Airbus Operations Gmbh

Airbus Deutschland Gmbh

Hensoldt Sensors Gmbh

Bruker Datonik, Gmbh

Peter Sander

Christian Nitsch

Hauke Lengsfeld

Hans Marquardt

Jan Reh

Peter Leopold Pirklbauer

Andrew Muin

Uwe Panzram

Oliver Nuessen

Martin Dehn

Michael Sillus

Hans Doersing

Hubert Piontek

Guenter Hoppe

Cosima Eggers

Johannes Petz

Daniel Preis

Rudolf Duwald

Oliver NÜSSEN

Michael Bechtold

A cargo hold comprises at least one luggage holder having at least one luggage compartment, wherein, when the hatch is in the closed state, the luggage holder is arranged in the cargo hold, and wherein, when the hatch is in the opened state, the luggage holder can be brought out of the cargo hold and can be introduced therein again by means of a guide mechanism in such a manner that the luggage holder, when it is brought out of the cargo hold, is arranged substantially radially to the substantially elliptical cross section of the fuselage.

Aircraft with a fuselage, luggage holder for an aircraft, and air cargo container having a luggage holder

A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Drone defense system

A luggage article is provided. The luggage article includes a shell, an electronic processing module integrated with the shell, and an electronic display coupled to the electronic processing module and arranged on an outer surface of the shell. The processing module is configured to control the display to display information items to a user of the luggage article. The luggage article may be configured to display itinerary or travel related information on the display under the control of a user of the luggage article.

Luggage article with display and communication system for luggage articles

A wearable device that is wearable by a user and connectable with one or more aircraft related systems, a device system comprising a plurality of such wearable devices, and an aircraft comprising such a device system. The wearable device that is connectable to one or more aircraft related systems comprises a system interface via which the wearable device is connectable to one or more aircraft related systems, and a control unit configured to communicate with at least one of the one or more aircraft related systems via the system interface.

Digital crew assist

A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded.

Riblet structure on a flow surface and method

A forming tool with a predefined mold portion is provided in a method for producing a reinforced fiber composite component for aviation and aerospace. A forming/support element is molded by means of the mold portion of the forming tool. A semi-finished fiber product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fiber product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fiber composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fiber composite component. A forming device is provided with a predefined mold portion which holds a forming/support element such that it can be removed.

Method and shaping device for producing a composite fiber component for air and space travel

A passenger seat has a backrest and a seat which has first and second sections each having a first surface for a seat area and a second opposite surface. The second section pivots relative to the first section between a first position, in which the first surfaces of the first and second sections form a usable total seat area, and a second operational position, in which the second section is folded relative to the first section in the direction towards the backrest. Attached to the second seat section is a holder movable relative to the second surface of the second seat section between a first position, in which the holder extends substantially parallel to the second surface of the second seat section, and a second position, in which the holder extends at from 60&#xb0; to 120&#xb0; relative to the second surface of the second seat section.

Passenger seat with a luggage receiving device

The present invention relates to a production method for a workpiece () composed of a fibre-composite material, having the following steps: at least one support means () is provided. A main material () composed of a pre-impregnated fibre semi-finished product and/or of a secondary material () are/is applied to the at least one support means () in order to form at least two blank-mould areas (), in such a manner that at least one of the at least two blank-mould areas () has the main material, and at least one of the blank-mould areas () has the secondary material. The blank-mould areas () are pressure-bonded to one another to form a workpiece blank () such that the at least one support means () is provided on a surface of the workpiece blank (). The at least one support means () and the secondary material () are removed from the workpiece blank () in order to form the workpiece ().

Production method for a workpiece composed of a fibre-composite material

The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.

Method for joining cured stringers to at least one structural component of an aircraft or spacecraft

The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.

Method for joining a profiled first structural component to a second structural component

The invention relates to a method for determining at least one characteristic parameter of a CRP specimen (), in particular a specimen of prepreg material, for aerospace, comprising the following method steps: presenting the specimen (), irradiating the. specimen () with a predetermined spectrum of electromagnetic radiation, recording the interaction between the specimen () and the electromagnetic radiation in a data record () and determining the at least one characteristic parameter from the recorded data record ().

Method for determining a characteristic parameter of a CRP specimen

The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement necessary for the joining is produced in two parts. In a first step, each precured stringer is covered in advance with a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Respective vacuum film strips are subsequently arranged on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum filmsform a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.

Method for joining precured or cured stringers to at least one structural component of an aircraft or spacecraft

The invention relates to a method for joining an uncured stringer to a structural component of an aircraft or spacecraft. The uncured stringer is supplied with at least one joining section and at least one web section. A rapidly curing low-temperature auxiliary material is deposited on web flanks of the at least one web section, which are to be supported. The at least one joining section of the uncured stringer is fitted to the structural component. Curing of the auxiliary material then takes place at a first curing temperature in order to form cured supporting elements for the web flanks of the at least one web section, which are to be supported. Curing of the uncured stringer is undertaken at a second curing temperature which is greater than the first precuring/curing temperature, and then the deposited and cured auxiliary material is removed.

Method for joining a stringer to a structural component of an aircraft or spacecraft

A hollow structural component suitable for an aircraft structure includes an inner framework of intersecting longitudinal and transverse ribs, cover sheets covering the top and bottom of the framework, and end closure sheets covering ends of the framework. The transverse ribs have slots to receive the intersecting longitudinal ribs and vice versa, so the ribs intermesh in a grid pattern. Top and bottom edges of the ribs have protruding connector tabs that are fitted into slots provided in the cover sheets. Additional connector tabs at the ends of the transverse ribs are fitted into slots in the end closure sheets. After the parts are assembled by intermeshing the longitudinal and transverse ribs and fitting the connector tabs of the ribs into the slots of the cover sheets and end closure sheets, the resulting plugged-in joints are permanently mechanically secured, e.g. by welding, brazing, soldering or adhesive bonding.

Hollow structural component made of plural connected parts

The invention relates to the identification of substance ions, which are usually generated by electro spray ionization after separation by liquid chromatography or capillary electrophoresis, with the help of libraries with mass spectra. The substance ions are frequently formed not only in a protonated (or deprotonated) form but also as adducts with cations or anions, a fact which complicates identification. The invention involves making identification more accurate by additionally carrying out a determination of the most probable molar mass with the help of adduct patterns.

Growing community of inventors

Bremen, Germany

Peter Sander