This paper presents a methodology for the development of an UAV Autopilot System, based on modeling, instrumentation and a control law, with the purpose of stabilizing the airplane attitude. Firstly, were made experimental test flights by manual control for obtaining the longitudinal model parameters using the Matlab toolbox called "System Identification Tool". The model is represented by a transfer function of the pitch angle with respect to the elevator into an open-loop system. The system is stabilized using a PD controller (derivative-proportional) tuned with poles placement method. The zero exclusion principle is used to compute the robustness margin of the closed-loop system. Different experiments were made in order to validate theoretical results which are presented at the end of this work.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Robust Control Design Techniques Applied to Mini‐Rotorcraft UAV: Simulation and Experimental Results

    Guerrero, José Alfredo / Romero, Gerardo / Lozano, Rogelio et al. | Wiley | 2013


    H[unknown]-LTR Technique Applied to Robust Control of Propulsion-Controlled Aircraft

    Hitachi, Y. / Liu, H. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2009




    FRAME DESIGN PARAMETERS AND TECHNIQUES APPLIED IN SAE'S COLLEGIATE MINI BAJA COMPETITION

    Schumacher, R. / Society of Allied Weight Engineers | British Library Conference Proceedings | 2000