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Airbus Operations Sas patents


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

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


Terrain avoidance device and method for an aircraft

In an aircraft comprising a terrain warning device monitoring the flight of the aircraft with respect to the surrounding terrain and a terrain sensor, the terrain avoidance device is linked to the terrain warning device, to the terrain sensor and to a terrain relief database. The terrain avoidance device comprises a processing unit configured to determine a valid terrain avoidance trajectory as a function at one and the same time of an item of information regarding current position of the aircraft, of terrain relief information arising from the database and of terrain relief information provided by the terrain sensor when the terrain avoidance device receives a warning signal from the terrain warning device.. ... Airbus Operations Sas

Flexible seal for an aircraft

A flexible seal intended to be fixed between a fixed part and a mobile part of an aircraft, the seal comprising an elongate hollow body, a shoe secured to the hollow body, intended to be fixed to the fixed part, a blade secured to the hollow body and designed to extend from the hollow body towards the mobile part, the blade having a leak edge having a non-linear edge, such as with notches or chevrons. The provision of a notched leak edge reduces a pressure differential on either side of the blade, and by allowing the air to pass between the blade and the fixed part just before the contact with the fixed part, the lifting of the blade is prevented.. ... Airbus Operations Sas

Process and system for fastening a functional flexible element to a flexible support by zigzag stitching

A process for attaching a functional flexible element on a flexible support without the use of adhesive composition. The process comprises a step of depositing a functional flexible element on a flexible support, a step of stitching along a zigzag line of at least one binding yarn on either side of the functional flexible element along the functional flexible element while retaining the functional flexible element on the flexible support. ... Airbus Operations Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

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 Sas

04/05/18 / #20180094761

Fluidic piping system for aircraft and method for repairing same

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

03/29/18 / #20180087707

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

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

03/22/18 / #20180079402

Brake wear reduction apparatus

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

03/15/18 / #20180074515

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

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

03/01/18 / #20180056494

Punching tool equipped with a guide sleeve

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

01/25/18 / #20180024237

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

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

01/25/18 / #20180022442

System for actuating a control surface of an aircraft

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

01/18/18 / #20180015998

Crocodile-type flight control surface for aircraft

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

01/11/18 / #20180009543

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

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

01/11/18 / #20180009533

Method of automatic positioning of a seat

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

12/28/17 / #20170372626

Method and system for aiding the ground rolling of an aircraft

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

12/21/17 / #20170363514

Method for monitoring the engines of an aircraft

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

12/21/17 / #20170363482

Aircraft brake temperature measurement

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

12/21/17 / #20170361939

Assembly for aircraft comprising engines with boundary layer propulsion by injection

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

12/14/17 / #20170358108

Display system and method for an aircraft

A display system for an aircraft cockpit comprises a display device configured to be secured to a user's head, a sensor to determine an orientation of the user's head, and a display computer. The computer is configured to control the display of information relating to the flight of the aircraft on the display device, to acquire information on the user's head orientation, to determine an angular offset value between a direction corresponding to the head orientation and a longitudinal axis of the aircraft, to evaluate at least one condition as a function of the angular offset value, and to control the display device display in accordance with a first display mode when the condition is verified, this first display mode corresponding to a display comprising at least one aircraft piloting assistance symbol displayed in a conforming manner, and another display mode when the condition is not verified.. ... Airbus Operations Sas

12/14/17 / #20170356757

Method and device for verifying a guidance signal

A verification method comprising a first step of measuring at least one position parameter of an aircraft and a first set of steps implemented after the flight of at least one aircraft, in an automatic and repetitive manner, comprising computing a geographical height of an aircraft with respect to the runway on the basis of the position parameters of an aircraft, computing an evaluated vertical deviation, between the geographical height and a reference height, and computing a vertical error on the basis of a comparison between the evaluated vertical deviation and the reference vertical deviation.. . ... Airbus Operations Sas

12/14/17 / #20170355472

Method for adjusting the position of elements of a structure of an aircraft, and device for implementing same

A device for adjusting the position of structural elements of a structure of an aircraft, comprising a measurement tool for determining a value for the actual position of each structural element, a processing and calculation system for comparing each value of the actual position determined by the analysis system with a corresponding theoretical value, and for determining therefrom an adjustment value, an adjustment tool configured to be attached in use to a structural element, comprising at least one measurement sensor configured to measure a distance between the measurement sensor and the structural element, a calculator for comparing the value measured by the measurement sensor with the corresponding adjustment value, and for deriving therefrom corrective actions to finalize adjustment of the structural element, and a communication system for exchanging information between the adjustment tool and the processing and calculation system.. . ... Airbus Operations Sas

12/07/17 / #20170351269

Method for optimizing the take-off parameters of an aircraft

A method for optimizing the take-off parameters of an aircraft. The aircraft comprises a system for automatically controlling the high lift devices at the moment when the wheels of the aircraft leave the ground. ... Airbus Operations Sas

11/23/17 / #20170336453

On-board system for evaluating the severity of a lightning strike

An on-board system for evaluating the severity of a lightning strike, intended to be installed in the interior of an airplane and connected to an avionic system of the airplane. The system comprises four devices, a master device and three slave devices, each device comprising a magnetic-field sensor. ... Airbus Operations Sas

11/23/17 / #20170332975

System and method for evaluating action capacities of an individual

A system for evaluating the action capacities of an individual comprising at least one measurement module, each measurement module being configured to produce at least one measurement point of a physiological parameter of the individual; a computation module configured to determine at least one set of measurement points representative of a distribution law for the measurement point or points, termed measured set; a computation module configured to compute at least one conditional probability of having one or more states of health; a third computation module configured to compute an average of the computed conditional probability or probabilities; a fourth computation module configured to determine at least one level of action capacity of the individual; a transmission module configured to transmit a signal representative of the level or levels of action capacity of the individual to a user device.. . ... Airbus Operations Sas

10/12/17 / #20170295145

Ground unit, aircraft and method for transmitting flight instructions from a ground unit to an aircraft

The transmission of flight instructions from a ground unit to an aircraft comprising an onboard system. The ground unit is configured to generate, on the basis of flight data intended for the aircraft, at least one optical symbol containing a flight instruction. ... Airbus Operations Sas

09/21/17 / #20170270804

Center for assisting the flight management of a plurality of aircraft

A center to assist flight management of a plurality of an entity's aircraft comprising a control unit and at least two stations and communication equipment configured to receive data signals and to transmit/receive audio signals to/from each aircraft. The control unit comprises a man-machine interface connected to a central unit, the central unit being connected to a computation unit of each station and to the communication equipment to receive data signals and to transmit/receive audio signals to/from the equipment. ... Airbus Operations Sas

09/07/17 / #20170257160

Communication system and method for the transmission of audio data signals from an aircraft cockpit to a ground station

A communication system installed in an aircraft, the system comprising a transmitter configured to transmit audio data signals to a ground recording station provided with memories for the recording of the data, at least one audio assembly per pilot of the aircraft for transmitting and receiving audio data signals, a cvr recorder and an audio management unit connected to each audio assembly, to the cvr recorder and to the transmitter, the unit being configured to transfer the audio signals received or transmitted by an audio assembly to the transmitter and to the cvr recorder. Each audio assembly comprises an in-use detection system connected to the transmitter and configured to transmit to the transmitter a signal representative of the in-use state of the audio assembly. ... Airbus Operations Sas

08/31/17 / #20170247121

Unknown

A tooling making it possible to mount a module directly in an aircraft without making any modifications to the module. This tooling is made up of upper beams connected to the structure of the aircraft, lower beams secured to the module, lift elements connecting the lower beams to the upper beams and a drive system. ... Airbus Operations Sas

08/31/17 / #20170247101

Unified floor and aircraft nose including such a floor, and method for incorporating such a nose

An aircraft nose floor comprising a grid structure formed by an interlacing of crosspieces and longitudinal elements. The crosspieces are parallel to one another and the longitudinal elements are parallel to one another and fastened to the crosspieces. ... Airbus Operations Sas

08/31/17 / #20170247100

Doors for an easy access to the pressurized housing of a flying wing, from the trailing edge

An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is outside a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall. ... Airbus Operations Sas

08/24/17 / #20170240288

Aircraft engine assembly, comprising an engine attachment device equipped with structural movable cowls connected to the central box

In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.. ... Airbus Operations Sas

08/10/17 / #20170228037

Control device of a communication system of an aircraft

The control device of a communication system of an aircraft having a predefined number of communication channels comprises a processing unit and sets of buttons each associated with a communication channel and comprising a button for setting sound volume, a reception button and a transmission button. The number of sets of buttons is at least equal to two and less than the predefined number of communication channels of the communication system. ... Airbus Operations Sas

08/10/17 / #20170225786

Control device of a communication system of an aircraft

The control device of a communication system of an aircraft having a predefined number of communication channels comprises a processing unit and one or more sets of buttons each associated with a communication channel. The number of sets of buttons is less than the predefined number of communication channels of the communication system. ... Airbus Operations Sas

06/29/17 / #20170183077

Aircraft cell comprising a door opening in rectilinear translation

In order to simplify the connection of a door to the outer envelope of an aircraft cell, it is provided to dispose the door into a portion of the outer envelope having tilted sides, as is the case at the nose cones and the tail cones of conventional airplanes, and in various portions of blended wing body airplanes and flying wings. Thus, the door can be configured to displace, in rectilinear translation, from one of its extreme opening and closing positions to the other, without requiring that the door protrudes outside of the outer envelope in the closing position.. ... Airbus Operations Sas

06/15/17 / #20170167437

Jet engines and their arrangement in the rear section of an aircraft

A jet engine comprises at least three zones including an air intake zone and an exhaust zone. The axis of the air intake zone is not coincident with the axis of the exhaust zone of the engine, the engine as a result, having at least two intersecting axes and being referred to as a multiaxial engine. ... Airbus Operations Sas

06/15/17 / #20170166317

Support pylon for a turbomachine, provided with a thermal protection element

A support pylon for an aircraft turbomachine having the overall shape of a box defined by lateral walls, at least one of the lateral walls having an external surface comprising a thermal protection element, the element being mobile as a result of a rise in temperature between a first, retracted position, in which the element is aligned with the external surface and a second, deployed position, in which the element protrudes from the external surface. The element provides thermal protection which is able to be automatically deployed-retracted in order to protect the parts of the pylon against thermal heating. ... Airbus Operations Sas

06/15/17 / #20170166296

Curvilinear rudder bar for an aircraft and aircraft comprising such a curvilinear rudder bar

The rudder bar includes two actuation arrangements, each provided with two pedals, each actuation arrangement having a frame provided with two rails arranged on either side of said frame and being in the form of a concave curve, and, associated with each one of said rails, a movable carriage, each one of said movable carriages bearing one of said pedals, each one of said movable carriages being configured such that it can be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said pedals.. . ... Airbus Operations Sas

06/15/17 / #20170166293

Windshield with support rod

An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. ... Airbus Operations Sas

06/15/17 / #20170166291

System for holding a forward pressure bulkhead via non-parallel rods attached to the floor

A zone provided between the forward pressure bulkhead in an aircraft and the floor. The nose section of the aircraft in which the flat surface pressure bulkhead including at least one transverse frame comprises at least two rods, of which one of the front ends is attached to the bulkhead and/or the frame and the other rear end is attached to a structural element, the two rods further apart from the front to the rear, thus providing a work space. ... Airbus Operations Sas

06/08/17 / #20170162066

Method and system for aiding landing of an aircraft

A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented automatically by a processing unit: a) acquiring information relating to the runway; b) acquiring information relating to a current situation of the aircraft; i) determining a landing position of the aircraft on a central longitudinal axis of the runway, as a function of a trajectory determined between a current position of the aircraft and this landing position to comply with at least one constraint relating to a roll angle of the aircraft; j) determining a parameter relating to the landing position; k) determining a deviation between this parameter and a reference value; l) comparing this deviation with a predetermined threshold; and m) as a function of the result of the comparison carried out in step l), commanding, if appropriate, the signaling of an alert via the signaling system of the aircraft.. . ... Airbus Operations Sas

06/08/17 / #20170162065

Method and system for aiding landing of an aircraft

A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; c) determining, as a function of said information, at least one deviation between at least one parameter relating to a landing position of the aircraft on the landing runway and a reference relating to a central longitudinal axis of the landing runway; d) comparing this deviation with a predetermined threshold; and e) as a function of the result of the comparison carried out in step d), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.. . ... Airbus Operations Sas

06/08/17 / #20170158349

Method and system for aiding landing of an aircraft

A method for aiding the landing of an aircraft on a landing runway comprising the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position and a target landing position on the landing runway; g) comparing this maximum roll angle with a predetermined limit; and h) as a function of the result of the comparison carried out in step g), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.. . ... Airbus Operations Sas

06/01/17 / #20170152052

Aircraft engine assembly comprising rear engine attachments in the form of shackles

An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.. . ... Airbus Operations Sas

05/11/17 / #20170132942

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

A method and device for generating an optimum vertical path intended to be followed by an aircraft. The device comprises at least one database relating to fixed and moving obstacles, a data entering unit, a data processing unit implementing iterative processing to generate an optimum vertical path between an initial state and a final state as a function of flight strategies, that optimum vertical path being generated in such a manner as to be free of any collision with surrounding obstacles and to conform to energy constraints, and a data transmission link for transmitting that optimum vertical path to at least one user system.. ... Airbus Operations Sas

05/11/17 / #20170129140

Forming tool of a preform in composite material and method of manufacturing a part in composite material using said tool

A forming tool of a preform made of composite material, the tool comprising at least one flexible element and at least a first and a second rigid plate connected to the flexible element and disposed on either side of the flexible element. The first and second rigid plates and the flexible element comprise first, second and third reference surfaces, respectively. ... Airbus Operations Sas

04/27/17 / #20170113425

Method for repairing an aircraft structure using deformable sheets

A method for repairing an aircraft structure made of composite material which comprises a damaged zone having at least one bend. The method comprises the stacking of at least two sheets of composite material, which each have a thickness allowing manual deformation thereof, a first sheet being applied to the damaged zone and shaped manually so as to follow said at least one bend of the zone, a second sheet being applied to the first sheet and shaped manually so as to follow the shape of the first sheet thus shaped. ... Airbus Operations Sas

04/20/17 / #20170109946

Method and device for detecting oscillatory failures in an automatic position control chain of an aircraft control surface

A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.. . ... Airbus Operations Sas

04/20/17 / #20170108145

Support for a conduit

A support for a pipe which comprises a body which comprises a through-orifice for the pipe. The through-orifice has a diameter which is greater than an external diameter of the pipe. ... Airbus Operations Sas

04/13/17 / #20170101195

Method for predicting temperatures which are tolerable by a component, a piece of equipment or an airplane structure

A method for predicting temperatures tolerable by a component, a piece of equipment or a vehicle structure. This method includes the steps of determining, for each piece of equipment, component or structure of the vehicle, such as an airplane, a temperature spectrum depending on a plurality of extrinsic parameters measured during a full operating cycle of the airplane, by taking into account, for each piece of equipment, component or structure, possible combinations of the extrinsic parameters and setting aside unlikely combinations of the extrinsic parameters, determining, for each piece of equipment, component or structure, the probability of occurrence of the spectrum during the full airplane operating cycle, and defining a database including the temperature spectra so as to predict the lifetimes of the piece of equipment, component or structure and redefine weather and operational standards indicating extreme temperatures and their probability of occurrence obtained with the measured extrinsic parameters.. ... Airbus Operations Sas

04/06/17 / #20170096238

Aircraft propulsion system having at least one anti-fire tank

A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. ... Airbus Operations Sas

04/06/17 / #20170096230

Compartmentalized structure for the acoustic treatment and the de-icing of an aircraft nacelle and aircraft nacelle incorporating said structure

An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.. ... Airbus Operations Sas

03/30/17 / #20170092391

Method for mounting a sheath on a wire harness and a set comprising a sheath and a wire harness

The method for fitting a sheath on a cable harness includes a series of steps including determining the length of sheath to be used, mounting the sheath on a mounting tool of tubular shape, inserting the cable harness into the mounting tool, removing the mounting tool and arranging the sheath around the cable harness, fitting a sheath stop at one of the ends of the sheath, the sheath stop fastening the end of the sheath to the cable harness stretching the sheath over the cable harness so as to extend it and tension it, and fitting a sheath stop at the other one of the ends of the sheath.. . ... Airbus Operations Sas

03/09/17 / #20170070507

High assurance segregated gateway interconnecting different domains

A gateway having an architecture authorizing bidirectional communication between applications located in different domains and presenting a high assurance level of protection. The gateway interconnects a first and second domain. ... Airbus Operations Sas

03/02/17 / #20170057656

Aircraft attitude indicator device

An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artefact. ... Airbus Operations Sas

03/02/17 / #20170057652

Aircraft engine unit comprising an improved front engine attachment

An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.. ... Airbus Operations Sas

02/09/17 / #20170040764

Interface device for the connection and the passage of an electric route through an airtight wall of an aircraft

An interface device that includes a plastic part including at least one through-opening in a longitudinal direction, the plastic part being adapted to be fixed in an airtight manner into an opening in the wall. At least one metal shaft is arranged and fixed in the through-opening. ... Airbus Operations Sas

02/02/17 / #20170028655

Method for repairing a composite-material panel of an aircraft and tool for implementing said method

A method and a tool for repairing a composite-material panel of an aircraft with at least one repair part made of composite material without using an autoclave. The repair method includes the steps of preparing the panel, placing at least one repair part made of composite material on the second face to cover a damaged zone, positioning a vacuum bag configured to sealingly cover the repair part, polymerizing or consolidating the repair part, compressing the vacuum bag against the repair part using a compression plate concomitantly with the step in which the repair part is polymerized or consolidated.. ... Airbus Operations Sas

01/26/17 / #20170021919

Rear door of a landing gear box comprising an air passage orifice and a closure member of the latter

A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.. . ... Airbus Operations Sas

01/19/17 / #20170015410

Methods and control systems for controlling a drive system of an aircraft

A method of controlling a drive system of an aircraft. The drive system comprised a drive motor arranged to drive at least one wheel of an aircraft landing gear. ... Airbus Operations Sas

01/12/17 / #20170011568

Data processing unit for aircraft undercarriage performance monitoring

A data processing unit for monitoring the performance of at least one undercarriage which is used for braking and/or steering an aircraft, wherein the data processing unit is configured to: receive data representative of operating characteristics of the undercarriage(s) and use that data to calculate a maximum achievable braking force and/or yaw moment to be generated by the undercarriage(s). Also a method for monitoring the performance of at least one aircraft undercarriage which is used for braking and/or steering an aircraft, the method including: receiving data representative of operating characteristics of the undercarriage(s); and using that data to calculate a maximum achievable braking force and/or yaw moment to be generated by the undercarriage(s).. ... Airbus Operations Sas

01/12/17 / #20170008619

Aircraft steering system controller

A controller for an aircraft steering system, the controller being configured to receive a steering input representative of a desired direction of travel of a steerable nose landing gear, and to receive one or more force-based inputs representative of lateral forces acting upon the nose landing gear, wherein the controller is adapted to automatically adjust the steering input based upon the force-based input(s) so as to output an adjusted steering command for a steering actuator of the nose landing gear.. . ... Airbus Operations Sas

01/12/17 / #20170008503

Braking control system for an aircraft

A braking control system for an aircraft having braking wheels, the braking control system being configured to receive input of signals from sensors representative of a plurality of measured aircraft parameters, and to output a plurality of brake commands to brakes associated with the braking wheels, wherein the braking control system includes a health monitoring system for determining the operability and/or reliability of the sensor signals and/or of the braking wheels, and a task manager for automatically self-reconfiguring the braking control system so as to change the manner in which the braking control system utilises the input signals in the event that the health monitoring system judges a failure of one or more of the braking wheels or sensor signals. Also a method for operating an aircraft having a plurality of braking wheels.. ... Airbus Operations Sas

01/05/17 / #20170004715

Systems and methods for providing optimized taxiing path operation for an aircraft

A taxiing path optimization system is provided for computing a taxi path of an aircraft using available taxi routes of a corresponding airport. An interaction means management unit manages interactions between a user and the taxiing path optimization system using an interactive device for inputting a taxi clearance. ... Airbus Operations Sas

01/05/17 / #20170001583

System for electrically connecting cabin equipment of an aircraft to a control system and to at least one electrical power supply source of the aircraft

A system for electrically connecting a piece of cabin equipment of an aircraft to a control system and to at least one electrical power supply source of the aircraft. The connection system comprises a host interface module to which the control system and the at least one electrical power supply source are connected. ... Airbus Operations Sas








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