摘要
针对一个吸气式高超声速飞行器模型,研究了其鲁棒自适应控制方法并进行了稳定性分析。针对高超声速飞行器的非最小相位特征,通过输出重定义的方法使非最小相位系统的不稳定零动态变为渐近稳定。采用反馈线性化方法设计控制器,实现对速度信号和航迹角信号的稳定跟踪,同时采用切换控制方法消除系统不确定性带来的影响,提高系统的鲁棒性。稳定性分析结果证明系统具有公共李雅普诺夫函数,且所有状态量均能收敛到原点附近的一个小邻域内。仿真结果表明,所设计的控制系统能够有效跟踪参考轨迹,且在给定的有界连续不规则变化模型不确定性和外界干扰范围内也具有良好的跟踪性能。
Considering a model of air-breathing hypersonic vehicle,a robust adaptive control strategy and stability analysis is presented.In light of the non-minimum phase property of hypersonic vehicle,output redefinition is carried out to make the unstable zero-dynamics exhibit an asymmetrically stable behavior.To achieve the stable tracking of both velocity and flight-path angle references,a feedback linearization control method is adopted.Moreover,a switching control method is employed to eliminate the effect of model uncertainties,thus improving the robust of the system.The stability analysis shows that the control system has a common Lyapunov function and all of the states are stable.Finally,the simulation results show that the designed controller can track the reference trajectories effectively in given disturbances.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2014年第3期331-339,共9页
Journal of Astronautics
基金
国家自然科学基金(60974014,61074027)
