抄録
We address nonlinear attitude control problem of flexible spacecraft. For this issue, we must consider elastic vibration of flexible structure. In this paper, we treat the affect of elastic vibration as uniformly bounded disturbance and derive stabilizing controller of flexible spacecraft by using backstepping method and concept of nonlinear damping. By the approach, boundedness and asymptotic stability of attitude angle and angular velocity of this system are shown to be guaranteed. Effectiveness of proposed method is verified by simulations.
