Thermal design and analysis of the Spartan Lite spacecraft

Details Thermal design and analysis of the Spartan Lite spacecraft Thermal design and analysis of the Spartan Lite spacecraft

Jan 1998

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1998aipc..420..488t&link_type=abstract

Space technology and applications international forum - 1998. AIP Conference Proceedings, Volume 420, pp. 488-494 (1998).

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Applications

Spaceborne And Space Research Instruments, Apparatus, And Components, Thermal Analysis, Differential Thermal Analysis, Differential Thermogravimetric Analysis

Scientific paper

The Spartan Lite spacecraft is an expendable instrument carrier bus with a generic design capable of accommodating 50 kg. class science instruments. The spacecraft is stowed prior to operations in the Space Shuttle cargo bay in an extended ``Hitchhiker'' canister. The Orbiter carries the spacecraft into space and ejects it into a free flying, low earth orbit. The spacecraft then assumes either a stellar or solar inertial attitude for a 3 to 12 month science observing mission. The Spartan Lite thermal design is passive, with the exception of a payload powered heater bus. Challenges in the thermal design included working with limited heater power, a wide range of possible on-orbit environments, and a requirement to provide thermal boundary conditions that accommodate a variety of science instruments. This paper will present the thermal design and analysis up to the Critical Design Review status for the Spartan Lite spacecraft. A description of analytical tools used, results from analysis, and thermal design implementation will be included.

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