Abstract: A feedback system senses a steering position of a nose wheel assembly for an aircraft. The nose wheel assembly has a first element rotatably associated with a second element about an axis, and the rotational position of the first element relative to the second element corresponds to the steering position of the nose wheel assembly. The feedback system includes a first magnetic field sensor fixedly positioned relative to the first element and configured to sense a first element orientation. A second magnetic field sensor is fixedly positioned relative to the second element and configured to sense a second element orientation. The feedback system further includes a controller programmed to determine the steering position of the nose wheel according to the sensed first element orientation and the sensed second element orientation.

Abstract: A measurement device for measuring an angular position of a movable body that is rotatable about an axis of rotation relative to a stationary body, the device comprising, facing each other, a movable portion with a first printed circuit having first tracks formed thereon defining a plurality of target patterns and a stationary portion with a second printed circuit having second tracks formed thereon defining a plurality of measurement patterns that are angularly distributed in regular manner. The target patterns are angularly distributed in irregular manner, the number of target patterns is not less than two, and the product of the number of target patterns multiplied by the number of measurement patterns is not less than twelve.

Abstract: A drive system includes a motor having a rotatable output shaft that is operably coupled to a lead screw by a transmission that converts rotary output of the motor into linear translation of the lead screw. The drive system further includes a position sensor configured to sense a position of the lead screw. A method for determining a backlash of the drive system includes the steps of sensing an initial position and driving the lead screw in a first direction to a calculated second position by controlling the motor to rotate the output shaft an amount that corresponds to a distance between the initial position and the calculated second position. The method further includes the steps of sensing an actual second position of the lead screw; and determining a backlash value according to a difference between the calculated second position and the actual second position.

Abstract: The invention relates to a method of diagnosing the state of wear of an actuator including at least one electric motor. The method comprises the following steps: recording a signal coming from the motor during activation and deactivation of the actuator, the signal including a first maximum during activation and a second maximum during deactivation; executing a windowing algorithm on the signal in order to obtain a standardized dataset including the first and second maximums; using at least one classification method for classifying into at least two classes in order to establish a score for the dataset in each of the classes of the classification method; and evaluating the state of wear of the actuator from the scores of the dataset.

Abstract: A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

Abstract: A brake assembly is suitable for use with a vehicle wheel that has a rim rotatably mounted to an axle. The brake assembly includes a housing fixedly positioned relative to the axle and a plurality of disks disposed within the housing and fixedly positioned relative to the rim. A fluid is disposed within the housing and has a selectively variable viscosity. The viscosity of the fluid is selectively increased to increase a braking force applied to the wheel.

Abstract: A machine for forming an annular textile preform includes: a horizontal sheet-forming turntable for forming a helical fiber; a horizontal intermediate turntable positioned under the sheet-forming turntable; a horizontal intermediate unwinder positioned on the intermediate; a final horizontal unwinder positioned under the intermediate unwinder; and a horizontal preform-forming turntable positioned under the final unwinder.

Abstract: A landing gear of an aircraft includes a pair of wheels between which an electric actuator at least partially covered with a lightning arrester cowl is placed. The lightning arrester cowl has an insulating matrix onto which at least an electrical conductor is attached. The electrical conductor includes electrical connection means for connecting the electrical conductor to a ground conductor of the aircraft.

Abstract: A landing gear of an aircraft having an upper portion intended to be joined to a structure of the aircraft and a lower portion provided with a first and second axle, the first axle being provided with a braked wheel and the second axle being provided with a motorised wheel, includes a first actuator that moves one of the axles between remote and close positions with respect to the upper portion while the other axle is kept stationary with respect to the upper portion. In one of the remote and close positions, and the wheels on the axles are simultaneously in contact with a running surface while, in the other position, each wheel on the second axle is at a distance from said running surface.

Abstract: An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.

Abstract: A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module; at least one power supply unit (21, 22); two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.

Abstract: A measurement device for measuring the pressure of a wheel (3) of a vehicle, the measurement device comprising a stationary portion (5) and a movable portion (14) for being driven in rotation by the wheel, the stationary portion including a first printed circuit (7) having at least one first track formed thereon defining a first winding, the movable portion including a second printed circuit (16) having at least one second track formed thereon defining a second winding, the second printed circuit being arranged to be connected to a pressure sensor (15), the first winding and the second winding being coupled together to form a wireless communication channel, the measurement device being arranged in such a manner that the pressure sensor is electrically powered by the stationary portion via the wireless communication channel, and in such a manner that uplink data comprising pressure measurement data is transmitted to the stationary portion (5) by the movable portion (14) via the wireless communication channel.

Abstract: The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.

Abstract: An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element. First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.

Abstract: An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.

Abstract: A bistable electromagnetic actuator includes a housing extending along an exertion axis of the actuator, two excitation coils arranged inside the housing and having at least one winding around the exertion axis for generating a magnetic control flux, a core that can be moved along the exertion axis and immobilized in two end positions depending on the magnetic flux generated by the coils, an actuating member coupled to the core to form a movable assembly, and a manual control device comprising a drive shaft mounted such that it can rotate about a first axis orthogonal to the exertion axis. The drive shaft has at least one tooth engaging with at least one first raised part translationally connected to the actuating member such that rotation of the drive shaft generates translational movement of the movable assembly.

Abstract: The invention relates to a braking device (1) of an aircraft wheel, comprising a ring (15) which has a plurality of cavities (17) in which actuators (18) are fitted in order to apply a braking force to a stack of discs (11) which extend opposite the ring. The ring is provided with a heat shield (25) which extends opposite a face of the ring directed towards the stack of discs in order to protect the ring from thermal radiation which is generated by the stack of discs. According to the disclosure, the heat shield is provided with holes (26) through which the actuators extend and which have a sectional profile which is formed to reflect the thermal radiation away from the device.

Abstract: An aircraft wheel (1) comprising a hub connected to a rim (3) provided with a tire (100), the hub having an outer surface that extends facing an inner surface (4) of the rim (3) and that co-operates therewith to define an annular space for receiving a stack of brake disks including rotor disks having axial peripheral notches, each notch receiving a segment of an axial bar (10) extending projecting from the inner surface (4) of the rim (3), and respective heat shields (20), each in the form of an annular segment, being mounted between the two bars (10) of respective pairs of adjacent bars. Each heat shield (20) includes at least one holder portion bearing against at least one first abutment (19, 119) secured to the rim (3) in order to hold the heat shield (20) in position on the rim (3) elastically.

Abstract: A method determines an inflation pressure expected in an aircraft tire provided with a pressure and temperature sensor. Also disclosed is a method for assistance in the maintenance for an aircraft tire and also a portable electronic device intended for assistance in the maintenance.