抄録
In this paper, an on-orbit inspection system of a separable inspection device (a deputy satellite) controlled with Coulomb force is presented. The deputy satellite performs unidirectional inspection which is an application of this system and the deputy satellite inspects a part of the surface of the main satellite maintain the relative position to the main satellite continuously. A guidance, navigation and control method applied to the deputy satellite during a separation guidance operation from the main satellite to a specified inspection position is proposed. It is investigated with a numerical simulation whether the proposed separation guidance operation succeeds or not to arbitrary target points in defined target area, and the optimization of proposed method is performed from various perspectives of position control accuracy and electricity consumption.
