中国科学院机构知识库网格系统: 检索

Observer-Based Multiple Faults Diagnosis Scheme for Satellite Attitude Control System 期刊论文 OAI收割
Asian Journal of Control, 2020, 卷号: 22, 期号: 1, 页码: 307-322
作者: Gao S(高升); Zhang W(张伟); He X(何旭)

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收藏 | 浏览/下载：18/0 | 提交时间：2018/08/11

Multiple Faults Diagnosis Scheme Nonlinear Observer Sliding Mode Observer Satellite Attitude Control System

Sliding Mode Observer based Satellite Actuator Fault Diagnosis with Attitude-Only Measurement 会议论文 OAI收割
Nanchang, China, June 3-5, 2019
作者: Gao S(高升); Zhang W(张伟); He X(何旭); Yang F(杨帆); Huang H(黄昊)

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收藏 | 浏览/下载：18/0 | 提交时间：2019/11/14

Fault diagnosis Sliding mode observer Satellite Attitude control system

Coordination of multiple rigid bodies under distance-induced interaction topologies 期刊论文 OAI收割
IET CONTROL THEORY AND APPLICATIONS, 2018, 卷号: 12, 期号: 15, 页码: 2067-2075
作者: Deng, Juan; Wang, Lin; Liu, Zhixin; Hu, Xiaoming

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收藏 | 浏览/下载：42/0 | 提交时间：2018/11/16

synchronisation control system synthesis graph theory attitude control distributed control multi-robot systems collision avoidance velocity control mobile robots multiple rigid bodies distance-induced interaction topologies coordination control problem distance-induced neighbour graphs nearby bodies angular velocity linear velocity attitude synchronisation

Observer-Based Multiple Faults Diagnosis Scheme for Satellite Attitude Control System 期刊论文 OAI收割
Asian Journal of Control, 2018
作者: Zhang W(张伟); He X(何旭); Gao S(高升); Xu ZG(徐志刚); Chang CG(昌成刚)

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收藏 | 浏览/下载：15/0 | 提交时间：2018/08/11

Multiple faults diagnosis scheme nonlinear observer sliding mode observer satellite attitude control system

Fault tolerant control with switched LPV method based on hysteresis strategy and an application to a microsatellite model 会议论文 OAI收割
34th Chinese Control Conference (CCC 2015), Hangzhou, China, July 28-30, 2015
作者: He X(何旭); Zhang W(张伟); Leng YQ(冷雨泉); Zhang Y(张阳)

收藏 | 浏览/下载：22/0 | 提交时间：2015/11/22

Switched LPV system Fault-tolerant control H∞ controller design Hysteresis method Attitude system control Microsatellite

微小型直升机姿态估计和鲁棒控制技术研究 学位论文 OAI收割
工学博士, 中国科学院自动化研究所: 中国科学院研究生院, 2012
作者: 常冠清

收藏 | 浏览/下载：59/0 | 提交时间：2015/09/02

微小型直升机姿态估计 EKF SR-UKF 自抗扰控制 Backstepping 自适应模糊系统飞控系统平台 Miniature Helicopters Attitude Estimation EKF SR-UKF ADRC Backstepping Adaptive Fuzy System Flight Control platform

Trajectory tracking control of a quad-rotor UAV based on command filtered backstepping (EI CONFERENCE) 会议论文 OAI收割
2012 3rd International Conference on Intelligent Control and Information Processing, ICICIP 2012, July 15, 2012 - July 17, 2012, Dalian, China
Gong X.; Bai Y.; Peng C.; Zhao C.; Tian Y.

收藏 | 浏览/下载：30/0 | 提交时间：2013/03/25

A quad-rotor unmanned aerial vehicle is an under-actuated strong coupled nonlinear system with parameters uncertainty and unknown external aerodynamic disturbance. The trajectory tracking control system with a nested double-loops structure is designed in this paper according to the coupling characteristic between the attitude angles and translational position. A PD control algorithm is proposed in the translational outer-loop to export the desired attitude signals to the attitude inner-loop. An adaptive backstepping control algorithm is designed in the inner-loop with respect to the uncertain rotational inertia and un-modeled disturbance while in order to reduce the computational complexity the command filtered approach is introduced into the designing procedure. And finally the numerical simulation results are presented for the trajectory tracking stabilization of a Quad-rotor which demonstrates the excellent performance of the proposed control system and illustrate its robustness in face of disturbance and uncertain parameters. 2012 IEEE.

Design of semi-physical simulation for small satellite by virtual display (EI CONFERENCE) 会议论文 OAI收割
2011 3rd International Conference on Mechanical and Electronics Engineering, ICMEE 2011, September 23, 2011 - September 25, 2011, Hefei, China
Xu K.; Lv Y.; Jin G.

收藏 | 浏览/下载：20/0 | 提交时间：2013/03/25

Semi-physical simulation of attitude control system is the more synthetically test and verify for designing of small satellite control system. It is an important means of small satellite development. However the results of current semi-physical simulation system have a lot of non-intuitive. Compare with the actual environment the simulation environment still has striking disparity. So the shortcomings affect precision of simulation. Based on the virtual display technology the group semi-physical simulation system has been constructed for attitude control of small satellite due to the combination with xPC real-time environment the simulation computer high-precision single-axis air-bearing turntable reaction wheel air thrust device fiber gyroscopes sensors synchronizer power subsystem and wireless devices virtual display computer etc. Semi-physical simulation achieved the visual simulation in orbit and tracked new information of virtual environment of space into real-time simulation computer. Simulation results show that the simulation system for real-time attitude and orbit position of small satellite semi-physical simulation has an excellent display effect. At the same time Real-time transfuse of orbit information provides a more accurate space environment simulation. The simulation system of small satellite attitude control to design and evaluate the more direct and convenient. (2012) Trans Tech Publications Switzerland.

Reliable attitude stability control of quad-rotor based on fault-tolerant approach (EI CONFERENCE) 会议论文 OAI收割
2012 9th IEEE International Conference on Mechatronics and Automation, ICMA 2012, August 5, 2012 - August 8, 2012, Chengdu, China
作者: Gao Q.

收藏 | 浏览/下载：39/0 | 提交时间：2013/03/25

The reliability flight property has received much attention within the aircraft control community throughout the last decades. In this paper the fault-tolerant control technique is introduced into the attitude stability control system of a quadrotor UAV in order to compensate the influence of the actuators fault of the aircraft. This control scheme is composed of two components: a robust fault detection module using the modelbased observation approach and a reconfigurable controller. Besides the designing procedure the theoretical analysis of robustness and stability of the designed FTC scheme are also contained in this article. And finally the availability of the proposed scheme is verified through numerical simulation. 2012 IEEE.

Adaptive control at launching using three loop autopilot (EI CONFERENCE) 会议论文 OAI收割
2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China
作者: Zhang Y.

收藏 | 浏览/下载：25/0 | 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.