Recent advances in composite materials and active control principles have lead to renewed interest in the Forward Swept Wing (FSW) as a feasible aircraft design alternative. Sweeping a wing forward results in low static divergence speeds and additional aeroelastic instabilities which must be adequately controlled for an aircraft employing this wing design to have an acceptable flight envelope. This thesis seeks to demonstrate the utility of applying active feedback control principles to suppress aeroelastic instabilities associated with a FSW design. Analytical studies investigate the potential of applying optimal control theory techniques to synthesis of active flutter suppression control laws. For an example application, a FSW/fuselage model previously analyzed by Thomas Noll of AFFDL was used. Through use of Pade approximants to represent unsteady aerodynamic forces, the equations of motion are written in standard state space form. Linear optimal regulator theory is then applied to determine particular sets of gains which minimize a quadratic cost function in terms of the states and controls. Control laws are developed at a design flight condition which increases the onset of the lowest instability speed 20% above the wing bending/torsion instability speed. The optimal control law is then applied at off-design flight conditions to assess the robustness of the optimal regulator. Program listings are included.


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    Titel :

    Active Suppression of Aeroelastic Instabilities on a Forward Swept Wing Using a Linear Optimal Regulator


    Beteiligte:
    G. J. Pasquini (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    102 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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