远程多管火箭动力学研究  

STUDY ON DYNAMICS OF LONG RANGE MULTIPLE LAUNCH ROCKET SYSTEM

作　　者：王国平[1] 芮筱亭[1] 

机构地区：[1]南京理工大学动力学院,南京210094

出　　处：《动力学与控制学报》2004年第1期59-64,共6页Journal of Dynamics and Control

摘　　要：对某远程多管火箭发射与控制动力学进行了深入的理论、计算和试验研究,建立了某远程多管火箭刚弹耦合的多体系统发射动力学模型和发射与控制动力学方程.应用多体系统传递矩阵法,实现了对刚柔耦合远程多管火箭振动特性的计算;构造了远程多管火箭增广特征矢量及其正交性条件,实现了对该远程多管火箭动力响应的精确分析.对某远程多管火箭武器振动特性和动力响应的仿真结果得到了试验验证.为提高远程多管火箭密集度和减少试验用弹量奠定了基础.This paper studied the Launch and control dynamics of Long Range Multiple Launch Rocket System (LRMLRS). We established a launch dynamics model and derived the launch and control dynamics equations for LRMLRS, which is a coupling multibody system including both rigid bodies and elastic bodies. By using the transfer matrix method of multibody system. We computed its vibration characteristics, we also presented the augmented eigenvector and its orthogonality conditions for LRMLRS. The dynamic response of LRMLRS was simulated, and the simulation results agreed well with the experimented datas. This study provided some basis to improve dispersion of fire and decrease rockets consumption in testing a LRMLRS .

关 键 词：远程多管火箭 火箭弹 发射动力学 传递矩阵法 正交性 弹道学 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]