Control System Design for the Powered Ascent of Winged Rocket Based on Dynamic Inversion Theory

Flight dynamics of winged reusable space transportation system strongly depends on the flight environment such as the dynamic pressure and Mach number. Therefore, classical PID attitude controller is not fully applicable to the complex and sudden change in flight environment. On the other hand, the dynamic inversion theory cancels the nonlinear dynamics by state feedback and gives desired linear response. In this paper, the control system design for the powered ascent of winged rocket based on dynamic inversion theory is proposed. In order to determine the command values of control devices (i.e., aileron, elevator, rudder and thrust vector control) from the required control moment around each axis, the minimum-energy control is employed.