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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。
The inversion control technique, the preset performance control and the neural network are combined to study the design of the hypersonic vehicle fine attitude controller for cruising flight. The influence of the elastic deformation of the hypersonic vehicle on the attack angle of the flight is considered, and the concept of induced attack angle is introduced to describe the influence of the aeroelasticity on the aircraft. In the case of considering the elasticity, the design of the preset attitude is used to satisfy the requirement of fine attitude control Index requirements, at the same time can take into account the transient performance of the system; the global adjustment of dynamic neural network online approximation induced angle of attack unknown in the equation, the use of Lyapunov stability theory to get the neural network weights, the center point and the impact of the range of adaptive regulation , The robust items are introduced to deal with the influence of the approximation error of the neural network. Finally, the design of the fine attitude controller for the hypersonic vehicle considering the aeroelasticity is finally designed. The stability of the system is proved by Lyapunov stability theory and all the signals in the closed-loop system are bounded. The simulation results show that the designed controller can make the tracking error of the system meet the requirement of the preset performance, so as to realize the fine attitude control.