摘要
为提高攻击时间控制制导律的鲁棒性和工程适应性,以弹目拦截几何关系为基础,采用滑模技术设计了一种带导引头视场角约束的无奇点攻击时间控制制导律。通过Lyapunov理论证明了该制导律的稳定性和收敛性。理论分析及仿真结果表明:当攻击时间误差变为0 s时,该制导律可演变成纯比例导引律,末端需用过载变化平缓、命中点处为0 g;所设计制导律可有效实现静止目标拦截、多导弹协同攻击等场合的攻击时间控制。
To improve the robustness and engineering adaptability of the impact time control guidance law, a nonsingular impact time control guidance law with seeker s field of view constraint is designed using sliding mode technique based on the geometrical relation of projectile interception. The stability and convergence of the proposed guidance law are proved by Lyapunov theory. The theoretically analyzed and simulated results show that, when the impact time error is zero, the proposed guidance law can evolve into a pure proportional navigation guidance law, and the required terminal acceleration of the proposed guidance law is fairly smooth, converging to zero during interception. The proposed guidance law can be used to effectively control the impact time for stationary target interception and multi-missile cooperative attack.
作者
陈升富
常思江
吴放
CHEN Shengfu;CHANG Sijiang;WU Fang(School of Energy and Power Egineering,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China)
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2019年第4期777-787,共11页
Acta Armamentarii
基金
国家自然科学基金项目(11402117)
关键词
导弹
攻击时间控制
视场角约束
滑模控制
比例导引法
missile
impact time control
field-of-view angle constraint
sliding mode control
proportional navigation law
作者简介
陈升富(1993—),男,硕士研究生。E-mail:chenshengfu@njust.edu.cn;通信作者:常思江(1983—),男,副研究员,硕士生导师。E-mail:ballistics@126.com.
