Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An actuator for hinging a first element to a second element about a first pivot axis (A1), the actuator comprising a motor-drive device, a first mounting plate (4) connected to a body (2) of the motor-drive device, a second mounting plate (5) 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 (6) mounted in the second mounting plate to pivot about a second axis (A2) perpendicular to the first axis. The motor-drive device has an outlet shaft (3) pivotable about a third axis (A3) perpendicular to the first axis and intersecting the first axis, and it is extended by a pin (7) that is pivotally received in the bush and that has a central axis (A4) 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.

Abstract: 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.

Abstract: 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.

Abstract: An actuator for hinging a first element to a second element about a first pivot axis (A1), the actuator comprising a motor-drive device, a first mounting plate (4) connected to a body (2) of the motor-drive device, a second mounting plate (5) 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 (6) mounted in the second mounting plate to pivot about a second axis (A2) perpendicular to the first axis. The motor-drive device has an outlet shaft (3) pivotable about a third axis (A3) perpendicular to the first axis and intersecting the first axis, and it is extended by a pin (7) that is pivotally received in the bush and that has a central axis (A4) 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.

Abstract: 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.

Abstract: The invention relates to a joystick (1) for controlling an aircraft, including a frame (2), a lever (3), a mechanical linking assembly (4) for connecting the lever to the frame enabling a rotation of the lever (3) relative to the frame (2) about a first rotation axis (X), in which the mechanical linking assembly (4) includes a first pivot joint (9), the first pivot joint (9) 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a joystick (200) for controlling an aircraft, including a frame (201), a lever (202) mounted so as to be rotatably movable relative to the frame, and a mechanical linking assembly (203) for connecting the lever to the frame, the mechanical linking assembly (203) including: a first linking piece (213, 223) movably mounted relative to the frame (201) about a first rotation axis (X), a second linking piece (233, 243) movably mounted relative to the frame (201) about a second rotation axis (Y), the second rotation axis forming a non-zero angle with the first rotation axis, a third intermediate piece (255, 265) mounted so as to the rotatably movable relative to the first linking piece (213, 223) about a third rotation axis (Y?), a fourth intermediate piece (275, 285) mounted so as to be rotatably movable relative to the second linking piece (233, 243) about a fourth rotation axis (X?), the fourth rotation axis forming a non-zero angle with the third rotation axis, in which the linking piec

Abstract: The invention relates to a joystick (200) for controlling an aircraft, including a frame (201), a lever (202) mounted so as to be rotatably movable relative to the frame, and a mechanical linking assembly (203) for connecting the lever to the frame, the mechanical linking assembly (203) including: a first linking piece (213, 223) movably mounted relative to the frame (201) about a first rotation axis (X), a second linking piece (233, 243) movably mounted relative to the frame (201) about a second rotation axis (Y), the second rotation axis forming a non-zero angle with the first rotation axis, a third intermediate piece (255, 265) mounted so as to the rotatably movable relative to the first linking piece (213, 223) about a third rotation axis (Y?), a fourth intermediate piece (275, 285) mounted so as to be rotatably movable relative to the second linking piece (233, 243) about a fourth rotation axis (X?), the fourth rotation axis forming a non-zero angle with the third rotation axis, in which the linking piec

Abstract: The invention relates to a joystick (1) for controlling an aircraft, including a frame (2), a lever (3), a mechanical linking assembly (4) for connecting the lever to the frame enabling a rotation of the lever (3) relative to the frame (2) about a first rotation axis (X), in which the mechanical linking assembly (4) includes a first pivot joint (9), the first pivot join (9) 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.