飞机飞行姿态系统控制律设计分析及仿真  

Control Law Design and Simulation Study for Aircraft Attitude Control System

作　　者：曲东才 李智慧 王浩志[1] 戴宏发 常波 QU Dongcai;LI Zhihui;WANG Haozhi;DAI Hongfa;CHANG Bo(Aeronautical College,Yantai Nanshan University,Yantai 265713,China;School of Aviation Fundamentals,Naval Aeronautical and Astronautical University,Yantai 265713,China)

机构地区：[1]烟台南山学院航空学院,山东烟台265713 [2]海军航空大学航空基础学院,山东烟台265713

出　　处：《飞机设计》2021年第1期6-9,共4页Aircraft Design

摘　　要：飞机的飞行性能与其相关系统控制律设计密切相关。基于飞机俯仰姿态系统基本状态及工作原理,构建了飞机比例式/积分式姿态系统结构框图,对比例式/积分式控制律进行设计,分析了2种控制律的演变思路及其优缺点。大量仿真数据显示:在比例式/积分式控制律传动比选取恰当时,飞机姿态系统品质良好,具有较好的动态和稳态性能。The flight performance of aircraft is closely related to its control law design.Based on the basic state and working principle of the airplane pitching attitude system, the structure block diagram of the airplane proportional/integral attitude system is constructed, the proportional/integral control law is designed, and the evolution ideas of the two control laws and their advantages and disadvantages are analyzed.A large number of simulation data show that when the transmission ratio of proportional/integral control law is properly selected, the aircraft attitude system has good quality and good dynamic and steady-state performance.

关 键 词：飞行姿态系统 比例式/积分式控制律 系统性能 仿真 

分 类 号：V212.13[航空宇航科学与技术—航空宇航推进理论与工程]