With the rapid development of aeronautics technology, hypersonic flying vehicle is playing an increasingly important role, yet control methods on such vehicle were stilled confined with classical PID (proportional, integration and differentiation) or its variations. In order to have better control performance, a switching control method was used to design the attitude control law for hypersonic missile, which guaranteed higher angle precise control than PID. Simulation results showed the effectiveness and the superiority of the proposed switching methods over the classical PID and other typical switching methods.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    A Novel Switching Control Method for Hypersonic Flying Vehicle



    Published in:

    Publication date :

    2014-10-08


    Size :

    4 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Towards High Efficiency Hypersonic Flight-Hypersonic Bi-Directional Flying Wing

    Nieto, A. / Perez, K. / Rojas, M. et al. | British Library Conference Proceedings | 2012


    METHOD OF LAUNCHING A HYPERSONIC FLYING AIRCRAFT

    KUZIN ALEKSANDR VLADIMIROVICH / MISHCHENKO ANATOLIJ PETROVICH / SHARKOV SERGEJ PETROVICH | European Patent Office | 2018

    Free access

    Towards High Efficiency Hypersonic Flight-Hypersonic Bi- Directional Flying Wing

    Nieto, Andy / Perez, Karen / Rojas, Marcus et al. | AIAA | 2012