Airbus Operations Gmbh

Airbus Deutschland Gmbh

Marc Schimmler

Carsten Paul

Wolfgang Eilken

Memis Tiryaki

Karim Grase

Wolfgang Schulze

Thomas Kruse

Lars Krog

Bernd Raeckers

Thomas Grauerholz

Alastair Tucker

Bernd Räckers

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 method for the manufacture of a fiber composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mold core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fiber composite component with a multiplicity of openings, each of which is edged by an integral collar.

Method and a device for the manufacture of a fibre composite component, and a fibre composite component

An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.

Aircraft door and a method for the manufacture of an aircraft door of this type

A holder assembly for a line installation in an opening of a support structure of an aircraft, includes at least one holder element to mount a line that is guided through the opening, with the line featuring a clamping section, arranged radially on the outside, to be attached to the opening as well as at least one central receiving section to fix the line, wherein the receiving section of a first holder element encompasses the line hook-like, and the receiving section of at least a second, oppositely positioned holder element also encompasses the line hook-like such that both hook-like receiving sections encompass the line.

Holder assembly for a secure line installation in structure openings of aircraft

A connecting device having two curved ribs of an aircraft or spacecraft, with: a coupling element which can be connected by means of predetermined coupling sections to respective connecting sections of the two ribs; wherein at least the predetermined coupling sections of the coupling element are rectilinearly designed; and wherein at least the respective connecting sections of the two ribs each have rectilinearly running inner belt regions for a respective rectilinear connection of the predetermined coupling sections of the coupling element.

Connecting arrangement comprising a coupling element and two curved ribs of an aircraft or spacecraft

The present invention relates to an intercostals for an aircraft or space craft for diverting a load from a first rib to a second rib and/or a skin of the aircraft and/or space craft, with at least one opening region for guiding through system lines or the like, wherein the intercostal has a traverse that is movable at least between a first and a second position, wherein the traverse in the first position is provided for forming a force flow for diverting a load between the first rib and the second rib, and in the second position reveals the opening region from a predetermined side.

Intercostal for an aircraft or spacecraft

An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.

Intercostal for aircraft

A locking device contains a displaceable bolt and internal and external control components. In a normal state of the locking device, the internal control component and the external control component displace the bolt and, in an override state of the locking device, only the external control component engages the bolt in order to displace it.

Growing community of inventors

Heinbockel, Germany

Marc Schimmler