A mathematical model derived from spacecraft attitude dynamics is treated as an example to demonstrate its application.
以一个呈现混沌姿态运动的航天器动力学模型为例说明了该控制律的应用。
The error between satellite attitude dynamics and its linearized model can affect the attitude control precision.
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 model of spacecraft attitude dynamics and the attitude control technology are generalized.
对航天器姿态动力学模型和姿态控制技术进行了概括和总结。
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.
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；
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