Societe Hispano Suiza Aerostructures

Societe Hispano Suiza

Aircelle Limited

Sagem Defense Securite

Hispano Suiza Aerostructures

Aircella

Pierre Andre Baudu

Guy Bernard Vauchel

Patrick Gonidec

Pascal Gerard Rouyer

Jean-Philippe Joret

David Pereira

Jérôme Piaton

Jean-François Weibel

Xavier Raymond Lore

Christophe Guenadou

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

This actuator for an aircraft engine nacelle mobile structure () comprises a motor () intended to be mounted on a fixed part of the said nacelle, an endless screw () able to be turned by this motor (), a slideway () intended to be connected to the said mobile structure () and comprising a nut () in mesh with the said endless screw, and a first ball end () allowing an angular offset between the axis of the said endless screw () and the said slideway (). This actuator is notable in that it comprises a sleeve () able to accommodate the said screw () and extending with clearance inside the said slideway (), the said nut () being mounted on that end of the said sleeve () that is closest to the said motor (), and the said first ball end being interposed between the other end of the said sleeve () and the said slideway ().

Actuator for an aircraft nacelle mobile structure, and nacelle comprising at least one such actuator

A thrust reverser for aircraft gas-turbine engines includes latch devices that display a tell-tale visible indication when thrust reverser shutters (doors, etc.) are ajar. A latch of the lock at least partly projects from a wall (13, 14) radially bounding the annular structure (12) of the thrust reverser (10) when the latch (37) is in the open mode.

Thrust reverser with lock-status display

A latching mechanism is disclosed for a jet engine thrust reverser having a thrust reverser door movably connected to an engine cowling with a reverse thrust opening, the thrust reverser door being movable between a forward thrust position, in which the thrust reverser door covers the reverse thrust opening, and a reverse thrust position, in which the reverse thrust opening is uncovered. The latching mechanism has a lock bar mounted on the thrust reverser door, the lock bar having a distal end, and a latch member pivotally located on the cowling, the latch member having a slot engaged by the distal end of the lock bar when the thrust reverser door is in the forward thrust position. The latch member is movable between a latched position, in which the latch member prevents disengagement of the distal end of the lock bar from the slot, so as to lock the thrust reverser door in the forward thrust position, and an unlatched position which permits disengagement of the distal end of the lock bar from the slot. The latching mechanism also includes a hook member connected to the cowling and located so as to engage the distal end of the lock bar upon relative movement between the cowling and the thrust reverser door away from each other in a direction generally parallel to a longitudinal axis of the cowling, such engagement preventing disengagement of the distal end of the lock bar from the slot and displacement of the thrust reverser door from the forward thrust position.

Latching mechanism for a jet engine thrust reverser door

A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having a plurality of lateral openings and a plurality of thrust reverser doors connected to the cowling so as to be movable between forward thrust positions and reverse thrust positions. The thrust reverser also includes a plurality of linear actuators, one linear actuator connected to the cowling and to each thrust reverser door so as to move the thrust reverser doors between their forward and reverse thrust positions. A synchronization system is included in the thrust reverser and interconnects two of the plurality of linear actuators, the synchronization system having an electric motor, a plurality of transmission drive links, each transmission drive link having one end connected to one of the two linear actuators and a second end, and a gear drive mechanism connecting the output of the electric motor to the second ends of the transmission drive links. Operation of the electric motor rotates the transmission drive links to operate the respective linear actuators to move the thrust reverser doors between their forward and reverse thrust positions. The gear drive mechanism and the connections between the transmission drive links and the linear actuators are such that, in the absence of rotation of the transmission drive links, operation of the linear actuators is prohibited, thereby locking the thrust reverser doors in their forward thrust positions.

Synchronizing control system for aircraft jet engine thrust reversers

A locking system is disclosed for an aircraft jet engine thrust reverser door that is movably connected to an engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the cowling having a reverse thrust opening that is covered by the thrust reverser door when in the forward thrust position and uncovered when the thrust reverser door is in the reverse thrust position. The locking system has a plurality of locking devices attached to the cowling at the forward side of the reverse thrust opening with at least one locking device located on opposite sides of a longitudinal line equidistantly spaced from opposite lateral sides of the thrust reverser door such that the locking devices simultaneously lock the thrust reverser door in the forward thrust position.

Locking system for an aircraft jet engine thrust reverser door including

An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort the annular thrust-reverser structure or to break its bracing components. An emergency locking system for such thrust reverser (35) each comprises a hinging latch (38) of which one end is in the form of a hook (40) partly enclosing the lock-interfacing mechanism (43) with the latch (38) being automatically biased into closing by an elastic arrangement (47). Such a configuration allows setting up additional mechanical connections which are able to compensate for any distortion of the thrust-reverser's annular structure or for any ruptured bracing component in the event of impact by an engine piece.

Thrust reverser with improved impact strength

A security hydraulic coupling system includes at least two hydraulic connector fittings (4, 5) which may be connected to adjacent fluid ports (1, 2) of a hydraulic unit (12) and which are linked to each other by means of a base plate (3) which is also shaped to cooperate with at least one projection (10) on the hydraulic unit (12) to thereby physically prescribe the positions of the various elements during the steps of fitting connection and disconnection. An interlock system comprises a security pin (6) which is housed in the base plate (3) and is mounted between the fittings (4, 5) and cooperates with grooves (7, 8) provided in the fittings (4, 5) to prescribe the possible sequence of steps in connecting/disconnecting the fittings (4, 5) from the ports of the hydraulic unit (12).

Hydraulic fittings for a hydraulic unit with a security connection system

A device for closing and locking the shutters of an aircraft thrust reverser includes a lock having a latch which is motorized so as to complete the closure of a shutter utilizing energy supplied by the motor, thereby relieving the jack which is the prime mover of the shutter. The device includes a stop which opposes the latch and interacts with a counter-stop so as to immobilize the shutter in the closed position and thus reduce vibration and flapping of the shutter.

Device for closing and locking the shutters of a thrust reverser

An actuating mechanism is disclosed for a thrust reverser of a turbojet engine having an engine cowling with a reverse thrust opening, a thrust reverser door pivotally connected to the engine cowling so as to pivot between forward and reverse thrust positions, and a linear actuator having a casing with an extendable and retractable piston rod. The piston rod is connected to the thrust reverser by a first connection forming a first connection point. An interface bracket is fixedly attached to the turbojet engine structure and engages a mounting flange in a connector affixed to the actuator casing at a second connection point, the mounting flange being in contact with the interface bracket at a third connection point, the first, second and third connection points lying in a straight line.

Pivoting door thrust reverser with actuating mechanism

An electric control system is disclosed for a turbojet engine thrust reverser having at least one movable component movable between a forward thrust position and a reverse thrust position, the control system having at least one electromechanical drive device mechanically connected to the moveable component such that actuation of the electromechanical drive device moves the component between the forward and reverse thrust positions, and an electronic control unit electrically connected to the electromechanical drive device and to a turbojet engine control system to transmit actuation signals to the electromechanical drive device to control the movement of the component between the forward and reverse thrust positions. The electronic control system preferably also has at least one electrically actuated locking device to hold the movable component in the forward thrust position.

Growing community of inventors

Le Havre, France

Pierre Andre Baudu