针对某空间遥感器主承力结构机身结构进行了设计与分析。首先通过对比分析对机身进行结构选型,然后优选出一种新兴材料作为机身结构材料,即高体分硅铝合金材料,并确定连接方案,然后再通过拓补优化手段对机身结构进行优化,把反射镜组件等负载等效成力偶,进行合理的边界约束,大体上确定基本形式,进而优化出一种薄壁加筋结构,在保证机身动、静态刚度的前提下,提高了材料的轻量化率,并应用计算机仿真手段进行了静、动态及热特性的分析。分析结果证明该方案是合理可行的。

A space remote sensor main loadbearing structure of fuselage structure is designed and analysed. Firstly,through the comparative analysis,the body structure is selected,and then a new material as the material of body structure——high volume silicon aluminum alloy material is selected,and the connection scheme is determined,and then through the topology optimization method,the structure of the fuselage is optimized,the mirror assembly,etc. the load is coupled equivalently,the boundary constraints are reasonable on the whole,the basic form is determined,and a stiffened thinwall structure is optimized to ensure the dynamic and static stiffness,improve the rate of lightweight materials. The static,dynamic and thermal characteristics are analyzed applying computer simulation. The analysis results show that the scheme is feasible.