公开(公告)号：US06450450B1

公开(公告)日：2002-09-17

申请号：US09709784

申请日：2000-11-06

申请人： Frank D. MacDonald ,  Patrick B. Stickler ,  Ryon C. Warren ,  Chun-Hua Kathy Chuang

发明人： Frank D. MacDonald ,  Patrick B. Stickler ,  Ryon C. Warren ,  Chun-Hua Kathy Chuang

IPC分类号： B32B512

CPC分类号： B32B5/26 ,  B29C70/24 ,  B29K2995/0017 ,  B29L2031/3097

摘要： 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.

摘要翻译： 提供了一种制造，其制造简单，并且在优化高性能空中车辆的适度扩展的高速度任务的性能方面具有成本效益。 为了抵抗快速热负载而提供相对低成本的结构，在优选实施方案中，层压体将层压为树脂基体中的织物层的中间模量碳纤维与玻璃纤维材料缝合。 然后将该层压板固化并形成为超音速导弹的皮肤部分，从而能够延伸超音速操作，通常在达到或超过层压板的Tg后几分钟。 此外，公开了根据本发明的优选实施例构造的机身​​和机身构件。 与现有材料相比，降低了成本和重量，增加了热稳定性，并使内部有效载荷最大化。