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EA7AFE > NASA 27.11.98 13:35l 349 Lines 14093 Bytes #-9795 (0) @ WW
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STS-88
Mission Synopsis
LAUNCH DATE: Dec. 3, 1998
LAUNCH SITE:KSC/Pad 39B
LAUNCH WINDOW: 10 minutes
LANDING DATE: Dec. 15, 1998
NOMINAL LANDING SITE:KSC
ABORT LANDING SITES:Return to Launch Site -- KSC
Transoceanic Abort Landing -- ZZA
Alternates – BEN, MRN
Abort Once Around – KSC
Alternate -- KSC
ORBITER: OV-105 (Endeavour)
ALTITUDE: 170 nm
210 nm (rendezvous altitude)
INCLINATION:51.6 degrees
DURATION: 12+2 days (two additional days are provided for
contingency ops and weather avoidance)
CREW: Robert Cabana, Commander
Frederick Sturckow, Pilot
Jerry Ross, Mission Specialist, EV1
Nancy Currie, Mission Specialist
Jim Newman, Mission Specialist, EV2
Sergei Krikalev, Mission Specialist
CARGO BAY PAYLOADS: ISS-01-2A
MIGHTY SAT
ICBC (IMAX Cargo Bay Camera)
SAC-A (Satelite de Aplicaciones/Cientifico-A)
SIMPLEX
SEM (Space Experiment Module)
GAS-093 (Getaway Special)
HIGHLIGHTS: First shuttle mission in the assembly of the
International Space Station. Launch of the 2A cargo element,
which
is the Node 1 and PMA's 1 and 2, rendezvous with the Russian
Functional Cargo Block (FGB), mate the FGB with the 2A cargo
element, and perform assembly tasks necessary. Two crewmembers
will
perform three spacewalks to connect umbilicals and attach
tools for
future EVAs.
SYNOPSIS OF FLIGHT
The primary objective of this flight is to deliver and
assemble the
2A Launch Package (LP) to the Orbiting International Space
Station
(ISS) Stage 1 which consists of the FGB (Functional Cargo
Block).
Prior to rendezvous, the Cargo Element (CE), which consists of
Node
1 with Pressurized Mating Adapter-1 (PMA-1) and PMA-2
pre-integrated
on the Node 1 axial ports, will be installed on the Orbiter
Docking
System using the Shuttle Remote Manipulator System (SRMS).
After
final approach to Stage 1, the SRMS will be used to capture
Stage 1
and berth it to the PMA-1 Androgynous Peripheral Docking
System
(APDS). Prior to undocking, three scheduled Extravehicular
Activities (EVA's) will be performed to connect three sets of
umbilicals and to install EVA tools/hardware. The secondary
objectives of this flight are to perform IMAX Cargo Bay Camera
(ICBC) operations, perform AMTEC/AWCS operations, to deploy
Mighty
Sat 1 and to deploy SAC-A.
2A Launch Package
The 2A Launch Package (LP) consists of the Unity connecting
module
(Node 1). Also, two Articulating Portable Foot Restraints
(APFR) and
a Portable Foot Restraint (PFR) workstation stanchion attached
with
latches to a mounting plate on a Small Payloads Accommodations
(SPA)
Get-Away Special (GAS) beam mounted on the Orbiter's starboard
side,
two APFR's and a PFR workstation stanchion attached with
latches to
a mounting plate on a Goddard Space Flight Center
(GSFC)-provided
GAS beam mounted on the Orbiter's portside and items stowed in
the
middeck lockers, external airlock and stowage bags are
manifested
for support of the International Space Station Program. The CE
return compliment consists of the two Assembly Power Converter
Units
(APCU) and CE attach/mounting hardware.
Two Androgynous Peripheral Docking Systems (APDS) mechanisms
are
attached to the CE. One active mechanism is located on PMA-1
and
provides the berthing interface to the Stage 1 passive APDS
mechanism. One passive APDS mechanism is located on PMA-2 and
will
provide the initial berthing interface to the Orbiter Docking
System
(ODS) APDS mechanism.
Crew compartment items, consisting of two Portable Computer
Systems
(PCS), 2A Extravehicular Activity (EVA) tools/equipment, 3A
and 5A
EVA tools, early communications hardware, and Node 1 ingress
equipment will be stowed in middeck lockers, the external
airlock
and stowage bags.
Prior to rendezvous, the crew will unberth the CE from the
payload
bay latches and berth it to the ODS APDS interface using the
Shuttle
Remote Manipulator System (SRMS). The crew will activate the
active
APDS capture latches on the ODS from the Aft Flight Deck
(AFD).
After rendezvous of the Orbiter and the final approach with
Stage 1,
the crew will use the SRMS to capture the Stage 1 and berth it
to
the PMA-1 APDS interface. The crew will activate the PMA-1
APDS
active capture latches from the AFD.
The crew will perform three EVA's. EVA tasks will include
connection
of the three sets of umbilicals and installation of the
trunnion pin
covers, addition of the zenith Multiplexer/Demultiplexer (MDM)
sunshade, handrails, and sockets, tools and connection of APCU
jumper cables. Between EVA's, the crew will activate the Node
1 MDM
and PMA-1 and Node 1 heaters.
During the docked phase, the crew will ingress PMA 2 to
perform
ODS-to-PMA 2 duct connections. The crew will then perform Node
1
ingress, take air samples, set up portable fans for module air
circulation, portable lighting, prepare Node 1 for dryout,
activate
the early communications equipment and transfer equipment from
the
Orbiter stowage to Node 1. The crew will perform Node 1 dryout
each
time Node 1 reentry after hatch closure is performed.
Following completion of the assembly operations, the crew will
undock the Orbiter from the Stage 2, deorbit, and return to
the
landing site.
MightySat 1
The MightySat 1 payload consists of four separate experiments:
the
MightySat 1, AMTEC (Alkali Metal Thermal-to-Electric
Converter),
AWCS (Automated Wafer Cartridge System), and SAC-A (Satelite
de
Aplicaciones/Cientifico-A).
MightySat 1 is a United States Air Force (USAF) Philips
Laboratory/Space Experiments Directorate ejectable technology
demonstration platform. Four advanced technologies will be
demonstrated on MightySat 1. These technologies include a
composite
structure, advanced solar cells, advanced electronics, and a
shock
device.
The experiment consists of the MightySat 1 satellite,
integrated
with the Hitchhiker Ejection System (HES), then mounted inside
a
lidless carrier. MightySat 1 remains in a dormant state until
following ejection from orbiter cargo bay. MightySat 1 is
spring
ejected at a minimum rate of 1.7 fps and desires an overflight
of a
specific location in Albuquerque, NM within 6 hours of deploy.
SAC-A
SAC-A is a small nonrecoverable satellite built by the
Argentinean
National Commission of Space Activities (CONAE). The satellite
will
test and characterize the performance of new equipment and
technologies which may be used in future operational or
scientific
missions. The satellite payload includes a Differential Global
Positioning System (DGPS), a Charge Coupled Device (CCD)
camera,
Argentinean built silicon solar cells, and a magnetometer.
The SAC-A payload consists of the SAC-A installed in an HH
canister
equipped with an HH ejection system and an HH Motorized Door
Assembly (HMDA). SAC-A is mounted in the forward position on
an
adapter beam which is attached to the side wall of the Orbiter
in
the Bay 2 port location.
The satellite power will not be applied until the flightcrew
opens
the HMDA. As the HMDA opens, a switch on top of the satellite
will
engage, and power from the satellite batteries will be applied
to a
single momentum wheel. The satellite may be ejected after a
minimum
of 3 minutes to provide time for the momentum wheel to reach
its
operating speed. At a predetermined time after ejection,
another set
of switches will engage and the batteries will provide power
to the
remaining SAC-A systems.
ICBC
The IMAX Cargo Bay Camera (ICBC) payload is a 65mm color
motion
picture camera system. The system consists of a camera, a lens
assembly, and a film magazine containing approximately 3500 ft
of
film. The camera system is housed in an insulated pressurized
enclosure with a movable lens window cover, and is mounted in
the
cargo bay on a Get Away Special (GAS) beam or Extended
Adaptive
Payload Carrier (EAPC). The camera system is operated from the
Aft
Flight Deck (AFD) with the GAS Autonomous Payload Controller
(GAPC).
SEM
The SEM program is an educational initiative to increase
student
access to space. Kindergarten through University students are
represented. The SEM-07 utilizes a standard 5 cubic-foot GAS
canister with a Goddard Space Flight Center (GSFC)-provided
internal
support structure, battery, power distribution system, data
sampling
and storage devices, and harness. It will be mounted on an
SSP/JSC-provided adaptor beam in Bay 13, port side, forward
position. SEM-07 will be PASSIVE. There will be no batteries
or
power supplied by the Orbiter.
GAS-093
The GAS payload G-093 is sponsored by the University of
Michigan.
The objective of this experiment is to investigate the
propagation
of a vortex ring through a liquid-gas interface in
microgravity.
During ascent, a barometric altitude switch will activate the
G-093
payload power and Thermal Control System (TCS). Early in the
mission
the crew will unstow and set up the Payload and General
Support
Computer/Bus Interface Adapter (PGSC/BIA) in the Aft Flight
Deck
(AFD). The crew will then initiate the experiment, just prior
to a
low-g period (1.0 X 10-4) lasting 8 hours. It is desired that
no
Orbital Maneuvering Subsystem (OMS) firings occur during this
time.
The experiment is controlled by an internal sequencer, which
will
allow the experiment to operate for 8 hours. A minimum of 8
hours
after experiment activation, the crew will deactivate the
experiment, and remove experiment power.
Extravehicular Activities
Three scheduled Extravehicular Activities (EVA) will be
conducted by
Mission Specialists Jerry Ross (EV1) and Jim Newman (EV2):
EVA 1 - During the first EVA, scheduled for Flight Day 5, Ross
and
Newman will make all umbilical connections necessary to
activate
Node 1. Upon completion of the first EVA the ground will send
commands to the Node to confirm power and activation.
EVA 2 - Tasks to be completed during the second EVA, scheduled
for
Flight Day 7, include installation of EVA translation aids and
tools
(handrails and foot restraint sockets), installation of the
early
communications (ECOMM) system antennas, and routing of the
comm
cable from the FGB to the starboard antenna.
EVA 3 - On Flight Day 9, the third scheduled EVA will be
performed
to support objectives of downstream assembly missions. Tasks
include
installation of a large tool bag for storing EVA tools outside
the
station and repositioning of foot restraints. Additionally,
the two
crewmembers will disconnect the umbilical on PMA-2 so that
PMA-2 can
be relocated in the future.
Ingress of the Node 1 and FGB to install ECOMM system
equipment and
transfer stowage items is planned to be performed between the
second
and third EVA's, on Flight Day 8. Following the completion of
the
three EVA's and Node 1 and FGB ingress activities, the orbiter
will
undock from the ISS.
Curator: Kim Dismukes
Responsible NASA Official: Radislav Sinyak
Updated: 23 November 1998
Mensaje enviado a las 10:32 horas EA - 25 Nov 1998
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