会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 66. 发明授权
    • Rocket motor joint construction including thermal barrier
    • 火箭发动机接头结构包括热障
    • US06446979B1
    • 2002-09-10
    • US09613053
    • 2000-06-27
    • Bruce M. SteinetzPatrick H. Dunlap, Jr.
    • Bruce M. SteinetzPatrick H. Dunlap, Jr.
    • F16J1510
    • F16J15/104F16J15/065Y10S277/938
    • A thermal barrier for extremely high temperature applications consists of a carbon fiber core and one or more layers of braided carbon fibers surrounding the core. The thermal barrier is preferably a large diameter ring, having a relatively small cross-section. The thermal barrier is particularly suited for use as part of a joint structure in solid rocket motor casings to protect low temperature elements such as the primary and secondary elastomeric O-ring seals therein from high temperature gases of the rocket motor. The thermal barrier exhibits adequate porosity to allow pressure to reach the radially outward disposed O-ring seals allowing them to seat and perform the primary sealing function. The thermal barrier is disposed in a cavity or groove in the casing joint, between the hot propulsion gases interior of the rocket motor and primary and secondary O-ring seals. The characteristics of the thermal barrier may be enhanced in different applications by the inclusion of certain compounds in the casing joint, by the inclusion of RTV sealant or similar materials at the site of the thermal barrier, and/or by the incorporation of a metal core or plurality of metal braids within the carbon braid in the thermal barrier structure.
    • 用于极高温度应用的热障碍包括碳纤维芯和围绕芯的一层或多层编织碳纤维。 热障优选是具有相对较小横截面的大直径环。 热障特别适合用作固体火箭发动机壳体中的接头结构的一部分,以保护低温元件,例如火箭发动机的高温气体中的初级和次级弹性体O形环密封件。 热障壁表现出足够的孔隙度,以允许压力到达径向向外设置的O形密封圈,从而使它们能够坐下并执行主密封功能。 热屏障设置在套管接头中的空腔或凹槽内,火箭发动机内部的热推进气体与主O形密封件和次级O形密封件之间。 在不同的应用中,通过在套管接头中包含某些化合物,通过在隔热部位包含RTV密封剂或类似材料,和/或通过引入金属芯,可以增强热障的特性 或多个在热障壁结构中的碳编织物内的金属编织物。