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Thermal Control Subsystem Design for the Avionics of a Space Station PayloadA case study of the thermal control subsystem development for a space based payload is presented from the concept stage through preliminary design. This payload, the Space Acceleration Measurement System 2 (SAMS-2), will measure the acceleration environment at select locations within the International Space Station. Its thermal control subsystem must maintain component temperatures within an acceptable range over a 10 year life span, while restricting accessible surfaces to touch temperature limits and insuring fail safe conditions in the event of loss of cooling. In addition to these primary design objectives, system level requirements and constraints are imposed on the payload, many of which are driven by multidisciplinary issues. Blending these issues into the overall system design required concurrent design sessions with the project team, iterative conceptual design layouts, thermal analysis and modeling, and hardware testing. Multiple tradeoff studies were also performed to investigate the many options which surfaced during the development cycle.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Moran, Matthew E.
(NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1996
Subject Category
Electronics And Electrical Engineering
Report/Patent Number
NAS 1.15:107334
Meeting Information
Meeting: International Mechanical Engineering Congress and Exposition
Location: Atlanta, GA
Country: United States
Start Date: November 17, 1996
End Date: November 22, 1996
Sponsors: American Society of Mechanical Engineers
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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