Adaptive Fully Actuated Prescribed Performance Control for Combined Spacecraft with Unknown Inertial Parameters

This paper discusses the problem of attitude and orbit control for a type of combined spacecraft in which the inertia parameters are unknown. Firstly, the attitude and orbit dynamics for the combined spacecraft are constructed by using the Euler attitude dynamics and the orbit dynamics. The fully actuated system model of attitude and orbit dynamics is transformed into a linear regression equation related to unknown inertia parameters, and an identification method involving dynamic regressor extension and mixing approach is employed to identify the unknown inertia parameters. Then, a prescribed performance function is introduced to obtain a fully actuated error system model for attitude and orbit. Furthermore, an adaptive fully actuated prescribed performance controller is designed to ensure that the combined spacecraft satisfies the prescribed transient and steady-state performance during the attitude and orbit control process. The stability of the fully actuated system is proved by constructing the Lyapunov function. Finally, the effectiveness and practicality of the proposed control method are validated using the numerical simulation.