导弹协同编队H_∞制导律设计  

Design of H_∞ Guidance Law for Missile Cooperative Formation

作　　者：黄伟[1] 徐建城[1] 吴佳斌[2] 吴华兴[3] 

机构地区：[1]西北工业大学电子信息学院,陕西西安710072 [2]西北工业大学自动化学院,陕西西安710072 [3]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《西北工业大学学报》2017年第5期767-773,共7页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(61472441)资助

摘　　要：在导弹协同编队飞行过程中,为使从弹制导系统在满足干扰抑制指标要求的同时,具有良好的动态响应特性,提出一种基于H_∞控制理论的比例积分制导律算法。在三维空间中建立新的领从弹相对运动方程,将领弹加速度信息视为有界扰动,以相对距离和从弹加速度作为状态量和控制量,得到从弹制导系统的状态方程。通过状态变换和系统增广,将从弹制导律设计问题转换为H_∞控制问题,得到满足H_∞性能指标的比例积分控制器,实现了导弹编队队形的生成、跟踪和保持。仿真结果验证了算法的有效性。In the flight process of missile cooperative formation, to meet anti-interference performance and dynamic responsive characteristics of guiding system for following missiles, a proportion-integration guiding law based on H∞ control theory is proposed. By building new equation of relative motion between the leader and the follower in 3D space, considering the leader＇s acceleration as bounded disturbance, and taking relative range and the follower＇s acceleration as the state variable and control variable respectively, the state equation of the follower is derived. State transformation and system augmentation are used to transfer the guiding law design problem into H∞ control problem, and a proportion-integration controller meeting H∞ performance is presented, thus the generation, tracking and keeping of missile formation shape is implemented. Simulation results demonstrate the validity of the arithmetic.

关 键 词：导弹编队 比例积分控制器 鲁棒性 响应特性 制导律 角速度 

分 类 号：V249[航空宇航科学与技术—飞行器设计] TJ765.3[兵器科学与技术—武器系统与运用工程]