Importance

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Abstract

A method and apparatus are disclosed for providing an aircraft thermal protection system for hypersonic cruise and space launch vehicles. A flexible outer skin formed from a metal super alloy is designed to flex and accommodate thermal growth in the vehicle structure. The flexible super alloy skin is made from a plurality of hexagonal shaped cups which are welded together at the edges in a honeycomb type of array with thermal expansion gaps provided between the outermost surfaces of the hexagonal cups. Gap covers extend across the thermal expansion gaps to reduce aerodynamic drag. The flexible outer skin extends over hexagonal shaped, high temperature ceramic blocks, which provide both an insulation layer and support for the outer skin. The flexible outer skin distributes airloads across various ones of the rigid ceramic blocks. A strain isolation pad extends across the ends of the blocks, opposite the flexible outer skin, to absorb strains induced by thermal expansion of the ceramic blocks and the materials beneath. A closed cell foam sheeting extends adjacent to the strain isolation pads, opposite the ceramic blocks, to provide a moisture barrier for preventing liquid formation and freezing on cryogenic fuel tanks. A thin super alloy backing foil extends along the closed cell foam sheeting, opposite the strain isolation pads. The flexible outer skin is secured to the backing foil by super alloy rods.

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First Claim