Recent interest in oblique-wing aircraft has focused on the potential aerodynamic performance advantage of a variable-skew oblique wing over a conventional or symmetric sweep wing. Unfortunately, the resulting asymmetric configuration has significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes. Presented here is a decoupling control law synthesis technique that integrates stability augmentation, decoupling, and the direct incorporation of desired handling qualities into an output feedback controller. The proposed design technique uses linear quadratic regulator concepts in the framework of explicit model following. The output feedback strategy used is a suboptimal projection from the state space to the output space. Dynamics are then introduced into the controller to improve steady-state performance and increase system robustness. Closed-loop performance is shown by application of the control laws to the linearized equations of motion and nonlinear simulation of an oblique-wing aircraft.


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    Titel :

    Output Model-Following Control Synthesis for an Oblique-Wing Aircraft


    Beteiligte:
    J. W. Pahle (Autor:in)

    Erscheinungsdatum :

    1990


    Format / Umfang :

    30 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Model-Following Control for an Oblique-Wing Aircraft

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


    Model-following control for an oblique-wing aircraft

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