基于预测控制的寻的导弹末制导律研究  

The Terminal Guidance Law Based on Predictive Control for Homing Missile

作　　者：周卫文[1] 史鲲[2] 梁晓庚[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]西北工业大学自动化学院,西安710129

出　　处：《弹箭与制导学报》2013年第4期4-8,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为提高寻的导弹末制导性能,解决传统比例导引律在目标大机动的情况下,制导性能较差的问题,文中通过对一个简化了的二维导弹目标遭遇模型的研究,基于连续时间预测控制理论的输出跟踪方法,给出了一种寻的导弹最优末制导规律,并对其稳定性进行了分析。该预测制导规律不但解决了反馈线性化制导律在使用条件上的限制问题,而且通过数字仿真表明,所设计的预测制导规律比传统的比例导引规律具有更好的制导性能。特别是在得出的加速度指令方面,具有很大优势。Traditional proportional navigation guidance law is weak in guidance ability against highly maneuvering target. In order to improve the performance of homing missile＇ s terminal guidance, one simplified model of two-dimensional engagement was taken as the study object; An optimal terminal guidance law for homing missile based on the output tacking formulation of tF/e continuous time predictive con- trol theory was designed. The results of digital simulation show that the designed predictive guidance law has better guidance property in comparison with the conventional PN guidance, especially in the aspect of the missile＇ s commanded acceleration.

关 键 词：寻的导弹 末制导 预测控制 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]