Safran Nacelles

Societe Hispano Suiza

Aircelle Limited

Societe Hispano Suiza Aerostructures

Hispano Suiza Aerostructures

Hurel Hispano Le-havre

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Safran Landing Systems

Ateca

Herakles

Patrick Gonidec

Guy Bernard Vauchel

Pascal Gerard Rouyer

Pierre Andre Baudu

Olivier Kerbler

Pierre Caruel

Patrick Boileau

Jean-Paul Rami

Hakim Maalioune

Bertrand Desjoyeaux

Eric Conete

Laurent Georges Valleroy

Marc Versaevel

Vincent Peyron

Pierre Moradell-Casellas

Vincent Joseph Studer

Jean Fabrice Portal

Bernard Guy Vauchel

Alexandre Phi

Nicolas Dezeustre

Osmin Regis Delverdier

Philippe Jean Vie

Alexandre Bellanger

Jean-Nicolas Bouchout

Loïc Grall

Xavier Bouteiller

Corentin Hue

François Taillard

Eric Lecossais

Loïc Chapelain

Sarah Tissot

Laurent Albert Blin

Bernard Vauchel Guy

Gerard Pascal Rouyer

Georges Alain Bouret

Emmanuel Drevon

Guillaume Ruckert

Olivier Gilo

Virginie Emmanuelle Anne-Marie Digeos

Paul Ferrey

Jean-Baptiste Goulard

Jacques Michel Julliard

Georges Jean Riou

Franck Zaganelli

Philippe Avenel

Loic Chapelain

Matthieu Vanderlinden

Denis Jontef

Fabrice Henri Emile Metezeau

Faycel Bouabdallah

Gerard Rouyer Pascal

Arnaud Carles-Espiteau

Rémi Billard

Xavier Carcenac

Vincent Lefeuvre

Stephane Tirel

Gerard Clere

Albin Lafont

Stuart Hardyman

Marie-Laure De-Crescenzo

François Pierre Clément Grigis

Vincent Rigolet

Jean-Denis Sauzade

Pascal-G&eacute;rard Rouyer

Pascal G&eacute;rard Rouyer

Jean Adam Roger Treger

Pierre Andr&eacute; Marcel Baudu

Pierre André Marcel Baudu

Renaud Barreteau

Pierre Moradell-Casallas

Thierry Jacques Le Docte

Jean-François Hammann

Bernard Louis Le Barazer

Nicolas Bouchout

Pascal Gérard Rouyer

An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.

Reinforced acoustic treatment panel for an aircraft propulsion unit

A door for a thrust reverser of a propulsion assembly, the door being provided with a flexible baffle. The baffle is configured to change state by moving from a folded position to an unfolded position, and vice versa, depending on the configuration of the reverser. When the reverser is in reverse jet configuration, the door is open and the baffle is in an unfolded position in order to direct a flow of gas upstream of the propulsion assembly, thus generating a counter-thrust. When the reverser is in direct jet configuration, the door is closed and the baffle is in a folded position so as to cancel or minimise interference caused by the baffle in the flow of gas passing through the propulsion assembly and thus generating a thrust.

Door for thrust reverser of an aircraft propulsion assembly, comprising a flexible baffle

A thrust reverser including doors and at least one flexible deflector obstructing a lateral opening of the thrust reverser when the doors are open. Such a deflector allows better controlling the airflows in thrust reverser configuration and maximizing the counter-thrust force.

Thrust reverser comprising doors and at least one retractable deflector for closing a lateral opening

A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising:

Propulsive assembly, in particular for an aircraft, for protection against an unbalance force and method of protection

The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

Device and method for data communication in an aircraft subassembly

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

An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

Membrane thrust inverter for an aircraft propulsion unit

A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.

Turbine engine nacelle comprising a cooling device

The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.

Acoustic attenuation structure with a plurality of attenuation degrees for a propulsion assembly of an aircraft

A pod for a turbojet engine includes an outer cowl having a structure with at least one opening and a panel pivotably mounted about an axis between a closed position and an open position, and a system for actuating the panel designed to lock the panel in closed position and to move same between the closed position and the open position thereof. The actuation system includes a lateral connecting rod connected to the panel and to the structure, pivoting relative to the structure about a first pivoting axis and about a second pivoting axis, and a linear actuator attached to the lateral connecting rod. The actuator system is designed to move the lateral connecting rod during the extension of the actuator, and the lateral connecting rod exerts a force on the panel during the movement thereof, pivoting the panel about the axis thereof.

System for actuating a panel of a turbojet engine nacelle

The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.

Aircraft turbojet engine nacelle

A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

Turbine engine nacelle fitted with a heat exchanger

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

The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

Nacelle for a turbojet engine with a variable nozzle

The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.

Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors

Growing community of inventors

Montivilliers, France

Patrick Gonidec