立方星剩磁在轨辨识与主动补偿技术
发布时间：2018-11-09 19:41
【摘要】：立方星的姿态测量与控制系统常采用磁测磁控结合偏置动量轮的方案,整星剩磁干扰力矩是影响姿态控制精度的重要因素之一。提出了一种利用磁强计实现剩磁矩在轨辨识与利用磁力矩器实现剩磁矩主动补偿的新方案:基于磁强计输出和卫星姿态动力学建立了剩磁矩在轨辨识模型,并利用采样滤波器(UKF)提高单磁强计条件下的辨识效果;把控制对象简化成线性定常系统,分析了剩磁干扰力矩对姿态的影响数学模型,并针对磁力矩器和磁强计分时工作的特点,基于叠加性原理提出了基于角速度的剩磁矩主动补偿算法。仿真研究表明,在1000 s内剩磁矩在轨辨识精度为0.001 A×m~2量级,主动补偿后,偏航角、滚动角与俯仰角控制误差分别从4.3°、4.6°与2.1°均减少至0.4°以内。提出的方法为类似配置卫星减少剩磁干扰力矩的影响提供了一种新思路。
[Abstract]:The attitude measurement and control system of cubic star usually adopts the scheme of magnetic measurement and control combined with biased momentum wheel. The residual magnetic disturbance moment is one of the important factors that affect the precision of attitude control. In this paper, a new scheme is proposed to identify the residual magnetic moment in orbit by using magnetometer and to realize active compensation of residual magnetic moment by using magnetic torque device. Based on the output of magnetometer and the dynamics of satellite attitude, a model of on-orbit identification of residual magnetic moment is established. The sample filter (UKF) is used to improve the identification effect under the condition of single magnetometer. The control object is simplified as a linear time-invariant system, the mathematical model of the influence of residual magnetic disturbance moment on attitude is analyzed, and the characteristics of time-sharing of magnetic torque and magnetometer are analyzed. Based on the principle of superposition, an active compensation algorithm of residual magnetic moment based on angular velocity is proposed. The simulation results show that the accuracy of the residual magnetic moment in orbit identification is 0.001 A 脳 m ~ (2) in 1000 s. After active compensation, the control errors of yaw angle, rolling angle and pitch angle are reduced from 4.3 掳, 4.6 掳and 2.1 掳to less than 0.4 掳, respectively. The proposed method provides a new way for similar satellites to reduce the influence of residual magnetic disturbance moment.
【作者单位】： 航天恒星科技有限公司;南京航空航天大学航天学院;
【基金】：国家自然科学基金资助项目(61203197)
【分类号】：V448.22
本文编号：2321371
[Abstract]:The attitude measurement and control system of cubic star usually adopts the scheme of magnetic measurement and control combined with biased momentum wheel. The residual magnetic disturbance moment is one of the important factors that affect the precision of attitude control. In this paper, a new scheme is proposed to identify the residual magnetic moment in orbit by using magnetometer and to realize active compensation of residual magnetic moment by using magnetic torque device. Based on the output of magnetometer and the dynamics of satellite attitude, a model of on-orbit identification of residual magnetic moment is established. The sample filter (UKF) is used to improve the identification effect under the condition of single magnetometer. The control object is simplified as a linear time-invariant system, the mathematical model of the influence of residual magnetic disturbance moment on attitude is analyzed, and the characteristics of time-sharing of magnetic torque and magnetometer are analyzed. Based on the principle of superposition, an active compensation algorithm of residual magnetic moment based on angular velocity is proposed. The simulation results show that the accuracy of the residual magnetic moment in orbit identification is 0.001 A 脳 m ~ (2) in 1000 s. After active compensation, the control errors of yaw angle, rolling angle and pitch angle are reduced from 4.3 掳, 4.6 掳and 2.1 掳to less than 0.4 掳, respectively. The proposed method provides a new way for similar satellites to reduce the influence of residual magnetic disturbance moment.
【作者单位】： 航天恒星科技有限公司;南京航空航天大学航天学院;
【基金】：国家自然科学基金资助项目(61203197)
【分类号】：V448.22
【相似文献】
相关期刊论文 前5条
1 易忠;;中低轨道卫星的磁补偿[J];环模技术;1997年04期
2 易忠;史尧宜;;地磁场中测量卫星磁矩的一种新的方法[J];环模技术;1996年04期
3 李杨,涂歆滢;星体剩磁矩对姿控系统影响的仿真研究[J];系统仿真学报;2002年02期
4 程丽丽;肖琦;张志强;董勇伟;张力;;某型号卫星磁环境兼容性分析与控制[J];航天器环境工程;2009年04期
5 ;[J];;年期
，本文编号：2321371
本文链接：https://www.wllwen.com/kejilunwen/hangkongsky/2321371.html
