Mathematical Modeling and Nonlinear Attitude and Trajectory Tracking Control of a One Stage Rocket With Varying Mass

摘要

The thrust vector control (TVC) for a one-stage rocket with variable mass is considered. TVC control is used here to correct the rocket deviations from an intended parabolic trajectory and desired attitude angle during powered flight. A rigid body mathematical model with varying mass in the plane is presented. A nonlinear feedback controller together with a SDRE controller is designed. The effectiveness of the proposed mathematical model and control is illustrated through numerical simulations. By controlling the direction of the thrust vectors it is possible to control the angle of attack of the rocket. In this work only the pitch angle is considered. Only one liquid propellant thruster is used. It is also considered here only the flight period when the rocket propulsion system is firing and therefore the TVC is operative.