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Thermal design of the Galileo spun and despun scienceThe delay in the launching of the Galileo spacecraft, which was to be launched aboard the Space Shuttle Atlantis, caused by the Challenger accident resulted in a decrease in the Radioisotope Thermoelectric Generator (RTG) power. A change to the Inertial Upper Stage from the more powerful Centaur G-Prime resulted in a trajectory that requires gravity assists, once by Venus and twice by earth. The resulting peak solar intensity of this roundabout trajectory is more than twice the previous design value for the direct trajectory. The resulting changes in solar intensity range and the RTG power output were substantial and forced major thermal design changes. This paper discusses the thermal design and redesign of the Galileo Spun and Despun sciences. Data are presented on the allowable temperatures for the Spun and Despun sciences, the energy balance calculated for the Despun science, and the Despun science test results.
Document ID
19890055892
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Greenfield, M.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Reeve, R.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Stultz, J.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Wu, P.
(California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 89-1750
Accession Number
89A43263
Distribution Limits
Public
Copyright
Other

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