Integral structural shell component for an aircraft and method of manufacturing the same
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United States of America Patent
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Feb 3, 2004
Grant Date -
Aug 23, 2001
app pub date -
Feb 22, 2001
filing date -
Feb 22, 2000
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Abstract
A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.
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