Thermal Design of the ORBCOMM Constellation Spacecraft

961491

07/01/1996

Event
International Conference On Environmental Systems
Authors Abstract
Content
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.
Meta TagsDetails
DOI
https://doi.org/10.4271/961491
Pages
11
Citation
DeMauro, F., and Ducas, W., "Thermal Design of the ORBCOMM Constellation Spacecraft," SAE Technical Paper 961491, 1996, https://doi.org/10.4271/961491.
Additional Details
Publisher
Published
Jul 1, 1996
Product Code
961491
Content Type
Technical Paper
Language
English