Airbus Operations Gmbh

Airbus Deutschland Gmbh

Robert Alexander Goehlich

Alexei Vichniakov

Daisuke Hirabayashi

Holger Frauen

Cihangir Sayilgan

Steffen Biesek

Ingo Krohne

Malte Sander

Rolf Bense

Kai Fink

Sven Chromik

Atsushi Kanda

Marco Pacchione

Rainer Schildt

Robert Weidner

Frank Neuhaus

Yuichiro Aoki

Yutaka Iwahori

Marc Fette

Yoshiyasu Hirano

Christian Kulik

Johannes Maslennikov

Michael Kreimeyer

Jens Wulfsberg

Zhejun Yao

Hikaru Hoshi

Dirk Groβ

Mihaela Colceriu

Sebastian Dyllong

Alexander Gahn

Matthias Van Hove

Daniel Wenninger

Gaby Soehner

Karl-Hinrich Herbst

Michel Bädker

Clara Marie Hauser

Simon Braun

A mobile manufacturing module comprising a platform configured to receive and support one or more interchangeable manufacturing elements and engageable with a removable positioning device that when engaged is configured to enable movement of the platform relative to a work piece, and one or more supports connected to the platform that are configured to contact a floor in order to support the platform when the removable positioning device is disengaged.

Mobile manufacturing module

A wearable manufacturing assistance device () for supporting a manufacturing tool (), the manufacturing assistance device () includes a body unit () including a fastener () for fastening the body unit () to the back () of a technician () in a wearing position (), and an arm member () which has an attachment end () attached to the body unit () and a tool end () opposite to the attachment end (), wherein at the tool end () a mounting device () for mounting the manufacturing tool () to the arm member () is provided. While the wearable manufacturing assistance device () is fastened to the back () of the technician () and is in a wearing position (), the arm member () extends from the attachment end () at the body unit () over a shoulder () and laterally past a head () of the technician ().

Wearable manufacturing assistance device

A support device, in particular an assembly support device for stabilizing a body part of a person includes a plurality of hinged-together elements designed to at least partially envelop a body part of a person, so that the plurality of hinged-together elements collectively form a flexible shell for the body part of the person. The flexible shell is designed to transfer a portion of a load acting on the body part of the person in order to stabilize the body part of the person. A vehicle, to which is secured an assembly support device, as well as a method for stabilizing a body part of a person during the assembly of a vehicle are also described.

Support device for stabilizing a body part of a person

A method of installing a fixture or bracket in a fuselage structure of an aircraft or spacecraft. The method includes arranging an apparatus in, on or adjacent the structure, pre-treating a surface region of the structure by heat ablation using the apparatus and forming the fixture in situ on the structure at the pre-treated surface region using the apparatus based on a digital model of the fixture. The fixture is installed by connecting the fixture to the structure at the pre-treated surface region as the fixture is formed.

Method of installing a fixture and associated apparatus

A process for manufacturing an integrated shell element including: providing a shell element lay-up tool with an upper tool surface; laying-up a resin impregnated fibers on the upper tool surface to form the shell element; providing on the resin impregnated fibers a stiffener element layup tool having surfaces to support a stiffener element structure; laying-up resin impregnated fibers on the stiffener element lay-up tool to form the stiffener element; curing in a single step the resin impregnated fibers such that the fibers forming the shell element and the fibers forming the stiffener element are laminated into an integrated shell element having a longitudinal or transversal stiffener element; and separating the integrated shell element from the shell element and stiffener element lay-up tools.

Integrated lamination process for manufacturing a shell element

This relate to a method for attaching a component to a fuselage section of an aircraft or spacecraft. In a step of the method, a rail is arranged within a fuselage section of an aircraft, which rail extends in a longitudinal direction of the fuselage section. In another step, a support structure is movably mounted to the rail such that the support structure can be moved along the rail in the longitudinal direction of the fuselage section. The support structure comprises a positioning unit for positioning a tool for attaching the component to the fuselage section at a location where the component is to be attached to the fuselage section. The embodiments also relate to a device for attaching a component to a fuselage section of an aircraft.

Method and device for attaching an aircraft or spacecraft component to a fuselage section

A method of installing a fixture, such as a bracket, in a fuselage structure of an aircraft includes the steps of: providing or generating a three-dimensional digital model of the fixture; arranging a head of an additive manufacturing apparatus in the fuselage structure; and forming the fixture in situ in the fuselage structure with the head of the additive manufacturing apparatus based upon the digital model of the fixture. The fixture is installed in the fuselage structure by bonding or fusing the fixture to the fuselage structure as the fixture is formed. A fixture, such as a bracket, which is generated in situ in a fuselage structure of an aircraft based upon a three-dimensional digital model, wherein the fixture is bonded or fused to the fuselage structure as the fixture is formed.

Method of installing a fixture

A robot system for carrying out a plurality of operations during assembly or maintenance of an aircraft or spacecraft includes a first robot having a base portion, a movable robot arm having a first coupling portion, and a first control means for controlling the robot arm, a plurality of second robots having movement means, a drive portion operable to drive the movement means, a tool portion having a tool for carrying out a specific one of the operations, a second coupling portion adapted to be selectively and releasably coupled with the first coupling portion in a predetermined positional relationship, and a second control means for controlling the respective second robot. The first and second control means are adapted to control the drive portion of one of the second robots and the robot arm to couple the first coupling portion and the respective second coupling portion in the predetermined positional relationship.

Robot system and method of operating a robot system

A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.

Method for the assembly of an aircraft fuselage and fuselage manufacturing station

A mounting system includes a first and second mounting part having a first and second base part with a first and second plurality of first and second locking means respectively, for mounting two components to each other. Each of the locking means is attached to the respective base part and is provided with an attachment part extending from the base part, and a distal part provided as a head portion with at least one engaging section protruding sidewards over the attachment part. The locking means are laterally displaceable in relation to the base part to allow sidewards displacement of the engaging sections for engagement and disengagement of the locking means and thus the first and the second base. In the engaged state, latching means are provided blocking the sidewards displacement of the engaging sections to an extent that a disengagement of the locking means is prevented.

System for mounting of components

A device is provided for producing a bonded joint between fiber-reinforced thermoplastic parts to be joined, in which fiber-containing plastic material is mixed into the joining zone while friction stir welding the parts to be joined in the form of a butt joint.

Devices for bonding parts to be joined

An aircraft fuselage structure is disclosed having an outer skin, a support structure arrangement with frame elements, and a floor structure arrangement with floor support struts, the floor structure arrangement connected to the support structure arrangement via connection parts. A connection exists between the floor structure arrangement and the support structure arrangement, with a clamping element on the connection part and a locking element on the connection part. The clamping element includes a longitudinal section having a first and a second end. The first end is pivotally attached to the connection part. The second end includes a transverse section, the locking element including at least one locking groove, and the clamping element pivotable between an engagement position in which the transverse section engages the locking groove, and a released position, in which the transverse section is disengaged therefrom.

Aircraft fuselage structure

Provided is an aircraft fuselage structure having an outer skin, a support structure arrangement comprising a multiplicity of frame elements and a floor structure arrangement having a multiplicity of floor support struts. The aircraft fuselage structure provides a connection between the floor structure arrangement and the support structure arrangement which is as simple and quick to produce as possible, while not significantly increasing the weight or weakening the structure. Either the floor structure arrangement or the support structure arrangement can have at a connection there between a male connector element or a female connector element. The male connector element can have a peg which extends in the engagement direction and which has a circumferential outer surface which is provided with a multiplicity of circumferential projections. The female connector element can have a cavity, the inner surface of which is provided with a multiplicity of circumferential tabs.

A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced.

Fuselage cell for an aircraft, particularly an airplane

Systems and methods for fabrication of composite shell elements and to the assembly of large scale structures comprising such composite shell elements are provided. The composite shell elements comprise two regions in which the resin is cured to different levels. As a consequence, the flexibility of the first region is greater than the flexibility of the second region. Since the first region defines a bending line, the composite shell element can be deformed along the bending line during assembly of the large scale structure. Thus, tolerances in fabrication of the composite shell elements may be compensated for in a time-efficient manner without the need for applying a shimming process.

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Hamburg, Germany

Robert Alexander Goehlich