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国家自然科学基金(s61225015)

作品数:5 被引量:98H指数:4
相关作者:邓志红付梦印夏元清任雪梅更多>>
相关机构:北京理工大学更多>>
发文基金:国家自然科学基金国家重点基础研究发展计划北京市自然科学基金更多>>
相关领域:自动化与计算机技术航空宇航科学技术文化科学更多>>

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Recent Progress in Networked Control Systems——A Survey被引量:7
2015年
For the past decades,networked control systems(NCSs),as an interdisciplinary subject,have been one of the main research highlights and many fruitful results from different aspects have been achieved.With these growing research trends,it is significant to consolidate the latest knowledge and information to keep up with the research needs.In this paper,the results of different aspects of NCSs,such as quantization,estimation,fault detection and networked predictive control,are summarized.In addition,with the development of cloud technique,cloud control systems are proposed for the further development of NCSs.
Yuan-Qing XiaYu-Long GaoLi-Ping YanMeng-Yin Fu
关键词:QUANTIZATION
滑模控制和自抗扰控制的研究进展(英文)被引量:68
2013年
本文概括了滑模控制和自抗扰控制的研究进展,进一步给出了复合控制的思想.滑模控制和自抗扰控制都有它们各自的优点,但是也都有它们各自的局限,例如:滑模控制中的抖振问题和自抗扰控制中的估计能力受限问题.复合控制结合了滑模控制和自抗扰控制的优点,并能提高闭环系统的性能.
夏元清付梦印邓志红任雪梅
关键词:复合控制滑模控制自抗扰控制稳定性
Trajectory tracking control of a VTOL unmanned aerial vehicle using offset-free tracking MPC被引量:12
2020年
Designing a stable and robust flight control system for an Unmanned Aerial Vehicle(UAV)is an arduous task.This paper addresses the trajectory tracking control problem of a Ducted Fan UAV(DFUAV)using offset-free Model Predictive Control(MPC)technique in the presence of various uncertainties and external disturbances.The designed strategy aims to ensure adequate flight robustness and stability while overcoming the effects of time delays,parametric uncertainties,and disturbances.The six degrees of freedom DFUAV model is divided into three flight modes based on its airspeed,namely the hover,transition,and cruise mode.The Dryden wind turbulence is applied to the DFUAV in the linear and angular velocity component.Moreover,different uncertainties such as parametric,time delays in state and input,are introduced in translational and rotational components.From the previous work,the Linear Quadratic Tracker with Integrator(LQTI)is used for comparison to corroborate the performance of the designed controller.Simulations are computed to investigate the control performance for the aforementioned modes and different flight phases including the autonomous flight to validate the performance of the designed strategy.Finally,discussions are provided to demonstrate the effectiveness of the given methodology.
Tayyab MANZOORYuanqing XIADi-Hua ZHAIDailiang MA
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