초록 ▼

Provided is a fabrication that is simple to make and cost effective in optimizing performance for moderately extended high velocity missions of high performance airborne vehicles. To counter rapid thermal loading while providing a relatively low cost structure, a laminate, in a preferred embodiment

Provided is a fabrication that is simple to make and cost effective in optimizing performance for moderately extended high velocity missions of high performance airborne vehicles. To counter rapid thermal loading while providing a relatively low cost structure, a laminate, in a preferred embodiment an intermediate modulus carbon fiber laminated as fabric layers in a resin matrix, is stitched through with glass fiber material. This laminate is then cured and formed as a section of skin of a supersonic missile, enabling extended supersonic operation, nominally some minutes after the laminate's Tg has been reached or exceeded. Additionally, an airframe and airframe members constructed in accordance with a preferred embodiment of the present invention are disclosed. Compared to existing materials, it reduces cost and weight, increases thermal stability, and maximizes internal payload.

대표청구항 ▼

1. A structural member that accommodates high rate thermal and G-force loading for a time beyond that moment at which the glass transition temperature, Tg, of at least one constituent of said member is reached, comprising:a composite material having a Tg, and three dimensions, wherein one of said th

1. A structural member that accommodates high rate thermal and G-force loading for a time beyond that moment at which the glass transition temperature, Tg, of at least one constituent of said member is reached, comprising:a composite material having a Tg, and three dimensions, wherein one of said three dimensions, termed thickness, is much smaller than either of the other two said three dimensions; and a material compatible with said composite material and suitable for use with a device for penetrating said thickness of said composite material such that said thickness has pass throughs across said thickness, wherein said pass throughs are occupied by stitching said material compatible with said composite material through said pass throughs, wherein multiple layers of said composite material, comprising a lamination, may be penetrated by said stitching of said layers, and wherein said pass throughs provide the member with pathways for outgassing of at least some of its constituent compounds during high rate thermal loading of the member, and wherein said Tg of said composite material is to be at least attained in the normal operation of an apparatus constructed with said member.