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.
结果表明设计出的新型太阳帆板驱动机构对卫星姿态动力学和控制具有重大影响，能够明显改善卫星姿态控制的效果。
Results showed that the new driving mechanism has significant influence on dynamics of satellite and could improve attitude control performance.
所得结果不仅适用于具有大型运动部件的航天器的姿态动力学分析及控制系统设计，也适用于灵敏小卫星的相应研究。
The proposed results are useful to the attitude dynamic analysis and control system design for not only the spacecraft with large rotation parts, but also the agile small satellite.
在挠性卫星动力学模型的基础上，建立了只考虑太阳帆板三阶振动模态的挠性卫星三轴姿态控制模型。
The three-axis attitude stabilization system of the flexible satellite has been studied, in which three basic vibration modes of the solar array have been considered.
由于地磁场的方向在轨道上周期变化，卫星的姿态动力学方程是一个线性周期系统。
Since the geomagnetic field varies periodically on orbit, the dynamics of satellite is a linear periodic system.
建立了小卫星相对轨道和姿态的误差动力学模型，根据作业任务和姿态指向要求确定了小卫星相对轨道和姿态的期望运动；
Positional and attitude error dynamics model of small satellite relative to a target satellite was derived, then the desired relative orbit and desired attitude of small satellite were designed.
建立了小卫星相对轨道和姿态的误差动力学模型，根据作业任务和姿态指向要求确定了小卫星相对轨道和姿态的期望运动；
Positional and attitude error dynamics model of small satellite relative to a target satellite was derived, then the desired relative orbit and desired attitude of small satellite were designed.
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