火箭卫星舱壳体分离灵敏度分析与优化设计  

Rocket Satellite Cabin Separation Sensitivity Analysis and Optimization

作　　者：葛悦 王洪波[1] 龚旻[1] 赵俊锋[1] 高峰[1] 罗波[1] 牛飞[1] GE Yue;WANG Hongbo;GONG Min;ZHAO Junfeng;GAO Feng;LUO Bo;NIU Fei(China Academy of Launch Vehicle Technology, Beijing 100076, China)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《兵器装备工程学报》2020年第12期46-52,72,共8页Journal of Ordnance Equipment Engineering

基　　金：国家自然科学基金面上项目(11972377);爆炸科学与技术国家重点实验室开放基金资助项目(KFJJ19-04M)。

摘　　要：考虑分离安全性的运载火箭卫星舱壳体结构设计,基于柔性多体动力学理论,建立了卫星舱壳体平抛分离参数化模型,采用基于方差测度的非线性回归法,对卫星舱壳体各分区结构尺寸、铺层厚度、推冲器作用位置等参数进行灵敏度分析。选取重要设计变量,以壳体质量最轻为优化目标,以分离速度和分离最小间隙为约束,应用近似模型进行优化设计。优化后的卫星舱壳体质量降低48.3%,提高了火箭的有效载荷运载能力。For structural design of the satellite cabin considering separation availability and safety,this paper established parameterized dynamics model of the satellite cabin separation based on flexible multi-body dynamics theory.Sensitivity analysis was conducted for design parameters of the satellite cabin such as structure size,ply thickness,position of thruster using nonlinear regression theory.Important design variables distinguished by sensitivity analysis were selected to optimize the design by taking the lightest satellite cabin mass as the objective and the average separation speed and minimum clearance during separation as the constraints by approximation model.The optimized satellite cabin mass was reduced by 48.3%,which increased the payload carrying capacity.

关 键 词：刚柔耦合 卫星舱分离 灵敏度分析 优化设计 近似模型 

分 类 号：O326[理学—一般力学与力学基础] V421.3[理学—力学]