Abstract: An aircraft assembly, having: a reference component; a first component and a first actuator, the first actuator configured to move the first component relative to the reference component; a second component and a second actuator, the second actuator configured to move the second component relative to the reference component; a position sensor configured to measure a position of the first component, and to output a position value, the sensor being capable of outputting a plurality of non-zero position values; and a controller configured to control the movement of the second component by the second actuator based at least partially on the position value output by the position sensor.

Abstract: A roller pinion for rotating about a central axis generally includes a core having an axial bore at its center for mounting on a drive shaft and recesses extending the length of the core. The recesses define faces with a plurality of regularly distributed sectors extending between them. The roller pinion also includes a cage associated with a plurality of rollers. The cage extends around the outer peripheral surface of the core, and presents, facing the outer peripheral surface of the core, a concentric spherical inner surface that faces the recesses of the core. Protuberances are provided that extend into the recesses. The protuberances have faces positioned parallel to and facing the faces of the recesses. Metal strips arranged in bundles with elastomer material interposed between the strips are inserted in a space between the respective faces of one recess in the core and one protuberance of the cage.

Abstract: An aircraft assembly, having: a reference component; a first component and a first actuator, the first actuator configured to move the first component relative to the reference component; a second component and a second actuator, the second actuator configured to move the second component relative to the reference component; a position sensor configured to measure a position of the first component, and to output a position value, the sensor being capable of outputting a plurality of non-zero position values; and a controller configured to control the movement of the second component by the second actuator based at least partially on the position value output by the position sensor

Abstract: A roller pinion for rotating about a central axis generally includes a core having an axial bore at its center for mounting on a drive shaft and recesses extending the length of the core. The recesses define faces with a plurality of regularly distributed sectors extending between them. The roller pinion also includes a cage associated with a plurality of rollers. The cage extends around the outer peripheral surface of the core, and presents, facing the outer peripheral surface of the core, a concentric spherical inner surface that faces the recesses of the core. Protuberances are provided that extend into the recesses. The protuberances have faces positioned parallel to and facing the faces of the recesses. Metal strips arranged in bundles with elastomer material interposed between the strips are inserted in a space between the respective faces of one recess in the core and one protuberance of the cage.

Abstract: A structure comprising firstly a differential sensor of linear displacement comprising a body and a core slidably mounted relative to said body, and secondly a rod of a servo-control actuator in which the core is mounted, said rod terminating in an endpiece which has a bore in which the core is received close to its end, said bore and the core having complementary threads which co-operate to hold said core relative to said bore, and means enabling the engagement of the core in said bore to be adjusted, wherein said means comprise an adjustment screw extending through the actuator rod and whose thread co-operates with complementary means carried by the core so that turning movement applied to the adjustment screw by an operator gives rise to axial displacement of the core in the bore of the endpiece.

Abstract: The invention relates to a system for powering the driving actuator of an aircraft undercarriage, the system including a hydraulic generator capable of delivering fluid under pressure to one or the other of two chambers of the driving actuator. According to the invention, the power supply system includes a safety device enabling any overloading of the actuator rod under the effect of pressure peaks to be avoided: said device comprises two pressure relief valves, the first valve limiting the pressure delivered to the annular chamber and being under the control of the pressure in the full-section chamber, and the second pressure relief valve being of the differential type and continuously controlling the pressure difference between the two chambers of the actuator. The invention is applicable to providing very safe power supply systems for aircraft undercarriages.