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Thermal Design of the ORBCOMM Constellation Spacecraft
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English
Abstract
The thermal design strategy is discussed as it relates to the production of up to 34 identical small satellites in a relatively short period of time. Tight production and launch schedules and the need to design for low mass, risk, and cost presented a design challenge for all disciplines. A specific arrangement of passive thermal control features, including ITO-coated AgTef covered structure radiators, MLI, and software controlled heaters established a robust design. Thermal modeling of the bus and unique antenna are presented including a comparison between the predicted and required component temperature ranges. Also described are the primary mission objective, the spacecraft configuration, requirements and design drivers, mission environments, and design parameters.
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Citation
DeMauro, F. and Ducas, W., "Thermal Design of the ORBCOMM Constellation Spacecraft," SAE Technical Paper 961491, 1996, https://doi.org/10.4271/961491.Also In
References
- ORBCOMM Satellite Specification 12 September 1995
- Thermal Radiation Analysis System II User's Manual National Aeronautics and Space Administration Lyndon B. Johnson Spacecraft Center under contract NAS9-15832 October 1986
- SINDA/FLUINT User's Manual, Version 2.4 National Aeronautics and Space Administration (NASA) Lyndon B. Johnson Space Center (JSC) 1991