Sagem Defense Securite

Aircelle Limited

Jean-François Weibel

François Guillot

Etienne Merlet

Pierre Andre Baudu

Philippe Elie

Jean-Eric Besold

David Pereira

Jérôme Piaton

Roland Casimir

Alexandre Guyamier

Daniel Hors

Pascal Nauroy

Marc Pontrucher

Van Lam Nguyen

Arnaud Boucaud

David Wong

Sébastien Magnan

Philippe Gouze

Francis Lepore

Pierre Baudu

Sebastien Magnan

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

An assembly having actuators and an electricity power supply system. The assembly includes an input unit connecting the actuators to a three-phase AC electricity network and to a control system. The input unit includes a transformation member arranged to transform the AC into DC at high voltage and connected to a bidirectional power line having connected in series therewith at least one protective switch, a communications interface, and at least one of the actuators. The communications interface is arranged and connected to a central unit to exchange signals over the power line with a signal communications interface of at least one of the actuators. The input unit also includes a charger/discharger unit that connects an energy store to the power line.

Assembly of actuators and of a system for supplying electrical power from a network

A power supply and control device for a plurality of electric actuators, the device comprising a control circuit and a power circuit, the power circuit having an inverter module connected to a switch module provided with connection means for connection to the actuators, the control circuit being connected to the switch module to operate it so as to connect the actuators sequentially to the inverter module, wherein the control circuit is arranged to control the inverter module and the switch module sequentially, and wherein the control circuit includes a monitoring module arranged to detect a malfunction of the device. An actuator assembly comprising a plurality of actuators and such a power supply and control device, and an aircraft including a plurality of actuators and such a power supply and control device of the above-specified type.

Power supply and control device for actuators, corresponding acutation assembly, and aircraft comprising such a device

The invention relates to a rotolinear actuator that comprises: a central rod having an outer thread and surrounded by a ring with an inner thread, and threaded satellite rollers distributed between the central rod and the outer ring engaged with the threaded faces thereof. The actuator includes means for dispensing by capillarity a liquid lubricant at least one contact area of at least one satellite roller with the central rod and with the outer ring, wherein the lubricant is economically dispensed by capillarity in an amount that is just sufficient and precisely at the contact locations of the interacting members, from a tank that may be sufficient for the lifetime of the actuator.

Rotolinear actuator with satellite rollers

A control device () for controlling on-board equipment has a mount () having hinged thereto at least one drive lever () movable between two extreme positions, and also including a magnetic friction member () connected to the lever () and opposing resistance to movement thereof.

Device for controlling an on-board apparatus

The invention relates to a method for monitoring the output of an electromechanical actuator of the rotary-linear type in order to detect a gradual seizing thereof, wherein said method comprises: measuring the intensity, representative of the motor torque, of the electrical current powering an induction winding of the actuator and the axial stress undergone by an actuator rod; calculating the ratio (axial stress undergone by an actuator rod/motor torque) representative of the global output of the actuator and of its present state; and generating an evaluation of the present condition of the actuator based on its present state and optionally on previous stored states and on outer parameters.

Method for monitoring the output of an electromechanical actuator of the rotary-linear type

Growing community of inventors

Paris, France

Jean-François Weibel