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Airbus Operations Gmbh patents


Recent patent applications related to Airbus Operations Gmbh. Airbus Operations Gmbh is listed as an Agent/Assignee. Note: Airbus Operations Gmbh may have other listings under different names/spellings. We're not affiliated with Airbus Operations Gmbh, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "A" | Airbus Operations Gmbh-related inventors


 new patent  Fibre-optic communication system and an aircraft

A fibre-optic communication system for an aircraft including: a light source operable to generate light; a transceiver in optical communication with the light source, the transceiver including a control input and a reflector; an optical fibre in optical communication with the transceiver; and a light detector in optical communication with the optical fibre. The transceiver is operable to generate an amplitude modulated light signal by selectively reflecting the light received from the light source into the optical fibre using the reflector according to information received at the control input. ... Airbus Operations Gmbh

 new patent  Aircraft incorporating a main engine starting system

A system for controlling aircraft main engines cooling during starting operations. An aircraft incorporates a main engine and a pneumatic starter for starting the same, and a pneumatic source fluidly communicated with the pneumatic starter to supply pressurized air thereto. ... Airbus Operations Gmbh

 new patent  System and method for determining the origin of an oil leakage in an air supply system

An air supply system comprising at least two bleed sources configured to provide bleed air, wherein each bleed source comprises an engine or an auxiliary power unit and an oil as lubricant for the engine or the auxiliary power unit. The system also includes at least one air conditioning pack for cooling the bleed air from the bleed sources, and a plurality of bleed ducts, wherein each bleed duct connects one of the bleed sources to the at least one air conditioning pack. ... Airbus Operations Gmbh

 new patent  Slat assembly

A main aircraft wing slat assembly comprising a slat and two elongate slat tracks. A drive arrangement drivingly engages the two slat tracks and effects parallel synchronous movement of the slat tracks between retracted and extended positions. ... Airbus Operations Gmbh

 new patent  Self-perforating spacer for an insulation blanket of an aircraft, assembly method for said spacer and insulation blanket for an aircraft fitted with said spacer

A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.. ... Airbus Operations Gmbh

 new patent  Method and tool system for manufacturing a multilayer fiber structure

A method for manufacturing a multilayer fiber structure includes providing a receiving surface being formed by a first surface region of a contoured tool surface of a forming tool component and a support surface of a support component. Further, at least one fiber layer is formed on the receiving surface by laying down a plurality of fiber tapes onto the receiving surface. ... Airbus Operations Gmbh

 new patent  Apparatus for carrying a fiber composite resin system in a heat transfer device

An apparatus for carrying a fiber composite resin system in a heat transfer device, in particular an autoclave, for transferring heat between the fiber composite resin system and a directed gas flow, to produce a fiber composite aircraft component. The apparatus comprises a carrier structure for carrying the fiber composite resin system, the carrier structure having at least one flow path which, when the apparatus is accommodated in the heat transfer device, extends from an inlet on a side facing the directed gas flow along the fiber composite resin system accommodated by the carrier structure, to allow heat exchange between the gas flow in the flow path and the fiber composite resin system, and a diverting device for diverting at least a part of the directed gas flow when the apparatus is accommodated in the heat transfer device, to feed this part to the carrier structure flow path.. ... Airbus Operations Gmbh

Actuator with brushless dc motor

An actuator includes a brushless dc motor, an output device, a reduction system coupled between the brushless dc motor and the output device, and a contactless position sensor configured to sense a position of the output device.. . ... Airbus Operations Gmbh

Aircraft gap seal

An aircraft assembly including: first and second external skin panels having opposing edge faces separated by a gap, the gap having a width in a first direction extending between the opposing edge faces and a depth in a second direction generally orthogonal to the first direction; and a gap seal arranged in the gap to at least partially fill the gap, wherein the gap seal is formed of a material configured such that compression of the gap seal in the first direction results in substantially no expansion of the gap seal in the second direction.. . ... Airbus Operations Gmbh

Roller components

A roller component configured to engage with a toothed component such that when the roller component is engaged with the toothed component, rotational movement of one of the roller component and the toothed component drives linear movement along an actuation direction of the other one of the roller component and the toothed component. The roller component includes a support member and cantilevered first rollers, each of which has a mounted end connected to a first side of the support member such that each first roller is rotatable relative to the support member about a roller axis perpendicular to the actuation direction, and an unsupported end distal from the mounted end.. ... Airbus Operations Gmbh

Aircraft

An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.. ... Airbus Operations Gmbh

Aircraft seat kit, and aircraft seat and cabin arrangement with different types of seat rail adapters

An aircraft seat kit with one aircraft seat, and an aircraft seat and cabin arrangement with at least two aircraft seats for being mounted one after the other onto a seat rail are described. The seat rail provides a grid with a pre-determined grid pitch for mounting the at least two aircraft seats. ... Airbus Operations Gmbh

Cooling arrangement for a galley and method for operating such a cooling arrangement

A cooling arrangement for a galley for installation in a transport apparatus includes a cooling energy consumer with a housing with a cooling fluid inlet opening and a cooling fluid outlet opening for the supply and removal of a cooling fluid to and from the housing. A cooling compartment includes an interior for taking up the cooling energy consumer, a cooling air inlet for supplying cooling air to the cooling compartment and a cooling air outlet for removing cooling air from the cooling compartment. ... Airbus Operations Gmbh

System for suctioning a fluid as well as a vehicle having such a system

A system for suctioning fluid is disclosed. In a cabin monument, a vacuum source and a vacuum interface unit is provided. ... Airbus Operations Gmbh

05/17/18 / #20180134374

Aircraft structure component for laminar flow

An aircraft structure component for laminar flow, the aircraft structure component having an outer skin with an aerodynamic surface, wherein the aerodynamic surface has a leading edge portion and a downstream portion adjacently downstream from the leading edge portion, and wherein the downstream portion of the aerodynamic surface includes a paint layer that is not present in the leading edge portion, so that an edge line is formed between the leading edge portion and the downstream portion by the beginning paint layer. An object, to provide an aircraft structure component that allows for a reduced aerodynamic drag, is achieved in that the edge line has a ramp-shaped cross section, wherein the thickness of the paint layer increases from a starting point over a predetermined ramp length to a saturation point where the full thickness of the paint layer is reached.. ... Airbus Operations Gmbh

05/17/18 / #20180134373

Integral component with an active flow control device

A flow body for a vehicle includes at least one planar skin section with an outer side, an inner side and at least one opening that penetrates the skin section, as well as at least one active flow control device that is designed for moving an air volume. The at least one active flow control device includes an air discharge section that is fluidically connected to the at least one opening, wherein the air discharge section and the at least one planar skin section are manufactured by a layer manufacturing process in the form an integral component that is free of joints, and wherein the air discharge section at least partially supports the skin section in a load-bearing fashion.. ... Airbus Operations Gmbh

05/17/18 / #20180134371

Air brake system for aircraft

An air brake system for aircraft comprising control surfaces, such as slats, flaps and spoilers mounted to the wings of an aircraft, wherein each control surface is split, along a spanwise direction, into parts of the control surface, and the parts of each control surface are deployed desynchronously when the aircraft touches down.. . ... Airbus Operations Gmbh

05/17/18 / #20180134365

Aircraft component comprising a chiral lattice

An aircraft protective component for an aircraft module, the aircraft protective component includes: a plurality of cells connected together to form a lattice, each cell having a chiral structure, wherein the lattice of the cells is configured to at least partially surround the aircraft module to provide an energy absorption barrier for the aircraft module. The aircraft protective component enables the energy generated by an impact to the aircraft to be dissipated throughout the lattice of the protective component. ... Airbus Operations Gmbh

05/17/18 / #20180133850

Method for reconditioning of a damaged portion of a component and insert therefor

According to an embodiment, a method is provided for preparing a reconditioning of a damaged portion of a component, particularly of an aircraft, by adding an insert, which fills and/or bridges the damaged portion. The method involves: producing a 3d cad repair model of the damaged portion by scanning; analysing the repair model and thus evaluating complexity of the damage and/or its reconditioning; as a function of the complexity, deciding between at least two alternative means to perform at least a following step, which is analysing the repair model and thus dimensioning the reconditioning including the insert. ... Airbus Operations Gmbh

05/17/18 / #20180133681

Autoclave and method for welding thermoplastic composite parts

An autoclave for welding thermoplastic composite parts comprises a sealed process chamber, a pressure source, a microwave source and a workpiece supporting member configured to support at least two thermoplastic composite parts which contact each other in an abutting section within the process chamber. The pressure source is configured to generate positive pressure in the process chamber which is higher than an ambient pressure surrounding the process chamber while the microwave source emits microwaves towards the abutting section in order to locally melt the thermoplastic composite parts and weld them together in the region of the abutting section.. ... Airbus Operations Gmbh

05/10/18 / #20180132019

Loudspeaker arrangement for a passenger cabin of a transport means

A loudspeaker arrangement for a passenger cabin of a transport means, including a loudspeaker and a housing having a receiver for the loudspeaker. The loudspeaker includes at least one membrane capable of oscillation and at least one loudspeaker coil. ... Airbus Operations Gmbh

05/10/18 / #20180131110

Base module and aviation computer system having the base module

A base module and an aviation computer system having the base module includes a printed circuit board, an integrated power supply and communication connector, a smarc connector, and an fmc connector. A power supply circuit supplies the smarc connector and the fmc connector with power from dedicated power supply contacts of the integrated power supply and communication connector, and a communication circuit connects the smarc connector to dedicated communication contacts of the integrated power supply and communication connector. ... Airbus Operations Gmbh

05/10/18 / #20180128724

System and method for testing bonded joints

A system for testing bonded joints that comprises a swing tool, an actuator, pressure measuring device and a first fixing arrangement. The actuator of the system is configured to apply a compression force or a traction force on the swing tool in order to separate two elements, and the pressure measuring device is configured to measure the force applied on the swing tool. ... Airbus Operations Gmbh

05/10/18 / #20180127105

Rear mount for an aircraft engine

A rear engine mount for a turbomachine of an aircraft comprising a pylon. The rear engine mount comprises a beam attached to the pylon, a first and a second lateral connecting rod having an abutment and attached between the beam and the turbomachine, a three-point, v-shaped central connecting rod, of which the vertex is attached to the turbomachine, and of which the ends of the arms are attached to the beam. ... Airbus Operations Gmbh

05/10/18 / #20180127100

Lining panel and method for manufacturing lining panel

A lining panel having a panel element, a rectangular through hole and a flap is provided. The lining panel has a flap which is rotatable about a hinge integrated into the panel element in order to open and/or close the rectangular through hole. ... Airbus Operations Gmbh

05/10/18 / #20180127081

Panel structure for an aircraft and manufacturing method thereof

A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. ... Airbus Operations Gmbh

05/03/18 / #20180124945

Protected electronic device

An electronic device includes an electronic component and a protective shield including a phase change material having a phase change temperature of between 20° c. And 90° c., an antivibration gel having hyperelastic and/or viscoelastic behavior at 20° c., and a separation barrier positioned so as to separate the phase change material and the antivibration gel. ... Airbus Operations Gmbh

05/03/18 / #20180123679

Wireless distribution of aircraft data and/or avionics parameters and/or control commands between a standardized aircraft interface point and other systems, e.g., passenger entertainment systems

A system for wireless distribution of aircraft data, avionics parameters or control commands between a standardized aircraft interface point and other systems, including a portable in-flight entertainment (ife) server. The system comprises an aircraft data system with avionics buses for carrying at least one of aircraft data, avionics parameters or control commands. ... Airbus Operations Gmbh

05/03/18 / #20180123337

System and method for managing short-circuits in a meshed electrical energy distribution network of an aircraft

A system for managing short-circuits in an aircraft meshed electrical energy distribution network, comprising nodes connected to one another by inter-node links forming a mesh of the network. A system node comprises a switch, a current limiter, circuitry elements to measure the current intensity circulating on the link and circuitry elements to measure a voltage drop on the link, and a control unit configured to acquire a link current measurement, compare the measurement with a predetermined current threshold and, if the measurement exceeds this threshold, command the current limiter to limit the link current, acquire a link voltage drop measurement, determine a time associated with the value of the voltage drop and check whether the voltage drop is still present after a time period equal to the time obtained, and if the voltage drop is still present then, command the opening of the switch corresponding to this link.. ... Airbus Operations Gmbh

05/03/18 / #20180121687

Configuring an embedded electronic device by reading a radiofrequency tag

The disclosure relates to a system embedded in an airplane comprising an electronic device intended to be inserted into a frame, a frame that can accommodate the electronic device, in which system the electronic device includes a radiofrequency tag reader, a radiofrequency tag, having a configuration information item, is fixed to the frame such that the radiofrequency tag reader can read the radiofrequency tag once the electronic device is inserted into the frame and the electronic device is adapted to, in a phase of configuration of the electronic device: read the configuration information item via the radiofrequency tag reader and determine a configuration of the electronic device as a function of the configuration information item read.. . ... Airbus Operations Gmbh

05/03/18 / #20180118372

Method and device for managing configurations of an aircraft

The device for assisting the landing of an aircraft in a phase of descent for the purpose of a landing on a runway with the help of an instrument landing assistance module includes an image capturing module for capturing a sequence of successive images of the ground, an image processing module, a monitoring module for detecting on the processed images at least one visual characteristic corresponding to a runway, a computation module for computing a current position of the aircraft and a comparison module for comparing the computed current position with a signal representative of a current position of the instrument landing assistance module, a go-around warning being transmitted to a display unit, if the current positions are not substantially identical.. . ... Airbus Operations Gmbh

05/03/18 / #20180118355

Aircraft engine assembly, comprising flexible force transmitting devices radially arranged between the thrust reversal cowls and the engine

To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.. ... Airbus Operations Gmbh

05/03/18 / #20180118348

Toilet module for a vehicle and a vehicle including a toilet module

A toilet module and a vehicle including a toilet module are provided. An exemplary toilet module includes a toilet unit and a housing. ... Airbus Operations Gmbh

05/03/18 / #20180118347

Cabin monument for an aircraft

A cabin monument for an aircraft is described. The cabin monument has a framework with a base frame and a frame structure connected to the base frame, and side walls fastened to the frame structure. ... Airbus Operations Gmbh

05/03/18 / #20180118333

Landing gear drive system flexible interface

A drive system for an aircraft landing gear, the drive system including a pinion gear, a drive shaft arranged to rotate the pinion gear about a drive axis, a driven gear arranged to mesh with the pinion gear to be rotatable by the pinion gear, the driven gear being connectable to a wheel of the landing gear to be capable of rotating the wheel about a wheel axis; and a flexible interface. The flexible interface includes a plurality of driven gear coupling members, each driven gear coupling member having a first connection portion attached to the driven gear, a second connection portion adapted to be attached to the wheel at an offset distance from the wheel axis, and a joint between the first connection portion and the second connection portion, the joint permitting relative movement between the first connection portion and the second connection portion.. ... Airbus Operations Gmbh

05/03/18 / #20180118329

Wing for an aircraft having a simplified movable aerodynamic surface and a flexible sealing

A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. ... Airbus Operations Gmbh

05/03/18 / #20180118328

Fairing for an aircraft

A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.. . ... Airbus Operations Gmbh

05/03/18 / #20180118056

Seat rail adapter comprising two mounting parts, seat rail and cabin arrangement comprising such a seat rail adapter

A seat rail adapter for flexibly mounting an object onto a seat rail, a seat arrangement and a cabin arrangement with same are described. The seat rail has a u-shaped profile with a lower flange, two web portions, two upper flanges, a gap between the upper flanges, and a cavity inside the seat rail. ... Airbus Operations Gmbh

05/03/18 / #20180117662

Manufacturing of a bearing

A method for manufacturing a bearing includes the following steps: a) providing of an outer part with a concave running surface which forms a receiving area for receiving an inner part, b), providing an inner part that is arranged inside the outer part, which inner part is shaped annularly, c) arranging the inner part within the outer part in a machining position in which at least a part of an outer surface of the inner part is exposed for machining, and d), generating of a convex running surface of the inner part, which running surface engages with the receiving area of the outer part whereby the inner part is held captively in the outer part. Subsequently, the inner part may be tilted from the machining position into a running position in which the inner part is concentric with the outer part.. ... Airbus Operations Gmbh

04/19/18 / #20180108187

System and method for detecting radome damage

A system for detecting radome damage. The system comprises a sensor unit and a processing unit. ... Airbus Operations Gmbh

04/19/18 / #20180105281

Aircraft nacelle including a link between a conduit of an air inlet and a conduit of an engine

An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.. ... Airbus Operations Gmbh

04/12/18 / #20180102557

Fuel cell system, a fire fighting system, and an aircraft

A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.. ... Airbus Operations Gmbh

04/12/18 / #20180101181

Aircraft flight control method and system

A system including a set of computation modules configured to be utilized for computation of gains of at least one piloting law relative to at least one piloting axis of the aircraft and a data capture unit for capturing in at least one computation unit associated with a given piloting axis of the aircraft first values illustrating aerodynamic coefficients of the aircraft and second values defining delay and filter characteristics of the control chain relative to the given piloting axis, the computation unit being configured to compute the gains of the piloting law utilizing at least a part of the set of computation modules and the computation unit computing inputs intended for at least one actuator of a control surface adapted to control the aircraft relative to the given piloting axis in accordance with a corresponding current control value.. . ... Airbus Operations Gmbh

04/12/18 / #20180099737

Control device for an aircraft

A control device (34) for an aircraft wing (3) including upper and lower spoilers (35, 37) mountable to a wing (3) behind a leading edge slat (26), wherein each of the upper and lower spoilers (35, 37) are movable in a direction towards each other into a wing (3) from a neutral position, to an enabled position to form an airflow slot (52) between the slat (26) and said upper and lower spoilers (35, 37). Each of the upper and lower spoilers (35, 37) may also be movable in a direction away from each other out of a wing (3) from said neutral position.. ... Airbus Operations Gmbh

04/12/18 / #20180099735

Aircraft wing with aileron

An aircraft wing having a fixed wing with a wing tip device. The wing tip device is movable between a flight configuration for use during flight, and a ground configuration for use during ground-based operations. ... Airbus Operations Gmbh

04/12/18 / #20180099462

System and method for curing polymer matrix composite parts in manufacturing and repairing processes

A system for curing polymer matrix composite parts out of autoclave in manufacturing and repairing processes including: (i) an inner vacuum bag (3) placed over the lay-up to be cured located over a working area (15, 18) with the edges of the inner vacuum bag (3) joined to the working area by first sealing elements (8); (ii) a perforated bulkhead (4) located over the inner vacuum bag (3), (iii) an outer vacuum bag (2) over a perforated bulkhead (4) and over the edges of the inner vacuum bag with the edges of the outer vacuum bag (2) joined to the working area (15, 18) by second sealing elements (1), (iv) a vacuum device (5, 7, 6) and (v) a heating source (9, 20).. . ... Airbus Operations Gmbh

04/05/18 / #20180097747

Processor designed for a deterministic switched ethernet network

Multiple-core processor to be connected, by way of communication ports, to a deterministic switched ethernet network using virtual links to which items of equipment are connected, the processor including clusters each including cores, wherein at least one cluster of the processor implements a switch function that makes it possible to interconnect the items of equipment in the network. At least one cluster of the processor implements an end system function providing functions of sending and receiving data in the network, and at least one cluster of the processor implements an application.. ... Airbus Operations Gmbh

04/05/18 / #20180096673

Process for manufacturing an acoustic panel reinforced by at least one thermoplastic composite layer

A process for manufacturing an acoustic panel including at least one acoustically resistive layer, at least one cellular structure and a reflective wall. The process includes steps of depositing the parts of the acoustic panel made of thermosetting composite, depositing a film made of thermoplastic resin that is miscible with the thermosetting composite at the polymerization temperature of the thermosetting composite, polymerizing the parts of the acoustic panel made of thermosetting composite, and depositing and consolidating at least one layer made of thermoplastic composite against the film made of thermoplastic resin in order to form the reflective wall.. ... Airbus Operations Gmbh

04/05/18 / #20180096607

Method and device for identification of a recipient aircraft of an audio communication

A method and device for identification of a recipient aircraft of an audio communication. The device includes at least one reception unit, for example a vhf radio or an hf radio, for receiving an audio message on board the aircraft, a transcription unit for transcribing the audio message received into a text message, an analysis unit for analyzing the text message in order to extract interpretation data therefrom, a data generation assembly for determining flight data of the aircraft, a processing unit for determining discriminating data from these flight data, a comparison unit for comparing the interpretation data to the discriminating data so as to deduce therefrom whether the audio message received is indeed intended for the aircraft or not, and an indication unit for indicating to at least one crew member of the aircraft whether the aircraft is recipient or not of the audio message received.. ... Airbus Operations Gmbh

04/05/18 / #20180095784

Processor comprising a plurality of computation cores

A processor including computation groups, each computation group including computation cores, the processor being capable of simultaneously implementing a plurality of applications, each application being implemented by a computation core and possibly requiring a read-mode or write-mode access to an external memory connected to the processor. At least one core, called dedicated core, of at least one computation group is dedicated to management of the external memory, the management making it possible to temporally and spatially organize read-mode and write-mode accesses to the external memory of each application requiring a read or a write in the external memory implemented by the processor.. ... Airbus Operations Gmbh

04/05/18 / #20180095133

Component monitoring

A component monitoring apparatus [100] including an input [110] to receive sensor data from a sensor arrangement [s1-s4]. The sensor data representative of a use of a respective component [105] during a monitoring interval. ... Airbus Operations Gmbh

04/05/18 / #20180094761

Fluidic piping system for aircraft and method for repairing same

A fluidic piping system for aircraft, comprising a pipe made in a single piece and an insulating sheath surrounding the pipe. The pipe comprises potential cutoff zones defining sections of the fluidic piping system, reinforced zones arranged in pairs on either side of each potential cutoff zone, and non-reinforced zones defined between the pairs of reinforced zones as intermediate zones. ... Airbus Operations Gmbh

04/05/18 / #20180093774

Cooling system for a galley, and method of operating such a cooling system

A cooling system for a galley installed in a transportation device, in particular an aircraft, comprises a cooling device with a coolant circuit configured to have a coolant flow therethrough. A fluid line is configured to have a fluid to be cooled flow therethrough and is thermally coupled with the coolant circuit to transfer heat from the fluid to be cooled to the coolant circulating in the coolant circuit, and an air line configured to be flowed through with air and thermally coupled to the coolant circuit of the cooling device to transfer heat from the coolant to the air line. ... Airbus Operations Gmbh

04/05/18 / #20180093773

Trolley, waste module and system for collecting waste

A trolley for collecting waste includes a housing having a main waste chamber for receiving waste, and wheels attached to a bottom wall of the housing. The housing has at least one module seating, each configured to receive a waste module for collecting waste. ... Airbus Operations Gmbh

04/05/18 / #20180093756

System for driving and guiding of a trailing edge control surface

A system for driving and guiding a trailing edge control surface arranged on a wing of an aircraft includes a first guide device attachable to the wing and coupled with an inboard section of the control surface for guiding the inboard section along a trajectory relative to the trailing edge region of the wing between a retracted position and an extended position, a second guide device attachable to the wing and holding a connecting means of an outboard section of the control surface, and a drive device attachable to the wing and the control surface for moving the control surface. The trajectory is a spatial path at least along one dimension, wherein a distance between the inboard section of the control surface and a fixed part of the wing changes during a motion of the inboard section on the trajectory.. ... Airbus Operations Gmbh

03/29/18 / #20180091253

Enodeb with masking functionality and aircraft

A method for masking communication signals, particularly for masking terrestrial rf communication signals on board of an aircraft, includes parallelizing a first information data stream to be transmitted on a first lte transmission channel. The first lte transmission channel has a first channel transmission bandwidth and at least one guard band adjacent to the channel transmission bandwidth. ... Airbus Operations Gmbh

03/29/18 / #20180090019

Device, system and method for assisting the taxiing of an aircraft

In an aircraft including a cockpit, a unit for monitoring the situation of the aircraft and a radio communication unit, the device for aiding the ground rolling is configured to: acquire, from the monitoring unit, information the situation of the aircraft and determine predicted positions of the aircraft for a set of future instants, and for each vehicle of a set of other vehicles situated on the surface of the airport: acquire, from the radio communication unit, information regarding the situation of the vehicle, which information is transmitted by this vehicle, determine predicted positions of the vehicle and calculate a distance between the predicted position of the aircraft and the predicted position of the vehicle for each instant of the set of future instants and compare this distance with a predetermined distance threshold and, emit an alert in the cockpit if this distance is less than this distance threshold.. . ... Airbus Operations Gmbh

03/29/18 / #20180090015

Method and device for generating an optimum flight path intended to be followed by an aircraft

A device includes a database including data related to obstacles, a first determination module for determining at least one obstacle intercepted by a direct flight path connecting an initial point to the target point, a second determination module for determining at least one lateral extreme apex of at least one intercepted obstacle, an evaluation module for assigning a rating to each section corresponding to a segment between a lateral extreme apex and the initial point, a storage module for storing in a memory the section corresponding to the optimum extreme apex having the best rating, the optimum flight path corresponding to all of the sections stored in the memory, the preceding modules being used iteratively, the device further including a transmission module for transmitting the optimum flight path to a user device.. . ... Airbus Operations Gmbh

03/29/18 / #20180088913

Generation of application codes from a formal specification

System and method to generate automatically a compact application code suitable for taking advantage of the intrinsic power of processors. The system can generate the application code executable by a processor from a formal specification associated with an application, the formal specification including operators, and the system including an analyzer to code each operator of the formal specification by a corresponding operation code followed by a minimum number of input code(s) and output code identifying input and output parameters associated with the operator, thus automatically generating a compact application code suitable for being stored in a memory associated with the processor and for being executed by an interpreter of the processor.. ... Airbus Operations Gmbh

03/29/18 / #20180088085

Inspection tool

An inspection tool for inspection of a hole of a metallic lug, including, a first arm, a second arm, a third arm, and a housing element, wherein the first arm, the third arm and the housing element may vary their position independently of each other in relation to the second arm. Also, the present invention discloses an inspection device for inspection of a metallic lug that comprises an inspection tool and a probe housed in the housing element, and a method for detecting cracks around metallic lug.. ... Airbus Operations Gmbh

03/29/18 / #20180087707

Connection device comprising a flexible tube for collection of a liquid in the event of leakage or oozing

A connection comprising a first duct, a second duct, a flexible tube which comprises a first end configured to cover part of the first duct, and a second end configured to cover part of the second duct, a first clamping system configured to clamp the first end of the flexible tube around the first duct, and a second clamping system configured to clamp the second end of the flexible tube around the second duct.. . ... Airbus Operations Gmbh

03/29/18 / #20180086469

Space-optimized cooling system for a galley, and method of operating such a cooling system

A galley cooling system for installation in a transportation means, in particular an aircraft, comprises a cooling device comprising a coolant circuit configured to be flowed through with a coolant. The cooling system further comprises a first fluid line configured to be flowed through with a first fluid and being thermally coupled with the coolant circuit to transfer heat from the first fluid line fluid to the coolant circuit coolant, and a second fluid line configured to be flowed through with a second fluid and being thermally coupled to the coolant circuit to transfer heat from the coolant circuit coolant to the second fluid line fluid. ... Airbus Operations Gmbh

03/29/18 / #20180086467

Trolley compartment and on-board kitchen

A trolley compartment for an on-board kitchen intended for installation in a transport vehicle comprises a frontal access aperture as well as a rear wall that lies opposite the access aperture. A worktop forms an upper boundary of the trolley compartment. ... Airbus Operations Gmbh

03/29/18 / #20180086465

Dynamically adapting pre-recorded announcements

A method of providing an audio signal containing flight-related information to passengers on board the aircraft, a computer program product for carrying out such a method, an apparatus for providing an audio signal containing flight-related information to passengers on board an aircraft, and an aircraft comprising such an apparatus. A method embodiment comprises receiving a trigger to provide the audio signal, obtaining one or more predefined data fragments, obtaining flight-related information corresponding to a current flight of the aircraft, generating the audio signal based on the one or more predefined data fragments and the flight-related information, and providing the audio signal to one or more of the passengers on board the aircraft.. ... Airbus Operations Gmbh

03/29/18 / #20180086464

Electronic baggage stowage system and methods

An electronic baggage stowage system for an aircraft comprising a first detector to detect free space in a cabin stowage space, wherein the first detector is configured to output cabin stowage space data based on the detection, a processing unit communicating with the first detector, wherein the processing unit is configured to process the cabin stowage space data, receive and process baggage size data indicating the size of one or more baggage items, and output baggage stowage mapping data in response to the processing of the cabin stowage space data and the baggage size data. The baggage stowage mapping data indicates one or more target positions in the cabin stowage space at which the baggage items are to be placed. ... Airbus Operations Gmbh

03/29/18 / #20180086439

Aircraft landing detector

Sustained ground contact of an aircraft is determined by detecting a change in a mechanical vibration characteristic of a part of the aircraft. Apparatus for determining sustained ground contact of an aircraft includes an analyser [300] for analysing aircraft vibration signals and a trigger [310] for triggering occurrence of sustained ground contact to an aircraft control system [315] when the analyser [300] detects sustained ground contact.. ... Airbus Operations Gmbh

03/29/18 / #20180086432

Slat track device for an aircraft wing

A slat track device (7) for an aircraft wing (1) including a beam-shaped main load bearing track structure (9) connected to a slat (5) and movably connected to a main wing (3), a guidance surface (11) at the track structure (9) and guided along a corresponding guidance device (19) at the main wing, a connection device (13) at the track structure (9) connecting the track structure (9) to the slat (5), and an engagement device (15) at the track structure (9) and configured to engage a drive member (33) of a drive unit (37) provided at a main wing (3). The slat track device has redundant main load paths achieved by the track structure (9) having a first track member (41) and a separate second track member (43) both connected to the connection device (13) and the engagement device (15).. ... Airbus Operations Gmbh

03/22/18 / #20180082558

System and a method for detecting low concentrations of specific chemical compounds in the air of an aircraft cabin

A system for detecting low concentrations of specific chemical compounds in the air of an aircraft cabin. The system includes a cabin management system with a processing unit and a user interface and a plurality of sensors. ... Airbus Operations Gmbh

03/22/18 / #20180081615

Visual output assembly for aircraft cabin

A visual output assembly for an aircraft cabin includes at least one electronic display device, a projection screen, an image projector configured to project images onto the projection screen, and at least one illumination device.. . ... Airbus Operations Gmbh

03/22/18 / #20180079507

Passenger supply unit for an aircraft cabin

A passenger supply unit for an aircraft cabin, including an input device for detecting a control command from a passenger, and for outputting a control signal to a further device for controlling the further device according to the control command. A passenger supply unit can be controlled by a passenger independent of its height above the passenger seat. ... Airbus Operations Gmbh

03/22/18 / #20180079402

Brake wear reduction apparatus

An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.. ... Airbus Operations Gmbh

03/22/18 / #20180079171

Bonding arrangement and production method

In order to provide a new and improved bonding arrangement, especially for use in an aircraft or spacecraft, which is designed to overcome problems of bonding arrangements under mode i loading stress and which is designed or configured particularly to create a bond design which is incapable of locally loading the adhesive bond above the peel strength, a bonding arrangement is disclosed with a coating structure, which is split into a plurality of neighboring structural elements spatially separated from each other, and at least one supporting member is provided, which comprises a plurality of recesses receiving the structural elements in operating position.. . ... Airbus Operations Gmbh

03/22/18 / #20180079154

Method for manufacturing a component from composite material

A method for manufacturing a composite component from a plurality of plies of fibres embedded in a resin includes the following steps: forming a preliminary composite component by draping the plurality of fibre plies in a mould; laying up the preliminary composite component by stacking layers comprising at least one airtight film, a drainage fabric and a cover sheet; polymerizing the preliminary composite component arranged on a table of an enclosure of an apparatus of the autoclave type, equipped with a device for measuring the temperature t inside the enclosure, by applying a temperature cycle and a pressure cycle; demoulding a raw composite component; testing the dimensions and defect rate of the raw component, wherein the polymerization step includes the application of a pressure p in the enclosure as soon as the temperature t in the enclosure is greater than or equal to a threshold temperature ts.. . ... Airbus Operations Gmbh

03/15/18 / #20180074515

Method and device for assisting with the landing of an aircraft during a flare maneuver

A device including an acquisition module for acquiring current parameters of the aircraft, a computational module for computing a current load factor of the aircraft, a computational module for computing a minimum load factor, a computational module for computing the difference between the current load factor and the minimum load factor, and an acoustic emission module for emitting a sound signal, the level of which increases gradually as a function of time when the difference between the current load factor and the minimum load factor is less than zero.. . ... Airbus Operations Gmbh

03/15/18 / #20180072425

Aircraft cabin area comprising a door aisle and an aircraft monument arrangement, aircraft comprising such an aircraft cabin area, and method of operating said aircraft

An aircraft cabin area comprises a door aisle extending between two opposite aircraft doors and an aircraft monument arrangement. The door aisle has a door section adjacent each aircraft door. ... Airbus Operations Gmbh

03/15/18 / #20180072423

Integrated detachable ballistic shield

A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.. ... Airbus Operations Gmbh

03/15/18 / #20180072004

Method for producing a fiber composite component

A method for producing a fiber composite component includes a step (a) that includes a production of a semi-finished product by: providing a core layer having cavities; covering an outer face of the core layer with a layer-shaped semi-finished product having continuous fibers pre-impregnated with a first duroplastic matrix material; and applying a molding compound to a first deposit area of a front face of the first semi-finished product, the front face facing away from the core layer, wherein the molding compound includes a second long-fiber-reinforced duroplastic matrix material. The method also includes a step (b) for extruded reshaping of the semi-finished product to the fiber composite component. ... Airbus Operations Gmbh

03/08/18 / #20180068170

Virtual window device and method for operating a virtual window device

A virtual window device, particularly for use in an airplane, includes a bezel, or a frame, with a display arranged within the bezel, or within the frame; a distance sensor unit configured to produce at least one first distance signal indicating a first distance to an object; a first camera unit configured to capture a live video of a real scene; and a computing unit configured to select, based at least on the at least one first distance signal, a section of the live video of the real scene captured by the first camera unit; wherein the computing unit is further configured to control the display to display the selected section.. . ... Airbus Operations Gmbh

03/08/18 / #20180066773

Piping system with leak detection

A piping system includes a first and a second inner tube assembled end to end and a hot fluid detector. For each inner tube, a first peripheral tube into which the inner tube is introduced and fixed. ... Airbus Operations Gmbh

03/08/18 / #20180066606

Thrust reverser system limiting aerodynamic perturbation in an inactive configuration

A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.. ... Airbus Operations Gmbh

03/08/18 / #20180065725

Damage visualization

A structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. ... Airbus Operations Gmbh

03/01/18 / #20180063034

Wireless flight attendant panels

An adapter for tapping into an aircraft panel network in order to provide support for a wireless flight attendant panel (fap). The adapter includes first and second connectors to insert into the server-to-fap connection of the panel network and a third connector configured to connect to a wireless access point. ... Airbus Operations Gmbh

03/01/18 / #20180061543

3d printer with hovering printing head or printing bed

A three-dimensional printing device includes a movable unit with a superconductor and a printing head arrangement for printing a printing material, a magnetic field generator adapted to generate a magnetic field, and a control device. The magnetic field generator and the movable unit are adapted for coupling in a force-locking manner by means of frozen magnetic flux, and the controlling device is adapted to control a magnetic field strength of the magnetic field generator.. ... Airbus Operations Gmbh

03/01/18 / #20180061244

Data acquisition system and methods for data acquisition

A data acquisition system, particularly for use in avionics systems, has a control and monitoring apparatus having a plurality of electronic application components and a multiplexer coupled to the plurality of electronic application components, a domain network interface coupled to the multiplexer, a data collection component having a data flow controller and a data collection memory component coupled to the data flow controller, a plurality of external interfaces, and an interface component implemented in the data collection component and coupled between the data flow controller and the plurality of external interfaces. The interface component is configured to allow bidirectional protocol-based communication between the data flow controller and systems connected to the plurality of external interfaces.. ... Airbus Operations Gmbh

03/01/18 / #20180057175

Operating-phase-dependently controllable aircraft air conditioning system and method for operating such an aircraft air conditioning system

An aircraft air conditioning system comprises an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which comprises a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.. ... Airbus Operations Gmbh

03/01/18 / #20180057174

Aircraft air conditioning system and method for operating such an aircraft air conditioning system

An aircraft air conditioning system comprises an ambient air line configured to have ambient air flow therethrough and being connected to a mixer of the air conditioning system to feed ambient air to the mixer, and a recirculation air line configured to have recirculation air flow therethrough and being connected to the mixer to feed to the mixer recirculation air discharged from an aircraft area to be air conditioned. A refrigerating machine of the air conditioning system comprises a refrigerant circuit configured to have a refrigerant flow therethrough and being thermally coupled to the ambient air line and to the recirculation air line to transmit heat from the ambient air flowing through the ambient air line and from the recirculation air flowing through the recirculation air line to the refrigerant circulating in the refrigerant circuit, before the ambient air and the recirculation air are fed into the mixer.. ... Airbus Operations Gmbh

03/01/18 / #20180057168

Lateral linear moving curtain rail

A vehicle cabin curtain rail attachment comprising a guiding rail configured to be mounted fixedly within a cabin and a movable curtain rail section to receive or guide a curtain, wherein the movable curtain rail section is configured to slide along the guiding rail to a desired position.. . ... Airbus Operations Gmbh

03/01/18 / #20180057144

Latching and locking mechanism for a foldable wing arrangement

A wing arrangement for an aircraft including a latching arrangement (29, 29′, 29″) having a latching member (31, 31′, 31″) and an engagement device (33), wherein the latching member (31, 31′, 31″) is fixed to a wing tip section (13), and the engagement device (33) has a base member (35) on a wing base section (7) and has an abutment surface (43), and an engagement member (45, 45′, 63) supported on the base section (7) and moves between a release position and a latching position by an actuator (49, 49′) coupled to the engagement member (45, 45′, 63) and the base section (7), wherein when the tip section (13) is in the deployed position, the latching member (31, 31′, 31″) abuts the abutment surface (43) and the engagement member (45, 45′, 63) can move between the release position and the latching position, wherein when the latching member (31, 31′, 31″) abuts the abutment surface (43) and the engagement member (45, 45′, 63) is in the latching position, the engagement member (45, 45′, 63) abuts on a surface section of the latching member (31, 31′, 31″) facing away from the abutment surface (43) to prevent a pivot movement of the tip section.. . ... Airbus Operations Gmbh

03/01/18 / #20180056848

System for moving loads comprising a locking arrangement that is operable by means of a transport vehicle

A system for moving loads, in particular within an aircraft, comprising: a cargo hold floor, at least one row of rollers including a plurality of rollers integrated into the floor one behind another, at least one guide rail in the floor extending substantially parallel to the row of rollers, and at least one transport vehicle removably received in and movable along the guide rail. At least one coupling arrangement selectively couples the vehicle with a load arranged on the row of rollers, the load being movable with the vehicle. ... Airbus Operations Gmbh

03/01/18 / #20180056494

Punching tool equipped with a guide sleeve

A punching tool which comprises a body, a rod oriented in a first direction and comprising a free end configured to cooperate with the element to be punched, a guide sleeve containing a conduit extending from a first end face to a second end face and configured to rest against the part. The conduit comprises a first portion which opens at the first end face and is configured to house the body of the punching tool and to allow a translation movement of the body of the punching tool relative to the guide sleeve.. ... Airbus Operations Gmbh

02/22/18 / #20180050818

Segmented lightning diverter element having integrated esd protection

A lightning diverter element having integrated esd protection, including a support and metallic segments disposed on the support is disclosed, wherein the support has a resistance per unit length in a range from 100 kΩ/m to 100 mΩ/m. Furthermore, a high-frequency device is disclosed, wherein such a lightning diverter element is disposed on a surface of a component of the high-frequency device. ... Airbus Operations Gmbh

02/22/18 / #20180050802

Waste compaction system for a vehicle and cabin monument with such a waste compaction system

A waste compaction system includes a trolley for collecting waste and a docking station that is integratable into a cabin monument of a vehicle. The trolley includes a housing with chambers for waste, an opening for introducing waste, a vacuum compaction mechanism assigned to a chamber, and a suction port accessible from outside the housing and couplable to the compaction mechanism. ... Airbus Operations Gmbh

02/22/18 / #20180050790

Wing-tip arrangement having vortilons attached to a lower surface, and aircraft having such a wing-tip arrangement and the use of vortilons on a wing-tip arrangement

A wing-lip arrangement couplable with a wing of an aircraft includes a connection region for coupling or integration with the wing end region, at least one tip, at least one upper surface and at least one lower surface, which extend between a leading edge and a trailing edge of the wing-tip arrangement from the connection region to the at least one tip, and at least one vortilon. The local dihedral of the wing-tip arrangement changes between the at least one tip and the connection region, such that at least a part of the wing-tip arrangement projects at an angle relative to the wing. ... Airbus Operations Gmbh

02/22/18 / #20180050786

Drain mast of an aircraft

A drain mast for draining liquids from an aircraft. The drain mast comprises a tube and further comprises a pipe coupled to the inner longitudinal surface of the tube and configured such that the drained liquid flows from the tube to the pipe. ... Airbus Operations Gmbh

02/15/18 / #20180046740

Method for the structural analysis of panels consisting of an isotropic material and stiffened by triangular pockets

A method for dimensioning of panels stiffened by triangular pockets that make it possible to take into account aeronautical specifics and more particularly the stresses that are admissible for the different types of buckling and the calculations of adapted reserve factors is presented. The method relates to dimensioning of a substantially plane panel of homogeneous and isotropic material by an analytical procedure, wherein the panel is composed of a skin reinforced by an assembly of three parallel bundles of stiffeners integrated with the panel, and triangular pockets defined on the skin, the stiffeners are strip-shaped and the panel must satisfy a specification of mechanical resistance to predetermined external loads, including steps organized in such a way that they can be repeated iteratively for different values of input data until reserve factors are obtained to determine the dimensions and arrangement of the panel elements necessary to obtain the imposed mechanical resistance.. ... Airbus Operations Gmbh

02/15/18 / #20180045353

Damping device

A damping device, in particular for damping or avoiding pressure surges, such as pulses, in hydraulic supply circuits, preferably in the form of a silencer, having a damping housing (1) which surrounds a damping chamber and has at least one fluid inlet (35) and at least one fluid outlet (41) and a fluid receiving chamber which extends between the fluid inlet (35) and the fluid outlet (41), wherein, during operation of the device, a fluid flow crosses the damping chamber in a throughflow direction (11), coming from the fluid inlet (35) in the direction of the fluid outlet (41), and wherein at least parts of the fluid receiving chamber extend in at least one extent direction transversely with respect to the throughflow direction (11), is characterized in that more than one fluid receiving chamber is arranged one after the other in the throughflow direction (11) and in that the fluid receiving chamber which is first upstream and the fluid receiving chamber which is last downstream immediately adjoin the fluid inlet (35) and the fluid outlet (41), respectively.. . ... Airbus Operations Gmbh

02/15/18 / #20180043834

Equipment mounting device and installation arrangement including an equipment mounting device

An equipment mounting device and an installation arrangement for mounting an equipment to two fittings. The mounting device comprises a longitudinal carrier configured to be coupled to the equipment, and sized to span a space between the two fittings. ... Airbus Operations Gmbh

02/08/18 / #20180040945

System for emitting and/or receiving electromagnetic waves embedded in an aircraft

A system for emitting and/or receiving electromagnetic waves embedded in an aircraft, the aircraft including an emitting and/or receiving device for emitting and/or receiving electrical signals, a radome having an electrically insulating protective envelope (12), on which at least one lightning arrester strip (21) is arranged, the radome being attached to a metal frame of the aircraft (30), a first part of the at least one lightning arrester strip is electrically connected to the metal frame of the aircraft, a second part of the at least one lightning arrester strip is connected to the emitting and/or receiving device via a metal element (35) of a predetermined shape, the at least one lightning arrester strip forming an antenna and a part of the metal element (35) is placed at a predetermined distance (d) from a part of the metal frame of the aircraft (30) for forming a capacitive link between the metal element and the metal frame of the aircraft.. . ... Airbus Operations Gmbh

02/08/18 / #20180039725

Aircraft assembly system

An aircraft assembly system as described herein includes an input module, a database, and a processing unit. The input module is adapted for inputting customer-specific data and, in particular, parameters which relate to the expected time of delivery, the number of personnel working in the aircraft assembly system or an apparatus of the system which cannot be used. ... Airbus Operations Gmbh

02/08/18 / #20180038280

Turbomachine comprising a heat management system

A dual-flow turbomachine including a nacelle, compressors, turbines, a fuel supply line, a transfer line, a de-icing circuit, and a heat management system having: a first heat exchanger providing an exchange of heat between fuel in the supply line and oil in the transfer line, a loop comprising a main line and a pump which circulates a heat transfer fluid in the main line, where the main line is connected to an outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger the main line meets an inlet of the de-icing circuit, where at the outlet of the de-icing circuit the main line meets the inlet of the pump, and where the third heat exchanger transfers heat between the heat transfer fluid of the main line and the oil of the transfer line.. . ... Airbus Operations Gmbh

02/08/18 / #20180037339

Component design system for generating aircraft component designs

The disclosed subject matter relates to a component design system for generating aircraft component designs. The component design system includes a database having a set of rules representative for different load characteristics of different component geometries. ... Airbus Operations Gmbh

02/08/18 / #20180037327

Aircraft having a redundant and efficient bleed system

An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. ... Airbus Operations Gmbh

02/08/18 / #20180037315

Landing gear drive system

The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. ... Airbus Operations Gmbh

02/08/18 / #20180037314

Landing gear

An aircraft include a landing gear is disclosed. The landing gear comprises a main strut and an inboard stay assembly connected to the aircraft fuselage such that landing gear loads can be transferred from the inboard stay assembly into the fuselage. ... Airbus Operations Gmbh

02/01/18 / #20180033418

Method for masking a sound signal generated by an element of the skin of an aircraft

A masking method includes: a step of choosing a generating element which is part of the skin of an aircraft, a first step of measuring a fundamental frequency of a sound signal emitted by the generating element, a step of selecting a masking element which is part of the skin, a second step of measuring a fundamental frequency of another sound signal emitted by the masking element, a step of modification of the structure of the masking element in such a way as to shift the fundamental frequency of the sound signal emitted by the masking element to a frequency lower than the fundamental frequency of the sound signal emitted by the generating element. Such a masking method thus makes it possible to mask the sound signal emitted by the generating element by the sound signal emitted by the masking element.. ... Airbus Operations Gmbh

02/01/18 / #20180029716

Variable seat module with an ottoman for a seating arrangement in a vehicle cabin

A seat module includes a passenger seat attachable to a cabin floor, and a separate ottoman unit associated with the passenger seat. The ottoman unit has at least one resting surface for a passenger and a base, which base is attachable to the cabin floor by an adjustment unit at a position in a first direction of the passenger seat. ... Airbus Operations Gmbh

02/01/18 / #20180029713

Space-optimized passenger seat arrangement for a vehicle cabin

A seat arrangement includes a first group of seats having first and second passenger seats, a second group of seats having third and fourth passenger seats, a first aisle parallel to a longitudinal axis, and a second aisle parallel to the longitudinal axis. The first passenger seat is situated next to the first aisle with a seat direction parallel thereto, and the fourth passenger seat is situated next to the second aisle with a seat direction parallel thereto. ... Airbus Operations Gmbh

02/01/18 / #20180029712

Seat arrangement for an interior space or a passenger cabin of a vehicle, as well as a respective vehicle

A seat arrangement for a vehicle has: parallel aisles in a longitudinal direction of a cabin; cabin walls arranged parallel to the aisles; a central region enclosed by the aisles; and two outer regions neighboring the central region and separated from the central region through the aisles. Seat rows having two inner seat modules and two outer seat modules, are arranged in the central region behind each other. ... Airbus Operations Gmbh

02/01/18 / #20180029711

Passenger cabin area

A passenger cabin area, which is suitable for installation in an aircraft cabin, includes passenger seats arranged one behind another along a longitudinal axis of the passenger cabin area. The passenger cabin area also includes luggage compartments which are arranged, at least in certain sections, in an area between an inner face, which faces towards an interior space of the passenger cabin area, of a fuselage sidewall and the passenger seats, and have an access aperture which faces towards the passenger seats.. ... Airbus Operations Gmbh

02/01/18 / #20180029710

System for disposing waste products in a means of transportation

A system for disposing waste in a transportation system includes a collection device for collecting waste in the cabin of the transportation system, a separate receptacle device for receiving collected waste from the collection device, and a connection device for selectively connecting the collection device to the receptacle device in order to deliver collected waste from the collection device into the receptacle device. The receptacle device is arranged in a lower deck region underneath the cabin floor. ... Airbus Operations Gmbh

01/25/18 / #a suspension system for an aircraft auxiliary power unit located in a fuselage structure, the system including:

Airbus Operations S.l.

. . ... Airbus Operations Gmbh

01/25/18 / #20180024237

Method and device for determining the position of an aircraft in an approach for a landing

A device comprising a radar for taking at least one radar image of the terrain in front of the aircraft in a zone containing at least one characteristic pattern, the position of the characteristic pattern being known, an image processing unit for detecting, on the radar image taken by the radar, a characteristic symbol representing the characteristic pattern, a computation unit for determining, from at least the position of the characteristic symbol in the image and from characteristics of the radar image acquisition, relative position information illustrating the position of the aircraft in relation to the characteristic pattern, and for determining the position of the aircraft, from the relative position information and from the known position of the characteristic pattern, and a unit for transmitting at least the position of the aircraft to at least one user system, for example a landing aiding system or an svs display.. . ... Airbus Operations Gmbh

01/25/18 / #20180023729

Support for a pipe

A support for a pipe. The support includes a body and at least one base configured so as to be in contact with and connected to a fixing surface. ... Airbus Operations Gmbh

01/25/18 / #20180023526

Removing water from fuel tanks

A combination of a fuel tank assembly and a tool for opening an outlet of the fuel tank assembly. The assembly includes a tank for storing a liquid hydrocarbon; and an operator-openable valve arrangement configured to move between a closed flow condition in which flow through the valve arrangement is prevented and an open flow condition in which liquid is allowed to drain out of the tank. ... Airbus Operations Gmbh

01/25/18 / #20180022458

Space-optimized passenger seat arrangement for a vehicle cabin

A passenger seat arrangement for a vehicle cabin includes at least one first group of passenger seats with a first passenger seat and a second passenger seat, at least one third passenger seat, and an aisle extending parallel to a longitudinal axis. The first passenger seat or the third passenger seat is arranged directly adjacent to the aisle and with a seating direction extending parallel thereto. ... Airbus Operations Gmbh

01/25/18 / #20180022442

System for actuating a control surface of an aircraft

An actuating system comprising a hydraulic actuator provided with a cylindrical cavity containing a piston configured to slide within the cylindrical cavity and a rod. The piston separates the cylindrical cavity into a first actuating chamber and a second actuating chamber. ... Airbus Operations Gmbh

01/25/18 / #20180022438

Thermoplastic moulded injected tip structure for an aircraft

A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, htp's, vtp's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.. ... Airbus Operations Gmbh

01/25/18 / #20180022436

Magnetic union of access panels and fairings of aircraft to its resistant structure

A union arrangement between a non-structural panel of the outer surface of an aircraft and a supporting member belonging to the aircraft resistant structure using mechanical and magnetic devices as an attachment arrangement. The magnetic devices comprise permanent magnets located in one of the non-structural panel or the supporting member and devices cooperating with the permanent magnets located in the other of the supporting member or the non-structural panel. ... Airbus Operations Gmbh

01/25/18 / #20180021902

Effector comprising a contact surface having an interface made of a ductile material

An effector includes at least one contact surface configured to bear against a face of a workpiece near a zone of the workpiece that is impacted by a tool supported by the effector. The contact surface includes at least one interface made of a ductile material interposed between the contact surface and the face of the workpiece.. ... Airbus Operations Gmbh

01/25/18 / #20180021880

Method of manufacturing a multi-alloy aerospace component

A method of making an aerospace component such as a spar for an aircraft wing is disclosed. The method includes placing two billets of different alloy in abutting relation, there being no voids or channels formed therebetween, partial penetration friction stir welding together the two billets from opposing sides of the billets, the welds so formed being separated by a central region formed partly by one billet and partly by the other billet, and then machining away material. ... Airbus Operations Gmbh

01/18/18 / #20180019527

Bonding clip shell

A bonding clip shell for protecting a bonding point between a bonding lead and a bonding strap. The bonding clip shell comprises a first part which comprises a first end, a second end, and an inner surface, the inner surface comprising a protrusion and a first seal, and a second part which comprises a first end, a second end and an inner surface, the inner surface comprising a cavity and a second seal. ... Airbus Operations Gmbh

01/18/18 / #20180016165

Waste separation device with separation magnetic filter

A device for separating waste includes a tank having a closed internal chamber, the device being provided with an inlet opening and an outlet opening that can be connected to a suction system. The internal chamber of the tank is provided with a magnetic filter making it possible to attract and retain ferromagnetic waste likely to be entrained by the suction system into the tank, with a grating placed between the filter and the base of the tank, with a fluid discharge system at the level of its base. ... Airbus Operations Gmbh

01/18/18 / #20180016029

Aircraft landing gear arrangement, a kit therefor, an aircraft comprising the same and a method of determining the angular position of an aircraft wheel

An aircraft landing gear arrangement is provided comprising: a first landing gear portion comprising one or more wheels, a second landing gear portion, the first landing gear portion being rotatable with respect to the second landing gear portion; and a sensor for determining a rotational position of the first landing gear portion in relation to the second landing gear portion, the sensor comprising a first magnetic field generator operable to generate a magnetic field and a first magnetic field modulator for modulating said magnetic field, the sensor being operable to sense the magnetic field as modulated by the first magnetic field modulator, the first landing gear portion comprising the first magnetic field generator or the first magnetic field modulator, the second landing gear portion comprising the other of the first magnetic field generator and the first magnetic field modulator.. . ... Airbus Operations Gmbh

01/18/18 / #20180016016

Arrangement in a vehicle cabin with folding seat protected from impacts

An arrangement in a cabin of a vehicle includes at least one cabin monument having a first wall and at least one second wall, at least one folding seat with an installation width occupied due to a back side of the folding seat and an installation depth occupied due to a lateral surface of the seat frame of the folding seat, and a delimiting device. At least one of the at least one second walls is arranged at an angle of at least 45° relative to the first wall. ... Airbus Operations Gmbh

01/18/18 / #20180016010

Large self-carrying monument assembly for an aircraft and an aircraft having such a monument assembly

A monument assembly for an aircraft includes at least one component of a primary structure of the aircraft, in particular a fuselage stiffening element, and a plurality of interconnected framework elements for creating a self-carrying three-dimensional framework. The at least one fuselage stiffening element is attachable to a skin of the aircraft and includes at least one bracket, wherein the framework is mechanically supported on the at least one bracket of the at least one component of the primary structure of the aircraft and wherein the framework comprises a plurality of compartments accessible from an interior region of the aircraft. ... Airbus Operations Gmbh

01/18/18 / #20180015998

Crocodile-type flight control surface for aircraft

A crocodile-type flight control surface comprising an upper foil flap, a lower foil flap, an actuating mechanism which guarantees the rotational displacement of each foil flap about a joint axis, either in the same direction or in different directions, and a locking mechanism alternatively adopting a locking position in which the upper foil flap and the lower foil flap are fixed with respect to each other and an unlocking position in which the upper foil flap and the lower foil flap are free with respect to the other. A crocodile-type flight control surface of this kind is therefore stiffened by the locking mechanism that joins the two foil flaps.. ... Airbus Operations Gmbh

01/18/18 / #20180015995

Structural component with an electrical transmission device, method for providing a structural component with an electrical transmission device, electrical wiring system and aircraft component

A structural component includes a composite laminate built up of a plurality of layers of carbon fibres, wherein the layers of carbon fibres are oriented in different directions, wherein the carbon fibres are surrounded by a conductive polymer resin, wherein the carbon fibres of at least one of the layers comprise an electrically insulating coating, and wherein at least one of the coated carbon fibres extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another.. . ... Airbus Operations Gmbh

01/18/18 / #20180015705

Structural component forming an electrical power source, structural component with an electrical transmission device, method for providing a structural component forming an electrical power source and/or an electrical transmission device, electrical wiring system and aircraft component

A structural component includes a composite laminate built up of layers of carbon fibers, wherein the layers of carbon fibers are oriented in different directions and wherein the carbon fibers are surrounded by a conductive polymer resin. The carbon fibers of at least one of the layers include an electrically insulating coating, and wherein at least one of the coated carbon fibers extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another. ... Airbus Operations Gmbh

01/11/18 / #20180013671

Embedded communications network of a vehicle

An embedded communications network of a vehicle is a deterministic switched ethernet network using virtual links, including a set of subscribers and a set of switches. A first subscriber is connected to a first switch and a third switch, and a second subscriber is connected to a second switch and to a fourth switch. ... Airbus Operations Gmbh

01/11/18 / #20180009548

Aircraft light

A wingtip device 1 including an upwardly extending winglet 2 and a downwardly extending winglet 4. The downwardly extending winglet 4 is connected to the upwardly extending winglet 2 at a join 6. ... Airbus Operations Gmbh

01/11/18 / #20180009543

Aircraft engine mount comprising at least one transverse nut and aircraft comprising the said engine mount

An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.. ... Airbus Operations Gmbh

01/11/18 / #20180009535

Seat rail mounting member

An aircraft assembly with first and second seat rails for interlocking with an aircraft seat, and a systems component mounting member interlocked with those seat rails. The mounting member has a first anchor member interlocked with the first seat rail and a second anchor member interlocked with the second seat rail. ... Airbus Operations Gmbh

01/11/18 / #20180009533

Method of automatic positioning of a seat

A method of automatic positioning a seat in an apparatus comprising two cameras located on either side of the seat, each one in a position able to acquire images of a face of a user seated on the seat. The seat comprises at least one motor, each motor acting on a position of the seat along a predefined axis. ... Airbus Operations Gmbh

01/11/18 / #20180009532

Aircraft cockpit module, aircraft comprising such a module and method for installing the module in a cockpit

An aircraft cockpit module (10) that incorporates, on the one hand, a single pilot seat (12) and, on the other hand, at least a part of the piloting equipment and controls necessary for flying an aircraft, the module (10). The aircraft cockpit module forms an assembly which can be moved unitarily and to be incorporated in a single operation in an aircraft cockpit. ... Airbus Operations Gmbh

01/11/18 / #20180009530

Aircraft installation arrangement and installation system for mounting an overhead luggage compartment

An installation arrangement comprising a first carrier element configured to fasten an overhead luggage compartment thereto. The first element includes a main body comprising a tubular opening, a barrel-shaped component arranged inside the tubular opening, the component comprising a through hole extending substantially perpendicular to a component longitudinal axis, and a fastener to fasten a portion of the overhead luggage compartment to the main body of the first carrier element. ... Airbus Operations Gmbh

01/11/18 / #20180009520

Interior component carrier system and method for mounting an interior component carrier system

An interior component carrier system comprises a first and second installation rail. Each rail includes at least one connecting portion connectable to an associated primary structure component to fasten the rail to the component, and a carrier portion extending from the connecting portion in a direction along a longitudinal axis of the system. ... Airbus Operations Gmbh

01/04/18 / #20180007813

Cooling system for cooling electronic aircraft equipment, aircraft equipped with a cooling system for cooling electronic aircraft equipment and method for cooling electronic aircraft equipment

A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. ... Airbus Operations Gmbh

01/04/18 / #20180001989

Window frame system, window frame attachment system and vehicle hull window frame attachment system

A window frame system, comprising a window frame having an aperture there-through and circumferentially arranged window frame through-holes in a first window frame portion and a second window frame portion, and a stringer coupling with stringer coupling through-holes in a first stringer coupling portion and a second stringer coupling portion. In an overlapping arrangement, the first window frame portion and the first stringer coupling portion are adapted to overlap with their through-holes coaxially, wherein the respective through-holes of the two first portions have different diameters.. ... Airbus Operations Gmbh

12/28/17 / #20170372626

Method and system for aiding the ground rolling of an aircraft

In an aircraft comprising a cockpit comprising a display screen, a camera configured to acquire images of the environment of the aircraft, as well as a display management system, a ground rolling aid system configured so as to a) acquire several successive images of the environment of the aircraft via the camera, corresponding to various ground positions of the aircraft, b) modify these images by removing at least zones corresponding to the aircraft, so as to produce modified images, c) combine several of the modified images to produce a recomposed image, d) superpose an image characteristic of the aircraft on the recomposed image so as to produce a reference image, and e) display, on the cockpit display screen, an image corresponding to the reference image.. . ... Airbus Operations Gmbh

12/28/17 / #20170369170

Arrangement in a vehicle cabin with cabin monuments placeable in rows with laminar contact of the lateral surfaces thereof

An arrangement in a cabin of a vehicle has a plurality of cabin monuments, placeable in rows, of which the lateral surfaces are in laminar contact, said cabin monuments having a front side and a rear side and a wall surface of the aircraft fuselage, at least sections of which face toward the cabin of the vehicle and are not aligned parallel with a lengthwise axis of the cabin. The cabin monuments are arranged in rows parallel to the lengthwise axis of the cabin, so that the front sides and the rear sides are each aligned parallel to the lengthwise axis of the cabin. ... Airbus Operations Gmbh

12/28/17 / #20170369151

Methods of configuring a wing tip device on an aircraft

A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).. ... Airbus Operations Gmbh

12/28/17 / #20170369146

Aircraft comprising a clearance between an opening and a door which comprises an upstream edge with a sharp edge

An aircraft includes a clearance between an opening and a door. The clearance communicates with a cavity and is oriented in a direction intersecting a flow direction of an air flow to the outside of the aircraft in flight. ... Airbus Operations Gmbh

12/28/17 / #20170368769

Method of forming a structural portion of a fuel tank for an aircraft

The present application relates to a method of forming a structural portion of a fuel tank for an aircraft in which the structural portion is formed from a fibre reinforced polymer and a sensor is integrated in the structural portion. The method includes providing a fibre ply which acts as a structural component, and embroidering an electrically conductive wire in a predetermined pattern on the fibre ply to form the sensor. ... Airbus Operations Gmbh

12/21/17 / #20170363514

Method for monitoring the engines of an aircraft

A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.. ... Airbus Operations Gmbh

12/21/17 / #20170363482

Aircraft brake temperature measurement

A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. ... Airbus Operations Gmbh

12/21/17 / #20170361940

Aircraft strut comprising at least one lateral frame in lattice form and aircraft comprising said strut

An aircraft strut includes a primary structure which includes: a top stringer, a bottom stringer, at least one transverse frame which links the top stringer to the bottom stringer, a front end wall which links a front end of the top stringer to a front end of the bottom stringer, a rear end wall which links a rear end of the top stringer to a rear end of the bottom stringer, two lateral frames arranged on either side of the transverse frame, each lateral frame having a lattice form. An aircraft includes at least one strut described herein.. ... Airbus Operations Gmbh

12/21/17 / #20170361939

Assembly for aircraft comprising engines with boundary layer propulsion by injection

In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.. . ... Airbus Operations Gmbh

12/21/17 / #20170361932

Expandable cargo storage, transportation means section, transportation means and method of operating a cargo storage, a transportation means section, or a transportation means

An expandable cargo storage for a transportation means, comprising a first storage wall and a second storage wall opposite of the first storage wall, and a plurality of foldable walls arranged between the first and the second storage wall, each of the plurality of foldable walls being foldable between a first position in which the respective foldable wall is arranged essentially in parallel with the second storage wall, and a second position in which the foldable wall is arranged essentially perpendicularly to the second storage wall, wherein, when each of the foldable walls is arranged in its first position, the cargo storage is in a first operational state enclosing a first volume, and when each of the foldable walls is in its second position, the cargo storage is in a second operational state enclosing a second volume which is larger than the first volume.. . ... Airbus Operations Gmbh

12/21/17 / #20170361918

Active flow control devices for aircraft wings

An aircraft wing incorporating an active flow control (afc) device the afc device comprises a fluid chamber housed in the wing providing a conduit for receiving fluid and accommodating the fluid at elevated pressure. Forward and rearward fluid channels having respective inlets and outlets are also provided, wherein the inlets are in fluid communication with the fluid chamber and the outlets emerge on the upper surface of the wing at or adjacent the leading edge. ... Airbus Operations Gmbh

12/21/17 / #20170361917

Aircraft exhibiting independent elevators

An aircraft includes a structure exhibiting a median plane xz and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane xz, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane xz independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.. ... Airbus Operations Gmbh








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