A linear modal control algorithm is applied to the NASA Oblique Wing Research Aircraft (OWRA). The control law is evaluated using a detailed nonlinear flight simulation. It is shown that the modal control law attenuates the coupling and nonlinear aerodynamics of the oblique wing and remains stable during control saturation caused by large command inputs or large external disturbances. The technique controls each natural mode independently allowing single-input/single-output techniques to be applied to multiple-input/multiple-output systems.


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    Title :

    Modal Control of an Oblique Wing Aircraft


    Contributors:

    Publication date :

    1989


    Size :

    49 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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