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AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsSalvatore R. Riccitiello, Marnell Smith, Howard E. Goldstein, Norman B. Zimmerman
Estimating the term…
The present invention discloses a ceramic reusable externally applied thermal protection system (TPS). The system functions by using the composite device created by combining an upper shell, thermal insulation and lower tile components shown in FIG. 2. The upper shell effectively separates its primary functions as a toughened outer-surface and load carrier. In a preferred embodiment, a structurally strong ceramic/ceramic upper shell is manufactured from ceramic cloth upon which additional ceramic material has been deposited and maintains the configuration of the upper shell. The lower tile is composed of lightweight ceramic normally acceptable in this application. One or more lightweight rigid or flexible insulation materials are used in the cavity created by combining the upper shell and lower tile. The assembly of the overall tile is facilitated by attachment means effective to withstand the temperature and stress conditions. These attachment means include a self-locking wedge and complementary surface, ceramic pins, augers and the like. The device is useful on the interior surface of a kiln or the like and is also attached to the exterior surface of an aerospace vehicle for thermal protection.
A ceramic composite tile device specially adapted for use as a component of a reusable thermal protection system for use on the surface of an object in need of thermal protection, which device comprises:
A ceramic composite tile device specially adapted for use as a component part of a reusable externally applied thermal protection system on the surface of an aerospace vehicle, which device comprises:
As an article of manufacture, a ceramic-coated ceramic-fabric upper shell as a component for use in a ceramic, reusable, externally applied thermal protection device on the surface of an aerospace vehicle, which upper shell comprises:
In a composite ceramic thermal protection device for use on the exterior surface of an aircraft or spacecraft, wherein the improvement is the use of a thermally stable rigid protective ceramic-coated ceramic-fabric upper shell itself comprising a woven ceramic fabric in the shape of an upper shell wherein the upper shell is coated with additional ceramic by chemical vapor deposition and chemical vapor infiltration, attached to a complimentary ceramic lower base, tile wherein the upper shell and the lower base tile are stress/strain independent and do not comprise the same ceramic materials and the upper shell is attached securely to the lower base tile by interlocking means effective to survive temperatures up to 3200.degree. F.
Dependencies are inferred from the claim text.