Airbus Helicopters

Eurocopter

Jean-Romain Bihel

Thibaut Marger

Arnaud Groll

Jean-Pierre Jalaguier

Damien Sequera

Pascal Leguay

Clement Coic

Zouhair Sassi

Marc Salesse-Lavergne

Jacques Joseph Gaffiero

Romuald Biest

Kamel Abdelli

Sylvain Berthalon

Stephane Mazet

Mathias Fournier

Gérard Couderc

Christophe Serr

Christophe Pujol

Cédric Carlavan

Olivier Sellier

Alexandre Pantaine

Nicolas Bourdais

Clement Coiec

Wojciech Gregorczyk

Guillaume Fiocchi

Clément COÏC

Stéphane Mazet

Bastien Houpert

Clément Coïc

A hydroelastic damper comprising at least a first resilient assembly that is provided with a first inner strength member engaged at least in part in a first outer strength member, a first resilient member providing resilient return for the first outer strength member and the first inner strength member towards a rest position (POSREP). The hydroelastic damper comprises at least one hydraulic assembly provided with a first hydraulic chamber and a second hydraulic chamber in communication with each other via a connection provided in a first wall of the hydraulic assembly. A first floating piston is movable at least in translation along the longitudinal axis relative to the first inner strength member and to the first outer strength member, the first hydraulic chamber being defined at least by the first floating piston and the first wall in order to protect the first resilient member.

Hydroelastic damper, and an aircraft

A hydro-elastic damper comprising at least one elastic assembly comprising an elastic member between two strength members. The elastic assembly including a compression chamber. The hydro-elastic damper includes a damping assembly provided with an expansion chamber that is defined in a transverse direction by an end wall and by a piston. The compression chamber is hydraulically connected to the expansion chamber by three hydraulic connections comprising respectively: a duct; at least one first passage with an overpressure valve; and at least one second passage with a check valve.

Hydro-elastic damper and an aircraft

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. The two strength members and the elastomer material member extending beyond the zone around the cage so that the relative movements between two strength members resulting from the movements of the blade are damped by deformations of the elastomer material member, at least a portion of the lead-lag damper being designed to occupy a portion of the inside of the blade that is conventionally filled with foam.

Lead-lag damper integrated inside a blade of a rotor

A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

Rotorcraft having a rotary wing and at least two propellers, and a method applied by the rotorcraft

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. The grip is linked to the stick via a helical link, rotation of the grip about the stick giving rise to movement in translation of the grip together with the movable assembly along the stick, the grip being movable in translation in both a first direction in translation and in a second direction in translation that is opposite to the first direction in translation.

Control member, a rotary wing aircraft, and a method

A servo-control. The servo-control comprises at least one body as well as a power shaft and a control piston arranged in each body, the at least one body and the power shaft respectively forming two power members. One of the power members bears at least on end-stop member and the power member without an end-stop member bears a passivation actuator. The passivation actuator comprises a passivation shaft which bears an end-stop and a passivation piston, the passivation piston being arranged to be mobile in longitudinal translation in an enclosure, an elastic system being arranged between the passivation piston and the enclosure.

Servo control, rotor and aircraft

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. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.

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

An adaptive flight control system for controlling the pitch of blades of a propulsive propeller of a hybrid helicopter as a function of the return value of the pitch. The adaptive flight control system comprises control means supplying the pitch control order, a piloting member controlling variation of the pitch, and piloting means applying a control gain in order to transform the control order into a setpoint, and transmitting the setpoint to the piloting member. The piloting means include information return means applying a return gain that is variable to the return value of the variation of the pitch to the piloting means, also modifying the control gain as a function of the return value.

Adaptive flight control system for the yaw and thrust flight controls of a hybrid helicopter

A ball-bearing control cable comprising an outer sheath surrounding a central blade. The outer sheath comprises a central portion extending between two endpieces. Each endpiece comprises a tubular central body that surrounds the central blade, each central body extending from a proximal abutment secured to the central portion towards a free distal abutment, each abutment of an endpiece projecting from the central body of the endpiece, each endpiece including a resilient system interposed around the central body of the endpiece between an abutment of the endpiece and a ring, the resilient system of one endpiece being arranged between the distal abutment and the ring of the endpiece, and the resilient system of the other endpiece being arranged between the proximal abutment and the ring of the other endpiece.

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

A servo-control having at least one movable cylinder that includes a hydraulic directional control valve. The hydraulic valve includes a control shaft that is rotatable about a longitudinal axis, the control shaft being connected to a distributor slide. The servo-control including a stationary abutment member secured to a cylinder and an input lever situated outside the cylinder. The input lever is connected to the control shaft and includes a stop portion arranged in the abutment member. The servo-control includes movement means for moving the input lever longitudinally, a first abutment surface of the abutment member limiting a travel amplitude of the stop portion when the input lever is in a first position.

Servo-control and an aircraft having such a servo-control

A pressure-balance valve for balancing the pressures of fluids admitted into the pressure-balance valve via respective second ducts. The pressure-balance valve has both a chamber for guiding movement in translation of a piston, and also fluid flow paths, each comprising a said second duct and a first duct for admitting a fluid coming from the same fluid source as the fluid flowing in its second duct. Each of the first ducts is provided with a shutter co-operating with a ramp arranged on the piston. Movement of the piston in translation as a result of a pressure difference between the fluids respectively admitted into the second ducts causes one of the shutters to slide along the corresponding ramp and consequently allows additional fluid to be delivered from a first duct to the second duct of the same fluid flow path.

Pressure-balance valve for balancing fluid feed to actuator cylinders of a servo-control for controlling rotor blades of a rotorcraft

A hydraulic valve (') of a servo-control for feathering the blades () of a rotorcraft rotor. The hydraulic valve (&#x2032;) comprises a main valve member () and an emergency valve member () blocked relative to a valve cylinder () of the hydraulic valve (&#x2032;) by means of a pin () in sliding thrust engagement in a cavity () of the emergency valve member (). Relative movement between the emergency valve member () and the valve cylinder () initiating sliding movement of the pin () inside the cavity () and causing mover means () for moving the pin () to be put into operation, thereby releasing the emergency valve member () to move freely.

Double hydraulic valve of a servo-control for feathering the blades of a rotorcraft rotor

A hydraulic system of an aircraft, the system comprising at least one servo-control, each servo-control comprising at least one cylinder together with a drive rod and a piston arranged in each cylinder. Between each cylinder of servo-control and the drive rod of that servo-control, at least one servo-control presents main sealing means with controlled leakage allowing a hydraulic fluid to leak out from the cylinder, the hydraulic system further comprising at least one enclosure, each cylinder of the servo-control being arranged inside the enclosure so that the fluid is collected in the enclosure.

Aircraft hydraulic system comprising at least one servo-control, and an associated rotor and aircraft

The present invention relates to a servo-control () provided with at least one body () defining an inside space () together with a slider element () having a control piston () suitable for sliding in said inside space (), said control piston () subdividing said inside space () into a retraction chamber () and an extension chamber (). The servo-control () has at least one limit force detector device () comprising a casing () secured to said body () and defining a detection space (). Furthermore, a movable member () subdivides said detection space () into a first detection chamber () opening out to said inside space () and a second detection chamber (). Finally, the device includes detector means () for detecting the position of said movable member () in said detection space ().

Hydraulic actuator with a limit force detector device

The present invention relates to a method of determining the static force developed by a servo-control () having an actuator () and a hydraulic distributor control valve (), with the actuator () including at least one cylinder () and a slidable element (). The method comprises determining an instantaneous travel speed of the slidable element () relative to the cylinder () and determining the static force based at least in part on the instantaneous static force developed by the servo-control (), the predetermined maximum static force, the instantaneous travel speed raised to the second power, and the maximum travel speed of the slidable element () relative to the cylinder () raised to the second power.

Growing community of inventors

Le Rove, France

Jean-Romain Bihel