Abstract: The invention relates to a mechanical part made from a metal preform presenting at least one housing (5) that extends longitudinally relative to a preferred direction for the application of forces to the mechanical part in service, and into at least one piece of fiber reinforcement is inserted and then bonded to the blank by hot isostatic compression, wherein the piece of fiber reinforcement (10) presents a chamfered end (12).

Abstract: A method of controlling a cooling device for cooling a cutting tool in a machine tool. The method comprising the steps of: controlling the motor to drive the pump in such a manner that the pump feeds the nozzle with machining fluid at a constant flow rate D1 that is equal to a first flow rate setpoint; measuring a parameter P representative of a fluid outlet pressure from the nozzle; and comparing an estimated outlet pressure Pestim as estimated from the parameter P with a first predetermined pressure threshold Ps1, and controlling the motor so as to increase the fluid flow rate D1 as delivered by the pump if the estimated output pressure drops below the first pressure threshold Ps1.

Abstract: Aircraft landing gear including at least one load bearing longitudinal structural element wherein said longitudinal structural element is hollow and is arranged to have at least one non-structural element located inside.

Abstract: A method for manufacturing a straight insert intended to be incorporated in a metal container by HIC includes placing coated wires in a rectilinear juxtaposition over a predefined length in a straight gutter-shaped tool and joining the coated wires together. The insert includes a bundle of coated wires that are joined together and have a predefined length. The wires are made from metal-coated ceramic fibers.

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: A method of fabricating a friction part out of carbon/carbon composite material, the method including obtaining a three-dimensional fiber preform of carbon fibers impregnated with a solution or a suspension enabling a dispersion of refractory metal oxide particles to be left on the fibers of the preform; applying heat treatment to form a metallic carbide by a carboreduction reaction of the refractory oxide with the carbon of the fibers; continuing the heat treatment until the carbide is transformed into carbon by eliminating of the metal; and then densifying the preform with a carbon matrix by chemical vapor infiltration.

Abstract: Aircraft hydraulic parking architecture, including a brake with a wheel braking hydraulic actuator, a pressure source (Alim) of high-pressure fluid, a normal braking hydraulic circuit (C1) including at least pressure control servo valve with a supply port (P) connected to the pressure source (Alim), a return port (R), a utilization port (U) connected to the actuator, the brake architecture further including a parking hydraulic circuit (C2) including a parking brake valve (PkBV) having an outlet port (Ps1) selectively connected either to the pressure source (Alim) or a low-pressure return circuit (CR). The outlet port (Ps1) of the parking brake valve (PkBV) is connected to the return port (R) of the pressure control servo valve.

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: The invention relates to a method of limiting a current idc supplied by a DC power supply, the method comprising: interposing a switching stage between the power supply and a load, the switching stage including a controllable switch in series with a freewheel diode; and periodically controlling the switch so that for each period of duration T, the following averaged quantity 1 T ? ? o t ? i _ · ? t is calculated in which i is a current that is an image of the power supply current idc, the averaged quantity being reset to zero at the beginning of each period, with the switch being caused to be closed so long as said averaged quantity remains below a predetermined current threshold ithresh, and with the switch being caused to be open, otherwise.

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

Abstract: The invention relates to a power distribution architecture for an aircraft for powering aircraft electromechanical actuators, the architecture comprising at least one power distribution member for distributing power to such and such an electromechanical actuator connected to the architecture, the architecture receiving power from at least one power supply bus of the aircraft. According to the invention, a DC network of voltage that is variable in controlled manner is interposed between the power supply bus of the aircraft and the power distribution members.

Abstract: Friction device includes at least two members, one of which is mobile, or potentially mobile, in terms of relative displacement with respect to the other under the action of an external stimulus. The relative displacement is liable to cause the relative displacement of two friction surfaces subjected to pressing forces, so as to convert the external stimulus into a friction force and to thus control the displacement of the mobile or potentially mobile member. The pressing forces are produced by pre-stressing mechanisms and the members are able to act on the effects of the pre-stressing mechanisms so as to use the resultant effect of the relative displacement of the mobile or potentially mobile member to reduce the pressing forces.

Abstract: A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

Abstract: The present invention relates to a method of fabricating a metal link rod (6) that is longitudinally reinforced in its thickness by fiber reinforcement (2), the method comprising the following steps: making a metal blank including at least one longitudinal housing (11, 12) leading into an edge face of the blank; inserting fiber reinforcement (2) in the housing; connecting the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (2); and finishing the blank in order to obtain a link rod (6). The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.

Abstract: A method of fabricating a composite material part having carbon fiber reinforcement densified by a matrix, including making a coherent fiber preform of carbon fibers presenting holes formed from at least a first face of the preform, and densifying the preform by depositing therein a material constituting a matrix by means of a chemical vapor infiltration type process. The holes are formed by causing a plurality of non-rotary elongate tools to penetrate simultaneously, the tools being substantially mutually parallel and presenting on their surfaces roughnesses or portions in relief suitable for breaking and/or transferring fibers they encounter, the tools being caused to penetrate simultaneously by moving a support carrying the tools, and the tools being selected to have a cross-section that makes it possible to obtain in the carbon fiber preform holes that present a cross-section with a mean dimension lying in the range 50 ?m to 500 ?m.

Abstract: A device for driving at least one door (4a, 4b) of an aircraft undercarriage bay, the device comprising a permanent mechanical linkage (20, 23, 24, 25a, 25b) between the door and the undercarriage. The permanent linkage is arranged to transform a movement of the undercarriage between a stowed position and a deployed position, or vice versa, into a go-and-return movement suitable for causing the door to open and then to close during the movement of the undercarriage between said positions.

Abstract: An apparatus includes a fitting connected to a body. The fitting has an engagement portion including a channel formed into a peripheral surface of it and an axis. The body includes an axial layer provided around at least some of the peripheral surface of the engagement portion of the end fitting and a hoop layer provided around the axial layer at a location corresponding to at least some of the channel so as to urge at least some of the axial layer into a portion of the channel. The channel is arranged such that at least some of it defines a pathway that is non-orthogonal with respect to the axis of the fitting, such that at least some of the surface area of the channel defines a load bearing surface for the transfer of torque between the fitting and body when a rotational force is applied to one of them.

Abstract: A method of making at least one stiffener element includes cutting out two substantially identical elongate flanks from fiber plates, each flank presenting two lateral projections on either side of a central portion. The flanks are superimposed with one another and stitched together along two parallel lines that mark the boundaries between the lateral projections and the central portions. The lateral projections are folded along the lines of stitching to either side of the assembly in order to form flanges.

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 telescopic actuator comprising: a cylinder having means for coupling it to a first external element; a rod mounted to slide telescopically in the cylinder along a sliding axis and including means for coupling it to a second external element; a lead screw mounted to rotate in the cylinder about the sliding axis and extending inside the rod to co-operate with a nut secured to the rod, such that rotating the lead screw causes the rod to slide; drive means for driving the lead screw in rotation; and retention means for axially retaining the lead screw, which means hold a bearing of the lead screw captive in an axial direction; wherein the retention means are arranged to retain the bearing of the lead screw with axial clearance suitable for absorbing movements imparted to the rod relative to the cylinder.