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MARCH 2008 CONTENTS i

CONTENTS

Section Page

STS-123 MISSION OVERVIEW .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

TIMELINE OVERVIEW .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

MISSION PROFILE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . 15

MISSION PRIORITIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

MISSION PERSONNEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

STS-123 ENDEAVOUR CREW .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

PAYLOAD OVERVIEW .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

K I B O O V E R V I E W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 1

K I B O M I S S I O N C O N T R O L C E N T E R . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . 3 9

T S U K U B A S P A C E C E N T E R . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . 4 3

S P A C E S T A T I O N I N T E G R A T I O N A N D P R O M O T I O N C E N T E R . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 7

J A X A ’ S E X P E R I M E N T S D U R I N G T H E 1 J / A S T A G E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 7

J A X A A E R O S P A C E O P E N L A B P R O G R A M . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 8

D E X T R E : C A N A D I A N R O B O T I C S F O R T H E I N T E R N A T I O N A L S P A C E S T A T I O N . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 0

RENDEZVOUS AND DOCKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

U N D O C K I N G , S E P A R A T I O N A N D D E P A R T U R E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 8

SPACEWALKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . 59

E V A - 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 6 1

E V A - 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 6 2

E V A - 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 6 3

E V A - 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 6 4

E V A - 5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 6 5

EXPERIMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . 67

D E T A I L E D T E S T O B J E C T I V E S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 7

S H O R T - D U R A T I O N R E S E A R C H . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 8

ii CONTENTS MARCH 2008

SPACE SHUTTLE CONTINUOUS IMPROVEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73

E N D E A V O U R ’ S U M B I L I C A L W E L L D I G I T A L C A M E R A N O W H A S F L A S H C A P A B I L I T Y . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 3

SHUTTLE REFERENCE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77

LAUNCH AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91

L A U N C H . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . 9 1

A B O R T - T O - O R B I T ( A T O ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1

T R A N S A T L A N T I C A B O R T L A N D I N G ( T A L ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1

R E T U R N - T O - L A U N C H - S I T E ( R T L S ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1

A B O R T O N C E A R O U N D ( A O A ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . 9 1

L A N D I N G . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . 9 1

ACRONYMS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93

MEDIA ASSISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105

PUBLIC AFFAIRS CONTACTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107

MARCH 2008 MISSION OVERVIEW 1

STS-123 MISSION OVERVIEW

This graphic illustrates Endeavour docked to the International Space Stationas the shuttle robotic arm grapples a component of the Kibo laboratory.

The first pressurized component of theJapanese Kibo laboratory, a Canadian roboticdevice called Dextre and five spacewalks aremajor elements of STS 123. Endeavour’s 16 dayflight is the longest shuttle mission to theInternational Space Station (ISS).

The Kibo laboratory will eventually be berthedto the left side of the station s Harmonynode. The Japanese Experiment LogisticsModule Pressurized Section (ELM PS), the

smaller of two pressurized modules of Kibo,will be attached temporarily to a docking porton the space facing side of Harmony.

Kibo is the major Japanese contribution to thestation, and will increase its research capabilityin a variety of disciplines. The name, whichmeans “hope,” was chosen by the JapanAerospace Exploration Agency (JAXA) in anational contest.

2 MISSION OVERVIEW MARCH 2008

STS 123 crew members are attired in training versions of their shuttle launch and entry suits.From the left are astronauts Rick Linnehan, Robert L. Behnken, both mission specialists;

Gregory H. Johnson, pilot; Garrett Reisman, mission specialist; Dominic Gorie,commander; Mike Foreman and JAXA’s Takao Doi, both mission specialists.

Dextre, the Canadian device, will work with thestation’s robotic arm, Canadarm2. Designed forstation maintenance and service, Dextre iscapable of sensing forces and movement ofobjects it is manipulating. It can automaticallycompensate for those forces and movements toensure an object is moved smoothly.

Dextre is the final element of the MobileServicing System, part of Canada’s contributionto the station. The name was chosen byCanadian students in a national contest. Dextrehad been called the Special Purpose DexterousManipulator.

Once assembled, Dextre will look a little like ahuman upper torso stick figure. It will havetwo arms, and be capable of performingdelicate tasks and using tools. Its four cameraswill give crew members inside the station viewsof its activities. Dextre will be able to workfrom the end of Canadarm2, or from theorbiting laboratory’s mobile base system.

The STS 123 mission, also called assembly flight1J/A, includes representation of all five stationpartner interests — the U.S., Japan, Canada,Russia and the European Space Agency.

MARCH 2008 MISSION OVERVIEW 3

The flight includes five scheduled spacewalks.Three of them will include tasks devoted toassembly of Dextre and installation of relatedequipment.

Other spacewalk activities include work tounberth Kibo’s ELM PS, installation of spareparts and tools, installation of a materialsexperiment, replacement of a circuit breakerbox and demonstration of a repair procedurefor tiles of the shuttle’s heat shield.

Spacewalkers also will stow the Orbiter BoomSensor System (OBSS), the extension of theshuttle’s robotic arm, onto the station’s maintruss during the fifth spacewalk.

The boom sensor system is being left on thestation because the size of the large Japanesepressurized module to be launched on STS 124won’t allow it to be carried in Discovery’s cargobay. The OBSS will be returned to Earth at theend of that mission.

This graphic depicts the location of the STS 123 payload hardware.

MISSION OVERVIEW MARCH 2008

Astronaut Dominic Gorie, STS 123 commander, dons a training version of his shuttle launch andentry suit in preparation for a post insertion/de orbit training session at Johnson Space Center (JSC).

MARCH 2008 MISSION OVERVIEW

Dominic Gorie (GOR ee), 50, a veteran of threespace flights and a retired Navy captain, willcommand Endeavour. The spacecraft’s pilot isGregory H. Johnson, 45, an Air Force colonel.STS 123 mission specialists are Robert L.Behnken (BANK en), 37, an Air Force major;

Navy Capt. Mike Foreman, 50; Japaneseastronaut Takao (tah cowe) Doi (DOY), 53;Rick Linnehan (LIN eh han), 50, a veteran ofthree shuttle flights; and Garrett Reisman(REES man), 39.

Astronauts Robert L. Behnken (left) and Japan Aerospace Exploration Agency’sTakao Doi, both STS 123 mission specialists, participate in a training session

in the Space Vehicle Mockup Facility at the JSC.

MISSION OVERVIEW MARCH 2008

Reisman will remain aboard the station withCommander Peggy Whitson and fellow FlightEngineer Yuri Malenchenko (mal EN chen ko).He will replace Leopold Eyharts ( arts), aFrench Air Force general and European SpaceAgency astronaut who will return to Earth onEndeavour. Eyharts was launched to the station aboard Atlantis on STS 122.

The day after Endeavour’s launch fromKennedy Space Center in Florida, Gorie,Johnson and Doi will use the shuttle’s roboticarm and its OBSS for the standard surveyof Endeavour’s heat resistant reinforced

carbon carbon and heat shield tiles. Behnken,Linnehan and Reisman will check out thespacesuits on Endeavour.

Flight day 3 is docking day. Once Endeavourreaches a point about 600 feet below the station,Gorie will fly it in a back flip, so station crewmembers can photograph its heat shield. Thedigital images will be sent to the ground foranalysis. Gorie then will fly Endeavour to apoint ahead of the station and maneuver it to adocking with Pressurized Mating AdapterNo. 2, at the forward end of the Harmony node.

This graphic depicts the rendezvous pitch maneuver while crew aboard theISS photograph the orbiter for analysis by specialists on the ground.


Astronauts Gregory H. Johnson (background), STS 123 pilot, and Garrett Reisman,Expedition 16 flight engineer, use the virtual reality lab at JSC to train for some

of their duties aboard the space shuttle and space station.

Reisman will become a station crew memberwith the exchange of his custom Soyuz seatlinerwith that of Eyharts, who joins the shuttle crewfor his flight home. Johnson and Behnken willuse the station’s Canadarm2 to remove thepallet containing Dextre from the payload bayand attach it to a fixture on the station’s maintruss. A review of procedures for the firstspacewalk will wind up the Endeavour crew’sworking day.

Flight day 4 focuses on the first spacewalk, byLinnehan and Reisman. Foreman will serve asintravehicular officer, while Behnken and

Eyharts will operate the station’s Canadarm2.Tasks include preparation for the ELM PSinstallation and work on Dextre assembly. Doiand Gorie will subsequently install the ELM PSon Harmony with the shuttle arm.

Flight day 5 includes outfitting of the ELM PSvestibule, ELM PS entry by Doi and Linnehan,transfer of equipment and supplies betweenshuttle and station, and briefings on stationactivities for the new station crew memberReisman. An hour long procedure reviewlooks ahead to the second spacewalk.


Astronaut Rick Linnehan, STS 123 mission specialist, participates inan Extravehicular Mobility Unit spacesuit fit check in the Space StationAirlock Test Article (SSATA) in the Crew Systems Laboratory. Astronaut

Robert L. Behnken, mission specialist, assists Linnehan.


The second spacewalk, with Linnehan andForeman, is scheduled for flight day 6. It willfocus on Dextre and include installation of itstwo arms. Behnken will provide intravehicularsupport while Johnson and Reisman operateCanadarm2.

Flight day 7 is filled with a variety of activities,including work with the new Japanese moduleand transfer operations. The standardspacewalk procedures review, this one for thethird spacewalk, comes toward the end of thecrew day.

EVA 3, by Linnehan and Behnken, will occuron flight day 8, with Foreman providingintravehicular support. Johnson and Reismanwill run Canadarm2 to help the spacewalkersstow replacement gear and install a materials

experiment and a Dextre platform for spareparts.

Flight day 9 is highlighted by roboticsoperations, with the station arm manipulatingDextre. The arm first will move Dextre from itspallet to a power and data grapple fixture onthe U.S. laboratory Destiny. The arm willreturn the pallet to Endeavour’s payload bayand then move Dextre again, this time to aposition where it will be protected during a tilerepair test on spacewalk four.

Flight day 10 includes some off duty time forshuttle crew members and tool configurationfor spacewalk four, preparations for the tilerepair test, and the standard day beforespacewalk procedures review.

Attired in a training version of his shuttle launch and entry suit, astronaut Mike Foreman,STS 123 mission specialist, takes a moment for a photo during a training session in the

Space Vehicle Mockup Facility.


On flight day 11, Behnken and Foreman arescheduled to do EVA 4, with intravehicularsupport from Linnehan. The spacewalk includesthe shuttle tile repair test and change out of an ISScircuit breaker.

An OBSS survey of Endeavour’s wings and nosecap by Gorie, Johnson and Doi is scheduled forflight day 12. Once again, spacewalk toolsconfiguration and the end of day proceduresreview for the flight’s final spacewalk are alsoplanned.

During the fifth and final spacewalk on flightday 13, Behnken and Foreman will stow the OBSSon the station’s main truss. With Linnehan asintravehicular officer, they’ll also release launchlocks on Harmony’s left and Earth facingcommon berthing mechanisms and perform othertasks including installation of Trundle BearingAssembly 5 in starboard Solar Alpha Rotary Joint(SARJ) andmore SARJ inspection work.

Much of flight day 14’s morning will be off dutytime for shuttle crew members. Later they’ll alsohold the joint crew news conference, wrap upequipment and logistics transfers between thestation and shuttle and check out rendezvoustools.

Highlighting flight day 15 are crew farewells,hatch closings, undocking, Endeavour’sfly around of the station with pilot Johnson at thecontrols, and departure.

Landing preparations, including checkout of theflight control system and the reaction controlsystem, are the focus of flight day 16. Crewmembers will stow items in the cabin and hold adeorbit briefing just before bedtime.

Deorbit preparations, and landing at the KennedySpace Center (KSC) on flight day 17 wind upEndeavour’s lengthy and demanding STS 123mission to the ISS.

This image shows the pressurized Kibo Japanese Experiment LogisticsModule that will be installed during the STS 123 mission.

MARCH 2008 TIMELINE OVERVIEW 11

TIMELINE OVERVIEW Flight Day 1

Launch

Payload Bay Door Opening

Ku band Antenna Deployment

Shuttle Robotic Arm Activation andCheckout

Umbilical Well and Handheld ExternalTank Video and Stills Downlink

2

Endeavour Thermal Protection SystemSurvey with OBSS

Extravehicular Mobility Unit Checkout

Centerline Camera Installation

Orbiter Docking System Ring Extension

Orbital Maneuvering System Pod Survey

Rendezvous Tools Checkout

3

Rendezvous with the ISS

Rendezvous Pitch Maneuver Photographyby the Expedition 16 Crew

Docking to Harmony/Pressurized MatingAdapter 2

Hatch Opening and Welcoming

Station to Shuttle Power Transfer System(SSPTS) Activation

Canadarm2 Grapple of Spacelab Palletcontaining the Dextre Special PurposeDexterous Manipulator (SPDM) andtransfer and mate to the Payload OrbitalReplacement Unit Attachment Device(POA) on the Mobile Base System.

Reisman and Eyharts exchange Soyuzseatliners; Reisman joins Expedition 16,Eyharts joins the STS 123 crew

Extravehicular Activity (EVA) 1 ProcedureReview

EVA 1 Campout by Linnehan and Reisman

EVA 1 by Linnehan and Reisman JapaneseExperiment Logistics Module PressurizedSection (ELM PS) unberth preparations,Orbital Replacement Unit and ToolChangeout Mechanism installation on eachof Dextre’s two arms

JEM ELM PS Grapple, Unberth andInstallation on Zenith Port of Harmony

JEM ELM PS Ingress Preparations

JEM ELM PS Ingress

Canadarm2 Grapple of OBSS and Handoffto Shuttle Robotic Arm

EVA 2 Procedure Review

EVA 2 Campout by Linnehan and Foreman

12 TIME INE OVERVIEW MARCH 2008

EVA 2 by Linnehan and Foreman (Dextreassembly)

Dextre Joint and Brake Tests andDiagnostics

JEM ELM PS Outfitting

JEM ELM PS Racks and Systems Outfitting

Dextre Arm and Brake Tests


EVA 3 Campout by Linnehan and Behnken

8

EVA 3 by Linnehan and Behnken (OrbitalReplacement Unit stowage, MISSE 6lightweight adapter plate assemblyinstallation and transfer of MISSE 6experiments to Columbus and Dextre sparepart platform and tool handling assembly)

Dextre End Effector Checkout andCalibration

Crew Off Duty Periods

Canadarm2 Grapple of Dextre and Transferto Power and Data Grapple Fixture onDestiny Laboratory; Dextre’s L.C. Arms areStowed

T RAD EVA Hardware Preparation

10



EVA 4 Campout by Foreman and Behnken

11

EVA 4 by Foreman and Behnken (T RADDTO, Remote Power Control Modulereplacement including temporary CMG 2shutdown and spinup)

Retrieve the JEM TV Electronics Boom fromthe ELM PS

12

OBSS Inspection of Endeavour’s HeatShield

Mobile Transporter Move from Worksite 6to Worksite 4


EVA 5 Campout by Foreman and Behnken

13

EVA 5 by Foreman and Behnken (OBSSstow on station truss, repair andreplacement of Destiny Laboratorymicrometeoroid debris shields, release oflaunch locks on Harmony port and nadirCommon Berthing Mechanisms)

Installation of Trundle Bearing Assembly 5in starboard SARJ

SARJ Inspection

1

Joint Crew News Conference


Rendezvous Tools Checkout

Final Transfers


1

Final Farewells and Hatch Closing

Undocking

Flyaround of the ISS

Final Separation

1

Flight Control System Checkout

Reaction Control System Hot Fire Test

Cabin Stowage

European Space Agency’s (ESA’s)PAO Event

Eyharts’ Recumbent Seat Set Up

Crew Deorbit Briefing

Ku Band Antenna Stowage

1

Deorbit Preparations

Payload Bay Door Closing

Deorbit Burn

KSC Landing


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MARCH 2008 MISSION PROFILE 15

MISSION PROFILE CREW

Commander: Dominic GoriePilot: Gregory H. JohnsonMission Specialist 1: Robert L. BehnkenMission Specialist 2: Mike ForemanMission Specialist 3: Takao DoiMission Specialist 4: Rick LinnehanMission Specialist 5: Garrett Reisman (Up)Mission Specialist 5: Léopold Eyharts (Down)

LAUNCHOrbiter: Endeavour (OV 105)Launch Site: Kennedy Space Center

Launch Pad 39ALaunch Date: March 11, 2008Launch Time: 2:28 a.m. EDT (Preferred

In Plane launch time for3/11)

Launch Window: 5 MinutesAltitude: 122 Nautical Miles

(140 Miles) OrbitalInsertion; 185 NM(213 Miles) Rendezvous

Inclination: 51.6 DegreesDuration: 15 Days 16 Hours

48 Minutes

VEHICLE DATA Shuttle Liftoff Weight: 4,521,086

poundsOrbiter/Payload Liftoff Weight: 269,767

poundsOrbiter/Payload Landing Weight: 207,582

poundsSoftware Version: OI 32

Space Shuttle Main Engines:

SSME 1: 2047SSME 2: 2044SSME 3: 2054External Tank: ET 126SRB Set: BI 133RSRM Set: 101

SHUTTLE ABORTS

Abort Landing Sites

RTLS: Kennedy Space Center ShuttleLanding Facility

TAL: Primary – Zaragoza, SpainAlternates – Moron, Spain andIstres, France

AOA: Primary – Kennedy Space CenterShuttle Landing Facility;Alternate – White Sands SpaceHarbor

LANDING

Landing Date: March 26, 2008Landing Time: 8:35 p.m. EDTPrimary landing Site: Kennedy Space Center

Shuttle Landing Facility

PAYLOADSKibo Logistics Module, Dextre Robotics System

1 MISSION RO I E MARCH 2008


MARCH 2008 MISSION PRIORITIES 17

MISSION PRIORITIES 1. Dock Endeavour to Pressurized Mating

Adapter 2 and do station safety briefingsfor all crew members

2. Replace Expedition 16 Flight EngineerLeopold Eyharts with Expedition 16/17Flight Engineer Garrett Reisman andtransfer crew rotation cargo

3. Transfer remaining items on flightballasting plan

4. Install the ELM PS, the smaller of twopressurized modules of Kibo, to atemporary position on a docking port on thespace facing side of Harmony

5. Do critical ELM PS activation

6. Using the station’s Canadarm2, unberth theSPDM, or Dextre, on its pallet and install itin a temporary position on the station

7. Do Mobile Base System checkout to ensurethe MBS can provide heater power toDextre

8. Install umbilical for keep alive power andstow OBSS on station

9. Transfer water from shuttle to space station

10. Transfer critical items

11. Transfer European plant experiment(WAICO) samples from station to shuttleincubator

12. Transfer two double cold bags with HumanResearch Program (HRP) nutrition samplesand IMMUNO samples to shuttle mid deck

13. Assemble and deploy SPDM Dextre

14. Use Canadarm2 to berth SPDM Dextrepallet

15. Transfer Canadarm2 yaw joint fromshuttle to station External StowagePlatform 2 (ESP 2)

16. Transfer two direct current switching unitsfrom shuttle to ESP 2.

18 MISSION RIORITIES MARCH 2008


MARCH 2008 MISSION PERSONNEL 19

MISSION PERSONNEL KEY CONSOLE POSITIONS FOR STS-123

Flt. Director CAPCOM PAO

Ascent Bryan Lunney Jim DuttonKevin Ford (Weather)

Kyle Herring

Orbit 1 (Lead) Mike Moses Terry Virts John Ira Petty(Lead)

Orbit 2 Rick LaBrode Nick Patrick Kylie Clem

Planning Matt Abbott Alvin Drew Brandi Dean

Entry Richard Jones Jim DuttonKevin Ford (Weather)

Kyle Herring

Shuttle Team 4 Richard Jones/Tony Ceccacci

N/A N/A

ISS Orbit 1 Kwatsi Alibaruho Zach Jones N/A

ISS Orbit 2 (Lead) Dana Weigel Steve Robinson N/A

ISS Orbit 3 Ginger Kerrick Mark Vande Hei N/A

Station Team 4 Heather Rarick Bob Dempsey Ron Spencer

Int. Partner FD – Emily Nelson (interfaces with Canadian Space Agency and Japan AerospaceExploration Agency)

HQ PAO Representative at KSC for Launch – Michael Curie

JSC PAO Representative at KSC for Launch – Rob Lazaro

KSC Launch Commentator – George Diller

KSC Launch Director – Mike Leinbach

NASA Launch Test Director – Steve Payne

20 MISSION ERSONNE MARCH 2008


MARCH 2008 CREW 21

STS-123 ENDEAVOUR CREW The STS 123 crew patch depicts the shuttle inorbit with the crew names trailing behind.STS 123’s major additions to the InternationalSpace Station: the Kibo Japanese ELM PS and

the Canadian SPDM, known as Dextre, are bothillustrated. The station is shown in theconfiguration that the STS 123 crew willencounter upon arrival.

22 CREW MARCH 2008

These seven astronauts take a break from training to pose for the STS 123 crew portrait. Fromthe right (front row) are astronauts Dominic Gorie, commander; and Gregory H. Johnson, pilot.From the left (back row) are astronauts Rick Linnehan, Robert L. Behnken, Garrett Reisman,

Mike Foreman and JAXA’s Takao Doi, all mission specialists. The crew members arewearing shuttle launch and entry suits that are used for training.

Short biographical sketches of the crew followwith detailed background available at:

http://www.jsc.nasa.gov/Bios/

MARCH 2008 CREW 23

STS-123 CREW IO RA HIES

Dominic Gorie

Retired Navy Capt. Dominic Gorie will lead thecrew of STS 123 on the 25th shuttle mission tothe International Space Station. Gorie served asthe pilot of STS 91 in 1998 and STS 99 in 2000.He was the commander of STS 108 in 2001.Making his fourth spaceflight, he has loggedmore than 32 days in space. He has overallresponsibility for the execution of the mission,

orbiter systems operations and flightoperations, including landing. In addition,Gorie will fly the shuttle in a procedure calledthe rendezvous pitch maneuver whileEndeavour is 600 feet below the station toenable the station crew to photograph theshuttle’s heat shield. He then will dockEndeavour to the station.

2 CREW MARCH 2008

Gregory H. Johnson

Air Force Col. Gregory H. Johnson has morethan 4,000 flight hours in more than 40 differentaircraft. He will make his first journey intospace as the pilot of Endeavour for the STS 123mission. Selected by NASA in 1998, Johnsonhas served as a technical assistant to thedirector of flight crew operations. He has also

worked in the Astronaut Office’s space shuttle,safety and exploration branches. He will beresponsible for orbiter systems operations,shuttle and station robotic arm operations andwill help Gorie in the rendezvous and dockingwith the station. Johnson will undockEndeavour from the station.

MARCH 2008 CREW 2

Robert L. Behnken

Air Force Maj. Robert L. Behnken will bemaking his first spaceflight as missionspecialist 1 for STS 123. He holds a doctorate inmechanical engineering and has logged morethan 1,000 hours in more than 25 differentaircraft. Selected as an astronaut in 2000,Behnken has worked in the Astronaut Office

shuttle operations branch, supporting launchand landing activities at KSC. During STS 123he is designated as EV2, or spacewalker 2, andwill conduct three spacewalks. He also willserve as an intravehicular coordinator andoperator of the station robotic arm for the otherspacewalks.

2 CREW MARCH 2008

Mike Foreman

Navy Capt. Mike Foreman will be making hisfirst spaceflight as mission specialist 2 forSTS 123. He has logged more than 5,000 hoursin more than 50 aircraft. Selected as anastronaut in 1998, Foreman has worked in theAstronaut Office space station and space shuttlebranches. Foreman will be on the flight deck

during launch and landing, serving as the flightengineer to assist Gorie and Johnson. He isdesignated as EV3 and will conduct threespacewalks. He also will serve as anintravehicular coordinator for the other twospacewalks.

MARCH 2008 CREW 2

Takao Doi

JAXA astronaut Takao Doi will be making hissecond trip into space as mission specialist 3 forSTS 123. Doi holds doctorates in bothaerospace engineering and astronomy. Helogged more than 376 hours in space for STS 87in 1997. He conducted two spacewalks,including the manual capture of a Spartan

satellite. Doi was selected as an astronaut in1985 with the National Space DevelopmentAgency (NASDA), currently known as JAXA.He reported to JSC in 1995. During STS 123 Doiwill lead the ingress and initial setup of the firstelement of the Kibo Japanese ExperimentLaboratory, the ELM PS.

28 CREW MARCH 2008

Rick Linnehan

Astronaut Rick Linnehan, a doctor of veterinarymedicine, will be making his fourth spaceflightas mission specialist 4 for the STS 123 mission.Selected by NASA in 1992, he has logged morethan 43 days in space, including threespacewalks to service the Hubble SpaceTelescope on Servicing Mission 3B. Linnehan

flew on STS 78 in 1996, STS 90 in 1998 andSTS 109 in 2002. Designated as EV1 for theSTS 123 mission, he will oversee the planningand choreography of all five spacewalks. Hewill conduct the first three and serve as anintravehicular coordinator for the remainingtwo.

MARCH 2008 CREW 2

Garrett Reisman

Astronaut Garrett Reisman will be making hisfirst spaceflight for STS 123. He holds adoctorate in mechanical engineering. Selectedby NASA in 1998, Reisman has worked in theAstronaut Office robotics and advancedvehicles branches. He was part of theNEEMO V mission, living on the bottom of thesea in the Aquarius habitat for two weeks. He

is designated EV4 on STS 123 and will conductone spacewalk. He also will assist withintravehicular duties during the otherspacewalks and operate the station robotic arm.He will serve as a flight engineer duringExpedition 16 and the transition to Expedition17 aboard station. He is scheduled to return onshuttle mission STS 124.

30 CREW MARCH 2008

Leopold Eyharts

Leopold Eyharts, a French astronaut from theCenter National d’Etudes Spatiales (CNES), willreturn to Earth on STS 123. He was selected asan astronaut by CNES in 1990 and by theEuropean Space Agency (ESA) in 1992. Hisfirst mission was to the Mir Space Station in1998, where he supported the CNES scientificspace mission “Pégase.” He performed variousFrench experiments in the areas of medical

research, neuroscience, biology, fluid physicsand technology. He logged 20 days, 18 hoursand 20 minutes in space. In 1998, ESA assignedEyharts to train at NASA’s JSC. He launched tothe space station on the STS 122 mission inFebruary. He was aboard station as a flightengineer during Expedition 16 for thecommissioning of the European Columbuslaboratory.

PAYLOAD OVERVIEW

MARCH 2008 PAYLOAD OVERVIEW 31

KIBO OVERVIEW

Japan’s contribution to the International Space Station Program

The first component of the Japanese experimentmodule, Kibo, will fly to the International SpaceStation (ISS) after 23 years of developmentefforts by the Japan Aerospace ExplorationAgency JAXA. Japan’s role in the space stationprogram is to develop and contribute theJapanese Experiment Module (JEM), logisticsvehicles, and the H II Transfer Vehicle (HTV),using accumulated Japanese technologies.

Once in orbit, the Kibo facilities will be used toperform collaborative experiments by all the

station partners. In addition, JAXA planseducational, cultural and commercial uses ofthe Kibo facility which will provideopportunities for expanded utilization of thespace environment.

Kibo’s contributions are not strictly limited tospace utilizations. The actual development andoperation of Kibo has great significance in thecontinued expansion of Japan’s accumulatedtechnologies. Acquisition of advancedtechnologies required to support human life inspace enhances both the level of Japan’sscientific and technological skill, andcontributes to other worldwide spacedevelopment activities in the futureexploration.

This is an artist’s concept image of Kibo once fully assembled on the space station.

32 A OA OVERVIEW MARCH 2008

Graphic images of the Kibo Pressurized Module interior

E M

Kibo (key boh) means “hope.” It is Japan’s firsthuman rated space facility. Kibo will be thelargest experiment module on the space station,accommodating 31 racks in its pressurizedsection, including experiment, stowage, andsystem racks. Kibo is equipped with externalfacilities that can accommodate 10 exposedexperiment payloads.

Kibo is a complex facility that enables severalkinds of specialized functions. In total, Kiboconsists of: Pressurized Module (PM) andExposed Facility (EF), a logistics moduleattached to both the PM and EF and a RemoteManipulator System – Japanese ExperimentModule Remote Manipulator System(JEMRMS.)

To make maximum use of its limited space,Kibo possesses every function required toperform experiment activities in space: thepressurized and exposed sections, a scientific

airlock in the PM, and a remote manipulatorsystem that enables operation of exposedexperiments without the assistance of aspacewalking crew.

A

The Kibo elements will be delivered to thespace station by three space shuttle flights.STS 123 will deliver the ELM PS, STS 124 willdeliver the PM and JEMRMS, and STS 127 willdeliver the EF and the Experiment LogisticsModule–Exposed Section (ELM ES).

For each of the three missions, a JAXAastronaut will fly to the station to assist withthe assembly, activation, and checkout of theKibo component. Astronaut Takao Doi isassigned as a NASA mission specialist for theSTS 123 mission, astronaut Akihiko Hoshide isassigned as a mission specialist for the STS 124mission, and astronaut Koichi Wakata isassigned as a space station flight engineer forExpedition 18.

MARCH 2008 PAYLOAD OVERVIEW 33

Takao Doi JAXA astronaut

Akihiko Hoshide

Koichi Wakata JAXA astronaut

Launch of ELM-PS Launch of PM and

JEMRMS Launch of EF and ELM-ES

STS-119(15A)

STS-127(2J/A)


T C E M- S

Kibo’s ELM PS will be launched to the spacestation aboard the space shuttle Endeavour onthe STS 123/1J/A mission, which is the first ofthe three Kibo related ISS assembly flights. TheELM PS is a Kibo storage facility that providesstowage space for experiment payloads,samples, and spare items. The pressurizedinterior of the ELM PS is maintained at oneatmosphere, thus providing a shirt sleeveworking environment. The crew will be able tofreely move between the ELM PS and the mainexperiment module, called the PressurizedModule. On the space station, Kibo is the onlyexperiment facility with its own dedicatedstorage facility.

When the ELM PS is launched aboard the spaceshuttle, it will be used as a logistics module fortransporting eight Kibo subsystems and

experiment racks to the space station. Once theELM PS is on orbit, it will be used as a Kibostowage compartment. Maintenance tools,experiment samples, and other spare items willall be stored inside the ELM PS. The volume ofthe ELM PS is less than that of the PM, and upto eight racks can be housed in the ELM PS.

ELM PS structural location

ELM-PS Exposed Facility Unit Common Berthing Mechanism (CBM)

CBM Hatch (for PM)

4.4m

4.2m

ELM PS Structure

MARCH 2008 A OA OVERVIEW 3

ELM PS

ELM-PS Specifications

Shape: indrica

Outer Diameter: eters feet

Inner Diameter: eters feet

Length: eters feet

Mass: 18,490 pounds

Number of Racks: racks

Power Required: kW D

Environment

*Temperature:

*Humidity:

to de rees e sius to

de rees Fahrenheit

to

Design Life: More than ears

The ELM PS will be attached to the zenith porton top of the Harmony Node 2 module onSTS 123’s fourth flight day. The ELM PS willremain attached to the Harmony module untilthe Kibo PM is delivered to the ISS on thefollowing space shuttle mission, STS 124. Thefinal location of the ELM PS will be on the topport of the PM.

E M- S C

The ELM PS will carry five Kibo subsystemracks, two experiment racks, and one stowagerack when transported to the space station onthe STS 123 mission. This includes some of theKibo subsystem racks, which must be installedin the PM before activation after its launch onthe STS 124 mission.

With the exception of the Inter OrbitCommunication System (ICS) –PM rack, thesubsystem racks shown below (marked in redoutline) are crucial to the activation of the PM.


The racks marked in blue outline house theJAXA experiments. In the SAIBO Rack,cultivation of animal cells, plants, and othermicroorganisms will be performed in bothmicrogravity and simulated gravity — 0.1 G to

2 G conditions. In the RYUTAI Rack, fluidphysics phenomena, solution crystallization,and protein crystallization experiments will bemonitored and analyzed.

Star oardFor

ard Aft

E ectrica Po er S ste EPS Rack

Pressuri ed Section Resu Rack PSRR

E eri ent Rack SA

nter- r it o unication S ste S-PM Rack Data Mana e ent S ste

DMS Rack

E eri ent Rack R TA

JEM Re ote Mani uator S ste JEMRMS Rack

Work Station WS Rack

Air in et

Airin et

Airoutet

Air outet

Li ht

Port

Image above shows rack locations in the ELM PS as seen from the PM side. Subsystemracks are marked in red outline, experiment racks in blue, and a stowage rack in green.


M

Pressurized Module and Japanese ExperimentModule Remote Manipulator System(JEMRMS) to be launched on the STS 124/1JMission

The Pressurized Module (PM) is 11.2 meters, or36.7 feet in length, and 4.4 meters, or 14.4 feet indiameter. The pressurized interior of the PM ismaintained at one atmosphere to provide ashirt sleeve working environment. The ISScrew will conduct unique microgravityexperiments within the PM laboratory. The PMwill hold 23 racks, 10 of which are InternationalStandard Payload Racks designed forexperiment payloads. The PM will be deliveredto the ISS aboard the space shuttle Discovery onthe STS 124/1J mission.

Kibo’s robotic arm, or JEMRMS, serves as anextension of the human hand and arm inmanipulating experiments on the EF. TheJEMRMS is composed of the Main Arm and theSmall Fine Arm, which both have sixarticulating joints. The Main Arm is used forexchanging EF payloads and for moving largeitems. The Small Fine Arm, which attaches tothe end of the Main Arm, is used for moredelicate tasks. The crew will operate theserobotic arms from the JEMRMS Console locatedin the PM. The JEMRMS will be launched,along with the PM, to the ISS aboard the spaceshuttle Discovery on the STS 124/1J mission.

Exposed Facility and Experiment LogisticsModule Exposed Section to be launched onthe STS 127/2J/A Mission

The EF provides a multipurpose platformwhere ten science experiment and systempayloads can be deployed and operated in theunpressurized environment of space. Theexperiment payloads attached to the EF will beexchanged using the JEMRMS. The EF will bedelivered to the ISS aboard the space shuttleEndeavour on the STS 127/2J/A mission.

The ELM ES is attached to the end of the EFand provides a storage space for EF experimentpayloads and samples. Up to three experimentpayloads can be stored on the ELM ES. TheELM ES will be launched, along with the EFand ICS EF, to the ISS aboard the space shuttleEndeavour on the STS 127/2J/A mission.


Kibo will be capable of independentcommunications with Tsukuba Space Center(TKSC) once the ICS is installed in both the PMand EF, and fully activated. Through JAXA’sData Relay Test Satellite (DRTS), commandsand voice are uplinked from the ground toKibo, and experiment data, image data or voiceare downlinked from Kibo to the ground forscientific payload operations. The ICS EF has

an antenna and a pointing mechanism that willbe used to communicate with the DRTS.

The ICS EF will be launched, along with the EFand ELM ES, to the ISS aboard the space shuttleEndeavour on the STS 127/2J/A mission, whilethe Inter Orbit Communication System PMRack will be delivered to the ISS onSTS 123/1J/A and installed in the PM duringSTS 124/1J.

S-PM Rack S-EF Su s ste S-EF


I O MISSION CONTRO CENTER

After the Kibo element components are fullyassembled and activated aboard the ISS,full scale experiment operations will begin.

Kibo operations will be jointly monitored andcontrolled from the Space Station Integrationand Promotion Center at Tsukuba, in Japan,and the Mission Control Center at NASA’s JSCin Houston, where the overall operations of thespace station are controlled.

A A C T

The JAXA Flight Control Team (JFCT) consistsof flight directors and more than 50 flightcontrollers assigned to 10 technical disciplinesrequired to support Kibo flight operations. The

flight director oversees and directs the team,and the flight controllers possess specializedexpertise on all Kibo systems. The team willmonitor and control Kibo around the clock in athree shift per day schedule.

Once operational, the JFCT will monitor thestatus of command uplinks, data downlinks,system payloads and experiments aboard Kibo.The JFCT will have the capability to makereal time changes to operations, and cancommunicate directly with the crew aboardKibo and the various international partnermission control centers located around theworld. The team will troubleshoot problems oranomalies that may occur aboard the Kiboduring flight operations.

Kibo Mission Control Room


The JFCT organizes and conducts missionspecific training that accurately simulates actualKibo flight operations. The team is responsiblefor the preparation and evaluation of all plansand procedures that will be performed by thecrew aboard Kibo, and by controllers on theground. In addition, the JFCT regularlyconducts contingency training for all certifiedflight controllers, and candidate flightcontrollers.

The roles of the respective sections of JFCT areas follows:

A A

JAXA Flight Director (J FLIGHT) is the leaderof the JFCT. J FLIGHT will direct the overalloperation of Kibo, including operationsplanning, system and experiment operations,and other tasks performed by the crew aboardKibo.

The flight controllers assigned to each controlsection must ensure that the J FLIGHT is giventhe current status of every detail of Kibooperations.

Mayumi Matsuura will serve as the leadJ FLIGHT for the STS 123/1J/A mission, andwill direct the ELM PS related operationsduring the 1J/A stage.

Lead J FLIGHT for STS 123Mayumi Matsuura

C N S E ICS C

Control and Network Systems, ElectricalPower, and ICS Communication officer(CANSEI) is responsible for Kibo’s flightcontrol, network systems, electrical power andICS communications. CANSEI will monitor thecontrol status of on board computers, networksystems, and electrical power systems throughdata downlinked from Kibo on a real timebasis.

T

Fluid and Thermal officer (FLAT) is responsiblefor monitoring the status of the EnvironmentalControl and Life Support System and theThermal Control System which regulate theheat generated by the equipment aboard Kibo.These systems will be monitored throughtelemetry data downlinked from Kibo on areal time basis.

R

Kibo Robotics officer (KIBOTT) is responsiblefor the overall operation of Kibo’s robotic arms,scientific airlock, and other associatedmechanisms. During robotic arm and airlockoperations, KIBOTT will prepare and monitorthe related systems necessary for the flight crewto perform the appropriate tasks aboard Kibo.

O

Operations Planner (J PLAN) is responsible forplanning the actual flight operations. WhenKibo is in a flight operations status, J PLANwill monitor the status and progress of Kibooperations and, if necessary, will amend ormodify the operation plans as required.


S E I I

System Element Investigation and Integrationofficer (SENIN) is responsible for Kibo’s systemelements. SENIN will monitor and ensure thateach Kibo system is running smoothly and willintegrate all systems information provided byeach flight control section.

T C

Tsukuba Ground Controller (TSUKUBA GC) isresponsible for the overall operation andmaintenance of the ground support facilitiesthat are essential for Kibo flight operations.

This includes the operations control systemsand the operations network systems.

EM C

JEM Communicator (J COM) is responsible forvoice communications with the crew aboardKibo. J COM will communicate all essentialinformation to the crew for operating Kibosystems and experiments, and/or respond toKibo specific inquiries from the crew. JAXAAstronaut Naoko Yamazaki (who is alsoassigned as the Crew Support Astronaut forSTS 123 Mission Specialist Takao Doi) willserve as a J COM officer during the STS 123mission.

JAXA astronaut Naoko Yamazaki will serve as a J COM officer during the STS 123 mission.

42 PAYLOAD OVERVIEW MARCH 2008

Astronaut Related Intravehicle Activity and Equipment Support

Astronaut Related Intravehicular Activity (IVA)and Equipment Support (ARIES) is responsiblefor Intra Vehicular Activity (IVA) operationsaboard Kibo. ARIES will manage the tools andother IVA related support equipment on Kibo.

JEM Payload officer

JEM Payload Officer (JEM PAYLOADS) isresponsible for Kibo’s experiment payloadoperations, and will coordinate payloadactivities with the Primary Investigators of eachrespective experiment.

JAXA Extravehicular Activity

JAXA Extravehicular Activity (JAXA EVA) isresponsible for Kibo related EVA operationsand will provide technical support to the

crew members who perform Kibo relatedspacewalks.

Note: The JAXA EVA console will not belocated in the Space Station OperationsFacility at the Tsukuba Space Center.Instead, the JAXA EVA flight controllerswill be stationed at the NASA JSC.

JEM Engineering Team

The JEM Engineering Team (JET) is responsiblefor providing technical evaluation of real timedata and pre and post flight analysis. JETconsists of the JET lead and electricalsubsystem, fluid subsystem and IVA engineerswho are members of the JEM DevelopmentProject Team. JET engineers also work in theNASA Mission Evaluation Room at NASA JSCin order to perform joint troubleshooting andanomaly resolution.

CANSEI FLAT

Screen Screen Screen

J-COM J-FLIGHT SENIN JEM

PAYLOADTSUKUBA

GC

KIBOTT ARIES J-PLAN

JEMMission Control Room


TSUKUBA SPACE CENTER

Tsukuba Space Center (TKSC) is JAXA’s largestspace development and utilization researchcomplex. As Japan’s primary site for humanspaceflight research and operations, TKSCoperates the following facilities in support ofthe Kibo mission.

S S T

Comprehensive Kibo system tests wereconducted in this building. The main purposeof the tests was to verify function, physicalinterface and performance of the entire Kibosystem including all the associated elements:PM, EF, ELM PS and ELM ES and JEM RMS.In addition, subsystems, payloads, and groundsupport equipment were all tested in thisbuilding. Once Kibo operations begin aboardthe ISS, engineering support will be providedfrom this building.

S E

The following activities are conducted in theSpace Experiment Laboratory (SEL) building:

Development of technologies required forspace experiments

Preparation of Kibo experiment programs

Experiment data analysis and support

A T

The following activities are conducted in theAstronaut Training Facility (ATF) building:

JAXA astronaut candidate training

Astronaut training and health care

This building is a primary site for Japan’s spacemedicine research.

A OA OVERVIEW MARCH 2008

W E T

The Weightless Environment Test Building(WET) facility provides a simulated weightlessenvironment, using water buoyancy, forastronaut training. Design verification tests onvarious Kibo components, and development ofpreliminary spacewalk procedures, wereconducted in this facility.

MARCH 2008 A OA OVERVIEW

S S I C

A OA OVERVIEW MARCH 2008


S ACE STATION INTE RATION AN ROMOTION CENTER

The Space Station Integration and PromotionCenter is responsible for controlling Kibooperations. At the center, operation of Kibosystems and payloads are supervised and Kibooperation plans are prepared in cooperationwith NASA’s Mission Control Center andPayload Operation Integration Center.

The center is responsible for the following:

Monitoring and controlling Kibo operatingsystems

Monitoring and controlling Japaneseexperiments onboard Kibo

Implementing operation plans

Supporting launch preparation

The center consists of the following sections:

M C R

The Mission Control Room (MCR) providesreal time Kibo support on a 24 hour basis. Thisincludes monitoring the health and status ofKibo’s operating systems, payloads, sendingcommands, and real time operational planning.

O A

The User Operations Area (UOA) distributesthe status of Japanese experiments andprovides collected data to the respective usersthat are responsible for the experiments and thesubsequent analysis.

O R

The Operations Planning Room (OPR) isresponsible for the planning of on orbit andground operations based on the power

distribution, crew resources, and datatransmission capacity. If the baseline plansneed to be changed, adjustments will beconducted in tandem with the MCR, the UserOperations Area and NASA.

O R R

The Operations Rehearsal Room (ORR)provides training for flight controllers, andconducts integrated rehearsals and jointsimulations with NASA.

E S R

The Engineering Support Room (ESR) providesengineering support for Kibo operations. Inthis room, the JEM Engineering Team (JET)monitors the data downlinked to the MCR fromKibo, and provides engineering support asrequired.

A A S E ERIMENTS RIN THE 1 A STA E

CE WA RESIST WA

Supported by NASA and ESA, JAXA’s lifescience experiment will be performed on boardthe ISS during the 1J/A Stage. The experimentcombines two research themes entitled CELLWALL and RESIST WALL.

Seeds of thale cress, or “mouse ear cress” —Arabidopsis thaliana — will be launched to theISS on the STS 123 mission. Using ESA’scultivation chamber, “European ModularCultivation System: EMCS” located in theColumbus module, half of the seeds will begrown in a microgravity condition and theother half will be grown in an artificial 1Ggravity condition. The stems of the thale cresswill be collected into sample collection tubes


when the stems have grown to 10 cm in height,approximately 43 days after initiation ofincubation, and then, will be returned to theground on the STS 124 mission.

The goal of this research is to uncover themolecular mechanism in plants that areassumed to be regulated by earth’sgravitational force, and/or verify the gravityresistance mechanism, which is assumed to bean essential response for plants to developagainst the force of gravity on earth.

Thale cress, a.k.a mouse ”ear cress”

PCC and EC (Plant Cultivation Chamberand Experiment Container)

Sample collection tube

A A AEROS ACE O EN A RO RAM

JAXA has been conducting the Aerospace OpenLab Program since June 2004. This program isone of JAXA’s space development supportmeasures, aiming for establishing a foundationfor easier access to the current or future spacedevelopment programs. Currently, 25 jointresearch projects are ongoing as part of theprogram.

Development of clothing for astronauts aboardspacecraft, known as “crew cabin clothing,” isone of the research themes. This research is runby the “Near Future Space Living Unit” groupled by Prof. Yoshiko Taya of Japan Women’sUniversity.


Shirt with short sleeves

The goal of this research group is to developcrew cabin clothing that meets the safetyrequirements for spaceflight, and that ensuresthe following functions:

Thermal comfort

Cleanliness

Mobility

Beautiful clothing contour

Lightweight and compact design

Clothing developed by this research group willbe launched aboard STS 123. During themission, JAXA astronaut Takao Doi will wearthe various clothing types developed by thegroup to evaluate the comfort and functionalityof the clothing.

The group has developed clothing materialswith the following properties required for crewcabin clothing:

Heat insulation

Water absorption

Quick evaporation

Antibacterial

Odor elimination

Antistatic

Antifouling

Soft and comfortable to skin

In addition to those properties, non sewingtechnology has given the clothing softness andwearable comfort. Cutting technology hasimproved the way the clothing fits and movesas the crew works in space.

The group has also developed a hook & loopfastener with fire retardant properties andfabricated with soft touch materials.

Shorts


E TRE CANA IAN RO OTICS OR THE INTERNATIONA S ACE STATION

Dextre is the third and final component of theMobile Servicing System developed by Canadafor the ISS. The two armed Special PurposeDexterous Manipulator, known as “Dextre,”complements the mobile base and the roboticarm Canadarm2 already installed andoperating on the station. These make the MSS a

vital tool for external station maintenance.With advanced stabilization and handlingcapabilities, Dextre can perform delicatehuman scale tasks such as removing andreplacing small exterior components. Operatedby crew members inside the station or by flightcontrollers on the ground, it also is equippedwith lights, video equipment, a stowageplatform, and three robotic tools.

The Special Purpose Dexterous Manipulator can perform delicate humanscale tasks such as removing and replacing small exterior components.


The technology behind Dextre evolved from itsfamous predecessor Canadarm2. Dextre is theworld’s first on orbit servicing robot with anoperational mission, and it lays the foundationfor future satellite servicing and spaceexploration capabilities.

W C

While one arm is used to anchor and stabilizethe system, the other can perform finemanipulation tasks such as removing andreplacing station components, opening andclosing covers, and deploying or retractingmechanisms. Dextre can either be attached tothe end of Canadarm2 or ride independently onthe Mobile Base System. To grab objects,Dextre has special grippers with built in socketwrench, camera, and lights. The two pan/tiltcameras below its rotating torso provideoperators with additional views of the workarea.

Currently, astronauts execute many tasks thatcan only be performed during long, arduous,and potentially dangerous spacewalks.Delivery of this element increases crew safetyand reduces the amount of time that astronautsmust spend outside the station for routinemaintenance. They should therefore have moretime for scientific activities.

Some of the many tasks Dextre will performinclude:

Installing and removing small payloadssuch as batteries, power switching units,and computers

Providing power to payloads

Manipulating, installing, and removingscientific payloads

A typical task for Dextre would be to replace adepleted battery (100 kg, 220 pounds) andengage all the connectors. This involves boltingand unbolting, as well as millimetre levelpositioning accuracy for aligning and insertingthe new battery.

I R S

This kind of task demands high precision and agentle touch. To achieve this, Dextre has aunique technology: precise sensing of theforces and torque in its grip with automaticcompensation to ensure the payload glidessmoothly into its mounting fixture. Dextre canpivot at the waist, and its shoulders supporttwo identical arms with seven offset joints thatallow for great freedom of movement. Thewaist joint allows the operator to change theposition of the tools, cameras, and temporarystowage on the lower body with respect to thearms on the upper body. Dextre is designed tomove only one arm at a time for severalreasons: to maintain stability, to harmonizeactivities with Canadarm on the shuttle andCanadarm2 on the station and to minimize thepossibility of self collision.

At the end of each arm is an orbital replacementunit/tool changeout mechanism, or OTCM —parallel jaws that hold a payload or tool with avice like grip. Each OTCM has a retractablemotorized socket wrench to turn bolts and mateor detach mechanisms, as well as a camera andlights for close up viewing. A retractableumbilical connector can provide power, data,and video connection feed through to payloads.

From a workstation aboard the station,astronauts can operate all the Mobile ServicingSystem components, namely Canadarm2, themobile base, and Dextre. To prepare for


operating each component, astronauts andcosmonauts undergo rigorous training at theCanadian Space Agency’s OperationsEngineering Training Facility at the John H.Chapman Space Centre in Longueuil, Quebec.

C C I S S

Renowned for its expertise in space robotics,Canada’s contribution to the ISS a uniquecollaborative project with the United States,Japan, Russia and several European nations

is the Mobile Servicing System. Combining tworobotic elements and a mobile platform, theyare designed to work together orindependently. The first element, Canadarm2,whose technical name is the Space StationRemote Manipulator System, was deliveredand installed by Canadian Space Agencyastronaut Chris Hadfield in 2001. The mobilebase system was added to the station in 2002.Dextre launches aboard space shuttleEndeavour on flight STS 123.

This image illustrates Dextre working at the end of the station’s Canadarm2.


Dextre can pivot at the waist and its shoulders support two identical armswith seven offset joints that allow for great freedom of movement.

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For more information, visit:

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54 PAYLOAD OVERVIEW MARCH 2008


MARCH 2008 REN E VO S OC IN

REN E VO S AN OC IN

Backdropped by a blue and white Earth, space shuttle Endeavour approaches the InternationalSpace Station during STS 118 rendezvous and docking operations. A Russian spacecraft,

docked to the station, can be seen in the right foreground.

Rendezvous begins with a precisely timedlaunch of the shuttle on the correct trajectoryfor its chase of the International Space Station.A series of engine firings over the nexttwo days will bring Endeavour to a point about50,000 feet behind the station.

Once there, Endeavour will start its finalapproach. About 2.5 hours before docking, theshuttle’s jets will be fired during what is calledthe terminal initiation burn. Endeavour willcover the final miles to the station during thenext orbit.

As Endeavour moves closer to the station, theshuttle’s rendezvous radar system andtrajectory control sensor will give the crewrange and closing rate data. Several smallcorrection burns will place Endeavour about1,000 feet below the station.

Commander Dominic Gorie, with help fromPilot Gregory H. Johnson and other crewmembers, will manually fly the shuttle for theremainder of the approach and docking.

REN E VO S OC IN MARCH 2008

Gorie will stop Endeavour about 600 feet belowthe station. Once he determines there is properlighting, he will maneuver the shuttle through anine minute back flip called the RendezvousPitch Maneuver. That allows the station crewto take as many as 300 digital pictures of theshuttle’s heat shield.

Station crew members will use digital cameraswith 400 mm and 800 mm lenses to photographEndeavour’s upper and bottom surfacesthrough windows of the Zvezda ServiceModule. The 400 mm lens provides up to3 inch resolution and the 800 mm lens up to1 inch resolution.

The photography is one of several techniquesused to inspect the shuttle’s thermal protectionsystem for possible damage. Areas of specialinterest include the tiles, the reinforced carboncarbon of the nose and leading edges of thewings, landing gear doors and the elevon cove.

The photos will be downlinked through thestation’s Ku band communications system foranalysis by systems engineers and missionmanagers.

When Endeavour completes its back flip, it willbe back where it started, with its payload bayfacing the station.

This image illustrates space shuttle Endeavour docking with the International Space Station.

MARCH 2008 REN E VO S OC IN

Gorie then will fly Endeavour through aquarter circle to a position about 400 feetdirectly in front of the station. From that pointhe will begin the final approach to dock at thePressurized Mating Adaptor 2 at the forwardend of the Harmony module.

The shuttle crew members operate laptopcomputers processing the navigational data, thelaser range systems and Endeavour’s dockingmechanism.

Using a video camera mounted in the center ofthe Orbiter Docking System, Gorie will line upthe docking ports of the two spacecraft. Ifnecessary, he will pause 30 feet from the stationto ensure proper alignment of the dockingmechanisms.

He will maintain the shuttle’s speed relative tothe station at about one tenth of a foot per

second, while both Endeavour and the stationare moving at about 17,500 mph. He will keepthe docking mechanisms aligned to a toleranceof three inches.

When Endeavour makes contact with thestation, preliminary latches will automaticallyattach the two spacecraft. The shuttle’s steeringjets will be deactivated to reduce the forcesacting at the docking interface. Shock absorbersprings in the docking mechanism will dampenany relative motion between the shuttle andstation.

Once motion between the shuttle and thestation has been stopped, the docking ring willbe retracted to close a final set of latchesbetween the two vehicles.

Backdropped by Earth, the International Space Station is seen from spaceshuttle Atlantis as the two spacecraft begin separation and the

STS 122 mission nears its completion.

8 REN E VO S OC IN MARCH 2008

N OC IN SE ARATION AN E ART RE

At undocking, hooks and latches will beopened and springs will push Endeavour awayfrom the station. The shuttle’s steering jets willbe shut off to avoid any inadvertent firingsduring the initial separation.

Once Endeavour is about two feet from thestation and the docking devices are clear of oneanother, Johnson will turn the steering jets on

and will manually fly Endeavour in a tightcorridor as the shuttle moves away from thestation.

Endeavour will move away about 450 feet.Then, if propellant and time permit, Johnsonwill begin to fly the shuttle around the stationand its new laboratory. Once Endeavourcompletes 1.5 revolutions of the station,Johnson will fire Endeavour’s jets to leave thearea.

This image depicts space shuttle Endeavour undockingfrom the station following the STS 123 mission.

MARCH 2008 SPACEWALKS 59

SPACEWALKS Five spacewalks performed by four of STS 123’sastronauts will help install the JapaneseELM PS and assemble Dextre, the SPDM.

Spacewalkers also will demonstrate a spaceshuttle heat shield repair technique, using theTile Repair Ablator Dispenser (T RAD), similarto a caulk gun. Foreman and Behnken will usethe T RAD to mix a goo like substance known

as STA 54 and extrude it into holes in severaldemonstration tiles. They will smooth thematerial by tamping it with foam tipped tools.The repaired samples will be stowed inEndeavour’s cargo bay for return to Earth,where they will undergo extensive testing.

STS 123’s spacewalks will occur on flight days4, 6, 8, 11, and 13.

This image illustrates the station’s robotic arm grappling the Orbiter Boom Sensor System inpreparation for its temporary stowage on the station’s S1 truss.

0 S ACEWA S MARCH 2008

Veteran Rick Linnehan is the mission’s leadspacewalker. He conducted three spacewalksin March 2002 during STS 109, the fourthHubble Space Telescope servicing mission.Linnehan will conduct the first three excursionswith three different first time spacewalkers —Garrett Reisman, Mike Foreman andRobert L. Behnken.

Behnken and Foreman will perform the twofinal spacewalks, including the heat shieldrepair demonstration.

The spacewalkers will be identifiable byvarious markings on their spacesuits. Linnehan

will wear the suit bearing solid red stripes.Reisman will wear an all white spacesuit.Foreman’s suit will be distinguished by brokenhorizontal red stripes, and Behnken’s suit willbe marked with a diagonal candy cane stripe.

Each spacewalk will start from the station’sQuest airlock. The astronauts will prepare byusing the campout prebreathe protocol,spending the night before the spacewalk in theairlock. The prebreathe exercise purgesnitrogen from the astronauts’ systems toprevent decompression sickness, also known as“the bends.”

This image depicts the Kibo Japanese Experiment Module that will be installedon the International Space Station during the STS 123 mission.

MARCH 2008 S ACEWA S 1

Mission Specialists Rick Linnehan and Garrett Reisman willconduct the first of the mission’s five scheduled spacewalks.

During the campout, the spacewalking crewmembers isolate themselves in the airlock. Theairlock’s air pressure is lowered to 10.2 poundsper square inch (psi) while the station is kept at14.7 psi, or near sea level pressure. When theywake up, the astronauts don oxygen masks,and the airlock’s pressure is raised to 14.7 psifor an hour. After breakfast, the pressure islowered back to 10.2 psi for an additional houras the astronauts don their spacesuits. Anadditional 30 minutes in the suits completes theprotocol. The campout procedure enablesspacewalks to begin earlier in the crew’s daythan before the protocol was adopted.

EVA-1

EV1: Linnehan

EV4: Reisman

IV: Foreman

Behnken and Eyharts will operate the station’srobotic arm

Duration: 6.5 hours

2 S ACEWA S MARCH 2008

EVA Operations:

Prepare the ELM PS for un erthin froa oad a

Open the Centerline Berthing CameraSystem on top of the Harmony module.The system provides live video to assistwith docking spacecraft and modulestogether

Remove Passive Common BerthingMechanism, the round flange which canattach to another spacecraft or module.Disconnect the launch throughactivation cables

Install both the Orbital ReplacementUnit (ORU) tool change out mechanisms onDextre.

EVA-2

EV1: Linnehan

EV3: Foreman

IV: Behnken

Duration: 7 hours

EVA Operations:

Assemble Dextre, removing covers andinstalling arm components.

Mission specialists Rick Linnehan and Mike Foremanwill conduct the second spacewalk on flight day 6.

MARCH 2008 S ACEWA S 3

EVA-3

EV1: Linnehan

EV2: Behnken

IV: Foreman

Duration: 6.5 hours

EVA Operations:

Outfit Dextre

1. Install the ORU and tool platform/toolholder assembly

2. Install the Camera Light Pan TiltAssembly (CLPA)

3. Remove the cover

Prepare the Spacelab Logistics Pallet forlanding

Move the MISSE 6 experiment to theColumbus module

Transfer a spare Canadarm2 yaw joint

Transfer two spare Direct CurrentSwitching Units

Mission specialists Rick Linnehan and Robert Behnken will conductthe mission’s third spacewalk scheduled for flight day 8.

S ACEWA S MARCH 2008

EVA-

EV2: Behnken

EV3: Foreman

IV: Linnehan

Duration: 6.5 hours

EVA Operations:

Replace a failed Remote Power ControllerModule on the station’s truss

T RAD Detailed Test Objective (DTO) 848,the heat shield repair demonstration

Mission specialists Robert Behnken and Mike Foreman will conductthe mission’s final two spacewalks on flight days 11 and 13.

MARCH 2008 S ACEWA S

EVA-

EV2: Behnken

EV3: Foreman

IV: Linnehan

Duration: 6.5 hours

EVA Operations:

Transfer the OBSS to a temporary stowagelocation on the S1 truss.

Install ELM PS trunnion covers

Reinstall Trundle Bearing Assembly No. 5in the starboard SARJ

Release launch locks on Harmony’s portand nadir Common Berthing Mechanisms

Remove additional covers from thestarboard SARJ and perform inspections,capture digital photography and performdebris collection

S ACEWA S MARCH 2008


MARCH 2008 EXPERIMENTS 67

EXPERIMENTSDETAILED TEST OBJECTIVES

Detailed Test Objectives (DTOs) are aimed attesting, evaluating or documenting spaceshuttle systems or hardware, or proposedimprovements to the space shuttle or spacestation hardware, systems and operations.

DTO 848 Tile Repair Ablator Dispenser

The primary purpose of the detailed testobjective is to evaluate the Shuttle TileAblator 54 (STA 54) material and a tile repairablator dispenser in a microgravity andvacuum environment for their use as a spaceshuttle thermal protection system repairtechnique.

Spacewalkers Robert Behnken and MikeForeman on flight day 11 will set up for the teston the outside of the Destiny lab.

The Tile Repair Ablator Dispenser (T RAD) issimilar to a caulk gun. Both spacewalkers willuse the T RAD to mix and extrude the STA 54material into holes in several demonstrationtiles. The spacewalkers will watch for swellingof the material and work it in until it is smoothby tamping the material with foam tippedtools.

The repaired samples and tools will be stowedin Endeavour’s cargo bay for return to Earth.The samples will undergo extensive testing onthe ground.

DTO 853 In-Flight Evaluation for Areas of CO 2 Concentration

The purpose of the DTO is to evaluate carbondioxide (CO2) levels at specific times during themission and in shuttle areas that have the

potential to contain elevated levels. The DTO isbeing carried out over four missions: STS 118,STS 120, STS 122 and STS 123. During themissions, the data will be collected over aperiod of five days, during similar time periodsand in similar locations.

The CO2 levels will be recorded using theCarbon Dioxide Monitor (CDM) – a portablehandheld device designed to monitor andquantify CO2 concentrations.

The test was prompted by the STS 121 andSTS 115 mission crews who reportedexperiencing stuffiness and headaches whilesleeping in the middeck area. The symptomsare believed to most likely result from exposureto high levels of CO2.

For the reported times during STS 121 andSTS 115, the CO2 levels within the crewmodule, as indicated by the vehicleinstrumentation, were within the acceptablerange. Additionally, for the course of thedocked phase, the CO2 levels in the shuttletracked well with the levels in the station. Thestation crew did not report any symptoms.

Data sampling locations for the test aredependent upon crew sleep locations and highactivity locations because the post sleep activityperiod and high activity periods are the timeswhen CO2 symptoms were reported by the twocrews.

During the upcoming four missions, the crewswill place the CDM in the middeck before theygo to sleep so that ground controllerscan monitor CO2 levels continuously. Theinformation will be used to identify CO2 “hotspots” within the shuttle.

8 E ERIMENTS MARCH 2008

As a result, engineering evaluations will bemade to fine tune air exchange analyses, todetermine if any configuration changes arenecessary to optimize airflow and to determineif operational improvements are needed or ifcrew exposure time in identified areas shouldbe limited.

CDM technology was successfully used todetermine the existence of CO2 pockets on thespace station. The kit that will be used on theshuttle will include the CDM, filters and severalbattery packs. The CDM is capable ofmonitoring CO2 in a localized area for eitherlong or short durations of time, depending onthe operating mode.

TO 80 C I

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

1. Pre launch: Ensure planning will allowselection of a runway with MicrowaveScanning Beam Landing System support,which is a set of dual transmitters locatedbeside the runway providing precisionnavigation vertically, horizontally andlongitudinally with respect to the runway.This precision navigation subsystem helpsprovide a higher probability of a moreprecise landing with a crosswind of 10 to15 knots as late in the flight as possible.

2. Entry: This test requires that the crewperform a manually controlled landing inthe presence of a 90 degree crosswindcomponent of 10 to 15 knots steady state.

During a crosswind landing, the drag chute willbe deployed after nose gear touchdown when

the vehicle is stable and tracking the runwaycenterline.

SHORT- RATION RESEARCH

The space shuttle and International SpaceStation have an integrated research programthat optimizes use of shuttle crew members andlong duration space station crew members toaddress research questions in a variety ofdisciplines.

For information on science on the station:

// / / //

or

// - /

Detailed information is located at:

// / / // /

Validation of Procedures for Monitoring CrewMember Immune Function (IntegratedImmune) will assess the clinical risks resultingfrom the adverse effects of spaceflight on thehuman immune system and will validate aflight compatible immune monitoring strategy.Researchers will collect and analyze blood,urine and saliva samples from crew membersbefore, during and after spaceflight to monitorchanges in their immune systems.

Maui Analysis of Upper AtmosphericInjections (MAUI) will observe the spaceshuttle engine exhaust plumes from theMaui Space Surveillance Site in Hawaii. Theobservations will occur when the shuttle firesits engines at night or twilight. A telescope andall sky imagers will take images and data whilethe shuttle flies over the Maui site. The imageswill be analyzed to better understand the

MARCH 2008 E ERIMENTS

interaction between the spacecraft plume andthe upper atmosphere.

Test of Midodrine as a CountermeasureAgainst Post Flight Orthostatic Hypotension(Midodrine) is a test of the ability of the drugmidodrine to reduce the incidence or severity oforthostatic hypotension. If successful, the drugwill be employed as a countermeasure to thedizziness caused by the blood pressuredecrease that many astronauts experience uponreturning to the Earth’s gravity.

Bioavailablity and Performance Effects ofPromethazine during Spaceflight (PMZ) willexamine the performance impacting side effectsof promethazine and its bioavailability – thedegree to which a drug can be absorbed andused by the parts of the body on which it isintended to have an effect. Promethazine is amedication taken by astronauts to preventmotion sickness.

Sleep Wake Actigraphy and Light Exposureduring Spaceflight Short (Sleep Short) willexamine the effects of spaceflight on thesleep wake cycles of the astronauts duringshuttle missions. Advancing state of the arttechnology for monitoring, diagnosing andassessing treatment of sleep patterns is vital totreating insomnia on Earth and in space.

Rigidizable Inflatable Get Away SpecialExperiment (RIGEX) operates in the spaceshuttle cargo bay and is designed to test andcollect data on inflated and rigid structures inspace. Inflatable tubes will be heated andcooled to form structurally stiff tubes. It willoperate in the U.S. Department of Defense’s(DoD) Canister for All Payload Ejections, alsoknown as CAPE.

S R ISS STS-123

Nutritional Status Assessment (Nutrition) isNASA’s most comprehensive in flight study todate of human physiologic changes duringlong duration spaceflight; this includesmeasures of bone metabolism, oxidativedamage, nutritional assessments and hormonalchanges. This study will impact both thedefinition of nutritional requirements anddevelopment of food systems for future spaceexploration missions to the moon and Mars.The experiment also will help to understand theimpact of countermeasures – exercise andpharmaceuticals – on nutritional status andnutrient requirements for astronauts.

Neuroendocrine and Immune Responses inHumans During and After Long Term Stay atISS (Immuno) provided an understanding forthe development of pharmacological tools tocounter unwanted immunological side effectsduring long duration missions in space. Theaim of this experiment was to determinechanges in stress and immune responses,during and after a stay on the space station.This experiment will help better understand thecoupling between stress and the functioning ofthe immune system.

Waving and Coiling of Arabidopsis Roots atDifferent g levels (WAICO)l studied theinteraction of circumnutation (the successivebowing or bending in different directions of thegrowing tip of the stems and roots) andgravitropism (a tendency to grow toward oraway from gravity) in microgravity and 1 g ofArabidopsis thaliana (commonly known as thalecress). This experiment flew on STS 122 andwas sponsored by the European Space Agency.


A Comprehensive Characterization ofMicroorganisms and Allergens in Spacecraft(SWAB) used advanced molecular techniquesto comprehensively evaluate microbes on boardthe space station, including pathogens(organisms that may cause disease). It trackedchanges in the microbial community asspacecraft visit the station and new stationmodules are added. This study allowed anassessment of the risk of microbes to the crewand the spacecraft.

E ISS

The Reverse Genetic Approach to ExploringGenes Responsible for Cell Wall Dynamics inSupporting Tissues of Arabidopsis UnderMicrogravity Conditions and Role ofMicrotubule Membrane Cell Wall Continuumin Gravity Resistance in Plants (CWRW) is apair of investigations that will explore themolecular mechanism by which the cell wall(rigid outermost layer) construction inArabidopsis thaliana (a small plant of themustard family) is regulated by gravity. Thesecond will determine the importance of thestructural connections between microtubule,plasma membrane, cell wall as the mechanismof gravity resistance. The results of theseinvestigations will support future plans tocultivate plants on long duration explorationmissions.

BCAT 4 (Binary Colloidal Alloy Test 4) is afollow on experiment to BCAT 3. BCAT 4 willstudy ten colloidal samples. Seven of thesesamples will determine phase separation ratesand add needed points to the phase diagram ofa model critical fluid system initially studied inBCAT 3. Three of these samples will use modelhard spheres to explore seeded colloidal crystal

nucleation and the effects of polydispersity,providing insight into how nature brings orderout of disorder.

Lab on a Chip Application DevelopmentPortable Test System (LOCAD PTS) is ahandheld device for rapid detection ofbiological and chemical substances aboard thespace station. Astronauts will swab surfaceswithin the cabin, add swab material to theLOCAD PTS, and within 15 minutes obtainresults on a display screen. The study’spurpose is to effectively provide an earlywarning system to enable crew members totake remedial measures if necessary to protectthe health and safety of those on the station.

Test of Midodrine as a CountermeasureAgainst Post Flight Orthostatic Hypotension –Long (Midodrine Long) is a test of the abilityof the drug midodrine to reduce the incidenceor severity of orthostatic hypotension. Ifsuccessful, it will be employed as acountermeasure to the dizziness caused by theblood pressure decrease that many astronautsexperience upon returning to the Earth’sgravity.

Materials International Space StationExperiment 6A and 6B (MISSE 6A and 6B) isa test bed for materials and coatings attached tothe outside of the station being evaluated forthe effects of atomic oxygen, direct sunlight,radiation, and extremes of heat and cold. Thisexperiment allows the development and testingof new materials to better withstand the rigorsof space environments. Results will provide abetter understanding of the durability ofvarious materials when they are exposed to thespace environment with applications in thedesign of future spacecraft.

MARCH 2008 E ERIMENTS 1

A E A

Saibo Experiment Rack (Saibo) means “livingcell” and is a JAXA multipurpose payload racksystem that transports, stores and supportssub rack facilities aboard the station. Saibo willsupport the following JAXA sub rack facilities:Clean Bench (CB) and Cell Biology ExperimentFacility (CBEF) by providing structuralinterfaces, power, data, cooling, water andother items needed to operate scienceexperiments in microgravity aboard the station.

Ryutai Experiment Rack (Ryutai) means“fluid” and is a JAXA multipurpose payloadrack system that transports, stores and supportssub rack facilities aboard the station. Ryutaiwill support the following JAXA sub rackfacilities: Fluid Physics Experiment Facility(FPEF); Solution Crystallization ObservationFacility (SCOF); Protein CrystallizationResearch Facility (PCRF) and the ImageProcessing Unit (IPU) by providing structuralinterfaces, power, data, cooling, water andother items needed to operate scienceexperiments in microgravity aboard the station.

SPACE SHUTTLE CONTINUOUS IMPROVEMENT

MARCH 2008 CONTINUOUS IMPROVEMENT 73

ENDEAVOUR’S UMBILICAL WELL DIGITAL CAMERA NOW HAS FLASH CAPABILITY

A lighting system derived from an off the shelfflash has been added to the digital cameramounted inside one of the orbiter’s umbilicalwells to capture 23 illuminated photographs ofthe tank as it falls away from the shuttle afterthe main engines shut down 8.5 minutesfollowing launch.

NASA’s JSC Engineering Directorate designedand assembled the Digital Umbilical CameraFlash Module, which consists of two modifiedNikon SB800 flash units, a charging powersystem and thermostatically controlled heaters— all mounted inside a single sealed aluminumhousing measuring 5 x 9 x 13 inches. A slightmodification was made by Nikon to itscommercial off the shelf flash units, whichinvolved gluing the internal reflector in theoptimum position to focus and project the light.

Shedding new light on space shuttle external fuel tanks takes on a new meaningbeginning with Endeavour’s launch on the STS 123 mission.

CONTIN O S IM ROVEMENT MARCH 2008

The flash module will provide light to enablephotography of the external tank as it separatesfrom the shuttle during darkness or heavyshadowing. The flash module, installed in theleft side orbiter external tank umbilical well,begins flashing when signals are sent from thepreviously flown digital umbilical camerainstalled in the right side orbiter external tankumbilical well.

The tank separates 19 seconds after the threemain engines are shutdown, and the digitalcamera and new flash start taking photos fourseconds later. Both flash units dischargesimultaneously in sync with the digital camera,once every two seconds during a 46 secondperiod. The light from the flash will provideadequate lighting for photographs out to therequired distance of 130 feet. At that distance,the tip of the external tank will have movedinto the field of view, and the camera is capableof detecting damage to the tank insulation assmall as 1 to 2 inches in diameter.

The digital umbilical camera system fulfilled arecommendation from the Columbia AccidentInvestigation Board to provide a capability todownlink high resolution images of the externaltank. The digital umbilical camera takes asequence of digital still photographs as the tankseparates from the shuttle. The images arestored in camera memory and are retrievedthrough 130 feet of firewire cable from a laptopcomputer on the shuttle’s flight deck set up bythe crew on the first day of the mission.

The digital images of the tank’s exteriorcondition are transmitted to the Mission

Control Center (MCC) in Houston, and ExternalTank Project Office in Huntsville, Ala., foranalysis. Though there currently is norequirement for lighted imagery of the externaltank, it is highly desirable for imagery analysisexperts to review and correlate any foam lossseen during launch by ground cameras andthose located on the tank itself and on the solidrocket boosters.

Prototype and qualification units were testedover the operational range of 15 to 130 feet.Johnson imagery experts then verified that thedesign provided sufficient light output to meetresolution requirements and determinedoptimal camera aperture settings for day ornight. The design, fabrication and certificationof four flight units cost about $1.2 million.

The new umbilical well flash will fly onremaining shuttle missions and will flash on allpictures — day or night. The camera will havedifferent settings for day or night photography.These settings can be changed remotely fromthe laptop computer in the crew cabin beforelaunch if the date slips such that the tankseparation would occur in day or night, or viceversa.

The camera and flash unit are installed after theshuttle is mated to its tank in KSC’s VehicleAssembly Building. After installation, thecamera, flash and image transmission are testedto ensure the system is working properly.

Expectations are that the flash will be visible inthe external tank feedline camera view as thetank falls away from the shuttle afterseparation.

MARCH 2008 CONTIN O S IM ROVEMENT

Orbiter Umbilical Cameras and Flash

CONTIN O S IM ROVEMENT MARCH 2008


SHUTTLE REFERENCE DATA

MARCH 2008 SHUTTLE REFERENCE DATA 77

SHUTTLE ABORT MODES

Redundant Sequence Launch Sequencer (RSLS) Aborts

These occur when the on board shuttlecomputers detect a problem and command ahalt in the launch sequence after taking overfrom the ground launch sequencer and beforesolid rocket booster ignition.

Ascent Aborts

Selection of an ascent abort mode may becomenecessary if there is a failure that affects vehicleperformance, such as the failure of a spaceshuttle main engine or an orbital maneuveringsystem engine. Other failures requiring earlytermination of a flight, such as a cabin leak,might also require the selection of an abortmode. There are two basic types of ascent abortmodes for space shuttle missions: intact abortsand contingency aborts. Intact aborts aredesigned to provide a safe return of the orbiterto a planned landing site. Contingency abortsare designed to permit flight crew survivalfollowing more severe failures when an intactabort is not possible. A contingency abortwould generally result in a ditch operation.

Intact Aborts

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

Return to Launch Site

The RTLS abort mode is designed to allow thereturn of the orbiter, crew, and payload to thelaunch site, Kennedy Space Center,approximately 25 minutes after liftoff.

The RTLS profile is designed to accommodatethe loss of thrust from one space shuttle mainengine between liftoff and approximatelyfour minutes 20 seconds, after which notenough main propulsion system propellantremains to return to the launch site. An RTLScan be considered to consist of three stages — apowered stage, during which the space shuttlemain engines are still thrusting; an externaltank separation phase; and the glide phase,during which the orbiter glides to a landing atthe Kennedy Space Center. The powered RTLSphase begins with the crew selection of theRTLS abort, after solid rocket boosterseparation. The crew selects the abort mode bypositioning the abort rotary switch to RTLS anddepressing the abort push button. The time atwhich the RTLS is selected depends on thereason for the abort. For example, athree engine RTLS is selected at the lastmoment, about 3 minutes, 34 seconds into themission; whereas an RTLS chosen due to anengine out at liftoff is selected at the earliesttime, about 2 minutes, 20 seconds into themission (after solid rocket booster separation).

After RTLS is selected, the vehicle continuesdownrange to dissipate excess main propulsionsystem propellant. The goal is to leave onlyenough main propulsion system propellant tobe able to turn the vehicle around, fly backtoward the Kennedy Space Center and achievethe proper main engine cutoff conditions so thevehicle can glide to the Kennedy Space Centerafter external tank separation. During thedownrange phase, a pitch around maneuver isinitiated (the time depends in part on the timeof a space shuttle main engine failure) to orientthe orbiter/external tank configuration to aheads up attitude, pointing toward the launch

8 SH TT E RE ERENCE ATA MARCH 2008

site. At this time, the vehicle is still movingaway from the launch site, but the space shuttlemain engines are now thrusting to null thedownrange velocity. In addition, excess orbitalmaneuvering system and reaction controlsystem propellants are dumped by continuousorbital maneuvering system and reactioncontrol system engine thrustings to improve theorbiter weight and center of gravity for theglide phase and landing.

The vehicle will reach the desired main enginecutoff point with less than 2 percent excesspropellant remaining in the external tank. Atmain engine cutoff minus 20 seconds, a pitchdown maneuver (called powered pitch down)takes the mated vehicle to the required externaltank separation attitude and pitch rate. Aftermain engine cutoff has been commanded, theexternal tank separation sequence begins,including a reaction control system maneuverthat ensures that the orbiter does not recontactthe external tank and that the orbiter hasachieved the necessary pitch attitude to beginthe glide phase of the RTLS.

After the reaction control system maneuver hasbeen completed, the glide phase of the RTLSbegins. From then on, the RTLS is handledsimilarly to a normal entry.

T A

The TAL abort mode was developed toimprove the options available when a spaceshuttle main engine fails after the last RTLSopportunity but before the first time that anAOA can be accomplished with only two spaceshuttle main engines or when a major orbitersystem failure, for example, a large cabinpressure leak or cooling system failure, occursafter the last RTLS opportunity, making itimperative to land as quickly as possible.

In a TAL abort, the vehicle continues on aballistic trajectory across the Atlantic Ocean toland at a predetermined runway. Landingoccurs about 45 minutes after launch. Thelanding site is selected near the normal ascentground track of the orbiter to make the mostefficient use of space shuttle main enginepropellant. The landing site also must have thenecessary runway length, weather conditionsand U.S. State Department approval. The threelanding sites that have been identified for alaunch are Zaragoza, Spain; Moron, Spain; andIstres, France.

To select the TAL abort mode, the crew mustplace the abort rotary switch in the TAL/AOAposition and depress the abort push buttonbefore main engine cutoff (Depressing it aftermain engine cutoff selects the AOA abortmode). The TAL abort mode begins sendingcommands to steer the vehicle toward the planeof the landing site. It also rolls the vehicleheads up before main engine cutoff and sendscommands to begin an orbital maneuveringsystem propellant dump (by burning thepropellants through the orbital maneuveringsystem engines and the reaction control systemengines). This dump is necessary to increasevehicle performance (by decreasing weight) toplace the center of gravity in the proper placefor vehicle control and to decrease the vehicle’slanding weight. TAL is handled like a normalentry.

A O

An ATO is an abort mode used to boost theorbiter to a safe orbital altitude whenperformance has been lost and it is impossibleto reach the planned orbital altitude. If a spaceshuttle main engine fails in a region that resultsin a main engine cutoff under speed, theMission Control Center will determine that an

MARCH 2008 SH TT E RE ERENCE ATA

abort mode is necessary and will inform thecrew. The orbital maneuvering system engineswould be used to place the orbiter in a circularorbit.

A O A

The AOA abort mode is used in cases in whichvehicle performance has been lost to such anextent that either it is impossible to achieve aviable orbit or not enough orbital maneuveringsystem propellant is available to accomplish theorbital maneuvering system thrustingmaneuver to place the orbiter on orbit and thedeorbit thrusting maneuver. In addition, anAOA is used in cases in which a major systemsproblem (cabin leak, loss of cooling) makes itnecessary to land quickly. In the AOA abortmode, one orbital maneuvering systemthrusting sequence is made to adjust thepost main engine cutoff orbit so a secondorbital maneuvering system thrusting sequencewill result in the vehicle deorbiting and landingat the AOA landing site (White Sands, N.M.;Edwards Air Force Base, Calif.; or the KennedySpace Center, Fla). Thus, an AOA results in theorbiter circling the Earth once and landingabout 90 minutes after liftoff.

After the deorbit thrusting sequence has beenexecuted, the flight crew flies to a landing at theplanned site much as it would for a nominalentry.

C A

Contingency aborts are caused by loss of morethan one main engine or failures in othersystems. Loss of one main engine whileanother is stuck at a low thrust setting also maynecessitate a contingency abort. Such an abortwould maintain orbiter integrity for in flightcrew escape if a landing cannot be achieved at asuitable landing field.

Contingency aborts due to system failures otherthan those involving the main engines wouldnormally result in an intact recovery of vehicleand crew. Loss of more than one main enginemay, depending on engine failure times, resultin a safe runway landing. However, in mostthree engine out cases during ascent, theorbiter would have to be ditched. The inflightcrew escape system would be used beforeditching the orbiter.

A

There is a definite order of preference for thevarious abort modes. The type of failure and thetime of the failure determine which type of abortis selected. In cases where performance loss isthe only factor, the preferred modes are ATO,AOA, TAL and RTLS, in that order. The modechosen is the highest one that can be completedwith the remaining vehicle performance.

In the case of some support system failures,such as cabin leaks or vehicle cooling problems,the preferred mode might be the one that willend the mission most quickly. In these cases,TAL or RTLS might be preferable to AOA orATO. A contingency abort is never chosen ifanother abort option exists.

Mission Control Houston is prime for callingthese aborts because it has a more preciseknowledge of the orbiter’s position than thecrew can obtain from on board systems. Beforemain engine cutoff, Mission Control makesperiodic calls to the crew to identify whichabort mode is (or is not) available. If groundcommunications are lost, the flight crew hason board methods, such as cue cards, dedicateddisplays and display information, to determinethe abort region. Which abort mode is selecteddepends on the cause and timing of the failurecausing the abort and which mode is safest or


improves mission success. If the problem is aspace shuttle main engine failure, the flightcrew and Mission Control Center select the bestoption available at the time a main engine fails.

If the problem is a system failure thatjeopardizes the vehicle, the fastest abort modethat results in the earliest vehicle landing ischosen. RTLS and TAL are the quickest options(35 minutes), whereas an AOA requires about90 minutes. Which of these is selected dependson the time of the failure with three good spaceshuttle main engines.

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

SH TT E A ORT HISTOR

RS S A H

STS- 1 2 1 8

The countdown for the second launch attemptfor Discovery’s maiden flight ended at T 4seconds when the orbiter’s computers detecteda sluggish valve in main engine No. 3. Themain engine was replaced and Discovery wasfinally launched on Aug. 30, 1984.

STS- 1 12 1 8

The countdown for Challenger’s launch washalted at T 3 seconds when on boardcomputers detected a problem with a coolantvalve on main engine No. 2. The valve wasreplaced and Challenger was launched onJuly 29, 1985.

STS- M 22 1 3

The countdown for Columbia’s launch washalted by on board computers at T 3 secondsfollowing a problem with purge pressurereadings in the oxidizer preburner on main

engine No. 2. Columbia’s three main engineswere replaced on the launch pad, and the flightwas rescheduled behind Discovery’s launch onSTS 56. Columbia finally launched onApril 26, 1993.

STS- 1 A 12 1 3

The countdown for Discovery’s third launchattempt ended at the T 3 second mark whenonboard computers detected the failure of one offour sensors in main engine No. 2 which monitorthe flow of hydrogen fuel to the engine. All ofDiscovery’s main engines were ordered replacedon the launch pad, delaying the shuttle’s fourthlaunch attempt until Sept. 12, 1993.

STS- 8 A 18 1

The countdown for Endeavour’s first launchattempt ended 1.9 seconds before liftoff whenon board computers detected higher thanacceptable readings in one channel of a sensormonitoring the discharge temperature of thehigh pressure oxidizer turbopump in mainengine No. 3. A test firing of the engine at theStennis Space Center in Mississippi onSeptember 2nd confirmed that a slight drift in afuel flow meter in the engine caused a slightincrease in the turbopump’s temperature. Thetest firing also confirmed a slightly slower startfor main engine No. 3 during the pad abort,which could have contributed to the highertemperatures. After Endeavour was broughtback to the Vehicle Assembly Building to beoutfitted with three replacement engines,NASA managers set Oct. 2 as the date forEndeavour’s second launch attempt.

A O H

STS- 1 2 1 8

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

MARCH 2008 SH TT E RE ERENCE ATA 81

Five minutes and 45 seconds after launch, asensor problem resulted in the shutdown ofcenter engine No. 1, resulting in a safe “abort toorbit” and successful completion of the mission.

S ACE SH TT E MAIN EN INES

Developed in the 1970s by NASA’s MarshallSpace Flight Center in Huntsville, Ala., the spaceshuttle main engine is the most advancedliquid fueled rocket engine ever built. Everyspace shuttle main engine is tested and provenflight worthy at NASA’s Stennis Space Center insouth Mississippi, before installation on anorbiter. Its main features include variable thrust,high performance reusability, high redundancyand a fully integrated engine controller.

The shuttle’s three main engines are mountedon the orbiter aft fuselage in a triangularpattern. Spaced so that they are movableduring launch, the engines are used — inconjunction with the solid rocket boosters — tosteer the shuttle vehicle.

Each of these powerful main engines is 14 feet(4.2 meters) long, weighs about 7,000 pounds(3,150 kilograms) and is 7.5 feet (2.25 meters) indiameter at the end of its nozzle.

The engines operate for about 8 1/2 minutesduring liftoff and ascent — burning more than500,000 gallons (1.9 million liters) of super coldliquid hydrogen and liquid oxygen propellantsstored in the huge external tank attached to theunderside of the shuttle. The engines shutdown just before the shuttle, traveling at about17,000 mph (28,000 kilometers per hour),reaches orbit.

The main engine operates at greatertemperature extremes than any mechanicalsystem in common use today. The fuel,liquefied hydrogen at 423 degrees Fahrenheit

( 253 degrees Celsius), is the second coldestliquid on Earth. When it and the liquid oxygenare combusted, the temperature in the maincombustion chamber is 6,000 degreesFahrenheit (3,316 degrees Celsius), hotter thanthe boiling point of iron.

The main engines use a staged combustioncycle so that all propellants entering the enginesare used to produce thrust or power — moreefficiently than any previous rocket engine. Ina staged combustion cycle, propellants are firstburned partially at high pressure and relativelylow temperature — then burned completely athigh temperature and pressure in the maincombustion chamber. The rapid mixing of thepropellants under these conditions is socomplete that 99 percent of the fuel is burned.

At normal operating level, each enginegenerates 490,847 pounds of thrust (measuredin a vacuum). Full power is 512,900 pounds ofthrust; minimum power is 316,100 pounds ofthrust.

The engine can be throttled by varying theoutput of the pre burners, thus varying thespeed of the high pressure turbopumps and,therefore, the flow of the propellant.

At about 26 seconds into launch, the mainengines are throttled down to 316,000 poundsof thrust to keep the dynamic pressure on thevehicle below a specified level — about580 pounds per square foot or max q. Then, theengines are throttled back up to normaloperating level at about 60 seconds. Thisreduces stress on the vehicle. The main enginesare throttled down again at about sevenminutes, 40 seconds into the mission tomaintain three g’s — three times the Earth’sgravitational pull — again reducing stress onthe crew and the vehicle. This acceleration


level is about one third the accelerationexperienced on previous crewed space vehicles.

About 10 seconds before main engine cutoff orMECO, the cutoff sequence begins; aboutthree seconds later the main engines arecommanded to begin throttling at 10 percentthrust per second to 65 percent thrust. This isheld for about 6.7 seconds, and the engines areshut down.

The engine performance has the highest thrustfor its weight of any engine yet developed. Infact, one space shuttle main engine generatessufficient thrust to maintain the flight of2 1/2 747 airplanes.

The space shuttle main engine is also the firstrocket engine to use a built in electronic digitalcontroller, or computer. The controller willaccept commands from the orbiter for enginestart, change in throttle, shutdown, andmonitor engine operation. In the event of afailure, the controller automatically corrects theproblem or safely shuts down the engine.

NASA continues to increase the reliability andsafety of shuttle flights through a series ofenhancements to the space shuttle mainengines. The engines were modified in 1988,1995, 1998, and 2001. Modifications includenew high pressure fuel and oxidizerturbopumps that reduce maintenance andoperating costs of the engine, a two ductpowerhead that reduces pressure andturbulence in the engine, and a single coil heatexchanger that lowers the number of post flightinspections required. Another modificationincorporates a large throat main combustionchamber that improves the engine’s reliabilityby reducing pressure and temperature in thechamber.

After the orbiter lands, the engines are removedand returned to a processing facility atKennedy Space Center, Fla., where they arerechecked and readied for the next flight. Somecomponents are returned to the main engine’sprime contractor, Pratt & Whitney RocketDyne,West Palm Beach, Fla., for regular maintenance.The main engines are designed to operate for7.5 accumulated hours.

S ACE SH TT E SO I ROC ET OOSTERS

The two SRBs provide the main thrust to lift thespace shuttle off the pad and up to an altitudeof about 150,000 feet, or 24 nautical miles(28 statute miles). In addition, the two SRBscarry the entire weight of the external tank andorbiter and transmit the weight load throughtheir structure to the mobile launcher platform.

Each booster has a thrust (sea level) of about3,300,000 pounds at launch. They are ignitedafter the three space shuttle main engines’thrust level is verified. The two SRBs provide71.4 percent of the thrust at liftoff and duringfirst stage ascent. Seventy five seconds afterSRB separation, SRB apogee occurs at analtitude of about 220,000 feet, or 35 nauticalmiles (40 statute miles). SRB impact occurs inthe ocean about 122 nautical miles (140 statutemiles) downrange.

The SRBs are the largest solid propellantmotors ever flown and the first designed forreuse. Each is 149.16 feet long and 12.17 feet indiameter. Each SRB weighs about1,300,000 pounds at launch. The propellant foreach solid rocket motor weighs about1,100,000 pounds. The inert weight of each SRBis about 192,000 pounds.


Primary elements of each booster are the motor(including case, propellant, igniter and nozzle),structure, separation systems, operationalflight instrumentation, recovery avionics,pyrotechnics, deceleration system, thrust vectorcontrol system and range safety destructsystem.

Each booster is attached to the external tank atthe SRB’s aft frame by two lateral sway bracesand a diagonal attachment. The forward end ofeach SRB is attached to the external tank at theforward end of the SRB’s forward skirt. On thelaunch pad, each booster also is attached to themobile launcher platform at the aft skirt by fourbolts and nuts that are severed by smallexplosives at liftoff.

During the downtime following the Challengeraccident, detailed structural analyses wereperformed on critical structural elements of theSRB. Analyses were primarily focused in areaswhere anomalies had been noted duringpostflight inspection of recovered hardware.

One of the areas was the attach ring where theSRBs are connected to the external tank. Areasof distress were noted in some of the fastenerswhere the ring attaches to the SRB motor case.This situation was attributed to the high loadsencountered during water impact. To correctthe situation and ensure higher strength marginsduring ascent, the attach ring was redesigned toencircle the motor case completely (360 degrees).

Previously, the attach ring formed a C andencircled the motor case 270 degrees.

Additionally, special structural tests were doneon the aft skirt. During this test program, ananomaly occurred in a critical weld between thehold down post and skin of the skirt. Aredesign was implemented to add

reinforcement brackets and fittings in the aftring of the skirt.

These two modifications added about450 pounds to the weight of each SRB.

The propellant mixture in each SRB motorconsists 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 mixturetogether, 12.04 percent), and an epoxy curingagent (1.96 percent). The propellant is an11 point star shaped perforation in the forwardmotor segment and a double truncated coneperforation in each of the aft segments and aftclosure. This configuration provides highthrust at ignition and then reduces the thrust byabout a third 50 seconds after liftoff to preventoverstressing the vehicle during maximumdynamic pressure.

The SRBs are used as matched pairs and each ismade up of four solid rocket motor segments.The pairs are matched by loading each of thefour motor segments in pairs from the samebatches of propellant ingredients to minimizeany thrust imbalance. The segmented casingdesign assures maximum flexibility infabrication and ease of transportation andhandling. Each segment is shipped to thelaunch site on a heavy duty rail car with aspecially built cover.

The nozzle expansion ratio of each boosterbeginning 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 hydraulicpumps. The all axis gimbaling capability is8 degrees. Each nozzle has a carbon cloth linerthat erodes and chars during firing. The nozzleis a convergent divergent, movable design in


which an aft pivot point flexible bearing is thegimbal mechanism.

The cone shaped aft skirt reacts the aft loadsbetween the SRB and the mobile launcherplatform. The four aft separation motors aremounted on the skirt. The aft section containsavionics, a thrust vector control system thatconsists of two auxiliary power units andhydraulic pumps, hydraulic systems and anozzle extension jettison system.

The forward section of each booster containsavionics, a sequencer, forward separationmotors, a nose cone separation system, drogueand main parachutes, a recovery beacon, arecovery light, a parachute camera on selectedflights and a range safety system.

Each SRB has two integrated electronicassemblies, one forward and one aft. Afterburnout, the forward assembly initiates therelease of the nose cap and frustum, a transitionpiece between the nose cone and solid rocketmotor, and turns on the recovery aids. The aftassembly, mounted in the external tank/SRBattach ring, connects with the forward assemblyand the orbiter avionics systems for SRBignition commands and nozzle thrust vectorcontrol. Each integrated electronic assemblyhas a multiplexer/demultiplexer, which sendsor receives more than one message, signal orunit of information on a single communicationchannel.

Eight booster separation motors (four in thenose frustum and four in the aft skirt) of eachSRB thrust for 1.02 seconds at SRB separationfrom the external tank. Each solid rocketseparation motor is 31.1 inches long and12.8 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 aminimum operating life of 72 hours and whenrefurbished are considered usable up to20 times. The flashing light is an exception. Ithas an operating life of 280 hours. The batteryis used only once.

The SRB nose caps and nozzle extensions arenot recovered.

The recovery crew retrieves the SRBs,frustum/drogue chutes, and main parachutes.The nozzles are plugged, the solid rocketmotors are dewatered, and the SRBs are towedback to the launch site. Each booster isremoved from the water, and its componentsare disassembled and washed with fresh anddeionized water to limit salt water corrosion.The motor segments, igniter and nozzle areshipped back to ATK Thiokol forrefurbishment.

Each SRB incorporates a range safety systemthat includes a battery power source,receiver/decoder, antennas and ordnance.

H -

Each solid rocket booster has four hold downposts that fit into corresponding support postson the mobile launcher platform. Hold downbolts hold the SRB and launcher platform poststogether. Each bolt has a nut at each end, butonly the top nut is frangible. The top nutcontains two NASA standard detonators(NSDs), which are ignited at solid rocket motorignition commands.

When the two NSDs are ignited at each holddown, the hold down bolt travels downwardbecause of the release of tension in the bolt(pretensioned before launch), NSD gas pressure


and gravity. The bolt is stopped by the studdeceleration stand, which contains sand. TheSRB bolt is 28 inches long and 3.5 inches indiameter. The frangible nut is captured in ablast container.

The solid rocket motor ignition commands areissued by the orbiter’s computers through themaster events controllers to the hold downpyrotechnic initiator controllers on the mobilelauncher platform. They provide the ignition tothe hold down NSDs. The launch processingsystem monitors the SRB hold down PICs forlow voltage during the last 16 seconds beforelaunch. PIC low voltage will initiate a launchhold.

SR I

SRB ignition can occur only when a manuallock pin from each SRB safe and arm device hasbeen removed. The ground crew removes thepin during prelaunch activities. At T minusfive minutes, the SRB safe and arm device isrotated to the arm position. The solid rocketmotor ignition commands are issued when thethree SSMEs are at or above 90 percent ratedthrust, no SSME fail and/or SRB ignition PIClow voltage is indicated and there are no holdsfrom the LPS.

The solid rocket motor ignition commands aresent by the orbiter computers through theMECs to the safe and arm device NSDs in eachSRB. A PIC single channel capacitor dischargedevice controls the firing of each pyrotechnicdevice. Three signals must be presentsimultaneously for the PIC to generate the pyrofiring output. These signals — arm, fire 1 andfire 2 — originate in the orbiter general purposecomputers and are transmitted to the MECs.The MECs reformat them to 28 volt dc signalsfor the PICs. The arm signal charges the

PIC capacitor to 40 volts dc (minimum of20 volts dc).

The fire 2 commands cause the redundantNSDs to fire through a thin barrier seal down aflame tunnel. This ignites a pyro boostercharge, which is retained in the safe and armdevice behind a perforated plate. The boostercharge ignites the propellant in the igniterinitiator; and combustion products of thispropellant ignite the solid rocket motorinitiator, which fires down the length of thesolid rocket motor igniting the solid rocketmotor propellant.

The GPC launch sequence also controls certaincritical main propulsion system valves andmonitors the engine ready indications from theSSMEs. The MPS start commands are issued bythe on board computers at T minus 6.6 seconds(staggered start — engine three, engine two,engine one — all about within 0.25 of a second),and the sequence monitors the thrust buildupof each engine. All three SSMEs must reach therequired 90 percent thrust within three seconds;otherwise, an orderly shutdown is commandedand safing functions are initiated.

Normal thrust buildup to the required 90percent thrust level will result in the SSMEsbeing commanded to the liftoff position atT minus three seconds as well as the fire 1command being issued to arm the SRBs. AtT minus three seconds, the vehicle basebending load modes are allowed to initialize(movement of 25.5 inches measured at the tip ofthe external tank, with movement towards theexternal tank).

At T minus zero, the two SRBs are ignitedunder command of the four on boardcomputers; separation of the four explosivebolts on each SRB is initiated (each bolt is


28 inches long and 3.5 inches in diameter); thetwo T 0 umbilicals (one on each side of thespacecraft) are retracted; the on board mastertiming unit, event timer and mission eventtimers are started; the three SSMEs are at100 percent; and the ground launch sequence isterminated.

The solid rocket motor thrust profile is tailoredto reduce thrust during the maximum dynamicpressure region.

E

Electrical power distribution in each SRBconsists of orbiter supplied main dc bus powerto each SRB via SRB buses A, B and C. Orbitermain dc buses A, B and C supply main dc buspower to corresponding SRB buses A, B and C.In addition, orbiter main dc bus C suppliesbackup power to SRB buses A and B, andorbiter bus B supplies backup power to SRBbus C. This electrical power distributionarrangement allows all SRB buses to remainpowered in the event one orbiter main bus fails.

The nominal dc voltage is 28 volts dc, with anupper limit of 32 volts dc and a lower limit of24 volts dc.

H

There are two self contained, independentHPUs on each SRB. Each HPU consists of anauxiliary power unit, fuel supply module,hydraulic pump, hydraulic reservoir andhydraulic fluid manifold assembly. The APUsare fueled by hydrazine and generatemechanical shaft power to a hydraulic pumpthat produces hydraulic pressure for the SRBhydraulic system. The two separate HPUs andtwo hydraulic systems are located on the aftend of each SRB between the SRB nozzle andaft skirt. The HPU components are mounted on

the aft skirt between the rock and tilt actuators.The two systems operate from T minus28 seconds until SRB separation from theorbiter and external tank. The two independenthydraulic systems are connected to the rock andtilt servoactuators.

The APU controller electronics are located inthe SRB aft integrated electronic assemblies onthe aft external tank attach rings.

The APUs and their fuel systems are isolatedfrom each other. Each fuel supply module(tank) contains 22 pounds of hydrazine. Thefuel 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 positivefuel supply to the APU throughout itsoperation.

The fuel isolation valve is opened at APUstartup to allow fuel to flow to the APU fuelpump and control valves and then to the gasgenerator. The gas generator’s catalytic actiondecomposes the fuel and creates a hot gas. Itfeeds the hot gas exhaust product to the APUtwo stage gas turbine. Fuel flows primarilythrough the startup bypass line until the APUspeed is such that the fuel pump outlet pressureis greater than the bypass line’s. Then all thefuel is supplied to the fuel pump.

The APU turbine assembly providesmechanical power to the APU gearbox. Thegearbox drives the APU fuel pump, hydraulicpump and lube oil pump. The APU lube oilpump lubricates the gearbox. The turbineexhaust of each APU flows over the exterior ofthe gas generator, cooling it, and is thendirected overboard through an exhaust duct.

When the APU speed reaches 100 percent, theAPU primary control valve closes, and the


APU speed is controlled by the APU controllerelectronics. If the primary control valve logicfails to the open state, the secondary controlvalve assumes control of the APU at112 percent speed. Each HPU on an SRB isconnected to both servoactuators on that SRB.One HPU serves as the primary hydraulicsource for the servoactuator, and the other HPUserves as the secondary hydraulics for theservoactuator. Each servoactuator has aswitching valve that allows the secondaryhydraulics to power the actuator if the primaryhydraulic pressure drops below 2,050 psi. Aswitch contact on the switching valve will closewhen the valve is in the secondary position.When the valve is closed, a signal is sent to theAPU controller that inhibits the 100 percentAPU speed control logic and enables the112 percent APU speed control logic. The100 percent APU speed enables one APU/HPUto supply sufficient operating hydraulicpressure to both servoactuators of that SRB.

The APU 100 percent speed corresponds to72,000 rpm, 110 percent to 79,200 rpm, and112 percent to 80,640 rpm.

The hydraulic pump speed is 3,600 rpm andsupplies hydraulic pressure of 3,050, plus orminus 50, psi. A high pressure relief valveprovides overpressure protection to thehydraulic system and relieves at 3,750 psi.

The APUs/HPUs and hydraulic systems arereusable for 20 missions.

T V C

Each SRB has two hydraulic gimbalservoactuators: one for rock and one for tilt.The servoactuators provide the force andcontrol to gimbal the nozzle for thrust vectorcontrol.

The space shuttle ascent thrust vector controlportion of the flight control system directs thethrust of the three shuttle main engines and thetwo SRB nozzles to control shuttle attitude andtrajectory during liftoff and ascent. Commandsfrom the guidance system are transmitted to theATVC drivers, which transmit signalsproportional to the commands to eachservoactuator of the main engines and SRBs.Four independent flight control systemchannels and four ATVC channels control sixmain engine and four SRB ATVC drivers, witheach driver controlling one hydraulic port oneach main and SRB servoactuator.

Each SRB servoactuator consists of fourindependent, two stage servovalves thatreceive signals from the drivers. Eachservovalve controls one power spool in eachactuator, which positions an actuator ram andthe nozzle to control the direction of thrust.

The four servovalves in each actuator provide aforce summed majority voting arrangement toposition the power spool. With four identicalcommands to the four servovalves, the actuatorforce sum action prevents a single erroneouscommand from affecting power ram motion. Ifthe erroneous command persists for more than apredetermined time, differential pressuresensing activates a selector valve to isolate andremove the defective servovalve hydraulicpressure, permitting the remaining channels andservovalves to control the actuator ram spool.

Failure monitors are provided for each channelto indicate which channel has been bypassed.An isolation valve on each channel provides thecapability of resetting a failed or bypassedchannel.

Each actuator ram is equipped with transducersfor position feedback to the thrust vectorcontrol system. Within each servoactuator ram


is a splashdown load relief assembly to cushionthe nozzle at water splashdown and preventdamage to the nozzle flexible bearing.

SR R A

Each SRB contains two RGAs, with each RGAcontaining one pitch and one yaw gyro. Theseprovide an output proportional to angular ratesabout the pitch and yaw axes to the orbitercomputers and guidance, navigation and controlsystem during first stage ascent flight inconjunction with the orbiter roll rate gyros untilSRB separation. At SRB separation, a switchoveris made from the SRB RGAs to the orbiter RGAs.

The SRB RGA rates pass through the orbiterflight aft multiplexers/demultiplexers to theorbiter GPCs. The RGA rates are thenmid value selected in redundancy managementto provide SRB pitch and yaw rates to the usersoftware. The RGAs are designed for20 missions.

SR S

SRB separation is initiated when the three solidrocket motor chamber pressure transducers areprocessed in the redundancy managementmiddle value select and the head end chamberpressure of both SRBs is less than or equal to50 psi. A backup cue is the time elapsed frombooster ignition.

The separation sequence is initiated,commanding the thrust vector control actuatorsto the null position and putting the mainpropulsion system into a second stageconfiguration (0.8 second from sequenceinitialization), which ensures the thrust of eachSRB is less than 100,000 pounds. Orbiter yawattitude is held for four seconds, and SRB thrustdrops to less than 60,000 pounds.

The SRBs separate from the external tankwithin 30 milliseconds of the ordnance firingcommand.

The forward attachment point consists of a ball(SRB) and socket (ET) held together by one bolt.The bolt contains one NSD pressure cartridge ateach end. The forward attachment point alsocarries the range safety system cross strapwiring connecting each SRB RSS and the ETRSS with each other.

The aft attachment points consist of threeseparate struts: upper, diagonal, and lower.Each strut contains one bolt with an NSDpressure cartridge at each end. The upper strutalso carries the umbilical interface between itsSRB and the external tank and on to the orbiter.

There are four booster separation motors oneach end of each SRB. The BSMs separate theSRBs from the external tank. The solid rocketmotors in each cluster of four are ignited byfiring redundant NSD pressure cartridges intoredundant confined detonating fuse manifolds.

The separation commands issued from theorbiter by the SRB separation sequence initiatethe redundant NSD pressure cartridge in eachbolt and ignite the BSMs to effect a cleanseparation.

S ACE SH TT E S ER I HT WEI HT TAN S WT

The super lightweight external tank (SLWT)made its first shuttle flight June 2, 1998, onmission STS 91. The SLWT is 7,500 poundslighter than the standard external tank. Thelighter weight tank allows the shuttle to deliverInternational Space Station elements (such asthe service module) into the proper orbit.


The SLWT is the same size as the previousdesign. But the liquid hydrogen tank and theliquid oxygen tank are made of aluminumlithium, a lighter, stronger material than themetal alloy used for the shuttle’s current tank.The tank’s structural design has also beenimproved, making it 30 percent stronger and5 percent less dense.

The SLWT, like the standard tank, ismanufactured at Michoud Assembly, nearNew Orleans, by Lockheed Martin.

The 154 foot long external tank is the largestsingle component of the space shuttle. It standstaller than a 15 story building and has adiameter of about 27 feet. The external tankholds over 530,000 gallons of liquid hydrogenand liquid oxygen in two separate tanks. Thehydrogen (fuel) and liquid oxygen (oxidizer)are used as propellants for the shuttle’s threemain engines.

LAUNCH AND LANDING

MARCH 2008 LAUNCH & LANDING 91

LAUNCH

As with all previous space shuttle launches,Atlantis has several options to abort its ascent ifneeded due to engine failures or other systemsproblems. Shuttle launch abort philosophy isintended to facilitate safe recovery of the flightcrew and intact recovery of the orbiter and itspayload.

Abort modes include:

ABORT-TO-ORBIT (ATO)

This mode is used if there’s a partial loss ofmain engine thrust late enough to permitreaching a minimal 105 by 85 nautical mile orbitwith the orbital maneuvering system engines.The engines boost the shuttle to a safe orbitalaltitude when it is impossible to reach theplanned orbital altitude.

TRANSATLANTIC ABORT LANDING (TAL)

The loss of one or more main engines midwaythrough powered flight would force a landingat either Zaragoza, Spain; Moron, Spain; orIstres, France. For launch to proceed, weatherconditions must be acceptable at one of theseTAL sites.

RETURN-TO-LAUNCH-SITE (RTLS)

If one or more engines shuts down early andthere’s not enough energy to reach Zaragoza,the shuttle would pitch around towardKennedy until within gliding distance of theShuttle Landing Facility. For launch toproceed, weather conditions must be forecast tobe acceptable for a possible RTLS landing atKSC about 20 minutes after liftoff.

ABORT ONCE AROUND (AOA)

An AOA is selected if the vehicle cannotachieve a viable orbit or will not have enoughpropellant to perform a deorbit burn, but hasenough energy to circle the Earth once and landabout 90 minutes after liftoff.

LANDING

The primary landing site for Atlantis onSTS 122 is the Kennedy Space Center’s ShuttleLanding Facility. Alternate landing sites thatcould be used if needed because of weatherconditions or systems failures are at EdwardsAir Force Base, Calif., and White Sands SpaceHarbor, N.M.

92 LAUNCH & LANDING MARCH 2008


MARCH 2008 ACRON MS A REVIATIONS 3

ACRON MS AN A REVIATIONS

A/G Alignment GuidesA/L AirlockAAA Avionics Air AssemblyABC Audio Bus ControllerACBM Active Common Berthing MechanismACDU Airlock Control and Display UnitACO Assembly Checkout OfficerACS Atmosphere Control and SupplyACU Arm Control UnitADS Audio Distribution SystemAE Approach EllipsoidAEP Airlock Electronics PackageAI Approach InitiationAJIS Alpha Joint Interface StructureAM Atmosphere MonitoringAMOS Air Force Maui Optical and Supercomputing SiteAOH Assembly Operations HandbookAPAS Androgynous Peripheral AttachmentAPCU Assembly Power Converter UnitAPE Antenna Pointing Electronics

Audio Pointing EquipmentAPFR Articulating Portable Foot RestraintAPM Antenna Pointing MechanismAPS Automated Payload SwitchAPV Automated Procedure ViewerAR Atmosphere RevitalizationARCU American to Russian Converter UnitARS Atmosphere Revitalization SystemASW Application SoftwareATA Ammonia Tank AssemblyATCS Active Thermal Control SystemATU Audio Terminal Unit

BAD Broadcast Ancillary DataBC Bus ControllerBCDU Battery Charge/Discharge Unit

Berthing Mechanism Control and Display UnitBEP Berthing Mechanism Electronics PackageBGA Beta Gimbal Assembly

ACRON MS A REVIATIONS MARCH 2008

BIC Bus Interface ControllerBIT Built In TestBM Berthing MechanismBOS BIC Operations SoftwareBSS Basic SoftwareBSTS Basic Standard Support Software

C&C Command and ControlC&DH Command and Data HandlingC&T Communication and TrackingC&W Caution and WarningC/L Crew LockC/O CheckoutCAM Collision Avoidance ManeuverCAPE Canister for All Payload EjectionsCAS Common Attach SystemCB Control BusCBCS Centerline Berthing Camera SystemCBM Common Berthing MechanismCCA Circuit Card AssemblyCCAA Common Cabin Air AssemblyCCHA Crew Communication Headset AssemblyCCP Camera Control PanelCCT Communication Configuration TableCCTV Closed Circuit TelevisionCDR CommanderCDRA Carbon Dioxide Removal AssemblyCETA Crew Equipment Translation AidCHeCS Crew Health Care SystemCHX Cabin Heat ExchangerCISC Complicated Instruction Set ComputerCLA Camera Light AssemblyCLPA Camera Light Pan Tilt AssemblyCMG Control Moment GyroCOTS Commercial Off the ShelfCPA Control Panel AssemblyCPB Camera Power BoxCR Change RequestCRT Cathode Ray TubeCSA Canadian Space AgencyCSA CP Compound Specific AnalyzerCVIU Common Video Interface Unit

MARCH 2008 ACRON MS A REVIATIONS

CVT Current Value TableCZ Communication Zone

DB Data BookDCDCSUDDCU

Docking CompartmentDirect Current Switching UnitDC to DC Converter Unit

DEM DemodulatorDFL Decommutation Format LoadDIU Data Interface UnitDMSDMS RDPGDPUDRTSDYF

Data Management SystemData Management System RussianDifferential Pressure GaugeBaseband Data Processing UnitJapanese Data Relay SatelliteDisplay Frame

E/LEATCSEBCSECC

Equipment LockExternal Active Thermal Control SystemExternal Berthing Camera SystemError Correction Code

ECLSSECSECU

Environmental Control and Life Support SystemEnvironmental Control SystemElectronic Control Unit

EDSUEDU

External Data Storage UnitEEU Driver Unit

EE End EffectorEETCSEEUEFEFBMEFHXEFUEGILEIU

Early External Thermal Control SystemExperiment Exchange UnitExposed FacilityExposed Facility Berthing MechanismExposed Facility Heat ExchangerExposed Facility UnitElectrical, General Instrumentation, and LightingEthernet Interface Unit

ELM ESELM PSELPSEMGFEMIEMUE ORU

Japanese Experiment Logistics Module – Exposed SectionJapanese Experiment Logistics Module – Pressurized SectionEmergency Lighting Power SupplyElectric Mechanical Grapple FixtureElectro Magnetic ImagingExtravehicular Mobility UnitEVA Essential ORU

EP Exposed Pallet

ACRON MS A REVIATIONS MARCH 2008

EPS Electrical Power SystemES Exposed SectionESA European Space AgencyESC JEF System ControllerESW Extended Support SoftwareET External TankETCS External Thermal Control SystemETI Elapsed Time IndicatorETRS EVA Temporary Rail StopETVCG External Television Camera GroupEV ExtravehicularEVA Extravehicular ActivityEXP D Experiment DEXT External

FA Fluid AccumulatorFAS Flight Application SoftwareFCT Flight Control TeamFD Flight DayFDDI Fiber Distributed Data InterfaceFDIR Fault Detection, Isolation, and RecoveryFDS Fire Detection SystemFE Flight EngineerFET SW Field Effect Transistor SwitchFGB Functional Cargo BlockFOR Frame of ReferenceFPP Fluid Pump PackageFR Flight RuleFRD Flight Requirements DocumentFRGF Flight Releasable Grapple FixtureFRM Functional Redundancy ModeFSE Flight Support EquipmentFSEGF Flight Support Equipment Grapple FixtureFSW Flight Software

GAS Get Away SpecialGCA Ground Control AssistGLA General Lighting Assemblies

General Luminaire AssemblyGLONASS Global Navigational Satellite SystemGNC Guidance, Navigation, and ControlGPC General Purpose ComputerGPS Global Positioning System


GPSRGUI

Global Positioning System ReceiverGraphical User Interface

H&S Health and StatusHCEHCTL

Heater Control EquipmentHeater Controller

HEPAHPAHPP

High Efficiency Particulate AcquisitionHigh Power AmplifierHard Point Plates

HRDRHRELHRFMHRM

High Rate Data RecorderHold/Release ElectronicsHigh Rate Frame MultiplexerHold Release Mechanism

HRMSHTV

High Rate Multiplexer and SwitcherH II Transfer Vehicle

HTV ProxHTVCC

HTV ProximityHTV Control Center

HX Heat Exchanger

I/FIAAIAC

InterfaceIntravehicular Antenna AssemblyInternal Audio Controller

IBM International Business MachinesICBICCICSICS EFIDRDIELKIFHXIMCSIMCUIMV

Inner Capture BoxIntegrated Cargo CarrierInterorbit Communication SystemInterorbit Communication System Exposed FacilityIncrement Definition and Requirements DocumentIndividual Equipment Liner KitInterface Heat ExchangerIntegrated Mission Control SystemImage Compressor UnitIntermodule Ventilation

INCO Instrumentation and Communication OfficerIP International PartnerIP PCDU ICS PM Power Control and Distribution UnitIP PDBISPISPRISSISSSHITCSITS

Payload Power Distribution BoxInternational Standard PayloadInternational Standard Payload RackInternational Space StationInternational Space Station Systems HandbookInternal Thermal Control SystemIntegrated Truss Segment

8 ACRON MS A REVIATIONS MARCH 2008

IVAIVSU

Intravehicular ActivityInternal Video Switch Unit

JAL JEM Air LockJAXAJCP

Japan Aerospace Exploration AgencyJEM Control Processor

JEFJEMJEMAL

JEM Exposed FacilityJapanese Experiment ModuleJEM Air lock

JEM PM JEM – Pressurized ModuleJEMRMSJEUSJFCTJLEJPMJPMWS

Japanese Experiment Module Remote Manipulator SystemJoint Expedited Undocking and SeparationJapanese Flight Control TeamJapanese Experiment Logistics Module – Exposed SectionJapanese Pressurized ModuleJEM Pressurized Module Workstation

JSCJTVE

Johnson Space CenterJEM Television Equipment

KbpsKOSKSC

Kilobit per secondKeep Out SphereKennedy Space Center

LB Local BusLCALCDLEDLEELMCLSWLTA

LAB Cradle AssemblyLiquid Crystal DisplayLight Emitting DiodeLatching End EffectorLightweight MPESS CarrierLight SwitchLaunch to Activation

LTAB Launch to Activation BoxLTL Low Temperature Loop

MA Main ArmMAUIMbMbpsMBSMBSUMCAMCC

Main Analysis of Upper Atmospheric InjectionsMegabitMegabit per secondMobile Base SystemMain Bus Switching UnitMajor Constituent AnalyzerMission Control Center

MCC H Mission Control Center – Houston


MCC M Mission Control Center – MoscowMCDS Multifunction Cathode Ray Tube Display SystemMCS Mission Control SystemMDA MacDonald, Dettwiler and Associates Ltd.MDM Multiplexer/DemultiplexerMDP Management Data ProcessorMELFI Minus Eighty Degree Laboratory Freezer for ISSMGB Middle Grapple BoxMIP Mission Integration PlanMISSE Materials International Space Station ExperimentMKAM Minimum Keep Alive MonitorMLE Middeck Locker EquivalentMLI Multi layer InsulationMLM Multipurpose Laboratory ModuleMMOD Micrometeoroid/Orbital DebrisMOD ModulatorMON Television MonitorMPC Main Processing ControllerMPESS Multipurpose Experiment Support StructureMPEV Manual Pressure Equalization ValveMPL Manipulator Retention LatchMPLM Multipurpose Logistics ModuleMPM Manipulator Positioning MechanismMPV Manual Procedure ViewerMSD Mass Storage DeviceMSFC Marshall Space Flight CenterMSP Maintenance Switch PanelMSS Mobile Servicing SystemMT Mobile TrackerMTL Moderate Temperature LoopMUX Data Multiplexer

n.mi. nautical mileNASA National Aeronautics and Space AdministrationNCS Node Control SoftwareNET No Earlier ThanNLT No Later ThanNPRV Negative Pressure Relief ValveNSV Network ServiceNTA Nitrogen Tank AssemblyNTSC National Television Standard Committee


OBSS Orbiter Boom Sensor SystemOCA Orbital Communications AdapterOCAD Operational Control Agreement DocumentOCAS Operator Commanded Automatic SequenceODF Operations Data FileODS Orbiter Docking SystemOI Orbiter InterfaceOIU Orbiter Interface UnitOMS Orbital Maneuvering SystemOODT Onboard Operation Data TableORCA Oxygen Recharge Compressor AssemblyORU Orbital Replacement UnitOS Operating SystemOSA Orbiter based Station AvionicsOSE Orbital Support EquipmentOTCM ORU and Tool Changeout MechanismOTP ORU and Tool Platform

P/L PayloadPAL Planning and Authorization LetterPAM Payload Attach MechanismPAO Public Affairs OfficePBA Portable Breathing ApparatusPCA Pressure Control AssemblyPCBM Passive Common Berthing MechanismPCN Page Change NoticePCS Portable Computer SystemPCU Power Control UnitPDA Payload Disconnect AssemblyPDB Power Distribution BoxPDGF Power and Data Grapple FixturePDH Payload Data Handling unitPDRS Payload Deployment Retrieval SystemPDU Power Distribution UnitPEC Passive Experiment ContainerPEHG Payload Ethernet Hub GatewayPFE Portable Fire ExtinguisherPGSC Payload General Support ComputerPIB Power Interface BoxPIU Payload Interface UnitPLB Payload BayPLBD Payload Bay Door


PLCPLT

Pressurized Logistics CarrierPayload Laptop TerminalPilot

PM Pressurized ModulePMAPMCUPOAPOR

Pressurized Mating AdapterPower Management Control UnitPayload ORU AccommodationPoint of Resolution

PPRV Positive Pressure Relief ValvePRCSPREX

Primary Reaction Control SystemProcedure Executor

PRLAPROXpsiaPSPPSRRPTCSPTR

Payload Retention Latch AssemblyProximity Communications CenterPounds per Square Inch AbsolutePayload Signal ProcessorPressurized Section Resupply RackPassive Thermal Control SystemPort Thermal Radiator

PTUPVCU

Pan/Tilt UnitPhotovoltaic Controller Unit

PVM Photovoltaic ModulePVR Photovoltaic RadiatorPVTCS Photovoltaic Thermal Control System

QD Quick Disconnect

R&MARACU

Restraint and Mobility AidRussian to American Converter Unit

RAMRBVM

Read Access MemoryRadiator Beam Valve Module

RCCRCTRFRGARHC

Range Control CenterRack Configuration TableRadio FrequencyRate Gyro AssembliesRotational Hand Controller

RIGEXRIP

Rigidizable Inflatable Get Away Special ExperimentRemote Interface Panel

RLFRLTRMSROEUROMR ORU

Robotic Language FileRobotic Laptop TerminalRemote Manipulator SystemRemotely Operated Electrical UmbilicalRead Only MemoryRobotics Compatible Orbital Replacement Unit


ROSRPC

Russian Orbital SegmentRemote Power Controller

RPCM Remote Power Controller ModuleRPDARPM

Remote Power Distribution AssemblyRoll Pitch Maneuver

RSRSPRSRRT

Russian SegmentReturn Stowage PlatformResupply Stowage RackRemote Terminal

RTASRVFSRWS

Rocketdyne Truss Attachment SystemRendezvous Flight SoftwareRobotics Workstation

SAFERSAM

Simplified Aid for EVA RescueSFA Airlock Attachment Mechanism

SARJSCUSD

Solar Alpha Rotary JointSync and Control UnitSmoke Detector

SDSSEDASEDA APSELSSEUSFA

Sample Distribution SystemSpace Environment Data Acquisition equipmentSpace Environment Data Acquisition equipment Attached PayloadSpaceOps Electronic Library SystemSingle Event UpsetSmall Fine Arm

SFAE SFA ElectronicsSI Smoke IndicatorSLM Structural Latch MechanismSLP DSLP D1SLP D2SLT

SM

Spacelab Pallet – DSpacelab Pallet – DeployableSpacelab Pallet D2Station Laptop TerminalSystem Laptop TerminalService Module

SMDP Service Module Debris PanelSOCSODFSPASPB

System Operation ControlSpace Operations Data FileSmall Payload AttachmentSurvival Power Distribution Box

SPDASPDMSPECSRAM

Secondary Power Distribution AssemblySpecial Purpose Dextrous ManipulatorSpecialistStatic RAM


SRB Solid Rocket BoosterSRMS Shuttle Remote Manipulator SystemSSAS Segment to Segment Attach SystemSSC Station Support ComputerSSCB Space Station Control BoardSSE Small Fine Arm Storage EquipmentSSIPC Space Station Integration and Promotion CenterSSME Space Shuttle Main Engine.SSOR Space to Space Orbiter RadioSSP Standard Switch PanelSSPTS Station to Shuttle Power Transfer SystemSSRMS Space Station Remote Manipulator SystemSTC Small Fire Arm Transportation ContainerSTR Starboard Thermal RadiatorSTS Space Transfer SystemSTVC SFA Television CameraSVS Space Vision System

T RAD Tile Repair Ablator DispenserTA Thruster AssistTAC TCS Assembly ControllerTAC M TCS Assembly Controller MTCA Thermal Control System AssemblyTCB Total Capture BoxTCCS Trace Contaminant Control SystemTCCV Temperature Control and Check ValveTCS Thermal Control SystemTCV Temperature Control ValveTDK Transportation Device KitTDRS Tracking and Data Relay SatelliteTHA Tool Holder AssemblyTHC Temperature and Humidity Control

Translational Hand ControllerTHCU Temperature and Humidity Control UnitTIU Thermal Interface UnitTKSC Tsukuba Space Center (Japan)TLM TelemetryTMA Russian vehicle designationTMR Triple Modular RedundancyTPL Transfer Priority ListTRRJ Thermal Radiator Rotary Joint


TUSTVC

Trailing Umbilical SystemTelevision Camera

UCCASUCM

Unpressurized Cargo Carrier Attach SystemUmbilical Connect Mechanism

UCM EUCM PUHFUILULCUMAUOPUPCUS LABUSAUSOS

UCM – Exposed Section HalfUCM – Payload HalfUltrahigh FrequencyUser Interface LanguageUnpressurized Logistics CarrierUmbilical Mating AdapterUtility Outlet PanelUp ConverterUnited States LaboratoryUnited Space AllianceUnited States On Orbit Segment

VAJVBSPVCU

Vacuum Access JumperVideo Baseband Signal ProcessorVideo Control Unit

VDSVLUVRAVRCSVRCV

Video Distribution SystemVideo Light UnitVent Relief AssemblyVernier Reaction Control SystemVent Relief Control Valve

VRIV Vent Relief Isolation ValveVSU Video Switcher UnitVSW Video Switcher

WAICOWCLWETAWIF

Waiving and CoilingWater Cooling LoopWireless Video System External Transceiver AssemblyWork Interface

WRMWRSWS

Water Recovery and ManagementWater Recovery SystemWater SeparatorWork SiteWork Station

WVA Water Vent Assembly

ZSR Zero g Stowage Rack

MARCH 2008 MEDIA ASSISTANCE 105

MEDIA ASSISTANCE NASA TELEVISION TRANSMISSION NASA Television is carried on an MPEG 2digital signal accessed via satellite AMC 6, at72 degrees west longitude, transponder 17C,4040 MHz, vertical polarization. For those inAlaska or Hawaii, NASA Television will beseen on AMC 7, at 137 degrees west longitude,transponder 18C, at 4060 MHz, horizontalpolarization. In both instances, a Digital VideoBroadcast (DVB) compliant IntegratedReceiver Decoder (IRD) (with modulation ofQPSK/DBV, data rate of 36.86 and FEC 3/4) willbe needed for reception. The NASA Televisionschedule and links to streaming video areavailable at:

// /

NASA TV’s digital conversion will requiremembers of the broadcast media to upgradewith an ‘addressable’ Integrated ReceiverDe coder, or IRD, to participate in live newsevents and interviews, media briefings andreceive NASA’s Video File news feeds on adedicated Media Services channel. NASAmission coverage will air on a digital NASAPublic Services (“Free to Air”) channel, forwhich only a basic IRD will be needed.

Television Schedule

A schedule of key on orbit events and mediabriefings during the mission will be detailed ina NASA TV schedule posted at the link above.The schedule will be updated as necessary andwill also be available at:

Status Reports

Status reports on launch countdown andmission progress, on orbit activities andlanding operations will be posted at:

// /

This site also contains information on the crewand will be updated regularly with photos andvideo clips throughout the flight.

Briefings

Amission press briefing schedule will be issuedbefore launch. The updated NASA televisionschedule will indicate when mission briefingsare planned.

Participation in Mission Status Briefings by Phone

During STS 123, JSC will operate a phonebridge for press briefings that take placeoutside of the normal business hours of8 a.m. 5 p.m. CST Monday through Friday.The system will allow media not present atJohnson to ask questions by phone duringmission status briefings. To be eligible to usethis service, media must possess a valid NASAmedia credential.

Media planning to use the service must contactthe Johnson Newsroom at 281/483 5111 no laterthan 15 minutes prior to the start of a briefing.Newsroom personnel will verify theircredentials and transfer them to the phonebridge. During the briefing, the moderator willcall on each participant that has beentransferred into the system for questions. Thecapacity of the phone bridge is limited, and itwill be available on a first come, first servedbasis.

10 ME IA ASSISTANCE MARCH 2008

M I I

Information on the International Space Stationis available at:

// /

Information on safety enhancements madesince the Columbia accident is available at:

// / //

Information on other current NASA activities isavailable at:

//

Resources for educators can be found at thefollowing address:

//

MARCH 2008 PUBLIC AFFAIRS CONTACTS 107

PUBLIC AFFAIRS CONTACTS HEADQUARTERSWASHINGTON, DC

Michael BraukusPublic Affairs OfficerInternational Partners202 358 1979

ichae raukus nasa o

Katherine TrinidadPublic Affairs OfficerSpace Operations202 358 3749katherine trinidad nasa o

John YembrickPublic Affairs OfficerSpace Operations202 358 0602ohn e rick- nasa o

Mike CuriePublic Affairs OfficerSpace Operations202 358 4715

ichae curie nasa o

OHNSON S ACE CENTER HO STON TE AS

James HartsfieldNews Chief281 483 5111a es a hartsfie d nasa o

Kyle HerringPublic Affairs SpecialistSpace Shuttle Program Office281 483 5111k e herrin nasa o

Rob NaviasProgram and Mission Operations Lead281 483 5111ro na ias- nasa o

Kylie ClemPublic Affairs SpecialistAstronauts and Mission Operations Directorate281 483 5111k ie s c e nasa o

Nicole Cloutier LemastersPublic Affairs SpecialistInternational Space Station281 483 5111nico e c outier- nasa o

ENNE S ACE CENTER CA E CANAVERA ORI A

Allard BeutelNews Chief321 867 2468a ard eute nasa o

Candrea ThomasPublic Affairs SpecialistSpace Shuttle321 861 2468candrea k tho as nasa o

Tracy YoungPublic Affairs SpecialistInternational Space Station321 867 2468trac oun nasa o

108 IC A AIRS CONTACTS MARCH 2008

MARSHA S ACE I HT CENTER H NTSVI E A A AMA

Dom AmatorePublic Affairs Manager256 544 0034do inic a a atore nasa o

June MalonePublic Affairs SpecialistNews Chief/Media Manager256 544 0034une e a one nasa o

Steve RoyPublic Affairs SpecialistSpace Shuttle Propulsion256 544 0034ste en e ro nasa o

STENNIS S ACE CENTER A ST O IS MISSISSI I

Linda TheobaldPublic Affairs Officer228 688 3249inda theo a d nasa o

Paul FoermanNews Chief228 688 1880au foer an- nasa o

AMES RESEARCH CENTER MO ETT IE CA I ORNIA

Mike MewhinneyNews Chief650 604 3937

ichae e hinne nasa o

Jonas DinoPublic Affairs Specialist650 604 5612onas dino nasa o

R EN I HT RESEARCH CENTER E WAR S CA I ORNIA

Fred JohnsenDirector, Public Affairs661 276 2998frederick a ohnsen nasa o

Alan BrownNews Chief661 276 2665a an ro n nasa o

Leslie WilliamsPublic Affairs Specialist661 276 3893es ie a i ia s nasa o

ENN RESEARCH CENTER C EVE AN OHIO

Lori RachulNews Chief216 433 8806ori rachu nasa o

Katherine MartinPublic Affairs Specialist216 433 2406katherine artin nasa o

AN E RESEARCH CENTER HAM TON VIR INIA

Marny SkoraHead, News Media Office757 864 3315

arn skora nasa o

Chris RinkPublic Affairs Officer757 864 6786christo her rink nasa o

MARCH 2008 IC A AIRS CONTACTS 10

Kathy BarnstorffPublic Affairs Officer757 864 9886katherine a arnstorff nasa o

NITE S ACE A IANCE

Jessica PieczonkaHouston Operations281 212 6252832 205 0480essica iec onka usa-s aceo s co

David WatersFlorida Operations321 861 3805da id aters usa-s aceo s co

OEIN

Tanya Deason SharpMedia RelationsBoeing Space Exploration281 226 6070tan a e deason-shar oein co

Ed MemiMedia RelationsBoeing Space Exploration281 226 4029ed und e i oein co

A AN AEROS ACE E ORATION A ENC A A

JAXA Public Affairs OfficeTokyo, Japan011 81 3 6266 6414, 6415, 6416, 6417

roffice a a

Kumiko TanabeJAXA Public Affairs RepresentativeHouston281 483 2251tana e ku iko a a

CANA IAN S ACE A ENC CSA

Jean Pierre ArseneaultManager, Media Relations& Information ServicesCanadian Space Agency514 824 0560 (cell)ean- ierre arseneau t s ace c ca

Isabelle LaplanteMedia Relations AdvisorCanadian Space Agency450 926 4370isa e e a ante s ace c ca

E RO EAN S ACE A ENC ESA

Clare MattokCommunication Dept.Paris, France011 33 1 5369 7412c are attok esa int

110 IC A AIRS CONTACTS MARCH 2008


215905main sts123 press kit b[1] · 2012-08-11 · Dextre, 1the 1Canadian 1device, 1will 1work...

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