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重新设计的航天飞机固体发动机现场接头的内部绝热层是发动机钢壳体和O型密封环的热防护部件.为了防止燃烧室高温燃气到达接头内部,采用了一种无通孔绝热层设计方案.对假想的缺陷和由这些缺陷造成的沿接头粘合面以及O型密封环发展的泄漏通道进行了分析,以验证接头在这些不希望出现的条件下能否完满地起到密封作用.同时还进行了接头中有预设缺陷的发动机的静态试车,验证这种设计对缺陷和由此产生的泄漏通道的不敏感性.试验与分析的结果表明,该设计满足所有的性能和安全要求.
Redesigned Space Shuttle Solid Engine The internal insulation of the field fittings is the thermal shield of the engine steel housing and O-ring, and a through-hole insulation design was used to prevent the hot gas in the combustion chamber from reaching the inside of the joint. An analysis of the hypothetical defects and the leak pathways along the joint bonding surfaces and O-ring development caused by these imperfections was performed to verify that the joint could function satisfactorily under these unwanted conditions. A static test run of the engine with the default defects in the joint was performed to verify the insensitivity of the design to the defects and the resulting leakage path.The results of the tests and analyzes showed that the design met all the performance and safety requirements.