基于最优制导律的空空导弹制导指令校正算法研究  

Research on Air-to-Air Missile Guidance Command Correction Algorithm Based on Optimal Guidance Law

作　　者：候冰 杜英杰[1] HOU Bing;DU Yingjie(Chengdu Aeronautic Polytechnic,Chengdu 610100,China)

机构地区：[1]成都航空职业技术学院,成都610100

出　　处：《成都航空职业技术学院学报》2024年第1期33-37,79,共6页Journal of Chengdu Aeronautic Polytechnic

基　　金：成都航空职业技术学院校级自然科研项目“基于深度学习的导弹制导指令校正算法研究”(ZZX0623075)。

摘　　要：通过引入校正环节等以提高制导大回路的快速性、减少延迟,从而达到提高系统制导精度的目的。依据弹目相对运动方程,建立了状态空间方程,并利用最优控制理论,在性能指标中考虑降低对剩余飞行时间估计误差的敏感度,同时引入指令校正环节,弥补需用过载和实际过载之间传递函数的时间延迟。仿真表明,该新型制导算法在攻击大机动目标时,综合性能指标是最优的,并且对系统稳定性和带来的负面影响之间取得了良好平衡。By introducing correction links,etc.,the rapidity of the guidance loop and the guidance accuracy of the system are improved.According to the relative motion equation of the projectile,the state-space equation is established,and the optimal control theory is used to reduce the sensitivity to the estimation error of remaining flight time in the performance index,and the command correction link is introduced to make up for the time delay of the transfer function between the required overload and the actual overload.Simulations show that the novel guidance algorithm is optimal in terms of comprehensive performance indexes when attacking large maneuvering targets,and strikes a good balance between system stability and the negative impact it brings.

关 键 词：指令校正 机动目标 最优制导 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]