摘要
围绕某日-地空间环境组网探测系统中三轴稳定微小卫星定姿分系统的设计需求,基于陀螺、太阳敏感器、磁强计和星敏感器4种敏感器,研究了微小卫星在速率阻尼模式、太阳捕获模式、对日对地定向及维持模式、试验模式下的系统建模方法,以及基于Unscented卡尔曼滤波(UKF)的组合定姿方法。数值仿真结果表明,本文定姿方法的姿态确定精度满足该系统中三轴稳定微小卫星在轨运行的定姿精度要求,为该微小卫星半物理仿真系统的研究及其在轨运行时的姿态确定提供了依据。
According to the design requirements of attitude determination subsystem of a three-axis stabilized micro-satellite for space environment exploration,the method of system modeling is studied in this paper based on the sensors such as MEMS gyro,sun sensor,magnetometer and star sensor.And the algorithm of unscented Kalman filter（UKF） is presented to solve the combined attitude control of micro-satellite.The simulation results show that the precision of attitude determination obtained by our attitude determination algorithm meets the attitude determination requirements of the three-axis stabilized micro-satellite.The simulation results provide the support for the micro-satellite attitude determination,and are important to the research of the micro-satellite semi-physical simulation system.
出处
《航天控制》
CSCD
北大核心
2010年第2期12-16,共5页
Aerospace Control
基金
国家高技术研究发展计划(863)重点项目(2008AA12A200)
国家自然科学基金(60704010)资助
