Airbus Deutschland Gmbh

Herwig Assler

Hans-Juergen Schmidt

Alexei Vichniakov

A seat mounting rail suitable for mounting passenger seats to a floor, for example an aircraft cabin floor, is divided into an upper section for securing a seat and a lower section for mounting the rail to the floor. The upper section is preferably made of a titanium alloy. The lower section is preferably made of an aluminum alloy. Both sections are connected to each other by an interconnection preferably in the form of a metallurgical bond formed under heat and pressure. A bonding metal foil compatible with the metals of which the rail sections are made is used for enhancing the bonding strength of the interconnection.

Seat mounting rail, particularly for a commercial aircraft

A lightweight, laminated structural component, such as a skin section for an aircraft fuselage, is constructed of at least two sheet metal plies that are adhesively bonded to each other. One ply is an uninterrupted ply. The other ply is a lattice with open fields surrounded by strip shaped lands which fortify load exposed areas of the lamination. The open fields of the lattice make mechanical or chemical pocketing operations unnecessary. By shaping and positioning the strip shaped lands including struts in accordance with load patterns to which an aircraft skin is exposed in use, the skin characteristics can be tailored as required.

Lightweight structural component made of metallic ply materials

A rivet splice that holds an upper and a lower sheet metal end portion together includes at least one row () of rivets that is subject to dynamic loads and a further row () of rivets that holds the sheet metal end portions together so that a limited sliding motion between the sheet metal end portions is possible. The further row () of rivets is positioned between an end edge (A) of an upper sheet metal end portion and the at least one row () of rivets. The limited sliding motion provides a load relief of the at least one row of rivets thereby reducing the starting of cracks at the walls of the rivet holes and impeding the spreading of cracks.

Splicing for interconnected thin-walled metal structures

A metallic structural component for an aircraft includes stiffening profile members integrally formed or connected onto a skin sheet. Each stiffening profile member includes a first part integrally connected to the skin sheet, and a second part non-integrally connected to the first part so as to form an internal boundary surface within the multi-part stiffening profile member. If a crack forms in the skin sheet and propagates into the first part of the stiffening profile member, the internal boundary surface resists the further propagation of the crack past this boundary surface. The crack propagation resistance is improved, the remaining strength of the structural component after formation of a crack is increased, and the overall structural component is light in weight. The outer contour of the stiffening profile member is not affected by the provision of the separate first and second parts or the internal boundary surface therebetween.

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Jork, Germany

Herwig Assler