Abstract The attitude control of a launch vehicle is a challenging task due to the dramatically varying vehicle dynamics along a flight path. The objective of this paper is to design a switching robust control strategy for launch vehicles, applied here to a notional nanosat launch vehicle. In order to control the rocket along a trajectory ascending through the Earth's atmosphere, a set of operating points at different times along the flight path are selected, the corresponding dynamics models of the rocket are obtained via linearization, and a robust H controller is designed for each operating point using the linear matrix inequality approach. These controllers are applied to the nonlinear plant model via a switching strategy when the rocket flies along the flight path. Both linear and nonlinear simulation results are given to show the performance of the closed-loop system.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Switching robust control for a nanosatellite launch vehicle


    Beteiligte:
    Lu, Bei (Autor:in) / Falde, Derek (Autor:in) / Iriarte, Estuardo (Autor:in) / Besnard, Eric (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2015-01-22


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Nanosatellite Launch Adapter System (NLAS)

    Yost, Bruce D. / Hines, John W. / Agasid, Elwood F. et al. | NTRS | 2010


    Nanosatellite Launch Adapter System (NLAS)

    B. D. Yost / J. W. Hines / E. F. Agasid et al. | NTIS | 2010


    Nanosatellite Cluster Launch Collision Analysis

    Santoni, F. | Online Contents | 2013


    ELaNa: Education Launch of Nanosatellite

    Skrobot, Garrett | NTRS | 2011