面向战机大迎角机动过程的智能学习控制  

Intelligent Learning Control for Fighter Maneuvers at High Angle of Attack

作　　者：于目航 王霞 杨林 许斌[1] YU Mu-Hang;WANG Xia;YANG Lin;Xu Bin(School of Automation,Northwestern Polytechnical University,Xi'an 710072;School of Control Science and Engineering,Shandong University,Jinan 250061;Chengdu Aircraft Design&Research Institute,Chengdu 610041)

机构地区：[1]西北工业大学自动化学院,西安710072 [2]山东大学控制科学与工程学院,济南250061 [3]成都飞机设计研究所,成都610041

出　　处：《自动化学报》2024年第4期719-730,共12页Acta Automatica Sinica

基　　金：国家自然科学基金(61933010);陕西省自然科学基础研究计划(2023JC-XJ-08)资助。

摘　　要：针对战机大迎角动力学呈现的强非线性、气动不确定和通道耦合特性,提出了一种基于智能学习的自适应机动跟踪控制方法.通过将通道耦合视为集总扰动的一部分,把模型分解为迎角子系统、侧滑角子系统和滚转角速率子系统.采用神经网络估计不确定,设计跟踪误差反馈与集总干扰估计前馈相结合的控制器获取期望操纵力矩,并基于串接链分配方法求解气动舵偏角和推力矢量偏角.对于神经网络权重更新,构建预测误差表征集总干扰的估计性能,结合跟踪误差设计复合学习更新律.基于李雅普诺夫方法证明了闭环系统的一致最终有界稳定性.针对眼镜蛇机动和赫伯斯特机动指令进行了仿真验证和抗干扰参数拉偏测试,结果表明所提方法具有较高的机动指令跟踪精度和鲁棒性能.Considering the strong nonlinearity,aerodynamic uncertainty and channel coupling characteristics of fighter dynamics at high angle of attack,an adaptive maneuver tracking control is proposed based on intelligent learning.By taking the channel coupling into a part of the total disturbance,the model is decomposed into the angle of attack subsystem,the sideslip angle subsystem and the roll angle rate subsystem.Neural networks are used to estimate aerodynamic uncertainties,and the controllers using tracking error feedback and total disturbance estimation feed-forward are designed to obtain the desired control torque.Then the aerodynamic surface deflection and thrust vector deflection are calculated based on daisy chain method.For the neural network weight update,the prediction error is constructed to reflect the estimation performance of the total disturbance,and the composite learning update law is designed combining with the tracking error.The uniformly ultimate boundedness of the closed-loop system is proved based on the Lyapunov method.Simulation and anti-disturbance parameter deviation tests are carried out for the Cobra and Herbst maneuvers,and the results show that the proposed method presents high tracking accuracy and more robust performance.

关 键 词：战机 大迎角机动 复合学习 自适应控制 控制分配 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计] TP181[自动化与计算机技术—控制理论与控制工程]