摘要
载人航天器大型化、轻量化的特点对结构效率提出了更高的要求,文章提出一种薄壁密封舱大承载胶接结构设计方法,通过采取胶接区域变厚度设计、通气孔分布式设计、打磨工艺设计和抽真空加压设计等针对性改进措施,有效解决了"浴盆效应"、支座与舱壁的刚度匹配、舱壁局部表面处理以及胶接加压等问题。仿真分析和试验表明:支座在胶层剥离前可承受约12 000N的剪力,胶接性能得到明显提高,此方法可用于密封舱舱内结构设计。
Large-scale and lightweighting feature of manned spacecraft bring forward higher quire- ment to the structure efficiency. The paper presents a method used to design large load bonding structure of sealed cabin with thin wall. By taking improved measures, including braker variable thickness design, distributed vent design, sanding process design and vacuum pumping pressure design, the following problems have been solved： ＂Bathtub effect＂, stiffness matching between bracket and panel of sealed cabin, optimizing partial surface micro topography and multi direction compression. Simulation results and tests results demonstrate that the bearing shear force before peeling reaches up to 12000N, and bonding property is improved significantly. The method is available to the inner structure design of sealed cabin.
出处
《航天器工程》
北大核心
2016年第5期45-50,共6页
Spacecraft Engineering
基金
国家重大科技专项工程
关键词
航天器
密封舱
薄壁
胶接
支座
spacecraft
sealed cabin
thin wall
bonding
bracket
