侧推矢量在提高火箭弹射击精度的技术研究  

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

作　　者：赵捍东[1] 郭锡福[1] 王芳[1] 刘庆上[1] 

机构地区：[1]南京理工大学

出　　处：《弹箭与制导学报》2005年第2期72-74,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中首先建立了有控弹道的动力学方程,给出了侧推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(CEP)减小了11%,说明文中提出的脉冲点火控制算法是可行的。In this thesis, the technique that precision of rocket-projectile can be improved with controlling trajectory error has been investigated. At first, to build up controllable trajectory dynamics equation, and to establish control logic of lateral push vector motor ignition. A number of pulse motors are located on the nose 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 is considered to obey normal distributing, the result indicates that the circular error probable(CEP) is reduced 11%. The feasibility of the method about lateral push vector motor firing control logic has been proved.

关 键 词：射击精度 火箭弹 矢量 技术 动力学方程 发动机点火 圆概率误差 控制逻辑 理想弹道 质心位置 弹道仿真 正态分布 控制算法 脉冲点火 控制力 随机量 主动段 落点 

分 类 号：TJ22[兵器科学与技术—武器系统与运用工程] TJ415