高超声速飞行器轨迹凸优化与跟踪制导方法  

Trajectory Convex Optimization and Tracking Guidance for Hypersonic Vehicle

作　　者：王吉瑞 夏丰领 Wang Jirui;Xia Fengling(Faculty of Civil Aviation and Aeronautics,Kunming University of Science and Technology,Kunming 650500,China)

机构地区：[1]昆明理工大学民航与航空学院,昆明650500

出　　处：《航空兵器》2024年第4期57-63,共7页Aero Weaponry

摘　　要：为了提升高超声速飞行器无动力下滑段在制导探测信息不完整或探测设备被干扰情况下的突防生存性能,建立了下滑段高超声速飞行器的动力学模型。采用序列凸优化方法对弹道进行优化,在满足终端约束的前提下具有更优的控制能量消耗,同时保证了末端加速度收敛以及良好的计算性能。轨迹跟踪部分采用线性LQR控制器设计,稳定跟踪规划弹道。相比与传统最优控制的角度约束的制导律,下滑段采用轨迹规划-轨迹跟踪的方法,无需线视线角度信息,可在下滑段结束后再引入目标相对角度信息,在复杂电磁情况下具有更强的生存能力。In order to improve the penetration and survival performance of hypersonic vehicles in the unpowered glide section under incomplete guidance and detection information or interference of detection equipment,this paper establishes a dynamic model of hypersonic vehicles in the glide section.The trajectory is optimized using sequential convex optimization method,which has better control energy consumption while satisfying terminal constraints,as well as ensuring terminal acceleration convergence and good computational performance.The trajectory tracking part adopts a linear LQR controller design to stably track and plan the trajectory.Compared with the traditional optimal control gui-dance law with angle constraints,the sliding phase adopts a trajectory planning-trajectory tracking method without the need for line of sight angle information.The relative angle information of the target can be introduced after the sliding phase ends,which has stronger survival performance in complex electromagnetic situations.

关 键 词：高超声速飞行器 下滑段 序列凸优化 LQR控制器 末制导 

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