The launch vehicle of a spacecraft involves longitudinal and latitudinal control. The longitudinal behavior of a launch vehicle is the primary focus of this paper. The main parameter is the attitude angle that is to be controlled considering the launch vehicle rigid body equations. The controller designed is a PID, where integral and derivative gains are obtained using proportional LQR optimization. The controller synthesis is based on the desired specifications of nominal plant and relative dominance. The efficacy of the proposed technique is validated by its robustness in the presence of perturbations.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Control of Attitude Trajectory of Launch Vehicle Using Optimal LQR-Based PID Controller


    Weitere Titelangaben:

    Smart Innovation, Systems and Technologies


    Beteiligte:
    Jha, Pradeep Kumar (Herausgeber:in) / Jamwal, Prashant (Herausgeber:in) / Tripathi, Brajesh (Herausgeber:in) / Garg, Deepak (Herausgeber:in) / Sharma, Harish (Herausgeber:in) / Mohan, Ambili (Autor:in) / Sivadas, Meera (Autor:in) / Samuel, Elizabeth Rita (Autor:in)

    Kongress:

    Congress on Control, Robotics, and Mechatronics ; 2024 ; Warangal, India February 03, 2024 - February 04, 2024



    Erscheinungsdatum :

    31.10.2024


    Format / Umfang :

    14 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch