Space vehicle thermal rejection system

Details Space vehicle thermal rejection system Space vehicle thermal rejection system

1987-07-15

1989-05-16

Davis, Jr., Albert W.

Heat exchange

With vehicle feature

16510414, 16510426, 122366, F28D 1502

Patent

active

048300977

ABSTRACT:
A space vehicle thermal heat rejection system 10 utilizing separate optimized heat pipe components for the functions of heat acquisition, heat transport, and heat rejection. A honeycomb panel heat pipe evaporator section 20 performs the function of heat acquisition, and forms a closed thermodynamic system with a dual channel heat pipe transport section 30, which performs the function of heat transport. A plurality of truss or channel core heat pipe rejection fins 41 form the condenser section 40, which performs the function of heat rejection. A common wall 32 separates the condenser section 40 from the transport section 30. Using the above heat pipe components and having efficient interfacing between them results in high performance factors for the overall system.

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patent: 4231423 (1980-11-01), Haslett
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patent: 4602679 (1986-07-01), Edelstein et al.
patent: 4627487 (1986-12-01), Basiulis
patent: 4706740 (1987-11-01), Mahefbey
Tanzer, H. J., "High Capacity Honeycomb Panel Heat Pipes for Space Radiators", AIAA-83-1430, Jun. 1-3, 1983.
Alario J., Haslett, R. and Kosson, R., "The Monogroove High Performance Heat Pipe", AIAA-81-1156, Jun. 23-25, 1981.

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