抗目标大机动的制导指令校正算法研究  

Study on Correction Proportional Guidance Law Against High Maneuvering Target

作　　者：候冰 张金鹏[1] 曹有亮[1] 赵阳[1] Hou Bing;Zhang Jinpeng;Cao Youliang;Zhao Yang(China Airborne Missile Academy, Luoyang 471009, China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2018年第2期29-33,共5页Aero Weaponry

基　　金：航空科学基金项目(20160112002)

摘　　要：针对寻的末制导中对抗大机动目标的情况,同时考虑导弹制导系统动力学及重力影响,提出了一种新的制导算法,即在制导回路中加入指令校正环节。该制导算法通过引入校正环节,并在制导律中引入导弹加速度,可以弥补弹体动态响应引起的延迟,减小脱靶量,在一定程度上提升系统快速性,提高制导控制系统对抗目标大机动的能力。Considering the high maneuvering target in homing terminal guidance, the dynamic of missile guidance system and the i-fl]uence of gravity are also taken into account, so this paper gives a new guidance arithmetic, which adds instruction correction link in the guidance loop. By adding the instruction correction link to reduce miss distance, and introducing the actual acceleration of the missile into the guidance law, the rapidity of the system can be improved to a certain extent, and the ability of the guid- ance and control system against the high maneuvering target can be strengthened.

关 键 词：目标机动 动力学滞后 制导律 导弹加速度 校正算法 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V438[航空宇航科学与技术—航空宇航推进理论与工程]