摘要
针对高超声速飞行器俯冲段制导控制问题,提出了一种基于李代数和增量非线性动态逆的制导控制系统联合设计方法。将飞行器在俯冲段的制导目标转换为需求视线坐标系约束,在李群上建立了以当前视线坐标系与需求视线坐标系转换矩阵变化率表示的飞行器与目标的相对运动模型,同时建立以欧拉运动方程表示的飞行器姿态运动模型。针对李群上建立的相对运动方程,基于SO(3)上的广义PD控制方法设计了制导律,并针对姿态运动方程借助增量非线性动态逆方法设计了对气动干扰具有强鲁棒的姿态控制律。通过蒙特卡洛仿真试验,验证了制导控制系统联合设计方法的有效性和鲁棒性。
A joint design method of guidance and control system based on Lie algebra and incremental nonlinear dynamic inversion is proposed for hypersonic vehicle in dive phase. The guidance target of the aircraft in the dive phase is converted into the constraint of the required line-of-sight(LOS) coordinate system.The relative motion model of the aircraft and the target expressed by the rate of the transformation matrix between the current LOS coordinate system and the required LOS coordinate system is established on the Lie group, and the attitude motion model of aircraft is established by Euler motion equation. For the relative motion, the guidance law is designed based on the generalized PD control method on SO(3), and the attitude control law with strong robustness to aerodynamic disturbances is designed for the attitude motion using the incremental nonlinear dynamic inversion method. The effectiveness and robustness of the joint design method of guidance and control system are verified by the Monte Carlo simulation.
作者
刘达
赵暾
张占月
Liu Da;Zhao Tun;Zhang Zhanyue(Graduate School,Space Engineering University,Beijing 101416,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Space Security Research Center,Space Engineering University,Beijing 101416,China)
出处
《战术导弹技术》
北大核心
2023年第5期97-103,123,共8页
Tactical Missile Technology
关键词
高超声速飞行器
俯冲段
联合设计
制导控制
李代数
增量非线性动态逆
蒙特卡洛仿真
hypersonic vehicle
dive phase
joint design
guidance and control system
Lie alge-bras
incremental nonlinear dynamic inverse
Monte Carlo simulation
