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US 5,372,183 AGranted
Thermal control arrangements for a geosynchronous spacecraft
OwnerHarold P. Strickbergerinventor
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OwnerHarold P. Strickbergerinventor
Estimating the term…
A spacecraft adapted for operation in a low inclination angle earth orbit comprises north, south, east and west panels defining a spacecraft interior volume. The north and south panels are oppositely disposed with respect to each other and the east and west panels are oppositely disposed with respect to each other. The spacecraft interior volume generally and preferably lacks structural elements that substantially restrict thermal radiation among the panels. The north and south panels, to which spacecraft equipment is usually mounted, each include conductive heat pipes for reducing the temperature differences across each panel. The exterior surfaces of the north, south, east and west panels have a covering, preferably of optical solar reflectors (OSRs), for radiating thermal energy therefrom, wherein the OSRs have a solar absorptivity that is substantially less than their thermal emissivity. The interior surfaces of the north, south, east and west panels have a covering for effectively radiating thermal energy between and among the panels across the interior volume.
A thermal control arrangement for a spacecraft adapted for orbiting a body illuminated by a sun, said spacecraft comprising a plurality of external panels at least first and second of which are oppositely disposed on said spacecraft in locations not subject to substantial illumination by said sun, and at least third and fourth of said panels are oppositely disposed on said spacecraft and receive illumination from said sun in different portions of the orbiting of said spacecraft about said body, at least one of said first and second external panels including means for conducting heat therethrough in a manner for reducing temperature differences over substantially the entire area of said panel, said first and second panels each having external surfaces having a solar absorptivity substantially lower than its thermal emissivity, said third and fourth panels each having external surfaces having a solar absorptivity substantially lower than its thermal emissivity, and wherein said first, second, third and fourth panels have surfaces internal to said spacecraft adapted to radiate thermal energy therebetween.
A thermal control arrangement for a spacecraft adapted for orbiting a body illuminated by a sun, said spacecraft comprising a plurality of external panels at least first and second of which are oppositely disposed on said spacecraft in locations not subject to substantial illumination by said sun, and at least third and fourth of said panels are oppositely disposed on said spacecraft and receive illumination from said sun in different portions of the orbiting of said spacecraft about said body, said first and second panels each having external surfaces having a solar absorptivity substantially lower than its thermal emissivity, said third and fourth panels each having external surfaces having a solar absorptivity substantially lower than its thermal emissivity, and wherein said first, second, third and fourth panels have surfaces internal to said spacecraft adapted to radiate thermal energy therebetween without interference from substantial intervening structural elements of said spacecraft.
A spacecraft adapted for operation in a low inclination angle earth orbit comprising:
Dependencies are inferred from the claim text.