STS-98 

Table of Contents

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

Crew Members .............................................................................................................. 5 

Mission Profile ...............................................................................................................8 

Mission Objectives ..................................................................................................... 10 

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

Rendezvous ................................................................................................................ 18 

EVAs 

STS-98 EVA ............................................................................................................... 20 

Experiments 

Biological Protein Crystal Growth -- Enhanced Gaseous Nitrogen Dewar (EGN)......... 24 

Shuttle Ionospheric Modification With Pulsed Local Exhaust (SIMPLEX)..................... 25 

Using Space to Observe the Earth ............................................................................... 26 

Changes in the Yellow River Delta, 1989-2000 ............................................................ 27 

Coral Reefs................................................................................................................... 28 

El Niño – Southern Oscillation ...................................................................................... 29 

Lower Nile River, Egypt ................................................................................................ 30 

DTO/DSO/RME 

DTO 263 Shuttle Automatic Reboost Tuning................................................................ 31 

DSO 496 Individual Susceptibility to Post-Space Flight Orthostatic Intolerance........... 32 

DSO 498 Space Flight and Immune Function (pre-/postflight only).............................. 33 

DTO 675 Incapacitated EVA Crewmember Translation................................................ 34 

DTO 700-14 Single-String Global Positioning System.................................................. 35 

DTO 805 Crosswind Landing Performance .................................................................. 36 

DSO 802 Educational Activities .................................................................................... 37 
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Mission Benefits 

Scientific Research on the International Space Station ................................................ 38 

Documenting Changes on our Home Planet ................................................................ 39 

Shuttle Reference and Data 

Shuttle Abort History ................................................................................................... 40 

Shuttle Abort Modes ................................................................................................... 42 

Space Shuttle Rendezvous Maneuvers ...................................................................... 46 

Space Shuttle Solid Rocket Boosters ......................................................................... 47 

Space Shuttle Super-Lightweight Tank (SLWT) ......................................................... 55 

Acronyms and Abbreviations .................................................................................. 56 

Media Assistance ...................................................................................................... 65 

Media Contacts ......................................................................................................... 67
STS-98

Mission Overview 

Scientific Cornerstone Set for Delivery to ISS 

The U.S. Laboratory "Destiny" - centerpiece of scientific research aboard the 

International Space Station – is poised for launch aboard Space Shuttle Atlantis no 

earlier than 6:11 p.m. EST on Feb. 7, 2001. It is the first of six planned research 

modules of the station, and also will serve as the command and control center for the 

entire complex. 

Partially outfitted with five systems racks containing equipment to provide electrical 

power and cooling for future racks, and computers for control of the entire ISS, 

Destiny’s delivery and activation heralds the transfer of ISS operations from the Russian 

Mission Control Center outside Moscow to NASA’s Mission Control in Houston. Destiny 

is the second U.S. module to be launched to the ISS and will be mated to the Unity 

module, which was launched in December 1998. 

The 28-foot-long, 14-foot-diameter laboratory weighs 31,000 pounds and cost 

approximately $1.4 billion. It is the most sophisticated and versatile space laboratory 

ever built and eventually will house an additional 18 racks for crew support and scientific 

research that can be removed and replaced periodically as experiment operations 

warrant. This versatility will allow researchers from around the world to conduct 

experiments in the unique microgravity environment of space as never before. New 

racks will arrive with the next shuttle mission in March that also will deliver the second 

group of station residents – the Expedition Two crew – and bring home the current 

occupants, Expedition One Commander Bill Shepherd, Pilot Yuri Gidzenko and Flight 

Engineer Sergei Krikalev. 

Veteran astronaut Ken Cockrell, making his fourth space flight, will command the STS -

98 mission of Atlantis. Rookie Pilot Mark Polansky joins Cockrell on the forward flight 

deck. Seated behind them on the flight deck for launch and landing is Mission Specialist 

Marsha Ivins, who will serve as the flight engineer, and help activate Destiny after she 

uses the shuttle’s robot arm to attach the lab to the station. She is the most experienced 

space traveler on the crew with four previous flights, including one to the Mir space 

station in 1997. 

Atlantis will serve as the platform for three space walks to complete outside assembly 

and connection of electrical and plumbing lines between the laboratory, station and a 

relocated shuttle docking port. Mission Specialists Tom Jones and Bob Curbeam will 

conduct the space walks. While outside, Jones’ suit will have red striping around the 

pant legs and Curbeam’s will be all white. The third and final space walk will be the 60th 

in the shuttle program dating back to 1983 and the 100th in U.S. spaceflight history 

dating back to 1965. 

Jones is making his fourth flight, while Curbeam is embarking on his second mission. 

For launch, Curbeam will sit behind Polansky on the flight deck swapping places with 

Jones on the middeck for entry and landing. 

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The day after launch, the shuttle crew will check out the robotic arm’s operation in 

preparation for the work it will do to install the laboratory and serve as a high-tech 

cherry picker to move the two astronauts around the outside of the station and shuttle 

during the space walks. The primary arm operator will be Ivins with Cockrell serving as 

her backup. Polansky will be the intravehicular crewmember, or choreographer for the 

three space walks. 

Atlantis will dock to the station about 43 hours after launch no earlier than the evening 

of Feb. 9th. Later that day, the cabin pressure will be lowered in preparation for the 

space walks, which will begin the next day. Within two hours of docking, hatches will 

swing open between Atlantis and the ISS enabling the shuttle and station crews to greet 

one another. It will be the second visit of a shuttle crew with the Expedition One crew, 

which has been aboard the station since Nov. 2. The hatches will be closed and 

reopened periodically throughout docked operations to accommodate the space walks 

and the outfitting of Destiny. 

The two crews will spend a week working together transferring supplies to and from the 

station and activating the newest pressurized module of the ISS. Destiny will bring the 

station to a mass of about 112 tons with dimensions of 171 feet long, 90 feet high and 

240 feet wide. That surpasses Mir in terms of habitable volume. 

Destiny will provide many more functions of the station in addition to serving as the 

platform for experiment operations. It is launched with five system racks already 

installed. They include two avionics racks, two thermal control system racks and an 

atmosphere revitalization system rack. Each is capable of being tilted downward to 

provide access to the area behind. 

The two avionics racks house equipment controlling the Communications and Tracking, 

Environmental Control and Life Support System, Thermal Control System, Command 

and Data Handling, and the Electrical Power System. These racks manage the audio 

equipment, video switching, and the computer switching boxes, called 

Multiplexer/Demultiplexers, which provide computer control of lab systems. 

There are two thermal control system racks that circulate chilled water to cool other 

racks and the cabin air. One is a ‘low temperature’ system, with water chilled to about 4 

degrees Celsius. The low temperature system provides cooling to selected racks. The 

‘moderate temperature’ system, with water chilled to about 17 degrees Celsius, cools 

selected racks and the cabin air. 

The atmosphere revitalization (AR) rack provides for carbon dioxide removal, trace 

contaminant control, and monitoring of the cabin air. On orbit, the AR rack will be moved 

from its launch location to its operational location during lab outfitting on Flight Day 5. 

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Additionally, the lab controls the function of the gyroscopes, called Control Moment 

Gyros (CMGs). These were preintegrated into the Z1 Truss launched on STS-92 in the 

fall of 2000 and will be activated during STS-98. The four CMGs are electrically 

powered and will provide attitude control of the station. At least two are required to 

provide attitude control without the need for supplementary control using the thrusters 

on Zvezda or Zarya. 

Atlantis is scheduled to undock from the station no earlier than Feb. 16 and land no 

earlier than Feb. 18 back at the Kennedy Space Center, FL. The Expedition One crew 

will continue the outfitting of Destiny after Atlantis departs. 

STS-98 marks the 23rd flight for Atlantis and the 102nd in shuttle program history. It 

also will be the seventh shuttle visit to the station and 12th dedicated to the assembly 

and operation of the complex. The other launches included two Russian Protons, two 

Progress supply vehicles and the Soyuz carrying the Expedition One crew. 

A Quick Look at the STS-98 Mission 

Flight Day One 

Atlantis launches and conducts the first in a series of rendezvous burns to prepare for a 

docking with the International Space Station. 

Flight Day Two

Flight Day Two is a day of preparation as the astronauts check out the shuttle's robotic 

arm, tools that will be used in support of the next day's rendezvous and docking with the 

Space Station, and a checkout of the spacesuits that will be used during three 

scheduled space walks. 

Flight Day Three

Atlantis will dock with the International Space Station, and after a series of leak checks, 

the hatches between the two spacecraft will swing open allowing the STS-98 and 

Expedition One crews to meet. Cabin pressure on board Atlantis will be lowered in 

preparation for space walks. 

Flight Day Four 

Astronauts Tom Jones and Bob Curbeam will conduct the first of three space walks to 

remove and temporarily stow a shuttle docking port on the Z1 Truss; install Destiny to 

the station’s Unity module; make umbilical connections between Destiny and the Z1 

Truss; and begin laboratory activation. 

Flight Day Five 

Control Moment Gyros, that will provide attitude control for the station will be spun up 

and initial testing begun; outfitting of Destiny will continue as will transfer operations and 

set up of environmental racks and systems. 

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Flight Day Six

On the second of three space walks, the astronauts will attach a shuttle docking port to 

the forward end of Destiny; install a Power Data Grapple Fixture and Video Signal 

Converter on Destiny, for subsequent use by the ISS robotic arm scheduled for delivery 

in April 2001; and install micrometeoroid debris shielding on Destiny. 

Flight Day Seven

The crew will enjoy some scheduled off-duty time as testing of the CMGs continue and 

the shuttle boosts the station's altitude. 

Flight Day Eight

On the third and final scheduled space walk, the astronauts will install a spare S-band 

antenna assembly; connect umbilicals between the shuttle docking port and Destiny; 

install window shutters on Destiny; and practice an "incapacitated crew rescue" 

technique. 

Flight Day Nine

The two crews will complete final transfer operations; conduct a crew news conference 

and educational television event; perform an additional altitude reboost for the station if 

required; say final farewells and close the hatches between the two space craft. 

Flight Day Ten

Atlantis will undock from the station and perform a flyaround before departing from the 

vicinity of the station. The crew is scheduled for additional off-duty time. 

Flight Day Eleven

The astronauts' attention will turn to a return trip home as they check out all of the 

shuttle systems used for landing and stow away equipment on board. 

Flight Day Twelve

The crew will begin formal deorbit preparations, conduct a deorbit burn and return for a 

landing at the Kennedy Space Center. 

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Crew Members 

Commander: Kenneth D. Cockrell 

Ken Cockrell, 50, is the Commander of Atlantis for the first flight of 2001 to install 

the U.S. Laboratory Destiny to the International Space Station. 

As Commander, Cockrell is primarily responsible for overall mission success and 

safety of the flight, and will be at the controls for Atlantis’ docking to the ISS on 

the third day of the mission. 

Cockrell will be the lead for the initial activation of Destiny’s systems from a 

control panel at the aft flight deck of Atlantis after the facility is installed and will 

back up Marsha Ivins in the operation of Atlantis’ robot arm, which will be used to install Destiny, 

relocate a Station docking port to the aft berthing mechanism on Destiny and transport Atlantis’ space 

walkers to various locations on the ISS during their three excursions outside the shuttle.

Previous Space Flights:

A former Navy test pilot, Cockrell is making his fourth flight into space, having previously served as a 

Mission Specialist on STS-56 in 1993, as Pilot on STS-69 in 1995 and as Commander on STS-80 in 

1996. 

Ascent Seating: Flight Deck - Port Forward

Entry Seating: Flight Deck - Port Forward

Pilot: Mark L. Polansky 

Mark Polansky, 44, is Atlantis’ Pilot for the STS-98 mission to install the U.S. 

Laboratory Destiny to the International Space Station. 

Polansky will be responsible for Atlantis’ key propulsion, hydraulic and guidance 

systems during launch and landing and will assist Commander Ken Cockrell 

during Atlantis’ rendezvous with the ISS. Polansky also will be at Atlantis' 

controls during the post undocking flyaround of the station. Photographs taken 

during the flyaround are used to document the current conditions of the station 

following the addition of the Destiny module. 

In addition, Polansky will be the intravehicular crew member, or choreographer, for the three space 

walks to be conducted by Tom Jones and Bob Curbeam to help install Destiny to the Unity module, 

hook up critical umbilical lines between the newly arrived laboratory and other Station components 

and perform other Station assembly tasks. 

Previous Space Flights:

Making his first flight during STS-98, Polansky is a former Air Force test pilot who joined NASA in 

1992 as an aerospace engineer and research test pilot prior to becoming an astronaut.

Ascent Seating: Flight Deck - Starboard Forward

Entry Seating: Flight Deck - Starboard Forward

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Mission Specialist 1: Robert L. Curbeam 

Bob Curbeam (Cdr., USN), 38, is making his second flight into space aboard 

Atlantis to deliver the U.S. Laboratory Destiny to the International Space Station, 

having first flew on the STS-85 mission in 1997. 

Curbeam is Mission Specialist 1 (MS 1) for the STS-98 mission and will be one 

of two space walkers during the flight. He is designated Extravehicular 

crewmember 2 (EV 2) for the three space walks he will conduct with Tom Jones 

and will wear the pure white spacesuit. He and Jones will help to install the 

laboratory on the Unity module, hook up umbilical lines between Destiny and the 

Unity module and perform other Station assembly tasks. He will also be responsible for the operation 

of Atlantis’ docking system which will be used to link up to a similar device on the ISS. 

Curbeam will be seated on Atlantis’ flight deck for launch and down on the middeck for landing.

Previous Space Flights:

STS-98 is Curbeam's second space flight.

Ascent Seating: Flight Deck - Starboard Aft 

Entry Seating: Middeck - Port

EV2 

Mission Specialist 2: Marsha S. Ivins 

Marsha Ivins, 49, is making her fifth flight into space on Atlantis’ mission to 

install the U.S. Laboratory Destiny to the International Space Station. 

Ivins will serve as flight engineer during Atlantis’ launch and landing, backing up 

Commander Ken Cockrell and Pilot Mark Polansky on the shuttle’s flight deck as 

Mission Specialist 2 (MS 2). 

Ivins will play a key role during the flight, with primary responsibility for the 

operation of Atlantis’ robot arm which will be used to install Destiny to the Unity 

module, relocate a Station docking port to the aft berthing mechanism on Destiny and transport 

Atlantis’ space walkers to various locations on the ISS during their three excursions outside the 

Shuttle. Ivins will also join Commander Ken Cockrell for the initial activation of laboratory systems and 

the rest of her crewmates for the outfitting of the laboratory itself. Ivins will also be the lead for the 

transfer of cargo from Atlantis to the ISS and the stowage of used items on Atlantis transferred from 

the Station. 

Ivins will also be responsible for much of the photography and television tasks on the mission, in 

documenting the continuing assembly of the growing orbital outpost.

Previous Space Flights:

Ivins previously flew on the STS-32 mission in 1990, the STS-46 mission in 1992, the STS-62 mission 

in 1994 and the STS-81 mission to the Russian Mir Space Station in 1997. 

Ascent Seating: Flight Deck - Center Aft

Entry Seating: Flight Deck - Center Aft

RMS 

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Mission Specialist 3: Thomas D. Jones 

Tom Jones (Ph.D.), 45, will be making his fourth flight into space on Atlantis’ 

mission to install the U.S. Laboratory Destiny to the International Space Station. 

Jones will serve as Mission Specialist 3 (MS 3) and will be down on the middeck 

for launch and on the flight deck for landing. Jones is designated Extravehicular 

crewmember 1 (EV 1) for the three space walks he and Bob Curbeam will 

conduct during Atlantis’ mission and wear the spacesuit bearing the red stripes 

on the elbows and the knees. 

Jones and Curbeam will help to install the Destiny laboratory on the Unity module, hook up umbilical 

lines between Destiny and Unity and perform other Station assembly tasks. Jones will also join his 

crewmates for the outfitting of the laboratory once they enter Destiny on the fifth day of the mission. 

Jones is responsible for many of Atlantis’ navigation systems during the Shuttle’s rendezvous with the 

ISS and will perform Earth observation photography during the flight, using his expertise from his first 

two missions on which he served as the Payload Commander for a series of radar systems to study 

the Earth’s topography and environment.

Previous Space Flights:

Jones previously flew on the STS-59 and 68 missions in 1994 and the STS-80 mission in 1996. 

Ascent Seating: Middeck - Port

Entry Seating: Flight Deck - Starboard Aft

EV1 

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Mission Profile

Crew

Commander: Kenneth D. Cockrell

Pilot: Mark L. Polansky

Mission Specialist 1: Robert L. Curbeam

Mission Specialist 2: Marsha S. Ivins

Mission Specialist 3: Thomas D. Jones

Launch

Orbiter: Atlantis OV104

Launch Site: Kennedy Space Center Launch Pad 39A

Launch Window: 2.5 to 5 Minutes

Altitude: 173 Nautical Miles

Inclination: 51.6 Degrees

Duration: 10 Days 19 Hrs. 28 Min.

Vehicle Data

Shuttle Liftoff Weight: 4,520,235 lbs.

Orbiter/Payload Liftoff Weight: 254,694 lbs.

Orbiter/Payload Landing Weight: 198,909 lbs.

Software Version: OI-28

Space Shuttle Main Engines: (1 MB pdf)

SSME 1: 2052 SSME 2: 2044 SSME 3: 2047

External Tank: ET-106A ( Super Light Weight Tank)

SRB Set: BI-105PF

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Shuttle Aborts

Abort Landing Sites

 RTLS: Kennedy Space Center Shuttle Landing Facility

 TAL: Zaragoza

 AOA: Edwards Air Force Base, California

Shuttle Abort History

Landing

Landing Date: 02/18/01

Landing Time: 12:56 PM (eastern time)

Primary Landing Site: Kennedy Space Center Shuttle Landing Facility

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Mission Objectives

Atlantis OV104

Launch: Wednesday, Feb. 7, 2001 

 6:11 PM (eastern time)

Overview

The primary objective of STS-98, International Space Station Assembly Mission 5A, is 

to deliver and install the U.S. Destiny Laboratory onto the ISS. The centerpiece of 

research on this world-class scientific orbiting outpost, this workshop in space will 

support experiments and studies in cancer, diabetes and materials, just to name a few.

The aluminum U.S. laboratory module is 28 feet long and 14 feet wide. It is comprised 

of three cylindrical sections and two endcones that contain the hatch openings through 

which astronauts will enter and exit the module. Destiny will be mated to the forward 

port of Unity.

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In Destiny are five systems racks that will provide life-sustaining functions on board 

including electrical power, cooling water, air revitalization, and temperature and humidity 

control. Each rack weighs about 1,200 pounds. Six additional racks will be flown to 

Destiny on STS-102. Four standoffs provide raceways for module utilities—interfaces 

for ducting, piping, and wiring to be run to/from the individual racks and throughout the 

Lab. Twelve racks that will provide platforms for a variety of scientific experiments will 

follow on subsequent missions. In total, Destiny will hold 23 racks – six each on the port 

and starboard sides and overhead, and five on the deck. 

Astronauts will work inside the pressurized facility to conduct research in numerous 

scientific fields. Scientists throughout the world will use the results to enhance their 

studies in medicine, engineering, biotechnology, physics, materials science, and Earth 

science. 

The Boeing Co. began construction of the 16-ton, state-of-the art research laboratory in 

1995 at the Marshall Space Flight Center in Huntsville, Ala. Destiny was shipped to the 

Kennedy Space Center in Florida in 1998 and was turned over to NASA for pre-launch 

preparations in August 2000. 

Destiny’s Laboratory Structure

Internal to the laboratory are racks, rack standoffs, and vestibule jumpers. The lab racks 

house the system hardware in removable modular units. The rack standoffs provide a 

volume for ducting, piping and wiring to be run to/from the individual racks and 

throughout the Lab. The racks interface to the piping and wiring in the standoff via 

outlets and ports located in the standoffs at the base end of each rack location.

Jumpers in the vestibule, the area between Unity and Destiny, connect the piping and 

wiring between the two. Grounding straps between Unity and Destiny will be installed. 

One side of the grounding strap will be connected to the Active Common Berthing 

Mechanism (ACBM) on Unity, while the other end will be connected to the Passive 

Common Berthing Mechanism (PCBM) on Destiny.

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Some of the mechanisms on Destiny are the CBMs (passive and active), hatches, and 

the laboratory window shutter. The ACBM is in the forward port of the laboratory. It will 

be attached to the PCBM in Pressurized Mating Adapter 2 (PMA 2) when the PMA is 

berthed to the forward port of Destiny at the conclusion of the mission. Destiny’s ACBM 

cannot be operated until the laboratory is activated. The PCBM on Destiny is located in 

the laboratory’s aft port. The ACBM in Unity’s forward port will be latched to the 

laboratory’s PCBM to berth Destiny to Unity.

Each of the two berthing ports on Destiny contains a hatch. The aft hatch (hatch to 

Unity) will be opened and will remain open (unless a situation arises requiring a module 

to be isolated). The forward hatch will be used as the main access to the orbiter on 

future missions until Node 2 arrives. 

Each hatch has a window. The hatches can be opened or closed from either side. The 

hatches have a pressure interlock feature, which prevents the hatch from being opened 

if there is a negative pressure across the hatch (higher pressure on the outside of the 

hatch).

Destiny has an optical quality window (principally for Earth science observations) and a 

window shutter to protect the window from potential micrometeoroid and orbital debris 

strikes during the life of the ISS. The crew manually opens the shutter to use the 

window. The shutter will be installed during the third scheduled space walk.

Installation and Activation 

Mission Specialist Marsha Ivins will use the shuttle’s robotic arm to attach Destiny to the 

forward port of Unity. Over the course of three scheduled space walks, Mission 

Specialists Tom Jones and Bob Curbeam will perform external outfitting and connect 

umbilical cables to provide power and data capability between Destiny and the space 

station. Following Destiny’s installation to Unity, Ivins will once again use the robot arm 

to relocate Pressurized Mating Adapter 2 (PMA-2), which was moved to a temporary 

location to allow the installation of Destiny. She then will remove PMA-2 from its 

temporary location on the Z1 Truss and attach it to Destiny’s forward Common Berthing 

Mechanism (CBM). At that point, Commander Ken Cockrell will issue a series of 

computer commands from the aft flight deck of Atlantis to command the final latching 

and berthing operations.

Lab installation activities will begin on Flight Day 4 with the first space walk. Key 

activities include connecting all of the critical power and fluid umbilicals between the Z1 

Truss and the lab. The ISS crew will complete Unity-to-Destiny vestibule outfitting 

toward the end of the space walk. Together these connections will permit the lab 

activation upon completion of the space walk. The activation sequence of events is as 

follows:

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Lab Activation Sequence of Events

Step Rationale Executed by

1 Activates the converters in the Lab DDCUs to provide secondary power to the Lab 

systems

Orb crew

2-3 Once the DDCUs are on, there is no need to have the Node 1 MDMs be the bus 

controllers on the CB GNC-1 and CB GNC-2. The Config 9 command is sent to each 

of the Node 1 MDMs so that once power is applied to the C&C MDM, it will not see 

any BCs on the GNC buses, and it will automatically transition to Primary.

Orb crew

4-5 The configuration command sent to the Primary Node 1 MDM will likely cause a loss of 

connection with the EPCS as well as the OIU. These interfaces are reestablished so 

the procedure can continue.

Orb crew

6 The RPCs are closed that provide power to the C&C1 MDM. It should initialize and 

transition to Primary in approximately 4 minutes.

Orb crew

7-8 The status of the C&C1 MDM is checked to verify that it is nominal. The ISS crew will 

have direct connectivity through a PCS machine once the C&C1 MDM transitions to 

Primary, providing extra insight to the orbiter crew.

Orb/ISS crew

9 The ISS crew can then perform the procedures to reestablish LDR S-band which was 

lost during the vestibule connections made on FD-5.

ISS crew

10 The N1-1 MDM is commanded to be an RT on the LB SYS-LAB 1 bus since it no 

longer needs to be BC, and the INT MDM will be expecting to find no BC on that bus 

when it is powered up.

Orb crew

11 The INT2 MDM is powered up by closing the appropriate RPCs that allow power to the 

MDM. The N1-2 MDM must become an RT on the LB SYS-LAB 2 bus within 2 

minutes of powering on the INT2 MDM so that the INT2 MDM will transition to the 

Operational mode.

Orb crew

12-13 The configuration command sent to the Primary Node 1 MDM will likely cause a loss of 

connection with the EPCS as well as the OIU. These interfaces are reestablished so 

the procedure can continue.

Orb crew

14 The status of the INT2 MDM is checked after the approximate 4-minute initialization 

time.Once again, the ISS crewmember through the PCS machine has a little more 

insight into the status of the MDM than the orbiter crew.

Orb/ISS crew

15 The Node 1 MDMs should already be synced to the broadcast time coming from the 

C&C1 MDM. Orb crew

16

The pass-thru interface is commanded that will allow the C&C1 MDM to be the 

recipient of all commands from the orbiter AFD PCS, and will also flow telemetry from 

the C&C1 MDM to the OIU and AFD PCS through the Node 1 MDMs. Orb crew

17 The OIU format is reloaded to accept the data stream coming from the C&C1 MDM 

rather than the Node 1 MDM.

Orb crew

18 The orbiter crew must now set up a PCS machine in the AFD to communicate with the 

C&C1 MDM.

Orb crew

19-21 The LA MDMs are powered on. After the 2-minute initialization is complete, their 

status is verified.

Orb crew

22 Bus communication is enabled to the RPCMs to prepare for closing various RPCs. Orb crew

23-26 RPCs are closed applying power to various pieces of MTL and LTL equipment in 

preparation for IATCS startup.

Orb crew

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After Destiny is activated and active cooling has been established to avionics, the 

ground will take over activation of the laboratory systems. The Pressure Control 

Assembly (PCA) will be activated, followed by smoke detectors. Then the Common 

Cabin Air Assembly will be started to provide air circulation and scrubbing of the 

atmosphere inside the laboratory. The Guidance, Navigation and Control 

Multiplexer/Demultiplexers (MDMs) will then be activated and loaded with the 

appropriate software. Destiny’s Power Management Controller Unit MDMs will be 

checked out as well. The ground will then command the Emergency Egress Lighting 

batteries to begin charging, followed by activation of the laboratory’s interior lights. The 

condensation (shell) heaters will be activated, and the survival heaters will be 

deactivated. The ground will also activate and check out much of the audio equipment 

in the laboratory. The Control Moment Gyros (CMGs) will also be prepared for spinup, 

which will occur the following day. 

Upon successful activation of Destiny’s systems, both the STS-98 crew and the 

Expedition One crewmembers will enter Destiny on Flight Day 5 and begin outfitting the 

lab.

During the second space walk scheduled for Flight Day 6, PMA-2 will be moved to 

Destiny’s forward port. The spacewalkers will then work together to remove the 

laboratory Power Data Grapple Fixture (PDGF) from the orbiter sidewall and install the 

PDGF on Destiny. The PDGF will be used by the Space Station Remote Manipulator 

System, the new station robotic arm that will arrive on Mission 6A. 

The third space walk is scheduled for Flight Day 8. Key activities planned include 

moving the spare S-Band Antenna Support Assembly from the orbiter to the ISS 

stowage site, installing the window shutter on the lab and connecting PMA-2 umbilicals 

to the lab.

Deferred Activation and Checkout

The ISS crew and/or ground controllers will perform some activation and checkout tasks 

of the laboratory after the orbiter crew ingress is complete. The ground will command a 

checkout of the Internal Video Distribution Subsystem Orbital Replacement Units 

(ORUs). As there is no video capability on this mission, this will be a functional checkout 

of the equipment to verify that it survived launch in good shape. The ground also will 

perform a health and status check of the Ku-band radio frequency group. Once again, 

this will be a health check of the ORUs because there will not be any Ku-band capability 

until Mission 5A.1.

The ISS crew will inspect the wastewater tank in Destiny to verify there are no leaks. 

Other activation procedures that will be performed by the ISS crew after Atlantis leaves, 

include the activation and checkout of the water vent system, inhibiting the water vent 

system, and activation and checkout of the vacuum vent system. The ISS crew will also 

install a Pressure Control System extension duct to assist the flow of air through the 

PCA.

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Systems

Destiny will provide the following for the International Space Station: Environmental 

Control and Life Support System, or ECLSS (temperature and humidity control; fire 

detection and suppression; atmosphere control and supply; wastewater, recovery and 

management; vacuum system); Thermal Control System (active thermal control system, 

passive thermal control system); Guidance, Control and Navigation; Extravehicular 

Activity; Extravehicular Robotics; Flight Crew Support; Communication and Tracking 

(audio system, video system, space-to-space communication system, Ku-band and Sband systems); Electrical Power System (EPS); Command and Data Handling; 

Structures and Mechanism; and Payload Capability.

The Command and Data Handling system gains 11 MDMs with the arrival of the lab. 

These MDMs are used to control the U.S. on-orbit segment systems including payloads. 

The Communication and Tracking system activates high-data rate S-band to replace the 

early com system. The audio system comes online and the hardware for Ku-band, UHF 

and the video distribution system are delivered but not activated until future missions.

The ECLSS maintains a pressurized habitable environment within the ISS by supplying 

correct amounts of oxygen and nitrogen, controlling the temperature and humidity, 

removing carbon dioxide and other atmospheric contaminants, and monitoring the 

atmosphere for the presence of combustion products. The system also collects, 

processes, and stores water removed from the ISS atmosphere. 

The ECLSS receives equipment in the laboratory that will be used during most of the 

assembly stages. The atmosphere control and supply subsystem contains the pressure 

control assembly, vent relief assembly, and manual pressure equalization valves and 

gas lines. A complete rack of atmosphere revitalization equipment arrives, and the 

Sample Delivery System lines launched in the Destiny and Unity are connected to the 

major constituent analyzer in Destiny. The temperature and humidity control subsystem 

sees the arrival of two common cabin air assemblies and more intermodule ventilation 

equipment, as well as avionics air assemblies in several racks. The standard fire 

detection and suppression equipment is launched with Destiny, as are the water 

recovery and management condensate tank, water vent assembly and waste and fuel 

cell water lines.

The electrical power system, which manages, controls, and distributes electrical power 

to the U.S pressurized modules, receives all the new electrical loads in the laboratory. 

Power is brought to the Destiny from the P6 array through the Z1/laboratory umbilical 

tray. The power is brought to two DC-to-DC converter units in the laboratory and is 

distributed to the secondary power distribution assemblies and downstream loads.

The Motion Control System takes a major step with this mission. The U.S. segment 

begins contributing to the attitude control of the ISS with the CMGs. The U.S. segment 

Guidance, Navigation and Control System takes control of the ISS with state vector and 

attitude inputs from the Russian segment. The Russian segment propulsive capability is 

still needed for joint attitude control during CMG desaturation and for reboost.

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Mission 5A delivers the systems that will assume station management and control from 

the Zvezda Service Module. The Motion Control System becomes integrated between 

Zvezda and Destiny’s computers.

The Thermal Control System activates the early external and internal thermal control 

systems to accommodate the addition of Destiny’s thermal loads.

The Russian segment continues to manage its own modules while interfacing with the 

U.S. segment Motion Control System for certain data and operations. The Node 1 MDM 

Node control software continues to provide closed-loop control of environmental, heater, 

thermal systems and power for Unity, the PMAs, and truss segments. Destiny’s MDM 

architecture controls the rest of the U.S. on-orbit segment. 

Mission 5A adds the additional capability of high-rate S-band and internal audio to the 

U.S. on-orbit segment. The S-band high-rate capability is the major communications 

and tracking addition to the ISS for Mission 5A. The S-band system provides two-way 

communications with the ISS and the Mission Control Center via the Tracking and Data 

Relay Satellite System for commands and system telemetry, voice and file transfer. The 

internal audio subsystem allows crewmembers to communicate with other 

crewmembers aboard the ISS.

Science

The centerpiece of research on the International Space Station, the U.S. Laboratory 

Destiny will support experiments and studies that may contribute to research toward 

cures for diseases like cancer and diabetes.

Destiny is the primary research laboratory for U.S. payloads. It will support experiments 

in microgravity research, human life science, fundamental biology and ecology, Earth 

observations, space science and commercial applications. By Flight 5A.1 (STS-102), 

the Destiny will support Earth photography and the Human Research Facility in which 

radiation measurements, psychological evaluations, and neural response experiments 

will be conducted. 

In 2002, shuttle flights will deliver the Minus Eighty Laboratory Freezer for ISS, 

Microgravity Science Glovebox and Window Observational Research Facility. 

Eventually, Destiny will house up to 13 payload racks with experiments in human life 

science, materials research, Earth observations and commercial applications. The 

results of these experiments will allow scientists to better understand our world and 

ourselves and prepare us for future missions, perhaps to the Moon and Mars.

Destiny will be joined by laboratory modules sponsored by the National Space 

Development Agency of Japan, European Space Agency and Rosaviakosmos.

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Flight Day Summary

DATE TIME (EST) DAY MET EVENT

02/07/01 6:11:00 PM 1 000/00:00 Launch

02/07/01 6:55:00 PM 1 000/00:44 OMS2 Burn

02/07/01 9:53:00 PM 1 000/03:42 NC1 Burn

02/08/01 9:17:00 AM 2 000/15:06 NC2 Burn

02/08/01 1:41:00 PM 2 000/19:30 NPC Burn

02/08/01 6:21:00 PM 2 001/00:10 NC3 Burn

02/09/01 7:08:00 AM 3 001/12:57 NH Burn

02/09/01 7:53:00 AM 3 001/13:42 NC4 Burn

02/09/01 9:26:00 AM 3 001/15:15 TI Burn

02/09/01 10:41:00 AM 3 001/16:30 RBar

02/09/01 11:56:00 AM 3 001/17:45 Docking

02/09/01 1:41:00 PM 3 001/19:30 ISS Hatch Open

02/09/01 2:11:00 PM 3 001/20:00 Transfer Operations

02/10/01 10:31:00 AM 4 002/16:20 EVA 1 Start

02/10/01 4:46:00 PM 4 002/22:35 EVA 1 End

02/11/01 8:11:00 AM 5 003/14:00 Lab Ingress

02/12/01 10:56:00 AM 6 004/16:45 EVA 2 Start

02/12/01 5:11:00 PM 6 004/23:00 EVA 2 End

02/14/01 10:36:00 AM 8 006/16:25 EVA 3 Start

02/14/01 4:46:00 PM 8 006/22:35 EVA 3 End

02/16/01 7:16:00 AM 10 008/13:05 ISS Hatch Close

02/16/01 9:10:00 AM 10 008/14:59 ISS Undock

02/16/01 10:17:00 AM 10 008/16:06 Final Sep

02/18/01 11:53:00 AM 12 010/17:42 Deorbit Burn

02/18/01 12:56:00 PM 12 010/18:45 Landing

Updated: 01/31/2001 

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Rendezvous 

Rendezvous and Docking Overview 

Overview 

Atlantis’ rendezvous with the International Space Station actually begins with its 

precisely timed launch from the Kennedy Space Center in Florida. The shuttle will 

rendezvous with the station either on Flight Day 3 or 4, based on the time and date of 

launch, and at a time based on ISS-orbiter phasing. 

The primary pre-rendezvous activities include a check-out of the orbiter's remote 

manipulator system, or robot arm, (RMS), the extravehicular mobility units (EMUs) or 

spacesuits, the Ku-band antenna, the orbiter docking system (ODS), and the ground 

command system. 

The final phase of rendezvous operations begins about three hours prior to Atlantis’ 

docking with the ISS. Atlantis will approach the ISS from below, in what is referred to as 

a plus-R bar approach, to minimize the effects of jet thruster firings on the station and its 

solar arrays. About 40 minutes before the terminal initiation burn (Ti burn) when Atlantis 

moves within 135,000 feet of the station, the shuttle’s rendezvous radar system is 

activated to provide supplemental navigation information. Prior to initiating the Ti burn, 

the crew will power on the ODS and activate Atlantis’s docking lights. 

A series of course correction burns will bring Atlantis to a point almost directly below 

and behind the station, at which point Commander Ken Cockrell initiates the manual 

portion of his approach to the ISS. 

Atlantis will intercept the R-bar about 700 feet below the station. Cockrell will slowly 

move Atlantis to a point about 600 feet below the station before performing a 180 

degree yaw maneuver to position Atlantis in a “tail forward” attitude for the final 

approach and docking. As Cockrell gently moves Atlantis toward the station, the shuttle 

will stationkeep at distances of 170 feet and 30 feet before initiating the final approach 

and docking. Solar arrays on the Zarya and Zvezda modules and the recently-installed 

P6 solar arrays will be feathered and locked at a predetermined angle, to limit the 

induced loads from shuttle thruster firings. 

Atlantis will dock with Pressurized Mating Adapter (PMA) 3 on the downward-facing port 

of the Unity module. 

At initial contact and capture, the ISS and Atlantis will go to free drift to avoid imposing 

excessive loads on the orbiter docking system (ODS). 

After capture, light-emitting diodes on PMA-3 will blink confirming the ISS is in free drift. 

The crew will be able to see the red indicators through the overhead window on 

Atlantis’s aft flight deck and verify that the ISS is in the free-drift mode before beginning 

the automatic rigidization and retraction process and closure of the capture latches 

between the two docking hatches. 

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Once a “hard dock” is confirmed, the ODS will be deactivated, solar arrays will resume 

sun tracking, and the Atlantis-ISS complex will maneuver to the mated attitude. 

Docked Operations

Hatches between Atlantis and the ISS will open about two hours after docking to allow 

the Expedition One and STS-98 crews to greet one another. After the greeting and 

some initial cargo transfer, the hatches will be closed and Atlantis’ cabin pressure will 

be lowered in preparation for the space walks, which will begin the next day. 

Throughout a week of docked operations, the hatches will be opened and closed to 

support the transfer of supplies and three scheduled space walks to outfit the Destiny 

laboratory module. 

On Flight Days 4, 6 and 8, Astronauts Tom Jones and Robert Curbeam will conduct 

space walks to relocate one docking port, attach the Destiny module and connect power 

cables; remove thermal coverings and hatch pins that were installed for launch; and 

relocate a spare S-band antenna assembly. 

The astronauts also will transfer equipment and supplies to the space station and outfit 

the Destiny laboratory for future use. 

Departure

Atlantis is scheduled to undock from the ISS on Flight Day 10. In preparation for the 

undocking the STS-98 crew will once again power-up the orbiter docking system, turn 

on the shuttle docking lights, terminate all OIU operations, and enable the shuttle’s 

navigational aids. 

Following its undocking, Pilot Mark Polansky will slowly back Atlantis away from the ISS 

at the rate of about 1/10 of a foot-per-second before beginning a flyaround. Atlantis will 

move to a point about 450 feet below the station before beginning a tail-forward circuit 

of the station, arriving once again at a position approximately 450 feet below the station. 

At that point, Polansky will perform a final separation burn to move Atlantis away from 

the station. 

Once Atlantis is about 30 feet away from the station, the Expedition One crew will 

activate the station’s attitude control systems. The Zvezda module will then maneuver 

station to its normal orientation for orbital operations, the solar arrays will be 

commanded to resume sun tracking, and the station docking system and lights will be 

deactivated. 

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STS-98

EVAs 

Three Space Walks Will Add Sophisticated Laboratory 

Overview 

Astronauts Tom Jones and Robert Curbeam will perfrom three spacewalks to continue 

assembly of the International Space Station while Atlantis is docked to the station during 

Shuttle mission STS-98. During the spacewalks, Jones will be identifiable by red stripes 

around the legs of his spacesuit while Curbeam's suit will be pure white. Astronaut 

Marsha Ivins will operate Atlantis' robotic arm from within the shuttle cabin during all of 

the spacewalks, and Pilot Mark Polansky will serve as the intravehicular crewmember, 

assisting with the choreography of the spacewalks from inside the cabin. As they are 

scheduled, the third spacewalk on STS-98 will be the 100th spacewalk conducted by 

United States astronauts. 

Flight Day Four: First Space Walk

The first space walk, planned to last about six hours and fifteen minutes, will be 

conducted on the fourth day of the mission, the day after Atlantis docks to the station. 

The overall objective is to mechanically attach the Destiny laboratory to the station and 

then connect electrical, computer and cooling lines between the lab module and station. 

The space walk is planned to prepare the laboratory to be entered by both the shuttle 

and station crews for the first time on the following day to begin its activation. 

Shortly before Jones and Curbeam begin the spacewalk, astronaut Marsha Ivins will 

latch Atlantis' robotic arm onto a capture fixture on one of the station's cone-shaped 

shuttle docking ports, called Pressurized Mating Adapter 2 (PMA-2), which occupies the 

berthing mechanism to which the Destiny lab must be attached. Before the 

spacewalkers leave the airlock, the shuttle crew will send commands to release the 

bolts holding PMA-2 to the station, and Ivins will move it from its berth, clearing the way 

for attaching Destiny to that berthing mechanism on the station's Unity connecting 

module. 

Jones and Curbeam will begin the space walk working in separate locations. Curbeam's 

first task will be to disconnect umbilicals between Atlantis and Destiny that had powered 

heaters on the module while in the shuttle payload bay. Next, he will remove covers, in 

place to prevent contamination during launch, from the Destiny lab's berthing 

mechanism at the aft end of Atlantis' payload bay. Meanwhile, Jones will climb up the 

station to the first truss segment, called the Z-1 Truss, almost 40 feet above Atlantis' 

cargo bay. On the Z-1 Truss, Jones will guide Ivins' work with the robotic arm, providing 

verbal cues to assist in aligning PMA-2 with a temporary storage location on the truss. 

Once properly aligned, Jones then will manually latch PMA-2 in place to the truss, 

temporarily out of the way of ongoing activities to attach the Destiny lab. 

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Next, as Ivins latches the arm onto Destiny, lifts it from the shuttle cargo bay and rotates it 

into position to be attached to the station, the two spacewalkers will work farther up the 

station truss to prepare the station's starboard early cooling system radiator to be 

outstretched later in the mission. Then, they will release gimbal locks on a station 

communications antenna in preparation for the later activation of that system. When Ivins 

maneuvers Destiny to its berthing port on Unity and the crew sends commands for the 

berthing system to bolt together, Jones and Curbeam will stand by to assist if needed. 

Once Destiny is securely attached to the station, Jones and Curbeam will begin connecting 

electrical, data and cooling lines between the new module and the rest of the station. 

Flight Day Six: Second Space Walk

During the second space walk, also planned to last about six hours and fifteen minutes, 

the PMA-2 shuttle docking port will be relocated from the temporary position on the 

station truss where it was placed during the first spacewalk to a permanent location at 

the forward end of the Destiny lab. Jones and Curbeam also will attach various 

equipment and fixtures to the exterior of the new module. 

After Ivins has latched Atlantis robotic arm onto PMA-2, Jones will manually loosen the 

latch that holds it to the temporary stowage location on the station. While Jones is 

working at the point on the station truss, Curbeam's first task will be to remove covers 

from the berthing mechanism at the forward end of the lab. Once Jones has released 

the temporary latch, Ivins will maneuver PMA-2 to the lab's forward berthing mechanism 

and attach it there, where it will serve as the primary shuttle docking location for most 

missions to come. 

Next, Jones will install thermal covers on the Destiny's four trunnions, the pins which 

held the module in the shuttle cargo bay during launch, and attach the exterior portion of 

a vent that will be used by the station's life support systems. Curbeam will install a 

slidewire along the length of the lab's exterior that will be used to ease the tether work 

required by future spacewalkers as they move up and down the length of the lab. 

Curbeam also will install several foot platform mounts and handrails. Jones will install a 

non-propulsive vent to Destiny’s Pressure Control Assembly (PCA), part of its 

environmental control and life support system. 

The next major task for both spacewalkers will be to install the future connection point 

for the station's robotic arm to Destiny’s exterior, preparing for the launch of that arm on 

shuttle mission STS-100 later in 2001. 

Ivins will maneuver the robotic arm into position for Jones to install a foot platform at its 

end in preparation for his work with the arm connection point, called a Power and Data 

Grapple Fixture (PDGF). Then, working from the arm foot platform, Jones will release 

the PDGF from its launch location in Atlantis' cargo bay and carry it to the position 

where it will be attached to Destiny. Meanwhile, Curbeam will be working at the 

attachment location on Destiny, removing two portions of the modules debris shielding 

to prepare to make electrical and computer connections for the PDGF. Jones will then 

install the fixture and both spacewalkers will replace the lab debris shields. 

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Flight Day Eight: Third Space Walk

The third space walk, planned to last a little over five hours, will attach a spare S-band 

communications antenna and equipment, called the S-Band Antenna Support Assembly 

(SASA), to the station; install an exterior shutter on the Destiny lab window; and connect 

electrical and data lines between the PMA-2 shuttle docking port and Destiny. At the 

end of the space walk, Jones and Curbeam also plan to conduct a test of the ability of 

the Simplified Aid for Extravehicular Activity Rescue (SAFER) jet backpack to maneuver 

two crewmembers. The SAFER jet packs are attached to spacewalker's spacesuits at 

all times as a type of "space lifejacket," to allow an astronaut to fly back to the station 

under his own power in the event he were to become untethered. 

The first task on the third space walk will be to remove the spare SASA from Atlantis’ 

cargo bay and attach it to a stowage location on the exterior of the station's lower truss 

segment, the Z-1 Truss. For that task, Curbeam will be in a foot platform at the end of 

the shuttle's robotic arm and Jones will assist from the station and shuttle exterior. 

Next, the two spacewalkers will work together to install an outside shutter on the 

Destiny lab window. The two spacewalkers will install the shutter and its associated 

gearbox and then remove a soft cover of insulation that protected the window during 

launch. 

They then will attach electrical and data connections between the PMA-2 shuttle 

docking port and the Destiny module. The connections will allow shuttle power and 

commands to reach the station on future missions, when PMA-2 becomes the primary 

shuttle docking location. 

The 30-minute SAFER test is planned as the last activity for the spacewalkers before 

they re-enter the shuttle cabin. 

EVA Timeline for Three Space Walks Will Add Sophisticated Laboratory 

Time Event

2/16:20 EVA 1 Airlock Egress

2/16:25 EVA 1 Sortie Setup

2/16:40 EVA 1 Secure PMA2 to Z1 Truss

2/16:40 EVA 1 Disconnect Lab Heater Umbilicals

2/17:05 EVA 1 Remove PCBM Cover

2/17:15 EVA 1 Release Starboard Radiator Cinch

2/17:35 EVA 1 Unbearth Lab

2/17:50 EVA 1 Release Starboard Radiator Winch

2/17:55 EVA 1 Release Space to Ground Antenna Gimbal Locks

2/18:05 EVA 1 Lab Pre-Install

2/18:40 EVA 1 EZ Setup Tasks

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Time Event

2/19:45 EVA 1 Connect LTA P612 Umbilical

2/19:45 EVA 1 Connect Z1/Lab NH3 Umbilical

2/20:30 EVA 1 Starboard Connectors CIDS 1

2/20:30 EVA 1 Port Connectors CIDS 1

2/21:25 EVA 1 Starboard Connectors CIDS 2

2:21:25 EVA 1 Port Connectors CIDS 2

2/21:55 EVA 1 Sortie Cleanup

2/22:15 EVA 1 Airlock Ingress

4/16:45 EVA 2 Airlock Egress

4/16:45 EVA 2 Release PMA 2

4/16:45 EVA 2 Remove Lab Thermal Cover

4/17:15 EVA 2 Sortie Setup

4/17:35 EVA 2 Install Trunnion Covers

4/17:35 EVA 2 Install Slidewire

4/18:30 EVA 2 Install Pressure Control Assembly (PCA) Vent

4/19:45 EVA 2 Install Payload Data Grapple Fixture (PDGF)

4/21:45 EVA 2 Install MMOD

4/22:15 EVA 2 Sortie Cleanup

4/22:40 EVA 2 Airlock Ingress

6/16:20 EVA 3 Airlock Egress

6/16:25 EVA 3 Transfer S-Band Antenna Support Assembly (SASA)

6/16:25 EVA 3 Sortie Setup

6/17:40 EVA 3 Install Shutter and Gearbox

6/18:10 EVA 3 Attach PMA 2 toLab Umbilicals

6/19:50 EVA 3 Sortie Cleanup

6/20:40 EVA 3 Incapacited Crew Demonstration

6/21:10 EVA 3 Airlock Ingress

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Experiments 

Biological Protein Crystal Growth -- Enhanced Gaseous 

Nitrogen Dewar (EGN) 

Prime: Principal Investigator: 

Project Manager:

Dr. Alexander McPherson, University 

of California, Irvine; 

Raymond A. French, NASA’s Marshall 

Space Flight Center in Huntsville, Ala.

 

Overview 

The second in a series of low-cost biological protein crystal growth experiments to be 

transferred to, and conducted aboard, the International Space Station, will again use the 

Enhanced Gaseous Nitrogen Dewar (EGN). Scientists anticipate that analysis of the 

human and other proteins that make up the payload may contribute to their 

understanding of gene function and help uncover the genetic roots of diseases. As part 

of a pilot education program, the payload also contains protein samples loaded by high 

school students and teachers from Alabama, California, Florida, Michigan, Tennessee 

and Texas. 

The microgravity environment, or near-weightlessness of space sometimes helps grow 

higher-quality protein crystals. This allows researchers to better understand the 

molecular structure of proteins and how these proteins perform everything from carrying 

medicines in the body to making plants resist disease. The data obtained from the 

crystals grown in space are used to produce models of the structure of the protein 

molecules. Researchers also expect these experiments to contribute to their 

understanding of how, and why, biological crystals grow differently in space than they 

do on Earth. 

History/Background 

The Enhanced Gaseous Nitrogen Dewar is a vacuum-jacketed container, similar to a 

thermos bottle, with an absorbent inner liner saturated with liquid nitrogen. Before 

launch, the protein samples are frozen to -321 degrees Fahrenheit (-196 degrees 

Celsius) and placed in the Dewar. Once in orbit, the Dewar is transferred from the 

shuttle to the International Space Station. During this time, the liquid nitrogen warms 

and boils off (changes to gas), and the samples begin to thaw. After about 11 days, 

when the nitrogen is completely boiled off and thawing is completed, the crystallization 

process begins. The experiment is self-activating and does not require crew interaction. 

The Dewar and protein crystals remain aboard the space station until they are returned 

to Earth by STS-102, scheduled for March 2001. 

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STS-98

Experiments 

Shuttle Ionospheric Modification With Pulsed Local Exhaust 

(SIMPLEX) 

 .

 

Overview 

The SIMPLEX payload has no flight hardware. Shuttle orbital maneuvering system 

(OMS) thruster firings are used to create ionospheric disturbances for observation by 

the SIMPLEX radars. SIMPLEX has five different radar sites used for collecting data: 

Arecibo, Kwajalein, Millstone Hill, Alice Springs, and Jicamarca. One of the radar sites 

will also use a low-level laser to observe the effects on the ionosphere resulting from the 

thruster firing. 

SIMPLEX is actually a "simple experiment" to study the complex interactions of exhaust 

vapors with the background atmosphere. This understanding will someday help us to 

detect, identify, and track the flight of unfriendly space vehicles with instruments that 

characterize and interpret the vehicle's exhaust plume. 

The objective of the SIMPLEX activity is to determine the source of very high frequency 

radar echoes caused by the orbiter and its OMS engine firings. The principal 

investigator will use the collected data to examine the effects of orbital kinetic energy on 

ionospheric irregularities and to understand the processes that take place with the 

venting of exhaust materials. SIMPLEX sensors may collect data during any encounter 

opportunity when the orbiter support activities meet the criteria defined. 

History/Background 

The Earth is surrounded by a layer of electrons and ions called the ionosphere, which 

ranges in altitude from 30 to 250 miles. This layer becomes disturbed when gaseous 

materials released in engine exhaust, like those from the Space Shuttle OMS, burn in 

the ionosphere. The gases react chemically with the ions to produce ion beams, which 

move at orbital speeds, leaving a trail of turbulence in their wake. Eventually, the ions 

recombine with electrons to produce an ionospheric hole covering an area of 30 by 30 

miles or greater. 

The SIMPLEX engine burns are scheduled over each radar site. The radar will send up 

radio wave pulses that scatter off of the electrons in the ionosphere. Radar will monitor 

both the turbulence produced by the ion beams and the ultimate reduction in electron 

density that causes the ionospheric hole. 

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Experiments 

Using Space to Observe the Earth 

 .

 

Overview 

Astronauts and Cosmonauts on the International Space Station are beginning their first 

scientific studies. They will be photographing the Earth’s surface as part of an early 

payload -- Crew Earth Observations. 

Since early space missions in the 1960s, astronauts have photographed the Earth 

below, observing the world’s geography and documenting transient events like storms, 

floods, fires, and volcanic eruptions. 

Target sites include major deltas in south and east Asia; coral reefs; smog-prone urban 

regions; areas experiencing major floods or droughts triggered by El Niño cycles, high 

altitude glaciers (reflecting longer-term climate changes), faults associated with major 

tectonic plate boundaries, and features on Earth, like impact craters, that are analogs to 

structures on other planets, like Mars. The Earth Sciences and Image Analysis 

Laboratory at the Johnson Space Center has provided a set of fact sheets as examples 

to better explain the science and applications behind some of these sites. 

The Expedition One crew continues that tradition observing selected sites throughout 

the world to enhance the existing data base and assist scientists in understanding these 

changes. During their time on the ISS, the astronauts will document ecologically 

sensitive areas such as coral reefs and meteorological phenomena such as El Nino. 

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STS-98

Experiments 

Changes in the Yellow River Delta, 1989-2000 

 .

 

Overview 

Underlying Science 

Coastal change caused by the effects of global warming and sea level rise, increasing 

population and development along all the world’s coastlines, and human modifications 

of coasts (subsidence, seawalls, jetties) is a global issue. The Chinese coastline along 

the Gulf of Bohai has always experienced dramatic changes — the delta of the Yellow 

River is the fastest changing coast on the Earth’s surface. Because the river carries an 

extremely heavy sediment load, the lower river channel silts up rapidly, resulting in 

frequent river course changes. The river has been engineered for millennia, but recent 

water demands and water diversions (amplified by several years of drought in the 

1990s) have resulted in little or no water reaching the coast. 

Dramatic changes in the tip of the Yellow River delta were documented by astronauts 

on the Space Shuttle between 1989 and 2000. Over this time, several hundred square 

kilometers have accreted and eroded from the coast. The delta grew nearly 400 km2 

between 1989 and 1995, then began eroding back. In 1997 a new channel was cut near 

the tip of the delta, providing the water and sediment a shorter route to the sea. 

Between 1995 and 1997, the delta area eroded back about 255 square kilometers. 

From 1997 to February 2000, the delta tip again grew nearly 100 square kilometers. 

Application 

Remote sensing and image analysis of image data are efficient strategies for examining 

regional changes that occur over large areas, and are a way of providing context for 

smaller-scale changes. The photographs collected by astronauts can be assembled in a 

time series of images demonstrating both the scale and specific locations of coastal 

change. Quantitative measurements can be made when the images are referenced to 

standard maps. Such analyses can identify both natural and human-induced changes, 

lending some understanding of the processes involved in the coastline evolution. The 

Crew Earth Observations payload on the International Space Station will target rapidly 

changing wetlands in southeast Asia, such as the Yellow River. 

27
STS-98

Experiments 

Coral Reefs 

 .

 

Overview 

Underlying Science 

Healthy coral reefs sustain local and national economies through fisheries, coastal 

protection, and tourism. In spite of these benefits, it has been estimated that 58% of 

coral reefs globally are threatened by human activities. Scientists still lack basic data 

about the locations, spatial extent and health of reefs. Major efforts are underway in the 

U.S. and around the world to improve the mapping information on coral reefs. Astronaut 

photographs are a unique data source for these efforts because data on reefs has been 

collected for many years, and the images are available in the public domain. Of 

particular value is the fact that the astronauts actively looked for low-cloud opportunities, 

and used them to photograph reef areas. Astronaut photographs can be used as 

primary data for maps of the locations of reef crests and as supplemental data for use 

with other satellite images, especially when it is important to distinguish small clouds 

from reef areas. 

Application 

Astronaut photographs are being used as base layers in an international compilation of 

information on coral reefs and their resources, known as ReefBase. Images have also 

been included in a prototype reef data distribution system that uses data from the 

SeaWiFS satellite sensor as a backbone for distribution of reef remote sensing data 

from a number of different satellites. Investigations comparing the level of detail that can 

be mapped from an astronaut photograph compared to other satellite data are nearing 

completion. The Crew Earth Observations payload on the International Space Station 

will collect targeted images of the Tuamotu Archipelago, American Samoa and the 

Philippines, to provide additional data for these mapping investigations. 

References 

Robinson, J. A., G. C. Feldman, N. Kuring, B. Franz, E. Green, M. Noordeloos, and R. 

P. Stumpf. 2000. Data fusion in coral reef mapping: working at multiple scales with 

SeaWiFS and astronaut photography. Proceedings of the 6th International Conference 

on Remote Sensing for Marine and Coastal Environments, Vol. 2, pp. 473-483. 

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Experiments 

El Niño – Southern Oscillation 

 .

 

Overview 

Underlying Science 

El Niño- Southern oscillation (ENSO) cycles occur every few years. During these 

events, weather patterns around the world are disrupted, the human and economic tolls 

from extreme droughts and floods can be great. ENSO events affect rainfall patterns—

leading to droughts in some places and extraordinary rainfall in others. Astronauts track 

indicators of drought such as increased incidence of wildfires and drops in the levels of 

lakes and reservoirs. Where rainfall increases, they observe floods and vegetation 

greening. The ISS crews will collect comparative photographs over parts of the world 

that were hardest hit by precipitation anomalies associated with the 1997-1998 El Niño. 

These new observations will build on the unprecedented data on El Niño-related floods 

and droughts that was collected by astronauts living on Mir. 

Application 

Imagery from space provides regional context for local events like floods or fires. The 

presence of smoke, the boundaries of smoke palls, and lake level fluctuations can be 

compiled for a regional and global assessment of El Niño impact. Rising and falling 

water levels in lakes, reservoirs and rivers, and vegetation characteristics can be 

monitored repeatedly to determine responses and rates of response to extreme weather 

events. 

References 

Evans, C.A.; Robinson, J.A.; Wilkinson, M.J.; Runco, S.; Dickerson, P.W.; Amsbury, 

D.L.; and Lulla, K.P.; 2000. The 1997-1998 El Niño: Images of floods and drought, in 

Dynamic Earth Environments: Remote Sensing Observations from Shuttle-Mir Missions. 

K. Lulla and L. Desinov (eds); John Wiley & sons, New York, pp. 61-76.

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Experiments 

Lower Nile River, Egypt 

 .

 

Overview 

Underlying Science 

When it was completed in 1971, the Aswan Dam and Lake Nasser were considered one 

of the engineering marvels of the world. The lake functions as a water reservoir and 

allows Egypt to maintain high agricultural and industrial productivity in the Nile Valley 

despite flood and drought cycles. Lake levels fluctuated in the 1980s and 1990s in 

response to regional cycles of drought and monsoons. Today, the Egyptian government 

has broken ground on new irrigation projects that will further transform the Egyptian 

landscape. Since late 1998, four new lakes have been flooded in the Toshka depression 

(the New Valley Project) west of Lake Nasser . Soon, the Toshka depression will 

support agriculture and industry, and expand the amount of Egypt’s arable land. 

Application 

The images of the New Valley Project and the rest of the lower Nile can be used as a 

time series to demonstrate changes over time. Astronauts have photographed the Nile 

and Lake Nasser since 1965, and the filling of the Toshka depression since late 1998. 

Since November 1998, the area of the lakes has grown from roughly 250 km2 

(November 1998) to about 1300 km2 (February 2000). We anticipate seeing the extents 

of these lakes fluctuate with changes in annual rainfall annual wet-dry seasons, and 

future development in the New Valley. Monitoring watershed changes from space 

provides a useful and efficient way to demonstrate changes over a large area and 

communicate impacts to government and scientific user groups. Analyses from these 

images can be used as contributing or stand-alone data for regional impacts of climate 

shifts and continued development in the New Valley. 

References 

Evans, C., Robinson, J. and Stern, R., 2000. NASA Astronaut Observations of Egyptian 

Water Projects, presented at the International Conference on the Western Desert, 

Cairo, Egypt, Jan 17-20, 2000. 

Evans, C.; Robinson, J., Scott, J; Stern, R.; Thurmond, A; Abdelsalam, M., 2000. 

Egypt’s new reservoirs: a 35-year time series of land and water changes along the 

lower Nile, American Geophysical Union.

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DTO/DSO/RME

Shuttle Automatic Reboost Tuning 

DTO 263 

Overview 

Shuttle reboost of the space station using the automatic reboost software requires jetfiring separation to avoid excitation of the joined Shuttle/ISS structural natural 

frequencies. Accurate specification of this jet-firing separation requires measurement of 

the on-orbit joined structure natural frequencies. A brief execution of the reboost 

software using benign parameters, such as burn length, will allow acquisition of 

structural dynamics data to validate the preflight estimate of the structural natural 

frequencies and damping and, thus, the jet-firing separation time. 

The structural natural frequencies can be measured using the shuttle inertial 

measurement unit downlinked data, and the jet-firing separation time can be 

implemented by display inputs by the crew. This DTO is appropriate for shuttle flights to 

the ISS between availability of OI-28 reboost software and availability of the vernier jet 

reboost capability and which have a significant structural configuration difference from 

previous flights. 

History/Background 

This is the first flight of DTO 263. 

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DTO/DSO/RME

Individual Susceptibility to Post-Space Flight Orthostatic 

Intolerance 

DSO 496 

Overview 

Susceptibility to postflight orthostatic intolerance – lightheadedness or fainting upon 

return to Earth – is highly individual. Some astronauts are little affected, while others 

have severe symptoms. Women are more often affected than men. The goal of this 

DSO is to discover the mechanisms responsible for these differences in order to 

customize countermeasure protocols. 

History/Background

It has been well documented that spaceflight significantly alters cardiovascular function. 

One of the most important changes from a crew safety standpoint is postflight loss of 

orthostatic tolerance, which causes astronauts to have difficulty walking independently 

and induces lightheadedness or fainting. These may impair their ability to leave the 

orbiter after it lands. 

This DSO will perform a flight-related study, designed to clarify preflight and postflight 

differences in susceptible and non-susceptible astronauts. There are no on-orbit 

activities associated with this DSO.

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DTO/DSO/RME

Space Flight and Immune Function (pre-/postflight only) 

DSO 498 

Overview 

Astronauts face an increasing risk of contracting infectious diseases as they work and 

live for longer periods in the crowded conditions and closed environments of spacecraft 

such as the International Space Station. The effects of spaceflight on the human 

immune system, which plays a pivotal role in warding off infections, is not fully 

understood. Understanding the changes in immune function caused by exposure to 

microgravity will allow researchers to develop countermeasures to minimize the risk of 

infection. 

History/Background 

The objective of this DSO is to characterize the effects of spaceflight on neutrophils, 

monocytes, and cytotoxic cells, which play an important role in maintaining an effective 

defense against infectious agents. The premise of this study is that the space 

environment alters the essential functions of these elements of human immune 

response. 

Researchers will conduct a functional analysis of neutrophils and monocytes from blood 

samples taken from astronauts before and after the flight. They will also assess the 

subjects’ pre- and postflight production of cytotoxic cells and cytokine. 

This study will complement previous and continuing immunology studies of astronauts’ 

adaptation to space. 

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DTO/DSO/RME

Incapacitated EVA Crewmember Translation 

DTO 675 

Overview 

The objective of this DTO is to verify techniques to allow an extravehicular activity 

(EVA) crewmember to return an incapacitated EVA crewmember to the shuttle airlock. 

History/Background 

The DTO will be manifested on several shuttle missions to allow the evaluation of a 

number of techniques to determine the most efficient. The evaluations will be conducted 

in the orbiter payload bay or on ISS so that the results of the DTO can be applicable to 

the ISS as well as the shuttle. Success will be defined as the ability to translate the 

equivalent length of the payload bay (at a minimum) and into the airlock safely, i.e., 

without posing additional risk to the crew, spacesuit, or vehicle. 

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DTO/DSO/RME

Single-String Global Positioning System 

DTO 700-14 

Overview 

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 using a modified military GPS receiver processor and the existing 

orbiter GPS antennas. GPS data may be downlinked during all mission phases. 

History/Background 

This is the 13th flight of DTO 700-14. 

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DTO/DSO/RME

Crosswind Landing Performance 

DTO 805 

Overview 

The purpose of this DTO is to demonstrate the capability to perform a manually 

controlled landing in the presence of a crosswind. The testing is done in two steps. 

1. Pre-launch: Ensure planning will allow selection of a runway with Microwave 

Scanning Beam Landing System support, which is a set of dual transmitters located 

beside the runway providing precision navigation vertically, horizontally, and 

longitudinally with respect to the runway. This precision navigation subsystem helps 

provide a higher probability of a more precise landing with a crosswind of 10 to 15 

knots as late in the flight as possible. 

2. Entry: 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. 

3. During a crosswind landing, the drag chute will be deployed after nose gear 

touchdown when the vehicle is stable and tracking the runway centerline. 

History/Background 

This DTO has been manifested on 61 previous flights. 

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DTO/DSO/RME

Educational Activities 

DSO 802 

Overview 

The purpose of this activity is to use the attraction of spaceflight to capture the interest 

of students and motivate them toward careers in science, engineering, and 

mathematics. Educational products will include 20-minute video lessons with scenes 

recorded both on-orbit and on the ground. The on-orbit video will comprise about a third 

of the finished video product and will consist of educational activities performed by the 

astronauts as well as other educational activities deemed appropriate by the 

Educational Working Group and the flight crew. 

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Benefits

Scientific Research on the International Space Station 

Crew Earth Observations 

The centerpiece of research on the International Space Station, the U.S. Laboratory 

Destiny will support experiments and studies that may lead to cures for cancer and 

diabetes. 

Destiny is the primary research laboratory for U.S. payloads. It will support experiments 

in microgravity research, human life science, fundamental biology and ecology, Earth 

observations, space science and commercial applications. By Flight 5A.1 (STS-102), 

the Destiny will support Earth photography and the Human Research Facility in which 

radiation measurements, psychological evaluations, and neural response experiments 

will be conducted. On Flight 6A, to expedite the processing of payloads to Space 

Station, racks containing microgravity and commercial payloads will be added to the 

Lab. 

In 2002, shuttle flights will deliver the Minus Eighty Laboratory Freezer for ISS, 

Microgravity Science Glovebox and Window Observational Research Facility. 

Eventually, Destiny will house up to 13 payload racks with experiments in human life 

science, materials research, Earth observations and commercial applications. The 

results of these experiments will allow scientists to better understand our world and 

ourselves and prepare us for future missions, perhaps to the Moon and Mars. 

Destiny will be joined by laboratory modules sponsored by the National Space 

Development Agency of Japan, European Space Agency and Rosaviakosmos.

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Benefits

Documenting Changes on our Home Planet 

Crew Earth Observations 

With much of their time committed to construction of the International Space Station, 

astronauts and cosmonauts also are beginning their first scientific studies. They will be 

photographing the Earth’s surface as part of an early payload, Crew Earth Observations. 

By keeping crew members active in observing the Earth, NASA is paving the way for a 

number of future Earth observing payloads that will place cameras and remote sensing 

instruments in an optical-quality window that is part of the U.S. Laboratory Module. 

Since early space missions in the 1960s, astronauts have photographed the Earth 

below, observing the world’s geography and documenting transient events like storms, 

floods, fires, and volcanic eruptions. Over the years, astronauts have also documented 

human impacts on the Earth — city growth, agricultural expansion, and reservoir 

construction. Today, images of the world from 10, 20 or 30 years ago provide valuable 

insight into Earth processes and the effects of human developments. 

Photographic images taken by astronauts serve as both primary data on the state of the 

Earth and as secondary data to be combined with images from other satellites in orbit. 

Through their photography of the Earth, ISS astronauts will build on the time series of 

imagery started 35 years ago—insuring that this record of Earth remains unbroken. Crew 

Earth Observations will focus on some of the most dramatic examples of change on the 

Earth’s surface. 

Target sites include major deltas in south and east Asia; coral reefs; smog-prone urban 

regions; areas experiencing major floods or droughts triggered by El Niño cycles, high 

altitude glaciers (reflecting longer-term climate changes), faults associated with major 

tectonic plate boundaries, and features on Earth, like impact craters, that are analogs to 

structures on other planets, like Mars. The Earth Sciences and Image Analysis 

Laboratory at the Johnson Space Center has provided a set of fact sheets as examples 

to better explain the science and applications behind some of these sites. 

Although today’s Earth observations made by astronauts are similar to those from historic 

space missions — crew members still use hand-held film cameras — they also use an 

electronic still camera that allows for near-real time image downlink and quick analysis. 

The first image of Earth downlinked from the ISS is posted at 

http://earthobservatory.nasa.gov/Newsroom/NewImages/images.php3?img_id=4436 . 

All of the imagery is cataloged and added to the database maintained at the Johnson 

Space Center by the Earth Sciences and Image Analysis Laboratory. Through today’s 

digital technologies and global networking, the catalog of imagery is available to 

scientists, educators, and the public at http://eol.jsc.nasa.gov.

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Shuttle Reference and 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 

T-4 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 and 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 threeengine 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 pitch-down maneuver (called powered pitch-down) takes the mated vehicle 

to the required external tank separation attitude and pitch rate. After main engine cutoff 

has been commanded, the external tank separation sequence begins, including a 

reaction control system 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. 

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(Depressing it after main engine cutoff selects the AOA abort mode.) The TAL abort 

mode begins sending commands to steer the vehicle toward the plane of the landing 

site. It also rolls the vehicle heads up before main engine cutoff and sends commands 

to begin an orbital maneuvering system propellant dump (by burning the propellants 

through the orbital maneuvering system engines and the reaction control system 

engines). This dump is necessary to increase vehicle performance (by decreasing 

weight), to place the center of gravity in the proper place for vehicle control, and to 

decrease the vehicle's landing weight. 

TAL is handled like a 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 in-flight 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 and 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 and 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 

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degrees). Previously, the attach ring formed a C and encircled the motor case 270 

degrees. 

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 heavyduty 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 

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ignition commands and nozzle thrust vector control. Each integrated electronic 

assembly has a multiplexer/ demultiplexer, which sends or receives more than one 

message, signal or unit of information on a single communication channel. 

Eight booster separation motors (four in the nose frustum and four in the aft skirt) of 

each SRB thrust for 1.02 seconds at SRB separation from the external tank. Each solid 

rocket 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. 

49
STS-98

SRB IGNITION 

SRB ignition can occur only when a manual lock pin from each SRB safe and arm 

device has been removed. The ground crew removes the pin during prelaunch 

activities. At T minus five minutes, the SRB safe and arm device is rotated to the arm 

position. The solid rocket motor ignition commands are issued when the three SSMEs 

are at or above 90-percent rated thrust, no SSME fail and/or SRB ignition PIC low 

voltage is indicated and there are no holds from the LPS. 

The solid rocket motor ignition commands are sent by the orbiter computers through the 

MECs to the safe and arm device NSDs in each SRB. A PIC single-channel capacitor 

discharge device controls the firing of each pyrotechnic device. Three signals must be 

present simultaneously for the PIC to generate the pyro firing output. These signalsarm, 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. 

50
STS-98

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 corre sponding SRB buses A, B and C. In addition, orbiter 

main dc bus C supplies backup power to SRB buses A and B, and orbiter bus B 

supplies backup power to SRB bus C. This electrical power distribution arrangement 

allows all SRB buses to remain powered in the event one orbiter main bus fails. 

The nominal dc voltage is 28 volts dc, with an upper limit of 32 volts dc and a lower limit 

of 24 volts dc. 

HYDRAULIC POWER UNITS 

There are two self- contained, independent HPUs on each SRB. Each HPU consists of 

an auxiliary power unit, fuel supply module, hydraulic pump, hydraulic reservoir and 

hydraulic fluid manifold assembly. The APUs are fueled by hydrazine and generate 

mechanical shaft power to a hydraulic pump that produces hydraulic pressure for the 

SRB hydraulic system. The two separate HPUs and two hydraulic systems are located 

on the aft end of each SRB between the SRB nozzle and aft skirt. The HPU 

components are mounted on the aft skirt between the rock and tilt actuators. The two 

systems operate from T minus 28 seconds until SRB separation from the orbiter and 

external tank. The two independent hydraulic systems are connected to the rock and tilt 

servoactuators. 

The APU controller electronics are located in the SRB aft integrated electronic 

assemblies on the aft external tank attach rings. 

The APUs and their fuel systems are isolated from each other. Each fuel supply module 

(tank) contains 22 pounds of hydrazine. The fuel tank is pressurized with gaseous 

nitrogen at 400 psi, which provides the force to expel (positive expulsion) the fuel from 

the tank to the fuel distribution line, maintaining a positive fuel supply to the APU 

throughout its 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 

51
STS-98

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. 

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 

52
STS-98

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. 

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 

53
STS-98

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. 

54
STS-98

Shuttle Reference and 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. 

55


1 

ACRONYMS AND ABBREVIATIONS 

A/L airlock 

AAA Avionics Air Assembly 

ABC Audio Bus Coupler 

ACBM Active Common Berthing Mechanism 

ACS Atmosphere Control System 

Atmosphere Control and Supply 

Attitude Control Subsystem 

AD Active Device 

AFD Aft Flight Deck 

AOH Assembly Operations Handbook 

APAS Androgynous Peripheral Assembly Systems 

APCU Assembly Power Converter Unit 

APDS Androgynous Peripheral Docking System 

APFR Articulating Portable Foot Restraint 

APM Attached Pressurized Module 

AR Atmosphere Revitalization 

ARCU American-to-Russian Power Control Unit 

ARS Air Revitalization System 

ASCR Assured Safe Crew Return 

ASV Air Selector Valve 

ATCS Active Thermal Control System 

ATU Audio Terminal Unit 

ATV Automated Transfer Vehicle 

AUAI ACS/UCS Audio Interface 

AV Avionics 

AVV Air Vent Valve 

BBA Baseplate Ballast Assembly 

BC Bus Controller 

BDT Binary Data Transfer 

BIA Bus Interface Adapter 

BIT Built-In Test 

BMR Body-Mounted Radiator 

BPDU Bitstream Protocol Data Unit 

BPSMU Battery Powered Speaker/Mike Unit 

BSP Baseband Signal Processor 

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 

CADU Channel Access Data Unit 

CB Command Bus 

CBM Common Berthing Mechanism 

56


2 

CCAA Common Cabin Air Assembly 

CCDB Configuration Control Data Bases 

CCH Crew Communication Headset 

CCHA Crew Communication Headset Assembly 

CCSDS Consultative Committee for Space Data Systems 

CCTV Closed-Circuit Television 

CDR Contract Data Requirement 

CDRA Carbon Dioxide Removal Assembly 

CETA Crew and Equipment Translation Aid 

CHeCS Crew Health Care System 

CHX Condensing Heat Exchanger 

CID Circuit Interrupt Device 

CIL Critical Items List 

CMG Control Moment Gyro 

CNPMS Current Navigational Parameters Measurement System 

CPS Cabin Pressure Sensor 

CRT Cathode-Ray Tube 

CRV Crew Return Vehicle 

CSCI Computer Software Configuration Item 

CSV Carbon Dioxide Selector Valve 

CTP Command and Telemetry Processor 

CTV Crew Transfer Vehicle 

CVIU Common Video Interface Unit 

CVT Current Value Table 

CVV Carbon Dioxide Vent Valve 

CWC Contingency Water Collection 

CWP Caution and Warning Panel 

DAIU Docked Audio Interface Unit 

DAP Digital Auto Pilot 

DCSU Direct Current Switching Unit 

DDCU DC to DC Converter Unit 

DDP Design Decision Package 

DDT&E Design, Development, Test and Engineering/Evaluation 

DMCU Docking Mechanism Control Unit 

DRAM Dynamic Random Access Memory 

DSCU Docking System Control Unit 

DSM Docking Storage Module 

DSP Digital Signal Processor 

EA Electronics Assembly 

Early Comm Early Communications 

EATC External Active Thermal Control 

EATCS External Active Thermal Control System 

ECLSS Environmental Control and Life Support System 

EDP Electronic Document Project 

57


3 

EEATCS Early External Active Thermal Control System 

EEL Emergency Egress Lighting 

EEPROM Electronically Erasable Programmable Read-Only Memory 

EETCS Early External Thermal Control System 

EF Exposed Facility 

EFGF Electrical Flight Grapple Fixture 

EIA Electrical Interface Assembly 

EIB Electrical Interface Box 

ELPS Emergency Lighting Power Source 

ELS Emergency Lighting Strip 

EMF Electromagnetic Force 

EMI Electromagnetic Interference 

EMU Extravehicular Mobility Unit 

EPCE Electrical Power Consuming Equipment 

EPCS Early Portable Computer System 

EPS Electrical Power System 

ERA European Robotic Arm 

ETI Elapsed Time Indicator 

ETRO Estimated Time of Return to Operation 

EV Extravehicular 

EVA Extravehicular Activity 

EVAS EVA System 

EXPRESS Expediting the Process of Experiments to the Space Station 

FCV Flow Control Valve 

FCT Flight Control Team 

FD Flight Day 

FDF Flight Data File 

FDIR Fault Detection, Isolation, and Recovery 

FDS Fire Detection and Suppression 

FGB Functional Cargo Block 

 Functional Energy Block (Russian) 

FQDC Fluid Quick Disconnect Coupling 

FRGF Flight Releasable Grapple Fixture 

FRR Flight Readiness Review 

FSE Flight Support Equipment (Environment) 

FSS Fluid Servicing System 

GFE Government-Furnished Equipment 

GFI Ground Fault Interrupter 

GLA General Luminaire Assembly 

GN&C Guidance, Navigation, and Control 

GLONASS Global Navigational Satellite System 

GPC General Purpose Computer 

GPS Global Positioning System 

GSFC Goddard Space Flight Center 

58


4 

H/W Hardware 

HCU Headset Control Unit 

HDR High Data Rate 

HEC Headset Extension Cable 

HEPA High Efficiency Particulate Air 

HGA High Gain Antenna 

HIC Headset Interface Cable 

HT High Temperature 

HX Heat Exchanger 

I/F Interface 

I/O Input/Output 

IAC Internal Audio Controller 

IAS Internal Audio System 

IATC Internal Active Thermal Control 

ICD Interface Control Document 

IDR Incremental Design Review 

IFHX Interface Heat Exchanger 

IG Inner Gimbal 

IMV Intermodule Ventilation 

INT Internal 

IOCU Input/Output Controller Unit 

IOS Integrated Operation Scenario 

IP International Partner 

IRD Interface Requirement Document 

ISPR International Standard Payload Rack 

ISA Inertial Sensor Assembly 

ISS International Space Station 

ITCS Internal Thermal Control System 

ITS Integrated Truss Segment 

IV Intravehicular 

IVA Intravehicular Activity 

IVDS Internal Video Distribution Subsystem 

IVS Internal Video System 

JEM Japanese Experiment Module 

JOP Joint Operation Panel 

JSC Lyndon B. Johnson Space Center 

Kbps Kilobytes per second 

kg kilogram 

km kilometer 

KSC Kennedy Space Center 

Lab Laboratory 

LCA Loop Crossover Assembly 

LCC Launch Commit Criteria 

59


5 

LDI Local Data Interface 

LDR Low Data Rate 

LDT Loads and Dynamics Team 

LED Light-Emitting Diode 

LGA Low Gain Antenna 

LHA Lamp Housing Assembly 

LLA Low Level Analog 

LP Launch Package 

LSAR Logistics Support Analysis Report 

LSS Life Support System 

LT Low Temperature 

LTA Launch to Activation 

LTL Low Temperature Loop 

M/OD Meteoroid/Orbital Debris 

MA Mechanical Assembly 

Mbps megabytes per second 

MBSU Main Bus Switching Unit 

MCA Major Constituent Analyzer 

MCS Motion Control System 

MCC-H Mission Control Center-Houston 

MCC-M Mission Control Center-Moscow 

MCDS Multifunction CRT Display System 

MDF Minimum Duration Flight 

MDM Multiplexer/Demultiplexer 

MET Mission Elapsed Time 

MFCV Manual Flow Control Valve 

MILA Merritt Island Launch Area 

MIP Mission Integration Plan 

MLI Multi-Layer Insulation 

mm millimeter 

MM/OD Micro Meteoroid/Orbital Debris 

MMU Mass Memory Unit

MOD Mission Operations Directorate 

MPDU Multiplexer Protocol Data Unit 

MPEV Manual Pressure Equalization Valve 

MPLM Mini Pressurized Logistics Module 

 Multi-Purpose Logistics Module 

MPM Manipulator Positioning Mechanism 

MRL Manipulator Retention Latch 

MRS BS Mobile Remote Servicer Base Structure 

ms milliseconds 

MSD Mass Storage Device 

MSS Mobile Servicing System 

MT Mobile Transporter 

Moderate Temperature 

60


6 

MTL Moderate Temperature Loop 

MUE MDM Utilities Extension 

μs microseconds 

n. mi. nautical mile 

NASA National Aeronautics and Space Administration 

NCS Node Control Software 

NPRV Negative Pressure Relief Valve 

NPV Nonpropulsive Vent 

NSP Network Signal Processor 

OCAD Operational Control Agreement Document 

OCC Onboard Complex Control 

OCCS Onboard Complex Control System 

ODF Onboard Data File 

ODS Orbiter Docking System 

OG Outer Gimbal 

OIU Orbiter Interface Unit 

OSD Operations Support Department 

OSTP Onboard Short Term Plan 

OSVS Orbiter Space Vision System 

P&S Pointing and Support 

P/L Payload 

P6 Port 6 

PAD PFR Attachment Device 

PAV Process Air Valve 

PBA Portable Breathing Apparatus 

PCA Pressure Control Assembly 

PCBM Passive Common Berthing Mechanism 

PCIA Portable Computer Interface Adapter 

PCMMU Pulse Code Modulation Master Unit 

PCN Page Change Notice 

PCP Pressure Control Panel 

PCR Portable Computer Receptacle 

PCS Portable Computer System 

PD Physical Device 

PDGF Lab Power Data Grapple Fixture 

PDI Payload Data Interleaver 

 Payload Data Interface Panel 

PDIP Payload Data Interface Panel 

PDRS Payload Deployment and Retrieval System 

PFCS Pump and Flow Control Subassembly 

PFE Portable Fire Extinguisher 

PFMC Pump Fan/Motor Controller 

PFR Portable Foot Restraint 

PG Product Group 

61


7 

PGSC Payload General Support Computer 

PIDS Prime Item Development Specifications 

PLB Payload Bay 

PM Pressurized Module 

PMA Pressurized Mating Adapter 

PMCA Power Management Control Application 

PMCU Power Management Controller Unit 

POST Power-On Self-Test 

PPA Pump Package Assembly 

PPL Pre-Positioned Load 

PPRV Positive Pressure Relief Valve 

PRCS Primary Reaction Control System 

PRLA Payload Retention Latch Assembly 

psid pounds per square inch differential 

psig pounds per square inch gauge 

PSP Payload Signal Processor 

PSS Power Supply System 

PTB Payload Timing Buffer 

PTCS Passive Thermal Control System 

PVCA Photovoltaic Controller Application 

PVCU Photovoltaic Control Unit 

RACU Remote Acquisition and Command Unit 

 Russian-to-American Converter Unit 

RAIU Russian Audio Interface Unit 

RAMV Rheostat Air Mix Valve 

RCS Reaction Control System 

RF Radio Frequency 

RFPDB RF/Power Distribution Box 

RHC Rotational Hand Controller 

RMS Remote Manipulator System 

ROEU Remotely Operated Electrical Umbilical 

ROS Russian On-Orbit Segment 

RPC Remote Power Controller 

RPCM Remote Power Controller Mode 

RPDA Remote Power Distribution Assembly 

RS Remote Station 

Russian Segment 

RSA Russian Space Agency 

RSCC RS Central Computer 

RSOS Russian On-Orbit Segment 

RT Remote Terminal 

RTL Ready to Latch 

S/W Software 

S0 Starboard-zero 

62


8 

S1 Starboard-one 

SARJ Solar Array Rotary Joint 

SASA S-Band Antenna Support Assembly 

SCI Signal Conditioning Interface 

SCU Synchronization and Control Unit 

SDA Sample Distribution Assembly 

SDO Solenoid Driver 

SDS Sample Delivery System 

SEPS Secondary Electrical Power System 

SFCA System Flow Control Assembly 

SIR Stage Integration Review 

SLP Spacelab-Pallet 

SM Service Module 

SMA Sensor Module Assembly 

SMC Station Management and Control 

SPDA Secondary Power Distribution Assembly 

SPDM Special Purpose Dexterous Manipulator 

SPDU Station Power Distribution Unit 

SPP Science Power Platforms 

SRAM Static Random Access Memory 

SRCA System Remote Control Assembly 

SRMS Shuttle Remote Manipulator System 

SRP Safety Review Panel 

SSAF S-Band Single Access Forward 

SSAS Segment-to-Segment Attachment System 

SSOR Space-to-Space Orbiter Radio 

SSP Standard Switch Panel 

SSRMS Space Station Remote Manipulator System 

SSSH Space Shuttle Systems Handbook 

SSSR Space to Space Station Radio 

STS Shuttle Program 

TB Talk-Back 

TBD To be Determined 

TC Terminal Computer 

TCCS Trace Contaminant Control Subassembly 

TCCV Temperature Control and Check Valve 

TCS Thermal Control System 

 Trajectory Control Sensor 

TDRS Tracking and Data Relay Satellite 

TDRSS Tracking and Data Relay Satellite System 

TEA Torque Equilibrium Attitude 

THC Temperature and Humidity Control 

 Translational Hand Controller 

TMA Torquer Motor Assembly 

TMSS Thermal Mode Control System 

63


9 

TP Tone Processor 

TRA Transmitter/Receiver Assembly 

TRC Transmitter/Receiver/Controller 

U.S. United States 

UDM Universal Docking Module 

UHF Ultrahigh Frequency 

UOP Utilization Outlet Panel 

UPLU Universal Program Logic Unit 

USA United Space Alliance 

USL U.S. Lab 

USOS U.S. On-Orbit Segment 

VAJ Vacuum Access Jumper 

VAP Vacuum Access Port 

VCDU Virtual Channel Data Unit 

VDS Video Distribution System 

VES/VRS Vacuum Exhaust/Resource System 

VRA Vent Relief Assembly 

VRCV Vent and Relief Control Valve 

VRIV Vent and Relief Isolation Valve 

VSC Video Signal Converter 

VSU Video Switching Unit 

VTS Video Teleconferencing System 

WIF Worksite Interface 

WRM Water Recovery and Management 

WVA Water Vent Assembly 

WS Water Separator 

WSC White Sands Complex 

WSS Workstation Stanchion 

XPNDR Transponder 

Z1 Zenith 1 

64
STS-98

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, FL; 

Marshall Space Flight Center, Huntsville, AL; Dryden Flight Research 

Center, Edwards, CA; Johnson Space Center, Houston, TX; 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 newscenter

 

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

 

65
STS-98

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

 

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.

66
STS-98

Media Contacts 

NASA PAO CONTACTS 

Dwayne Brown 202 358-1726

Space Shuttle/Space Station Policy

Washington, DC

NASA Headquarters

dwayne.brown@hq.nasa.gov

Debbie Rahn 202 358-1638

NASA Headquarters

Washington, DC

International Partners

debbie.rahn@hq.nasa.gov

Eileen Hawley 281 483-5111

NASA Johnson Space Center

Houston, TX

Astronauts/Mission Operations

eileen.hawley1@jsc.nasa.gov

Kyle Herring 281 483-5111

NASA Johnson Space Center

Houston, TX

International Space Station 

Operations

kyle.j.herring1@jsc.nasa.gov

Carlos Fontanot 256 961-6225 

Moscow

NASA Johnson Space Center

Houston, TX

NASA Moscow PAO

carlos.fontanot1@jsc.nasa.gov

Bruce Buckingham 321 867-2468

NASA Kennedy Space Center

Kennedy space Center, FL

Launch Operations

bruce.buckingham-1@kmail.ksc.nasa.gov

Dave Drachlis 256 544-0034

NASA Marshall Space Flight Center

Huntsville, AL

Space Station Science

Dave.Drachlis@msfc.nasa.gov

67
STS-98

Jack King 321 861-4358

United Space Alliance

Kennedy Space Center, FL

Shuttle Processing

KingJW@usafoo.unitedspacealliance.com

Kari Kelley Allen 281 336-4844

The Boeing Company

Houston, TX

International Space Station

kari.k.allen@boeing.com

Beth Hill 714 372-4736

The Boeing Company

Huntington Beach, CA

Space Shuttle

sara.b.hill@boeing.com

Dan Beck 818 586-4572

Boeing Rocketdyne

Canoga Park, CA

Space Shuttle Main Engines

daniel.c.beck@boeing.com

68
Table prepared by Richard W. Orloff, 02/2001 

SHUTTLE FLIGHTS AS OF FEBRUARY 2001 

101 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 76 SINCE RETURN TO FLIGHT 

STS-92 

10/11/00 - 10/24/00 

STS-103 

12/19/99 - 12/27/99 

STS-93 

07/23/99 - 07/27/99 

STS-96 

05/27/99 - 06/06/99 

STS-90 

04/17/98 - 05/03/98 

STS-95 

10/29/98 - 11/07/98 

STS-87 

11/19/97 - 12/05/97 

STS-91 

06/02/09 - 06/12/98 

STS-94 

07/01/97 - 07/17/97 

STS-85 

08/07/97 - 08/19/97 

STS-83 

04/04/97 - 04/08/97 

STS-82 

02/11//97 - 02/21/97 

STS-106 

09/08/00 - 09/20/00 

STS-80 

11/19/96 - 12/07/96 

STS-70 

07/13/95 - 07/22/95 

STS-101 

05/19/00 - 05/29/00 

STS-78 

06/20/96 - 07/07/96 

STS-63 

02/03/95 - 02/11/95 

STS-86 

09/25/97 - 10/06/97 

STS-75 

02/22/96 - 03/09/96 

STS-64 

09/09/94 - 09/20/94 

STS-84 

05/15/97 - 05/24/97 

STS-73 

10/20/95 - 11/05/95 

STS-60 

02/03/94 - 02/11/94 

STS-81 

01/12/97 - 01/22/97 

STS-65 

07/08/94 - 07/23/94 

STS-51 

09/12/93 - 09/22/93 

STS-79 

09/16/96 - 09/26/96 

STS-62 

03/04/94 - 03/18/94 

STS-56 

04/08/83 - 04/17/93 

STS-76 

03/22/96 - 03/31/96 

STS-58 

10/18/93 - 11/01/93 

STS-53 

12/02/92 - 12/09/92 

STS-74 

11/12/95 - 11/20/95 

STS-97 

11/30/00 - 12/11/00 

STS-55 

04/26/93 - 05/06/93 

STS-42 

01/22/92 - 01/30/92 

STS-71 

06/27/95 - 07/07/95 

STS-99 

02/11/00 - 02/22/00 

STS-52 

10/22/92 - 11/01/92 

STS-48 

09/12/91 - 09/18/91 

STS-66 

11/03/94 - 11/14/94 

STS-88 

12/04/98 - 12/15/98 

STS-50 

06/25/92 - 07/09/92 

STS-39 

04/28/91 - 05/06/91 

STS-46 

07/31/92 - 08/08/92 

STS-89 

01/22/98 - 01/31/98 

STS-40 

06/05/91 - 06/14/91 

STS-41 

10/06/90 - 10/10/90 

STS-45 

03/24/92 - 04/02/92 

STS-77 

05/19/96 - 05/29/96 

STS-35 

12/02/90 - 12/10/90 

STS-51L 

01/28/86 

STS-31 

04/24/90 - 04/29/90 

STS-44 

11/24/91 - 12/01/91 

STS-72 

01/11/96 - 11/20/96 

STS-32 

01/09/90 - 01/20/90 

STS-61A 

10/30/85 - 11/06/85 

STS-33 

11/22/89 - 11/27/89 

STS-43 

08/02/91 - 08/11/91 

STS-69 

09/07/95 - 09/18/95 

STS-28 

08/08/89 - 08/13/89 

STS-51F 

07/29/85 - 08/06/85 

STS-29 

03/13/89 - 03/18/89 

STS-37 

04/05/91 - 04/11/91 

STS-67 

03/02/95 - 03/18/95 

STS-61C 

01/12/86 - 01/18/86 

STS-51B 

04/29/85 - 05/06/85 

STS-26 

09/29/88 - 10/03/88 

STS-38 

11/15/90 - 11/20/90 

STS-68 

09/30/94 - 10/11/94 

STS-9 

11/28/83 - 12/08/83 

STS-41G 

10/05/84 - 10/13/84 

STS-51-I 

08/27/85 - 09/03/85 

STS-36 

02/28/90 - 03/04/90 

STS-59 

04/09/94 – 04/20/94 

STS-5 

11/11/82 - 11/16/82 

STS-41C 

04/06/84 - 04/13/84 

STS-51G 

06/17/85 - 06/24/85 

STS-34 

10/18/89 - 10/23/89 

STS-61 

12/02/93 - 12/13/93 

STS-4 

06/27/82 - 07/04/82 

STS-41B 

02/03/84 - 02/11/84 

STS-51D 

04/12/85 - 04/19/85 

STS-30 

05/04/89 - 05/08/89 

STS-57 

06/21/93 - 07/01/93 

STS-3 

03/22/82 - 03/30/82 

STS-8 

08/30/83 - 09/05/83 

STS-51C 

01/24/85 - 01/27/85 

STS-27 

12/02/88 - 12/06/88 

STS-54 

01/13/93 - 01/19/93 

STS-2 

11/12/81 - 11/14/81 

STS-7 

06/18/83 - 06/24/83 

STS-51A 

11/08/84 - 11/16/84 

STS-61B 

11/26/85 - 12/03/85 

STS-47 

09/12/92 - 09/20/92 

STS-1 

04/12/81 - 04/14/81 

STS-6 

04/04/83 - 04/09/83 

STS-41D 

08/30/84 - 09/05/84 

STS-51J 

10/03/85 - 10/07/85 

STS-49 

05/07/92 - 05/16/92 

 

OV-102 

Columbia 

(26 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(28 flights) 

OV-104 

Atlantis 

(22 flights) 

OV-105 

Endeavour 

(15 flights)