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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


Method and system for flight plan data transmission in an aircraft

A device and method for safe and secure flight management of an aircraft that includes: a flight management system (3) which determines a flight path for the aircraft; a guidance module (2) which supplies command instructions to a guidance system (4) of the aircraft based on the flight path; a safe and secure interface (5) between the flight management system (3) and the guidance module (2); the flight management system (3) including a first transmission module (7a) for transmitting the flight path determined by the flight management system (3) to the guidance module (2) via the safe and secure interface (5) after the flight path has been validated by the operator; a second transmission module (7b) for transmitting the flight path to the guidance module (2) via the safe and secure interface (5) periodically or subsequent to an event likely to modify the flight path.. . ... Airbus Operations Gmbh

Clip for fastening a pipe to a support

A clip for fastening a pipe to a support, comprising a fixed part, a mobile part, a first joint connecting a first edge of the fixed part and a first end of the mobile part, and a system for holding the mobile part a closed state. The system comprises a lever and a second joint connecting the lever to a second end of the mobile part, and an angled u-shape connected to the second edge of the fixed part, configured to permit the lever and the second joint to pass through the angled u-shape and to permit the lever to be positioned in a folded position against an external face of the mobile part to hold the mobile part in the closed state.. ... Airbus Operations Gmbh

Hydraulic actuator and accumulator arrangement

A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. ... Airbus Operations Gmbh

Adapter rail system and method for mounting an object to a floor rail in a transportation system

An adapter rail system for mounting objects to a floor rail in a transportation means includes an elongate adapter rail element, an arresting element and a movement rail element. The adapter rail element has a surface contour having regularly consecutively arranged neckings and widenings, which surface contour corresponds to an opening contour of a floor rail, which includes regularly consecutively arranged grid openings, which are penetrated by a slit. ... Airbus Operations Gmbh

Galley monument with charging station

A galley monument has at least one galley element and at least one charging station integrated in a slide-in compartment in the galley monument for charging electrical energy storage of personal electronic devices. The charging station has a locking element having a locking mechanism. ... Airbus Operations Gmbh

Cabin monument for an aircraft

A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. ... Airbus Operations Gmbh

Rotational joint for an aircraft folding wing

An aircraft (2) including a wing (1), the wing (1) having a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between flight and ground configurations, the aircraft including a rotational joint (10) with a rotation mechanism (11) that rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism including a locking bore (53, 54) and a locking pin (51) that is receivable in the locking bore to lock the wing tip device (4) in one of the flight or ground configurations, wherein the rotational joint includes an alignment mechanism including an alignment pin (61) and an alignment bore (62, 63) and at least one of the alignment pin and alignment bore is tapered such that engagement of the alignment pin (61) in the alignment bore acts to guide the locking bore and locking pin into alignment.. . ... Airbus Operations Gmbh

Opening and secure-closing system

A safety open and closing system for an overpressure door on fuselage of an aircraft. Wherein the safety opening and closing system allows safe access through the overpressure door to the compartment. ... Airbus Operations Gmbh

Bipolar high-voltage network and method for operating a bipolar high-voltage network

An aircraft bipolar high-voltage network includes a dc voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The dc voltage converter has a first dc voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second dc voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.. ... Airbus Operations Gmbh

Energy storage system, method for operating an energy storage system, and method for producing an energy storage system

An energy storage system, a method for operating the energy storage system, and a method for producing an energy storage system. The energy storage system comprises a housing having a laminated energy storage structure and at least one connector, disposed in the housing, for an energy storage element or a group of energy storage elements. ... Airbus Operations Gmbh

Linear guide mechanism for a passenger seat

A linear guide mechanism for a passenger seat includes a movable carriage and a guide rail. The linear guide mechanism further includes a guide unit for positioning the movable carriage on the guide rail. ... Airbus Operations Gmbh

Cable routing in aircraft

An aircraft configurator for calculating locations of consumers and routes along which consumers are to be connected to corresponding suppliers of the aircraft. A computing unit can calculate different connection routes and select the connection route where a key performance indicator is optimal and takes into account additional installations that influence the route. ... Airbus Operations Gmbh

Aircraft reconfigurator for reconfiguring an aircraft configuration

An aircraft reconfigurator for reconfiguring an aircraft configuration includes a storage unit that stores aircraft specific data of a predetermined initial configuration, and an input unit for inputting a mission specific reconfiguration parameter. The aircraft reconfigurator includes a processing unit for reconfiguring the initial aircraft configuration based on the stored aircraft specific data of the predetermined initial aircraft configuration and the predetermined mission specific reconfiguration parameter so as to design several alternative aircraft configurations, each of which has a different variant of a cabin layout.. ... Airbus Operations Gmbh

Reconfiguration of aircraft

An aircraft reconfigurator system reconfigures a predetermined aircraft configuration, in particular a cabin layout, for which a distance between a position of a center of gravity of the aircraft, the center of gravity being optimized with respect to aerodynamic characteristics, and the actual position of the center of gravity is determined and thereupon an element of the aircraft is selectively displaced such that the position of the center of gravity is approximated to the optimized position of the center of gravity. Afterwards, a new aircraft configuration, in which the selected element is arranged in the new position, is determined. ... Airbus Operations Gmbh

07/26/18 / #20180208329

Deformable shim and mounting arrangement

In order to improve and facilitate shimming between two parts, a deformable shim is provided that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. ... Airbus Operations Gmbh

07/26/18 / #20180208317

Space optimized cabin arrangement for a vehicle as well as a passenger cabin having a plurality of seats and such a cabin arrangement

A cabin arrangement for a vehicle includes a first lateral segment module having a first main extension axis, a second lateral segment module having a second main extension axis, and an aisle. The main extension axes run parallel to each other, wherein the first lateral segment module and the second lateral segment module are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle between each other. ... Airbus Operations Gmbh

07/26/18 / #20180208316

Forward interior space arrangement for an aircraft

An interior space for an aircraft includes a cockpit, a cockpit wall separating the cockpit from the remaining interior space, a cabin door arranged directly behind the cockpit wall for accessing the interior space of the aircraft from outside the fuselage, a modular installation space for installation equipment, a plurality of seat rows, a longitudinal aisle extending along the interior space through the seat rows to separate adjacent groups of seats from each other, and an access path for the cabin door. The access path extends from the cabin door to the longitudinal aisle to create an intersection region between the access path and the longitudinal aisle. ... Airbus Operations Gmbh

07/26/18 / #20180208315

Sleeping box, sleeping box arrangement and aircraft area

A sleeping box for installation in an aircraft includes a casing which is suitable for accommodating a person located in a reclining position parallel to a longitudinal axis of the casing and which has an access aperture in the area of a front side which extends perpendicularly to the longitudinal axis of the casing. The sleeping box also includes a fastening apparatus which is configured to fasten the sleeping box within a passenger cabin of the aircraft in such a way that the longitudinal axis of the casing extends perpendicularly to a longitudinal axis of the passenger cabin and the access aperture of the casing borders on an aisle which is present within the passenger cabin.. ... Airbus Operations Gmbh

07/26/18 / #20180208314

Space efficient cabin segment for a vehicle as well as a passenger cabin having a plurality of seats and such a cabin segment

A cabin segment for a vehicle includes a first lateral segment module having a first main extension axis, a second lateral segment module having a second main extension axis, and an aisle arranged in the cabin segment. The main extension axes parallel to each other, and the first and second lateral segment modules are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle, which runs parallel to the main extension axes. ... Airbus Operations Gmbh

07/26/18 / #20180208313

Monument

A monument has a connection device, a fluid source and a compartment for the installation of a modular unit. The connection device is intended for connecting the fluid source to a modular unit installed in the compartment. ... Airbus Operations Gmbh

07/26/18 / #20180208300

Fault detection based on brake torque and temperature

A fault detection system for an aircraft braking system including: a controller configured to receive braking demand information; torque information; wear information; wheel speed information; and brake temperature information. The controller is to calculate an expected maximum temperature of the brake based on the torque information, the wear information and the wheel speed information; to determine whether a significant temperature discrepancy exists between the expected maximum temperature and the brake temperature information; to determine whether a significant torque-related discrepancy exists based on the braking demand information and the torque information. ... Airbus Operations Gmbh

07/26/18 / #20180207890

Method for manufacturing of a fiber composite component

Disclosed is a method for manufacturing a fiber composite member. The method involves the step of producing a fiber layer by depositing at least two fiber webs in a plane adjacent to each other and along a circular guiding arc. ... Airbus Operations Gmbh

07/26/18 / #20180207726

Structural component, method for producing a structural component and method for designing a structural component

A structural component, in particular for an aircraft, has a grid structure which is constructed from rod elements, wherein the rod elements form basic units which are repeated within the grid structure and each have the same polyhedral outer shape. A first number of reinforcing elements are provided in a first region of the grid structure, and a second number of reinforcing elements are provided in a second region of the grid structure, wherein the second number of reinforcing elements is smaller than the first number of reinforcing elements.. ... Airbus Operations Gmbh

07/19/18 / #20180204490

Illumination device for illuminating the vertical tail plane of an aircraft and aircraft with exterior illumination on its vertical tail plane

A device for illuminating a vertical tail plane of an aircraft, comprising a matrix of leds or lasers, a laser diode with a diffractive optical element, an electronic board with a microcontroller, a power supply unit and a housing enclosing one or more of the matrix of leds, the laser diode, the electronic board and the power supply unit. The leds or lasers and the laser diode are individually and electronically controlled by the microcontroller, in such a way that the leds or lasers can be individually dimmed to create a dynamic illumination pattern on the side surfaces of the vertical tail plane. ... Airbus Operations Gmbh

07/19/18 / #20180201387

Air intake structure for an aircraft nacelle

An aircraft nacelle air intake structure including an air intake lip with a u-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. ... Airbus Operations Gmbh

07/19/18 / #20180201377

Compact functional arrangement in a cabin of a vehicle and vehicle with such a functional arrangement

A functional arrangement in a cabin of a vehicle includes a monument with a housing having several side walls, which define an interior space, and at least two adjacently arranged seats each having a backrest and headrest. The seats adjoin an exterior side of a first side wall of the housing, and have a seating direction facing away from the first side wall. ... Airbus Operations Gmbh

07/19/18 / #20180201374

Temperature regulating system for a galley compartment of an in-flight kitchen

A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, especially in an aircraft, includes a controllable cooling and heating element, which is designed for selectively cooling or heating a specified section of the cooling and heating element, and a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element. The heat-insulating partitioning wall is designed for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen.. ... Airbus Operations Gmbh

07/19/18 / #20180201362

Aircraft with a variable fuselage surface for boundary layer optimization

An aircraft including a propulsion system formed by engines arranged to ingest boundary layer air. These engines are placed inside of nacelles partially embedded in the aircraft fuselage and, thus, their intake conduits are delimited by specific fuselage areas and the nacelles. ... Airbus Operations Gmbh

07/19/18 / #20180201361

Lifting surface

A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.. . ... Airbus Operations Gmbh

07/19/18 / #20180201360

Lifting surface

A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. ... Airbus Operations Gmbh

07/19/18 / #20180200966

Apparatus and method for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material

An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line.. ... Airbus Operations Gmbh

07/19/18 / #20180200959

Method and apparatus for manufacturing a three-dimensional object by additive layer manufacturing

A method of manufacturing a three-dimensional object which successively applies layers of material in powder form one on top of the other, wherein the first layer is applied to a support. Prior to providing the subsequent layer, each layer is irradiated selectively in a portion of the layer corresponding to a three-dimensional object being manufactured and wherein the irradiation is carried out in such a manner that the material is melted locally in the corresponding portions. ... Airbus Operations Gmbh

07/12/18 / #20180194622

Ammonia borane confinement in graphene oxide 3d structures

The present disclosure relates to a composite having a porous graphene oxide material (a) and ammonia borane (b), wherein the porous graphene oxide material (a) has a density of 1-100 mg/cm3, and a method for producing the same. The disclosure also relates to a hydrogen-releasing device having the disclosed composite as well as to an energy-producing device having the disclosed composite. ... Airbus Operations Gmbh

07/12/18 / #20180194476

Passenger seat system having movable seats for a transportation means as well as an aircraft cabin having such a passenger seat system

A passenger seat system for a transportation system includes at least one support structure and at least one seat, which includes a seat frame, which is movable and arrestable on the support structure and has an underside that rests on the support structure and an upper side that receives a seating surface. The seat frame has an arresting device on the underside and an operating unit on the upper side coupled with the arresting device. ... Airbus Operations Gmbh

07/12/18 / #20180194453

A rotational joint for an aircraft folding wing

A folding wing having a wing tip device (3) rotatable between flight and ground configurations, about an euler axis of rotation (11). The wing tip device (3) and a fixed wing (1) are separated along an oblique cut plane (13) passing through the upper and lower surfaces of the folding wing. ... Airbus Operations Gmbh

07/12/18 / #20180194452

Method for manufacturing a thermoacoustic insulation module for an aircraft comprising a bending step

In order to facilitate the thermoacoustic insulation of an aircraft portion, a method for manufacturing a thermoacoustic insulation module for an aircraft comprises a step of providing a mat configured to provide thermoacoustic insulation of an aircraft portion, followed by a step of attaching a bendable structure to the mat, followed by a step of bending the bendable structure, along a bending axis parallel to a longitudinal direction of the mat, such that the bendable structure forms a load-bearing structure supporting the mat in a curved shape.. . ... Airbus Operations Gmbh

07/12/18 / #20180194096

Sandwich panel with recessed channel network

A composite sandwich panel comprises a top layer, a bottom layer, and a honeycomb core layer sandwiched between the top layer and the bottom layer. The honeycomb core layer includes an array of hollow cells formed between vertical walls. ... Airbus Operations Gmbh

07/05/18 / #20180187601

Oil heating system adapted for turbine engine to reduce starting torque

An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (apu). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. ... Airbus Operations Gmbh

07/05/18 / #20180186463

Primary structure of a pylon for an aircraft engine assembly comprising a pyramidal part with converging upright members

A primary structure of a support pylon for an aircraft engine assembly. The primary structure includes a pyramidal part, the pyramidal part including a single rib, the single rib forming the base of the pyramidal part, and straight, upright members converging towards an apex point of the pyramidal part, a fastening interface being provided at the apex of the pyramidal part. ... Airbus Operations Gmbh

07/05/18 / #20180186462

Engine assembly for an aircraft comprising a front engine attachment which facilitates its assembly

For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.. . ... Airbus Operations Gmbh

07/05/18 / #20180186459

Support structure for a flight attendant seat

A support structure for a flight attendant seat, the support structure having supporting elements arranged at an upper and a lower end of the support structure. The supporting elements connect the support structure to an aircraft structure via fastening points, the support structure having receiving elements for receiving the flight attendant seat. ... Airbus Operations Gmbh

07/05/18 / #20180186105

Diaphragm tool for forming reinforcement fiber tiers into preformed t-shaped profiles

A tool for shaping non-cured reinforcement fibers into a substantially t-shaped profile, comprising a web-shaping tool and a forming tool, wherein the forming comprises an inflatable diaphragm.. . ... Airbus Operations Gmbh

06/28/18 / #20180182369

Method for obtaining a porous acoustic layer and porous acoustic layer thus obtained

A method for obtaining a porous acoustic layer, comprising a step of deposition of a plurality of fiber wicks arranged in at least two secant directions, the width, the orientation and/or the spacing of the fiber wicks being determined as a function of the open surface ratio desired for each zone of the porous acoustic layer. A porous acoustic layer obtained according to the method, as well as an acoustic panel comprising at least one porous layer, are also disclosed.. ... Airbus Operations Gmbh

06/28/18 / #20180178923

Semi-continuous fixation of an engine attachment pylon to an attachment device belonging to the wings of an aircraft

Fixation of an aircraft engine attachment pylon to the wing of an aircraft by means of an attachment device attached to a wing structure by means of first attachment through-members. The attachment device and the attachment pylon have respective junction surfaces clamped to each other by means of second attachment through-members. ... Airbus Operations Gmbh

06/28/18 / #20180178917

Structure for propulsive aircraft assembly, associated propulsive system and assembly

A structure made of composite material for a propulsive aircraft assembly includes at least one thermal zone designed to receive electrical energy. Each thermal zone includes at least one resistive skin having an inner film produced in a thermoplastic material made conductive by the inclusion of carbon nanotubes, such that each resistive skin is designed to dissipate, by joule effect, at least a portion of the electrical energy received by the thermal zone, an intermediate ply produced in a satin fabric impregnated with a thermoplastic material, and an outer film produced in a thermoplastic material.. ... Airbus Operations Gmbh

06/28/18 / #20180178901

Wing for an aircraft

A wing for an aircraft, comprising a main wing, a slat, and a connection assembly for movably connecting the slat to the main wing. The connection assembly comprises first and second link elements. ... Airbus Operations Gmbh

06/28/18 / #20180178900

Wing for an aircraft

A wing for an aircraft, comprising a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, allowing the slat to be moved between a retracted and at least one extended position. The assembly comprises an elongate slat track mounted to the main wing movably along a track longitudinal axis and connected to the slat. ... Airbus Operations Gmbh

06/28/18 / #20180178897

Thermoacoustic insulation module for an aircraft, comprising a mat and a load-bearing structure, and thermoacoustic insulation method for insulating an aircraft by means of such a module

In order to facilitate the thermoacoustic insulation of an aircraft portion, a thermoacoustic insulation module for an aircraft comprises a mat and a load-bearing structure detachably attached to the mat and supporting the mat in a curved shape, with an axis of curvature parallel to a longitudinal direction of the mat. A thermoacoustic insulation method for insulating an aircraft portion comprises a step of inserting the thermoacoustic insulation module into the aircraft portion, followed by a step of detaching the mat from the load-bearing structure, followed by a step of attaching the mat to an aircraft structure delimiting the aircraft portion, followed by a step of removing the load-bearing structure from the aircraft portion.. ... Airbus Operations Gmbh

06/28/18 / #20180178894

Bendable element that can be bent by inflating an envelope, bendable batten and structure comprising such an element and associated bending methods

A bendable element is formed at least from an inflatable envelope, a first bendable, elongate base plate attached to a first face of the inflatable envelope, a second bendable, elongate base plate, attached to a second face of the inflatable envelope and shorter than the first base plate, and links connecting the first base plate to the second base plate. The links are slack when the inflatable envelope is in a deflated state. ... Airbus Operations Gmbh

06/28/18 / #20180178451

Additive manufacturing system and method for validating additively manufactured components

Validating additively manufactured components is carried out by transmitting to a distributed validation network printing specification data for a component that is to be additively manufactured, validating the printing specification data, and adding the printing specification data, together with a cryptographically encoded checksum, to a print history log, transmitting the printing specification to a 3d printing device, and implementing a generative manufacturing process for the component that is to be additively manufactured in accordance with the transmitted printing specification data. While the generative manufacturing process is being carried out, in each case following specified manufacturing stages, a plurality of manufacturing parameters prevailing in the preceding manufacturing stage are transmitted to the distributed validation network. ... Airbus Operations Gmbh

06/28/18 / #20180178370

Guiding device designed to be positioned on a surface with a double radius of curvature

A guiding device includes a rail which extends in a direction, a plurality of runners distributed in the direction, and, for each runner, at least one runner/rail connection connecting each runner and the rail, configured to allow each runner to pivot independently from the other runners relative to the rail, around an axis of pivoting parallel to the direction.. . ... Airbus Operations Gmbh

06/21/18 / #20180175753

Control device for a polyphase motor and method for driving a polyphase motor

An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (ub), a low terminal for applying a reference potential of the supply voltage (ub), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.. . ... Airbus Operations Gmbh

06/21/18 / #20180174568

Structure establishing a sound insulator

A structure establishing a sound insulator and including a first plate, a second plate having holes therethrough, and a web stuck between the plates. The web includes a plurality of intermediate strips perpendicular at least to one of the plates, a plurality of folded strips which are folded in a zig-zag formation, each folded strip being arranged between two successive intermediate strips, and establishes, with the intermediate strips, triangular prisms, where, for two folded strips on either side of a same intermediate strip, the generator of the triangular prism of one of the folded strips forms an acute angle with respect to the first plate, and the generator of the triangular prism of the other folded strip forms an obtuse angle with respect to the first plate.. ... Airbus Operations Gmbh

06/21/18 / #20180174565

Energy absorbing structure for attenuating the energy transmitted from an energy source

An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive poisson's ratio, one or more second layers of a material having a negative poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. ... Airbus Operations Gmbh

06/21/18 / #20180174473

Method and device for adjusting performance variables of an aircraft

A method and device for adjusting performance variables of an aircraft. The device which is intended for adjusting performance variables, the performance variables being generated by at least one performance module, includes an auxiliary data input unit for entering into a flight management system correction data intended to be used for adjusting at least one associated performance variable, and a correction unit for carrying out a correction, the correction including adjusting the associated performance variable on the basis of the input correction data.. ... Airbus Operations Gmbh

06/21/18 / #20180174014

Temperature detection system using a radio-tag comprising a thermistor

An onboard system for detecting a temperature of an element includes a radio-tag, the radio-tag being fixed onto the element and having an antenna, the antenna having a load, and a radio-tag reader. The radio-tag reader is designed to emit an interrogation signal and to receive in return a response signal coming from the radio-tag. ... Airbus Operations Gmbh

06/21/18 / #20180173841

Computer aided-method for a quick prediction of vortex trajectories on aircraft components

A computer-aided method suitable for assisting in the design of an object zone, such as a cror engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field, by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of the object zone and a system based on the method. The method steps are: a) obtaining a dataset containing all the cells or points satisfying one of the conditions of four region-based vortex detection criteria (the q-criterion, the kinematic vorticity number, the Δ-criterion, the λ2-criterion); b) obtaining a new dataset containing all the cells or points of the previous dataset satisfying one of the conditions mentioned in step a) not selected previously; c) repeating the step b) until all the conditions mentioned in step a) have been selected in step b).. ... Airbus Operations Gmbh

06/21/18 / #20180173840

Computer aided-method for a quick prediction of vortex trajectories on aircraft components checking high pressure gradients and high drag friction components

A computer-aided method suitable for assisting in the design of an object zone such as a cror engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of said object zone and a system based in said method. The method steps are: a) obtaining a dataset of candidate seeds containing all the cells or points satisfying a condition of the pressure gradient in the direction of the flow or a condition of the drag friction coefficient at the solid boundaries; b) updating the previous dataset of candidate seeds with all the cells or points satisfying the equation not used for obtaining the dataset in step a).. ... Airbus Operations Gmbh

06/21/18 / #20180172921

Optical fiber connection device for a composite structure, composite structure for an aircraft, and manufacturing method thereof

An optical fiber connection device comprising a prism, first and second connection elements, inner and outer ferrules and an elastic element. The prism has an inner conduit ending in a first bore configured to receive an input optical fiber, and in a second bore configured to receive the first connection element, which, in turn, is configured to receive the second connection element. ... Airbus Operations Gmbh

06/21/18 / #20180172719

Electronic device for detecting an air flow

An electronic device for detecting an air flow includes at least one sensor having a pair of platelets, each platelet having an rtd and having one end fixed, the other end being free and overlapping the free end of the other platelet. A platelet is flexible so as to form a switch for an electrical circuit. ... Airbus Operations Gmbh

06/21/18 / #20180172435

A measuring apparatus for measuring properties of a surface

The present invention provides a measuring apparatus (200) for measuring properties of a surface (101, 103), the apparatus (200) comprising a mounting structure (210) comprising a plurality of segments (211-216) moveably mounted (217) with respect to each other, an actuation mechanism to move the segments of the mounting structure with respect to each other, and a plurality of sensors (220), each sensor being mounted to a segment of the mounting structure (210). The invention also provides a method of measuring properties of a surface (101, 103). ... Airbus Operations Gmbh

06/21/18 / #20180172159

Aircraft seal assembly

An aircraft assembly may have a drag-inducing discontinuity 112. A seal assembly 101 includes a seal body 110 arranged to fair and/or seal the discontinuity 112; and a sealed chamber 114, wherein the sealed chamber 114 being pressurised such that in response to changes in the ambient pressure relative to the internal pressure of the chamber 114 the sealed chamber 114 alters the behaviour of the seal body 110.. ... Airbus Operations Gmbh

06/21/18 / #20180172056

Cap for a fastener

A cap configured for providing a sealed cavity around an end of a fastener and a method of bonding a cap to a structural member in which a contact adhesive is provided for fixing the cap to the structural member and a curable sealant is provided for bonding the cap to the substrate.. . ... Airbus Operations Gmbh

06/21/18 / #20180172047

Conductive support, tool for fitting said conductive support, method for fitting said conductive support on an aircraft structure and aircraft structure provided with said conductive support

A conductive support is disclosed which is configured to be fixed, thanks to an electrically conductive glue, on a surface of a metal structure and which includes an insert made from an electrical material which includes a first end face configured to be pressed against the surface of the structure and a second end face allowing the temporary fixing of an electrical element; and a body which includes a contact face coplanar with the first end face of the insert and which extends completely around the first end face of the insert.. . ... Airbus Operations Gmbh

06/21/18 / #20180170578

Device for protecting the airfoils of an aircraft against bad weather and positioning method

Devices for protecting aircraft against bad weather. A device for protecting a wing of an aircraft including a load-bearing structure for a protective wall for the wing, the load-bearing structure having a supporting frame having at least two uprights linked by at least one cross member, at least one upright, at the end of the frame having a linking attachment arrangement permitting at least rotation about an axis perpendicular to the surface, the other uprights, each having one foot with an arrangement configured to facilitate the movement of the frame over the surface on which the frame rests. ... Airbus Operations Gmbh

06/21/18 / #20180170563

Rear portion of an aircraft comprising a fuselage frame supporting two partly buried engines

In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.. ... Airbus Operations Gmbh

06/21/18 / #20180170557

Leading edge ice-protection system

An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.. . ... Airbus Operations Gmbh

06/21/18 / #20180170530

Landing gear drive systems

A drive system for rotating one or more wheels of an aircraft landing gear for ground taxiing and/or spin-up prior to landing has a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path. ... Airbus Operations Gmbh

06/21/18 / #20180170520

Impact resistant dorsal fin

An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.. . ... Airbus Operations Gmbh

06/21/18 / #20180170519

Locking device

An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof the wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. ... Airbus Operations Gmbh

06/21/18 / #20180170513

Aircraft having a rear section with a continuous skin for the fuselage and the vertical tail plane

An aircraft rear section (20) including a fuselage rear section (21) extending from the rear pressure bulkhead (23) to the end of the fuselage and an empennage (12) including at least a vertical tail plane (13). An aircraft rear section (20) with a continuous skin (31) is formed by two lateral sides placed symmetrically with respect to the middle vertical plane of the aircraft, each side including an upper portion (26) for the torsion box (14) of the vertical tail plane (13), a lower portion (28) for the fuselage rear section (21) and a transition portion (27) between the upper and lower portions (26, 28). ... Airbus Operations Gmbh

06/21/18 / #20180170512

Aircraft door arrangement with sound reduced hollow space which can be covered by an aircraft door

An aircraft door arrangement includes a door, a door seal, and a door opening. The door opening has an opening edge adjoining the door opening and extending into the aircraft fuselage, at which a seal seat is arranged, which can be brought into flush contact with the door seal. ... Airbus Operations Gmbh

06/14/18 / #20180167608

Display system and method for an aircraft

A display system for a cockpit of an aircraft comprises a display device configured to be secured to a user's head in the cockpit of the aircraft. A display computer is configured to control the display of information on the display device. ... Airbus Operations Gmbh

06/14/18 / #20180166734

Method for tailoring and integrating a fuel cell unit into a vehicle

A method for integrating a fuel cell unit into a vehicle structural component, includes determining an available receiving space in an interior structural component of the vehicle, providing two casing parts assembleable to a closed casing, providing a fuel cell having an anode, a cathode and an electrolyte, assembling the casing parts and the fuel cell to form the fuel cell unit, and inserting the fuel cell unit into the receiving space. A casing part is additively manufactured such that the fuel cell unit precisely fits into the receiving space. ... Airbus Operations Gmbh

06/14/18 / #20180163773

Damping connecting rod

A damping connecting rod that can be converted into a rigid connecting rod in the case of abnormal vibrations. The damping connecting rod comprises a body having a cavity and a shaft inside the cavity, with a clevis associated with the body and allowing the clevis to be fixed to an element. ... Airbus Operations Gmbh

06/14/18 / #20180163769

Hot joint fastener

A method for joining together different components or different sections of a single component, wherein at least one of the components is a thermoplastic fiber composite component, by using a threaded fastener. Heat is used for softening the thermoplastic fiber composite component to be joined together with the threaded fastener. ... Airbus Operations Gmbh

06/14/18 / #20180163734

Method and device for testing samples on a turbine engine minimizing the risk of surge by the exchange of information between an energy manager and a system for testing the turbine engine

A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. ... Airbus Operations Gmbh

06/14/18 / #20180162706

Elevator system for auxiliary power unit

An elevator system (400) to assist the installation of a heavy load (122), such as an auxiliary power unit (apu) in into a compartment of an aircraft (110) compartment (126). The elevator system includes bar assemblies which rotate to lift the load into the compartment. ... Airbus Operations Gmbh

06/14/18 / #20180162680

Method and machine for producing bindings

The method for producing bindings includes: positioning at least one binding bobbin on a machine having: a winding bobbin including a device for supporting and a notch, an electric motor which is coupled to the winding bobbin; and at least one shaft capable of receiving a binding bobbin, supporting a free end of the binding of the binding bobbin on the winding bobbin, by the device for supporting; supplying electricity to the electric motor of the machine to drive the winding bobbin in rotation, so as to wind the binding of the binding bobbin over a plurality of turns around the winding bobbin; stopping the supply of electricity to the electric motor of the machine; and in the region of the notch of the winding bobbin, cutting the plurality of turns of bindings wound onto the winding bobbin.. . ... Airbus Operations Gmbh

06/14/18 / #20180162523

Aircraft autonomous pushback

The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. Under the aircraft's own power without a pushback tractor. ... Airbus Operations Gmbh

06/14/18 / #20180162514

Aircraft comprising a common structure for supporting a power plant and a landing gear element

An aircraft comprising at least one power plant linked to an airfoil by a power plant support structure comprising a primary structure housed in an aerodynamic fairing. The power plant is formed overhanging behind the airfoil, mostly or wholly above the upper surface of the airfoil. ... Airbus Operations Gmbh

06/07/18 / #20180159449

Actuating apparatus for a motor and method for actuating a motor

A motor actuating apparatus includes three phase connections for three motor phase connections, a high-connection for a supply voltage and a low-connection for a reference potential of the supply voltage, three bridge branches having a series connection of a high-switch and a low-switch and a control device for actuating the switches of the bridge branches. The high-switches are connected to the high-connection and the low-switches are connected to the low-connection. ... Airbus Operations Gmbh

06/07/18 / #20180156912

Method for controlling transmission power and aircraft anti-collision system for implementing such a method

A method and system for controlling the transmission of power of request-response messages implemented by a system to prevent collisions between a first aircraft and a second aircraft. The method comprises measuring at least the value, referred to as the quality value, of a quantity representative of the reception quality of the transponder of the second aircraft and, implemented by the anti-collision device of the first aircraft, and a control step to control the transmission power of the radio-frequency signals carrying the request-response messages according to the quality value or values contained in the response messages sent by the transponder.. ... Airbus Operations Gmbh

06/07/18 / #20180156696

Actuator testing

An apparatus for in-situ testing of a linear actuator configured to exert an actuation force in an actuation direction by movement of a first part of the actuator relative to a second part of the actuator. The apparatus includes a test device, a test actuator and a measurement device. ... Airbus Operations Gmbh

06/07/18 / #20180155055

Structural composite component and method for configuring a structural composite component

A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.. ... Airbus Operations Gmbh

06/07/18 / #20180155013

Aircraft airflow modification device and vortex generator arrangement for an aircraft

An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.. ... Airbus Operations Gmbh

06/07/18 / #20180155012

Method for producing a smooth aerodynamic surface of an aircraft component

A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.. ... Airbus Operations Gmbh

06/07/18 / #20180155006

Aircraft stabilizer leading edge integration with torsion box and fuselage

An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).. ... Airbus Operations Gmbh

06/07/18 / #20180155004

Aerofoil structure components

A component for an aerofoil structure including a unitary member having a spar; a cover panel; and a substantially flat intermediate section which connects the spar to the cover panel. The spar, the cover panel and the intermediate section are integrally formed such that a first angle between the intermediate section and the cover panel and a second angle between the intermediate section and the spar are both in the range 90° to 180°.. ... Airbus Operations Gmbh

05/31/18 / #20180152013

Connection box for a system of an aircraft

A connection box for a system of an aircraft is provided, which includes a plurality of connection boxes, with a holder for holding a line connector for the supply of the system of the aircraft, wherein the system includes, in addition to this connection box, a further connection box with a holder for holding a line connector for the supply of the system of the aircraft. The connection box is configured to receive the further connection box in such a way that both connection boxes can be mounted under an opening in the floor of the aircraft so that both connection boxes are accessible from the opposite side of the floor through the opening in the floor.. ... Airbus Operations Gmbh

05/31/18 / #20180149524

System for protecting a thermocouple

A system for protecting a thermocouple placed in an environment comprising at least one radiative element, comprising a plate positioned between the thermocouple and the radiative element. The plate has an overall surface condition of an internal face facing towards the thermocouple such that the internal face absorbs radiation coming from the radiative element more than the internal face reflects the radiation.. ... Airbus Operations Gmbh

05/31/18 / #20180149498

Fibre-optic communication system, a communication apparatus for the same, and a vehicle

A communication apparatus for a fibre-optic communication system for an aircraft that includes: an optical coupler; an input port optically coupled to the optical coupler via a first waveguide, the input port arranged to receive light; a modulator optically coupled to the optical coupler via a second waveguide, the modulator having a logic input and a fibre having a fibre bragg grating (fbg) receiving light from the input port via the optical coupler, the modulator operable to vary a strain force applied to the fibre according to a logic signal received at the logic input to modulate a wavelength of a modulated light signal reflected by the fbg back to the optical coupler; and an output port optically coupled to the optical coupler via a third waveguide to receive the modulated light signal therefrom, the output port being operable to output the modulated light signal.. . ... Airbus Operations Gmbh

05/31/18 / #20180149178

Actuators for flow control at surfaces of aerodynamic profiles

An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.. . ... Airbus Operations Gmbh

05/31/18 / #20180148186

Assembly for an aircraft comprising an engine of the "open rotor puller" type and means for attaching the latter to the rigid structure of an attachment pylon

To allow the attachment of an engine of the “open rotor puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.. ... Airbus Operations Gmbh

05/31/18 / #20180148184

Aircraft air conditioning system that is operable assisted by cabin exhaust air with a pneumatically powered ambient air compressor

An aircraft air conditioning system includes an ambient air line connected to an aircraft air conditioning system mixer to supply ambient air, and a cabin exhaust air line connectable to an aircraft cabin, and a bleed air line drawn off from an engine or auxiliary power unit. An ambient air compressor in the ambient air line compresses ambient air. ... Airbus Operations Gmbh

05/31/18 / #20180148183

Aircraft air conditioning system that is operable assisted by cabin exhaust air with an electrically powered ambient air compressor

An aircraft air conditioning system includes an ambient air line connected to an air conditioning system mixer to supply ambient air, and a cabin exhaust air line connectable to an aircraft cabin for being flown through with cabin exhaust air. An ambient air compressor in the ambient air line compresses ambient air in the ambient air line. ... Airbus Operations Gmbh

05/31/18 / #20180148178

Flight attendant seat and method for fitting a flight attendant seat

A flight attendant seat comprising a frame that can be mounted on a carrier fixture or integrated into the carrier fixture, and at least one seat arrangement integrated into the frame. The frame comprises a lower section, an upper section and a central section taking up the at least one seat arrangement, at least partially. ... Airbus Operations Gmbh

05/31/18 / #20180148171

Construction group for an aircraft for feeding a line to a cabin module

A construction group of an aircraft for feeding a line to a connector section of the cabin module includes a flex zone for providing of at least one cabin module having a connector section for physical connection to a line of the aircraft. The flex zone is configured to receive different cabin modules and/or a cabin module at different positions. ... Airbus Operations Gmbh

05/31/18 / #20180148164

Lifting surface of an aircraft for increasing the generated lift force

A lifting surface of an aircraft, comprising a leading edge and a notch located in the leading edge. The notch comprises two walls adapted to be parallel to the direction of the incident flow to the lifting surface and a third wall adapted to face the incident flow to the lifting surface when it is in flight. ... Airbus Operations Gmbh

05/31/18 / #20180148162

Aircraft having a drag compensation device based on a boundary layer ingesting fan

An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.. . ... Airbus Operations Gmbh

05/31/18 / #20180148155

Aircraft assembly comprising a self-stiffened panel assembled with a structural element by means of an alternation of terminal ribs and terminal tabs

In order to allow robust assembly between a structural element and a self-stiffened panel comprising a skin and a stiffening structure formed of a network of ribs extending out from a first face of the skin, the structural element comprises at least one end formed of terminal tabs separated by cut-outs delimited by the terminal tabs and applied to the first face of the skin at an end part of the skin. In addition, the stiffening structure comprises at least one end formed of several terminal ribs extending respectively through the cut-outs. ... Airbus Operations Gmbh

05/31/18 / #20180148154

Aircraft composite panel assembly and manufacturing method thereof

An aircraft composite panel assembly includes a first panel having upper and lower faces, the lower face having a recess on a first side of the panel, a second panel having upper and lower faces, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge overlapping the first side of the first panel, and the number of plies of the forward stack of plies decreasing toward the opposite side of the first side of the first panel.. . ... Airbus Operations Gmbh

05/31/18 / #20180148152

Aircraft assembly comprising a self-stiffened panel comprising a portion of increasing height by means of which the panel is fixed to a structural element

In order to allow robust assembly in an aircraft between a structural element and a self-stiffened panel comprising a skin and a stiffening structure formed of a network of ribs extending out from a first face of the skin, the structural element comprises at least one end formed of a first closure rib, the stiffening structure comprises at least one end formed of a second closure rib, and a portion the height of which increases progressively as far as the second closure rib, and the structural element being fixed to the self-stiffened panel via first through-fixing elements which fix the first closure rib to the second closure rib. The structural element comprises a sole exhibiting a second face having an inset delimiting a space which accepts an end part of the skin.. ... Airbus Operations Gmbh

05/24/18 / #20180145751

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

05/24/18 / #20180142623

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

05/24/18 / #20180141665

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

05/24/18 / #20180141637

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

05/24/18 / #20180141635

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

05/24/18 / #20180141288

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

05/24/18 / #20180141242

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

05/17/18 / #20180135772

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

05/17/18 / #20180135760

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

05/17/18 / #20180135735

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

05/17/18 / #20180134406

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

05/17/18 / #20180134394

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

05/17/18 / #20180134392

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

05/17/18 / #20180134391

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








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