Abstract: An aircraft landing gear includes a strut mounted to an aircraft structure and moveable between extended and retracted positions. A bracing member includes a first bracing connecting rod hinged to the aircraft structure and a second bracing connecting rod hinged to the first bracing connecting rod and to the strut. A stabilizing member includes a first stabilizing connecting rod and a second stabilizing connecting rod hinged together. The second connecting stabilizing rod is hinged to the first bracing connecting rod. At least one spring is arranged to be resiliently subjected to a bending force when the hinges of the first and second stabilizing connecting rods move from their aligned position.

Abstract: The invention provides a locking device for preventing movement between two elements (11, 12) that are mounted to move relative to each other, the locking device including a lock (31) mounted to rotate relative to one of the elements in order to present successive angular positions for locking and for release in which the lock alternates between preventing and allowing relative movement between the two elements, the lock being constrained to rotate with a selector (55) of an angular indexing mechanism (50) actuated by a pulse-controlled actuator (70, 71) arranged to push the selector against a spring member (58) in order to cause it to turn on each pulse and thereby cause the lock to pass from one angular position to the other.

Abstract: The invention provides a method of moving an aircraft undercarriage comprising a leg (1) that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut (2) held in an aligned position by a stabilizer member (4), the method including using a drive actuator (10) for raising the undercarriage from the deployed position to the retracted position. According to the invention, the actuator is coupled firstly to the leg and secondly to the stabilizer member in such a manner that on being activated the actuator begins by causing the stabilizer member to unlock and then moves the undercarriage leg towards the retracted position.

Abstract: The invention relates to a method of driving an aircraft undercarriage between a deployed position and a retracted position, the undercarriage comprising a leg (2) that is hinged to a structure of the aircraft in order to be movable between those two positions and being stabilized in the deployed position by means of a brace member (10) comprising two limbs (11, 12) that are hinged to each other, one of which is coupled to the leg and the other of which is coupled to the structure of the aircraft, the limbs being brought into an aligned position when the leg is in the deployed position. According to the invention, a rotary actuator (20) is arranged on the aircraft, which actuator comprises first and second cranks (22, 24) that are mounted to turn freely about a common axis of rotation but that have a relative angular position that can be controlled, and that are arranged to stabilize the limbs of the brace member in the substantially aligned position.

Abstract: The invention provides a locking device for preventing movement between two elements (11, 12) that are mounted to move relative to each other, the locking device including a lock (31) mounted to rotate relative to one of the elements in order to present successive angular positions for locking and for release in which the lock alternates between preventing and allowing relative movement between the two elements, the lock being constrained to rotate with a selector (55) of an angular indexing mechanism (50) actuated by a pulse-controlled actuator (70, 71) arranged to push the selector against a spring member (58) in order to cause it to turn on each pulse and thereby cause the lock to pass from one angular position to the other.

Abstract: An aircraft undercarriage includes a steerable bottom portion carrying one or more wheels and fitted with a steering device configured to turn the steerable bottom portion in response to a steering order. The steering device has a single electromechanical steering actuator having a steering electric motor driving, by a reduction gearing, an outlet pinion on an axis of the steering electric motor. The outlet pinion cooperates with a spur gear secured to the steerable bottom portion. A connection between the steering electric motor and the steerable bottom portion is reversible. The electromechanical steering actuator is fitted with a monitor configured to monitor at least one operating parameter of the steering device and to detect an actuator performance deterioration condition.

Abstract: The invention relates to a method of driving an aircraft undercarriage between a deployed position and a retracted position, the undercarriage comprising a leg (2) that is hinged to a structure of the aircraft in order to be movable between those two positions and being stabilized in the deployed position by means of a brace member (10) comprising two limbs (11, 12) that are hinged to each other, one of which is coupled to the leg and the other of which is coupled to the structure of the aircraft, the limbs being brought into an aligned position when the leg is in the deployed position. According to the invention, a rotary actuator (20) is arranged on the aircraft, which actuator comprises first and second cranks (22, 24) that are mounted to turn freely about a common axis of rotation but that have a relative angular position that can be controlled, and that are arranged to stabilize the limbs of the brace member in the substantially aligned position.

Abstract: The invention provides a method of moving an aircraft undercarriage comprising a leg (1) that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut (2) held in an aligned position by a stabilizer member (4), the method including using a drive actuator (10) for raising the undercarriage from the deployed position to the retracted position. According to the invention, the actuator is coupled firstly to the leg and secondly to the stabilizer member in such a manner that on being activated the actuator begins by causing the stabilizer member to unlock and then moves the undercarriage leg towards the retracted position.

Abstract: An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. The drive include a rotary drive inside the rack adapted to turn about the sliding axis and to cooperate via a helicoidal coupling with the rack, The rotary drive is immobilized axially by two opposite axial thrust bearings allowing angular tilting of the rotary drive. The thrust bearings are carried by at least one elongate support inside the rack having a proximal end fixed to an end of a cylinder in which the rack slides.

Abstract: An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. The drive include a rotary drive inside the rack adapted to turn about the sliding axis and to cooperate via a helicoidal coupling with the rack,. The rotary drive is immobilized axially by two opposite axial thrust bearings allowing angular tilting of the rotary drive. The thrust bearings are carried by at least one elongate support inside the rack having a proximal end fixed to an end of a cylinder in which the rack slides.