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Proceedings Paper

Space Interferometry Mission (SIM) thermal design
Author(s): Kim M. Aaron; Ab Hashemi; Peter A. Morris; Jeff Nienberg
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Paper Abstract

The Space Interferometry Mission (SIM) has some very tight stability requirements that drive the thermal control approach well beyond the traditional spacecraft thermal control regime. The precision support structure will be constructed of composite materials with a quite low coefficient of thermal expansion (CTE) on the order of 10-7/K. Even then, the temperature variations of the structure cannot exceed about 0.2°C. For the main optical elements, which will be fabricated of ultra-low expansion glass, the temperature stability must be such that the temperature gradient through the glass cannot vary by more than a couple of millikelvin through the 5 cm thickness over a one hour period. The laser metrology system, which measures motions on the order of a few tens of picometers, contains some sensitive optical elements whose temperature variations cannot exceed a few tens of microkelvin. This paper will describe how the SIM thermal control designers have addressed some of these very challenging requirements.

Paper Details

Date Published: 26 February 2003
PDF: 10 pages
Proc. SPIE 4852, Interferometry in Space, (26 February 2003); doi: 10.1117/12.460870
Show Author Affiliations
Kim M. Aaron, Jet Propulsion Lab. (United States)
Ab Hashemi, Lockheed Martin Corp. (United States)
Peter A. Morris, TRW, Inc. (United States)
Jeff Nienberg, TRW, Inc. (United States)

Published in SPIE Proceedings Vol. 4852:
Interferometry in Space
Michael Shao, Editor(s)

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