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.
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.
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. |
Project Management: Contacts at NASA Glenn Research Center |
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