Abstract: An assembly including an accessory gearbox mechanically connected to an electricity generator having a support shaft that includes a calibrated breakable section designed to disconnect the electricity generator physically from the accessory gearbox when an incident is detected on the electricity generator, the protection device including an unlocking mechanism provided with a lock that, under the action of an external control unit, releases a cutting tool so as to cut said calibrated breakable section.

Abstract: The invention relates to a system for the rotational decoupling of shafts, in particular drive shafts. The invention also relates to a generator protection system on a connection between a generator and a gas turbine engine. FIG. 1C illustrates the shaft-decoupling system in the decoupled position.

Abstract: An assembly for rotationally friction driving the wheel of an airplane provided with a driving track. The assembly has a base intended to be fixed to a lower part of the landing gear, two arms mounted to pivot on the base, and rollers so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving the roller. A central pinion is mounted so as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion. A drive actuator acts on the arms of the assembly so as to position the assembly either in a disengaged position in which the rollers are separated from the driving track, or in an engaged position in which the rollers are held to rest on the driving track.

Abstract: The invention relates to a system for the rotational decoupling of shafts, in particular drive shafts. The invention also relates to a generator protection system on a connection between a generator and a gas turbine engine. FIG. 1C illustrates the shaft-decoupling system in the decoupled position.

Abstract: An assembly including an accessory gearbox mechanically connected to an electricity generator having a support shaft that includes a calibrated breakable section designed to disconnect the electricity generator physically from the accessory gearbox when an incident is detected on the electricity generator, the protection device including an unlocking mechanism provided with a lock that, under the action of an external control unit, releases a cutting tool so as to cut said calibrated breakable section.

Abstract: The invention relates to an assembly for rotationally friction driving the wheel of an airplane (3) provided with a driving track (4) and so mounted as to rotate about an axis of rotation on an axle (2) carried by the lower part of an airplane landing gear, with the assembly comprising: a base (22) intended to be fixed to the lower part of the landing gear; two arms (24) mounted to pivot on the base; rollers (21) so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving (31) the roller; a central pinion (26) so mounted as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion; actuating means (29) so acting on the arms of the assembly as to position same either in a disengaged position in which the rollers are separated from the driving track, or in an engaged position in which the rollers are held to rest on the driving track with a predetermined bearing force.

Abstract: The invention relates to a device (4) for actuating a control surface (2) of an aircraft, comprising: —a frame intended to be mounted fixed in relation to a structure of an aircraft, —a bell crank part (7) mobile in rotation in relation to the frame around an axis of rotation (X, X?) and adapted in order to be connected to a mechanical unit (1) for displacement of the control surface (2), —a slider (6) intended to be connected to a drive member (5), the slider (6) being mobile in translation in relation to the frame according to a direction of translation, parallel to the axis of rotation (X, X?) of the bell crank part (7), —first connecting means (61) between the slider (6) and the bell crank part (7) in order to convert a displacement in translation of the slider (6) generated by the drive member (5) into a displacement in rotation of the bell crank part (7), in order to actuate the mechanical unit (1) for displacement of the control surface (2), an input part (53, 16) able to be driven in rotation by the m

Abstract: The invention relates to a device for driving rotation of an aircraft wheel comprising a rim (4) mounted to rotate on an axle (2) of landing gear about an axis of rotation (X), the device comprising a drive ring gear (103) and a drive actuator (101) having an outlet pinion (102) that co-operates with the drive ring gear to drive the wheel in rotation. The drive ring gear is mounted to rotate about the axis of the rim of the wheel, the drive device including selective coupling means (150) that are operable to link the rim and the drive ring gears together in rotation, or to disconnect them.

Abstract: The invention relates to an actuation system (100) for a propulsive unit including a nacelle, a turbojet engine, and an air circulation channel defined between the nacelle and the turbojet engine, the actuation system (100) including: a body and a connection device for attaching the body to the nacelle, the connection device enabling the body to move relative to the nacelle along two axes of rotation; a first member for moving a flap for controlling the airflow in the channel, the first member extending from the body and having a first point for attaching the first member to the flap; a second member for moving a thrust-reversing flap, the second member extending from the body and having a second point for attaching the second member to the flap, the body being arranged between the first and second attachment points; and a transmission device (40) having an input (42), a first output (44) connected to the first member (50), and a second output (43) connected to the second member (70), the transmission device

Abstract: The invention relates to a device for driving rotation of an aircraft wheel comprising a rim (4) mounted to rotate on an axle (2) of landing gear about an axis of rotation (X), the device comprising a drive ring gear (103) and a drive actuator (101) having an outlet pinion (102) that co-operates with the drive ring gear to drive the wheel in rotation. The drive ring gear is mounted to rotate about the axis of the rim of the wheel, the drive device including selective coupling means (150) that are operable to link the rim and the drive ring gears together in rotation, or to disconnect them.

Abstract: The invention relates to an actuation system (100) for a propulsive unit including a nacelle, a turbojet engine, and an air circulation channel defined between the nacelle and the turbojet engine, the actuation system (100) including: a body and a connection device for attaching the body to the nacelle, the connection device enabling the body to move relative to the nacelle along two axes of rotation; a first member for moving a flap for controlling the airflow in the channel, the first member extending from the body and having a first point for attaching the first member to the lap; a second member for moving a thrust-reversing flap, the second member extending from the body and having a second point for attaching the second member to the flap, the body being arranged between the first and second attachment points; and a transmission device (40) having an input (42), a first output (44) connected to the first member (50), and a second output (43) connected to the second member (70), the transmission device (

Abstract: The invention relates to a device (4) for actuating a control surface (2) of an aircraft, comprising:-a frame intended to be mounted fixed in relation to a structure of an aircraft, -a bell crank part (7) mobile in rotation in relation to the frame around an axis of rotation (X, X?) and adapted in order to be connected to a mechanical unit (1) for displacement of the control surface (2), -a slider (6) intended to be connected to a drive member (5), the slider (6) being mobile in translation in relation to the frame according to a direction of translation, parallel to the axis of rotation (X, X?) of the bell crank part (7), -first connecting means (61) between the slider (6) and the bell crank part (7) in order to convert a displacement in translation of the slider (6) generated by the drive member (5) into a displacement in rotation of the bell crank part (7), in order to actuate the mechanical unit (1) for displacement of the control surface (2),an input part (53, 16) able to be driven in rotation by the mot

Abstract: The invention relates to an actuator for actuating an aircraft member, said actuator essentially comprising a screw and at least two nuts including a primary nut and a secondary nut that are engaged on the screw, relative movement between the screw and the nuts generating said actuation, the secondary nut being disposed to take up the load on the screw in the event that the primary nut fails, the actuator further comprising a third nut, the secondary nut and the third nut having mutually overlapping portions and a breakable pin passing through said overlapping portions, the third nut being constrained to turn with the secondary nut by the pin so that, after the pin breaks, the third nut is free to turn relative to the secondary nut.

Abstract: Actuator apparatus, in particular for an airplane flight control. The apparatus has at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including a mechanism for locking each outlet shaft of the drive systems when the system for driving it is no longer operating. The apparatus also includes at least one auxiliary drive motor and a clutch mechanism mounted on the outlet shaft of one of the main systems and suitable for automatically driving the outlet shaft using the auxiliary motor when the corresponding main drive system is not operating and for automatically locking the outlet shaft when the main drive system and the auxiliary motor are not operating.

Abstract: An override device is presented having a manual control, an inlet gear, and an outlet gear, which are mounted to rotate about the same axis. The inlet gear rotates the outlet gear. The manual control has a cam which, in co-operation with an intermediate part suitable for following the cam, serves to disengage the rotation of the inlet gear under torque exerted on the manual control. The manual control drives the outlet gear. The Inlet gear rotates by having a set of friction disks and spring part suitable for exerting a force to compress the disks against one another. The intermediate part carries at least one pusher-forming element, which at the end of a displacement exerts force opposing that of the spring part and relaxes the friction force on at least some of the disks.

Abstract: Actuator apparatus, in particular for an airplane flight control, the device comprising at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including means for locking each outlet shaft of the drive systems when the system for driving it is no longer operating; the apparatus including at least one auxiliary drive motor and a clutch mechanism mounted on the outlet shaft of one of the main systems and suitable for automatically driving said outlet shaft by means of the auxiliary motor when the corresponding main drive system is not operating and for automatically locking said outlet shaft when said main drive system and said auxiliary motor are not operating.

Abstract: An electromechanical actuator comprising a screw that is driven in rotation, a nut that is driven in translation by rotation of the screw, and a guide rod which is driven in translation by the nut, the actuator having a plurality of rollers interposed between the guide rod and the nut, said rollers having a succession of annular grooves and ridges, while the outside surface of the nut and the inside surface of the guide rod have respective pluralities of complementary grooves and ridges, the grooves and ridges of the rollers co-operating with the grooves and ridges of the nut and of the guide rod to transmit axial force on the guide rod to the nut when said rollers are in an engaged position, the nut and/or the guide rod having release channels in angular positions that are designed to coincide with the positions of the rollers when they are declutched, said channels being such that they enable at least some of the grooves and ridges to be disengaged so as to release the guide rod to move in translation relat