[1]钟晨星,郭 毓,郭 健,等.带有非线性内模补偿的挠性航天器姿态控制[J].南京理工大学学报(自然科学版),2016,40(06):635.[doi:10.14177/j.cnki.32-1397n.2016.40.06.001]
 Zhong Chenxing,Guo Yu,Guo Jian,et al.Attitude control for flexible spacecraft with nonlinear internal model compensation[J].Journal of Nanjing University of Science and Technology,2016,40(06):635.[doi:10.14177/j.cnki.32-1397n.2016.40.06.001]
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带有非线性内模补偿的挠性航天器姿态控制
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
40卷
期数:
2016年06期
页码:
635
栏目:
出版日期:
2016-12-30

文章信息/Info

Title:
Attitude control for flexible spacecraft with nonlinear internal model compensation
文章编号:
1005-9830(2016)06-0635-08
作者:
钟晨星郭 毓郭 健朱志浩
南京理工大学 自动化学院,江苏 南京 210094
Author(s):
Zhong ChenxingGuo YuGuo JianZhu Zhihao
School of Automation,Nanjing University of Science and Technology,Nanjing 210094,China
关键词:
非线性内模补偿 挠性航天器 姿态控制 干扰抑制 振动抑制 内模原理
Keywords:
nonlinear internal model compensation flexible spacecrafts attitude control disturbance rejection vibration suppression internal model principle
分类号:
TP273; V448.22
DOI:
10.14177/j.cnki.32-1397n.2016.40.06.001
摘要:
针对挠性航天器姿态控制中的干扰和振动抑制问题,提出了1种带有非线性内模补偿的鲁棒姿态控制器。基于内模原理设计非线性动态干扰补偿器,可渐近抑制非线性外部系统产生的时变干扰信号。分析刚挠耦合关联系统特性并应用Lyapunov方法,提出1种基于姿态角速度反馈镇定挠性模态的鲁棒态控制律,实现了包括挠性模态在内系统状态量的渐近稳定。该控制器仅采用姿态角和姿态角速度测量信息,不需要测量模态,易于工程实现。将该控制器用于挠性航天器姿态控制,仿真结果验证了其有效性和对干扰的鲁棒性。
Abstract:
A novel robust attitude controller with nonlinear internal model compensation is proposed for the disturbance rejection and vibration suppression problems of flexible spacecraft attitude control.A novel nonlinear dynamic disturbance compensator is designed via internal model principle aiming at achieving asymptotic rejection to the time-varying disturbances generated by a nonlinear exosystem.A robust attitude controller is proposed to stabilize flexible modes based on angular velocity feedback control by analyzing the characteristic of the interconnected structure of rigid-flex system and using Lyapunov technique,and the convergence of the system state variables including flexible modal variables is guaranteed.The proposed controller is easy to be implemented because only the attitude angle and angular velocity other than modal variables are applied.The effectiveness and robustness of the controller are demonstrated by numerical simulation for flexible spacecraft attitude control.

参考文献/References:

[1] 吕振铎,雷拥军.卫星姿态测量与确定[M].北京:国防工业出版社,2013.
[2]邱志成.基于自适应滤波的压电智能挠性悬臂板振动控制研究[J].系统仿真学报,2006,18(5):1131-1138.
Qiu Zhicheng.Study on adaptive filter control for piezoelectric intelligent plate[J].Journal of System Simulation,2006,18(5):1131-1138.
[3]Singhose W E,Banerjee A K,Seering W P.Slewing flexible spacecraft with deflection-limiting input shaping[J].Journal of Guidance,Control,and Dynamics,1997,20(2):291-298.
[4]Guo Yu,Zhou Chunfeng,Yu Zhen,et al.Study on attitude control for move-to-rest manoeuvre of flexible spacecraft[J].International Journal of Modelling,Identification and Control,2013,19(1):23-31.
[5]周端,申晓宁,郭毓,等.基于多目标优化的挠性航天器姿态机动路径规划[J].南京理工大学学报,2012,36(5):846-853.
Zhou Duan,Shen Xiaoning,Guo Yu,et al.Profile planning for attitude maneuver of flexible spacecrafts based on multi-objective optimization[J].Journal of Nanjing University of Science and Technology,2012,36(5):846-853.
[6]Zhong Chenxing,Guo Yu,Yu Zhen,et al.Finite-time attitude control for flexible spacecraft with unknown bounded disturbance[J].Transactions of the Institute of Measurement and Control,2016,38(2):240-249.
[7]Hu Qinlei,Wang Zidong,Gao Huijun.Sliding mode and shaped input vibration control of flexible systems[J].IEEE Trans on Aerospace and Electronic Systems,2008,44(2):503-519.
[8]Xiao Bing,Hu Qinlei,Zhang Youmin.Adaptive sliding mode fault tolerant attitude tracking control for flexible spacecraft under actuator saturation[J].IEEE Trans on Control Systems Technology,2012,20(6):1605-1612.
[9]Liu Hua,Guo Lei,Zhang Yumin.An anti-disturbance PD control scheme for attitude control and stabilization of flexible spacecrafts[J].Nonlinear Dynamics,2012,67(3):2081-2088.
[10]王卫杰,任元,李怡勇,等.航天器非线性鲁棒自适应姿态机动控制律[J].系统工程与电子技术,2015,37(1):135-140.
Wang Weijie,Ren Yuan,Li Yiyong,et al.Nonlinear robust adaptive attitude maneuver control law for spacecraft[J].Systems Engineering and Electronics,2015,37(1):135-140.
[11]Ding Shihong,Zheng Weixing.Nonsmooth attitude stabilization of a flexible spacecraft[J].IEEE Trans on Aerospace and Electronic Systems,2014,50(2):1163-1181.
[12]Yang C D,Sun Yunping.Mixed H2/H state-feedback design for microsatellite attitude control[J].Control Engineering Practice,2002,10(9):951-970.
[13]Chen Zhiyong,Huang Jie.Attitude tracking and disturbance rejection of rigid spacecraft by adaptive control[J].IEEE Trans on Automatic Control,2009,54(3):600-605.
[14]陆栋宁,刘一武.基于内模原理的复杂挠性卫星姿态控制研究[J].宇航学报,2014,35(3):306-314.
Lu Dongning,Liu Yiwu.Research on internal model principle based attitude control for complex flexible satellites[J].Journal of Astronautics,2014,35(3):306-314.
[15]刘献平.空间飞行器的姿态和扰动抑制控制器设计[J].哈尔滨工程大学学报,2011,32(12):1637-1641.
Liu Xianping.The design of an attitude and disturbance rejection controller for spacecraft[J].Journal of Harbin Engineering University,2011,32(12):1637-1641.
[16]Zhang Xuxi,Cheng Daizhan.Nonlinear internal model based attitude tracking and disturbance rejection[J].Asian Journal of Control,2012,14(5):1397-1402.
[17]Gennaro S D.Output stabilization of flexible spacecraft with active vibration suppression[J].IEEE Trans on Aerospace and Electronic Systems,2003,39(3):747-759.

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备注/Memo

备注/Memo:
收稿日期:2016-06-23 修回日期:2016-09-13
基金项目:国家自然科学基金(61473152; 61673219); 南京理工大学优秀博士培养基金
作者简介:钟晨星(1988-),男,博士生,主要研究方向:挠性航天器姿态控制,E-mail:njustzcx@gmail.com; 通讯作者:郭毓(1964-),女,博士,教授,博士生导师,主要研究方向:挠性航天器姿态控制、高精度伺服系统、机器人控制技术等,E-mail:guoyu@njust.edu.cn。
引文格式:钟晨星,郭毓,郭健,等.带有非线性内模补偿的挠性航天器姿态控制[J].南京理工大学学报,2016,40(6):635-642.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2016-12-30