Two-sided deployable thermal radiator system and method
View Patent ↗A spacecraft heat dissipation method, and a spacecraft having an improved thermal radiator system that uses two-sided deployable thermal radiators that dissipates heat from both front and back surfaces thereof. The use of the two-sided deployable thermal radiators enables the thermal radiator system to have approximately 50% more heat dissipating capability than a system with just one surface exposed to dissipate heat. The spacecraft includes a body, one or more solar arrays, and the present radiator system which comprises opposite facing fixed payload radiators that are thermally coupled to selected ones of the deployable radiators by way of heat pipes. In an exemplary method a spacecraft is configured to have a body, one or more solar arrays opposite facing fixed payload radiators, and one or more two-sided deployable radiators selectively coupled to the fixed payload radiators. The spacecraft is launched into orbit. When in orbit, heat coupled to the opposite facing fixed payload radiators is transferred to the two-sided deployable radiators for radiation into space from both sides thereof.
1. A spacecraft radiator system for use on a spacecraft having a body and one or more solar arrays, the system comprising:
first and second opposite facing payload radiators;
one or more deployable radiators that radiate heat from both sides thereof; and
heat pipes that thermally couple each payload radiator to the one or more deployable radiators disposed on a side of the spacecraft that is opposite to the respective payload radiator.
2. A spacecraft comprising:
a body;
one or more solar arrays; and
a spacecraft radiator system comprising:
first and second opposite facing payload radiators;
one or more deployable radiators that radiate heat from both sides thereof; and
heat pipes that thermally couple the respective payload radiators to the one or more deployable radiators disposed on a side of the spacecraft that is opposite to the respective payload radiator.
3. A spacecraft heat dissipation method comprising the steps of:
configuring a spacecraft to have a body, one or more solar arrays, first and second opposite facing fixed payload radiators, one or more deployable radiators that radiate heat from both sides thereof, and heat pipes that thermally couple the respective payload radiators to the one or more deployable radiators disposed on a side of the spacecraft that is opposite to the respective payload radiator;
launching the spacecraft into orbit; and
when in orbit, transferring heat coupled to the opposite facing fixed payload radiators to the deployable radiators disposed on the opposite side of the spacecraft for radiation into space from both sides to the deployable radiators.