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 .
飞行器姿态控制的驱动扭矩与系统的转动惯量之间存在密切的联系。
The driving torque requirements for attitude control of a space vehicle are typically closely related to the mass moment inertia of the system.
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.
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