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.
Contour Assessment of Formed Wing Panels
Sae Technical Papers
General Aviation Aircraft Meeting and Exposition ; 1985
01.04.1985
Aufsatz (Konferenz)
Englisch
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