Abstract: A method for producing a metallic part including inner reinforcements of ceramic fibers, according to which: at least one recess for an insert is machined in a metallic body having an upper surface; at least one insert of ceramic fibers in a metallic matrix is arranged in the recess; the insert is covered with a cover; the gap around the insert is placed under a vacuum and hermetically sealed; the entire metallic body with the cover is treated by hot isostatic compaction; and the treated assembly is machined to produce the part. The insert is rectilinear, and the recess for the insert in the metallic body forms a rectilinear groove, the cover being dimensioned so as to be able to placed on the insert in the recess after having been shrunk by cooling and to establish a tight fit in the groove by dilation such as to close the space.

Abstract: The invention relates to a shock absorber for an aircraft undercarriage, the shock absorber comprising a main cylinder in which a rod is mounted to slide telescopically, the shock absorber having one or more pneumatic chambers filled with gas, a supply of hydraulic fluid, and throttle means for throttling the hydraulic fluid such that when the shock absorber is shortened, the gas in the pneumatic chamber(s) is compressed and the hydraulic fluid is throttled, in which the pneumatic chamber(s) is/are fully contained in one or more auxiliary cylinders external to the main cylinder, and in each of which a sealed piston is slidably mounted to separate a pneumatic chamber contained in said external auxiliary cylinder from a fluid chamber in fluid flow communication with the main cylinder. According to the invention, the throttle means are disposed at the inlet of a fluid flow connection between the main cylinder and the auxiliary cylinder(s).

Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.

Abstract: The invention relates to a method for making a metal part that comprises a reinforcement (15) made of ceramic fibres. The method comprises the following steps: forming at least one annular-shaped insert (15) by assembling a bundle of metal-coated fibres; placing the insert into a hollow metal mould (10) such that the insert is spaced between the walls (10a, 10b) of the mould; filling the mould with a metal powder; generating vacuum in the mould and closing the same; hot isostatic compressing the assembly at a temperature and under a pressure sufficient for binding the powder particles between them and for binding the insert fibres between them; removing the mould and optionally machining to the desired shape.

Abstract: The invention relates to a process for manufacturing a metal part reinforced with ceramic fibres, in which: a housing for an insert is machined in a metal body (10) having an upper face (10A, 10B); an insert (11) formed from a fibre bundle having a metal matrix is placed in the housing; a metal cover (12) is placed on the body so as to cover the insert (11); the cover (12) is welded onto the metal body (10); the assembly comprising the metal body with the cover undergoes a hot isostatic compression treatment; and said treated assembly is machined so as to obtain said part. The process is characterized in that the insert (11) is a rectilinear insert and the housing forms a rectilinear groove (10A1, 10A2, 10B1, 10B2) that extends beyond the insert and is open at each end, said groove being filled by a tab (14) during closure by the cover (12).

Abstract: The present invention relates to a process for manufacturing a metal part reinforced with ceramic fibres, in which: a housing is formed for an insert in a main metal body (2) having an upper face (21); an insert (3) formed from a bundle of fibres with a metal matrix is placed in the housing; a metal cover (4) is placed on the main body (2) so as to cover the insert (3); the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The process is characterized in that the housing has the shape of a notch of L-shaped cross section with a face (23P) perpendicular to the upper face (21) and a face (23S) parallel to the upper face (21), the cover (4) having an internal notch (43) of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover (4) being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch (23).

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 present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.

Abstract: The invention relates to a method of manufacturing a mechanical component comprising at least one insert made of metal matrix composite, within which matrix ceramic fibers extend, the composite insert being obtained from a plurality of coated filaments each comprising a ceramic fiber coated with a metal sheath, the method involving manufacturing at least one insert with a step of winding a bonded lap or bundle of coated filaments about a component of revolution. According to the invention, at least some of the winding is done in a rectilinear direction. The invention also relates to a mechanical component thus obtained and to a winding device designed for implementing the method of manufacture according to the invention.

Abstract: A landing gear for an aircraft includes a shock absorber strut (1) with upper and lower telescoping portions (2, 3), the upper portion (2) being connectable to the airframe of the aircraft. An arm (4) extends fore and aft relative to the aircraft and carrying a landing wheel, (7, 71), and pivotally connects by a main pivot (5) to the lower portion (3) of the shock absorber strut. A load reacting unit (9) connects between the arm (4) and the shock absorber strut (1) for reacting to load applied between the arm and shock absorber strut on landing. An indicator (60) monitors the load applied to the load reacting unit (9) on landing. The load reacting unit (9) may be connected between a forward end of the arm (4) and the upper portion (2) of the shock absorber strut to make the gear act as a semi-levered landing gear. Alternatively, the load reacting unit (9) may be connected between the arm (4) and the lower portion (3) of the shock absorber strut to act as a pitch trimmer.

Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

Abstract: A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with the second load bearing member such that it is frangible above an indicator load, and the cavity (25) containing an indicator liquid which escapes from the cavity once the first load bearing member is fractured by said load. The load bearing members (22, 23) comprise cylindrical members arranged concentrically with the outer member (23) having a portion of reduced thickness to render it frangible and to define the cavity (25). The cavity (25) includes an internal volume within the second load bearing member (22). The load indicator may be configured as a load bearing pin to connect two components.

Abstract: The invention relates to a shock-absorber for aircraft landing gear, the shock-absorber having two elements (1, 2) mounted to slide telescopically one in the other and defining an internal volume that is filled with hydraulic fluid and with gas, the internal volume being separated into at least two chambers (7, 8) by a separation (5) including at least one throttling orifice (10) through which the hydraulic fluid passes from one chamber to the other while the shock-absorber is being compressed. According to the invention, the separation includes at least one degassing orifice to enable gas to be transferred from one chamber to the other when the landing gear is in the deployed position, the degassing orifice being offset vertically relative to the throttling orifice so as to be located above it when the landing gear is in the deployed position.

Abstract: The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door.

Abstract: The invention relates to a power supply having two inverters (A, B) in series for powering an electromechanical actuator having an electric motor including a plurality of windings (R1, R2, R3) forming phases, each inverter being connected to its own ground (50; 51) and having a voltage source (U1; U2) having as many arms (A1, A2, A3; B1, B2, B3) as there are windings to be powered, each arm including two controlled switches (5, 6) connected in series, with a point therebetween being provided for connection to one end of one of the windings. According to the invention, each inverter includes an additional arm (A4; B4) having two controlled switches, the two additional arms being interconnected by a bridge (7) that is connected to each of the additional arms at a point that is situated between the switches.

Abstract: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.