STS-117 Press Kit 
STS-117 Press Kit 
OCTOBER 2007 CONTENTS i

CONTENTS 

Section Page

STS-120 MISSION OVERVIEW................................................................................................ 1

TIMELINE OVERVIEW .............................................................................................................. 7

MISSION PROFILE................................................................................................................... 11

MISSION PRIORITIES............................................................................................................. 13

MISSION PERSONNEL ............................................................................................................. 15

STS-120 DISCOVERY CREW ................................................................................................... 17

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

HARMONY (NODE 2) ............................................................................................................................ 27

STATION RELOCATION ACTIVITIES........................................................................................ 33

PORT 6 SOLAR ARRAYS RELOCATION.................................................................................................. 33

PRESSURIZED MATING ADAPTER-2 (PMA-2) RELOCATION.................................................................. 42

RENDEZVOUS AND DOCKING .................................................................................................. 47

UNDOCKING, SEPARATION AND DEPARTURE ....................................................................................... 49

SPACEWALKS ......................................................................................................................... 51

EXPERIMENTS ......................................................................................................................... 57

DETAILED TEST OBJECTIVES ............................................................................................................... 57

SHORT-DURATION RESEARCH TO BE COMPLETED DURING STS-120 ................................................... 59

EUROPEAN EXPERIMENT PROGRAM ..................................................................................................... 62

EXTERNAL TANK ET-120 (ET-120) .......................................................................................... 67

SHUTTLE REFERENCE DATA .................................................................................................... 71

LAUNCH AND LANDING ........................................................................................................... 85

LAUNCH............................................................................................................................................... 85

ABORT-TO-ORBIT (ATO)...................................................................................................................... 85

TRANSATLANTIC ABORT LANDING (TAL) ............................................................................................. 8 5
ii CONTENTS OCTOBER 2007

Section Page

RETURN-TO-LAUNCH-SITE (RTLS)....................................................................................................... 85

ABORT ONCE AROUND (AOA)............................................................................................................... 85

LANDING ............................................................................................................................................. 85

ACRONYMS AND ABBREVIATIONS ......................................................................................... 87

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

PUBLIC AFFAIRS CONTACTS .................................................................................................. 105
OCTOBER 2007 MISSION OVERVIEW 1

STS-120 MISSION OVERVIEW: 

HARMONY: A GLOBAL GATEWAY PROVIDING A 

CONNECTION TO RESEARCH FOR THE WORLD 

This graphic depicts the International Space Station as it will appear after Discovery undocks,

following relocation of the Port 6 truss and delivery of the Harmony module.

Expansion of the International Space Station

will make great strides during STS‐120, also

known as Assembly Flight 10A.    The Node 2

connecting module, Harmony, will travel to the

station inside space shuttle Discovery’s payload  

bay for installation on the station.  This addition

sets the stage for the arrival of new research

laboratories from the European Space Agency

and the Japan Aerospace Exploration Agency in

upcoming shuttle missions.
2 MISSION OVERVIEW OCTOBER 2007

As part of assembling the giant laboratory,

STS‐120 astronauts will relocate the Port 6 (P6)

truss element and solar arrays to a permanent

position.  The element is presently on orbit and

attached to the truss segment Zenith 1 (Z1).  P6

will be removed from its current location, reat‐

tached to the Port 5 (P5) truss and then the solar

arrays will be redeployed and activated to

gather sunlight for power generation.

Discovery’s seven astronauts include Com‐

mander Pam Melroy, Pilot George Zamka, mis‐

sion specialists Scott Parazynski, Stephanie

Wilson, Doug Wheelock, and Paolo Nespoli,

representing the European Space Agency

(ESA).

Expedition 16 Flight Engineer Daniel Tani will

serve as a mission specialist aboard Discovery

before rotating positions with station resident

NASA astronaut Clayton Anderson after dock‐

ing.  Anderson arrived at the station aboard the

space shuttle Atlantis during STS‐117 in June.

Tani will join Expedition 16 Commander

Peggy Whitson and Flight Engineer Yuri

Malenchenko, who arrived at the station aboard

a Russian Soyuz spacecraft Oct. 12.

Following the successful simulated launch countdown and emergency egress practice, the STS‐120

crew gathers for the traditional photo near the top of the launch pad fixed service structure.  From

left are Mission Specialists Scott Parazynski and Stephanie Wilson, Pilot George Zamka,

Commander Pam Melroy, and Mission Specialists Daniel Tani, Doug Wheelock and  

Paolo Nespoli, who represents the European Space Agency.  The countdown was the  

culmination of the prelaunch terminal countdown demonstration test, or TCDT.
OCTOBER 2007 MISSION OVERVIEW 3

The space shuttle is poised for launch from pad 39A at Kennedy Space Center,  

backdropped by the Vehicle Assembly Building.

The space shuttle mission begins with the

targeted liftoff of Discovery from NASA’s

Kennedy Space Center at 11:38 a.m. EDT on

Oct. 23.    The next day includes the close

inspection of Discovery’s heat shield using the

shuttle’s robotic arm and Orbiter Boom Sensor

System to check for any ascent‐imposed

damage to the orbiter.

Discovery arrives at the International Space Sta‐

tion on the third day of the mission.    Melroy

will perform the rendezvous pitch maneuver

with Discovery about 600 feet below the station.  

This activity allows Anderson and

Malenchenko to take detailed photographs of

the underside of Discovery’s heat shield as it

approaches the station.    The images will be

added to the ascent imagery and flight day 2

data being analyzed by engineers on the

ground to verify the heat shield’s condition fol‐

lowing liftoff.

Melroy then will move Discovery in for dock‐

ing to the pressurized mating adapter at the

end of the station’s Destiny laboratory.

The graphic above shows the configuration of

Discovery’s payload bay for the STS‐120

mission.
4 MISSION OVERVIEW OCTOBER 2007

After hatches are opened, Tani and Anderson’s

specialized seat liners will be exchanged inside

the emergency‐return Soyuz spacecraft; signify‐

ing the crew members’ rotation between the

space station and shuttle.

Parazynski and Wheelock will enter the sta‐

tion’s Quest airlock for the overnight campout

procedure to prepare for the first spacewalk on

the next day.  This procedure will be followed

before each spacewalk.

Flight day 4 features the first of five spacewalks

during STS‐120.  Parazynski and Wheelock will

prepare Harmony for its removal from Discov‐

ery’s payload bay, retrieve an S‐band antenna

for return to Earth and disconnect umbilicals

between the P6 and Z1 truss elements.

During the spacewalk Wilson, Tani and

Anderson will operate the station’s robotic arm

for the antenna retrieval, to unberth Harmony

from Discovery’s cargo bay and install it on the

port side of Node 1, known as Unity.  Harmony

will be secured in place on Unity through

internal connections.    Anderson and Zamka

will close out the day with leak checks of the

interface between Unity and Harmony.

The station’s robotic arm places the Harmony

module onto the port side of the Unity

module.

The P6 truss is handed between the station’s

robotic arm and the shuttle’s robotic arm  

during its installation.

Flight day 5 features the first ingress of

Harmony in space.  The hatches between Unity

and Harmony will be opened by Nespoli and

Whitson.    Outfitting of the station’s newest

pressurized module will continue throughout

the mission.  Time also is allotted this day for a

focused inspection of Discovery’s heat shield, if

required.

The mission’s second spacewalk occurs on

flight day 6.    Parazynski and Tani will assist

with detaching the P6 truss from its current

location, complete external outfitting of

Harmony and replace a remote power

controller, or circuit breaker.  Wilson, Wheelock

and Anderson will operate the station’s robotic

arm for the P6 removal and to place it in an

overnight parked position.

The next day, Wheelock, Wilson and Anderson

will handoff the P6 element to the shuttle

robotic arm, operated by Zamka and Melroy.  

The station robotic arm will then be moved

down the station’s truss atop the mobile

transporter to a closer position for the P6

installation on the outboard, port side of the

truss.  The P6 will then be handed back to the

station robotic arm for installation during the
OCTOBER 2007 MISSION OVERVIEW 5

next day’s spacewalk.    Flight day 7 also

includes off duty time for the crew members in

the morning.

On flight day 8, Tani and Wilson will use the

station’s robotic arm to move P6 to a pre‐install

position.  During the mission’s third spacewalk,

Parazynski and Wheelock will assist with

attaching P6 to the P5 short spacer truss.   The

spacewalkers also will transfer the spare main

bus switching unit hardware from Discovery to

the space station.

The station’s robotic arm moves the P6

upwards to its new location at the  

outboard, port side of the truss.

The P6 solar array wings will be redeployed

following the spacewalk.    The ground control

team will begin the deployment to one of 31

mast bays.    Melroy, Zamka and Whitson will

continue the full deployment of the arrays.

Flight day 9 includes transferring equipment

between the shuttle and space station, as well

as preparations for the next spacewalk.

The fourth spacewalk will be conducted on

flight day 10 by Parazynski and Wheelock.  

They will perform Detailed Test Objective 848,

a demonstration of space shuttle thermal

protection system repair techniques. The

primary purpose of the test is to evaluate

STA‐54 material and a tile repair ablator

dispenser for potential use in a microgravity

and vacuum environment.

P6 is guided to its new location  

by the station robotic arm.

Flight day 11 includes the fifth and final space‐

walk of the joint mission.   The spacewalk will

be conducted by station residents, Whitson and

Malenchenko, to complete several external sta‐

tion configuration tasks.

The crew will complete final transfer work,

enjoy off duty time and then close the hatches

between Discovery and the space station the

evening of flight day 12.

Discovery will undock early on flight day 13

and complete a fly around of the newly remod‐

eled space station.  The crew also will conduct a

detailed inspection of Discovery’s heat shield

for any indications of micrometeoroid debris

impacts.

Flight day 14 includes standard preparations of

Discovery for entry and landing on the follow‐

ing day, flight day 15.
6 MISSION OVERVIEW OCTOBER 2007

The P6 solar arrays are shown deployed against the blackness of space on the end of the port truss.
OCTOBER 2007 TIMELINE OVERVIEW 7

TIMELINE OVERVIEW 

FLIGHT DAY 1 

• Launch

• Payload Bay Door Opening  

• Ku‐Band Antenna Deployment

• Shuttle Robotic Arm Activation and

Checkout

• Umbilical Well and Handheld External

Tank Video and Stills Downlink

FLIGHT DAY 2 

• Discovery Thermal Protection System

Survey with 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

by the Expedition 16 Crew

• Docking to the Stationʹs Pressurized Mating

Adapter‐2

• Hatch Opening and Welcoming

• Soyuz Seat Liner Swap and Expedition

Crew Exchange by Anderson and Tani

• Station‐to‐Shuttle Power Transfer System

(SSPTS) Activation

• OBSS Unberth by Canadarm2

• Extravehicular Activity (EVA) 1 Procedure

Review

• EVA 1 Campout by Parazynski and

Wheelock

FLIGHT DAY 4 

• EVA‐1 by Parazynski and Wheelock

(Node 2 Unberth Preparations, S‐Band

Antenna Retrieval, P6/Z1 Umbilical

Disconnection)

• Harmony (Node 2) Unberth and Installation

on Port Side of Unity (Node 1)

• Harmony/Unity Vestibule Leak Checks

FLIGHT DAY 5 

• Discovery Thermal Protection System

Focused Inspection with OBSS (if required)

• Harmony Node 2 Vestibule Outfitting and

Ingress

• OBSS Handoff to Shuttle Robotic Arm and

Berthing

• EVA‐2 Procedure Review

• EVA‐2 Campout by Parazynski and Tani
8 TIMELINE OVERVIEW OCTOBER 2007

FLIGHT DAY 6 

• EVA‐2 by Parazynski and Tani

(P6 Detachment from Z1 Truss, Harmony

(Node 2) Outfitting, Remote Power

Controller Unit Replacement, Harmony

Node 2 Power and Data Grapple Fixture

Installation)

• P6 Truss Grapple by Canadarm2 and

Demate from Z1 Truss

• Harmony (Node 2) Outfitting

FLIGHT DAY 7 

• P6 Truss Handoff from Canadarm2 to

Shuttle Robotic Arm

• Mobile Transporter Move to Far Port Side of

Truss

• Crew Off Duty Periods

• P6 Truss Handoff from Shuttle Robotic Arm

to Canadarm2

• Harmony Node 2 Avionics Rack Outfitting

• EVA Procedure Review

• EVA‐3 Campout by Parazynski and

Wheelock

FLIGHT DAY 8 

• EVA‐3 by Parazynski and Wheelock

(P6/P5 Installation, Main Bus Switching

Unit Transfer)

• P6 Truss Installation to P5 Truss

• P6 4B and 2B Solar Array Redeployment

FLIGHT DAY 9 

• Shuttle and Station Transfers

• Joint Crew News Conference

• EVA Procedure Review

• EVA‐4 Campout by Parazynski and

Wheelock

FLIGHT DAY 10 

• Shuttle and Station Transfers

• EVA‐4 by Parazynski and Wheelock

(Tile Repair Detailed Test Objective

Demonstration)

• EVA Procedure Review

• EVA‐5 Campout by Whitson and

Malenchenko

FLIGHT DAY 11 

• Shuttle and Station Transfers

• EVA‐5 by Whitson and Malenchenko

(SSPTS Cable Stow, Destiny

Lab/Pressurized Mating Adapter‐2 Stow,

Removal of Harmony Active Common

Berthing Mechanism Cover, Reconfigure

S0 Truss/Unity Node 1 and Zarya

Module/Pressurized Mating Adapter‐1

Power and Jumper Cables)

FLIGHT DAY 12 

• Crew Off Duty Periods

• Farewells and Hatch Closing
OCTOBER 2007 TIMELINE OVERVIEW 9

FLIGHT DAY 13 

• Undocking from ISS Pressurized Mating

Adapter‐2 and Flyaround

• Final Separation from the International

Space Station

• OBSS Unberth and Late Inspection of

Discovery’s Thermal Protection System

• OBSS Final Berthing

FLIGHT DAY 14 

• Cabin Stow

• Flight Control System Checkout

• Reaction Control System Hot‐Fire Test

• Crew Deorbit Briefing

• Launch and Entry Suit Checkout

• Recumbent Seat Set Up for Anderson

• Ku‐Band Antenna Stow

FLIGHT DAY 15 

• Deorbit Preparations

• Payload Bay Door Closing

• Deorbit Burn

• Kennedy Space Center Landing
10 MISSION PROFILE OCTOBER 2007

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OCTOBER 2007 MISSION PROFILE 11

MISSION PROFILE 

CREW 

Commander: Pam Melroy

Pilot: George Zamka

Mission Specialist 1: Scott Parazynski

Mission Specialist 2: Stephanie Wilson

Mission Specialist 3: Doug Wheelock

Mission Specialist 4: Paolo Nespoli

Mission Specialist 5: Daniel Tani (up)

Mission Specialist 5: Clayton Anderson

(down)

LAUNCH 

Orbiter: Discovery (OV‐103)

Launch Site: Kennedy Space Center

Launch Pad 39A

Launch Date: No earlier than

Oct. 23, 2007

Launch Time: 11:38 a.m. EDT (Preferred

In‐Plane launch time for

10/23)

Launch Window: 5 Minutes

Altitude: 122 Nautical Miles (140

Miles) Orbital Insertion;

185 NM (213 Miles)

Rendezvous

Inclination: 51.6 Degrees

Duration: 13 Days, 18 Hours,

09 Minutes

VEHICLE DATA 

Shuttle Liftoff Weight: 4,524,141

pounds

Orbiter/Payload Liftoff Weight: 286,211

pounds

Orbiter/Payload Landing Weight: 201,895

pounds

Software Version: OI‐32

Space Shuttle Main Engines: 

SSME 1: 2050

SSME 2: 2048

SSME 3: 2058

External Tank: ET‐120

SRB Set: BI‐131

RSRM Set: 98

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

Nov. 6, 2007

Landing Time: 4:47 a.m. EST

Primary landing Site: Kennedy Space Center

Shuttle Landing Facility

PAYLOADS 

Node 2 - Harmony
12 MISSION PROFILE OCTOBER 2007

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OCTOBER 2007 MISSION PRIORITIES 13

MISSION PRIORITIES 

1. Node 2 Installation

2. Crew Rotation  

3. P6 Relocation from Z1 to P5

4. P6 Activation

(a) Deploy P6 forward radiator

(b) Deploy P6 Solar Arrays (2B and 4B)

5. Deploy S1 radiator outer panels

6. Orbital Replacement Unit

Installation/Return

(a) Node 2 Power and Data Grapple

Fixture Install, S‐band Antenna

Support Assembly (SASA)/Baseband

Signal Processor (BSP) Return, Main

Bus Switching Unit Install, Remote

Power Controller Module R&R

7. Cargo Transfer from/to middeck

8. Preparations for PMA 2 Relocation and

Node 2 Fluid Umbilical Tray Relocation and

Avionics Connections

9. Internal Thermal Control System

Remediation

10. Oxygen/Nitrogen Transfer

11. Node 2 Ingress and Outfitting

12. Detailed Test Objectives: Tile Repair

Ablator Dispenser; Station Wireless

Instrumentation System; Carbon Dioxide

monitoring; Multi‐Protocol Converter for

live HDTV downlink  
14 MISSION PROFILE OCTOBER 2007

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OCTOBER 2007 MISSION PERSONNEL 15

MISSION PERSONNEL 

KEY CONSOLE POSITIONS FOR STS-120 

Flt. Director CAPCOM PAO

Ascent Norm Knight Terry Virts Kylie Clem

Lee Archambault

(Weather)

Orbit 1 (Lead) Rick LaBrode Chris Ferguson Kylie Clem (Lead)

Orbit 2 Mike Moses Tony Antonelli Nicole Lemasters

Planning Mike Sarafin Shannon Lucid Pat Ryan

Entry Bryan Lunney Terry Virts Kylie Clem

Lee Archambault

(Weather)

Shuttle Team 4 Paul Dye N/A N/A

ISS Orbit 1 Dana Weigel Hal Getzelman N/A

ISS Orbit 2 (Lead) Derek Hassmann Kevin Ford N/A

ISS Orbit 3 Heather Rarick Zack Jones N/A

Station Team 4 Ginger Kerrick N/A N/A

JSC PAO Representative at KSC for Launch – John Ira Petty

KSC Launch Commentator – Mike Curie (Fueling)

KSC Launch Director – Mike Leinbach

NASA Launch Test Director – Steve Payne
16 MISSION PERSONNEL OCTOBER 2007

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OCTOBER 2007 CREW 17

STS-120 DISCOVERY CREW 

The STS‐120 patch reflects the role of the mis‐

sion in the future of the space program.    The

shuttle payload bay carries the Harmony mod‐

ule, the doorway to the future international

laboratory elements on the International Space

Station.

On the left the star represents the space station;

the red colored points represent the current

location of the P6 solar arrays, furled and await‐

ing relocation when the crew arrives.    During

the mission, the crew will move P6 to its final

home at the end of the port truss.    The gold

points represent the P6 solar arrays in their new

location, unfurled and producing power for

science and life support.

On the right, the moon and Mars can be seen

representing the future of NASA.  The constel‐

lation Orion rises in the background, symboliz‐

ing NASAʹs new crew exploration vehicle.  

Through all, the shuttle rises up and away,

leading the way to the future.
18 CREW OCTOBER 2007

Discovery’s seven astronauts take a break from training to pose for the STS‐120 crew portrait.  

Pictured from the left are mission specialists Scott Parazynski, Doug Wheelock, Stephanie Wilson,

Pilot George Zamka, Commander Pam Melroy, Expedition 16 Flight Engineer Daniel Tani and  

Paolo Nespoli, a mission specialist from Italy representing the European Space Agency (ESA).  

The crew members are attired in training versions of their shuttle launch and entry suits.

Short biographical sketches of the crew follow

with detailed background available at:

http://www.jsc.nasa.gov/Bios/
OCTOBER 2007 CREW 19

STS-120 CREW BIOGRAPHIES 

Pam Melroy

A retired Air Force colonel, Pam Melroy will

lead the crew of STS‐120 on the 23rd shuttle

mission to the International Space Station.  

Melroy served as the pilot of STS‐92 in 2000 and

STS‐112 in 2002.  Making her third spaceflight,

she has logged more than 562 hours in space.  

She has overall responsibility for the execution

of the mission, orbiter systems operations and

flight operations, including landing.    In addi‐

tion, Melroy will fly the shuttle in a rendezvous

pitch maneuver while Discovery is 600 feet

below the station to enable the station crew to

photograph the shuttle’s heat shield.    She will

then dock Discovery to the station.
20 CREW OCTOBER 2007

George Zamka

Marine Col. George Zamka has more than 4,000

flight hours in more than 30 different aircraft.  

He will make his first journey into space as the

pilot of space shuttle Discovery for the STS‐120

mission.  Selected by NASA in 1998, Zamka has

served in various technical and leadership roles

in the astronaut office.  He has been the lead for

the shuttle training and procedures division

and the supervisor for the astronaut candidate

class of 2004.  He will be responsible for orbiter

systems operations and will help Melroy in the

rendezvous and docking with the station.  

Zamka will undock Discovery from the station

at the end of the joint mission.  He will also be

operating the shuttle robotic arm for various

activities, including the handoff of the P6 truss.
OCTOBER 2007 CREW 21

Scott Parazynski

A medical doctor, mountaineer and former U.S

Luge Team athlete, veteran astronaut Scott

Parazynski will be making his fifth spaceflight

on STS‐120 as mission specialist 1.    He has

logged more than 1,019 hours in space, includ‐

ing 20 hours of spacewalking time.   Following

the Columbia tragedy, Parazynski was the

astronaut lead for the space shuttle Thermal

Protection System inspection and repair tech‐

niques development.  He will serve as the lead

spacewalker and will conduct four of the five

spacewalks during the mission.    The space‐

walks are focused on installation of Node 2,

robotically relocating the P6 truss element and

evaluating material and a dispenser for poten‐

tial space shuttle tile repair.    Parazynski also

will be operating the shuttle robotic arm during

heat shield inspections.
22 CREW OCTOBER 2007

Stephanie Wilson

Astronaut Stephanie Wilson will be making her

second spaceflight for STS‐120 as mission spe‐

cialist 2.    Selected as an astronaut in 1996, she

logged more than 306 hours in space during the

STS‐121 mission in 2006.  Wilson will be on the

flight deck during launch and landing, serving

as the flight engineer to assist Melroy and

Zamka.  She will be heavily involved in operat‐

ing both the shuttle and station robotic arms for

the shuttle thermal protection system inspec‐

tions, spacewalk activities, Node 2 installation

and the P6 truss element and solar array reloca‐

tion.
OCTOBER 2007 CREW 23

Doug Wheelock

Army Col. Doug Wheelock will be making his

first flight into space aboard Discovery as

mission specialist 3.  He has a bachelor’s degree

in applied science and engineering from the

U.S. Military Academy and a master’s degree in

aerospace engineering from Georgia Tech.  

Wheelock has logged more than 2,500 flight

hours in 43 different rotary and fixed‐wing

aircraft.    Selected as an astronaut in 1996, he

served as the crew support astronaut for

Expedition 2 in 2001 and as NASA’s Director of

Operations in Star City, Russia in 2005.  During

STS‐120, he will conduct three spacewalks and

operate the shuttle robotic arm.
24 CREW OCTOBER 2007

Paolo Nespoli

European Space Agency (ESA) astronaut Paolo

Nespoli will be making his first spaceflight.  He

received a Bachelor of Science in aerospace

engineering in 1988 and a Master of Science in

aeronautics and astronautics in 1989 from the

Polytechnic University of New York.    He was

selected as an astronaut by the Italian space

agency (ASI) in July 1998 and, one month later,

joined ESA’s European astronaut corps.    In

August 1998, he was relocated to NASA’s

Johnson Space Center and assigned to the 27th

NASA Astronaut Class.    He was assigned to

STS‐120 in June 2006.    As mission specialist 4

for the STS‐120 mission, he will serve as one of

the shuttle robotics officers for the survey of

Discoveryʹs wings and nose cap using the

Orbiter Boom Sensor System.    He will handle

rendezvous tools in preparation for Discoveryʹs

rendezvous and docking with the International

Space Station on flight day 3.  He will serve as

the intra‐vehicular crew member, or spacewalk

choreographer, for the first four spacewalks to

help install Node 2, relocate the P6 truss and

test shuttle heat shield repair techniques.    He

will be seated on the middeck for launch and

on the flight deck for entry.
OCTOBER 2007 CREW 25

Daniel Tani

Veteran space shuttle flyer Daniel Tani will

serve as a flight engineer aboard the Interna‐

tional Space Station.   He will travel to the sta‐

tion on STS‐120 and stay with Expedition 16.  

He is scheduled to return to Earth on Atlantis

during STS‐122.    A Massachusetts Institute of

Technology graduate, Tani joined NASA in

1996.    He served in numerous roles, including

the EVA Branch and as a Crew Support Astro‐

naut for Expedition 4.  Tani flew on STS‐108 in

2001 and has logged more than 11 days in

space, including a spacewalk to wrap thermal

blankets around ISS Solar Array Gimbals.  Dur‐

ing STS‐120, Tani will perform the second

spacewalk and operate the station robotic arm

for the P6 relocation, Node 2 installation and

various spacewalk activities.
26 MISSION PERSONNEL OCTOBER 2007

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OCTOBER 2007 PAYLOAD OVERVIEW 27

PAYLOAD OVERVIEW 

Harmony is shown attached to the Destiny module in the middle of the image above.

HARMONY (NODE 2) 

Expansion of the International Space Station

will continue with the delivery of the Harmony

connecting module.  Harmony will travel to the

station inside space shuttle Discovery’s payload

bay during STS‐120, also known as Assembly

Flight 10A.  Harmony’s addition sets the stage

for the arrival of new research laboratories.

Also known as Node 2, Harmony will be the

first pressurized module added to the station

since the Russian Pirs Docking Compartment

was installed in September 2001.    Harmony

joins three other named U.S. modules on the

station:   the Destiny laboratory, the Quest air‐

lock and the Unity node.  The most recent addi‐

tion was the Quest airlock in July 2001.

Harmony, measuring 23.6 feet long, 14.5 feet

wide and weighing 31,500 pounds, is a utility

hub, providing air, electrical power, water and

other systems essential to support life on the

station.    It will distribute resources from the

station’s truss to the Destiny lab and to the

European Space Agency’s Columbus Research

Laboratory and the Japanese Experiment Mod‐

ule (Kibo), when they are added to the station.  

The module will act as an internal connecting

port and passageway to additional interna‐

tional science labs and cargo spacecraft.
28 PAYLOAD OVERVIEW OCTOBER 2007

The picture above shows Harmony’s future port utilization as the space station expands.

In addition to increasing the living and working

space inside the station by more than

2,500 cubic feet, its exterior will serve as a work

platform for the stationʹs robotic arm, Cana‐

darm2.    Harmony is similar in shape to the

Unity module, known also as Node 1, which

was launched in 1998.  Unity links the Destiny

lab and the Russian Zarya Module.

Harmony was designed and built for NASA by

Thales Alenia Space in Torino, Italy, as part of

an agreement between NASA and the Euro‐

pean Space Agency.    The Boeing Company

provided a large number of Harmony’s subsys‐

tem components, including lights, fans, power

switches and converters, racks, air diffusers,

smoke detectors, hatches and Common Berth‐

ing Mechanisms.  The node’s subsystems were

tested by Thales Alenia to ensure they operated

within specifications common to all station

elements.

Boeing also built, installed onto Harmony, and

tested five Active Common Berthing

Mechanisms (ACBMs).  The mechanisms enable

on‐orbit mating and airtight seals between ISS

pressurized elements.    The ACBMs consist of

powered, computer‐controlled components that

align capture and are secured to the passive

CBMs.  The CBM system is used throughout the

station to mate arriving pressurized elements to

the existing on‐orbit platform.    The system is

comprised of two mating structures:  the active

half on the ISS and the passive half used on

arriving structures.
Node 2 Specifications 

Dimensions: Length: 23.6 ft. 

Diameter: 14.5 ft. 

Weight: 31,500 lbs. 

Pressurized Volume: 2,666 cubic ft. 

Habitable Volume: 1,230 cubic ft. 

Exterior Structure: Aluminum cylindrical 

sections, 2 endcones

Equipment Racks: 8

OCTOBER 2007 PAYLOAD OVERVIEW 29

While the active CBM contains all of the pow‐

ered components and associated alignment

hardware for berthing, the passive CBM con‐

figurations include the reciprocal mating fit‐

tings and alignment components, inclusive of

the atmospheric seal.  In a precisely controlled

sequence of events, the ISS remote manipula‐

tion system positions the mating module pas‐

sive CBM near the ISS active CBM for the

automated berthing, resulting in a structurally

sealed assembly.

Boeing employees are shown  

working on Harmony.

Node 2 will launch with 4 Avionics Racks,  

2 Resupply Stowage Racks (RSRs) loaded

with cargo, and 2 Zero‐g Stowage Racks.  

Show here are the RSRs.

Naming the Module 

On March 15, 2007, Node 2 received its name

after a competition involving more than 2,200

students from 32 states.    Six different schools

submitted “Harmony.”

A panel of NASA educators, engineers, scien‐

tists and senior agency managers selected the

name because it symbolizes the spirit of inter‐

national cooperation embodied by the station,

as well as the moduleʹs specific role in connect‐

ing the international partner modules.

The Node 2 Challenge required students to

learn about the space station, build a scale

model and write an essay explaining their pro‐

posed name for the module that will serve as a

central hub for science labs.

Harmony is the first U.S. piece of the space

station named by people outside of NASA.
30 PAYLOAD OVERVIEW OCTOBER 2007

Installation 

Harmony’s installation is a two‐step process.  

First, Discovery will dock to pressurized mat‐

ing adapter‐2 (PMA‐2), located on the end of

Destiny.    Then, the crew will attach the new

module to a temporary position on the outside

of Unity.    On orbit, PMA2 is outfitted with a

Pressurized Common Berthing Mechanism.

After Discovery leaves, the Expedition 16 crew

will use Canadarm2 to move PMA‐2 to the

forward port, onto one of the five active CMBs

on Harmony.  Then, the crew will use the arm

to move and install Harmony to its permanent

location at the end of Destiny.

Shown here are the steps to install Unity Node 2 onto Node 1  

using the shuttle and station robotic arms.
OCTOBER 2007 PAYLOAD OVERVIEW 31

Aft View of Harmony
32 MISSION PROFILE OCTOBER 2007

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OCTOBER 2007 STATION RELOCATION ACTIVITIES 33

STATION RELOCATION ACTIVITIES 

PORT 6 SOLAR ARRAYS RELOCATION 

The International Space Station derives its

power from the conversion of solar energy into

electrical power.    The P6 Photovoltaic Power

Module (PVM) — or Port 6 — performs this

energy conversion and is one of four such

modules on the station. (One more, S6, will be

launched on STS‐119.) The P6 has four primary

functions: the conversion or generation,

storage, regulation and distribution of electrical

power for the station.    P6 has two identical

PVMs that consist of two major elements called

the Solar Array Assembly (SAA) containing

two Solar Array Wings (SAW) connected to a

mast.    The wings are presently folded into a

mast canister for relocation and eventual

deployment.    Most of the electronics are

contained in the Integrated Equipment

Assembly (IEA), which is designed to condition

and store the electrical power collected by the

photovoltaic arrays for use aboard the station.

The integrated truss segments started with

Starboard 0 (S0) as the center assignment and

were numbered in ascending order outward to

the port and starboard sides.  At one time, an S2

and P2 were planned, but those segments were

eliminated when the station design was scaled

back.    From S0, the truss segments are P1, P3,

P4, P5 and P6, and S1, S3, S4, S5, and S6.

P6 is shown installed on the far right, while Harmony is shown attached to Destiny.
   

P6 Specifications 

Dimensions: Width: 35 ft. 

Length: 240 ft. 

Retracted Dimensions: 

Width: 16 ft

Length: 35 ft

Weight: 34,994 lbs. 

Launched: STS-97 

11/30/2000 

Cost: $275,968,083 

34 STATION RELOCATION ACTIVITIES OCTOBER 2007

P6 is presently in orbit and attached to the truss

segment Zenith 1 (Z1).  On flight day 6 during

the second spacewalk, P6 will be demated from

the Z1 truss i.e. separated from the Rocketdyne

Truss Attachment System (RTAS).    During

flight day 7, P6 will be handed off from the

station’s robotic arm to the shuttle’s arm.  

During this time, the mobile transporter with

the station’s robotic arm attached will travel

along the station’s truss structure rails to work

site number 8.  P6 will then be handed off to the

station’s robotic arm.   During flight day 8, the

station’s robotic arm will move P6 to the pre‐

install position.    During the mission’s third

spacewalk on flight day 8, astronauts will

attach P6 to the P5 short spacer.    Following

docking, the P6 solar array wings (2B/4B) will

be deployed as well as the radiator.  The solar

arrays wings will be deployed on flight day 8.  

Due to the issues with the retraction of these

arrays, testing was done to ensure the guide

wires would not impact the deploy process.  

The key difference during deployment is that

there is significantly more force available

during deploy to pull the guide wire through

the grommets so a snag is highly unlikely.   In

the event of a snag or any other issue, the crew

is trained to identify the warning signs and

immediately stop the deployment. The

indicator is the rising of the array tension bar.  

This will ensure no structural damage to the

array occurs.    If needed, astronauts will

perform a contingency spacewalk on flight

day 10, if there are problems in getting the solar

arrays properly deployed.

Following successful deployment, the P6 array

will be brought back on line again along with

P6 and P4.  There are two Solar Array Wings on

the P6 module yielding a total power genera‐

tion capability approaching 66 kilowatts of

unregulated power prior to distribution.

Major Elements 

Photovoltaic Module (PVMs) 

The primary functions of the power module are

to collect, convert, store, and distribute electri‐

cal power to loads within the segment and to

other station segments.  Electrical power is the

most critical resource for the station because it

allows astronauts to live comfortably, safely

operate the station and perform complex scien‐

tific experiments.  Since the only readily avail‐

able source of energy for spacecraft is sunlight,

technologies were developed to efficiently con‐

vert solar energy to electrical power.

The PVMs use large numbers of solar cells

assembled onto solar arrays to produce high

power levels.    NASA and Lockheed Martin

developed a method of mounting the solar

arrays on a “blanket” that can be folded like an

accordion for delivery to space and then

deployed to their full size once in orbit.    The

cells are made from purified crystal ingots of

silicon that directly convert light to electricity

for immediate use through a process called

photovoltaics.
OCTOBER 2007 STATION RELOCATION ACTIVITIES 35

Photovoltaic Module

Gimbals are used to rotate the arrays so that

they face the sun to provide maximum power

to the space station.    After the conversion

process, the PVMs also use the electricity to

recharge onboard batteries for continuous

sources of electricity while the station is in the

Earth’s shadow.    The complete power system,

consisting of U.S. and Russian hardware, will

generate approximately 80 kilowatts of total

power.

PVM components were assembled by The

Boeing Company in Tulsa, Okla., and Lockheed

Martin in Sunnyvale, Calif., before final

assembly and testing by Boeing at the Kennedy

Space Center, Fla.

Solar Array Wings (SAW) 

There are two SAWs designed, built and tested

by Lockheed Martin in Sunnyvale, Calif., on the

P6 module, and deployed in the opposite

direction from each other.  Each SAW is made

up of two solar blankets mounted to a common

mast.  Before deployment, each panel is folded

accordion style into a Solar Array Blanket Box

measuring 20 inches high and 15 feet in length.  

Each blanket is only about 20 inches thick while

in this stored position.    The mast consists of

interlocking battens that are stowed for launch
36 STATION RELOCATION ACTIVITIES OCTOBER 2007

inside a Mast Canister Assembly (MCA)

designed, built and tested by ATK‐Able.    The

blanket boxes are deployed prior to SAW

deploy.    While the P6 SAWs are retracted for

relocation, the blanket boxes will remain in the

deployed position.

When fully deployed, the SAW extends 115 feet

and spans 38 feet and extends to each side of

the Integrated Equipment Assembly.  Since the

second SAW is deployed in the opposite direc‐

tion, the total wing span is more than 240 feet.

Each SAW weighs more than 2,400 pounds and

uses 32,800 solar array cells per wing, each

measuring 8‐cm square with 4,100 diodes.  The

individual cells were made by Boeing’s

Spectrolab and ASEC.  There are 400 solar array

cells to a string and there are 82 strings per

wing.    Each SAW is capable of generating

nearly 32.8 kilowatts of direct current power.  

There are two SAWs on the P6 module yielding

a total power generation capability

approaching 66 kilowatts of unregulated power

prior to distribution.

Solar Array Wings
OCTOBER 2007 STATION RELOCATION ACTIVITIES 37

Beta Gimbal Assembly (BGA) 

The solar array wings also are oriented by the

Beta Gimbal Assembly, which can change the

pitch of the wings by spinning the solar array.  

The assembly measures 3‐ by 3‐ by 3 feet.  The

assemblyʹs most visual functions are to deploy

and retract the SAW and rotate it about its lon‐

gitudinal axis.    The assembly consists of three

major components:  the Bearing, Motor and Roll

Ring Module (BMRRM), the Electronic Control

Unit (ECU) and the Beta Gimbal Transition

Structure.    The BGA was designed by Boeing

Rocketdyne in Canoga Park, Calif., which has

since been acquired by Pratt and Whitney.  The

Sequential Shunt Unit (SSU) that serves to

manage and distribute the power generated

from the arrays also is mounted on each assem‐

bly platform.    The Sequential Shunt Unit was

designed by the company Space Systems/Loral.

Both the Solar Alpha Rotary Joints (SARJ)

(located between the P3 and P4 and the S3 and

S4 elements) and Beta Gimbal Assemblies are

pointing mechanisms and mechanical devices

used to point the arrays toward the sun.  They

can follow an angle target and rotate to that

target in the direction toward the sun.  In‐orbit

controllers continuously update those targets so

it keeps moving continuously as the station

orbits the Earth approximately every

90 minutes, maintaining contact with the sun at

the same orbital rate.    The SARJ mechanism,

which rotates the P4 and P6 (and its companion

S4 and eventually S6) arrays like a large

waterwheel, will move much more than the

Beta Gimbal Assembly, which moves about

four or five degrees per day, whereas the SARJ

will rotate 360 degrees every orbit or about

4 degrees per minute.

Direct Current Switching Unit (DCSU) 

Power received from each photovoltaic array

assembly (PVAA) is fed directly into the

appropriate DCSU, a high‐power, multi‐path

remotely controlled unit used for primary and

secondary power distribution, protection and

fault isolation within the Integrated Equipment

Assembly.  The DCSU also distributes primary

power to the station.    During periods of

sunlight, the DCSU routes primary power

directly to the station from its PVAA and also

routes power to the power storage system for

battery charging.  During periods of eclipse, the

DCSU routes power from the power storage

system to the station.    The DCSU measures

28‐ by 40‐ by 12 inches and weighs 238 pounds.

Direct Current to Direct Current 

Converter Unit (DDCU) 

Primary power from the DCSU is distributed to

the DDCU, a power processing system that

conditions the coarsely regulated power from

the PVAA to 123 +/‐ 2 volt direct current.  It has

a maximum power output of 6.25 kilowatts.  

This power is used for all station operations

employing secondary power.    By transmitting

power at higher voltages and stepping it down

to lower voltages where the power is to be

used, much like municipal power systems, the

station can use smaller wires to transmit this

electrical power and thus reduce launch loads.  

The converters also isolate the secondary

system from the primary system and maintain

uniform power quality throughout the station.  

The DDCU measures 27.25‐ by 23‐ by 12 inches

and weighs 129 pounds.
38 STATION RELOCATION ACTIVITIES OCTOBER 2007

Battery Charge/Discharge Unit (BCDU) 

Primary power from the DCSU also is distrib‐

uted to the three power storage systems within

each channel of the IEA.    The power storage

system consists of a Battery Charge/Discharge

Unit (BCDU) and two battery subassembly

Orbital Replacement Units.  The BCDU serves a

dual function of charging the batteries during

solar collection periods and providing condi‐

tioned battery power to the primary power

busses (via the DCSU) during eclipse periods.  

The BCDU has a battery charging capability of

8.4 kilowatts and a discharge capability of

6.6 kilowatts.    The BCDU also includes provi‐

sions for battery status monitoring and protec‐

tion from power circuit faults.  Commanding of

the BCDU is from the Photovoltaic Controller

Unit (PVCU).   The BCDU measures 28‐ by 40‐ 

by 12 inches and weighs 235 pounds.

Battery Subassembly Orbital 

Replacement Units 

Each battery subassembly ORU consists of

38 lightweight nickel hydrogen cells and asso‐

ciated electrical and mechanical equipment.  

Two battery subassembly ORUs connected in

series are capable of storing 8 kilowatts of elec‐

trical power.    This power is fed to the station

via the BCDU and DCSU respectively.    The

batteries have a design life of 6.5 years and can

exceed 38,000 charge/discharge cycles at

35 percent depth of discharge.    Each battery

measures 41‐  by 37‐  by 19 inches and weighs

372 pounds.

Sequential Shunt Unit (SSU) 

The SSU is designed to coarsely regulate the

solar power collected during periods of

isolation — when the arrays collect power

during sun‐pointing periods.    A sequence of

82 separate strings, or power lines, leads from

the solar array to the SSU.    Shunting, or

controlling, the output of each string regulates

the amount of power transferred.    The

regulated voltage setpoint is controlled by a

computer located on the IEA and is normally

set to around 160 volts.    The SSU has an

overvoltage protection feature to maintain the

output voltage below 200 V DC maximum for

all operating conditions.    This power is then

passed through the Bearing Motor and Roll

Ring Module (BMRRM) to the DCSU located in

the IEA.    The SSU measures 32‐  by 20‐  by 12

inches and weighs 185 pounds.

Photovoltaic Thermal Control System 

(PVTCS) 

To maintain the electronics at safe operating

temperatures in the harsh space environments,

they are conditioned by the PVTCS.    The

PVTCS consist of ammonia coolant, 11 cold‐

plates, two Pump Flow Control Subassemblies

(PFCS) and one Photovoltaic Radiator (PVR).

The coldplate subassemblies are an integral

part of the IEA structural framework.    Heat is

transferred from the IEA orbital replacement

unit electronic boxes to the coldplates via fine

interweaving fins located on both the coldplate

and the electronic boxes.    The fins add lateral

structural stiffness to the coldplates in addition

to increasing the available heat transfer area.

Pump Flow Control Subassemblies 

(PFCS) 

The PFCS is the heart of the thermal system,

consisting of all the pumping capacity, valves

and controls required to pump the heat transfer

fluid to the coldplates and radiator, and

regulate the temperature of the thermal control

system ammonia coolant.    The PVTCS is

designed to dissipate 6,000 watts of heat per

orbit on average and is commanded by the IEA
OCTOBER 2007 STATION RELOCATION ACTIVITIES 39

computer.    Each PFCS consumes 275 watts

during normal operations and measures

approximately 40‐  by 29‐  by 19 inches,

weighing 235 pounds.

Photovoltaic Radiator (PVR) 

The PVR — the radiator — is deployable on

orbit and comprised of two separate flow paths

through seven panels.  Each flow path is inde‐

pendent and is connected to one of the two

PFCSs on the IEA.  In total, the PVR can reject

up to 14 kilowatts of heat into deep space.  The

PVR weighs 1,633 pounds and when deployed

measures 44‐ by 12‐ by 7 feet.

P5 Long Spacer 

The P5 Long Spacer physically separates the

P6 solar arrays from the P4 solar arrays.

P6 uninstall using Space Station’s Remote Manipulator System (robotic arm)
40 STATION RELOCATION ACTIVITIES OCTOBER 2007

P6 handoff from the Space Station Remote Manipulator System (SSRMS)  

to Shuttle Remote Manipulator System (SRMS) and SSRMS ungrapple

Shuttle Remote Manipulator System (SRMS) handoff of P6  

to the SSRMS at Worksite 8
OCTOBER 2007 STATION RELOCATION ACTIVITIES 41

The station crew maneuvers P6 to the pre‐install position.

The crew drives the manual capture latch and bolt mechanisms to install P6 onto P5.
42 STATION RELOCATION ACTIVITIES OCTOBER 2007

PRESSURIZED MATING ADAPTER-2 

(PMA-2) RELOCATION 

The Boeing‐built Pressurized Mating Adapters

(PMA) permit pressurized spacecraft to dock

with one‐another despite differences in the

diameters of the spacecraft adapters.  They also

provide passageways for crew, equipment and

supplies.

The International Space Station uses three Pres‐

surized Mating Adapters (PMAs).    PMAs one

and two were launched with the Unity module

aboard STS‐88 on Dec. 4, 1998.    The third

launched aboard STS‐92 on Oct. 11, 2000, and

installed on the Unity Nadir port in preparation

of Destiny laboratory installation.  PMA‐2 was

temporarily relocated off of Node 1 to Zenith‐1

(Z‐1) Manual Berthing Mechanism until Des‐

tiny installation was completed on STS‐98 on

Feb. 7, 2001.   Following installation of Destiny

onto Unity, PMA‐2 was relocated from Z‐1

Manual Berthing Mechanism to Destiny’s for‐

ward endcone, where it has remained until the

STS‐120 mission.

Harmony (Node 2) 

PMA 2 

Unity (Node 1) 

Destiny (US Lab) 

Pictured above is the Harmony (Node 2) module installed on the Unity (Node 1) port Common

Berthing Mechanism.  The Boeing‐built Pressurized Mating Adapter‐2 is shown at the bottom of  

the U.S. Destiny laboratory before relocation onto Harmony, scheduled after the shuttle undocks.
OCTOBER 2007 MISSION PROFILE 43

    o

P6 Specifications 

Dimensions: Width: 8 ft.

Length: 5 ft.

Weight: 2,504 lbs. 

Launched: STS-88 

12/04/1998 

Cost: $219,254,000 

PMA‐1 has computers mounted externally for

use in command and control of Unity.  PMA‐2

and PMA‐3 are interchangeable with each

other.    Because PMAs are pressurized and

heated, they also serve as short, tunnel‐like

bridges that crews can use to go from one part

of the station to another, as well as between the

station and spacecraft that are docked there.  

PMAs also include mechanical interfaces,

spacewalk hardware and thermal control

equipment, electrical power subsystem and

command and data handling passthroughs.  

PMA‐2 also passes high pressure oxygen and

nitrogen from the orbiter to the station.

All three PMAs perform the same basic func‐

tion of connecting a Common Berthing Mecha‐

nism (CBM) port of a station module to the

Androgynous Peripheral Attach System

(APAS) docking port of another module or

visiting spacecraft.  PMAs 1, 2, & 3 each have a

passive CBM port.    Of the 3 PMAs, PMA‐1 is

the only one with an active APAS and it was

operated only one time on STS‐88 in mating the

Functional Cargo Block (FGB) to PMA‐1.  PMAs

2 & 3 each have a passive APAS port.  The CBM

is on the big end of the PMA and the APAS is

on the small end.  The CBM is used to connect

station hardware elements while the APAS is

used for docking spacecraft.  Airtight seals are

formed by these devices that pull together, lock

and seal  ‐‐ a different method than the  ʺbump‐

to‐trip latch, then sealʺ  procedure that most

spacecraft use to dock.

During STS‐120, space shuttle Discovery will

dock to PMA‐2.  When a shuttle docks with the

station, its final approach is at a relative veloc‐

ity of one‐tenth of a foot per second as it makes

contact with PMA‐2.   As the latches automati‐

cally attach the two spacecraft together and

nce relative motion between the spacecraft

stops, a shuttle astronaut retracts the docking

ring on the shuttleʹs mechanism, closing latches

to firmly secure the shuttle to the station.

On Aug. 30, 2007, PMA‐3 was moved to the

nadir hatch of Unity (Node 1) to make room for

the temporary berthing of Harmony.    During

flight day 4 of Flight 10A, the space station

robotic arm will move Harmony from the shut‐

tle cargo bay to a temporary location at the port

hatch of Unity.

PMA‐2 is shown attached to the  

U.S. Destiny laboratory
44 STATION RELOCATION ACTIVITIES OCTOBER 2007

At shuttle undock plus 2, the station’s robotic

arm will unberth PMA‐2 from the U.S. Destiny

laboratory and place it on the forward hatch of

Harmony.   At shuttle undock plus 4, the sta‐

tion arm then will move the integrated stack

(PMA‐2 and Node‐2) to its final location —

Destiny’s forward endcone.    The combined

operation to relocate PMA‐2 to its final position

on Harmony is expected to take 10 to 12 hours

with the actual robotic operation estimated to

take about two hours.

Pressurized Mating Adapters are Boeing prod‐

ucts, built in Huntington Beach, Calif.  The tight

seal that permits shirt‐sleeved transit between

station elements and spacecraft is provided in

part by Common Berthing Mechanism technol‐

ogy.

On the day of shuttle undock, Harmony will be

ingressed for the Centerline Berthing Camera

System (CBCS) installation.    The CBCS is

needed to berth the PMA‐2 to Harmony.   The

lab‐PMA‐2 umbilicals are disconnected during

STS‐120ʹs fifth spacewalk.  PMA‐2 will be relo‐

cated two days after shuttle undocking.    The

lab‐PMA‐2 umbilicals will be reconnected dur‐

ing Expedition 16/10A Stage spacewalks

planned for Nov. 14 (USOS EVA 10) and

Nov. 18 (USOS EVA 11).

Relocation of PMA‐2
OCTOBER 2007 MISSION PROFILE 45

Shown here is a drawing of PMA‐2.  The outside diameter of the ACBM and PCBM diameter  

is approximately 80 inches.  The ISS Common hatch opening is approx 48 inches x 48 inches.  

The APAS outside diameter is approximately 56 inches.  APAS hatch opening  

is approximately 31.5 inches.
46 STATION RELOCATION ACTIVITIES OCTOBER 2007

Relocation of Harmony (Node 2)

Shown here are the steps to relocate the Harmony (Node 2) module to its final position  

at the end of the Destiny lab.  PMA‐2 is shown here at the end of Harmony.  This  

relocation will be done approximately four days after the space shuttle undocks.
OCTOBER 2007 RENDEZVOUS & DOCKING 47

RENDEZVOUS AND DOCKING 

During STS‐118, the Space Shuttle Endeavour flew into position for a photo survey by

crewmembers aboard the International Space Station.  A Russian spacecraft, docked  

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

The shuttle launch is timed precisely to place

the orbiter on the correct trajectory and course

for its two‐day chase of the station.    Periodic

engine firings will gradually bring Discovery to

about 50,000 feet behind the station — the start‐

ing point for a final approach.

About 2.5 hours before docking, Discovery’s

jets will be fired during what is called the Ter‐

minal Initiation burn to begin the final phase of

the rendezvous.   Discovery will close the final

miles to the station during the next orbit.

As Discovery moves closer to the station, the

shuttle’s rendezvous radar system and

trajectory control sensor will track the complex

and provide range and closing rate data to the

crew.    During the final approach, Discovery

will execute several small mid‐course correction

burns that will place the shuttle about 1,000 feet

directly below the station.    STS‐120

Commander Pam Melroy then will manually

control the shuttle for the remainder of the

approach and docking.
48 RENDEZVOUS & DOCKING OCTOBER 2007

ISS crew members will photograph Discovery

during the Rendezvous Pitch Maneuver.

Melroy will stop the approach 600 feet beneath

the station to ensure proper lighting for

imagery prior to initiating the standard

Rendezvous Pitch Maneuver (RPM), or backflip.

Melroy will maneuver Discovery through a

9‐minute, 360‐degree backflip that allows the

station crew to take as many as 300 digital pic‐

tures of the shuttle’s heat shield.

On verbal cue from Pilot George Zamka to the

station crew, Melroy will command Discovery

to begin a nose‐forward, three‐quarter of a

degree per second rotational backflip.

Both 400 and 800 mm digital camera lenses will

be used to photograph Discovery by station

crew members.  The 400 mm lens provides up

to 3‐inch resolution and the 800 mm lens can

provide up to 1‐inch resolution.    The imagery

includes the upper surfaces of the shuttle as

well as Discovery’s underside, capturing pic‐

tures of the nose landing gear door seals, the

main landing gear door seals and the elevon

cove.

The photos will be taken out of windows in the

Zvezda Service Module using Kodak DCS 760

digital cameras.  The imagery is one of several

inspection techniques to determine the health of

the shuttle’s thermal protection system, includ‐

ing the tiles and reinforced carbon‐carbon wing

leading edges and nose cap.

The photos will be downlinked through the sta‐

tion’s Ku‐band communications system for

analysis by systems engineers and mission

managers.

When Discovery completes its rotation, its pay‐

load bay will be facing the station.

Melroy then will move Discovery to a position

about 400 feet directly in front of the station in

preparation for the final approach to docking to

the Destiny docking port.

The shuttle’s crew members operate laptop

computers processing the navigational data, the

laser range systems and Discovery’s docking

mechanism.

Using a view from a camera mounted in the

center of the Orbiter Docking System, Melroy

will precisely match up the docking ports of the

two spacecraft.  If necessary, she will temporar‐

ily pause 30 feet from the station to ensure

proper alignment of the docking mechanisms.

The ISS, as viewed by Space Shuttle

Endeavour’s STS‐118 astronauts.
OCTOBER 2007 RENDEZVOUS & DOCKING 49

Rendezvous Approach Profile

Space Shuttle Rendezvous Maneuvers 

OMS-1 (Orbit insertion) – Rarely used ascent 

burn. 

OMS-2 (Orbit insertion) – Typically used to 

circularize the initial orbit following ascent, 

completing orbital insertion. For ground-up 

rendezvous flights, also considered a 

rendezvous phasing burn.

NC (Rendezvous phasing) – Performed to hit 

a range relative to the target at a future time. 

NH (Rendezvous height adjust) – Performed 

to hit a delta-height relative to the target at a 

future time. 

NPC (Rendezvous plane change) – Performed 

to remove planar errors relative to the target at 

a future time. 

NCC (Rendezvous corrective combination) – 

First on-board targeted burn in the rendezvous 

sequence. Using star tracker data, it is 

performed to remove phasing and height errors 

relative to the target at Ti. 

Ti (Rendezvous terminal intercept) – Second 

on-board targeted burn in the rendezvous 

sequence. Using primarily rendezvous radar 

data, it places the orbiter on a trajectory to 

intercept the target in one orbit. 

MC-1, MC-2, MC-3, MC-4 (Rendezvous 

midcourse burns) – These on-board targeted 

burns use star tracker and rendezvous radar 

data to correct the post Ti trajectory in 

preparation for the final, manual proximity 

operations phase.

For Discovery’s docking, Melroy will maintain

the shuttleʹs speed relative to the station at

about one‐tenth of a foot per second (while both

Discovery and the station are traveling at about

17,500 mph), and keep the docking mechanisms

aligned to within a tolerance of three inches.  

When Discovery makes contact with the

station, preliminary latches will automatically

attach the two spacecraft.    Immediately after

Discovery docks, the shuttleʹs 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 the

station.

Once the motion between the spacecraft 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.  Discovery’s steering jets

will be shut off to avoid any inadvertent firings

during the initial separation.

Once Discovery is about two feet from the sta‐

tion and the docking devices are clear of one

another, Zamka will turn the steering jets back

on and will manually control Discovery within

a tight corridor as the shuttle separates from the

station.

Discovery will move to a distance of about

450 feet, where Zamka will begin to fly around

the station in its new configuration.    This ma‐

neuver will occur only if propellant margins

and mission timeline activities permit.
50 RENDEZVOUS & DOCKING OCTOBER 2007

Once Discovery completes 1.5 revolutions of

the complex, Zamka will fire Discovery’s jets to

leave the area.    The shuttle will move about

46 miles from the station and remain there

while ground teams analyze data from the late

inspection of the shuttleʹs heat shield.    The

distance is close enough to allow the shuttle to

return to the station in the unlikely event that

the heat shield is damaged, preventing the

shuttleʹs re‐entry.

Backdropped by Earthʹs horizon and the blackness of space, the  

International Space Station appears to be very small as the Space  

Shuttle Endeavour departs from the station during STS‐118.
OCTOBER 2007 SPACEWALKS 51

SPACEWALKS 

The primary objectives for STS‐120’s space‐

walks are to temporarily install the Node 2

module, also known as Harmony, and relocate

the stationʹs P6 truss and solar arrays.  The first

three spacewalks, known as extravehicular

activities or EVAs, will focus on these activities.  

The fourth spacewalk, recently added to the

mission, involves a demonstration of space

shuttle thermal protection system repair tech‐

niques.  The fifth and final spacewalk prepares

for the relocation of Harmony and the Pressur‐

ized Mating Adapter‐2, scheduled to occur just

after the shuttle mission.

The spacewalks are planned on flight days 4, 6,

8, 10 and 11.  Five spacewalks is the most con‐

ducted during a shuttle mission to the space

station.    STS‐120 also is the first mission with

five different spacewalkers.

Scott Parazynski and Doug Wheelock will perform the first, third and fourth spacewalks.
52 SPACEWALKS OCTOBER 2007

Veteran astronaut Scott Parazynski is the lead

spacewalker and will conduct the first four

excursions.    He will be joined by first time

spacewalker Doug Wheelock on the first, third

and fourth spacewalks.    Expedition 16 Flight

Engineer Daniel Tani will conduct the second

spacewalk with Parazynski.    Expedition 16

Commander Peggy Whitson and Expedition 16

Flight Engineer Yuri Malenchenko will conduct

the fifth spacewalk.

Mission Specialist Paolo Nespoli will be the

intravehicular lead for the first four spacewalks,

assisting the spacewalkers with their tasks from

inside the spacecraft.  Tani will be the intrave‐

hicular lead for the fifth spacewalk.

Wilson, Wheelock and Anderson will operate

the space station’s robotic arm for the Harmony

installation, P6 relocation and various

spacewalking tasks.  Zamka will join Wilson in

robotic arm operations to use the shuttle arm

for tasks during the third spacewalk.

Parazynski and Daniel Tani will conduct the second spacewalk.
OCTOBER 2007 SPACEWALKS 53

The spacewalkers will be identifiable by vari‐

ous markings on their spacesuits.  Parazynski’s

suit will have solid red stripes.  Wheelock will

wear an all‐white spacesuit.    Tani’s suit will

have broken red stripes.    Whitson’s suit will

have a red stripe and a candy cane stripe.  

Malenchenko will wear a suit with candy cane

stripes.

The spacewalks will start from the station’s

Quest airlock.  As in recent missions, the astro‐

nauts will prepare for the EVA by using the

“campout” prebreathe protocol, spending the

night before the spacewalk in the airlock.  The

prebreathe exercise purges nitrogen from the

astronauts’ systems so they avoid the condition

known as the bends.

During the campout, the spacewalking crew

members isolate themselves in the airlock.  The

airlockʹs air pressure is lowered to 10.2 psi

while the station is kept at 14.7 psi, or near sea‐

level pressure.  Upon rising, the astronauts don

oxygen masks, and the airlock’s pressure is

raised again to 14.7 psi for an hour.    After

breakfast, the pressure is lowered back to

10.2 psi for an additional hour as the spacewalk

suits are donned.  An additional 30 minutes in

the suits completes the protocol.  As a result, the

crew can get outside earlier to perform the day’s

tasks.

Expedition 16 crew members Peggy Whitson and Yuri Malenchenko  

will perform the fifth spacewalk.
54 SPACEWALKS OCTOBER 2007

EVA-1 

EV1:  Parazynski

EV2:  Wheelock

IV:  Nespoli

Duration:  6.5 hours

EVA Operations:

• Retrieve the S‐band Antenna Structural

Assembly (SASA) from Z1 truss

• Prepare Harmony for removal from

Discovery’s cargo bay

• Install the Payload and Data Grapple

Fixture on Harmony

• Remove contamination covers and caps

• Disconnect power cables from

Discovery’s cargo bay

• Disconnect P6/Z1 fluid umbilicals

Wilson, Tani and Anderson will position the

station’s robotic arm outside the Quest airlock.  

Wheelock will ride on the end of the arm for the

S‐band Antenna Structural Assembly removal

and to carry it to Discovery’s payload bay for

return to Earth.    Parazynski will “free float”

(not attached to a foot restraint) to complete

this task.

Both crew members will work in Discovery’s

payload bay to prepare Harmony for removal.  

They will secure a Payload and Data Grapple

Fixture onto Harmony that could not be in

place during launch, remove contamination

covers and disconnect the power cables linking

Harmony to Discovery.

The station robotic arm operators then will

remove Harmony from the payload bay and

begin moving it toward its position on Node 1,

also known as Unity.

Moving on to prepare P6 for its relocation,

Parazynski will disconnect four ammonia fluid

umbilicals from P6 and mate them to Z1.  

Meanwhile, Wheelock will prepare a shroud for

the aft radiator of P6.  Both crew members will

work together to install that shroud and two

more on electrical boxes, called sequential

shunt units, on P6.  The shrouds will keep the

hardware warm during the truss’ relocation.

EVA-2 

EV1:  Parazynski

EV3:  Tani

IV:  Nespoli

Duration: 6.5 hours

EVA Operations:

• Detach the P6 truss

• Remove and replace a remote power control

module

• Externally outfit Harmony

Before the spacewalk begins, Wilson, Wheelock

and Anderson will grapple the P6 truss with

the station robotic arm.  At the beginning of the

spacewalk, Parazynski and Tani will disconnect

nine cables from P6 to remove it from Z1.  

Parazynksi also will disconnect grounding

straps and bolts that hold P6 in place.

The robotic arm operators then will remove P6

and begin its relocation process.

Tani will work on the starboard 1 (S1) truss to

reconfigure connectors that will allow the

radiator on S1 to be deployed from the ground

later.  He then will work inside the S0 truss to
OCTOBER 2007 SPACEWALKS 55

re‐route electrical lines that will lead to the P6

truss once it is re‐installed outboard on the

truss structure. Tani will complete the

replacement of a remote power control module

that is associated with the station’s robotic arm

and its use of a grapple fixture on Harmony as

an operating base.

Parazynski will work on external outfitting of

Harmony by installing 11 handrails, two gap

spanners, three worksite interfaces, an electrical

connector and five trunion and keel pin covers.  

Four pins will be removed from the radial

berthing mechanisms, and launch restraints

will be released on the zenith berthing petals

and 16 caps under micrometeoroid debris cov‐

ers.  Tani will assist with the outfitting once his

tasks on the truss are complete.

Together, the spacewalkers also will affix the

power and data grapple fixture that was tem‐

porarily put in place during the first spacewalk.

EVA-3 

EV1:  Parazynski

EV2:  Wheelock

Duration:  7 hours

EVA Operations:

• Install the P6 truss

• Transfer the main bus switching unit to the

station

Parazynski and Wheelock will work at the out‐

board end of the port truss to assist with the

robotic arm attachment of P6 in its new location

on P5.  P6 will be positioned 130 cm away and

2 cm forward of the truss.  The spacewalk crew

will provide verbal cues to the robotic arm

operators, Tani, Wilson and Anderson, during

the installation.  Once P6 is in place, Wheelock

will close the mechanical capture claw to secure

it in place.  They will install bolts on each cor‐

ner for permanent attachment then release the

capture latch.    They will mate four umbilicals

from P5 to P6 to provide power.

The spacewalkers then will move to the edge of

P6 to remove the thermal shrouds from the

electronic hardware, or sequential shunt units,

which were installed during the first spacewalk

to protect them.

Parazynski will release cinches on a P6 radiator

to allow its deployment from the ground later.  

He then will move to the S1 truss to reconfigure

the electrical connectors that allowed the

ground to deploy the S1 radiators by this point

in the mission.    Parazynski then has time to

complete various get‐ahead tasks on the outside

of the station.

Meanwhile, Wheelock will work from the end

of the shuttle robotic arm, operated by Zamka

and Wilson, to install the main bus switching

unit spare hardware.  Wheelock will get on the

arm near the Destiny lab, ride it down to

Discovery’s cargo bay, retrieve the spare

hardware and carry it up to an external storage

platform.  Parazynski will assist with bolting it

in place on External Stowage Platform‐2.

EVA-4 

EV1:  Parazynski

EV2:  Wheelock

IV:  Nespoli

Duration: 4 hours

EVA Operations:

Tile Repair Ablator Dispenser (T‐RAD)

Detailed Test Objective (DTO) 848
56 SPACEWALKS OCTOBER 2007

The primary purpose of the detailed test objec‐

tive is to evaluate the Shuttle Tile Ablator‐54

(STA‐54) material and a tile repair ablator dis‐

penser in a microgravity and vacuum environ‐

ment for their use as a space shuttle thermal

protection system repair technique.

Parazynski has been involved in the develop‐

ment of space shuttle thermal protection system

repair techniques and will lead the testing dur‐

ing the spacewalk.    Wheelock will assist with

managing the tools and samples during the test.

The spacewalkers will setup for the test on the

outside of the Destiny lab.

The Tile Repair Ablator Dispenser, or T‐RAD, is

similar to a caulk‐gun.  Parazynski will use the

T‐RAD to mix and extrude the STA‐54 material

into holes in several demonstration tiles.    The

crew members will watch for swelling of the

material and work it in until it is smooth by

tamping the material with foam‐tipped tools.

The repaired samples and tools will be stowed

in Discovery’s cargo bay for return to Earth.  

The samples will undergo extensive testing on

the ground.

EVA-5 

EV4:  Whitson

EV5:  Malenchenko

IV:  Tani

Duration: 6.5 hours

EVA Operations:

• Prepare for Pressurized Mating Adapter‐2

relocation

• Stow the station to shuttle power trans‐

fer (SSPTS) cable

• Stow the Destiny Lab/Pressurized Mat‐

ing Adapter‐2 cables

• Remove Harmonyʹs active common

berthing mechanism cover

• Reconfigure S0 truss/Unity and Zarya

Module/Pressurized Mating Adapter‐1

power and jumper cables

For the primary objective of this spacewalk,

Whitson and Malenchenko will work at the

forward end of the Destiny lab.  They will clear

the area of cables and obstructions in prepara‐

tion for the permanent installation of Harmony

and its associated umbilical trays.

They will demate and stow the Station to

Shuttle Power Transfer cables and eight cables

between the Pressurized Mating Adapter‐2 and

the Destiny lab.

To make way for umbilical tray installation for

Harmony, they will demate connectors on each

side of the lab, and Whitson will remove a light

and place it in the airlock.

Malenchenko then will reconfigure connectors

on P1 that will allow the outboard radiators to

be deployed from the ground.

The spacewalkers will work together to remove

the active common berthing mechanism cover

on Harmony to clear it for attachment to

Destiny.  They will remove a strap around the

circumference of the cover, fold it and take it to

the airlock for disposal.

Malenchenko will work behind the Z1 truss,

near the Russian segment, to remove an electri‐

cal jumper for the power reconfigurations.  

Whitson will configure a power cable on the

starboard side of Z1.    She will retrieve hard‐

ware, called the base band single processor, and

bring it inside for later return and upgrade on

the ground.

The spacewalkers also will transfer tools

needed for spacewalks after the shuttle leaves.
OCTOBER 2007 EXPERIMENTS 57

EXPERIMENTS 

DETAILED TEST OBJECTIVES 

Detailed Test Objectives (DTOs) are aimed at

testing, evaluating or documenting space

shuttle systems or hardware, or proposed

improvements to the space shuttle or space

station hardware, systems and operations.

The following DTOs are planned for STS‐120:

DTO 848 TPS Repair Techniques 

(T-RAD/STA-54 Tile Repair Demo) 

The primary purpose of the DTO is to evaluate

Shuttle Tile Ablator‐54 (STA‐54) material and

the tile repair ablator dispenser in a micrograv‐

ity and vacuum environment for use as a space

shuttle thermal protection system repair tech‐

nique.

The Tile Repair Ablator Dispenser, or T‐RAD, is

similar to a caulk‐gun and is designed to facili‐

tate the repair of tiles near the orbiter’s nose

landing gear door, its two main landing gear

doors and the external tank attachment doors.

During the test, an Extra‐Vehicular Activity

(EVA) crew member will use T‐RAD to mix and

extrude STA‐54 material into holes in several

demonstration tiles.    The crew member will

then work it in until it is smooth by tamping the

material.

STA‐54 is a two‐part silicone‐based ablator that

consists of a base material and a catalyst.  Once

mixed, it resembles the consistency of cake‐

frosting.    However, the material cures to the

texture of a pencil eraser within 24 to 48 hours.  

During re‐entry, the STA‐54 dissipates heat by

charring, thus protecting the shuttle tiles.

The T‐RAD is comprised of a single, carbon

dioxide‐pressurized vessel separated into two

main sections.    Its mixing, delivery system

consists of a static mixer, a 3‐foot length of hose

and an applicator gun that controls the flow of

the extruding material.    The assembly weighs

55 pounds and is about the same size as a hand‐

held vacuum.

DTO 853 In-Flight Evaluation for Areas 

of CO2 Concentration 

The purpose of the DTO is to evaluate carbon

dioxide (CO2) levels at specific times during the

mission and in shuttle areas that have the

potential to contain elevated levels.  The DTO is

being carried out over four missions:  STS‐118,

STS‐120, STS‐122 and STS‐123.    During the

missions, the data will be collected over a

period of five days, during similar time periods

and in similar locations.

The CO2 levels will be recorded using the Car‐

bon Dioxide Monitor (CDM) — a portable

handheld device designed to monitor and

quantify CO2 concentrations.

The test was prompted by the STS‐121 and

STS‐115 mission crews who reported experienc‐

ing stuffiness and headaches while sleeping in

the middeck area.  The symptoms are believed

to most likely result from exposure to high

levels of CO2.

For the reported times during STS‐121 and

STS‐115, the CO2 levels within the crew mod‐

ule, as indicated by the vehicle instrumentation,

were within the acceptable range.    Addition‐

ally, for the course of the docked phase, the CO2

levels in the shuttle tracked well with the levels
58 EXPERIMENTS OCTOBER 2007

in the station.  The station crew did not report

any symptoms.

Data sampling locations for the test are

dependent upon crew sleep locations and high

activity locations because the post‐sleep activity

period and high activity periods are the times

when CO2 symptoms were reported by the two

crews.

During the upcoming four missions, the crews

will place the CDM in the middeck before they

go to sleep so that ground controllers can moni‐

tor CO2 levels continuously.    The information

will be used to identify CO2 “hot spots” within

the shuttle.

As a result, engineering evaluations will be

made to fine‐tune air exchange analyses, to

determine if any configuration changes are

necessary to optimize airflow and to determine

if operational improvements are needed or if

crew exposure time in identified areas should

be limited.

CDM technology was successfully used to

determine the existence of CO2 pockets on the

space station.  The kit that will be used on the

shuttle will include the CDM, filters and several

battery packs.    The CDM is capable of

monitoring CO2 in a localized area for either

long or short durations of time, depending on

the operating mode.

DTO 805 Crosswind Landing 

Performance (If opportunity) 

The purpose of this DTO is to demonstrate the

capability to perform a manually controlled

landing in the presence of a crosswind.    The

testing is done in two steps.

1. Pre‐launch: Ensure planning will allow

selection of a runway with Microwave

Scanning Beam Landing System support,

which is a set of dual transmitters located

beside the runway providing precision

navigation vertically, horizontally and lon‐

gitudinally with respect to the runway.  

This precision navigation subsystem helps

provide a higher probability of a more pre‐

cise landing with a crosswind of 10 to

15 knots as late in the flight as possible.

2. Entry:  This test requires that the crew per‐

form a manually controlled landing in the

presence of a 90‐degree crosswind compo‐

nent of 10 to 15 knots steady state.

During a crosswind landing, the drag chute will

be deployed after nose gear touchdown when

the vehicle is stable and tracking the runway

centerline.

SDTO 17010-J/A, Multi-Protocol 

Converter, for live HDTV downlink with 

MPC and incorporation into HDTV 

system 

The purpose of this Station Development Test

Objective (SDTO) is to demonstrate the

capability of the multi‐protocol converter (MPC)

before the installation and activation of the

Japanese Experiment Module. The purpose of

the JAXA supplied hardware is to provide high‐

definition television (HDTV) downlink to the

space station, while simplifying the processing

of the data system.    The objectives include

demonstrating the MPC system’s ability to

capture, process, and downlink a live digital

HDTV signal from the station to the ground via

the Ku‐band system and to evaluate the long‐

term radiation tolerance of HD digital video

cameras and of the high‐speed, high‐density

electronic components and circuitry required to

process digital HD video imagery for downlink.  

If time permits, the crew will also use the
OCTOBER 2007 EXPERIMENTS 59

JAXA‐provided HD camcorder in conjunction

with the Space Video Gateway system to

evaluate downlink compression methods.

SDTO 13005-U ISS Structural Life and 

Life Validation and Extension 

The purpose of this Station Development Test

Objective (SDTO) is to guarantee safety of the

station structure and crew by validating the

on‐orbit math models that were created for the

space station.  The test will be used to validate

critical interface load and to help improve

fatigue life prediction on the station.

During this mission, if crew time is available,

three tests will be performed:    one during the

shuttle‐station mated reboost, one during

undocking and one during S5 truss installation.  

The tests will provide dynamic loads

information for engineers to use in creating

precise models that can be used for analysis.  

On‐orbit data may aid in detecting structural

anomalies, and the station’s response to actual

loading events aids in post‐flight reconstruction

of loads that help determine structural life usage.

The test requires actual or educated estimates

of input (forcing function) and actual output

(on‐orbit sensor measurements) of the station

response.  Measurement of the force input (i.e.,

thruster firing sequences, video of crew activ‐

ity, etc.) and station response will aid recon‐

struction of station loads and structural life

usage over the life of the station, thus allowing

life extension of the structure.

All of the on‐orbit dynamic tests were also

performed on the ISS‐Orbiter mated configura‐

tion models.

SDTO 15003-U ISS Microgravity 

The purpose of this Station Development Test

Objective (SDTO) is to measure the space

station microgravity environment.    Operation

of equipment on the station creates vibrations

which can disturb — vibrate — science

experiments.    To minimize the vibration some

experiments experience, station hardware is

built with isolation systems, somewhat similar

to automotive shocks and springs.    Such

systems reduce the vibration transmitted from

station hardware to the experiment locations.

The biggest source of vibration on the station is

created by the crew members during routine

exercise.  As crew members cycle, run, walk, or

perform resistive exercise, large vibrations are

created that can affect the experiments.    This

SDTO will measure the accelerations caused by

the shuttle’s ergometer, or stationary exercise

bicycle, to determine the amount of load it

places on the station and shuttle.

SHORT-DURATION RESEARCH TO BE 

COMPLETED DURING STS-120 

The space shuttle and International Space Sta‐

tion have an integrated research program that

optimizes use of shuttle crew members and

long‐duration space station crew members to

address research questions in a variety of disci‐

plines.

Validation of Procedures for Monitoring Crew

Member Immune Function (Integrated

Immune) will assess the clinical risks resulting

from the adverse effects of spaceflight on the

human immune system and will validate a

flight‐compatible immune monitoring strategy.  

Researchers will collect and analyze blood,

urine and saliva samples from crew members

before, during and after spaceflight to monitor

changes in their immune systems.

Maui Analysis of Upper Atmospheric Injec‐

tions (MAUI) will observe the space shuttle

engine exhaust plumes from the Maui Space
60 EXPERIMENTS OCTOBER 2007

Surveillance Site in Hawaii.    The observations

will occur when the shuttle fires its engines at

night or twilight.  A telescope and all‐sky imag‐

ers will take images and data while the shuttle

flies over the Maui site.    The images will be

analyzed to better understand the interaction

between the spacecraft plume and the upper

atmosphere.

Test of Midodrine as a Countermeasure

Against Post‐Flight Orthostatic Hypotension

(Midodrine) is a test of the ability of the drug

midodrine to reduce the incidence or severity of

orthostatic hypotension.  If successful, the drug

will be employed as a countermeasure to the

dizziness caused by the blood‐pressure

decrease that many astronauts experience upon

returning to the Earthʹs gravity.

Perceptual Motor Deficits in Space (PMDIS)

will investigate why astronauts experience

difficulty with hand‐eye coordination while in

space.    These measurements will be used to

distinguish between three possible explana‐

tions:    the brain not adapting to the near

weightlessness of space; the difficulty of per‐

forming fine movements when floating in

space; and stress due to factors such as space

sickness and sleep deprivation.    This experi‐

ment is a cooperative effort with the Canadian

Space Agency.

Bioavailablity and Performance Effects of

Promethazine during Spaceflight (PMZ) will

examine the performance‐impacting side‐effects

of promethazine and its bioavailability — the

degree to which a drug can be absorbed and

used by the parts of the body on which it is

intended to have an effect.   Promethazine is a

medication taken by astronauts to prevent

motion sickness.

Ram Burn Observations (RAMBO) is an

experiment in which the Department of

Defense uses a satellite to observe space shuttle

orbital maneuvering system engine burns.  The

studyʹs purpose is to improve plume models

that predict the direction of the plume, or rising

column of exhaust, as the shuttle maneuvers on

orbit.  Understanding this flow direction could

be significant to the safe arrival and departure

of spacecraft on current and future exploration

missions.

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 shuttle

missions.    Advancing state‐of‐the‐art technol‐

ogy for monitoring, diagnosing and assessing

treatment of sleep patterns is vital to treating

insomnia on Earth and in space.

International Partner Experiments 

Fischer Rat Thyroid Low Serum 5 percent

(FRTL5) will be used as a biological system to

measure radiation and microgravity effects The

FRTL5 rat thyroid cell strain was chosen

because of its relevance to human physiology

and medicine.  Thyroid tissue is an ideal target

for space radiation research because it is

resistant to radiation’s acute effects.    This

experiment should help improve knowledge of

the effect of the space environment on the

human body, especially with longer‐term

missions planned in the future.

Study of Space Environment Effects on PY17

Bacterial Spores onboard International Space

Station (SPORE) is the study of PY17 bacterial

spores response to the effects of microgravity

and radiation.   The experiment was conceived

by high school students.
OCTOBER 2007 EXPERIMENTS 61

Samples and Hardware Returning on 

STS-120 

Analysis of a Novel Sensory Mechanism in

Root Phototropism (Tropi) sprouted Arabi‐

dopsis thaliana (thale cress) plants from seeds

under different frequencies of light and levels

of artificial gravity.  The plants will be analyzed

at the molecular level to determine what genes

are responsible for successful plant growth in

microgravity.

Capillary Flow Experiment (CFE) is a suite of

fluid physics experiments that investigate

capillary flows and flows of fluids in containers

with complex geometries.  Results will improve

current computer models that are used by

designers of low gravity fluid systems and may

improve fluid transfer systems on future

spacecraft.

Coarsening in Solid Liquid Mixtures‐2

(CSLM‐2) examines the kinetics of competitive

particle growth within a liquid matrix.  During

this process, small particles shrink by losing

atoms to larger particles, causing the larger

particles to grow (coarsen) within a liquid

lead/tin matrix.    This study defined the

mechanisms and rates of coarsening that

govern turbine blades, dental amalgam fillings,

iron copper, etc.

Commercial Generic Bioprocessing Apparatus

Science Insert – 02 (CSI‐02) is an educational

payload designed to interest middle school

students in science, technology, engineering

and math by participating in near real‐time

research conducted aboard the station.    Stu‐

dents will observe four experiments through

data and imagery downlinked and distributed

directly into the classroom via the Internet.  The

first is a seed germination experiment through

which students will learn how gravity affects

plant development.  Small seeds will be devel‐

oped on orbit in a garden habitat.  The second

experiment will examine yeast cells’ adaptation

to the space environment; the third will exam‐

ine plant cell cultures.    A fourth experiment

will examine crystal formation using silicates —

compounds containing silicon, oxygen and one

or more metals.  For the crystal growth experi‐

ment, students will grow crystals in their class‐

rooms and analyze growth of those compared

to the crystals grown in space.

Education Payload Operations – Kit C

(EPO ‐ Kit C) is an on‐orbit plant growth

investigation using basil seeds.    The still and

video imagery captured will be used as part of a

national engineering design challenge for

students in kindergarten through 12th grade.  

On the ground, students will grow basil seeds —

control and flown seeds — in growth chambers

to conduct their own plant growth science

experiments.

Nutritional Status Assessment (Nutrition) is

NASA’s most comprehensive in‐flight study to

date of human physiologic changes during long‐

duration spaceflight; 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.  The experiment also will help

to understand the impact of countermeasures —

exercise and pharmaceuticals — on nutritional

status and nutrient requirements for astronauts.

Test of Reaction and Adaptation Capabilities

(TRAC) will test the theory of brain adaptation

during spaceflight by testing hand‐eye

coordination before, during and after the

mission.    This experiment is a collaborative

effort between NASA and the Canadian Space

Agency.
62 EXPERIMENTS OCTOBER 2007

Smoke and Aerosol Measurement Experiment

(SAME) will measure the smoke properties, or

particle size distribution, from typical space‐

craft fire smokes to identify ways to improve

smoke detectors on future spacecraft.

Returning International Partner 

Experiments 

Color consists of an astronaut building a col‐

ored scene utilizing non‐representational and

super‐imposable painted transparent films to

identify the most favorable impression.

Neuroendocrine and Immune Responses in

Humans During and After Long‐term Stay at

ISS (Immuno) will provide an understanding

for the development of pharmacological tools to

countermeasure unwanted immunological side

effects during long‐duration missions.

Motion Perception:  Vestibular Adaptation to

G‐Transitions (MOP) is to gain insight in the

process of vestibular adaptation to a gravity

transition.

LBP‐Muscle:    Study of Lower Back Pain in

Astronauts during Spaceflight will study the

development of lower back pain in crew mem‐

bers during spaceflight and determine if there

is a relationship to muscle atrophy.

Experiments Delivered to the 

International Space Station on STS-120 

Investigating the Structure of Paramagnetic

Aggregates from Colloidal Emulsions

(InSPACE)‐2 will study the fundamental

behavior of magnetic colloidal fluids under the

influence of various magnetic fields.    This

technology has promise to improve the ability

to design structures, such as bridges and

buildings, and to better withstand earthquake

damage.

EUROPEAN EXPERIMENT PROGRAM 

In addition to his tasks as an STS‐120 mission

specialist, European Space Agency (ESA) astro‐

naut Paolo Nespoli will undertake the Euro‐

pean Esperia mission, during which he will

carry out a number of experiments on behalf of

the European science community.  Two of these

experiments (Chromosome‐2 and Neocytolysis)

are sponsored by ESA.  The other three experi‐

ments (HPA, FRTL‐5 and SPORE) are spon‐

sored by the Italian Space Agency, or ASI.  

Chromosome‐2, Neocytolysis and HPA are

experiments in the field of human physiology.  

FRTL‐5 and SPORE are biology experiments.  

Nespoli also will be conducting Educational

Activities (see ARISS) coordinated by both ESA

and ASI.

Chromosome-2 

During spaceflights, crew members are exposed

to different types of ionizing radiation.    To

assess the genetic impact of these radiations,

this experiment will study chromosome

changes and sensitivity to radiation in lympho‐

cytes (white blood cells) of ISS crew members.  

The Chromosome‐2 experiment is planned to

be carried out using eight subjects:   four from

short‐duration flights and four expedition crew

members.

Multi‐fluorescent chromosome map of a cell

exposed to cosmic radiation.  (Image:  M. Durante)
OCTOBER 2007 EXPERIMENTS 63

Science Team:

C. Johannes, M. Horstmann

Universität Duisburg‐Essen

Essen, Germany

Neocytolysis 

This experiment covers the effects of weight‐

lessness on the hemopoietic system, which is

the system of the body responsible for the for‐

mation of blood cells.    The experiment will

study a process called neocytolysis, the selec‐

tive destruction of young red blood cells.  The

experimentwill analyze the physical and func‐

tional characteristics of young red blood cells

taken from astronaut blood samples before and

after spaceflight.    It will be carried out with

three subjects from short‐term missions.

Constituents of blood.  E is an erythrocyte or

red blood cell, L is a lymphocyte or white

blood cell and P is a blood platelet.  (Image:  NASA)

Science Team:

A. Risso, G. Antonutto,

University of Udine, Udine, Italy

M. Cosulich, G. Minetti.

University of Pavia, Pavia, Italy

Hand Posture Analyzer (HPA) 

This experiment has two goals:  understanding

the ability of the human brain to mentally

represent the presence or absence of gravity

effects on object motion, and studying the

effects of weightlessness on movement.    The

Hand Posture Analyzer, was launched to the

ISS on Progress flight 12P in August 2003, and

used during Expeditions 7 and 8.    The

preliminary version of the same hardware was

used on board the station during the “Marco

Polo” mission with ESA astronaut Roberto

Vittori in 2002.    During his second mission in

April 2005, astronaut Roberto Vittori again

performed the HPA experiment.

Astronaut Roberto Vittori uses the CHIRO

device during the “Marco Polo” mission  

(April 2002) (Image:  V. Zolesi)

The HPA hardware consists of two dynamome‐

ters for measuring pinch and grip force and a

gloved instrumentation device worn by the

astronaut, which is attached to an electronics

box.   The astronaut will carry out three differ‐

ent experiment protocols:    IMAGINE, during

which the astronaut simulates throwing an

imaginary ball up against the ceiling and catch‐

ing it on the way down using the instrumented

glove and electronics box; MAIS, during which

the subject uses the same hardware and carries
64 EXPERIMENTS OCTOBER 2007

out a protocol of reaching out, gripping and

releasing different sized cylindrical objects; and

CHIRO, which measures the maximum force

exerted on the hand and pinch grip dynamome‐

ters by the astronaut.

Science Team:

F. Lacquaniti,

Università Tor Vergata, Rome, Italy

M. Zago, W. Miller, S. Gravano,

IRCCS Santa Lucia Foundation, Italy

P. Pastacaldi,

Azienda Ospedaliera Pisana, Pisa, Italy.

F. Posteraro,

Ospedale della Versilia, Lido di Camaiore (LU),

Italy

V. Zolesi,

Kayser Italia, Livorno, Italy

Fischer Rat Thyroid Low serum 5% 

(FRTL5) 

This experiment is aimed at assessing the effects

of the space environment (weightlessness and

radiation) on normal in vitro cultures of

so‐called FRTL5 rat thyroid cells.    This

experiment will use cells already exposed to the

space environment during the FRTL‐5

experiment on the 10‐day Eneide mission with

ESA astronaut Roberto Vittori in April 2005.

FTRL5 equipment (Image:  S. Ambesi)

The FRTL5 cells will be used in a proliferative

state, which is affected much more by the space

environment.  The cells will be sealed in sterile

culture flasks and kept under controlled

conditions.    One of the reasons for choosing

these specific thyroid cells is the relevance they

have to human physiology and medicine.  

Thyroid tissue is an ideal target for space

radiation research.

The cells will be tested after returning to Earth

for DNA modifications because of radiation

and magnetic fields, and the effect of weight‐

lessness on cell behavior.  This kind of research

helps to improve our knowledge of the effect of

the space environment on the human body,

especially with longer‐term missions planned

in the future (e.g., Mars).

Science Team:

F. Curcio, University of Udine, Italy

S. Ambesi, University of Udine, Italy

SPORE 

The SPORE educational experiment’s purpose

is the study of PY17 bacterial spores’ response

to exposure to weightlessness and ionizing

radiations, which are characteristic of the ISS

environment.    The experiment was conceived

by high school students.

PY17 is the name given to a culture of the wild

type stock spores of Bacillus subtilis.  

Ninety‐six sealed cuvettes containing the spores

will be equally split into three experiment con‐

tainers.    The experiment will last the duration

of the mission.  The bacterial spores are harm‐

less to humans.
OCTOBER 2007 EXPERIMENTS 65

Cuvette used in SPORE experiment

Once retrieved, the spores will be compared to

control samples that have followed the same

experiment protocol on the ground.  The com‐

parison will help determine the effects of resid‐

ual gravity variation and exposure to ionizing

radiations on the spores’ survival and devel‐

opment.

Science Team:

M. Mezzacappa,

Liceo Scientifico “Majorana” di Isernia, Italy

A. Iscra,

Istituto di Istruzione Superiore “Vittorio

Emanuele II – Ruffini” di Genova, Italy

L.i Naclerio,

Università del Molise, Italy

ARISS (and additional education 

activities)

ARISS stands for Amateur Radio on the ISS.  It

is an international association of national ama‐

teur radio societies from the countries partici‐

pating in the ISS program.    The association

forms a valuable part of ESA’s education pro‐

gram, helping to stimulate children and young

people’s interest in science, technical‐based

subjects and space in general.    The goal is to

stimulate interest for future careers in these

areas.

During the mission, Paolo Nespoli will be

involved in two live amateur radio contacts

from the ISS.    He will answer questions from

school children and university students at the

IIS Deambrosis‐Natta school in Sestri Levante,

Genoa, Italy and the University of L’Aquila

respectively.

A web‐chat with Nespoli before or after the

flight is also foreseen, as well as the distribution

of education material about the mission to

youngsters in Italy.  The education‐based activi‐

ties are being coordinated by ESA and ASI.

Competition winner at ESA’s ESRIN facility

in Frascati, Italy asks a question of ESA

astronaut Roberto Vittori on the ISS.  

21 April 2005. (Image:  ESA)

Project Team

G. Bertels, Brussels, Belgium

ESA‐HME Education Office,

ESTEC, Noordwijk, The Netherlands
66 EXPERIMENTS OCTOBER 2007

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OCTOBER 2007 EXTERNAL TANK REPAIRS 67

EXTERNAL TANK ET-120 (ET-120) 

ET‐120 was first shipped from the Michoud

Assembly Facility Dec. 31, 2004.  It was the first

tank slated to fly on the space shuttleʹs return to

flight, which was Discovery’s STS‐114 mission

in July 2005.  ET‐120 also was the first tank to be

modified with the safety improvements man‐

dated by the Columbia Accident Investigation

Board.    Improvements included the forward

bipod, liquid hydrogen tank/intertank flange

and liquid oxygen feedline bellows.

Lockheed Martin technician Dennis Silbernagel torques bolt fasteners on the redesigned –Y bipod

fitting on ET‐120 at NASA’s Michoud Assembly Facility in New Orleans in November 2004.  The

bipod redesign was one of the Return to Flight changes to the external tank to minimize potential

debris by eliminating the large insulating foam covering the bipod area in favor of electric heaters.
68 EXTERNAL TANK REPAIRS OCTOBER 2007

ET‐120 was fueled twice at the Kennedy Space

Center, Fla., in preparation for launch of

STS‐114.    The resulting Thermal Protection

System (foam) conditions were reported and

documented.    ET‐120 eventually was replaced

by another tank before the launch of STS‐114.

ET‐120 returned to the Michoud Assembly

Facility in New Orleans on Oct. 18, 2005, for

TPS modifications and was used as a dissection

test article during an STS‐114 foam loss investi‐

gation.    Foam loss events on the Protuberance

Air Load (PAL) and Ice/Frost ramps during

STS‐114 required dissections to be performed

on ET‐120 to further understand foam loss

mechanisms.

Dissections also revealed TPS cracking at the

liquid hydrogen PAL ramp and liquid hydro‐

gen Ice/Frost ramp locations.  Other TPS appli‐

cations considered “at risk” to the overall Space

Shuttle Program for thermal cracking also were

removed from ET‐120 and evaluated.  All other

dissected TPS applications were returned to

flight‐ready configuration.    In addition to the

TPS attention ET‐120 received, other systems,

including the structure, electrical, propul‐

sion/mechanical subsystems, went through a

verification reassessment process.

Lance Mercier, Lockheed Martin technician, measures foam prior to removing it from ET‐120’s liquid

hydrogen tank protuberance airloads (PAL) ramp in November 2005. Following STS‐114, studies  

and testing determined that both the liquid oxygen and the liquid hydrogen PAL ramps could be  

removed from the external tank to minimize potential foam loss.  The two PAL ramps, made entirely

of foam, weighed almost 37 pounds.  ET‐119 was the first tank to fly without PAL ramps.
OCTOBER 2007 EXTERNAL TANK REPAIRS 69

A recovery plan was presented and accepted by

the program, and the External Tank Project

initiated a recovery/repair plan effort to return

the tank to flight status.  The goal for the tank’s

TPS repairs was to keep debris risk at the same

level or better than the existing configuration.  

ET‐120 repair work began in October 2006 to

support the August 2007 launch on need mis‐

sion for shuttle Endeavour’s STS‐118 mission.  

ET‐120 is the primary tank for Discovery’s

STS‐120 mission.

ET‐120 was shipped by barge from the

Michoud Assembly Facility on July 24, 2007 and

arrived at the Kennedy Space Center, Fla., on

July 29.

ET-120 – BEFORE AND AFTER: HOW 

THE ET-120 TANK FOR STS-120 IS 

DIFFERENT FROM ET-120 FOR STS-114 

LH2 Ice/Frost Ramp modifications have been

made at 14 locations (stations1151‐1980).  

LO2 (Liquid Oxygen) Ice/Frost Ramps modifica‐

tions have been made at four locations (stations

XT, 718, 760, 794 and 828).  A complete redesign

is planned and will fly next year on ET‐128

during the STS‐124 mission.

LO2 Feedline Brackets – Four feedline brackets

(stations 1129, 1623, 1377, and 1871) on ET‐120

were modified with a different foam configura‐

tion as an interim measure before a new tita‐

nium bracket design flies on ET‐128/STS‐124.  

BX foam and Super‐Lightweight Ablator (SLA)

were removed from the upper portion of the

four brackets, which were resprayed only with

BX foam and restored to near the original mold

line.    Bracket BX foam is about one‐inch thick

and the underlying SLA is about one‐half‐inch

thick, but the SLA is denser, or heavier than the

BX foam.  Approximately five inches of TPS is

being removed, which eliminates about

.12 pounds of TPS mass for each bracket.  Less

foam on the brackets is acceptable for the shut‐

tle’s ascent.    It is now known that SLA is not

required on the brackets.

LO2 and LH2 (Liquid Hydrogen) PAL Ramps

were removed.

Bipod Harness Modifications – Wire harness

sealing/bonding, flown as a return‐to‐flight

modification on ET‐119 during the STS‐121

mission was performed to preclude a debris

event similar to the one observed on STS‐114.  

Voids within cabling and underneath the

harnesses have the potential to cause

cryoingestion and cryopumping failure.    A

process was developed to seal cables and bond

harnesses with minimal defects.

A United Space Alliance external tank

technician maps out the cutting area of the

LO2 feed line bracket where BX265 foam

insulation and super lightweight ablator,  

or SLA, cork insulation is to be removed.   

The BX265 foam insulation was later

reapplied without the SLA.
70 EXTERNAL TANK REPAIRS OCTOBER 2007

Intertank Acreage Machining/Venting – The

area of vented intertank TPS foam was

increased to reduce the potential for foam loss

because of “popcorning,” which results from air

bubbles becoming trapped in foam, then flaking

off and falling away from heating and

expansion during launch.

Two ET Camera Antennas Replaced –

Corrosion on antennas observed during visual

inspection were believed to have been caused

by the tank’s extended stay at the launch pad or

exposure to moisture at the Michoud Assembly

Facility.    Two LO2 Feedline Camera System

antennas were removed and replaced with new

nickel‐plated antennas.    TPS closeout material

was reapplied using the existing verified and

validated procedure.

The Space Shuttle Program remains committed

to understanding external tank foam in order to

more accurately assess potential risks and make

improvements to the tank.    A number of

improvements were made prior to STS‐114 and

more were made before STS‐121.    While

external tank foam loss never can be completely

eliminated, the program continues to make

tank improvements to minimize foam and ice

loss by looking at areas where debris may be

shed, prioritizing them and methodically

eliminating them one at a time.

The super lightweight ablator, or SLA,  

cork insulation has been removed from  

the external tank and a United Space  

Alliance external tank technician sands  

off the residue from the LO2 feed line  

bracket.  The BX265 foam insulation  

was later reapplied without the SLA.
OCTOBER 2007 SHUTTLE REFERENCE DATA 71

SHUTTLE REFERENCE DATA 

SHUTTLE ABORT MODES 

RSLS Aborts 

These occur when the on‐board shuttle com‐

puters 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), trans‐

oceanic 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, Kennedy Space Center, approxi‐

mately 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, at which time not

enough main propulsion system propellant

remains to return to the launch site.  An RTLS

can be considered to consist of three stages — a

powered stage, during which the space shuttle

main engines are still thrusting; an external

tank separation phase; and the glide phase,

during which the orbiter glides to a landing at

the Kennedy Space Center.  The powered RTLS

phase begins with the crew selection of the

RTLS abort, 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 Kennedy Space Center and achieve

the proper main engine cutoff conditions so the

vehicle can glide to the Kennedy Space Center

after external tank separation.    During the

downrange phase, a pitch‐around maneuver is
72 SHUTTLE REFERENCE DATA OCTOBER 2007

initiated (the time depends in part on the time

of a space shuttle main engine failure) to orient

the orbiter/external tank configuration to a

heads‐up attitude, pointing toward the launch

site.    At this time, the vehicle is still moving

away from the launch site, but the space shuttle

main engines are now thrusting to null the

downrange velocity.  In addition, excess orbital

maneuvering system and reaction control sys‐

tem propellants are dumped by continuous

orbital maneuvering system and reaction con‐

trol 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 perform‐
OCTOBER 2007 SHUTTLE REFERENCE DATA 73

ance has been lost and it is impossible to reach

the planned orbital altitude.   If a space shuttle

main engine fails in a region that results in a

main engine cutoff under speed, the Mission

Control Center will determine that an abort

mode is necessary and will inform the crew.  

The orbital maneuvering system engines would

be used to place the orbiter in a circular orbit.

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 maneu‐

ver 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 sys‐

tems.  Loss of one main engine while another is

stuck at a low thrust setting also may necessi‐

tate 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 orbiterʹs position than the

crew can obtain from on‐board systems.  Before

main engine cutoff, Mission Control makes

periodic calls to the crew to tell them which

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

communications are lost, the flight crew has

on‐board methods, such as cue cards, dedicated

displays and display information, to determine
74 SHUTTLE REFERENCE DATA OCTOBER 2007

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 jeopard‐

izes 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 posi‐

tioning 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 sec‐

onds 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 on‐board com‐

puters 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 on‐board computers at T‐3 seconds

following a problem with purge pressure read‐

ings 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

on‐board 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,

NASA managers set Oct. 2 as the date for

Endeavour’s second launch attempt.
OCTOBER 2007 SHUTTLE REFERENCE DATA 75

Abort to Orbit History 

(STS-51 F) July 29, 1985 

After an RSLS abort on July 12, 1985, Chal‐

lenger 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 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 per‐

formance 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 pat‐

tern.    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

(4.2 meters) long, weighs about 7,000 pounds

(3,150 kilograms) and is 7.5 feet (2.25 meters) in

diameter at the end of its nozzle.

The engines operate for about 8‐1/2 minutes

during liftoff and ascent — burning more than

500,000 gallons (1.9 million liters) of super‐cold

liquid hydrogen and liquid oxygen propellants

stored in the huge external tank attached to the

underside of the shuttle.    The engines shut

down just before the shuttle, traveling at about

17,000 mph (28,000 kilometers per hour),

reaches orbit.

The main engine operates at greater tempera‐

ture extremes than any mechanical system in

common use today.  The fuel, liquefied hydro‐

gen at  ‐423 degrees Fahrenheit (‐253 degrees

Celsius), is the second coldest liquid on Earth.  

When it and the liquid oxygen are combusted,

the temperature in the main combustion cham‐

ber is 6,000 degrees Fahrenheit (3,316 degrees

Celsius), 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 — then burned completely at

high temperature and pressure in the main

combustion chamber.  The rapid mixing of the

propellants under these conditions is so com‐

plete that 99 percent of the fuel is burned.

At normal operating level, each engine gener‐

ates 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 pre‐burners, thus varying the

speed of the high‐pressure turbopumps and,

therefore, the flow of the propellant.

At about 26 seconds into launch, 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 or max q.  Then, the

engines are throttled back up to normal

operating level at about 60 seconds.    This

reduces stress on the vehicle.  The main engines
76 SHUTTLE REFERENCE DATA OCTOBER 2007

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 — again 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 sec‐

ond to 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 2‐1/2

747 airplanes.

The space shuttle main engine is also the first

rocket engine to use a built‐in electronic digital

controller, or computer.    The controller will

accept commands from the orbiter for engine

start, change in throttle, shutdown, and moni‐

tor engine operation.  In the event of a failure,

the controller automatically corrects the prob‐

lem or safely shuts down the engine.

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, and 2001.    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.

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 

The two SRBs provide the main thrust to lift the

space shuttle off the pad and up to an altitude

of about 150,000 feet, or 24 nautical miles

(28 statute miles).    In addition, the two SRBs

carry the entire weight of the external tank and

orbiter and transmit the weight load through

their structure to the mobile launcher platform.

Each booster has a thrust (sea level) of about

3,300,000 pounds at launch.    They are ignited

after the three space shuttle main engines’

thrust level is verified.   The two SRBs provide

71.4 percent of the thrust at liftoff and during

first‐stage ascent.    Seventy‐five seconds after

SRB separation, SRB apogee occurs at an alti‐

tude of about 220,000 feet, or 35 nautical miles

(40 statute miles).    SRB impact occurs in the

ocean about 122 nautical miles (140 statute

miles) downrange.

The SRBs are the largest solid‐propellant

motors ever flown and the first designed for

reuse.  Each is 149.16 feet long and 12.17 feet in

diameter.    Each SRB weighs about 1,300,000

pounds at launch.  The propellant for each solid

rocket motor weighs about 1,100,000 pounds.  
OCTOBER 2007 SHUTTLE REFERENCE DATA 77

The inert weight of each SRB is about

192,000 pounds.

Primary elements of each booster are the motor

(including case, propellant, igniter and nozzle),

structure, separation systems, operational flight

instrumentation, recovery avionics, pyrotech‐

nics, deceleration system, thrust vector control

system and range safety destruct system.

Each booster is attached to the external tank at

the SRB’s aft frame by two lateral sway braces

and a diagonal attachment.  The forward end of

each SRB is attached to the external tank at the

forward end of the SRB’s forward skirt.  On the

launch pad, each booster also is attached to the

mobile launcher platform at the aft skirt by four

bolts and nuts that are severed by small explo‐

sives at liftoff.

During the downtime following the Challenger

accident, detailed structural analyses were

performed on critical structural elements of the

SRB.  Analyses were primarily focused in areas

where anomalies had been noted during post‐

flight inspection of recovered hardware.

One of the areas was the attach ring where the

SRBs are connected to the external tank.  Areas

of distress were noted in some of the fasteners

where the ring attaches to the SRB motor case.  

This situation was attributed to the high loads

encountered during water impact.    To correct

the situation and ensure higher strength margins

during ascent, the attach ring was redesigned to

encircle the motor case completely (360 degrees).

Previously, the attach ring formed a C and

encircled the motor case 270 degrees.

Additionally, special structural tests were done

on the aft skirt.    During this test program, an

anomaly occurred in a critical weld between the

hold‐down post and skin of the skirt.  A redes‐

ign was implemented to add reinforcement

brackets and fittings in the aft ring of the skirt.

These two modifications added about

450 pounds to the weight of each SRB.

The propellant mixture in each SRB motor

consists of an ammonium perchlorate (oxidizer,

69.6 percent by weight), aluminum (fuel,

16 percent), iron oxide (a catalyst, 0.4 percent), a

polymer (a binder that holds the mixture

together, 12.04 percent), and an epoxy curing

agent (1.96 percent).    The propellant is an

11‐point star‐shaped perforation in the forward

motor segment and a double‐truncated‐cone

perforation in each of the aft segments and aft

closure.    This configuration provides high

thrust at ignition and then reduces the thrust by

about a third 50 seconds after liftoff to prevent

overstressing the vehicle during maximum

dynamic pressure.

The SRBs are used as matched pairs and each is

made up of four solid rocket motor segments.  

The pairs are matched by loading each of the

four motor segments in pairs from the same

batches of propellant ingredients to minimize

any thrust imbalance.    The segmented‐casing

design assures maximum flexibility in fabrica‐

tion and ease of transportation and handling.  

Each segment is shipped to the launch site on a

heavy‐duty rail car with a specially built cover.

The nozzle expansion ratio of each booster

beginning with the STS‐8 mission is 7‐to‐79.  

The nozzle is gimbaled for thrust vector (direc‐

tion) control.  Each SRB has its own redundant

auxiliary power units and hydraulic pumps.  

The all‐axis gimbaling capability is 8 degrees.  

Each nozzle has a carbon cloth liner that erodes

and chars during firing.    The nozzle is a con‐

vergent‐divergent, movable design in which an
78 SHUTTLE REFERENCE DATA OCTOBER 2007

aft pivot‐point flexible bearing is the gimbal

mechanism.

The cone‐shaped aft skirt reacts the aft loads

between the SRB and the mobile launcher

platform.    The four aft separation motors are

mounted on the skirt.  The aft section contains

avionics, a thrust vector control system that

consists of two auxiliary power units and

hydraulic pumps, hydraulic systems and a

nozzle extension jettison system.

The forward section of each booster contains

avionics, a sequencer, forward separation

motors, a nose cone separation system, drogue

and main parachutes, a recovery beacon, a

recovery light, a parachute camera on selected

flights and a range safety system.

Each SRB has two integrated electronic

assemblies, one forward and one aft.    After

burnout, the forward assembly initiates the

release of the nose cap and frustum, a transition

piece between the nose cone and solid rocket

motor, and turns on the recovery aids.  The aft

assembly, mounted in the external tank/SRB

attach ring, connects with the forward assembly

and the orbiter avionics systems for SRB

ignition commands and nozzle thrust vector

control.    Each integrated electronic assembly

has a multiplexer/demultiplexer, which sends

or receives more than one message, signal or

unit of information on a single communication

channel.

Eight booster separation motors (four in the

nose frustum and four in the aft skirt) of each

SRB thrust for 1.02 seconds at SRB separation

from the external tank.  Each solid rocket sepa‐

ration motor is 31.1 inches long and 12.8 inches

in diameter.

Location aids are provided for each SRB, frus‐

tum/drogue chutes and main parachutes.  

These include a transmitter, antenna,

strobe/converter, battery and salt‐water switch

electronics.  The location aids are designed for a

minimum operating life of 72 hours and when

refurbished are considered usable up to

20 times.  The flashing light is an exception.  It

has an operating life of 280 hours.  The battery

is used only once.

The SRB nose caps and nozzle extensions are

not recovered.

The recovery crew retrieves the SRBs, frus‐

tum/drogue chutes, and main parachutes.  The

nozzles are plugged, the solid rocket motors are

dewatered, and the SRBs are towed back to the

launch site.  Each booster is removed from the

water, and its components are disassembled

and washed with fresh and deionized water to

limit salt‐water corrosion.  The motor segments,

igniter and nozzle are shipped back to ATK

Thiokol for refurbishment.

Each SRB incorporates a range safety system

that includes a battery power source,

receiver/decoder, antennas and ordnance.

Hold-Down Posts 

Each solid rocket booster has four hold‐down

posts that fit into corresponding support posts

on the mobile launcher platform.    Hold‐down

bolts hold the SRB and launcher platform posts

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

only the top nut is frangible.  The top nut con‐

tains two NASA standard detonators (NSDs),

which are ignited at solid rocket motor ignition

commands.

When the two NSDs are ignited at each hold‐

down, the hold‐down bolt travels downward

because of the release of tension in the bolt

(pretensioned before launch), NSD gas pressure

and gravity.    The bolt is stopped by the stud
OCTOBER 2007 SHUTTLE REFERENCE DATA 79

deceleration stand, which contains sand.    The

SRB bolt is 28 inches long and 3.5 inches in

diameter.    The frangible nut is captured in a

blast container.

The solid rocket motor ignition commands are

issued by the orbiter’s computers through the

master events controllers to the hold‐down

pyrotechnic initiator controllers on the mobile

launcher platform.  They provide the ignition to

the hold‐down NSDs.    The launch processing

system monitors the SRB hold‐down PICs for

low voltage during the last 16 seconds before

launch.   PIC low voltage will initiate a launch

hold.

SRB Ignition 

SRB ignition can occur only when a manual

lock pin from each SRB safe and arm device has

been removed.   The ground crew removes the

pin during prelaunch activities.    At T minus

five minutes, the SRB safe and arm device is

rotated to the arm position.    The solid rocket

motor ignition commands are issued when the

three SSMEs are at or above 90 percent rated

thrust, no SSME fail and/or SRB ignition PIC

low voltage is indicated and there are no holds

from the LPS.

The solid rocket motor ignition commands are

sent by the orbiter computers through the

MECs to the safe and arm device NSDs in each

SRB.  A PIC single‐channel capacitor discharge

device controls the firing of each pyrotechnic

device. Three signals must be present

simultaneously for the PIC to generate the pyro

firing output.  These signals — arm, fire 1 and

fire 2 — originate in the orbiter general‐purpose

computers and are transmitted to the MECs.  

The MECs reformat them to 28‐volt dc signals

for the PICs.    The arm signal charges the PIC

capacitor to 40 volts dc (minimum of 20 volts

dc).

The fire 2 commands cause the redundant

NSDs to fire through a thin barrier seal down a

flame tunnel.    This ignites a pyro booster

charge, which is retained in the safe and arm

device behind a perforated plate.   The booster

charge ignites the propellant in the igniter ini‐

tiator; and combustion products of this propel‐

lant ignite the solid rocket motor initiator,

which fires down the length of the solid rocket

motor igniting the solid rocket motor propel‐

lant.

The GPC launch sequence also controls certain

critical main propulsion system valves and

monitors the engine‐ready indications from the

SSMEs.  The MPS start commands are issued by

the on‐board computers at T minus 6.6 seconds

(staggered start — engine three, engine two,

engine one — all about within 0.25 of a second),

and the sequence monitors the thrust buildup

of each engine.  All three SSMEs must reach the

required 90 percent thrust within three seconds;

otherwise, an orderly shutdown is commanded

and safing functions are initiated.

Normal thrust buildup to the required 90 per‐

cent thrust level will result in the SSMEs being

commanded to the liftoff position at T minus

three seconds as well as the fire 1 command

being issued to arm the SRBs.  At T minus three

seconds, the vehicle base bending load modes

are allowed to initialize (movement of

25.5 inches measured at the tip of the external

tank, with movement towards the external

tank).

At T minus zero, the two SRBs are ignited

under command of the four on‐board

computers; separation of the four explosive

bolts on each SRB is initiated (each bolt is
80 SHUTTLE REFERENCE DATA OCTOBER 2007

28 inches long and 3.5 inches in diameter); 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.

The solid rocket motor thrust profile is tailored

to reduce thrust during the maximum dynamic

pressure region.

Electrical Power Distribution 

Electrical power distribution in each SRB

consists of orbiter‐supplied main dc bus power

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

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

power to 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

arrangement allows all SRB buses to remain

powered in the event one orbiter main bus fails.

The nominal dc voltage is 28 volts dc, with an

upper limit of 32 volts dc and a lower limit of

24 volts dc.

Hydraulic Power Units 

There are two self‐contained, independent

HPUs on each SRB.    Each HPU consists of an

auxiliary power unit, fuel supply module,

hydraulic pump, hydraulic reservoir and

hydraulic fluid manifold assembly.  The APUs

are fueled by hydrazine and generate

mechanical shaft power to a hydraulic pump

that produces hydraulic pressure for the SRB

hydraulic system.  The two separate HPUs and

two hydraulic systems are located on the aft

end of each SRB between the SRB nozzle and

aft skirt.  The HPU components are mounted on

the aft skirt between the rock and tilt actuators.  

The two systems operate from T minus

28 seconds until SRB separation from the

orbiter and external tank.  The two independent

hydraulic systems are connected to the rock and

tilt servoactuators.

The APU controller electronics are located in

the SRB aft integrated electronic assemblies on

the aft external tank attach rings.

The APUs and their fuel systems are isolated

from each other.    Each fuel supply module

(tank) contains 22 pounds of hydrazine.    The

fuel tank is pressurized with gaseous nitrogen

at 400 psi, which provides the force to expel

(positive expulsion) the fuel from the tank to

the fuel distribution line, maintaining a positive

fuel supply to the APU throughout its opera‐

tion.

The fuel isolation valve is opened at APU

startup to allow fuel to flow to the APU fuel

pump and control valves and then to the gas

generator.   The gas generator’s catalytic action

decomposes the fuel and creates a hot gas.   It

feeds the hot gas exhaust product to the APU

two‐stage gas turbine.    Fuel flows primarily

through the startup bypass line until the APU

speed is such that the fuel pump outlet pressure

is greater than the bypass line’s.    Then all the

fuel is supplied to the fuel pump.

The APU turbine assembly provides mechani‐

cal power to the APU gearbox.    The gearbox

drives the APU fuel pump, hydraulic pump

and lube oil pump.    The APU lube oil pump

lubricates the gearbox.  The turbine exhaust of

each APU flows over the exterior of the gas

generator, cooling it, and is then directed over‐

board through an exhaust duct.

When the APU speed reaches 100 percent, the

APU primary control valve closes, and the APU
OCTOBER 2007 SHUTTLE REFERENCE DATA 81

speed is controlled by the APU controller

electronics.    If the primary control valve logic

fails to the open state, the secondary control

valve assumes control of the APU at

112 percent speed.    Each HPU on an SRB is

connected to both servoactuators on that SRB.  

One HPU serves as the primary hydraulic

source for the servoactuator, and the other HPU

serves as the secondary hydraulics for the

servoactuator. Each 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 operating hydraulic

pressure to both servoactuators of that SRB.

The APU 100 percent speed corresponds to

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

112 percent to 80,640 rpm.

The hydraulic pump speed is 3,600 rpm and

supplies hydraulic pressure of 3,050, plus or

minus 50, psi.    A high‐pressure relief valve

provides overpressure protection to the

hydraulic system and relieves at 3,750 psi.

The APUs/HPUs and hydraulic systems are

reusable for 20 missions.

Thrust Vector Control 

Each SRB has two hydraulic gimbal servoactua‐

tors:  one for rock and one for tilt.  The servoac‐

tuators provide the force and control to gimbal

the nozzle for thrust vector control.

The space shuttle ascent thrust vector control

portion of the flight control system directs the

thrust of the three shuttle main engines and the

two SRB nozzles to control shuttle attitude and

trajectory during liftoff and ascent.  Commands

from the guidance system are transmitted to the

ATVC drivers, which transmit signals propor‐

tional 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 servoac‐

tuator.

Each SRB servoactuator consists of four inde‐

pendent, two‐stage servovalves that receive

signals from the drivers.  Each servovalve con‐

trols one power spool in each actuator, which

positions an actuator ram and the nozzle to

control the direction of thrust.

The four servovalves in each actuator provide a

force‐summed majority voting arrangement to

position the power spool.    With four identical

commands to the four servovalves, the actuator

force‐sum action prevents a single erroneous

command from affecting power ram motion.  If

the erroneous command persists for more than a

predetermined time, differential pressure

sensing activates a selector valve to isolate and

remove the defective servovalve hydraulic

pressure, permitting the remaining channels and

servovalves to control the actuator ram spool.

Failure monitors are provided for each channel

to indicate which channel has been bypassed.  

An isolation valve on each channel provides the

capability of resetting a failed or bypassed chan‐

nel.

Each actuator ram is equipped with transducers

for position feedback to the thrust vector con‐

trol system.  Within each servoactuator ram is a
82 SHUTTLE REFERENCE DATA OCTOBER 2007

splashdown load relief assembly to cushion the

nozzle at water splashdown and prevent dam‐

age to the nozzle flexible bearing.

SRB Rate Gyro Assemblies 

Each SRB contains two RGAs, with each RGA

containing one pitch and one yaw gyro.   These

provide an output proportional to angular rates

about the pitch and yaw axes to the orbiter com‐

puters and guidance, navigation and control

system during first‐stage ascent flight in con‐

junction with the orbiter roll rate gyros until SRB

separation.   At SRB separation, a switchover is

made from the SRB RGAs to the orbiter RGAs.

The SRB RGA rates pass through the orbiter

flight aft multiplexers/demultiplexers to the

orbiter GPCs. The RGA rates are then

mid‐value‐selected in redundancy management

to provide SRB pitch and yaw rates to the user

software.    The RGAs are designed for

20 missions.

SRB Separation 

SRB separation is initiated when the three solid

rocket motor chamber pressure transducers are

processed in the redundancy management

middle value select and the head‐end chamber

pressure of both SRBs is less than or equal to

50 psi.  A backup cue is the time elapsed from

booster ignition.

The separation sequence is initiated, command‐

ing the thrust vector control actuators to the

null position and putting the main propulsion

system into a second‐stage configuration

(0.8 second from sequence initialization), which

ensures the thrust of each SRB is less than

100,000 pounds.    Orbiter yaw attitude is held

for four seconds, and SRB thrust drops to less

than 60,000 pounds.

The SRBs separate from the external tank

within 30 milliseconds of the ordnance firing

command.

The forward attachment point consists of a ball

(SRB) and socket (ET) held together by one bolt.  

The bolt contains one NSD pressure cartridge at

each end.    The forward attachment point also

carries the range safety system cross‐strap wir‐

ing connecting each SRB RSS and the ET RSS

with each other.

The aft attachment points consist of three sepa‐

rate struts:    upper, diagonal and lower.    Each

strut contains one bolt with an NSD pressure

cartridge at each end.    The upper strut also

carries the umbilical interface between its SRB

and the external tank and on to the orbiter.

There are four booster separation motors on

each end of each SRB.   The BSMs separate the

SRBs from the external tank.   The solid rocket

motors in each cluster of four are ignited by

firing redundant NSD pressure cartridges into

redundant confined detonating fuse manifolds.

The separation commands issued from the

orbiter by the SRB separation sequence initiate

the redundant NSD pressure cartridge in each

bolt and ignite the BSMs to effect a clean sepa‐

ration.

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

International Space Station elements (such as

the service module) into the proper orbit.
OCTOBER 2007 SHUTTLE REFERENCE DATA 83

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 manufac‐

tured 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.
84 SHUTTLE REFERENCE DATA OCTOBER 2007

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OCTOBER 2007 LAUNCH & LANDING 85

LAUNCH AND LANDING 

LAUNCH 

As with all previous space shuttle launches,

Discovery has several options to abort its ascent

if needed due to engine failures or other sys‐

tems problems.    Shuttle launch abort philoso‐

phy 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’s a partial loss of

main engine thrust late enough to permit reach‐

ing a minimal 105 by 85 nautical mile orbit with

the orbital maneuvering system engines. The

engines boost the shuttle to a safe orbital alti‐

tude 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 shuts down early and

there’s 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 Discovery on

STS‐120 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.
86 LAUNCH & LANDING OCTOBER 2007

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OCTOBER 2007 ACRONYMS/ABBREVIATIONS 87

ACRONYMS AND ABBREVIATIONS 

AA Antenna Assembly

AAA Avionics Air Assembly

ABC Audio Bus Coupler

AC Assembly Complete

ACBM Active Common Berthing Mechanism

ACO Assembly and Checkout Officer

ACS Atmosphere Control and Supply

ACSM Attitude Control System Moding

ACU Arm Computer Unit

ADO Adaptation Data Overlay

ADSEP Advanced Separation

ADVASC Advanced Astroculture

ADVASC‐GC Advanced Astroculture—Growth Chamber

AEA Antenna Electronics Assembly

AFD Aft Flight Deck

AJIS Alpha Joint Interface Structure

AKA Active Keel Assembly

APAS Androgynous Peripheral Attachment System

APCU Assembly Power Converter Unit

APDS Androgynous Peripheral Docking System

APFR Articulating Portable Foot Restraint

APM Attached Pressurized Module

APPCM Arm Pitch Plane Change Mode

APS Automated Payload Switch

AR Atmosphere Revitalization

ARCU American‐to‐Russian Converter Unit

ARIS Active Rack Isolation System

ARS Air Revitalization System

ASCR Assured Safe Crew Return

ATA Ammonia Tank Assembly

ATCS Active Thermal Control System

ATU Audio Terminal Unit

AUAI Assemble Contingency System/UHF Audio Interface

AVU Artificial Vision Unit

AVV Accumulator Vent Valve

BA Bearing Assembly

BBC Bus Bolt Controller

BC Bus Controller
88 ACRONYMS/ABBREVIATIONS OCTOBER 2007

BCDU Battery Charge/Discharge Unit

BCU Backup Controller Unit  

BDU Backup Drive Unit

BG Beta Gimbal

BGA Beta Gimbal Assembly

BGDTS Beta Gimbal Deployment Transition Structure

BGHS Beta Gimbal Housing Subassembly

BIT Built‐In Test

BITE Built‐In Test Equipment

BMRRM Bearing Motor and Roll Ring Module

BONEMAC Bone Marrow Macrophages in Space

BPSMU Battery Powered Speaker Microphone Unit

BRS Bottom Right Side

BSP Baseband Signal Processor

BTS Bolt Tight Switch

C&C Command and Control

C&DH Command and Data Handling

C&M Control and Monitor

C&T Communication and Tracking

C&W Caution and Warning

C/A‐code Coarse/Acquisition‐code

C/L Crew Lock

CA Control Attitude

CAS Common Attach System

CBM Common Berthing Mechanism

CBOSS Cellular Biotechnology Operating Science System

CCAA Common Cabin Air Assembly

CCASE Commercial Cassette Experiment

CCD Cursor Control Device

CCMS Concentric Cable Management System

CCS Communication and Control System

CCTV Closed‐Circuit Television

CDDT Common Display Development Team

CDRA Carbon Dioxide Removal Assembly

CDS Command and Data Software

CETA Crew and Equipment Translation Aid

CEU Control Electronics Unit

CFA Circular Fan Assembly

CGBA Commercial Generic Bioprocessing Apparatus

CHeCS Crew Health Care System

CHX Condensing Heat Exchanger
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 89

CID Circuit Interrupt Device

CIOB Cargo Integration and Operations Branch

CLA Camera and Light Assembly

CLPA Camera Light and Pan/Tilt Assembly

CMG Control Moment Gyroscope

CMG‐TA Control Moment Gyroscope‐Thruster Assist

CO2 Carbon Dioxide

COAS Crew Optical Alignment Sight

COR Communication Outage Recorder

COTS Commercial‐Off‐The‐Shelf

CP Cold Plate

CPCG‐H Commercial Protein Crystal Growth‐High

CR Change Request

CRES Corrosion Resistant Steel

CRIM Commercial Refrigerator Incubator Module

CRIM‐M Commercial Refrigerator Incubator Module‐Modified

CRPCM Canadian Remote Power Controller Module

CSA Computer Systems Architecture

CSA‐CP Compound Specific Analyzer‐Combustion Products

CSCI Computer Software Configuration Item

CSM Cargo Systems Manual

CSS Crew Support Station

CTB Cargo Transfer Bag

CVIU Common Video Interface Unit

CVT Current Value Table

CVV Carbon Dioxide Vent Valve

CWC Contingency Water Collection

DAA Docked Air‐to‐Air

DAG1 Docked A/G 1

DAIU Docked Audio Interface Unit

DAP Digital Autopilot

dc direct current

DC Docking Compartment

DCP Display and Control Panel

DCSU Direct Current Switching Unit

DDCU DC‐to‐DC Converter Unit

DDCU‐CP DC‐to‐DC Converter Unit‐Cold Plate

DDCU‐E External DDCU

DDCU‐HP DC‐to‐DC Converter Unit‐Heat Pipe

DDCU‐I Internal DDCU

DFL Data Format Load
90 ACRONYMS/ABBREVIATIONS OCTOBER 2007

DLA Drive Locking Assembly

DMCU Docking Mechanism Control Unit

DMS‐R Data Management System‐Russian

dp/dt delta pressure/delta time

DPA Digital Preassembly

DPS Data Processing System

DTO Development Test Objective

DTV Digital Television

E/L Equipment Lock

E‐Stop Emergency Stop

EACP EMU Audio Control Panel

EAIU EMU Audio Interface Unit

EAS Early Ammonia Servicer

EATCS External Active Thermal Control Subsystem

ECLSS Environmental Control and Life Support System

ECU Electronics Control Unit

ED Engagement Drive

EDDA External Maneuvering Unit Don/Doff Assembly

EE End Effector

EEATCS Early External Active Thermal Control System

EET Experiment Elapsed Time

EETCS Early External Thermal Control System

EFGF Electrical Flight‐releasable Grapple Fixture

EGIL Electrical Generation and Integrated Lighting Systems Engineer

EIA Electrical Interface Assembly

EMPEV Emergency Manual Pressure Equalization Value

EMU Extravehicular Mobility Unit

EOA EVA Ohmmeter Assembly

EPCE Electrical Power Consuming Equipment

EPG Electrical Power Generator

EPS Electrical Power System

ER Edge Router

ESA External Sampling Adapter

ESP External Stowage Platform

ESSMDM Enhanced Space Station Multiplexer/Demultiplexer

ESU End Stop Unit

ETCS External Thermal Control System

ETI Elapsed Time Indicator

ETRS EVA Temporary Rail Stop

ETSD EVA Tool Storage Device

ETVCG External Television Cameras Group
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 91

EUE Experiment Unique Equipment

EV Extravehicular

EV‐CPDS Extravehicular‐Charged Particle Directional Spectrometer

EVA Extravehicular Activity

EVR Extravehicular Robotics

EVSU External Video Switching Unit

EXPRESS EXpedite the PRocessing of Experiments to the Space Station

EXT Experimental Terminal

EWIS External Wireless Instrumentation System

FAWG Flight Assignment Working Group

FC Firmware Controller

FCC Flat Controller Circuit

FCT Flight Control Team

FCV Flow Control Valve

FD Flight Day

FDA Fault Detection Annunciation

FDIR Failure, Detection, Isolation and Recovery

FDS Fire Detection and Suppression

FET Field Effect Transistor

FGB Functional Cargo Block

FHRC Flex Hose Rotary Coupler

FI Fault Isolator

FPU Fluid Pumping Unit

FQDC Fluid Quick Disconnect Coupling

FRD Flight Requirements Document

FRGF Flight Releasable Grapple Fixture

FSE Flight Support Equipment

FSS Fluid System Servicer

FWCI Firmware Configuration Item

GAS Get Away Special

GC Growth Cell

GCA Growth Cell Assembly

GFE Government‐Furnished Equipment

GFI Ground Fault Interrupter

GJOP Generic Joint Operations Panel

GLONASS GLObal Navigational Satellite System

GN&C Guidance, Navigation and Control

GNC Guidance Navigation Computer

GPC General Purpose Computer

GPRV Gas Pressure regulating Valve
92 ACRONYMS/ABBREVIATIONS OCTOBER 2007

GPS Global Positioning System

GUI Graphical User Interface

H2 Hydrogen

HAB Habitat Module

HC Hand Controller

HCA Hollow Cathode Assembly

HCOR High‐Rate Communication Outage Recorder

HDR High Data Rate

HDRL High Date Rate Link

HEPA High Efficiency Particulate Air

HGA High Gain Antenna

HHL Handheld Lidar

HP Heat Pipe

HPGT High Pressure Gas Tank

HRF Human Research Facility

HRF‐PUF‐DK Human Research Facility Puff Data Kit

HRF‐Res Human Research Facility Resupply

HRFM High Rate Frame Multiplexer

HRM High Rate Modem

HRS Hand Reaction Switch

I/F Interface

I/O Input/Output

IAC Internal Audio Controller

IAS Internal Audio Subsystem

IATCS Internal Active Thermal Control System

ICC Integrated Cargo Carrier

ICOM Intercom

IDA Integrated Diode Assembly

IDRD Increment Definition Requirements Document

IEA Integrated Equipment Assembly

IFHX Interface Heat Exchanger

IFI Item for Investigation

IFM In‐flight Maintenance

IMCA Integrated Motor Control Assembly

IMCS Integrated Mission Control System

IMU Impedance Matching Unit

IMV Intermodule Ventilation  

INCO   Instrumentation and Communication Officer

INSTM Instrumentation

INT Internal

INTSYS Internal Systems
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 93

IOC Input/Output Controller

IOCU Input/Output Controller Unit

IP International Partner

IRU In‐Flight Refill Unit

ISA Internal Sampling Adapter

ISIS International Space Station Interface Standard

ISL Integrated Station LAN

ISO Inventory and Stowage Officer

ISPR International Standard Payload Rack

ISS International Space Station

ISSPO International Space Station Program Office

ISSSH International Space Station Systems Handbook

IT Integrated Truss

ITCS Internal Thermal Control System

ITS Integrated Truss Segment

IUA Interface Umbilical Assembly

IV Intravehicular  

IVA Intravehicular Activity

IVSU Internal Video Switch Unit

IWIS Internal Wireless Instrumentation System

JAXA Japan Aerospace Exploration Agency

JEM Japanese Experiment Module

JEU Joint Electronic Unit

KSC Kennedy Space Center

kW Kilowatt

LA Launch Aft

Lab Laboratory  

LAN Local Area Network

LB Local Bus

LB‐RWS RWS Local Bus

LCA Lab Cradle Assembly

LCC Launch Commit Criteria

LCD Liquid Crystal Display

LDI Local Data Interface

LDR Low Data Rate

LDU Linear Drive Unit

LED Light‐Emitting Diode

LEE Latching End Effector

LEU LEE Electronic Unit

LFDP Load Fault Detection Protection
94 ACRONYMS/ABBREVIATIONS OCTOBER 2007

LGA Low Gain Antenna

LH2 Liquid Hydrogen

LLA Low Level Analog

LMC Lightweight Multipurpose Carrier

LO2 Liquid Oxygen

LON Launch On Need

LT Low Temperature

LTA Launch to Activation

LTL Low Temperature Loop

LTU Load Transfer Unit

LVLH Local Vertical Local Horizontal

MA Mechanical Assembly

MAM Manual Augmented Role

MBA Motorized Bolt Assembly  

MBE Metal Bellows Expander

MBM Manual Berthing Mechanism

MBS Mobile Remote Service Base System

MBSU Main Bus Switching Unit

MC Midcourse Correction

MCA Major Constituent Analyzer

MCAS MBS Common Attach System

MCC Mission Control Center

MCC‐H Mission Control Center‐Houston

MCC‐M Mission Control Center‐Moscow

MCDS Multifunction CRT Display System

MCS Motion Control System

MCU MBS Computer Unit

MDA Motor Drive Assembly

MDL Middeck Locker

MDM Multiplexer/Demultiplexer

MED OPS Medical Operations

MEPS Microencapsulation Electrostatic Processing System

MEPSI Micro‐Electromechanical System‐based Pico Satellite Inspector

MER Mission Evaluation Room

MET Mission Elapsed Time

METOX Metal Oxide

MFCV Manual Flow Control Valve

MHS MCU Host Software

MIL‐STD Military Standard

MILA Mode Indicating Light Assembly

MIP Mission Integration Plan
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 95

MISSE Materials International Space Station Experiment

MLI Multi‐Layer Insulation

MM/OD Micrometeoroid/Orbital Debris

MMT Mission Management Team

MOD Mission Operations Directorate

MPEV Manual Pressure Equalization Valve

MPLM Multipurpose Logistics Module

MPM Manipulator Positioning Mechanism

MRL Manipulator Retention Latch

MRS Mobile Remote Servicer

MRSBS Mobile Remote Servicer Base System

MSD Mass Storage Device

MSFC Marshall Space Flight Center

MSG Microgravity Science Glovebox

MSS Mobile Servicing System

MT Mobile Transporter

MTCL Mobile Transporter Capture Latch

MTL Moderate Temperature Loop

MTS Module‐to‐Truss Segment

MTSAS Module‐to‐Truss Segment Attachment System

MTWsN Move to Worksite Number

Module‐to‐Truss Segment Attachment System

N

2 Nitrogen

N. mi. Nautical mile

NASA   National Aeronautics and Space Administration

NCC Nominal Corrective Combination burn

NCG Non Condensable Gas

NCS Node Control Software

NCU Network Control Unit

NET No Earlier Than

NIA Nitrogen Interface Assembly

NiH

2 Nickel Hydrogen

NIV Nitrogen Introduction Valve

NSI NASA Standard Initiator

NSTS National Space Transportation System

NTA Nitrogen Tank Assembly O2 Oxygen

OCA Orbital Communications Adapter

OCAD Operational Control Agreement Document

OCJM Operator‐Commanded Joint Position Mode

OCPM Operator‐Commanded POR Mode
96 ACRONYMS/ABBREVIATIONS OCTOBER 2007

OCS Operations and Control Software

ODIN Orbital Design Integration System

ODS Orbiter Docking System

OI Operational Increment

OIU Orbiter Interface Unit

OIV Oxygen Isolation Valve

OMI On‐Orbit Maintainable Item

OMS Orbital Maneuvering System

OPCGA Observable Protein Crystal Growth Apparatus

OPP OSVS Patch Panel

Ops Operations

OPS LAN Operations Local Area Network

ORBT Optimized RBar Targeting Technique

ORCA Oxygen Recharge Compressor Assembly

ORU Orbital Replacement Unit

OSE Orbiter Support Equipment

OSO Operations Support Officer

OSVS Orbiter Space Vision System

OTD ORU Transfer Device

OV Orbiter Vehicle

P&S Pointing and Support

P‐Code Precision Code

P/L Payload

P/TV Photo/Television  

P3/P4 Port 3/Port 4

PAS Payload Attach System

PBA Portable Breathing Apparatus

PC Personal Computer

PCA Pressure Control Assembly

PCAM Protein Crystallization Apparatus for Microgravity

PCBM Passive Common Berthing Mechanism

PCC Power Converter Controller

PCG‐STES Protein Crystal Growth‐Single Thermal Enclosure System

PCMCIA Personal Computer Memory Card International Adapter

PCP Pressure Control Panel

PCR Portable Computer Receptacle  

PCS Portable Computer System

PCT Post‐Contact Thrusting

PCU Plasma Connector Unit

PCVP Pump and Control Valve Package

PDGF Power and Data Grapple Fixture
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 97

PDI Payload Data Interface

PDIP Payload Data Interface Panel

PDRS Payload Deployment and Retrieval System

PDTA Power Data Transfer Assembly

PDU Power Drive Unit

PEHG Payload Ethernet Hub Gateway

PF Payload Forward  

PFCS Pump Flow Control Subassembly

PFE Portable Fire Extinguisher

PFMC Pump/Fan Motor Controller

PFR Portable Foot Restraint  

PGBA‐S Plant Generic Bioprocessing Apparatus‐Stowage

PGSC Portable General Support Computer

PGT Pistol Grip Tool

PHALCON Power, Heating, Articulation, Lighting, and Control Officer

PJPAM Pre‐stored Joint Position Autosequence Mode

PLB Payload Bay

PM Pump Module

PMA Pressurized Mating Adapter

PMCU Power Management Control Unit

PMDIS Perceptual Motor Deficits In Space

PMP Payload Mounting Panel

POA Payload/ORU Accommodation

POC Portable Onboard Computer  

POR Point of Reference

POST Power ON Self‐Test

PP Planning Period

PPA Pump Package Assembly

PPAM Pre‐stored POR Autosequence Mode

ppO2 partial pressure of oxygen

PPRV Positive Pressure Relief Valve

PPT Precipitate  

PRD Payload Retention Device

PRLA Payload Retention Latch Assembly

Prox‐Ops Proximity Operations

PSN Power Source Node

PSP Payload Signal Processor  

PTB Payload Training Buffer

PTCS Passive Thermal Control System

PTR Port Thermal Radiator

PTU Pan/Tilt Unit

PV Photovoltaic
98 ACRONYMS/ABBREVIATIONS OCTOBER 2007

PVCA Photovoltaic Controller Application

PVCE Photovoltaic Controller Element

PVCU Photovoltaic Controller Unit

PVM Photovoltaic Module

PVR Photovoltaic Radiator

PVRGF Photovoltaic Radiator Grapple Fixture

PVTCS Photovoltaic Thermal Control System

PWP Portable Work Platform

PWR Portable Water Reservoir

PYR Pitch Yaw Roll

QD Quick Disconnect

R/F Refrigerator/Freezer

R&R Removal and Replacement

RACU Russian‐to‐American Converter Unit

RAIU Russian Audio Interface Unit

RAM Random Access Memory

RAMV Rheostat Air Mix Valve

RB Radiator Beam

RBB Right Blanket Box

RBI Remote Bus Isolator

RBVM Radiator Beam Valve  

RCC Reinforced Carbon‐Carbon

RCS Reaction Control System

RDA Retainer Door Assembly

RF Radio Frequency

RFCA Rack Flow Control Assembly

RFG Radio Frequency Group

RGA Rate Gyro Assemblies

RHC Rotational Hand Controller

RHX Regenerative Heat Exchanger

RIC Rack Interface Controller

RJMC Rotary Joint Motor Controller

RMS Remote Manipulator System

ROBO Robotics Operations Support Officer  

ROS Russian Orbital Segment

RP Receiver/Processor  

RPC Remote Power Controller

RPCM Remote Power Controller Module

RPDA Remote Power Distribution Assembly

RPM Rbar Pitch Maneuver

RPOP Rendezvous and Proximity Operations Program
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 99

RS Russian Segment

RSC RMS Sideview Camera

RSP Resupply Stowage Platform

RSR Resupply Stowage Rack

RSTS Rack Standalone Temperature Sensor

RSU Roller Suspension Unit

RT Remote Terminal

RT‐Box Reaction Time Box

RTAS Rocketdyne Truss Attachment System

RTD Resistive Thermal Device

RTL Ready to Latch

RWS Robotic Workstation

S Starboard

S&M Structures and Mechanisms

S3/S4 Starboard 3/Starboard 4

SA Solar Array

SABB Solar Array Blanket Box

SAGE Space Arabidoposis Genomics Experiment

SARJ Solar Alpha Rotary Joint

SARJ_C SARJ Controller

SARJ_M SARJ Manager

SASA S‐band Antenna Support Assembly

SAW Solar Array Wing

SCA Switchgear Controller Assembly

SCI Signal Conditioning Interface

SCU Service and Cooling Umbilical

SD Smoke Detector

SDO Solenoid Driver Output

SDS Sample Delivery System

SEM Shunt Electronics Module

SEPS Secondary Electrical Power Subsystem

SFCA System Flow Control Assembly

SFU Squib Firing Unit

SGANT Space‐to‐Ground Antenna

SHOSS Spacehab Oceaneering Space System

SHOT Space Hardware Optimization Technology

SIGI Space Integrated Global Positioning System/Inertial Navigation System

SJRM Single Joint Rate Mode

SLDP Spacelab Data Processing

SLP Spacelab Logistics Pallet

SM Service Module
100 ACRONYMS/ABBREVIATIONS OCTOBER 2007

SMCC Shuttle Mission Control Center

SMDP Service Module Debris Panel

SOC State of Charge

SOV Shutoff Valve

SPCE Servicing Performance and Checkout Equipment

SPD Spool Positioning Device

SPDA Secondary Power Distribution Assembly

SPDM Special Purpose Dexterous Manipulator

SPG Single‐Point Ground

SRMS Shuttle Remote Manipulator System

SSAS Segment‐to‐Segment Attach System

SSBA Space Station Buffer Amplifier

SSC Station Support Computer

SSMDM Space Station Multiplexer/Demultiplexer

SSOR Space‐to‐Space Orbiter Ratio

SSP Standard Switch Panel

SSPTS Station‐to‐Shuttle Power Transfer System  

SSRMS Space Station Remote Manipulator System

SSSH Space Shuttle Systems Handbook

SSSR Space‐to‐Space Station Radio

SSU Sequential Shunt Unit

STCR Starboard Thermal Control Radiator

STES Single Thermal Enclosure System

STR Starboard Thermal Radiator

SVS Space Vision System

TA Thruster Assist

TAA Triaxial Accelerometer Assembly

TAH Tray Actuation Handle

TBA Trundle Bearing Assembly

TC Terminal Computer

TCCS Trace Contaminant Control Subassembly

TCCV Temperature Control and Check Valve

TCS Trajectory Control Sensor

TD Translation Drive

TDRS Tracking and Data Relay Satellite

TDRSS Tracking and Data Relay Satellite System

TEA Torque Equilibrium Attitude

TFR Translation Foot Restraint

THC Temperature and Humidity Control

THOR Thermal Operations and Resources Officer

TI Terminal Phase Initiation
OCTOBER 2007 ACRONYMS/ABBREVIATIONS 101

TORF Twice Orbital Rate Flyaround

TORU Teleoperator Control Mode

TORVA Twice Orbital Rate +Rbar to +Vbar Approach

TPL Transfer Priority List

TRAC Test of Reaction and Adaption Capabilities

TRC Transmitter Receiver Controller

TRRJ Thermal Radiator Rotary Joint

TSP Twisted Shielded Pair

TTCR Trailing Thermal Control Radiator

TUS Trailing Umbilical System

TVIS Treadmill Vi

bration Isolation System

TWMV Three‐Way Mixing Valve

UB User Bus  

UCCAS Unpressurized Cargo Carrier Attach System

UDG User Data Generation

UF Utilization Flight

UHF Ultrahigh Frequency

UIA Umbilical Interface Assembly

ULCAS Unpressurized Logistics Carrier Attach System

UIP Utility Interface Panel

ULF Utilization Logistics Flight  

UMA Umbilical Mechanism Assembly

UOP Utility Outlet Panel

USA United Space Alliance  

USL U.S. Laboratory

USOS United States On‐Orbit Segment

UTA Utility Transfer Assembly

VAJ Vacuum Access Jumper

VBSP   Video Baseband SignalProcessor

VCP Video Camera Port

VCSA Video Camera Support Assembly  

VDS Video Distribution System

VDU Video Distribution Unit

VES Vacuum Exhaust System

VGS Video Graphics Software

VRCV Vent/Relief Control Valve

VRIV Vent/Relief Isolation Valve

VRS VES Resource System

VRV Vent/Relief Valve

VSC Video Signal Converter
102 ACRONYMS/ABBREVIATIONS OCTOBER 2007

VSSA Video Stanchion Support Assembly

W/S Worksite

WETA WVS External Transceiver Assembly

WHS Workstation Host Software

WIF Worksite Interface

WRM Water Recovery Management

WS Water Separator

WVA Water Vent Assembly

XPOP X‐axis Pointing Out of Plane

ZCG‐SS Zeolite Crystal Growth—Sample Stowage

ZSR Zero‐g Stowage Rack
OCTOBER 2007 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 (DVB)‐compliant Integrated Receiver

Decoder (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 mis‐

sion 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 on‐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:

Status Reports 

Status reports on launch countdown and mis‐

sion progress, on‐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.

Briefings 

A mission press briefing schedule will be issued

before launch. The updated NASA television

schedule will indicate when mission briefings

are planned.

More Internet Information 

Information on the International Space Station

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 OCTOBER 2007

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OCTOBER 2007 PUBLIC AFFAIRS CONTACTS 105

PUBLIC AFFAIRS CONTACTS 

HEADQUARTERS 

WASHINGTON, DC 

Michael Braukus

Public Affairs Officer

International Partners

202‐358‐1979

michael.j.braukus@nasa.gov

Katherine Trinidad

Public Affairs Officer

Space Operations

202‐358‐3749

katherine.trinidad@nasa.gov

John Yembrick

Public Affairs Officer

Space Operations

202‐358‐0602

john.yembrick-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

Kylie Clem

Public Affairs Specialist

Mission Operations Directorate and Shuttle Crew

281‐483‐5111

kylie.s.clem@nasa.gov

Nicole Cloutier‐Lemasters

Public Affairs Specialist

Space Station Crew

281‐483‐5111

nicole.cloutier-1@nasa.gov

KENNEDY SPACE CENTER 

CAPE CANAVERAL, FLORIDA 

Allard Beutel

News Chief

321‐861‐4769

allard.beutel@nasa.gov

George Diller

Public Affairs Specialist

Space Shuttle

321‐867‐2468

george.h.diller@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
106 PUBLIC AFFAIRS CONTACTS OCTOBER 2007

June Malone

Public Affairs Specialist

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 

MISSISSIPPI 

Linda Theobald

Public Affairs Specialist

228‐688‐3249

linda.l.theobald@nasa.gov

Paul Foerman

News Chief

228‐688‐1880

paul.foerman-1@nasa.gov

Rebecca Strecker

Public Affairs Specialist

228‐688‐3346

rebecca.a.strecker@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

DRYDEN FLIGHT RESEARCH CENTER 

CALIFORNIA 

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

Katherine Martin

Public Affairs Specialist

216‐433‐2406

katherine.martin@nasa.gov

LANGLEY RESEARCH CENTER 

HAMPTON, VIRGINIA 

Marny Skora

Head, News Media Office

757‐864‐3315

marny.skora@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
107 PUBLIC AFFAIRS CONTACTS JULY 2007

UNITED SPACE ALLIANCE 

Mike Curie

Space Program Operations Contract

Houston Operations

281‐483‐9251

321‐861‐3805

michael.j.curie@usa-spaceops.com

Tracy Yates

Florida Operations

321‐861‐3956

tracy.e.yates@usa-spaceops.com

BOEING 

Ed Memi

Media Relations

Boeing NASA Systems

281‐226‐4029

edmund.g.memi@boeing.com
108 PUBLIC AFFAIRS CONTACTS OCTOBER 2007

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