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本文研究了大型柔性结构空间飞行器的控制问题。采用设定模态法,将系统化为常微分方程组所描述的系统。此系统是非线性的,被控运动是绕中心毂体的转动机动运动,并详细的讨论了变结构控制规律的应用。
This paper studies the control of large flexible spacecraft. Using modal set-up, the system is systematized to the system described by the system of ordinary differential equations. The system is non-linear. The controlled motion is the rotational maneuvering around the central hub body, and the application of variable structure control law is discussed in detail.