THERMAL CONTROL SYSTEM FOR A SPACECRAFT MODULAR HOUSING

• US 3,749,156 A
• Filed: 04/17/1972
• Issued: 07/31/1973
• Est. Priority Date: 04/17/1972
• Status: Expired due to Term

• Current Assignee: Fletcher James C Administrator of The National Aeronautics and Space Administration With Respect To An Invention of, N/a,
• Original Assignee: Fletcher James C Administrator of The National Aeronautics and Space Administration With Respect To An Invention of, N/a,
• Inventors: Fletcher, James C. Administrator of the National Aeronautics and Space, N/a,
• Primary Examiner(s): Davis, Jr., Albert W.
• Application Number:
  US05/244,523
• Time in Patent Office: 470 Days
• Field of Search: 165/32,96,105,47 244/1SS
• US Class Current: 165/276
• CPC Class Codes: B64G 1/50 for temperature control
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: F28D 15/0233 the conduits having a particular shape, e.g. non-circular cross-section, annular F28D15/0241, F28D15/0266 take precedence
• CPC Class Codes: F28D 15/0275 Arrangements for coupling heat-pipes together or with other structures, e.g. with base blocks; Heat pipe cores
• CPC Class Codes: Y10S 165/904 Radiation

Abstract

This disclosure includes a thermal control system for a spacecraft module wherein certain wall structures of said module are constructed of superinsulation and others of thermally conductive material, thermal louvres and a plurality of heat pipes to provide a path of heat transfer from the interior of the module to space permitting a relatively uniform temperature to be maintained throughout the module at all times with a relatively wide variation of the amount of heat dissipated by components within the module.

Claims

1. A thermal control system for an enclosure having space application wherein said enclosure comprises a. a wall structure comprised of a thermal conduction panel having opposed, spaced, outer thermally conductive interior and exterior faceplates and means for retaining said plates in said spAced relation and transmitting heat through said panels;

b. a plurality of heat pipes mounted in said wall structure between said faceplates and thermally coupled to said plates, said heat pipes being comprised of a closed tube and having a working fluid in said tube, said fluid being capable of conversion to a gas and being condensed back to a liquid within a desired working temperature range. c. louvre means operatively mounted on the exterior of said wall structure and actuated responsively to the temperature level of the panel to which the louvre is mounted for resisting the transfer of heat from the panel when in a closed position and permitting heat transfer from said panel when in an open position.

2. A thermal control system as recited in claim 1 wherein the exterior plate has a highly reflective coating of fused silica with a layer of vapor deposited silver thereon comprising the exterior surface thereof.

3. A thermal control system as recited in claim 1 wherein said wall structure is comprised of at least two spaced opposed thermally conductive panels forming opposite sides of said enclosure and means for thermally coupling said panels together, each of said panels having said heat pipes mounted therein and said louvres operatively mounted thereon.

4. A thermal control system as recited in claim 3 wherein said means for thermally coupling said panels is comprised of a plurality of heat pipes extending between and thermally coupled to said panels.

5. A thermal control system as recited in claim 4 wherein said means for thermally coupling said panels includes a third thermally conductive panel having said heat pipes mounted therein, said third panel extending between and being thermally coupled to said side panels.

6. A thermal control system as recited in claim 3 wherein said enclosure is of a cubical configuration with said thermally conductive panels comprising two opposed sides of said enclosure and the four remaining sides of said enclosure are comprised of wall structures having superinsulation to prevent the transmission of heat therethrough and thus define a positive flow path for heat transfer.

7. A thermal control system as recited in claim 6 wherein said means for thermally coupling said side panels is comprised of a plurality of heat pipes mounted in an intermediate wall structure, said intermediate wall structure being comprised of said thermally conductive panel and having said heat pipes mounted between the faceplates of said panel and thermally coupled to said faceplates.

8. A thermal control system as recited in claim 6 forming an integral part of a spacecraft module wherein said thermally conductive panels comprise the north and south sides of the module which are not exposed directly to the rays of the sun during orbital flight of the spacecraft.

9. A thermal control system as recited in claim 7 wherein said plurality of heat pipes mounted in the intermediate wall structure includes a pair of opposite end portions and a central portion and wherein said central portion extends normally to said side panels and said end portions extend parallel to said side panels, said opposite end portions being thermally coupled to said side panels whereby heat from said end portions of the heat pipes of the intermediate wall structure is transferred to said side panels for ultimate transmission to the exterior of said enclosure.