Airbus Helicopters

Romain Nevers

Olivier Honnorat

Francois Malburet

Francois Marchand

Romain Kovel

Ludovic Aubertin

Leo Trierweiler

François Malburet

François Marchand

Léo Trierweiler

An actuator provided with a motor for moving an output arrangement, the actuator including both an output lever and a fusible connection that acts up to a mechanical torque threshold to constrain the output arrangement and the output lever to move together in rotation about an axis of rotation. The actuator also includes a fluid damper device housed between the output lever and the output arrangement to act, following rupture of the fusible connection, to damp movement of the output lever relative to the output arrangement in rotation about the axis of rotation.

Actuator provided with a fluid-damped fuse system, and a vehicle provided with the actuator

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.

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

A damping device for a shaft in rotation around an axis of rotation parallel to a direction (A). The said damping device includes a support, a plate, a collar, and clamping means. The said support is stationary and is provided with a first opening, with the said plate being provided with a second opening and the said collar being provided with a third opening. The said shaft passes simultaneously through the said first, second, and third openings with, respectively, a first radial gap, a second radial gap, and a third radial gap, with the said third radial gap being smaller than the said first and second radial gaps. The said collar is movable with respect to the said support in a plane perpendicular to the said direction (A), with the said clamping means pressing the said plate against the said collar and the said collar against the said support.

Damping device for a supercritical transmission shaft

A coupling device () providing end-to-end coupling between link shafts () and a supercritical transmission shaft () for driving a rotorcraft rotor (). Since the transmission shaft () is movable in angular deflection (B), spherical bearing surface friction members () are incorporated in the bearings () for mounting the transmission shaft () on a carrier structure (). The friction members () are caused to press against each other in dry friction via respective friction surfaces. A first friction member () is secured to the carrier structure () and a second friction member () is secured to a cage () for housing rolling members () carried by the transmission shaft (). The cage is itself engaged on the transmission shaft () to accompany it in its movement in angular deflection (B).

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Pelissanne, France

Romain Nevers