Attitude switching control of spacecraft based on Hamilton system

In modern space missions, such as space rendezvous and docking, actuator switching, booster stage separation for carrier rockets, the instantaneous mass or structure variations are exist. A Hamilton system based spacecraft attitude switching control scheme is proposed. The passivity control law is designed based on the Hamilton system model of spacecraft. A dynamic inversion method is used to compensate the nonlinear dynamic and establish the linear switched system approach. Asymptotic stability condition with instantaneous mass or structure variation existence is given. The energy based control law ensures the robustness and anti-disturbance ability of each switched subsystem. On the other hand, the proposed scheme can guarantee the stability with the presence of the instantaneous mass or structure changes. The results of numerical simulation validate the proposed scheme has strong robustness and can achieve accurate command tracking.