中国空间科学技术2012，Vol.32Issue(4)：45-53,9.DOI:10.3780/j.issn.1000-758X.2012.04.007
小型控制力矩陀螺扰动建模及性能指标分析
Disturbance Modeling and Performance Index Evaluation of the Small Control Moment Gyroscope
摘要
Abstract
Control moment gyro (CMG) is widely used as the actuator for attitude control an satellites recently.To realize high-precise pointing capability of a high resolution remote sensing satellite, the disturbance modeling and performance index evaluation of CMG were discussed.Firstly, considering the static and dynamic imbalances of the rotor and installation errors, the small CMG dynamic model was constructed by means of the theorem of momentum and theorem of angular momentum.The validity of this model was analyzed based on an experience model of a flywheel and testified by numerical simulation.Secondly, a cluster nf the CMGs were adopted and the whole satellite dynamic model was derived.To complete the mission of the satellite attitude stabilization control.the reasonable servo-control systems of the gimbals and the rotor wptp selected.Finally, the influences of the CMG disturbances on the attitude precision' and satellite stability were analyzed in detail.According to the space mission of the high resolution remote sensing satellite, the constraint condition of the CMG performance index was obtained to meet the imaging requirements of the optical payloads.关键词
小型控制力矩陀螺/扰动建模/姿态稳定/性能指标/遥感卫星Key words
Small control moment gyroscope Disturbance modeling Attitude stabilization Performance index Remote sensing satellite引用本文复制引用
张尧,金磊,徐世杰..小型控制力矩陀螺扰动建模及性能指标分析[J].中国空间科学技术,2012,32(4):45-53,9.基金项目
国家自然科学基金(10902003)资助项目 （10902003）
