不同制导律在减小火箭弹散布中的技术研究  

The Investigation about Using Different Guidance Laws on Improving Impact Point Dispersion of Rocket

作　　者：赵捍东[1] 郭锡福[2] 王芳[1] 刘庆上[1] 

机构地区：[1]华北工学院机械电子工程系,山西太原030051 [2]南京理工大学,南京210094

出　　处：《弹箭与制导学报》2004年第4期45-47,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：利用一组安装在火箭弹头部环向均匀分布的侧向脉冲发动机提供的多次、恒定的控制力,可减小火箭弹落点的散布。文中对二种不同制导律在脉冲发动机点火时序控制逻辑中的应用进行了对比研究,为利用脉冲发动机进行弹道修正提供了技术参考。The impact point dispersion of a rocket can be reduced with a number of distant control impulse provided by lateral jet motors that are located on the nose of the rocket. In the work reported here, two different guidance laws applied to lateral pulse jet firing time logic are compared. The researching result provides the method by which the trajectory of rocket can be corrected by using lateral jet motors.

关 键 词：制导律 火箭弹 弹头 侧向脉冲发动机 弹道 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程] TJ765.3