Abstract: The invention relates to a method of using and renovating a disk (9) from a stack of disks (7) of a vehicle brake, the method comprising the steps of using the disk during a plurality of lives and of compensating for loss of thickness after each life by assembling the disk with a complementary portion.

Abstract: The invention relates to a device for coupling together two elements mounted to rotate about a common axis of rotation (X) in order to enable one of the elements to be selectively driven in rotation by the other, the device comprising two members (3, 4), each secured to a respective one of the elements for coupling together, the elements being axially movable relative to each other between a remote position in which the members do not co-operate and the elements are decoupled, and an engaged position in which the members co-operate with each other in order to provide a rotary connection between the two elements.

Abstract: The invention provides a device (2) for guiding a cable (8a, 8b) in a duct (4), the device (2) being characterized in that it comprises at least one guide tube (12) receiving the cable (8a, 8b) and at least one expandable clamp (13) secured to one end (12a) of the tube (12), the expandable clamp (13) being deployed so as to be blocked against the inside wall of the duct (4) in order to hold the tube (12) in the duct (4). The device serves to guide and hold the cable in the duct without damaging the duct.

Abstract: The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135).

Abstract: A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means (21, 30) for attaching one end of each vane to the casing, the casing being characterized in that the attachment means extend on a face of the casing facing away from the vanes, the casing including orifices (26) for passing the ends of the vanes so that they can co-operate with the attachment means of the casing. A turbojet including such a casing.

Abstract: A method for distributing braking energy between a group of the braked wheels numbered 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels having a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with a unit for measuring a thickness of the stack of discs, and in which—the setting C j = E j E 1 + … ? + E p · N · C is an individual setting of braking to be generated by brake j, where p is the number of wheels concerned, C is the general setting of braking to be developed by the braked wheels of one and the same undercarriage, Ej is the thickness of the stack of discs of the brake of wheel j, and Cj the individual braking setting for wheel j. Each brake is controlled according to the individual braking setting thus determined.

Abstract: The invention provides a steering resetting method for an aircraft undercarriage that includes a leg in which a steerable bottom portion is mounted to slide against a suspension force generated by a shock absorber, the undercarriage being provided with a controllable steering member for causing the steerable bottom portion to swivel in response to an angular position setpoint, the undercarriage also including at least one angular position sensor adapted to generate an electrical signal representative of the angular position of the steerable bottom portion and suitable for use in controlling the steering member; the method comprises the step, performed when the steerable bottom portion is in an indexed angular position while the aircraft is in flight and the undercarriage is fully extended, of setting the electrical signal from the sensor to a determined reset value.

Abstract: The invention relates to a hydraulic valve comprising a body in which a bore is formed in order to receive a sleeve that includes sealing seats that cooperate with a wall of the bore to define hydraulically isolated chambers that are connected to hydraulic ports in the body, the sleeve including connection holes in order to connect at least certain chambers with the inside of the sleeve and receiving a movable element that is slidable between two end positions in order to slide in leaktight manner against an inside wall of the sleeve, wherein the sleeve includes at least one regulator hole that opens out inside the sleeve in such a manner as to be the first bore to be uncovered or the last bore to be blocked by one of the fitted portions of the movable element when said element slides from one position to another, said fitted portion having at least one face portion that presents a setback that passes over the regulator hole.

Abstract: A method of actuating undercarriage latching boxes and associated hatch latching boxes of an aircraft in an emergency mode, the latching boxes having at least one feed port and at least one unlatching member that is operable when the port is fed with fluid under pressure, the aircraft also being provided with a hydraulic braking circuit. The method includes connecting at least one tapping circuit to the braking circuit of the aircraft in association with an isolation valve that is kept, in a normal mode, in an isolation state and that can be controlled to be placed in an open state in which at least some of the feed ports of the latching boxes are fed by the tapping circuit connected to the braking circuit.

Abstract: An electric brake for an aircraft wheel comprising a support 4 formed by a torsion tube 5 and by an actuator-carrier 6, a stack 7 of disks mounted around the torsion tube 5, electromechanical actuators 8 carried by the actuator-carrier 6, each actuator comprising an electric motor 12 and a pusher 14, the electric motor 12 being adapted to move the pusher 14 facing the stack 7 of disks in order to apply a braking force selectively to the stack 7 of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack 7 of disks. The temperature measurement means comprises at least one temperature sensor 18 arranged in the pusher 14 of one of the electromechanical actuators 8 so as to be located in the immediate proximity of the stack 7 of disks when the pusher 14 is brought into contact therewith.

Abstract: The invention relates to a method of making a composite material part, the method comprising the steps of: producing a mandrel; braiding a fiber covering (11) around the mandrel fitting as closely as possible to the shapes of the mandrel; locally applying at least one fiber patch (12a, 12b, 12c) on the braided covering; repeating the two steps of braiding and patch application as often as needed to obtain a preform; and delivering resin into the preform and polymerizing it.

Abstract: An aircraft undercarriage having a strut (1) hingedly mounted to the aircraft, and a bottom part (2) carrying the wheels and movable relative to the strut. The bottom part has a rod that slides in the strut and a scissors linkage between the strut and the rod. The undercarriage has a shortener for shortening the undercarriage between a deployed position and a raised position by causing the rod to enter into the strut (1). The shortener has coupled first and second members (11, 12), the first member (11) coupled to the bottom part (2) or to an element (5) that moves with the bottom part during its movement relative to the strut. The second member (12) is hinged to the aircraft so that while the undercarriage is raised, the second member abuts before the undercarriage reaches the raised position. The first member (11) is coupled to the scissors linkage.

Abstract: The invention provides a control box for selectively delivering orders to receivers (8, 12), the control box comprising: a shaft (14) mounted to turn about an axis of rotation (X), while being capable of sliding along said axis (X) between a rest position towards which it is urged by return means (24), and an active position; order delivery means (16, 11) co-operating with the shaft (14) to deliver orders as a function of the angular position of the shaft (14); rotary drive means (15) for causing the shaft to turn; and safety actuation means (23) for causing the shaft to slide from the rest position in which anti-rotation means (27, 28) prevent the shaft from turning to the active position in which the anti-rotation means (27, 28) leave the shaft free to turn under drive from the rotary drive means (15).

Abstract: A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing is formed for an insert in a main metal body having an upper face; an insert formed from a bundle of fibers with a metal matrix is placed in the housing; a metal cover is placed on the main body so as to cover the insert; 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 housing has the shape of a notch of L-shaped cross section with a face perpendicular to the upper face and a face parallel to the upper face, the cover having an internal notch of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch.

Abstract: The invention relates to a method of fabricating a structural part comprising a tubular portion from which there projects a structural element made of composite material, the method comprising the steps of: shaping a plane preform comprising a stack of a plurality of superposed fiber plies such that over at least a fraction of the preform that is to form a structural portion, the plies are secured to one another, and over at least another fraction of the preform that is to form a portion for connecting to the tube, the plies are separable so as to form two facing sheets; inserting a tube between the sheets of the connection portion so that the sheets surround the tube at least in part; and bonding the tube to the preform such that the tube forms the tubular portion and the preform forms the structural element of the structural part.

Abstract: A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements: an elongate one-piece front portion (2) cut out from a pultruded section member comprising fibers bonded together by resin and forming a leading edge; an elongate one-piece rear portion (3) cut out from a pultruded section member comprising fibers bonded together by resin and forming a trailing edge; and a skin (5) based on resin-impregnated fibers extending between the leading edge and the trailing edge in order to form side faces of the vane and covering at least zones (6, 7) of the leading edge (2) and of the trailing edge (3); these elements being assembled together by hot compaction.

Abstract: A device, which connects a gearmotor to an aircraft wheel, comprising: a casing rotatably carrying a shaft driven by the gearmotor, the shaft having a fluted portion on which a gearwheel is mounted to slide along a longitudinal axis of the shaft without rotating relative to the shaft; a toothed ring for constraining to rotate with the aircraft wheel; and means for moving the gearwheel axially between a retracted position (disengaged from the toothed ring) and an engaged position (gearwheel meshes with the toothed ring). The means for moving comprises a hollow screw-and-nut assembly extending around the shaft, one of the elements being axially secured to the gearwheel but prevented from rotating by an anti-rotation member, and the other element of the screw-and-nut assembly being rotatably mounted inside the casing to be driven selectively by an electric motor so that rotating the electric motor causes the gearwheel to move axially.

Abstract: The invention relates to a method of fabricating a mechanical member, the method including a plurality of operations of braiding and depositing layers of braided reinforcing fibers on a mandrel (11) by using braiding machine. Each operation comprises braiding a braided layer and depositing it by moving the mandrel (11) along a central axis of the braiding machine. Each of the various superposed braided layers comprises both longitudinal fibers (12, 12G) that are parallel to a main direction of the mandrel (11), and interlacing fibers that are inclined. At least one operation is configured to form and deposit a braided layer having, in at least one cross-section of the member, a density of longitudinal fibers that differs depending on whether consideration is given to one angular region (S1) or another angular region (S2) of the same extent around the center of gravity (G) of the mandrel (11) in the section under consideration. The invention applies to fabricating structural elements in the field of aviation.

Abstract: The invention relates to a latching box for selectively retaining a movable element such as an undercarriage or a hatch in position, the box comprising a body carrying: a hook pivotally mounted about a first pivot axis between an engaged position and a disengaged position relative to the movable element; a locking member pivotally mounted about a second pivot axis parallel to the first pivot axis to pivot between a position for blocking the hook in the engagement position and a release position for releasing the hook; and at least one cam actuator in which the cam co-operates operationally with the locking member to move it towards the release position. The cam of the actuator is a cylindrical cam mounted to rotate about an axis of rotation orthogonal to the first and second pivot axes.

Abstract: A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing for an insert is machined in a metal body having an upper face; an insert formed from a fiber bundle having a metal matrix is placed in the housing; a metal cover is placed on the metal body so as to cover the insert; the cover is welded onto the metal body; the assembly including the metal body with the cover undergoes a hot isostatic compression treatment; and the treated assembly is machined to obtain the part. The insert is a rectilinear insert and the housing forms a rectilinear groove that extends beyond the insert and is open at each end, the groove being filled by a tab when the cover is placed on the metal body.