根据线性迭加理论实现微小卫星姿态磁控制

Micro-Satellite Magnetic Attitude Control Basing on Theory of Linearity Superposition

根据地磁力矩定向阻尼特性和线性迭加理论,提出仅用磁力矩器实现对地指向微小卫星三轴姿态稳定的控制律。推导了采用迭加补偿,并考虑附加磁矩影响时改进的卫星姿态动力学方程。理论分析和仿真结果表明,该控制律简单、姿态控制精度高。

According to the direction and damping characteristic of magnetic torque and the theory of linearity, the control scheme of three axis attitude stabilization for micro-satellite just using magnetic torque was presented in this paper. The attitude kinetic equation of micro-satellite and its improved form were also derived. The theory analysis and simulation results showed that the control law in this paper was simple, which would provide the improved attitude precision.