Airbus France

Airbus Operations (s.a.s.)

Aerospatiale Societe Nationale Industrielle

Centre National De La Recherche Scientifique

Airbus (sas)

Airbus Operations Gmbh

Airbus Operations Sl

Airbus Corporation

Technofan

Etienne Foch

Jean-Louis Lando

Xavier Roboam

Olivier Langlois

Didier Poirier

Lucien Prisse

Paul-Emile Roux

Michel Durandeau

Dominique Alejo

Pascal Maussion

Gaetan Bisson

Maria Pietrzak-David

Maurice Fadel

Guillaume Alix

Roger Bellego

Jan Barkowsky

Christophe Fleury

Emmanuelle Escorihuela

Jérôme Mavier

Christophe Lochot

Marcos Javier Chibrando

Xavier Chasseriaud

Sébastien Laclau

Franck Albero

Caroline Barnier

Nicolas Rapin

Marc Duces

Souhaib Boukaya

Nicolas Chauvet

Sébastien Vergnat

Sebastien Vergnat

A DC electrical network intended to supply electricity to an electrical load via an electric power source. A first pole of the electric power source is linked to first ends of two first electrical lines, second ends of which are linked to one another, and also to a first pole of the electrical load via two stages of a contactor. A second pole of the electric power source is linked to first ends of two second electrical lines, second ends of which are linked to one another, and also to a second pole of the electrical load via two other stages of the contactor. The electrical network further comprises a processing unit configured to control the contactor to open if current measurements correspond to currents flowing in opposite directions through the two first electrical lines or through the two second electrical lines.

DC electrical network

An aircraft including a first electrical distribution busbar and a second electrical distribution busbar extending at least in part in a fuselage of the aircraft, in a longitudinal direction of the fuselage. A first electric generator is connected to the distribution conductors of the first electrical distribution busbar via a first coupling switch directly connected to the first electric generator and to the distribution conductors of the first busbar. A second electric generator is connected to the distribution conductors of the second electrical distribution busbar via a second coupling switch directly connected to the second electric generator and to the distribution conductors of the second busbar. The first coupling switch and the second coupling switch are positioned in the aircraft independently of one another.

Aircraft comprising an electric power distribution network

A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

Method and system for controlling idle speed and drawing of power generated by an aircraft engine

A method for managing the offtake of power produced by an auxiliary power unit of an aircraft. The method comprises a step of calculating a maximum capacity for offtake of mechanical power that the auxiliary power unit can provide to the aircraft, a step of determining an actual offtake of mechanical power taken off by a first mechanical power offtake system of the auxiliary power unit, a step of comparing the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, a step of optimizing the offtake of mechanical power which step, based on the comparison of the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, determines at least one corrective action. A device for managing the offtake of power produced by an auxiliary power unit of an aircraft and an aircraft including such a device are provided.

Method and device for managing the offtake of power produced by an auxiliary power unit of an aircraft and aircraft equipped with said power offtake management device

The invention concerns an aircraft comprising a reversible rotary electrical machine), a wheel () for imparting movement to a stream of air, linked to said machine (), a first ventilation duct () configured to supply said wheel () with air, an electricity distribution network (), a reversible power converter () connected to said machine () and to said network (), and a control circuit () configured to control said converter () for, in a motor operating mode of said machine (), taking a supply current from said network () to supply said machine () and drive said wheel (), and, in an alternator operating mode of said machine (), in which a stream of air flows in said first ventilation duct () and imparts movement to said wheel (), to provide supply power to said network () which is generated by said machine () driven by said wheel ().

Aircraft comprising a reversible rotary electrical machine

A device and a method for emergency electricity supply on board an aircraft, able to supply a part of the aircraft's electrical power circuit. The device includes a synchronous machine with separate excitation, associated with a flywheel, and an auxiliary device to set the flywheel in rotation and to maintain rotation of the flywheel.

Device and method for emergency electricity supply on board an aircraft

A system for electrical generation, conversion, distribution and starting on board an aircraft, of 'bleedless' type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of 'bleedless' type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines.

System for electrical generation, conversion, distribution, and starting on board an aircraft

The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics () and means of connecting these at least two power supply electronics to at least two user systems (), characterised in that these connecting means comprise a network of connecting contactors () from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

System and method for supplying power to user systems onboard an aircraft

The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (and), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (and) which supply power loads and at least one master box () devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

System and method for supplying power for actuators on board an aircraft

A system and a power supply method, on board an aircraft, in which the power supply system of an aircraft includes several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aircraft are connected to each of these cores. Each core includes an input driver, several identical power modules, means of placing in parallel several power modules including interconnection inductances between power modules, and a switching matrix including a set of relays, means of piloting the relays of the switching matrix, so as to reconfigure all of these relays in the case of failure of a power module, several output filters, and relays of the switching matrix that may each be connected to at one load.

Power supply system and method on board an aircraft

This invention relates to a device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft, including a multi-phased starter-generator, a multi-phased transformer-rectifier unit, a multi-phased DC-AC converter, a multi-phased rectifier unit, and at least one three-phase inverter, wherein the number of phases is equal to or greater than 5.

Device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft

A power system including at least two self-controlled synchronous machines operating in parallel synchronously, a central three-phase converter to which all these machines are connected in parallel, at least two rotor position sensors. The system also includes at least one control module that receives phase currents from each synchronous machine, signals output from position sensors, and a required reference torque value and that powers the three-phase central converter so as to slave the phase currents for each machine as a function of the required reference torque.

Power system comprising several synchronous machines synchronously self-controlled by a converter and control method for such a system

The invention relates to a device for protection against overcurrents in an electrical energy distribution cabinet which receives electrical energy supplied by at least one generator and which distributes this energy to at least two loads, which comprises:

Device and method for protection against overcurrents in an electrical energy distribution cabinet

This invention relates to a system for controlling several actuators (Al, . . . , Anr), comprising at least two computers (L, L, . . . , Lk) and at least two means (C, C, . . . , Cn) of controlling at least one actuator, each control module being capable of controlling at least one actuator through at least one first connection () and being capable of receiving information about this at least one actuator through at least one second connection (), in which each control module is connected to at least two computers through at least two first communication buses ().

Control system and process for several actuators

According to the invention, the common control device ( ) for the power and interconnection contactors ( ) is a programmable computer operating according to a truth table, without prior checking of the state of said contactors, and, with each interconnection contactor ( ) there is associated a device ( ) able to prevent the closure of said contactor if its contact terminals ( ) are simultaneously energized.

Growing community of inventors

Toulouse, France

Etienne Foch