基于迭代反馈调参的伞翼飞行器无模型自适应控制方法研究  

Study of IFT-MFAC Method for Parafoil Systems

作　　者：赵令公 贺卫亮[2] 赵志高 刘志君 Zhao Linggong;He Weiliang;Zhao Zhigao;Liu Zhijun(Chinese Aeronautical Establishment,Beijing 100012,China;Beihang University,Beijing 100191,China)

机构地区：[1]中国航空研究院,北京100012 [2]北京航空航天大学,北京100191

出　　处：《航空科学技术》2023年第1期51-60,共10页Aeronautical Science & Technology

摘　　要：针对伞翼飞行器强非线性特点,本文使用基于数据驱动的控制方法——基于迭代反馈调参的无模型自适应控制方法(IFT-MFAC)设计伞翼飞行器控制系统,该方法在构建过程中仅利用系统的输入和输出数据,不需要构建动力学模型。本文首先介绍了无模型自适应控制方法(MFAC)的构建过程,并进行了简洁的稳定性分析,然后采用迭代反馈调参方法对无模型自适应控制方法的两个步长因子进行迭代调参。为验证该方法的控制效果,对IFT-MFAC与PID控制、主动抗干扰控制(ADRC)和MFAC进行了一系列仿真对比,结果显示,IFT-MFAC控制器在复杂环境下的控制效果更好,尤其是在随机扰动环境下对折线轨迹的跟踪效果。According to the strong nonlinear characteristics of the parafoil aircraft,this paper uses a data-driven control method:a model free adaptive control method based on iterative feedback tuning(IFT-MFAC)method for parafoil systems which only input/output(I/O)data are needed during construction.In this paper,the MFAC construction process and stability analysis are explained,and then the IFT method is used to tune the two stepping factors of the MFAC method.A six-degree-of-freedom(DOF)dynamic parafoil system model is built to assess the performance of the method in a simulation with disturbances added to imitate real flights.A series of simulations are designed to verify the performance of the IFT-MFAC controller compared with the PID control method,the active disturbance rejection control(ADRC)method,and the MFAC method.

关 键 词：伞翼飞行器 无模型自适应控制 迭代反馈调参 数字仿真 控制器 

分 类 号：V249.122[航空宇航科学与技术—飞行器设计]