一种飞行器直气复合控制方法研究  

Study on a Direct Force/Aerodynamic Composite Control Method for Aircraft

作　　者：申奇睿 SHEN Qi-rui(The Overall Design Institute of the Academy of Hubei Aerospace Technology,Wuhan 430040,China)

机构地区：[1]湖北航天技术研究院总体设计所,湖北武汉430061

出　　处：《湖北科技学院学报》2025年第2期117-124,共8页Journal of Hubei University of Science and Technology

摘　　要：近年来,各国争先发展高超声速飞行器技术。传统飞行器完全依靠气动力飞行,具有响应速度慢、易受大气环境干扰等缺点。本文以一种尾部具有脉冲式姿控发动机的高超声速飞行器作为研究对象,对直接力/气动力复合控制方法进行研究。针对高超声速飞行器进行数学建模,设计姿控发动机的点火逻辑,基于滑模变结构控制理论进行飞行器复合控制系统设计,并分析了闭环系统的稳定性。根据设计内容,进行了六自由度数学仿真,仿真结果表明该方法合理可行,具有很强的工程实践意义。In recent years,many countries have been vying to develop hypersonic vehicles.Traditional vehicles rely entirely on aerodynamic flights,which have shortcomings such as slow response speed and easy interference from the atmospheric environment.In this paper,a hypersonic vehicle with a pulsed attitude control engine at the tail is taken as the research object,and the direct force/aerodynamic composite control method is studied.The mathematical modeling of the hypersonic vehicle is carried out,the ignition logic of the attitude control engine is designed,the aircraft composite control system is designed based on the sliding mode variable structure control theory,and analyze the stability of the closed-loop system.According to the design content,the six-degree-of-freedom mathematical simulation is carried out,and the simulation results show that the method is reasonable and feasible,and has strong engineering practical significance.

关 键 词：高超声速飞行器 姿控发动机 姿态控制 滑模变结构控制 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]