不同制导律在脉冲式弹道修正灵巧弹上的应用  

Application of Different Guidance Laws to Pulse Trajectory Corrected Smart Munitions

作　　者：葛健全[1] 贾天宝[1] 张晓今[1] 杨涛[1] 寇保华[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹箭与制导学报》2008年第4期182-185,218,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：研究两种制导律在脉冲式弹道修正灵巧弹上的应用。建立基于零效脱靶量概念的两种末制导律——弹体追踪和脉冲比例导引,并给出对应的脉冲发动机点火控制方法。采用6自由度动力学模型进行仿真,计算结果表明在理想情况下文中方法可以实现对地面固定目标精确打击。最后结合算例指出两种制导方案的特点,为总体设计提供有益的参考。The application of two kinds of guidance law to the terminal guidance stage of the pulse trajectory corrected smart munitions was researched. The pulsed proportional navigation （PPN） guidance and attitude pursuit guidance （APG） by the concept of zero effort miss （ZEM） were established, and the corresponding ignition control strategy of the pulse jet was presented. By using six-freedom-degree ballistic equations, the two cases of PPN and APG were investigated. Result of simulation indicates that under ideal circumstances, the method given by this paper is practicable and correct, and the analysis of the two schemes can. provide helpful references for the future design.

关 键 词：弹道修正 脉冲发动机 零效脱靶量 弹体追踪 脉冲比例导引 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]