利用侧向脉冲力减小火箭弹散布的技术研究  

The Investigation about Improving Impact Point Dispersion of Rocket-projectile Using Lateral Pulse Jets

作　　者：赵捍东[1] 刘庆上[2] 王芳[2] 

机构地区：[1]南京理工大学,江苏南京210094 [2]华北工学院仪器科学与动态测试实验室,山西太原030051

出　　处：《弹箭与制导学报》2004年第2期49-50,57,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中对利用侧向脉冲力减小火箭弹散布的技术进行了研究。一组脉冲发动机安装在火箭弹的头部,在垂直于弹轴的平面内环向均匀分布,可提供多次、恒定的控制力,以减小火箭弹的落点散布。通过模型弹的外弹道仿真对比,落点的横向散布距离减小了54.8%及73.3%,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 the impact point dispersion of a rocket-projectile can be reduced with a ring of appropriately sized lateral pulse jets has been investigated. A number of jet motors are located on the nose of the rocket-projectile, and can provide a set of constant correct forces, in order to reduce the impact point dispersion. An individual jet motor is distributed equably on vertical plane with the projectile axis. In the example case, the yaw dispersion error is reduced 54.8% or 73.3%. A according to exterior ballistic numerical simulation's result, the feasibility of the method about lateral pulse jet motor firing control logic has been proved.

关 键 词：火箭弹 脉冲发动机 侧喷 算法 仿真 

分 类 号：TJ415.9[兵器科学与技术—火炮、自动武器与弹药工程]