摘要
将反演控制技术、预设性能控制和神经网络相结合,研究设计巡航飞行的高超声速飞行器精细姿态控制器。研究中考虑了高超声速飞行器弹性形变对飞行攻角的影响,引入诱发攻角的概念来刻画气动弹性对飞行器的影响;在考虑弹性的情况下,利用预设性能的设计来满足精细姿态控制的指标要求,同时可以兼顾系统的瞬态性能;利用全局调节动态神经网络在线逼近诱发攻角方程中的未知项,利用Lyapunov稳定性理论得到神经网络权值、中心点和影响范围的自适应调节律,引入鲁棒项来处理神经网络逼近误差的影响,最终设计出考虑气动弹性情况下的高超声速飞行器预设性能精细姿态控制器。通过Lyapunov稳定性理论证明了系统的稳定性以及闭环系统所有信号均有界,仿真分析验证了所设计的控制器能够使系统跟踪误差满足预设性能的要求,以此实现姿态精细控制。
A fine attitude controller for hypersonic cruise vehicle is designed by combining the backstepping technique,prescribed performance control and neural network. The influence of elastic deformation of hypersonic vehicle on angle of attack is taken into consideration. The effect of aeroelasticity on hypersonic vehicle is described by using the induced angle of attack. The index of fine attitude control is satisfied by the design of prescribed performance in consideration of aeroelasticity,and the transient performance of hypersonic vehicle is assured. The unknown terms of the induced angle-of-attack equations are approximated online by using the fully tuned dynamic neural networks,and the adaptive laws of weight,core and scope of influence of the neural networks are designed by Lyapunov theory. The robust term is induced to solve the approximate errors of the neural networks. A fine attitude controller with prescribed performance for hypersonic vehicle in considering the aeroelasticity is designed. The stability of system and all the signals in the closed-loop system bounded are proved by Lyapunov theory. The simulated results show that the controller can make the tracking errors satisfy the prescribed performance,and the fine attitude control can be implemented.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2017年第3期501-511,共11页
Acta Armamentarii
基金
航空科学基金项目(20155884012)
关键词
兵器科学与技术
高超声速飞行器
气动弹性
预设性能
精细姿态控制
诱发攻角
ordnance science and technology
hypersonic vehicle
aeroelasticity
prescribed performance
sophisticated attitude control
induced angle of attack
