Ratier-figeac Sas

Ratier Figeac

Hamilton Sundstrand Corporation

Bruno Seminel

Paul A Carvalho

David P Nagle

Frédéric Vermande

Arnaud Andrzejewski

Cedric Antraygue

Pascal Amat

Christian Fages

Hélène Bergonnier

Stanislas Tutaj

Jean De La Bardonnie

Patrick Moles

Adil Sardi

Arnaud Delpeuch

Stéphane Grimal

Catherine Delmas

Stephane Andrieu

Bruno Petallaz

A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position and a disengaged position A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold. Each of the contact surfaces comprises one or more grooves, wherein at least one rotatable member is disposed in at least one of said grooves.

Torque limiter

A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.

Multi-layer braided article

An actuator assembly may comprise a screw shaft having a shaft axis; a drive arrangement pivotally supported about the screw shaft axis for driving the screw shaft, e.g., about the shaft axis or along the shaft axis, and a rod mounted to the drive arrangement at a location off the shaft axis for providing a primary function of reacting torque about the shaft axis on the drive arrangement. The rod may comprise a rod axis and provide a load path along the rod axis for reacting torque. The rod may also comprise a device for which provides a secondary function for the actuator assembly based on the load experienced along the load path provided by the rod.

Actuator assembly

An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.

Cockpit inceptor system

A torque limiter device includes an input shaft having a first contact surface and an output shaft having a second contact surface. The input and output shafts are operable in an engaged position wherein the contact surfaces are brought into mechanical engagement, and a disengaged position wherein the contact surfaces are separated. A biasing mechanism provides a bias force that mechanically biases the input and output shafts in one of the positions and sets a threshold torque. An electromagnet is arranged to selectively provide an electromagnetic force that opposes the bias force when an activation current is supplied. A rotation sensor arrangement measures a respective rotation of the input shaft and of the output shaft. A controller determines a difference in rotations of the shafts and selectively supply the activation current to the electromagnet so as to disengage the input and output shafts when the rotation difference exceeds a threshold.

A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.

Propeller blade arrangement

A method of manufacturing a spar for a propeller blade comprises forming a hollow inner core from a composite material, and then braiding carbon fibres around the inner core to form an outer spar structure. The hollow inner core may be formed using an inflatable bladder and a mould defining an outer shape of the spar. This construction avoids the need for a foam core to be provided within the spar.

Propeller blade spar

A gas distribution assembly for providing gas to an actuator for opening an aircraft door and to an aircraft evacuation slide, the assembly comprising a single common gas supply and valve means for controlling distribution of gas from the common supply between the slide and the door actuator based on door opening position.

Gas supply assembly for aircraft door actuator and evacuation system

A rotating system comprising two or more bladesmounted on a hub installed on a rotatable propeller shaft, each blade provided with a respective sensorarranged to detect response of the respective blade to harmonic excitation; and the system further comprising means configured to compare the response of the respective blade to that of the other blade(s).

Blade structure health monitoring system

There is provided a system comprising a brushless DC ('BLDC') electric motor for a propeller engine and a motor controller. The motor comprises a rotor including one or more permanent magnets and one or more alternator windings, and a stator including one or more stator windings. The controller is configured to apply a first, transient DC voltage to the windings of the stator, wherein the first, transient DC voltage is configured to provide commutation switching for the windings of the stator so as to generate a torque on the rotor. The controller is further configured to apply a second, static DC voltage to the windings of the stator, wherein the second, static DC voltage is configured to induce an electric current in the alternator windings so as to generate an AC voltage in the alternator windings.

Electric motor for a propeller engine

The system of the present disclosure provides two or more sensors located on two parallel transmission or kinematic paths having different ratios with respect to the actuator position. Each sensor provides a different position measurement output and the difference between the sensor outputs provides a reduced indication of the position of the actuator/moved component. Integrating sensors in the reduction path avoids the need for the reduction gear mechanism.

Actuator position sensor mechanism

A system for providing pressure/load control at an end stroke stop is provided. The system includes an actuator housing having an end stroke stop and a first actuator housing side, an actuator piston provided in the actuator housing, wherein the actuator piston is movable along a longitudinal axis (A), the actuator piston having a first piston portion perpendicular to the longitudinal axis (A), and means for regulating the pressure/load control at the end stroke stop provided in the first piston portion, wherein the means for regulating the pressure/load control at the end stroke stop is configured to move from a closed position to an open position when in contact with the first actuator housing side.

Hydraulic actuator end stroke stop pressure/load control

A tank that may be used in combination with an actuating means such as a pneumatic door actuator includes a first, inner, enclosure positioned and enclosed within a second, outer, enclosure, to provide an enclosed chamber between the inner enclosure and outer enclosure. The pressure in the chamber may be measured with a gauge that does not extend into the inner enclosure. The measured pressure may then be monitored and compared in order to detect a change in pressure and thereby also detect a leak through a wall from the inner enclosure. The tank may also be used to inflate and/or deploy an emergency evacuation slide in an aircraft.

Fail-safe tank with integrated sensor and methods for detecting a leak in a wall of the tank

A propeller component, for example a propeller blade airfoil, includes an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.

Growing community of inventors

Figeac, France

Bruno Seminel