Low cost structural fabrication that resists catastrophic failure under rapid thermal loading
US6450450B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 6, 2000 |
| Grant date | Sep 17, 2002 |
| Priority date | — |
| Expiry date | Nov 6, 2020 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB29L2031/3097
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.