Safran Electronics & Defense

Yannick Attrazic

Mickael Werquin

Corentin Le Roux

Rémi-Louis Lawniczak

Pascal Coppee

Blaise Lapôtre

Corentin Leroux

Pascal Coppée

Julien Argenton

Xavier Marcel Adolphe Ferraud

A rotating electric machine includes a rotor and a wound stator. The wound stator has a stator shaft, wherein the stator coils are inserted in the rotor, and the stator shaft is inserted in the center of the rotor. At least one angular position sensor of the rotor is inserted in the center of the space delimited by the stator shaft and the rotor.

Rotating electric machine, force feedback mini-joystick and related aircraft

The invention relates to a force application device for a control stick of an aircraft, said control stick comprising a control lever that is connected to at least one motor comprising a drive shaft that can be rotated about an axis, the force application device comprising: a first pin connected to the shaft, a housing, an electromagnet, a movable actuator comprising a magnetic material, a coupling device comprising an input gear connected to the housing and an output gear comprising a second pin, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the output gear is positioned at a distance from the input gear, and a blocking configuration in which the electromagnet is inactive and the gears are meshed.

Force application device for a control stick of an aircraft

The present invention relates to a force application device for a control stick of an aircraft comprising a shaft and a control lever configured to rotate the shaft about a first axis, the device comprising: a magnetic brake comprising a braking part configured to be connected to the shaft, and a volume containing a rheological fluid in contact with the braking part, of variable shear resistance as a function of a magnetic field applied to the rheological fluid, a force feedback motor configured to exert a resistive force opposing the rotation of the shaft about the first axis, a motor power source, a movable magnetic element biased towards a position close to the magnetic brake, and distancing means configured to maintain the movable magnetic element in a position away from the magnetic brake, when such distancing means are powered by the power source.

Force application device for control stick in a power failure situation

The present invention relates to a force application device for a control stick of an aircraft, wherein the control stick comprises a control lever () rotating a shaft (A) about a first axis (A), the device comprising a magnetic brake () which comprises a magnetisable element () mounted on the shaft and a magnetic transmitter () which is opposite the magnetisable element and free to rotate about the first axis relative to the magnetisable element, the magnetic transmitter having an activated state in which the magnetic transmitter is supplied with current and generates a magnetic field in a volume occupied by the magnetisable element, and a deactivated state in which the magnetic transmitter is not supplied with current and does not generate a magnetic field, so as to prevent the magnetisable element from rotating about the shaft relative to the magnetic transmitter.

Force application device for a control stick

The invention relates to a force application device for an aircraft control stick comprising: &#x2014;a casing (), &#x2014;an electromagnet () mounted on the casing (), &#x2014;an actuator () mounted on the shaft (), the actuator () being mobile in translation in relation to the shaft () along the axis (A), the actuator () comprising a magnetic material, and &#x2014;a coupling device comprising an input gear () that is mounted so as to be stationary in relation to the casing () and an output gear () connected to the actuator () by means of an attachment part (), the attachment part () being configured so as to allow a limited angular displacement between the output gear () and the shaft () around the axis (A) and to allow the actuator () of the output gear () to translate along the axis (A).

Force application device for an aircraft control stick

The invention relates to a force application device for a control stick of an aircraft, said stick comprising a control lever that is connected to a motor comprising a drive shaft, said device having: a first pin connected to the drive shaft, a housing, a second pin secured to the housing, an electromagnet secured in relation to the housing, a movable actuator which comprises a magnetic material such that said actuator can be displaced depending on a supply of current of the electromagnet, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the actuator separates the teeth away from the first pin and the second pin, and a blocking configuration in which the electromagnet is inactive, with the first tooth and the second tooth coming into contact with the first pin and the second pin.

Growing community of inventors

Boulogne Billancourt, France

Yannick Attrazic