Micrometeoroid and debris protection system for a thermal control system on a spacecraft
AssigneeThe Boeing Company
InventorAnthony Pang
Life of this patent
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Abstract
Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.
Claims20
A micrometeoroid and debris protection system for a thermal control system on a spacecraft, the system comprising:
- a radiator face-sheet;
- a truss extending from an outward surface of the radiator face-sheet;
- and
- a thermally transparent bumper disposed on the truss, comprising:
- a first surface, oriented away from the radiator face-sheet, configured to reflect radiation from space, and
- a second surface, oriented toward the radiator face-sheet, that is thermally transparent to heat energy radiated from the radiator face-sheet, wherein the heat energy from the radiator face-sheet is configured to radiate away from the radiator face-sheet through the thermally transparent bumper.
A method for manufacturing a micrometeoroid and debris protection system for a thermal control system on a spacecraft, the method comprising:
- providing a truss to extend from an outer surface of a radiator face-sheet, wherein the radiator face-sheet includes an inner surface attached to the thermal control system and the truss is positioned opposite a location of the thermal control system;
- and
- attaching a thermally transparent bumper on to the truss, the thermally transparent bumper comprising:
- a first surface, oriented away from the radiator face-sheet, configured to reflect radiation from space, and
- a second surface, oriented toward the radiator face-sheet, that is thermally transparent to heat energy radiated from the radiator face-sheet, wherein the heat energy from the radiator face-sheet is configured to radiate away from the radiator face-sheet through the thermally transparent bumper.
A micrometeoroid and debris protection system for a thermal control system on a spacecraft, the thermal control system having a first heat-pipe and a second heat-pipe, the system comprising:
- a radiator face-sheet having an inner surface, wherein the first heat-pipe and the second heat-pipe are attached to the inner surface of the radiator face-sheet;
- a first truss and a second truss attached to an outer surface of the radiator face-sheet;
- and
- a first thermally transparent bumper disposed on the first truss and a second thermally transparent bumper disposed on the second truss, at least one of the first thermally transparent bumper or the second thermally transparent bumper comprising:
- a first surface, oriented away from the radiator face-sheet, configured to reflect radiation from space, and
- a second surface, oriented toward the radiator face-sheet, that is thermally transparent to heat energy radiated from the radiator face-sheet, wherein the heat energy from the radiator face-sheet is configured to radiate away from the radiator face-sheet through the at least one of the first thermally transparent bumper or the second thermally transparent bumper.
Dependencies are inferred from the claim text.