US 6,883,588 B1 · Spacecraft radiator system using a heat pump

Abstract

Heat dissipating apparatus or system for dissipating heat generated by a payload on a spacecraft having a plurality of surfaces. The system includes at least one radiator-condenser coupled to one or more of the surfaces of the spacecraft and a heat pump including an evaporator, a compressor, and an expansion valve coupled in a closed-loop manner to the radiator-condenser. The system components are coupled together using small diameter, thin- and smooth-walled tubing. The system enables the radiator-condenser to be elevated above the source or payload temperature, and, along with the use of thin walled tubing, reduces the mass of the spacecraft. Because the radiator-condenser temperatures are elevated, multiple surfaces of the spacecraft (west, east, earth and aft) can be effectively used as radiating surfaces.

Claims11

Dependent claims

In a spacecraft having a plurality of surfaces, including at least one radiating surface and at least one solar loaded surface, a heat dissipating system for dissipating heat from a spacecraft payload comprising:

an evaporator which receives a fluid medium heated by said payload, and evaporates said medium producing an evaporated fluid medium at a first operating temperature,
a compressor which receives the evaporated fluid medium and compresses the evaporated fluid medium raising the temperature of the evaporated fluid medium to a second operating temperature which is greater than the temperature of the at least one solar loaded surface;
and
a radiator-condenser which receives the compressed fluid medium from the compressor and radiates the heat from the spacecraft through said radiator-condenser and said at least one solar loaded surface.

1 more element

Dependencies are inferred from the claim text.

Spacecraft radiator system using a heat pump

Life of this patent

Spacecraft radiator system using a heat pump

Life of this patent

Abstract

Claims11