Interest in oblique-wing aircraft has surfaced periodically since the 1940's. This concept offers some substantial aerodynamic performance advantages but also has significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes. This paper presents a technique for synthesizing a decoupling controller while providing the desired stability augmentation. The proposed synthesis procedure uses the concept of a real model-following control system. Feedforward gains are selected on the assumption that perfect model-following conditions are satisfied. The feedback gains are obtained by using eigensystem assignment, and the aircraft is stabilized by using partial state feedback. The effectiveness of the control laws developed in achieving the desired decoupling is illustrated by application to linearized equations of motion of an oblique-wing aircraft for a given flight condition.


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    Title :

    Decoupling Control Synthesis for an Oblique-Wing Aircraft


    Contributors:
    G. S. Alag (author) / R. W. Kempel (author) / J. W. Pahle (author)

    Publication date :

    1986


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Decoupling control synthesis for an oblique-wing aircraft

    Alag, G. S. / Kempel, R. W. / Pahle, J. W. | NTRS | 1986


    Decoupling control synthesis for an oblique-wing aircraft

    Alag, G. S. / Kempel, R. W. / Pahle, J. W. | NTRS | 1986


    Decoupling Control For Oblique-Wing Airplane

    Kempel, Robert W. / Pahle, Joseph W. / Alag, Gurbux S. | NTRS | 1992


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