Dual function deployable radiator cover

• US 5,806,800 A
• Filed: 12/22/1995
• Issued: 09/15/1998
• Est. Priority Date: 12/22/1995
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Inventors: Caplin, Glenn N.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/577,596
• Time in Patent Office: 998 Days
• Field of Search: 244/158 R, 244/163, 165/41, 165/104.14, 165/171
• US Class Current: 244/171.8
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields

Abstract

The present invention is a dual function deployable radiator and radiator cover for use on a communication satellite. A deployable radiator is folded or in a "stowed" configuration over a fixed radiator when a satellite is in a launch vehicle. The deployable radiator thereby serves as insulation for the satellite when heat rejection is not necessary. When heat rejection becomes necessary, the deployable radiators are deployed whereby unwanted heat is rejected from the satellite. The deployable radiators, therefore serve a dual purpose, functioning as insulators for part of a mission and radiators for the remainder.

Claims

1. A spacecraft having a spacecraft body with at least one fixed radiator, said spacecraft comprising:

a deployable radiator hinged on said spacecraft body, such that said deployable radiator covers said fixed radiator when said deployable radiator is in a stowed position.

2. The spacecraft of claim 1, wherein said deployable radiator is secured in said stowed position by at least one launch lock.

3. The spacecraft of claim 2, wherein said deployable radiator is deployed by unsecuring said at least one launch lock.

4. The spacecraft of claim 1 comprising a material blanketing the exterior of said deployable radiator, said material being capable of limiting thermal radiation.

5. The spacecraft of claim 4, wherein said material is a multilayer aluminum deposited on KAPTON™

blanket.

6. A spacecraft having a spacecraft body with at least one fixed panel, said spacecraft comprising:

a deployable radiator hinged on said spacecraft body, such that said deployable radiator covers said fixed panel when said deployable radiator is in a stowed position; and

a material blanketing the exterior of said deployable radiator, said material being capable of limiting thermal radiation.

7. The spacecraft of claim 6, wherein said material is a multilayer aluminum deposited on KAPTON™

blanket.

8. The spacecraft of claim 6, wherein said deployable radiator is secured in said stowed position by at least one launch lock.

9. The spacecraft of claim wherein said deployable radiator is deployed by unsecuring said at least one launch lock.

10. A method for using a deployable radiator as an insulator on a spacecraft structure, said structure having at least one fixed panel, comprising the steps of:

stowing said deployable radiator over said at least one fixed panel for a part of a space mission; and

deploying said deployable radiator for a part of said mission, such that said deployable radiator is no longer stowed over said at least one fixed panel.

11. The method of claim 10, further comprising the step of blanketing said deployable radiator with a multilayer aluminum deposited on KAPTON™

blanket.

12. The method of claim 10, further comprising the step of blanketing said deployable radiator with a material capable of limiting thermal radiation.

13. A method for using a deployable radiator as an insulator on a spacecraft structure, said structure having at least one fixed radiator, comprising the steps of:

stowing said deployable radiator over said at least one fixed radiator for a part of a space mission; and

deploying said deployable radiator for a part of said mission, such that said deployable radiator is no longer stowed over said at least one fixed radiator.

14. The method of claim 13, further comprising the step of blanketing said deployable radiator with a multilayer aluminum deposited on KAPTON™

blanket.

15. The method of claim further comprising the step of blanketing said deployable radiator with a material capable of limiting thermal radiation.