Safran Electronics & Defense

Sagem Defense Securite

Benoit Cremiere

Oleg Gomolko

Pascal Coppee

Cedric Bara

Daniel Bezanere

Manuel Amaral

Cédric Bara

The invention relates to an aircraft flight control column device () comprising: a casing () for attaching to an aircraft structure; an output shaft () for connecting to a flight control column (), the output shaft () being mounted such that it rotates in relation to the casing (); a primary group () comprising a first torque-generating body () for applying a first torque to the output shaft (); a secondary group () comprising a second torque-generating body () for applying a second torque to the output shaft (); and a clutch for selectively connecting the primary group () and the secondary group () to the output shaft ().

Aircraft flight control column device with force-feedback having an emergency group

The invention relates to a flight control device for an aircraft, including a connection lever, mechanical means for limiting an angular stroke of the connection lever, first means for generating force feedback on the connection lever about said pivot axis, second means for generating force feedback on the connection lever, which means are arranged in parallel with the first means, at least one element selected from the second means and the connection lever comprising mechanical means for connecting them together temporarily, which means are arranged to be active when the connection lever is moved beyond a predetermined angular position in the angular range so that the second means are connected to the connection lever.

Flight control device for an aircraft

An actuating device to displace a part of an empennage of a helicopter, including a first part including a first casing fixed to a frame of the helicopter, a first element mounted in rotation with respect to the first casing and a first motor the first element. A second part includes a second casing connected to the part of the empennage, a second element mounted in rotation with respect to the second casing and a second motor driving the second element. A connecting element connects the first part with the second part, being mobile in translation with respect to the first element. Rotation of the first element causes a translation of the connecting element, and is mobile in translation with respect to the second element. Rotation of the second element causes a translation of the connecting element with respect to the second element.

Actuating device for displacing a part of the empennage of a helicopter

An actuator device for actuating equipment has an electric motor arranged to be connected to an autopilot device and connected by a drivetrain to an outlet shaft, itself designed to be connected to a control instrument, the drivetrain incorporating stepdown gearing dividing the drivetrain into a high-speed segment beside the motor and a low-speed segment beside the outlet shaft. The high-speed segment comprising a deactivator member for deactivating the autopilot device. The deactivator member having a first element secured to a first portion of the high-speed segment; a second element secured to a second portion of the high-speed segment and connected to the first element to allow the first element to be angularly offset relative to the second element when a torque for transmission reaches a predetermined threshold; and a detector member for detecting the angular offset.

Growing community of inventors

Boulogne-Billancourt, France

Benoit Cremiere