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The output torque estimation of MCMG for agile satellites 被引量:5
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作者 Jingrui Zhang 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2010年第1期141-146,共6页
Studied in this paper are the attitude control law design and the output torque estimation problem of micro control moment gyros (MCMGs) for the agile satellites executing rapid attitude maneuver mission. An algorit... Studied in this paper are the attitude control law design and the output torque estimation problem of micro control moment gyros (MCMGs) for the agile satellites executing rapid attitude maneuver mission. An algorithm is proposed for estimating the output torques and the gimbal angular rates of MCMGs, which can help engineers to choose reasonable size for actuators so that the cost of satellite can be decreased. According to some special maneuver missions, a numerical example of attitude control system for a small satellite with MCMGs in pyramid configuration is studied, and the simulation results validate the proposed estimation algorithm. 展开更多
关键词 Agile satellite Micro control moment gyro Rapid attitude maneuver
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Low-frequency Periodic Error Identification and Compensation for Star Tracker Attitude Measurement 被引量:12
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作者 WANG Jiongqi XIONG Kai ZHOU Haiyin 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2012年第4期615-621,共7页
The low-frequency periodic error of star tracker is one of the most critical problems for high-accuracy satellite attitude determination.In this paper an approach is proposed to identify and compensate the low-frequen... The low-frequency periodic error of star tracker is one of the most critical problems for high-accuracy satellite attitude determination.In this paper an approach is proposed to identify and compensate the low-frequency periodic error for star tracker in attitude measurement.The analytical expression between the estimated gyro drift and the low-frequency periodic error of star tracker is derived firstly.And then the low-frequency periodic error,which can be expressed by Fourier series,is identified by the frequency spectrum of the estimated gyro drift according to the solution of the first step.Furthermore,the compensated model of the low-frequency periodic error is established based on the identified parameters to improve the attitude determination accuracy.Finally,promising simulated experimental results demonstrate the validity and effectiveness of the proposed method.The periodic error for attitude determination is eliminated basically and the estimation precision is improved greatly. 展开更多
关键词 star trackers attitude determination low-frequency periodic error gyro drift precision analysis
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