考虑输入受限的高超声速飞行器非奇异固定时间自适应切换控制  

Singularity-free fixed-time adaptive switching control for hypersonic flight vehicle with input constraints

作　　者：董泽洪 李颖晖[1] 吕茂隆 李哲[1] 裴彬彬 DONG Zehong;LI Yinghui;LYU Maolong;LI Zhe;PEI Binbin(Aviation Engineering School,Air Force Engineering University,Xi’an 710038,China;Graduate School,Air Force Engineering University,Xi’an 710038,China;Air Traffic Control and Navigation School,Air Force Engineering University,Xi’an 710051,China)

机构地区：[1]空军工程大学航空工程学院,陕西西安710038 [2]空军工程大学研究生院,陕西西安710038 [3]空军工程大学空管领航学院,陕西西安710051

出　　处：《系统工程与电子技术》2023年第5期1476-1488,共13页Systems Engineering and Electronics

基　　金：国家自然科学基金(62103440,62003368)资助课题。

摘　　要：考虑了高超声速飞行器输入饱和、气动参数不确定性以及跟踪误差收敛速率慢等问题,设计了一种抗输入饱和非奇异固定时间自适应切换控制策略。首先将高超声速飞行器纵向动力学模型分解为速度子系统和高度子系统,然后分别设计非奇异固定时间跟踪控制器。为解决传统固定时间控制器中存在的奇异值问题,设计了一种新的可微切换函数,该函数以跟踪误差为判定量对控制律进行切换,保证了虚拟控制律的可微性以及反步设计的可行性。针对高超声速飞行器的输入饱和问题,设计了一种固定时间辅助误差补偿系统,将补偿信号的误差收敛速度由指数收敛提高到固定时间收敛。而后,利用Lyapunov定理证明了速度跟踪误差和高度跟踪误差以及逼近器的估计误差在固定时间内收敛至原点的任意小邻域内。最后,通过仿真验证了所提控制器的有效性及优越性。A singularity-free fixed-time adaptive switching control strategy is proposed for hypersonic flight vehicles subject to input saturation,uncertainties of aerodynamic parameters and slow convergence rate of tracking errors.Firstly,the longitudinal dynamics model of hypersonic flight vehicles is decomposed into velocity subsystem and altitude subsystem,then the singularity-free fixed-time tracking controller is designed separately.In order to solve the singular value problem of traditional fixed-time controller,a new differentiable switching function is designed,which switches control laws with tracking error as the decision quantity,ensuring the differentiability of virtual control laws and the feasibility of back-stepping design.Aiming at the input saturation problem of hypersonic flight vehicles,a fixed-time auxiliary error compensation system is designed,which improves the error convergence rate of compensation signals from exponential convergence to fixed-time convergence.Then,with the help of the Lyapunov theorem,it is proved that the velocity tracking error,altitude tracking error and estimation error of approximator converge to arbitrarily small neighborhood of origin within fixed-time.Finally,simulations results validate the effectiveness and superiority of the proposed controller.

关 键 词：高超声速飞行器 固定时间稳定 输入饱和 非奇异切换控制 神经网络 

分 类 号：V448[航空宇航科学与技术—飞行器设计]