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.


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    Title :

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


    Additional title:

    Smart Innovation, Systems and Technologies



    Conference:

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



    Publication date :

    2024-10-31


    Size :

    14 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English