Airbus Operations Gmbh

Airbur Operations Gmbh

Karim Grase

Ichwan Zuardy

Axel Siegfried Herrmann

Paul Joern

Markus Mueller

Claas De Jong

Mathias Jessrang

Pierre C Zahlen

Alexei Vichniakov

Wolfgang Eilken

Memis Tiryaki

Paul Jörn

Marc Schimmler

Henning Scheel

M Ichwan Zuardy

Bernd Schwing

Dieter Hachenberg

Wolfgang Voege

Claudio Vultaggio

Thomas Konsolke

Lars Fiedler

Carsten Rowedder

Marianne Jacoba Reijerkerk

Matthias Jessrang

Jelle Bloemhof

Martin Röhrig

B Claudio Vultaggio

Martin Roehrig

Ichwan Muhammad Zuardy

Claudio B Vultaggio

Mathias Jeßrang

Simon Shone

A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Pressure bulkhead system

A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.

Sandwich structure

A pressure bulkhead () for an aircraft fuselage () having a sandwich structure () which defines a central axis () and which extends between a circumferential edge area (), wherein the sandwich structure () includes an inner cover layer (), an outer cover layer (), and a core layer (), which extends between the inner and outer cover layers () and connects them. The object of providing a pressure bulkhead () for an aircraft fuselage () which, even in the case of larger fuselage diameters, can particularly effectively absorb the occurring pressure forces and which can also be built with minimal weight, is achieved in that, between the inner and the outer cover layers (), in addition to the core layer (), a support structure () is provided, which is connected to the cover layers () and which extends from the inner cover layer () to the outer cover layer (), and in that the support structure () comprises at least one layer () which, viewed in a cross section () parallel to the central axis (), extends from a first section () of the edge area () to an opposite second section () of the edge area ().

Pressue bulkhead for an aircraft fuselage

A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Pressurized airplane fuselage, comprising a pressure bulkhead

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 pressure bulkhead comprises a plurality of material plies arranged one above the other, wherein each material ply contains reinforcing fibers embedded in a matrix material. The reinforcing fibers, in at least one first material ply are oriented in such a manner that their longitudinal axes lie in an angle range of &#xb1;2&#xb0; about a radial direction of the pressure bulkhead.

Pressure bulkhead and method for producing a pressure bulkhead

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 pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.

Pressure bulkhead for an aircraft and device as well as method for manufacturing an aircraft structural component

The invention relates to methods and to a manufacturing device for manufacturing a sandwich component. A semifinished product arrangement is soaked with a flowable matrix material, for example a resin, in particular by an infusion method. By using the method of the invention, inherent tensile stresses introduced by the respective method and remaining in the sandwich component to be manufactured are reduced, and moreover the risk of crack formation in the course of the process, afterwards and during operation of the sandwich component is minimized.

Method and manufacturing device for manufacturing a fiber compound sandwich component

The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.

Structural element for an aircraft or spacecraft and method for producing such a structural element

The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behavior of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behavior of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.

Structural element for an aircraft and spacecraft and method for producing a structural element of this type

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Hamburg, Germany

Karim Grase