Airbus Helicopters

Eurocopter

Charles Chuc

Nicolas Imbert

Serge Giordano

Vincent Bourget

Christophe Perrin

Jean-Philippe Colmas

Raphaël Paquin

Jean Philippe Colmas

Riantsoa Rabemarolahy

Riantsoa Rabemarolahi

Raphael Paquin

The present invention relates to a rotorcraft rotor () having a plurality of blades () movably mounted on a hub () via blade roots () that are respectively associated therewith. The rotor () is fitted with an information capture appliance having at least one measurement assembly (E) comprising a flexible bar () interposed in engagement at its respective ends between the hub () and a blade root () that is allocated thereto. A strain gauge () formed of a SAW transducer is implanted on the bar () and generates information relative to the bending of the bar () following tilting orientations of the blade root () in flapping (B) and/or in lag (T).

Device for monitoring the flapping and/or lag behavior of a blade of a rotorcraft rotor

A device () for feeding electricity to equipment () of a vehicle (), the device including a harness (), a socket () electrically connected to said harness (), and a plug () electrically connected to said equipment () and co-operating with said socket () to provide the electrical connection between said harness () and said equipment (). The device () provides for said harness () to run in the thickness of a floor () of the vehicle (), said socket () being embedded in the thickness of said floor () so that the top surface of said floor () does not present any projecting portion. The device () includes a movable protection cap () for opening and closing said socket (), together with opening means () driven by mounting said equipment () on said floor (), thereby causing said movable protection cap () to open.

Device for feeding electricity to equipment, the device being incorporated in the floor of an aircraft cabin

A rotor () provided with a hub () and a plurality of blades (), said rotor () including a mast () secured to said hub () and protection means () for providing protection against lightning. The protection means () comprise rotary electric current conduction means () constrained to rotate with said mast () and connected to each of the blades () via a respective first electrical connection member (), said protection means () including non-rotary electric current conduction means () facing said rotary conduction means () while not being constrained to rotate with said mast (), said protection means () including electrical connection trigger means (), said non-rotary conduction means () being provided with a second electrical connection member () suitable for being electrically connected to a target member () external to said rotor ().

Rotor provided with a device for protecting it against lightning, and an aircraft provided with such a rotor

A communication device () for communication between a movable piece of equipment () of a rotary rotor () and a stationary piece of equipment (). Said communication device () is fitted with a set () of controlling swashplates including a rotary swashplate () and a non-rotary swashplate (), the communication device () comprising a movable transfer unit () and a stationary transfer unit () for exchanging information respectively with the movable equipment () and with the stationary equipment (). Each transfer unit () is connected to a respective transmit-and-receive antenna (), including a movable antenna () connected to the movable transfer unit () and fastened to the rotary swashplate () and a stationary antenna () connected to the stationary transfer unit () and fastened to the non-rotary swashplate (), the movable antenna () and the stationary antenna () being suitable for communicating with each other wirelessly.

Communication device, an aircraft rotor, and an aircraft

A de-icing system for a fixed or rotary aircraft wing. The system is capable of generating ultrasound that is transmitted at least locally to an outside surface of the wing, wherein the system comprising a base structure () covered at least locally with at least one leading edge (), an elastomer structure () arranged and secured between the base structure () and the leading edge (), housings () defined in the elastomer structure () and open towards the leading edge (), piezoelectric actuators arranged in at least some of the housings () in order to generate ultrasound, wiring () connecting the piezoelectric actuators to an electrical control and power supply unit, and a fastener for fastening the leading edge () onto the base structure () while coming into contact with the piezoelectric actuators () arranged in their respective housings ().

De-icing system for a fixed or rotary aircraft wing

An electrical power supply device () for electrically powering equipment on a rotary rotor () of an aircraft (), which rotor is driven by a shaft (), said device () comprising a removable stick (). The stick () includes an upper alternator () and an upper tube () secured to said shaft () so as to be constrained in rotation therewith, said upper alternator () having a plurality of upper coils () fastened to an upper inside peripheral surface (') of said upper tube (), said stick () having a rod () carrying an upper permanent magnet (), said device () having a mechanism () so that said rod () and said upper tube () move with distinct rotary movements, said mechanism () having connection means () so as to be connectable to a reference member () of an aircraft ().

Electrical power supply device for electrically powering at least one item of equipment on a rotary rotor of an aircraft, and an aircraft

The present invention relates to an electrical power supply and control device () for equipment () of a rotor (), the device having a three-phase AC generator () in a stationary frame of reference. The device () comprises a rotary field transformer () having a stationary portion () connected to said generator () and a rotary portion () connected to a sequencer () that is arranged in a rotary frame of reference, said device () including control means () for controlling the sequencer () and located in said stationary frame of reference, the control means being connected to the sequencer () via contactless connection means (), said sequencer () being suitable for electrically powering said equipment () on order of said control means ().

Electrical power supply and control device for equipment of a rotor, and an aircraft fitted with such a device

A device () for interconnecting electrical bundles, includes a plurality of pluggable connection and cross-connect cards (to) for the electrical bundles. The device further includes a 'main' printed circuit () fitted with connectors or slots (to) designed and arranged to receive the pluggable cards, the printed circuit having a plurality of parallel tracks (), each enabling two tracks (to) or tracks starters (to) provided respectively on two distinct pluggable cards plugged in the connectors of the main printed circuit to be put to the same potential, each of the parallel tracks () being in contact with a respective pin () of a plurality of connectors of the main printed circuit.

Growing community of inventors

Marseilles, France

Charles Chuc