建立卫星姿态动力学数学模型，并分析星体所受的外部扰动力矩。
Mathematic model of satellite attitude dynamic is set up, and external disturbance torque is analyzed.
卫星姿态动力学系统与其线性化模型之间的误差会影响姿态控制的精度。
The error between satellite attitude dynamics and its linearized model can affect the attitude control precision.
为验证模型有效性，将其应用于某三轴稳定对地定向卫星姿态动力学仿真中，得到了相应的太阳光压干扰力矩曲线。
As illustration, these models are applied to an attitude control dynamics simulation of a three-axis stability satellite and the corresponding toques were plotted in curves.
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