National Aeronautics and Space Administration

SPACE SHUTTLE MISSION

STS-130

A Room with a View

PRESS KIT/JANUARY 2010

www.nasa.gov
 
CONTENTS 

FEBRUARY 2010 CONTENTS i

Section Page 

STS-130/20A MISSION OVERVIEW ....................................................................................... 1

STS-130 TIMELINE OVERVIEW ............................................................................................... 9

MISSION PROFILE ................................................................................................................... 13

MISSION OBJECTIVES ............................................................................................................ 15

MISSION PERSONNEL ............................................................................................................. 17

STS-130 CREW ....................................................................................................................... 19

PAYLOAD OVERVIEW .............................................................................................................. 27

NODE 3 ................................................................................................................................................ 2 7

THE CUPOLA OBSERVATION MODULE .................................................................................................. 3 3

RENDEZVOUS & DOCKING ....................................................................................................... 43

UNDOCKING, SEPARATION, AND DEPARTURE ...................................................................................... 4 4

SPACEWALKS ......................................................................................................................... 47

EXPERIMENTS ......................................................................................................................... 53

DETAILED TEST OBJECTIVES AND DETAILED SUPPLEMENTARY OBJECTIVES ....................................... 5 3

SHORT-DURATION U.S. INTEGRATED RESEARCH TO BE COMPLETED DURING STS-130/20A .............. 5 4

TROPI-2: STUDYING PLANT G R O W T H I N S P A C E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 9

ADDITIONAL STATION RESEARCH FROM NOW UNTIL THE END OF EXPEDITION 21/22 ............ . . . . . . . . . . . . 6 3

SHUTTLE REFERENCE DATA .................................................................................................... 69

LAUNCH AND LANDING ...........................................................................................................87

LAUNCH ............................................................................................................................................... 8 7

ABORT-TO-ORBI T ( A T O ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ............. 8 7

TRANSATLANTIC ABORT LANDING (TAL) ............................................................................................. 8 7

RETURN-TO-LAUNCH-SI T E ( R T L S ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ...... 8 7

ABORT ONCE ARO U N D ( A O A ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ......... 8 7

LANDING ............................................................................................................................................. 8 7
ii CONTENTS FEBRUARY 2010

Section Page 

ACRONYMS AND ABBREVIATIONS ......................................................................................... 89

MEDIA ASSISTANCE ............................................................................................................... 103

PUBLIC AFFAIRS CONTACTS .................................................................................................. 105

 

 

 

 

 

 
FEBRUARY 2010 MISSION OVERVIEW 1

STS-130/20A MISSION OVERVIEW 

Space shuttle Endeavour launches on the STS-127 mission to the 

International Space Station in 2009. 

Endeavour’s 13-day mission will deliver and 

assemble the last U.S module onto 

the International Space Station, giving the 

laboratory a room with quite a view. The 

mission kicks off the final year of shuttle flights, 

with five missions planned through September. 

Node 3, known as Tranquility, will provide 

additional room for crew members and many 

of the space station’s life support and 

environmental control systems. Attached to the 

node is a cupola, which is a robotic control 

station with six windows around its sides and 

another in the center that will provide a 

panoramic view of Earth, celestial objects and 

visiting spacecraft. 

Tucked away inside Tranquility and 

Endeavour’s middeck will be a ton of 

equipment, supplies and experiments for the 

space station. Included are a new distillation 

assembly and fluid control pump assembly for 

the urine processing assembly, an external filter 

assembly for the water processing assembly, a 
2 MISSION OVERVIEW FEBRUARY 2010

new bed for the carbon dioxide removal 

assembly, laptop computers, crew provisions, 

health care supplies, spacewalk tools and 

others. 

Endeavour, commanded by spaceflight veteran 

George Zamka, is scheduled to lift off from 

Kennedy Space Center at 4:39 a.m. EST on 

Sunday, Feb. 7, and arrive at the orbiting 

complex in the early morning hours Tuesday, 

Feb. 9. 

While docked to the station, Endeavour’s crew 

will conduct three spacewalks and extensive 

robotic operations to install Tranquility and 

then relocate its Cupola. 

Zamka, 47, a U.S. Marine Corps colonel, served 

as pilot on STS-120 in 2007. He will be joined 

on the mission by pilot Terry Virts, 41, a 

U.S. Air Force colonel, who will be making his 

first trip to space. Mission specialists are 

Kathryn Hire, a U.S. Navy Reserve captain who 

flew on STS-90 in 1998; Stephen Robinson who 

flew on STS-85 in 1997, STS-95 in 1988 and 

STS-114 in 2005; Nicholas Patrick who flew on 

STS-116 in 2006; and Robert Behnken, a 

lieutenant colonel in the U.S. Air Force, who 

flew on STS-123 in 2008. Robinson, Patrick and 

Behnken all have doctorates in mechanical 

engineering. 

Astronaut George Zamka, STS-130 commander, dons a training version of his shuttle launch and 

entry suit in preparation for a training session in the Space Vehicle Mock-up Facility at NASA’s 

Johnson Space Center. United Space Alliance suit technician Joel Alvarado assisted Zamka. 
FEBRUARY 2010 MISSION OVERVIEW 3

The major tasks for the mission are to install, 

activate and checkout Tranquility, including 

connecting internal and external avionics, 

cables, and ammonia cooling system jumpers; 

relocating the Cupola from the end port of 

Tranquility to its Earth-facing port and then 

activating and checking out the Cupola; 

relocating the Pressurized Mating Adapter 3 

(PMA 3) from the top of the Harmony node to 

the port side of Tranquility; and transferring 

water, equipment and experiments to the 

station. 

The day after launch, Zamka, Virts, Hire and 

Patrick will take turns from Endeavour’s aft 

flight deck maneuvering its robotic arm in the 

traditional day-long scan of the reinforced 

carbon-carbon on the leading edges of the 

shuttle’s wings and its nose cap. This initial 

inspection, using a 50-foot-long robotic arm 

extension equipped with sensors and lasers, 

called the Orbiter Boom Sensor System (OBSS), 

will provide imagery experts on the ground a 

close-up look at the orbiter’s heat shield 

following the dynamic liftoff. A follow-up 

inspection will take place after Endeavour 

undocks from the station. 

Astronaut Terry Virts, STS-130 pilot, attired in a training version of his shuttle launch and entry 

suit, occupies the pilot’s station during a training session in the Mission Simulation Development 

Facility at NASA’s Johnson Space Center. 
4 MISSION OVERVIEW FEBRUARY 2010

While the inspection takes place, Behnken and 

Patrick will prepare the spacesuits they will 

wear for their three spacewalks out of the Quest 

airlock at the station. Robinson will assist with 

spacewalk tool preparation that day as he will 

serve as the internal choreographer of the 

excursions. Docking preparations will occupy 

the remainder of the crew’s workday. 

On the third day of the flight, Endeavour will 

be flown by Zamka and Virts on its approach 

for docking to the station. After a series of jet 

firings to fine-tune Endeavour’s path to the 

complex, the shuttle will arrive at a point about 

600 feet directly below the station about an 

hour before docking. At that time, Zamka will 

execute the rendezvous pitch maneuver, a 

one-degree-per-second rotational “backflip” to 

enable station crew members to snap hundreds 

of detailed photos of the shuttle’s heat shield 

and other areas of potential interest – another 

data point for imagery analysts to pore over in 

determining the health of the shuttle’s thermal 

protection system. 

Astronaut George Zamka (foreground), STS-130 commander; and astronaut Nicholas Patrick, 

mission specialist, work with an Extravehicular Mobility Unit (EMU) spacesuit during a training 

session in an International Space Station mock-up/trainer in the Space Vehicle Mock-up Facility at 

NASA’s Johnson Space Center. 
FEBRUARY 2010 MISSION OVERVIEW 5

Once the rotation is completed, Zamka will fly 

Endeavour in front of the station before slowly 

closing in for a linkup to the forward docking 

port on the Harmony module. Less than 

two hours later, hatches will be opened 

between the two spacecraft and a combined 

crew of 11 will begin eight days of work. 

Endeavour’s crew will be working with 

Expedition 22 commander NASA astronaut 

Jeff Williams and flight engineers cosmonaut 

Max Suraev, NASA astronaut T.J. Creamer 

and Japan Aerospace Exploration Agency 

astronaut Soichi Noguchi. Noguchi and 

Robinson flew together on the STS-114 space 

shuttle return-to-flight mission in 2005. 

After a station safety briefing, Patrick and 

Creamer will operate the station’s robotic arm 

to remove the OBSS from Endeavour’s payload 

bay and hand it off to the shuttle robotic arm 

being operated by Virts and Hire. 

The next day, Endeavour’s crew will begin 

transferring supplies from the middeck to the 

station, including spacewalking equipment, 

and then will have the afternoon off. 

That night, spacewalkers Behnken and Patrick 

will sleep in the Quest airlock as part of the 

overnight “campout” procedure that helps 

purge nitrogen from their bloodstreams, 

preventing decompression sickness once they 

move out into the vacuum of space. The 

campout will be repeated the night before each 

spacewalk. 

Behnken (EV 1) will wear a suit with stripes. 

Patrick (EV 2) will wear a suit with no stripes. 

Behnken performed three spacewalks during 

the STS-123 mission in March 2008 totaling 

19 hours and 19 minutes. The spacewalks 

conducted during STS-130 will be the first 

extravehicular excursions for Patrick. 

The fifth day of the mission will focus on the 

first spacewalk and robotics work to install 

Tranquility. Spacewalkers Patrick and Behnken 

will prepare Tranquility for its removal from 

Endeavour’s payload bay and then install 

avionics cabling once the new module is in 

place. Virts and Hire will operate the station’s 

robotic arm to install Tranquility with the 

Cupola. The spacewalkers will also remove 

a tool platform from the station’s special 

purpose dexterous manipulator while 

Tranquility is being maneuvered. Williams and 

Hire will begin a leak check of the interface to 

Tranquility. 

The sixth day is available for focused inspection 

of Endeavour’s heat shield, if mission managers 

deem it necessary. Zamka, Virts and Hire 

would conduct that survey in the crew’s 

morning while Williams, Noguchi and 

Robinson continue the steps to open the hatch 

to Tranquility. Those five crew members will 

work together after the heat shield survey, 

continuing Tranquility checkout and opening 

the hatch into the Cupola. Patrick and Behnken 

will prepare their equipment for the next 

spacewalk. 
6 MISSION OVERVIEW FEBRUARY 2010

Astronaut Robert Behnken, STS-130 mission specialist, gets help in the donning of a training 

version of his Extravehicular Mobility Unit (EMU) spacesuit in preparation for a spacewalk 

training session in the waters of the Neutral Buoyancy Laboratory (NBL) near NASA’s Johnson 

Space Center. 

Flight day seven will focus on configuring the 

new Tranquility module, inside and out, for 

its space operations. The spacewalkers will 

continue external outfitting of Tranquility by 

connecting fluid jumpers and remaining 

avionics cables, and installing covers as well 

as hardware to assist with future spacewalks, 

such as handrails and gap spanners. Virts, 

Hire, Williams and Noguchi will work on 

configuring avionics racks and the ventilation 

system inside Tranquility. At the end of the 

day they will close the hatch to the Cupola 

again and prepare it for its relocation. Virts and 

Hire will latch onto the Cupola with the 

station’s robotic arm for the night. 

The crew members will work inside the 

complex for two days before the final 

spacewalk. On the eighth day of the flight, 

Virts and Hire will move the Cupola to its 

permanent position on the Earth-facing side of 

Tranquility and then open the hatch again. 

Behnken and Robinson will grapple the PMA 3 

with the station’s robotic arm at the end of the 

day. 
FEBRUARY 2010 MISSION OVERVIEW 7

Astronauts Stephen Robinson and Kathryn Hire, both STS-130 mission specialists, read a procedure 

checklist during a training session in a fixed-base Shuttle Mission Simulator (SMS) training session 

in the Jake Garn Simulation and Training Facility at NASA’s Johnson Space Center. 

The ninth day includes moving the PMA 3 

to the end of Tranquility to enhance 

micrometeoroid debris protection of the node, 

while Cupola internal outfitting continues. The 

crew will have the afternoon off. 

The final planned spacewalk is on the tenth day 

to complete the work on Tranquility and the 

Cupola’s exterior, including removing covers 

and launch locks. Inside, Noguchi will move a 

robotics workstation, which has served as a 

backup inside the Destiny lab, into the Cupola. 

An additional docked day could be added to 

the flight, should Endeavour’s onboard 

consumables support it. This day would be 

inserted as a new flight day 11 and would 

include transferring the station’s regenerative 

life support racks, such as the water recovery 

system and oxygen generation system, from the 

Destiny lab into the Tranquility node. These 

racks were to have been moved earlier in the 

mission, but keeping them in Destiny longer 

will help recycling experts conduct tests 

following the planned repair work. If an 

additional docked day cannot be supported, the 

move may be completed after Endeavour 

departs. 

The planned final full day of docked operations 

will include preparations for Endeavour’s 

undocking and departure on the following day. 
8 MISSION OVERVIEW FEBRUARY 2010

The crew will finish packing, reconfigure 

spacesuits and transfer them to Endeavour, and 

check out the rendezvous tools that will be 

used for undocking, flyaround and separation. 

The Endeavour crew will say farewell to the 

five-member station crew and close the hatches 

between the two spacecraft. 

Endeavour’s crew will leave the station 

approximately 90 percent completely 

assembled. The station will be in its final 

internal configuration, with most life support 

systems inside the nodes and workspace for 

research in the laboratories. 

After Endeavour undocks the evening of 

Feb. 17, Virts will guide the shuttle on a 

360-degree flyaround of the station so that 

other crew members can document the exterior 

condition of the orbiting outpost with its new 

additions. After the flyaround is complete, 

Zamka, Virts, Hire, Robinson and Patrick will 

conduct one last inspection of Endeavour’s heat 

shield using the shuttle’s Canadarm and the 

OBSS. 

The last full day of orbital activities by 

the STS-130 crew will focus on landing 

preparations. Zamka, Virts and Robinson will 

conduct the traditional checkout of the shuttle’s 

flight control systems and steering jets, setting 

Endeavour up for its supersonic return to Earth. 

On the 14th day of the mission, weather 

permitting, Zamka and Virts will steer 

Endeavour to a landing at the Kennedy Space 

Center late in the evening of Feb. 19 to 

wrap up the 24th flight for Endeavour, the 

130th mission in shuttle program history and 

the 32nd shuttle visit to the International 

Space Station. 

Set against the background of a cloud covered Earth, the International Space Station is featured in 

this image photographed by an STS-129 crew member on Atlantis soon after the station and shuttle 

began their post-undocking relative separation. 
FEBRUARY 2010 TIMELINE OVERVIEW 9

STS-130 TIMELINE OVERVIEW 

Flight Day 1 

• Launch 

• Payload Bay Door Opening 

• Ku-Band Antenna Deployment 

• Shuttle Robotic Arm Activation and 

Payload Bay Survey 

• Umbilical Well and Handheld External 

Tank Photo and TV Downlink 

Flight Day 2 

• Endeavour’s Thermal Protection System 

Survey with Shuttle Robotic Arm/Orbiter 

Boom Sensor System (OBSS) 

• Extravehicular Mobility Unit Checkout 

• Centerline Camera Installation 

• Orbiter Docking System Ring Extension 

• Orbital Maneuvering System Pod Survey 

• Rendezvous tools checkout 

Flight Day 3 

• Rendezvous with the International Space 

Station 

• Rendezvous Pitch Maneuver Photography 

of Endeavour’s Thermal Protection System 

by Williams and Kotov of the Expedition 22 

crew 

• Docking to Harmony/Pressurized Mating 

Adapter-2 

• Hatch Opening and Welcoming 

• Canadarm2 grapple of OBSS and handoff to 

Shuttle robotic arm 

Flight Day 4 

• Spacewalk 1 preparations by Behnken and 

Patrick 

• Crew off duty time 

• Williams replacement and checkout of 

Distillation Assembly in the Water 

Recovery System 

• Spacewalk 1 procedure review 

• Spacewalk 1 campout by Behnken and 

Patrick in the Quest airlock 

Flight Day 5 

• Spacewalk 1 by Behnken and Patrick 

(Tranquility unberth preparations, tool 

stowage assembly removal from Dextre, 

launch to activation and avionics cable 

installation for Tranquility) 

• Tranquility unberth from Endeavour’s 

payload bay and installation on port side of 

Unity 

• Tranquility/Unity vestibule leak checks 
10 TIMELINE OVERVIEW FEBRUARY 2010

Flight Day 6 

• Focused inspection of Endeavour’s thermal 

protection heat shield, if required 

• Tranquility hatch opening 

• Canadarm2 base change 

• Cupola hatch opening 

• Tranquility interior outfitting 

• Spacewalk 2 procedure review 

• Spacewalk 2 campout by Behnken and 

Patrick in the Quest airlock 

Note: A decision on whether to transfer 

regenerative system racks to the new 

Tranquility Node 3 during docked 

operations is dependent on the required 

run time for the newly installed Water 

Recovery System hardware; if rack 

transfers are approved during docked 

operations, they would occur on an 

additional docked day, which would be 

a newly inserted Flight Day 11; a final 

decision would occur no earlier than the 

end of Flight Day 6; if rack transfers to 

Tranquility do not occur during docked 

operations, they would occur in stage 

operations for the station crew. 

Flight Day 7 

• Spacewalk 2 by Behnken and Patrick (install 

ammonia jumper cables, thermal insulation 

and other outfitting items on Tranquility) 

• Opening of fluid lines for cooling of 

Tranquility’s avionics 

• Ground activation of Tranquility’s systems 

• Depressurization of the Cupola/Tranquility 

hatch interface 

• Canadarm2 grapple of the Cupola 

Flight Day 8 

• Cupola unberth from forward end of 

Tranquility and installation to nadir port of 

Tranquility 

• Cupola vestibule outfitting 

Flight Day 9 

• Pressurized Mating Adapter-3 (PMA-3) 

unberth from Harmony zenith port and 

installation on forward port of Tranquility 

for micrometeoroid debris protection 

• Cupola interior outfitting 

• Crew off duty time 

• Spacewalk 3 procedure review 

• Spacewalk 3 campout by Behnken and 

Patrick in the Quest airlock 

Flight Day 10 

• Spacewalk 3 by Behnken and Patrick 

(PMA-3 cable installations, Cupola thermal 

insulation removal, Cupola launch lock 

release, video cable installations, and 

worksite handrail installations) 

• Cupola robotic work station installation 

• PMA-3 repressurization 
FEBRUARY 2010 TIMELINE OVERVIEW 11

Flight Day 11 

• Endeavour to ISS transfer operations 

• Joint Crew News Conference 

• Rendezvous Tool Checkout 

• Farewells and Hatch Closure 

• ISS reboost, if required 

Flight Day 12 

• Endeavour undocking from ISS and 

flyaround 

• Final separation from the ISS 

• OBSS late inspection of Endeavour’s 

thermal heat shield 

• OBSS berth 

Flight Day 13 

• Cabin stowage 

• Flight Control System checkout 

• Reaction Control System hot-fire test 

• Deorbit Preparation Briefing 

• Ku-band antenna stowage 

Flight Day 14 

• Deorbit preparations 

• Payload Bay Door closing 

• Deorbit burn 

• KSC Landing 
12 TIMELINE OVERVIEW FEBRUARY 2010

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FEBRUARY 2010 MISSION PROFILE 13

MISSION PROFILE 

CREW 

Commander: George D. Zamka 

Pilot: Terry W. Virts Jr. 

Mission Specialist 1: Kathyrn P. Hire 

Mission Specialist 2: Stephen K. Robinson 

Mission Specialist 3: Nicholas J.M. Patrick 

Mission Specialist 4: Robert L. Behnken 

LAUNCH 

Orbiter: Endeavour (OV-105)

Launch Site: Kennedy Space Center 

Launch Pad 39A 

Launch Date: Feb. 7, 2010 

Launch Time: 4:39 a.m. EST 

(Preferred In-Plane 

launch time for 2/7) 

Launch Window: 10 minutes 

Altitude: 122 Nautical Miles 

(140 Miles) Orbital 

Insertion; 185 NM 

(213 Miles) Rendezvous 

Inclination: 51.6 Degrees 

Duration: 12 Days 18 Hours 

37 Minutes 

VEHICLE DATA 

Shuttle Liftoff Weight: 4,521,961

pounds 

Orbiter/Payload Liftoff Weight: 267,470 

pounds 

Orbiter/Payload Landing Weight: 200,694 

pounds 

Software Version: OI-34

Space Shuttle Main Engines: 

SSME 1: 2059 

SSME 2: 2061 

SSME 3: 2057 

External Tank: ET-134 

SRB Set: BI-141 

RSRM Set: 109 

SHUTTLE ABORTS 

Abort Landing Sites 

RTLS: Kennedy Space Center Shuttle 

Landing Facility 

TAL: Primary – Zaragoza, Spain 

Alternates – Moron, Spain and 

Istres, France 

AOA: Primary – Kennedy Space Center 

Shuttle Landing Facility 

Alternate – White Sands Space 

Harbor 

LANDING 

Landing Date: No Earlier Than 

Feb. 19, 2010 

Landing Time: 11:13 p.m. EST 

Primary landing Site: Kennedy Space Center 

Shuttle Landing Facility 

PAYLOADS 

Tranquility Node 3/Cupola 
14 MISSION PROFILE FEBRUARY 2010

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FEBRUARY 2010 MISSION OBJECTIVES 15

MISSION OBJECTIVES 

MAJOR OBJECTIVES 

1. Dock Endeavour to Pressurized Mating 

Adapter (PMA)-2 and perform mandatory 

crew safety briefing for all crew members. 

2. Transfer mandatory quantities of water 

from the shuttle to the International Space 

Station. 

3. Transfer and stow critical items. 

4. Install Tranquility (Node 3) to Unity 

(Node 1) Port Common Berthing 

Mechanism using the space station robotic 

arm. 

5. Connect Node 3 internal and external 

avionics and ammonia jumpers. 

6. Activate and check out Node 3. 

7. Support space station dual docked 

operations for the following visiting 

vehicles, if required. 

− 20 Soyuz undocking from Multipurpose 

Research Module 2 (MRM-2) 

− 22 Soyuz docking to MRM-2 

8. Relocate the Cupola from Node 3 port CBM 

and install on Node 3 nadir CBM. 

9. Install, activate, and check out the Water 

Recovery System (WRS) Distillation 

Assembly (DA), Fluids Control and Pump 

Assembly (FCPA) and Recycle Filter Tank 

Assembly (RFTA).

10. Transfer remaining cargo items. 

11. Relocate PMA-3 from Node 2 Zenith to 

Node 3 Port. 

12. Activate and check out the Cupola. 

13. Perform daily station payload status checks. 

14. Perform Program-approved spacewalk 

tasks. 

15. Perform daily middeck activities to support 

payloads. 

16. Transfer, install, activate, and check out the 

following Node 3 racks: 

− Advanced Resistive Exercise 

Device (ARED) 

− Air Revitalization System (ARS) 

17. Remove Integrated Stowage Platforms from 

Node 3. 

18. Perform payload research operations tasks. 

19. Perform Node 3 outfitting tasks. 

20. Perform Cupola outfitting tasks. 

21. Transfer oxygen from Endeavour to the 

station Airlock High Pressure Gas 

Tanks (HPGTs). 

22. Perform Program-approved spacewalk 

get-ahead tasks. 
16 MISSION OBJECTIVES FEBRUARY 2010

23. Reboost the station with the orbiter if 

mission resources allow and are consistent 

with station trajectory analysis and 

planning. 

24. Perform imagery survey of the station 

exterior during shuttle flyaround after 

undocking. 

25. Perform payloads of opportunity: 

RAMBO-2, MAUI, SEITE, and SIMPLEX. 

26. Perform Program-approved intravehicular 

get-head tasks (the crew will have the 

option to perform if time is available). 

− Transfer, install, activate and checkout 

the Regen ECLSS racks 

− Perform Node 3 fuel cell water bus fill 

and connection to station bus in Node 1 

− Repressurize PMA3 

− Perform Cupola window shutter 

functional test 

− Unstow and assemble the JEM Airlock 

Vacuum Pump and Driver 

− Install the JAXA CGSE valve unit 

− Install Carbon Dioxide Removal 

Assembly (CDRA) bed in Node 3 rack 

− Unpack 20A middeck and ISP cargo 

27. Relocate the Special Purpose Dexterous 

Manipulator to the lab power data grapple 

fixture. 

28. Perform SDTO 13005-U, ISS Structural 

Life Validation and Extension, during 

Node 3/Cupola and PMA3 berthing events. 

29. Perform SDTO 13005-U, ISS Structural Life 

Validation and Extension, during shuttle 

mated reboost. 

30. Perform SDTO 13005-U, ISS Structural Life 

Validation and Extension, during shuttle 

undocking.
FEBRUARY 2010 MISSION PERSONNEL 17

MISSION PERSONNEL 

KEY CONSOLE POSITIONS FOR STS-130 

 Flt. Director CAPCOM PAO

Ascent Norm Knight Rick Sturckow Kylie Clem 

Steve Frick (Wx) 

Orbit 1 (Lead) Kwatsi Alibaruho Danny Olivas Kylie Clem 

Rick Sturckow 

(Flight Days 3 and 12) 

Orbit 2 Gary Horlacher Mike Massimino Brandi Dean 

Planning Chris Edelen Shannon Lucid Pat Ryan 

Entry Norm Knight Rick Sturckow Kylie Clem 

Steve Frick (Wx) 

Shuttle Team 4 Paul Dye N/A N/A 

ISS Orbit 1 Royce Renfrew Robert Hanley N/A 

ISS Orbit 2 (Lead) Bob Dempsey Hal Getzelman N/A 

ISS Orbit 3 Mike Lammers Kathy Bolt N/A 

Station Team 4 Dana Weigel 

JSC PAO Representative at KSC for Launch – Josh Byerly

KSC Launch Commentator – Allard Beutel

KSC Launch Director – Mike Leinbach

NASA Launch Test Director – Jeff Spaulding 
18 MISSION PERSONNEL FEBRUARY 2010

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FEBRUARY 2010 CREW 19

STS-130 CREW 

The STS-130 patch was designed by the crew to 

reflect both the objectives of the mission and its 

place in the history of human spaceflight. The 

main goal of the mission is to deliver Node 3 

and the Cupola to the International Space 

Station. Node 3, named “Tranquility,” will 

contain life support systems enabling continued 

human presence in orbit aboard the space 

station. The shape of the patch represents the 

Cupola, which is the windowed robotics 

viewing station, from which astronauts will 

have the opportunity not only to monitor a 

variety of station operations, but also to study 

our home planet. The image of Earth depicted 

in the patch is the first photograph of the Earth 

taken from the moon by Lunar Orbiter I on 

Aug. 23, 1966. As both a past and a future 

destination for explorers from the planet Earth, 

the moon is thus represented symbolically 

in the STS-130 patch. The space shuttle 

Endeavour is pictured approaching the station, 

symbolizing the space shuttle’s role as the 

prime construction vehicle for the station. 
20 CREW FEBRUARY 2010

The STS-130 crew is commanded by George Zamka (seated, right) and piloted by 

Terry Virts (seated, left). Standing from the left are mission specialists Nicholas Patrick, 

Robert Behnken, Kathryn Hire and Stephen Robinson. 

Short biographical sketches of the crew follow 

with detailed background available at: 

http://www.jsc.nasa.gov/Bios/
FEBRUARY 2010 CREW 21

STS-130 CREW BIOGRAPHIES 

George Zamka 

George Zamka, a colonel in the U.S. Marines, 

will serve as commander of STS-130. In that 

capacity, he has overall responsibility for the 

safety and execution of the mission. His role 

includes overseeing the crew and ensuring 

mission objectives are met, and commanding 

the shuttle during dynamic phases of flight 

including launch, landing, rendezvous and 

docking to the space station. He was pilot of 

STS-120, which flew in 2007 to deliver the 

Node 2 “Harmony” module to the orbiting 

complex. 

Zamka has more than 15 days in space and has 

logged more than 4,000 flight hours in more 

than 30 different aircrafts. 
22 CREW FEBRUARY 2010

Terry Virts 

Terry Virts, a colonel in the U.S. Air Force, will 

serve as pilot for STS-130, which will be his first 

trip into space. He was selected by NASA in 

2000. Most recently, he served as lead Ascent 

and Entry CAPCOM. He will be responsible 

for orbiter systems and robotic arm operations. 

He will also be outfitting both Tranquility and 

the Cupola and will fly Endeavour during 

undocking and the flyaround. He has logged 

more than 3,800 flight hours in more than 

40 different aircraft. 
FEBRUARY 2010 CREW 23

Kathryn Hire 

On her second spaceflight, Kathryn Hire, a 

captain in the U.S. Navy Reserve, will be 

responsible for the shuttle robotic arm 

operations. She also will install and activate 

equipment in the Cupola. A former Kennedy 

Space Center engineer, she accumulated more 

than 15 days in space as the flight engineer on 

the STS-90 Neurolab mission. 
24 CREW FEBRUARY 2010

Stephen Robinson 

Veteran astronaut Stephen Robinson flew on 

STS-85 in 1997, STS-95 in 1998 and STS-114 

in 2005. He has logged more than 831 hours 

in space, including more than 20 hours of 

spacewalking time. He has held various 

technical assignments within the Astronaut 

Office including testing space shuttle control 

software in the Shuttle Avionics Integration 

Laboratory and helping to develop the space 

station robot arm. 
FEBRUARY 2010 CREW 25

Nicholas Patrick 

This will be the second flight for Nicholas 

Patrick, who will serve as a mission specialist. 

Selected by NASA in 1998, he flew on STS-116 

in 2006. On that mission, he accrued more than 

12 days and 20 hours of spaceflight experience. 
26 CREW FEBRUARY 2010

Robert Behnken 

Robert Behnken, a lieutenant colonel in the U.S. 

Air Force, will serve as a mission specialist on 

STS-130. He flew on STS-123 in 2008. During 

the mission, Behnken served as mission 

specialist 1 for ascent and entry, performed 

three spacewalks, and operated both the space 

station robotic arm and the Dextre robot. He 

earned more than 19 hours of spacewalk 

experience during the 15-day mission. 
FEBRUARY 2010 PAYLOAD OVERVIEW 27

PAYLOAD OVERVIEW 

NODE 3 

The European-built Node 3 being lowered onto a work stand in the Space Station Processing 

Facility at the Kennedy Space Center on May 26, 2009. This image shows a clear view of the 

uncovered docking mechanism to which the Cupola will be attached during its transport to the 

International Space Station in space shuttle Endeavour’s cargo bay. 

(Image: NASA/Jim Grossmann) 

The European-built Node 3 is the final one of 

the three International Space Station nodes, 

which will be launched into orbit. The nodes 

are the interconnecting elements between 

the various pressurized modules on the 

space station. They provide a shirtsleeve 

environment to allow the passage of crew 

members and equipment through to other 

station elements and provide vital functions 

and resources for the crew members and 

equipment. 

Node 3 has systems, which provide many 

different functions and resources to the 

attached modules, and to itself, for maintaining 

a safe and ideal working and living 

environment on board the space station. 

Today’s Node 3 is significantly different from 
28 PAYLOAD OVERVIEW FEBRUARY 2010

the Node 3 that Europe initially agreed to 

develop back in 1997. It has evolved over 

the years from a connecting module into a 

very complex element, able to accommodate 

sophisticated crew and life support equipment, 

with many more capabilities than originally 

foreseen. Node 3 will support a six-member 

Expedition crew on the station by 

accommodating relevant hardware as well as 

supporting Node 3 cabin crew operations. 

Node 3 consists of a pressurized cylindrical hull 

4.5 meters (14.5 feet) in diameter with a shallow 

conical section enclosing each end. It is more 

than 7 meters (23.6 feet) long and will weigh 

together with the Cupola more than 

16.5 tons at launch. The pressurized shell of 

Node 3 is constructed from aluminium alloys. 

This is covered with a multi-layer insulation 

blanket for thermal stability and around 

75 sections of panelling to act as a protective 

shield against bombardment from space debris. 

This panelling is also constructed of an 

aluminium alloy, together with a layer of 

Kevlar and Nextel. Internal and external 

secondary structures are used to support the 

installation of equipment, piping and electrical 

harnesses. Two water loops (respectively lowtemperature and moderate-temperature loops) 

allow the rejection of the heat generated inside 

the element to the station ammonia lines by 

means of two heat exchangers mounted on the 

external side of one end cone. 

Side view of Node 3 clearly showing debris protection panels covering outer surface, 

one with inverted ESA logo, and one of the radial docking ports with its cover installed. 

(Image: ESA/S. Corvaja) 
FEBRUARY 2010 PAYLOAD OVERVIEW 29

Node 3 can be considered in two halves. 

One half has a single docking port on one of 

the end cones where Node 3 will be docked to 

the station. This half also accommodates 

eight standard-sized racks, which will house 

relevant systems and equipment. 

The other half consists of an additional 

five docking ports, one on the other end cone 

and four arranged around the circumference of 

the cylindrical main body of Node 3. 

Originally, the Habitation module, the Crew 

Return Vehicle and Pressurized Mating 

Adaptor 3 (PMA-3) were to be attached to 

Node 3 along with the Cupola. However, the 

first two elements were removed from the 

station configuration and PMA-3 will be 

moved to the port-side docking port of Node 3 

once it is installed. 

Internal view of Node 3 showing empty rack locations (bottom and right). 

(Image: ESA/S. Corvaja) 
30 PAYLOAD OVERVIEW FEBRUARY 2010

In its launch configuration in the shuttle’s cargo 

bay, Node 3 will have the Cupola attached to 

the end cone that will eventually face out from 

the station and be connected to PMA-3. Inside 

Node 3, the eight rack locations will be taken 

up with two avionics racks, three racks 

containing pallets with equipment and cargo 

for the station, with the three remaining racks 

remaining empty. 

The Cupola berthed to Node 3 in launch configuration in the Space Station Processing Facility 

at the Kennedy Space Center in September 2009. (Image: ESA/S. Corvaje) 
FEBRUARY 2010 PAYLOAD OVERVIEW 31

In its final in-orbit configuration Node 3 will 

look slightly different. The Cupola will be 

relocated to the Earth-facing port of Node 3 

during the STS-130 mission. The three cargo 

pallet racks will be removed and returned on 

shuttle flight STS-131 in March 2010. In place of 

these three rack locations and the three empty 

rack locations will come six new racks which 

are already on the station. These include the 

second Air Revitalization System rack for air 

composition monitoring including carbon 

dioxide removal; an Oxygen Generation System 

rack for producing oxygen from water; Water 

Recovery System Racks 1 and 2 for urine and 

water processing; a Waste and Hygiene 

Compartment Rack for crew waste and hygiene 

processing and a second treadmill. Node 3 also 

will be outfitted with the Advanced Resistive 

Exercise Device for crew in-orbit physical 

exercise. All these racks and equipment are 

necessary since the station crew number was 

increased from three to six in the spring of 2009. 

Water Recovery System rack 1 at the Kennedy Space Center on 17 October 2008 prior to launch. 

This rack is used as part of the systems to reclaim drinking-quality water from processing 

urine and waste water. (Image: NASA) 
32 PAYLOAD OVERVIEW FEBRUARY 2010

The atmosphere of Node 3’s internal 

pressurized volume is controlled in terms of 

air pressure, temperature, humidity, velocity, 

particulate and microbial concentrations. 

Node 3 provides a piping network for the 

distribution of water (for fuel cells, drinking, 

waste and processes) between Node 1 and 

Node 3 and within Node 3. It also provides the 

line for the transfer of pretreated urine from 

Waste and Hygiene Compartment to Water 

Recovery System racks inside Node 3. Special 

lines and sectioning devices are adapted to 

distribute oxygen and nitrogen. 

Fire detection is supported by two cabin 

smoke sensors and monitoring of electrical 

equipment. Other smoke sensors are used 

in particular racks. Fire suppression within 

predefined internal enclosures is by portable 

fire extinguisher. 

Two avionics racks accommodate almost all the 

electronic units for the command and data 

handling, audio and video functions, and for 

the conversion and distribution of the electrical 

power from the station’s solar arrays to the 

internal and attached elements. Command 

and control functions, as well as fault 

detection isolation and recovery algorithms, 

are supported by processing capabilities 

implemented in Node 3 computers. 

Two of the three station nodes, Node 2 

(Harmony) and Node 3, were made under a 

contract in Europe, while Node 1 (Unity) was 

made under a NASA contract in the 

United States. Node 1 has been in orbit 

since December 1998 while Node 2 has been 

in orbit since October 2007. 

Nodes 2 and 3 are an evolution of Node 1. 

Thales Alenia Space put forward a design for 

Nodes 2 and 3, deriving from the experience 

with the Multi-purpose Logistics Modules 

that took into account new habitability 

requirements, making possible permanent crew 

quarters for four astronauts, with the capability 

to treat and recycle water, cater for personal 

hygiene and waste, jettison carbon dioxide and 

generate oxygen. 
FEBRUARY 2010 PAYLOAD OVERVIEW 33

THE CUPOLA OBSERVATION MODULE 

The European Space Agency-developed Cupola observation module at the 

Kennedy Space Center. (Image: NASA) 

The Cupola will become a panoramic control 

tower for the International Space Station, a 

dome-shaped module with windows through 

which operations on the outside of the 

station can be observed and guided. It is a 

pressurized observation and work area that 

will accommodate command and control 

workstations and other hardware. 

Through the robotics workstation, astronauts 

will be able to control the space station’s robotic 

arm, which helps with the attachment and 

assembly of the various station elements, very 

much like the operator of a building crane 

perched in a control cabin. At any time, crew 

members in the Cupola can communicate with 

other crew members, either in another part of 

the station or outside during spacewalk 

activities. 

Spacewalking activities can be observed from 

the Cupola along with visiting spacecraft and 

external areas of the station with the Cupola 

offering a viewing spectrum of 360 degrees. 
34 PAYLOAD OVERVIEW FEBRUARY 2010

Thus, the Cupola will have an important role in 

external space station activities. 

However, the Cupola will operate as more 

than a workstation. With a clear view of Earth 

and celestial bodies, the Cupola will have 

scientific applications in the areas of Earth 

observation and space science as well as 

holding psychological benefits for the crew. 

The Cupola is a 1.6-ton aluminium 

structure 3 meters (9.8 feet) in diameter 

and 1.5 meters (4.7 feet) high. Its dome is 

a single forged unit with no welding. 

This gives it superior structural characteristics, 

which helped shorten the production schedule 

and lower overall costs. 

The Cupola is a “shirtsleeve” module with 

six trapezoidal side windows and a circular 

top window of 80 cm (31.5 inches) in diameter, 

making it the largest window ever flown 

in space. Each window is built using very 

advanced technologies to defend the sensitive 

fused silica glass panes from years of exposure 

to solar radiation and debris impacts. 

Produced from a single forging, Cupola’s dome requires no welds. Shown is the actual flight 

unit dome just after machining in October 2002 at the Ratier-Figeac facility in Figeac, France. 

(Image: Thales Alenia Space) 
FEBRUARY 2010 PAYLOAD OVERVIEW 35

The windows are protected by special external 

shutters, which can be opened by the crew 

inside the Cupola with the simple turn of a 

wrist. At the end of their tasks, the window 

shutters are closed to protect the glass from 

micrometeoroids and orbital debris and to 

prevent solar radiation from heating up the 

Cupola or to avoid losing heat to space. 

Each window has three subsections: an inner 

scratch pane to protect the pressure panes from 

accidental damage from inside the Cupola; two 

25 mm-thick (.98-inch) pressure panes to help 

maintain the cabin pressure and environment 

(the outer pane is a back-up for the inner pane); 

and a debris pane on the outside to protect the 

pressure panes from space debris when the 

Cupola shutters are open. 

The 10-year in-orbit lifetime calls for 

user-friendly replacement of the windows 

while in orbit. The entire window or the 

individual scratch and debris panes can be 

replaced in space. To replace an entire 

window, an astronaut would first fit an external 

pressure cover over the window during a 

spacewalk. 

NASA astronaut Terry Virts conducts a fit check of the robotic workstation of the 

Cupola observation module at the Space Station Processing Facility of NASA’s 

Kennedy Space Center on 31 July 2008. (Image: NASA/Cory Huston) 
36 PAYLOAD OVERVIEW FEBRUARY 2010

Internally, the Cupola must provide functions 

to support the presence of two astronauts 

operating the instruments. Cupola’s internal 

layout is dominated by upper and lower 

handrails around the inside of its cabin 

supporting most of the equipment and by 

“close-out” panels, which cover the harness and 

water lines attached to the Cupola. These 

internal panels form a pressurized air 

distribution system with the outer structure. 

These panels are removable to allow inspection 

and connection of different utilities. 

Limited space for the crew and equipment 

means that the man-machine interfaces have to 

be optimized for entry and exit from the Cupola 

and carrying out workstation tasks and 

maintenance. 

NODE 3 INTERNAL RACKS AND 

EQUIPMENT: ENVIRONMENTAL 

CONTROL 

Two Water Recovery System racks delivered to 

the station in November 2008 and the Oxygen 

Generation System rack which was delivered in 

July 2006 will be relocated to Node 3 after its 

arrival. These racks make up the core of the 

Regenerative Environmental Control and Life 

Support System. 

Water Recovery System Racks 

The Water Recovery System racks use a series 

of chemical processes and filters to treat the 

astronauts’ urine, perspiration and hygiene 

water, recycling about 93 percent of the fluid it 

receives to provide water clean enough to 

drink. 

ESA astronaut Frank De Winne works with the Water Recovery System’s Recycle Filter Tank 

Assembly in the Destiny laboratory of the International Space Station. (Image: NASA) 
FEBRUARY 2010 PAYLOAD OVERVIEW 37

Recovering water from urine is achieved in the 

Urine Processor Assembly by spinning up a 

keg-sized distiller to create artificial gravity. 

Contaminants press against the side of the 

distiller while steam in the middle is pumped 

out. Water from the urine processor is 

combined with all other wastewaters and 

delivered to the Water Processor Assembly 

for treatment. The water processor removes 

free gas and solid materials such as hair and 

lint before the water goes through a series 

of multifiltration beds for further purification. 

Any remaining organic contaminants and 

micro-organisms are removed by a 

high-temperature catalytic reactor assembly. 

This rigorous treatment creates water that 

meets stringent purity standards for human 

consumption. The purity of water is checked 

by sensors, with unacceptable water being 

reprocessed, and clean water being sent to a 

storage tank, ready for use by the crew. The 

Water Recovery System reduces the amount of 

water that needs to be delivered to the station 

by about 65 percent; i.e., about 2,850 liters over 

the course of a year. 

The Expedition 19 crew with drink bags aboard the station in May 2009 after being given the 

all clear to drink water reclaimed by the Water Recovery System. (Image: NASA) 
38 PAYLOAD OVERVIEW FEBRUARY 2010

Oxygen Generation System Rack 

The Oxygen Generation System produces 

oxygen for breathing air for the crew and 

laboratory animals, as well as for replacement 

of oxygen lost due to experiment use, airlock 

depressurization, module leakage and carbon 

dioxide venting. The system consists mainly of 

the Oxygen Generation Assembly and a Power 

Supply Module. 

The Oxygen Generation Assembly electrolyzes, 

or breaks apart, water provided by the Water 

Recovery System, yielding oxygen and 

hydrogen as by-products. The oxygen is 

delivered to the cabin atmosphere, and the 

hydrogen is vented overboard. The Power 

Supply Module provides the power needed by 

the Oxygen Generation Assembly to electrolyze 

the water. 

The Oxygen Generation System is designed to 

generate oxygen at a selectable rate and is 

capable of operating both continuously and 

cyclically. It provides up to 9 kg (19.8 pounds) 

of oxygen per day during continuous operation 

and a normal rate of about 5.5 kg (12 pounds) of 

oxygen per day during cyclic operation. 

NASA astronaut Michael Barratt working with the Air Revitalization System (ARS) 

in the US laboratory in September 2009. (Image: NASA) 
FEBRUARY 2010 PAYLOAD OVERVIEW 39

Air Revitalization System 

The Air Revitalization System is one of the 

Environmental Control and Life Support 

Systems that will be relocated to the 

European-built Node 3 when it arrives at the 

station in February 2010. It provides carbon 

dioxide removal, trace contaminant control, 

and monitors the major constituents in the 

cabin atmosphere. 

Crew-generated carbon dioxide is removed 

from the cabin atmosphere by sorbent beds that 

are designed to absorb carbon dioxide. The 

beds are regenerated upon exposure to heat 

and space vacuum. A Trace Contaminant 

Control System ensures that more than 

200 various trace chemical contaminants 

generated from material off-gassing and crew 

metabolic functions in the habitable volume 

remain within allowable and safe concentration 

limits. The cabin atmosphere is analyzed by a 

mass spectrometer, measuring oxygen, 

nitrogen, hydrogen, carbon dioxide, methane 

and water vapour present in the cabin. 

The Waste and Hygiene Compartment in the Destiny laboratory of the 

International Space Station on April 12, 2009. (Image: NASA) 
40 PAYLOAD OVERVIEW FEBRUARY 2010

Waste and Hygiene Compartment 

The Waste and Hygiene Compartment in the 

U.S. Destiny laboratory was the second 

toilet facility to arrive on the station in 

November 2008 as part of the STS-126 mission. 

The first toilet facility is in the Russian Service 

Module. 

This Russian-built toilet system is contained in 

a booth-like compartment and separately 

channels liquid and solid waste. While the 

solid waste goes to a holding tank, the Urine 

Processor Assembly, which forms a major part 

of the Water Recovery System racks delivered 

in November 2008, reclaims drinking water 

from crew members’ urine. 

ESA astronaut and Expedition 21 Commander Frank De Winne exercises on the 

COLBERT treadmill in the European-built Node 2 of the station in 

October 2009. (Image: NASA) 
FEBRUARY 2010 PAYLOAD OVERVIEW 41

NODE 3 INTERNAL RACKS AND 

EQUIPMENT: 

CONDITIONING/EXERCISE EQUIPMENT 

T2 COLBERT Treadmill 

The T2 Combined Operational Load Bearing 

External Resistance Treadmill or COLBERT was 

temporarily installed in the European-built 

Node 2 in September 2009 as an important 

exercise device to keep the station crew healthy 

while in orbit and prepare them for return to 

Earth. It will be relocated to its permanent 

place in Node 3 after its attachment in 

February 2010. The T2 treadmill is adapted 

from a regular treadmill but designed so as not 

to shake the rest of the station. This vibration 

damping system does not use power and hence 

makes it more reliable. 

The astronauts use elastic straps over the 

shoulders and round the waist to keep them in 

contact with the running belt and generate the 

foot force necessary to give the astronaut’s 

bones and muscles a workout in the absence of 

gravity. The treadmill is also wider than the 

TVIS treadmill in the Zvezda Service Module 

of the station. Although it is built to handle 

240,000 km (149,000 miles) of running, it will 

likely see about 60,000 km (37,282 miles) during 

its time in orbit. 

Japan Aerospace Exploration Agency astronaut and Expedition 19/20 Flight Engineer Koichi Wakata 

exercising using the advanced Resistive Exercise Device (aRED) in Node 1 in May 2009. 

(Image: NASA) 
42 PAYLOAD OVERVIEW FEBRUARY 2010

Advanced Resistive Exercise Device 

The advanced Resistive Exercise Device (aRED) 

will not take up a rack location in Node 3 but 

will be located in the new European-built 

module. It was developed to improve existing 

International Space Station exercise capabilities. 

It mimics the characteristics of traditional 

resistive exercises (weighted bars or dumbbells) 

by providing a more constant force throughout 

the range of motion. It offers traditional upper 

and lower-body exercises, such as squats, dead 

lift, heel raises, bicep curls, bench press, and 

many others. 

The aRED uses vacuum cylinders to provide 

concentric workloads up to 270 kg 

(595 pounds), with an eccentric load up to 

90 percent of the concentric force. The aRED 

also provides feedback to the astronaut during 

use and data to the NASA exercise 

physiologists. Flight surgeons, trainers and 

physiologists expect that the greater loads 

provided by aRED will result in more efficient 

and effective exercise, thereby preventing the 

muscle and bone loss that crew members 

sometimes experience during long space 

missions. 
FEBRUARY 2010 RENDEZVOUS & DOCKING 43

RENDEZVOUS & DOCKING 

Space Shuttle Endeavour prepares to dock with the International Space Station 

during the STS-127 mission. 

Endeavour’s launch for the STS-130 mission is 

precisely timed to lead to a link up with the 

International Space Station about 220 miles 

above the earth. A series of engine firings 

during the first two days of the mission will 

bring the shuttle to a point about 50,000 feet 

behind the station. Once there, Endeavour will 

start its final approach. About 2.5 hours before 

docking, the shuttle’s jets will be fired during 

what is called the terminal initiation burn. The 

shuttle will cover the final miles to the station 

during the next orbit. 

As Endeavour moves closer to the station, its 

rendezvous radar system and trajectory control 

sensor will provide the crew with range and 

closing-rate data. Several small correction 

burns will place the shuttle about 1,000 feet 

below the station. 

Commander George Zamka, with help from 

Pilot Terry Virts and other crew members, will 

manually fly the shuttle for the remainder of 

the approach and docking. 
44 RENDEZVOUS & DOCKING FEBRUARY 2010

Zamka will stop Endeavour about 600 feet 

below the station. Once he determines there is 

proper lighting, he will maneuver the shuttle 

through a nine-minute backflip called the 

Rendezvous Pitch Maneuver, also known as a 

the R-bar Pitch Maneuver as Endeavour is in 

line with an imaginary vertical R-bar directly 

below the station. During this maneuver, 

station crew members Jeff Williams and 

Oleg Kotov will use digital cameras with 

800mm and 400mm lenses, respectively, 

to photograph Endeavour’s upper and 

bottom surfaces through windows of the 

Zvezda Service Module. The 800mm lens 

provides up to one-inch resolution and the 

400mm lens up to three-inch resolution. 

The photography is one of several techniques 

used to inspect the shuttle’s thermal protection 

system for possible damage. Areas of special 

interest include the thermal protection tiles, the 

reinforced carbon-carbon of the nose and 

leading edges of the wings, landing gear doors 

and the elevon cove. The photos will be 

downlinked through the station’s Ku-band 

communications system for analysis by systems 

engineers and mission managers. 

When Endeavour completes its backflip, it will 

be back where it started, with its payload bay 

facing the station. Zamka then will fly the 

shuttle through a quarter circle to a position 

about 400 feet directly in front of the station. 

From that point he will begin the final approach 

to docking to the Pressurized Mating Adapter 2 

at the forward end of the Harmony node. 

The shuttle crew members will operate laptop 

computers that process the navigational data, 

the laser range systems, and Endeavour’s 

docking mechanism. 

Using a video camera mounted in the center of 

the Orbiter Docking System, Zamka will line up 

the docking ports of the two spacecraft. If 

necessary, he will pause the shuttle 30 feet from 

the station to ensure proper alignment of the 

docking mechanisms. He will maintain the 

shuttle’s speed relative to the station at about 

one-tenth of a foot per second, while both 

Endeavour and the station are moving at 

about 17,500 mph. Zamka will keep the 

docking mechanisms aligned to a tolerance 

of three inches. 

When Endeavour makes contact with the 

station, preliminary latches will automatically 

attach the two spacecrafts. The shuttle’s 

steering jets will be deactivated to reduce the 

forces acting at the docking interface. Shock 

absorber springs in the docking mechanism 

will dampen any relative motion between the 

shuttle and station. 

Once motion between the shuttle and the 

station has been stopped, the docking ring will 

be retracted to close a final set of latches 

between the two vehicles. 

UNDOCKING, SEPARATION, AND 

DEPARTURE 

At undocking time, the hooks and latches will 

be opened and springs will push the shuttle 

away from the station. Endeavour’s steering 

jets will be shut off to avoid any inadvertent 

firings during the initial separation. 

Once the shuttle is about two feet from the 

station and the docking devices are clear of one 

another, Virts will turn the steering jets back on 

and will manually control Endeavour within a 

tight corridor as the shuttle separates from the 

station. 
7 

FEBRUARY 2010 RENDEZVOUS & DOCKING 45

Endeavour will move to a distance of about 

450 feet, where Virts will begin to fly around 

the station. Virts will circle the shuttle around 

the station at a distance of 600 - 700 feet. 

Once the shuttle completes 1.5 revolutions of 

the complex, Virts will fire Endeavour’s jets to 

leave the area. The shuttle will begin to 

increase its distance from the station with each 

trip around the earth while ground teams 

analyze data from the late inspection of the 

shuttle’s heat shield. However, the distance 

will be close enough to allow the shuttle to 

return to the station in the unlikely event that 

the heat shield is damaged, preventing the 

shuttle’s safe re-entry. 
46 RENDEZVOUS & DOCKING FEBRUARY 2010

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FEBRUARY 2010 SPACEWALKS 47

SPACEWALKS 

Astronaut Robert L. Behnken, STS-123 mission specialist, participates in the mission’s third 

scheduled session of extravehicular activity (EVA) as construction and maintenance continue 

on the International Space Station. 

There are three spacewalks scheduled for the 

STS-130 mission. 

Mission specialists Robert Behnken and 

Nicholas Patrick will spend a total of 19.5 hours 

outside the station on flight days 5, 6 and 8. 

Behnken, the lead spacewalker for the mission, 

will wear a spacesuit marked with solid red 

stripes. These will be his fourth, fifth and 

sixth spacewalk – his first three, during the 

STS-123 mission in 2008, totaled 19 hours and 

19 minutes. Patrick , a first-time spacewalker, 

will wear an all-white suit. 

When a spacewalk – also called extravehicular 

activity, or EVA for short – is going on outside, 

one crew member inside the International 

Space Station is assigned the job of 

intravehicular officer, or spacewalk 

choreographer. In this case, that crew member 

will be Mission Specialist Stephen Robinson, 

a veteran spacewalker with more than 

20 hours of spacewalking experience under his 
48 SPACEWALKS FEBRUARY 2010

belt. The first spacewalks will also require 

astronauts inside the station to be at the 

controls of the station’s 58-foot-long robotic 

arm for the installation of the Tranquility Node. 

Pilot Terry Virts and Mission Specialist 

Kathryn Hire will be at the arm’s controls for 

that operation. 

Preparations will start the night before each 

spacewalk, when the astronauts spend time in 

the station’s Quest Airlock. This practice is 

called the campout prebreathe protocol and is 

used to purge nitrogen from the spacewalkers’ 

systems and prevent decompression sickness, 

also known as “the bends.” 

During the campout, the two astronauts 

performing the spacewalk will isolate 

themselves inside the airlock while the air 

pressure is lowered to 10.2 pounds per square 

inch, or psi. The station is kept at the near-sealevel pressure of 14.7 psi. The morning of the 

spacewalk, the astronauts will wear oxygen 

masks while the airlock’s pressure is raised 

back to 14.7 psi for an hour and the hatch 

between the airlock and the rest of the station is 

opened. That allows the spacewalkers to 

perform their morning routines before 

returning to the airlock, where the air pressure 

is lowered again. Approximately 50 minutes 

after the spacewalkers don their spacesuits, 

the prebreathe protocol will be complete. 

The procedure enables spacewalks to begin 

earlier in the crew’s day than was possible 

before the protocol was adopted. 
FEBRUARY 2010 SPACEWALKS 49

EVA-1 

Duration: 6 hours, 30 minutes

EVA Crew: Behnken and Patrick

IV CREW: Robinson 

Robotic Arm Operators: Virts and Hire 

EVA Operations: 

• Remove covers on Tranquility node 

berthing mechanism 

• Disconnect Tranquility node cables in the 

shuttle cargo bay 

• Move temporary storage platform from the 

special purpose dexterous manipulator to 

the P5/P6 truss segment 

• Connect temporary Tranquility heating 

cables 

• Connect Tranquility avionics cables 

The first order of business, once Behnken and 

Patrick begin the first spacewalk of the mission, 

will be the preparation of the new Tranquility 

node for installation on the Unity node. 

Behnken will begin by moving to Unity and 

opening a flap that will expose Unity’s 

centerline camera, which will be used to line up 
50 SPACEWALKS FEBRUARY 2010

the two nodes during installation. He will then 

remove eight contamination covers from the 

port on Tranquility that will be docked to 

Unity. 

While Behnken is doing so, Patrick will begin 

by installing an electric circuit on the avionics 

panel of Tranquility and removing cables that 

provide the node power from the shuttle before 

its installation. 

After a trip back to the airlock to retrieve 

insulation and jumpers to be stored for use in a 

later spacewalk, both Behnken and Patrick will 

come together at the special purpose dexterous 

manipulator – or Dextre – to remove its orbital 

replacement unit temporary platform, a storage 

platform that allows the robot to carry spare 

parts. They will retrieve two handles from 

storage and install them on the robot and the 

platform, then work together to release the four 

fasteners connecting the platform to the robot. 

Behnken will carry the platform to a stowage 

bin on the left side of the station’s truss, where 

it will be available for use as a backup to a new 

enhanced platform that will be installed on 

Dextre during the STS-132 mission. 

While that work is going on, Virts and Hire will 

have unloaded Tranquility from Endeavour’s 

cargo bay and installed it on the Unity node, 

at which point Behnken and Patrick can 

begin hooking it up. Patrick will begin by 

connecting Tranquility’s heater cables to Unity 

to provide a temporary power supply. 

Behnken, meanwhile, will connect eight 

avionics cables between the nodes. 

EVA-2 

Duration: 6 hours, 30 minutes

EVA Crew: Behnken and Patrick 

IV Crew: Robinson 

Robotic Arm Operator: None

EVA Operations 

• Install insulation covers on Tranquility 

trunnions and keel pin 

• Connect Tranquility ammonia cables 

• Install Tranquility atmospheric control and 

resupply system vent relief valve 

Behnken and Patrick will spend the first 

four hours of their second spacewalk 

connecting the ammonia loops on the new 

Tranquility node to those of the Destiny 

laboratory. There are two loops, with two lines 

apiece, each of which must be connected to 

both Tranquility and Destiny and routed 

through a bracket on Unity, which connects 

Tranquility to Destiny. Behnken will open one 

of the loops so that ammonia will be allowed to 

flow to the node from the station’s external 

thermal control system. 

Once that task is complete, the spacewalkers 

will spend the remaining time outfitting 

Tranquility. Behnken will install insulation on 

the keel pin and four trunnions that connected 

Tranquility to the shuttle while it was in transit. 

He will also set up the centerline camera on the 

nadir, or Earth-facing, port of Tranquility and 

release the launch locks that held the petals of 

the port’s berthing mechanism in place during 

launch. The Cupola will be moved to that port 

the following day. 
FEBRUARY 2010 SPACEWALKS 51

While Behnken works on that, Patrick will 

install eight handrails and a vent valve on 

Tranquility. The handrails will be used by 

spacewalkers to move along the exterior of the 

node, and the vent valve will be part of the 

atmospheric control and resupply system. 

That will be Patrick’s final task of the 

spacewalk. Behnken will wrap up his duties by 

removing tape on five gap spanners that act as 

a bridge for astronauts between areas on 

Tranquility without handrails. 

EVA-3 

Duration: 6 hours, 30 minutes

EVA Crew: Behnken and Patrick 

IV Crew: Robinson 

Robotic Arm Operator: None 

EVA Operations 

• Connect pressurized mating adapter 3 

heater and data cables 

• Open ammonia flow to Tranquility 

• Disconnect temporary Tranquility heating 

cables 

• Remove Cupola insulation covers 

• Release Cupola window covers launch locks 

• Install Tranquility handrails, worksite 

interfaces and gap spanners 

Tranquility outfitting will continue on the third 

and final spacewalk of the mission. Behnken 

will open the second of the two ammonia loops 

he and Patrick routed during the previous 

spacewalk, and disconnect the temporary 

power cables Patrick set up during the first 

spacewalk. 

By this time in the mission, the Cupola will 

have been moved to its permanent home on 

Tranquility’s nadir docking port, and the 

pressurized mating adapter 3 will have taken 

its place on the end of the node. That leaves 

Patrick and Behnken free to begin getting them 

into the right configuration. Patrick will 

connect the mating adapter’s heater and data 

cables to Tranquility. Then he will work with 

Behnken to remove six panels of insulation over 

the Cupola’s windows. 

With the insulation out of the way, Patrick will 

be able release the three bolts on each of the 

seven window’s covers; those bolts held the 

covers in place during Endeavour’s launch. 

While he does so, Behnken will get back to 

outfitting Tranquility by installing four 

worksite interfaces and five more handrails. 

At this point the two spacewalkers will come 

back together to route cables for the station’s 

video signal converter, or VSC. The VSC is 

used with power and data grapple fixtures, of 

PDGFs, which provide locations on the exterior 

of the station’s modules for the station’s robotic 

arm to attach to. 

Behnken and Patrick will wrap up the last of 

the spacewalk activities for the mission with 

two final tasks. First, they will close off the 

centerline camera that was used on the zenith, 

or space-facing, port of the Harmony node 

when the pressurized mating adapter 3 was 

attached it. And finally, they will each remove 

six clamps and the flex hose rotary coupler on 

the port 1 segment of the station’s truss. 
52 SPACEWALKS FEBRUARY 2010

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FEBRUARY 2010 EXPERIMENTS 53

EXPERIMENTS 

The space shuttle and International Space 

Station have an integrated research program 

that optimizes the use of shuttle crew members 

and long-duration space station crew members 

to address research questions in a variety of 

disciplines. 

For information on science on the station, visit 

http://www.nasa.gov/mission_pages/station/

science/index.html

or 

http://www.nasa.gov/mission_pages/station/

science/experiments/

Detailed information is located at 

http://www.nasa.gov/mission_pages/station/

science/experiments/Expedition.html

DETAILED TEST OBJECTIVES AND 

DETAILED SUPPLEMENTARY 

OBJECTIVES 

Detailed Test Objectives (DTOs) are aimed at 

testing, evaluating or documenting systems or 

hardware or proposed improvements to 

hardware, systems and operations. Many of 

the DTOs on this mission are to provide 

additional information for engineers working 

for the Constellation Program as they develop 

requirements for the rocket and crew module 

that will return humans to the moon. 

DTO 900 Solid Rocket Booster Thrust 

Oscillation 

The Space Shuttle Program is continuing to 

gather data on pressure oscillation, or periodic 

variation, a phenomenon that regularly occurs 

within solid rocket motors through the 

remaining Shuttle flights. The data obtained 

from five flights designated to acquire pressure 

oscillation data have provided a better 

understanding of solid rocket motor dynamics. 

The collection of these additional data points 

will provide greater statistical significance of 

the data for use in dynamic analyses of the 

four segment motors. These analyses and 

computer models will be used for future 

propulsion system designs. 

The pressure oscillation that is observed in 

solid rocket motors is similar to the hum made 

when blowing into a bottle. At 1.5 psi, or 

pounds per square inch, a pressure wave will 

move up and down the motor from the front to 

the rear, generating acoustic noise as well as 

physical loads in the structure. These data are 

necessary to help propulsion engineers confirm 

modeling techniques of pressure oscillations 

and the loads they create. As NASA engineers 

develop alternate propulsion designs for use in 

NASA, they will take advantage of current 

designs from which they can learn and 

measure. 

In an effort to obtain data to correlate pressure 

oscillation with the loads it can generate, the 

Space Shuttle Program is continuing to use the 

Enhanced Data Acquisition System to gather 

detailed information. 
54 EXPERIMENTS FEBRUARY 2010

EXPERIMENTS 

The STS-130/20A mission continues the 

transition from a focus on International Space 

Station (ISS) assembly to continuous scientific 

research beginning in the fall of 2010. 

Nearly 150 operating experiments in human 

research; biological and physical sciences; 

technology development; Earth observation, 

and educational activities will be conducted 

aboard the station, including several 

pathfinder investigations under the auspices 

of the station’s new role as a U.S. National 

Laboratory. 

In the past, assembly and maintenance 

activities have dominated the available time for 

crew work. But as completion of the orbiting 

laboratory nears, additional facilities and the 

crew members to operate them will enable a 

measured increase in time devoted to research 

as a national and multinational laboratory. 

Among the new National Laboratory 

Pathfinder (NLP) investigations is a new 

experiment that will look at the effect of 

microgravity on cells of the Jatropha curcas

plant. The purpose of the study is to assess 

the effects on cell structure, growth and 

development and breeding process for 

commercial use. Accelerated breeding could 

allow J. curcas to be used as an alternative 

energy crop (or biofuel) on Earth. 

The National Lab plant experiment joins plant 

experiments from NASA, the Canadian Space 

Agency, the Japan Aerospace Exploration 

Agency and the Russian Federal Space 

Agency that are looking at plant development 

for potential use as resources for future 

long-duration spaceflights, fundamental 

research into plant growth and development, 

and horticulture and crop monitoring. 

SHORT-DURATION U.S. INTEGRATED 

RESEARCH TO BE COMPLETED DURING 

STS-130/20A 

Maui Analysis of Upper Atmospheric 

Injections (MAUI) will observe the space 

shuttle engine exhaust plumes from the 

Maui Space Surveillance Site in Hawaii. The 

observations will occur when the Space Shuttle 

fires its engines at night or twilight. 

A telescope and all-sky imagers will take 

images and data while the space shuttle flies 

over the Maui site. The images will be 

analyzed to better understand the interaction 

between the spacecraft plume and the upper 

atmosphere of Earth. 

National Lab Pathfinder – Vaccine – 7 

(NLP-Vaccine-7) is a commercial payload 

serving as a pathfinder for the use of the 

ISS as a National Laboratory after station 

assembly is complete. It contains several 

different pathogenic (disease causing) 

organisms. This research is investigating the 

use of space flight to develop potential 

vaccines for the prevention of different 

infections caused by these pathogens on Earth 

and in microgravity. 

Ram Burn Observations – 2 (RAMBO-2) is an 

experiment in which the Department of 

Defense uses a satellite to observe space shuttle 

orbital maneuvering system engine burns. Its 

purpose is to improve plume models, which 

predict the direction the plume, or rising 

column of exhaust, will move as the shuttle 

maneuvers on orbit. Understanding the 

direction in which the spacecraft engine 

plume, or exhaust flows could be significant 
FEBRUARY 2010 EXPERIMENTS 55

to the safe arrival and departure of spacecraft 

on current and future exploration missions. 

Shuttle Exhaust Ion Turbulence Experiments 

(SEITE) will use space-based sensors to detect 

the ionospheric turbulence inferred from the 

radar observations from a previous space 

shuttle Orbital Maneuvering System (OMS) 

burn experiment using ground-based radar. 

Shuttle Ionospheric Modification with Pulsed 

Localized Exhaust Experiments (SIMPLEX)

will investigate plasma turbulence driven by 

rocket exhaust in the ionosphere using 

ground-based radars by providing direct 

measurements of exhaust flow sources and 

developing quantitative models of plasma 

turbulence that degrades tracking and imaging 

radars. This is a payload of opportunity on 

every shuttle flight based on available OMS 

fuel, crew time, and overflight of ground sites. 

Sleep-Wake Actigraphy and Light Exposure 

During Spaceflight – Short (Sleep-Short) 

will examine the effects of spaceflight 

on the sleep-wake cycles of the astronauts 

during space shuttle missions. Advancing 

state-of-the-art technology for monitoring, 

diagnosing and assessing treatment of sleep 

patterns is vital to treating insomnia on Earth 

and in space. 

Spinal Elongation and its Effects on Seated 

Height in a Microgravity Environment 

(Spinal Elongation) investigation provides 

quantitative data about the amount of change 

that occurs in the seated height due to spinal 

elongation in space. Spinal elongation has 

been observed to occur in crew members 

during space flight, but has only previously 

been recorded in the standing position. 

The seated height data in microgravity is 

considered necessary to correctly identify the 

seated height projections of the crew in the 

Orion configuration. The projections of seated 

height will provide data on the proper 

positioning of the seats within the vehicle, 

adequate clearance for seat stroke in high 

acceleration impacts, fit in seats, correct 

placements of seats with respect to each other 

and the vehicle and the proper orientation to 

displays and controls. 

Japan Aerospace Exploration Agency 

Research 

Mycological Evaluation of Crew Exposure to 

ISS Ambient Air (Myco) evaluates the risk of 

inhalation of microorganisms when breathing 

and of adhesion to the skin, which is exposed to 

ambient air during a stay in the ISS. Samples 

collected from the nasal cavity, pharynx and the 

skin of crew members during the pre/in/post 

flight periods will be examined by teams on 

Earth, focusing on fungi, which act as strong 

allergens in a living environment. 

SAMPLES/HARDWARE RETURNING 

FROM THE SPACE STATION: 

U.S. Research 

Bisphosphonates as a Countermeasure to 

Space Flight Induced Bone Loss 

(Bisphosphonates) will determine whether 

antiresorptive agents (help reduce bone loss), 

in conjunction with the routine in-flight 

exercise program, will protect station crew 

members from the regional decreases in bone 

mineral density documented on previous 

station missions. 
56 EXPERIMENTS FEBRUARY 2010

Commercial Generic Bioprocessing Apparatus 

Science Insert – 03 (CSI-03) is the third set of 

investigations in the CSI program series. The 

CSI program provides the K - 12 community 

opportunities to utilize the unique microgravity 

environment of the ISS as part of the regular 

classroom to encourage learning and interest 

in science, technology, engineering and math. 

CSI-03 will examine the painted lady butterfly 

and Monarch butterfly in space. 

Validation of Procedures for Monitoring 

Crew Member Immune Function (Integrated 

Immune) will assess the clinical risks resulting 

from the adverse effects of space flight on the 

human immune system and will validate a 

flight-compatible immune monitoring strategy. 

Researchers collect and analyze blood, urine 

and saliva samples from crew members before, 

during and after space flight to monitor 

changes in the immune system. 

Materials Science Laboratory – Columnar-toEquiaxed Transition in Solidification 

Processing and Microstructure Formation in 

Casting of Technical Alloys under Diffusive 

and Magnetically Controlled Convective 

Conditions (MSL-CETSOL and MICAST) are 

two investigations that support research into 

metallurgical solidification, semiconductor 

crystal growth (Bridgman and zone melting), 

and measurement of thermophysical properties 

of materials. This is a cooperative investigation 

with the European Space Agency (ESA) and 

NASA for accommodation and operation 

aboard the ISS. Microgravity offers a unique 

opportunity to obtain well-controlled 

solidification conditions for these alloys. 

Nutritional Status Assessment (Nutrition) is 

the most comprehensive inflight study done 

by NASA to date of human physiologic 

changes during long-duration space flight; 

this includes measures of bone metabolism, 

oxidative damage, nutritional assessments, and 

hormonal changes. This study will impact both 

the definition of nutritional requirements and 

development of food systems for future space 

exploration missions to the moon and Mars. 

This experiment will also help to understand 

the impact of countermeasures (exercise and 

pharmaceuticals) on nutritional status and 

nutrient requirements for astronauts. 

National Aeronautics and Space 

Administration Biological Specimen 

Repository (Repository) is a storage bank 

that is used to maintain biological specimens 

over extended periods of time and under 

well-controlled conditions. Biological samples 

from the ISS, including blood and urine, will be 

collected, processed and archived during the 

preflight, inflight and postflight phases of space 

station missions. This investigation has been 

developed to archive biosamples for use as a 

resource for future spaceflight-related research. 

A Comprehensive Characterization of 

Microorganisms and Allergens in Spacecraft 

(SWAB) will use advanced molecular 

techniques to comprehensively evaluate 

microbes on board the space station, including 

pathogens (organisms that may cause disease). 

It also will track changes in the microbial 

community as spacecraft visit the station and 

new station modules are added. This study 

will allow an assessment of the risk of microbes 

to the crew and the spacecraft. Previous 

microbial analysis of spacecraft only identify 

microorganisms that will grow in culture, 

omitting greater than 90 percent of all 

microorganisms including pathogens such as 

Legionella (the bacterium which causes 

Legionnaires‘ disease) and Cryptosporidium 
FEBRUARY 2010 EXPERIMENTS 57

(a parasite common in contaminated water). 

The incidence of potent allergens, such as dust 

mites, has never been systematically studied in 

spacecraft environments and microbial toxins 

have not been previously monitored. 

Canadian Space Agency 

The Cambium investigation is one in a pair 

of investigations which utilizes the Advanced 

Biological Research System (ABRS). Cambium 

seeks definitive evidence that gravity has 

a direct effect on cambial cells (cells located 

under the inner bark where secondary growth 

occurs) in willow, Salix babylonica. The 

Cambium research is needed to help 

understand the fundamental processes by 

which plants produce cellulose and lignin, the 

two main structural materials found in plant 

matter. 

European Space Agency Research 

Mental Representation of Spatial Cues 

During Space Flight (3D-Space) investigates 

the effects of exposure to microgravity on the 

mental representation of spatial cues by 

astronauts during and after space flight. The 

absence of the gravitational frame of reference 

during spaceflight could be responsible for 

disturbances in the mental representation 

of spatial cues, such as the perception of 

horizontal and vertical lines, the perception 

of objects‘ depth, and the perception of 

targets‘ distance. This experiment involves 

comparisons of preflight, inflight, and 

postflight perceptions and mental imagery, 

with special reference to spaceflight-related 

decreases in the vertical component of percepts. 

Japan Aerospace Exploration Agency 

Research 

RNA interference and protein 

phosphorylation in space environment using 

the nematode Caenorhabditis elegans

(CERISE) is an experiment that addresses 

two scientific objectives. The first is to evaluate 

the effect of microgravity on ribonucleic 

acid (RNA) interference. The second is to 

study how the space environment effects 

protein phosphorylation (addition of a 

phosphate molecule) and signal transduction 

in the muscle fibers of gene knock-downed 

Caenorhabditis elegans. 

Passive Dosimeter for Lifescience Experiment 

in Space (PADLES) measures radiation 

exposure levels onboard the ISS. PADLES uses 

passive and integrating dosimeters to detect 

radiation levels. These dosimeters are located 

near the biological experiment facilities and on 

the end of the Japanese Experiment Module, 

Kibo. The proposed research seeks to survey 

the radiation environment inside the Kibo by 

using Area dosimeter. The dosimeters measure 

absorbed doses, equivalent doses and Liner 

Energy Transfer (LET) distributions. 

EXPERIMENTS AND HARDWARE TO BE 

DELIVERED TO INTERNATIONAL SPACE 

STATION 

U.S. Research 

Validation of Procedures for Monitoring 

Crew Member Immune Function (Integrated 

Immune) will assess the clinical risks resulting 

from the adverse effects of space flight on the 

human immune system and will validate a 

flight-compatible immune monitoring strategy. 
58 EXPERIMENTS FEBRUARY 2010

Researchers collect and analyze blood, urine 

and saliva samples from crew members before, 

during and after space flight to monitor 

changes in the immune system. 

National Lab Pathfinder – Cells – 3 

(NLP-Cells-3) assesses the effects of 

microgravity on cells of the Jatropha curcas

plant. The purpose of the study is to verify 

the potential effects of microgravity on 

improving characteristics such as cell structure, 

growth and development, for accelerating the 

breeding process of new cultivars of J. curcas 

for commercial use. Accelerated breeding 

could allow J. curcas to be used as an alternative 

energy crop (or biofuel). This would allow 

the inclusion of a major biofuel plant as an 

alternative energy crop for the United States. 

Sleep-Wake Actigraphy and Light Exposure 

During Spaceflight – Long (Sleep-Long) will 

examine the effects of space flight and ambient 

light exposure on the sleep-wake cycles of the 

crew members during long-duration stays on 

the space station. 

Transgenic Arabidopsis Gene Expression 

System (TAGES) investigation is one in a 

pair of investigations that use the Advanced 

Biological Research System facility. TAGES 

uses Arabidopsis thaliana, thale cress, with 

sensor promoter-reporter gene constructs 

that render the plants as biomonitors 

(an organism used to determine the quality of 

the surrounding environment) of their 

environment using real-time nondestructive 

Green Fluorescent Protein imagery and 

traditional postflight analyses. The TAGES 

research is needed to help understand how 

plants perceive stresses in the spaceflight 

environment such as drought, inadequate 

light, or uneven temperature. Such genetically 

modified plants and imaging tools could be 

used as “biosensors” for characterizing other 

spacecraft environments. These same tools 

could also be used to further develop and 

analyze plants that could grow in either 

lunar or Martian bases. 

Analysis of a Novel Sensory Mechanism in 

Root Phototropism (Tropi) will observe growth 

and collect samples from plants sprouted from 

seeds. By analyzing the samples at a molecular 

level, researchers expect to gain insight on what 

genes are responsible for successful plant 

growth in microgravity. 

European Space Agency Research 

The Long Term Microgravity: A Model for 

Investigating Mechanisms of Heart Disease 

with New Portable Equipment (Card) 

experiment studies blood pressure decreases 

when the human body is exposed to 

microgravity. In order to increase the blood 

pressure to the level it was on Earth, salt is 

added to the crew members‘ diet. To monitor 

this, blood pressure readings and urine 

samples are performed at different intervals 

during the mission. This study will examine 

the relationship between salt intake and the 

cardiovascular system when exposed to the 

microgravity environment. Results from this 

may lead to additional health safety measures 

for astronauts to protect them on long 

duration missions. 

Japan Aerospace Exploration Agency 

Research 

The effect of long-term microgravity exposure 

on cardiac autonomic function by analyzing 

24-hours electrocardiogram (BioRhythms) will 

examine the effect of long-term microgravity 

exposure on cardiac autonomic function by 
FEBRUARY 2010 EXPERIMENTS 59

analyzing 24-hour eletrocardiogram. The 

objective of this study is to examine the effect 

of long-term microgravity exposure on cardiac 

autonomic function by monitoring pre; in; and 

post-flight 24-hours electrocardiogram. The 

results will be analyzed for improving crew 

health care technology in long-duration space 

flight. 

Educational Payload Observation (JAXA-EPO) 

aims to excite everyone‘s interest in 

microgravity research. Activities will include 

educational events and artistic activities 

with astronauts on orbit. These artistic 

activities will enlighten the general public 

about microgravity research and human 

space flight. 

Production of high performance 

nanomaterials Nanoskeleton in microgravity 

(Nanoskeleton) clarifies the gravity effect 

such as the flotation of oil, sedimentation and 

convection on the generated TiO2 crystal on 

hexagonal arranged micelle tube structure. 

Passive Dosimeter for Lifescience Experiment 

in Space (PADLES) measures radiation 

exposure levels onboard the ISS. PADLES uses 

passive and integrating dosimeters to detect 

radiation levels. These dosimeters are located 

near the biological experiment facilities and on 

the end of the Japanese Experiment Module, 

Kibo. The proposed research seeks to survey 

the radiation environment inside the Kibo 

by using Area dosimeter. The dosimeters 

measure absorbed doses, equivalent doses and 

LET distributions. 

TROPI-2: STUDYING PLANT GROWTH 

IN SPACE 

NASA scientists will send seeds into space to 

better understand how and why plants grow 

differently in microgravity than on Earth. In 

addition to carrying a third connecting-module, 

called Tranquility, and a seven-windowed 

control room for robotics to the International 

Space Station, STS-130 space shuttle Endeavour 

and its crew will deliver the Tropi-2 

experiment to space. After running two six-day 

experiments studying the early stages of plant 

growth, Tropi-2 will return to Earth in STS-131 

space shuttle Discovery. Scientists will use data 

from these experiments to better understand 

how light and gravity affect plant growth. 

Future astronauts may be able to 

grow plants as part of life support systems on 

long-duration space missions to the moon or 

Mars. 

Mission Overview 

Tropi-2 is a semi-autonomous space-based 

experiment to study Arabidopsis thaliana (thale 

cress) seedling sprouts to observe their 

response to light and gravity at a cellular level. 

Specifically, the seeds will be grown in 

microgravity – the weightlessness experienced 

on the station – or at gravity levels on Earth, the 

moon and Mars. Tropi-2 derives its name from 

the term “tropism.” For example, phototropism 

is a plant's growth response to a direct source 

of light, and gravitropism is its growth in 

response to the pull of gravity. 
60 EXPERIMENTS FEBRUARY 2010

European Modular Cultivation System (EMCS) Experiment Container with 

five Tropi Experiment Cards (ECs). Photo credit: NASA Ames/Tom Trower 
FEBRUARY 2010 EXPERIMENTS 61

A Tropi Experiment Card (EC) with seeds. 

Photo credit: NASA Ames/Dominic Hart 

The International Space Station 

Non-Exploration Projects Office at NASA’s 

Ames Research Center, Moffett Field, Calif., 

along with the principal investigator team 

at Miami University, Oxford, Ohio, prepared 

16 Experiment Containers (ECs), each 

containing five seed cassettes, by inserting 

more than 1,000 tiny sterilized seeds 

crossways onto a gridded membrane. 

The gridded membrane has lines that measure 

3 millimeters-by-3 millimeters to help scientists 

measure the plants’ growth – approximately 

10 millimeters during a six-day experiment. 

Using a microscope and tweezers, scientists 

precisely embedded the seeds, which are about 

the size of a grain of sand, into guar gum, an 

adhesive, to keep them in place during their 

launch, orbit and re-entry phase of the mission. 

The European Space Agency (ESA) developed 

the European Modular Cultivation System 

(EMCS), a facility focused on plant biology 

research located on the station that can 

house up to eight experiment containers at 

a time. Once in orbit, NASA astronauts 

Jeff Williams and T.J. Creamer will 

place the Tropi-2 experiment containers 

in the EMCS incubator to conduct the 

experiment in a temperature, humidity, and 

atmosphere-controlled environment. 

Once the experiment begins, the seeds will be 

continuously spun in centrifuges, to achieve 

varying levels of gravity, and given fresh water. 

The first three days are considered the 

“growth phase” of the experiment, during 

which the ECs will be exposed to gravity forces 

equivalent to Earth’s. For the first 32 hours the 

seeds will remain in the darkness, with the 
62 EXPERIMENTS FEBRUARY 2010

exception of a four-hour exposure to 

red LED lights. From then until the end 

of the “growth phase,” they will be illuminated 

with white LED lights. The last three days 

of the experiment are called the 

“stimulation phase,” when they will be 

“photostimulated” – or constantly exposed to 

red, blue or a combination of red and blue 

LED lights and exposed to either microgravity, 

or levels of gravity found on Earth, the moon 

or Mars. During the final phase of the 

experiment, cameras in the centrifuges will take 

three images per minute to collect the majority 

of the scientists’ data. 

After the experiment is completed, Williams 

and Creamer will remove the containers from 

the incubator and take out the cassettes with 

seedlings. Then they will place the cassettes 

into the station’s Minus Eighty (Degrees 

Celsius) Laboratory Freezer (MELFI) where 

they will remain until STS-131 space shuttle 

Discovery undocks. However, before 

Discovery undocks, astronauts will place 

the cassettes in precooled double cold bags as 

they transfer them from the MELFI to the 

Glacier freezer on the space shuttle. The 

samples are frozen to ensure they are preserved 

and to prevent any ribonucleic acid (RNA) 

degradation, prior to analysis on Earth. 

Tropi-2 is based on an earlier gravitropism and 

phototropism experiment, Tropi, which flew to 

the station on STS-121 and STS-115 in 2006. 

While this earlier experiment successfully 

obtained data in microgravity, no moon or 

Mars gravity levels data were obtained. 

Sterilized Arabidopsis thaliana seeds in guar gum adhesive are carefully positioned 

on a gridded membrane. Photo credit: NASA Ames/Dominic Hart 
FEBRUARY 2010 EXPERIMENTS 63

Relevance to Space Exploration and 

Earth Science 

During long-duration space exploration, 

astronauts will need regenerative sources of 

food, as well as a method to recycle carbon 

dioxide into breathable oxygen. As new 

information about how plants grow in 

microgravity emerges, scientists will refine 

existing sustainable plant-based life support 

systems. Further understanding of how plants 

grow and develop at a molecular level can lead 

to advancements in agricultural production on 

Earth. 

The Tropi-2 Team 

NASA Ames’ International Space Station 

Non-Exploration Projects Office will manage 

the Tropi-2 experiment for the Advanced 

Capabilities Division and Exploration 

Technology Development Program of the 

Exploration Systems Mission Directorate at 

NASA Headquarters, Washington. The 

Multi-Mission Operations Center at NASA 

Ames, along with the Norwegian User Support 

and Operations Centre in Trondheim, will 

provide mission operations support and receive 

Tropi-2 science data in real-time. John Z. Kiss, 

professor and chair of the Botany Department 

at Miami University, Oxford, Ohio, 

is the Tropi-2 principal investigator; 

Richard E. Edelmann of Miami University 

and Melanie J. Correll of the University 

of Florida, Gainesville, are Tropi-2 

co-investigators; Kenny Vassigh of NASA 

Ames, is the Tropi-2 project manager; 

Marianne Steele of NASA Ames, is the Tropi-2 

project scientist; Tom Luzod of NASA Ames is 

the Tropi-2 project engineer, David Heathcote 

of NASA Ames is the Tropi-2 operations lead. 

For More Information 

The Tropi-2 mission Web site is located at: 

http://spacebiosciences.arc.nasa.gov/STS130.html

ADDITIONAL STATION RESEARCH 

FROM NOW UNTIL THE END OF 

EXPEDITION 21/22 

Human Research and Countermeasure 

Development for Exploration 

Cardiovascular and Cerebrovascular Control 

on Return from ISS (CCISS) will study the 

effects of long-duration space flight on 

crewmembers’ heart functions and their blood 

vessels that supply the brain. Learning more 

about the cardiovascular and cerebrovascular 

systems could lead to specific countermeasures 

that might better protect future space travelers. 

This experiment is collaborative effort with the 

Canadian Space Agency. (NASA/CSA) 

Sleep-Wake Actigraphy and Light 

Exposure During Spaceflight-Long (SleepLong) examines the effects of space flight and 

ambient light exposure on the sleep-wake 

cycles of the crewmembers during longduration stays on the space station. (NASA) 

Nutritional Status Assessment (Nutrition) is 

the most comprehensive inflight study done by 

NASA to date of human physiologic changes 

during long-duration space flight; this includes 

measures of bone metabolism, oxidative 

damage, nutritional assessments, and hormonal 

changes. This study will impact both the 

definition of nutritional requirements and 

development of food systems for future space 

exploration missions to the Moon and Mars. 

This experiment will also help to understand 

the impact of countermeasures (exercise and 
64 EXPERIMENTS FEBRUARY 2010

pharmaceuticals) on nutritional status and 

nutrient requirements for astronauts. (NASA) 

The National Aeronautics and Space 

Administration Biological Specimen 

Repository (Repository) is a storage bank 

that is used to maintain biological specimens 

over extended periods of time and under 

well-controlled conditions. Biological samples 

from the International Space Station (ISS), 

including blood and urine, will be collected, 

processed and archived during the preflight, 

inflight and postflight phases of ISS missions. 

This investigation has been developed to 

archive biosamples for use as a resource for 

future space flight related research. (NASA) 

Validation of Procedures for Monitoring Crew 

Member Immune Function (Integrated 

Immune) assesses the clinical risks resulting 

from the adverse effects of space flight on the 

human immune system and will validate a 

flight-compatible immune monitoring strategy. 

Researchers collect and analyze blood, urine 

and saliva samples from crewmembers before, 

during and after space flight to monitor 

changes in the immune system. Changes in the 

immune system are monitored by collecting 

and analyzing blood and saliva samples from 

crewmembers during flight and blood, urine, 

and saliva samples before and after space flight. 

(NASA) 

Cardiac Atrophy and Diastolic Dysfunction 

During and After Long Duration Spaceflight: 

Functional Consequences for Orthostatic 

Intolerance, Exercise Capability and 

Risk for Cardiac Arrhythmias (Integrated 

Cardiovascular) will quantify the extent, time 

course and clinical significance of cardiac 

atrophy (decrease in the size of the heart 

muscle) associated with long-duration space 

flight. This experiment will also identify the 

mechanisms of this atrophy and the functional 

consequences for crewmembers that will spend 

extended periods of time in space. (NASA) 

Bisphosphonates as a Countermeasure to 

Space Flight Induced Bone Loss 

(Bisphosphonates) determines whether 

antiresorptive agents (help reduce bone loss), in 

conjunction with the routine inflight exercise 

program, will protect ISS crewmembers from 

the regional decreases in bone mineral density 

documented on previous ISS missions. (NASA) 

The effect of long-term microgravity 

exposure on cardiac autonomic function by 

analyzing 24-hours electrocardiogram 

(Biological Rhythms) examines the effect of 

long-term microgravity exposure on cardiac 

autonomic function by analyzing 24-hour 

electrocardiogram. (JAXA) 

SOdium LOading in Microgravity (SOLO) is a 

continuation of extensive research into the 

mechanisms of fluid and salt retention in the 

body during bed rest and spaceflights. It 

is a metabolically-controlled study. During 

long-term space missions astronauts will 

participate in two study phases, 5 days each. 

Subjects follow a diet of constant either low or 

normal sodium intake, fairly high fluid 

consumption and isocaloric nutrition. (ESA) 

Observing the Earth and Educational 

Activities 

Crew Earth Observations (CEO) takes 

advantage of the crew in space to observe and 

photograph natural and human-made changes 

on Earth. The photographs record the Earth’s 

surface changes over time, along with dynamic 

events such as storms, floods, fires and volcanic 

eruptions. These images provide researchers 
FEBRUARY 2010 EXPERIMENTS 65

on Earth with key data to better understand the 

planet. (NASA) 

Earth Knowledge Acquired by Middle School 

Students (EarthKAM) an education activity, 

allows middle school students to program a 

digital camera on board the International Space 

Station to photograph a variety of geographical 

targets for study in the classroom. Photos are 

made available on the world wide web for 

viewing and study by participating schools 

around the world. Educators use the images 

for projects involving Earth Science, geography, 

physics, and social science. (NASA) 

Physical and Biological Science in 

Microgravity 

Foam-Stability examines the characteristics 

and stability of foam under microgravity 

conditions. (ESA) 

Multi-User Droplet Combustion Apparatus – 

FLame Extinguishment Experiment 

(MDCA-FLEX) assesses the effectiveness of fire 

suppressants in microgravity and quantify the 

effect of different possible crew exploration 

atmospheres on fire suppression. The goal of 

this research is to provide definition and 

direction for large scale fire suppression tests 

and selection of the fire suppressant for next 

generation crew exploration vehicles. (NASA) 

Selectable Optical Diagnostics Instrument – 

Influence of Vibration on Diffusion of 

Liquids (SODI-IVIDIL) studies the influence 

of controlled vibration stimulus (slow shaking) 

on diffusion between different liquids in 

absence of convection induced by the gravity 

field. This investigation aims help scientists to 

model numerically this physical phenomenon. 

(NASA/ESA) 

Life Cycle of High Plants under Microgravity

Conditions (SpaceSeed) uses Arabidopsis 

thaliana to determine if the life cycle of the plant 

can be achieved in microgravity. Additionally, 

this study will examine the specific genes in the 

cell wall of the plant that do not activate under 

microgravity conditions that normally activated 

in 1-g conditions. (JAXA) 

Technology Development 

Synchronized Position Hold, Engage, 

Reorient, Experimental Satellites (SPHERES)

are bowling-ball sized spherical satellites. They 

are used inside the space station to test a 

set of well-defined instructions for spacecraft 

performing autonomous rendezvous and 

docking maneuvers. Three free-flying spheres 

fly within the cabin of the Space Station, 

performing flight formations. Each satellite is 

self-contained with power, propulsion, 

computers and navigation equipment. The 

results are important for satellite servicing, 

vehicle assembly and formation flying 

spacecraft configurations. (NASA) 

Space Dynamically Responding Ultrasonic 

Matrix System (SpaceDRUMS) comprises a 

suite of hardware that enables containerless 

processing (samples of experimental materials 

can be processed without ever touching a 

container wall). Using a collection of 

20 acoustic beam emitters, SpaceDRUMS can 

completely suspend a baseball-sized solid or 

liquid sample during combustion or heat-based 

synthesis. Because the samples never contact 

the container walls, materials can be produced 

in microgravity with an unparalleled quality of 

shape and composition. The ultimate goal of 

the SpaceDRUMS hardware is to assist with the 

development of advanced materials of a 

commercial quantity and quality, using the 
66 EXPERIMENTS FEBRUARY 2010

space-based experiments to guide development 

of manufacturing processes on Earth. 

Microgravity Acceleration Measurement 

System (MAMS) and Space Acceleration 

Measurement System (SAMS-II) measure 

vibration and quasi-steady accelerations that 

result from vehicle control burns, docking and 

undocking activities. The two different 

equipment packages measure vibrations at 

different frequencies. 

Payload Operations Coordination 

The work of more than 400 scientists, this 

research has been prioritized based on 

fundamental and applied research needs 

established by NASA and the international 

partners – the Canadian Space Agency (CSA), 

the European Space Agency (ESA), the Japan 

Aerospace and Exploration Agency (JAXA) and 

the Russian Federal Space Agency (RSA). 

Managing the international laboratory’s 

scientific assets, as well as the time and space 

required to accommodate experiments and 

programs from a host of private, commercial, 

industry and government agencies nationwide, 

makes the job of coordinating space station 

research critical. 

Teams of controllers and scientists on the 

ground continuously plan, monitor and 

remotely operate experiments from control 

centers around the globe. Controllers staff 

payload operations centers around the world, 

effectively providing for researchers and the 

station crew around the clock, seven days a 

week. 

State-of-the-art computers and communications 

equipment deliver up-to-the-minute reports 

about experiment facilities and investigations 

between science outposts across the United 

States and around the world. The payload 

operations team also synchronizes the payload 

time lines among international partners, 

ensuring the best use of valuable resources and 

crew time. 

The control centers of NASA and its partners 

are 

• NASA Payload Operations Center, Marshall 

Space Flight Center in Huntsville, Ala. 

• RSA Center for Control of Spaceflights 

(“TsUP” in Russian) in Korolev, Russia 

• JAXA Space Station Integration and 

Promotion Center (SSIPC) in Tskuba, Japan 

• ESA Columbus Control Center (Col-CC) in 

Oberpfaffenhofen, Germany 

• CSA Payloads Operations Telesciences 

Center, St. Hubert, Quebec, Canada 

NASA’s Payload Operations Center serves as a 

hub for coordinating much of the work related 

to delivery of research facilities and 

experiments to the space station as they are 

rotated in and out periodically when space 

shuttles or other vehicles make deliveries and 

return completed experiments and samples to 

Earth. 

The payload operations director leads the 

POC’s main flight control team, known as the 

“cadre,” and approves all science plans in 

coordination with Mission Control at NASA’s 

Johnson Space Center in Houston, the 

international partner control centers and the 

station crew. 
FEBRUARY 2010 EXPERIMENTS 67

On the Internet 

For fact sheets, imagery and more on 

International Space Station experiments and 

payload operations, visit: 

http://www.nasa.gov/mission_pages/station/

science/
68 EXPERIMENTS FEBRUARY 2010

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FEBRUARY 2010 SHUTTLE REFERENCE DATA 69

SHUTTLE REFERENCE DATA 

SHUTTLE ABORT MODES 

Redundant Sequence Launch Sequencer 

(RSLS) Aborts 

These occur when the on-board shuttle 

computers detect a problem and command a 

halt in the launch sequence after taking over 

from the ground launch sequencer and before 

solid rocket booster ignition. 

Ascent Aborts 

Selection of an ascent abort mode may become 

necessary if there is a failure that affects vehicle 

performance, such as the failure of a space 

shuttle main engine or an orbital maneuvering 

system engine. Other failures requiring early 

termination of a flight, such as a cabin leak, 

might also require the selection of an abort 

mode. There are two basic types of ascent abort 

modes for space shuttle missions: intact aborts 

and contingency aborts. Intact aborts are 

designed to provide a safe return of the orbiter 

to a planned landing site. Contingency aborts 

are designed to permit flight crew survival 

following more severe failures when an intact 

abort is not possible. A contingency abort 

would generally result in a ditch operation. 

Intact Aborts 

There are four types of intact aborts: abort to 

orbit (ATO), abort once around (AOA), 

transoceanic abort landing (TAL) and return to 

launch site (RTLS). 

Return to Launch Site 

The RTLS abort mode is designed to allow the 

return of the orbiter, crew, and payload to the 

launch site, KSC, approximately 25 minutes 

after liftoff. 

The RTLS profile is designed to accommodate 

the loss of thrust from one space shuttle main 

engine between liftoff and approximately 

four minutes 20 seconds, after which not 

enough main propulsion system propellant 

remains to return to the launch site. An RTLS 

can be considered to consist of three stages – a 

powered stage, during which the space shuttle 

main engines are still thrusting; an external 

tank separation phase; and the glide phase, 

during which the orbiter glides to a landing at 

the KSC. The powered RTLS phase begins with 

the crew selection of the RTLS abort, after solid 

rocket booster separation. The crew selects the 

abort mode by positioning the abort rotary 

switch to RTLS and depressing the abort push 

button. The time at which the RTLS is selected 

depends on the reason for the abort. For 

example, a three-engine RTLS is selected at the 

last moment, about 3 minutes, 34 seconds into 

the mission; whereas an RTLS chosen due to an 

engine out at liftoff is selected at the earliest 

time, about 2 minutes, 20 seconds into the 

mission (after solid rocket booster separation). 

After RTLS is selected, the vehicle continues 

downrange to dissipate excess main propulsion 

system propellant. The goal is to leave only 

enough main propulsion system propellant to 

be able to turn the vehicle around, fly back 

toward the KSC and achieve the proper main 

engine cutoff conditions so the vehicle can glide 

to the KSC after external tank separation. 

During the downrange phase, a pitch-around 

maneuver is initiated (the time depends in part 

on the time of a space shuttle main engine 
70 SHUTTLE REFERENCE DATA FEBRUARY 2010

failure) to orient the orbiter/external tank 

configuration to a heads-up attitude, pointing 

toward the launch site. At this time, the vehicle 

is still moving away from the launch site, but 

the space shuttle main engines are now 

thrusting to null the downrange velocity. In 

addition, excess orbital maneuvering system 

and reaction control system propellants are 

dumped by continuous orbital maneuvering 

system and reaction control system engine 

thrustings to improve the orbiter weight and 

center of gravity for the glide phase and 

landing. 

The vehicle will reach the desired main engine 

cutoff point with less than 2 percent excess 

propellant remaining in the external tank. At 

main engine cutoff minus 20 seconds, a pitch 

down maneuver (called powered pitch-down) 

takes the mated vehicle to the required external 

tank separation attitude and pitch rate. After 

main engine cutoff has been commanded, the 

external tank separation sequence begins, 

including a reaction control system maneuver 

that ensures that the orbiter does not recontact 

the external tank and that the orbiter has 

achieved the necessary pitch attitude to begin 

the glide phase of the RTLS. 

After the reaction control system maneuver has 

been completed, the glide phase of the RTLS 

begins. From then on, the RTLS is handled 

similarly to a normal entry. 

Transoceanic Abort Landing 

The TAL abort mode was developed to 

improve the options available when a space 

shuttle main engine fails after the last RTLS 

opportunity but before the first time that an 

AOA can be accomplished with only two space 

shuttle main engines or when a major orbiter 

system failure, for example, a large cabin 

pressure leak or cooling system failure, occurs 

after the last RTLS opportunity, making it 

imperative to land as quickly as possible. 

In a TAL abort, the vehicle continues on a 

ballistic trajectory across the Atlantic Ocean to 

land at a predetermined runway. Landing 

occurs about 45 minutes after launch. The 

landing site is selected near the normal ascent 

ground track of the orbiter to make the most 

efficient use of space shuttle main engine 

propellant. The landing site also must have the 

necessary runway length, weather conditions 

and U.S. State Department approval. The three 

landing sites that have been identified for a 

launch are Zaragoza, Spain; Moron, Spain; and 

Istres, France. 

To select the TAL abort mode, the crew must 

place the abort rotary switch in the TAL/AOA 

position and depress the abort push button 

before main engine cutoff (depressing it after 

main engine cutoff selects the AOA abort 

mode). The TAL abort mode begins sending 

commands to steer the vehicle toward the plane 

of the landing site. It also rolls the vehicle 

heads up before main engine cutoff and sends 

commands to begin an orbital maneuvering 

system propellant dump (by burning the 

propellants through the orbital maneuvering 

system engines and the reaction control system 

engines). This dump is necessary to increase 

vehicle performance (by decreasing weight) to 

place the center of gravity in the proper place 

for vehicle control and to decrease the vehicle’s 

landing weight. TAL is handled like a normal 

entry. 

Abort to Orbit 

An ATO is an abort mode used to boost the 

orbiter to a safe orbital altitude when 

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

shuttle main engine fails in a region that results 

in a main engine cutoff under speed, the MCC 

will determine that an abort mode is necessary 

and will inform the crew. The orbital 

maneuvering system engines would be used to 

place the orbiter in a circular orbit. 

Abort Once Around 

The AOA abort mode is used in cases in which 

vehicle performance has been lost to such an 

extent that either it is impossible to achieve a 

viable orbit or not enough orbital maneuvering 

system propellant is available to accomplish the 

orbital maneuvering system thrusting 

maneuver to place the orbiter on orbit and the 

deorbit thrusting maneuver. In addition, an 

AOA is used in cases in which a major systems 

problem (cabin leak, loss of cooling) makes it 

necessary to land quickly. In the AOA abort 

mode, one orbital maneuvering system 

thrusting sequence is made to adjust the 

post-main engine cutoff orbit so a second 

orbital maneuvering system thrusting sequence 

will result in the vehicle deorbiting and landing 

at the AOA landing site (White Sands, N.M.; 

Edwards Air Force Base, Calif.; or the Kennedy 

Space Center, Fla). Thus, an AOA results in the 

orbiter circling the Earth once and landing 

about 90 minutes after liftoff. 

After the deorbit thrusting sequence has been 

executed, the flight crew flies to a landing at the 

planned site much as it would for a nominal 

entry. 

Contingency Aborts 

Contingency aborts are caused by loss of more 

than one main engine or failures in other 

systems. Loss of one main engine while 

another is stuck at a low thrust setting also may 

necessitate a contingency abort. Such an abort 

would maintain orbiter integrity for in-flight 

crew escape if a landing cannot be achieved at a 

suitable landing field. 

Contingency aborts due to system failures other 

than those involving the main engines would 

normally result in an intact recovery of vehicle 

and crew. Loss of more than one main engine 

may, depending on engine failure times, result 

in a safe runway landing. However, in most 

three-engine-out cases during ascent, the 

orbiter would have to be ditched. The inflight 

crew escape system would be used before 

ditching the orbiter. 

Abort Decisions 

There is a definite order of preference for the 

various abort modes. The type of failure and the 

time of the failure determine which type of abort 

is selected. In cases where performance loss is 

the only factor, the preferred modes are ATO, 

AOA, TAL and RTLS, in that order. The mode 

chosen is the highest one that can be completed 

with the remaining vehicle performance. 

In the case of some support system failures, 

such as cabin leaks or vehicle cooling problems, 

the preferred mode might be the one that will 

end the mission most quickly. In these cases, 

TAL or RTLS might be preferable to AOA or 

ATO. A contingency abort is never chosen if 

another abort option exists. 

Mission Control Houston is prime for calling 

these aborts because it has a more precise 

knowledge of the orbiter’s position than the 

crew can obtain from on-board systems. Before 

main engine cutoff, Mission Control makes 

periodic calls to the crew to identify which 

abort mode is (or is not) available. If ground 

communications are lost, the flight crew has 

FEBRUARY 2010 SHUTTLE REFERENCE DATA 71
72 SHUTTLE REFERENCE DATA FEBRUARY 2010

onboard methods, such as cue cards, dedicated 

displays and display information, to determine 

the abort region. Which abort mode is selected 

depends on the cause and timing of the failure 

causing the abort and which mode is safest or 

improves mission success. If the problem is a 

space shuttle main engine failure, the flight 

crew and Mission Control Center select the best 

option available at the time a main engine fails. 

If the problem is a system failure that 

jeopardizes the vehicle, the fastest abort mode 

that results in the earliest vehicle landing is 

chosen. RTLS and TAL are the quickest options 

(35 minutes), whereas an AOA requires about 

90 minutes. Which of these is selected depends 

on the time of the failure with three good space 

shuttle main engines. 

The flight crew selects the abort mode by 

positioning an abort mode switch and 

depressing an abort push button. 

SHUTTLE ABORT HISTORY 

RSLS Abort History 

(STS-41 D) June 26, 1984 

The countdown for the second launch attempt 

for Discovery’s maiden flight ended at T-4 

seconds when the orbiter’s computers detected 

a sluggish valve in main engine No. 3. The 

main engine was replaced and Discovery was 

finally launched on Aug. 30, 1984. 

(STS-51 F) July 12, 1985 

The countdown for Challenger’s launch was 

halted at T-3 seconds when onboard computers 

detected a problem with a coolant valve on 

main engine No. 2. The valve was replaced and 

Challenger was launched on July 29, 1985. 

(STS-55) March 22, 1993 

The countdown for Columbia’s launch was 

halted by onboard computers at T-3 seconds 

following a problem with purge pressure 

readings in the oxidizer preburner on main 

engine No. 2. Columbia’s three main engines 

were replaced on the launch pad, and the flight 

was rescheduled behind Discovery’s launch 

on STS-56. Columbia finally launched on 

April 26, 1993. 

(STS-51) Aug. 12, 1993 

The countdown for Discovery’s third launch 

attempt ended at the T-3 second mark when 

onboard computers detected the failure of one 

of four sensors in main engine No. 2 which 

monitor the flow of hydrogen fuel to the 

engine. All of Discovery’s main engines were 

ordered replaced on the launch pad, delaying 

the shuttle’s fourth launch attempt until 

Sept. 12, 1993. 

(STS-68) Aug. 18, 1994 

The countdown for Endeavour’s first launch 

attempt ended 1.9 seconds before liftoff when 

onboard computers detected higher than 

acceptable readings in one channel of a sensor 

monitoring the discharge temperature of the 

high pressure oxidizer turbopump in main 

engine No. 3. A test firing of the engine at the 

Stennis Space Center in Mississippi on 

September 2nd confirmed that a slight drift in a 

fuel flow meter in the engine caused a slight 

increase in the turbopump’s temperature. The 

test firing also confirmed a slightly slower start 

for main engine No. 3 during the pad abort, 

which could have contributed to the higher 

temperatures. After Endeavour was brought 

back to the Vehicle Assembly Building to be 

outfitted with three replacement engines, 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 73

NASA managers set Oct. 2 as the date for 

Endeavour’s second launch attempt. 

Abort to Orbit History 

(STS-51 F) July 29, 1985 

After an RSLS abort on July 12, 1985, 

Challenger was launched on July 29, 1985. 

Five minutes and 45 seconds after launch, a 

sensor problem resulted in the shutdown of 

center engine No. 1, resulting in a safe “abort to 

orbit” and successful completion of the mission. 

SPACE SHUTTLE MAIN ENGINES 

Developed in the 1970s by NASA’s Marshall 

Space Flight Center, MSFC in Huntsville, Ala., 

the space shuttle main engine is the most 

advanced liquid-fueled rocket engine ever built. 

Every space shuttle main engine is tested and 

proven flight worthy at NASA’s Stennis Space 

Center in south Mississippi, before installation 

on an orbiter. Its main features include variable 

thrust, high performance reusability, high 

redundancy and a fully integrated engine 

controller. 

The shuttle’s three main engines are mounted 

on the orbiter aft fuselage in a triangular 

pattern. Spaced so that they are movable 

during launch, the engines are used, in 

conjunction with the solid rocket boosters, to 

steer the shuttle vehicle. 

Each of these powerful main engines is 14 feet 

long, weighs about 7,000 pounds and is 7.5 feet 

in diameter at the end of its nozzle. 

The engines operate for about 8.5 minutes 

during liftoff and ascent, burning more than 

500,000 gallons of super-cold liquid hydrogen 

and liquid oxygen propellants stored in the 

external tank attached to the underside of the 

shuttle. The engines shut down just before the 

shuttle, traveling at about 17,000 miles per 

hour, reaches orbit. 

The main engine operates at greater 

temperature extremes than any mechanical 

system in common use today. The fuel, 

liquefied hydrogen at -423 degrees Fahrenheit, 

is the second coldest liquid on Earth. When it 

and the liquid oxygen are combusted, the 

temperature in the main combustion chamber is 

6,000 degrees Fahrenheit, hotter than the 

boiling point of iron. 

The main engines use a staged combustion 

cycle so that all propellants entering the engines 

are used to produce thrust, or power, more 

efficiently than any previous rocket engine. In 

a staged combustion cycle, propellants are first 

burned partially at high pressure and relatively 

low temperature, and then burned completely 

at high temperature and pressure in the main 

combustion chamber. The rapid mixing of the 

propellants under these conditions is so 

complete that 99 percent of the fuel is burned. 

At normal operating level, each engine 

generates 490,847 pounds of thrust, measured 

in a vacuum. Full power is 512,900 pounds of 

thrust; minimum power is 316,100 pounds of 

thrust. 

The engine can be throttled by varying the 

output of the preburners, thus varying the 

speed of the high-pressure turbopumps and, 

therefore, the flow of the propellant. 

At about 26 seconds into ascent, the main 

engines are throttled down to 316,000 pounds 

of thrust to keep the dynamic pressure on the 

vehicle below a specified level, about 

580 pounds per square foot, known as max q. 

Then, the engines are throttled back up to 
74 SHUTTLE REFERENCE DATA FEBRUARY 2010

normal operating level at about 60 seconds. 

This reduces stress on the vehicle. The main 

engines are throttled down again at about 

seven minutes, 40 seconds into the mission to 

maintain three g’s, three times the Earth’s 

gravitational pull, reducing stress on the crew 

and the vehicle. This acceleration level is about 

one-third the acceleration experienced on 

previous crewed space vehicles. 

About 10 seconds before main engine cutoff, or 

MECO, the cutoff sequence begins. About 

three seconds later the main engines are 

commanded to begin throttling at 10 percent 

thrust per second until they achieve 65 percent 

thrust. This is held for about 6.7 seconds, and 

the engines are shut down. 

The engine performance has the highest thrust 

for its weight of any engine yet developed. In 

fact, one space shuttle main engine generates 

sufficient thrust to maintain the flight of two 

and one-half Boeing 747 airplanes. 

The space shuttle main engine also is the first 

rocket engine to use a built-in electronic digital 

controller, or computer. The controller accepts 

commands from the orbiter for engine start, 

change in throttle, shutdown and monitoring of 

engine operation. 

NASA continues to increase the reliability and 

safety of shuttle flights through a series of 

enhancements to the space shuttle main 

engines. The engines were modified in 1988, 

1995, 1998, 2001 and 2007. Modifications 

include new high-pressure fuel and oxidizer 

turbopumps that reduce maintenance and 

operating costs of the engine, a two-duct 

powerhead that reduces pressure and 

turbulence in the engine, and a single-coil heat 

exchanger that lowers the number of post flight 

inspections required. Another modification 

incorporates a large-throat main combustion 

chamber that improves the engine’s reliability 

by reducing pressure and temperature in the 

chamber. 

The most recent engine enhancement is the 

Advanced Health Management System, or 

AHMS, which made its first flight in 2007. 

AHMS is a controller upgrade that provides 

new monitoring and insight into the health of 

the two most complex components of the space 

shuttle main engine – the high pressure fuel 

turbopump and the high pressure oxidizer 

turbopump. New advanced digital signal 

processors monitor engine vibration and have 

the ability to shut down an engine if vibration 

exceeds safe limits. AHMS was developed by 

engineers at Marshall. 

After the orbiter lands, the engines are removed 

and returned to a processing facility at 

Kennedy Space Center, Fla., where they are 

rechecked and readied for the next flight. Some 

components are returned to the main engine’s 

prime contractor, Pratt & Whitney Rocketdyne, 

West Palm Beach, Fla., for regular maintenance. 

The main engines are designed to operate for 

7.5 accumulated hours. 

SPACE SHUTTLE SOLID ROCKET 

BOOSTERS (SRB) 

The two solid rocket boosters required for a 

space shuttle launch and first two minutes 

of powered flight boast the largest 

solid-propellant motors ever flown. They are 

the first large rockets designed for reuse and 

are the only solid rocket motors rated for 

human flight. The SRBs have the capacity to 

carry the entire weight of the external tank, or 

ET, and orbiter, and to transmit the weight load 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 75

through their structure to the mobile launch 

platform, or MLP.

The SRBs provide 71.4 percent of the thrust 

required to lift the space shuttle off the launch 

pad and during first-stage ascent to an altitude 

of about 150,000 feet, or 28 miles. At launch, 

each booster has a sea level thrust of 

approximately 3.3 million pounds and is 

ignited after the ignition and verification of the 

three space shuttle main engines, or SSMEs. 

SRB apogee occurs at an altitude of about 

230,000 feet, or 43 miles, 75 seconds after 

separation from the main vehicle. At booster 

separation, the space shuttle orbiter has reached 

an altitude of 24 miles and is traveling at a 

speed in excess of 3,000 miles per hour. 

The primary elements of each booster are nose 

cap, housing the pilot and drogue parachute; 

frustum, housing the three main parachutes in 

a cluster; forward skirt, housing the booster 

flight avionics, altitude sensing, recovery 

avionics, parachute cameras and range safety 

destruct system; four motor segments, 

containing the solid propellant; motor nozzle; 

and aft skirt, housing the nozzle and thrust 

vector control systems required for guidance. 

Each SRB possesses its own redundant 

auxiliary power units and hydraulic pumps. 

SRB impact occurs in the ocean approximately 

140 miles downrange. SRB retrieval is 

provided after each flight by specifically 

designed and built ships. The frustums, 

drogue and main parachutes are loaded onto 

the ships along with the boosters and towed 

back to the Kennedy Space Center, where they 

are disassembled and refurbished for reuse. 

Before retirement, each booster can be used as 

many as 20 times. 

Each booster is just over 149 feet long and 

12.17 feet in diameter. Both boosters have a 

combined weight of 1,303,314 pounds at lift-off. 

They are attached to the ET at the SRB aft attach 

ring by an upper and lower attach strut and a 

diagonal attach strut. The forward end of each 

SRB is affixed to the ET by one attach bolt and 

ET ball fitting on the forward skirt. While 

positioned on the launch pad, the space shuttle 

is attached to the MLP by four bolts and 

explosive nuts equally spaced around each SRB. 

After ignition of the solid rocket motors, the 

nuts are severed by small explosives that allow 

the space shuttle vehicle to perform lift off. 

United Space Alliance (USA) 

USA, at KSC facilities, is responsible for all SRB 

operations except the motor and nozzle 

portions. In conjunction with maintaining 

sole responsibility for manufacturing and 

processing of the non-motor hardware and 

vehicle integration, USA provides the service 

of retrieval, post flight inspection and 

analysis, disassembly and refurbishment of the 

hardware. USA also exclusively retains 

comprehensive responsibility for the orbiter. 

The reusable solid rocket motor segments are 

shipped from ATK Launch Systems in Utah to 

KSC, where they are mated by USA personnel 

to the other structural components – the 

forward assembly, aft skirt, frustum and nose 

cap – in the Vehicle Assembly Building. Work 

involves the complete disassembly and 

refurbishment of the major SRB structures – the 

aft skirts, frustums, forward skirts and all 

ancillary hardware – required to complete an 

SRB stack and mate to the ET. Work then 

proceeds to ET/SRB mate, mate with the orbiter 

and finally, space shuttle close out operations. 

After hardware restoration concerning flight 
76 SHUTTLE REFERENCE DATA FEBRUARY 2010

configuration is complete, automated checkout 

and hot fire are performed early in hardware 

flow to ensure that the refurbished components 

satisfy all flight performance requirements. 

ATK Launch Systems (ATK) 

ATK Launch Systems of Brigham City, Utah, 

manufactures space shuttle reusable solid 

rocket motors, or RSRMs, at their Utah facility. 

Each RSRM – just over 126 feet long and 12 feet 

in diameter – consists of four rocket motor 

segments and an aft exit cone assembly is. 

From ignition to end of burn, each RSRM 

generates an average thrust of 2.6 million 

pounds and burns for approximately 

123 seconds. Of the motor’s total weight of 

1.25 million pounds, propellant accounts for 

1.1 million pounds. The four motor segments 

are matched by loading each from the same 

batches of propellant ingredients to minimize 

any thrust imbalance. The segmented casing 

design assures maximum flexibility in 

fabrication and ease of transportation and 

handling. Each segment is shipped to KSC on a 

heavy-duty rail car with a specialty built cover. 

SRB Hardware Design Summary 

Hold-Down Posts 

Each SRB has four hold-down posts that fit into 

corresponding support posts on the MLP. 

Hold-down bolts secure the SRB and MLP posts 

together. Each bolt has a nut at each end, but 

the top nut is frangible, or breakable. The top 

nut contains two NASA Standard detonators, 

or NSDs, that, when ignited at solid rocket 

motor ignition command, split the upper nut in 

half. 

Splitting the upper nuts allow the hold-down 

bolts to be released and travel downward 

because of NSD gas pressure, gravity and the 

release of tension in the bolt, which is 

pretensioned before launch. The bolt is 

stopped by the stud deceleration stand which 

contains sand to absorb the shock of the bolt 

dropping down several feet. The SRB bolt is 

28 inches long, 3.5 inches in diameter and 

weighs approximately 90 pounds. The 

frangible nut is captured in a blast container on 

the aft skirt specifically designed to absorb the 

impact and prevent pieces of the nut from 

liberating and becoming debris that could 

damage the space shuttle. 

Integrated Electronic Assembly (IEA) 

The aft IEA, mounted in the ET/SRB attach ring, 

provides the electrical interface between the 

SRB systems and the obiter. The aft IEA 

receives data, commands, and electrical power 

from the orbiter and distributes these inputs 

throughout each SRB. Components located in 

the forward assemblies of each SRB are 

powered by the aft IEA through the forward 

IEA, except for those utilizing the recovery and 

range safety batteries located in the forward 

assemblies. The forward IEA communicates 

with and receives power from the orbiter 

through the aft IEA, but has no direct electrical 

connection to the orbiter. 

Electrical Power Distribution 

Electrical power distribution in each SRB 

consists of orbiter-supplied main dc bus power 

to each SRB via SRB buses A, B and C. Orbiter 

main dc buses A, B and C supply main dc bus 

power to corresponding SRB buses A, B and C. 

In addition, orbiter main dc, bus C supplies 

backup power to SRB buses A and B, and 

orbiter bus B supplies backup power to SRB 

bus C. This electrical power distribution 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 77

arrangement allows all SRB buses to remain 

powered in the event one orbiter main bus fails. 

The nominal dc voltage is 28 V dc, with an 

upper limit of 32 V dc and a lower limit of 

24 V dc. 

Hydraulic Power Units (HPUs) 

There are two self-contained, independent 

HPUs on each SRB. Each HPU consists of an 

auxiliary power unit, or APU; Fuel Supply 

Module, or FSM; hydraulic pump; hydraulic 

reservoir; and hydraulic fluid manifold 

assembly. The APUs are fueled by hydrazine 

and generate mechanical shaft power to a 

hydraulic pump that produces hydraulic 

pressure for the SRB hydraulic system. The 

APU controller electronics are located in the 

SRB aft integrated electronic assemblies on the 

aft ET attach rings. The two separate HPUs 

and two hydraulic systems are located inside 

the aft skirt of each SRB between the SRB 

nozzle and skirt. The HPU components are 

mounted on the aft skirt between the rock and 

tilt actuators. The two systems operate from 

T minus 28 seconds until SRB separation from 

the orbiter and ET. The two independent 

hydraulic systems are connected to the rock 

and tilt servoactuators. 

The HPUs and their fuel systems are isolated 

from each other. Each fuel supply module, or 

tank, contains 22 pounds of hydrazine. The 

fuel tank is pressurized with gaseous nitrogen 

at 400 psi to provide the force to expel via 

positive expulsion the fuel from the tank to the 

fuel distribution line. A positive fuel supply to 

the APU throughout its operation is 

maintained. 

The fuel isolation valve is opened at APU 

startup to allow fuel to flow to the APU fuel 

pump and control valves and then to the gas 

generator. The gas generator’s catalytic action 

decomposes the fuel and creates a hot gas. It 

feeds the hot gas exhaust product to the APU 

two-stage gas turbine. Fuel flows primarily 

through the startup bypass line until the APU 

speed is such that the fuel pump outlet pressure 

is greater than the bypass line’s, at which point 

all the fuel is supplied to the fuel pump. 

The APU turbine assembly provides 

mechanical power to the APU gearbox, which 

drives the APU fuel pump, hydraulic pump 

and lube oil pump. The APU lube oil pump 

lubricates the gearbox. The turbine exhaust of 

each APU flows over the exterior of the gas 

generator, cooling it and directing it overboard 

through an exhaust duct. 

When the APU speed reaches 100 percent, the 

APU primary control valve closes and the 

APU speed is controlled by the APU controller 

electronics. If the primary control valve logic 

fails to the open state, the secondary control 

valve assumes control of the APU at 

112 percent speed. Each HPU on an SRB is 

connected to both servoactuators. One HPU 

serves as the primary hydraulic source for the 

servoactuator and the other HPU serves as the 

secondary hydraulics for the servoactuator. 

Each servoactuator has a switching valve that 

allows the secondary hydraulics to power the 

actuator if the primary hydraulic pressure 

drops below 2,050 psi. A switch contact on the 

switching valve will close when the valve is in 

the secondary position. When the valve is 

closed, a signal is sent to the APU controller 

that inhibits the 100 percent APU speed control 

logic and enables the 112 percent APU speed 

control logic. The 100 percent APU speed 

enables one APU/HPU to supply sufficient 
78 SHUTTLE REFERENCE DATA FEBRUARY 2010

operating hydraulic pressure to both 

servoactuators of that SRB. 

The APU 100 percent speed corresponds to 

72,000 rpm, 110 percent to 79,200 rpm and 

112 percent to 80,640 rpm. 

The hydraulic pump speed is 3,600 rpm and 

supplies hydraulic pressure of 3,050, plus or 

minus 50 psi. A high-pressure relief valve 

provides overpressure protection to the 

hydraulic system and relieves at 3,750 psi. 

The APUs/HPUs and hydraulic systems are 

reusable for 20 missions. 

Thrust Vector Control (TVC) 

Each SRB has two hydraulic gimbal 

servoactuators: one for rock and one for tilt. 

The servoactuators provide the force and 

control to gimbal the nozzle for TVC. The 

all-axis gimbaling capability is 8 degrees. Each 

nozzle has a carbon cloth liner that erodes 

and chars during firing. The nozzle is a 

convergent-divergent, movable design in which 

an aft pivot-point flexible bearing is the 

gimbal mechanism. 

The space shuttle ascent TVC portion of the 

flight control system directs the thrust of the 

three SSMEs and the two SRB nozzles to control 

shuttle attitude and trajectory during liftoff and 

ascent. Commands from the guidance system 

are transmitted to the ascent TVC, or ATVC, 

drivers, which transmit signals proportional to 

the commands to each servoactuator of the 

main engines and SRBs. Four independent 

flight control system channels and four ATVC 

channels control six main engine and four 

SRB ATVC drivers, with each driver controlling 

one hydraulic port on each main and SRB 

servoactuator. 

Each SRB servoactuator consists of four 

independent, two-stage servovalves that 

receive signals from the drivers. Each 

servovalve controls one power spool in each 

actuator, which positions an actuator ram and 

the nozzle to control the direction of thrust. 

The four servovalves in each actuator provide a 

force-summed majority voting arrangement to 

position the power spool. With four identical 

commands to the four servovalves, the actuator 

force-sum action prevents a single erroneous 

command from affecting power ram motion. If 

the erroneous command persists for more than 

a predetermined time, differential pressure 

sensing activates a selector valve to isolate and 

remove the defective servovalve hydraulic 

pressure. This permits the remaining channels 

and servovalves to control the actuator ram 

spool. 

Failure monitors are provided for each channel 

to indicate which channel has been bypassed. 

An isolation valve on each channel provides the 

capability of resetting a failed or bypassed 

channel. 

Each actuator ram is equipped with transducers 

for position feedback to the thrust vector 

control system. Within each servoactuator ram 

is a splashdown load relief assembly to cushion 

the nozzle at water splashdown and prevent 

damage to the nozzle flexible bearing. 

SRB Rate Gyro Assemblies (RGAs) 

Each SRB contains two RGAs mounted in the 

forward skirt watertight compartment. Each 

RGA contains two orthogonally mounted 

gyroscopes – pitch and yaw axes. In 

conjunction with the orbiter roll rate gyros, they 

provide angular rate information that describes 

the inertial motion of the vehicle cluster to the 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 79

orbiter computers and the guidance, navigation 

and control system during first stage ascent 

to SRB separation. At SRB separation, all 

guidance control data is handed off from the 

SRB RGAs to the orbiter RGAs. The RGAs are 

designed and qualified for 20 missions. 

Propellant 

The propellant mixture in each SRB motor 

consists of ammonium perchlorate, an oxidizer, 

69.6 percent by weight; aluminum, a fuel, 

16 percent by weight; iron oxide, a catalyst, 

0.4 percent by weight; polymer, a binder that 

holds the mixture together, 12.04 percent by 

weight; and epoxy curing agent, 1.96 percent by 

weight. The propellant is an 11-point 

star-shaped perforation in the forward motor 

segment and a double truncated cone 

perforation in each of the aft segments and aft 

closure. This configuration provides high 

thrust at ignition and then reduces the thrust by 

about one-third 50 seconds after liftoff to 

prevent overstressing the vehicle during 

maximum dynamic pressure. 

SRB Ignition 

SRB ignition can occur only when a manual 

lock pin from each SRB safe and arm device has 

been removed by the ground crew during 

prelaunch activities. At T minus 5 minutes, the 

SRB safe and arm device is rotated to the arm 

position. The solid rocket motor ignition 

commands are issued when the three SSMEs 

are at or above 90 percent rated thrust; no 

SSME fail and/or SRB ignition pyrotechnic 

initiator controller, or PIC low voltage is 

indicated; and there are no holds from the 

launch processing system, or LPS. 

The solid rocket motor ignition commands are 

sent by the orbiter computers through the 

master events controllers, or MECs, to the 

NSDs installed in the safe and arm device in 

each SRB. A pyrotechnic initiation controller, 

or PIC, is a single-channel capacitor discharge 

device that controls the firing of each 

pyrotechnic device. Three signals must be 

present simultaneously for the PIC to generate 

the pyro firing output. These signals – arm, fire 

1 and fire 2 – originate in the orbiter 

general-purpose computers and are transmitted 

to the MECs. The MECs reformat them to 

28 V dc signals for the PICs. The arm signal 

charges the PIC capacitor to 40 V dc, minimum 

20 V dc. 

The fire 2 commands cause the redundant 

NSDs to fire through a thin barrier seal down a 

flame tunnel. This ignites a pyro booster 

charge, which is retained in the safe and arm 

device behind a perforated plate. The booster 

charge ignites the propellant in the igniter 

initiator; and combustion products of this 

propellant ignite the solid rocket motor igniter, 

which fires down the length of the solid rocket 

motor igniting the solid rocket motor 

propellant. 

The general purpose computer, or GPC, launch 

sequence also controls certain critical main 

propulsion system valves and monitors the 

engine-ready indications from the SSMEs. The 

main propulsion system, or MPS, start 

commands are issued by the on-board 

computers at T minus 6.6 seconds. There is a 

staggered start – engine three, engine two, 

engine one – within 0.25 of a second, and the 

sequence monitors the thrust buildup of 

each engine. All three SSMEs must reach the 

required 90 percent thrust within three seconds; 

otherwise, an orderly shutdown is commanded 

and safing functions are initiated. 
80 SHUTTLE REFERENCE DATA FEBRUARY 2010

Normal thrust buildup to the required 

90 percent thrust level will result in the SSMEs 

being commanded to the liftoff position at 

T minus 3 seconds as well as the fire 1 

command being issued to arm the SRBs. At 

T minus three seconds, the vehicle base 

bending load modes are allowed to initialize. 

At T minus 0, the two SRBs are ignited by the 

four orbiter on-board computers; commands 

are sent to release the SRBs; the two T-0 

umbilicals, one on each side of the spacecraft, 

are retracted; the on-board master timing unit, 

event timer and mission event timers are 

started; the three SSMEs are at 100 percent; and 

the ground launch sequence is terminated. 

SRB Separation 

The SRB/ET separation subsystem provides for 

separation of the SRBs from the orbiter/ET 

without damage to or recontact of the elements 

– SRBs, orbiter/ET – during or after separation 

for nominal modes. SRB separation is initiated 

when the three solid rocket motor chamber 

pressure transducers are processed in the 

redundancy management middle value select 

and the head end chamber pressure of both 

SRBs is less than or equal to 50 psi. A backup 

cue is the time elapsed from booster ignition. 

The separation sequence is initiated, 

commanding the thrust vector control actuators 

to the null position and putting the main 

propulsion system into a second-stage 

configuration 0.8 second from sequence 

initialization, which ensures the thrust of each 

SRB is less than 100,000 pounds. Orbiter yaw 

attitude is held for four seconds and SRB thrust 

drops to less than 60,000 pounds. The SRBs 

separate from the ET within 30 milliseconds of 

the ordnance firing command. 

The forward attachment point consists of a ball 

on the SRB and socket on the ET, held together 

by one bolt. The bolt contains one NSD 

pressure cartridge at each end. The forward 

attachment point also carries the range safety 

system cross-strap wiring connecting each SRB 

range safety system, or RSS, and the ET RSS 

with each other. 

The aft attachment points consist of three 

separate struts: upper, diagonal, and lower. 

Each strut contains one bolt with an NSD 

pressure cartridge at each end. The upper strut 

also carries the umbilical interface between its 

SRB and the external tank and on to the orbiter. 

Redesigned Booster Separation Motors (RBSM) 

Eight Booster Separation Motors, or BSMs, are 

located on each booster – four on the forward 

section and four on the aft skirt. BSMs provide 

the force required to push the SRBs away from 

the orbiter/ET at separation. Each BSM weighs 

approximately 165 pounds and is 31.1 inches 

long and 12.8 inches in diameter. Once the 

SRBs have completed their flight, the BSMs are 

fired to jettison the SRBs away from the orbiter 

and external tank, allowing the boosters to 

parachute to Earth and be reused. The BSMs in 

each cluster of four are ignited by firing 

redundant NSD pressure cartridges into 

redundant confined detonating fuse manifolds. 

The separation commands issued from the 

orbiter by the SRB separation sequence initiate 

the redundant NSD pressure cartridge in each 

bolt and ignite the BSMs to effect a clean 

separation. 

Redesigned BSMs flew for the first time in both 

forward and aft locations on STS-125. As a 

result of vendor viability and manifest support 

issues, space shuttle BSMs are now being 

manufactured by ATK. The igniter has been 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 81

redesigned and other changes include material 

upgrades driven by obsolescence issues and 

improvements to process and inspection 

techniques. 

SRB Cameras 

Each SRB flies with a complement of four 

cameras, three mounted for exterior views 

during launch, separation and descent; and one 

mounted internal to the forward dome for main 

parachute performance assessment during 

descent. 

The ET observation camera is mounted on the 

SRB forward skirt and provides a wide-angle 

view of the ET intertank area. The camera is 

activated at lift off by a G-switch and records 

for 350 seconds, after which the recorder is 

switched to a similar camera in the forward 

skirt dome to view the deployment and 

performance of the main parachutes to splash 

down. These cameras share a digital tape 

recorder located within the data acquisition 

system. 

The ET ring camera is mounted on the ET 

attach ring and provides a view up the stacked 

vehicle on the orbiter underside and the bipod 

strut attach point. 

The forward skirt camera is mounted on the 

external surface of the SRB forward skirt and 

provides a view aft down the stacked vehicle of 

the orbiter underside and the wing leading 

edge reinforced carbon-carbon, or RCC, panels. 

The ET attach ring camera and forward skirt 

camera are activated by a global positioning 

system command at approximately T minus 

1 minute 56 seconds to begin recording at 

approximately T minus 50 seconds. The camera 

images are recorded through splash down. 

These cameras each have a dedicated recorder 

and are recorded in a digital format. The 

cameras were designed, qualified, and 

implemented by USA after Columbia to 

provide enhanced imagery capabilities to 

capture potential debris liberation beginning 

with main engine start and continuing through 

SRB separation. 

The camera videos are available for engineering 

review approximately 24 hours following the 

arrival of the boosters at KSC. 

Range Safety Systems (RSS) 

The RSS consists of two antenna couplers; 

command receivers/decoders; a dual 

distributor; a safe and arm device with two 

NSDs; two confined detonating fuse manifolds; 

seven confined detonator fuse, or CDF 

assemblies; and one linear-shaped charge. 

The RSS provides for destruction of a rocket or 

part of it with on-board explosives by remote 

command if the rocket is out of control, to 

limit danger to people on the ground from 

crashing pieces, explosions, fire, and poisonous 

substances. 

The space shuttle has two RSSs, one in each 

SRB. Both are capable of receiving two 

command messages – arm and fire – which are 

transmitted from the ground station. The RSS 

is only used when the space shuttle violates a 

launch trajectory red line. 

The antenna couplers provide the proper 

impedance for radio frequency and ground 

support equipment commands. The command 

receivers are tuned to RSS command 

frequencies and provide the input signal to the 

distributors when an RSS command is sent. 

The command decoders use a code plug to 
82 SHUTTLE REFERENCE DATA FEBRUARY 2010

prevent any command signal other than the 

proper command signal from getting into the 

distributors. The distributors contain the logic 

to supply valid destruct commands to the RSS 

pyrotechnics. 

The NSDs provide the spark to ignite the CDF 

that in turn ignites the linear shaped charge for 

space shuttle destruction. The safe and arm 

device provides mechanical isolation between 

the NSDs and the CDF before launch and 

during the SRB separation sequence. 

The first message, called arm, allows the 

onboard logic to enable a destruct and 

illuminates a light on the flight deck display 

and control panel at the commander and pilot 

station. The second message transmitted is the 

fire command. The SRB distributors in the 

SRBs are cross-strapped together. Thus, if one 

SRB received an arm or destruct signal, the 

signal would also be sent to the other SRB. 

Electrical power from the RSS battery in each 

SRB is routed to RSS system A. The recovery 

battery in each SRB is used to power RSS 

system B as well as the recovery system in the 

SRB. The SRB RSS is powered down during the 

separation sequence, and the SRB recovery 

system is powered up. 

Descent and Recovery 

After separation and at specified altitudes, the 

SRB forward avionics system initiates the 

release of the nose cap, which houses a pilot 

parachute and drogue parachute; and the 

frustum, which houses the three main 

parachutes. Jettison of the nose cap at 

15,700 feet deploys a small pilot parachute and 

begins to slow the SRB decent. At an altitude 

of 15,200 feet the pilot parachute pulls the 

drogue parachute from the frustum. The 

drogue parachute fully inflates in stages, and at 

5,500 feet pulls the frustum away from the SRB, 

which initiates the deployment of the three 

main parachutes. The parachutes also inflate in 

stages and further slow the decent of the SRBs 

to their final velocity at splashdown. The 

parachutes slow each SRB from 368 mph at first 

deployment to 52 mph at splashdown, allowing 

for the recovery and reuse of the boosters. 

Two 176-foot recovery ships, Freedom Star and 

Liberty Star, are on station at the splashdown 

zone to retrieve the frustums with drogue 

parachutes attached, the main parachutes and 

the SRBs. The SRB nose caps and solid rocket 

motor nozzle extensions are not recovered. The 

SRBs are dewatered using an enhanced diver 

operating plug to facilitate tow back. These 

plugs are inserted into the motor nozzle and 

air is pumped into the booster, causing it to 

lay flat in the water to allow it to be easily 

towed. The boosters are then towed back to 

the refurbishment facilities. Each booster is 

removed from the water and components are 

disassembled and washed with fresh and 

deionized water to limit saltwater corrosion. 

The motor segments, igniter and nozzle are 

shipped back to ATK in Utah for 

refurbishment. The nonmotor components and 

structures are disassembled by USA and are 

refurbished to like-new condition at both KSC 

and equipment manufacturers across the 

country. 

SPACE SHUTTLE SUPER LIGHT WEIGHT 

TANK (SLWT) 

The super lightweight external tank (SLWT) 

made its first shuttle flight June 2, 1998, on 

mission STS-91. The SLWT is 7,500 pounds 

lighter than the standard external tank. The 

lighter weight tank allows the shuttle to deliver 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 83

International Space Station elements (such as 

the service module) into the proper orbit. 

The SLWT is the same size as the previous 

design. But the liquid hydrogen tank and the 

liquid oxygen tank are made of aluminum 

lithium, a lighter, stronger material than the 

metal alloy used for the shuttle’s current tank. 

The tank’s structural design has also been 

improved, making it 30 percent stronger and 

5 percent less dense. 

The SLWT, like the standard tank, is 

manufactured at Michoud Assembly, near 

New Orleans, by Lockheed Martin. 

The 154-foot-long external tank is the largest 

single component of the space shuttle. It stands 

taller than a 15-story building and has a 

diameter of about 27 feet. The external tank 

holds over 530,000 gallons of liquid hydrogen 

and liquid oxygen in two separate tanks. The 

hydrogen (fuel) and liquid oxygen (oxidizer) 

are used as propellants for the shuttle’s three 

main engines. 

EXTERNAL TANK 

The 154-foot-long external tank is the largest 

single component of the space shuttle. It stands 

taller than a 15-story building and has a 

diameter of about 27 feet. The external tank 

holds more than 530,000 gallons of liquid 

hydrogen and liquid oxygen in two separate 

tanks, the forward liquid oxygen tank and the 

aft liquid hydrogen tank. An unpressurized 

intertank unites the two propellant tanks. 

Liquid hydrogen (fuel) and liquid oxygen 

(oxidizer) are used as propellants for the 

shuttle’s three main engines. The external tank 

weighs 58,500 pounds empty and 

1,668,500 pounds when filled with propellants. 

The external tank is the “backbone” of the 

shuttle during launch, providing structural 

support for attachment with the solid rocket 

boosters and orbiter. It is the only component 

of the shuttle that is not reused. Approximately 

8.5 minutes after reaching orbit, with its 

propellant used, the tank is jettisoned and falls 

in a preplanned trajectory. Most of the tank 

disintegrates in the atmosphere, and the 

remainder falls into the ocean. 

The external tank is manufactured at NASA’s 

Michoud Assembly Facility in New Orleans by 

Lockheed Martin Space Systems. 

Foam Facts 

The external tank is covered with spray-on 

foam insulation that insulates the tank before 

and during launch. More than 90 percent of the 

tank’s foam is applied using an automated 

system, leaving less than 10 percent to be 

applied manually. 

There are two types of foam on the external 

tank, known as the Thermal Protection System, 

or TPS. One is low-density, closed-cell foam on 

the tank acreage and is known as Spray-OnFoam-Insulation, often referred to by its 

acronym, SOFI. Most of the tank is covered by 

either an automated or manually applied SOFI. 

Most areas around protuberances, such as 

brackets and structural elements, are applied by 

pouring foam ingredients into part-specific 

molds. The other is a denser composite 

material made of silicone resins and cork and 

called ablator. An ablator is a material that 

dissipates heat by eroding. It is used on areas 

of the external tank subjected to extreme heat, 

such as the aft dome near the engine exhaust, 

and remaining protuberances, such as the cable 

trays. These areas are exposed to extreme 

aerodynamic heating. 
84 SHUTTLE REFERENCE DATA FEBRUARY 2010

Closed-cell foam used on the tank was 

developed to keep the propellants that fuel the 

shuttle’s three main engines at optimum 

temperature. It keeps the shuttle’s liquid 

hydrogen fuel at -423 degrees Fahrenheit 

and the liquid oxygen tank at near 

-297 degrees Fahrenheit, even as the tank sits 

under the hot Florida sun. At the same time, 

the foam prevents a buildup of ice on the 

outside of the tank. 

The foam insulation must be durable enough to 

endure a 180-day stay at the launch pad, 

withstand temperatures up to 115 degrees 

Fahrenheit, humidity as high as 100 percent, 

and resist sand, salt, fog, rain, solar radiation 

and even fungus. Then, during launch, the 

foam must tolerate temperatures as high as 

2,200 degrees Fahrenheit generated by 

aerodynamic friction and radiant heating from 

the 3,000 degrees Fahrenheit main engine 

plumes. Finally, when the external tank begins 

reentry into the Earth’s atmosphere about 

30 minutes after launch, the foam maintains the 

tank’s structural temperatures and allows it to 

safely disintegrate over a remote ocean location. 

Though the foam insulation on the majority of 

the tank is only 1-inch thick, it adds 

4,823 pounds to the tank’s weight. In the areas 

of the tank subjected to the highest heating, 

insulation is somewhat thicker, between 1.5 to 

3 inches thick. Though the foam’s density 

varies with the type, an average density is 

about 2.4 pounds per cubic foot. 

Application of the foam, whether automated by 

computer or hand-sprayed, is designed to meet 

NASA’s requirements for finish, thickness, 

roughness, density, strength and adhesion. As 

in most assembly production situations, the 

foam is applied in specially designed, 

environmentally controlled spray cells and 

applied in several phases, often over a period of 

several weeks. Before spraying, the foam’s raw 

material and mechanical properties are tested 

to ensure they meet NASA specifications. 

Multiple visual inspections of all foam surfaces 

are performed after the spraying is complete. 

Most of the foam is applied at NASA’s 

Michoud Assembly Facility in New Orleans 

when the tank is manufactured, including most 

of the “closeout” areas, or final areas applied. 

These closeouts are done either by hand 

pouring or manual spraying. Additional 

closeouts are completed once the tank reaches 

Kennedy Space Center, Fla. 

The super lightweight external tank, or SLWT, 

made its first shuttle flight in June 1998 on 

mission STS-91. The SLWT is 7,500 pounds 

lighter than previously flown tanks. The SLWT 

is the same size as the previous design, but the 

liquid hydrogen tank and the liquid oxygen 

tank are made of aluminum lithium, a lighter, 

stronger material than the metal alloy used 

previously. 

Beginning with the first Return to Flight 

mission, STS-114 in June 2005, several 

improvements were made to improve safety 

and flight reliability. 

Forward Bipod 

The external tank’s forward shuttle attach 

fitting, called the bipod, was redesigned to 

eliminate the large insulating foam ramps as a 

source of debris. Each external tank has two 

bipod fittings that connect the tank to the 

orbiter through the shuttle’s two forward 

attachment struts. Four rod heaters were 

placed below each forward bipod, replacing the 
FEBRUARY 2010 SHUTTLE REFERENCE DATA 85

large insulated foam Protuberance Airload, or 

PAL, ramps. 

Liquid Hydrogen Tank & Liquid Oxygen 

Intertank Flange Closeouts 

The liquid hydrogen tank flange located at the 

bottom of the intertank and the liquid oxygen 

tank flange located at the top of the intertank 

provide joining mechanisms with the intertank. 

After each of these three component tanks, 

liquid oxygen, intertank and liquid hydrogen, 

are joined mechanically, the flanges at both 

ends are insulated with foam. An enhanced 

closeout, or finishing, procedure was added to 

improve foam application to the stringer, or 

intertank ribbing, and to the upper and lower 

area of both the liquid hydrogen and liquid 

oxygen intertank flanges. 

Liquid Oxygen Feedline Bellows 

The liquid oxygen feedline bellows were 

reshaped to include a “drip lip” that allows 

condensate moisture to run off and prevent 

freezing. A strip heater was added to the 

forward bellow to further reduce the potential 

of high density ice or frost formation. Joints on 

the liquid oxygen feedline assembly allow the 

feedline to move during installation and during 

liquid hydrogen tank fill. Because it must flex, 

it cannot be insulated with foam like the 

remainder of the tank. 

Other tank improvements include: 

Liquid Oxygen & Liquid Hydrogen 

Protuberance Airload (PAL) Ramps 

External tank ET-119, which flew on the second 

Return to Flight mission, STS-121, in July 2006, 

was the first tank to fly without PAL ramps 

along portions of the liquid oxygen and 

liquid hydrogen tanks. These PAL ramps were 

extensively studied and determined to not be 

necessary for their original purpose, which was 

to protect cable trays from aeroelastic instability 

during ascent. Extensive tests were conducted 

to verify the shuttle could fly safely without 

these particular PAL ramps. Extensions were 

added to the ice frost ramps for the pressline 

and cable tray brackets, where these PAL ramps 

were removed to make the geometry of the 

ramps consistent with other locations on 

the tank and thereby provide consistent 

aerodynamic flow. Nine extensions were 

added, six on the liquid hydrogen tank and 

three on the liquid oxygen tank. 

Engine Cutoff (ECO) Sensor Modification 

Beginning with STS-122, ET-125, which 

launched on Feb. 7, 2008, the ECO sensor 

system feed through connector on the liquid 

hydrogen tank was modified by soldering the 

connector’s pins and sockets to address false 

readings in the system. All subsequent tanks 

after ET-125 have the same modification. 

Liquid Hydrogen Tank Ice Frost Ramps 

ET-128, which flew on the STS-124 shuttle 

mission, May 31, 2008, was the first tank to fly 

with redesigned liquid hydrogen tank ice frost 

ramps. Design changes were incorporated at 

all 17 ice frost ramp locations on the liquid 

hydrogen tank, stations 1151 through 2057, to 

reduce foam loss. Although the redesigned 

ramps appear identical to the previous design, 

several changes were made. PDL* and NCFI 

foam have been replaced with BX* manual 

spray foam in the ramp’s base cutout to reduce 

debonding and cracking; Pressline and cable 

tray bracket feet corners have been rounded to 

reduce stresses; shear pin holes have been 

sealed to reduce leak paths; isolators were 

primed to promote adhesion; isolator corners 
86 SHUTTLE REFERENCE DATA FEBRUARY 2010

were rounded to help reduce thermal 

protection system foam stresses; BX manual 

spray was applied in bracket pockets to reduce 

geometric voids. 

*BX is a type of foam used on the tank’s 

“loseout,” or final finished areas; it is applied 

manually or hand-sprayed. PDL is an acronym 

for Product Development Laboratory, the first 

supplier of the foam during the early days of 

the external tank’s development. PDL is 

applied by pouring foam ingredients into a 

mold. NCFI foam is used on the aft dome, or 

bottom, of the liquid hydrogen tank. 

Liquid Oxygen Feedline Brackets 

ET-128 also was the first tank to fly with 

redesigned liquid oxygen feedline brackets. 

Titanium brackets, much less thermally 

conductive than aluminum, replaced aluminum 

brackets at four locations, XT 1129, XT 1377, 

Xt 1624 and Xt 1871. This change minimizes ice 

formation in under-insulated areas, and 

reduces the amount of foam required to cover 

the brackets and the propensity for ice 

development. Zero-gap/slip plane Teflon 

material was added to the upper outboard 

monoball attachment to eliminate ice adhesion. 

Additional foam has been added to the liquid 

oxygen feedline to further minimize ice 

formation along the length of the feedline. 
FEBRUARY 2010 LAUNCH & LANDING 87

LAUNCH AND LANDING 

LAUNCH 

As with all previous space shuttle launches, 

Endeavour has several options to abort its 

ascent if needed after engine failures or other 

systems problems. Shuttle launch abort 

philosophy is intended to facilitate safe 

recovery of the flight crew and intact recovery 

of the orbiter and its payload. 

Abort modes include: 

ABORT-TO-ORBIT (ATO) 

This mode is used if there is a partial loss of 

main engine thrust late enough to permit 

reaching a minimal 105 by 85 nautical mile orbit 

with the orbital maneuvering system engines. 

The engines boost the shuttle to a safe orbital 

altitude when it is impossible to reach the 

planned orbital altitude. 

TRANSATLANTIC ABORT LANDING 

(TAL) 

The loss of one or more main engines midway 

through powered flight would force a landing 

at either Zaragoza, Spain; Moron, Spain; or 

Istres, France. For launch to proceed, weather 

conditions must be acceptable at one of these 

TAL sites. 

RETURN-TO-LAUNCH-SITE (RTLS) 

If one or more engines shut down early and 

there is not enough energy to reach Zaragoza, 

the shuttle would pitch around toward 

Kennedy until within gliding distance of 

the Shuttle Landing Facility. For launch to 

proceed, weather conditions must be forecast to 

be acceptable for a possible RTLS landing at 

KSC about 20 minutes after liftoff. 

ABORT ONCE AROUND (AOA) 

An AOA is selected if the vehicle cannot 

achieve a viable orbit or will not have enough 

propellant to perform a deorbit burn, but has 

enough energy to circle the Earth once and land 

about 90 minutes after liftoff. 

LANDING 

The primary landing site for Endeavour on 

STS‐130 is the Kennedy Space Center’s Shuttle 

Landing Facility. Alternate landing sites that 

could be used if needed because of weather 

conditions or systems failures are at Edwards 

Air Force Base, Calif., and White Sands Space 

Harbor, N.M. 
88 LAUNCH & LANDING FEBRUARY 2010

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FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 89

ACRONYMS AND ABBREVIATIONS 

A/G Alignment Guides 

A/L Airlock 

AAA Avionics Air Assembly 

ABC Audio Bus Controller 

ACBM Active Common Berthing Mechanism 

ACDU Airlock Control and Display Unit 

ACO Assembly Checkout Officer 

ACS Atmosphere Control and Supply 

ACU Arm Control Unit 

ADS Audio Distribution System 

AE Approach Ellipsoid 

AEP Airlock Electronics Package 

AI Approach Initiation 

AIS Automatic Identification System 

AJIS Alpha Joint Interface Structure 

AM Atmosphere Monitoring 

AMOS Air Force Maui Optical and Supercomputing Site 

AOA Abort Once Around 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Attachment 

APCU Assembly Power Converter Unit 

APE Antenna Pointing Electronics 

Audio Pointing Equipment 

APFR Articulating Portable Foot Restraint 

APM Antenna Pointing Mechanism 

APS Automated Payload Switch 

APV Automated Procedure Viewer 

AR Atmosphere Revitalization 

ARCU American-to-Russian Converter Unit 

ARED Advanced Resistive Exercise Device 

ARS Atmosphere Revitalization System 

ASW Application Software 

ATA Ammonia Tank Assembly 

ATCS Active Thermal Control System 

ATO Abort To Orbit 

ATU Audio Terminal Unit 
90 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

BAD Broadcast Ancillary Data 

BC Bus Controller 

BCDU Battery Charge/Discharge Unit 

Berthing Mechanism Control and Display Unit 

BEP Berthing Mechanism Electronics Package 

BGA Beta Gimbal Assembly 

BIC Bus Interface Controller 

BIT Built-In Test 

BM Berthing Mechanism 

BOS BIC Operations Software 

BSS Basic Software 

BSTS Basic Standard Support Software 

C&C Command and Control 

C&DH Command and Data Handling 

C&T Communication and Tracking 

C&W Caution and Warning 

C/L Crew Lock 

C/O Checkout 

CAM Collision Avoidance Maneuver 

CAPE Canister for All Payload Ejections 

CAS Common Attach System 

CB Control Bus 

CBCS Centerline Berthing Camera System 

CBM Common Berthing Mechanism 

CCA Circuit Card Assembly 

CCAA Common Cabin Air Assembly 

CCHA Crew Communication Headset Assembly 

CCP Camera Control Panel 

CCT Communication Configuration Table 

CCTV Closed-Circuit Television 

CDR Space Shuttle Commander 

CDRA Carbon Dioxide Removal Assembly 

CETA Crew Equipment Translation Aid 

CHeCS Crew Health Care System 

CHX Cabin Heat Exchanger 

CISC Complicated Instruction Set Computer 

CLA Camera Light Assembly 

CLPA Camera Light Pan Tilt Assembly 

CMG Control Moment Gyro 

COTS Commercial Off the Shelf 

CPA Control Panel Assembly 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 91

CPB Camera Power Box 

CR 

CRT 

CSA 

CSA-CP 

CTC 

CVIU 

Change Request 

Cathode-Ray Tube 

Canadian Space Agency 

Compound Specific Analyzer 

Cargo Transport Container 

Common Video Interface Unit 

CVT Current Value Table 

CZ Communication Zone 

DA 

DB 

Distillation Assembly 

Data Book 

DC 

DCSU 

DDCU 

Docking Compartment 

Direct Current Switching Unit 

DC-to-DC Converter Unit 

DEM Demodulator 

DFL Decommutation Format Load 

DIU Data Interface Unit 

DMS 

DMS-R 

DPG 

DPU 

DRTS 

DYF 

Data Management System 

Data Management System-Russian 

Differential Pressure Gauge 

Baseband Data Processing Unit 

Japanese Data Relay Satellite 

Display Frame 

E-ORU EVA Essential ORU 

E/L 

EATCS 

EBCS 

ECC 

Equipment Lock 

External Active Thermal Control System 

External Berthing Camera System 

Error Correction Code 

ECLSS 

ECS 

ECU 

Environmental Control and Life Support System 

Environmental Control System 

Electronic Control Unit 

EDSU 

EDU 

External Data Storage Unit 

EEU Driver Unit 

EE End Effector 

EETCS 

EEU 

EF 

EFBM 

EFHX 

EFU 

Early External Thermal Control System 

Experiment Exchange Unit 

Exposed Facility 

Exposed Facility Berthing Mechanism 

Exposed Facility Heat Exchanger 

Exposed Facility Unit 
92 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

EGIL Electrical, General Instrumentation, and Lighting 

EIU Ethernet Interface Unit 

ELC ExPRESS Logistics Carrier 

ELM-ES Japanese Experiment Logistics Module – Exposed Section 

ELM-PS Japanese Experiment Logistics Module – Pressurized Section 

ELPS Emergency Lighting Power Supply 

EMGF Electric Mechanical Grapple Fixture 

EMI Electro-Magnetic Imaging 

EMU Extravehicular Mobility Unit 

EP Exposed Pallet 

EPS Electrical Power System 

ES Exposed Section 

ESA European Space Agency 

ESC JEF System Controller 

ESW Extended Support Software 

ET External Tank 

ETCS External Thermal Control System 

ETI Elapsed Time Indicator 

ETRS EVA Temporary Rail Stop 

ETVCG External Television Camera Group 

EV Extravehicular 

EVA Extravehicular Activity 

EXP-D Experiment-D 

EXT External 

FA Fluid Accumulator 

FAS Flight Application Software 

FCT Flight Control Team 

FD Flight Day 

FDDI Fiber Distributed Data Interface 

FDIR Fault Detection, Isolation, and Recovery 

FDS Fire Detection System 

FE Flight Engineer 

FET-SW Field Effect Transistor Switch 

FGB Functional Cargo Block 

FOR Frame of Reference 

FPMU Floating Potential Measurement Unit 

FPP Fluid Pump Package 

FR Flight Rule 

FRD Flight Requirements Document 

FRGF Flight Releasable Grapple Fixture 

FRM Functional Redundancy Mode 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 93

FSE Flight Support Equipment 

FSEGF Flight Support Equipment Grapple Fixture 

FSW Flight Software 

GAS Get-Away Special 

GATOR Grappling Adaptor to On-orbit Railing 

GCA Ground Control Assist 

GLA General Lighting Assemblies 

General Luminaire Assembly 

GLONASS Global Navigational Satellite System 

GNC Guidance, Navigation, and Control 

GPC General Purpose Computer 

GPS Global Positioning System 

GPSR Global Positioning System Receiver 

GUI Graphical User Interface 

H&S Health and Status 

HCE Heater Control Equipment 

HCTL Heater Controller 

HEPA High Efficiency Particulate Acquisition 

HPA High Power Amplifier 

HPGT High Pressure Gas Tank 

HPP Hard Point Plates 

HRDR High Rate Data Recorder 

HREL Hold/Release Electronics 

HRFM High Rate Frame Multiplexer 

HRM Hold Release Mechanism 

HRMS High Rate Multiplexer and Switcher 

HTV H-II Transfer Vehicle 

HTVCC HTV Control Center 

HTV Prox HTV Proximity 

HX Heat Exchanger 

I/F Interface 

IAA Intravehicular Antenna Assembly 

IAC Internal Audio Controller 

IBM International Business Machines 

ICB Inner Capture Box 

ICC Integrated Cargo Carrier 

ICS Interorbit Communication System 

ICS-EF Interorbit Communication System – Exposed Facility 

IDRD Increment Definition and Requirements Document 
94 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

IELK Individual Equipment Liner Kit 

IFHX Interface Heat Exchanger 

IMCS Integrated Mission Control System 

IMCU Image Compressor Unit 

IMV Intermodule Ventilation 

INCO Instrumentation and Communication Officer 

IP International Partner 

IP-PCDU ICS-PM Power Control and Distribution Unit 

IP-PDB Payload Power Distribution Box 

ISP International Standard Payload 

ISPR International Standard Payload Rack 

ISS International Space Station 

ISSSH International Space Station Systems Handbook 

ITCS Internal Thermal Control System 

ITS Integrated Truss Segment 

IVA Intravehicular Activity 

IVSU Internal Video Switch Unit 

JAXA Japan Aerospace Exploration Agency 

JCP JEM Control Processor 

JEF JEM Exposed Facility 

JEM Japanese Experiment Module 

JEM-EF Japanese Experiment Module Exposed Facility 

JEM-PM Japanese Experiment Module – Pressurized Module 

JEMAL JEM Airlock 

JEMRMS Japanese Experiment Module Remote Manipulator System 

JEUS Joint Expedited Undocking and Separation 

JFCT Japanese Flight Control Team 

JLE Japanese Experiment Logistics Module – Exposed Section 

JLP Japanese Experiment Logistics Module – Pressurized Section 

JLP-EDU JLP-EFU Driver Unit 

JLP-EFU JLP Exposed Facility Unit 

JPM Japanese Pressurized Module 

JPM WS JEM Pressurized Module Workstation 

JSC Johnson Space Center 

JTVE JEM Television Equipment 

Kbps Kilobit per second 

KOS Keep Out Sphere 

LB Local Bus 

LCA LAB Cradle Assembly 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 95

LCD Liquid Crystal Display 

LED Light Emitting Diode 

LEE Latching End Effector 

LMC Lightweight MPESS Carrier 

LSW Light Switch 

LTA Launch-to-Activation 

LTAB Launch-to-Activation Box 

LTL Low Temperature Loop 

MA Main Arm 

MAUI Main Analysis of Upper-Atmospheric Injections 

Mb Megabit 

Mbps Megabit per second 

MBS Mobile Base System 

MBSU Main Bus Switching Unit 

MCA Major Constituent Analyzer 

MCC Mission Control Center 

MCC-H Mission Control Center – Houston 

MCC-M Mission Control Center – Moscow 

MCDS Multifunction Cathode-Ray Tube Display System 

MCS Mission Control System 

MDA MacDonald, Dettwiler and Associates Ltd. 

MDM Multiplexer/Demultiplexer 

MDP Management Data Processor 

MELFI Minus Eighty-Degree Laboratory Freezer for ISS 

MGB Middle Grapple Box 

MIP Mission Integration Plan 

MISSE Materials International Space Station Experiment 

MKAM Minimum Keep Alive Monitor 

MLE Middeck Locker Equivalent 

MLI Multi-layer Insulation 

MLM Multipurpose Laboratory Module 

MMOD Micrometeoroid/Orbital Debris 

MOD Modulator 

MON Television Monitor 

MPC Main Processing Controller 

MPESS Multipurpose Experiment Support Structure 

MPEV Manual Pressure Equalization Valve 

MPL Manipulator Retention Latch 

MPLM MultiPurpose Logistics Module 

MPM Manipulator Positioning Mechanism 

MPV Manual Procedure Viewer 
96 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

MRM

MSD 

MSFC 

MSP 

 Multipurpose Research Module 

Mass Storage Device 

Marshall Space Flight Center 

Maintenance Switch Panel 

MSS 

MT

Mobile Servicing System 

 Mobile Tracker 

MTL 

MUX

 Mobile Transporter 

Moderate Temperature Loop 

 Data Multiplexer 

n.mi. nautical mile 

NASA 

NCS 

National Aeronautics and Space Administration 

Node Control Software 

NET No Earlier Than 

NLT No Less Than 

NPRV 

NSV

Negative Pressure Relief Valve 

 Network Service 

NTA 

NTSC 

Nitrogen Tank Assembly 

National Television Standard Committee 

OBSS 

OCA 

OCAD 

OCAS 

ODF 

ODS 

OGS 

OI 

Orbiter Boom Sensor System 

Orbital Communications Adapter 

Operational Control Agreement Document 

Operator Commanded Automatic Sequence 

Operations Data File 

Orbiter Docking System 

Oxygen Generation System 

Orbiter Interface 

OIU Orbiter Interface Unit 

OMS 

OODT 

ORCA 

ORU 

OS 

OSA 

Orbital Maneuvering System 

Onboard Operation Data Table 

Oxygen Recharge Compressor Assembly 

Orbital Replacement Unit 

Operating System 

Orbiter-based Station Avionics 

OSE 

OTCM 

OTP 

Orbital Support Equipment 

ORU and Tool Changeout Mechanism 

ORU and Tool Platform 

P/L

PAL 

PAM 

 Payload 

Planning and Authorization Letter 

Payload Attach Mechanism 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 97

PAO Public Affairs Office 

PAS Payload Adapter System 

PBA Portable Breathing Apparatus 

PCA Pressure Control Assembly 

PCBM Passive Common Berthing Mechanism 

PCN Page Change Notice 

PCS Portable Computer System 

PCU Plasma Contactor Unit 

Power Control Unit 

PDA Payload Disconnect Assembly 

PDB Power Distribution Box 

PDGF Power and Data Grapple Fixture 

PDH Payload Data Handling unit 

PDRS Payload Deployment Retrieval System 

PDU Power Distribution Unit 

PEC Passive Experiment Container 

PEHG Payload Ethernet Hub Gateway 

PFE Portable Fire Extinguisher 

PFRAM Passive Flight Releasable Attachment Mechanism 

PGSC Payload General Support Computer 

PIB Power Interface Box 

PIU Payload Interface Unit 

PLB Payload Bay 

PLBD Payload Bay Door 

PLC Pressurized Logistics Carrier 

PLT Payload Laptop Terminal 

Space Shuttle Pilot 

PM Pressurized Module 

 Pump Module 

PMA Pressurized Mating Adapter 

PMCU Power Management Control Unit 

PMU Pressurized Mating Adapter 

POA Payload ORU Accommodation 

POR Point of Resolution 

PPRV Positive Pressure Relief Valve 

PRCS Primary Reaction Control System 

PREX Procedure Executor 

PRLA Payload Retention Latch Assembly 

PROX Proximity Communications Center 

psia Pounds per Square Inch Absolute 

PSP Payload Signal Processor 
98 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

PSRR 

PTCS 

PTR 

Pressurized Section Resupply Rack 

Passive Thermal Control System 

Port Thermal Radiator 

PTU 

PVCU 

Pan/Tilt Unit 

Photovoltaic Controller Unit 

PVM Photovoltaic Module 

PVR Photovoltaic Radiator 

PVTCS Photovoltaic Thermal Control System 

QD Quick Disconnect 

R&MA 

R-ORU 

RACU 

Restraint and Mobility Aid 

Robotics Compatible Orbital Replacement Unit 

Russian-to-American Converter Unit 

RAM 

RBVM 

Read Access Memory 

Radiator Beam Valve Module 

RCC 

RCT 

RF 

RGA 

RHC 

Range Control Center 

Rack Configuration Table 

Radio Frequency 

Rate Gyro Assemblies 

Rotational Hand Controller 

RIGEX 

RIP 

Rigidizable Inflatable Get-Away Special Experiment 

Remote Interface Panel 

RLF 

RLT 

RMS 

ROEU 

ROM 

ROS 

RPC 

Robotic Language File 

Robotic Laptop Terminal 

Remote Manipulator System 

Remotely Operated Electrical Umbilical 

Read Only Memory 

Russian Orbital Segment 

Remote Power Controller 

RPCM Remote Power Controller Module 

RPDA 

RPM 

Remote Power Distribution Assembly 

Roll Pitch Maneuver 

RS

RSP 

RSR 

RT

 Russian Segment 

Return Stowage Platform 

Resupply Stowage Rack 

 Remote Terminal 

RTAS 

RTLS 

Rocketdyne Truss Attachment System 

Return To Launch Site 

RVFS 

RWS

Rendezvous Flight Software 

 Robotics Workstation 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 99

SAFER Simplified Aid for EVA Rescue 

SAM SFA Airlock Attachment Mechanism 

SAPA Small Adapter Plate Assembly 

SARJ Solar Alpha Rotary Joint 

SASA S-Band Antenna Sub-Assembly 

SCU Sync and Control Unit 

SD Smoke Detector 

SDS Sample Distribution System 

SEDA Space Environment Data Acquisition equipment 

SEDA-AP Space Environment Data Acquisition equipment - Attached Payload 

SELS SpaceOps Electronic Library System 

SEU Single Event Upset 

SFA Small Fine Arm 

SFAE SFA Electronics 

SI Smoke Indicator 

SLM Structural Latch Mechanism 

SLP-D Spacelab Pallet – D 

SLP-D1 Spacelab Pallet – Deployable 

SLP-D2 Spacelab Pallet – D2 

SLT Station Laptop Terminal 

System Laptop Terminal 

SM Service Module 

SMDP Service Module Debris Panel 

SOC System Operation Control 

SODF Space Operations Data File 

SPA Small Payload Attachment 

SPB Survival Power Distribution Box 

SPDA Secondary Power Distribution Assembly 

SPDM Special Purpose Dexterous Manipulator 

SPEC Specialist 

SRAM Static RAM 

SRB Solid Rocket Booster 

SRMS Shuttle Remote Manipulator System 

SSAS Segment-to-Segment Attach System 

SSC Station Support Computer 

SSCB Space Station Control Board 

SSE Small Fine Arm Storage Equipment 

SSIPC Space Station Integration and Promotion Center 

SSME Space Shuttle Main Engine 

SSOR Space-to-Space Orbiter Radio 

SSP Standard Switch Panel 
100 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

SSPTS Station-to-Shuttle Power Transfer System 

SSRMS Space Station Remote Manipulator System 

STC Small Fire Arm Transportation Container 

STR Starboard Thermal Radiator 

STS Space Transfer System 

STVC SFA Television Camera 

SVS Space Vision System 

TA Thruster Assist 

TAC TCS Assembly Controller 

TAC-M TCS Assembly Controller – M 

TAL Transatlantic Abort Landing 

TCA Thermal Control System Assembly 

TCB Total Capture Box 

TCCS Trace Contaminant Control System 

TCCV Temperature Control and Check Valve 

TCS Thermal Control System 

TCV Temperature Control Valve 

TDK Transportation Device Kit 

TDRS Tracking and Data Relay Satellite 

THA Tool Holder Assembly 

THC Temperature and Humidity Control 

Translational Hand Controller 

THCU Temperature and Humidity Control Unit 

TIU Thermal Interface Unit 

TKSC Tsukuba Space Center (Japan) 

TLM Telemetry 

TMA Russian vehicle designation 

TMR Triple Modular Redundancy 

TPL Transfer Priority List 

TRRJ Thermal Radiator Rotary Joint 

TUS Trailing Umbilical System 

TVC Television Camera 

UCCAS Unpressurized Cargo Carrier Attach System 

UCM Umbilical Connect Mechanism 

UCM-E UCM – Exposed Section Half 

UCM-P UCM – Payload Half 

UHF Ultrahigh Frequency 

UIL User Interface Language 

ULC Unpressurized Logistics Carrier 

UMA Umbilical Mating Adapter 
FEBRUARY 2010 ACRONYMS/ABBREVIATIONS 101

UOP 

UPC 

USA 

US LAB 

USOS 

UTA 

Utility Outlet Panel 

Up Converter 

United Space Alliance 

United States Laboratory 

United States On-Orbit Segment 

Utility Transfer Assembly 

VAJ 

VBSP 

VCU 

Vacuum Access Jumper 

Video Baseband Signal Processor 

Video Control Unit 

VDS 

VLU 

VRA 

VRCS 

VRCV 

Video Distribution System 

Video Light Unit 

Vent Relief Assembly 

Vernier Reaction Control System 

Vent Relief Control Valve 

VRIV Vent Relief Isolation Valve 

VSU Video Switcher Unit 

VSW Video Switcher 

WAICO 

WCL 

WETA 

WIF 

Waiving and Coiling 

Water Cooling Loop 

Wireless Video System External Transceiver Assembly 

Work Interface 

WRM 

WRS 

WS

Water Recovery and Management 

Water Recovery System 

 Water Separator 

Work Site 

Work Station 

WVA 

WX

Water Vent Assembly 

 Weather 

ZSR Zero-g Stowage Rack 
102 ACRONYMS/ABBREVIATIONS FEBRUARY 2010

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FEBRUARY 2010 MEDIA ASSISTANCE 103

MEDIA ASSISTANCE 

NASA TELEVISION TRANSMISSION 

NASA Television is carried on an MPEG‐2 

digital signal accessed via satellite AMC‐6, at 

72 degrees west longitude, transponder 17C, 

4040 MHz, vertical polarization. For those in 

Alaska or Hawaii, NASA Television will be 

seen on AMC‐7, at 137 degrees west longitude, 

transponder 18C, at 4060 MHz, horizontal 

polarization. In both instances, a Digital Video 

Broadcast, or DVB‐compliant Integrated 

Receiver Decoder, or IRD, with modulation of 

QPSK/DBV, data rate of 36.86 and FEC 3/4 will 

be needed for reception. The NASA Television 

schedule and links to streaming video are 

available at: 

http://www.nasa.gov/ntv

NASA TV’s digital conversion will require 

members of the broadcast media to upgrade 

with an “addressable” Integrated Receiver 

De‐coder, or IRD, to participate in live news 

events and interviews, media briefings and 

receive NASA’s Video File news feeds on a 

dedicated Media Services channel. NASA 

mission coverage will air on a digital NASA 

Public Services “Free to Air” channel, for which 

only a basic IRD will be needed. 

Television Schedule 

A schedule of key in‐orbit events and media 

briefings during the mission will be detailed in 

a NASA TV schedule posted at the link above. 

The schedule will be updated as necessary and 

will also be available at: 

http://www.nasa.gov/multimedia/nasatv/

mission_schedule.html

Status Reports 

Status reports on launch countdown and 

mission progress, in‐orbit activities and landing 

operations will be posted at: 

http://www.nasa.gov/shuttle

This site also contains information on the crew 

and will be updated regularly with photos and 

video clips throughout the flight. 

More Internet Information 

Information on the ISS is available at: 

http://www.nasa.gov/station

Information on safety enhancements made 

since the Columbia accident is available at: 

http://www.nasa.gov/returntoflight/

system/index.html

Information on other current NASA activities is 

available at: 

http://www.nasa.gov

Resources for educators can be found at the 

following address: 

http://education.nasa.gov
104 MEDIA ASSISTANCE FEBRUARY 2010

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FEBRUARY 2010 PUBLIC AFFAIRS CONTACTS 105

PUBLIC AFFAIRS CONTACTS 

HEADQUARTERS 

WASHINGTON, DC 

Space Operations Mission Directorate 

Michael Braukus 

International Partners 

202-358-1979 

michael.j.braukus@nasa.gov

Katherine Trinidad 

Shuttle, Space Station Policy 

202-358-1100 

katherine.trinidad@nasa.gov

John Yembrick 

Shuttle, Space Station Policy 

202-358-1100 

john.yembrick-1@nasa.gov

Mike Curie 

Shuttle, Space Station Policy 

202-358-1100 

michael.curie@nasa.gov

Grey Hautaluoma 

Research in Space 

202-358-0668 

grey.hautaluoma-1@nasa.gov

Ashley Edwards 

Research in Space 

202-358-1756 

ashley.edwards-1@nasa.gov

JOHNSON SPACE CENTER 

HOUSTON, TEXAS 

James Hartsfield 

News Chief 

281-483-5111 

james.a.hartsfield@nasa.gov

Kyle Herring 

Public Affairs Specialist 

Space Shuttle Program Office 

281-483-5111 

kyle.j.herring@nasa.gov

Rob Navias 

Program and Mission Operations Lead 

281-483-5111 

rob.navias-1@nasa.gov

Kelly Humphries 

Public Affairs Specialist 

International Space Station and Mission 

Operations Directorate 

281-483-5111 

kelly.o.humphries@nasa.gov

Nicole Cloutier-Lemasters 

Public Affairs Specialist 

Astronauts 

281-483-5111 

nicole.cloutier-1@nasa.gov
106 PUBLIC AFFAIRS CONTACTS FEBRUARY 2010

KENNEDY SPACE CENTER 

CAPE CANAVERAL, FLORIDA 

Allard Beutel 

News Chief 

321-867-2468 

allard.beutel@nasa.gov

Candrea Thomas 

Public Affairs Specialist 

Space Shuttle 

321-867-2468 

candrea.k.thomas@nasa.gov

Tracy Young 

Public Affairs Specialist 

International Space Station 

321-867-2468 

tracy.g.young@nasa.gov

MARSHALL SPACE FLIGHT CENTER 

HUNTSVILLE, ALABAMA 

Dom Amatore 

Public Affairs Manager 

256-544-0034 

dominic.a.amatore@nasa.gov

June Malone 

News Chief/Media Manager 

256-544-0034 

june.e.malone@nasa.gov

Steve Roy 

Public Affairs Specialist 

Space Shuttle Propulsion 

256-544-0034 

steven.e.roy@nasa.gov

STENNIS SPACE CENTER 

BAY ST. LOUIS, MISSISSIPPI 

Chris McGee 

News Chief 

228-688-3249 

christopher.mcgee@nasa.gov

Paul Foerman 

Public Affairs Officer 

228-688-1880 

paul.foerman-1@nasa.gov

AMES RESEARCH CENTER 

MOFFETT FIELD, CALIFORNIA 

Mike Mewhinney 

News Chief 

650-604-3937 

michael.mewhinney@nasa.gov

Jonas Dino 

Public Affairs Specialist 

650-604-5612 

jonas.dino@nasa.gov

Rachel Prucey 

Public Affairs Specialist 

650-604-0643 

Rachel.L.Purcey@nasa.gov

Ruth Marlaire 

Public Affairs Officer 

650-604-4709 

ruth.marlaire@nasa.gov
FEBRUARY 2010 PUBLIC AFFAIRS CONTACTS 107

DRYDEN FLIGHT RESEARCH CENTER 

EDWARDS, CALIFORNIA 

Kevin Rohrer 

Director, Public Affairs 

661-276-3595 

kevin.j.rohrer@nasa.gov

Alan Brown 

News Chief 

661-276-2665 

alan.brown@nasa.gov

Leslie Williams 

Public Affairs Specialist 

661-276-3893 

leslie.a.williams@nasa.gov

GLENN RESEARCH CENTER 

CLEVELAND, OHIO 

Lori Rachul 

News Chief 

216-433-8806 

lori.j.rachul@nasa.gov

Sally Harrington 

Public Affairs Specialist 

216-433-2037 

sally.v.harrinton@nasa.gov

Katherine Martin 

Public Affairs Specialist 

216-433-2406 

katherine.martin@nasa.gov

LANGLEY RESEARCH CENTER 

HAMPTON, VIRGINIA 

Marny Skora 

Head, Office of Communications 

757-864-6121 

marny.skora@nasa.gov

Mike Finneran 

News Chief 

757-864-6110 

Michael.p.finneran@nasa.gov

Keith Henry 

Public Affairs Officer 

757-864-6120 

h.k.henry@nasa.gov

Chris Rink 

Public Affairs Officer 

757-864-6786 

christopher.p.rink@nasa.gov

Kathy Barnstorff 

Public Affairs Officer 

757-864-9886 

katherine.a.barnstorff@nasa.gov

Amy Johnson 

Public Affairs Officer 

757-864-7022 

amy.johnson@nasa.gov
108 PUBLIC AFFAIRS CONTACTS FEBRUARY 2010

UNITED SPACE ALLIANCE 

Jessica Pieczonka 

Houston Operations 

281-212-6252 

832-205-0480 

jessica.b.pieczonka@usa-spaceops.com

Tracy Yates 

Florida Operations 

321-861-3956 

(c) 321-750-1739 

tracy.e.yates@usa-spaceops.com

BOEING 

Ed Memi 

Media Relations 

Boeing Space Exploration 

281-226-4029 

edmund.g.memi@boeing.com

Adam Morgan 

International Space Station 

281-226-4030 

adam.k.morgan@boeing.com

JAPAN AEROSPACE EXPLORATION 

AGENCY (JAXA) 

Kumiko Sagara 

JAXA Public Affairs Representative 

Houston 

281-792-7468 

sagara.kumiko@jaxa.jp

JAXA Public Affairs Office 

Tokyo, Japan 

011-81-50-3362-4374 

proffice@jaxa.jp

CANADIAN SPACE AGENCY (CSA) 

Jean-Pierre Arseneault 

Manager, Media Relations & Information 

Services 

514-824-0560 (cell) 

jean-pierre.arseneault@space.gc.ca

Media Relations Office 

Canadian Space Agency 

450-926-4370 

EUROPEAN SPACE AGENCY (ESA) 

Clare Mattok 

Communication Manager 

Paris, France 

011-33-1-5369-7412 

clare.mattok@esa.int