Orbit Injection Control of Launcher via a Fully-Actuated System Approach

This study handles the control problem of the orbit injection phase for a launcher. By doing so, the coupled position and attitude dynamics of the launcher is firstly formulated. A partial integrated guidance and control (IGC) scheme is then proposed based on the backstepping philosophy. On the one hand, since the position error sub-dynamics possesses to be a two-order fully-actuated nonlinear system, a parametric design technique is utilized to construct the command thrust control vector by using the high-order fully actuated system theory. On the other hand, the control torque is designed within the Lyapunov framework to complete the partial IGC scheme. Finally, numerical simulation is given to verify the effect of the proposed control scheme.