초록 ▼

The present invention provides a thermal, and if desired, a radiation barrier to protect the exterior surface of a spacecraft. In particular, the present invention protects the polymeric materials of construction utilized in inflatable and expandable spacecraft from the deleterious effects of both t

The present invention provides a thermal, and if desired, a radiation barrier to protect the exterior surface of a spacecraft. In particular, the present invention protects the polymeric materials of construction utilized in inflatable and expandable spacecraft from the deleterious effects of both thermal and radiation aging. The protective barrier is formed from a tube or tubes through which a fluid circulates. The tube segment substantially enclose the spacecraft, and in particular, the critical layers that are desired to be protected. This protective barrier provides a thermal heat sink, temperature equalization, and a waste heat rejection system, that can moderate the temperature extremes encountered by spacecraft. In addition, dependent on the fluid selected, substantial radiation shielding can be provided that can protect the entire spacecraft.

대표청구항 ▼

1. Apparatus for spacecraft thermal management comprising:a. a thermal radiator to reject heat; b. a pump, said pump having a first port and a second port, the first port of said pump connected to said thermal radiator; c. a tube, said tube substantially covering a surface of the spacecraft, one end

1. Apparatus for spacecraft thermal management comprising:a. a thermal radiator to reject heat; b. a pump, said pump having a first port and a second port, the first port of said pump connected to said thermal radiator; c. a tube, said tube substantially covering a surface of the spacecraft, one end of said tube connected to the second port of said pump, the other end of said tube connected to said thermal radiator, said tube, said thermal radiator, and said pump in fluid communication to form a continuous fluid flow loop, and d. a fluid, said pump circulating said fluid through the fluid flow loop; whereby the fluid flow in said tube controls the spacecraft's surface temperature.