航天器高温热密封设计方法及性能评价

Design Method and Performance Evaluation Criteria of Advanced Spacecraft Heat Seal

针对先进航天器高温热密封设计领域缺乏系统的设计方法及性能评价准则的现状,基于飞行器热密封设计基本原理,通过理论分析及设计流程优化,设计并开展了高温热失重试验、高温压缩/回弹试验、高温摩擦/磨损试验、冲击和反复加载试验以及高温缝隙泄漏试验,获得了典型密封结构与密封材料的基本性能参数,并提出系统的高温热密封性能评价方法。在此基础上,利用电弧射流平台,对典型连接位置以及某折叠翼热密封设计方案的有效性进行了验证与性能评价,相关成果可为航天器高温热密封设计及性能评价提供理论基础与试验数据支撑。

Aiming at the current situation that the advanced spacecraft heat seal design lacks the systematic design method and the performance evaluation criteria,the following researches are carried out： the theoretical analysis is conducted and the design process is optimized on the basic principle of the spacecraft heat seal design. The thermal weight loss test,compressive resilience test,frictional wear test,impact/repeated load test and the leakage test are designed and carried out under the high temperature condition. The basic performance parameters of the typical sealing structures and materials are acquired. Performance evaluation method of heat seal plan is put forward systematically. On these bases,the effectiveness of the heat seals of the typical connection positions and a folding wing is verified and their performances are evaluated with the arc jet tunnel. The relevant results and experimental data provide theoretical surpport to the spacecraft heat seal design and evaluation.