The invention relates to a rotor assembly having a shaft along an axis of rotation, a base projecting radially from the shaft, and a ring projecting radially from the base and having two main faces, at least one of which comprises locations accommodating permanent magnets, the base projecting axially relative to the ring, characterised in that the ring is arranged inside a winding of at least one elongate and flexible reinforcing element in order to hold the permanent magnets in place in the locations; and in which method the reinforcing element comprises fibres and the fibres are wound around the rotor assembly with an orientation having an angle close to 0° with the first axis of rotation, thereby covering the two main faces and the outer periphery.
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
H02K 1/28 - Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
H02K 1/2795 - Rotors axially facing stators the rotor consisting of two or more circumferentially positioned magnets
2.
AIRCRAFT BRAKING DEVICE HAVING A SENSOR FOR MEASURING THE BRAKING TORQUE OF SAID DEVICE
The invention relates to a device for braking an aircraft wheel (101), comprising at least one stack (8) of at least one rotor disc (8.1) and one stator disc (8.2), an actuator-carrying housing (2), at least one actuator (13) mounted in the actuator-carrying housing (2) in order to exert a pressing force on the stack of discs (8), the actuator-carrying housing (2) comprising a connecting portion (2.1) for connecting to the landing gear and a receiving portion (2.2) for receiving the actuator. The device comprises a braking force sensor comprising: a body (1.1) having a first end (1.1.1) mechanically attached to the connecting portion (2.1) and a second end (1.1.2) mechanically attached to the receiving portion (2.2), the body being designed to have a state representing a distance between its two ends, and a detection component close to the body (1.1) for measuring a variation in the state of the body (1.1).
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
F16D 66/00 - Arrangements for monitoring working conditions of brakes, e.g. wear or temperature
G01L 3/22 - Rotary-absorption dynamometers, e.g. of brake type electrically or magnetically actuated
G01L 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
G01L 5/28 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for testing brakes
The invention relates to an assembly having a wheel and a shaft carrying the wheel, the assembly further comprising a locking device (1) that comprises a male member (3) and a female member (2), wherein one from among the male member and the female member is connected to the wheel and the other from among the male member and the female member is connected to the shaft, and wherein the female member further comprises: • - a housing (4) extending along a given axis so as to have two ends, one of which is open; • - a positioning grid (21) arranged in the housing; • - and a plurality of pins extending into the housing through one of the holes in the positioning grid, wherein the male member comprises at least one finger capable of bearing on at least one of the pins of the female member. The invention further relates to an associated vehicle.
F16D 59/02 - Self-acting brakes, e.g. coming into operation at a predetermined speed spring-loaded and adapted to be released by mechanical, fluid, or electromagnetic means
The invention relates to a fibrous assembly (200) intended to form the reinforcement of a part (100) made of composite material, the fibrous assembly (200) comprising a fibrous core preform (210) produced by three-dimensional weaving, at least one opening (231) which is adjacent to the fibrous core preform (210) and is intended to be passed through by a shaft in order to produce a connection, and a fibrous belt preform (220) surrounding the fibrous core preform (210) and said at least one opening (231), the fibrous core preform (210) comprising a central portion (211) in which the warp threads (211c) or weft threads have a first shrinkage and at least one flexible portion (212), present between the fibrous belt preform (220) and the central portion (211) and extending from the opening (231), in which the warp threads (212c) or weft threads have a second shrinkage which is greater than the first shrinkage.
The invention relates to a core fibrous bundle (100) intended to form the fibrous reinforcement of a core (11) of a part (10) made of composite material comprising a first body (110) and a second body (120), the core fibrous bundle (100) being characterized in that it further comprises at least a first connecting flange (111) extending from the first body (110) and a second connecting flange (122) extending from the second body (120), the end portion (111e) of the first connecting flange (111) and the end portion (122e) of the second connecting flange (122) overlapping so as to form an upper connecting portion (100a) connecting the upper ends (110a, 120a) of the two bodies (110, 120), the lower ends (110b, 120b) of the two bodies (110, 120) being connected by a lower connecting portion (100b).
The invention relates to a retractable landing gear (1) for aircraft, comprising: a main part (3) for connecting the landing gear to the aircraft, which part is arranged to pivot about a first main rotation axis (X1) substantially parallel to a longitudinal direction of the aircraft; a leg having one end provided with a wheel (2) and opposite same a strut assembly (4) having a top portion (4.1) connected to the main connecting part in order to pivot about a second main rotation axis (X2) substantially perpendicular to the first main rotation axis; a mechanism for moving/stabilising the leg in order to move the leg between a deployed position and a retracted position by a simultaneous rotation of the leg about the main rotation axes, the movement/stabilisation mechanism comprising a strut (7) for bracing the leg in the deployed position and a guide rod (10) for guiding the rotation of the leg about the main axes of rotation.
The present invention relates to a part (1) based on aluminum or on an aluminum alloy, comprising - a body (10) made of aluminum or of an aluminum alloy, - an inner layer (12) comprising aluminum oxide placed on the body (10), - an intermediate layer (14) comprising chromium and zirconium, and - an outer layer (16) comprising an organosilicate, the intermediate layer (14) being placed between the inner layer (12) and the outer layer (16). The invention also relates to a method for post-anodization sealing of a body (10) made of aluminum or of an aluminum alloy.
The invention relates to a landing gear (1) comprising: - a strut (2) arranged so as to be mounted movably on a structure (3) between a deployed position and a retracted position; - at least one bracing member (4) for holding the strut in the deployed position, comprising a first link rod (4a) articulated to the structure and a second link rod (4b) articulated to the first link rod and to the strut; - a stabilizing member (6) for holding the first and second link rods (4a, 4b) in an aligned position, and comprising a first link (6a) and a second link (6b) which are articulated to each other, and of which the second link is articulated to the first link rod; and - at least one leaf spring (11) and a rocker (12) for elastically returning the articulations of the first link and of the second link to a substantially aligned position.
The present invention relates to a tool (100) for winding a fibre structure around a winding support (120), the tool being configured to reduce wrinkling in the structure obtained after compaction. The tool is specially adapted for winding a structure of large size and significant weight, and comprises in particular a connecting bar for connection to a winding machine, and a frame secured to the winding support in order to provide rigidity.
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29C 53/56 - Winding and joining, e.g. winding spirally
10.
WEDGE FOR FIXING A BAR FOR A BRAKED AIRCRAFT WHEEL
The invention relates to a braked aircraft wheel (103) comprising: - a rim (104) having an inner periphery delimiting a space for receiving brake rotor discs (107b); - at least one bar (10) attached to the rim by means of a screw (31) for rotatably connecting the brake rotor discs to the rim, the screw extending in a radial direction (Y) with respect to the rim in a first bore (104.2) provided in the rim and in a second bore (12) provided in the bar; and - a wedge (20, 20', 20'') interposed between the rim and the bar and traversed by the screw, characterized in that a portion of the wedge is received with a fit in a first counterbore (104.3) provided at an inlet of the first bore (104.2) of the rim and/or in a second counterbore provided at an outlet of the second bore of the bar.
The invention relates to a magnetic braking device comprising at least one stator (2) and at least one rotor (3), and electromagnets (5) rigidly connected to the rotor and/or the stator so as to produce therebetween, when the rotor rotates, at least one magnetic field capable of generating eddy currents braking the rotor. According to the invention, the device comprises at least one control unit (7) capable of controlling an AC power supply of at least some of the electromagnets such that the magnetic field is a rotating magnetic field, the control unit being configured to adapt a rotational speed of the magnetic field as a function of at least one data item characteristic of the rotational speed of the rotor (1) by determining at least one of the power supply parameters of at least one of the electromagnets.
H02P 3/18 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an AC motor
A wheel for an aircraft including a first annular half-rim, a first hub coaxial with the first half-rim, and a first disc connecting the first hub to the first half-rim, the first half-rim including a first radially outwardly projecting collar for interacting with a tire. The wheel includes a sleeve formed as a single piece with the first half-rim, the first disc and the first hub to form a first one-piece first half-wheel, and the sleeve extends coaxially with the first half-rim, has an outer surface extending at a distance from an inner surface of the first half-rim, has an end projecting axially from the first half-rim on the opposite side to the first disc, and is provided internally with internal ribs intended for rotatably connecting the wheel to at least one brake rotor disc housed between the sleeve and the first hub.
A tachometer for an aircraft wheel is mounted on an axle so as to rotate about an axis of rotation. The tachometer includes a stator intended configured to be secured to the axle and a rotor configured to be rotatably connected to the wheel. Either the stator or the rotor has at least one contactless sensor with at least two measurement cells adapted to interact with a plurality of targets borne by the other of the stator or the rotor in order to generate two signals representative of a rotational speed of the wheel. The measurement cells are angularly offset from one another about the axis so as to detect a direction of rotation of the wheel by combining the two signals.
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
14.
METHOD FOR REPAIRING PARTS COMPRISING A HOLE, WHEREIN THE SURFACE BORDERING THE HOLE IS DAMAGED
The method comprises the following successive steps: - machining the part (1) to be repaired in order to remove a thickness of damaged material (5) and form a recess (6), the bottom (8) of which opens into the hole (2); - inserting a sealing element (9) into the hole (2) such that its outer face (10) is flush with the bottom of the recess (6) and at least partially seals the hole (2); - depositing a repair material (7) in the recess (6) and on the outer face (10) of the sealing element (9), with an excess thickness of repair material (7) extending beyond the nominal dimensions of the surface (3) and the hole (2); and - removing the sealing element (9) and machining the part (1) to be repaired so that the surface (3) and the hole (2) are restored to their nominal dimensions.
The invention relates to a method for manufacturing a fibrous reinforcement of a composite brake disc, which comprises: - producing (E10) fibrous portions (11), each intended to define a friction face (F1) separate from the brake disc, using a custom fibre placement technique in which, for each of the portions, carbon or carbon precursor fibres are deposited on a substrate and stitched thereto by a sewing thread made of carbon or polymeric material; - positioning (E20) an intermediate fibrous portion (13), intended to define a non-friction area of the brake disc, between the portions; and - joining (E30) the intermediate fibrous portion (13) to the fibrous portions (11).
D04H 3/105 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between yarns or filaments made mechanically by needling
D04H 1/40 - Non-woven fabrics formed wholly or mainly of staple fibres or like relatively short fibres from fleeces or layers composed of fibres without existing or potential cohesive properties
16.
RHEOSTATIC SAFETY BRAKING FOR MOTORIZED ELECTRICAL SYSTEMS
Disclosed is a safety braking device (10) for a motorized electrical system, comprising: a polyphase motor (11) comprising a frame (12) forming a stator and a rotor (13) mounted in the frame (12) to pivot about an axis of rotation; at least one dissipative circuit (14) per phase of the motor comprising a plurality of braking resistors (15) and a plurality of activation switches (16) for activating the braking resistors; a plurality of connection switches (17) each connecting one of the dissipative circuits (14) to one of the phases of the motor and a control unit (30) connected to the switches in order to control them; the braking resistors (15) being arranged on the frame (12) and the activation switches (16) and the connection switches (17) being grouped together in an electrical box (18) fixed to the frame (12). A motorized electrical system (1) comprising such a device (10).
H02P 3/22 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an AC motor by short-circuit or resistive braking
A method for manufacturing a part includes a metal substrate at least partially covered with a finished protective layer, the method including preparing an initial surface to produce a rough surface, without sandblasting, the preparing including shot-blasting an initial surface of the substrate to obtain a roughness having an overall height Rt of between 10 μm and 15 μm and cleaning the rough surface; forming, by spraying a powder mixture containing submicron metal carbide grains according to a HVOF thermal spraying method, on the cleaned rough surface, a rough coating layer, to a thickness of between 95 μm and 120 μm; and polishing the surface of the rough coating layer formed from the powder mixture so as to form the finished protective layer having a thickness of between 75 μm and 100 μm, thus forming a polished surface having a roughness of less than 0.2 μm.
A method for manufacturing a fiber preform for a part, includes weaving a first core texture of elongate shape extending in a longitudinal direction and comprising, in cross section, a central portion having, on its opposite sides, two edges each including two non-interlinked fibrous portions, shaping the first texture which involves at least opening out the non-interlinked portions to form a positioning surface defined by the portions thus opened out and by an interleaved portion, situated between these opened-out portions, which can be formed by a prolongation of the central portion, and 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 to define empty spaces for articulation to other parts.
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 70/22 - 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
A fibrous preform of a core portion of a fibrous reinforcement for a composite material part, the preform having an elongated shape along a longitudinal direction and being formed by first yarns extending along the longitudinal direction with second yarns transverse to the first yarns, the preform including two longitudinal ends intended for articulation with other parts and 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 including a stiffening segment including first non-woven yarns and each longitudinal end including a three-dimensional weave of the first yarns of this stiffening segment with second yarns.
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]
B29K 63/00 - Use of epoxy resins as moulding material
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
A landing gear for an aircraft having an automated kinematic-based oil pump system is provided. The landing gear includes an oleo strut having an upper strut housing, a piston slidingly received in the upper strut housing, a lower housing, a bogie truck beam pivotably coupled to the lower housing at a bogie pivot joint, and an automated lubrication system. This system can include a lubrication piston, and a lubrication outer cylinder operably coupled to the lower housing by a shaft and having an internal chamber for retaining lubricant therein and being fluidly coupled to a grease fitting of the bogie pivot joint by an oil passageway. Relative movement of the upper strut housing toward the lower housing causes the lubrication piston to travel axially within the lubrication outer cylinder and thereby pump lubricant from the internal chamber to the grease fitting of the bogie pivot joint through the oil passageway.
22333'), the main body including a first supply port (14.1) and a second supply port (14.2) opening into the first chamber and the second chamber, respectively; and the secondary body including a third supply port (26) opening into the third chamber.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
22.
METHOD FOR PROTECTION AGAINST OXIDATION OF A COMPOSITE MATERIAL PART COMPRISING CARBON
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
A method for protection against oxidation of a composite material part includes carbon, the method including impregnating an internal porosity of the part with an impregnation composition including, as percentages by weight: (i) between 1% and 60% of colloidal silica; (ii) between 0.5% and 20% of a flux precursor including at least one nitrate of an alkali metal Ml; (iii) between 0.5% and 20% of a lattice modifying precursor, including 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 including at least silica, an oxide of M1 and an oxide of M2.
C03B 32/00 - Thermal after-treatment of glass products not provided for in groups , e.g. crystallisation, eliminating gas inclusions or other impurities
C03C 3/078 - Glass compositions containing silica with 40% to 90% silica by weight containing an oxide of a divalent metal, e.g. an oxide of zinc
C03C 3/097 - Glass compositions containing silica with 40% to 90% silica by weight containing phosphorus, niobium or tantalum
23.
THERMAL OXIDATION PROTECTION LAYER FOR A COMPOSITE MATERIAL PART COMPRISING CARBON
104622 in which M represents a divalent cation selected from among Ca2+, Sr2+, Ba2+, Na2+, Pb2+, Mg2+, Zn2+, Mn2+, Be2+, Co2+, Fe2+, Ni2+and Cu2+44 represents a trivalent ionic group where X is selected from among P, Si, As and V and Y represents a monovalent anion selected from among Cl-, Br-, I- and OH- to protect a carbon-containing composite material part against thermal oxidation. The invention further relates to a part intended for the aeronautical or aerospace sector, made of a carbon-containing composite material and comprising the thermal oxidation protection layer, as well as to a method for manufacturing the part.
A landing gear for an aircraft having an axle carried by a strut, the axle including a rotatably-mounted wheel and a drive device for rotating the wheel about a rotation axis. The drive device can have a motor mounted at one end of the axle for transmitting a rotational torque to the wheel, a body projecting out of the motor and snugly received in the axle, and at least a first harness extending along the body and connecting the motor to at least a first coupler carried by a free end of the body to cooperate with a second coupler of the landing gear to supply the motor with power. The second coupler received in an opening formed in the axle at the junction between the strut and the axle, the opening extending along an axis perpendicular to the axis of rotation of the wheel.
A linear actuator (200) includes a cylinder (210) having a central cavity (212). A gland (260) is mounted to the cylinder and has an aperture (264) extending through the middle of the gland (260). The actuator further includes a piston (240) with a body (242) slidably disposed within the central cavity (212). A first seal (248) is mounted to an outer surface of the body (242) and sealingly engages the cylinder, and a first damping member (252) is mounted to the outer surface of the body (242) and engages the cylinder. The first seal (248) is made from a different material than the first damping member (252).
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
F15B 21/00 - Common features of fluid actuator systemsFluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
A linear actuator includes a cylinder having a central cavity A gland is mounted to the cylinder and has an aperture extending through the middle of the gland. The actuator further includes a piston with a body slidably disposed within the central cavity. A first seal is mounted to an outer surface of the body and sealingly engages the cylinder, and a first damping member is mounted to the outer surface of the body and engages the cylinder. The first seal is made from a different material than the first damping member.
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
F15B 21/00 - Common features of fluid actuator systemsFluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
27.
BRAKING SYSTEM FOR AN AIRCRAFT, THE SYSTEM BEING ACTUATED BY A CONTROL DEVICE AND COMPRISING AN ELECTRICALLY ACTUATED DEVICE
Fn1Fn2o/fp1p1'p22'p1p2p2) being configured to activate the progressive operating mode of the electrically actuated device (2, 2', 2E, 2I) according to the at least one inhibition system.
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/00 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems
28.
BRAKING SYSTEM FOR AN AIRCRAFT ACTUATED BY A PARKING BRAKE CONTROL MEMBER AND A PROGRESSIVE BRAKE CONTROL MEMBER AND COMPRISING AN ELECTRICALLY ACTUATED DEVICE
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/00 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems
29.
VARIABLE-LENGTH LANDING GEAR AND AIRCRAFT EQUIPPED WITH SUCH A LANDING GEAR
A landing gear includes a supporting structure, and a damping cylinder connected to a lever which is hinged to the supporting structure about a hinge axis. The lever is movable between a towards end position, in which the wheel is moved towards the hinge axis, and an away end position, in which the wheel is moved away from the hinge axis. The towards and away end positions are on either side of an intermediate position, in which the lever and the cylinder are aligned. The end away position is defined by a stop secured to the supporting structure and against which the lever in the away position is applied to take up the landing forces.
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
SAFRAN (France)
SAFRAN ELECTRONICS & DEFENSE (France)
SAFRAN LANDING SYSTEMS (France)
Inventor
Neba, Eric Carin
Abstract
A method and a system for determining the temperature in a mounted aircraft tyre is characterized in that it has two temperature sensors installed inside the tire.
The invention relates to a device (100) for activating an emergency function for the deployment of the landing gear of an aircraft, wherein the device comprises: an electric motor; a screw (120) configured to be translated by the electric motor between an extended position and a retracted position, and configured to disengage a holding element that keeps the landing gear in the closed position when it is in the extended position, and to secure the holding element that keeps the landing gear in the closed position when it is in the retracted position; two magnetic field sensors (151, 152); and a finger (160) that comprises a permanent magnet (165) at one of its ends, and which is capable of moving between the two magnetic field sensors, driven by the screw in such a way that the permanent magnet aligns with the magnetic field sensors.
o/fvv) which activates the progressive operating mode, at least one direction of the first movement between a return position of the control member (4) and a supply position being different from a direction of the second movement between the return position and the supply position.
B60T 8/17 - Using electrical or electronic regulation means to control braking
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
33.
BRAKING SYSTEM FOR AN AIRCRAFT COMPRISING AN ELECTRICALLY ACTUATED DEVICE CONTROLLED BY A FIRST AND A SECOND CONTROL MEMBER
o/fvv) that activates the progressive operating mode, and wherein the at least one first control member (4) is independent of the at least one second control member (5).
An electromagnet includes a cylindrical core and a bobbin. The bobbin has a first barrel portion delimited by a first flange and a second flange. The bobbin further includes a second barrel portion delimited by the second flange and a third flange. A diameter of the first flange is greater than a diameter of the third flange. The bobbin also includes an aperture extending through the first and second barrel portions, wherein the core is disposed within the aperture. A wire is wrapped around the first barrel portion to define a first portion of a coil and around the second barrel portion to define a second portion of the coil. A power source provides current through the wire.
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 63/00 - Brakes not otherwise provided forBrakes combining more than one of the types of groups
H02K 49/04 - Dynamo-electric clutchesDynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type
35.
ELECTROMAGNET DESIGN FOR HIGH MAGNETIC FLUX APPLICATIONS
An electromagnet (200) includes a cylindrical core (204) and a bobbin (210). The bobbin (210) has a first barrel portion (212) delimited by a first flange (216) and a second flange (218), and a second barrel portion (214) delimited by the second flange (218) and a third flange (220). A diameter of the first flange (216) is greater than a diameter of the third flange (220). The bobbin (210) also includes an aperture (228) extending through the first and second barrel portions (212, 214), wherein the core (204) is disposed within the aperture (228). A wire (230) is wrapped around the first barrel portion (212) to define a first portion (234) of a coil (232) and around the second barrel portion (214) to define a second portion (236) of the coil (232). A power source provides current through the wire (230).
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 63/00 - Brakes not otherwise provided forBrakes combining more than one of the types of groups
H02K 49/04 - Dynamo-electric clutchesDynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type
36.
METHOD FOR DETECTING DAMAGE TO A PART MADE OF CONDUCTIVE MATERIAL
The invention relates to a method (300) for detecting damage (201) to a part (200) made of conductive material, the damage (201) being a burn or a crack, the part (200) being heated (310) by induction by injecting an energy pulse. The method comprises receiving (330) a temporal sequence of thermal images of the part after heating the part (200), and the temporal signal of the intensity of each pixel of the thermal image is used to construct (370) a phase image of the part by means of a discrete Fourier transformation of the temporal signal.
The invention relates to a method for diagnosing a state of health of an actuator of an electro-hydraulic valve (110A; 110B) of a first hydraulic control circuit (100A; 100B) of a parking brake system of an aircraft, which comprises: - determining a delay (Δt, Δt'), referred to as "actuation delay", between a determined instant following an activation or a deactivation of the valve (110A; 110B) and another instant of exceeding a given pressure threshold measured on a given pressure sensor (121A; 121B) downstream of the valve; - comparing the actuation delay (Δt, Δt') with a predetermined threshold value (Anomaly_threshold_A; Anomaly_threshold_B) referred to as "anomaly detection threshold".
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 17/22 - Devices for monitoring or checking brake systemsSignal devices
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
38.
HEAT SINK CONFIGURATIONS FOR EDDY CURRENT BRAKE APPLICATIONS
A heat sink configuration for an eddy current brake having a rotor (120) configured to be operably coupled to a wheel (102) of an aircraft is provided. The rotor (120) can include an annular central disc portion (126) and a plurality of heat sinks (122) arranged circumferentially around an outer radial edge. The plurality of heat sinks (122) can each have first and second detachable flanges on opposite axial sides of the heat sinks (122). The rotor (120) may further include grooves (124) arranged between two circumferentially adjacent heat sinks to receive a clamp (140) for operably coupling the brake rotor assembly (110) to the wheel (102) of the aircraft. An axial thickness of the annular central disc portion (126) can be less than an axial thickness of the plurality of heat sinks (122) to promote heat transfer from the annular central disc portion (126) into the plurality of heat sinks (122) during use.
A heat sink configuration for an eddy current brake having a rotor (120) configured to be operably coupled to a wheel (102) of an aircraft is provided. The rotor (120) can include an annular central disc portion (126) and a plurality of heat sinks (122) arranged circumferentially around an outer radial edge. The plurality of heat sinks (122) can each have first and second detachable flanges on opposite axial sides of the heat sinks (122). The rotor (120) may further include grooves (124) arranged between two circumferentially adjacent heat sinks to receive a clamp (140) for operably coupling the brake rotor assembly (110) to the wheel (102) of the aircraft. An axial thickness of the annular central disc portion (126) can be less than an axial thickness of the plurality of heat sinks (122) to promote heat transfer from the annular central disc portion (126) into the plurality of heat sinks (122) during use.
A rolling device for a vehicle includes a wheel having a hub to be mounted to pivot on a shaft and a rim including first annular portion delimiting a recess receiving an eddy current magnetic braking device including a stator constrained to rotate with the shaft, a rotor constrained to rotate with the wheel and provided with a first surface facing a first surface of the stator to form a first pair of surfaces, and first magnets for generating a first magnetic flux which passes through the first pair of surfaces. The rotor includes a second surface facing a second surface of the stator to form a second pair of surfaces and the magnetic braking device includes second magnets for generating a second magnetic flux which passes through the second pair of surfaces. The first magnetic flux is axial and the second magnetic flux is radial.
A vehicle wheel (1), rotatably mounted on an axle (E), comprising a wheel-braking device and a wheel-driving device, the braking device comprising a brake disk (11) constrained to rotate with the wheel and a brake caliper (14) straddling the disk in order to exert friction forces on the disk by means of a brake actuator mounted on the caliper, and the drive device comprising a gear motor (23) driving in rotation a pinion which is arranged to mesh with a ring gear (21) constrained to rotate with the disk.
B60T 1/06 - Arrangements of braking elements, i.e. of those parts where braking effect occurs acting by retarding wheels acting otherwise than on tread, e.g. employing rim, drum, disc, or transmission
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
F16D 65/18 - Actuating mechanisms for brakesMeans for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
A device (10) for driving at least one wheel (12) of an aircraft landing gear (14), this device (10) comprising: - at least one landing-gear wheel (12), this wheel (12) comprising a rim (16) having an axis of rotation (X), - an electric motor (20) comprising a shaft (30), - a system (22) for mechanical transmission between the shaft of the motor (20) and the rim (16), this mechanical transmission system (22) comprising a mechanical reduction gear (28) which has: - a movable ring gear (38) which rotates conjointly with the shaft of the motor (20), - a movable sun gear (32) which rotates conjointly with the rim (16), - a stationary sun gear (56) attached to a stator of the device (10), and - planet gears (34) which mesh with the ring gear and the sun gears.
The invention relates to a mechanical part (100) comprising a core (110) having a fibrous reinforcement densified by a matrix, comprising at least one opening adjacent to the core (110) through which a shaft is intended to pass in order to establish a connection with another part, and comprising a belt (120) having a fibrous reinforcement densified by the matrix surrounding the core (110) and the at least one opening. According to the invention, the part (100) is characterized in that at least one insert (140) extending from the opening is positioned between the core (110) and the belt (120).
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
44.
ROLLING DEVICE WITH MIXED FRICTION/MAGNETIC BRAKING, AND AIRCRAFT THUS EQUIPPED
A rolling device for a vehicle, having a wheel rim pivoting about a shaft and delimiting two recesses, one receiving a friction braking device and the other a magnetic braking device having a stator constrained to rotate with the shaft, a rotor constrained to rotate with the wheel, and a control member of the magnetic braking de-vice extending at least partially into the shaft. An aircraft having such a rolling device.
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
A method diagnoses a state of deterioration of an uplock having an unlocking actuator provided with a hydraulic cylinder. The method includes the step of supplying the cylinder with pressurized fluid with an evolution law according to which the pressure of the fluid is, for a predetermined period, equal to a predetermined pressure lower than a full pressure, then equal to the full pressure. The method further includes the steps of determining a time of deactivation of the uplock and comparing it with the time when the predetermined time period ends; and deducing therefrom a state of deterioration of the uplock.
B64C 25/28 - Control or locking systems therefor with indicating or warning devices
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F15B 20/00 - Safety arrangements for fluid actuator systemsApplications of safety devices in fluid actuator systemsEmergency measures for fluid actuator systems
A gantry crane and associated method of erection, the gantry including a frame having at least three first members; a longitudinal rail supported by the frame; and at least three second members extending between a first end portion and an opposite second end portion. Each second member can be connected to the frame by means for rigid connection and continuous rotational movement of the second member relative to the frame between a first position in which the second member forms an angle of less than 90° with the first plane and a second position in which the second member is substantially perpendicular to the first plane.
B66C 17/00 - Overhead travelling cranes comprising one or more substantially-horizontal girders the ends of which are directly supported by wheels or rollers running on tracks carried by spaced supports
B66C 23/78 - Supports, e.g. outriggers, for mobile cranes
47.
METHOD FOR SEALING ALUMINIUM ALLOYS USING A TUNGSTEN SALT AND ALUMINIUM-BASED OR ALUMINIUM ALLOY-BASED PART OBTAINED BY THIS METHOD
The present invention relates to a part (1) based on aluminium or an aluminium alloy, comprising a body (10) made of aluminium or of an aluminium alloy, an inner layer (12) comprising aluminium oxide placed on the body (10), an intermediate layer (14) comprising chromium and zirconium, and an outer layer (16) comprising tungsten oxide, the intermediate layer (14) being placed between the inner layer (12) and the outer layer (16). It also relates to a method for post-anodizing sealing of a body (10) made of aluminium or of an aluminium alloy.
The invention relates to a method for measuring the wear of the discs of an aircraft brake provided with a wear indicator (6) movably mounted on a fixed part of the aircraft brake and moving as the discs wear, the method comprising the steps of: - acquiring an image of a portion of the discs of the aircraft brake, - identifying the wear indicator (6) in the acquired image, - identifying at least three reference points (A1, B1, C2) on the wear indicator (6), and - determining at least one measurement of the wear of the discs of the aircraft brake by determining at least one dimension (L, W) associated with the wear indicator (6) from the three identified reference points (A1, B1, C2).
B60T 17/22 - Devices for monitoring or checking brake systemsSignal devices
B60T 17/00 - Component parts, details, or accessories of brake systems not covered by groups , or , or presenting other characteristic features
49.
Strut for aircraft landing gear equipped with an accumulator, landing gear comprising such a strut, and aircraft comprising at least one such landing gear
A strut for an aircraft landing gear is provided. The strut includes a casing configured to absorb landing forces applied to the aircraft landing gear. The casing includes a cavity in which an energy accumulator is housed. The energy accumulator can be a removable cartridge which can be inserted in the cavity. An aircraft landing gear comprising such a strut is also provided. An aircraft comprising at least one such landing gear having such a strut is also provided. A method for emergency deployment of such a landing gear, using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear is also provided.
PARKING ELECTROVALVE FOR AN AIRCRAFT BRAKING SYSTEM, ELECTRIC CIRCUIT FOR CONTROLLING A PARKING BRAKE AND BRAKING SYSTEM COMPRISING SUCH AN ELECTOVALVE
L1L1'L2L3L4.1L4.2L4.2) connected to the electromagnet, the logic switch being arranged to adopt a closed state or an open state according to a logic operation taking account of at least a signal representative of a critical state of progress of the aircraft that requires the slide-valve to be in the first stable position or the second stable position.
B60T 8/17 - Using electrical or electronic regulation means to control braking
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
51.
METHOD FOR LIMITING THE VIBRATIONS INDUCED BY BRAKES PROVIDED ON AIRCRAFT LANDING GEAR WHEELS
1.11.22.12.21.11.42.12.41.11.62.12.61212121.11.22.12.21.11.42.12.41.11.62.12.62.6'') of the brake discs of each of the two wheels; − determining, from the acquired temperatures, the wheel whose brake is the least likely to induce vibrations; − activating the brake that is the least likely to induce vibrations.
1.11.22.12.2 1.11.42.12.41.11.62.12.61212121.11.22.12.21.11.42.12.41.11.62.12.62.6'') of the brake discs of each of the two wheels; − determining the wheel whose brake has the lowest or highest temperature; − activating the brake having the lowest or highest temperature depending on the material from which the brake discs are made.
A landing gear system (5) for an aircraft (1), the landing gear system comprising a front landing gear (2) and at least one rear landing gear, the rear landing gear being of the bogie beam type and comprising at least two wheels, the landing gear system furthermore being equipped with a hybrid braking system comprising at least one friction brake and at least one auxiliary brake providing energy dissipation by means other than friction, at least one of the wheels of the rear landing gear being equipped solely with one or more auxiliary brakes and at least one of the wheels of the rear landing gear being equipped solely with one or more friction brakes, all the wheels of the rear landing gear being equipped with at least one auxiliary brake or with a friction brake. An aircraft equipped with such a landing gear system.
The invention relates to a method for controlling the braking of an aircraft comprising at least one control member (11) providing a value of at least one braking control parameter, and an eddy current magnetic braking device (1), the method comprising the steps of: acquiring the value of the braking control parameter and values of state parameters of the magnetic braking device (1), and determining a braking torque command and an air gap setpoint and/or a supply current setpoint from a model which is stored in the electronic processing unit (7) and which correlates values of the braking control parameter, values of the braking torque, values of the air gap and values of the supply current according to the state parameters of the magnetic braking device (1). The invention also relates to a magnetic braking device implementing this method.
A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tubes of a second individual module and the gas inlet openings of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.
C04B 35/52 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbon, e.g. graphite
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic warePreparation thereof
Disclosed is a vehicle wheel (1) rotatably mounted on an axle (E) and comprising: - an annular rim (2), a web (3) and a hub (4) delimiting a closed-off annular space, - an electric motor (10) comprising a first stator (11) and a first rotor (12) which are arranged coaxially to the wheel, and - a magnetic brake (20). The motor and the brake extend one inside the other within the annular space. Either the first rotor serves as a rotor for the brake (22), or the first stator (11) serves as a stator for the brake (21) in order to produce a second magnetic flux capable of inducing eddy currents that generate a braking torque. Either the first stator or the first rotor has a Halbach array formed at least in part by electromagnets.
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
57.
Chemical vapor infiltration densification method using single-pile plates for a semi-forced flow
A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tube of a second individual module and the gas inlet opening of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.
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 16/04 - 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 16/458 - 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
58.
WHEEL WITH MAGNETIC BRAKING DEVICE; AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a wheel comprising an eddy current magnetic braking device, the device comprising at least one stator and at least one rotor, and magnets secured to one of these in order to produce a magnetic flux therebetween that is capable of inducing 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 comprising such a wheel.
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 present invention relates to a method for manufacturing a fibrous preform (40, 240) of a core for a composite part intended to be articulated to other parts, comprising the formation of a strip (10, 110) in a single piece by three-dimensional weaving and the shaping thereof to give it a generally H-shaped cross-section.
The invention relates to an eddy current magnetic braking device (1) comprising two outer stators (2.1) surrounding a central stator (2.2) and two rotors (3) made of an electrically conductive material. Each outer stator has a surface facing a surface of one of the rotors and is provided with a plurality of permanent magnets (11, 13) having a magnetisation vector normal to the surface so as to emit, via the surface, a first magnetic flux capable of inducing eddy currents in the rotors. The central stator comprises electromagnets (21) that have a magnetisation vector parallel to those of the permanent magnets and that are connected to a controlled power source (22) to produce a second magnetic flux that either opposes the first magnetic flux or reinforces the first magnetic flux. The invention also relates to a vehicle wheel, an aircraft landing gear and an aircraft comprising such a device.
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
H02K 49/04 - Dynamo-electric clutchesDynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type
The invention relates to an industrial process for the heat treatment of preforms made of a carbon precursor material, the process comprising the following sequential steps: - introducing (S10) a load of preforms made of a carbon precursor material into a first sealed airlock that selectively communicates with a first furnace; - replacing (S20) the air present in the first sealed airlock with a neutral gas; - transferring (S30) the load into the first furnace; - performing a first carbonisation treatment (S40) in the first furnace; - transferring (S50) the load into a second sealed airlock that selectively communicates with the first and second furnaces; - evacuating (S60) the second sealed airlock; - transferring (S70) the load into the second furnace; - performing a second carbonisation treatment (S80) in the second furnace; - transferring (S80) the load into a third sealed airlock that selectively communicates with the second furnace and with an open air outlet.
C04B 35/626 - Preparing or treating the powders individually or as batches
D01F 9/14 - Carbon filamentsApparatus specially adapted for the manufacture thereof by decomposition of organic filaments
D01F 9/20 - Carbon filamentsApparatus specially adapted for the manufacture thereof by decomposition of organic filaments from polyaddition, polycondensation or polymerisation products
F27B 9/02 - Furnaces through which the charge is moved mechanically, e.g. of tunnel type Similar furnaces in which the charge moves by gravity of multiple-track typeFurnaces through which the charge is moved mechanically, e.g. of tunnel type Similar furnaces in which the charge moves by gravity of multiple-chamber typeCombinations of furnaces
F27B 9/04 - Furnaces through which the charge is moved mechanically, e.g. of tunnel type Similar furnaces in which the charge moves by gravity adapted for treating the charge in vacuum or special atmosphere
F27B 19/02 - Combinations of different kinds of furnaces that are not all covered by any single one of main groups combined in one structure
A hydraulic assembly for an aircraft engine includes a pump with a housing and a rotor arranged inside the housing. The housing has at least one hydraulic line configured for the passage of a fluid; and a hydraulic transfer unit comprising: a hydraulic transfer block attached to the housing and comprising an internal fluid passage channel which communicates with the hydraulic line, and a casing which covers the transfer block and which is guided in rotation about an axis of revolution (Y) and about the transfer block, the casing having a fluid outlet port that communicates with the internal channel.
The invention relates to a method for powering actuators of an aircraft comprising at least one generator (500), the actuators being associated with landing gear of the aircraft and comprising at least one actuator for providing at least one of the following functions: A/ extending/retracting the landing gear, B/ steering the steerable wheels of the landing gear, C/ normal braking of the aircraft; and one actuator for providing at least one of the following functions: D/ applying the parking brake of the aircraft, E/ extending the landing gear in emergency mode, F/ braking in emergency mode. The method of the invention comprises the steps of: • - powering the actuator providing at least one of the functions A/, B/, C/ directly with the generator; • - powering the actuator providing at least one of the functions D/, E/, F/ by means of an accumulator (501) connected to the generator by a power line (502) comprising a normally closed switching member (503) for isolating the accumulator from the generator so as to have two independent and segregated power sources, each powering actuators that perform separate functions, the switching member (503) being controllable to open and allow the accumulator to be charged by the generator.
A method for filling a hydraulic circuit of an electro-hydrostatic system includes connecting first and third shut-off valves to a discharge valve, and connecting a second shut-off valve to a filling valve, while the second and third shut-off valves are closed, opening the filling valve, the discharge valve and the first shut-off valve and operating a vacuum generator, once a vacuum has been established in the hydraulic circuit, opening the second shut-off valve in order to fill the hydraulic circuit with pressurized hydraulic fluid while the vacuum generator is still in operation, once the hydraulic circuit has been filled with fluid, closing the first shut-off valve and then opening the third shut-off valve in order to bypass the vacuum generator and circulate the fluid through the electro-hydrostatic system until the fluid contained in the hydraulic circuit reaches a predetermined pressure, and closing the discharge valve and the filling valve.
F15B 21/00 - Common features of fluid actuator systemsFluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
The invention relates to a device for measuring the oxidation of an element comprising a carbon-carbon composite, including a means for measuring the diamagnetism of the element and a means for converting the diamagnetism measurement into an oxidation measurement.
G01N 27/82 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
B60T 17/22 - Devices for monitoring or checking brake systemsSignal devices
F16D 66/00 - Arrangements for monitoring working conditions of brakes, e.g. wear or temperature
67.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR, AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to an eddy current magnetic braking device (1) for a vehicle wheel, the device comprising a first element (3) and a second element (2) that has a main surface (2.1) facing a main surface (3.1) of the first element, the first element being made of an electrically conductive material and the second element being provided with magnets (7) for producing, between the main surfaces of the elements, a magnetic flux capable of generating eddy currents in the first element. The first element comprises a core that is made of a first metal for transmitting a braking torque and is at least partially coated with an outer layer made of a second metal in order to form the main face of the first element. The invention also relates to a vehicle wheel, a landing gear and an aircraft comprising such a device, and to a method for manufacturing the first element of such a device.
A system and method for a hybrid braking architecture for an aircraft is provided. The system can include a friction brake operably coupled to a main landing gear assembly, an eddy current brake operably coupled to a nose or main landing gear assembly and configured to impart up to a maximum resistive force, and a brake controller in communication with the friction brake and the eddy current brake. The brake controller can actuate one or both of the friction and eddy current brakes in response to receiving a braking signal with a required braking force based on an input amplitude of a braking input device. When the required braking force of the braking signal is less than or equal to the maximum resistive force, the eddy current brake can be actuated in the absence of actuating the friction brake to reduce wear on the friction brake, e.g., during taxiing maneuvers.
A system and method for a hybrid braking architecture for an aircraft is provided. The system can include a friction brake operably coupled to a main landing gear assembly, an eddy current brake operably coupled to a nose or main landing gear assembly and configured to impart up to a maximum resistive force, and a brake controller in communication with the friction brake and the eddy current brake. The brake controller can actuate one or both of the friction and eddy current brakes in response to receiving a braking signal with a required braking force based on an input amplitude of a braking input device. When the required braking force of the braking signal is less than or equal to the maximum resistive force, the eddy current brake can be actuated in the absence of actuating the friction brake to reduce wear on the friction brake, e.g., during taxiing maneuvers.
A diffuser for diffusing a gas flow within a stack of blanks that are impregnated with a sol-gel solution, the gas flow evaporating a solvent, each blank having a central through-opening, the openings forming a central well, includes diffusion fins extending from a central cavity toward the periphery of the diffuser, each fin having a central through-opening, the openings forming the open central cavity of the diffuser so as to form an upwardly open gas inlet, the cross section of the central cavity decreasing from the gas inlet, the fins extending into the central well, the fins diffusing and homogenizing the gas flow flowing from the central well through the stack.
F26B 21/00 - Arrangements for supplying or controlling air or gases for drying solid materials or objects
F26B 3/04 - Drying solid materials or objects by processes involving the application of heat by convection, i.e. heat being conveyed from a heat source to the materials or objects to be dried by a gas or vapour, e.g. air the gas or vapour circulating over, or surrounding, the materials or objects to be dried
71.
VEHICLE WHEEL COMPRISING A DRIVE DEVICE AND A BRAKING DEVICE
A wheel (1) rotatably mounted on an axle and comprising: - a rim (2) connected by a web (3) to a hub (4) pivotably received on the axle, and delimiting with the hub an annular space; - a radial flux electric motor (10) comprising a first stator (11) and a first rotor (12) which are arranged to generate a torque for the rotational driving of the wheel; - a magnetic brake (20) comprising a second stator (21) and a second rotor (22) which are arranged to generate a torque for the braking of the wheel, the electric motor and the magnetic brake extending one inside the other inside the annular space, of the first rotor and the second rotor one being adjacent to the rim and of the the first rotor and the second rotor the other being adjacent to the hub, the first stator and the second stator extending between the first rotor and the second rotor.
A method for drying a blank of a part made of a carbon/carbon composite material impregnated with a sol-gel solution, the solution including a solvent and one or more compounds, in a system forming an oven includes gelling the solution so as to form a gel within the blank disposed in the chamber by heating a chamber, where a gas circulator and a desaturation component are deactivated, so as to restrict circulation and desaturation of the gas in a solvent, and drying the gel within the blank by heating, where the gas circulator and the desaturation component are activated, so as to enable circulation and desaturation of the gas in a solvent.
F26B 3/04 - Drying solid materials or objects by processes involving the application of heat by convection, i.e. heat being conveyed from a heat source to the materials or objects to be dried by a gas or vapour, e.g. air the gas or vapour circulating over, or surrounding, the materials or objects to be dried
F26B 9/06 - Machines or apparatus for drying solid materials or objects at rest or with only local agitationDomestic airing cupboards in stationary drums or chambers
The invention relates to a device for preventing the rotation of a wheel (1) rotatably mounted on an axle (2) so as to rotate about an axis of rotation (X), the device comprising a receiving member (4) that is rigidly attached to the wheel and provided with an internal face that has regularly distributed axial cavities (4e); a rotationally stationary cage (6) that extends around the axle facing the receiving member, the cage comprising axial recesses (6a) that accommodate segments (7) that are movable in the cage in respective radial directions between an engagement position in which the segments are engaged in the receptacles in the receiving member and a release position in which the segments are disengaged from the receptacles in the receiving member; a push member (5) made of a material capable of channelling a magnetic flux, the push member extending around the axle in order to co-operate with the segments via oblique bearing surfaces and mounted so as to move axially between a locking position in which the push member forces the segments into the engagement position and an unlocking position in which the push member forces the segments into the release position; a return member (12) for returning the push member to its locking position and maintaining it therein; a permanent magnet (14) exerting an electromagnetic force on the push member designed to maintain the push member in the unlocking position against the force of the return member; an electromagnet (15) that can be selectively powered so as to counteract the force of the permanent magnet in order to allow the push member to move from the unlocking position to the locking position under the effect of the return member or to enhance the force of the permanent magnet in order to move the push member from the locking position to the unlocking position against the force of the return member. The invention also relates to a wheel and an aircraft provided with such a device.
An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.
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 forBrakes combining more than one of the types of groups
77.
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 memberMeans 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 convertingTransducers 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 systemsSignal devices
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
F16D 65/18 - Actuating mechanisms for brakesMeans 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
79.
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 forBrakes 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
87.
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 regulationMeasuring 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
92.
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
93.
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, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using fluid means
97.
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 driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
F16D 63/00 - Brakes not otherwise provided forBrakes combining more than one of the types of groups
F16D 65/18 - Actuating mechanisms for brakesMeans 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
98.
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 clutchesDynamo-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 driveBrake 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 vapoursRecovering vapours of volatile solvents from gasesChemical 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
