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The thermal control challenge of the Mars observer spacecraft
- Publication Year :
- 1987
- Publisher :
- United States: NASA Center for Aerospace Information (CASI), 1987.
-
Abstract
- The thermal control subsystem for the Mars Observer spacecraft has been synthesized from hardware currently in use on earth-orbiting satellites. Heat input to the spacecraft from environmental and internal sources varies widely throughout the mission, and system requirements, such as accommodation of payload instrument fields-of-view and minimization of weight and power, limit the sizes and locations of thermal control elements. Subsystem components are primarily passive, although heaters and louvers provide augmented control where required. Spacecraft-level finite difference thermal models have shown that all component temperature requirements are met with margin.
- Subjects :
- Spacecraft Design, Testing And Performance
Subjects
Details
- Language :
- English
- Database :
- NASA Technical Reports
- Publication Type :
- Report
- Accession number :
- edsnas.19870055755
- Document Type :
- Report