A procedure has been developed which utilizes finite element analysis methods in the contour assessment of formed wing panels. The procedure utilizes a finite element model reflecting the bi-directional stiffnesses of the panel in conjunction with local deviations from contour derived from reported inspection data. Final assembly fit-up forces are predicted and compared to the maximum allowable fit-up forces specified on the engineering drawing. The procedure also provides for the determination of local gap conditions with the panel subjected to the allowable fit-up forces. The local gap conditions are compared to the shimming allowances specified on the engineering drawing. These comparisons provide a basis for ascertaining the necessity for contour adjustments. Early detection of the need for contour adjustment minimizes the schedule impact and cost of the rework.


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    Title :

    Contour Assessment of Formed Wing Panels


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    General Aviation Aircraft Meeting and Exposition ; 1985



    Publication date :

    1985-04-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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