Orbital and Attitude Cooperative Control of Fly-Around Small Satellite

This paper deals with the problem of controlling both orbital and attitude states for a fly-around small satellite during proximity operations. Firstly, We derive the six degree of freedom error dynamics model. Then, for the uncertainties such as mass and inertia moment, we put forward an adaptive output feedback control method that can be used to solve above control problem and design the control law when considering translational and attitude coupling. Finally, the simulation results show that the designed control law is effective and the control method is feasible.