Heat transport system for spacecraft integration

Details Heat transport system for spacecraft integration Heat transport system for spacecraft integration

1995-12-22

1998-04-07

Kashnikow, Andres

Aeronautics and astronautics

Spacecraft

Attitude control

244158R, B64G 150

Patent

active

057354898

ABSTRACT:
The present invention relates to an apparatus for transferring heat in a spacecraft. The apparatus includes a flexible heat pipe having a first section, a second section, and a flexible section. A first member of a spacecraft is coupled to the first section of the flexible heat pipe, and a second member of the spacecraft is coupled to the second section of the flexible heat pipe. The first member of the spacecraft is in a rigidly fixed relationship to the second member of the spacecraft. A method of using a heat transport system for transferring heat in a spacecraft is also provided. The method includes providing a flexible heat pipe having a first section, a second section, and a flexible section, coupling the first section of the flexible heat pipe to a first member of a spacecraft, and coupling the second section of the flexible heat pipe to a second member of the spacecraft rigidly fixed with respect to the first member.

REFERENCES:
patent: 3749156 (1973-07-01), Fletcher et al.
patent: 3931532 (1976-01-01), Byrd
patent: 4324375 (1982-04-01), O'Neill
patent: 4880050 (1989-11-01), Nakamura et al.
patent: 5027892 (1991-07-01), Bannon et al.
patent: 5036905 (1991-08-01), Eninger et al.
patent: 5344104 (1994-09-01), Homer et al.
European Search Report, Application No. EP 96 12 0402, dated Apr. 4, 1997.

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