S. Mills-Parole Elementary, Annapolis, Md.

This experiment will study the effects of microgravity, radiation, and temperature on

mouthwash and antibacterial hand gel.

History/BackgroundThe Space Experiment Module program is one of a number of educational initiatives ofNASA's Shuttle Small Payloads Project. Recognizing the need to provide easy accessto space for all students, NASA began the SEM program in 1995. SEM participants areencouraged to focus on the educational act of creating experiments rather than thecomplexities of engineering.

More information about the SEM program can be found athttp://www.wff.nasa.gov/~sspp/sem/sem.html. BenefitsThe SEM program offers simplified access to space for students at every grade level. Ituses cross-curriculum learning, particularly in math, science and technology, to promoteinterest in space exploration.

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Experiments

HTD 1403 Micro-Wireless Instrumentation System (Micro-WIS)HEDS Technology Demonstration

In-CabinOverviewHTD 1403 will demonstrate the operational utility and functionality of the micro-WIS on orbit, initially in the crew cabin of the Shuttle orbiter and then on theInternational Space Station.

The micro-WIS consists of tiny autonomous sensors for data acquisition. Twoversions have been developeda transmitter and a recorder. This HTD isdesigned to demonstrate the micro-WIS transmitter and recorder.

One of the objectives of this HTD is to obtain meaningful real-timemeasurements for use in the orbiter's environmental control and life supportsystem (ECLSS) operations. The micro-WIS transmitter's simultaneous real-timemeasurements of air cabin temperatures in many interior compartments of theorbiter will help ECLSS operations personnel address issues encountered onSTS-88 and early International Space Station flights. Currently, only onetemperature reading in the aft flight deck of the orbiter is available for adjustingmodel predictions for real-time environments.

Micro-WIS will also reduce the time it takes the crew to obtain on-orbittemperature measurements and will increase the capability to monitortemperatures over long periods. On busy Space Station assembly flights, thedistances traveled and the time required to make the measurements can beprohibitive.

Micro-WIS data will also be used to validate cabin air temperature models thatare used to make critical predictions of the dew point on early ISS missions,which is important because orbiter cabin air exerts a significant influence on theentire station volume. Although the physical configuration of the air ducts in theorbiter cabin has been changed significantly, the sensors have remained thesame and some temperature data has never been available.History/BackgroundIn the past, space missions have been limited by the penalties associated withweight and integration costs. However, breakthroughs in the miniaturization ofvery low power radio transceivers have led to the introduction of a 1-inch-diameter wireless instrumentation system that can send temperaturemeasurements to a laptop computer for five months.

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BenefitsThis breakthrough in miniaturization means significant cost, weight, and powersavings for current and future space vehicles and ground test facilities andshould revolutionize the design of future spacecraft systems. The micro-WIS on-orbit demonstration should also increase the flexibility, reliability, andmaintainability of data acquisition systems for spacecraft and lead to a reductionin vehicle turnaround time and increased reliability by eliminating cableconnectors and by providing near-real-time reconfigurable data paths.

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Experiments

Protein Crystal Growth (PCG) Enhanced Gaseous Nitrogen (EGN)Dewar

In-CabinPrincipal Investigator: Dr. Alexander McPherson, University of California, Irvine

OverviewThe primary purpose of the EGN Dewar experiment is to demonstrate a low-costplatform for conducting a large number of experiments to determine the optimumconditions for growing large, high-quality protein crystals in space. Researchersrequire crystals of sufficient size and suitable quality for crystallographic analysisof their molecular structure by X-ray diffraction and computer modeling. EGNpromises to give researchers greater access to space and the opportunity to

conduct a statistically significant number of experiments per mission, which willincrease the likelihood of obtaining crystals worthy of X-ray analysis.

Researchers will also use data from EGN in selecting the methodologies andproteins for future liquid-liquid diffusion experiments, which will investigate thefactors that influence the nucleation, growth, order, and stability of crystals anddetermine the effects of microgravity on those phenomena.

Protein samples are flash frozen before a mission and placed inside the Dewar,a vacuum-jacketed container similar to a thermos bottle. An absorbent innerliner is saturated with liquid nitrogen, which keeps the samples frozen until theyreach orbit. As the system absorbs heat, the nitrogen boils away and thesamples begin to thaw. Crystals begin to grow when the samples havecompletely thawed.

Astronauts will transfer the EGN payload from Atlantis' middeck to theInternational Space Station, where the crystals will continue to grow until thepackage is returned to Earth for analysis on the next Shuttle mission. EGN is thefirst microgravity science experiment to be conducted on board the InternationalSpace Station.

EGN is upgrade of an experiment that was flown on Shuttle-Mir missions. Theearlier version allowed the samples to thaw gradually over 12 to 20 days. Theenhanced version incorporates heaters that will control the rate of nitrogen boil-off and, thus, the rate of thawing. The new design also includes devices forrecording the temperatures inside the Dewar and storing the data.

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History/BackgroundThe gaseous nitrogen Dewar was flown on five Shuttle-Mir missionsSTS-71,74, 76, 79, and 81. The experiment packages were transferred from the Shuttleorbiter to a module of the Mir station, and the samples were allowed to growuninterrupted until the next Shuttle mission.BenefitsProteins play an important role in every biochemical reaction in plants andanimals. In order to understand the basic processes of living things, scientistsmust first understand proteins. Computer models of the structures of proteincrystals grown in the near-vacuum of space are expected to improve theirunderstanding of the function and behavior of proteins. Scientists also hope tolearn more about why biological crystals grow differently in space than they dounder the influence of Earth's gravity.

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Single-String Global Positioning SystemDTO 700-14

OverviewThe purpose of this DTO is to evaluate the performance and operation of theGlobal Positioning System as a Shuttle navigation aid during the ascent, on-orbit, entry, and landing phases of the mission. A modified military GPSreceiver processor and the orbiter's existing GPS antenna will be used for thisevaluation.

This is the tenth flight for DTO 700-14. It was last flown on STS-101.

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SIGI Orbital Attitude ReadinessDTO 700-21Payload Bay

OverviewThe objective of DTO 700-21 is to demonstrate the operation of the space integratedGlobal Positioning System/inertial navigation system (SIGI) on orbit. The SIGI isintended to be the primary GPS source for the International Space Station (ISS) andthe primary navigation source for the crew return vehicle (CRV). The ability of the SIGIto perform GPS attitude determination in space has not been demonstrated. Data fromthis DTO will be used to evaluate the SIGI design before it is used on the ISS or CRV.

The payload consists of the SIGI in a pressurized container on a GPS antenna

mounting structure (GAMS). The SIGI has RF connections to four antennaassemblies, which are mounted on the corners of the GAMS. The experiment packageis mounted on the integrated cargo carrier in the payload bay. A payload and generalsupport computer (PGSC) located in SPACEHAB is used for commanding and datastorage. Data from two star trackers mounted on the GAMS will be collected by aseparate PGSC inside SPACEHAB.

This is the second flight of DTO 700-21.

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Crosswind Landing PerformanceDTO 805

OverviewThis DTO will continue to gather data to demonstrate the capability to perform amanually controlled landing with a 90-degree, 10- to 15-knot steady-statecrosswind. This DTO can be performed regardless of landing site or vehiclemass properties. During a crosswind landing, the drag chute will be deployedafter nose gear touchdown when the vehicle is stable and tracking the runwaycenterline. This DTO has been manifested on 59 previous flights.

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Monitoring Latent Virus Reactivation and Shedding in Astronauts UsingSaliva KitsDSO 493

OverviewThe premise of this DSO is that the incidence and duration of latent virus reactivationin saliva and urine will increase during space flight. The objective is to determine thefrequency of induced reactivation of latent viruses, latent virus shedding, and clinicaldisease after exposure to the physical, physiological, and psychological stressorsassociated with space flight.

Space-flight-induced alterations in the immune response become increasinglyimportant on long missions, particularly the potential for reactivation and dissemination(shedding) of latent viruses. An example of a latent virus is Herpes Simplex Type 1(HSV-1), which infects 70 to 80% of all adults. Its classic manifestations are coldsores, pharyngitis, and tonsillitis; and it usually is acquired through contact with thesaliva, skin, or mucous membranes of an infected individual. However, manyrecurrences are asymptomatic, resulting in shedding of the virus. Twenty subjectshave been studied for Epstein-Barr virus. Three additional viruses will be examined inan expanded subject group.

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Individual Susceptibility to Postflight Orthostatic Intolerance (Tilt Test)DSO 496

OverviewIt is well known that space flight alters cardiovascular function significantly. One of themost important changes negatively affecting flight operations and crew safety is thepostflight loss of orthostatic tolerance, which causes astronauts to have difficultywalking independently and induces lightheadedness or fainting. These may impairtheir ability to leave the orbiter after it lands.

Susceptibility to postflight orthostatic hypotension is highly individual; some astronautsare affected very little and others have severe symptoms. This DSO will test the

hypothesis that orthostatic hypotension is caused, in part, by gender-relateddifferences in the autonomic regulation of arterial pressure and changes in autonomicfunction brought on by space flight.

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Space Flight and Immune FunctionDSO 498

OverviewAstronauts face an increasing risk of contracting infectious diseases as they work andlive for longer periods in the crowded conditions and closed environments ofspacecraft such as the International Space Station. The effects of space flight on thehuman immune system, which plays a pivotal role in warding off infections, is not fullyunderstood. Understanding the changes in immune function caused by exposure tomicrogravity will allow researchers to develop countermeasures to minimize the risk ofinfection.

The objective of this DSO is to characterize the effects of space flight on neutrophils,monocytes, and cytotoxic cells, which play an important role in maintaining an effective

defense against infectious agents. The premise of this study is that the spaceenvironment alters the essential functions of these elements of human immuneresponse.

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

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

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Eye Movements and Motion Perception Induced by Off-Vertical-AxisRotation (OVAR) at Small Angles of Tilt After Space Flight

DSO 499

OverviewAstronauts returning to Earth have experienced perceptual and motor coordinationproblems caused by sensorimotor adaptation to microgravity. The hypothesis is thatthe central nervous system changes the way it processes gravitational tilt informationthat it receives from the vestibular (otolith) system. Eye movements and perceptualresponses during constant-velocity off-vertical-axis rotation will reflect changes inotolith function as astronauts readapt to gravity. The length of recovery is a function offlight duration (i.e., the longer astronauts are exposed to microgravity the longer theywill take to recover).

This DSO will examine changes in astronauts' spatial neural processing ofgravitational tilt information following readaptation to gravity. Postflight oculomotor andperceptual responses during off-vertical-axis rotation will be compared to preflightresponses to track the time of recovery.

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Shuttle Reference and Data

Shuttle Abort ModesSelection of an ascent abort mode may become necessary if there is a failure thataffects vehicle performance, such as the failure of a space shuttle main engine or anorbital maneuvering system. Other failures requiring early termination of a flight, such asa cabin leak, might also require the selection of an abort mode.

There are two basic types of ascent abort modes for space shuttle missions: intactaborts and contingency aborts. Intact aborts are designed to provide a safe return of theorbiter to a planned landing site. Contingency aborts are designed to permit flight crewsurvival following more severe failures when an intact abort is not possible. Acontingency 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 islower than the nominal orbit. This mode requires less performance and allows time toevaluate 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 anormal entry and landing. This mode generally involves two orbital maneuvering systemthrusting sequences, with the second sequence being a deorbit maneuver. The entrysequence 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 AtlanticOcean. This mode results in a ballistic trajectory, which does not require an orbitalmaneuvering system maneuver.

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RETURN TO LAUNCH SITE (RTLS)

The RTLS mode involves flying downrange to dissipate propellant and then turningaround 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 failureand the 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 theremaining 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 amore precise knowledge of the orbiter's position than the crew can obtain from onboardsystems. Before main engine cutoff, Mission Control makes periodic calls to the crew totell 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 displayinformation, to determine the current abort region.

Which abort mode is selected depends on the cause and timing of the failure causingthe abort and which mode is safest or improves mission success. If the problem is aspace shuttle main engine failure, the flight crew and Mission Control Center select thebest 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 modethat results in the earliest vehicle landing is chosen. RTLS and TAL are the quickestoptions (35 minutes), whereas an AOA requires approximately 90 minutes. Which ofthese is selected depends on the time of the failure with three good space shuttle mainengines.

The flight crew selects the abort mode by positioning an abort mode switch anddepressing an abort push button.

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RETURN TO LAUNCH SITE OVERVIEWThe RTLS abort mode is designed to allow the return of the orbiter, crew, and payloadto 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 shuttlemain engine between lift-off and approximately four minutes 20 seconds, at which timenot 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 whichthe space shuttle main engines are still thrusting; an ET separation phase; and the glidephase, during which the orbiter glides to a landing at the Kennedy Space Center. Thepowered RTLS phase begins with the crew selection of the RTLS abort, which is doneafter solid rocket booster separation. The crew selects the abort mode by positioningthe abort rotary switch to RTLS and depressing the abort push button. The time atwhich the RTLS is selected depends on the reason for the abort. For example, a three-

engine RTLS is selected at the last moment, approximately three minutes 34 secondsinto the mission; whereas an RTLS chosen due to an engine out at lift-off is selected atthe earliest time, approximately two minutes 20 seconds into the mission (after solidrocket booster separation).

After 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 tothe 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 headsup attitude, pointing toward the launch site. At this time, the vehicle is still moving awayfrom the launch site, but the space shuttle main engines are now thrusting to null thedownrange velocity. In addition, excess orbital maneuvering system and reaction controlsystem propellants are dumped by continuous orbital maneuvering system and reactioncontrol system engine thrustings to improve the orbiter weight and center of gravity forthe glide phase and landing.

The vehicle will reach the desired main engine cutoff point with less than 2 percentexcess propellant remaining in the external tank. At main engine cutoff minus 20seconds, 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 cutoffhas been commanded, the external tank separation sequence begins, including areaction control system translation that ensures that the orbiter does not recontact theexternal tank and that the orbiter has achieved the necessary pitch attitude to begin theglide phase of the RTLS.

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.

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TRANSATLANTIC LANDING ABORT OVERVIEWThe TAL abort mode was developed to improve the options available when a spaceshuttle main engine fails after the last RTLS opportunity but before the first time that anAOA 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 aspossible.

In a TAL abort, the vehicle continues on a ballistic trajectory across the Atlantic Oceanto land at a predetermined runway. Landing occurs approximately 45 minutes afterlaunch. The landing site is selected near the nominal ascent ground track of the orbiterin order to make the most efficient use of space shuttle main engine propellant. Thelanding site also must have the necessary runway length, weather conditions and U.S.State Department approval. Currently, the three landing sites that have been identifiedfor 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 theTAL/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 abortmode begins sending commands to steer the vehicle toward the plane of the landingsite. It also rolls the vehicle heads up before main engine cutoff and sends commandsto begin an orbital maneuvering system propellant dump (by burning the propellantsthrough the orbital maneuvering system engines and the reaction control systemengines). This dump is necessary to increase vehicle performance (by decreasingweight), to place the center of gravity in the proper place for vehicle control, and todecrease 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 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 underspeed, the Mission Control Center will determine that an abort mode is necessary andwill inform the crew. The orbital maneuvering system engines would be used to place

the orbiter in a circular orbit.

ABORT ONCE AROUND OVERVIEW

The AOA abort mode is used in cases in which vehicle performance has been lost tosuch an extent that either it is impossible to achieve a viable orbit or not enough orbitalmaneuvering system propellant is available to accomplish the orbital maneuveringsystem thrusting maneuver to place the orbiter on orbit and the deorbit thrusting

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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-mainengine cutoff orbit so a second orbital maneuvering system thrusting sequence willresult 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 theorbiter 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 landingat 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 inother systems. Loss of one main engine while another is stuck at a low thrust settingmay 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 engineswould normally result in an intact recovery of vehicle and crew. Loss of more than onemain 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 beditched. The in-flight crew escape system would be used before ditching the orbiter.

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Space Shuttle Rendezvous ManeuversCOMMON 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-boardtargeted burns use star tracker and rendezvous radar data to correct the post-Titrajectory in preparation for the final, manual proximity operations phase

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Space Shuttle Solid Rocket BoostersThe 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, thetwo SRBs carry the entire weight of the external tank and orbiter and transmit the weightload 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. Thetwo 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 ofapproximately 220,000 feet, or 35 nautical miles (41 statute miles). SRB impact occursin the ocean approximately 122 nautical miles (141 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 eachsolid rocket motor weighs approximately 1,100,000 pounds. The inert weight of eachSRB is approximately 192,000 pounds.

Primary elements of each booster are the motor (including case, propellant, igniter andnozzle), structure, separation systems, operational flight instrumentation, recoveryavionics, pyrotechnics, deceleration system, thrust vector control system and rangesafety destruct system.

Each booster is attached to the external tank at the SRB''s 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 SRB''s 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 analyseswere performed on critical structural elements of the SRB. Analyses were primarilyfocused in areas where anomalies had been noted during postflight inspection ofrecovered hardware.

One of the areas was the attach ring where the SRBs are connected to the externaltank. Areas of distress were noted in some of the fasteners where the ring attaches tothe SRB motor case. This situation was attributed to the high loads encountered duringwater impact. To correct the situation and ensure higher strength margins duringascent, the attach ring was redesigned to encircle the motor case completely (360degrees). Previously, the attach ring formed a C and encircled the motor case 270degrees.

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Additionally, 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 theaft 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 anepoxy curing agent (1.96 percent). The propellant is an 11-point star- shapedperforation in the forward motor segment and a double- truncated- cone perforation ineach of the aft segments and aft closure. This configuration provides high thrust atignition and then reduces the thrust by approximately a third 50 seconds after lift-off toprevent overstressing the vehicle during maximum dynamic pressure.

The SRBs are used as matched pairs and each is made up of four solid rocket motorsegments. The pairs are matched by loading each of the four motor segments in pairsfrom the 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-duty rail car with a specially built cover.

The nozzle expansion ratio of each booster beginning with the STS-8 mission is 7-to-79.The nozzle is gimbaled for thrust vector (direction) control. Each SRB has its ownredundant auxiliary power units and hydraulic pumps. The all-axis gimbaling capabilityis 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- pointflexible bearing is the gimbal mechanism.

The cone- shaped aft skirt reacts the aft loads between the SRB and the mobilelauncher platform. The four aft separation motors are mounted on the skirt. The aftsection contains avionics, a thrust vector control system that consists of two auxiliarypower units and hydraulic pumps, hydraulic systems and a nozzle extension jettisonsystem.

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

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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 andturns on the recovery aids. The aft assembly, mounted in the external tank/SRB attachring, connects with the forward assembly and the orbiter avionics systems for SRBignition commands and nozzle thrust vector control. Each integrated electronic

assembly has a multiplexer/ demultiplexer, which sends or receives more than onemessage, 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) ofeach SRB thrust for 1.02 seconds at SRB separation from the external tank. Each solidrocket separation motor is 31.1 inches long and 12.8 inches in diameter.

Location aids are provided for each SRB, frustum/ drogue chutes and main parachutes.These include a transmitter, antenna, strobe/ converter, battery and salt water switchelectronics. The location aids are designed for a minimum operating life of 72 hours 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.The nozzles are plugged, the solid rocket motors are dewatered, and the SRBs aretowed back to the launch site. Each booster is removed from the water, and itscomponents are disassembled and washed with fresh and deionized water to limit saltwater corrosion. The motor segments, igniter and nozzle are shipped back to Thiokol forrefurbishment.

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 supportposts on the mobile launcher platform. Hold- down bolts hold the SRB and launcherplatform posts together. Each bolt has a nut at each end, but only the top nut isfrangible. The top nut contains two NASA standard detonators, which are ignited at solidrocket motor ignition commands.

When the two NSDs are ignited at each hold- down, the hold- down bolt travelsdownward 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. Thefrangible nut is captured in a blast container.

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The solid rocket motor ignition commands are issued by the orbiter''s computersthrough the master events controllers to the hold- down pyrotechnic initiator controllerson the mobile launcher platform. They provide the ignition to the hold- down NSDs. Thelaunch processing system monitors the SRB hold- down PICs for low voltage during thelast 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 armd

nasa space shuttle sts-106 press kit

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