Airbus Operations Gmbh

Axel Sauermann

Rolf Bense

Eugen Gorr

Dirk Bausen

Peter Freimark

Thomas Opschondek

The invention relates to a method of connecting two fuselage sections () formed by a fiber-reinforced plastics material, in particular wound fuselage sections () for aircraft fuselage cells, having a multiplicity of stringers () arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (), with the formation of a transverse joint (). In order to be able in particular to join together wound CFRP fuselage sections so that simple tolerance compensation is made possible in a continuous, industrial production process, the method according to the invention comprises the following steps: aligning a first and a second fuselage section () with respect to one another, heating and adapting at least one transverse butt strap (), formed by a fiber-reinforced thermoplastic material, in such a way that tolerance compensation between differing cross-sectional geometries of the first and second fuselage sections () is made possible, or heating at least one end region () of a second fuselage section () formed by a fiber-reinforced thermoplastic material, and joining together the two fuselage sections ().

Method for joining two fuselage sections by creating a transverse butt joint as well as transverse butt joint connection

A method for final assembly of at least two aircraft includes assembling the at least two aircraft in a transverse direction on a carousel, the at least two aircraft disposed side-by-side, and rotating the carousel on a vertical rotation axis 360&#xb0;.

Method and apparatus for the final assembly of aircraft

A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area.

Aerodynamic fairing device, aircraft component arrangement with an aerodynamic fairing device and method for installing such a fairing part

A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.

Clamping device and method for assembly of stringer couplings

Disclosed is a method for producing a releasable seal with a sealing compound between two fairing parts, in particular between two fairing parts for the wing-fuselage fillet of aircraft, including the steps of applying adhesive strips to respectively opposite edges, of the fairing parts and outer surfaces adjacent to them of the fairing parts; filling a sealing joint extending between the opposite edges with the sealing compound; and removing the adhesive strips after the curing of the sealing compound. This makes it possible to provide a re-releasable seal with a sealing compound which is curable or cures on its own in air between two fairing parts without the use of release agents. Also disclosed is the use of adhesive strips for carrying out this method.

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Helmste, Germany

Axel Sauermann