Deployable radiators for spacecraft

• US 6,439,297 B1
• Filed: 07/17/1997
• Issued: 08/27/2002
• Est. Priority Date: 07/31/1996
• Status: Expired due to Fees

• Current Assignee: Matra Marconi Space UK Limited
• Original Assignee: Matra Marconi Space UK Limited
• Inventors: McGoldrick, Philip David, Dunbar, Neil William
• Primary Examiner(s): ATKINSON, CHRISTOPHER MARK
• Application Number:
  US08/896,332
• Time in Patent Office: 1,867 Days
• Field of Search: 165/46, 165/104.21, 165/41, 165/104.26, 244/158.R, 244/159
• US Class Current: 165/46
• CPC Class Codes: B64G 1/50 for temperature control
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: F28D 15/043 forming loops, e.g. capillary pumped loops

Abstract

A limiting feature in spacecraft such as communication satellites is becoming the amount of surface such as 5, 6 available for dissipating waste heat from the electrical equipment in the satellite. The invention provides a deployable radiator 11 which carries a number of capillary pumped loops consisting of an evaporator, an outward limb and a return limb. The panel 11 is rolled up to coil the elements prior to launch, and unrolled when in orbit. The outward and return lengths of tube act as condenser for the capillary pumped loop, transport the heat over the radiating panel 11 and also provide the spring force for the panel to unroll.

Claims

1. A deployable radiator adapted to be mounted on a radiating surface of a spacecraft, which radiator comprises a linking panel structure.

at least ten springy closed loops of pipe each containing a working fluid and each at least partially extending across the linking structure panel and being attached thereto, and

a plurality of capillary evaporators connected, one in each closed loop of pipe, each of which evaporators is adapted to be secured to the radiating surface of a spacecraft,

said closed pipe loops and linking panel being sufficiently flexible to be rolled-up, whereby the linking panel structure and the springy closed loops of pipe secured thereto can be rolled up and secured for launch, and deployed by unrolling under influence of the spring force of the rolled up loops.

2. A deployable radiator as claimed in claim 1, in which the spring force of the rolled up loops provides the entire force for unrolling the linking panel structure.

3. A deployable radiator as claimed in claim 1, including a hinged arm extension mechanism for assisting the unrolling of the linking panel structure.

4. A deployable radiator as claimed in claim 2, wherein the extension mechanism is reversible to permit the linking panel structure and attached springy closed loops of pipe to be at least partially re-rolled up in space.

5. A deployable radiator as claimed in claim 1, further comprising a telescopic mast extension mechanism for assisting the unrolling of the linking panel structure.

6. A deployable radiator as claimed in claim 1, wherein the linking panel structure includes at least one layer of conducting material and at least one layer of plastics material.

7. A deployable radiator as claimed in claim 6, wherein the layer of conducting material is coated on the layer of plastics material.

8. A deployable radiator as claimed in claim 7, wherein the linking panel structure comprises a pair of layers of plastics material coated with respective layers of conducting material, an in which the springy closed loops of pipe are sandwiched between the facing conducting material layers.

9. A deployable radiator as claimed in claim 1, further comprising a heat pipe provided on said spacecraft radiating surface, said capillary evaporators being thermally connectable with said heat pipe.

10. A deployable radiator as claimed in claim 1, wherein the capillary evaporators are arrangeable in a row on said spacecraft radiating surface.

11. A deployable radiator as claimed in claim 1 wherein the springy closed loops of pipe extend parallel to each other across the linking panel structure.