Labinal Power Systems

Aircelle Limited

Safran Helicopter Engines

Safran Electrical & Power

Turbomeca

Universite Dé Lorraine

Hispano Suiza

Safran Power Units

Sagem Defense Securite

Messier-bugatti-dowty

Microturbo

Sebastien Vieillard

Serge Thierry Roques

Olivier Bedrine

Gilles Le Gouellec

Michel Philippe Dehu

Eric Lecossais

Serge Berenger

Fabien Silet

Farid Meibody-Tabar

Fabrice Henri Emile Metezeau

Serge Lionel Pierfederici

Regis Meuret

Babak Nahid-Mobarakeh

Pascal Dauriac

Charif Karimi

Julien Rambaud

Loïc Le Duigou

Guilhem Lejeune

Christian Sarrat

Pierre Magne

Laurent Bernard Brosson

Serge Pierfederici

Marc Henri Pontrucher

Loic Le Duigou

A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Method and configuration for an auxiliary power engine to deliver propulsive and/or non-propulsive energy in a helicopter architecture

A method of stabilizing a DC electricity network, the network including a DC voltage source powering electrical loads that are connected in parallel to terminals of the voltage source and each of which is to receive a current or voltage setpoint. The method stabilizes the network by regulating setpoints applied to the loads by a virtual stabilization impedance generated at terminals of each load, the virtual impedances being dimensioned to stabilize the network in desired operating points and in given configurations of the network including a state in which at least one load is inactive or has failed and a state in which the stabilization of a load is inactive. Each virtual impedance is generated by a non-linear regulation loop acting on the setpoint for the corresponding load.

Stabilizing a DC electricity network

A device for supplying electrical power to an aircraft on the ground, including two electric generators driven by an auxiliary power unit. The first generator is connected by a connection/disconnection mechanism to an aircraft network and to an electric taxiing network, to supply either an AC voltage to the aircraft network when it is connected to the aircraft network, or an AC voltage or a power to the taxiing network when it is connected to the taxiing network. The second generator is connected by the connection/disconnection mechanism to the aircraft or taxiing networks to supply the AC voltage to one of those networks.

Device for supplying electrical power to an aircraft on the ground

An electrical control and power supply system for at least one helicopter motor/generator, the system including a first DC/AC converter selectively delivering AC electrical power to the at least one motor/generator, depending on respective positions of contactors of a connection matrix actuated from an electronic control circuit, the first DC/AC converter powered with DC by a DC power supply device that includes either a circuit for rectifying an AC voltage delivered via a contactor by a starter/generator of an APU, or a voltage booster DC/DC converter powered from a battery via a contactor. The connection matrix further includes a contactor connecting the first DC/AC converter in parallel with the second DC/AC converter to make it possible, once at least one of the motors/generators has started, to inject additional power from the starter/generator of the APU.

Control and power supply system for helicopter turbine engines

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

A method and architecture processing electrical energy regenerated from an aircraft, to address drawbacks posed by customary solutions for dissipating low energy of resistors, conventionally ceramics, which require a significant volume of ceramic and an additional power converter. The method and architecture return energy to an electric generator to convert the energy into mechanical energy. The architecture includes a reversible electric generator, driven by a thermal machine and configured to deliver an AC voltage, electric actuators, and a voltage converter circuit with multiple links. The circuit includes AC voltage rectifiers for voltage originating from the generator and power converters arranged on the multiple links to drive as many electric actuators. The converter circuit also includes a mechanism for electrical energy inverse transmission applied to the generator operating in a motor mode.

Method and architecture for processing electrical energy regenerated from an aircraft

The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterized in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor.

Method for controlling electric motors of a thrust reverser

A permanent magnet synchronous machine (PMSM) includes a stator and rotor powered by an inverter. A device to control the PMSM includes a sensor to sample a measurement &#x3b8;of the position of the rotor, a control unit to control an operating point of the PMSM according to the position of the rotor and settings, and an estimation unit to determine an estimate {circumflex over (&#x3b8;)} of the rotor position. The device also includes a malfunction detector to detect a malfunction of the sensor and a switch to connect the control unit to the sensor so that the control unit receives the measured position &#x3b8;of the rotor while the malfunction detector does not indicate any sensor malfunction, and otherwise to connect the control unit to the estimation unit so that the control unit receives the estimated position {circumflex over (&#x3b8;)} of the rotor when the malfunction detector indicates a sensor malfunction.

Device for control of a PMSM

Growing community of inventors

La Chapelle Gauthier, France

Sebastien Vieillard