Aircelle Limited

Sagem Defense Securite

Safran Nacelles

David Pereira

Hakim Maalioune

Laurence Lemains

Pierre Andre Baudu

Jérôme Piaton

Michel Dunand

Jean-François Weibel

Vincent Pierre Le Coq

Caroline Coat-Lenzotti

Jean Lamarre

Philippe Vancon

Manuel Sanchez

Pierre Baudu

The present invention relates to a method for commanding and controlling at least one resistive heating element () belonging to an aircraft turbojet engine nacelle deicing set, characterized in that it involves the steps aimed at: obtaining, from a central control unit () of the aircraft, parameters representative of the exterior flight conditions; determining a thermal model corresponding to the flight conditions obtained; as a function of the thermal model, delivering the appropriate corresponding electrical power () to the resistive heating element.

Method for controlling an electrical deicing system

The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source () and thus defining an assembly () of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

Electric de-icing device and related monitoring system

A lip assembly of a turbojet engine nacelle is equipped with at least one electric de-icing system. The lip assembly includes at least one electric heating member, electrically powered through at least one power conductor. Each power-supply conductor is associated with a neutral conductor or 'ground' arranged in a regrouped manner adjacent to a corresponding power-supply conductor.

Lip unit for an electrically deiced turbojet engine nacelle

The invention relates to a method for controlling a plurality of actuators () for a movable thrust reverser cowl (), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.

Method for synchronizing the actuators of a movable thrust reverser cowl

A nacelle for a turbojet engine includes an air inlet forward section, a median section surrounding a fan of the turbojet engine, an aft section equipped with a thrust reverser system, a power control unit able to convert a high voltage electric supply into an electric supply towards an electromechanical actuator, and a drive unit for the power control unit which is distinct and separate from the latter and has a control input and a drive output to be connected to the power control unit. The thrust reverser system includes a mobile cowl which, under action of an electromechanical actuator, is able to move from a closed position to an open position in which the mobile cowl opens a passage in the nacelle.

System for controlling the cowl of a turbojet engine nacelle thrust reverser

A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors.

Aircraft engine nacelle comprising a mobile cowl moved by electric motors

The present invention relates to an electric power supply circuit () for a turbojet engine nacelle including at least one electric generator () mechanically connected to the shaft of a turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit, characterized in that said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit, as well as to a nacelle including such an electric circuit.

Electric power supply circuit for a turbojet engine nacelle

The invention relates to a method and a device for controlling the power supply of at least one aircraft maintenance actuator () from an electrical power supply network () of the aircraft comprising means () for controlling the electrical power supply of at least one maintenance actuator, and means () for establishing communication between the control means and at least one control unit () allowing a user to control the operation of at least one actuator. The control means are designed to compare the state of at least one control unit with at least one reference state (SBR) and/or an abnormal state (SBE, SBE, SBE) for switching-on purposes, and to prohibit the activation of the actuator if the state of the control unit is different from a reference state (SBR) or corresponds.

Device and method for controlling the power supply of at least one aircraft maintenance actuator

The invention relates to a device () for controlling the maintenance actuators () of the cowlings of a turbojet engine nacelle of an aircraft, that comprises a first stage () to be connected to an electric power network () of the aircraft, at least one second power stage () including converters of a first DC voltage from the first stage () into a second DC voltage for powering at least one maintenance actuator () connected downstream from the device (), a control means () for the first and second stages (), and a means () for establishing a communication between the control means () and at least one control housing () so that a user can control the operation of the actuators, the control means being arranged so as to carry out switching operations between a first operation mode in which the second stage(s) () are powered, and a second standby mode in which the second stage(s) () are not powered by the first stage ().

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Limours, France

David Pereira