Abstract: 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.

Abstract: A self-actuated structure, such as an antenna structure, is provided that can be stowed in a compact manner and can be deployed in a self-actuated fashion. The self-actuated structure includes a flexible skin, a boom extending thereacross and rings about which the flexible skin can be folded such that a payload volume is defined therewithin. The self-actuated structure also has a plurality of ribs extending parallel to the boom that cooperate with the flexible skin to define a number of channels extending between the boom and an edge of the flexible skin. The structure also includes a plurality of self-deploying stiffeners disposed within respective channels. In this regard, the stiffeners can have an unbiased relaxed shape, such as a “U” shape, in the absence of external forces and a biased shape, such as a flat shape, upon the application of external bias forces.