星体剩磁矩对姿控系统影响的仿真研究

Simulation of the Remanence Moment Influencing on Satellite Attitude Control System

低轨道长寿命三轴稳定卫星采用动量轮提供其姿态控制力矩,利用磁力矩器对动量轮进行饱和卸载,本文通过建立整星动力学、运动学、动量轮控制系统和近地空间磁场模型,进行仿真运行,研究整星剩磁矩与近地空间磁场相互作用及其对动量轮姿态控制系统的影响。

The reaction-wheel system is usually used to provide the attitude control torques of the LEO 3-axis attitude steady satellite, and at the same time, the magnetorquers are used in unloading of the reaction-wheel system. In this paper, the model of the satellite dynamic, the model of reaction-wheel control system and the model of the Earth magnetic field are built. The simulation of these models are run to study the interaction of the remanence disturb torques in the satellite and the space magnetic field around the Earth. The influence of the satellite attitude which is cased by remanence torques is also studied.