【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.更多还原

【Abstract】 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.更多还原