考虑视场角约束的碰撞角控制预设性能制导律  

Prescribed performance guidance law with field-of-view and impact angle constraints

作　　者：李昊键 刘远贺 梁彦刚[1,2] 黎克波 LI Haojian;LIU Yuanhe;LIANG Yangang;LI Kebo(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410072,China;Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions,Changsha 410072,China)

机构地区：[1]国防科技大学空天科学学院,长沙410072 [2]空天任务智能规划与仿真湖南省重点实验室,长沙410072

出　　处：《航空学报》2023年第15期452-466,共15页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12002370)。

摘　　要：针对导弹打击非机动目标问题,提出一种基于预设性能控制理论且满足导引头视场角约束的碰撞角控制制导律。首先,设计一种预设时间性能函数,以实现对跟踪误差收敛时间和上下界的直接设置,并通过误差转换,将该性能边界约束下的跟踪误差控制问题转化为无约束稳定控制问题;其次,采用纯比例导引项加偏置项的制导模型,基于最优误差动力学方法设计偏置制导项,以控制转换误差使其有界,并保证跟踪误差总在性能边界内收敛,从而实现终端碰撞角约束;进一步基于所提制导律,对性能函数中的参数进行深入分析,给出合理取值范围;然后考虑导引头视场受限情况以及移动目标场景,分别引入辅助函数和预测命中点概念对制导律进行改进,以实现视场角约束与打击移动目标的拓展。最后通过数值仿真,验证了所提制导律的有效性。To address the problem of guided missiles against non-maneuvering targets,a prescribed performance guidance law with seeker Field-of-View(FOV)and impact angle constraints is proposed.Firstly,a prescribed time performance function is designed to enable direct setting of the convergence time,the upper and lower bounds of the tracking error.Through error transformation,the tracking error control problem under performance boundary con⁃straints is transformed into an unconstrained stable control problem.Secondly,the guidance law is designed as the sum of a pure proportional guidance term and a bias term.The bias term is derived based on the optimal error dynam⁃ics method to control the transformation error within a bound,ensure that the tracking error consistently converges within the performance boundary,and ultimately achieve terminal impact angle constraint.Furthermore,based on the proposed guidance law,the in-depth analysis of the parameters in the performance function is conducted,and reason⁃able parameters ranges are provided.Moreover,considering seeker FOV limitation and moving target scenario,an auxiliary function and the predicted interception point concept are introduced to improve the guidance law respectively,which realize the FOV constraint and the extension of proposed law against moving target.Finally,the effectiveness of the proposed guidance law is verified through numerical simulations.

关 键 词：导弹 碰撞角控制 预设性能控制 最优误差动力学 视场角约束 预测命中点 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]