航空学报 > 2022, Vol. 43 Issue (1): 324799-324799   doi: 10.7527/S1000-6893.2020.24799

基于虚拟视角约束的机动目标拦截制导方法

王亚宁1,2, 王辉1,2, 林德福1,2, 袁亦方3   

  1. 1. 北京理工大学 宇航学院, 北京 100081;
    2. 北京理工大学 无人机自主控制技术北京市重点实验室, 北京 100081;
    3. 中国人民解放军63961部队, 北京 100012
  • 收稿日期:2020-09-27 修回日期:2020-11-23 出版日期:2022-01-15 发布日期:2020-11-13
  • 通讯作者: 王辉 E-mail:wanghuibit@bit.edu.cn
  • 基金资助:
    国家自然科学基金(U1613225);"高动态导航技术北京市重点实验室"的开放课题基金(HDN2020101)

Guidance method for maneuvering target interception based on virtual look angle constraint

WANG Yaning1,2, WANG Hui1,2, LIN Defu1,2, YUAN Yifang3   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
    2. Beijing Key Laboratory of UAV Autonomous Control, Beijing Institute of Technology, Beijing 100081, China;
    3. Unit 63961 of Chinese People’s Liberation Army, Beijing 100012, China
  • Received:2020-09-27 Revised:2020-11-23 Online:2022-01-15 Published:2020-11-13
  • Supported by:
    National Natural Science Foundation of China(U1613225); Open Project Fund of "Beijing Key Laboratory of High Dynamic Navigation Technology"(HDN2020101)

摘要: 为使导弹能够以一定的末端攻击角度对机动目标进行拦截,提出了一种带有终端虚拟视角约束以及终端视线角约束的机动目标拦截制导方法。基于速度系各运动矢量之间的变换关系,建立了虚拟相对运动坐标系下的非线性模型,并将线性模型中多项式制导的思想创新性地引入到非线性模型中,通过末端虚拟视角约束以及末端视线角约束对关于弹目距离的多项式虚拟控制量进行求解,并根据虚拟矢量与运动矢量之间的变换关系得到速度系下的加速度指令表达式。针对不同制导系数、不同末端攻击角度及不同类型的机动目标等条件进行了仿真验证,同时与弹道成型制导律进行了仿真对比。仿真结果表明,所提出的制导律可以使导弹以期望的攻击角度拦截机动目标,末端虚拟视角收敛为零,避免了末端指令饱和现象。

关键词: 相对运动, 虚拟视角约束, 视线角约束, 多项式制导, 机动目标, 最优制导

Abstract: To enable the missile to intercept one maneuvering target with a certain terminal attack angle, a guidance method for interception of the maneuvering target with terminal virtual look angle and terminal line-of-sight angle constraints is proposed. According to the transform relationship between the motion vectors in the velocity coordinates system, the nonlinear model of relative motion in the virtual coordinates system is established. Then, the thought of polynomial guidance in the linear model is introduced into the nonlinear model creatively. Through the constraints of the terminal virtual look angle and the terminal line-of-sight angle, the solution of the polynomial virtual control variable of the distance between the missile and the target is derived. Finally, according to the transformation relation between the virtual vectors and the motion vectors, the acceleration command expression in the velocity coordinates system is obtained. Simulations under the conditions of different guidance coefficients, terminal attack angles and types of maneuvering targets are carried out to verify the method proposed. The simulation results are compared with those of the optimal guidance law of Trajectory Shaping Guidance. Simulation results show that the proposed guidance lawallows the missile to intercept the maneuvering target with a desired attack angle and the terminal virtual look angle converges to zero, which can avoid terminal command saturation.

Key words: relative motion, virtual look angle constraint, constraint of line-of-sight angle, polynomial guidance, maneuvering target, optimal guidance

中图分类号: