再入飞行器冷热结构一体化设计及分析  

Integrative Design and Analysis of Reentry Thermal Protection and Structure System

作　　者：王兆伟[1] 孙国岭[2] 姚星合[1] 吴勇军[1] 屈强[1] 

机构地区：[1]中国运载火箭技术研究院研发中心,北京100076 [2]The Chinese Liberation Army's Representative Office at Capital Spaceflight Machinery Company,beijing100076

出　　处：《航天制造技术》2015年第6期15-17,20,共4页Aerospace Manufacturing Technology

摘　　要：针对多层热结构存在的热短路和连接方式复杂问题,设计了防/隔热双层热结构与冷结构一体化。在典型服役环境条件下,采用有限元法对热结构组件与冷结构进行了强度和热匹配分析,计算发现气动力对组件强度影响不大;惯性力作用下,组件的薄弱环节是螺钉和隔热层;再入热环境条件下,连接件位置出现应力集中现象。完成的强度及热匹配分析结果可应用于再入飞行器冷热结构一体化设计。To avoid the complicated joint and thermal short problems in multi-layer type thermal protection structures, a double-layer thermal protection system with integrated cold and hot structure design was obtained. Numerical simulation models were established in order to obtain mechanical response and conduct thermal compatibility analysis based on the typical service environment. Results found that the effect of aerodynamic load on the designed thermal structures can be ignored. Under inertial force, the weakness points are the insulation structures and bolts. The key load which could cause the failure of the thermal structures was found to be the thermal load during the reentry process. The maximum stress for double-layer thermal structure is impacted by the non-metallic bolts. Results obtained can be used in reentry vehicles thermal and cold structure integrative design.

关 键 词：多层热结构一体化设计 强度分析 热匹配分析 

分 类 号：V423[航空宇航科学与技术—飞行器设计]