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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    Titel :

    Model-following output feedback controller for oblique-wing aircraft


    Beteiligte:

    Erscheinungsdatum :

    01.01.1987


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch







    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. / KEMPEL, R. / PAHLE, J. et al. | AIAA | 1986