Abstract
The ability of Reusable Launch Vehicles (RLVs) to carry out multiple missions would significantly reduce the operational expenses for space exploration. However, the control and coordination of RLVs during flight operations present many design challenges. For instance, RLVs travel from earth's surface to space in uncertain environments causing the values of the parameters for the RLVs' dynamic equations not constant. Therefore, various researchers have proposed several adaptive control methods as well as digital control systems for RLVs. We have proposed a digital adaptive feedback linearization control method with time-scale separation using Dynamic Inversion method and Kalman Filter for the control system of a winged rocket. Furthermore, Euler angles are commonly used in calculations related to kinematics of rigid body dynamics. Quaternion is often being used in attitude control system of a spacecraft compared to Euler angles due to the relation between the Quaternion and its angular rate is linear and it has no singular point. In this paper, we propose a digital adaptive feedback linearization control method for the winged rocket using Quaternion. Simulation results show the effectiveness of the proposed method.
