The goal of this research is to formulate flight controllers for highly maneuverable munitions. Complex aerodynamic phenomena such as vortex interactions and flow separation exist on munitions flying at certain maneuvering conditions. Aerodynamic models are proposed to capture these mechanisms within an adaptive control framework. The adaptive control algorithm is derived and wrapped around a nominal optimal controller using inertial sensor feedback. The vehicle dynamics and flight control algorithms are implemented in simulation. Results indicate that only the adaptive algorithm recovers satisfactory control when encountering these complex aerodynamic phenomena.


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    Title :

    Adaptive Missile Flight Control for Complex Aerodynamic Phenomena


    Contributors:
    F. Fresconi (author) / B. Gruenwald (author) / T. Yucelen (author) / J. Sahu (author)

    Publication date :

    2017


    Size :

    40 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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