Airbus Operations Gmbh

Mathias Jessrang

Karim Grase

Ichwan Zuardy

Markus Mueller

Claas De Jong

M Ichwan Zuardy

Carsten Rowedder

Martin Roehrig

A method of producing a composite panel member, especially a composite panel member having a foam core sandwich structure for an airframe of an aircraft or spacecraft, including: providing at least one fiber reinforcement layer in a panel molding tool; moving or transferring the molding tool to an infusion station that is pre-heated to an infusion temperature and infusing the fiber reinforcement layer in the molding tool with a polymer resin; moving or transferring the molding tool to a curing station that is pre-heated to a curing temperature and curing the at least one resin-infused fiber reinforcement layer in the molding tool to form a composite panel member; and moving or transferring the molding tool to a cooling station that is provided at a cooling temperature and cooling the composite panel member in the molding tool.

Method and system for producing a panel member for an airframe

A device for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section. The device includes a tool mold configured and arranged to be continuously traversed in the feed direction for purposes of positioning module components relative to one another. A pressure application head is configured and arranged to be traversed in the feed direction and in the counter-direction for purposes of connecting the module components. The pressure application head is configured and arranged to move at the same speed and in the same direction as the continuously moving tool mold, and then in an opposite direction, in order to connect to each section of the fiber reinforced thermoplastic composite during reciprocal movement.

Device for producing a fiber-reinforced thermoplastic composite component

A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

Pressure fuselage of an aircraft with a fuselage shell and a pressure bulkhead disposed therein

A method for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section by means of a pressure application head that can be traversed in the feed direction and in the counter-direction. A device for the execution of the method is also disclosed.

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Hamburg, Germany

Mathias Jessrang