航天器长期在轨运行期间，空间磁场与其自身磁矩相互作用的累积，会对航天器的姿态造成较大影响，加重姿态控制系统负担，降低航天器的可靠性。文章分别针对航天器轨道计算及地磁场模型的使用，对航天器地磁干扰力矩数值的仿真进行了系统的研究，最终得到航天器在轨运行时地磁干扰力矩计算仿真方法。%During a long time of a spacecraft staying in its orbit, the accumulation of the interaction between the space magnetic field and the remnant magnetic moment has a great impact on the attitude of the spacecraft. For a 3-axis stabilised spacecraft, there will be an interference torque, which will shift the stable axis of a spacecraft. The attitude control system will have to do extra work, and the reliability of the spacecraft will be affected. The satellite orbit calculation and the geomagnetic field model are used in the numerical simulation of the geomagnetic disturbance torque on the spacecraft. The method for simulating the geomagnetic disturbance torque is finally established for the operation of the spacecraft on orbit.
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