Techniques for minimizing diurnal temperature variation of a radiator of a spacecraft are disclosed. In one aspect, a spacecraft includes a body, a radiator panel, and a heat dissipating unit thermally coupled with the radiator panel. The spacecraft is configured to operate in an orbital plane, and has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane, and a roll axis orthogonal to the pitch axis and the yaw axis. The radiator panel includes a surface area external to a body of the spacecraft, a first portion of the surface area facing a first direction that is substantially parallel to the roll axis, and a second portion of the surface area facing a second direction that has a substantial component parallel to the yaw axis.
Method of operating a spacecraft radiator panel
2023-11-07
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
SPACECRAFT AND RADIATOR PANEL FOR SPACECRAFT WITH COMPOSITE FACE-SHEET
European Patent Office | 2016
|Engineering Index Backfile | 1968
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