Airbus Operations Gmbh

Thomas Hoffmeister

Pierre C Zahlen

Alexei Vichniakov

Axel Siegfried Herrmann

Dirk Humfeldt

Ichwan Zuardy

Tassilo Witte

Benedikt Kircher

Joachim Piepenbrock

Markus Mueller

Markus Müller

Alexander Engels

Mohamed-Mourad Sayeh

M Ichwan Zuardy

Julian Kupski

Felix Helfrich

Dirk Fritsche

Markus MÜLLER

A lightweight overhead stowage compartment comprising a self-supporting hull having an open cross-section forming a stowage space and an opening to the stowage space, wherein in a longitudinal direction of the self-supporting hull any section of the self-supporting hull has an open end in the front and rear. The stowage compartment includes a vertical connector configured to be placed into the stowage space, wherein the vertical connector is mounted to the self-supporting hull at vertical sides of the vertical connector in a force transferring manner. At least one lid is mounted at an arbitrary section of the self-supporting hull and configured to close the opening to the stowage space.

Lightweight overhead stowage compartment and method of installing the same

A system for lacquer transfer is disclose having a device for lacquer transfer. The device includes a frame, a transfer roller with a circumferential lateral wall, and a slit nozzle for dispensing lacquer. The slit nozzle is connected to the frame. An outside contact surface of the lateral wall includes several depressions. The transfer roller is mounted rotatably to the frame. The slit nozzle is arranged contactless to or in direct contact with the outside contact surface of the lateral wall for dispensing lacquer into respective depressions in the lateral wall while the transfer roller is rotated. The transfer roller is configured to roll with the outside contact surface on a work surface of a work piece for transferring the lacquer from the depressions to the work surface.

System for lacquer transfer

An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

Assembly having individual components made of a fibre-reinforced composite material

A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

Method for producing a smooth aerodynamic surface of an aircraft component

A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

Pressure bulkhead for an aircraft fuselage

A device for shaping a semi-finished fiber product for manufacturing a C-shaped or I-shaped former, and including clamping mechanisms and a forming tool. Each clamping mechanism has a first and a second clamping element and together they hold a semi-finished fiber product along two longitudinal and opposite edges. The clamping elements and forming tool move in a coupled manner between starting and end positions. During this movement, the longitudinal edges of the semi-finished fiber product are transformed into a curved shape, wherein a length of one of the longitudinal edges of the semi-finished fiber product does not change and a length of the other longitudinal edge becomes greater. During the movement, the forming tool is transformed into a curved shape and guided relative to the clamping elements against the semi-finished fiber product such that the semi-finished fiber product is deep drawn over the forming tool.

Device and method for shaping a semi-finished fiber product

A curing tool for a shell component, includes a first tool component, which is a polyhedron and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is a polyhedron, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.

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Hamburg, Germany

Thomas Hoffmeister