Eurocopter

Airbus Helicopters

Romuald Biest

Bernard Gemmati

Gérard Couderc

Jean-Romain Bihel

Arnaud Groll

Philippe Vincent

Zouhair Sassi

Guillaume Franchini

Julien Pruss

Carine Mirman

Mathilde Chouteau

Robert Convers

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 system () having a control plate () for controlling the pitch of the blades () of a propeller, a power block (), and a directional control valve () for feeding said power block () with fluid. The power block () is sealed and includes at least a body in which at least one piston () that is secured to a piston rod () projecting from said body () is movable in translation, a repeater rod () connecting said piston rod () to said control plate (). The control valve () is sealed and comprises a stationary manifold () and a movable manifold () that is movable in rotation, said stationary manifold () being controlled by a control lever () connected by repeater means () to said repeater rod (). A respective pipe () connects each chamber () of said power block () to said movable manifold ().

System for controlling pitch variation of the blades of a propeller, a propeller, and an aircraft

A control lever () provided with a stick () extending axially from a stand (') towards grip means (&#x2033;) and with a carrier structure () for said stick () that is hinged about a first hinge axis (AX) and about a second hinge axis (AX). The control lever () includes phasing means () constrained to move in rotation with said stick () about said first hinge axis (AX) and about said second hinge axis (AX), said phasing means () comprising at least three main arms (), each for controlling a respective power member () that is connected to a set () of swashplates for controlling a rotary wing ().

Control lever for controlling a rotary wing, a mechanical control system including said control lever, and an aircraft

The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick () that is mounted to tilt (B, B) on a carrier structure () and that is in engagement with remote mechanical transmission members (). The stick () is arranged as a telescopic member provided with locking means () for locking it in a normal-use retracted position, and is equipped with deployment means (). Unlocking of the locking means () and use of the deployment means () depend on an assistance device () associated with the stick () being in a defective state. In the event of such a defective state being detected, the stick () is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.

Cyclic stick for mechanically transmitting commands for controlling a rotorcraft, the stick having a lever arm that is amplified selectively in the event of an emergency

A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque.

Breakable coupling device, and an associated trim actuator

The present invention relates to a mechanical device () suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure () suitable for being fastened to a support () by at least one main fastener pin () about which said carrier structure () is capable of performing a pivoting movement. In addition, the device includes at least one connection lever () per rotary assembly, and at least one secondary fastener pin () per connection lever (), said secondary fastener pin () being secured firstly to said carrier structure () and being fastened secondly by rotary means () to the connection lever ().

Mechanical device for combining first and second control orders, and an aircraft provided with such a device

The present invention relates to haptic feedback for operating at least one manual flight control device () for controlling the cyclic pitch of the blades () of a rotary wing () of a hybrid helicopter () via power assistance (). Said operations of said control device () are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter () in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member () between its minimum and maximum thrust values ().

Variable damping of haptic feedback for a flight-attitude changing linkage of an aircraft

The present invention relates to a bellcrank () for a flight-attitude-changing linkage (A,A) of the variable gain type. The linkage (A,A) connects a manual flight control device of a rotary wing aircraft (), e.g. a hybrid helicopter, to at least one airfoil of said aircraft () suitable for causing a change in flight attitude. Said bellcrank () includes first and second sliders (). Said first slider () is connected to a movable portion () of a setpoint flight-attitude-changing linkage () that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (A,A) to be adjusted, which gain is proportional to the position of said movable portion ().

Variable ratio crank for a manual flight control linkage of a rotary wing aircraft

A rotary actuator incorporating a force relationship includes a twistably-deformable structure having a first and a second end plate and a helical spring with a first and a second terminal end secured on the first and the second end plate, respectively, and wherein the first and the second end plate have a first and a second notch, respectively, and wherein the first and the second notch have a first and a second contact zone, respectively. The rotary actuator further includes an outlet shaft and a motor assembly having an outlet gear configured to drive the twistably-deformable structure so as to drive the outlet shaft in rotation, wherein the motor assembly, the twistably-deformable structure and the outlet shaft are disposed in succession. The rotary actuator has a first finger constrained to rotate with the outlet gear and a second finger constrained to rotate with the outlet shaft.

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Lambesc, France

Romuald Biest