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.

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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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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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