Aircelle Limited

Safran Nacelles

Safran Electronics & Defense

Safran Landing Systems

Safran Aircraft Engines

Sagem Defense Securite

Hispano Suiza

Hakim Maalioune

Alain Nourrisson

Patrick Gonidec

Pierre Moradell-Casellas

David Pereira

Jérémy Edmond Fert

Christophe Bastide

Olivier Kerbler

Vincent Jean-François Peyron

Vincent Le-Coq

Vincent Hupin

Hervé Hurlin

Jean-Paul Rami

Corentin Hue

Julien Corbin

Yvon Joncour

Julien Hautecoeur

François Taillard

Vincent Pierre Le Coq

Thierry Marin Martinod

Alexandre Descamps

Caroline Coat-Lenzotti

Fernand Rodrigues

Guillermo Garcia Soto

Jean-Denis Sauzade

Marie-Laure De-Crescenzo

Jihane Bellahbib

Kambiz Tehrani

Laurent Christian Vincent Roger Miralles

Denis Jontef

Laurent Miralles

Jean-François Hammann

Alice Portalier

Julien Calmels

Ghaleb Hoblos

Maxime Pouyet

Jean-Michel Figuet

Djemouai Hadjidj

Fernand Rodriguez

Jean-Philippe Joignet

Moussa Bendjedia

Vincent Pierre Germain Le Coq

Rémi Billard

Vincent Rigolet

Matthieu Lerouvreur

Allice Portalier

Thierry Marin-Martinod

A system for managing the deceleration of an aircraft enabling the control in real time of the position of the aircraft on a braking axis, includes a braking system; a calculator configured to: calculate, from aircraft data and from external data, a sequence of use of the braking system intended to brake the aircraft over a predetermined braking distance which associates a predetermined position on the braking axis with each braking instant; update in real time the sequence of use as a function of the difference between the position of the aircraft and the predetermined position; and a controller configured to control the braking system as a function of the sequence of use.

System for managing the deceleration of an aircraft on a runway on the ground and associated method

Aircraft having at least one propulsion unit supplied with hydrogen by at least one hydrogen tank, and having at least one thrust reversal system including at least one actuator. The aircraft can include at least one means for storing or transporting the residual hydrogen of the propulsion unit, a fuel cell disposed in the hydrogen power source and supplied with hydrogen by the at least one means for storing the residual hydrogen, and a hydrogen thrust reverser actuation system. The thrust reverser actuation system can include a hydrogen thrust reverser actuation controller and a hydrogen primary power unit with a fuel cell supplied with hydrogen and powering the at least one thrust reverser actuator.

Aircraft assembly fitted with at least one hydrogen-powered thrust reverser actuation system

This system () for controlling an aircraft thrust reversal means comprises a reverse idle control means (), a first detection means () configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means () configured to activate the thrust reversal means when the first detection means () detects a condition for activation of the thrust reversal means. It further comprises a second detection means () configured to detect a condition for activation of the reverse idle control, the control means () being configured to activate the reverse idle control when the second detection means () detects a condition for activating the reverse idle control.

System for controlling an aircraft thrust reversal means

An electrical control system intended for an aircraft turbojet engine nacelle includes two control modules of a single power module controlling an electric machine and an approval module linking each of the control modules to the single power module. The approval module selectively authorizes the control of the single power module by one of the control modules.

High availability electrical switcher: monitoring of a simplex actuation chain by a redundant control

An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

Aircraft control architecture, of at least one actuator of a nacelle movable cowl

A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

Method for supplying electric power to an ultrasonic nacelle de-icing and anti-icing

A testability method for the in-flight testing of an operating state of an electronic power chain having at least one power converter intended for driving an electric motor that actuates at least one aircraft component includes controlling actuation of the converter, transmitting a test signal, collecting at least one measurement signal, and determining an operating state.

Testability method for an electronic power chain associated with an electric motor

An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

Device for actuating a thrust reverser with an anti-deployment member

The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

Method and system for controlling the braking of an aircraft equipped with a thrust-reversal system

A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

Variable-section nozzle, and aircraft turbojet engine nacelle equipped with such a nozzle

A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

Thrust-reversal device for an aircraft including at least two thrust reversers

A control system for a thrust reverser with a movable cowl includes an electromechanical actuator to actuate the movable cowl, an electric drive unit (M) driving the actuator, and a power control unit capable of controlling the electric drive unit (M). The power control unit moves the movable cowl to a closed position and/or to a deployed position. In particular, the control system includes an electronic circuit for electric braking capable of braking the electric drive unit (M), in case of overspeed of the drive unit when the movable cowl is moved to the closed position and/or to the deployed position.

Thrust reverser control system

The invention relates to a control system for at least one actuator () for the cowlings of a thrust inverter in a turbojet engine, that comprises an assembly of actuation and/or control components. A control means () is provided for detecting the failure of an actuation and/or control component (), for determining the blocking or non-blocking character of the failure for the system operation and, in case of a non-blocking failure, for switching from a nominal operation mode to a failure-adaptation operation mode in which the failure of the actuation and/or control component () is compensated at least partially by a modified instruction of the other actuation and/or control components ().

Method and system for controlling at least one actuator of the cowlings of a turbojet engine thrust inverter

The invention relates to a system () for controlling an aircraft propelled by at least one jet engine housed in a nacelle, characterised in that said system includes: a full authority electronic control unit () of the jet engine, intended for monitoring the jet engine, suitable for monitoring and controlling at least one electrical device of the nacelle; and an electric power unit () of the nacelle, external to said full authority electronic control unit of the jet engine for monitoring the jet engine, suitable for managing the electric power supply of said electrical device of the nacelle.

Aircraft control system

The invention relates to a system for controlling a plurality of actuators () that can displace a mobile panel () pertaining to a nacelle () of an aircraft, said system comprising at least two motors () that can drive the actuators (). The system also comprises two separate control units (), each unit being configured in such a way as to control and feed at least one motor that is not fed or controlled by the other control unit. The invention also relates to a nacelle comprising such a system.

Control system for a turboreactor nacelle

Growing community of inventors

Orgeval, France

Hakim Maalioune