多管火箭动力学灵敏度分析及优化设计新方法

Novel sensitivity analysis method and dynamics optimization for multiple launch rocket systems

为降低多管火箭发射动力学响应,基于多体系统Riccati传递矩阵法(RMSTMM)、直接微分法(DDM)、遗传算法(GA),分别建立了多管火箭发射动力学仿真计算方法、灵敏度分析方法和多目标动力学优化方法,并用于多管火箭动力学仿真分析.结果表明,动力学响应仿真结果与试验结果吻合.建立的灵敏度分析方法程式化程度高,矩阵阶次低,计算时间远小于Lagrange方法.随着系统复杂度的增加,计算速度优势愈发明显.俯仰体与回转体的连接刚度、回转体与车体的连接刚度以及14^(#)、16^(#)、17^(#)车轮与地面的连接刚度是对动力学响应影响最大的结构参数,也是优化中的设计变量.优化后,俯仰体回转方向和俯仰方向的角速度方差分别降低了97.84%和95.22%.

This study establishes the launch dynamics method,sensitivity analysis method,and multiobjective dynamic optimization method for the dynamic simulation analysis of the multiple launch rocket system(MLRS)based on the Riccati transfer matrix method for multibody systems(RMSTMM),direct differentiation method(DDM),and genetic algorithm(GA),respectively.Results show that simulation results of the dynamic response agree well with test results.The sensitivity analysis method is highly programming,the matrix order is low,and the calculation time is much shorter than that of the Lagrange method.With the increase of system complexity,the advantage of a high computing speed becomes more evident.Structural parameters that have the greatest influence on the dynamic response include the connection stiffness between the pitching body and the rotating body,the connection stiffness between the rotating body and the vehicle body,and the connection stiffnesses among 14^(#),16^(#),and 17^(#)wheels and the ground,which are the optimization design variables.After optimization,angular velocity variances of the pitching body in the revolving and pitching directions are reduced by 97.84%and 95.22%,respectively.