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作 者:陈升泽[1] 张旋[1] 袁建平[2] 郑子轩 CHEN Shengze;ZHANG Xuan;YUAN Jianping;ZHENG Zixuan(China Academy of Launch Vehicle Technology,Beijing 100076,P.R.China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,P.R.China)
机构地区:[1]中国运载火箭技术研究院,中国北京100076 [2]西北工业大学航天学院,中国西安710072
出 处:《Transactions of Nanjing University of Aeronautics and Astronautics》2024年第2期233-243,共11页南京航空航天大学学报(英文版)
摘 要:升力式飞行器具有飞行空域宽、速度变化范围大、机动性强等特点,是近年来国内外的研究热点。本文针对升力式飞行器模型大不确定及外界干扰强带来的控制难题,提出了一种基于干扰观测器的改进离散滑模变结构控制方法。首先,建立了俯仰通道的离散控制模型。其次,设计了一种基于干扰估计的改进离散滑模变结构控制律,并证明了其稳定性。再次,分析了参数选择对控制系统的影响,验证了控制律的有效性。最后,与传统的离散滑模变结构控制方法进行了比较。仿真结果表明,与传统的离散滑模控制方法相比,本文提出的控制律控制精度更高、鲁棒性更强、滑模面收敛速度更快及抖振更小,可有效提高升力式飞行器的飞行品质,实现复杂任务的稳定控制。Lift-type aircraft has the characteristics of wide flight airspace,large range of speed changes,strong maneuverability requirements,which makes it a research focus in recent years.Aiming at difficulties of large uncertainty and strong external disturbance in the control model of lift-type aircraft,an improved discrete-time sliding mode variable structure control method based on disturbance observer is presented.Firstly,the discrete control model of the pitch channel is established.Secondly,an improved discrete-time sliding mode variable structure control system based on disturbance estimation is designed and its stability is proved.Thirdly,the influence of parameter selection on control system is analyzed,and the validity of control law is verified.Finally,the comparison with the traditional discrete sliding mode variable structure control system is carried out.The control system’s simulation results demonstrate that,compared with the traditional discrete-time sliding mode control system,the proposed control system has higher control accuracy,stronger robustness,faster convergence to zero and less chattering.The proposed control law can effectively improve the flight quality,and can realize stable control for complex mission of lift-type aircraft.
关 键 词:升力式飞行器 干扰观测器 离散滑模控制 鲁棒控制 抖振
分 类 号:TJ765.2[兵器科学与技术—武器系统与运用工程]
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