星敏感器是为空间飞行器姿态控制系统提供姿态信息的测量系统。
The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
本文针对空间飞行器姿态控制问题，给出了一种基于优化控制与有限时间控制技术的控制方法。
In this paper, a control approach based on optimal control and finite-time control technology is derived for spacecraft.
本文应用区间矩阵的理论，研究三轴稳定的挠性空间飞行器姿态控制系统的鲁棒稳定性分析问题。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
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