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Updated May 16, 2001

Continuing the Human 

Presence in Space

STS - 111
STS-111

Table of Contents 

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

Mission Objectives ................................................................................................ 13 

Crewmembers ......................................................................................................... 14 

Rendezvous and Docking ..................................................................................... 19 

Spacewalk 

STS-111 Extravehicular Activity ............................................................................... 23 

Payloads 

Payload Overview .................................................................................................... 30 

Mobile Remote Servicer Base System...................................................................... 32 

Multi-Purpose Logistics Module ............................................................................... 36 

Experiments 

Science Overview .................................................................................................... 39 

DSOs and DTOs ...................................................................................................... 42 

Ram Burn Observations ........................................................................................... 45 

Shuttle Reference Data 

Shuttle Abort History ................................................................................................ 46 

Shuttle Abort Modes ................................................................................................ 48 

Shuttle Rendezvous Maneuvers .............................................................................. 52 

Shuttle Solid Rocket Boosters .................................................................................. 53 

Shuttle Super-lightweight Tank ................................................................................ 60 

Acronyms and Abbreviations ............................................................................... 61 

Media Assistance ................................................................................................... 73 

Media Contacts ...................................................................................................... 75 
STS-111

Overview 

New Station Crew, Three Spacewalks Set for STS-111 

A new International Space Station crew, the fifth flight of an Italian-built Multi-Purpose 

Logistics Module (MPLM) and three spacewalks are major elements of the STS-111 flight 

of Endeavour. 

The STS-111 crew, from left to right, Philippe Perrin, Paul Lockhart, Ken Cockrell 

and Franklin Chang-Diaz 

Ken Cockrell is making his third flight as commander and his fifth on a shuttle. He was 

commander on STS-80, the longest shuttle flight to date, on Columbia in November and 

December 1996. He also commanded STS-98 in February 2001, a mission that 

successfully delivered and installed the U.S. laboratory Destiny on the International Space 

Station. He served as pilot on STS-69 on Endeavour in September 1995 and as a mission 

specialist on STS-56, a scientific flight on Discovery in April 1993. 

Paul Lockhart (Lt. Col., USAF), making his first flight into space, is Endeavour’s pilot. Two 

mission specialists round out the orbiter crew. Franklin Chang-Diaz will be making a recordtying seventh flight into space. Chang-Diaz has six previous spaceflights to his credit: 

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STS-61C in January 1986, STS-34 in October 1989, STS-46 in August 1992, STS-60 in 

February 1994, STS-75 in February and March 1996, and STS-91 in June 1998. Philippe 

Perrin, a colonel in the French Air Force representing CNES, the French Space Agency, is 

making his first spaceflight. 

The space station’s Expedition 5 crew, pictured above from left to right, is Russian 

Commander Valery Korzun, Astronaut Peggy Whitson and Cosmonaut Sergei Treschev. 

Crewmembers will extend a continuous human presence aboard the space station that 

began when the Expedition 1 crew arrived on Nov. 2, 2000. 

They will replace the Expedition 4 crew, Russian Commander Yury Onufrienko and 

Astronauts Carl Walz and Dan Bursch. That crew was brought to the station on 

Endeavour’s STS-108 flight launched Dec. 5, 2001, and will return to Earth on Endeavour. 

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About 40 hours after its launch, Endeavour is scheduled to dock with the International 

Space Station. After hatches are opened, a welcoming ceremony and a safety briefing will 

be held for the new arrivals. Crew transfer operations begin shortly after docking, as do 

preparations for the first spacewalk. 

A crewmember’s transfer officially occurs when a new arrival’s custom seat liner is installed 

in the Soyuz crew return vehicle attached to the space station. Treschev and Walz will 

swap out seat liners on docking day, while Whitson and Bursch and then Korzun and 

Onufrienko will change out liners the next day. 

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Leonardo, shown in the rear of Discovery’s payload bay during shuttle mission 

STS-102 in March 2001 

The Italian MPLM named Leonardo is making its third visit to the space station. It first flew 

on STS-102 in March 2001 and again on STS-105 in August 2001. It is one of three 

virtually identical modules that serve as pressurized moving vans, bringing equipment and 

supplies to the space station. 

A sister module named Raffaello has visited the station twice, on STS-100 in April 2001 

and on STS-108 in December 2001. 

Leonardo will be lifted out of Endeavour’s payload bay and attached directly to the station’s 

Unity node for the unloading of its cargo. The MPLM brings to the station contents of eight 

resupply stowage racks, five resupply stowage platforms, two international standard 

payload racks and two scientific racks for the U.S. laboratory Destiny. One of the scientific 

racks is EXPRESS (for Expedite the Processing of Experiments to the Space Station) Rack 

No. 3. The other is the Microgravity Science Glovebox. 

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ISS crewmember Jim Voss works inside the Destiny lab, as shuttle astronaut 

Scott Horowitz enters the lab during STS-105 

Destiny, installed on the STS-98 mission of Atlantis in February 2001, has slots for 24 of 

the interchangeable racks (six on the top, six on the bottom and six on each side). Eleven 

are systems racks, and one slot has Destiny ’s 20-inch-diameter, optical-quality window. 

Remaining slots are for scientific racks. 

The MPLM will be put back into the cargo bay and returned to Earth for refurbishment and 

reuse on a subsequent mission. The MPLM is valued at $150 million. 

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STS-111 spacewalker Philippe Perrin practices in a ground-based mockup of the 

Quest Airlock 

The mission’s spacewalks will be conducted from the Joint Airlock Quest of the space 

station. Chang-Diaz and Perrin will perform all three. 

During the first, on the crew’s flight day five, Korzun, assisted by Walz, will operate the 

station robotic arm to move spacewalkers around while Cockrell will operate the shuttle’s 

arm. The shuttle arm is used to provide camera views for the station arm operator. Lockhart 

will provide intravehicular support, providing guidance and advice to the spacewalkers to 

help them through their tasks and keep them on their timeline. 

Chang-Diaz will remove a Power and Data Grapple Fixture (PDGF) from a carrier in the 

payload bay and both he and Perrin will install it on the P6 truss. This PDGF will be used 

during the 13A.1 stage to relocate the P6 truss structure to its final location on the station. 

The spacewalkers will then remove Service Module Debris Panel shields and install them 

on a temporary stowage location on Pressurized Mating Adapter 1 (PMA 1). These will be 

removed later by the station crew and installed at their final locations on the Zvezda 

module. Finally, they will remove thermal blankets from the Mobile Remote Servicer Base 

System (MBS) after it has been grappled and supplied with power by the station arm. The 

MBS will be unberthed from the payload bay by the Canadarm2 at the end of the first 

spacewalk, activated overnight by ground controllers, and latched to the Mobile Transporter 

the next morning. 

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Astronauts Philippe Perrin, foreground, and Franklin Chang-Diaz practice EVA 

tasks in the Neutral Buoyancy Lab in Houston 

The second spacewalk, on flight day seven, will focus on connecting video/data cables and 

power umbilicals to the MBS and bolting it to its Mobile Transporter base. Spacewalkers 

also will deploy the POA (Payload ORU—On-Orbit Replaceable Unit—Accommodation), a 

fixed end effector identical to the one on the Canadarm2 to hold large payloads being 

transported along the truss structure, and will relocate a camera on the MBS. Neither the 

station arm nor the shuttle arm will be needed for the second spacewalk. 

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During the third spacewalk, on flight day nine, Chang-Diaz and Perrin will replace the wrist 

roll joint of the station’s Canadarm2 with a backup unit brought into space aboard 

Endeavour. The shuttle arm will be used extensively on the third spacewalk to transport 

Perrin from worksite to worksite. 

Handover briefings between Expedition 4 and Expedition 5 crewmembers continue 

throughout docked operations. A minimum of 12 hours of handover briefings is required for 

each Expedition 5 crewmember. 

Logistics operations also continue throughout much of the docked period. Before the MPLM 

is returned to Endeavour’s cargo bay, crewmembers will load Leonardo with unneeded 

equipment and trash from the station for return to Earth. 

Leonardo is to be unberthed from the station and returned to Endeavour’s cargo bay on 

flight day 10. 

Pilot Paul Lockhart in the right-hand simulator seat 

at the Johnson Space Center, Houston 

The shuttle will undock from the station the next day. Lockhart will do a one-revolution 

flyaround of the station before Endeavour leaves the area. 

Endeavour is scheduled to land at Kennedy Space Center two days later. 

STS-111 is the 14th space shuttle mission in support of the International Space Station, the 

18th mission of Endeavour and the 110th flight in shuttle program history. 

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Day-by-day summary of the mission: 

Day 1 – Launch 

Activities consist primarily of post insertion, APCU activation and activating the MPLM shell 

heaters. 

Day 2 – Equipment Checkout, Rendezvous Preparations 

Crewmembers will check out the Docking Mechanism, the orbiter-based rendezvous tools 

and systems, the EMUs (spacesuits), make preparations for transfer, check out the 

shuttle’s robotic arm, and use its cameras to do a payload bay survey. 

Day 3 – Rendezvous and Docking 

ISS rendezvous, culminating in docking with the station, is the day’s major activity. The 

shuttle will dock to the PMA 2 on the forward end-cone of the U.S. laboratory Destiny. After 

docking and Orbiter Docking System (ODS) preparation, the crew will open the ODS hatch 

and the ISS and shuttle crews will meet for the first time in space. The ISS crew will give a 

safety briefing to the shuttle crew. Spacewalking equipment and one of the custom seat 

liners for the Soyuz crew return vehicle will be transferred later in the day. 

Day 4 – Crew Transfer, MPLM Installation 

The two remaining Expedition 5 crewmembers will transfer their seat liners to the Soyuz. 

The crew also will check the MPLM environment, and install, activate and outfit the 

vestibule, and prepare for entering the MPLM. Some equipment and supplies will be 

transferred from the middeck to the station and other cargo will be moved from the station 

to the shuttle for return to Earth. 

Day 5 – Spacewalk 1, Transfer 

Flight day five consists of MPLM transfer preparations and handover operations between 

ISS Expedition 4 and 5 commanders and the flight engineers. The first spacewalk is 

performed to install the P6 PDGF, install the meteoroid/debris shields on the PMA 1, 

remove the MBS thermal blankets and unberth the MBS from the payload bay. Flight 

controllers will activate the MBS from the ground overnight in preparation for the next day’s 

operations. 

Day 6 – MBS Installation, Transfer 

The day is reserved for MBS installation and middeck and MPLM transfer. 

Day 7 – Spacewalk 2, Transfer 

During this transfer and spacewalk day, EVA 2 will connect the MBS utilities, fully secure 

the MBS to the MT, deploy the MBS POA and relocate the camera. Middeck and MPLM 

transfer will continue. 

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Day 8 – MBS Checkout, Transfer 

MBS checkout and transfer operations from both the MPLM and the shuttle’s middeck are 

the focus of this day. 

Day 9 – Spacewalk 3 

During the third spacewalk of the mission, Canadarm2’s wrist roll joint will be replaced. This 

spacewalk was added to the mission in late March. 

Day 10 – MPLM Return to Endeavour 

Preparations for Leonardo’s return to the shuttle’s cargo bay include crew egress and 

closeout, atmosphere conditioning, deactivation and utility disconnect. That done, 

Endeavour’s robotic arm will grapple and unberth the MPLM from the station and return it to 

Endeavour’s cargo bay. Once there, crewmembers will turn on its shell heaters. Middeck 

transfer will continue. 

Day 11 – Farewell, Undocking 

The departing crewmembers will bid Expedition 5 farewell. After hatches are closed and 

other preparations complete, Endeavour detaches itself from the International Space 

Station. Pilot Lockhart will fly Endeavour around the station before moving the orbiter away 

to begin its return to Earth. 

Day 12 – Entry Preparations 

The shuttle crew prepares for entry, checking out flight control surfaces and reaction control 

system jets, as well as stowing items for Endeavour’s return to Earth. 

Day 13 – Landing 

Endeavour is scheduled to land at Kennedy Space Center. 

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Crew

Commander: Kenneth D. Cockrell

Pilot: Paul S. Lockhart

Mission Specialist 1: Philippe Perrin

Mission Specialist 2: Franklin R. Chang-Diaz

(Up) Mission Specialist 3: Peggy A. Whitson

(Up) Mission Specialist 4: Valery G. Korzun

(Up) Mission Specialist 5: Sergei Y. Treschev

(Dn) Mission Specialist 3: Carl E. Walz 

(Dn) Mission Specialist 4: Daniel W. Bursch 

(Dn) Mission Specialist 5: Yury I. Onufrienko 

Launch

Orbiter: Endeavour (OV-105)

Launch Site: Kennedy Space Center Launch Pad 39A

Launch Date: May 30, 2002

Launch Window: TBA

Altitude: 122 Nautical Miles

Inclination: 51.6 Degrees

Duration: 11 Days 18 Hrs. 22 Min.

Vehicle Data

Shuttle Liftoff Weight: 4,518,239 lbs.

Orbiter/Payload Liftoff Weight: 256,884 lbs.

Orbiter/Payload Landing 

Weight: 219,103 lbs.

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Software Version: OI-29

Space Shuttle Main Engines:

SSME 1: 2050 SSME 2: 2044 SSME 3: 2054

External Tank: ET-113A (Super Light Weight Tank) 

SRB Set: BI113PF

Shuttle Aborts

Abort Landing Sites

 RTLS: Kennedy Space Center Shuttle Landing Facility 

 TAL: Primary – Zaragoza; Alternates Ben Guerir, Moron 

 AOA: Kennedy Space Center Shuttle Landing Facility

Landing 

Landing Date: 06/11/02

Primary Landing Site: Kennedy Space Center Shuttle Landing 

Facility

 

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Mission Objectives 

Priorities 

Top priorities of the STS-111 (UF-2) mission of Endeavour are rotation of the International 

Space Station Expedition 4 and Expedition 5 crews, delivering water, equipment and 

supplies to the station and completion of robotics and spacewalk tasks. 

International Space Station Program priorities include the following: 

--Rotation of the Expedition 4 crew with Expedition 5 crew, transfer crew rotation equipment 

and perform crew handover. 

--Transfer consumables – water and food -- from the shuttle to the station. 

--Berth the Multi-Purpose Logistics Module to the station using the shuttle’s robotic arm, 

and transfer experiment racks, equipment and supplies in it to the station. 

--Remove the Mobile Remote Servicer Base System from Endeavour’s cargo bay and 

install it on the Mobile Transporter. 

--Replace the wrist-roll joint of Canadarm2. 

--Install six Service Module Debris Panels on a temporary stowage location on Pressurized 

Mating Adapter 1. 

--Install the Power, Data and Grapple Fixture on the P-6 truss. 

--Transfer middeck powered payloads to the U.S. laboratory Destiny, install them and 

check them out. 

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STS-111 Crewmembers 

Commander: Kenneth D. Cockrell 

Ken Cockrell, 52, is the commander of Endeavour for the third 

shuttle flight of 2002 to deliver a new crew to the International 

Space Station and install the Mobile Remote Servicer Base 

System (MBS) on the station’s railcar, the Mobile Transporter. 

He is making his third flight as commander and his fifth on a 

shuttle mission. As the STS-111 commander, Cockrell is 

primarily responsible for the success and safety of the flight, 

and will be at the controls for Endeavour’s docking to the ISS 

on the third day of the mission. He will operate the shuttle’s 

robotic arm during the spacewalks, moving the arm to 

optimize views from its television cameras for the first 

spacewalk and to position Mission Specialist Philippe Perrin during the third spacewalk. He 

will land Endeavour at the end of the mission. 

A veteran of four spaceflights, Cockrell has logged more than 1,215 hours in space. He 

served as a mission specialist on STS-56 in 1993, was the pilot on STS-69, and was the 

mission commander on STS-80 in 1996 and STS-98 in 2001. 

Pilot: Paul S. Lockhart 

Paul Lockhart, 46, an Air Force lieutenant colonel making his 

first flight into space, is Endeavour’s pilot. He holds a master’s 

degree in aerospace engineering from the University of Texas. 

Lockhart will provide intravehicular support during the 

spacewalks. After the shuttle undocks on flight day 11, he will 

do a one-revolution flyaround of the station before Endeavour 

leaves the area. Selected by NASA in April 1996, Lockhart 

completed four years of training and evaluation. 

Lockhart is making his first spaceflight. 

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Mission Specialist 1: Franklin R. Chang-Dìaz 

Franklin Chang-Diaz, 52, will be making a record-tying 

seventh flight into space, equaling a record set by fellow 

astronaut Jerry Ross. Chang-Dìaz and fellow crewmember 

Philippe Perrin will perform three spacewalks during the 

mission on flight days five, seven and nine. Included in the 

activities for the first spacewalk will be the installation of a 

Power and Data Grapple Fixture for the station’s robotic 

arm on the complex’s P6 truss. Hooking up power, data 

and video lines to the newly attached MBS as well as 

bolting it permanently in place will be the focus of the 

second spacewalk. During the third spacewalk, ChangDiaz and Perrin will replace the wrist roll joint of the station’s Canadarm2 with a backup 

unit brought into space aboard Endeavour. 

Selected by NASA in May 1980, Chang-Diaz holds a doctorate in applied plasma 

physics from the Massachusetts Institute of Technology earned in 1977. In December 

1993, Chang-Dìaz was appointed director of the Advanced Space Propulsion 

Laboratory at the Johnson Space Center where he continues his research on plasma 

rockets. He is an adjunct professor of physics at Rice University and the University of 

Houston and has presented numerous papers at technical conferences and in scientific 

journals. 

A veteran of six spaceflights (STS 61-C in 1986, STS-34 in 1989, STS-46 in 1992, STS60 in 1994, STS-75 in 1996 and STS-91 in 1998), Chang-Diaz has logged more than 

1,269 hours in space. 

Mission Specialist 2: Philippe Perrin 

Philippe Perrin, 39, is a colonel in the French Air Force 

and a French Space Agency (CNES) astronaut. Perrin and 

fellow crewmate Franklin Chang-Diaz will conduct all three 

of the mission’s planned spacewalks to complete several 

tasks including hooking up power, data and video lines for 

the MBS and bolting it to the station’s railcar, the Mobile 

Transporter, which was delivered, installed and 

successfully tested during STS-110. During the third 

spacewalk, they will replace the wrist roll joint of the 

station’s robotic arm, Canadarm2. Perrin has flown 26 

combat missions and has logged more than 2,500 flying 

hours in more than 30 types of aircraft (from jet fighters to Airbus). 

Perrin is making his first spaceflight. 

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Expedition Five (Up only) 

Commander: Valery Korzun 

Valery Grigorievich Korzun, a cosmonaut and colonel in the 

Russian Air Force, is a veteran of 197 days on the Russian 

space station Mir. Korzun, 49, is a first-class military pilot. He 

has logged 1,473 hours in four types of aircraft. He also is an 

instructor of parachute training, with 337 parachute jumps to 

his credit. Korzun graduated from Kachin Military Aviation 

College in 1974. He served as a pilot, a senior pilot, flight 

section, and commanded an Air Force squadron. He was 

awarded six Air Force Medals. 

In 1987 he was selected as a cosmonaut for training at the Gagarin Cosmonaut Training 

Center. Korzun was certified as a test cosmonaut in 1989. His flight aboard Mir began Aug. 

17, 1996, and continued through March 2, 1997. During that period three NASA astronauts 

flew aboard Mir. A French astronaut and a German astronaut also visited the station during 

that time. While on Mir, Korzun performed two spacewalks totaling 12 hours and 33 

minutes. 

Flight Engineer: Peggy Whitson 

U.S. astronaut Peggy A. Whitson holds a doctorate in 

biochemistry from Rice University and served in several 

research positions at Johnson Space Center before being 

selected as an astronaut in 1996. She completed two years of 

training and then performed technical duties in the Astronaut 

Office Operations Planning Branch. Whitson, 42, served as 

the lead for the Crew Test Support Team in Russia during 

1998 and 1999. After receiving her doctorate in 1985, she 

remained at Rice as a postdoctoral fellow until late 1986. She 

began her studies at JSC as a National Research Council 

Resident Research Associate. She later served the center in 

a variety of scientific positions, including duty as the project scientist for Shuttle-Mir from 

1992 to 1995. During Endeavour’s approach to the station, she will operate a handheld 

laser range finder. This will be her first flight into space. 

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Flight Engineer: Sergei Treschev 

Sergei Yevgenyevich Treschev, a cosmonaut of the RSC 

ENERGIA, is a graduate of the Moscow Energy Institute and 

served from 1982 to 1984 as a group leader in an Air Force 

regiment. He then joined RSC ENERGIA as a foreman and 

engineer. Responsibilities included analysis and planning of 

cosmonaut activities and their in-flight technical training. He 

also developed technical documentation and helped set up 

cosmonaut training with the Yuri Gagarin Cosmonaut Training 

Center. He supported training of crewmembers aboard Mir to 

help them maintain skills in performing descent and 

emergency escape operations. As a cosmonaut, Treschev, 

43, trained from June 1999 to July 2000 as a flight engineer for the Soyuz-TM backup ISS 

contingency crew. This will be his first spaceflight. 

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Expedition Four (Down only) 

Commander: Yury Onufrienko 

Col. Yury Ivanov Onufrienko, 40, a test cosmonaut and former 

senior pilot in his country’s air force, commanded the 

Expedition 4 crew. It was his second space station command 

– he led the Mir 21 expedition. Fellow crewmembers on Mir 

included astronaut Shannon Lucid and ISS Expedition 2 

Commander Yury Usachev. As ISS commander, he has 

overall responsibility for expedition safety and success of the 

space station and the Expedition 4 crew. Onufrienko has 

made one previous spaceflight, as commander of the Mir 21 

expedition from Feb. 21 to Sept. 2, 1996. 

Flight Engineer: Daniel Bursch 

Daniel W. Bursch, 44, is a Navy captain, a former test pilot 

and test pilot school instructor, and a veteran of three 

spaceflights. He is a Naval Academy graduate and holds an 

M.S. in engineering science from the Naval Postgraduate 

School. He has more than 3,100 flight hours in 35 aircraft 

types. He became an astronaut in 1991. Bursch flew on STS51, the Advanced Communications Technology Satellite and 

Shuttle Pallet Satellite flight, in September 1993. He also flew 

on STS-68, the Space Radar Lab-2 flight launched in 

September 1994 and on STS-77, with the fourth Spacehab 

module, in May 1996. 

Flight Engineer: Carl Walz 

Air Force Col. Carl E. Walz, 46, a former flight test engineer 

and flight test manager, was selected as an astronaut in 1990 

and is a veteran of three spaceflights. He holds B.S. and M.S. 

degrees in physics and enjoys sports and music – he is lead 

singer for MAX-Q, the astronaut rock-n-roll band. Walz flew as 

a mission specialist with Bursch on STS-51, the Advanced 

Communications Technology Satellite and Shuttle Pallet 

Satellite flight, in September 1993. He also flew on STS-65, 

the second International Microgravity Laboratory Spacelab 

module, in July 1994 and on STS-79, a mission to the 

Russian space station Mir, in September 1997. 

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Rendezvous and Docking 

Endeavour’s rendezvous and docking with the International Space Station actually begins 

with the precisely timed launch of the shuttle on a course for the station. During the first two 

days of the mission, periodic engine firings will gradually bring Endeavour to a point about 

91⁄2 statute miles behind the station, the starting point for a final approach to the station. 

About 21⁄2 hours before the scheduled docking time on flight day three, Endeavour will 

reach that point about 50,000 feet -- 91⁄2 statute miles -- behind the ISS. At that time, 

Endeavour’s jets will be fired in a Terminal Intercept (TI) burn to begin the final phase of the 

rendezvous. Endeavour will close the final miles to the station during the next orbit of Earth. 

As Endeavour closes in, the shuttle’s rendezvous radar system will begin tracking the 

station and providing range and closing rate information to the crew. During the approach 

toward the station, the shuttle will have an opportunity to conduct four, small mid-course 

corrections at regular intervals. Just after the fourth correction is completed, Endeavour will 

reach a point about half a mile below the station. At that time, about an hour before the 

scheduled docking, Commander Ken Cockrell will take over manual control of the 

approach. 

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STS-111 Commander Ken Cockrell gives the “thumbs up” signal during simulator 

training at the Johnson Space Center, Houston 

Cockrell will slow Endeavour’s approach and fly to a point about 600 feet directly below the 

station, from which he will begin a quarter-circle of the station, slowly moving to a position 

in front of the complex, in line with its direction of travel. During the rendezvous, Pilot Paul 

Lockhart will assist Cockrell in controlling Endeavour’s approach. Mission Specialists 

Philippe Perrin and Franklin Chang-Diaz also will play key roles in the rendezvous, with 

Perrin overseeing rendezvous navigation displays on a laptop computer aboard Endeavour 

and Chang-Diaz overseeing operations of the shuttle’s docking system. Expedition 5 Flight 

Engineer Peggy Whitson also will assist, using a handheld laser ranging device to provide 

supplemental range and closing rate information to Cockrell. 

Cockrell will fly the quarter-circle of the station, starting at a point 600 feet below, while 

slowly closing in on the complex, stopping at a point a little over 300 feet directly in front of 

the station. From that point, he will begin slowly moving directly toward the station’s shuttle 

docking port – moving at a speed of about a tenth of a mile per hour. Using a view from a 

camera mounted in the center of Endeavour’s docking mechanism as a key alignment aid, 

Cockrell will precisely center the docking ports of the two spacecraft. Cockrell will fly to a 

point where the docking mechanisms are 30 feet apart, and pause to check the alignment 

before proceeding to docking. 

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For Endeavour’s docking, Cockrell will maintain the shuttle’s speed relative to the station at 

about one-tenth of a foot per second, and keep the docking mechanisms aligned to within 

three inches of one another. When Endeavour makes contact with the station, preliminary 

latches will automatically attach the two spacecraft together. Immediately after Endeavour 

docks, the shuttle’s steering jets will be deactivated to reduce the forces acting at the 

docking interface. Shock absorber-type springs in the docking mechanism will dampen any 

relative motion between the shuttle and the station. 

Once relative motion between the spacecraft has been stopped, Chang-Diaz will secure the 

docking mechanism, sending commands for Endeavour’s mechanism to retract and close a 

final set of latches between the shuttle and station. 

Undocking, Separation and Fly-Around 

Once Endeavour is ready to undock, Chang-Diaz will send a command that will release the 

docking mechanism. The initial separation of the spacecraft will be performed by springs in 

the docking mechanism that will gently push the shuttle away from the station. Endeavour’s 

steering jets will be shut off to avoid any inadvertent firings during this initial separation. 

Once the docking mechanism’s springs have pushed Endeavour away to a distance of 

about two feet, when the docking devices will be clear of one another, Lockhart will turn the 

steering jets back on and fire them to begin very slowly moving away. From the aft flight 

deck, Lockhart will manually control Endeavour within a tight corridor as he separates from 

the ISS, essentially the reverse of the task performed by Cockrell when Endeavour docked. 

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Endeavour will continue away to a distance of about 450 feet, where Lockhart will begin a 

close flyaround of the station, circling the complex 11⁄4 times. Lockhart will pass a point 

directly above the station, then behind, then underneath, then in front and then reach a 

point directly above the station for a second time. At that point, passing above the station 

for a second time, Lockhart will fire Endeavour’s jets to depart the vicinity of the station. 

The flyaround is expected to be completed about an hour and half after undocking. 

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Spacewalks 

STS-111 Extravehicular Activity 

Astronauts Franklin Chang-Diaz and Philippe Perrin will perform three spacewalks during 

STS-111 to install the International Space Station's Mobile Remote Servicer Base System 

(MBS) and to replace a joint on the station's robotic arm. The spacewalks will be performed 

with one-day breaks in between to allow the crew to rest and prepare. The first spacewalk 

will take place on flight day five of the mission. The second will be on flight day seven, and 

the final venture outside is planned for flight day nine. The spacewalks will be the first 

extravehicular activity for both astronauts. During all of the spacewalks, Endeavour Pilot 

Paul Lockhart will serve as the Intravehicular (IV) crewmember, coordinating activities for 

the two spacewalkers from Endeavour's flight deck. STS-111 Commander Ken Cockrell will 

operate the shuttle’s robotic arm during the spacewalks, moving the arm to optimize views 

from its television cameras for the first spacewalk and to position Perrin during the third 

spacewalk. All of the spacewalks will originate from the station's Quest Airlock. During the 

work outside, the astronauts can be distinguished from one another by the markings on 

their spacesuits. 

Recognizing the spacewalkers: 

Chang-Diaz, Extravehicular Crewmember 1 (EV1) -- solid red stripes on legs of suit and top 

of backpack 

Perrin, EV2 -- solid white suit legs (no stripes), French flag on arm of suit 

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Spacewalk No. 1, Flight Day Five: Install P6 Power and Data Grapple 

Fixture, Transfer and Stow Service Module Debris Panels, Remove Mobile 

Remote Servicer Base System Thermal Blankets

Chang-Diaz and Perrin will begin the spacewalks with the first excursion outside of 

Endeavour on flight day five. For the majority of the first spacewalk, planned to last about 

six hours, Chang-Diaz will work from a foot platform mounted at the end of the station's 

Canadarm2 robotic arm. The arm will be operated by station Expedition 5 Commander 

Valery Korzun and Expedition 4 Flight Engineer Carl Walz working at controls within the 

station’s Destiny lab. Perrin will work free-floating during much of the first EVA. 

STS-111 astronauts Franklin Chang-Diaz, left, and Philippe Perrin practice their 

spacewalk tasks at the Johnson Space Center’s Virtual Reality Lab 

The first spacewalk will begin with the installation of a Power and Data Grapple Fixture 

(PDGF) for the station's robotic arm on the complex's P6 truss. The PDGF will allow the 

robotic arm to grip the P6 truss for future station assembly operations. Chang-Diaz and 

Perrin will install the new fixture about halfway up the P6 truss, the vertical structure that 

currently supports the station's set of large U.S. solar arrays. The grapple fixture will be 

used during a later assembly flight when the robotic arm must reposition the P6 truss from 

its current location. Working from a foot platform at the end of the station arm, Chang-Diaz 

will remove the new grapple fixture from a shuttle cargo bay carrier where it was secured 

for launch. While Chang-Diaz is removing the grapple fixture from its payload bay carrier, 

Perrin will be installing a temporary attachment on the station's Pressurized Mating Adapter 

1 (PMA 1). The attachment will be used later in the spacewalk to hold debris protection 

panels to be installed on the exterior of the station's Zvezda service module during a future 

spacewalk by station crewmembers. When Perrin has completed that task, he will climb up 

the P6 truss to await the arrival of Chang-Diaz, being maneuvered at the end of the station 

arm, carrying the grapple fixture. Midway up the P6 truss, the spacewalkers will work 

together to bolt the new fixture into place. 

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STS-111

Once the grapple fixture has been installed, both spacewalkers will move to Endeavour's 

payload bay to unload the package of Service Module Debris Panels, shielding panels that 

will be installed on the Zvezda exterior by station crewmembers on a future spacewalk. 

Once unfastened from Endeavour, Chang-Diaz, still at the end of the station arm, will 

secure the panels as he is maneuvered to the station's PMA 1, a conical adapter between 

the Unity and Zarya modules of the station. Perrin will move to PMA 1 as well to assist with 

stowing the panels on the exterior of that adapter. Once the panels have been stowed on 

PMA 1, Chang-Diaz will get out of the arm foot platform and work free-floating for the 

remainder of the spacewalk along with Perrin. 

Chang-Diaz and Perrin during one of many simulated spacewalks at Houston’s 

Neutral Buoyancy Lab (NBL) 

Before the spacewalkers begin the final task of EVA 1, Expedition 5 Flight Engineer Peggy 

Whitson will maneuver the station's robotic arm into position and latch it to a fixture on the 

MBS launched in Endeavour’s payload bay. Once latched to the MBS, connections 

between the arm's tip and the MBS fixture will supply power to the base system's 

electronics heaters. Once those heaters are confirmed operating, Chang-Diaz and Perrin 

will begin removing insulating blankets from the MBS that had been in place for launch. 

Removing the blankets clears the way for the initial installation of the MBS atop the Mobile 

Transporter "railcar" that rides atop the station's truss. The MBS will serve as a movable 

base of operations for the station's robotic arm, enabling it to ride the railway on the station 

truss as it builds and maintains the eventual 356-foot-long structure. Removing the thermal 

blankets is the final task for the first spacewalk. 

25
STS-111

While Chang-Diaz and Perrin are gathering the tools and equipment they used during the 

work outside, Whitson, assisted by Walz, will use the station arm to lift the MBS from 

Endeavour's payload bay. They will maneuver the new station component into position just 

above the Mobile Transporter on the station truss where it will be installed. It will remain in 

that position overnight, to ensure temperatures on the MBS and the MT are similar before 

the MBS is lowered into place. 

MBS Installation, Flight Day Six

While Chang-Diaz and Perrin rest and prepare for their second excursion planned on day 

seven, Whitson and Walz will lower the MBS into position to be initially latched to the MT. 

Once the MBS has been lowered into the proper location on the MT, a capture latch on the 

MBS will be commanded to close around a bar on the MT, providing the initial attachment 

of the new base system. 

Spacewalk No. 2, Flight Day Seven: MBS connection 

The second spacewalk, planned to last 6 1⁄2 hours, will focus on hooking up power, data 

and video lines to the newly attached MBS as well as bolting it permanently in place. 

During the second spacewalk, both spacewalkers will be free-floating. At the start of the 

spacewalk, the station's Canadarm2 will have a grip on the MBS, which it had maneuvered 

into place and attached to the Mobile Transporter on day six. Through its grip, the 

Canadarm2 will be providing power to heaters and electronics on the base system. As the 

spacewalkers prepare to begin hooking up power and other lines from the MT to the MBS, 

the power provided to the base system by the arm will be shut off. Then Chang-Diaz and 

Perrin will work together to connect primary and redundant cables for video and data and 

primary cables for power between the MT and the MBS. Once the cable connections are 

completed, commands will be sent to the MT to remotely plug in its umbilical attachments 

to receptacles on the railway, a system called the Umbilical Mating Adapter (UMA), which 

will supply power and other services to the MBS via the MT. While the spacewalkers move 

on to other tasks, ground controllers will begin a check of MBS systems to ensure all 

connections are established. 

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STS-111

Next, Chang-Diaz and Perrin will rotate a payload accommodations fixture, called the 

Payload Orbital Replacement Unit Accommodation (POA), on the MBS. The POA fixture 

will hold future cargoes on the base system as it is moved along the truss railway. 

Then, with the ground-controlled MBS checks completed, Chang-Diaz will hook up 

redundant power cables between the MBS and the MT. Next, using a power wrench, the 

two spacewalkers will secure four bolts that complete the permanent structural connection 

between the MBS and the transporter railcar. 

The final tasks for the second spacewalk will have the two EVA crewmembers work 

together to relocate a television camera on the MBS and to attach a bag to the MBS 

structure that contains a contingency MBS extension cable. The camera will be relocated 

from a position on the keel of the MBS, where it was used to provide visual cues needed to 

attach the MBS to the MT, to a position atop the MBS where it will be used to assist with 

the addition of the next station truss segment. 

Spacewalk No. 3, Flight Day Nine: Replace Canadarm2 Wrist Roll Joint 

The third spacewalk, added to STS-111 in March and planned to last 6 1⁄2 hours, will replace 

the wrist roll joint on the International Space Station's Candarm2 with a new joint carried to 

the station by Endeavour. The wrist roll joint being replaced has experienced a problem that 

prevents brakes from being released when operating in a secondary mode. For the 

replacement, Chang-Diaz will work free-floating while Perrin works from a foot platform at the 

end of the shuttle's robotic arm. The station's arm will be positioned with its free end poised 

several feet away from the underside of the Destiny laboratory, the side of the lab that will be 

facing Endeavour's tail and will be directly above the shuttle payload bay. 

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STS-111

All of the Canadarm2's joints are removable and were designed to be replaceable in orbit 

during a spacewalk. The new wrist roll joint is being carried aboard a special plate in 

Endeavour's cargo bay, a plate that will allow the faulty joint to be secured as well for the 

trip home aboard the shuttle. To access the wrist of the arm, the spacewalkers will first 

remove the Latching End Effector (LEE), the tip of the arm that is used to grip objects. 

Once the LEE is removed, the next portion of the arm is the wrist roll joint. Before removing 

the LEE, Perrin will install an insulating cover over the temperature-sensitive television 

camera and light assembly on the LEE. The insulation will moderate the temperatures 

experienced by that assembly while the LEE is unpowered. After the blanket is installed, 

the station crew will roll the end of the arm to provide access to the areas required for the 

joint changeout. Once in position, power will be shut off to the station arm. 

Perrin maneuvers underwater during a simulated spacewalk at the NBL 

When the station arm is powered off, Perrin will turn a bolt that will disconnect internal 

power, data and video connections between the LEE and the wrist roll joint. Next, Perrin 

and Chang-Diaz will loosen six special bolts, called Expandable Diameter Fasteners 

(EDFs), around the circumference of the LEE and roll joint. With those disconnected, 

Perrin, assisted by Chang-Diaz, will remove the almost 500-pound, washing machine-sized 

LEE from the arm and temporarily stow it in a fixture a few feet away on the exterior of the 

Destiny lab. 

With the LEE removed, the wrist roll joint to be replaced will then be at the tip of the 

station's arm. The two spacewalkers, Perrin continuing to work from a foot platform at the 

end of Endeavour's robotic arm and Chang-Diaz working from a foot platform attached to 

Destiny, will turn their attention to removal of the faulty joint. In a fashion identical to the 

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STS-111

removal of the LEE, they will turn a bolt that detaches power, data and video connections 

within the roll joint and then loosen six EDF bolts. Once those are disconnected, the faulty 

joint will be detached from the rest of the arm. 

Perrin, carrying the wrist roll joint, will then be maneuvered to Endeavour's payload bay to 

temporarily stow the faulty joint in a location adjacent to the new joint's launch position on a 

carrier designated the Flight Releasable Attachment Mechanism (FRAM). The joint can be 

"soft-docked" to the FRAM carrier. Installing three or four EDF bolts will complete the 

temporary stowage. Later, once the new joint has been removed and installed on the arm, 

the old joint will be permanently secured into the position where the new joint was for 

launch. 

Together, the spacewalkers will then release the new joint from the FRAM payload bay 

carrier. Before removing the new joint from the FRAM, Lockhart will turn off power that ran 

heaters on the joint during its time in the shuttle bay. To release the new joint, the 

spacewalkers will first fold back insulation blankets that covered it during launch and then 

release six EDF bolts to free it from the shuttle carrier. Perrin will then carry the new joint as 

he is maneuvered at the end of the shuttle arm back up to the end of the station arm. 

Chang-Diaz will meet him there to begin the task of installing the new joint. 

To install the new joint, Perrin and Chang-Diaz will align the wrist roll joint with the wrist 

yaw joint which will be at the end of the arm at that time and soft dock the new joint in 

place. Then, the two spacewalkers will work together to sequentially insert and tighten the 

six EDF bolts around the joint's circumference. They will tighten the bolts to a specified 

torque in stages. Once all of the EDFs are properly secured, Perrin will tighten a bolt that 

will connect power, video and data cables internal to the new joint with connections on the 

arm. 

The next task will be to reinstall the LEE. The two will work together to remove the LEE 

from its position stowed on the exterior of Destiny and align it with the newly installed wrist 

joint. The LEE will be soft docked into position first, and then the six EDF bolts around its 

circumference tightened to secure it in place. Then a bolt will be turned to reconnect 

internal power, video and data connections. Once the LEE is reconnected and verified 

operating, the insulating cover will be removed from the camera assembly. 

The final task for Chang-Diaz and Perrin will be to secure the failed joint in Endeavour's 

payload bay for return to Earth. The spacewalkers, with Perrin still working from a foot 

platform at the end of the shuttle's robotic arm, will first remove the joint from the payload 

bay bracket where they had temporarily secured it earlier. Then, they will move it to the 

adjacent bracket upon which the newly installed joint had been secured for launch. Using 

six EDF bolts, they will secure the joint in place for return to Earth. The bracket also will 

allow power to be supplied for heaters on the joint during its trip aboard Endeavour. The 

crew also will cover the old joint with a thermal cover that had protected the new joint 

during launch. 

29
STS-111

Payloads 

Payload Overview 

The launch package for mission STS-111 (International Space Station Assembly Flight UF2) consists of a Multi-Purpose Logistics Module (MPLM), a Mobile Remote Servicer (MRS) 

Base System (MBS), a Space Station Remote Manipulator System (SSRMS) Wrist Roll 

Joint (WRJ) on a Get Away Special (GAS) Can beam, one Power and Data Grapple Fixture 

(PDGF) on an Increased Capacity Adaptive Payload Carrier (ICAPC) sidewall carrier, a set 

of six Service Module Debris Panel (SMDP) shields on a GAS Can beam, middeck 

payloads/stowage items, and crew rotation gear located in the shuttle middeck. 

The MPLM is manifested at the rear of the shuttle’s payload bay with the MPLM berthing 

mechanism facing forward. On orbit, a Remotely Operated Electrical Umbilical will provide 

electrical power to the MPLM shell heaters. After the payload bay door opening, avionics 

will be activated on the MPLM to monitor temperatures and pressures. 

The MBS is manifested in the midsection of the payload bay, forward of the MPLM and aft 

of the Orbiter Docking System. 

The SSRMS WRJ is manifested in Bay 6 port on a GAS beam using the Flight Releasable 

Attach Mechanism. 

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STS-111

The ICAPC beam is manifested in Bay 13, port side, for carrying the PDGF. The PDGF will 

be attached to the P6 truss during the mission’s first Extravehicular Activity (EVA). 

The GAS Can beam is manifested in Bay 13, starboard side, for carrying the SMDP 

shields, with the Transportation Device Kit (TDK). The shields will be flown to the station 

aboard Endeavour on the STS-111 mission and will be temporarily stowed on the mating 

adaptor that connects the Unity module to the Zarya module by STS-111 spacewalkers 

Franklin Chang-Diaz and Philippe Perrin. The debris panels will be installed on the Service 

Module during the Expedition 5 stage via a spacewalk by Expedition 5 Commander Valery 

Korzun and Flight Engineer Peggy Whitson. The TDK will remain in the shuttle. 

Two Assembly Power Converter Units with interconnect cabling and mounting brackets are 

manifested. 

MPLM Transfer Items 

Name No.

Resupply Return Stowage Rack (RSR)......................................................8 

Resupply Stowage Platform (RSP) ............................................................5 

International Standard Payload Rack (ISPR) 

Expedite the Processing of Experiments to the 

Space Station (EXPRESS) Rack No. 3.................................................1 

Microgravity Science Glovebox (MSG) .................................................1 

Shuttle Lithium Hydroxide (LiOH) Canisters (up to 8 transferred to ISS)...26 

Various logistics and utilization items 

Middeck Powered Payload Transfer Items 

Biomass Production System (BPS) 

KSC Gaseous Nitrogen Freezer (KSC GN2 FREEZER) 

Commercial Generic Bioprocessing Apparatus – 3 (CGBA-3) 

Commercial Protein Crystal Growth – High Density – 1 (CPCG-H-1) 

Protein Crystal Growth – Single Locker Thermal Enclosure System 

(PCG-STES 009) 

STELSYS Commercial Refrigeration Incubator Module (CRIM) Contents 

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STS-111

Payloads 

Mobile Remote Servicer Base System 

In April 2001, the first component of the Mobile Servicing System, Canadarm2, was 

launched and installed on the International Space Station during space shuttle mission 

STS-100. A larger and more sophisticated version of its predecessor shuttle robotic arm, 

Canadarm2 has seven joints and can flip hand-over-hand along the length of the space 

station. Canadarm2 was built to operate with two other components, a work platform called 

the Mobile Remote Servicer Base System (MBS) and a smaller dual-arm robot designed to 

accomplish more precise tasks, the Special Purpose Dexterous Manipulator. These three 

elements are essential to the assembly and maintenance of the station and represent the 

Mobile Servicing System, Canada’s contribution to the ISS. 

At Kennedy Space Center’s Space Station Processing Facility, the Mobile Base 

System is hoisted to the weight and center of gravity stand 

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STS-111

As the assembly of the ISS continues and the station grows larger, the MBS supports the 

need to provide greater mobility to Canadarm2 and access to the length of the station. 

During shuttle mission STS-111, the MBS will be launched and installed on the space 

station. The MBS was designed and built by MD Robotics, the main contractor of 

Canadarm2, and a team of Canadian subcontractors. 

The MBS will be mounted on the U.S.-provided Mobile Transporter that will slide on tracks 

along the length of the station. Attached to the MT, the MBS will provide greater mobility to 

Canadarm2 and allow the transport of payloads across the station using a fixture called the 

Payload Orbital Replacement Unit Accommodation or POA. The platform’s POA will mainly 

be used to carry large structural elements and payloads, such as trusses, along the length 

of the station. Another attachment point called the MBS Common Attach System will be 

used to carry pallets containing lighter payloads like work tools and scientific experiments. 

Astronauts will also use the MBS as a platform from which to perform spacewalks. The 

MBS can be used by the astronauts as a storage facility where they can keep various work 

tools and also as a means of transportation from one end of the station to another. 

Canadarm2 is designed so that repairs can be made in orbit throughout its lifetime and the 

MBS may serve as a maintenance platform that would hold both ends of Candarm2 if the 

replacement of any of its joints were warranted. 

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STS-111

Four Payload Data Grapple Fixtures are clearly visible in this picture of the MBS 

at Kennedy Space Center’s Space Station Processing Facility 

The MBS has four anchor points, referred to as Power Data Grapple Fixtures, which can 

serve as a base for operation of Canadarm2 and the SPDM robot. Through these anchor 

points, the MBS provides power and data to the robots as well as to the payloads that they 

may be supporting. These anchor points also transfer computer commands and video 

signals to and from the Robotic Work Station, a console located inside the station, from 

which the astronauts operate the entire MSS. 

The MBS is also equipped with one removable Camera Light Pan & Tilt Assembly. The 

color camera is located on a mast behind the POA. This location provides not only a 

general view of the top surface of the MBS but also unobstructed views of all four of the 

anchor points. Initially, the camera will be installed on the underside of the MBS Common 

Attach System frame in order to provide suitable views of the mating of the MBS to the MT 

during STS-111. After the successful mating of the MBS to the MT, the camera will be 

relocated to its final position during a spacewalk. 

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STS-111

The MBS is a strong and resistant aluminum structure with a life expectancy of at least 15 

years. Like all elements of the ISS, the MBS is built with a series of separate and 

interchangeable modules called Orbital Replacement Units. In case of problems, the 

separate and interchangeable ORUs can be replaced during spacewalks or remotely once 

the SPDM has been installed on the space station. The MBS is also equipped with two 

main computer units. 

The MBS measures about 18.7 by 14.7 by 9.5 feet (5.7 by 4.5 by 2.9 meters). Its mass is 

about 3,307 lbs (1,500 kg). Its mass handling transportation capacity is about 46,076 lbs 

(20,900 kg). The peak power (operational) of the MBS is 825 W. The average power (keep 

alive) is 365 W. 

The MBS cost is $400 million (Canadian) or $254 million (usd). 

35
STS-111

Payloads 

Leonardo - An Italian Space Veteran 

Carrying 5,600 lbs of Cargo to the ISS 

The Leonardo Multi-Purpose Logistics Module (MPLM) acts as a moving van for the 

International Space Station Program, carrying laboratory racks with science equipment as 

well as storage racks and platforms filled with bags of experiments and supplies to and 

from the orbiting laboratory. 

Leonardo, shown here in the payload bay of Discovery during shuttle mission 

STS-105/ISS 7A.1 in August 2001 

Making its third trip into space, Leonardo is mounted in Endeavour’s payload bay for launch 

and remains there until after the shuttle docks with the space station. Endeavour’s 

astronauts will use the shuttle’s robotic arm to remove Leonardo from the payload bay and 

attach it to the nadir port of the space station’s Unity Node for unloading on flight day four. 

Aboard Leonardo are eight Resupply Stowage Racks, five Resupply Stowage Platforms, 

and two International Standard Payload Racks; the Microgravity Science Glovebox Rack, 

and a new scientific experiment rack for the station’s U.S. laboratory Destiny, the fifth rack 

to be carried to the station. 

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STS-111

The new science rack (EXPRESS Rack 3) will add increased science capability to the 

station. EXPRESS stands for Expedite the Processing of Experiments to the Space Station. 

EXPRESS Rack 3 weighs 1,345 pounds. The empty weight of each EXPRESS rack is 

about 785 pounds. 

EXPRESS Racks 4 and 5 were delivered to the station aboard the Leonardo cargo module 

during STS-105/7A.1 in August 2001. EXPRESS Racks 1 and 2A were delivered aboard 

the Raffaello cargo module during STS-100/6A in April 2001. 

The Resupply Stowage Racks and Resupply Stowage Platforms are filled with Cargo 

Transfer Bags that contain equipment and supplies for the station. The eight Resupply 

Stowage Racks and the five Resupply Stowage Platforms contain about 5,600 pounds of 

cargo, not including the weight of the straps and fences that hold the bags in place. 

The total weight of Leonardo with the cargo and racks is just over 23,275 pounds. 

Leonardo’s cargo includes equipment required for activation of the new science rack, a 

variety of parts for station systems and experiments including resupply items for the Human 

Research Facility and the Crew Health Care System, and food and other supplies to 

support the Expedition 5 crew. After the cargo is removed, the Resupply Stowage Racks 

and Resupply Stowage Platforms, which remain aboard Leonardo, will be filled with any 

unneeded station equipment and used crew provisions. Once filled, Leonardo will be 

detached from the station and put back into the shuttle’s payload bay for the trip home. 

History/Background 

Construction of Leonardo began in April 1996 at the Alenia Aerospazio factory in Turin, 

Italy. Leonardo was flown from Italy to the Kennedy Space Center in Florida in August 1998 

aboard a special Beluga cargo aircraft. Although built in Italy, Leonardo and two additional 

MPLMs, Raffaello and Donatello, are owned by the U.S. The MPLMs were provided in 

exchange for Italian access to U.S. research time on the space station. 

The cylindrical Leonardo module is about 21 feet (6.4 meters) long and 15 feet (4.6 meters) 

in diameter. It weighs over 9,600 pounds (4.3 metric tons) empty and can carry up to 

20,000 pounds (9.1 metric tons) of cargo packed into 16 standard space station equipment 

racks or platforms. 

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STS-111

Expedition 1 Flight Engineer Yuri Gidzenko is dwarfed by transient hardware 

aboard Leonardo, the Italian Space Agency-built Multi-Purpose Logistics Module 

Leonardo provides a controlled (human-rated) environment with components that provide 

some life support, fire detection and suppression, electrical distribution and computer 

functions. When in the payload bay, Leonardo is independent of the space shuttle and 

there is no passageway for shuttle crewmembers to travel to and from the module. In the 

future, the MPLMs will carry refrigerator freezers for transporting experiment samples and 

food to and from the station. 

Leonardo first flew to the space station aboard Discovery on STS-102/5A.1 in March 2001. 

It flew again on STS-105 aboard Discovery in August 2001. The second MPLM, Raffaello, 

flew to the station aboard Endeavour on STS-100/6A in April 2001 and again aboard 

Endeavour on STS-108/UF-1 in December 2001. Donatello, the first powered module, is 

scheduled for flight in 2005. 

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STS-111

Experiments 

STS-111 Science Overview 

When the space shuttle Endeavour returns to the International Space Station during the 

STS-111 mission, it will arrive with new equipment that enhances the orbiting outpost’s 

construction and science capabilities and improves its safety. 

The Multi-Purpose Logistics Module Leonardo will be making its third trip to space loaded 

with new science facilities and experiments to kick off Expedition 5. Leonardo is filled with 

new experiments and a major new science facility -- the Microgravity Science Glovebox. 

The glovebox – a sealed container with built-in gloves on its sides and fronts – provides a 

facility that safely contains fluids, flames, particles and fumes, but still allows the crew to 

“get a grip” on science equipment via the gloves. 

The glovebox, designed to stay in the Destiny laboratory for 10 years, will support the first 

two space station materials science experiments, also being delivered on STS-111. These 

experiments will study materials processes similar to those used to make semiconductors 

for electronic devices and components for jet engines. In exchange for building the 

glovebox, the European Space Agency will be able to perform experiments inside Destiny 

until that agency’s space station laboratory – the Columbus Orbital Facility – is attached to 

the station in a couple of years. 

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STS-111

The Microgravity Science Glovebox (MSG) is a sealed container with built-in gloves that 

provides an enclosed workspace for experiments with fluids, flames, particles or fumes. 

The MSG provides vacuum, venting and gaseous nitrogen, as well as power and data 

interfaces for experiments. The MSG occupies an entire rack inside the Destiny lab and is 

more than twice as large as gloveboxes flown previously on the space shuttle. This enables 

the MSG to hold experiments about the size of an airline carry-on bag. NASA’s Marshall 

Space Flight Center worked with the European Space Agency to build the MSG - a facility 

that will support station experiments for the next 10 years. The MSG will be delivered 

during STS-111/UF2. 

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STS-111

EXPRESS Rack 3, also ferried inside Leonardo, will be the fifth EXPRESS rack built at 

Marshall Space Flight Center, Huntsville, Ala., to be delivered to Destiny. These racks 

house experiments and provide them with power, fluids, cooling, data and other basic 

utilities. 

The Expedition 5 research complement includes 24 new and continuing investigations, 

including the first two materials science experiments; two new plant experiments sponsored 

by industry; a commercial bioreactor that grows liver cells; facilities that grow biological 

crystals and zeolite crystals used in petroleum processing; and numerous experiments that 

study how the human body adapts to spaceflight.

All the station’s science experiments are operated from the ground by controllers on duty 

around the clock, seven days a week at the Payload Operations Center at Marshall. It is the 

command post for both planning and executing space station science activities. It links 

Earth-bound researchers with their experiments and the station crew. 

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STS-111

Experiments 

DTOs and DSOs 

Detailed Test Objectives (DTOs) are aimed at testing, evaluating or documenting space 

shuttle systems or hardware, or proposed improvements to space shuttle hardware, 

systems and operations. 

Detailed Supplementary Objectives (DSOs) are space and life science investigations. Their 

purpose is to determine the extent of physiological deconditioning resulting from 

spaceflight, to test countermeasures to those changes and to characterize the environment 

of the space shuttle relative to crew health. 

The following such experiments are aboard Endeavour: 

DTO 700-14 

Single-String Global Positioning System 

The purpose of the Single-String Global Positioning System (GPS) is to demonstrate the 

performance and operation of the GPS during orbiter ascent, on-orbit, entry and landing 

phases. It uses a modified military GPS receiver processor and the existing orbiter GPS 

antennas. GPS data may be downlinked during all mission phases. This has been 

previously manifested 23 times and was scheduled to fly on STS-110. 

DTO 805 

Crosswind Landing Performance 

DTO 805 will demonstrate the capability to perform a manually controlled landing in the 

presence of a crosswind. This test requires that the crew perform a manually controlled 

landing in the presence of a 90-degree crosswind component of 10 to 15 knots steady 

state. This DTO has been manifested on 71 previous flights and was scheduled to fly on 

STS-110. 

DTO 694 

Biotechnology Water Treatment System 

The purpose of the Biotechnology Treatment System is to produce ultra-pure water from 

the shuttle’s fuel cell water. This water, when processed, can replace manifested ultra-pure 

water supplies, and thus significantly decreases the mass and volume required to support 

biotechnology payloads. This will be the first flight for this DTO. 

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STS-111

DSO 498 

Spaceflight and Immune Function 

The effects of spaceflight will be studied on selected immune elements that are important in 

maintaining an effective defense against infectious agents. The roles of neutrophils, 

monocytes, and cytotoxic cells -- all important elements of the immune response -- will be 

studied as part of this DSO. 

DSO 499 

Eye Movements and Motion Perception Induced by Off-Vertical Axis 

Rotation (OVAR) at Small Angles of Tilt after Spaceflight 

The purpose of this study is to examine changes in spatial neural processing of 

gravitational tilt information following adaptation to microgravity. Postflight oculomotor and 

perceptual responses during off-vertical axis rotation will be compared with preflight 

baselines to track the time course of recovery. Comparison of data from short-duration and 

long-duration (ISS) crewmembers will allow us to assess the effect of flight duration. 

DSO 500 

Spaceflight-Induced Reactivation of Latent Epstein-Barr Virus 

The combined effects of microgravity along with associated physical and psychological 

stress will decrease Epstein-Barr virus (EBV)-specific T-cell immunity and reactivate latent 

EBV in infected B-lymphocytes. 

The mechanisms of spaceflight-induced alterations in human immune function and latent 

virus reactivation will be examined. Specifically, this study will determine the magnitude of 

immunosuppression as a result of spaceflight by: 

1. Analysis of stress hormones 

2. Quantitative analysis of EBV replication using molecular and serological methods; and 

3. Determining virus-specific T-cell immune function. 

DSO 503-S 

Test of Midodrine as a Countermeasure Against Postflight Orthostatic 

Hypotension 

Following exposure to spaceflight, upright posture can result in the inability to maintain 

adequate arterial pressure and cerebral perfusion (orthostatic or postural hypotension). 

This may result in presyncope (lightheadedness) or syncope (loss of consciousness) during 

re-entry or egress. 

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STS-111

A new pharmacological countermeasure for protection from postflight orthostatic 

hypotension will be evaluated. This experiment will measure the efficacy of midodrine in 

reducing the incidence and/or severity of orthostatic hypotension in returning astronauts. 

Efficacy will be evaluated with an expanded tilt test. 

DSO 634 

Sleep–Wake Actigraphy and Light Exposure During Spaceflight 

Disruption of sleep during spaceflight, both short- and long-duration, is associated with 

inappropriately timed (non-24 hour) or insufficiently intense light exposure. Sleep 

disruption and circadian misalignment will lead to subjective dissatisfaction with selfreported sleep quality and daytime alertness. Both of these conditions are associated with 

insomnia and associated impairment of alertness and cognitive performance that could 

impair mission success. 

This experiment will use state-of-the-art ambulatory technology to monitor sleep-wake 

activity and light exposure patterns obtained in-flight. This data should help better 

understand the effects of spaceflight on sleep as well as aid in the development of effective 

countermeasures for both short- and long-duration spaceflight. 

DSO 635 

Spatial Reorientation Following Spaceflight 

Before and after spaceflight, spatial orientation is altered by a shift of central vestibular 

processing from a gravitational frame-of-reference to an internal, head-centered frame-ofreference. This occurs during adaptation to microgravity and is reversed during the first few 

days after return to Earth. Discordant sensory stimuli during the postflight re-adaptive 

period will temporarily disorient and destabilize the subject by triggering a shift (state 

change) to the previously learned, internally-referenced, microgravity-adapted pattern of 

spatial orientation and sensorimotor control. 

The purpose of this DSO is to examine both the adaptive changes in the spatial reference 

frame used for coding spatial orientation and sensorimotor control. Also being studied is the 

fragility of the adaptive process and the feasibility of driving state changes in central 

vestibular processing via discordant sensory stimuli using balance control tests and eye 

movement responses to pitch-axis rotation in a short-arm centrifuge. The findings are 

expected to demonstrate the degree to which challenging motion environments may affect 

postflight adaptation/re-adaptation and lead to a better understanding of safe postflight 

activity regimens. The findings are also expected to demonstrate the feasibility of triggering 

state changes between sensorimotor control sets using a centrifuge device. 

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Experiments 

Ram Burn Observations (RAMBO) 

Ram Burn Observations (RAMBO) is a Department of Defense experiment that observes 

shuttle Orbital Maneuvering System engine burns for the purpose of improving plume 

models. On STS-111 the shuttle will perform a 10-second, dual OMS burn to be observed 

by the appropriate sensors. 

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Shuttle Reference Data 

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 T4 seconds when the orbiter’s computers detected a sluggish valve in main engine #3. 

The main engine was replaced and Discovery was finally launched on August 30, 1984. 

(STS-51 F) July 12, 1985

The countdown for Challenger’s launch was halted at T-3 seconds when on-board 

computers detected a problem with a coolant valve on main engine #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 readings in the oxidizer preburner on 

main engine #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) August 12, 1993

The countdown for Discovery’s third launch attempt ended at the T-3 second mark 

when on-board computers detected the failure of one of four sensors in main engine #2 

which monitor the flow of hydrogen fuel to the engine. All of Discovery’s main engines 

were ordered replaced on the launch pad, delaying the Shuttle’s fourth launch attempt 

until September 12, 1993. 

(STS-68) August 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 #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 #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 October 

2nd as the date for Endeavour’s second launch attempt. 

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Abort to Orbit History:

(STS-51 F) July 29, 1985

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

minutes and 45 seconds after launch, a sensor problem resulted in the shutdown of 

center engine #1, resulting in a safe "abort to orbit" and successful completion of the 

mission.

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Shuttle Reference Data 

Shuttle Abort Modes 

RSLS ABORTS 

These occur when the onboard shuttle computers detect a problem and command a halt in 

the launch sequence after taking over from the Ground Launch Sequencer and before Solid 

Rocket Booster ignition. 

ASCENT ABORTS 

Selection of an ascent abort mode may become necessary if there is a failure that affects 

vehicle performance, such as the failure of a space shuttle main engine or an orbital 

maneuvering system. Other failures requiring early termination of a flight, such as a cabin 

leak, might also require the selection of an abort mode. 

There are two basic types of ascent abort modes for space shuttle missions: intact aborts 

and contingency aborts. Intact aborts are designed to provide a safe return of the orbiter to 

a planned landing site. Contingency aborts are designed to permit flight crew survival 

following more severe failures when an intact abort is not possible. A contingency abort 

would generally result in a ditch operation. 

INTACT ABORTS 

There are four types of intact aborts: abort to orbit (ATO), abort once around (AOA), 

transoceanic abort landing (TAL) and return to launch site (RTLS). 

Return to Launch Site 

The RTLS abort mode is designed to allow the return of the orbiter, crew, and payload to 

the launch site, Kennedy Space Center, approximately 25 minutes after lift-off. 

The RTLS profile is designed to accommodate the loss of thrust from one space shuttle 

main engine between lift-off 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 ET 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, which is done 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, approximately three minutes 34 seconds into the mission; 

whereas an RTLS chosen due to an engine out at lift-off is selected at the earliest time, 

approximately two minutes 20 seconds into the mission (after solid rocket booster 

separation). 

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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 towards 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 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 system propellants are 

dumped by continuous orbital maneuvering system and reaction control system engine 

thrustings to improve the orbiter weight and center of gravity for the glide phase and 

landing. 

The vehicle will reach the desired main engine cutoff point with less than 2 percent excess 

propellant remaining in the external tank. At main engine cutoff minus 20 seconds, a pitchdown 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 translation 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 translation 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 approximately 45 minutes after launch. 

The landing site is selected near the nominal ascent ground track of the orbiter in order 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. Currently, the three landing sites that have been identified for a due east launch 

are Moron, Spain; Dakar, Senegal; and Ben Guerur, Morocco (on the west coast of Africa). 

To select the TAL abort mode, the crew must place the abort rotary switch in the TAL/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 

49
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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 nominal entry. 

Abort to Orbit 

An ATO is an abort mode used to boost the orbiter to a safe orbital altitude when 

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

space shuttle main engine fails in a region that results in a main engine cutoff under speed, 

the 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 maneuver to place the orbiter on orbit and the deorbit thrusting maneuver. In 

addition, an AOA is used in cases in which a major systems problem (cabin leak, loss of 

cooling) makes it necessary to land quickly. In the AOA abort mode, one orbital 

maneuvering system thrusting sequence is made to adjust the post-main engine cutoff orbit 

so a second orbital maneuvering system thrusting sequence will result in the vehicle 

deorbiting and landing at the AOA landing site (White Sands, N.M.; Edwards Air Force 

Base; or the Kennedy Space Center). Thus, an AOA results in the orbiter circling the Earth 

once and landing approximately 90 minutes after lift-off. 

After the deorbit thrusting sequence has been executed, the flight crew flies to a landing at 

the planned site much as it would for a nominal entry. 

CONTINGENCY ABORTS 

Contingency aborts are caused by loss of more than one main engine or failures in other 

systems. Loss of one main engine while another is stuck at a low thrust setting may also 

necessitate a contingency abort. Such an abort would maintain orbiter integrity for in-flight 

crew escape if a landing cannot be achieved at a suitable landing field. 

Contingency aborts due to system failures other than those involving the main 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. 

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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 would be 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. 

The Mission Control Center-Houston is prime for calling these aborts because it has a more 

precise knowledge of the orbiter's position than the crew can obtain from onboard 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 onboard methods, such as cue cards, dedicated displays and display information, to 

determine the current 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 space shuttle main engine fails. 

If the problem is a system failure that jeopardizes the vehicle, the fastest abort mode that 

results in the earliest vehicle landing is chosen. RTLS and TAL are the quickest options (35 

minutes), whereas an AOA requires approximately 90 minutes. Which of these is selected 

depends on the time of the failure with three good space shuttle main engines. 

The flight crew selects the abort mode by positioning an abort mode switch and depressing 

an abort push button. 

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Shuttle Reference Data 

Space Shuttle Rendezvous Maneuvers 

COMMON SHUTTLE RENDEZVOUS MANEUVERS

OMS-1 (Orbit insertion) - Rarely used ascent abort burn 

OMS-2 (Orbit insertion) - Typically used to circularize the initial orbit following ascent, 

completing orbital insertion. For ground-up rendezvous flights, also considered 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 

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Shuttle Reference Data 

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 approximately 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 lift- off and during first-stage ascent. Seventy- five 

seconds after SRB separation, SRB apogee occurs at an altitude of approximately 220,000 

feet, or 35 nautical miles (40 statute miles). SRB impact occurs in the ocean approximately 

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 approximately 1,300,000 pounds at launch. The propellant for each solid 

rocket motor weighs approximately 1,100,000 pounds. The inert weight of each SRB is 

approximately 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, 

pyrotechnics, 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 explosives at lift-off. 

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 postflight inspection of recovered hardware. 

One of the areas was the attach ring where the SRBs are connected to the external tank. 

Areas of distress were noted in some of the fasteners where the ring attaches to the 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. 

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Additionally, special structural tests were performed 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 redesign was implemented to add reinforcement brackets and fittings in the aft 

ring of the skirt. 

These two modifications added approximately 450 pounds to the weight of each SRB. 

The propellant mixture in each SRB motor consists of an ammonium perchlorate (oxidizer, 

69.6 percent by weight), aluminum (fuel, 16 percent), iron oxide (a catalyst, 0.4 percent), a 

polymer (a binder that holds the mixture together, 12.04 percent), and 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 

approximately a third 50 seconds after lift-off 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 fabrication 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 (direction) 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 convergent-divergent, movable design in which an aft pivot-point flexible 

bearing is the gimbal mechanism. 

The cone- shaped aft skirt reacts the aft loads between the SRB and the mobile 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 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. 

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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 

separation motor is 31.1 inches long and 12.8 inches in diameter. 

Location aids are provided for each SRB, frustum/drogue chutes and main parachutes. 

These include a transmitter, antenna, strobe/converter, battery and salt water 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, frustum/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 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 contains two NASA standard detonators, 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 deceleration stand, which contains 

sand. The SRB bolt is 28 inches long and is 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. 

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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 initiator; 

and combustion products of this propellant ignite the solid rocket motor initiator, which fires 

down the length of the solid rocket motor igniting the solid rocket motor propellant. 

The GPC launch sequence also controls certain critical main propulsion system valves and 

monitors the engine-ready indications from the SSMEs. The MPS start commands are 

issued by the onboard computers at T minus 6.6 seconds (staggered start--engine three, 

engine two, engine one--all approximately within 0.25 of a second), and the 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-percent thrust level will result in the SSMEs being 

commanded to the lift-off 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 approximately 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 onboard computers; 

separation of the four explosive bolts on each SRB is initiated (each bolt is 28 inches long 

and 3.5 inches in diameter); the two T-0 umbilicals (one on each side of the spacecraft) are 

retracted; the onboard master timing unit, event timer and mission event timers are started; 

the three SSMEs are at 100 percent; and the ground launch sequence is terminated. 

The solid rocket motor thrust profile is tailored to reduce thrust during the 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. 

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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 

operation. 

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 mechanical 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 overboard through an exhaust duct. 

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

APU speed is controlled by the APU controller electronics. If the primary control valve logic 

fails to the open state, the secondary control valve assumes control of the APU at 112-

percent speed. 

Each HPU on an SRB is connected to both servoactuators 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 sevoactuator 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. 

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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 servoactuators: one for rock and one for tilt. The 

servoactuators 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 lift-off and ascent. Commands from the guidance system are 

transmitted to the ATVC drivers, which transmit signals proportional to the commands to 

each servoactuator of the main engines and SRBs. Four independent flight control system 

channels and four ATVC channels control six main engine and four SRB ATVC drivers, 

with each driver controlling one hydraulic port on each main and SRB servoactuator. 

Each SRB servoactuator consists of four independent, two-stage servovalves that receive 

signals from the drivers. Each servovalve controls one power spool in each actuator, which 

positions an actuator ram and the nozzle to control the direction of thrust. 

The four servovalves in each actuator provide a force-summed majority voting arrangement 

to position the power spool. With four identical commands to the four servovalves, the 

actuator force-sum action prevents a single erroneous command from affecting power ram 

motion. If the erroneous command persists for more than a predetermined time, differential 

pressure sensing activates a selector valve to isolate and remove the defective servovalve 

hydraulic pressure, 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 channel. 

Each actuator ram is equipped with transducers for position feedback to the thrust vector 

control system. Within each servoactuator ram is a splashdown load relief assembly to 

cushion the nozzle at water splashdown and prevent damage to the nozzle flexible bearing. 

SRB RATE GYRO ASSEMBLIES 

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 computers and guidance, navigation and control system during first-stage ascent 

flight in conjunction with the orbiter roll rate gyros until SRB separation. At SRB separation, 

a switchover is made from the SRB RGAs to the orbiter RGAs. 

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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, commanding the thrust vector control actuators to the 

null position and putting the main propulsion system into a second-stage configuration (0.8 

second from sequence initialization), which ensures the thrust of each SRB is less than 

100,000 pounds. Orbiter yaw attitude is held for four seconds, and SRB thrust drops to less 

than 60,000 pounds. 

The SRBs separate from the 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 wiring connecting each SRB RSS 

and the ET RSS with each other. 

The aft attachment points consist of three separate struts: upper, diagonal and lower. Each 

strut contains one bolt with an NSD pressure cartridge at each end. The upper strut also 

carries the umbilical interface between its SRB and the external tank and on to the orbiter. 

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 

separation. 

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Shuttle Reference Data 

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 will allow the shuttle to deliver International Space Station elements 

(such as the service module) into the proper orbit. 

The SLWT is the same size as the previous design. But the liquid hydrogen tank and the 

liquid oxygen tank are made of aluminum lithium, a lighter, stronger material than the metal 

alloy used for the shuttle's current tank. The tank's structural design has also been 

improved, making it 30% stronger and 5% less dense. 

The SLWT, like the standard tank, is manufactured at Michoud Assembly, near New 

Orleans, Louisiana, 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. 

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Acronyms and Abbreviations 

A/B Airborne 

A/L Airlock (ISS Joint Airlock) 

AAA Avionics Air Assembly 

AAC Aft Access Cone 

ABC Audio Bus Coupler 

ABOLT Acquire BOLT 

ACBM Active Common Berthing Mechanism 

ACLS Advanced Cardiac Life Support System 

ACO Assembly Checkout Officer 

ACS Assembly Contingency System 

Atmosphere Control and Supply 

Attitude Control System 

ACU Actuator Control Unit 

Arm Computer Unit 

AD Active Device 

ADF Air Diffusers 

ADM Antenna Distribution Module 

ADP Airlock Depressurization Pump 

AFD Aft Flight Deck 

AIO Analog Input/Output 

AL Airlock (ISS Joint Airlock) 

ALSP Advanced Life Support Pack 

AMP Ambulatory Medical Pack 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Attachment System 

APCF Advanced Protein Crystallization 

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 

Auxiliary Power Supply 

ARIS Active Rack Isolation System 

AR Atmosphere Revitalization 

ARC Ames Research Center 

ARS Atmospheric Revitalization System 

ASCR Assured Safe Crew Return 

ASK Ames Stowage Kit 

ASL Atmosphere Sampling Line 

ASV Air Selector Valve 

ATCS Active Thermal Control System 

Advanced Television Systems Committee 

ATU Audio Terminal Unit 

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AUAI Assembly UHF Audio Interface 

AVU Artificial Vision Unit 

AVV Air Vent Valve 

BC Bus Controller 

BCDU Battery Charge/Discharge Units 

BCU Backup Drive Control Unit 

BDU Backup Drive Unit 

BGA Beta Gimbal Assembly 

BIT/BITE Built-In Test/Equipment 

BIV Bulkhead Isolation Value 

BMRRM Bearing Motor Roll Ring Module 

BOL Beginning of Life 

BP/ECG Blood Pressure/Electrocardiogram 

BPS Biomass Production System 

BSP Baseband Signal Processor 

BTLS Basic Trauma Life Support System 

BTR Biotechnology Refrigerator 

BUS Bus Controller Unit 

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/D Countdown 

C/L Crew Lock 

CA Control Attitude 

CB 

cb 

Control Bus 

Circuit Breaker 

CBM Common Berthing Mechanism 

CCAA Common Cabin Air Assembly 

CCD Cursor Control Device 

CCDB Configuration Controller Database 

CCPK Crew Contamination Protection Kit 

CCTV Closed Circuit Television 

CDDT Common Display Development Team 

CDRA Carbon Dioxide Removal Assembly 

CDRS Carbon Dioxide Removal System 

CDS Command and Data Software 

CEU Control Electronics Unit 

CEVIS Cycle Ergometer with Vibration Isolation System 

CFA Cabin Fan Assembly 

CGA Cable Guide Assembly 

CGS Cable Guide Shoe 

CheCS Crew Health Care System 

CHX Condensing Heat Exchanger 

CLA Camera Light Assembly 

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CLPA Camera, Light, and Pan/Tilt Assembly 

CMG Control Moment Gyroscope 

CMO Crew Medical Officer 

CMRS Crew Medical Restraint System 

Comm Communications 

COTS Commercial-Off-The-Shelf 

CPCG-H Commercial Protein Crystal Growth-High 

CPFSK Continuous Phase Frequency Shift Key 

CPS Cabin Pressure Sensor 

CPU Central Processing Unit 

CRPCM Canadian Remote Power Control Module 

CSA-CP Compound Specific Analyzer-Combustion Products 

CSA-H CSA-Hydrazine 

CSC Computer Software Component 

CSCI Computer Software Configuration Item 

CTB Cargo Transfer Bag 

CVIU Common Video Interface Unit 

CVT Current Valve Table 

CVV Carbon Dioxide Vent Valve 

CWC Contingency Water Collection 

CWR Collapsible Water Reservoir 

DA Depressurization Assembly 

DAIU Docked Audio Interface Unit 

DC Docking Compartment 

DCP Display and Control Panel 

DCPCG-V Dynamically Controlled Protein Crystal Growth-Vapor 

DCSU Direct Current Switching Unit 

DDCU DC to DC Converter Unit 

DIO Discrete Input/Output 

DMCU Docking Mechanism Control Unit 

DOF Degrees of Freedom 

DPS Data Processing System 

E/L Equipment Lock 

EACP EMU Audio Control Panel 

EAIU EMU Audio Interface Unit 

EAS Early Ammonia Servicer 

ECB Electronics Control Board 

ECG Electrocardiogram 

ECLSS Environmental Control and Life Support System 

ECS Early Communications Subsystem 

Environmental Control System 

ECU Electronic Control Unit 

EDDA EMU Don/Doff Assembly 

EEATCS Early External Active Thermal Control System 

EELS Emergency Egress Lighting System 

EET Experiment Elapsed Time 

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EETCS Early External Thermal Control System 

EFGF Electrical flight grapple fixture 

EIA Electrical Interface Assembly 

ELPS Emergency Lighting Power Supply 

ELS Emergency Lighting Strip 

EMU Extravehicular Maneuvering Unit 

 EXPRESS Memory Unit 

EOL End of Life 

EPLS Emergency Lighting Power Supply 

EPS Electrical Power System 

ESA External Sampling Adaptor 

ESP External Stowage Platform 

ETI Elapsed Time Indicator 

EUE Experiment Unique Equipment 

EV Extravehicular 

EV-CPDS Extravehicular – Charged Particle Directional Spectrometer 

EVA Extravehicular Activity 

EVD External Visual Display 

EVR Extravehicular Robotics 

EXPRESS Expedite the Processing of Experiments to the Space Station 

FC Firmware Controller 

FCC Flat Collector Circuit 

Federal Communications Commission 

FCV Flow Control Valve 

FD Flight Day 

FDA Fault Detection Annunciation 

FDI Failure Detection and Isolation 

FDIR Fault, Detection, Isolation and Recovery 

FDS Fire Detection and Suppression 

FGB Functional Cargo Block 

FPU Fluid Pumping Unit 

FRGF Flight Releasable Grapple Fixture 

FSEGF FSE Grapple Fixture 

GAS Get Away Special 

GFE Government Furnished Equipment 

GLA General Lighting Assembly 

GLONASS Global Navigational Satellite System 

GNC Guidance and Navigation Computer 

GPC General Purpose Computer 

GPS Global Positioning System 

GSE Ground Support Equipment 

GSM Gas Supply Module 

GUI Graphical User Interface 

HCS Humidity Control System 

HCU Headset Control Unit 

64
STS-111

HDR High Data Rate 

HEC Headset Extension Cable 

HEPA High-Efficiency Particulate Arrestor (a filter for the CCAA) 

HGA High Gain Antenna 

HP High Pressure 

HPGT High Pressure Gas Tank (see ONTO) 

HRF Human Research Facility 

HRFM High Rate Frame Multiplexer 

HRM High Rate Modem 

 Heart Rate Monitor 

I/O Input/Output 

IAA Internal Antenna Assembly 

IAC Internal Audio Controller 

IAS Internal Audio System 

ICAPC Increased Capacity Adaptive Payload Carrier 

ICC Integrated Cargo Carrier 

IDA Integrated Diode Assembly 

IEA Integrated Equipment Assembly 

IELK Individual Equipment Liner Kit 

I/F Interface 

IFHX Interface Heat Exchanger 

IFM In Flight Maintenance 

IM-GAP Internal Motor Gap 

IMCA Integrated Motor Controller Assembly 

IMS Inventory Management System 

IMV Intermodule Ventilation 

IOCU Input/Output Controller Unit 

IP International Partner 

IRed interim Resistive Exercise Device 

IRED Isolated Resistive Exercise Device 

IRU In-flight Refill Unit 

ISA International Sampling Adapter 

ISIS International Subrack Interface Standard 

ISO Inventory Stowage Officer 

ISPR International Standard Payload Rack 

ISS International Space Station 

ISSIS International Space Station Interface Standard 

ISSP International Space Station Program 

ISSSH International Space Station Systems Handbook 

ITCS Internal Thermal Control System 

IV-CPDS Intravehicular-Charged Particle Directional Spectrometer 

IVA Intravehicular Activity 

IVSU Internal Video Switch Unit 

JEU Joint Electronics Unit 

JEUS Joint Expedited Undocking and Separation 

65
STS-111

JSC Johnson Space Center 

KBAR Knee-Brace Assembly Replacement 

KFT KSC Fixation Tube 

KSC Kennedy Space Center 

LAB Lower Avionics Bay 

LAN Local Area Network 

LARR Lab Atmosphere Revitalization Rack 

LB Local Bus 

LCA Lab Cradle Assembly 

LCD Liquid Crystal Display 

LDA Launch Deployment Assembly 

LDR Low Data Rate 

LEE Latching End Effector (both SRMS and SSRMS) 

LED Light Emitting Diode 

LFDP Load Fault Detect/Protect 

LGA Low Gain Antenna 

LLA Low Level Analog 

LNS Lab Nitrogen System 

LP Launch Package 

LRU Line Replaceable Unit 

LTA Launch to Activation 

LTL Low Temperature Loop 

LVLH Local Vertical/Local Horizontal 

MA Mechanical Assembly 

MAM Manual Augmented Mode 

MAS Microbial Air Sampler 

Mb Megabytes 

MBE Metal Bellows Expander 

MBM Manual Berthing Mechanism 

MBS Mobile Base System 

MBSU Main Bus Switching Unit 

MCA Major Constituent Analyzer 

MCAS MBS Common Attach System 

MCAVV MCA Vacuum Valve 

MCC Mission Control Center 

MCC-H MCC-Houston 

MCC-M MCC-Moscow 

MCDS Multifunction CRT Display System 

MCS Motion Control System 

MCU MBS Computer Unit 

MDL Middeck Locker 

MDM Multiplexer/Demultiplexer 

MDPS Meteoroid and Debris Protection System 

MEC Medical Equipment Computer 

MELFI Minus 80 Lab Freezer for ISS 

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STS-111

MER Mission Evaluation Room 

MFCV Manual Flow Control Valve 

MILA Merritt Island launch area 

MLE Middeck Locker Equivalent 

MLI Multilayer Insulation 

MM/OD Micrometeoroid/Orbital Debris 

MO Medical Operations 

MOD Mission Operations Directorate 

MOV Manual Only Valve 

MPEV Manual Pressure Equalization Valve 

MPLM Mini Pressurized Logistics Module 

Multipurpose Logistics Module 

MPMs/MRLs Manipulator Positioning Mechanisms/ 

Manipulator Retention Latches 

MPR Manual Pulmonary Resuscitator 

MRS Mobile Remote Servicer 

MSD Mass Storage Device 

MSG Microgravity Science Glovebox 

MSS Mobile Servicing System 

MT Mobile Transporter 

MTCL Mobile Transporter Capture Latch 

MTL Moderate Temperature Loop 

MUP Mission Unique Process 

MWA Maintenance Work Area 

NASA National Aeronautics and Space Administration 

NCS Node Control Software 

NDS Nutrient Delivery System 

NET No Earlier Than 

NIV Nitrogen Isolation Valve 

Nm Newton meter 

NPRV Negative Pressure Relief Valve 

NST Near Saturation Threshold 

NTSC National Television Systems Committee 

OCA Orbital Communication Adapter 

OCAD Operational Control Agreement Document 

OCJM Operator Commanded Joint Position Mode 

OCPM Operator Commanded POR Mode 

ODA Orbiter Disconnect Assembly 

ODM Orbiter Arm Drive Mechanism 

ODS Orbiter Docking System 

OIU Orbiter Interface Unit 

OIV Oxygen Isolation Valve 

ONS Off Nominal Situations 

OPP OSVS Patch Panel 

OPS Operations (Operational) 

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ORBITECH Orbital Technologies Corporation 

ORCA Oxygen Recharge Compressor Assembly 

ORU Orbital Replacement Unit 

OSO Operations Support Officer 

OSVS Orbiter Space Vision System 

OSVU Orbiter Space Vision Unit 

P&S Pointing and Support Software 

PAD Portable Foot Restraint Attachment Device 

PAV Process Air Valve 

PB Power Bus 

PBA Portable Breathing Apparatus (mask) 

PCA Pressure Control Assembly 

PCAM Protein Crystallization Apparatus for Microgravity 

PCBA Portable Clinical Blood Analyzer 

PCG-STES Protein Crystal Growth, Single Locker Thermal Enclosure System 

PCMCIA Personal Computer Memory Card International Adapter 

PCMMU Pulse Code Master Modulation Unit 

PCP Pressure Control Panel 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PD Physical Device 

PDA Payload Disconnect Assemblies 

Passive Docking Assembly 

PDB Power Distribution Box 

PDGF Power and Data Grapple Fixture 

PDI Payload Data Interface 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PDS Passive Dosimetry System 

PDV Perforated Damper Valve 

PEHB Payload Ethernet Hub Bridge 

PEHG Payload Ethernet Hub Gateway 

PESTO Photosynthesis Experiment and System and Operations 

PEV Pressure Equalization Valve 

PFCS Pump Flow Control Subassembly 

PFE Portable Fire Extinguisher 

PG Product Group 

PGSC Payload and General Support Computer 

PJAM Pre-stored Joint Position Auto-sequenced Mode 

PL Payload 

PL PRI Primary Payload 

PLSS Portable Life Support System 

PMA Pressurized Mounting Panel 

Pressurized Mating Adapter 

PMCU Power Management Control Unit 

PMP Payload Mounting Panel 

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PNOM Procedural Nomenclature 

POA Payload ORU Accommodation 

POR Points of Reference 

PPA Pump Package Assembly 

PPAM Pre-stored POR Auto-sequence Mode 

ppO2 Partial Pressure of Oxygen 

PPRA Positive Pressure Relief Assembly 

PPRV Positive Pressure Relief Valve 

PRLA Payload Retention Latch Assembly 

PSA Power Supply Assembly 

PSP Payload Signal Processor 

PSS POA Support Structure 

PTB Payload Timing Buffer 

PTCS Passive Thermal Control System 

PTT Push To Talk 

PTU Pan/Tilt Units 

PUNT Peremptory Unilateral Network Tracking 

PV Photovoltaic 

PVM Photovoltaic Module 

PWP Power Work Platform 

PV Photovoltaic 

PVCU Photovoltaic Control Unit 

PVM Photovoltaic Module 

PVTCS Photovoltaic Thermal Control System 

QD Quick Disconnect 

 

R&MA Restraint and Mobility Aids 

R&R Remove and Replace 

R-S Reed-Solomon 

R/F Refrigerator/Freezer 

RAB Rack Attachment Block 

RAIU Russian Audio Interface Unit 

RAM Random Access Memory 

Radiation Area Monitor 

RAMU Rheostat Air Mix Valve 

RCU Remote Control Unit 

RED Resistive Exercise Device 

RF Radio Frequency 

RFCA Rack Flow Control Assembly 

RFG Radio Frequency Group 

RGS Russian Ground Site 

RHC Rotational Hand Controller 

RHX Regenerative Heat Exchanger 

RIC Rack Interface Controller 

RIV Rack Isolation Value 

RMS Remote Manipulator System 

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STS-111

ROEU Remote Operated Electrical Umbilical 

ROFU Remote Operated Fluid Umbilical 

ROS Russian Orbital Segment 

RPC Remote Power Controller 

RPCM Remote Power Controller Module 

RPDA Remote Power Distribution Assembly 

RS Russian Segment 

RSA Russian Space Agency 

RSP Respiratory Support Pack 

Resupply Support Platform 

RSR Resupply Stowage Rack 

RT Remote Terminal 

RTD Resistive Temperature Device 

RTL Ready to Latch 

 Ready to Launch 

RU Remote Unit 

RWS Robotic Workstation 

S0 Starboard Zero 

SARJ Solar Alpha Rotary Joint 

SASA S-Band Antenna Support Assembly 

SAW Solar Array Wing 

SCA Switchgear Controller Assembly 

SCSI Serial Command and Monitoring Interface 

SCU Servicing and Cooling Umbilical 

Sync and Control Unit 

SD Smoke Detector 

SDO Solenoid Driver Output 

SDS Sample Delivery System 

SGANT Space-to-Ground Antenna 

SHOSS Space Hab Oceaneering Space System 

SJRM Single Joint Rate Mode 

SLDP Spacelab Logistics Double Pallet 

SM Service Module 

SMCC Service Module Central Computer 

SMDP Six Service Module Debris Panel 

SMMMOD Service Module Micrometeoroid/Orbital Debris 

SMTC Service Module Terminal Computer 

SOC State of Charge 

SOV Shutoff Valve 

SPCE Servicing and Performance Checkout Equipment 

SPD Serial Parallel Digital 

SPDA Secondary Power Distribution Assembly 

SPDM Special Purpose Dexterous Manipulator 

SPL Sound Pressure Level 

SPP Science Power Platform 

SRMS Shuttle Remote Manipulator System 

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SSC Station Support Computer 

Subsystem Computer 

SSCS Space-to-Space Communication System 

SSE Space Station Eyewash 

SSER Space-to-Space EMU Radio 

SSK Surface Sampler Kit 

SSOR Space-to-Space Orbiter Radio 

SSOV Sample line Shut-off Valve 

SSP Space Shuttle Program 

Standard Switch Panel 

SSPC Solid State Power Controller 

SSPCM Solid State Power Control Module 

SSRMS Space Station Remote Manipulator System 

SSSR Space-to-Space Station Radio 

SSU Sequential Shunt Unit 

SSW Scenario Set-up Workstation 

STS Space Transportation System 

SVS Space Vision System 

SW Software 

TA Thruster Assist 

TCCS Trace Contaminant Control Subassembly 

TCCV Temperature Control and Check Valve 

TCS Thermal Conditioning System 

Thermal Control System 

TDK Transportation Device Kit 

TDMA Time Division Multiple Access 

TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

TEPC Tissue Equivalent Proportional Counter 

TFL Telemetry Format Load 

THC Temperature and Humidity Control 

Translational Hand Controller 

TIG Time of Ignition 

TOCA Total Organic Carbon Analyzer 

TRC Transmitter Receiver Controller 

TVIS Treadmill Vibration Isolation System 

UAB Upper Avionics Bay 

UB User Bus 

UDG User Data Generation 

UF Utilization Flight 

UIA Umbilical Interface Assembly 

UIP Utility Interface Panel 

UHF Ultrahigh Frequency 

UMA Umbilical Mechanism Assembly 

UOP Utility Outlet Panel 

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USOS United States Orbital Segment 

VAJ Vacuum Access Jumper 

VBSP Video Baseband Signal Processor 

VCR Video Cassette Recorder 

VDA-2 Vapor Diffusion Apparatus – Second Generation 

VDS Video Distribution System 

Video Distribution Subsystem 

VDU Video Distribution Unit 

VES Vacuum Exhaust System 

VES/VRS Vacuum Exhaust/Resource System 

VGA Video Graphics Array 

VGS Video Graphics Software 

VHF Very High Frequency 

VIS Vibration Isolation System 

VMDS Valve Motor Drive Switch 

VRCV Vent/Relief Control Valve 

VRIV Vent/Relief Isolation Valve 

VRS Vacuum Resource System 

VRV Vent/Relief Valve 

VSC Video Signal Converter 

VSU Video Switch Unit 

VTR Video Tape Recorder 

WAA Wireless Antenna Assembly 

WHS Workstation Host Software 

WMK Water Microbiology Kit 

WMV Water Modulating Valve 

WOV Water ON/OFF Valve 

WPP Water Pump Package 

WRM Water Recovery and Management 

WS Water Separator 

WS&A Water Sampler and Archiver Kit 

WVA Water Vent Assembly 

WVNT 

WVS Wireless Video System 

ZSR Zero-g Stowage Rack 

72
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Media Assistance 

NASA Television Transmission 

NASA Television is available through the GE2 satellite system which is located on 

Transponder 9C, at 85 degrees west longitude, frequency 3880.0 MHz, audio 6.8 MHz. 

The schedule for television transmissions from the orbiter and for mission briefings will be 

available during the mission at Kennedy Space Center, Fla.; Marshall Space Flight Center, 

Huntsville, Ala.; Dryden Flight Research Center, Edwards, Calif.; Johnson Space Center, 

Houston, Texas; and NASA Headquarters, Washington, DC. The television schedule will be 

updated to reflect changes dictated by mission operations. 

Status Reports 

Status reports on countdown and mission progress, on-orbit activities and landing 

operations will be produced by the appropriate NASA news center. 

Briefings 

A mission press briefing schedule will be issued before launch. During the mission, status 

briefings by a flight director or mission operations representative and when appropriate, 

representatives from the payload team, will occur at least once each day. The updated 

NASA television schedule will indicate when mission briefings are planned. 

Internet Information 

Information is available through several sources on the Internet. The primary source for 

mission information is the NASA Human Space Flight Web, part of the World Wide Web. 

This site contains information on the crew and its mission and will be updated regularly with 

status reports, photos and video clips throughout the flight. The NASA Shuttle Web's 

address is: 

http://spaceflight.nasa.gov

General information on NASA and its programs is available through the NASA Home Page 

and the NASA Public Affairs Home Page: 

http://www.nasa.gov

or 

http://www.nasa.gov/newsinfo/index.html

Shuttle Pre-Launch Status Reports 

http://www-pao.ksc.nasa.gov/kscpao/status/stsstat/current.htm

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STS-111

Information on other current NASA activities is available through the Today@NASA page: 

http://www.nasa.gov/today/index.html

The NASA TV schedule is available from the NTV Home Page: 

http://spaceflight.nasa.gov/realdata/nasatv/schedule.html

Resources for educators can be found at the following address: 

http://education.nasa.gov

Access by CompuServe 

Users with CompuServe accounts can access NASA press releases by typing "GO NASA" 

(no quotes) and making a selection from the categories offered. 

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STS-111

Media Contacts 

Dwayne Brown 

NASA Headquarters 

Washington 

Dwayne.brown@hq.nasa.gov

Space Shuttle/Space Station Policy 

202-358-1726 

Debbie Rahn 

NASA Headquarters 

Washington 

Debbie.rahn@hq.nasa.gov

International Partners 

202-358-1638 

Donald Savage 

NASA Headquarters 

Washington 

donald.savage@hq.nasa.gov 

Space Science Policy, Budget 

202-358-1727 

Eileen Hawley 

Johnson Space Center 

Houston 

Eileen.hawley1@jsc.nasa.gov

Astronauts/Mission Operations 

281-483-5111 

George Diller 

Kennedy Space Center 

Kennedy Space Center, Fla. 

George.Diller-1@ksc.nasa.gov

Space Shuttle Launch Operations 

321-867-2468 

Bruce Buckingham 

Kennedy Space Center 

Kennedy Space Center, Fla. 

Bruce.Buckingham-1@kmail.ksc.nasa.gov

Launch Operations 

321-867-2468 

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Kari Kelley Allen 

The Boeing Company 

Houston 

Kari.k.allen@boeing.com

International Space Station 

281-226-4844 

Glen Golightly 

The Boeing Company 

Huntington Beach, Calif. 

Robert.g.golightly@boeing.com

Space Shuttle 

714-372-4742 

Dan Beck 

Boeing Rocketdyne 

Canoga Park, Calif. 

Daniel.c.beck@boeing.com

Space Shuttle Main Engines 

818-586-4572 

Jack King 

United Space Alliance 

Kennedy Space Center, Fla. 

KingJW@usafoo.unitedspacealliance.com

Shuttle Processing 

321-861-4358 

Dave Drachlis 

Marshall Space Flight Center 

Huntsville, Ala. 

Dave.Drachlis@msfc.nasa.gov

Space Shuttle 

256-544-0034 

76