脉冲发动机对姿态稳定的近程反坦克火箭弹控制效果的研究  

Study on Pulse Jets' Control Effect on Short-range Antitank Rockets Using Attitude Stabilization

作　　者：倪慧[1] 杨树兴[1] 佘浩平[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《弹箭与制导学报》2006年第S4期759-762,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为研究近程反坦克火箭弹采用脉冲发动机进行姿态稳定控制的效果,文中提出脉冲点火算法和脉冲发动机的等效合力模型,通过弹道仿真分别研究了初始扰动、推力偏心、常值风等主要干扰因素作用下姿态稳定系统的控制效果。研究结果表明,姿态稳定控制对初始扰动、推力偏心等干扰因素造成的弹道偏差能进行有效的控制,但对常值风干扰造成的弹道偏差无修正能力。因此,可以采用姿态隐定方式提高近程反坦克火箭弹的射击精度,但发射时必须提供气象条件保障。To study the attitude stabilization control effect on short-range antitank rockets using pulse jets.in this paper the pulse ignition arithmetic and the equivalent resultant force model of pulse jets are brought forward,and ballistic sim- ulation models are set up respectively under primary disturbance factors such as constant winds,initial disturbances. off-center thrust and so on.Results show that the attitude stabilization control is effective for trajectory errors caused by initial disturbances,off-center thrust,while it is ineffective for ones caused by constant winds.Therefore,the preci- sion of short-range antitank rockets can be improved by the attitude stabilization project on condition that the weather data is provided before shooting.

关 键 词：姿态稳定 火箭弹 脉冲发动机 脉冲点火算法 干扰 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程]