柔性面对称星箭界面点式连接方案设计与分析  

The design and analysis method of flexible plane-symmetry satellite-launcher interface dotted joints conception

作　　者：张华山[1] 张家雄[1] 曹晓瑞[1] 叶林茂 贾亮[2] ZHANG Huashan;ZHANG Jiaxiong;CAO Xiaorui;YE Linmao;JIA Liang(R＆D Center,China Academy of Launch Vehicle Technology,Beijing 100076,China;Beijing Institute of Structure and Environment Engineering,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076 [2]北京强度环境研究所,北京100076

出　　处：《强度与环境》2018年第4期31-37,共7页Structure & Environment Engineering

基　　金："十三五"装备预研共用技术项目(41410040101)

摘　　要：以某型柔性、面对称的星体采用有限数目分离螺栓与运载火箭连接的方案为例,针对分离螺栓的载荷和强度,开展工程经验方法和有限元的对比分析。为解决分离螺栓强度不够问题,在分离螺栓的型号、数目和连接位置等约束不变的前提下,研究分离螺栓减载方法,提出一种增加小型辅助结构传递界面弯矩的改进方案,有效降低了分离螺栓载荷,分析结果表明该方案具有可行性。本文提出的界面载荷传递设计方法,对柔性飞行器与运载器采用点式连接的方案设计具有较重要的参考价值。Taking the concept that the flexible plane-symmetry satellite is jointed to launcher by limited separation explosive bolts as an example in the paper, both engineering experience method and finite element method are used to calculate the Satellite-launcher interface load transfer and strength. On the condition that the type, number and position of the separation bolts are constrained, the concept that an aided structure is designed to transfer interface bending to reduce loads of separation bolts, is promoted in order to improve the strengthen of the bolts. The result from finite element method shows that the concept is feasible. The method of the Interface load transfer in the paper offers a certain valuable reference to design of the dotted joints between the flexible satellite and its launcher.

关 键 词：分离螺栓 面对称截面 柔性结构 局部弯矩 辅助结构 

分 类 号：V415[航空宇航科学与技术—航空宇航推进理论与工程]