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=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_16.TXT
STS-51 RADIATION MONITORING EQUIPMENT-III (RME-III)
The Radiation Monitoring Equipment-III (RME-III) measures
ionizing radiation exposure to the crew within the orbiter cabin.
RME-III measures gamma ray, electron, neutron and proton radiation
and calculates in real time exposure in RADS-tissue equivalent. The
information is stored in a memory module for post-flight analysis.
The hand-held instrument is stored in a middeck locker during
flight except for when the crew activates it and replaces the memory
module every two days. RME-III will be activated by the crew as soon
as possible after they achieve orbit and it will operate throughout
the mission. A crew member will enter the correct mission elapsed
time upon activation. ME-III is sponsored by the Department of
Defense in cooperation with NASA.
AIR FORCE OPTICAL SITE (AMOS)
This geophysical environmental study will test ground based
optical sensors. The experiment will also examine
contamination/exhaust plume phenomena using the Space Shuttle as a
calibration target.
AURORA PHOTOGRAPHY EXPERIMENT-B (APE-B)
The mission objectives of the Aurora Photography Experiment-B
(APE-B) are to photograph the airglow aurora, auroral optical
effects, the Shuttle glow phenomenon and thruster emissions in the
imaging mode of photography as well as in the Fabry-Perot and
spectrometer modes of photography.
COMMERCIAL PROTEIN CRYSTAL GROWTH (CPCG)
The Commercial Protein Crystal Growth (CPCG) payload is designed
to conduct experiments which supply information on the scientific
methods and commercial potential for growing large high-quality
protein crystals in microgravity. The CPCG payload consists of
Commercial Refrigerator/Incubator Modules (CR/IM's) and their
contents.
There are two possible configurations for this experiment, Block
I and Block II. This experiment is configured in Block II
configuration for the STS-51 mission, in which the CR/IM contents
consist of four cylinder containers of the same diameter but
different volumes. The four cylinders are 500 mm, 200 mm, 100 mm and
20 mm. Depending on the specific protein being flown, the
temperature is either lowered or raised in up to a five-step process
over Flight Day 1 and 2.
One CR/IM occupies the space of one middeck stowage locker.
Orbiter 28V dc power is provided to the CPCG CR/IM via single power
cables from a standard middeck outlet. The CPCG experiment is
installed at the pad within launch minus 24 hours.
HIGH RESOLUTION SHUTTLE GLOW SPECTROSCOPY
(HRSGS-A)
The High Resolution Shuttle Glow Spectroscopy-A (HRSGS-A) is an
experimental payload designed to obtain high resolution spectra in
the visible and near visible wavelength range (4000 angstroms to 8000
angstroms) of the Shuttle surface glow as observed on the orbiter
surfaces which face the velocity vector while in low Earth-orbit.
The spectral resolution of the spectrograph is 2 angstroms and it is
hoped this will help identify the cause of the Shuttle glow. The
HRSGS-A will look at the vertical tail, Orbital Maneuvering System
Pod or a suitable alternative.
IMAX
The IMAX payload is a 70mm motion picture camera system for
filming general orbiter scenes. The system consists of a camera,
lenses, rolls of film, two magazines with film, an emergency speed
control, a Sony recorder and associated equipment, two photographic
lights, supporting hardware in the form of mounting brackets to
accommodate the mode of use, two cables and various supplemental
equipment.
The IMAX and supporting equipment are stowed in the middeck for
in-cabin use. The IMAX uses two film magazines which can be
interchanged as part of the operation. Each magazine runs for
approximately 3 minutes. When both magazines are consumed, reloading
of the magazines from the stowed supply of film is required. Lenses
are interchanged based on scene requirements. The IMAX will be
installed in the orbiter middeck approximately 7 days prior to
launch.
INVESTIGATION INTO POLYMER MEMBRANES PROCESSING (IPMP)
The research objectives of the IPMP is to flash evaporate mixed
solvent systems in the absence of convection to control the porosity
of a polymer membrane. Two experimental units will be flown. Each
unit will consist of two 304L stainless steel sample cylinders
connected to each other by a stainless steel packless valve with an
aluminum cap. Before launch, the two larger canisters are evacuated
and sealed with threaded stainless steel plugs using a Teflon( tape
threading compound.
In the smaller units, a thin film polymer membrane is swollen in
a solvent compound. The film is rolled up and inserted into the
canisters. The small canisters are sealed at ambient pressure
(approximately 14.7 psia). The valves are secured with Teflon(
tape.
The locker containing the IPMP payload will be installed in the
orbiter during the period from L-6 to L-3 days.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=