Eurocopter

Airbus Helicopters

Damien Sequera

Thomas Pierre Manfredotti

Jean-Pierre Jalaguier

Jean-Romain Bihel

Vincent Schwaller

Wojciech Gregorczyk

Roman Pniewski

Benny Liefmann

Marcin Wiklo

Kazimierz Król

Krzysztof Kolodziejczyk

Piotr Bojarczak

Krzysztof Olejarczyk

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 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.

Damper device and an aircraft

The present invention relates to a hydraulic distributor () of a servo-control () of an aircraft, the hydraulic distributor comprising main distributor member () and emergency distributor member () that are coaxial, said emergency distributor member () being caused to move by said main distributor member () in the event of said main distributor member () seizing, said hydraulic distributor being provided with a detector device () for detecting said seizing. The detector device () is provided with a reed switch () and with amplification means () for amplifying said movement of the emergency distributor member, said amplification means comprising a lever () having a magnetized free end () that activates said reed switch () in the event of said emergency distributor member () moving.

Hydraulic distributor provided with a device for detecting seizing

A mechanical transmission system for a rotorcraft, including a supercritical transmission shaft and an active magnetic damper secured to the structure of the rotorcraft via a mechanical damper is provided.

Magnetically-damped supercritical transmission system

An anti-vibratory device with rotary compensation weights includes two sets of two identical rotors with respective eccentric compensation weights, the units being symmetrically disposed in relation to an axis of symmetry and the axes of rotation of the rotors being parallel between themselves and orthogonal in relation to the axis of symmetry; and a rotational drive system for the rotors. Advantageously, the device includes controllable mobile equipment carrying the drive system and being able to slide along the axis of symmetry in order to drive the dephasing of the rotors with eccentric compensation weights associated with the sets.

Anti-vibratory device with rotary compensation weights

A device is provided for suspending a battery () of an aircraft, the device including at least one spring (); the device further includes an adjustment element enabling the stiffness of the spring to be adjusted.

Growing community of inventors

Nimes, France

Damien Sequera