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 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: The invention relates to a method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by means other than friction, the method comprising the steps of: when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking; and performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within said braking situation, and actuating the friction brakes only if the aircraft departs from said braking situation.

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.

Abstract: The invention provides a locking device for locking together first and second elements that are movable relative to each other in an axial direction, the device comprising firstly a bushing secured to first element and including catches that are cantilevered-out in an axial direction and that are elastically deformable, and secondly an anchor portion secured to the second element and including an annular setback to receive hook-shaped ends of the catches, the device also including a locking sleeve mounted to move relative to the catches between a release position in which the catches are free to flex, and a blocking position in which the catches are prevented from flexing, wherein the locking sleeve is movable in rotation relative to the catches and includes a circumferential succession of gaps and of obstacles, such that: when the sleeve is in a first angular position corresponding to the release position, the gaps are in register with the catches which are therefore free to flex under the effect of the a

Abstract: The invention relates to an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels, each of the wheels being fitted with brakes, each having a certain number of electromechanical braking actuators, the architecture including controllers for delivering power signals to the actuators in response to a braking order, the wheels on each of the undercarriages being grouped together in first and second complementary groups such that for each group of wheels, a first group of actuators is controlled by one controller that controls those actuators only, and a complementary second group of actuators is controlled by another controller that controls only those actuators.

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 an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels (L1, L2; R1, R2), each of the wheels being fitted with a brake having a certain number of electromechanical braking actuators (1, 2, 3, 4). The architecture has at least four power supply units that power groups of actuators taken from complementary groups of wheels.

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: The invention provides an emergency power network for aircraft, for powering actuator motors (4) connected to the network, the network comprising a power bus (11) adapted to convey three-phase AC power generated by at least one DC/AC converter (12) that is powered by a DC source of the aircraft, the converter being fitted with modulator means for modulating the voltage and/or the frequency of the three-phase power generated thereby.

Abstract: The invention relates to an aircraft braking circuit having brakes with electromechanical actuators for braking wheels located at the bottom end of at least one undercarriage. In accordance with the invention, a remote unit is located at the bottom of the undercarriage close to the actuators and connected to a certain number of said actuators, the remote unit receiving a power supply via a power supply cable going down along the undercarriage, and having as many controlled switches as connected actuators for selectively powering blocking members fitted to the connected actuators, the switches being controlled independently of one another by software parking orders generated by a control unit and passing via a single communications bus going down along the undercarriage to the remote unit.

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 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: 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).