变循环发动机模型参考自适应滑模控制方法研究  

Research on Variable Cycle Engine Control Based on Model Reference Adaptive Sliding Mode Control Method

作　　者：肖红亮 李华聪[1] 李嘉[1] 符江锋[1] 彭凯[1] Xiao Hongliang;Li Huacong;Li Jia;Fu Jiangfeng;Peng Kai(School of Power and Energy,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2018年第5期824-830,共7页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(51506176);航空动力基金(6141B090302)资助

摘　　要：针对变循环航空发动机存在系统不确定性及外部干扰条件下的多变量输出量跟踪控制器设计问题,给出了一种基于LQR方法的增广模型参考自适应滑模控制方法。首先,将模型进行增广,并通过采用最优LQR方法设计参考模型,向控制器提供参考状态。然后,在状态跟踪滑模控制方法的基础上基于李亚普诺夫函数严格稳定条件推导了系统摄动矩阵上界估计和外部干扰上界估计的自适应律。最后,控制器在不确定性和外部干扰条件下,实现系统跟踪误差渐近为零的目标。以一种带CDFS的双外涵变循环发动机为对象进行控制器仿真验证,结果表明:基于LQR方法的增广模型参考自适应滑模控制方法可解决传统滑模控制方法中需要预先指定参考状态的问题,同时改善了变循环发动机系统不确定性和外部干扰条件下的控制效果,有效实现了对控制指令的跟踪,达到了以下控制效果:不同工况下的稳态控制误差均小于0.1%,系统超调量小于0.5%,调节时间小于1 s,均符合发动机控制系统技术要求。As to solve the problem of multivariable output tracking control of variable cycle engine under system uncertainties and external disturbances,an augmented model reference adaptive sliding mode control method based on LQR method was developed.Firstly,the model is augmented and the reference state is provided to the controller by designing the reference model using the optimal LQR method.Then,based on the state tracking sliding mode control method,the adaptive law is derived based on the strict stability condition of Lyapunov function to estimate the upper bound of the system perturbation matrix and the upper bound of the external disturbances.Finally,the controller achieves the asymptotic zero tracking error of the system under the conditions of uncertainty and external disturbance.The simulation results showed that the LQR-based augmented model reference adaptive sliding mode control method can solve the problem that the traditional sliding mode control method needs to specify the reference state in advance and improve the control performance of the variable cycle engine control with system uncertainties and external disturbance.The tracking of the control command is effectively achieved and the steady-state and dynamic performance are improved.The steady-state control errors under different conditions are less than 0.1%,the system overshoot is less than 0.5%,and the adjustment time is less than 1s,which conformed to the requirements of the aero engine control system technology.

关 键 词：变循环航空发动机 多变量控制 不确定性 模型参考 自适应滑模控制 控制器 李雅普诺夫函数 

分 类 号：V235.16[航空宇航科学与技术—航空宇航推进理论与工程]