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.
The thermal control challenge of the Mars observer spacecraft
1987-06-01
Conference paper
No indication
English
The thermal control challenge of the mars observer spacecraft
Tema Archive | 1987
|NTRS | 1989
|AIAA | 1989
|Mars Observer spacecraft description
NTRS | 1991
|