基于磁强计卫星初始入轨速率阻尼控制

The Velocity Damping Control of Satellite During the Initial Entering Orbit Based on the Magnetometers

对三轴稳定对地定向卫星初始入轨基于磁强计的速率阻尼控制进行了研究。当在小采样时间间隔条件下 ,地磁场矢量在惯性坐标系下的变化可以忽略 ,采用磁强计连续测量地球磁场获得姿态数据 ,通过推广卡尔曼滤波建立了较完整和准确的姿态估计器模型。设计了喷气推力器控制规律 ,通过数学仿真表明本文提出的算法能够替代陀螺对卫星初始入轨的姿态进行速率阻尼 。

This paper deals with the velocity Damping of satellite during the initial entering orbit based on the magnetometers The algorithms using data from continuously running magnetometers on the basis of the underlying assumption that the geomagnetic field vector does not significantly change (relative to an inertial reference frame ) during the short sampling time Based on extended Kalman filter, an attitude estimator is designed which adopts the linearized dynamic model and measurement equation The control law of Jet-Thruster has been designed The simulation shows that precision attitude damping is achieved by using three-axis magnetometers which can take place of gyro in this paper