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Outpost in Orbit Outpost in Orbit

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Updated May 20, 1999

STS-96
STS-96 Table of Contents

*Grayed text - not published

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

Mission Profile ................................................................................................... 6

Shuttle Reference

Shuttle Abort History ............................................................................................ 9

Shuttle Abort Modes........................................................................................... 11

Crew................................................................................................................... 18

Flight Day Summary.......................................................................................... 23

Rendezvous

Docking Mechanisms......................................................................................... 27

Rendezvous and Docking................................................................................... 29

Undocking, Separation and Fly-Around ............................................................. 33

EVA

Space Walk to Install U.S., Russian Crane Systems ........................................ 34

Payloads

Cargo Transfer.................................................................................................... 38

Integrated Cargo Carrier..................................................................................... 42

Integrated Vehicle Health Monitoring HEDS Technology

 Demonstration 2............................................................................................ 44

MIRTs Changeout............................................................................................... 47

Shuttle Vibration Forces Experiment.................................................................. 49

SPACEHAB........................................................................................................ 51

Student-Tracked Atmospheric Research Satellite for

 Heuristic International Networking Equipment (STARSHINE) ...................... 55

*EXPERIMENTS
DTO/DSO/RME

DTO 686 Heat Exchange Unit Evaluation........................................................... 58

DTO 1214 Resource Transfer Line Capability Evaluation .................................. 59

DTO 700-14 Single-String Global Positioning System....................................... 60

DTO 847 Solid-State Star Tracker Size Limitations ........................................... 61

DTO 700-15 Space Integrated Global Positioning

 System/Inertial Navigation System................................................................ 62

DTO 690 Urine Collection Device....................................................................... 63

ISS Overview .................................................................................................... 64

Unity................................................................................................................... 71

Zarya .................................................................................................................. 73

Media Assistance.............................................................................................. 75

Contacts ............................................................................................................ 77
STS-96

Mission Overview 

DISCOVERY'S CREW TO MAKE FIRST STATION VISIT 

The Shuttle Discovery's international crew of seven will become the first

visitors to a new star in orbit on mission STS-96, preparing the International

Space Station for the arrival of its early living quarters and laying out a

welcome mat for the first station crew. 

Discovery will spend six days linked to the new outpost as the crew transfers

and installs gear that could not be launched aboard the Zarya and Unity

modules due to weight limitations. The Shuttle will carry more than 3,600

pounds of supplies to be stored aboard the station, ranging from food and

clothes for the first crew to laptop computers, a printer and cameras. 

1
 

Discovery's crew, led by U.S. Navy Commander Kent Rominger, 42, reflects

the global nature of the station with three of five international partners

represented. Included are cosmonaut Valery Tokarev, 46, a colonel in the

Russian Air Force, and Canadian Space Agency astronaut Julie Payette, 35,

who will become the first Canadian to board the station. U.S. Air Force Lt.

Col. Rick Husband, 41, will serve as pilot, and a spacewalk will be performed

by astronauts Tammy Jernigan,40, and Dr. Daniel Barry, 42. Jernigan and

Barry will attach a United States-built spacewalkers' "crane" and parts of a

Russian-built crane to the exterior for use on future missions. Astronaut Ellen

Ochoa rounds out the crew as flight engineer and operator of the Shuttle's

mechanical arm. 

Discovery's mission will set the stage for the launch this fall of the

Russian-provided Service Module, the first station living quarters, and the

arrival in early 2000 of the first three-person station crew. STS-96 is the first

of two Shuttle missions scheduled to visit the International Space Station this

year to continue its assembly, an unprecedented task that turns Earth orbit

into an ever-changing construction site, joining more than 100 elements on

45 assembly flights. 

2
The International Space Station will allow humankind to harness as never

before one of the fundamental forces of nature – gravity – to perform

research that may result in new medicines, materials and industries on

Earth. The station's scientific studies, performed in six state-of-the-art

laboratories, may even lead to a new understanding of the fundamental laws

of nature while they pave the way for the future human exploration of space.

Partners in the United States-led station include Canada, 11 member nations

of the European Space Agency, Japan and Russia. Italy and Brazil also are

contributing. 

3
Much of the gear destined for the station will be housed inside a double

Spacehab module in Discovery's payload bay. The spacewalking gear and

cranes will be stored outside in the Shuttle bay on a new piece of equipment

called the Integrated Cargo Carrier, a removable platform that will be used on

many future station assembly flights. The carrier, which will remain in the

Shuttle bay throughout STS-96, also includes a large, new spacewalking

equipment storage box developed by Spacehab. 

In addition to its primary cargo of station supplies, Discovery will carry aloft a

small satellite called Starshine that will provide educational observations for

students around the world. More than 1,000 schools across America and the

world have helped construct the satellite and will participate in the project,

calculating its orbit as they learn about math and physics. Although only

slightly larger than a basketball, Starshine is covered by almost 900 highly

polished mirrors that will make it visible from the ground. It will be released

from Discovery after the Shuttle has left the station. 

Discovery also will conduct several evaluations of equipment for future use

on the station and the Shuttle. Two new Shuttle sensor systems will be

tested. One system, called the Shuttle Vibration Forces experiment, will

record vibrations between the Shuttle and its cargo to assist in planning

4
future flights. Another test, called the Integrated Vehicle Health Monitoring

System, will send information on several of Discovery's systems to the

Kennedy Space Center, FL, during flight and may shorten the time needed to

prepare Shuttles for launch. Another evaluation will check equipment that

may be used on future flights to transfer water and fluids from the Shuttle to

the station. Another study, called the Volatile Removal Assembly, will test the

operation of equipment that will be used to help recycle station wastewater. 

Already easily visible from Earth, the International Space Station will grow

brighter as Discovery docks and continue to increase in magnitude as its

assembly in orbit progresses during the next five years. Components built at

factories around the world are now being readied for upcoming launches at

the Kennedy Space Center and at the Russian launch site, the Baikonur

Cosmodrome in Kazakstan. 

Updated: 05/14/1999

 

5
STS-96

Discovery OV103

Launch: Thursday, May 27, 1999 

 6:48 AM (eastern time)

 

Mission Objectives

The major objective of the first shuttle mission of the year is the transfer of

almost two tons of logistical supplies from the shuttle Discovery to the

International Space Station.

These supplies will be used to not only continue the outfitting of the Unity

and Zarya modules already joined together in orbit, but will be used by a

future Shuttle assembly crew later this year to set up the Russian Service

Module for occupancy by a three-man crew early next year.

In addition to the supply delivery, the astronauts will deploy a small satellite

called STARSHINE which will be observed by international students on

Earth as they calculate its precise orbit and the rate of its orbital decay over

a period of time.

The seven crew members will also collect data from an experiment

designed to test the amount of vibration imparted on shuttle-based payloads

and will begin to demonstrate the effect of technological upgrades to the

shuttle through the use of orbiter health monitoring devices designed to

improve the quality of life aboard future shuttles while making their use

more efficient over time.

6
Crew

Commander: Kent V. Rominger

Pilot: Rick D. Husband

Mission Specialist 1: Tamara E. Jernigan

Mission Specialist 2: Ellen Ochoa

Mission Specialist 3: Daniel T. Barry

Mission Specialist 4: Julie Payette

Mission Specialist 5: Valery Tokarev

Launch

Orbiter: Discovery OV103

Launch Site: Pad 39-B Kennedy Space Center

Launch Window: 10 minutes

Altitude: 173nm (205 nm for rendezvous)

Inclination: 51.6

Duration: 9 Days 19 Hrs. 55 Min.

Vehicle Data

Shuttle Liftoff Weight: 4,514,454 lbs.

Orbiter/Payload Liftoff Weight: 262,035 lbs.

Orbiter/Payload Landing

Weight:

220,980 lbs.

Payload Weights

IVHM-2 254 lbs.

STARSHINE 353 lbs.

ICC 3050 lbs.

SVFE 327 lbs.

SPACEHAB 16072 lbs.

Software Version: OI-27

Space Shuttle Main Engines

SSME 1: SN-2047 (2nd flt.) SSME 2: SN-2051 (1st flt.) SSME 3: SN-2049 (1st flt.)

External Tank: ET-100 (4th Super Light Weight Tank)

7
SRB Set: BI098

Auxiliary Power Units:

APU-1: SN-310 APU-2: SN-204 APU-3: SN-404

Fuel Cells:

FC-1: SN-117 FC-2: SN-111 FC-3: SN-103

Shuttle Aborts

Abort Landing Sites

 RTLS: Shuttle Landing Facility, KSC

 TAL: Zaragoza, Spain; Alternates: Ben Guerrir, Moron

 AOA: Shuttle Landing Facility, KSC; Alternates: White Sands Space Harbor

Landing

Landing Date: 06/06/99

Landing Time: 2:43 AM (eastern time)

Primary Landing Site: Shuttle Landing Facility, KSC 

First alternate, Edwards Air Force Base

Second alternate, White Sands Space Harbor 

Payloads

Cargo Bay

Integrated Vehicle Health Monitoring HEDS Technology Demonstration 2

Student-Tracked Atmospheric Research Satellite for Heuristic International Networking

Equipment (STARSHINE)

Integrated Cargo Carrier

Shuttle Vibration Forces Experiment

SPACEHAB

Spacehab

MIRTs Changeout

Cargo Transfer

8
STS-96

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. 

9
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.

Updated: 05/11/1999

10
STS-96

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.

11
An RTLS can be considered to consist of three stages-a powered stage,

during which the space shuttle main engines are still thrusting; an ET

separation phase; and the glide phase, during which the orbiter glides to a

landing at the Kennedy Space Center. The powered RTLS phase begins

with the crew selection of the RTLS abort, which is done after solid rocket

booster separation. The crew selects the abort mode by positioning the abort

rotary switch to RTLS and depressing the abort push button. The time at

which the RTLS is selected depends on the reason for the abort. For

example, a three-engine RTLS is selected at the last moment, approximately

three minutes 34 seconds into the mission; whereas an RTLS chosen due to

an engine out at lift-off is selected at the earliest time, approximately two

minutes 20 seconds into the mission (after solid rocket booster separation).

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.

12
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).

13
To select the TAL abort mode, the crew must place the abort rotary switch in

the TAL/AOA position and depress the abort push button before main engine

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

The TAL abort mode begins sending commands to steer the vehicle toward

the plane of the landing site. It also rolls the vehicle heads up before main

engine cutoff and sends commands to begin an orbital maneuvering system

propellant dump (by burning the propellants through the orbital maneuvering

system engines and the reaction control system engines). This dump is

necessary to increase vehicle performance (by decreasing weight), to place

the center of gravity in the proper place for vehicle control, and to decrease

the vehicle's landing weight.

14
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.

 

15
 

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.

16
 

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.

Updated: 05/11/1999

 

17
STS-96

Crew Profile Menu 

Commander: Kent V. Rominger 

During the flight, the Commander has onboard responsibility for the

vehicle, crew, mission success and safety of flight.

NASA EXPERIENCE: Selected by NASA in March 1992, Rominger

reported to the Johnson Space Center in August 1992. He completed

one year of training and is qualified for assignment as a pilot on future

Space Shuttle flight crews. Rominger was initially assigned to work

technical issues for the Astronaut Office Operations Development

Branch. A veteran of three space flights, Rominger has logged over

1,090 hours in space. He flew as pilot on STS-73 in 1995, STS-80 in 1996 and STS-85 in

1997. Rominger is assigned to command the crew of Discovery on STS-96, a logistics and

resupply mission for the International Space Station. Launch is targeted for May 1999.

SPACE FLIGHT EXPERIENCE: STS-73 Columbia (October 20 to November 5, 1995) was

the second United States Microgravity Laboratory mission. The mission focused on

materials science, biotechnology, combustion science, the physics of fluids, and numerous

scientific experiments housed in the pressurized Spacelab module. In completing his first

space flight, Rominger orbited the earth 256 times, traveled over 6 million miles, and logged

a total of 15 days, 21 hours, 52 minutes and 21 seconds in space. STS-80 Columbia

(November 19 to December 7, 1996) was a 17-day mission during which the crew deployed

and retrieved the Wake Shield Facility (WSF) and the Orbiting Retrievable Far and Extreme

Ultraviolet Spectrometer (ORFEUS) satellites. The free-flying WSF created a super vacuum

in its wake and grew thin film wafers for use in semiconductors and other high-tech

electrical components. The ORFEUS instruments, mounted on the reusable Shuttle Pallet

Satellite, studied the origin and makeup of stars. In completing his second space flight,

Rominger orbited the earth a record 278 times, traveled over 7 million miles and logged 17

days, 15 hours and 53 minutes in space. STS-85 (August 7-19, 1997) was a 12-day mission

during which the crew deployed and retrieved the CRISTA-SPAS satellite, operated the

Japanese Manipulator Flight Demonstration (MFD) robotic arm, studied changes in the

Earth's atmosphere and tested technology destined for use on the future International

Space Station. The mission was accomplished in 189 Earth orbits, traveling 4.7 million

miles in 11 days, 20 hours and 27 minutes. AUGUST 1998 

Ascent Seating: Flight Deck - Port Forward

Entry Seating: Flight Deck - Port Forward

18
Pilot: Rick D. Husband 

The pilot assists the Mission Commander in controlling and operating

the Shuttle. In addition, the pilot may assist in the deployment and

retrieval of satellites utilizing the Shuttle's robot arm, and often

coordinates the activities of astronauts conducting space walks or

Extravehicular Activities.

During STS-96, pilot Rick Husband will be a back-up EVA crew

member and also is the back-up robot arm operator during the space

walks.

NASA EXPERIENCE: Husband was selected as an astronaut candidate by NASA in

December 1994. He reported to the Johnson Space Center in March 1995 to begin a year

of training and evaluation. Upon completion of training, Husband was named the Astronaut

Office representative for Advanced Projects at Johnson Space Center, working on Space

Shuttle Upgrades, the Crew Return Vehicle (CRV) and studies to return to the Moon and

travel to Mars. Husband is assigned to pilot Discovery on STS-96, an 11-day logistics and

resupply mission for the International Space Station. Launch is targeted for May 1999. 

Ascent Seating: Flight Deck - Starboard Forward

Entry Seating: Flight Deck - Starboard Forward

Mission Specialist 1: Tamara E. Jernigan 

Dr. Jernigan will serve as the prime space walking crew member on

STS-96, designated EV 1, because of her striped space suit. She will

also be the first crew member to enter the International Space Station

the day after she conducts her space walk with Dan Barry. Jernigan

will also serve as a backup to Ellen Ochoa for many procedures

involving the shuttle's robot arm, or remote manipulator system,

except during the space walks when pilot Rick Husband is the

back-up arm operator.

NASA EXPERIENCE: Selected as an astronaut candidate by NASA in June 1985, Dr.

Jernigan became an astronaut in July 1986. Her assignments since then have included:

software verification in the Shuttle Avionics Integration Laboratory (SAIL); operations

coordination on secondary payloads; spacecraft communicator (CAPCOM) in Mission

Control for STS-30, STS-28, STS-34, STS-33, and STS-32; lead astronaut for flight

software development; Chief of the Astronaut Office Mission Development Branch; Deputy

Chief of the Astronaut Office. A veteran of four space flights, Dr. Jernigan has logged over

1,277 hours in space. She was a mission specialist on STS-40 (June 5-14, 1991) and

STS-52 (October 22-November 1, 1992), was the payload commander on STS-67 (March

2-18, 1995), and again served as a mission specialist on STS-80 (November 19 to

December 7, 1996). Dr. Jernigan is currently the Assistant for Station to the Chief of the

Astronaut Office, directing crew involvement in the development and operation of the

Station. SPACE FLIGHT EXPERIENCE: STS-40 Spacelab Life Sciences (SLS-1) was a

dedicated space and life sciences mission aboard Space Shuttle Columbia. During the

nine-day flight crew members performed experiments which explored how humans, animals

and cells respond to microgravity and readapt to Earth's gravity on return. Other payloads

included experiments designed to investigate materials science, plant biology and cosmic

radiation. Mission duration was 218 hours, 14 minutes, 20 seconds. Landing was at

Edwards Air Force Base, California. STS-52 was also launched aboard Space Shuttle

Columbia. During the ten-day flight, the crew deployed the Italian Laser Geodynamic

Satellite (LAGEOS) which will be used to measure movement of the Earth's crust, and

operated the U.S. Microgravity Payload 1 (USMP-1). Also, the Space Vision System (SVS),

developed by the Canadian Space Agency, was tested by the crew using a small target

assembly which was released from the remote manipulator system. The SVS will be used

for Space Station construction. In addition, numerous other experiments were performed by

the crew encompassing the areas of geophysics, materials science, biological research and

applied research for Space Station. Mission duration was 236 hours, 56 minutes 13

seconds. Landing was at Kennedy Space Center, Florida. STS-67 Astro-2 mission aboard 19
seconds. Landing was at Kennedy Space Center, Florida. STS-67 Astro-2 mission aboard

the Space Shuttle Endeavour was the second flight of the Astro observatory, a unique

complement of three telescopes. During this record-setting 16-day mission, the crew

conducted observations around the clock to study the far ultraviolet spectra of faint

astronomical objects and the polarization of ultraviolet light coming from hot stars and

distant galaxies. Mission duration was 399 hours and 9 minutes. Landing was at Edwards

Air Force Base in California. On STS-80 the crew aboard Space Shuttle Columbia

successfully deployed and retrieved the Wake Shield Facility (WSF) and the Orbiting

Retrievable Far and Extreme Ultraviolet Spectrometer (ORFEUS) satellites. The free-flying

WSF created a super vacuum in its wake and grew thin film wafers for use in

semiconductors and other high-tech electrical components. The ORFEUS instruments,

mounted on the reusable Shuttle Pallet Satellite, studied the origin and makeup of stars.

Her two planned spacewalks were lost due to a jammed outer hatch on the airlock. Mission

duration was a record breaking 423 hours, 53 minutes. MARCH 1998 

Ascent Seating: Mid Deck - Port

Entry Seating: Mid Deck - Port

EV1

Mission Specialist 2: Ellen Ochoa 

Dr. Ochoa will serve as the prime robot arm operator during STS-96,

using the arm to maneuver Tammy Jernigan and Dan Barry for certain

tasks during their space walk. Ochoa will also be the prime crew

member in charge of the tools to be used in Discovery's rendezvous

with the International Space Station and is responsible for activating

and deactivating the systems of the double Spacehab module in the

cargo bay. In addition, Ochoa is the so-called "loadmaster" during the

flight, responsible for the transfer of thousands of pounds of hardware

and logistical items from Discovery to the International Space Station

for future use. 

 

EXPERIENCE: As a doctoral student at Stanford, and later as a researcher at Sandia

National Laboratories and NASA Ames Research Center, Dr. Ochoa investigated optical

systems for performing information processing. She is a co-inventor on three patents for an

optical inspection system, an optical object recognition method, and a method for noise

removal in images. As Chief of the Intelligent Systems Technology Branch at Ames, she

supervised 35 engineers and scientists in the research and development of computational

systems for aerospace missions. Dr. Ochoa has presented numerous papers at technical

conferences and in scientific journals. Selected by NASA in January 1990, Dr. Ochoa

became an astronaut in July 1991. Her technical assignments to date include flight software

verification, crew representative for flight software and computer hardware development,

crew representative for robotics development, testing, and training, Assistant for Space

Station to the Chief of the Astronaut Office, directing crew involvement in the development

and operation of the Station, and spacecraft communicator (CAPCOM) in Mission Control.

A veteran of two space flights, Dr. Ochoa has logged over 484 hours in space. Dr. Ochoa is

assigned to the crew of STS-96, a 10-day logistics and resupply mission for the

International Space Station. Launch is targeted for May 1999. In April 1993, Dr. Ochoa flew

as a Mission Specialist on STS-56, carrying ATLAS-2. During this 9-day mission the crew of

Discovery conducted atmospheric and solar studies in order to better understand the effect

of solar activity on the Earth's climate and environment. Dr. Ochoa used the Remote

Manipulator System (RMS) to deploy and capture the Spartan satellite, which studied the

solar corona. Dr. Ochoa was the Payload Commander on the STS-66 Atmospheric

Laboratory for Applications and Science-3 mission (November 3-14, 1994). ATLAS-3

continues the series of Spacelab flights to study the energy of the Sun during an 11-year

solar cycle and to learn how changes in the sun's irradiance affect the Earth's climate and

environment. Dr. Ochoa used the RMS to retrieve the CRISTA-SPAS atmospheric research

satellite at the end of its 8-day free flight. 

20
Ascent Seating: Flight Deck - Center Aft

Entry Seating: Flight Deck - Center Aft

RMS

Mission Specialist 3: Daniel T. Barry 

In addition to his role as one of two space walkers during the flight, Dr.

Barry will be in charge of the operation of the various computers the

crew members will use. Barry will be one of three crew members

responsible for the systems of the International Space Station during

the docked phase of the flight, and will participate in a number of

secondary experiments and technology demonstrations.

NASA EXPERIENCE: Selected by NASA in March 1992, Dr. Barry

reported to the Johnson Space Center in August 1992. He completed one year of training

and is qualified for assignment as a mission specialist on Space Shuttle flight crews. Dr.

Barry has worked on primary payload development, the Shuttle Avionics Integration

Laboratory (SAIL), portable computing issues for Space Shuttle, Chief of Astronaut

Appearances, and as a source board member for the NASA Space Biomedical Research

Institute (NSBRI). He flew on STS-72 in 1996, and has logged over 214 hours in Space,

including a 6 hour, 9 minute spacewalk. Dr. Barry is assigned to STS-96 as an EVA

crewmember. STS-96 will be the first flight to dock to the International Space Station.

Launch is targeted for May 1999. SPACE FLIGHT EXPERIENCE: STS-72 Endeavour

(January 11-20, 1996) was a 9-day flight during which the crew retrieved the Space Flyer

Unit (launched from Japan 10-months earlier), deployed and retrieved the OAST-Flyer, and

Dr. Barry performed a 6 hour, 9 minute spacewalk designed to demonstrate and evaluate

techniques to be used in the assembly of the International Space Station. Mission duration

was 142 Earth orbits, traveling 3.7 million miles in 214 hours and 41 seconds. AUGUST

1998 

Ascent Seating: Flight Deck - Starboard Aft

Entry Seating: Mid Deck - Center

EV2

21
Mission Specialist 4: Julie Payette 

Payette will be the prime crew member in charge of Unity's systems

while Discovery is docked to the International Space Station and will

assist Valery Tokarev in monitoring Zarya's systems during the docked

phase of the mission. Payette is the lead crew member for any in-flight

maintenance of station systems or hardware, and will join Valery

Tokarev for the swapout of battery voltage regulators in Zarya. She will

also be the prime choreographer for the space walk to be conducted by

Tammy Jernigan and Dan Barry. Payette is responsible for stowing

equipment on the ISS and aboard Discovery, operating the Shuttle's robot arm for a camera

survey, and will be in charge of the STARSHINE student science satellite.

 

Canadian Space Agency Astronaut. Ms. Payette was selected as an astronaut by the

Canadian Space Agency (CSA) in June 1992 and underwent training in Canada. After basic

training, she worked as a technical advisor for the MSS (Mobile Servicing System), the

Canadian contribution to the International Space Station. In 1993, Ms. Payette established

the Human-Computer Interaction (HCI) Group at the Canadian Astronaut Program and

served as a technical specialist on the NATO International Research Study Group (RSG-10)

on speech processing (1993-1996). In preparation for a space assignment, Ms. Payette

studied Russian and logged over 120 hours of of reduced gravity flight time aboard various

parabolic aircraft (KC-135, T-33, Falcon-20, DC-9). In April 1996, Ms. Payette completed a

deep-sea diving hard suit training program in Vancouver BC and was certified as a

one-atmosphere diving suit operator. Ms. Payette obtained her captaincy on military jet at

the Canadian Air Force Base in Moose Jaw, Saskatchewan in February 1996. She has

since obtained her military instrument rating and continues to fly regularly with the training

squadron. Ms. Payette has logged more than 600 hours of flight time, including 150 hours

on the Tutor CT-114 jet aircraft. NASA EXPERIENCE: Ms. Payette reported to the Johnson

Space Center in August 1996 to begin mission specialist training. She completed initial

astronaut training in April 1998 and was assigned to work technical issues for the Astronaut

Office EVA/Robotics Branch. Ms. Payette is assigned as a mission specialist on the crew of

STS-96 Atlantis, a 10-day logistics and resupply mission for the International Space Station.

Launch is targeted for May 1999. AUGUST 1998 

Ascent Seating: Mid Deck - Center

Entry Seating: Flight Deck - Starboard Aft

IV1

Mission Specialist 5: Valery Tokarev 

Tokarev will join Tammy Jernigan as the first crew members to enter

the International Space Station on the fifth day of the flight and will be

responsible for Zarya's systems during the docked phase of the flight.

He will be joined by Julie Payette for the swapout of battery voltage

regulators aboard Zarya and will be involved in moving logistical items

from Discovery to the ISS during six days of docked operations.

Valery Ivanovich Tokarev (Colonel, Russian Air Force) Test

Cosmonaut at the Yu.A. Gagarin Cosmonaut Training Center In 1987, Valery Tokarev was

selected to join the cosmonaut corps to fly the Buran spacecraft. Since 1994,he has served

as commander of a group of cosmonauts of aerospace systems and, since 1997, as a test

cosmonaut for the Yuri A. Gagarin Cosmonaut Training Center. SEPTEMBER 1998 

Ascent Seating: Mid Deck - Starboard

Entry Seating: Mid Deck - Starboard

22
STS-96

Flight Day Summary 

DATE TIME (EST) DAY MET EVENT

05/27/99 6:48:00 AM 1 000/00:00 Launch Time

05/27/99 7:32:00 AM 1 000/00:44 OMS 2

05/27/99 9:49:00 AM 1 000/03:01 NC-1

05/27/99 11:48:00 AM 1 000/05:00 Flight Day 1 Sleep

05/27/99 7:48:00 PM 2 000/13:00 Flight Day 2 Wake

05/27/99 10:48:00 PM 2 000/16:00 SHAB Activation

05/27/99 10:50:00 PM 2 000/16:02 NC-2

05/27/99 11:53:00 PM 2 000/17:05 EMU Checkout

05/28/99 2:35:00 AM 2 000/19:47 NPC

05/28/99 3:18:00 AM 2 000/20:30 RMS C/O

05/28/99 4:33:00 AM 2 000/21:45 Waste Dump

05/28/99 7:16:00 AM 2 001/00:28 NC 3

05/28/99 8:03:00 AM 2 001/01:15 10.2 Cabin Depress

05/28/99 9:48:00 AM 2 001/03:00 Flight Day 2 Sleep

05/28/99 5:18:00 PM 3 001/10:30 Flight Day 3 Wake

05/28/99 5:42:00 PM 3 001/10:54 FGB OSK Build

05/28/99 7:16:00 PM 3 001/12:28 NH

05/28/99 8:01:00 PM 3 001/13:13 NC 4

05/28/99 9:33:00 PM 3 001/14:45 Ti

05/28/99 10:38:00 PM 3 001/15:50 SSC C/O

05/28/99 10:48:00 PM 3 001/16:00 SK at 170 ft (estimated)

05/28/99 10:53:00 PM 3 001/16:05 EPCS Setup

05/28/99 11:04:00 PM 3 001/16:16 +Rbar Arrival

05/28/99 11:31:00 PM 3 001/16:43 -Rbar Arrival

05/29/99 12:16:00 AM 3 001/17:28 Push from 30 ft

05/29/99 12:21:00 AM 3 001/17:33 Contact

05/29/99 12:41:00 AM 3 001/17:53 Docking complete

05/29/99 3:13:00 AM 3 001/20:25 Early Ingress PMA 2

05/29/99 3:28:00 AM 3 001/20:40 CBM Controller Removal

05/29/99 3:43:00 AM 3 001/20:55 Node 1 Powerup

05/29/99 4:28:00 AM 3 001/21:40 Early Egress PMA 2

05/29/99 9:48:00 AM 3 002/03:00 Flight Day 3 Sleep

05/29/99 5:48:00 PM 4 002/11:00 Flight Day 4 Wake

05/29/99 6:48:00 PM 4 002/12:00 Node 1 IMV Valve Reconfig

23
05/29/99 7:48:00 PM 4 002/13:00 EVA Prep

05/29/99 9:28:00 PM 4 002/14:40 Early Comm Ant Survey via RMS

05/29/99 11:03:00 PM 4 002/16:15 EVA 1 A/L Egress

05/30/99 4:58:00 AM 4 002/22:10 EVA 1 A/L Ingress

05/30/99 5:38:00 AM 4 002/22:50 OSVS Target Survey

05/30/99 9:48:00 AM 4 003/03:00 Flight Day 4 Sleep

05/30/99 5:48:00 PM 5 003/11:00 Flight Day 5 Wake

05/30/99 7:38:00 PM 5 003/12:50 PMA 2 Ingress

05/30/99 7:48:00 PM 5 003/13:00 Simo Dump

05/30/99 7:48:00 PM 5 003/13:00 SHAB Config

05/30/99 8:33:00 PM 5 003/13:45 Node Ingress

05/30/99 8:58:00 PM 5 003/14:10 PMA 1 Ingress

05/30/99 9:08:00 PM 5 003/14:20 FGB Ingress

05/30/99 10:03:00 PM 5 003/15:15 Bar Code Labels Installation

05/30/99 10:03:00 PM 5 003/15:15 Rack Pin Install

05/30/99 10:08:00 PM 5 003/15:20 CWC Initial S/U, Bag 1 of 7

05/30/99 10:33:00 PM 5 003/15:45 First ZSR Installation

05/30/99 10:38:00 PM 5 003/15:50 MIRTS Install (Batt Block 4)

05/30/99 11:03:00 PM 5 003/16:15 Second ZSR Installation

05/30/99 11:33:00 PM 5 003/16:45 Early Comm IFM Start

05/31/99 12:03:00 AM 5 003/17:15 ZSR Label Installation

05/31/99 12:08:00 AM 5 003/17:20 MIRTS Install (Batt Blocks 5 & 6)

05/31/99 12:13:00 AM 5 003/17:25 Transfer Ops Begin

05/31/99 12:23:00 AM 5 003/17:35 14.7 Cabin Repress

05/31/99 1:38:00 AM 5 003/18:50 MIRTS C/O (Batt Block 3)

05/31/99 1:58:00 AM 5 003/19:10 Radiation Monitors Deploy

05/31/99 2:03:00 AM 5 003/19:15 Node 1 Hatch Inspection

05/31/99 2:03:00 AM 5 003/19:15 Acoustic Sample, 1 of 2

05/31/99 2:38:00 AM 5 003/19:50 Muffler Install, Pt 1 of 2

05/31/99 3:58:00 AM 5 003/21:10 CWC Fill Init, Bag 2 of 7

05/31/99 5:13:00 AM 5 003/22:25 Formaldehyde Mon Dply

05/31/99 5:48:00 AM 5 003/23:00 PAO Event-CDR, MS1, MS3

05/31/99 9:18:00 AM 5 004/02:30 Flight Day 5 Sleep

05/31/99 5:18:00 PM 6 004/10:30 Flight Day 6 Wake

05/31/99 8:08:00 PM 6 004/13:20 MIRTS Install (Batt 1 & 2)

05/31/99 8:18:00 PM 6 004/13:30 CWC Fill Init, Bag 3 of 7

05/31/99 8:18:00 PM 6 004/13:30 Transfer Ops Begin

05/31/99 9:43:00 PM 6 004/14:55 Muffler Install, Pt 2 of 2

05/31/99 11:08:00 PM 6 004/16:20 Acoustic Sample, 2 of 2

06/01/99 1:18:00 AM 6 004/18:30 PAO Event-CDR, MS5

06/01/99 2:13:00 AM 6 004/19:25 CWC Fill Init, Bag 4 of 7

24
06/01/99 2:28:00 AM 6 004/19:40 DTO 700-14 Ops 2 Test

06/01/99 3:03:00 AM 6 004/20:15 VRA Initial Setup

06/01/99 5:13:00 AM 6 004/22:25 Formaldehyde Mon Retreive

06/01/99 5:33:00 AM 6 004/22:45 Simo Dump

06/01/99 8:48:00 AM 6 005/02:00 Flight Day 6 Sleep

06/01/99 4:48:00 PM 7 005/10:00 Flight Day 7 Wake

06/01/99 7:08:00 PM 7 005/12:20 PAO Event-CDR, MS4

06/01/99 8:03:00 PM 7 005/13:15 Transfer Ops Begin

06/01/99 8:13:00 PM 7 005/13:25 CWC Fill Init, Bag 5 of 7

06/01/99 8:58:00 PM 7 005/14:10 VRA Science Activation

06/01/99 11:13:00 PM 7 005/16:25 VRA Sample Pair 1

06/01/99 11:58:00 PM 7 005/17:10 Crew Conference

06/02/99 1:38:00 AM 7 005/18:50 VRA Sample Pair 2

06/02/99 2:03:00 AM 7 005/19:15 CWC Fill Init, Bag 6 of 7

06/02/99 4:48:00 AM 7 005/22:00 VRA Sample Pair 3

06/02/99 5:23:00 AM 7 005/22:35 PAO Event-CDR, PLT, MS2

06/02/99 8:48:00 AM 7 006/02:00 Flight Day 7 Sleep

06/02/99 4:48:00 PM 8 006/10:00 Flight Day 8 Wake

06/02/99 7:48:00 PM 8 006/13:00 Transfer Ops Begin

06/02/99 7:48:00 PM 8 006/13:00 VRA Sample Pair 4

06/02/99 7:48:00 PM 8 006/13:00 N1 Hatch Adjustment

06/02/99 7:48:00 PM 8 006/13:00 DTO 1214

06/02/99 7:48:00 PM 8 006/13:00 Rack Pin Locate

06/02/99 8:48:00 PM 8 006/14:00 FGB Dust Filter

06/02/99 9:38:00 PM 8 006/14:50 SDS Valves Troubleshoot

06/02/99 9:48:00 PM 8 006/15:00 CWC Fill Init, Bag 7 of 7

06/02/99 9:48:00 PM 8 006/15:00 FGB Harmful Cart Rplc

06/02/99 10:13:00 PM 8 006/15:25 VRA Sample Pair 5

06/02/99 11:48:00 PM 8 006/17:00 O2 Repress

06/03/99 1:03:00 AM 8 006/18:15 VRA Sample Pair 6

06/03/99 1:23:00 AM 8 006/18:35 FGB PGO Egress

06/03/99 2:28:00 AM 8 006/19:40 FGB GA Egress

06/03/99 2:33:00 AM 8 006/19:45 VRA Deact

06/03/99 3:13:00 AM 8 006/20:25 PMA 1 Egress

06/03/99 3:48:00 AM 8 006/21:00 Node 1 Egress

06/03/99 4:08:00 AM 8 006/21:20 PMA 2 Egress

06/03/99 4:18:00 AM 8 006/21:30 Reboost

06/03/99 4:38:00 AM 8 006/21:50 VEST/PMA 2 Depress

06/03/99 5:18:00 AM 8 006/22:30 ISS Egress Complete

06/03/99 8:48:00 AM 8 007/02:00 Flight Day 8 Sleep

06/03/99 9:48:00 AM 8 007/03:00 NCS TFL U/L

25
06/03/99 11:48:00 AM 8 007/05:00 NCS S/W Patch U/L

06/03/99 1:48:00 PM 8 007/07:00 NCS DBL U/L

06/03/99 3:48:00 PM 9 007/09:00 Flight Day 9 Wake

06/03/99 6:37:00 PM 9 007/11:49 Undock

06/03/99 8:08:00 PM 9 007/13:20 Final Sep

06/03/99 8:48:00 PM 9 007/14:00 FGB OSK Build

06/03/99 9:03:00 PM 9 007/14:15 Simo Dump

06/03/99 9:18:00 PM 9 007/14:30 PILOT Training

06/03/99 9:43:00 PM 9 007/14:55 Space Flight Awareness

06/04/99 12:48:00 AM 9 007/18:00 Off Duty

06/04/99 8:48:00 AM 9 008/02:00 Flight Day 9 Sleep

06/04/99 4:48:00 PM 10 008/10:00 Flight Day 10 Wake

06/04/99 7:48:00 PM 10 008/13:00 FCS C/O & RCS H/F

06/04/99 7:48:00 PM 10 008/13:00 SHAB Stow

06/04/99 9:13:00 PM 10 008/14:25 Cabin Stow

06/04/99 9:53:00 PM 10 008/15:05 MAGR OPS3 GPS Test

06/04/99 11:18:00 PM 10 008/16:30 PAO Taped Message

06/05/99 12:48:00 AM 10 008/18:00 D/O Brief

06/05/99 3:11:00 AM 10 008/20:23 Starshine Deploy

06/05/99 4:03:00 AM 10 008/21:15 L-1 Comm Check, part 1 of 2

06/05/99 5:03:00 AM 10 008/22:15 L-1 Comm Check, part 2 of 2

06/05/99 5:33:00 AM 10 008/22:45 Ku-antenna stow

06/05/99 8:48:00 AM 10 009/02:00 Flight Day 10 Sleep

06/05/99 4:48:00 PM 11 009/10:00 Flight Day 11 Wake

06/06/99 2:21:00 AM 11 009/19:33 Deorbit Tig

06/06/99 3:25:00 AM 11 009/20:37 Landing at KSC

Updated: 05/20/1999

26
STS-96

Rendezvous 

Docking Mechanisms

 

Overview

 

ISS Docking Mechanism plans for Discovery, other Shuttles and this first

logistics mission call for Discovery to dock at the ISS on Day 3 and remain

there for six days. The Shuttle’s external airlock will be connected to Unity’s

Pressurized Mating Adapter (PMA) 2 using an interlocking system

designed in Russia. It is termed an Androgynous Peripheral Attach System.

Discovery’s crew will control PMA-2’s docking mechanism from the

cockpit. 

 

 

 

27
 

 

Pressurized Mating Adapters 

Two PMAs are attached to Unity, one at each end. They provide

passageways for crew, equipment and supplies. They also feature docking

mechanisms for space shuttles at one end and Zarya at the other. 

Because they are pressurized, heated and supplied with hand-hold grips,

the 8-ft-long, tunnel-like PMAs permit shirt-sleeved crews to pass between

Discovery and the ISS. 

 

Androgynous Peripheral Attach System 

A structural ring, a movable ring, alignment guides, latches, hooks,

dampers and fixers are integrated to form the Androgynous Peripheral

Attach System. It mates with an exact copy, and each can act as the

passive or active half. 

During docking, the active half’s capture ring extends outward from the

structural ring toward the passive half. Upon contact, the system dampens

out any relative motion between the docking vehicles. Once that is

accomplished, the capture ring aligns the two 

vehicles. It is then retracted with the passive ring still attached. Twenty-four

structural hooks snug the connection down to form an airtight seal. 

 

History/Background

 

The Androgynous Peripheral Attach System’s technological roots reach

back to the Apollo-Soyuz and Shuttle-Mir missions. The System is built by

Moscow-based RSC-Energia.

 

Updated: 05/14/1999

28
STS-96

Rendezvous 

Rendezvous and Docking

 

Overview

 

Discovery’s rendezvous and docking with the International Space Station

actually begins with the precisely timed launch of the shuttle on a course for

the station. During the first two days of the mission, periodic engine firings

will gradually bring Discovery to a point about eight nautical miles behind the

station, the starting point for a final approach to the station.

 

Terminal Phase

About three hours before the scheduled docking time on Flight Day Three,

Discovery will reach the point about eight nautical miles behind the ISS. At

that time, Discovery's jets will be fired in a Terminal Phase Initiation (TI)

burn to begin the final phase of the rendezvous. Discovery will close the

final eight nautical miles to the station during the next orbit. As Discovery

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

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

29
As Discovery begins to close in on the station, flight controllers will

command the station to the docking orientation, perpendicular to the Earth's

surface with the Unity module pointed toward space and Zarya toward

Earth. For Discovery's final approach, the solar panels on the station will be

"feathered" to have their edge facing the shuttle. Also, when within about

1,000 feet of the station, Commander Kent Rominger will use Discovery's

steering jets in a mode called "Low Z," a mode that fires jets offset rather

than pointed directly at the station to control the shuttle's approach. This jet

mode together with the solar panel's feathering prevent exhaust from shuttle

jets from flexing and overstressing the station's solar panels.

 

Proximity Operations

As Discovery reaches close proximity to the station, the Trajectory Control

Sensor, a laser ranging device mounted in the shuttle payload bay, will

supplement the shuttle’s onboard navigation information by supplying

additional data on the range and closing rate. As Discovery closes in, the

shuttle will have the opportunity for several small successive engine firings

to fine-tune its approach using its onboard navigation information. As

Discovery moves to within about a half-mile of the station, Rominger will

take over manual control of the shuttle's approach, flying the spacecraft

from the aft flight deck and monitoring the approach through the rear and

overhead windows.

30
Rominger will slow Discovery's approach and fly to a point about 500 feet

directly below the station, from which he will begin a half-circle of the

station. During the rendezvous, Rominger will be assisted by Pilot Rick

Husband in controlling Discovery's approach. Mission Specialists Tammy

Jernigan and Ellen Ochoa also will play key roles in the rendezvous, with

Jernigan operating the shuttle's docking mechanism and Ochoa assisting

with the rendezvous navigation. The crew will use a handheld laser pointed

through the shuttle windows to provide supplemental information on the

station's range and closing rate.

Rominger will fly Discovery to cross about 350 feet in front of the station and

then continue to reach a point about 250 feet directly above the station. He

will stop Discovery and then slowly descend toward the station to a point

about 170 feet away from it. At approximately 170 feet distant, Rominger will

hold Discovery's position for about a half-hour to allow the station to move

within range of Russian communications stations. Also at this time, Jernigan

will power up the docking mechanism and prepare it for contact and capture

with the station. A day ahead of the rendezvous, the docking mechanism is

scheduled to be checked out and its docking ring extended.

 

Final Approach

Once the station is in communications with Russia and flight controllers

have confirmed it is in the proper configuration for docking, Rominger will

begin the final approach.

Using the view from a centerline camera fixed in the center of Discovery's

docking mechanism, Rominger will precisely align the shuttle mechanism

with the docking mechanism on Unity's conical mating adapter as he

approaches. At a distance of about 30 feet, Rominger will stationkeep

momentarily to adjust the alignment, if necessary.

 

Docking

For Discovery's docking, Rominger will maintain the shuttle's speed relative

to the station at about one-tenth of a foot per second, and keep the docking

mechanisms aligned to within three inches of one another. As Discovery

moves to within 25 feet, Rominger will switch the shuttle steering jets back

to normal mode from "Low Z" to provide better control of Discovery for the

final docking.

When Discovery makes contact with the station, latches will automatically

attach the two spacecraft together. Immediately after Discovery docks, the

shuttle's steering jets will be deactivated and ground controllers will

command off the station's steering jets to reduce the forces acting at the

31
docking interface. Shock absorber-type springs in the docking mechanism

will dampen any relative motion between the shuttle and the station.

Once relative motion between the spacecraft has been stopped, Jernigan

will command the docking ring on Discovery's mechanism to retract and

close latches in the mechanism to firmly secure the shuttle to the station.

Once the two vehicles are firmly secured, the shuttle’s steering jets will be

reactivated to control both spacecraft for the duration of the docked

operations.

 

Updated: 05/11/1999

32
STS-96

Rendezvous 

Undocking, Separation and Fly-Around

Overview

Once Discovery is ready to undock, the initial separation will be performed

by springs in the docking mechanism that will gently push the shuttle away

from the station. Both Discovery and the station’s steering jets will be shut

off to avoid any inadvertent firings during this initial separation. 

Once the docking mechanism’s springs have pushed Discovery away to a

distance of about two feet, when the docking devices will be clear of one

another, Husband will turn the shuttle's steering jets back on in "Low Z"

mode and fire them to begin very slowly moving away. From the aft flight

deck, Pilot Rick Husband will manually control Discovery within a tight

corridor as he separates from the ISS, essentially the reverse of the task

performed by Commander Kent Rominger when Discovery docked.

Discovery will continue away to a distance of about 450 feet, where

Husband will begin the close flyaround of the station, first crossing a point

directly behind, then directly underneath and then again above the station.

If Discovery’s propellant reserves allow it, Husband will circle the station

twice as the crew records views of the exterior with still photography and

video. As Discovery crosses directly above the station for the second time,

Husband will fire Discovery's jets to perform a final separation. The

separation firing will put Discovery on a course that will have it pass about a

half-mile behind the station and then about a mile and a half below the

station before moving ahead of it with constantly increasing distance.

Updated: 05/11/1999

33
STS-96

EVAs 

Space Walk to Install U.S., Russian Crane Systems

 

Overview

 

Astronauts Tammy Jernigan and Daniel Barry will conduct a six-hour space

walk on flight day four to install crane systems that will be used on future

missions to assist in assembly and transfer operations. The two astronauts

will be assisted by Flight Engineer Ellen Ochoa, who will operate the

Shuttle’s robotic arm from inside Discovery. 

 

Getting Ready 

Preparations for the space walk begin early in the mission, on flight day two,

with the checkout of the space suits, also called extravehicular mobility

units, or EMUs. Later that day, the air pressure in the crew cabin will be

reduced from the standard operating pressure at 14.7 psi to 10.2 psi in

order to gradually condition the astronauts to an atmospheric environment

more closely resembling that of the space suits, themselves, which operate

at 4.3 psi. This technique reduces the time required for the astronauts to

34
"prebreathe" pure oxygen so that nitrogen may be cleansed from their

bloodstream to prevent a condition commonly called the "bends." The

astronauts will prepare their EVA tools and review procedures for their

installation operation on the third day of the mission. 

 

The Space Walk 

On flight day four, Jernigan and Barry will don their space suits, pre-breathe

pure oxygen to cleanse the remaining nitrogen from their blood streams,

and exit the Orbiter into the payload bay for six hours of preparation,

installation and cleanup. Jernigan, designated "EV1" will exit the airlock

first and, after configuring tethers for the start of the space walk, will be

joined by Barry, designated "EV2." Jernigan will be visibly distinguished by

a red stripe around the legs on her space suit. 

Preparations will include the placement of a work station and portable foot

restraints into position for the installation of an American-built crane, called

the ORU Transfer Device, or OTD, and the Russian-built crane called Strela

(Russian, for "arrow"). Installation of the OTD and Strela are estimated to

take about 1 hour each. 

Ready to begin the installation work, Jernigan will fix her boots to a foot

restraint on the end of the Shuttle's robotic arm, and Ochoa will maneuver

her from a foot restraint at Pressurized Mating Adapter (PMA-1) to the

Integrated Cargo Carrier (ICC). PMA-1 is a passageway between Unity and

Zarya, and the ICC is a flatbed pallet attached in Discovery's payload bay. 

Jernigan will meet Barry on the Integrated Cargo Carrier, where they will

retrieve the small, 209-pound U.S. OTD. While holding the crane, Jernigan

will be transported back to PMA-1. Barry will join her to attach the crane to

an EVA worksite fixture on the PMA. 

The two will return to the Integrated Cargo Carrier and retrieve the

165-pound operator post and 33-pound grapple fixture adapter plate for the

Russian crane, Strela. They will assemble those pieces on one of the two

PMA-2 grapple fixtures. PMA-2 connects the Shuttle external airlock to

Unity. 

Strela is an updated version of the crane used on Mir. It will primarily be

used for Science Power Platform operations. Assembly of the

three-metric-ton capacity crane will be completed during this year's second

ISS logistics mission. A 45-ft. telescopic boom will then be added to the

operator post, and the completed assembly will be moved to a grapple

fixture on Zarya. 

The astronauts will then return to the ICC to retrieve two portable foot

restraints and transfer them into PMA-1. They will return to the Integrated

Cargo Carrier, one last time, to remove three tool and hardware bags and

three additional pieces of EVA support equipment from the SPACEHAB

35
Oceaneering Space System box. The bags will contain tools for handling

ISS replacement parts and to assist in the assembly of the Space Station,

as well as on-orbit installable handrails. Jernigan and Barry will stow them

on Unity. 

If time permits, the two space walkers will also install a thermal cover on a

Unity trunion pin, inspect Zarya's paint, checkout the ODT and survey the

Early Communications System antenna on the starboard side of Unity. 

 

 

36
Time Event Prime Backup

0:00 Airlock Egress Tamara

Jernigan

Daniel Barry

00:30 Post Depress/Egress; and

set-up for EVA activities

in Payload Bay

Tamara

Jernigan

Daniel Barry

01:30 Crane Setup by RMS

Operator Ochoa; Crane

Removal and Installation

by Jernigan & Barry

Tamara

Jernigan

Daniel Barry

02:30 STRELA Set up by RMS

Operator Ochoa; STRELA

Remove and Install by

Jernigan and Barry

Tamara

Jernigan

Daniel Barry

03:45 IAPFR Pre-Retrieve and

Install with RMS; IAPFR

Remove by EV1, Docking

Target Install by EV2

Tamara

Jernigan

Daniel Barry

04:30 Logistics Bags Retrieve

by RMS Operator; Tool

Bag Install by EV1 and

EV2; Photo Survey by

EV1

Tamara

Jernigan

Daniel Barry

05:30 Foot Restraint Install, and

Payload Bay Clean Up

Tamara

Jernigan

Daniel Barry

06:15 Airlock Ingress and

Re-press (approx. 20

minutes)

Tamara

Jernigan

Daniel Barry

06:35 EVA Conclusion Tamara

Jernigan

Daniel Barry

Updated: 05/14/1999

 

37
STS-96

Payloads 

Cargo Transfer

SpaceHab

 

Prime: Julie Payette

Overview

 

Mission Specialists working in the pressurized, shirtsleeves environment

provided by SPACEHAB are tasked with moving some 750 items to the ISS

from the cargo carrier’s racks, lockers and other stowage facilities. A

number of those items are being stowed aboard the Station for use by

crews on future missions, beginning with the addition of Russia’s Service

Module:

38
Items ISS Mission /Year Planned ISS Location

Computers, printers, 2R Russian Service Module / 1999 Zarya

cables

Vacuum access 3A Integrated Truss Z1 / 1999 Unity

jumper, charcoal

canisters, adapters

Oxygen canisters 4A Integrated Truss P6 / 1999 Unity

Vacuum access 5A US Laboratory Module / 2000 Unity

jumper

Russian hardware that will be placed on the ISS during STS-96 includes:

· Life support systems replacement spares

· Sanitary and hygienic equipment

· Medical support equipment

· On-board computer system replacement parts

· Maintenance repair kits

· Base unit and related components of the Strela ("Arrow") crane

· Zarya sound damping kits

· MIRT repair kits

Priorities

Logistics experts for this mission developed a categorical priority system for

moving cargo that puts the highest value on ensuring the safe entry and exit

of the crew members as they move between the shuttle and the ISS. These

priorities were set in accordance with the most mission critical to the least,

while accounting for what would be left undone were the mission to be

terminated earlier than planned.

Examples from each category are shown below, starting with the highest

priority.

1. Ingress/safety

· ISS oxygen communication assembly

· Atmosphere sampling bottles

· Charcoal filter analyzer element

· Zarya muffler [acoustic damping] hardware

39
2. Critical spares

· MIRTs

· Sequential shunt unit

· Common Berthing Mechanism seal patch kits

· Early communication command telemetry processor

3. Incremental assembly

· Tools and power equipment

· Tethers and related gear

· Photo-TV cameras, film, tape

· Space suits and associated garments, equipment

4. Crew health maintenance

· Medical support equipment

· Cardiorecorder

· Audio dosimeter biobag

· Formaldehyde monitor kit

5. Pre-position for future missions

6. Resupply

· 2A recovery hardware

· Driver drill charger kit

· Braycote lubricant

· Emergency exit decal

7. Spares/non-assembly equipment

· IMAX 3D movie production hardware, accessories

· Crew provisions

· Clothing

· Sleeping bags

8. Detailed test objectives

· Velcro ties

· Single-sided tape

· Strain gage extension cables

· Flex hose assembly

Cargo Handling

Despite the virtual weightlessness in which the astronauts will work, moving

the SPACEHAB's cargo won’t be easy. In carefully choreographed

movements not unlike those of research divers retrieving specimens from a

coral reef, the Mission Specialists will ease each cargo item out of its

individual location and push or pull it to its destination.

40
En route, the items must be taken through Discovery’s cargo bay tunnel,

negotiated around a right-angle turn and into Pressurized Mating Adapter 2,

and either deposited in Unity or pushed on into Zarya.

 

Additional Tasks

If time permits, additional tasks will be performed during the spacewalk and

internal transfers.

Space-walking astronauts Jernigan and Barry may have time to survey, for

instance, discoloration on Unity, the starboard omnidirectional antenna for

the ISS Early Communications System, and the paint on Zarya.

Mission Specialists inside will try to find the time to pressure-check a

nitrogen line, inspect Unity’s forward and aft hatch mechanisms and adjust

them if necessary, and trouble-shoot a sample delivery system valve. If

there is sufficient shuttle propellant following Discovery’s undocking from the

ISS, a fly-around visual inspection will be performed prior to de-orbit and

landing.

 

Updated: 05/11/1999

41
STS-96

Payloads 

Integrated Cargo Carrier

Payload Bay

3050 lbs. lbs.

 

Prime:

Backup:

Overview

 

The Integrated Cargo Carrier is an unpressurized flat bed pallet and keel

yoke assembly housed in Discovery's payload bay. Constructed of

aluminum, it is eight feet long, 15 feet wide and 10 inches thick and has the

capability to carry cargo on both faces of the pallet, both atop and below.

42
During STS-96, the ICC will carry the U.S. space walkers' crane, which is

called the OTD for Orbital Replacement Unit Transfer Device. The OTD

weighs 209 pounds and will be mounted to the exterior of Unity during a

space walk by astronauts Tammy Jernigan and Dan Barry. It also will carry

198 pounds of parts for the Russian Strela crane which will be stowed on

the exterior of Pressurized Mating Adapter 2 (PMA-2)by Jernigan and Barry.

Also mounted to the ICC, is the Spacehab-Oceaneering Space System Box

(SHOSS), which is designed to carry up to 400 pounds of space-walking

tools and flight equipment to assist astronauts during ISS assembly.

The ICC provides sufficient surface area in the cargo bay to carry

approximately 3,000 pounds of cargo which would otherwise have to be

carried in the Shuttle's cabin.

The ICC will be used by astronauts throughout the construction of the

Space Station as it transports hardware from locations on the station's

exterior to work sites on the truss assemblies.

 

Updated: 05/19/1999

43
STS-96

Payloads 

Integrated Vehicle Health Monitoring HEDS Technology

Demonstration 2

Payload Bay

254 lbs. lbs.

Prime: Rick Husband

Overview

This is the second of two planned flights of the IVHM HTD, an experiment

designed to evaluate the feasibility of using modern commercial sensors to

monitor the health of space shuttle systems during flight in order to reduce

ground processing of NASA's fleet of orbiters. IVHM HTD-1 was flown on

STS-95 in October-November of 1998. 

Shuttle processing currently involves the verification of thousands of

requirements to determine the health of shuttle systems. In early 1997,

NASA studied these requirements to determine if it could reduce the

processing time and increase vehicle safety. NASA found that ground

processing (planned and unplanned) could potentially be reduced 15 to

20%. Planned work could be reduced by implementing a system with

predictive capabilities to monitor subsystem health in real time during flight

and by extending the service life of life-limited components. Unplanned

work could be reduced by improving visibility of system health and

streamlining problem isolation.

IVHM is essentially an advanced form of a traditional vehicle

instrumentation system, which consists of sensors (pressure, temperature,

voltage, strain, acceleration, etc.), wiring, signal conditioning devices,

multiplexing devices, and recording devices. But an IVHM system goes a

step further by providing the capability to process data instead of merely

recording data. This allows an onboard trend analysis that could detect

system degradation and control in-flight systems checkout in addition to

allowing more efficient system servicing and checkout on the ground. 

During the terminal launch countdown, an IVHM data stream is transmitted

to the Launch Control Center for processing and viewing. Approximately 10

44
seconds before takeoff, the IVHM processor autonomously begins

recording data. Data is recorded during ascent and during predefined

periods on orbit. The recorded data is dumped to a ground system after the

mission.

On STS-96, the experiment will be activated during prelaunch cryogenic

propellant servicing. The pilot will deactivate the HTD about one hour after

launch. The crew will activate the experiment for one hour each day during

the mission.

The IVHM HTD-2 experiment package consists of an air transport rack for

data acquisition and processing and two remote health nodes mounted on a

getaway special beam in the orbiter payload bay. The ATR and RHNs are

connected by cables to 120 sensors in the orbiter aft crew compartment

and payload bay.

One of the technologies to be demonstrated is microelectromechanical

sensing for detecting the presence of hazardous gas and sensing pressure

in vacuum-jacketed lines in the orbiter's cryogenic distribution system. Other

technology demonstrations include Bragg-Grating fiber-optic sensing for

hazardous gas detection and structural strain/temperature determination,

thermal flow meter leak detection, accelerometers for space shuttle main

engine pump vibration sensing, VME bus architecture, and flash card

memory. 

The HTDs will also provide data on the performance of commercial

computing products, such as a VME bus architecture and ATR chassis, and

on the effects of radiation and heat on commercial and military VME

hardware.

The focus of IVHM HTD-2 is to determine the health of selected functions of

the orbiter's main propulsion system, main engines, and power reactant

storage and distribution system. The technologies to be developed include

Bragg-Grating fiber-optic sensors for hydrogen, strain, and temperature

sensing and smart sensors for hydrogen, oxygen, and pressure sensing.

IVHM HTD-2 will also evaluate distributed data acquisition by the remote

health nodes with fiber data distributed interface communication and a

lightweight, low-power microelectronic hardware platform; real-time

information processing of space shuttle main engine pump vibration;

solid-state data storage; and advanced control room equipment and

applications.

A complete flight IVHM system consists of advanced lightweight, low-power

sensors; distributed data acquisition and processing; real-time information

processing, including diagnostics, prognostics, and vehicle autonomy for

control or suggested action; and advanced solid-state, high-density data

storage. A complete ground IVHM system consists of improved control

room architectures and automated ground support equipment. This

45
experiment will advance the development of a subset of a complete IVHM

system.

History/Background

The IVHM HTD experiments are part of NASA's Human Exploration and

Development of Space enterprise. HEDS is pursuing answers to myriad

research and engineering questions that must be answered as humans

learn to live and work in space. The goals of the HEDS enterprise are to

explore the solar system, use the environment of space to expand scientific

knowledge, provide safe and affordable human access to space, and enrich

life on Earth through space. 

Benefits

The IVHM HTDs are providing data on the performance of advanced

sensing technologies and commercial products which may be useful in

reducing the cost and time associated with processing the space shuttle,

streamlining problem troubleshooting, and improving NASA's awareness of

shuttle systems during operation. Technologies and products that are found

to be useful will be incorporated into an IVHM system for the shuttle. The

data from these experiments may also be used to benefit other programs,

such as liquid flyback boosters, X vehicles, the crew return vehicle, and

lunar/Mars missions.

Updated: 05/11/1999

46
STS-96

Payloads 

MIRTs Changeout

SpaceHab

 

Prime: Julie Payette

Backup: Valery Tokarev

Overview

 

On Flight Days 5 and 6, astronaut Julie Payette and Cosmonaut Valery

Ivanovich Tokarev will replace all 18 of the battery charge/discharge units

that support Zarya’s six nickel-cadmium batteries. Known by the Russian

acronym "MIRTs," they are thought to be responsible for voltage problems

first detected in January. 

MIRTs are part of a system that indicates the level of charge for each of

Zarya’s batteries and, in turn, dictates when the onboard charging system

will begin to taper-off the power supply to each. 

47
Flight controllers have been working around the problem by cycling the

batteries, fully charging, and then fully discharging them every week. This

procedure resets the charge indication and maintains the batteries at peak

performance. It appears that when Zarya’s MIRTs measure the cumulative

charge or amp-hour readings of each battery, they introduce a slight error in

a compensation factor and thus prevent full charge/discharge cycles from

occurring. 

Replacement of the units -- they measure 5.9 x 4.7 x 3 inches and weigh

1.43 pounds -- may reduce the need for weekly cycling, resulting in better

long-term battery performance and additional backup equipment capabilities

for the ISS. Payette and Tokarev were trained for this part of the mission in

mid-March at the Gagarin Cosmonaut Training Center at Star City outside

Moscow, where a full-scale Zarya mock-up is located, and will follow

procedures jointly developed by engineers at Mission Control Center

Moscow and Mission Control Center-Houston. 

The MIRTs are located under Zarya’s floor panels. 

 

Updated: 05/11/1999

48
STS-96

Payloads 

Shuttle Vibration Forces Experiment

Payload Bay

327 lbs. lbs.

Principal Investigator: Terry Scharton, Jet Propulsion Laboratory, Pasadena, Calif.

Overview

The Shuttle Vibration Forces experiment will measure the dynamic forces

between Discovery and a canister attached to the orbiter's payload bay wall.

The experiment is designed to validate a new vibration testing method that,

if proven, will enable NASA to fly more sophisticated equipment on space

shuttle missions.

The vibration method that SVF will test has been used on other NASA flight

programs. It involves limiting the force of the vibration test to the force

expected during flight.

Commercial triaxial force transducers and three wideband stand-alone

acceleration measurement devices built by the Johnson Space Center will

measure the dynamic forces. 

The SVF payload will be carried in a standard getaway special canister

mounted on the sidewall of the payload bay. The force transducers have

been incorporated into four custom brackets, which replace the brackets

normally used to attach GAS canisters to the sidewall GAS adapter beam.

The SVF payload is self-supporting (the payload is battery powered and the

data is recorded within the payload) and does not require any crew

interface. The payload will be activated automatically by orbiter lift-off

vibrations and will operate for approximately 240 seconds. 

STS-96 is the second flight of the SVF experiment. The experiment's first

flight was STS-90 in April 1998.

49
History/Background

The powerful rocket engines used on the shuttle and other launch vehicles

generate a great deal of noise and vibration at liftoff. All shuttle equipment

must be designed for this severe environment, and most of the cargo for

shuttle missions is subjected to extreme vibration testing to ensure that it

will survive. 

Because conventional vibration testing methods have not changed

substantially in 50 years, they are not well suited for lightweight and

sometimes delicate aerospace equipment. Equipment, which could survive

space flight, often fails during vibration testing, wasting effort and money

because the equipment must be redesigned and retested. 

Benefits

The experiment is designed to validate a new vibration testing method that,

if proven, will enable NASA to fly more sophisticated equipment on space

shuttle missions.

Updated: 05/11/1999

50
STS-96

Payloads 

SPACEHAB

Payload Bay

16072 lbs. lbs.

 

Prime: Ellen Ochoa

Backup: Julie Payette

Overview

 

U.S. and Russian hardware for the International Space Station will be

carried in the SPACEHAB double module, a pressurized laboratory in the

shuttle's cargo bay that is connected to the middeck area of the orbiter.

Crew access is through a tunnel system located between the orbiter

middeck and the SPACEHAB module. 

Designed to augment the shuttle orbiter's middeck, the SPACEHAB double

module has a total cargo capacity of up to 10,000 pounds and contains

systems necessary to support astronauts, such as ventilation, lighting, and

limited power. 

Generally, two crew members are required for SPACEHAB operations. The

SPACEHAB environmental control system is designed to nominally

accommodate two crew members on a continuous basis. Additional crew

members can be accommodated for brief periods at the expense of

reduced cabin air heat rejection capability. 

51
 

Microgravity Research Program 

Working in partnership with the scientific community and commercial

industry, NASA's Microgravity Research Program strives to increase

understanding of the effects of gravity on biological, chemical, and physical

systems. 

Using both space flight- and ground-based experiments, researchers

throughout the nation, as well as international partners, are working

together to benefit economic, social, and industrial aspects of life for the

United States and the entire Earth. U.S. universities, designated by NASA

as commercial space centers, share these space advancements with U.S.

industry to create new commercial products, applications, and processes. 

Under the NASA Headquarters' Office of Life and Microgravity Sciences

and Application, the Microgravity Research Program supports NASA's

strategic plan in the Human Exploration and Development of Space

Enterprise. 

Microgravity research has been performed by NASA for more than 25

years. The term microgravity means a state of very little gravity. The prefix

micro comes from the Greek word mikros ("small"). In metric terms, the

prefix means one part in a million (0.000001). 

Gravity dominates everything on Earth, from the way life has developed to

the way materials interact. But aboard a spacecraft orbiting the Earth, the

effects of gravity are barely felt. In this microgravity environment, scientists

can conduct experiments that are all but impossible to perform on Earth. In

this virtual absence of gravity as we know it, space flight gives scientists a

unique opportunity to study the states of matter (solids, liquids, and gases)

and the forces and processes that affect them. 

Marshall Space Flight Center in Huntsville, Ala., is the lead center for

NASA's Microgravity Research Program. The program manages

Microgravity Science and Applications Project Offices at the Lewis

Research Center in Cleveland, Ohio, and the Jet Propulsion Laboratory in

Pasadena, Calif., and project offices at Marshall. 

Under the project offices, the Microgravity Research Program is divided into

nine major areas: five science disciplines, three research infrastructure

programs, and the Space Products Development Office. 

The science disciplines include biotechnology, fluid physics, materials

science, combustion science and fundamental physics. The infrastructure

activities include acceleration measurement, advanced technology, and the

Glovebox Flight Program. 

52
Marshall manages the Biotechnology Program and Material Science

Program as well as the Glovebox Flight Program and the Space Products

Development Office. Lewis Research Center manages the Fluid Physics,

Combustion Science and Acceleration Measurement programs, while the

Jet Propulsion Laboratory manages the Fundamental Physics and the

Advanced Technology Development Program. As an element of the

Biotechnology Program, Johnson Space Center manages bioreactor

research in cell tissue growth. 

In addition to the U.S. and Russian hardware for the International Space

Station carried within the SPACEHAB module, additional unpressurized

equipment for transfer to the space station will be carried on the new

SPACEHAB integrated cargo carrier. The ICC, a cross-bay carrier that can

accommodate 6,000 pounds of cargo, will be carrying a Russian cargo

crane known as STRELA, the SPACEHAB Oceaneering Space System

Box, and a U.S.-built crane called the orbital replacement unit transfer

device. 

History/Background

 

Early in the shuttle program, it became evident that the orbiter middeck is

the best place to conduct crew-tended experiments in space. Each shuttle

orbiter has 42 middeck lockers, but most are used to stow crew gear for a

typical seven-day mission, leaving only seven or eight for scientific studies.

But SPACEHAB, the first crew-tended commercial payload carrier, has

initiated a new era of space experimentation. 

The basic SPACEHAB module, which takes up a quarter of the orbiter's

payload bay, is like a second middeck. The 10-foot-long pressurized

module adds 1,100 cubic feet of pressurized work space that can hold 61

lockers or experiment racks or a combination of the two. The lockers are

sized and equipped like those in the shuttle middeck so that experiments

can be moved from one location to the other. The lockers accommodate up

to 60 pounds of experiment hardware in about 2 cubic feet. A rack, which

can be single or double, takes the space of ten lockers. Double racks are

similar in size and design to those planned for the space station so that they

can serve as test beds for future projects. A single rack can carry 655

pounds of hardware in 22.5 cubic feet. 

A new double module, developed specifically for shuttle missions to Mir, will

be used on STS-96. The double module, which can accommodate nearly

10,000 pounds of cargo, was created by joining two single modules. 

The astronauts enter the module through a modified Spacelab tunnel

adapter. SPACEHAB can accommodate two crew members on a

continuous basis, but additional crew members can work in the module for

53
brief periods. Power, command and data services, cooling, vacuum, and

other utilities are supplied by orbiter crew cabin and payload bay

resources. 

SPACEHAB was privately developed and is privately operated by

SPACEHAB, Inc., of Arlington, Va. STS-96 is the 13th flight of

SPACEHAB. 

The first flight of the SPACEHAB research laboratory was on STS-57 in

June 1993. All systems operated as expected, and the 21 NASA-sponsored

experiments met more than 90% of the criteria for mission success.

SPACEHAB 2 was flown on STS-60 in February 1994 and carried 13

experiments. More than 20 experiments were performed as part of

SPACEHAB 3 on STS-63 in February 1995. 

On STS-76, in March 1996, SPACEHAB carried 37 materials processing,

microgravity, Earth sciences, biology, life sciences, and ISS risk mitigation

experiments and logistics to Mir. Ten commercial space product

development payloads in the areas of biotechnology, electronic materials,

polymers, and agriculture were part of the SPACEHAB mission on STS-77

in May 1996. SPACEHAB carried additional stowage bags, experiments,

and other logistics to Mir on STS-79 in September 1996, STS-81 in January

1997, STS-84 in May 1997, STS-86 in September 1997, STS-89 in January

1998, STS-91 in June 1998, and STS-95 in November 1998. 

 

Benefits

 

Using both space flight- and ground-based experiments, researchers

throughout the nation, as well as international partners, are working

together to benefit economic, social, and industrial aspects of life for the

United States and the entire Earth. U.S. universities, designated by NASA

as commercial space centers, share these space advancements with U.S.

industry to create new commercial products, applications, and processes.

Updated: 05/11/1999

54
STS-96

Payloads 

Student-Tracked Atmospheric Research Satellite for Heuristic

International Networking Equipment (STARSHINE)

353 lbs. lbs.

 

Principal Investigator: Professor R. Gilbert Moore, Utah State University

Overview

 

Twenty-five thousand students scattered across the United States and

around the world are set to watch for their own twinkling satellite to sweep

across the sky in the morning and evening twilight hours. The students

polished nearly 900 aluminum mirrors that completely cover the

beachball-sized satellite's outer surface. The spacecraft, which was

designed and built by the Naval Research Laboratory in Washington, D.C.,

will be ejected from the space shuttle Discovery and placed in a circular

orbit 220 miles above the Earth.

As STARSHINE orbits the Earth this summer and into early winter, sunlight

reflecting off its mirrors will be visible during twilight hours to observers on

the ground as far north as central Canada and the northern tip of Scotland

and as far south as the southern tip of South America, Africa and New

Zealand. Teams of elementary, middle and high school students will visually

track the satellite and note the times that it passes between selected pairs

of targeted stars. 

The students will enter their observations on the STARSHINE project's

Internet site at http://www.azinet.com/starshine, and NRL and the U.S.

Space Command will use the measurements to calculate the satellite's

orbit. The German Space Operations Center in Oberpfaffenhafen,

Germany, will use the orbital data to issue sighting predictions so the

students will know where and when to look for STARSHINE's next

appearance over their observation sites. As the project progresses, high

school students will be taught how to calculate the orbits on their personal

computers.

Throughout the mission, students will measure the daily change in the time

it takes STARSHINE to circle the Earth. The students will use this

information to calculate the density of the Earth's upper atmosphere. During

its six-month lifetime, STARSHINE will gradually lose altitude because of

the aerodynamic drag caused by the atmosphere's density and eventually

will burn up like a flaming meteor approximately 60 miles above the Earth. 

55
Students will also look at daily solar images on the STARSHINE Web site

and count the sunspots on the solar surface. They will plot the daily number

of sunspots against the rate of change of STARSHINE's orbital period to

learn how solar storms heat and expand the Earth's upper atmosphere,

causing variations in its density and producing aerodynamic drag.

At the end of the mission, the students will attempt to photograph the

satellite's fiery reentry, and the best picture will win a prize.

The STARSHINE spacecraft is an 86.6-pound hollow aluminum sphere that

is 19 inches in diameter. It is covered with 878 polished aluminum mirrors

that are 1 inch in diameter. The mirrors were machined by Utah high school

technology students and shipped to schools in Argentina, Austria, Australia,

Belgium, Canada, China, Denmark, England, Finland, Japan, Mexico, New

Zealand, Pakistan, South Africa, Spain, Turkey, the United States, and

Zimbabwe for polishing.

On the day before landing, the satellite will be deployed from its hitchhiker

getaway special canister in Discovery's payload bay by a spring ejection

system at an altitude of 205 nautical miles. A combination of spring rotation

and tipoff will cause it to rotate about its pitch and yaw axes at a rate of one

revolution per minute. This angular motion, combined with STARSHINE's

orbital translation rate of 2 degrees per second, will produce flashes of

sunlight from its mirrors every few seconds.

Project STARSHINE plans to launch one satellite per year over an 11-year

solar cycle. Just as soon as STARSHINE 1 gets into orbit and begins its

twinkling trek across the twilight sky, project officials plan to push ahead

with preparations for STARSHINE 2. The basic spacecraft structure for

STARSHINE 2 has already been built by NRL, and Utah high school

technolgy students are working on the mirror blanks.

 

 

56
Benefits

The principal objectives of Project STARSHINE are educational and

motivational. If students help "build" the spacecraft (by polishing its mirrors),

they should be more excited about tracking it and using it to measure upper

atmospheric density and the response of that region of the atmosphere to

solar storms. 

Project STARSHINE is giving precollege students a chance to work with

real space hardware and learn how to do precision work on elements of that

hardware. They also learn about satellite orbits and Earth's upper

atmosphere and the interaction between the Earth's and sun's atmospheres

and magnetospheres. The participants use the Internet to obtain

knowledge, report their measurements, and communicate as team

members with students in other countries. They are taught how to make

precision optical measurements and use precision timing systems to make

those measurements, and they learn something about 

observational astronomy and amateur radio. In short, they learn that

science and engineering and technology can be fun and still produce useful

results.

The project has received overwhelmingly positive responses from teachers

and students around the world--before the satellite leaves the ground.

When the satellite completes its six months in orbit, project officials believe

that they will have built up a cadre of student participants who will be

interested in becoming even more involved in future projects of this nature.

If Project STARSHINE is able to fly a satellite every year throughout an

11-year solar cycle, as presently planned, generations of students will learn

the basic principles of solar-terrestrial physics. To further this end, the

project plans to post daily white-light, ground-based images of the sun on its

Web site as well as satellite images in other wavelengths and will link to

other solar activity indices in Boulder, Colo. In the fall, the project will begin

posting auroral images as well.

Besides educating and motivating students, Project STARSHINE may have

scientific benefits. If enough students do serious tracking of the spacecraft

to get good orbits, especially during the terminal phase of the flight, the

project might be able contribute to the pool of knowledge of the average

density of the atmosphere in the 60- to 120-mile altitude regime. Since

STARSHINE is spherical, it has a much more unifom drag coefficient than

spacecraft with solar arrays and helical antennas and other structures

protruding from them, so the density measurements that will be made from

tracking STARSHINE will be more precise than those from tracking other

reentering spacecraft.

Updated: 05/11/1999

57
STS-96

DTO/DSO/RMEs 

Heat Exchange Unit Evaluation

DTO 686

Prime: Daniel Barry

Backup: Julie Payette

Overview

This DTO will evaluate a commercial portable heat exchange unit that uses

water as the refrigerant and identify possible uses on the space shuttle. 

Chilling is caused by the evaporation of the water in the unit under reduced

pressure obtained from the vacuum of space. Since water and vacuum are

abundant resources on the shuttle, the unit has a potentially extensive

chilling capacity. The heat exchange unit also has a unique internal feature

that controls the water vaporization rate while maximizing the heat

exchange during the process. The system performed well in demonstrations

under gravity conditions, and in theory, should perform equally as well in

microgravity.

Beverages, ice cream, and other items are chilled by exposing them to the

outer surface of the heat exchange unit, which is smaller than a beverage

can. The vacuum for operating the device is provided by the orbiter's waste

control system vacuum port or the waste water overboard dump system.

The unit can operate for up to 12 hours. 

This is the first of three planned flights of DTO 686.

Updated: 05/11/1999

58
STS-96

DTO/DSO/RMEs 

Resource Transfer Line Capability Evaluation

DTO 1214

Prime: Kent Rominger

Backup: Rick Husband

Overview

The major objective of this DTO is to verify the installation and operation of

resource transfer bundle (RTB) drag-through lines for transferring nitrogen,

oxygen, and water from the space shuttle orbiter to the International Space

Station before their required first use. It is not cost-effective to complete the

end-to-end verification of the resource transfer lines on the ground. This

DTO will enhance the RTB design evaluation process and supplement the

ground verification program with actual flight experience.

In addition to evaluating the handling qualities of the RTB, this DTO will

demonstrate the installation of the three drag-through lines and verify the

installation procedures, evaluate the RTB's operating characteristics, verify

procedures for disconnecting the lines in an emergency, and evaluate

on-orbit stowage conditions.

The nitrogen and oxygen transfer lines will remain on the space station. The

water line will be returned.

This is the first of at least two planned flights for this DTO.

Updated: 05/11/1999

59
STS-96

DTO/DSO/RMEs 

Single-String Global Positioning System

DTO 700-14

Prime: Daniel Barry

Overview

The purpose of this DTO is to evaluate the performance and operation of

the Global Positioning System as a shuttle navigation aid during the ascent,

on-orbit, entry and landing phases of the mission. A modified military GPS

receiver processor and the orbiter's existing GPS antenna will be used for

this evaluation.

This is the eighth of eight planned flights for DTO 700-14. It was last flown

on STS-88.

Updated: 05/11/1999

60
STS-96

DTO/DSO/RMEs 

Solid-State Star Tracker Size Limitations

DTO 847

Overview

The objective of this DTO is to characterize the performance of the orbiter's

solid-state star tracker with a large and bright target-the International Space

Station. Laboratory tests show that the SSST can track significantly larger

and brighter objects than the orbiter's other star tracker-the

image-dissecting tracker. Since the ISS will reach a size very early in the

assembly sequence that could prohibit IDT operations under certain

conditions, it may be necessary to use the SSST to track the space station

during orbiter passes.

At a minimum, the SSST should be verified to accurately track ISS up to

22.6 arcminutes, which is the largest size tested in the lab and the number

that was used in analyzing potential problems because of the size of the

ISS. If possible, the absolute upper limit in the size of an object that the

SSST can track will be determined. 

This DTO will be performed when the orbiter separates from the ISS but

only if specific lighting conditions exist.

This is the first of three planned flights.

Updated: 05/11/1999

61
STS-96

DTO/DSO/RMEs 

Space Integrated Global Positioning System/Inertial Navigation

System

DTO 700-15

Prime: Kent Rominger

Backup: Rick Husband

Overview

The space integrated Global Positioning System/inertial navigation system

is intended to replace the shuttle's onboard tactical navigation system and,

eventually, its inertial measurement units. The DTO will evaluate the

system's performance in space flight to reduce the technical and schedule

risks associated with applying this new technology to the shuttle navigation

systems.

In addition to demonstrating the new navigation system's performance in a

realistic space vehicle environment during all mission phases, DTO 700-15

will prove the ability of the modified commercial military-grade unit to

accurately perform all required functions in the harsh environment of space

and determine if any changes of the unit are needed to support navigation

in space.

This is the fifth flight of DTO 700-15. It was last flown on STS-88. Fourteen

flights are planned.

Updated: 05/11/1999

62
STS-96

DTO/DSO/RMEs 

Urine Collection Device

DTO 690

Overview

This DTO will evaluate several sizes and types of manual urine collection

devices and their adapters (anatomical interface) in microgravity for fit,

leakage, hygiene (residual urine on adapter), and ease of use. 

An improved UCD would have two primary benefits. Used as a backup for

the orbiter's waste collection system, it would allow a mission to continue if

the WCS failed. Currently, missions must be cut short if the WCS fails.

Second, an improved UCD would allow women to participate in scientific

studies requiring the collection of urine. Female subjects have not been

able to use existing UCDs successfully.

Male astronauts have also experienced problems with the existing UCDs in

the areas of leakage, fit, and urine remaining in the dead volume.

Therefore, a secondary objective of this study will be to design and evaluate

improvements of the male interface.

The final designs will be flown on all missions that require the collection of

urine samples as either the primary method of collection or as a backup to

an automated urine collection system that has been proposed for the space

station.

This is the second of eight planned flights for this DTO. Its first flight was on

STS-91.

Updated: 05/11/1999

63
 

International Space Station 

The International Space Station

 

The International Space Station is the largest and most complex

international scientific project in history. And when it is complete just after

the turn of the century, the the station will represent a move of

unprecedented scale off the home planet. Led by the United States, the

International Space Station draws upon the scientific and technological

resources of 16 nations: Canada, Japan, Russia, 11 nations of the

European Space Agency and Brazil.

More than four times as large as the Russian Mir space station, the

completed International Space Station will have a mass of about 1,040,000

pounds. It will measure 356 feet across and 290 feet long, with almost an

acre of solar panels to provide electrical power to six state-of-the-art

laboratories.

 

64
The station will be in an orbit with an altitude of 250 statute miles with an

inclination of 51.6 degrees. This orbit allows the station to be reached by

the launch vehicles of all the international partners to provide a robust

capability for the delivery of crews and supplies. The orbit also provides

excellent Earth observations with coverage of 85 percent of the globe and

over flight of 95 percent of the population. By the end of this year, about

500,000 pounds of station components will be have been built at factories

around the world.

 

U.S. Role and Contributions

The United States has the responsibility for developing and ultimately

operating major elements and systems aboard the station. The U.S.

elements include three connecting modules, or nodes; a laboratory

module; truss segments; four solar arrays; a habitation module; three

mating adapters; a cupola; an unpressurized logistics carrier and a

centrifuge module. The various systems being developed by the U.S.

include thermal control; life support; guidance, navigation and control; data

handling; power systems; communications and tracking; ground operations

facilities and launch-site processing facilities.

 

International Contributions

The international partners, Canada, Japan, the European Space Agency,

and Russia, will contribute the following key elements to the International

Space Station:

· Canada is providing a 55-foot-long robotic arm to be used for assembly

and maintenance tasks on the Space Station.

· The European Space Agency is building a pressurized laboratory to be

launched on the Space Shuttle and logistics transport vehicles to be

launched on the Ariane 5 launch vehicle.

· Japan is building a laboratory with an attached exposed exterior platform

for experiments as well as logistics transport vehicles.

· Russia is providing two research modules; an early living quarters called

the Service Module with its own life support and habitation systems; a

science power platform of solar arrays that can supply about 20 kilowatts

of electrical power; logistics transport vehicles; and Soyuz spacecraft for

crew return and transfer.

In addition, Brazil and Italy are contributing some equipment to the station

through agreements with the United States.

 

65
ISS Phase One: The Shuttle-Mir Program

The first phase of the International Space Station, the Shuttle-Mir Program,

began in 1995 and involved more than two years of continuous stays by

astronauts aboard the Russian Mir Space Station and nine Shuttle-Mir

docking missions. Knowledge was gained in technology, international

space operations and scientific research.

Seven U.S. astronauts spent a cumulative total of 32 months aboard Mir

with 28 months of continuous occupancy since March 1996. By contrast, it

took the U.S. Space Shuttle fleet more than a dozen years and 60 flights to

achieve an accumulated one year in orbit. Many of the research programs

planned for the International Space Station benefit from longer stay times

in space. The U.S. science program aboard the Mir was a pathfinder for

more ambitious experiments planned for the new station. 

For less than two percent of the total cost of the International Space Station

program, NASA gained knowledge and experience through Shuttle-Mir that

could not be achieved any other way. That included valuable experience in

international crew training activities; the operation of an international space

program; and the challenges of long duration spaceflight for astronauts and

ground controllers. Dealing with the real-time challenges experienced

during Shuttle-Mir missions also has resulted in an unprecedented

cooperation and trust between the U.S. and Russian space programs, and

that cooperation and trust has enhanced the development of the

International Space Station. 

 

66
Research on the International Space Station

The International Space Station will establish an unprecedented

state-of-the-art laboratory complex in orbit, more than four times the size and

with almost 60 times the electrical power for experiments — critical for

research capability — of Russia's Mir. Research in the station's six

laboratories will lead to discoveries in medicine, materials and fundamental

science that will benefit people all over the world. Through its research and

technology, the station also will serve as an indispensable step in preparation

for future human space exploration.

Examples of the types of U.S. research that will be performed aboard the

station include:

· Protein crystal studies: More pure protein crystals may be grown in space

than on Earth. Analysis of these crystals helps scientists better understand

the nature of proteins, enzymes and viruses, perhaps leading to the

development of new drugs and a better understanding of the fundamental

67
building blocks of life. Similar experiments have been conducted on the

Space Shuttle, although they are limited by the short duration of Shuttle

flights. This type of research could lead to the study of possible treatments for

cancer, diabetes, emphysema and immune system disorders, among other

research. 

· Tissue culture: Living cells can be grown in a laboratory environment in

space where they are not distorted by gravity. NASA already has developed a

Bioreactor device that is used on Earth to simulate, for such cultures, the

effect of reduced gravity. Still, these devices are limited by gravity. Growing

cultures for long periods aboard the station will further advance this research.

Such cultures can be used to test new treatments for cancer without risking

harm to patients, among other uses.

· Life in low gravity: The effects of long-term exposure to reduced gravity on

humans – weakening muscles; changes in how the heart, arteries and veins

work; and the loss of bone density, among others – will be studied aboard the

station. Studies of these effects may lead to a better understanding of the

body’s systems and similar ailments on Earth. A thorough understanding of

such effects and possible methods of counteracting them is needed to

prepare for future long-term human exploration of the solar system. In

addition, studies of the gravitational effects on plants, animals and the

function of living cells will be conducted aboard the station. A centrifuge,

located in the Centrifuge Accommodation Module, will use centrifugal force to

generate simulated gravity ranging from almost zero to twice that of Earth.

This facility will imitate Earth’s gravity for comparison purposes; eliminate

variables in experiments; and simulate the gravity on the Moon or Mars for

experiments that can provide information useful for future space travels.

· Flames, fluids and metal in space: Fluids, flames, molten metal and other

materials will be the subject of basic research on the station. Even flames

burn differently without gravity. Reduced gravity reduces convection currents,

the currents that cause warm air or fluid to rise and cool air or fluid to sink on

Earth. This absence of convection alters the flame shape in orbit and allows

studies of the combustion process that are impossible on Earth, a research

field called Combustion Science. The absence of convection allows molten

metals or other materials to be mixed more thoroughly in orbit than on Earth.

Scientists plan to study this field, called Materials Science, to create better

metal alloys and more perfect materials for applications such as computer

chips. The study of all of these areas may lead to developments that can

enhance many industries on Earth. 

· The nature of space: Some experiments aboard the station will take place on

the exterior of the station modules. Such exterior experiments can study the

space environment and how long-term exposure to space, the vacuum and

the debris, affects materials. This research can provide future spacecraft

designers and scientists a better understanding of the nature of space and

enhance spacecraft design. Some experiments will study the basic forces of

nature, a field called Fundamental Physics, where experiments take

advantage of weightlessness to study forces that are weak and difficult to

68
study when subject to gravity on Earth. Experiments in this field may help

explain how the universe developed. Investigations that use lasers to cool

atoms to near absolute zero may help us understand gravity itself. In addition

to investigating basic questions about nature, this research could lead to

down-to-Earth developments that may include clocks a thousand times more

accurate than today’s atomic clocks; better weather forecasting; and stronger

materials.

· Watching the Earth: Observations of the Earth from orbit help the study of

large-scale, long-term changes in the environment. Studies in this field can

increase understanding of the forests, oceans and mountains. The effects of

volcanoes, ancient meteorite impacts, hurricanes and typhoons can be

studied. In addition, changes to the Earth that are caused by the human race

can be observed. The effects of air pollution, such as smog over cities; of

deforestation, the cutting and burning of forests; and of water pollution, such

as oil spills, are visible from space and can be captured in images that

provide a global perspective unavailable from the ground.

· Commercialization: As part of the Commercialization of space research on

the station, industries will participate in research by conducting experiments

and studies aimed at developing new products and services. The results may

benefit those on Earth not only by providing innovative new products as a

result, but also by creating new jobs to make the products.

 

Assembly in Orbit

By the end of this year, most of the components required for the first seven

Space Shuttle missions to assemble the International Space Station will have

arrived at the Kennedy Space Center. The first and primary fully Russian

contribution to the station, the Service Module, is scheduled to be shipped

from Moscow to the Kazakstan launch site in February 1999.

Orbital assembly of the International Space Station will begin a new era of

hands-on work in space, involving more spacewalks than ever before and a

new generation of space robotics. About 850 clock hours of spacewalks, both

U.S. and Russian, will be required over five years to maintain and assemble

the station. The Space Shuttle and two types of Russian launch vehicles will

launch 45 assembly missions. Of these, 36 will be Space Shuttle flights. In

addition, resupply missions and changeouts of Soyuz crew return spacecraft

will be launched regularly.

The first crew to live aboard the International Space Station, commanded by

U.S. astronaut Bill Shepherd and including Russian cosomonauts Yuri

Gidzenko as Soyuz Commander and Sergei Krikalev as Flight Engineer, will

be launched in early 2000 on a Russian Soyuz spacecraft. They, along with

the crews of the first five assembly missions, are now in training. The

timetable and sequence of flights for assembly, beyond the first two, will be

further refined at a meeting of all the international partners in December 1998.

Assembly is planned to be complete by 2004. 

69
 

Updated: 05/13/1999

70
 

ISS Element 

Unity

 

Unity Connecting Module: Cornerstone for a Home in Orbit

 

The first U.S.-built component of the International Space Station, a

six-sided connecting module and passageway, or node, named Unity, was

the primary cargo of Space Shuttle mission STS-88, the first mission

dedicated to assembly of the station.

The Unity connecting module, technically referred to as node 1, created a

foundation for all future U.S. International Space Station modules with six

berthing ports, one on each side, to which future modules will be attached.

Built by The Boeing Company at a manufacturing facility at the Marshall

Space Flight Center in Huntsville, Alabama, Unity is the first of three such

connecting modules that will be built for the station. Sometimes referred to

as Node 1, the Unity module measures 15 feet in diameter and 18 feet

long.

Carried to orbit aboard the Space Shuttle Endeavour, Unity was mated with

the already orbiting Zarya control module, or Functional Cargo Block

(Russian acronym FGB), a U.S.-funded and Russian-built component that

was launched earlier aboard a Russian Proton rocket from Kazakhstan. In

addition to connecting to the Zarya module, Unity eventually will provide

attachment points for the U.S. laboratory module; Node 3; an early exterior

framework, or truss for the station; an airlock; and a multi-windowed

cupola.

Essential space station resources such as fluids, environmental control

and life support systems, electrical and data systems are routed through

Unity to supply work and living areas.

71
More than 50,000 mechanical items, 216 lines to carry fluids and gases,

and 121 internal and external electrical cables using six miles of wire were

installed in the Unity node. The detailed and complex hardware installation

required more than 1,800 drawings. The node is made of aluminum.

Two conical docking adapters will be attached to each end of Unity prior to

its launch aboard Endeavour. The adapters, called pressurized mating

adapters (PMAs), allow the docking systems used by the Space Shuttle

and by Russian modules to attach to the node's hatches and berthing

mechanisms. One of the conical adapters attached Unity to the Zarya,

while the other will serve as a docking port for the Space Shuttle. The Unity

node with the two mating adapters attached, the configuration it was in for

launch, is about 36 feet long and weighs about 25,600 pounds.

Attached to the exterior of one of the pressurized mating adapters are

computers, or multiplexer-demultiplexers (MDMs), which will provide early

command and control of the Unity node. Unity was outfitted with an early

communications system that allows data, voice and low data rate video

with Mission Control, Houston, to supplement Russian communications

systems during the early station assembly activities.

The two remaining nodes are being built by the European Space Agency

(ESA) for NASA in Italy by Alenia Aerospazio. Nodes 2 and 3 will be

slightly longer than the Unity node, measuring almost 21 feet long, and

each will hold eight standard space station equipment racks in addition to

six berthing ports. ESA is building the two additional nodes as partial

payment for the launch of the ESA Columbus laboratory module and other

equipment on the Space Shuttle. Unity holds four equipment racks.

 

Updated: 05/14/1999

72
ISS Element 

Zarya

The Zarya control module, also known by the

technical term Functional Cargo Block and the

Russian acronym FGB, was the first component

launched for the International Space Station and is

providing the station's initial propulsion and power.

The 44,000-pound pressurized module was

launched on a Russian Proton rocket on Nov. 20

1998 from the Baikonur Cosmodrome, Kazakhstan.

Quick Look Facts: Zarya

Length (end-to-end) - 41.2 feet

Width (at widest point) - 13.5 feet

Gross launching weight - 53,020 pounds

Mass in orbit - 44,088 pounds

Launch vehicle - 3-stage Proton rocket

Launch site - Baikonur Cosmodrome, Kazakstan

Lifetime in orbit - 15 years

Inclination of orbit - 51.6 degrees

Preliminary orbit - 115 x 220 statute miles

Orbit at Rendezvous - 240 statute miles circular

73
Zarya Means "Sunrise"

The Zarya, which means Sunrise when translated to English, is actually a

U.S. component of the station that was built by the Khrunichev State

Research and Production Space Center (KhSC), in Moscow, under a

subcontract to The Boeing Co. for NASA. 

Zarya is providing orientation control, communications and electrical power

while attached to Unity for several months before the launch of the third

component, a Russian-provided crew living quarters and early station core

known as the Service Module. The Service Module will enhance or replace

many functions of the Zarya. Later in the station's assembly sequence, the

Zarya module will be used primarily for its storage capacity and external

fuel tanks.

Zarya's solar arrays and six nickel-cadmium batteries can provide an

average of 3 kilowatts of electrical power. Each of the two solar arrays is

35 feet long and 11 feet wide. Using the Russian Kurs system, the Zarya

will perform an automated and remotely piloted rendezvous and docking

with the Service Module in orbit. Its docking ports will accommodate

Russian Soyuz piloted spacecraft and unpiloted Progress resupply

spacecraft. The module has been modified to allow it to be refueled by a

Progress vehicle docked to its down-facing port if necessary. The module's

16 fuel tanks combined can hold more than 6 tons of propellant. The

attitude control system for the module includes 24 large steering jets and

12 small steering jets. Two large engines are available for reboosting the

spacecraft and making major orbital changes.

Updated: 05/14/1999

74
STS-96

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 Shuttle 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 

 

75
 

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.

Updated: 05/13/1999

76
STS-96

Media Contacts 

NASA PAO CONTACTS

, 

June Malone External Tank/SRBs/SSMEs 256/544-0034

Marshall Space Flight Center

Huntsville, AL

June.Malone@msfc.nasa.gov

Bruce Buckingham Launch Processing, KSC

Landing Information

407/867-2468

Kennedy Space Center

, FL

bruce.buckingham-1@ksc.nasa.gov

Eileen Hawley Mission Operations/Astronauts 281/483-5111

Johnson Space

Houston, TX

eileen.hawley1@jsc.nasa.gov

Dwayne Brown, Policy/Management 202/358-1726

NASA Headquarters,

Washington, DC

dwayne.brown@hq.nasa.gov

Kyle Herring Space Station Operations 281/483-5111

Johnson Space Center

Houston, TX

kyle.j.herring1@jsc.nasa.gov

Updated: 05/11/1999

77
Table prepared by Richard W. Orloff, 02/2001 

SHUTTLE FLIGHTS AS OF MAY 1999 

93 TOTAL FLIGHTS OF THE SHUTTLE SYSTEM -- 68 SINCE RETURN TO FLIGHT 

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-80 

11/19/96 - 12/07/96 

STS-70 

07/13/95 - 07/22/95 

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-55 

04/26/93 - 05/06/93 

STS-42 

01/22/92 - 01/30/92 

STS-71 

06/27/95 - 07/07/95 

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 

(25 flights) 

OV-099 

Challenger 

(10 flights) 

OV-103 

Discovery 

(25 flights) 

OV-104 

Atlantis 

(20 flights) 

OV-105 

Endeavour 

(13 flights)