Airbus Helicopters

Eurocopter

Paul Cranga

Thomas Pierre Manfredotti

Julien Guitton

Alain Eberhard

Jonathan Rodriguez

Guillaume Inquiete

Simon Chesne

Matthieu Pula

Benoit Rogier

Joachim Re

Benoît Rogier

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. An actuator is connected to a processor unit, the processor unit electrically powering the actuator with adjustable electrical power. A resilient member is interposed between said seismic mass and said support.

Resonator, and an aircraft fitted with the resonator

The invention relates to landing gear of an aircraft, the landing gear having skids and cross-members. The landing gear has at least one damper device arranged on at least one of the cross-members referred to as a 'damped' cross-member. The damper device includes two stroke-transfer means hinged to the damped cross-member and to a fuselage of the aircraft. Each stroke-transfer means comprises a crank hinged to the damped cross-member and a link rod hinged to the crank and to the fuselage. A damper is hinged to each crank.

Skid landing gear having at least one damper, and aircraft including the skid landing gear

A suspension device () provided with at least one suspension means () comprising a flapper () performing pendulum motion, the flapper () being provided with a mass support () supporting at least one flapping mass (). The mass support () is hinged to a carrier structure () for isolating and to a holder bar () for holding said mechanical assembly. The suspension device () includes at least one force generator (), said suspension device () having at least one computer () connected to a measurement system () measuring the levels of vibration, and to said force generator () to regulate said amplitude and said phase actively by controlling the force generator () as a function of at least one measurement signal coming from said measurement system ().

Antivibration suspension device for a mechanical element, and an aircraft

A carrier structure for a rotor and a method of preventing the coupling of the vibration modes of a carrier structure of a flying machine with the vibration modes of a rotor are provided. The carrier structure has an airframe and a mounting structure suitable for being engaged with the rotor. A vibration-damper mechanism is fitted to the mounting structure and has a resonator that includes a weight element, a damper, and a first deformable member. The weight element is a flapping weight element and is carried by the mounting structure via the first deformable member. The first deformable member allows the weight element to move with respect to the mounting structure and restrains the mobility of the weight element. The damper is interposed between the weight element and the mounting structure for damping the movement of the weight element.

Rotor carrier structure with a damper device for avoiding unstable coupling between resonant vibration modes

A vibration damping mechanism () for damping vibrations to prevent coupling of vibration modes of the carrier structure () with vibration modes of a rotor () secured to the carrier structure (). The mechanism comprises a support () suitable for being fastened to the rotor () and at least one resonator () including a mass () carried by the support () via mobile mounts () for mounting the mass () to move on the support (), the mechanism () including at least one damper () for damping the resonator (), with the damper being interposed between the resonator () and an engagement member () on the support ().

Vibration damper mechanism, and a flying machine including a carrier structure and a rotor provided with such a mechanism

The invention provides a vibration filter mechanism for aircraft equipment. A weighted lever arm () is hinged via bearings () associated respectively with a first structure connected to a fuselage and with a second structure connected to the equipment (). Deformable means () oppose pivoting movement of the lever arm. The lever arm () is arranged as a one-piece fork that comprises a pair of branches () that are interconnected by a crossbar () and that are hinged to the bearings () about spaced-apart parallel pivot axes (A, A). The fork carries a torsion shaft () that extends between the branches () at their free ends (), the torsion shaft () constituting the weight weighting the lever arm () and the deformable means () of the mechanism.

Filter mechanism for filtering vibration in aircraft

A blade () extending longitudinally from a root () of the blade () to a free end () of the blade (), the blade () having a resonator () incorporated therein to reduce the drag movements (F, F) of the blade (), the resonator () being provided with a solid and movable heavy element () and with resilient retaining element () secured to the heavy element () and to the blade (). Furthermore, the resonator () includes guide element () in which the heavy element () is capable of oscillating (F', F&#x2032;) longitudinally, the guide element () being arranged in a longitudinal direction (D) of the blade.

Blade for reducing the drag movements of said blade, and a method of reducing such a drag movement

Described is a blade () extending longitudinally from a root () of the blade () to a free end () of the blade (), the blade () being provided with an incorporated resonator () for reducing the drag movements (F, F) of the blade (), the resonator () being provided with a closed tank () that is partially filled with a liquid (). Furthermore, the resonator () includes a central tube () immersed inside the tank (), the tank () and the central tube () being arranged in a longitudinal direction (Y) of the blade (), the central tube () having first and second ends () that communicate with the tank () so that the liquid () can move from the tank () into the central tube (), and vice versa.

Growing community of inventors

Marseilles, France

Paul Cranga