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Airbus Helicopters patents


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

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


Seat bench device with a seat bench component and at least one restraining unit

A seat bench device with a seat bench component and at least one restraining unit. The seat bench component comprising a seating surface and a backrest, and the at least one restraining unit comprising a harness for restraining a seat bench occupant on the seat bench component, wherein at least two guide elements are provided and wherein the at least one restraining unit is movably arranged on the at least two guide elements for being movable on the at least two guide elements along the backrest at least between a storage position and an operating position, in which the harness is operational for buckling up of a seat bench occupant.. ... Airbus Helicopters

Gearbox casing, a gearbox, and an aircraft

An upper casing with a hollow shell made of composite materials. The shell was a side wall that extends in elevation from a housing flange to a housing collar, the side wall including at least one cutout. ... Airbus Helicopters

Device for regulating the speed of rotation of a gas generator shaft of a rotorcraft turboshaft engine, a rotorcraft provided with such a device, and an associated method of regulation

A regulator device for regulating a speed of rotation, of a shaft of a gas generator of at least one turboshaft engine of a rotorcraft. The rotorcraft has at least one main rotor for regulating at least lift and/or propulsion for said rotorcraft in the air; a control member for controlling a collective pitch of the blades of said at least one main rotor, said control member serving to generate a control setpoint for said collective pitch; at least one turboshaft engine suitable for driving rotation of said at least one main rotor, said at least one engine producing, at least temporarily, a drive torque that is transmitted to said at least one main rotor; and measurement means for taking at each instant a measurement of said drive torque transmitted by said at least one engine to said at least one main rotor.. ... Airbus Helicopters

Method of analyzing variations of at least one indicator of the behavior of a mechanism fitted to an aircraft

A method of analyzing variations of an indicator of the behavior of a mechanism fitted to an aircraft, the indicator being determined from measurements of a physical operating parameter of the mechanism during a mission of the aircraft. The method includes a storage step of storing the measurements of the physical operating parameter in a storage unit; a first transmission step of transmitting the measurements of the physical operating parameter contained in the storage unit to a communication station; a second transmission step of transmitting the measurements of the physical operating parameter from the communication station to an analysis center; an indicator generation step of generating the indicator performed on the basis of the measurements of the physical operating parameter; and an analysis step of analyzing variations of the indicator.. ... Airbus Helicopters

Flight control method for rotorcraft, and a rotorcraft

A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. ... Airbus Helicopters

Aircraft with an airframe that comprises a load carrying framework

An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. ... Airbus Helicopters

Aircraft with an airframe and at least one electrically powered thrust producing unit

An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.. . ... Airbus Helicopters

A combustion engine, an aircraft fitted with said engine, and a method of fabricating such an engine

The present invention relates to a combustion engine which includes at least one crankshaft rotating about a first rotation shaft; at least one output shaft outputting an engine torque, said output shaft rotating about a second rotation shaft separate from said first rotation shaft; at least one transmission assembly rotating about said first rotation shaft and being rotated by said crankshaft in order to transmit said engine torque to said output shaft.. . ... Airbus Helicopters

Control member, a rotary wing aircraft, and a method

A control member that is operable by a pilot to vary thrust from a thrust system of an aircraft. The control member comprises a stick and a movable assembly including a grip. ... Airbus Helicopters

Rotary wing aircraft with a sliding element, in particular a sliding door or a sliding window

A rotary wing aircraft with a fuselage that is equipped with at least one rail, comprising at least one sliding element, in particular a sliding door or a sliding window, that is slidably supported by the at least one rail, wherein the at least one sliding element is at least slidable along the at least one rail by means of an opening sliding movement into an opening movement direction from a fully closed position into a fully opened position, wherein a dampening unit is provided that dampens the opening sliding movement of the at least one sliding element upon reaching of the fully opened position.. . ... Airbus Helicopters

Actuatable emergency exit door and an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door

An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.. ... Airbus Helicopters

Method of fabricating a spar for a blade, a method of fabricating a blade, and a blade

A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. ... Airbus Helicopters

Estimating the speed and the heading of an aircraft, independently of a magnetic measurement

A device for estimating an aircraft's speed relative to the ground and heading, while making no use of the rotation of the earth or of the earth's magnetic field. The device comprises in particular a first linear estimator that hybridizes a measurement of the speed of the aircraft relative to the ground as provided by a gnss receiver with measurements of the acceleration and the attitudes of the aircraft coming from an ahrs device without a gyrocompass and without a magnetometer. ... Airbus Helicopters

Internal combustion engine having at least one crankcase of the dry-sump type

An internal combustion engine having at least one crankcase for defining a guide housing in which at least one crankshaft is guided in rotation about an axis of rotation and lubricated by a lubricating fluid, the at least one crankcase being of the “dry-sump” type. Such an internal combustion engine has at least two pumps forming a pump train of pumps on a common axis, the pump train being fitted in a cylindrical bore of the at least one crankcase.. ... Airbus Helicopters

04/19/18 / #20180106074

Aircraft with a plurality of aircraft doors

An aircraft with a plurality of aircraft doors, each aircraft door comprising at least one lock lever that is provided for engaging a counterpart in an engaged state for locking a respective aircraft door relative to the aircraft, wherein a real-time monitoring device is provided for generating a real-time representation of the at least one lock lever and the counterpart, the real-time representation being suitable for determining whether the at least one lock lever is in the engaged state.. . ... Airbus Helicopters

04/19/18 / #20180105265

Lead-lag damper integrated inside a blade of a rotor

A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper (comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged between the two strength members. ... Airbus Helicopters

04/12/18 / #20180099739

Electric control member, a rotary wing aircraft, and a method

An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. ... Airbus Helicopters

04/12/18 / #20180099406

Device for three-dimensionally positioning a coupling component and actuator system

The invention pertains to a device for 3-dimensionally positioning a coupling component, which forms part of an actuator-driven coupling structure, wherein said device comprises at least a first coupling element that extends in a first longitudinal direction and can be bidirectionally displaced along its first longitudinal direction by means of a first actuator, a second coupling element that extends in a second longitudinal direction and can be bidirectionally displaced along its second longitudinal direction, which extends orthogonal to the first longitudinal direction, by means of a second actuator, and a lever with a longitudinal lever direction that is mounted pivotably about a pivoting axis, which divides the lever into a work arm and a power arm. The longitudinal lever direction of the lever either extends along the first longitudinal direction and its work arm is on its end fixed on the second coupling element such that it can be pivoted about the second longitudinal direction or the longitudinal lever direction of the lever extends along the second longitudinal direction and its work arm is on its end fixed on the first coupling element such that it can be pivoted about the first longitudinal direction. ... Airbus Helicopters

04/05/18 / #20180093757

Aircraft control device, a corresponding aircraft, and a method of controlling an aircraft

A control device for controlling an aircraft, the control device including at least one motor-driven trim actuator with active type anchoring, the trim actuator including at least one electric motor, at least one electronic power circuit for electrically powering the electric motor(s), and speed reduction means for driving rotation of an outlet shaft of the trim actuator. The control device implements three distinct servo-control loops that are nested in one another, these three servo-control loops being formed by an electric current servo-control loop, a speed servo-control loop, and a force servo-control loop.. ... Airbus Helicopters

03/29/18 / #20180086482

External anchoring harpoon for aircraft

An external anchoring harpoon for an aircraft in order to anchor the aircraft on an anchor grid of a platform, the external anchoring harpoon comprises a frame connected to the aircraft, a harpoon head, and a deployment device for deploying the harpoon head. The deployment device comprises a cable, a movement device for moving the cable connected to the frame, the cable being connected to the harpoon head and to the movement device. ... Airbus Helicopters

03/29/18 / #20180085782

Rotary wing aircraft with a structural arrangement that comprises an electrically conductive connection

A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.. . ... Airbus Helicopters

03/15/18 / #20180072412

Adjustment of track and balance of a multi-blade rotor

A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever, wherein the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.. . ... Airbus Helicopters

03/15/18 / #20180072411

Method for automatic piloting of a rotary wing aircraft having at least one thruster propeller, associated automatic autopilot device, and aircraft

An autopilot device and method for automatically piloting a rotary wing aircraft, having at least one propulsion propeller, the rotary wing including at least one rotor with blades, the device including a processor co-operating with at least one collective control system for controlling the collective pitch of the blades. The device includes engagement means connected to the processor for engaging an assisted mode of piloting for maintaining an angle of attack, the processor automatically controlling the collective pitch of the blades when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling the collective control system to maintain an aerodynamic angle of attack (α) of the aircraft at a reference angle of attack (α*).. ... Airbus Helicopters

03/15/18 / #20180072407

Mechanical system for transmitting motion and an aircraft fitted with a corresponding system

A mechanical system for transmitting rotary motion between at least two shafts movable in rotation respectively about a first axis and a second axis, the first and second axes intersecting, the mechanical system including a bevel gear set made up of a first bevel gear having teeth and movable in rotation about the first axis and a bevel wheel having teeth and movable in rotation about the second axis, the teeth of the first bevel gear and of the bevel wheel respectively being suitable for co-operating in complementary manner with one another, the first bevel gear, referred to as a “power” gear, presenting a first defining pitch surface of conical shape, and the bevel wheel presenting a second defining pitch surface of conical shape.. . ... Airbus Helicopters

03/15/18 / #20180072406

Mechanical motion transmission system and an aircraft fitted with a corresponding system

A mechanical system for transmitting rotary motion between firstly at least one inlet wheel driven in rotation by at least one engine, each inlet wheel being suitable for being driven in rotation by a corresponding dedicated engine, and secondly at least two distinct driven shafts of an accessory box, the at least one engine serving to drive rotation of one of the at least two driven shafts in isolation, or to drive the at least two driven shafts simultaneously, jointly with at least one aircraft rotor, the mechanical system including a selective rotary drive member that is movable axially between two distinct drive positions.. . ... Airbus Helicopters

03/01/18 / #20180057183

Rotorcraft with cowling able to rotate and translate relative to the fuselage

A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling.. . ... Airbus Helicopters

03/01/18 / #20180057158

Rotorcraft having a rotary wing and an orientable propeller, and a method applied by the rotorcraft

A rotorcraft having a fuselage surmounted by a main rotor. The rotorcraft has a first propeller and a second propeller driven in rotation respectively about a first secondary axis of rotation and a second secondary axis of rotation. ... Airbus Helicopters

03/01/18 / #20180057156

Aircraft provided with a set of swashplates and with at least one servo-control that is inclined

An aircraft provided with a rotor that is provided with blades and a set of swashplates. The set of swashplates comprises both a rotary swashplate and also a non-rotary swashplate, a lower scissors linkage being hinged to the non-rotary swashplate and being hinged to a member that is stationary in rotation about the axis of rotation, the rotor comprising a plurality of servo-controls each provided with a top hinge hinged to a top attachment fitting of the non-rotary swashplate and with a bottom hinge hinged to a bottom attachment fitting that is stationary in a reference frame of the aircraft. ... Airbus Helicopters

03/01/18 / #20180057153

Aircraft with an emergency floatation system

An aircraft with an emergency flotation system, the emergency flotation system being activated upon an emergency landing of the aircraft on water, for preventing at least sinking of the aircraft, characterized in that a capsizing avoidance buoyancy system is provided, the capsizing avoidance buoyancy system being activated if predetermined activation criteria are satisfied and only after activation of the emergency flotation system upon an emergency landing of the aircraft on water, for preventing at least capsizing of the aircraft.. . ... Airbus Helicopters

02/22/18 / #20180052032

Immersion detector and an aircraft

An immersion detector having a thermoresistive detector with at least two temperature probes. The immersion device has a capacitive detector having a capacitor, a cap surrounding said temperature probes and the capacitor, said cap having orifices putting said temperature probes and the capacitor into fluid flow communication with an external medium (ext) surrounding said immersion detector.. ... Airbus Helicopters

02/15/18 / #20180044008

Control system for controlling at least collective pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft

A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.. . ... Airbus Helicopters

02/15/18 / #20180043982

Rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel

A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.. . ... Airbus Helicopters

02/01/18 / #20180030762

Load transfer interface for a vehicle door, in particular for an aircraft cabin door

A load transfer interface for a vehicle door that comprises an outer skin and at least one beam that is connected to the outer skin, wherein the outer skin and the at least one beam define a vehicle door plane, the load transfer interface comprising at least one door stop fitting that is provided to transfer pressure loads from the vehicle door to an associated vehicle structural frame, the at least one door stop fitting being provided for rotation in an associated rotation plane, wherein the associated rotation plane is at least approximately parallel to the vehicle door plane. The invention is further related to an aircraft cabin door having such a load transfer interface, as well as to an aircraft having such an aircraft cabin door.. ... Airbus Helicopters

02/01/18 / #20180029721

Electrical architecture with paired secondary electrical networks for starting engines of an aircraft

An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary dc electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. ... Airbus Helicopters

02/01/18 / #20180029702

Method of optimizing sections of a tail boom for a rotary wing aircraft

A method of optimizing sections of a tail boom for a rotary wing aircraft, and also to a tail boom including such sections. The method comprises the step of creating a database characterizing standard sections for a tail boom that give precedence to minimizing a negative lift and/or to increasing a lateral force generated by the air stream from the main rotor of the aircraft flowing over the tail boom, a step of establishing looked-for aerodynamic and structural characteristics for said tail boom, and a step of defining the sections of the tail boom as a function of the standard sections and of the looked-for aerodynamic and structural characteristics. ... Airbus Helicopters

01/25/18 / #20180022447

Resonator, and an aircraft provided with the resonator

A resonator provided with a heavy member comprising a casing fastened a spring blade. The heavy member comprises a set of masses that is movable in translation in said casing along a longitudinal direction. ... Airbus Helicopters

01/25/18 / #20180022433

Aircraft with a fuselage and a composite tail boom

An aircraft with a composite tail boom that comprises at least partly a tubular tail boom cone with an outer skin and an inner skin, wherein the inner skin delimits a hollow interior of the composite tail boom, wherein a plurality of rod-shaped stiffening elements and a plurality of ring-shaped stiffening elements are arranged between the outer skin and the inner skin, the plurality of rod-shaped stiffening elements being oriented in longitudinal direction of the composite tail boom and the plurality of ring-shaped stiffening elements being distributed along the longitudinal direction in the tubular tail boom cone.. . ... Airbus Helicopters

01/11/18 / #20180009546

Device for assisting the piloting of a rotorcraft, an associated display, and a corresponding method of assisting piloting

A device for assisting the piloting of a rotorcraft in order to pilot a rotorcraft during an approach stage preceding a stage of landing on a rotorcraft landing area. Such a device includes in particular a camera for taking a plurality of images of the environment of the rotorcraft along a line of sight, looking at least along a forward direction dx of the rotorcraft, and processor means for identifying in at least one image from among said plurality of images at least one looked-for landing area.. ... Airbus Helicopters

01/11/18 / #20180009534

Jumpseat, and a vehicle provided with the jumpseat

A jumpseat having a carrier structure comprising at least one seat pan. The jumpseat comprises a mounting structure provided with at least two arms having at least one degree of freedom to move in rotation about a stowage axis, said carrier structure being hinged to each arm by a pivot arrangement, said pivot arrangement being hinged to each arm about a folding axis, the folding and stowage axes being parallel to each other, said pivot arrangement giving the carrier structure at least one degree of freedom to move in rotation relative to the arms about an elevation axis.. ... Airbus Helicopters

01/04/18 / #20180002007

Duplicated hydraulic circuit with pressure regulation

. . The present invention relates to a device for supplying hydraulic power, the device comprising two hydraulic circuits jointly feeding multi-cylinder hydraulic power transmission means in which each cylinder is connected to a single one of the hydraulic circuits independently of the others. Each hydraulic circuit includes a hydraulic pressure and flow rate generator and a pressure control module controlling said hydraulic pressure and flow rate generator so as to regulate the pressure of said fluid flowing in said hydraulic circuit as a function of said pressure of said fluid flowing in each hydraulic circuit and possibly as a function of one or more parameters external to said device.. ... Airbus Helicopters

01/04/18 / #20180002006

Rotor and an aircraft provided with such a rotor

A rotor comprising a hub and a plurality of lift assemblies. Each lift assembly is connected to two adjacent lift assemblies respectively by a first damper and a second damper. ... Airbus Helicopters

12/28/17 / #20170369181

Detecting that a rotorcraft is approaching a vortex domain, and signaling that detection

A method and a device for detecting that a rotorcraft is approaching a vortex domain. After previously determining a limit advance speed threshold and a limit vertical speed threshold defining a limit for said rotorcraft entering into a vortex domain, a predictive advance speed and a predictive vertical speed for said rotorcraft are calculated, said predictive vertical speed being calculated differently depending on the value of said instantaneous advance speed. ... Airbus Helicopters

12/28/17 / #20170369159

Rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear

A rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear that is mounted to the fuselage, the non-retractable skid-type landing gear comprising at least one landing box, the at least one landing box being provided with a skid-type landing base member and an associated box shell that delimits an internal volume of the at least one landing box.. . ... Airbus Helicopters

12/07/17 / #20170349271

Resonator, and an aircraft fitted with the resonator

A resonator having a support and a seismic mass. Movement means include a first electromagnetic assembly comprising a first electric coil that is not electrically powered. ... Airbus Helicopters

11/30/17 / #20170341771

Method and a device for assisting the piloting of an aircraft, and an aircraft

A method of assisting the piloting of an aircraft. A collective pitch margin of a main rotor is determined by applying a recursive algorithm using a main relationship that supplies said collective pitch margin at each current calculation instant as a function of the quotient of a limiting power margin divided by a denominator, the denominator being equal to the product of a first term multiplied by a second term, the first term being a function of the current collective pitch at said current calculation instant and of the collective pitch limit at a previous calculation instant prior to said current calculation instant, said second term being a function at least of a predetermined coefficient for reducing said power margin of the power plant.. ... Airbus Helicopters

11/30/17 / #20170341748

Aircraft provided with a winch device

An aircraft provided with a wing and a winch device. The winch device is provided with a hoist device that includes a storage drum and a motor member for winding a suspension member around the storage drum and for unwinding said suspension member off the storage drum. ... Airbus Helicopters

11/30/17 / #20170341742

Multi-blade rotor for a rotary wing aircraft

A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.. . ... Airbus Helicopters

11/30/17 / #20170341738

Retraction / extension of a landing gear in an aircraft

A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. ... Airbus Helicopters

11/30/17 / #20170341322

Method of correcting an inappropriate countersink in a composite component

A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: preparing a repair patch; arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and fixing the repair patch in the inappropriate countersink.. . ... Airbus Helicopters

11/30/17 / #20170341315

Deposition head for depositing an impregnated fiber tape, and a device for placing such a tape

The present invention relates to a deposition head provided with an assemblage comprising a of impregnated fibers arranged against a backing tape. The deposition head includes a slide and a movement actuator connected to the slide to move the slide in translation from a high position to a low position, said slide carrying a peeling roller, said backing tape extending over a circular arc against the peeling roller, said low position being configured so that said peeling roller presses said tape of impregnated fibers against a deposition surface only in the low position of the slide, said circular arc occupying a first angle in the low position of the slide and a second angle in the high position of the slide, said first angle being greater than said second angle.. ... Airbus Helicopters

11/30/17 / #20170341312

Method and a thermoplastic blade

A method of fabricating a blade. The blade comprises subassemblies made of thermoplastic composite materials, each subassembly comprising an internal arrangement and at least one external arrangement, each internal arrangement comprising a stack of intermediate layers comprising reinforcing fibers impregnated with a semicrystalline thermoplastic matrix, each external arrangement comprising at least one surface layer comprising reinforcing fibers impregnated with an alloy of a semicrystalline thermoplastic polymer and of an amorphous thermoplastic polymer. ... Airbus Helicopters

11/23/17 / #20170336517

Redundant device of piloting sensors for a rotary-wing aircraft

A device of piloting sensors for a rotary wing aircraft having at least two imu inertial modules, at least two gnss receivers having respective first fault detection and exclusion modules for detecting and excluding failures and covering distinct gnss satellite navigation systems, at least two second fde modules, at least two hybridizing platforms, and at least one third fde module. The fde modules enable signals that are of integrity and/or signals that are erroneous to be detected so as to exclude each gnss system that is defective. ... Airbus Helicopters

11/23/17 / #20170334555

Monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft

A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.. ... Airbus Helicopters

11/16/17 / #20170327208

Control method for controlling a buoyancy system for an aircraft, a buoyancy system, and an aircraft

The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (mod1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (stp1) of predicting a forthcoming impact. ... Airbus Helicopters

11/16/17 / #20170327200

Rotary wing aircraft with an interface frame joining the fuselage tail boom and the tail cone

A rotary wing aircraft comprising a fuselage tail boom, a tail cone and an interface frame, the interface frame in turn having a connecting structure directly attached to the tail cone by means of a tail cone mechanical connection and a connecting sleeve fitting axially the fuselage tail boom, the connecting sleeve and the fuselage tail boom being directly attached by means of a one boom mechanical connection; the interface frame thereby joining the fuselage tail boom and the tail cone.. . ... Airbus Helicopters

11/09/17 / #20170320563

Aircraft provided with a buoyancy system, and a buoyancy method

An aircraft having an airframe that extends longitudinally along an anteroposterior plane. A buoyancy system is provided with at least one pair of two floats arranged transversely on opposite sides of said anteroposterior plane. ... Airbus Helicopters

10/26/17 / #20170308113

Haptic device for vibrating a control stick

A haptic device comprising a base and at least one shaker branch. Said at least one branch is connected to the base by mobility means conferring a degree of freedom on the branch to move in rotation about a pivot axis relative to the base. ... Airbus Helicopters

10/26/17 / #20170305526

Drone having at least three lift and propulsion rotors

A drone comprising a carrier structure, at least three lift propulsion rotors and a control system delivering at least one electrical power supply to at least three electric motors driving said at least three rotors, said at least three rotors being spaced apart longitudinally and transversely beside one another, wherein said drone includes a wing carrying two half-wings symmetrically about an anteroposterior plane of symmetry p of said drone, serving at least to increase the lift of said drone, each of said two half-wings including at least one movable portion suitable for moving relative to said carrier structure of said drone with at least a first degree of freedom to move in rotation about a first pivot axis parallel to a longitudinal direction x of said drone; and two first electric actuators respectively enabling each of said movable portions of one of said two half-wings.. . ... Airbus Helicopters

10/26/17 / #20170305003

Extraction device for extracting a trim weight from a rotor blade

An extraction device for extracting a trim weight from a rotor blade, comprising a supporting tube that is at least partly provided with a female thread, and a threaded rod that is at least partially arranged in the supporting tube, wherein the threaded rod is coupled to a fixing element that is adapted for being detachably fixed to the trim weight and that is at least partially provided with a male thread which engages at least partially the female thread of the supporting tube, and wherein the threaded rod is at least partly plastically deformable.. . ... Airbus Helicopters

10/12/17 / #20170293712

Probabilistic load and damage modeling for fatigue life management

A fatigue life management system for determining a remaining fatigue life of a component of an aircraft. The fatigue life management system may generate probability density functions of minimum load, maximum load, and timeframe damage for predetermined time intervals based on selected flight data of the aircraft and regression models for probabilistic prediction of minimum load, maximum load, and timeframe damage of the component. ... Airbus Helicopters

10/05/17 / #20170283056

Return device for retracting a movable attachment device, and an aircraft fitted with such a return device

A return device for retracting an attachment device of an aircraft. The attachment device is movable between a retracted storage position and a deployed working position, the return device tending to place the attachment device in the retracted storage position in the absence of an external load, while allowing the attachment device to move towards the deployed working position in the presence of an external load. ... Airbus Helicopters

10/05/17 / #20170283051

Method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor

A method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor. The method comprises at least the steps of: manufacturing an outer shell, manufacturing a stiffener member by means of an automated process, inserting the stiffener member into the outer shell, and bonding the stiffener member to the outer shell.. ... Airbus Helicopters

09/21/17 / #20170267364

Method of monitoring at least one freewheel of a rotary wing aircraft, and an aircraft

A method of monitoring a first freewheel interposed between a first drive shaft of a first engine and a rotor. The state of operation of said first freewheel is correct if the first inlet speed of rotation of the first drive shaft lies in a second range of values corresponding to the current stage of operation while the outlet speed of rotation of the rotor lies in a first range of values corresponding to the current stage of operation.. ... Airbus Helicopters

09/07/17 / #20170253337

Aircraft seat that is tolerant to floor deformation

A vehicle seat comprising a stand and a bucket having a seat pan and a seat back. Said stand serves to fasten said bucket to a floor of said vehicle and to absorb deformation of said floor while limiting the mechanical stresses that are transmitted to said bucket. ... Airbus Helicopters

08/24/17 / #20170240290

Device and a method of controlling engagement between the engine and a main power transmission gearbox of an aircraft

A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox mgb of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. ... Airbus Helicopters

07/27/17 / #20170212162

Method and a system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft

A monitor system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft. In order to monitor each piece of electronic equipment, such a monitor system comprises: monitor means for measuring variations of at least one state parameter p as a function of time t; concatenation means for generating data groups (ti, pi, sj); transmission means for transmitting the data groups (ti, pi, sj) to a centralized unit; first computation means for determining an observed reliability robs of the or each piece of electronic equipment; second computation means for determining an expected reliability rexp of the or each piece of electronic equipment; comparator means for comparing the observed reliability robs with the expected reliability rexp of the or each piece of electronic equipment; and warning means.. ... Airbus Helicopters

07/27/17 / #20170210465

Bottom abutment device for a rotorcraft rotor, a rotorcraft rotor, and a rotorcraft

A bottom abutment device for a rotor having a plurality of lift assemblies. The bottom abutment device comprises at least one abutment track per lift assembly. ... Airbus Helicopters

07/13/17 / #20170197709

Compound rotorcraft

A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.. . ... Airbus Helicopters

06/22/17 / #20170175875

Emergency lubrication device of simplified architecture for a power transmission main gearbox of an aircraft

An emergency lubrication device of simplified architecture for a mechanical system. The emergency lubrication device has a tank, trigger means, at least one pipe, and at least one distribution means. ... Airbus Helicopters

06/22/17 / #20170175673

Aircraft with a hot air exhaust that comprises two pivotally mounted exhaust sections

An aircraft with at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle.. . ... Airbus Helicopters

06/22/17 / #20170174340

Aircraft rotor blade of shape adapted for acoustic improvement during approach flights and for improving performance in hovering flight and in forward flight

A blade of a rotor for a rotary wing aircraft. The blade presents a combination of relationships for variation in the sweep, the chord, and the twist of the airfoil profiles of the sections of the blade in order, firstly to improve the aerodynamic performance of the blade both in forward flight and in stationary flight, and secondly to reduce the noise given off during approach flight. ... Airbus Helicopters

06/22/17 / #20170174339

Aircraft rotor blade of shape adapted for acoustic improvement during an approach flight and for improving performance in forward flight

A blade of a rotor for a rotary wing aircraft. The blade presents relationships for variation in the sweep and in the chord of the profiles of sections of the blade, in particular in order to improve the twisting stiffness and the bending stiffness of the blade. ... Airbus Helicopters

06/15/17 / #20170168680

Device and a method for assisting the piloting of an aircraft

A device and a method for assisting the piloting of an aircraft. The device comprises at least one touch screen, a memory containing a database, measurement and detection means, and analysis means. ... Airbus Helicopters

06/08/17 / #20170160749

Method and a device for piloting an aircraft

A method of assisting the piloting of an aircraft having at least one actuator acting on a control member. The aircraft has a main measurement system and a secondary measurement system respectively determining at least one predicted value and at least one measured value of a parameter that is used in at least one flight-control law. ... Airbus Helicopters

05/18/17 / #20170137139

Thermopile energy storage for a rotary wing aircraft

A rotary wing aircraft having an electrical installation including at least one thermopile for powering at least one piece of electrical load equipment. Technical specifications for the thermopile specify: a usable power for supplying to the load equipment in the range 20 w to 200 kw, a power rise time lapse lying in the range 3 s to 30 s, and a low operating time for usefully supplying a predetermined quantity of electrical energy lying in the range 10 s to 180 s. ... Airbus Helicopters

05/18/17 / #20170137108

Aircraft having a removable hold

An aircraft having an airframe including a hollow structure referred to as a “storage” structure, the storage structure having an opening that is open to the outside of the aircraft. A sealing device extends around the opening, the sealing device including at least one compressible gasket. ... Airbus Helicopters

05/11/17 / #20170131035

Plate heat exchanger comprising structural reinforcements for a turbine engine

A plate heat exchanger comprising a plurality of plates having a plane peripheral zone, an inner zone having sinusoidal undulations and two chimneys positioned at two opposite corners of the plates. Modules are formed by assembling two plates that make contact via the undulation troughs and the peripheral zones. ... Airbus Helicopters

05/04/17 / #20170121010

A rotorcraft tail boom, and a rotorcraft

A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (hext) and it extends laterally over an extension thickness (epext), the extension height (hext) lying in the range 0.05 times the maximum thickness (epmax) of the structure, included, to 0.5 times the maximum thickness (epmax), included, of the section, the extension thickness (epext) lying in the range 0 to 0.4 times the maximum thickness (epmax), included, of the section.. ... Airbus Helicopters

05/04/17 / #20170121008

Maintenance step for a helicopter

A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.. . ... Airbus Helicopters

04/27/17 / #20170113793

Compound aircraft having an additional anti-torque device

A compound aircraft having a fuselage, a main rotor, a main anti-torque device and two wings positioned on either side of the fuselage. Each wing has at least one movable flap situated at its trailing edge. ... Airbus Helicopters

04/27/17 / #20170113792

System for controlling a rotorcraft rotor, a rotorcraft fitted with such a system, and an associated control method

A control system for controlling at least one rotor of a rotorcraft, the control system comprising at least one piloting member suitable for operating at least one control for controlling movements of the at least one rotor. Such a control system comprises: at least one memory enabling information representative of a predetermined control margin threshold to be stored; calculation means for calculating a current control margin, which margin is defined as being the difference between a current position and a limit of the control for controlling movements of the rotor(s); comparator means for comparing the current control margin with the predetermined control margin threshold; and a control unit for modifying an operating relationship of the control for controlling movements of the rotor(s) when the current control margin is less than or equal to the predetermined control margin.. ... Airbus Helicopters

04/27/17 / #20170113781

Aircraft including a fuselage sponson

An aircraft having a sponson extending substantially transversely relative to a main body of the fuselage of the aircraft and substantially perpendicularly relative to a vertical anteroposterior plane of symmetry p of the main body of the fuselage when the aircraft is standing on a horizontal support, the sponson including a notch locally reducing a cross-section of the sponson in a connection zone of the sponson, the connection zone being suitable for being arranged in the immediate proximity of the main body of the fuselage of the aircraft from which the sponson emerges transversely, the notch being open at least to a front outside face and to a top outside face of the sponson and being suitable for receiving a bottom portion of a sliding side door when in its open position.. . ... Airbus Helicopters

04/20/17 / #20170107909

Gas ejection duct with acoustic treatment, an aircraft, and a method of fabricating such a duct

A gas ejection duct with acoustic treatment provided with at least one wall referred to as an “acoustic” wall for coming into contact with the gas. The acoustic wall comprises an inner skin and an outer skin that are spaced apart at least in part by a space, the acoustic wall including at least one internal mesh in the space, the mesh defining a plurality of cavities. ... Airbus Helicopters

03/30/17 / #20170089443

Mounting arrangement for mounting a gear box of a rotorcraft to a fuselage of a rotorcraft

A mounting arrangement for mounting at least a gear box of a rotorcraft to a fuselage of a rotorcraft, the mounting arrangement comprising a gear box of a rotorcraft and at least two support plates that are rigidly attached to at least approximately opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means that are adapted to allow attachment of the at least two support plates to a fuselage of a rotorcraft by means of associated struts in order to enable transfer of induced loads occurring in operation, which are directed into a predetermined load direction, via the associated struts.. . ... Airbus Helicopters

03/30/17 / #20170088281

Device for regulating the speed of rotation of a rotorcraft rotor, a rotorcraft fitted with such a device, and an associated regulation method

A device for regulating the speed of rotation of at least one main rotor of a rotorcraft, which speed is known as the speed nr. Such a rotorcraft comprises at least one manual flight control member for delivering a collective pitch control setpoint c for the blades of the at least one main rotor, the control setpoint c being a function of a current position of the at least one control member; and detector means enabling a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air.. ... Airbus Helicopters

03/30/17 / #20170088258

Rotor head, a rotor, and a rotorcraft

A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.. . ... Airbus Helicopters

03/16/17 / #20170073066

Power transmission system and an aircraft having a rotary wing

A power transmission system having at least one inlet speed-reducing gear and a main speed-reducing gear, each inlet speed-reducing gear comprising an inlet pinion meshing with an inlet gearwheel. The inlet gearwheel is constrained to rotate with a main pinion of the main speed-reducing gear, the main pinion meshing with a main gearwheel. ... Airbus Helicopters

03/09/17 / #20170066541

Method of regulating a three-engined power plant for a rotary wing aircraft

A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation nr. ... Airbus Helicopters

03/09/17 / #20170066526

Ball-bearing control cable, a mechanical system, and an aircraft

A ball-bearing control cable comprising an outer sheath surrounding a central blade. The outer sheath comprises a central portion extending between two endpieces. ... Airbus Helicopters

03/02/17 / #20170057617

Deflector assembly for an aircraft

A deflector assembly for the rope/cable hanging from a hoist mounted on an aircraft (a). The deflector assembly has an adjoined anchorage that includes a socket face that internally has a sliding bearing in which is housed an innermost end, so that the innermost end is slidably guided relative to the adjoined anchorage to have one degree of freedom along a linear translation axis (lt). ... Airbus Helicopters

02/16/17 / #20170045391

Liquid level sensor with insulating region over the probe foot

A liquid level sensor comprising an inner capacitor tube, an outer capacitor tube and a probe foot suitable for placing the liquid level sensor on a bottom surface of a liquid tank, wherein a capacitor region arranged to hold a liquid is defined between the outer capacitor tube and the inner capacitor tube, and wherein an insulating minimum distance is left between the inner capacitor tube base and the probe foot, the insulating minimum distance being sufficient to prevent a droplet of water on the probe foot from making contact with the inner capacitor tube.. . ... Airbus Helicopters

02/16/17 / #20170043868

Damper device and an aircraft

A damper device provided with a first connection member, a second connection member, a resilient member, and a hydraulic system. The hydraulic system includes an outer casing and a rod, the first connection member being fastened in reversible manner to the outer casing, the resilient member being arranged around a projecting portion of the rod, the resilient member comprising at least one resilient means interposed between a first strength member and a second strength member, the first strength member being fastened in reversible manner to the outer casing, the second strength member being constrained to move in translation with the projecting portion, and the connection member being fastened in reversible manner to the projecting portion.. ... Airbus Helicopters

02/09/17 / #20170037927

Vibration isolating device for an elastic coupling of two components

A vibration isolating device that is adapted for an elastic coupling of a first component to a second component and for vibration isolation in predetermined frequency ranges between the first and second components, the vibration isolating device comprising at least a first and a second elastically deformable plate that are attached to each other in at least two separate connecting points, the first elastically deformable plate comprising a first curvature and the second elastically deformable plate comprising a second curvature, wherein the first and second curvatures are respectively located in a region between the at least two separate connecting points and arranged such that a gap is defined between the first and second elastically deformable plates.. . ... Airbus Helicopters

02/09/17 / #20170037911

Flexible coupling means, a mechanical transmission, and an aircraft

A coupling means having a first member provided with a first diaphragm and a second member provided with a second diaphragm. The coupling means include an additional device having a plurality of protrusions circumferentially distributed on a first cylinder of the first member and a plurality of abutments distributed circumferentially on a second cylinder of the second member, each protrusion presenting at least one sliding face facing a first bearing face of an abutment, each protrusion presenting a blocking face facing a face of the second member referred to as a “second bearing” face.. ... Airbus Helicopters

02/02/17 / #20170029092

Adjustable and rotary rudder bar for a rotary wing aircraft

An adjustable and rotary rudder bar for a rotary wing aircraft. The rudder bar comprises a pedal bar, a main body, two pedals connected to the pedal bar on either side of the main body, a slider device enabling the pedal bar to slide relative to the main body, a structure fastened to a floor of the aircraft, and a shaft having a first axis (a1). ... Airbus Helicopters

02/02/17 / #20170028698

Method for joining thermoset components

A method for joining one or more first-type thermoset components to a second-type thermoset component, each first-type thermoset component being manufactured by providing an uncured starting thermoset component on which a thermoplastic material layer is placed, such that an interpenetrating network forms between the thermoset polymer of the starting thermoset component and the corresponding thermoplastic material layer when each first-type thermoset component is cured; and each first-type thermoset component being then placed on an uncured second-type thermoset component so that when the latter is cured, a further interpenetrating network forms between each thermoplastic material layer and the thermoset polymer of the second-type thermoset component; this results in a strong joint between the first-type and the second-type thermoset components.. . ... Airbus Helicopters

01/26/17 / #20170025032

Method of driving a main rotor of a rotorcraft in the context of simulating a failure of one of the engnes of the rotorcraft

A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (nr) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (s), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (a) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (oei/2) for regulating operation of the engine in simulation mode to be exceeded. ... Airbus Helicopters

01/26/17 / #20170021791

Energy absorbing system for absorbing energy of an object in a vehicle in a crash situation

An energy absorbing system that is adapted for absorbing energy of an object in a vehicle in a crash situation by decreasing acceleration and force acting on the object in the crash situation, the energy absorbing system comprising at least one plastically deformable energy absorber that is plastically deformable in the crash situation. A mass-dependent self-adjusting mechanism is provided, the mass-dependent self-adjusting mechanism being adapted for adjusting, on the basis of an underlying mass of the object, a required compensation force that is to be provided by the energy absorbing system in the crash situation for plastically deforming the at least one plastically deformable energy absorber in order to decrease the acceleration and force acting on the object.. ... Airbus Helicopters

01/19/17 / #20170016513

Power transmission gearbox and an aircraft

A power transmission gearbox having at least one driving gear with spur teeth presenting a large radius. The gearbox includes at least one mechanical outlet drive system suitable for driving an accessory, the mechanical outlet drive system having a gear with face teeth referred to as an “accessory pinion”, the accessory pinion presenting a “small” radius (r2) lying orthogonally between each face tooth and its axis of rotation, the small radius (r2) being smaller than the large radius (r1).. ... Airbus Helicopters

01/12/17 / #20170010148

Method of estimating the instantaneous mass of a rotary wing aircraft

A method and a device for estimating the instantaneous mass of a rotary wing aircraft, the aircraft having a power plant driving at least one main rotor and an anti-torque rotor in rotation, and also having a plurality of sensors. The method uses functional characteristics and flight characteristics of the aircraft, atmospheric characteristics, and performance curves for the aircraft to determine the measured instantaneous mass mm of the aircraft. ... Airbus Helicopters

01/12/17 / #20170009662

Device for automatically regulating aircraft power plant gas generator and free turbine speeds as a function of heating, electricity generation, noise emission, and fuel consumption

A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (ntl) of a free turbine of the turbine engine.. ... Airbus Helicopters

01/12/17 / #20170008641

Aircraft having at least one control device for controlling inflation of an inflatable safety bag, and an associated method of controlling inflation of an inflatable safety bag

A control device including at least one control member for measuring an acceleration of an aircraft, for generating an inflation order, and for transmitting the inflation order to an inflation member, the inflation member serving to inflate at least one inflatable safety bag, the control device, the inflation member and the inflatable bag being arranged together on a single seat of the aircraft. Such a control device includes at least one readying system connected to the at least one control member, the readying system comprising: at least a first sensor suitable for continuously measuring a first current acceleration of the aircraft relative to at least one axis; and at least one switch that is controllable as a function of the first current acceleration of the aircraft as measured by the first sensor.. ... Airbus Helicopters

01/05/17 / #20170001713

Method of controlling aerodynamic means of an aircraft, an associated control system, and an aircraft provided with such a control system

A control method for controlling aerodynamic means of an aircraft having mechanically decoupled flight controls enabling the aircraft to be piloted by at least two pilots. The aircraft has at least two control members operated by respective ones of the at least two pilots and each enabling control signals to be generated for causing the aerodynamic means to move relative to an incident air stream. ... Airbus Helicopters

01/05/17 / #20170001710

Airfoils for rotor blades of rotary wing aircrafts

An airfoil for a rotor blade of a rotary wing aircraft, the airfoil having a predetermined maximum thickness to chord ratio and comprising, between a leading edge and a trailing edge, an extrados and an intrados, the intrados being defined by predetermined intrados coordinate value pairs and the extrados being defined by predetermined extrados coordinate value pairs, wherein a maximum error of each one of the predetermined intrados coordinate value pairs and the predetermined extrados coordinate value pairs amounts to ±3%.. . ... Airbus Helicopters








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