A 4.5 percent DC-10 derivative flexible model with active controls is fabricated, developed, and tested to investigate the ability to suppress flutter and reduce gust loads with active controlled surfaces. The model is analyzed and tested in both semispan and complete model configuration. Analytical methods are refined and control laws are developed and successfully tested on both versions of the model. A 15 to 25 percent increase in flutter speed due to the active system is demonstrated. The capability of an active control system to significantly reduce wing bending moments due to turbulence is demonstrated. Good correlation is obtained between test and analytical prediction.


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    Title :

    Experimental Investigation of Elastic Mode Control on a Model of a Transport Aircraft


    Contributors:

    Publication date :

    1981


    Size :

    212 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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