用侧推力矢量控制技术提高火箭弹射击精度  

Investigation about Improving Precision of Rocket-projectile Using Lateral Push Vector

作　　者：赵捍东[1] 王芳[1] 刘庆上[1] 

机构地区：[1]中北大学教育部仪器科学与动态测试重点实验室

出　　处：《华北工学院学报》2005年第2期96-99,共4页Journal of North China Institute of Technology

摘　　要：　控制弹道偏差量以提高火箭弹的射击精度.建立了有控弹道的动力学方程,给出了侧推力矢量发动机点火控制逻辑.当实测弹道质心位置偏离理想弹道达到一定域值时,某个发动机被点火,提供一次或多次恒定的控制力,对弹道进行控制,以提高火箭弹的射击精度.模型弹外弹道仿真对比时,将主动段末速度和风视为符合正态分布的随机量.结果表明:火箭弹落点的圆概率误差减小了11%,说明本文提出的脉冲点火控制算法是可行的.In this thesis, the technique of improving the precision of rocket-projectile by controlling trajectory error has been investigated. After building up controllable trajectory dynamics equation, control logic of lateral push vector motor ignition is established. A number of pulse motors are located on the muzzle of the rocket-projectile, and can provide a set of constant correct forces in order to improve the precision of rocket-projectile. In simulation example contrast, the powered end velocity and wing are considered to obey normal distribution, and the result indicates that the circular error probable is reduced 11%. The feasibility of the method about lateral push vector motor firing control logic has been proved.

关 键 词：火箭弹 射击精度 侧推力矢量控制 脉冲点火控制 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程]