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Rapidly removable thermal protection system for reusable launch vehicle

机译:用于可重复使用运载火箭的可快速拆卸的热保护系统

摘要

A thermal protection system is composed of multiple panels, each of which has an ablative layer of cork thermal protection which is adhesively bonded to a flexible film. The rear surface of the film is coated with two types of adhesive. A first, high strength adhesive is applied at the edges of the cork panel and where aerodynamic forces may be higher. A second, lower strength adhesive is applied to the remaining surface of the film. Following the return of the launch vehicle from space, the thermal protection panels are removed by peeling away the high strength attachment edges with a knife, or other blade tool, and then removing the remainder of the panel, which is only lightly attached to the vehicle skin, without the aid of tools.
机译:热保护系统由多个面板组成,每个面板均具有软木热保护层,该软层可粘结到柔性薄膜上。薄膜的背面涂有两种粘合剂。在软木板的边缘处施加第一高强度粘合剂,在该处空气动力可能更高。将较低强度的第二种粘合剂施加到薄膜的其余表面。运载火箭从太空返回后,通过用小刀或其他刃口工具将高强度的固定边缘剥落,再拆下热保护板,然后取下仅轻轻附着在运载工具上的其余部分皮肤,无需借助工具。

著录项

  • 公开/公告号US6136418A

    专利类型

  • 公开/公告日2000-10-24

    原文格式PDF

  • 申请/专利权人 ROTARY ROCKET COMPANY;

    申请/专利号US19990259763

  • 发明设计人 BEVIN C. MCKINNEY;ANTHONY MARTIN;

    申请日1999-03-01

  • 分类号B32B3/10;B32B3/06;

  • 国家 US

  • 入库时间 2022-08-22 01:35:54

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