发明名称 |
INTEGRAL STRUCTURAL SHELL COMPONENT FOR AN AIRCRAFT AND METHOD OF MANUFACTURING THE SAME |
摘要 |
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 re- quirements. The manufacturing method is very simple and economical.
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申请公布号 |
CA2337725(A1) |
申请公布日期 |
2001.08.22 |
申请号 |
CA20012337725 |
申请日期 |
2001.02.22 |
申请人 |
ZINK, WALTER;BRENNEIS, HARTMUT |
发明人 |
ZINK, WALTER;BRENNEIS, HARTMUT |
分类号 |
B64C1/12;(IPC1-7):B64C1/00;B64F5/00;F16S1/10 |
主分类号 |
B64C1/12 |
代理机构 |
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代理人 |
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