Metallic aircraft component

Stock material or miscellaneous articles – All metal or with adjacent metals – Composite; i.e. – plural – adjacent – spatially distinct metal...

Reexamination Certificate

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Details

C428S600000, C428S636000, C244S119000

Reexamination Certificate

active

08039115

ABSTRACT:
The invention relates to metallic aircraft components which can preferably be used for aircraft structures in the fuselage region. A damage-tolerant design is usual for aircraft components in the fuselage region. It is the object of the invention to provide metallic components in which metal sheets are connected to one another by weld seams which have an improved damage tolerance behavior and fatigue crack propagation behavior. In an aircraft component in accordance with the invention, at least two metal sheets are welded to one another as butt joints. The centerline of the join line of the weld seam is predetermined by the outer edge contour of the metal sheets connected to one another. In this connection, it is formed deviant from a continuously straight line shape such that the total length of the weld seam is increased by changes in direction periodically occurring at the edge contours engaging into one another in a complementary manner.

REFERENCES:
patent: 1773068 (1930-08-01), Vienneau
patent: 5505365 (1996-04-01), Olsen
patent: 6048628 (2000-04-01), Hillmann et al.
patent: 169919 (1951-12-01), None
German Office Action for International Application DE102006046080.4.
German Office Action for International Application DE102006046080.4 Apr. 2007.

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