Abstract: An aircraft landing gear includes: a strut assembly hinged by its upper end to a structure element of the aircraft to pivot between deployed and retracted states; an interlocking system having a stay including an arm hinged to the strut assembly via a lifting pin carried by two lugs of a clevis of the strut assembly, this arm being terminated by a head through which the pin passes and which is located between the lugs; and a lifting jack having one end connected to a first end of the pin which is located outside the clevis, a first end stop carried by the pin at its first end beyond the jack, and a second end stop carried by the pin at its second end. The landing gear includes a system for translationally locking the lifting pin in the event of the pin breaking between its first end and the clevis.

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: An uplock for retaining a capture pin of a movable part includes a hook that is movable between a release position and a retaining position, a locking part that interacts with the hook and is movable between a locking position and an unlocking position, and a detector. The detector includes a first sensor for detecting whether the hook is in the retaining position, and a second sensor for detecting a presence of the mobile part in the immediate vicinity of the uplock in the position occupied by the mobile part when the capture pin is in the hook.

Abstract: A method for unlocking a door of an aircraft landing gear movably mounted between an open position and a closed position includes, during a first sequence of opening the door that is locked in the closed position by a first attachment housing and a second attachment housing, controlling a first unlocking actuator to deactivate the first attachment housing, waiting a first waiting time greater than a time necessary for the door to initiate a passage from the closed position to the open position, so as to enable a detector to detect the door starting to open, detecting the door starting to open by the detector and whether there is a failure of the second attachment housing, and controlling a second unlocking actuator to deactivate the second attachment housing.

Abstract: The invention relates to an aircraft undercarriage provided at its bottom end with a rocker arm (2) carrying at least two axles (4, 5), including one in front of a hinge between the rocker arm and the undercarriage and the other behind said hinge. According to the invention, one of the axles is fitted with one or more braked wheels (6) and the other axle is fitted with one or more motor-driven wheels (8).

Abstract: Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporate knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.

Abstract: A landing gear system for a vehicle includes a landing gear configured for reciprocating motion between a stowed position and a deployed position. The landing gear has a linkage with a first link rotatably coupled to a second link. The linkage reciprocates between folded and extended states when the landing gear reciprocates between the stowed and deployed positions, respectively. A fail-secure downlock includes first and second electromagnets fixedly positioned relative to the first and second links, respectively. The first electromagnet is proximate to the second electromagnet when the landing gear is in the stowed position. The first electromagnet is attracted to the second electromagnet when the downlock is in the locked state. The first electromagnet is repelled by the second electromagnet when the downlock is in the unlocked state.

Abstract: A landing gear system includes a landing gear assembly coupled to a body of a vehicle and configured for reciprocating motion between a retracted position and an extended position. A fail-secure uplock assembly is reciprocal between a locked state and an unlocked state. A first electromagnet and a first permanent magnet are mounted to the body, and a second electromagnet and a second permanent magnet are mounted to a component of the landing gear assembly. The first and second electromagnets generate magnetic fields with reversible polarities. When the landing gear assembly is in the retracted position, the first permanent magnet is attracted to the second permanent magnet. The first electromagnet is attracted to the second electromagnet when the uplock assembly is in the locked state and is repelled by the second electromagnet when the uplock assembly is in the unlocked state.

Abstract: A braking device includes one or more stationary elements and one movable element that is movable with respect to the one or more stationary elements, the moveable element being made of an electrically conductive material, one or the one or more stationary elements including magnets capable of generating eddy currents in the movable element, when the one or more stationary elements and the movable element are in relative movement. The magnets include first magnets and second magnets disposed alternating, the first magnets having a first magnetization vector and each of the second magnets having a second magnetization vector, and the magnets have widths such that the first magnets are spaced apart in pairs by a first distance that is less than a second distance separating the second magnets in pairs, and the length of the second magnets being around 70% of the length of the first magnets.

Abstract: An eddy current magnetic braking device includes two outer elements surrounding a central element in relative movement with respect to the two outer elements, the central element being made of an electrically conductive material, the two outer elements having first faces facing opposite second faces of the central element and each of the two outer elements including plural magnets for emitting, via the first faces, a magnetic flow that generates in the central element eddy currents when the two outer elements are in relative movement. The plural magnets are arranged in such a way that the two outer elements attract each other. The central element has a thickness such that a skin effect is generated from each face of the central element over more than half the thickness of the central element over at least a range of possible relative speeds of the central element relative to the two outer elements.

Abstract: An uplock for selectively retaining a capture pin of a movable element including a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position. The locking member is movable between a locked position that immobilizes the hook and an unlocked position in which the hook is free. The detector detects whether the hook is in the retaining position and the capture pin is present in the hook. The detector includes a sensor associated with a single target which is movable between two positions The sensor emits a signal which is modified when the target passes from one of the positions to the other. The target is independently in kinematic interaction with the hook and the capture pin.

Abstract: An aircraft comprising a fuselage, a pair of wings connected to an upper portion of the fuselage, and a pair of wing support struts, each wing support strut being connected between a lower portion of the fuselage and an underside of the adjacent wing, wherein at least one centre landing gear assembly is connected to the fuselage and is configured to be retractable within the fuselage, and a respective outrigger landing gear is connected to each wing support strut, each outrigger landing gear being configured to be retractable within the respective wing support strut.

Abstract: A method for manufacturing a diaphragm holder for a shock absorber of the oleo-pneumatic type, in particular for an aircraft landing gear. The diaphragm holder includes a first end with a dome, and a tubular portion extending from the dome to a second end. The method includes a step of overmolding a first material onto an insert. The insert can be a second material with a value of compression breaking stress divided by density that is higher than the first material or alternatively, of a material identical to the first material. A diaphragm carrier which can be manufactured by this method.

Abstract: An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.

Abstract: An eddy-current-based magnetic braking device includes two external elements flanking a central element that is aligned with a same axis as the external elements and that rotates about said axis with respect to the external elements, the external elements each bearing magnets that emit a magnetic flux that engenders in the central element eddy currents. The magnets are placed so as to generate a magnetic attraction between the external elements. Friction-based braking surfaces are joined so as to rotate as one with the external elements and with the central element, respectively. The external elements are moveable with respect to the axis between a proximate position of the central element, in which position the first braking surfaces are held applied against the second braking surfaces via the magnetic attraction, and a separated position of the central element, in which position the first braking surfaces are separated from the second braking surfaces.

Abstract: An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.

Abstract: An assembly of a disk brake system (2) of an aircraft landing gear (I) and a monitoring device (3), the disk brake system (2) comprising at least one stator disk (21) and at least one rotor disk (22) configured to be pressed against said stator disk (21), the monitoring device (3) comprising a tape (30), the tape (30) comprising at least one visual information item associated with a predetermined circumferential range of the stator disk (21), the tape (30) being positioned in contact with the circumference of the stator disk (21), a first gripping member (31) attached to a first end of the tape (30) and a second gripping member (32) attached to a second end of the tape (30) so as to make it possible to stretch the tape around the circumference of the stator disk (21) in order to accurately determine the circumference of the stator disk (21).

Abstract: A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.

Abstract: A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.

Abstract: A detection method for detecting a blocked or unlocked state of a parking brake member including a bistable linear electromagnet connected both to a power supply component arranged to generate a control voltage and to a current sensor arranged to measure the control current. The detection method includes controlling the power supply component to generate a test voltage across terminals of a coil and thus generate a test current flowing in the coil, the test voltage having an amplitude less than a predetermined voltage threshold so that a test magnetic field generated by the test current does not move a shuttle, acquiring measurements of the test current as produced by the current sensor, analyzing the measurements of the test current, and detecting the blocked or unlocked state of the parking brake member based on the analysis.