多体系统传递矩阵法在多管火箭动力学中的应用

多管火箭动力学分析是评估和提高多管火箭性能的前提和关键。应用多体系统传递矩阵法，建立某多管火箭刚柔耦合多体系统动力学模型，构造多管火箭增广特征矢量及其正交性条件，实现对多管火箭振动特性和动力响应的仿真，仿真结果得到了试验验证。对两种多管火箭的振动特性和动力响应的计算，为用非满管射击替代满管齐射客观评价多管火箭动态性能，为优化射序和射击时间间隔提高多管火箭射击密集度奠定基础，大幅度减少了某远程多管火箭密集度试验用弹量50％，提高某多管火箭射击密集度。

Application of Transfer Matrix Method of Multibody System in Dynamics of Multiple Launch Rocket System

The analysis on dynamics of multiple launch rocket system(MLRS) are the premise and key for evaluating and improving the performance of MLRS. The dynamics model of the MLRS including rigid bodies and elastic bodies are established by using the transfer matrix method of multibody system ( MSTMM). The augmented eigenvector and its orthogonality conditions of the MLRS are presented. The simulation of the vibration characteristics and the dynamic response of the MLRS are finished. The simulation results are verified by test. The bases to evaluate the dynamic performance by substituting non-full charge firing test for full charge firing test and to improve the firing dispersion for the MLRS by optimizing the firing orders and firing interval are established. The rocket consumption of a long-range MLRS in a firing dispersion experiment decreases by 50% compared with the traditional method and the firing dispersion for a MLRS is improved.