Sagem Defense Securite

Safran Electronics & Defense

Aircelle Limited

Jérôme Piaton

François Guillot

Pierre Andre Baudu

Badr Mansouri

David Pereira

Yann Vandenbaviere

Roland Casimir

Jean-François Weibel

Tony Fourmont

Guillaume Mercier

Alexandre Guyamier

Franck Delnaud

Bruno Tilly

Thierry Bessede

Bernard Rabret

Benjamin Daguse

Alberto Rossi

Geoffrey Beggiora

Arnaud Duyck

Guillaume Percheron

Matthieu Aubron

Bruno Andre

Kevin Brenugat

Bastien Cagnac

Pierre Baudu

Gaëtan Princay

Frédéric Marques

The invention relates to an electric machine comprising a rotor and a stator. The rotor () comprises a plurality of permanent magnets (), the stator comprises a plurality of coils suitable for being powered by an electric current and two Hall effect sensors () on supports (). The sensors are configured to detect a change in gradient of the normal component of a magnetic field generated by the permanent magnets (). The stator comprises a part () comprising —a first zone (), —a second zone (), and a third zone () extending from the first zone () up to the second zone (). The maximum radial thickness of the third zone () is less than the minimum radial thickness of the first zone and the second zone.

Electric machine with more precise measurement

The electric motor consists of a rotor fitted with permanent magnets and comprises a stator the armature of which is made up of two parts: a stack of laminations forming round teeth and a solid tube-shaped field frame made of a material of the stainless steel kind enveloping the said stack of laminations. This armature constitutes a non-disengageable braking system that produces a damping effect in the face of possible movements of its rotor which are brought about and/or imposed by the members with which it collaborates. This motor can be used for driving a roto-linear actuator device with satellite rollers which is used as an actuator for maneuvering the control surfaces of an aircraft, for example an aileron.

Electric motor braking system for rotolinear actuator

A control system, in particular an aircraft flight control system, having a linkage with a force-transmission link (), the link having a body () having at least one end housing () slidably receiving a coupling rod () for coupling the link to an adjacent element of the linkage, the housing being closed by an elastically-deformable test member () through which the rod passes and that has an inner periphery fastened to the rod and an outer periphery fastened to a wall defining the end housing, and the end housing receiving at least one sensor () for sensing relative movement between the rod and the body.

Aircraft flight control system comprising a connecting rod provided with a sensor

Sensor for continuously measuring the angular position of a shaft rotatably mounted relative to a housing. The sensor includes a stator, a rotor attachable to the shaft, and permanent magnets having alternating polarities located on a stator or a rotor capable of creating magnetic induction during the rotation of the rotor. A magnetic circuit channels the magnetic induction such that it is proportional to a sinusoidal function of the angle of the rotor. At least two electric transducers having linear output, each angularly offset one from the other relative to the stator, are located in the gaps arranged in the circuit. The magnetic circuit is toothed and includes at least one measuring unit having three teeth per pair of magnets, each tooth including a gap with a transducer.

Angular position sensor and assembly comprising a rotary system and such a sensor

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

A damper circuit for damping a synchronous servo-motor having at least one winding, at least one main damper resistor, connection means for connecting the main damper resistor in series with the winding, and at least one additional damper cell including at least one additional damper resistor connected in parallel with the main damper resistor via a static switch connected to a control module for controlling the switch as a function of a voltage of the winding. The control module has a shunt in parallel with the main damper resistor. The shunt has an output connected to the control input of the switch and a divider bridge connected to the shunt to form a comparator between the voltage of the winding and a conduction voltage of the shunt.

Variable damping circuit for a synchronous servomotor

The actuator is of the roto-linear type and comprises a sleeve, a clevis and an operating rod which transmits the load. An electromagnetic sensor that measures and controls the load is placed inside the actuator, at the shoulder of the clevis. This sensor is associated with measurement means for processing the signals from the said winding, which winding are torus-shaped and arranged inside a field frame which is magnetically closed by an armature.

Actuator with load cell

Growing community of inventors

Paris, France

Jérôme Piaton