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

Design and Analysis of Radiometric Calibration Mission in-orbit for Environment and Disasters Monitoring Satellite 会议论文 OAI收割
Yokohama, Japan, 2019-07-28
作者: Zhu, Yang; Zhu, Jun; Bai, Zhaoguang; Dong, Jun; Wu, Bin

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收藏 | 浏览/下载：50/0 | 提交时间：2020/03/10

environment and disasters monitoring in-orbit radiometric calibration side-slither calibration along track scanning satellite attitude stability

Vector Control-Based Singularity Avoidance/Escape Steering Law for Single Gimbal Control Moment Gyros 期刊论文 OAI收割
Ieee Access, 2019, 卷号: 7, 页码: 175727-175743
作者: N.Mao; T.Zhang; K.Xu; M.S.Chen; C.Dong

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收藏 | 浏览/下载：24/0 | 提交时间：2020/08/24

Steering law,SGCMG,satellite attitude control,logic,spacecraft,sgcmg,Computer Science,Engineering,Telecommunications

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

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

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.

United steering of control moment gyros for small satellite with limited gimbal rate (EI CONFERENCE) 会议论文 OAI收割
2010 IEEE International Conference on Information and Automation, ICIA 2010, June 20, 2010 - June 23, 2010, Harbin, Heilongjiang, China
Xu K.; Jin G.; Chen C.

收藏 | 浏览/下载：18/0 | 提交时间：2013/03/25

Single Gimbal Control Moment Gyroscopes (SGCMG) can could provide large control torque and quick attitude maneuver rate to small satellites without any increase in power volume and mass which will help small satellites become more powerful. Singularity avoidance and failure steering are two important problems to SGCMGs and also the main focus in this field. A new united steering law for SGCMGs with capabilities of singularity avoidance and quick transition of singularity surfaces is developed in this paper. To ensuring the existence of null motion the commanded output of controller was changed real-timely as the variation of singularity measurement of SGCMGs which can avoid the gimbal angle rate saturation. This developed steering law could help the SGCMGs provide real-time control toques in spite of limitation of gimbal angle rate. Simulation analysis is conducted for a certain 4-SGCMG system mounted on a small satellite. Simulation results indicate that the steering law is very effective in singularity avoidance. 2010 IEEE.

Design of ground-based physical simulation system for satellite-borne TDI-CCD dynamic imaging (EI CONFERENCE) 会议论文 OAI收割
Optoelectronic Imaging and Multimedia Technology, October 18, 2010 - October 20, 2010, Beijing, China
作者: Zhang L.; Zhang L.; Sun Z.

收藏 | 浏览/下载：23/0 | 提交时间：2013/03/25

As we know the existence of image motion has a bad effect on the image quality of satellite-borne TDI CCD camera. Although many theories on image motion are proposed to cope with this problem few simulations are done to justify the proposed theories on ground. And thus in this paper a ground-based physical simulation system for TDI CCD imaging is developed and specified which consists of a physical simulation subsystem for precise satellite attitude control based on a 3-axis air bearing table and an imaging and simulation subsystem utilizing area-array CCD to simulate TDI CCD. The designed system could realize not only a precise simulation of satellite attitude control whose point accuracy is above 0.1 and steady accuracy above 0.01/s but also an imaging simulation of 16-stage TDI CCD with 0.1s its integration time. This paper also gives a mathematical model of image motion of this system analogous with satellite-borne TDI CCD and detailed descriptions on the principle utilizing area-array CCD to simulate TDI CCD. It is shown that experiment results are in accordance with mathematical simulation and that the image quality deteriorate seriously when the correspondence between the image velocity and signal charges transfer velocity is broken out which suggest not only the validity of the system design but also the validity of the proposed image motion theory of TDI CCD. 2010 SPIE.

Earth elevation map production and high resolution sensing camera imaging analysis (EI CONFERENCE) 会议论文 OAI收割
Optoelectronic Imaging and Multimedia Technology, October 18, 2010 - October 20, 2010, Beijing, China
作者: Dai L.

收藏 | 浏览/下载：131/0 | 提交时间：2013/03/25

The Earth's digital elevation which impacts space camera imaging has prepared and imaging has analysed. Based on matching error that TDI CCD integral series request of the speed of image motion statistical experimental methods-Monte Carlo method is used to calculate the distribution histogram of Earth's elevation in image motion compensated model which includes satellite attitude changes orbital angular rate changes latitude longitude and the orbital inclination changes. And then elevation information of the earth's surface from SRTM is read. Earth elevation map which produced for aerospace electronic cameras is compressed and spliced. It can get elevation data from flash according to the shooting point of latitude and longitude. If elevation data between two data the ways of searching data uses linear interpolation. Linear interpolation can better meet the rugged mountains and hills changing requests. At last the deviant framework and camera controller are used to test the character of deviant angle errors TDI CCD camera simulation system with the material point corresponding to imaging point model is used to analyze the imaging's MTF and mutual correlation similarity measure simulation system use adding cumulation which TDI CCD imaging exceeded the corresponding pixel horizontal and vertical offset to simulate camera imaging when stability of satellite attitude changes. This process is practicality. It can effectively control the camera memory space and meet a very good precision TDI CCD camera in the request matches the speed of image motion and imaging. 2010 SPIE.

Analysis of inertia dyadic uncertainty for small agile satellite with control moment gyros (EI CONFERENCE) 会议论文 OAI收割
2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China
作者: Zhang L.; Zhang L.; Sun Z.

收藏 | 浏览/下载：19/0 | 提交时间：2013/03/25

With the increasing demands for the agility of the next earth imaging satellite control moment gyro (CMG) is considered to be the most suitable actuator because of its torque amplification capability. However a CMG system may introduce uncertainty of inertia dyadic to a satellite's attitude control system. The uncertainty is negligible for large space vehicles but it has not been tested whether it can be ignored for small agile satellites. How to model the CMG system inertia dyadic varying with gimbal angles and what influence it will put on the performance of attitude control system haven't been test accurately as well. All of them are dealt with mathematically and accurately in this paper. This paper firstly gives mathematic descriptions of the inertia dyadic of the 4-CMG pyramid configuration system varying with gimbal angles and then designs a variable structure control law for small agile satellite using CMGs. Finally numerical simulation suggests that the inertia dyadic variation of a 4-CMG pyramid configuration system is approximately centesimal of the total inertia dyadic of the satellite and that the designed variable structure control law is of good robust performance for an example of large-angle attitude maneuver despite of the variation of the inertia dyadic. 2010 IEEE.