火箭弹控制系统与弹体发生弹性耦合的条件分析  

Analysis of the Elastic Coupling Between the Control and Body of a Spinning Rocket Having High Length to Diameter Ratio

作　　者：朱伯立[1] 杨树兴[1] 胡勇[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2004年第7期587-591,共5页Transactions of Beijing Institute of Technology

基　　金：教育部跨世纪人才培养计划基金项目(10076021)

摘　　要：用数字仿真计算和理论分析方法,研究大长细比低速旋转火箭弹在控制段飞行中,陀螺仪输出信号中产生非正常频率干扰信号的因素.仿真结果表明,火箭弹弹体的弹性振动导致弹体结构与控制发生耦合.耦合的出现与初始扰动的大小以及弹体的固有频率有明显关系;耦合一般发生在控制段飞行的后半段;陀螺仪敏感到的干扰信号的频率为火箭弹旋转频率与弹体一阶固有频率之和.The factors are studied which lead to a disturbance of abnormal frequency added into the gyro-output signal during the control section flight of the rocket in some special conditions, when the spinning rocket is of high length to diameter ratio. Numerical simulation and theoretical analysis were used. The results show that this kind of disturbance is caused by the coupling between the control system and the flexible bending of the rocket body. Occurrance of coupling is evidently related to the magnitude of initial disturbance and the inherent frequency of rocket body. This kind of coupling generally happens in the later stage of the control section flight of the rocket. The frequency of the disturbance in the output signals of gyro is equal to the sum of the frequency of rocket rotation and the first rank inherent frequency of the rocket body.

关 键 词：火箭弹 弹性振动 弹性耦合 

分 类 号：TJ765.21[兵器科学与技术—武器系统与运用工程]