A method and system for mounting an axle in a bore of a bogie mounted on a landing gear of an aircraft, the landing gear being in a gear-down position, the bore extending in a substantially horizontal direction referred to as the axle installation direction, between a first open end and a second open end are disclosed. The method includes a) supplying a mobile bearing structure (30) comprising means for moving the axle (12) which are able to move along a direction substantially parallel to the axle installation direction, b) installing the axle (12) on the means for moving the axle, c) aligning the axis (C) of the axle (12) with the axis (B) of the bore (14), and d) inserting the axle (12) into said bore (14) of the bogie (16) by moving the means for moving the axle (12) along the direction substantially parallel to the axle installation direction.
The invention relates to a braked wheel (1) mounted on an axle (E) so as to be rotatable about an axis (X), comprising: − a first, magnetic braking device (10) comprising a stator (11) and a rotor (12) capable of producing a first braking torque, one of the stator and the rotor being arranged to move along the axis (X) between a position of free rotation and a braking position and to be returned to the position of free rotation by elastic return means; − a second, friction braking device (20) comprising a stack of discs (21.1, 21.2, 21.3, 22.1, 22.2) capable of producing a second braking torque on the wheel, the stack of discs comprising a rear face axially facing the stator or the rotor arranged to move along the axis; and - at least one actuator (41) designed to exert a pressing force on a front face of the stack of discs.
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
F16D 63/00 - Brakes not otherwise provided for; Brakes combining more than one of the types of groups
3.
METHOD FOR SECURING A PARKING FUNCTION IN AN AIRCRAFT BRAKING SYSTEM
The invention relates to a method for securing a parking function of a hydraulic braking circuit (1) supplying brakes (12a, 12b) of braked wheels (11a, 11b) carried by landing gear of an aircraft, the hydraulic circuit comprising a parking solenoid valve (13) having a service port connected to the brakes (12a, 12b) and a supply port connected, in the rest position, to a hydraulic return (102) of the aircraft, the parking solenoid valve (13) being controllable in order to connect the supply port to a pressure source (101, 2) so as to selectively transmit, to the brakes of the aircraft, a pressure that is sufficient to cause the brakes to operate, thus immobilising the aircraft, which method comprises a step of arranging, in series with the parking solenoid valve (13), a protective solenoid valve (20) allowing, when at rest, pressure to be supplied to the brakes via the parking solenoid valve, and which protective solenoid valve can be controlled to prevent pressure from being supplied to the brakes via the parking solenoid valve; and a step of controlling the protective solenoid valve (20) at least in a situation where a failure of the parking solenoid valve can induce undesired braking.
A measuring device has a magnetic circuit with a first and second armature elements that are positioned one on either side of an axis X and are manufactured with at least one ferromagnetic material. A magnet is situated between the armature elements such that a first pole of the magnet is positioned next to the first armature element and such that a second pole of the magnet is positioned next to the second armature element. A rod is arranged to be secured to a target and inserted between the armature elements to slide along the axis X. The rod has a variable section along its length such that a magnetic flux in the magnetic circuit depends on a linear position of the rod along the axis X. At least one sensor is arranged to measure the magnetic flux, which corresponds to the linear position of the target.
G01D 5/14 - Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
B60T 17/22 - Devices for monitoring or checking brake systems; Signal devices
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
F16D 66/00 - Arrangements for monitoring working conditions of brakes, e.g. wear or temperature
5.
MAGNETIC BRAKING DEVICE FOR A BRAKED WHEEL OF AN AIRCRAFT LANDING GEAR
The invention relates to a magnetic braking device (1) for a braked wheel of an aircraft landing gear, which braking device comprises a stator (2) and a rotor (3). The stator and the rotor comprise a first series of magnets (10.1) defining a radial main surface facing the air gap between the rotor and the stator, and a second series of magnets (10.2) defining a second axial main surface facing the air gap. The magnets are magnetised perpendicularly to the air gap. The first series of magnets and the second series of magnets are magnetised such that they are angularly offset from each other and such that a north pole in the first series is adjacent to a south pole in the second series.
The invention relates to an assembly consisting of a wheel and of a shaft carrying the wheel, comprising an eddy current magnetic braking device (1), the device comprising at least one stator (2) and at least one rotor (3) and at least one rotary actuator (7) connected to the rotor or to the stator, the device comprising a connection mechanism (10) connecting said actuator to the rotor or to the stator, the connection mechanism comprising: - a guide (11) mounted so as to be rotatable relative to the shaft about a first axis, - at least one connecting arm (17) connected at a first end to the guide and at a second end to the stator or to the rotor such that a rotation of the guide, via the actuator, in at least one direction of rotation, causes a translational movement of the stator or of the rotor relative to the shaft along the first axis. The invention also relates to a vehicle equipped with such an assembly.
A method for unlocking a door of an aircraft landing gear movably mounted between an open position and a closed position includes, during a first sequence of opening the door that is locked in the closed position by a first attachment housing and a second attachment housing, controlling a first unlocking actuator to deactivate the first attachment housing, waiting a first waiting time greater than a time necessary for the door to initiate a passage from the closed position to the open position, so as to enable a detector to detect the door starting to open, detecting the door starting to open by the detector and whether there is a failure of the second attachment housing, and controlling a second unlocking actuator to deactivate the second attachment housing.
The invention relates to a method for predicting an item of information on the friction of an aircraft landing runway, the method comprising, for a given time: obtaining (S100) items of runway context data, obtaining (S101) items of friction information history data for the runway comprising items of data that are all older than the given time, a prediction (S102) by a prediction model configured to receive, as input, at least the items of context data for the given time and the items of friction information history data, and to deliver an item of predicted friction information (p) for the runway for the given time.
A method for protecting a carbon-carbon composite material part from oxidation, the method including applying an impregnation composition comprising at least one metal phosphate to at least one portion of the outer surface of the part; depositing, by a dry deposition process, a solid composition of an oxidation-resistant glass on at least one portion of the outer surface of the part, once the impregnation composition has been applied; and conducting an impregnation heat treatment in order to soften or melt the solid composition deposited by a dry deposition process, to allow the internal porosity of the part to be impregnated with the thus-softened or thus-melted composition, and to form an oxidation-resistant glass in the internal porosity of the part.
An eddy current magnetic braking device includes two outer elements surrounding a central element in relative movement with respect to the two outer elements, the central element being made of an electrically conductive material, the two outer elements having first faces facing opposite second faces of the central element and each of the two outer elements including plural magnets for emitting, via the first faces, a magnetic flow that generates in the central element eddy currents when the two outer elements are in relative movement. The plural magnets are arranged in such a way that the two outer elements attract each other. The central element has a thickness such that a skin effect is generated from each face of the central element over more than half the thickness of the central element over at least a range of possible relative speeds of the central element relative to the two outer elements.
A braking device includes one or more stationary elements and one movable element that is movable with respect to the one or more stationary elements, the moveable element being made of an electrically conductive material, one or the one or more stationary elements including magnets capable of generating eddy currents in the movable element, when the one or more stationary elements and the movable element are in relative movement. The magnets include first magnets and second magnets disposed alternating, the first magnets having a first magnetization vector and each of the second magnets having a second magnetization vector, and the magnets have widths such that the first magnets are spaced apart in pairs by a first distance that is less than a second distance separating the second magnets in pairs, and the length of the second magnets being around 70% of the length of the first magnets.
The invention relates to a braked wheel (1) of a vehicle, which wheel is rotatably mounted on an axle (E) so as to rotate about an axis (X) and comprises a magnetic braking device (10, 10') comprising a rotor (20, 20'), a stator (30, 30') and an actuator (40, 40') arranged to move the rotor and the stator relative to one another along the axis of rotation of the wheel between a free rotation position and a braking position, wherein one of the rotor and the stator comprises a first magnetic ring (31, 31' 32', 33') inside which a second magnetic ring (32, 32', 33', 34') extends so as to form an annular groove (36, 36.1', 36.2', 36.3') and the other of the rotor and the stator comprises a sleeve (22, 21', 22', 23') that is arranged so as to fit into the annular groove in order to produce, between the rotor and the stator, a radial magnetic flux capable of generating eddy currents when the wheel rotates.
F16D 63/00 - Brakes not otherwise provided for; Brakes combining more than one of the types of groups
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
13.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a magnetic braking device for a vehicle wheel, the device comprising at least one stator element (2) arranged so as to be rotatably connected to a portion of the vehicle supporting the wheel, a rotor element (3) arranged so as to be rotationally connected to the wheel, magnets for producing, between these elements, a magnetic flux capable of generating eddy currents in one of the elements when the wheel rotates and a braking control unit (11) that receives, as input, a braking command to apply a braking force according to the braking command. The magnets comprise at least one electromagnet (9) and the device comprises at least one anti-locking control unit (16) that receives, as input, a vehicle speed signal and a wheel rotational speed signal and provides, as output, a control signal of the electromagnet according to a comparison of speeds from the signals received as input. The invention also relates to an aircraft wheel and a landing gear comprising such a device.
The invention relates to a method for recycling an effluent gas (50) resulting from chemical vapour deposition or infiltration of pyrocarbon and comprising dihydrogen, C1 to C4 light unsaturated hydrocarbons and C5+ heavy hydrocarbons, the method comprising the following steps: a) removing (60) the heavy hydrocarbons (501) from the effluent gas; b) catalytically hydrogenating (80) the light unsaturated hydrocarbons so as to remove them by transforming them into C1 to C4 light saturated hydrocarbons, this catalytic hydrogenation step being carried out on the effluent gas obtained after carrying out step a) and consuming some of the dihydrogen present in the effluent gas; and c) adding the effluent gas (402) obtained after carrying out step b) to a reaction chamber (30) and forming pyrocarbon by chemical vapour deposition or infiltration using the C1 to C4 light saturated hydrocarbons present in the effluent gas thus added.
Landing gear (101) comprising at least: - a shaft (102), - at least one wheel (103) rotatably mounted on the shaft, - at least one braking device (1) for braking the wheel, - at least one measurement device (10) arranged to measure a rotational speed of the wheel, the landing gear being configured in that the measurement device is arranged between the friction member and the shaft, the measurement device comprising at least one target (11) coupled in rotation to the wheel and at least one support (12) coupled to the shaft, the support bearing at least one sensing component (13) arranged facing a rotary trajectory of the target and able to cooperate with the target to generate at least one signal representative of the rotational speed of the wheel. Corresponding aircraft.
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/171 - Detecting parameters used in the regulation; Measuring values used in the regulation
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
The invention relates to a hydraulic actuation system (100) comprising at least one tank (104) connected, via a flow restriction, to a pump (103) driven by a motor (101), a hydraulic actuator (112) associated with a control valve (113), a temperature sensor (108) for the hydraulic fluid in the tank (104) and an electronic control unit (102) arranged to implement a heating phase when the temperature of the hydraulic fluid in the tank (104) reaches a first predetermined minimum temperature threshold by activating the motor (101) driving the pump (103) when the control valve (113) is in a state of not supplying the actuator in order to circulate the hydraulic fluid through the restriction. The invention also relates to an aircraft comprising such a system.
The invention relates to a braked vehicle wheel (1) rotatably mounted on an axle (E) about an axis (X), comprising: a first eddy current braking device (10), comprising a first actuator (31) having a first piston (31.1) received in a first cavity (30.1) in order to define therein a first chamber (41.1) and a second chamber (41.2); and a second friction braking device (20), comprising a second actuator (32) having a second piston (32.1) received in a second cavity (30.2) in order to define therein a third chamber (42.1) and a fourth chamber (42.2), characterised in that the first actuator comprises a first main port (51.1) opening into the first chamber, a first connection port (51.2) positioned to open into the first chamber or into the second chamber according to the position of the first piston, and a second connection port (51.3) positioned to open into the second chamber; and in that the second actuator comprises a second main port (52.1) opening into the third chamber, the second main port being connected to the first connection port and to the second connection port of the first actuator by a bypass duct (63).
B60T 1/10 - Arrangements of braking elements, i.e. of those parts where braking effect occurs acting by retarding wheels by utilising wheel movement for accumulating energy, e.g. driving air compressors
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
F16D 61/00 - Brakes with means for making the energy absorbed available for use
18.
WHEEL WITH COMBINED MAGNETIC/FRICTION BRAKING FOR A VEHICLE, AND AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a braked vehicle wheel (103) comprising at least one hub portion (104.1) and one rim portion (105.1) that is coaxial with the hub portion (104.1), thereby defining an annular space (108), which rim portion is connected to the hub portion (104.1) by a disc portion (106.1), the wheel comprising: - a first friction braking device (50) comprising at least one rotor disc and one stator disc housed in the annular space and at least one first actuator (56) rigidly attached to an actuator-bearing ring (54) that is fixed with respect to a shaft (102) for rotating the wheel; - a second magnetic braking device (1) comprising a rotor (3), a stator (2), at least one second actuator (7) for axially moving the stator (2) and the rotor (3) relative to one another between a braking position and a freely rotatable position, and a plurality of magnets (11, 12, 13, 14) arranged to emit, between the rotor (3) and the stator (2), a magnetic flux capable of producing a braking force when the stator (2) is in the braking position; characterised in that the second actuator (7) is mounted on the actuator-bearing ring (54) in opposition to the first actuator (56). The invention also relates to a landing gear and to an aircraft comprising such a wheel.
B60T 1/10 - Arrangements of braking elements, i.e. of those parts where braking effect occurs acting by retarding wheels by utilising wheel movement for accumulating energy, e.g. driving air compressors
B60T 8/17 - Using electrical or electronic regulation means to control braking
19.
AIRCRAFT LANDING GEAR COMPRISING A WHEEL WITH INTEGRATED MAGNETIC BRAKING DEVICE
The invention relates to a landing gear for an aircraft comprising a leg having an end carrying a shaft on which a wheel (103) is mounted. The wheel comprises a hub (104.1) and a rim (105.1) that is coaxial with the hub and connected to the hub via a disc portion (106.1). The wheel comprises an eddy-current magnetic braking device (1) comprising a rotor (3) that is rotatably connected to the wheel and a stator (2) that is rotatably connected to the leg, that is rotatable with respect to the rim (105.1) and to the rotor (3), and that carries a plurality of magnets (11, 12, 13, 14) capable of emitting a magnetic flux in the rotor. The rotor is made of an electrically conductive material so as to be able to give rise to eddy currents and the rotor is formed of one piece with the rim (105.1).
WHEEL LANDING GEAR PROVIDED WITH AN EDDY-CURRENT MAGNETIC BRAKING DEVICE USING RADIALLY MOVABLE MAGNETS, AND AIRCRAFT PROVIDED WITH SUCH A LANDING GEAR
The invention relates to a landing gear comprising a wheel provided with an eddy-current magnetic braking device (1) that comprises at least one stator (2) and one rotor (3), and magnets (4) rigidly attached to one of the stator or the rotor in order to produce therebetween an axial magnetic flux capable of generating eddy currents in the other of the stator or the rotor as the wheel rotates. One of the rotor (3) and of the stator (2) is a disc and the other of the rotor (3) and of the stator (2) is a ring divided into at least two ring sectors (2A, 2B, 2C, 2D) which are radially movable between a first position in which each ring sector (2A, 2B, 2C, 2D) has at least one face (2.1, 2.2) facing a face (3.1, 3.2) of the disc in order to establish the axial magnetic flux and a second position in which the at least one face (2.1, 2.2) of the ring sector (2A, 2B, 2C, 2D) is radially offset with respect to the face (3.1, 3.2) of the disc in order to interrupt the axial magnetic flux. The invention also relates to an aircraft comprising such a landing gear.
The invention relates to an assembly comprising at least a first part (1) and a second part (11) which are concentric, extending about a common axis (X). At least the first part (1) comprises first radial bores (1.1) having two open ends, and the second part (11) comprises second radial bores (11.1), each second radial bore (11.1) forming an extension of one of the first radial bores (1.1) and having one end opening opposite one of the open ends of the first radial bore (1.1) in order to form a pair of aligned bores. One key (2) extends in each pair of aligned bores in order to connect the concentric parts (1, 11) with one another so as to rotate about and translate along the common axis.
A method for manufacturing a diaphragm holder for a shock absorber of the oleo-pneumatic type, in particular for an aircraft landing gear. The diaphragm holder includes a first end with a dome, and a tubular portion extending from the dome to a second end. The method includes a step of overmolding a first material onto an insert. The insert can be a second material with a value of compression breaking stress divided by density that is higher than the first material or alternatively, of a material identical to the first material. A diaphragm carrier which can be manufactured by this method.
F16F 15/023 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system using fluid means
23.
BRAKED VEHICLE WHEEL ACTUATED BY MEANS OF DEFORMABLE PARALLELOGRAMS, AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to an eddy-current-based magnetic braking device comprising two external elements (2) flanking a central element (3) aligned with the same axis as the external elements, which central element rotates about the axis with respect to the external elements (2), the external elements (2) each carrying a plurality of magnets (11, 12, 13, 14) able to emit a magnetic flux which gives rise to eddy currents in the central element (3) when the elements (2, 3) are moving relative to one another. The magnets are arranged so as to cause the external elements to be magnetically attracted to one another. Friction-based braking surfaces are joined so as to rotate as one with the external elements and with the central element, respectively. The external elements are movable with respect to the axis between a position close to the central element, in which position the first braking surfaces are held applied against the second braking surfaces by magnetic attraction and a position spaced apart from the central element, in which position the first braking surfaces are spaced apart from the second braking surfaces. The invention also relates to an aircraft wheel and to a landing gear comprising such a device.
F16D 55/224 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads with a common actuating member for the braking members
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 63/00 - Brakes not otherwise provided for; Brakes combining more than one of the types of groups
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
F16D 121/20 - Electric or magnetic using electromagnets
24.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR AND AIRCRAFT WHICH ARE EQUIPPED WITH SUCH A WHEEL
An eddy current magnetic braking device (1) for a wheel, comprising a stator (2) and a rotor (3), wherein the rotor comprises at least two sub-assemblies (13) and the stator comprises at least two sub-assemblies (10), one proportion of the sub-assemblies each comprising at least one magnet (4) for producing, between the rotor and the stator, a magnetic flux in the other proportion of the sub-assemblies when the wheel rotates, the rotor or the stator being mounted so as to be movable between a first position in which each sub-assembly of the rotor has at least one face facing a face of one of the sub-assemblies of the stator and a second position in which said faces are offset from one another, the device comprising at least one actuator (6) connected to the rotor or to the stator in order to move the rotor or the stator between these two positions. The invention also relates to an aircraft wheel, landing gear and aircraft comprising such a device.
H02K 49/04 - Dynamo-electric clutches; Dynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
The invention relates to a wheel including an eddy current magnetic braking device, the device comprising at least one stator and at least one rotor, and magnets secured to one of the latter in order to produce therebetween a magnetic flux capable of generating eddy currents in the other when the wheel rotates. According to the invention, the rotor is rotatably connected to the wheel via a transmission mechanism of the wheel. The invention also relates to a landing gear and an aircraft including such a wheel.
An industrial assembly (80) with a gas turbine (90) comprises a pollutant-gas treatment device (70) capable of treating the gas flow displaced by the gas turbine (90). This treatment device (70) comprises a solid adsorbent (71), and the industrial assembly (80) comprises a heat recuperator (40) able to recover the heat emitted by the turbine (90) and then transfer this heat to a fluid supply device (50) that heats a fluid (51), the treatment device (70) being able to adsorb the pollutant gas from the gas flow into the adsorbent (71), and then to desorb the adsorbent (71) by heating, by the fluid (51), to a heating temperature (Tc) at least equal to the desorption temperature (Td) of said adsorbent (71), and to send the pollutant gas supplied by this desorption into a storage tank (60).
B01D 53/04 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
The invention relates to a gas turbine (90) test bench (80) comprising a building (88) which comprises an air inlet stack (81) at its first end and a gas exhaust stack (83) at its second end, a test hall (82) containing the gas turbine (90) intended to be tested, and at least one pollutant gas treatment device (70) capable of treating the gas flow which is displaced by the gas turbine (90) during operation and which flows to the exhaust stack (83). The pollutant gas treatment device (70) comprises a solid adsorbent (71) which consists of at least one modular block (72) having a plurality of channels (73), the walls of which are adsorbent and in which the displaced gas flow is able to flow.
B01D 53/04 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
28.
EDDY-CURRENT-BASED MAGNETIC BRAKING DEVICE, VEHICLE BRAKED WHEEL AND AIRCRAFT LANDING GEAR EQUIPPED WITH SUCH A WHEEL
An eddy-current-based magnetic braking device includes two external elements flanking a central element that is aligned with a same axis as the external elements and that rotates about said axis with respect to the external elements, the external elements each bearing magnets that emit a magnetic flux that engenders in the central element eddy currents. The magnets are placed so as to generate a magnetic attraction between the external elements. Friction-based braking surfaces are joined so as to rotate as one with the external elements and with the central element, respectively. The external elements are moveable with respect to the axis between a proximate position of the central element, in which position the first braking surfaces are held applied against the second braking surfaces via the magnetic attraction, and a separated position of the central element, in which position the first braking surfaces are separated from the second braking surfaces.
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 55/38 - Brakes with a plurality of rotating discs all lying side by side mechanically actuated
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
F16D 121/20 - Electric or magnetic using electromagnets
H02K 49/04 - Dynamo-electric clutches; Dynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type
29.
DEVICE FOR AXIALLY LOCKING A FIRST TUBULAR ELEMENT FITTING TIGHTLY INTO A SECOND TUBULAR ELEMENT
The invention relates to a device (100) for axially locking a first tubular element (20) fitting tightly into a second tubular element (E), the locking device comprising a tubular body (101) including an outer annular groove (101.2) in which a ring (102) is slidably mounted along a longitudinal axis (Y101) of the body between a locked position and a released position, the ring comprising a wheel (102.1) having a front face from which elastically deformable outer hooking claws (102.2) extend projecting axially between a state in which they project radially from the body and a state in which they are retracted into the body, and the groove in the body comprising a bottom (101.7) shaped to keep the claws in their projecting state when the ring is in the locked position, and to allow the claws to transition from the projecting state to the retracted state when the ring is in the released position.
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
F16D 1/033 - Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
F16B 21/18 - Means without screw-thread for preventing relative axial movement of a pin, spigot, shaft, or the like and a member surrounding it; Stud-and-socket releasable fastenings without screw-thread by separate parts with grooves or notches in the pin or shaft - Details
A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.
An assembly of a disk brake system (2) of an aircraft landing gear (I) and a monitoring device (3), the disk brake system (2) comprising at least one stator disk (21) and at least one rotor disk (22) configured to be pressed against said stator disk (21), the monitoring device (3) comprising a tape (30), the tape (30) comprising at least one visual information item associated with a predetermined circumferential range of the stator disk (21), the tape (30) being positioned in contact with the circumference of the stator disk (21), a first gripping member (31) attached to a first end of the tape (30) and a second gripping member (32) attached to a second end of the tape (30) so as to make it possible to stretch the tape around the circumference of the stator disk (21) in order to accurately determine the circumference of the stator disk (21).
A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.
An aircraft landing gear includes a strut mounted to an aircraft structure and moveable between extended and retracted positions. A bracing member includes a first bracing connecting rod hinged to the aircraft structure and a second bracing connecting rod hinged to the first bracing connecting rod and to the strut. A stabilizing member includes a first stabilizing connecting rod and a second stabilizing connecting rod hinged together. The second connecting stabilizing rod is hinged to the first bracing connecting rod. At least one spring is arranged to be resiliently subjected to a bending force when the hinges of the first and second stabilizing connecting rods move from their aligned position.
An aircraft landing gear includes a stationary element and one or more movable elements which can move relative to the stationary element between a first position and a second position, and one or more shape sensors, connected to an electronic processor arranged to deduce the position of the movable element of the shape of the shape sensor. The shape sensor includes a first section rigidly connected to the stationary element and a second section rigidly connected to the movable element so that the first section and the second section are immobile with respect to the stationary element and the movable element respectively, and are movable relative to one another.
The invention relates to a maintenance system (1) of an oleo-pneumatic shock absorber (2), comprising wedges arranged to be assembled so as to form a plurality of wedge devices of different heights and each associated with a separate temperature range, each wedge device being arranged to be installed on the shock absorber by being positioned between one end (8) of the cylinder (4) through which the rod (5) is inserted and one end (9) of the rod located outside the cylinder, such that, when the shock absorber is compressed so that the end of the cylinder or the end of the rod abuts against the wedge device, an oil volume in the chamber (10), when the latter is maximally filled, is equal to an optimised volume for an oil temperature comprised in the temperature range associated with the wedge device.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/44 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details such means combined with temperature correction
36.
SYSTEM FOR LOCKING A SLIDING MEMBER COMPRISING AN INTEGRATED MONITORING MEMBER, AND CORRESPONDING DRIVE MECHANISM, WHEEL AND AIRCRAFT
The invention relates to a system for locking a member comprising: - a housing (9) having a chamber (12) which is intended to slidably receive the member; - balls (20) that are arranged to at least partially project out into the chamber; - a lock (22) that is mounted in the housing so as to be movable between a locked position in which, when in operation, the lock presses the balls against the member in order to hold the member in position in the housing and an unlocked position in which, when in operation, the member can slide inside the housing, the lock being arranged in the housing in such a way that, in the locked position, the lock bears against at least one wall (15) of the chamber and that, in the unlocked position, the lock is away from the wall, the system further comprising at least one element (36) for detecting this temporary contact. The invention further relates to a corresponding drive mechanism and an aircraft wheel.
The invention relates to a method for braking an aircraft (11) on the ground, which aircraft comprises at least a first wheel (13a) provided with a first brake (14a) and with a drive actuator (15), and at least a second wheel (13b) provided with a second brake (14b) but not provided with a drive actuator, the method comprising the steps of: • - selecting, in order to brake the aircraft on the ground, a first braking mode or a second braking mode having a lower braking capacity; • - braking the aircraft by producing a first braking setpoint (Cl) for the first brake (14a) and a second braking setpoint (C2) for the second brake (14b) such that, if the first mode is chosen, a ratio of the first braking setpoint to the second braking setpoint is equal to a first value and, if the second mode is chosen, the ratio is equal to a second value that is lower than the first value.
The invention relates to an aircraft wheel (1) braking device (10), comprising: - a torque tube (13, 13') extending along a longitudinal axis; - a stack of brake discs (11) including a last stator disc; - at least one actuator (18) comprising a piston translatably mounted between a first end position in which the piston is spaced apart from the stack of discs and a second end position, in order to exert a pressing force on the first stator disc; and - at least one stud (14) arranged between a second end of the torque tube and the last stator disc in order to take up and transfer the pressing force to the torque tube. The last stator disc and the torque tube are shaped so as to define therebetween a minimum clearance which is less than the distance separating the piston from its second end position when the piston exerts the pressing force.
A wheel including a rim that rotates on a shaft defining a primary rotational axis and a magnetic braking device. The magnetic braking device includes an actuator which includes a first transmission assembly and one second transmission assembly each includes a pinion mounted on the support to pivot about a secondary rotational axis parallel to the primary axis, an operating bar extending about the secondary axis, a first mechanical connecting member connecting the operating bar to the pinion of the transmission assembly and a second mechanical connecting member connecting the operating bar to one of the stators, and the mechanical connecting members are arranged. The rotation of the pinions causes a movement of the stators parallel to the secondary axis in opposite directions, for varying the air gap, one or more of the mechanical connecting members of each transmission assembly being arranged to ensure a screw-nut helical connection.
A tooling for winding a fibrous fabric on a support, allowing gradual modification of the shape of the support as winding progresses, and includes compaction devices to reduce wrinkling of the fabric obtained after compaction.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
41.
METHOD FOR MONITORING AN AIRCRAFT LANDING GEAR EMPLOYING AT LEAST ONE ACCELEROMETER SUPPORTED BY A WHEEL OF THE LANDING GEAR, AND AIRCRAFT IMPLEMENTING THIS METHOD
A method for monitoring an aircraft landing gear. The method includes using information from at least one accelerometer firmly secured to a landing gear wheel mounted to rotate on a landing gear axle to estimate an angle of deflection α of the axle at least when the wheel is in contact with the ground.
An inspection tool configured to be fitted to an endoscope includes a body with an attachment portion configured to be attached to one end of the endoscope, and an opening. The tool further includes a transparent element with at least one visual reference mark having a calibrated dimension, wherein the transparent element is mounted at the opening in the body.
A61B 1/00 - Instruments for performing medical examinations of the interior of cavities or tubes of the body by visual or photographical inspection, e.g. endoscopes; Illuminating arrangements therefor
An uplock for retaining a capture pin of a movable part includes a hook that is movable between a release position and a retaining position, a locking part that interacts with the hook and is movable between a locking position and an unlocking position, and a detector. The detector includes a first sensor for detecting whether the hook is in the retaining position, and a second sensor for detecting a presence of the mobile part in the immediate vicinity of the uplock in the position occupied by the mobile part when the capture pin is in the hook.
E05B 81/68 - Monitoring or sensing, e.g. by using switches or sensors the bolt position, i.e. the latching status by sensing the position of the detent
E05B 81/70 - Monitoring or sensing, e.g. by using switches or sensors the wing position
Device (10, 10') for hooking a moving element (T) with a hook (C), the device comprising a roller (11, 11') mounted on a shaft (12) such that it can move in translation between two end positions along a longitudinal axis of the shaft, and be returned to a rest position between the two end positions by elastic return means (18.1, 18.2).
A method for treating a surface of a rod of a piston, the rod being made of high mechanical strength alloy with a minimum hardness above 45 HRC, includes a grinding procedure, and a polishing procedure performed until a mean roughness Ra≤0.2 μm is obtained. This results in a surface finish allowing the dynamic sealing requirements of the piston to be maintained without requiring chrome plating.
B24B 19/00 - Single purpose machines or devices for particular grinding operations not covered by any other main group
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
F16D 121/04 - Fluid pressure acting on a piston-type actuator, e.g. for liquid pressure
A method for manufacturing a part includes a metal substrate at least partially covered with a protective layer, includes preparing a surface of the substrate to be covered, forming by spraying, according to an HVOF spraying method, a coating layer on the prepared surface, this coating layer being formed by spraying a powder mixture containing submicronic metal carbide grains, impregnating the coating layer with an organic impregnant together forming an impregnated layer, finishing by polishing at least one surface of the impregnated layer in order to form a protective layer having a polished surface having a roughness Ra of less than 0.2 μm or of less than 0.1 μm depending on the applications.
The invention relates to a landing gear (1) comprising: a leg (2) having a hinge for pivoting between a retracted position and a deployed position; a main brace (5) having a state in which the leg (2) is stabilised in the deployed position, in which position the main brace (5) defines a main force-take-up path; a mechanism for manoeuvring the leg (2) at least from its deployed position to its retracted position; and a mechanism for stabilising the leg (2) in the retracted position. The manoeuvring mechanism comprises a rotary actuator (15) which is positioned outside the main force path when the leg (2) is in the deployed position and which actuates a single crank (16), and a connecting rod (17) having a first end hinged to the leg (2) and a second end hinged to the crank (16) in order to form with the crank the mechanism for stabilising the leg (2) in the retracted position. The invention also relates to an aircraft provided with such a landing gear.
A thrust reverser device for an aircraft turbojet engine nacelle an electro-hydrostatic actuation system that includes a motor pump and a first actuation assembly. The first actuation assembly includes a series of at least two actuators configured to be attached to a movable cover of the thrust reverser and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle. The first electro-hydraulic actuation system further includes a volumetric flow divider with an inlet connected to the motor pump and at least two outlets, wherein each outlet is connected to an actuator. The volumetric flow divider is configured to receive a fluid and to supply the fluid to the actuators with an equal flow rate.
F02K 1/76 - Control or regulation of thrust reversers
F15B 7/00 - Fluid-pressure actuator systems in which the movement produced is definitely related to the output of a volumetric pump; Telemotors
F15B 20/00 - Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
49.
AIRCRAFT LANDING GEAR PROVIDED WITH AT LEAST ONE MOTORIZED WHEEL
An aircraft has an upper portion and a lower portion provided with a first and second axle. The first axle is provided with a braked wheel and the second axle is provided with a motorized wheel. A landing gear of the aircraft includes a main arm pivoting with respect to the strut on which the first axle is fixed. The second axle is fixed on the strut, and a main actuator moves the first axle between a remote position and a close position with respect to the upper portion. In the close position, the braked and motorized wheels are simultaneously in contact against a running plane, and in the remote position, the braked wheels are in contact against the running plane while the motorized wheel is at a distance from the running plane.
Embodiments of the invention relate to a landing gear wherein it includes at least one static sealing point, the static sealing point comprising a gasket made of elastically deformable material held between a portion of a first part of the landing gear and a portion of a second part of the landing gear, the first and second parts of the landing gear comprising a steel substrate coated with a zinc and nickel alloy coating, including in mass percentage of the alloy between 12% and 18% and nickel, at most 0.5% of elements other than nickel and zinc, the balance being zinc, and the roughness Ra of the surface of the portions of the first and second parts of the landing gear being less than or equal to 1.6 μm.
The invention relates to a method for taxiing an aircraft while anticipating an inability of a drive member equipping at least one wheel (RA) borne by a landing gear (AA) of the aircraft (A) to move said aircraft on the ground, the method comprising the following steps: a) determining at least one of the following values: a minimum traction effort (101) required by the drive member to move the aircraft, a maximum traction effort (201) that is transmissible to the ground via the wheel through grip, and heating (301) of the drive member; b) comparing each value with a predetermined threshold (102, 202, 203); c) from the comparison, deducing a capacity of the drive member to move the aircraft.
An uplock for the selective retention of a capture pin of a movable element includes a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position for retaining the capture pin. The locking member moves between a locked position, and an unlocked position. The detector detects whether the hook is in the retaining position and the capture pin is in the hook. The detector includes a sensor movable relative to a target. The target or the sensor is carried by the locking member and the other by an indicator lever which is movable between a first position indicating absence of the capture pin in the hook and a second position indicating presence. The target and the sensor are only in the proximate position if the locking member is in the locked position and the indicator lever is in the second position.
The invention relates to a method for post-anodisation sealing of aluminium or aluminium alloy without using chromium. The invention also relates to a method for treating the surface of a part made of aluminium or aluminium alloy intended for use in the aviation sector, including at least the following steps: i) subjecting the part to an anodisation step; ii) treating the anodised part by a post-anodisation sealing method according to the invention; and optionally iii) applying one or more coat(s) of paint. The invention also relates to a part made of aluminium or aluminium alloy treated by a post-anodisation sealing method according to the invention, optionally including one or more coat(s) of paint.
An uplock for selectively retaining a capture pin of a movable element including a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position. The locking member is movable between a locked position that immobilizes the hook and an unlocked position in which the hook is free. The detector detects whether the hook is in the retaining position and the capture pin is present in the hook. The detector includes a sensor associated with a single target which is movable between two positions The sensor emits a signal which is modified when the target passes from one of the positions to the other. The target is independently in kinematic interaction with the hook and the capture pin.
Said method for determining aircraft landing runway conditions comprises the steps of: acquiring a set of data groups of different types (D1, D2) for evaluating and monitoring runway degradation conditions; deriving weighting coefficients (Ki) from each data group; filtering the data; determining, for each data group, a partial runway condition; modifying the weighting coefficients of each data group; and combining the partial runway conditions to derive a runway condition coefficient (RWYCC) associated with a confidence index (C1) derived from the modified weighting coefficients.
A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.
The invention relates to a method for manufacturing a steel part (10) for an aircraft, the method comprising the welding of at least two steel elements (12, 14) to one another so as to form this part (10), the application of a resistance treatment to the part (10) which comprises austenitization (30) followed by quenching (32) and at least one step of tempering (34), and the local application, to a weld bead (16) between the at least two elements (12, 14), of a softening treatment comprising heating the weld bead (16) to a softening temperature lower than the temperature Ac1 at which the steel starts to transform from ferrite into austenite.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
Method for manufacturing a part made from carbon/carbon composite material, comprising:
the formation of a carbonaceous preform,
partial densification of the preform by a pyrocarbon matrix thus forming a partially densified blank,
the impregnation of the partially densified blank with an impregnation solution including ceramic particles or ceramic precursors, and
the drying of the impregnated blank.
Method for manufacturing a part made from carbon/carbon composite material, comprising:
the formation of a carbonaceous preform,
partial densification of the preform by a pyrocarbon matrix thus forming a partially densified blank,
the impregnation of the partially densified blank with an impregnation solution including ceramic particles or ceramic precursors, and
the drying of the impregnated blank.
Furthermore, the viscosity of the dispersion or impregnation solution is controlled in order to control the homogeneity of the distribution of the ceramic particles in the part of the impregnated composite material during drying.
Method for creating a 3D digital model of at least one aircraft element in order to produce augmented reality image(s), the method including the steps of: a) scanning, at least one element of an aircraft so as to produce a set of digitised points representative of the 3-dimensional shape of the element, then, using a computer and/or at least one computer processing unit; b) forming, from the set of digitised points, at least one 3D mesh representative of the shape of the element; c) modifying a replica of the given mesh so as to add a missing geometric pattern corresponding, in particular, to a pattern of the element located in its inner volume and/or which is located outside the field of view of the scanner during the scanning in step a).
A connecting device for connecting two mechanical parts includes a rod having a section between a stop and a threaded portion. The rod is inserted into the parts, and a nut is screwed onto the threaded portion in order to hold the parts between the stop and the nut. An anti-rotation system blocks rotation of the nut and includes a washer interacting with the rod to be constrained to rotate with it. The washer has two protuberances, each engaged in a notch of shape complementary to the rod. The anti-rotation system has a ring with an inner periphery of with a shape complementary to that of an outer periphery of the nut in order to be secured to the nut. The ring is secured to the washer by a screw.
F16B 39/10 - Locking of screws, bolts, or nuts in which the locking takes place after screwing down by a plate or ring immovable with regard to the bolt or object
An aircraft wheel including a rim fitted with rotor disks driven in rotation with the rim by first splines secured to the rim and engaged in notches in the rotor disks, stator disks interposed between the rotor disks and provided with notches engaged on second splines secured to a brake torque tube arranged to be fastened to an axle carrying the aircraft wheel, one or more heatpipe extending in one or more of the first and second splines parallel to a plane containing an axis of rotation of the wheel, the heatpipe having an end projecting outside the aircraft wheel, and one or more heatsinks secured to the end of the heatpipe.
A braking device for braking a wheel of an aircraft, a hub of which is mounted rotatably on an axle includes a stack of discs threaded on a torque tube which is attached to the axle and equipped internally with a heat shield extending opposite an outer surface of the hub facing the stack of discs to protect the hub from heat radiation generated by the stack of discs. The heat shield includes a tubular body which is coaxial to the torque tube and retaining tabs which are resiliently deformable and secured to the tubular body, each of the retaining tabs and an inner surface of the torque tube including additional raised portions to engage with one another so as to axially immobilize the heat shield inside the torque tube.
A motor sub-assembly for an electromechanical brake actuator of an aircraft wheel includes a casing, a shaft mounted in the casing, and an electric motor mounted in the casing rotate the shaft, the shaft having an end connected to a screw-and-nut assembly to exert a force on a stack of disks for braking the aircraft wheel. The shaft has a first set of teeth and the motor sub-assembly has a shuttle mounted to slide relative to the casing and provided with a second set of teeth. The motor sub-assembly includes a selector mechanism that moves the shuttle selectively between first and second positions in which the first set of teeth is engaged and disengaged with the second set of teeth, respectively. The motor sub-assembly includes a holder device that holds the shuttle in the first position and a locking device that continuously prevents the shuttle from rotating relative to the casing.
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
CENTRALE LILLE INSTITUT (France)
ECOLE NATIONALE SUPERIEURE DE CHIMIE DE LILLE (France)
UNIVERSITE DE LILLE (France)
Inventor
Rousseau, Guillaume
Alousque, Fanny
Abstract
The invention relates to a method for protection against oxidation of a composite material part comprising carbon, said method comprising: - impregnating an internal porosity of the part with an impregnation composition comprising, as percentages by weight: (i) between 1% and 60% of colloidal silica; (ii) between 0.5% and 20% of a flux precursor comprising at least one nitrate of an alkali metal M1; (iii) between 0.5% and 20% of a lattice modifying precursor, comprising at least one nitrate or one oxynitrate of an element M2 which is chosen from metals or lanthanides; and (iv) between 20% and 88% of water; and - carrying out a vitrification heat treatment on the part impregnated with the impregnation composition so as to obtain a glass for protection against oxidation comprising at least silica, an oxide of M1 and an oxide of M2.
A method for adjusting the angular position of a wheel, in particular a wheel of a landing gear on an aircraft. The wheel being connected to at least one hydraulic cylinder controlled by a servo valve. The method comprising a step for determining an angular deviation between a measurement of the angular position and a setpoint angular position, a first proportional correction step, a second integral correction step and a step for adding the first current and the second current in order to determine a control current of the servo valve. The second integral control step comprising a sub-step for limiting the second current according to a parametric law imposing a second current of zero value when the angular deviation is less, in absolute value, than a first determined threshold.
An aircraft undercarriage comprising: a leg connected to an aircraft structure to be movable between a deployed position and a retracted position; a brace member for holding the leg in its deployed position and comprising a first rod hinged to the aircraft structure and a second rod hinged to the first link and to the leg; a stabilizer member for holding the first and second rods in an aligned position and comprising a first link and a second link that are hinged to each other, with at least one of them being hinged to the brace member; and a spring for elastically urging the hinges of the first and second links into a generally aligned position.
The spring comprises at least one spring blade arranged to be subjected to an axial compression force when the first and second links leave the generally aligned position.
A method of monitoring aircraft tire operating parameters includes pairing of transmission modules with wheel positions of an aircraft to obtain a cartography associating emission modules with wheel positions, storing the obtained cartography, transmitting data including information identifying the emission module, and operating parameter values of tire operating parameters measured by a sensor, checking an existence of an association between the information identifying the emission module and a wheel position on a given aircraft in the cartography to ensure that the information received belongs to the given aircraft, and displaying the operating parameter values and the wheel on which the one operating parameter values have been measured.
The invention relates to a part (1) comprising: - an aluminum alloy body (10), - a first layer (12) that contains aluminum oxide and is arranged on the body (10), - an intermediate layer (14) containing chromium, and - a second layer (16) containing aluminum oxide, the intermediate layer (14) being arranged between the first layer (12) and the second layer (16).
The present invention relates to a fibrous preform (1) of a core part of a fibrous reinforcement for a part made of composite material, the preform having a slender shape along a longitudinal direction (X) and being formed by three-dimensional weaving of first threads, extending in the longitudinal direction, with second threads that are transverse to said first threads, the preform comprising two longitudinal ends (3a; 3b) intended for articulation with other parts, as well as a median area (ZM) located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a first volume ratio of first threads relative to second threads which is greater than unity, and each longitudinal end having a second volume ratio of first threads relative to second threads which is less than the first ratio and closer to unity than the first ratio.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
D03D 15/37 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the fibres or filaments with specific cross-section or surface shape
D03D 25/00 - Woven fabrics not otherwise provided for
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
F16C 7/02 - Constructions of connecting-rods with constant length
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
70.
METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PART INTENDED TO BE ARTICULATED TO OTHER PARTS
The invention relates to a method for manufacturing a fibre preform for a part, comprising: - weaving a first core texture of elongate shape extending in a longitudinal direction and comprising, in cross section, a central portion (10) having, on its opposite sides, two edges each comprising two unravelled fibrous portions (16a; 16b), - shaping the first texture which involves at least opening out the unravelled portions to form a positioning surface (30) defined by the portions thus opened out and by an interleaved portion, situated between these opened-out portions, which may be formed by a prolongation (18a) of the central portion, - positioning a second, belt, texture over the opened-out lateral portions and the interleaved fibrous portion, the second texture forming a loop around the shaped first texture so as to define empty spaces for articulation to other parts.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
71.
BISTABLE ELECTROMAGNETIC ACTUATOR AND AIRCRAFT BRAKE VALVE PROVIDED WITH SUCH AN ACTUATOR
The invention provides a bistable electromagnetic actuator comprising a yoke extending in part around a pivot axis of the actuator, an excitation coil supported by the yoke in order to generate control magnetic flux, a rotor movable about the pivot axis of the actuator and suitable for being held stationary in two stable angular positions as a function of the magnetic flux generated by the coil, an actuator member coupled to the rotor in order to form an assembly that can be turned, and a manual control device including a drive shaft dynamically coupled to the rotor in such a manner that turning the drive shaft causes the rotor to turn.
The present invention relates to a fibrous preform of a core part of a fibrous reinforcement for a part made of composite material, the preform having a slender shape along a longitudinal direction (X) and being formed by first threads (C1-C16) extending in the longitudinal direction, with second threads (t1-t8) transverse to the first threads, the preform comprising two longitudinal ends intended for articulation with other parts, as well as a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a stiffening portion (102c) comprising non-woven first threads (C5-C12), and each longitudinal end comprising a three-dimensional weaving of the first threads of this stiffening portion with second threads.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
D03D 15/37 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the fibres or filaments with specific cross-section or surface shape
D03D 25/00 - Woven fabrics not otherwise provided for
F16C 7/02 - Constructions of connecting-rods with constant length
B29B 11/14 - Making preforms characterised by structure or composition
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
ABSTRACT The invention relates to an electric motor (1) comprising a casing (10) inside which are mounted at least one stator (30a, 30b) and a rotor (20) which can rotate about an axis (X) facing the stator, the rotor having magnetic poles and the stator comprising a ferromagnetic yoke (31) bearing windings (33) which are arranged so as to produce, with the magnetic poles of the rotor, an axial-flux electric motor. According to the invention, the stator is immobilized with respect to the casing by means of a fastening device (40a, 40b) which comprises studs (41.1, 41.2) projecting radially from a surface (42.1, 42.2) of the yoke, and at least one fastening element (42) fastened to the casing and designed to cooperate with the studs so as to block the stator along and around the axis (X). FIGURE 6A
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 21/24 - Synchronous motors having permanent magnets; Synchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
74.
MEANS FOR RECEIVING POWDER IN AN ADDITIVE MANUFACTURING MACHINE
An additive manufacturing machine includes a system for receiving powder, including four sides: a right-hand partition and a left-hand partition, a front partition and a rear partition, wherein at least two opposite sides each includes two hinged portions allowing the folding of the sides. The system is foldable and can be easily placed in the melt chamber without interfering with the manufacturing process; it can therefore be placed in the chamber before manufacturing.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
75.
DISTRIBUTED BRAKING ARCHITECTURE WITH IMPROVED SAFETY
A wheel-braking system architecture for an aircraft is provided. The architecture includes a friction brake; an electromechanical actuator associated with a power module connected to a digital communication module by a first driver module; and a controller having both a power supply unit for powering the power module by delivering a power supply voltage (Vc) thereto, and also a control unit connected to the digital communication unit in order to transmit a digital control signal to the digital communication module. The control unit can be connected to the driver unit by an analog wired connection in order to transmit that to a first analog braking order from which the first driver module drives the power module to produce a degraded power supply current for the actuator.
B60T 8/88 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
B60T 8/92 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means automatically taking corrective action
A system for real-time control of the trajectory of an aircraft on a runway, includes at least one steering system configured to steer the aircraft on the ground, each steering system being associated with at least one use parameter; a computer configured for determining, from aircraft data and external data including runway condition data and ground meteorological data, each steering system intended to steer the aircraft according to a predetermined trajectory and each corresponding use parameter; and a control system configured to control each steering system determined according to each corresponding determined use parameter.
The invention relates to an aircraft wheel comprising a first annular half-rim (101), a first hub (102) coaxial with the first half-rim (101) and a first wheel centre disc (103) connecting the first hub to the first half-rim, the first half-rim comprising a first flange (101.2) projecting radially outwards to engage with a tyre (400). The wheel comprises a sleeve (105) made in a single piece with the first half-rim, the first wheel centre disc and the first hub so as to form a first one-piece half-wheel (100). The sleeve: extends coaxially with respect to the first half-rim; has an external surface (105ext) extending some distance from an internal surface (101int) of the first half-rim; has an end (105.2) projecting axially from the first half-rim away from the first wheel centre disc; is internally provided with internal splines (107) intended to secure in terms of rotation the wheel to at least one brake rotor disc (501), these being housed between the sleeve and the first hub.
The invention relates to a tachometer (10) for an aircraft wheel (R) mounted on an axle (E) so as to rotate about an axis (X) of rotation, the tachometer comprising a stator (20) that is intended to be attached to the axle (E) and a rotor (30) that is intended to rotate with the wheel. According to the invention, one of the stator or the rotor comprises at least one contactless sensor (23) having at least two measurement cells (28.1, 28.2) suitable for co-operating with a plurality of targets (37) carried by the other of the stator or the rotor in order to generate two signals (S1, S2) that are representative of a speed of rotation of the wheel, the measurement cells being angularly offset from one another about the axis (X) so as to detect a direction of rotation of the wheel by combining the two signals.
G01P 3/44 - Devices characterised by the use of electric or magnetic means for measuring angular speed
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
G01P 3/487 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
G01P 13/04 - Indicating positive or negative direction of a linear movement or clockwise or anti-clockwise direction of a rotational movement
A locking device locks a landing gear mounted in rotation on an aircraft and includes a deployment hydraulic jack including a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device includes a hydraulic actuator connected to a rotary distributor. The rotary distributor includes a coupling operationally connecting the rotary distributor to a strut of the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.
One aspect of the invention relates to a method for manufacturing a part (1) comprising a metal substrate (Sub) at least partially covered with a finished protective layer (Rf), the method including the following steps: a first step (A) of preparing an initial surface to produce a rough surface, without sandblasting, comprising a sub-step of shot-blasting an initial surface of the substrate to obtain a roughness of the rough surface having an overall height of the roughness profile of the surface Rt of between 10 µm and 15 µm and a sub-step of cleaning the rough surface (Sub); a second step (B) of forming, by spraying a powder mixture containing submicron metal carbide grains according to a HVOF thermal spraying method, on the cleaned rough surface (S2), a rough coating layer (Rb), to a thickness of between 95 μm and 120 μm; and a third finishing step (D) by polishing the surface of said rough coating layer (S2) formed from the powder mixture so as to form the finished protective layer (Rf) having a thickness of between 75 μm and 100 μm, thus forming a polished surface (S3) having a roughness of less than 0.2 μm.
A maglev system includes a maglev vehicle that reciprocates between a levitated state and a non-levitated state. The vehicle includes a capsule supported by a first left wheel and a corresponding first right wheel when the vehicle is in the non-levitated state. The system further includes a track having a left rail and a right rail, each of the left and right rails having a plurality of plates arranged in series. Proximate ends of adjacent plates define a joint. Each rail provides a support surface that the first left and right wheels rollingly engage when the vehicle is in the non-levitated state. The joints of the left rail are offset in a longitudinal direction from the joints of the right rail.
The invention relates to a landing gear (P) for an aircraft comprising an axle (E) carried by a strut (T), said axle being provided with a rotatably-mounted wheel (RM) and a drive device (1, 1') for rotating the wheel (RM), the drive device comprising a motor (11) mounted at one end of the axle for transmitting a rotational torque to the wheel and a body (20, 20') projecting out of the motor and snugly received in the axle, at least a first harness (22) extending along the body and connecting the motor to a first coupler (21, 21') carried by a free end of the body in order to co-operate with a second coupler (30, 30') of the landing gear so as to supply the motor with power, characterised in that the second coupler is received in an opening (E2) formed in the axle at the junction between the strut and the axle.
A heat shield assembly for a braked aircraft wheel is provided. The heat sheild assembly includes a heat shield and at least one spacer having both a main body projecting from an outwardly-facing surface of the heat shield and a clamping element of generally cylindrical shape projecting from the body and passing perpendicularly through an opening in the heat shield. The clamping element can include an enlarged free end so as to co-operate with the body to form an annular groove engaged with the opening in the heat shield.
A drive system includes a motor having a rotatable output shaft that is operably coupled to a lead screw by a transmission that converts rotary output of the motor into linear translation of the lead screw. The drive system further includes a position sensor configured to sense a position of the lead screw. A method for determining a backlash of the drive system includes the steps of sensing an initial position and driving the lead screw in a first direction to a calculated second position by controlling the motor to rotate the output shaft an amount that corresponds to a distance between the initial position and the calculated second position. The method further includes the steps of sensing an actual second position of the lead screw; and determining a backlash value according to a difference between the calculated second position and the actual second position.
The invention relates to a taxiing device for a vehicle, comprising a wheel rim pivoting about a shaft and delimiting two recesses (107.1, 107.2), one receiving a friction braking device and the other a magnetic braking device comprising a stator (6) rotatably secured to the shaft, a rotor (5) rotatably secured to the wheel, and a control member (9) of the magnetic braking device extending at least partially into the shaft. The invention also relates to an aircraft comprising such a taxiing device.
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
86.
TAXIING DEVICE WITH COMBINED RADIAL AND AXIAL MAGNETIC FLUX BRAKING, AND AIRCRAFT EQUIPPED WITH SAME
The invention relates to a taxiing device for a vehicle, comprising a wheel provided with a magnetic eddy current braking device comprising a stator (20) and a rotor (10) having two pairs of facing surfaces (14, 31', 16.1, 32'), and two pluralities of magnets for generating an axial magnetic flux and a radial magnetic flux through said pairs of surfaces. The invention also relates to an aircraft comprising such a taxiing device.
F16D 55/00 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes
F16D 61/00 - Brakes with means for making the energy absorbed available for use
B60T 8/00 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
87.
VARIABLE-LENGTH LANDING GEAR AND AIRCRAFT EQUIPPED WITH SUCH A LANDING GEAR
The invention relates to a landing gear (10) comprising a supporting structure (11, 12, 13), and a damping cylinder (15) connected to a lever (17) which is hinged to the supporting structure about a hinge axis (A3) between an end position, in which the wheel is moved towards the hinge axis, and an end position, in which the wheel is moved away from the hinge axis, the end positions being on either side of an intermediate position, in which the lever and the cylinder are aligned, and the end away position being defined by a stop (21) which is secured to the supporting structure and against which the lever in the away position is applied to take up the landing forces. The invention also relates to an aircraft comprising at least one such landing gear.
The invention relates to a method for the densification, through gas-phase chemical infiltration, of porous annular substrates (21) having a central passage (21a), the method involving at least the following steps: providing stacks (20) of porous annular substrates (21), providing a plurality of individual modules (30) comprising stacks (20) placed on a support plate (31) comprising perforated injection tubes (33) each one mounted on a gas inlet opening (32), forming a pile of individual modules (30), aligning the individual modules (30) of the pile in a sealed manner using an annular seal (35) placed between the injection tubes (33) of the second individual module (30b) and the gas inlet openings (32) of a first individual module (30a) with which it collaborates, and injecting into the internal volume (24) of each stack (20) of porous annular substrates (21) a gas phase containing a gaseous precursor of a matrix material that is to be deposited within the porosity of the substrates (21).
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
The invention relates to a gantry crane (30) and to the associated method of erection, the gantry crane (30) comprising: - a frame (40) comprising at least three first members (32); - a longitudinal rail (50) supported by the frame (40); and - at least three second members (34) extending between opposite first end (34a) and second end (34b) portions, each second member (34) being connected to the frame (40) by means (48) of rigid connection of the second member to the frame and of continuous rotational movement of the second member relative to the frame between a first position in which the second member (34) makes an angle of less than 90° with the first plane (XY) and a second position in which the second member (34) is substantially perpendicular to said first plane (XY).
The invention relates to a method for the densification, by chemical vapour infiltration, of porous annular substrates (21) having a central passage (21a), the method comprising at least the following steps: providing stacks (20) of porous annular substrates (21); providing a plurality of individual modules (30) comprising stacks (20) placed on a support plate (31) comprising a perforated injection tube (33) each one mounted on a gas inlet opening (32); forming a stack of individual modules (30), aligning the individual modules (30) of the stack in a fluidtight manner using an annular seal (35) positioned between the injection tube (33) of a second individual module (30b) and the gas inlet opening (32) of a first individual module (30a) with which it collaborates, and injecting, into the internal volume (24) of each stack (20) of porous annular substrates (21), a gas phase comprising a gas precursor of a matrix material that is to be deposited within the porosities of the substrates (21).
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
mm) lower than full pressure (Ps), and subsequently equal to full pressure; • b) determining a time of deactivation of the uplock and comparing it with the time when the predetermined time period ends; • c) deducing therefrom a state of deterioration of the uplock. The present invention also relates to a hydraulic circuit for supplying a cylinder and thereby enabling such a method to be implemented.
F15B 13/042 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F15B 20/00 - Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
92.
STRUT FOR AIRCRAFT LANDING GEAR EQUIPPED WITH AN ACCUMULATOR, LANDING GEAR COMPRISING SUCH A STRUT, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH LANDING GEAR
Strut for aircraft landing gear, comprising a casing arranged to take up landing forces and provided with a cavity in which an energy accumulator is housed. Aircraft landing gear comprising such a strut. Aircraft comprising at least one such landing gear. Method for emergency deployment of such a landing gear, using the accumulator integrated in the strut of the landing gear.
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F15B 13/042 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure
F16K 3/24 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with sealing faces shaped as surfaces of solids of revolution with cylindrical valve members
B64C 25/28 - Control or locking systems therefor with indicating or warning devices
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
94.
DEVICE FOR DISCONNECTING AND BRAKING A ROTOR OF AN ELECTRICAL MACHINE
This device for disconnecting and braking a rotor of an electric machine comprises an inner axis driven in rotation by the rotor and longitudinally movable between an engagement position and a disconnection position, the disconnection and braking device further comprising a longitudinally fixed nut and a means for braking the rotation of the nut so that braking of the rotation of the nut urges the inner axis into its disconnection position and brakes the rotation of the rotor.
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
A landing gear of an aircraft includes a pair of wheels between which an electric actuator at least partially covered with a lightning arrester cowl is placed. The lightning arrester cowl has an insulating matrix onto which at least an electrical conductor is attached. The electrical conductor includes electrical connection means for connecting the electrical conductor to a ground conductor of the aircraft.
A landing gear of an aircraft having an upper portion intended to be joined to a structure of the aircraft and a lower portion provided with a first and second axle, the first axle being provided with a braked wheel and the second axle being provided with a motorised wheel, includes a first actuator that moves one of the axles between remote and close positions with respect to the upper portion while the other axle is kept stationary with respect to the upper portion. In one of the remote and close positions, and the wheels on the axles are simultaneously in contact with a running surface while, in the other position, each wheel on the second axle is at a distance from said running surface.
A braking system architecture for aircraft, the architecture comprising:
a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module;
at least one power supply unit (21, 22);
two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and
a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
B60T 17/22 - Devices for monitoring or checking brake systems; Signal devices
An aircraft landing gear includes: a strut assembly hinged by its upper end to a structure element of the aircraft to pivot between deployed and retracted states; an interlocking system having a stay including an arm hinged to the strut assembly via a lifting pin carried by two lugs of a clevis of the strut assembly, this arm being terminated by a head through which the pin passes and which is located between the lugs; and a lifting jack having one end connected to a first end of the pin which is located outside the clevis, a first end stop carried by the pin at its first end beyond the jack, and a second end stop carried by the pin at its second end. The landing gear includes a system for translationally locking the lifting pin in the event of the pin breaking between its first end and the clevis.
An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element.
An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element.
First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.
The invention relates to a hydraulic assembly (450) for an aircraft engine, the assembly comprising: - a pump (54) comprising a housing (54a) and a rotor (54b) arranged inside the housing (54a), the housing (54a) having at least one hydraulic line (540) for the passage of a fluid; and - a hydraulic transfer unit (56) comprising: a hydraulic transfer block (56a) attached to the housing (54a) and comprising an internal fluid passage channel (67, 68) which communicates with the hydraulic line (540), and a casing (56b) which covers the transfer block (56a) and which is guided in rotation about an axis of revolution (Y) and about the transfer block (56a), the casing (56b) having a fluid outlet port (75, 76) that communicates with the internal channel (67, 68).
