Safran Electronics & Defense

Safran Electrical & Power

Labinal, LLC

Labinal Power Systems

Aerospatiale Societe Nationale Industrielle

Airbus Operations (s.a.s.)

Airbus France

Societe Nationale Industrielle Et Aerospatiale

Airbus Corporation

Turbomeca

Airbus Operations Gmbh

Serge Thierry Roques

François Guillot

Philippe Pierre Avignon

Jean-Marc Blineau

Franck Albero

Arnaud Camille Ayme

Olivier Pujol

Francois Guillot

Nicolas Fanton

Gilles Tournier

Jean-Luc Ballenghien

Emmanuel Couturier

Sebastien Vieillard

Serge Berenger

Jean-Luc Biesse

Didier Laurent

Pascal Dauriac

Jerome Genoulaz

Sébastien Vieillard

Jérôme Genoulaz

Dominique Prost

Philippe Malaval

Francois Allaert

Pierre Faurie

Sylvain Segol

Nicolas Paris

Philippe Mallaval

An impact detection device includes an impact detector, a wireless communication device, an energy storage device, an autonomous electrical energy generation device, a device for receiving energy by radio frequency, the device being configured to adopt the following two modes: a first mode, referred to as autonomous mode, in which the autonomous electrical energy generation device is configured to supply the impact detector and the wireless communication device; a second mode, referred to as external mode, in which the device for receiving energy by radio frequency is configured to supply the impact detector and the wireless communication device.

Impact detection device, associated detection system and aircraft equipped with such a system

An autonomous impact detection device includes at least one impact detector; at least one wireless transmission device configured to transmit the information collected by the impact detector; at least one energy storage device configured to supply the impact detector and the wireless transmission device with energy; at least one Seebeck module configured to supply the storage device with energy when a temperature gradient is applied thereto; the wireless transmission device being configured to supply the storage device with energy when the temperature gradient to which the Seebeck module is exposed is not sufficient.

Device for detecting impacts, associated detection system and aircraft equipped with such a system

An aircraft comprising a fuselage () subdivided by a floor () into a top volume () and a bottom value () in which girders () extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings () that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units () are arranged in the lateral housings and each comprises a box () defining a main compartment containing calculation modules () insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors () carried by a back wall () of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

Aircraft having computers distributed in the fuselage

Electronic module comprising a protective casing defining an internal volume and an electronic board placed in the internal volume, the electronic module comprising: means, for detecting a predetermined environmental condition of the internal volume, means for generating a cool zone inside the internal volume, which means are arranged such that the cool zone is separated from the electronic board; a control unit that is linked to the means for detecting an environmental condition and to the means for generating a cool zone and arranged to trigger the means for generating a cool zone when the means for detecting a predetermined environmental condition in the internal volume detect an environmental condition that is liable to result in the moisture in the air contained in the internal volume condensing on the electronic board.

Electronic module with improved moisture protection

A system comprising a rack and at least one line replaceable module, the rack further comprising a primary transmission circuit comprising a primary antenna, primary emission components designed to generate an emitted power containing uplink data, and primary receiving components designed to receive downlink data, the line replaceable module comprising a secondary transmission circuit comprising a secondary antenna, secondary receiving components designed to receive the emitted power and the uplink data, and secondary emission components designed to generate the downlink data, the emitted power, the uplink data and the downlink data being transmitted via a shared coupling between the primary antenna and the secondary antenna.

System comprising a rack and a line replaceable module

An electrical power distribution assembly for an airplane, the assembly including an electric switch device for placing in a Karman fairing of the airplane.

Electrical power distribution assembly for an aircraft

An electronic unit comprising a box defining a reception compartment for receiving an electronic module along two mutually opposite directions of an insertion axis, the compartment including electrical power supply means for powering the electronic module and connection means for connecting the electronic unit to the electronic module, these means extending onto a connection face forming part of the reception compartment and extending parallel to the insertion axis. An electronic module for mounting in a compartment of an electronic unit of the invention.

Electronic unit with reversible modules

A cooling module including a first air inlet, a second air inlet, and an air discharge vent, the module having two check valves, each mounted in register with a respective inlet and arranged to allow air to pass towards the inside of the module and to oppose a flow of air in the opposite direction. An electronic unit including such a box.

Cooling module and electronic unit comprising such a module

A printed circuit board including at least one blind metal-plated hole, for receiving a pin of the printed circuit board being covered by a first layer of a protective film on which there extends a second layer of electrically insulating flexible material, the first layer and second layer are for piercing by the pins when they are engaged in the metal-plated holes, the first and second layers being for claming between a support of the pins and the printed circuit board. An electronic unit including such a device. A method of fabricating a printed circuit card for such a device.

Electronic device comprising a module connected to a PCB and electronic unit comprising such a device

The invention relates to an aircraft landing gear () comprising:&#x2014;a leg () having a first leg portion () that can be pivotably connected to a load-bearing structure of the aircraft () in order for the landing gear () to be deployed and retracted, and a second leg portion () that is rotatable in relation to the first leg portion ();&#x2014;a wheel () that is rotatable in relation to the second leg portion (), and an electric motor () that can rotate the wheel () in relation to the second leg portion ();&#x2014;a transmission mechanism () designed to selectively transmit torque generated by the electric motor () to the wheel () in order to rotate the wheel in relation to the second leg portion () or to the second leg portion () in order to rotate the second leg portion () in relation to the first leg portion ().

Aircraft landing gear

The invention relates to an aircraft landing gear () comprising: &#x2014;a leg () that can be pivotably connected to a load-bearing structure of the aircraft () in order for the landing gear () to be deployed and retracted; &#x2014;a wheel () that is rotatable in relation to the leg (), and an electric motor () that can rotate the wheel () in relation to the leg (); &#x2014;a transmission mechanism () designed to selectively transmit torque generated by the electric motor () to the wheel () in order to rotate the wheel in relation to the leg () or to the leg () in order to rotate the leg () in relation to the load-bearing structure of the aircraft () in order to deploy or retract the landing gear ().

An electrical connection member capable of detecting discontinuities in an electrical network is provided. The connection member includes a casing having at least three branches, each of the branches including, at the end of same, at least one terminal for electrical connection to a respective piece of equipment, and least one main conductor linking two terminals at the ends of two branches in the casing, at least one secondary conductor linking at least one terminal of the end of the third branch in the casing, and including an electrical coupler designed to inject an electrical test signal from the secondary conductor into the main conductor, and to transmit, to the secondary conductor, an electrical response signal generated by the reflection of the electrical test signal against a discontinuity encountered in the electrical network.

Electrical connector for detecting discontinuities in an electrical network

An electrical energy generator system for an aircraft, the system including a streamlined fairing containing at least one turbine housed in the front portion of the fairing, and an electrical energy generator connected to said turbine. The front portion of the fairing is fitted with air admission means that are movable between an open position in which the turbine is exposed to the stream of air outside the fairing and a closed position in which the turbine is masked inside the fairing. The system may serve to reduce the aerodynamic drag caused by turbulence present at a wing tip for a conventional wing having sharp edges during stages of takeoff, climbing, and cruising; and during stages of descent it makes it possible to recover the kinetic and potential energy that has been accumulated by the aircraft during its stages of climbing and cruising.

System for recovering and converting kinetic energy and potential energy as electrical energy for an aircraft

An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Device for electrically powering an aircraft on the ground

Connection between two elements of an electrical return circuit. The device comprises a female type connection receptacle fastened to a conductive structure and a male type plug connected to a cable, said plug including a groove, and a locking spring co-operating with the plug and with the receptacle.

Growing community of inventors

Cornebarrieu, France

Serge Thierry Roques