A variable-skew oblique-wing offers a substantial aerodynamic performance advantage for aircraft missions that require both high efficiency in subsonic flight and supersonic dash or cruise. The most obvious characteristics of the oblique-wing concept is the asymmetry of the wing-skew angle that causes a 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 use of output feedback in control law synthesis without the requirement of state estimation is presented. An explicit model-following control system with output feedback is developed. The effectiveness of the control laws developed in achieving the desired decoupling is illustrated for a given flight condition for an oblique-wing aircraft.


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    Title :

    Model-following output feedback controller for oblique-wing aircraft


    Contributors:

    Publication date :

    1987-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







    Model-following control for an oblique-wing aircraft

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


    Model-following control for an oblique-wing aircraft

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