Airbus (sas)

Airbus Group Sas

Airbus Corporation

Airbus Operations Gmbh

Airbus Helicopters

Eads (european Aeronautic Defence and Space Company Eads France)

Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Eads Deutschland Gmbh

European Aeronautic Defence and Space Company Eads France

Eads

Eads France Sas

Emmanuel Joubert

Hichem Smaoui

Bruno Rechain

Benoit Ferran

Charles Nespoulous

Clément Dinel

Antonin Sanitas

Erwin Bayer

Jürgen Steinwandel

Alban Corpron

Michel Bermudez

Didier Esteyne

Thierry Pelegrin

Matthieu Sautreuil

Gilles Bezes

Nadine Dyrla

Benoît Ferran

Thibault Baldivia

Clément Veillerot

Hichem Smaou

Fabien Argillier

Laurent Juve

Germain Morin

A charging system for electrical accumulator vehicle batteries, comprising a charging station principally designed to generate a charging current for the batteries, a system for thermally conditioning the batteries, by the circulation of a heat transfer fluid. A vehicle-mounted segment comprises a component for measuring the battery temperatures, a system for measuring the state of charge of the batteries, and a heat transfer fluid distribution circuit. A non-vehicle-mounted segment comprises a ground module of the thermal conditioning system for generating a flux of a heat transfer fluid, a control-command module designed to determine, during charging, as a function of the states of charge of the batteries and the battery temperatures, the flow rates and temperatures of the heat transfer fluid and a charging current required to achieve a target final state, characterized by a target temperature and a target charge at the end of a given charging time.

Charging system for at least one accumulator battery of a vehicle including heat transfer fluid distribution for thermal conditioning of the battery and method for managing the recharging of said at least one battery

A method for managing a battery according to a state of health of the battery, comprising, prior to using the battery, predetermining a maximum depth of discharge profile according to the state of health of the battery, the profile being dependent on a technology of the battery, on a nominal energy level to be made available each time the battery is discharged, the nominal energy level being substantially constant over a service life of the battery. While using the battery, a maximum depth of discharge of the battery is adjusted at regular intervals, each time the state of health of the battery decreases by a percentage corresponding to an update interval p % that is equal to p/100, that is, for all state of health values (SOH) that are equal to SOH-n&#xd7;p %, where n is an integer comprised between 0 and 20/p.

Method for managing a battery according to its state of health

The vehicle receives batteries comprising cells arranged into at least one pack configured to be held in a vehicle structure, the pack being alternatively chosen from among at least one pack(P) and at least one pack(E) which are mechanically interchangeable and electrically substitutable. The pack(P) cells exhibit a maximum power density substantially higher than the pack(E) cells exhibit, and comprise cells exhibiting an energy density per unit mass substantially less than the pack(E) cells exhibit. The maximum electrical power of the pack(P) corresponds to the maximum electrical power needed to accomplish a first vehicle mission and the energy storage capacity of the pack(P) is at least sufficient to accomplish the first mission. The electrical energy storage capacity of the pack(E) corresponds to the electrical energy storage capacity needed to accomplish a second vehicle mission and the maximum electrical power is at least sufficient to accomplish the second mission.

Vehicle receiving a system for storing electrical energy

A method for managing unbalanced thrusts caused by engine failures in an aircraft provided with a distributed propulsion system, the distributed propulsion system including 2N powertrains (PTi), with N a strictly positive integer and i an integer lying between 1 and 2N inclusive, distributed symmetrically in relation to a plane of symmetry of the aircraft, according to which the power of at least one powertrain belonging to a first side of the plane of symmetry is reduced when a failure occurs in a powertrain belonging to the opposite side, such that the sum of the moments of the thrusts generated by the powertrains in relation to the center of gravity of the aircraft is nil, to within regulatory tolerances.

Method for managing imbalance in a distributed propulsion system

An electromechanical machine includes at least one coil made from a material that becomes electrically superconducting when its temperature is below a critical temperature. A functional part is contained in an internal volume of a thermally insulating and fluid-tight enclosure of the machine. A wall of the insulating enclosure is traversed in a fluid-tight fashion by at least one shaft for transmitting mechanical power between the functional part located in the internal volume of the insulating enclosure and a space outside the insulating enclosure. The functional part can be used as a heat sink, pre-cooled to maintain the temperature conditions for maintaining superconductivity inside the insulating enclosure.

Electrical machine with superconducting coils

A device for cooling at least one autonomous electric power source of an aircraft, includes: an inlet for air cooling a cooling fluid; the cooling fluid being fed towards at least one autonomous electric power source of the aircraft; a convergent hot air outlet, including moving elements for controlling the air flowrate; and supervision elements of the aircraft, which control the moving elements for controlling the air flowrate depending on the need for cooling of the autonomous electric power source. A method for cooling at least one autonomous electric power source of an aircraft and an aircraft including such a device are also described.

Device and method for cooling at least one autonomous electric power source of an aircraft

An electric propulsion assembly for an aircraft includes a nacelle having a nacelle cowl which defines an inner space for arranging an electric propulsion unit, which includes a blower, of the aircraft. An electric motor assembly is placed in the inner space and connected to the propulsion unit to supply power to the propulsion unit. An airflow generated by the blower flows in a space between the motor assembly and the nacelle cowl defining a duct to supply thrust to the aircraft. A power electronics system has at least one heat exchanger to transfer thermal energy from the system to a work fluid to cool the system. The heat exchanger is placed to project at least partially into the duct, so that the work fluid consists of the air flow generated by the blower.

Electric propulsion assembly for an aircraft

The aircraft () includes: at least one electric motor (); at least one stand-alone electrical power supply () supplying power to the electric motor; propulsion elements () referred to as 'auxiliary propulsion elements', included in the group including: a stand-alone electrical power supply () supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure () configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.

Aircraft and method of fitting out such an aircraft

A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.

Device for moving aircraft along the ground

A drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system. The electrical energy is provided at least in part by at least one device for recovering thermal energy from hot gases of an internal combustion engine of the aircraft.

Aircraft propulsion architecture integrating an energy recovery system

An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

Electrical power supply device for aircraft with electric propulsion

A combined rescue beacon and flight recorder device for an airplane is ejectable, buoyant and/or provided with flotation devices. The combined rescue beacon and flight recorder device comprises a frame provided with at least one outer side surface having a solar panel. The combined rescue beacon and flight recorder device is configured to be placed in a housing created in an airfoil element of the aircraft.

Combined rescue beacon and flight recorder device for an aircraft and aircraft provided with such a device

A method of controlling a group () of engines developing a necessary power (W) for driving a rotor (), said group () of engines having at least one electrical member (), electrical energy storage means (), and a first number n of engines () that is greater than or equal to two. A processor unit () executes instructions for evaluating a main condition as to whether the group of engines can develop the necessary power while resting one engine, and if so for resting one engine and accelerating a second number engines not at rest, and for causing the electrical member to operate in motor mode, if necessary, the electrical member operating temporarily in electricity generator mode when the storage means are discharged.

Method of controlling a group of engines, and an aircraft

A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850&#xb0; C. to 1100&#xb0; C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Growing community of inventors

Issy les Moulineaux, France

Emmanuel Joubert