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CORC

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Smooth backstepping sliding mode control for missile attitude system based on parameters online adjusting and estimating for square of disturbance upper bound 期刊论文
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 2019, 卷号: 233, 页码: 22-33
作者:  Wu, Yun-Jie;  Zuo, Jing-Xing;  Sun, Liang-Hua
收藏  |  浏览/下载：13/0  |  提交时间：2019/12/30
基于滑模控制的空空导弹敏捷转弯控制研究 学位论文
2016, 2016
张海洋
收藏  |  浏览/下载：4/0  |  提交时间：2017/06/20
Integration control design for a semi-strapdown seeker missile 会议论文
PROCEEDINGS OF THE 28TH CHINESE CONTROL AND DECISION CONFERENCE (2016 CCDC), 2016-01-01
作者:  Yi, Ke;  Liu, Siyuan;  Yu, Jianglong;  Li, QingDong;  Ren, Zhang
收藏  |  浏览/下载：3/0  |  提交时间：2019/12/30
姿控式直接力/气动力拦截弹复合控制方法研究 学位论文
工学博士, 中国科学院自动化研究所: 中国科学院大学, 2015
作者:  常亚菲
收藏  |  浏览/下载：72/0  |  提交时间：2015/09/02
Backstepping sliding-mode control for missile attitude using a linear extended state observer 会议论文
6th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014, Yantai, China, 2014-08-08
作者:  Wang, Sen;  Wang, Weihong;  Xiong, Shaofeng
收藏  |  浏览/下载：1/0  |  提交时间：2020/01/06
滚珠丝杠式电动舵机非线性分析及控制策略研究 学位论文
博士: 中国科学院大学, 2014
张明月
收藏  |  浏览/下载：194/0  |  提交时间：2014/08/21
Integer Programming Based Optimal Side Jets Ignition Combination for Advanced Missile Attitude Control 会议论文
26TH CHINESE CONTROL AND DECISION CONFERENCE (2014 CCDC), 2014-01-01
作者:  Wang Zhenchao;  Yang Lingyu;  Zhang Jing;  Shen Gongzhang
收藏  |  浏览/下载：2/0  |  提交时间：2020/01/06
Backstepping Sliding-mode Control for Missile Attitude using a Linear Extended State Observer 会议论文
2014 IEEE CHINESE GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC), 2014-01-01
作者:  Wang, Sen;  Wang, Weihong;  Xiong, Shaofeng
收藏  |  浏览/下载：4/0  |  提交时间：2020/01/06
Attitude Tracking of Rigid Spacecraft With Bounded Disturbances 期刊论文
IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, 2011, 卷号: 58, 期号: 2, 页码: 647-659
作者:  Xia, Yuanqing;  Zhu, Zheng;  Fu, Mengyin;  Wang, Shuo
收藏  |  浏览/下载：13/0  |  提交时间：2015/08/12
Adaptive control at launching using three loop autopilot (EI CONFERENCE) 会议论文
2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China
Zhang Y.
收藏  |  浏览/下载：17/0  |  提交时间：2013/03/25
In order to guarantee the precise initial flight trajectory  control the missile disturbance of large disturbance torque  three loop adaptive autopilot was researched. The characteristics of the projectile and three loop autopilot instruction formation characteristics were analysed. From equivalent pitching angle of lateral acceleration feedback loop  combined with the instruction of generalized error  autopilot structure was simplified  and three loop autopilot adaptive control law and stability were designed. The test data show that when disturbance torque was 600Nm  the attitude angle generalized error was -4.4. In the time lasted about 15s  late trajectory accuracy was within 1.0.Three loop autopilot adaptive control law was able to control the disturbance of initial trajectory and adapt to dynamic characteristics changes  control system stability. It was the initial trajectory accurate solution method of flight. 2011 IEEE.  

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