The tailsitter aircraft merges the endurance and speed of fixed-wing aircraft with the flexibility and VTOL abilities of rotorcraft. Because of the requirement to be functional at a full range of attitudes, quaternions are typically employed to calculate attitude error. Attitude control is then accomplished by using the vector component of the error quaternion to drive flight control surfaces. This paper demonstrates that this method of driving the flight control surfaces can be suboptimal for tailsitter type aircraft and can lead to undesired vehicle movement. An alternate method of calculating attitude error called resolved tilt-twist is improved and validated. The resolved-tilt twist method is implemented in hardware and hardware-in-loop simulation results are presented.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Tailsitter attitude control using resolved tilt-twist


    Contributors:


    Publication date :

    2014-05-01


    Size :

    3470306 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Attitude Control of a Tilt-rotor Tailsitter Micro Air Vehicle Using Incremental Control

    Lovell-Prescod, Gervase H.L.H. / Ma, Ziqing / Smeur, Ewoud J.J. | IEEE | 2023


    Tailsitter VTOL flying wing aircraft attitude control

    Liang, Jianjian / Fei, Qing / Wang, Bo et al. | IEEE | 2016


    TAILSITTER AIRCRAFT

    OHASHI TOSHIO | European Patent Office | 2020

    Free access

    TAILSITTER AIRCRAFT

    OHASHI TOSHIO | European Patent Office | 2020

    Free access

    Design and Control of A Tilt-Rotor Tailsitter Aircraft with Pivoting VTOL Capability

    Ma, Ziqing / Smeur, Ewoud J. J. / de Croon, Guido C. H. E. | ArXiv | 2025

    Free access