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FIR Rack from rear |
The Fluids Integrated Rack (FIR) features a large user-configurable
volume for experiments. The volume resembles a laboratory optics
bench. An experiment can be built up on the bench from components,
or it can be attached as a self-contained package, or a combination.
The FIR provides data acquisition and control, sensor interfaces,
laser and white light sources, advanced imaging capabilities, power,
cooling, and other resources. Astronauts can quickly mount equipment
with final positioning by remote control from the FCF Telescience
Support or from the Principal Investigator (PI) home institution.
FIR is designed to be adaptable to nearly any kind of fluids experiment.
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FIR Rack with front doors open |
The
FIR contains the hardware and software necessary for conducting
fluid physics science experiments. It is designed
to accommodate a broad range of fluids experiments while meeting
the ISS requirements and limitations related to safety, power and
energy, cooling, mass, crew time, stowage, re-supply flights, and
downlink. The FIR will utilize six major subsystems to accommodate
experiments.
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FIR Team |
The International Standard Payload Rack (ISPR)
provides the supporting and mounting elements for the FIR subsystems
and mechanical connections to the Destiny Module. The Active Rack
Isolation System (ARIS) enhances the microgravity environment for experiments
in the FIR by attenuating on-orbit vibrations transmitted from the Destiny
Module to the ISPR. The centerpiece of the FIR structural sub-system
is the optics bench. The optics bench provides a mounting surface for
FIR light sources and avionics packages on the back of the bench and
for payload hardware on the front of the bench. Depending on the use
of the FIR diagnostics, the optics bench will be able to accommodate
up to 250 kg of payload hardware. The environmental subsystem
will utilize air and water to remove heat generated by the FIR and payload
hardware. Heat rejection by payload hardware to the air on the
front of the bench is nominally limited to 500 W. The Electrical
Power Control Unit (EPCU) is the heart of the electrical subsystem.
All power from ISS will flow through the EPCU. The EPCU will provide
power management and control functions, as well as fault protection. Payload
hardware will have access to 120 VDC (up to 1400 W) and 28 VDC (up to
672 W) of power from the EPCU. The FIR will provide payloads with
access to the ISS gaseous nitrogen and vacuum systems through the gas
interface subsystem, (Gas Interface Panel). These systems are
available to support experiment operations such as the purging of experimental
test cells and pressurizing or creating flows within experimental test
cells. The FIR Command and Data Management Subsystem (CDMS) provides
command and data handling for both facility and payload hardware. The
main components of the FIR CDMS are the Input Output Processor, the
Image Processing and Storage Unit, the Fluids Science Avionics Package,
and the Mass Data Storage Unit. In addition, the CMDS can support real-time
image analysis as well as post-processing data capabilities. The
FIR cameras will offer color and black and white imaging. |
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FIR Environment |
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FIR Integration |
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FIR Optics |
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