多管火箭发射系统虚实混合动力学建模与仿真  

Virtual-real dynamic modeling and simulation for multiple launch rocket system

作　　者：刘广 许自然 张广军 孙文钊 康海峰 LIU Guang;XU Ziran;ZHANG Guangjun;SUN Wenzhao;KANG Haifeng(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所,上海201109

出　　处：《计算机辅助工程》2018年第5期20-27,共8页Computer Aided Engineering

摘　　要：为减小火箭出管后的初始扰动,运用多体动力学虚实混合建模与仿真技术研究多管火箭的出管姿态。对试验数据进行频谱分析,对关键部件进行结构动态特性分析和模态试验,采用虚实混合建模方法,构建多管火箭发射系统的动力学虚拟样机模型。采用柔性连接Bushing模拟发射系统的弹性特性,经过工程计算获得燃气冲击力并以脉冲形式施加到模型中,研究弹管间隙、质量偏心、推力偏心、发射时序和发射时间间隔等因素对火箭出管姿态的影响。研究结果表明:合理的弹管间隙、质量偏心、发射时序和发射时间间隔可以减小火箭出管后的初始扰动。In order to reduce the initial disturbance of rocket outlet,a multi-body dynamics virtual-real modeling and simulation technology is presented to study outlet attitude of multiple launch rocket.The spectrum test data is analyzed,and the structural dynamic characteristic analysis and modal test of the key parts are done.The dynamics virtual prototype model of multiple launch rocket system is built using virtual-real modeling method.The flexible connection Bushing is adopted to simulate the flexible characteristic of multiple launch rocket system,and the gas impact force is computed using the engineering calculation and applied to the model in the form of impulse.The influence of a series of factors on outlet attitude is studied,such as the clearance between rocket and launching tube,the mass eccentricity,the thrust eccentricity,and the launching sequence and interval.The results show that the reasonable clearance between rocket and launching tube,mass eccentricity,launching sequence and interval can reduce the initial disturbance of the rocket.

关 键 词：多管火箭 扰动 虚实混合建模 虚拟样机 出管姿态 

分 类 号：TJ765.239[兵器科学与技术—武器系统与运用工程]