Abstract: The invention relates to an aircraft brake for braking a wheel received on an axle presenting in succession a large-diameter cylindrical upstream portion, a conical portion, and a smaller-diameter cylindrical downstream portion suitable for receiving the wheel, the brake comprising: a stack of disks; a structural engaged on the axle and having the disks mounted thereon, the structural part comprising a support member for receiving braking actuators and including a centering portion for centering the structural part on the upstream cylindrical portion of the axle; and a torsion tube receiving the disks, the torsion tube being made integrally with the support member and the centering bearing surface and extending substantially to extend the centering bearing surface in register with the conical portion of the axle; and a braking force takeup member separably fitted on a free end of the torsion tube remote from the centering bearing surface.

Abstract: A method of distribution braking between the brakes of an aircraft. The method includes a first step of estimating a braking force objective and a steering torque objective to be achieved by the brakes of the aircraft. It also includes the steps of defining at least two groups of brakes (12, 13) and determining, for each group, a braking level that is to be achieved by the group. The braking levels being calculated in such a manner that braking performed in application of the braking levels is, at least under normal operating conditions of the brakes, in compliance with a braking force objective and with a steering torque objective.

Abstract: The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

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 relates to an aircraft undercarriage including a steerable bottom portion and a steering member suitable for turning the steerable bottom portion in response to a steering order. According to the invention, the steering member comprises a plurality of electromechanical steering actuators each having at least one main electric motor, and the actuators are disposed on the undercarriage so as to enable all of them to co-operate simultaneously with the steerable bottom portion in order to steer it, each of the electro-mechanical steering actuators including controllable coupling means for selectively placing the actuator either in a coupled state in which it is coupled with the steerable bottom portion , in which the main electric motor of the actuator is suitable for causing the steerable bottom portion to turn; or else in an uncoupled state in which it is uncoupled from the steerable bottom portion and in which the main electric motor of the actuator is isolated from the steerable bottom portion.

Abstract: The invention relates to an actuator comprising a body in which a rod is mounted to slide, the actuator including a screw extending inside the rod to co-operate with a nut secured to the rod, the screw being driven in rotation by a motor. According to the invention, the rod is associated with a piston that slides in a cavity of the body so as to define two chambers therein, the chambers being filled with hydraulic fluid and being put into communication via fluid transfer means fitted with at least one regulator member adapted to throttle the fluid expelled from one of the chambers, in at least one travel direction of the rod.

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: A method of densifying porous substrates, such as brake performs, using a liquid precursor, in which the rate at which “fresh” or “new” liquid precursor is consumed is reduced by maintaining the liquid precursor being used for the densification at a purity level that is less that pure but still chemically suitable for obtaining the desired densification product.

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: After making a carbon fiber preform and prior to completing densification of the preform with a carbon matrix, impregnation is performed with a liquid formed of a sol-gel type solution and/or a colloidal suspension enabling one or more zirconium compounds to be dispersed. The impregnation and the subsequent treatment, up to obtaining the final part, are performed in such a manner as to have, in the final part, grains or crystallites of one or more zirconium compounds presenting a fraction by weight lying in the range 1% to 10% and of composition having at least a majority of the ZrOxCy type with 1?x?2 and 0?y?1.

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: The invention provides a method of taxiing an aircraft having at least one nose undercarriage at the front of the aircraft and main undercarriages, each undercarriage having wheels, the method comprising the steps of: fitting at least one of the wheels carried by the nose undercarriage with a main taxiing motor member, and fitting at least one of the wheels carried by the main undercarriages with an auxiliary taxiing motor member; and in response to a taxiing order, powering the main taxiing motor member to cause the aircraft to taxi, and in particular if the driving force developed by the main taxiing motor member on the aircraft is insufficient, powering the auxiliary taxiing motor member, as required.

Abstract: A method and apparatus are disclosed for improving densification of porous substrate using a film boiling process. In particular, the disclosed method and apparatus permit more complete densification of a substrate (i.e., densification closer to the surface of the substrate) by selectively providing a sort of barrier that reduces cooling of the surface of the substrate being densified caused by contact with the relatively cool boiling liquid precursor of the densifying material, such as carbon. In particular, contact between the substrate and the liquid precursor is reduced using one or both of physical barriers (such as a mesh material) or structures that promote the formation of an insulating gaseous layer between the substrate and the liquid precursor (such as a plate closely spaced apart from the surface of the porous substrate). The barrier is moved into operational position before the applied power level increases sharply (as is known) near the end of the film boiling densification process.

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: 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: The invention relates to a telescopic actuator comprising a cylinder in which a main rod is mounted to slide telescopically along a sliding axis between a retracted position and an extended position. The actuator includes an auxiliary rod mounted to slide telescopically in the main rod along said sliding axis between a retracted position and an extended position, the actuator including controlled retaining means for retaining the auxiliary rod in the retracted position inside the main rod.

Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.

Abstract: The present invention relates to an inductive heating apparatus, particularly using a liquid deposition precursor, for densifying porous articles. The inductive heating apparatus using induction coils that are made from machined or milled flat metal plates, such as copper plate, instead of bending a member (especially a hollow member) into a coil shape. The induction coils according to the present invention can be more precisely and more consistently fabricated than conventional bending techniques.