Airbus Helicopters

Ratier-figeac Sas

Hamilton Sundstrand Corporation

Thibaut Marger

Jean-Romain Bihel

Julien Lassalle

Romain Bouloc

Boris Grohmann

Pierre Estival

Clement Coic

Timothy Maver

Charles L DeGeorge

Pascal Leguay

Arnaud Groll

Pierre-Alex Picard

Gérard Couderc

Christophe Pujol

Jean-Christophe Labascoule

Gregory Giddings

Stephen J Bukowinski

François Pouly

Alexandre Pantaine

Louis Chauvet

Clément Coïc

Gerard Couderc

A pitch change actuation system for varying a propeller blade pitch includes: an actuator body defining an interior volume; and a chamber separator located within the interior volume of the actuator body and dividing the interior volume into a first chamber and a second chamber, the two chambers being fluidly separated by the chamber separator. The first and second chambers are configured to receive hydraulic fluid. The actuator body is configured to translate relative to the chamber separator in response to a difference in hydraulic pressure between the first chamber and second chamber; and the translation of the actuator body is configured to effect a change in propeller blade pitch.

Propeller blade pitch change actuation system

A system for controlling a propeller having a plurality of blades having a primary control system and a backup control system. The primary control system including a sensor responsive to a propeller state, and a controller connected to the sensor and to an electrohydraulic control actuator. The electrohydraulic control actuator is connected via a bypass valve to a hydraulic actuator that controls at least a blade angle of a blade of the propeller. The controller generating commands to the electrohydraulic control actuator based on at least the propeller state. The backup control system including a second controller, an electrohydraulic solenoid operably connected to the bypass valve. The backup control system is operable to hydraulically disable the primary control system via the bypass valve upon the occurrence of a selected condition, the second controller modulates the operation of the electrohydraulic solenoid to control the bypass actuator based on the propeller state.

Propeller blade angle closed loop control by solenoid modulation

An electromechanical actuator for electrical flight controls of an aircraft, the actuator comprising a transmission shaft, four electromechanical conversion members, each having a respective stator and rotor secured to the transmission shaft, and four control systems, each dedicated to respective ones of the electromechanical conversion members. The stator has teeth and windings surrounding at least one tooth, whereas the rotor is provided with permanent magnets. Each electromechanical conversion member is a flux-concentrating member and each winding is concentric and has a single layer. The electromechanical actuator is intended in particularly for controlling a hydraulic actuator via a mechanical transmission within an electrical flight control device of an aircraft.

Electromechanical actuator with stator teeth dimensioned to operate a saturation bend for electrical flight controls of an aircraft

There is provided an hydraulic actuation system for an aircraft, the hydraulic actuation system includes an actuator (A), a primary actuation arrangement to provide hydraulic fluid to control the actuator (A), wherein the hydraulic actuation system is configured to detect a fault in the actuator (A). The hydraulic actuation system also includes a secondary actuation arrangement to provide hydraulic fluid to control the actuator (A) in response to a detection of a fault in the actuator (A).

Hydraulic actuation system

A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

De-icing system and method

An actuator is disclosed comprising: a moveable member; a first hydraulic chamber in contact with a first surface of the moveable member; a second hydraulic chamber in contact with a second, opposing surface of the moveable member; a movable locking mechanism coupled to a moveable wall of the second hydraulic chamber; and a resilient biasing member acting on the moveable wall of the second hydraulic chamber so as to bias the moveable wall and locking mechanism. The actuator is configured to selectively vary the pressure in the second hydraulic chamber so that the resilient biasing member is able to bias the moveable wall to move, thereby moving the locking mechanism to engage the moveable member so as to prevent the movement of the moveable member towards at least one of the first and second hydraulic chambers.

Hydraulic actuator

Disclosed herein is a hydraulic actuator system comprising a servoactuator including a hydraulic actuator and a control valve, wherein the supply of hydraulic fluid to the servoactuator from a fluid supply is adjustable through a control system based on feedback information relating to the servoactuator. The hydraulic actuator system may e.g. be used for controlling blade pitch in a variable pitch propeller system such as may be found on a turboprop aircraft or a ship.

A servo-control having at least one movable cylinder that includes a hydraulic directional control valve. The hydraulic valve includes a control shaft that is rotatable about a longitudinal axis, the control shaft being connected to a distributor slide. The servo-control including a stationary abutment member secured to a cylinder and an input lever situated outside the cylinder. The input lever is connected to the control shaft and includes a stop portion arranged in the abutment member. The servo-control includes movement means for moving the input lever longitudinally, a first abutment surface of the abutment member limiting a travel amplitude of the stop portion when the input lever is in a first position.

Servo-control and an aircraft having such a servo-control

A pressure-balance valve for balancing the pressures of fluids admitted into the pressure-balance valve via respective second ducts. The pressure-balance valve has both a chamber for guiding movement in translation of a piston, and also fluid flow paths, each comprising a said second duct and a first duct for admitting a fluid coming from the same fluid source as the fluid flowing in its second duct. Each of the first ducts is provided with a shutter co-operating with a ramp arranged on the piston. Movement of the piston in translation as a result of a pressure difference between the fluids respectively admitted into the second ducts causes one of the shutters to slide along the corresponding ramp and consequently allows additional fluid to be delivered from a first duct to the second duct of the same fluid flow path.

Pressure-balance valve for balancing fluid feed to actuator cylinders of a servo-control for controlling rotor blades of a rotorcraft

A hydraulic valve (') of a servo-control for feathering the blades () of a rotorcraft rotor. The hydraulic valve (&#x2032;) comprises a main valve member () and an emergency valve member () blocked relative to a valve cylinder () of the hydraulic valve (&#x2032;) by means of a pin () in sliding thrust engagement in a cavity () of the emergency valve member (). Relative movement between the emergency valve member () and the valve cylinder () initiating sliding movement of the pin () inside the cavity () and causing mover means () for moving the pin () to be put into operation, thereby releasing the emergency valve member () to move freely.

Double hydraulic valve of a servo-control for feathering the blades of a rotorcraft rotor

A hydraulic system of an aircraft, the system comprising at least one servo-control, each servo-control comprising at least one cylinder together with a drive rod and a piston arranged in each cylinder. Between each cylinder of servo-control and the drive rod of that servo-control, at least one servo-control presents main sealing means with controlled leakage allowing a hydraulic fluid to leak out from the cylinder, the hydraulic system further comprising at least one enclosure, each cylinder of the servo-control being arranged inside the enclosure so that the fluid is collected in the enclosure.

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Beduer, France

Thibaut Marger