Spacecraft radiator system using a heat pump
View Patent ↗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.
1. 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.
2. The system as defined in claim 1 further comprising:
an expansion valve which receives the fluid medium from the radiator-condenser and returns the fluid medium to the evaporator.
3. The system recited in claim 1 wherein selected ones of said at least one solar loaded surface receives heat out from said radiator-condenser through tubing.
4. The system recited in claim 1 wherein the evaporator, compressor, expansion valve and radiator-condenser are interconnected by way of smooth walled tubing.
5. The system recited in claim 1 wherein the compressor is coupled to a spacecraft power source.
6. The system recited in claim 5 wherein the spacecraft power source comprises a solar array.
7. The system recited in claim 1 wherein the fluid medium comprises ammonia.
8. The system recited in claim 1 wherein the compressor comprises means for elevating the temperature of the fluid medium above the temperature of fluid medium in the evaporator.
9. The system recited in claim 1 wherein selected ones of the at least one solar loaded surface receives heat transmitted from said radiator-condenser through tubing embedded in said at least one solar loaded surface.
10. The system recited in claim 1 wherein tubing is mounted to selected ones of said at least one solar loaded surface.
11. The system recited in claim 1 wherein the plurality of surfaces of the spacecraft comprise a north face, a south face, an east face, a west face, an earth-facing surface and a surface facing away from the earth, and wherein the spacecraft comprises at least one deployable radiating surface.