基于奇异值方法的推力矢量/气动舵飞机复合控制律参数优化方法  

Parameter optimization method of thrust vector/pneumatic rudder composite control law for aircraft based on singular value method

作　　者：阮仕龙 董哲 孙尧[2] 曲晓雷 霍少泽 RUAN Shilong;DONG Zhe;SUN Yao;QU Xiaolei;HUO Shaoze(School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China;Shenyang Aircraft Corporation,Shenyang 110034,China;Shenyang Aircraft Design and Research Institute,Shenyang 110035,China)

机构地区：[1]大连理工大学航空航天学院,大连116024 [2]沈阳飞机工业(集团)有限公司,沈阳110034 [3]沈阳飞机设计研究所,沈阳110035

出　　处：《北京航空航天大学学报》2025年第4期1332-1341,共10页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金重点项目(U2141229);基础加强项目(2019-JCJQ-DA-001-131)。

摘　　要：推力矢量/气动舵布局的先进飞机存在显著的控制耦合问题,传统的单回路控制参数设计方法在该场景下无法兼顾多控制回路的性能。因此提出一种基于回差矩阵奇异值的控制律参数优化方法,利用时域控制性能指标确定控制参数优化区间,在此基础上用奇异值方法衡量多输入多输出(MIMO)系统的稳定裕度,并建立相应的最优目标函数,从而对控制器参数寻优。采用数值仿真验证了该方法的可行性,结果显示所设计的控制参数优化算法相较于传统单回路控制参数设计方法具有更好的时域控制性能与更大的系统稳定裕度。Control coupling is a major problem for advanced aircraft with thrust vector/aerodynamic rudder layouts,as the performance of numerous control loops cannot be balanced using conventional single loop control parameter design techniques.Therefore,a control law parameter optimization method based on the singular value of the feedback matrix is proposed.The optimization interval of the control parameters is first established using the time domain control performance index.The stability margin of the multiple-in multiple-out(MIMO)system is then measured using the singular value method,and the corresponding optimal objective function is established to optimize the controller parameters.The feasibility of this method was verified through numerical simulation,and the results showed that the designed control parameter optimization algorithm has better time-domain control performance and a larger system stability margin compared to traditional single loop control parameter design methods.

关 键 词：回差矩阵奇异值 参数寻优 稳定裕度 MIMO系统 推力矢量 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]