基于参数摄动模型的航空发动机鲁棒弹性自适应控制  

Robust Resilient Adaptive Control of Aero-engine Based on Parametric Perturbation Model

作　　者：马静[1] 曹督 麻莉莉[1] MA Jing;CAO Du;MA Lili(College of Power and Energy,Northwest Polytechnic University,Xi'an,Shaanxi 710072,China;AECC Xi´an Engine Control Co.,Ltd.,Xi'an,Shaanxi 710077,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航发西安动力控制科技有限公司,陕西西安710077

出　　处：《控制与信息技术》2023年第2期1-6,共6页CONTROL AND INFORMATION TECHNOLOGY

基　　金：航空发动机及燃气轮机基础科学中心项目(P2022-DB-V-001-001)。

摘　　要：航空发动机特性随飞行条件和工作状态变化,在复杂工作环境中同时存在模型不确定性和控制器自身参数变化问题,很大程度上影响整个飞行包线的控制性能。为此,文章提出一种基于参数摄动模型的航空发动机鲁棒弹性自适应控制方法。其首先建立了航空发动机参数摄动结构化模型;然后针对被控对象模型的不确定性和控制器增益的摄动,利用李雅普诺夫稳定性(Lyapunov stability)理论和线性矩阵不等式约束,设计了增益摄动有界但上界未知时的鲁棒弹性自适应控制律,将控制器的设计问题转化为线性矩阵不等式的可行解问题,使控制器的设计仅依赖线性矩阵不等式解矩阵的存在性,并证明了算法的稳定性。在此基础上,文章对飞行包线内发动机不同工作状态进行控制仿真验证。结果显示,调节时间小于1.8 s,超调量小于5%,这表明所设计控制器具有良好的稳定性和控制性能。Aero-engine´s characteristics vary with flight conditions and operating states.In complex operating environments,both model uncertainty and controller parameter variation exist simultaneously,which greatly affect the control performance in the whole flight envelope.Therefore,a robust elastic adaptive control method based on parameter perturbation model is proposed in this paper.The structural model of aero-engine parameter perturbation is established.Then,aiming at the uncertainty of the controlled object model and the perturbation of controller gain,the robust resilient adaptive control law is designed when the gain perturbation is bounded but the upper bound is unknown by using Lyapunov stability theory and linear matrix inequality constraints,and the controller design problem is transformed into a feasible solution problem of linear matrix inequalities.The controller design only depends on the existence of the solution matrix of linear matrix inequalities,and the stability of the algorithm is proved.On this basis,the control simulation of different operating states of the engine in the flight envelope is carried out.The simulation results show that the adjustment time is less than 1.8 s and the overshoot is less than 5%,which indicates good stability and control performance of the designed controller.

关 键 词：航空发动机 参数摄动结构化模型 增益摄动 鲁棒弹性自适应控制 线性矩阵不等式 

分 类 号：TP13[自动化与计算机技术—控制理论与控制工程]