A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.


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    Title :

    Load relief control of launch vehicle using aerodynamic angle estimation


    Contributors:
    Oh, Gyeongtaek (author) / Park, Jongho (author) / Park, Jeongha (author) / Lee, Hongju (author) / Kim, Youdan (author) / Shin, Sang-Joon (author) / Ahn, Jaemyung (author) / Cho, Sangbum (author)


    Publication date :

    2018-06-01


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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