Abstract: A bearing assembly (2?) comprising a housing (3?) supporting first and second bearing ring portions (4, 4?) with bearing surfaces to engage an inner tubular member (1?) at axially spaced regions, characterised in that either: said bearing ring portions are provided by separate bearing rings (4?) supported in the housing member (3?) with bearing surfaces of different diameters; or said bearing ring portions are provided by a single bearing ring (4?) that is free to flex radially and is supported so that the second bearing ring portion is free to flex radially under load and its bearing surface than assumes a position with a greater diameter than that of the first bearing ring portion (4?).

Abstract: A semi-levered landing gear for an aircraft includes a main shock absorber strut, a bogie beam and an auxiliary actuator mechanism. The bogie beam extends fore and aft of an airframe of the aircraft with forward and aft axles for respective forward and aft wheels, and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut. The auxiliary actuator mechanism includes a spring unit pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point offset from the pivot connection of the upper portion to the aircraft fuselage. During stowing the strut and spring unit pivot together about different pivot points, causing a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position.

Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.

Abstract: An auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising first (59, 63) and second (56, 50) stage piston and cylinder actuators operating coaxially within an outer casing (50). A respective actuator is connected to a respective one of the strut (1) and bogie beam (4). The second stage actuator (56, 60) serves to control the tilt position of the bogie beam (4) relative to the strut (1). The second stage actuator (56. 60), when in the retracted position with the first stage actuator (59, 63) in the extended position, limits the length ol the auxiliary actuator (9) between its connections (62,67) to the strut (1) and bogie beam (4), so as to assume a predetermined intermediate length in which the bogie beam (4) is restrained to tilt about the auxiliary pivot (14) and thereby lengthens the landing gear during take-off.

Abstract: A fabric includes a base pattern having at least twenty-eight weft fibers disposed in a staggered configuration and forming eight columns that comprise in alteration four weft fibers and three weft fibers, the weft fibers extending in seven layers. The fabric further includes at least twelve warp fibers disposed in at least four offset parallel planes, each of the planes containing at least three parallel warp fibers that follow paths that are distinct from one another.

Abstract: The invention provides a multifunction electromechanical device for an aircraft undercarriage, the device comprising at least: a first shaft (10) mounted to rotate on the aircraft about an axis of rotation (R) that is substantially parallel to a hinge axis (X) of the undercarriage relative to the aircraft; a telescopic second shaft (20) mounted to rotate on the undercarriage extending down therealong to the proximity of the wheels carried thereby; transmission means (19) for transmitting rotary motion from the first shaft to the second shaft; transmission means (21) for transmitting rotary motion from the second shaft to at least one wheel carried by the undercarriage; if the wheel is not fitted with a brake, specific brake means (30) for braking one of the shafts relative to the undercarriage; and motor means (11, 15) for causing the first shaft to rotate.

Abstract: An aircraft undercarriage comprising a strut (1) designed to be mounted in hinged manner to a structure of the aircraft, and a bottom portion (2) carrying the wheels and movable relative to the strut, the undercarriage also including an undercarriage shortener device for shortening the undercarriage between a deployed position and a raised position, said device comprising first and second members (11, 12) coupled to each other, the first member (11) being coupled to the bottom portion (2) of the undercarriage or to an element (5) that moves together with said bottom portion during movement of said bottom portion relative to the strut, while the second member (12) is hinged to the structure of the aircraft in such a manner that while the undercarriage is being raised, the second member comes into abutment before the undercarriage reaches the raised position.

Abstract: The invention relates to an overpressure and bottoming detector for a shock-absorber or the like, the detector including a hollow body inside which a piston slides sealingly and that is designed to be subjected to a pressure via an inlet of the body that is in communication with an enclosure in which said pressure exists, the piston being retained in position against the pressure by threshold retaining means adapted to release the piston when the pressure reaches or exceeds said threshold in such a manner that the piston is pushed under the effect of the pressure towards an indication position, and wherein the piston is secured to a pin that projects from the inlet of the body so as to be capable of being pushed against the threshold retaining means.

Abstract: The invention provides an active element (20) for an electromagnetic machine, the element comprising an alternating succession in a main direction (X) of portions (21) presenting a first magnetic property and of portions (22) presenting a second magnetic property, wherein the element includes a non-magnetic covering (25) that is thin relative to a thickness of the portions and that extends to cover a substantial fraction of an outside surface of the active element, the covering being secured to at least some of the portions and presenting sufficient strength to form a member for mechanically transmitting the magnetic forces to which the portions are subjected.

Abstract: The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at least one light position sensing device connected to the axle. The sensing device is located relative to the light beam emitting device for receiving at least one light beam from the light beam emitting device thereon and is operable to calculate the position of the light beam received on its surface.

Abstract: The invention provides a telescopic member that includes a cylinder in which a rod carrying a piston is mounted to slide telescopically, the telescopic member including internal abutment mechanisms that are overridable over a predetermined force when the rod comes into abutment inside the cylinder in the shortening direction. The internal abutment mechanisms include an abutment piece extending in an open bore within the rod and projecting therefrom, the abutment piece being held to the rod via a pin.

Abstract: The invention relates to a wind-brace device for an aircraft undercarriage, the device comprising a hinged brace movable between a folded position and a stabilization position for stabilizing the undercarriage in the deployed position, a stabilizer member for stabilizing the brace comprising two hinged-together arms, one of the arms having one end hinged to the brace about a hinge axis, and a spring member for urging the arm of the stabilizer member towards the locked position. The spring member is connected to a lever hinged to the brace, the lever presenting a slot in which there is engaged a finger secured to the arm that is hinged to the brace.

Abstract: The invention relates to an electrohydraulic actuator comprising a body (1) that defines a cylindrical cavity (2) in which a piston (3) slides in leaktight manner and divides an inside volume of the cavity into two chambers (A, B) of variable volume, the piston being associated with at least one rod (4) passing in leaktight manner through an end wall of the cavity, the actuator including a bidirectional pump (5) having two ports (P1, P2), each connected to one of the chambers, an electric motor (8) for selectively driving the pump in one direction or the other, the pump being placed inside the piston of the actuator so as to move together therewith.

Abstract: A method of manufacturing a mechanical component, and winding device to implementing the method. The component includes at least one insert of metal matrix composite, within which matrix ceramic fibers extend, the composite insert obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath. The method manufactures an insert preform by winding a bonded lap or bundle of coated filaments about a cylindrical component. At least some of the winding is performed in at least one rectilinear direction. The method further inserts the insert preform in a first container; performs hot isostatic compaction of the first container; and machines the first container to form a rectilinear insert.

Abstract: Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.

Abstract: A process for manufacturing a structural part made of an organic matrix composite including: production of a fibrous structure, forming a preform by braiding rovings of a fibrous material on a mandrel that includes a reinforcement in its axial extension, impregnation of the preform with an organic resin; and curing of this resin, the reinforcement, forming the cover, having a bore with an axis perpendicular to the axis for housing a connecting member. Barbs, some of which are projecting, are incorporated into the reinforcement over at least part of the surface of which lying on either side of the bore, the braiding being carried out around the barbs so that the rovings at least partly criss-cross around the barbs.

Abstract: The invention relates to a process for manufacturing a metal part reinforced with ceramic fibres, in which: at least one housing (10A) for an insert is machined in a metal body (10) having an upper face (10B); at least one insert (11) formed from ceramic fibres in a metal matrix is placed in the housing; the insert is covered with a cover; a vacuum is created in the interstitial space around the insert and said space is hermetically sealed under vacuum; the assembly, namely the metal body with the cover, is treated by hot isostatic pressure; and said treated assembly is machined in order to obtain said part. The process is characterized in that the cover comprises an element (12) covering the insert (11) in the slot and projecting from the upper face, and a sheet (14) covering the upper face with said element (12). In particular, the insert (11) is straight and the housing for the insert in the metal body forms a straight slot.