Integrated thermal insulation system for spacecraft
First Claim
1. A thermal protection system (TPS) for a spacecraft defining a front and a rear while in aerodynamic flight and having an external skin, the TPS comprising:
- a support frame attached to the skin of the spacecraft;
at least a first thermally insulative panel positionable on the support frame, the first panel including a first edge;
at least a second thermally insulative panel positionable on the support frame adjacent the first panel, the second panel including a second edge configured for interlocking engagement with the first edge of the first panel;
at least one alignment pin on the second panel and engageable with the first panel to align and interlock the panels together; and
at least one hold down fastener engageable with the support frame and the first panel to hold the first panel onto the frame.
1 Assignment
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Accused Products
Abstract
An integrated thermal protection system (TPS) for a spacecraft includes a grid that is bonded to skin of the spacecraft, e.g., to support the structural loads of the spacecraft. A plurality of thermally insulative, relatively large panels are positioned on the grid to cover the skin of the spacecraft to which the grid has been bonded. Each panel includes a rounded front edge and a front flange depending downwardly from the front edge. Also, each panel includes a rear edge formed with a rounded socket for receiving the rounded front edge of another panel therein, and a respective rear flange depends downwardly from each rear edge. Pins are formed on the front flanges, and pin receptacles are formed on the rear flanges, such that the pins of a panel mechanically interlock with the receptacles of the immediately forward panel. To reduce the transfer to the skin of heat which happens to leak through the panels to the grid, the grid includes stringers that are chair-shaped in cross-section.
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Citations
10 Claims
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1. A thermal protection system (TPS) for a spacecraft defining a front and a rear while in aerodynamic flight and having an external skin, the TPS comprising:
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a support frame attached to the skin of the spacecraft; at least a first thermally insulative panel positionable on the support frame, the first panel including a first edge; at least a second thermally insulative panel positionable on the support frame adjacent the first panel, the second panel including a second edge configured for interlocking engagement with the first edge of the first panel; at least one alignment pin on the second panel and engageable with the first panel to align and interlock the panels together; and at least one hold down fastener engageable with the support frame and the first panel to hold the first panel onto the frame. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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Specification