Messier-bugatti Inc.

Zodiac Aero Electric

Sagem Defense Securite

Messier-bugatti-dowty

Labinal, LLC

Jean-Clair Pradier

Max Erick Busse-Grawitz

Bertrand Maes

Thomas Lavaud

Olivier Collet

Jean-Pierre Balbinot

Antoine Gautier

Stéphane Guenot

Eric Evenor

Frédéric Pinard

Stéphane Le Garrec

William Roze

Loic Aoustin

Philippe Perez

A device for detecting an electrical load connected to an electric power supply network. The device comprises means for injecting a test signal into the electrical network and means for identifying the presence and the nature of an electrical load connected to the electrical network on the basis of the test signal.

Device and method for detecting an electrical load

Connection system arranged in a rack, for connecting at least one protection board () of an electrical distribution system of an aircraft with a primary power supply, to at least one powered device () and to a motherboard arranged in the rack. The connection system includes at least one modular connector on each protection board and, for each protection board capable of being inserted in the rack, at least one additional modular connector attached at least partly on the rack and at least one additional connector connected to the motherboard.

Assembly for protection boards of a distribution system

Supply system for electronic boards of an electrical distribution system comprising at least two protection boards () each able to control the supply of at least one protected pathway () on the basis of a power line (), characterized by the fact that each protection board () comprises at least one voltage converter () able to provide an internal supply voltage of the protection board on the basis of a supply voltage, the voltage converter () of a first protection board () being connected to at least one second protection board () so as to be able to provide the internal supply of the second protection board () in case of failure of the voltage converter () of the second protection board ().

Supply system for electronic boards of an electrical distribution system

Device for protecting against leakage currents, the device being intended to be wired up between a first electrical connection () and a second electrical connection (). The device comprises a switch () configured so as to at least partially divert the current flowing in the first electrical connection and controlled by the voltage of the first electrical connection.

Device and method for protecting against leakage currents

System, especially for use in aircraft, for controlling at least one switching device () able to open or close the connection between at least one power source and at least one supplied device, and means for measuring the state of the power supply channel. The system comprises: at least two microcontrollers () each able to emit a command intended for each switching device (), said microcontrollers () being connected to at least one portion of the means for measuring the state of the power supply channel; and a means () for determining the command to be transmitted, able to determine the command to be transmitted to each switching device () from the commands emitted by each microcontroller () and intended for said control switch.

System and method for controlling at least one switching device, especially for use in aircraft

Electrical distribution system for an aircraft comprising at least one electrical supply path comprising at least one power unit capable of opening or closing the connection between at least one electrical energy source and at least one device of the aircraft. The system comprises protection cards () each comprising at least two microcontrollers each capable of sending a command to each power unit of the electrical supply paths protected by each protection card and, among the set of microcontrollers of the protection cards, at least two microcontrollers are provided with a communication and computation function with all of the microcontrollers of the protection cards ().

Electrical distribution system for an aircraft

A method of distributing electric current to electrical outlets, and a program to implement same, including the steps of supplying electric current to the electrical outlets not yet connected to an electronic device upon receipt of a distribution request from the electrical outlets; determining the instantaneous current intensity supplied to the electrical outlets; comparing the determined current intensity to a threshold referred to as the maximum threshold; and when the predetermined current intensity is greater than the maximum threshold, selecting an electrical outlet and terminating the supply of electric current to the selected electrical outlet. The steps of selection and termination being carried out while continuing the step of supplying electric current to the electrical outlets not yet connected to an electronic device upon receipt of a distribution request from the electrical outlets.

Method of distributing electrical power to electrical outlets in a transport vehicle and an associated computer program

A device for selectively connecting a tire to a pneumatic unit of an aircraft, the tire forming part of a wheel mounted to rotate on a hollow axle of the aircraft, the device comprising a stator and a rotor that is mounted to rotate relative to the stator and that includes a structure enabling it to be rotated by the wheel. The stator is bell-shaped and is designed to be received as a push-fit in the axle, and includes an end wall carrying a first pneumatic port for connection to the pneumatic unit via a tube running along the inside of the axle, the rotor extending substantially inside the stator.

Device for connecting a tire of an aircraft wheel to a pneumatic unit of the aircraft

A device for selectively connecting a tire to a pneumatic unit of an aircraft, the tire forming part of a wheel mounted to rotate on a hollow axle of the aircraft, the device comprising a stator and a rotor that is mounted to rotate relative to the stator and that includes means enabling it to be rotated by the wheel. The stator is bell-shaped and is designed to be received as a push-fit in the axle, and includes an end wall carrying a first pneumatic port for connection to the pneumatic unit via a tube running along the inside of the axle, the rotor extending substantially inside the stator.

The invention relates to an aircraft undercarriage including at least one axle having at least one wheel mounted to rotate thereon, the undercarriage including a communication device for connecting a sensor mounted on a rim of the wheel to stationary processor means mounted on the aircraft. According to the invention, the communication device comprises firstly an antenna secured to the sensor and thus rotating together with the wheel, and secondly a stationary antenna extending at the end of the axle and connected to the processor means, the two antennas being in radio communication through a cover of non-conductive material secured to the wheel and covering the end of the axle.

Undercarriage fitted with a communication device between a wheel and the undercarriage

The invention relates to axle end equipment for a vehicle, in particular an aircraft, the equipment comprising a stationary portion for securing to the axle and a rotary portion for securing to the wheel carried by the axle. According to the invention, the rotary portion comprises first remote connection means in communication with a sensor mounted on the wheel so as to put the sensor and the rotary portion of the equipment into contactless electromagnetic relationship.

Axle end equipment for a vehicle, in particular an aircraft

Method and device for determining the weight and/or a characteristic value of the position of the center of gravity of an aircraft standing on the ground by means of a plurality of undercarriages, each undercarriage including at least one structural element exhibiting a variable level of stresses depending on the fraction of the weight of the aircraft transmitted to the ground through the undercarriage. The method includes the steps of a) measuring on each undercarriage at least one parameter representing the stress level of the element; and b) evaluating the characteristic value and/or the weight according to the parameters measured in step a). At least one parameter measured in step a) is a magnetic or electrical characteristic of the structural element of the undercarriage.

Device and method for determining the weight and/or a characteristic value of the position of the centre of gravity of an aircraft

A tachometer for an aircraft wheel mounted on an axle to rotate about an axis of rotation. The tachometer has a stationary part secured to the axle and a rotary part driven in rotation by the wheel. The stationary part and the rotary part are mountable independently on the axle and on the wheel, respectively, and have portions facing each other in a radial direction. A sensor and a target element carried by the stationary and rotary parts portions that extend facing each other in a radial direction and are in register with each other in a radial direction. The portion secured to the rotary part extends inside the axle.

Tachometer with independently mountable rotary and stationary parts for an aircraft wheel

The equipment for measuring the speed of rotation of a vehicle wheel () carried by a wheel axle () comprises a tachometer () having a stator () suitable for being secured to the wheel axle (), a rotor () suitable for being rotated by the wheel (), and a connector () secured to the stator () for electrical connection of the tachometer. The connector () includes a set of connection terminals (A). The equipment further comprises an information transmission member () carried by the tachometer stator () and suitable for co-operating with a complementary information transmission member () constrained to rotate with the wheel (). Said tachometer connector () includes additional connection terminals (B) to which said information transmission member () is connected for transmitting said information.

Wheel assembly equipped with a tachometer

An installation for measuring the pressure of at least one tire of a wheel of an aeroplane includes: at least a pressure measuring sensor associated with a tire; a unit operating on the pressure measurement provided in the aeroplane; and radio-frequency transmission elements including for the or each sensor, a revolving antenna borne by the wheel and connected to each measuring sensor and to a fixed antenna connected by a conductive cable to the unit operating on the pressure measurement. The fixed antenna is adapted to be borne by the aeroplane structure away from the or each wheel at least in an upper part of the shock strut of the landing gear bearing the wheel.

Growing community of inventors

Houilles, France

Jean-Clair Pradier