Abstract: A bistable linear electromagnet comprising a first housing (10) and a second housing (11) in alignment, a movable armature (18) comprising a rod (19) and a shuttle (20) that is slidably mounted, and a first coil (13) positioned in the first housing and a second coil (15) positioned in the second housing. A cavity (25) is made in a measurement wall (4) of one of the housings, and the electromagnet comprises a magnetic field sensor (26) positioned in the cavity and designed to measure a magnetic flux existing in a magnetic path formed by the walls of said housing and by the shuttle, in order to detect whether the shuttle has moved towards or away from the abutment wall of said first or second housing.

Abstract: The present invention relates to a method for monitoring the ageing of a landing gear of an aircraft, implemented by an autonomous measurement device installed on said landing gear and comprising sensors and a memory for storage, and comprising: after a landing of the aircraft, a stand-by step comprising detection by means of said sensors of the position of the landing gear at a first sampling frequency, for as long as the position of the landing gear is detected as vertical; after detection of a horizontal position of the landing gear, a sleep step comprising detection by means of said sensors of the position of the landing gear at least at a second sampling frequency, for as long as the position of the landing gear is detected as horizontal; after detection of a vertical position of the landing gear, a measurement step comprising acquisition by means of said sensors of physical parameters relating to the ageing of the landing gear, and detection of a landing of the aircraft at a third sampling frequency unt

Abstract: The present disclosure relates to a method of measuring wear of a disk in an aircraft brake having a wear indicator that is movably mounted on a stationary portion of the aircraft brake and that moves progressively with increasing wear of the disk. The method includes using a picture-taking appliance to take at least one photograph of the wear indicator while an aircraft is stationary on the ground, and estimating a position of the wear indicator and a wear level of the disk by analyzing the photograph.

Abstract: The invention relates to an aircraft (5) comprising: a structure (6); a landing gear (1) mounted on the structure (6) of the aircraft; and at least one obstacle detector (2). The aircraft (5) is characterized in that the obstacle detector (2) is secured to an arm (3), said arm (3) being mounted on the structure (6) such that it can move between a rest position in which the arm (3) is retracted and a detection position in which the arm (3) is deployed such that the obstacle detector (2) extends close to a lower portion of the landing gear (1) at a distance from the structure (6) of the aircraft (5).

Abstract: The invention relates to a method for adapting a stop that is adjustable by screwing onto the extremity of a fine tube (1), including the following stages: slipping onto the extremity of the tube (5) a ferrule (10) that is threaded on its external surface and is immobilized on the extremity of the tube by means of a plurality of pins (8) engaged in orifices (7,9) facing towards the ferrule and the tube; screwing onto the ferrule a nut (14) having a first end face (15) acting as a stop in order to preload any element (4, 4) mounted on the tube in front of the ferrule, and a second opposing end face (18) containing forms (25) adapted for it to be driven in rotation by a tool, the nut covering the pins in service.

Abstract: Electrical equipment of the type comprising calculation means or a data concentrator for connecting to a tachometer (2) via a cable (3) that comprises a measurement wire (36, 37) and a test wire (38), the electrical equipment having a measurement input (11, 12) to which the measurement wire can be connected and a test input (14) to which the test wire can be connected, measurement acquisition components (7) connected to the measurement input and arranged to acquire an electrical measurement signal present on the measurement wire and produced by the tachometer, test acquisition components (8) connected to the test input and arranged to detect whether the test wire is or is not open-circuit, and processor components (9) arranged to detect a break of the measurement wire if the test wire is open-circuit.

Abstract: A hydraulic actuator having a body defining a chamber, a piston rod including an annular groove and a piston head slidably housed within the chamber, the piston head having a number of segments each of which has a base portion mounted within the annular groove.

Abstract: A pressure regulation servo-valve comprising a body having a utilization port, a feed port, and a return port, a spool mounted as a sliding fit in the body, the spool co-operating with the body to define a pilot chamber connected to the utilization port. The spool and the body together further define a priming chamber connected to the feed port via a second constriction and connected to the nozzle via a third constriction, and in which there exists a priming pressure acting on the spool in the first direction.

Abstract: An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

Abstract: A magnetic measurement target is configured to be positioned inside a vehicle axle and to cooperate with at least two magnetic movement sensors to measure deformation of the axle. The magnetic measurement target includes a body with a fastener end for fastening to one end of the axle and a main portion. The main portion includes a slot formed in an axial direction to separate two longitudinal portions of the body. Each longitudinal portion of the body presents a target surface for which movement can be measured by a magnetic movement sensor.

Abstract: An aircraft undercarriage has an axle for carrying at least one wheel. The undercarriage further includes a magnetic measurement target and at least one magnetic movement sensor cooperating with the magnetic measurement target to measure bending of the axle. The magnetic measurement target has a body that extends inside the axle and includes a fastener end fastened to one end of the axle. The body also include a target surface that extends over an inside surface of the body. The magnetic movement sensor is positioned inside the axle to measure movement of the target surface.

Abstract: An actuating system for an aircraft having an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored. The system also includes a control unit (22) using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator and at least one digital transmission channel (50) connecting the control unit and the electromechanical actuator.

Abstract: An aircraft landing gear comprising at least an axle carried in the bottom portion of the landing gear, a wheel provided with a rim mounted on the axle of the landing gear via bearings in order to rotate about an axis of rotation, a brake threaded on the axle and including a torque tube extending around the axle, friction members mounted around the torque tube and extending between the torque tube and the rim of the wheel, and at least one brake actuator designed for selectively exerting a braking force on the friction members, the brake actuator being carried by an actuator carrier to which the torque tube is secured, and a rotary drive for driving the wheel in rotation comprising firstly an actuator for driving the wheel in rotation and secondly a transmission member for selectively transmitting movement in rotation from the rotation actuator to the rim of the wheel and extending between the axle and the torque tube.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

Abstract: The invention relates to a landing gear (1) of an aircraft (5), comprising: a strut assembly (10) including a first end (10a) designed to be mounted on the aircraft (5) and a second end (10b) opposite the first end (10a); a rod (14) slidably mounted on the second end (10b) of the strut assembly (10), said rod (14) being translationally movable in relation to the strut assembly (10); and at least one obstacle detector (2) secured to the landing gear (1), the landing gear (1) being characterized in that the obstacle detector (2) is secured in a zone adjacent to the second end (10b) of the strut assembly (10).

Abstract: Method for generating a tooth space profile (5) between two teeth (4) of a wheel (1) engaging with a roller (3) pinion (2) in a reference plane perpendicular to a central axis (X1) whose intersection with the reference plane defines a centre (C), comprising the step of defining a nominal tooth space with symmetrical first and second profiles so that the space is suitable for receiving a roller which comes into contact, without clearance, with the facing active portions of the first and second profiles at the level of a primitive diameter. The method of the invention comprises the steps of deforming the bottom portion (12) of the first profile so that the bottom point is brought nearer to the centre by an amount equal to a given radial clearance, and moving the first profile angularly through a given angular half-clearance around the centre to shift it away from the radial axis.

Abstract: An aircraft wheel rim includes a main portion and a removable portion. The main portion includes a hub and a disk extending between the hub and an annular outer portion that receives a tire and is shaped to form a rim one of its sides of the annular outer portion. A second side of the annular outer portion is shaped to receive the removable portion, which forms a second flange on the second side of the annular outer portion after a tire has been put into place. The rim further includes a blocking device that limits rotation of the removable portion relative to the main portion. The blocking element include at least one key having a head engaged in a matching receptacle in the removable portion and a root engaging a steel peg that is shrink fitted in the main portion.

Abstract: A linear telescopic actuator (1) that comprises a cylinder (2), a sliding part (3), a spring seat (4) and a first compression spring (5) capable of resiliently opposing the sliding part (3) approaching the spring seat (4). The spring seat (4) presents an outer annular groove (6) and the cylinder (2) includes an inner annular groove (7). The actuator (1) also presents a blocking part (8), the actuator (1) being adapted to adopt selectively an assembled configuration and a disassembled configuration. The blocking part (8) in the assembled configuration is engaged inside the inner and outer annular grooves (6, 7). The blocking part (8) in the disassembled configuration being disengaged from one of the grooves so as to allow spring seat (4) to slide in the cylinder (2).

Abstract: A control method for controlling an electrical taxiing system adapted to moving an aircraft while it is taxiing, the method comprising the steps of: generating a ground speed setpoint for the aircraft; transforming the ground speed setpoint into an optimized speed setpoint presenting a curve as a function of time that has a predefined function comprising a plurality of linear portions, each having a slope that is a function of the ground speed setpoint; implementing a regulator loop having the optimized speed setpoint as its setpoint; and generating a command for the electrical taxiing system from an output of the regulator loop.

Abstract: A landing-gear assembly (1) for an aircraft, the landing-gear assembly comprising: an axle shaft (2); a leg (3) presenting a first portion (3a) carrying said axle shaft (2) and a second portion (3b) connected to a carrier structure of the aircraft; a main damper (5); and a first secondary damper (6a) distinct from the main damper (5). The first secondary damper (6a) is carried by the axle shaft (2) and comprises: an inertial mass (M); and connection means (7a) between the inertial mass (M) and the axle shaft (2) damping movements of the inertial mass (M) along a first axis (X1) of movement of the inertial mass (M) relative to the axle shaft (2), said first axis of movement (X1) extending in a plane (P) perpendicular to said steering axis (Z).