基于多体系统传递矩阵法的多管火箭定向器振动控制  

VIBRATION CONTROL FOR LAUNCHER OF MULTIPLE LAUNCH ROCKET SYSTEM BASED ON TRANSFER MATRIX METHOD OF MULTIBODY SYSTEM

作　　者：展志焕[1] 芮筱亭[1] 王国平[1] 杨富锋[1] 贺军义[1] 

机构地区：[1]南京理工大学发射动力学研究所,南京210094

出　　处：《力学学报》2010年第3期583-590,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：江苏省自然科学基金攀登计划(BK2008046);国家自然科学基金(10902051)资助项目~~

摘　　要：应用多体系统传递矩阵法,建立了全新的多管火箭发射动力学控制模型,以二次型性能指标为成本函数,设计了脉冲推力器为控制执行机构的振动主动控制律,并设计了多管火箭发射系统在燃气流冲击下定向器的振动主动控制系统,获得了最优脉冲控制力幅值和脉冲推力器工作次数.应用设计的控制律数值仿真了某多管火箭定向器无控和受控状态下的振动响应,仿真结果表明该法可有效地降低定向器的振动.该方法易于工程实现,对控制多管火箭发射系统的振动、提高多管火箭射击的精度具有重要意义.High fire accuracy is one of performance goals of Multiple Launch Rocket System（MLRS）.One of effective methods to improve the fire accuracy with low cost is the vibration control of launcher in MLRS. In this paper,transfer matrix method of multibody system（MSTMM） is used to develop dynamical model of MLRS.Active vibration control law is designed for pulse thruster using quadratic performance index as cost function.In the law,the pulse thruster is taken as an actuator for launcher vibration control.Vibration control system of MLRS launcher is established under the impact of gas jet from rocket motor.A numerical simulation example on vibration controlling of MLRS launcher is given to obtain optimum amplitude of pulse control force and working times of pulse thruster.Numerical results of controlled and uncontrolled vibration response of launcher show that control law in this paper is efficient to reduce launcher vibration.Furthermore,the present method in this paper is easy to realize in practical engineering,and it is important to be used to control launcher vibration so as to improve fire accuracy of MLRS.

关 键 词：多管火箭 多体系统传递矩阵法 振动控制 脉冲推力器 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]