抄録
In this paper, we consider six dof (degree of freedom) control of rigid body spacecraft via nonlinear H∞ control method. Firstly, the motion equation of the six dof rigid body spacecraft is described and the error system is derived. Secondly, we show that the error system can be stabilized by PD control law with the constant coefficient as the case of attitude control and that it guarantees structural robust stability with respect to physical parameter error. Thirdly, based on nonlinear. H∞ control, the design conditions of a gain that the control law becomes suboptimal H∞ state feedback control are given. Finally, effectiveness of the control methods is verified by simulations.
