Sagem Defense Securite

Safran Electronics & Defense

Sagem Sa

Etienne Merlet

Jean-Eric Besold

Oleg Gomolko

Jean Thierry Audren

Herve Gorecki

Hafid Elabellaoui

Sebastien Pautard

David Engler

Fabrice Jean

Florence Buoy

Jérôme Meleard

Charles Mangeot

Jean-Marie Courteille

Yann Vandenbaviere

Jean-François Weibel

Thierry Cartry

Bertrand Sevagen

Nicolas Ravoux

Christian Gouard

Guillaume Pointel

Sébasiten Pautard

Sebastien Fontaine

Julie Rafaitin

Mickael Magalhaes

Didier Habert

Christian Cardoso

Hervé Gorecki

Mickaël Magalhaes

Laurent Desroches

Yannick Baudet

Zakaraya Imounssi

Sébastien Fontaine

Sébastien Pautard

A mechanical transmission device having a planet carrier and at least two planets mounted on the planet carrier by means of respective rotation shafts. The device includes a stop for stopping movement of the various rotation shafts in axial translation.

Mechanical transmission device

The invention provides a pendulum system including a pendulum connected to a connector, the system including wires connecting the pendulum to the connector, which wires are connected together in a twisted cable, the twisted cable presenting a spiral central portion generally shaped as a cone having its apex connected to the connector so as to be the portion of the spiral that is closest to the pivot point of the pendulum. The invention also provides a method of fabricating such a pendulum system.

Pendulum system

An actuator for hinging a first element to a second element about a first pivot axis (A), the actuator comprising a motor-drive device, a first mounting plate () connected to a body () of the motor-drive device, a second mounting plate () connected to the second element, the second mounting plate being mounted in the first mounting plate in order to pivot about the first axis, and a bush () mounted in the second mounting plate to pivot about a second axis (A) perpendicular to the first axis. The motor-drive device has an outlet shaft () pivotable about a third axis (A) perpendicular to the first axis and intersecting the first axis, and it is extended by a pin () that is pivotally received in the bush and that has a central axis (A) intersecting the first axis and the third axis, and forming an acute angle with the third axis. An aircraft guidance assembly including such an actuator.

Actuator for flight control surface

An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position.

Aircraft throttle control device including a cam coupling

An electronics module comprising a box including at least one pair of slideways to define a housing for receiving an electronics card, the slideways being fastened to two opposite faces of the box that are provided with ventilation means arranged to establish a flow of a total stream of air between the two faces. According to the invention, the electronics module includes at least one screen arranged in the housing between one of the slideways and the associated electronics card in order to define a passage for an individual stream of air in the housing.

Electronic module, guide rail of such a module and circuit board intended to be slotted into such a module

An aeroengine control device comprising a mount, having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel, each lever being movable between a rest position and a maximum actuation position, the secondary lever being mounted to pivot on the main lever. A connecting rod connects the secondary lever in permanent manner to the code wheel and the main lever is provided with a connection member arranged to co-operate with a portion in relief secured to the code wheel and with a portion in relief secured to the mount in such a manner that the connection member attaches to the code wheel when the main lever is moved while the secondary lever is in its rest position and attaches to the mount, thereby releasing the code wheel to turn, when the secondary lever is moved while the main lever is in its rest position, while movement of either lever is prevented when the other lever is away from its rest position.

Aircraft throttle control device including an engaging roller coupling

The invention relates to a joystick () for controlling an aircraft, including a frame (), a lever (), a mechanical linking assembly () for connecting the lever to the frame enabling a rotation of the lever () relative to the frame () about a first rotation axis (X), in which the mechanical linking assembly () includes a first pivot joint (), the first pivot joint () including a first portion, a second portion movably mounted relative to the first portion, and at least two flexible blades, each flexible blade having an end that is attached to the first portion and another end that is attached to the second portion, and being resiliently deformable in order to enable a rotation of the second portion relative to the first portion along the first rotation axis (X) and to generate a return torque which hinders the rotation of the second portion relative to the first portion.

Joystick for controlling an aircraft

Flow valve including a casing containing an electromagnetic assembly for detecting a magnetic field. The electromagnetic assembly is fixed to a pendulum suspended by an articulation from a plate of the casing. The casing contains a liquid for damping the movements of the pendulum. The pendulum includes a surface opposite the articulation which has a spherical cap shape and which extends facing a wall of the casing of complementary shape, defining a space having dimensions suitable for producing a laminar rolling of the damping liquid between them when the pendulum is in motion.

Fluxgate with laminar damping of the pendulum and method of assembling a fluxgate

An electrical housing includes power components grouped together in power modules and control components grouped together in a control module that is separate from the power modules.

Electrical pack with separate control and power modules

The invention relates to a mechanical member wherein a first part in contact with a second part movable relative to the first part, at least one of the parts including a coating of solid lubricant at least at contact zones between the first part and the second part, the solid lubricant being suitable on its own for lubricating the mechanical member. According to the invention, the mechanical member includes retention and capillary distribution means for distributing a fluid between the parts in such a manner as to form a film between said parts, which film can be pierced temporarily at each contact zone.

Mechanical member

The invention relates to a joystick () for controlling an aircraft, including a frame (), a lever () mounted so as to be rotatably movable relative to the frame, and a mechanical linking assembly () for connecting the lever to the frame, the mechanical linking assembly () including: a first linking piece () movably mounted relative to the frame () about a first rotation axis (X), a second linking piece () movably mounted relative to the frame () about a second rotation axis (Y), the second rotation axis forming a non-zero angle with the first rotation axis, a third intermediate piece () mounted so as to the rotatably movable relative to the first linking piece () about a third rotation axis (Y'), a fourth intermediate piece () mounted so as to be rotatably movable relative to the second linking piece () about a fourth rotation axis (X&#x2032;), the fourth rotation axis forming a non-zero angle with the third rotation axis, in which the linking pieces () or the intermediate pieces () are rotatably movable in relation to one another about a fifth rotation axis (Z&#x2032;) forming a non-zero angle with the first rotation axis (X) and the second rotation axis (Y) or with the third rotation axis (Y&#x2032;) and the fourth rotation axis (X&#x2032;), respectively, so as to enable a variation of the angle formed between the first rotation axis and the second rotation axis or of the angle formed between the third rotation axis and the fourth rotation axis, respectively.

The electrical card has power modules constituted by power components and by control components that are carried by strips fastened on a support plate comprising an electrical ground plate. The power components are connected firstly to control buses, and secondly to power buses carried by the support plate and extending in a layer adjacent to the electrical ground plate.

Modular electrical card for power components

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

Device with integrated electronic components, that comprises a board forming a support for the said components, a cover mounted on the said board to cover the said components, and a separating partition which extends from the cover to the board substantially perpendicularly to the latter, the said partition separating two distinct zones of the board, wherein it comprises an overcover covering the cover and defining an internal space between the cover and the overcover in which are provided cooling gas division means delimiting two distinct secondary spaces in the internal space, an upstream secondary space into which cooling gas is able to be injected and a downstream secondary space into which cooling gas is able to be discharged so that cooling gas injected into the upstream zone of the board is directed toward the downstream secondary space of the internal space and that cooling gas injected into the upstream secondary space of the internal space is directed toward the downstream zone of the board.

Device with integrated electronic components provided with a partition for separating ventilated zones

A ventilation system for electrical or electronic equipment installed in an enclosure of a box having an air inlet and an air outlet for establishing a flow of air through said enclosure, the ventilation system having at least two air suction sources, namely a primary source and a secondary source, and a chest for mounting on said box beside the air outlet, said chest defining at least two separate cavities, both for connection to the air outlet, namely a primary cavity connected to the primary source, and a secondary cavity connected to the secondary source, in such a manner as to create two separate air exhaust circuits from the outlet of the enclosure.

Growing community of inventors

Paris, France

Etienne Merlet