A method of fabricating a nitrided low-alloy steel part, includes a) decarburizing the surface of a low-alloy steel part including at least one alloying element that is both nitride-forming and carbide forming in order to obtain a decarburized part presenting a carbon-depleted surface layer of thickness less than or equal to 1.5 mm, the minimum content of carbon by weight in the carbon-depleted surface layer being less than or equal to 70% of the carbon content by weight in the core of the decarburized part; b) treating the decarburized part with quenching treatment followed by annealing treatment; and c) nitriding the carbon-depleted surface layer in order to obtain a nitrided low-alloy steel part, step c) being performed after step b).
C23F 17/00 - Multi-step processes for surface treatment of metallic material involving at least one process provided for in class and at least one process covered by subclass or or class
The invention relates to an aircraft wheel comprising a rim and a tire (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tire, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.
A drive roller (1) comprising a central hub (4), a body (5) extending around the central hub, the body (5) being made of a deformable material, a deformable band (8) extending over a circumference of the drive roller, and first rigid fins (17) and second rigid fins (18) arranged in alternation and extending radially inside the body (5). Each first fin presents a proximal end (17a) fastened to the central hub, and each second fin presents a distal end (18b) that extends in the proximity of the deformable band.
F16H 13/04 - Gearing for conveying rotary motion with constant gear ratio by friction between rotary members without members having orbital motion with balls or with rollers acting in a similar manner
F16D 3/50 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members
F16D 3/76 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members shaped as an elastic ring centered on the axis, surrounding a portion of one coupling part and surrounded by a sleeve of the other coupling part
A roller (1) having a rigid reinforcement (4) defining a hub (5) for rotation of the roller about an axis of rotation X and a plurality of bars (6) regularly arranged around the hub (5) and extending parallel to the axis X. The roller further has bushings (10), each engaged on a respective one of the bars (6) and each comprising an outer rigid ring (11) surrounding a bushing body (12) made of deformable material.
F16H 13/04 - Gearing for conveying rotary motion with constant gear ratio by friction between rotary members without members having orbital motion with balls or with rollers acting in a similar manner
B64C 25/40 - Alighting gear characterised by elements which contact the ground or similar surface the elements being rotated before touch-down
The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut. According to the invention, the undercarriage includes at least one vane (20) fastened to the end of the throttle needle in order to extend inside a portion of the second chamber that is filled with hydraulic fluid.
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
F16F 9/12 - Devices with one or more rotary vanes turning in the fluid, any throttling effect being immaterial
F16F 9/18 - Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts with a closed cylinder and a piston separating two or more working spaces therein
F15B 15/06 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member for mechanically converting rectilinear movement into non-rectilinear movement
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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
7.
Machining systems comprising a machining facility and control methods
a physical controller (18) for executing a machining program (19) and for controlling the actuators (14) as a function of the shape correction data (20), so as to move the real tool (12) relative to the real blank (13).
of the position of the real tool (12) at a given instant.
G05B 19/27 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by positioning or contouring control systems, e.g. to control position from one programmed point to another or to control movement along a programmed continuous path using an absolute digital measuring device
G05B 19/4069 - Simulating machining process on screen
G05B 19/04 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers
G05B 19/402 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for positioning, e.g. centring a tool relative to a hole in the workpiece, additional detection means to correct position
Subjecting an aluminum or aluminum alloy substrate to anti-corrosion and anti-wear treatment that is applicable in particular in the field of aviation for protecting certain mechanical parts of airplanes or helicopters that are subjected simultaneously to corrosion and to wear, including applying to the substrate, a sol-gel treatment step forming a sol-gel layer; and after the sol-gel treatment step, a hard oxidation step forming a hard oxide layer.
C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
A method of fabricating a nitrided low-alloy steel part, includes a) decarburizing the surface of a low-alloy steel part including at least one alloying element that is both nitride-forming and carbide forming in order to obtain a decarburized part presenting a carbon-depleted surface layer of thickness less than or equal to 1.5 mm, the minimum content of carbon by weight in the carbon-depleted surface layer being less than or equal to 70% of the carbon content by weight in the core of the decarburized part; b) treating the decarburized part with quenching treatment followed by annealing treatment; and c) nitriding the carbon-depleted surface layer in order to obtain a nitrided low-alloy steel part, step c) being performed after step b).
C23F 17/00 - Multi-step processes for surface treatment of metallic material involving at least one process provided for in class and at least one process covered by subclass or or class
10.
AIRCRAFT LANDING GEAR INCLUDING A TELESCOPIC LINEAR ROD
Aircraft landing gear including a telescopic liner rod (0, 0', 0") including first and second sliding parts of the rod. The landing gear in addition includes: a first set of permanent magnets (1a, 1a', 1a") affixed to the first part of the rod (1, 1', 1"); - a second set of permanent magnets (2a, 2a', 2a") affixed to the second part of the rod (2, 2', 2"); The first and second sets of permanent magnets (1a, 1a', 1a", 2a, 2a', 2a") generating a magnetic repulsion force between the first part of the rod (1, 1', 1") and the second part of the rod (2, 2', 2") and maintaining a first annular space (E1) between the first part of the rod and the second part of the rod.
a″) generating a magnetic repulsion force between the first rod portion (1, 1′, 1″) and the second rod portion (2, 2′, 2″) and maintaining a first annular space (E1) between the first rod portion and the second rod portion.
Control system (1) comprising a control rod (5) extending between a first zone (2) situated in a hydraulic chamber delimited by a chamber wall (3) and a second zone (4) situated outside the hydraulic chamber. The control system (1) further comprising a seal (6) arranged around and against this control rod (5) to oppose the passage of fluid between the first and second zones (2, 4). The system further comprises a guide piece (7) assembled removably with respect to the chamber wall (3), the seal (6) is assembled inside the guide piece (7) so as to allow relative movement of the rod (5) with respect to the guide piece (7) while at the same time achieving sealing between the first and second zones (2, 4).
F15B 15/28 - Means for indicating the position, e.g. end of stroke
F16H 21/04 - Guiding mechanisms, e.g. for straight-line guidance
F16H 21/44 - Gearings comprising primarily only links or levers, with or without slides all movement being in, or parallel to, a single plane for conveying or interconverting oscillating or reciprocating motions
F16J 15/18 - Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings
F16J 15/50 - Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall
F16J 15/52 - Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall by means of sealing bellows or diaphragms
13.
Proximity sensor for aircraft and having a hydraulic fuse
A sensor (1) having a housing (2) defining an internal volume (3), a movable part (4), a detector (5) for detecting movement of the movable part (4), a transfer mechanism (6) passing through a first opening (7) of the housing (2) to control movement of the movable part (4) from a first external zone (8), and a first sealing structure (9) for opposing the passage of fluid coming from the first external zone (8) towards said internal volume (3). The housing (2) includes a second opening (10) extending between the internal volume (3) and a second external zone (11); and a second sealing structure (12) between the internal volume (3) and the second external zone (11), the second sealing structure being adapted to break so as to allow fluid to pass as soon as a first predetermined pressure difference is exceeded.
B64C 25/28 - Control or locking systems therefor with indicating or warning devices
G01L 13/00 - Devices or apparatus for measuring differences of two or more fluid pressure values
F15B 20/00 - Safety arrangements for fluid actuator systemsApplications of safety devices in fluid actuator systemsEmergency measures for fluid actuator systems
14.
PROXIMITY SENSOR FOR AN AIRCRAFT FEATURING A HYDRAULIC FUSE
Sensor (1) including: - a housing (2) defining an internal volume (3); - a mobile part (4); - movement detection means (5) for the mobile part (4); - the means to activate (6) passing through a first opening (7) in the housing (2) to control the movement of the mobile part (4) from a first external zone (8); - first sealing means (9) to oppose the passage of fluid from the first external zone (8) toward the said internal volume (3). The housing (2) includes a second opening (10) extending between the internal volume (3) and a second external zone (11); and second sealing means (12) designed to break, to allow the passage of fluid, between the internal volume (3) and the second external zone (11), as soon as a first predetermined pressure differential is surpassed.
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 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 20/00 - Safety arrangements for fluid actuator systemsApplications of safety devices in fluid actuator systemsEmergency measures for fluid actuator systems
Control system (1) including a control rod (5) extending between: - a first zone (2) located in a hydraulic enclosure defined by an enclosure wall (3); and a second zone (4) located outside the said hydraulic enclosure; the control system (1) including in addition the means to seal (6) arranged around and against this control rod (5) to oppose the passage of fluid between the first and second zones (2, 4). The system includes a guiding part (7) assembled removably facing the enclosure wall (3), the means to seal (6) are assembled inside the guiding part (7) so as to allow the relative displacement of the rod (5) relative to the guiding part (7) while producing a seal between the said first and second zones (2, 4).
F15B 15/02 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member
16.
Method for rotationally driving the wheel of an airplane
An assembly for rotationally friction driving the wheel of an airplane provided with a driving track. The assembly has a base intended to be fixed to a lower part of the landing gear, two arms mounted to pivot on the base, and rollers so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving the roller. A central pinion is mounted so as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion. A drive actuator acts on the arms of the assembly so as to position the assembly either in a disengaged position in which the rollers are separated from the driving track, or in an engaged position in which the rollers are held to rest on the driving track.
Drive equipment for rotating by friction an aircraft wheel equipped with a drive track and mounted to turn about an axis (X) on an axle of an aircraft undercarriage. The equipment comprise a base (22), a slide (24) mounted on the base on a sliding axis extending in a radial direction (R1, R1), a support (26) pivotable on the slide on an axis parallel to the rotation axis of the wheel; two rollers (21) rotatable on rotation axes parallel to the pivot axis; a central shaft (28) mounted for rotation on the support and being in engagement with the two rollers to provide their rotation; and an actuator (23A, 23B, 30) for moving the slide and the support between a disengagement position with the rollers distant from the wheel drive track and an engagement position with the rollers are held in contact with the drive track of the wheel.
A honing tool (1) for honing a cylindrical external surface (2) of a rod (3). The tool comprises a plurality of honing inserts (4), adapted to hone a metal, and a support (5) for the honing inserts. The inserts (4) are carried by the support (5) and define a passage (6) around which the inserts (4) are to be found and in which the cylindrical external surface (2) of the rod (3) is insertable. The tool (1) includes a plurality of sliding skids (7) carried by the support (5), the sliding skids (7) and the honing inserts (4) being arranged to be capable of coming simultaneously into contact against the cylindrical external surface (2) of the rod (3) when the rod is placed inside the passage (6) and so as to be able to center the cylindrical external surface (2) inside the passage (6).
B24B 5/04 - Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfacesAccessories therefor involving centres or chucks for holding work for grinding cylindrical surfaces externally
B24B 33/04 - Honing machines or devicesAccessories therefor designed for working external surfaces of revolution
19.
HONING TOOL FOR THE EXTERNAL SURFACE OF A STRAIGHT CYLINDRICAL TUBE
Honing tool (1) to hone a cylindrical outer surface (2) of a rod (3), the tool including: - several honing stones (4) designed to hone metal; and a support (5) for these honing stones, the stones (4) borne by the support (5) so as to define a passage (6) around which the stones (4) are located and in which the outer cylindrical surface (2) of the rod (3) can be inserted. The tool (1) includes several sliding skates (7) borne by the support (5), these sliding skates (7) and the placement of the honing stones (4) enabling simultaneously contact against the external cylindrical surface (2) of the rod (3) when the latter is placed inside the said passage (6) and enabling centring of this external cylindrical surface (2) inside the said passage (6).
The invention relates to a method for managing the braking of an aircraft fitted with undercarriages (1) bearing braked wheels (2), the method comprising the step of generating braking commands by means of a braking computer (4) for each of the braked wheels as a function of longitudinal speed information representative of a longitudinal movement of the wheels in question, characterized in that there is placed at the bottom of the undercarriage, close to the braked wheels, a sensor adapted for generating a signal that can be used for generating the longitudinal speed information used for generating the braking commands.
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
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
21.
Method for fixing an actuator for rotatably driving a wheel of an aircraft
A method for fixing to an aircraft landing gear (1) at least one actuator (30) for rotatably driving a wheel (3) which is rotatably mounted on an axle (2) of the landing gear, the wheel being associated with a brake (5). The brake has an actuator carrier (8) which carries brake actuators, the actuator carrier being fitted onto the axle and stopped in terms of rotation by an obstacle (12) which is fixedly joined to the landing gear and which is introduced into one of several stop holes (11) of the actuator carrier. The drive actuator is fixedly joined to the actuator carrier in the region of a stop hole of the actuator carrier which does not receive the obstacle.
F16H 1/10 - Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members with parallel axes one of the members being internally toothed
22.
Method of coating the surface of a metal substrate
A method of coating the surface of a metal substrate includes a) applying a first composition on the surface of a metal substrate, the first composition being a solution comprising a liquid medium including sol-gel precursors of alcoxysilane type or of metallo-organic type; b) subjecting the first composition to first heat treatment to form an anchor layer on the metal substrate in which the sol-gel precursors are bonded to the metal substrate, a first temperature being imposed during the first heat treatment that is sufficient to eliminate all or part of the liquid medium and to encourage the bonding of the sol-gel precursors to the metal substrate; and c) applying a second composition on the anchor layer. The second composition includes coating compounds to obtain a coating on the anchor layer by forming bonds between the sol-gel precursors and the coating compounds.
B05D 7/00 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
C23C 22/78 - Pretreatment of the material to be coated
C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
23.
Aircraft undercarriage with wheel brake and drive assembly having a coupler member
An undercarriage having a wheel mounted on an axle (3), a brake and a drive assembly. The brake comprises a torsion tube (9), friction members (11) mounted around the torsion tube, and at least one brake actuator (13) for selectively exerting a braking force on the friction members. The drive assembly is operative to drive rotation of the wheel and comprises an electric motor (14) that is connected to a rim (5) of the wheel (4) by a coupler member (15). The coupler member extends at least in part around the axle (3) between the axle and the torsion tube (9) of the brake.
A sensor (1) comprising a casing (2) delimiting an internal volume (3) and having a passage (31) between the internal volume and a first external zone (Z1) external to the casing; a moving part (4) moveable inside the internal volume (3); detector (5) for detecting a movement of the moving part (4) comprising a detection portion (51) extending in the passage (31) and having a groove (52) open to the outside of the detection portion (51), the groove (52) extending between the first external zone (Z1) external to the casing and the internal volume (3) internal to the casing. The sensor (1) comprises first sealing structure (14) positioned around the detection portion (51) inside the passage (31), the first sealing structure (14) being arranged in such a way as to prevent fluid from passing between the internal volume (3) and the first external zone (Z1) via the groove (52).
G01D 5/12 - 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
25.
PROXIMITY SENSOR FOR AN AIRCRAFT EQUIPPED WIH A PARTICULAR SEALED ASSEMBLY
Proximity sensor (1) for aircraft including: a housing (2) defining an internal volume (3) and presenting a passage (31) between this internal volume and a first external zone (Z1) of the housing; - a mobile part (4) in the internal volume (3); - the means to detect (5) movement of the said mobile part (4) comprising a detection portion (51) and extending into the passage (31) and a groove (52) open to the exterior of the detection portion (51) and extending between the first external zone (Z1) and the said internal volume (3). To improve the seal between the external zone (Z1) and the internal volume (3), first sealing means (14) are located around the detection portion (51) inside the passage (31), these first sealing means (14) preventing the passage of fluid through the said groove (52).
A method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (5). According to the method, a drive member for generating a torque for driving the wheel is controlled. The transfer of the drive torque to the wheel is accomplished via the rim assembly bolts.
B21D 1/00 - Straightening, restoring form or removing local distortions of sheet metal or specific articles made therefromStretching sheet metal combined with rolling
B23P 19/02 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same
B60B 3/00 - Disc wheels, i.e. wheels with load-supporting disc body
B25B 27/06 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same inserting or withdrawing sleeves or bearing races
28.
PROCESS FOR MAKING A RIM COMPLIANT AND TOOLS FOR THE IMPLEMENTATION OF THE PROCESS
Procédé de remise en conformité d'une jante de roue comportant une pluralité d'alésages ovalisés. Le procédé est caractérisé en ce qu'il comporte au moins une étape d'alésage d'un premier alésage ovalisé à l'aide d'un alésoir présentant des portions longitudinales de pilotage et de coupe, la portion de coupe présentant des dents définissant un diamètre de coupe et la portion de pilotage présentant un diamètre de pilotage strictement inférieur au diamètre de coupe, l'étape d'alésage de ce premier alésage ovalisé consistant à insérer l'alésoir dans ce premier alésage ovalisé en commençant par la portion de pilotage puis par la portion de coupe, le diamètre de pilotage étant tel qu'il permette un guidage en translation de l'alésoir à l'intérieur de ce premier alésage ovalisé à aléser.
The invention relates to an aircraft undercarriage intended to be mounted so as to be able to move on the aircraft between a deployed position and a retracted position, the undercarriage comprising a roller (1) carried by a support (4) secured to the undercarriage while being able to be moved with respect thereto, characterised in that the support is mounted pivotally on the undercarriage.
Leak detection process for a dynamic joint in an aircraft landing gear including at least: - a housing; - a sliding rod mounted in the housing; - an offset bearing at one extremity of the housing to guide the rod, the said bearing comprising at least one pad equipped with at least one dynamic sealing joint arranged to rub on the rod to ensure a seal between the housing and the rod, delimiting a chamber filled with hydraulic fluid between the said housing and the said rod, and a stop bolt for the pad in translation relative to the housing featuring at least one wiping joint arranged to wipe the hydraulic fluid on the rod. According to the invention the process includes the step of installing a test bolt without a wiping joint in the place of the stop bolt, of putting hydraulic fluid under pressure in the landing gear and to check for the existence of a potential hydraulic fluid leak on an outer surface of the rod.
The invention relates to a tubular fusible member (21) extending along a longitudinal axis (AL) and for engaging in a two-lug clevis (14) and a single-lug clevis (12) in order to form a hinge (11). According to the invention, the fusible member (21) is constrained in rotation with one of the clevises (12, 14), and it presents a cross-section of shape that varies gradually between a central section and two distal sections, each distal section having reinforced thickness in its regions that extend parallel to the bending plane (PF) in which the fusible member (21) bends when it is stressed, the central section having a second moment of area relative to an axis normal to the bending plane (PF) that is greater than the second moment of area of the distal sections.
Protection device for a part to be protected including a body separable into at least two sub-elements, each sub-element including a cavity intended to at least partly receive the part to be protected, the device including the means to hold the sub-elements in position relative to one another and at least one of the sub-elements including a portion of its cavity which features a surface opposing the relative sliding of the protection device and the part to be protected.
B05B 12/32 - Shielding elements, i.e. elements preventing overspray from reaching areas other than the object to be sprayed
B05D 1/32 - Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
33.
Protecting parts made of carbon-containing composite material from oxidation
4C powder; and b) applying heat treatment to the coating composition applied during step a) with a treatment temperature lying in the range 330° C. to 730° C. being imposed during the heat treatment in order to obtain a coating on the outside surface of the part, the coating including a first phase in which the metallic phosphate is in crystalline form and a second phase in which the metallic phosphate is in amorphous form.
C04B 41/85 - Coating or impregnating with inorganic materials
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
B05D 3/02 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
C04B 111/00 - Function, property or use of the mortars, concrete or artificial stone
34.
Method for maneuvering doors of bays of aircraft, and actuator used therefor
The invention relates to a method for locking a mobile element (101) of an aircraft, such as a hold door or a landing gear, the mobile element being moved between a deployed position and a closed or retracted position by means of an actuator (200) having a sliding stem (3) coupled to the mobile element, the stem being mounted so as to be able to slide in a body (1) of the actuator between an extended position corresponding to the deployed position of the mobile element and a withdrawn position corresponding to the closed or retracted position of the mobile element. The method of the invention comprises the step of positively blocking the sliding stem of the actuator in the withdrawn position.
The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106′) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16′) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112′; 112″) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.
B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/22 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/24 - 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
F16C 7/02 - Constructions of connecting-rods with constant length
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
36.
MEASUREMENT OF DIMENSIONAL CHARACTERISTICS OF A PRODUCTION PART
Measurement tool (1) for the dimensional characteristics (D) of a production part (2), this tool (1) including: - positioning means (3a, 3b) for the measurement tool (1) relative to the part (2); - at least one measurement device (4a, 4b) mechanically connected to the positioning means (3a, 3b) by means of mechanical links (5). The positioning means (3a, 3b) include: - first and second centering means (6a, 6b) to come into contact against an inner surface (7a) of a first bore (22a1) of the production part (2); - second centering means (6b) to come into contact with an inner surface (7b) of a second bore (22b1) of the production part (2), these first and second bores (22a1, 22b1) being coaxial. The mechanical linking means (5) allow the relative displacement of the measurement device (4a, 4b) relative to the first and second centering means (6a, 6b) so that the measurement device (4a, 4b) touches one of the inner surfaces (7a, 7b).
Aircraft landing gear (100) with a lower part (110) that is orientable by means of an orientation actuator (1) which comprises a cogged wheel (70) secured to the orientable lower part (110), collaborating with a rack (20) capable of translational movement along an axial axis of movement (X) and having ends (21a, 21b) connected to pistons (30a, 30b) slideably mounted in respective cylinders (10a, 10b). Each connection between one of the pistons (30a, 30b) of the associated end of the rack (20) has a least an axial play (J), possibly an angular play (E) and at least one seal, referred to as internal seal (25), between the rack (20) and a piston (30a, 30b), this seal being arranged in such a way as to oppose the relative movements of the rack (20) with respect to the pistons (30a, 30b).
B62D 5/22 - Power-assisted or power-driven steering fluid, i.e. using a pressurised fluid for most or all the force required for steering a vehicle specially adapted for particular type of steering gear or particular application for rack-and-pinion type
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
F16H 19/04 - Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and reciprocating motion comprising a rack
38.
MACHINING SYSTEMS COMPRISING A MACHINING FACILITY AND CONTROL METHODS
Machining system (10) comprising a facility comprising: - a real tool (12);- actuators (14) for displacing the real tool (12); - sensors (15) for generating positioning data (16) for the real tool (12); - a memory (17) for storing correction data in respect of the geometry (20) of the real tool (12); - a physical controller (18) for executing a machining program (19) and commanding the actuators (14), as a function of the data for correction of geometry (20), to displace the real tool (12) with respect to the real blank (13). On the basis of said data (22) representative of the positions of the real tool (12) and of the real blank (13), means for displaying images (24) generate a reconstituted image (25) representative: of the shape of the real blank (13); and of the position of the real tool (12) at a given instant.
Machining system (10) comprising a facility comprising: - a real tool (12);- actuators (14) for displacing the real tool (12); - sensors (15) for generating positioning data (16) for the real tool (12); - a memory (17) for storing correction data in respect of the geometry (20) of the real tool (12); - a physical controller (18) for executing a machining program (19) and commanding the actuators (14), as a function of the data for correction of geometry (20), to displace the real tool (12) with respect to the real blank (13). On the basis of said data (22) representative of the positions of the real tool (12) and of the real blank (13), means for displaying images (24) generate a reconstituted image (25) representative: of the shape of the real blank (13); and of the position of the real tool (12) at a given instant.
The invention relates to a method for anticorrosion and antiwear treatment of an aluminium or aluminium alloy substrate, especially in the field of aeronautics, for protecting mechanical parts of aeroplanes or helicopters subjected to both corrosion and wear. According to the invention, the method comprises applying to the substrate (10): a step of sol-gel treatment forming a sol-gel layer (200); and, following the sol-gel treatment step, a step of hard oxidation forming a hard oxide layer (30).
The invention relates to a method for anticorrosion and antiwear treatment of an aluminium or aluminium alloy substrate, especially in the field of aeronautics, for protecting mechanical parts of aeroplanes or helicopters subjected to both corrosion and wear. According to the invention, the method comprises applying to the substrate (10): a step of sol-gel treatment forming a sol-gel layer (200); and, following the sol-gel treatment step, a step of hard oxidation forming a hard oxide layer (30).
The invention relates to a method for managing the braking of an aircraft equipped with landing gear (1) comprising braked wheels (2), the method comprising the step of generating braking instructions for each of the braked wheels, by means of a braking calculator (4), according to forward speed information representative of a forward movement of the wheels in question, characterised in that a sensor is placed at the bottom of the landing gear, close to the braked wheels, said sensor being suitable for generating a signal that can be used to generate the forward speed information used to generate braking instructions.
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
B60T 8/17 - Using electrical or electronic regulation means to control braking
43.
SUPPORTING TOOL FOR SUPPORTING CYLINDRICAL PARTS, LIKE LANDING GEAR RODS AND CYLINDERS
Supporting tool (1) for supporting a substantially cylindrical part, like a landing gear rod or cylinder, said supporting tool comprising a metallic frame carrying at least one metallic ring (3) in electrical conductive relation with the frame, wherein the metallic ring carries a plurality of conical spikes (6) of non-conductive material projecting inward so as to engage the part with limited contact surface when said part is in place within the tool, said ring being openable so as to allow the part to be inserted into the ring and closable after the part has been inserted.
The invention relates to a method for protecting a metal substrate coated using the HVOF method with a coating of the WC-Co-Cr type, comprising the application on the coating of a lubricant agent that comprises particles of solid lubricant incorporated into a fluid having a low enough surface tension to penetrate into the pores of the coating and drive the solid lubricant particles therein.
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
An electromechanical actuator comprising an actuator member and an electric motor (2) adapted to drive the actuator member. The electric motor (2) comprises a rotor portion (4), a stator portion (5) comprising a yoke-forming body (9) and a set of coils received in slots (12) in the body (9), and at least one electrical module (17). The electrical module is adapted to generate an electrical power supply current (Ia) for the electric motor (2), which current flows in the set of coils. The electrical module (17) is carried by the body (9).
H02K 11/00 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 19/36 - Structural association of synchronous generators with auxiliary electric devices influencing the characteristic of the generator or controlling the generator, e.g. with impedances or switches
H02K 3/50 - Fastening of winding heads, equalising connectors, or connections thereto
46.
Table and a method for needling a textile structure formed from an annular fiber preform, with radial offsetting of the needling head
A circular needling table for needling a textile structure made from an annular fiber preform, includes: a horizontal top on which an annular fiber preform is to be placed; a driver system constructed and arranged to drive the fiber preform in rotation about a vertical axis of rotation; and a needling device for needling the fiber preform, the device including a needling head extending over a predetermined angular sector of the table top and to be driven with vertical reciprocating motion relative to the table top, and a mover system constructed and arranged to move the needling head in a direction that is radial relative to the axis of rotation of the fiber preform.
D04H 1/46 - 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 the fleeces or layers being consolidated by mechanical means, e.g. by rolling by needling or like operations to cause entanglement of fibres
D04H 1/498 - 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 the fleeces or layers being consolidated by mechanical means, e.g. by rolling by needling or like operations to cause entanglement of fibres entanglement of layered webs
47.
CONTROL PROCESS IN A ROBOTIC SYSTEM FOR COATING A PART BY SPRAYING A MATERIAL
La présente invention concerne la découverte de polymorphismes génétiques qui sont associés à la fibrose du foie et à des pathologies associées. Cette invention concerne en particulier des molécules dacides nucléiques qui contiennent ces polymorphismes, des protéines de variant codées par de telles molécules dacides nucléiques, des réactifs pour la détection de ces molécules et de ces protéines dacides nucléiques polymorphiques, ainsi que des techniques dutilisation de ces acides nucléiques et de ces protéines et des techniques dutilisation de réactifs qui permettent leur détection.
A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29C 65/72 - Joining of preformed partsApparatus therefor by combined operations, e.g. welding and stitching
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/24 - 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
F16C 7/02 - Constructions of connecting-rods with constant length
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
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]
49.
AIRCRAFT LANDING GEAR PROVIDED WITH AN ADJUSTABLE ROLLER
The invention relates to an aircraft undercarriage to be mounted on the aircraft such that it can be moved between a deployed position and a retracted position, the undercarriage comprising a roller (1) carried by a support (4) which is both secured to the undercarriage and movable in relation thereto, characterised in that the support is pivotably mounted on the undercarriage.
The invention relates to an aircraft undercarriage to be mounted on the aircraft such that it can be moved between a deployed position and a retracted position, the undercarriage comprising a roller (1) carried by a support (4) which is both secured to the undercarriage and movable in relation thereto, characterised in that the support is pivotably mounted on the undercarriage.
The invention concerns an electromechanical actuator for a vehicle brake comprising a first part 8 separable from a second part 9, the first part 8 including an electric motor 5 and the means to connect 15 for connecting the actuator to external control means 4, and the second part 9 including a sliding plunger 6, the second part 9 including in addition the means to measure 21. According to the invention, the first part 8 comprises a first antenna 14 connected to the connection means 15 and the second part 9 comprises a second antenna 22 connected to the means to measure 21 and the two antennae 14, 22 located so as to be electromechanically coupled to one another when the first part 8 and the second part 9 are coupled, so as to enable electrical signals to be transferred between the means to measure 21 and the connection means 15.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
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
The invention concerns a multifunctional device for landing gear, including at least a first shaft (10) rotary mounted onto the aircraft around a rotation axis essentially parallel to an articulation axis on the aircraft landing gear; a second telescopic shaft (20) rotary mounted on the landing gear extending downward along the latter until it is in the vicinity of the wheels borne by the latter, and motors (11, 15) designed to rotate the first shaft. According to the invention, the second telescopic shaft is singular and extends inside the landing gear until it is in the vicinity of an axle (8) bearing the wheels of the landing gear, and linked to a differential (21) connected to the wheels via drive shafts (22) extending into the axle.
Process for fabricating a part (1) comprising a metallic substrate (Sub) at least partially covered with a coating layer (Coat), the process comprising: - the preparation (A) of a surface of the substrate (Sub) to be covered, in order to obtain a prepared surface having a roughness Ra of between 0.6 and 1.6 µm and preferably of between 0.8 and 1.6 µm; - the formation (C) on the prepared surface of the substrate, of the coating layer (Coat), this coating layer (Coat) being formed by spraying, according to an HVOF spraying process, a pulverulent mixture containing metal carbide grains (G), these grains (G) having dimensions strictly less than 1 µm and the thickness (Thk min) of the coating layer (Coat) thus formed being less than 50 µm; next - the finishing by polishing (D) of at least one surface of said coating layer (Coat) so as to ensure that its roughness Ra is less than 1.6 µm.
C23C 4/02 - Pretreatment of the material to be coated, e.g. for coating on selected surface areas
C23C 4/10 - Oxides, borides, carbides, nitrides or silicidesMixtures thereof
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
Process for fabricating a part (1) comprising a metallic substrate (Sub) at least partially covered with a coating layer (Coat), the process comprising: - the preparation (A) of a surface of the substrate (Sub) to be covered, in order to obtain a prepared surface having a roughness Ra of between 0.6 and 1.6 μm and preferably of between 0.8 and 1.6 μm; - the formation (C) on the prepared surface of the substrate, of the coating layer (Coat), this coating layer (Coat) being formed by spraying, according to an HVOF spraying process, a pulverulent mixture containing metal carbide grains (G), these grains (G) having dimensions strictly less than 1 μm and the thickness (Thk min) of the coating layer (Coat) thus formed being less than 50 μm; next - the finishing by polishing (D) of at least one surface of said coating layer (Coat) so as to ensure that its roughness Ra is less than 1.6 μm.
C23C 4/02 - Pretreatment of the material to be coated, e.g. for coating on selected surface areas
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.
The invention concerns a tubular fusible member (21) extending along a longitudinal axis (AL), intended to engage in a double yoke (14) and in a single yoke (12) to form a hinge (11). According to the invention, the fusible member (21) is integral in rotation with one of the yokes (12, 14), and has a transverse section of which the shape gradually changes between a central section and two distal sections, each distal section having a thickness that is reinforced in the regions thereof that extend parallel to the bending plane (PF) in which the fusible member (21) works when it is biased, the central section having a quadratic moment relative to an axis normal to the bending plane (PF) that is greater than the quadratic moment of the distal sections.
The invention concerns a tubular fusible member (21) extending along a longitudinal axis (AL), intended to engage in a double yoke (14) and in a single yoke (12) to form a hinge (11). According to the invention, the fusible member (21) is integral in rotation with one of the yokes (12, 14), and has a transverse section of which the shape gradually changes between a central section and two distal sections, each distal section having a thickness that is reinforced in the regions thereof that extend parallel to the bending plane (PF) in which the fusible member (21) works when it is biased, the central section having a quadratic moment relative to an axis normal to the bending plane (PF) that is greater than the quadratic moment of the distal sections.
The invention relates to an aircraft landing gear comprising: a strut (12) intended to be articulated to a structure of the aircraft in order to be able to move between a deployed position and a retracted position, a brace strut (15); a lock link assembly (20) and an unlocking actuator (30) having a first end coupled to the lock link assembly and operable to bring about a misalignment of the links during retraction or deployment of the landing gear against the action of the elastic member. According to the invention, the unlocking actuator is of the dual acting type and the landing gear comprises means (31, 33) of coupling a second end of the unlocking actuator which cause a relative movement of said second end with respect to the strut so that, in one and the same action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of the positions and tends to reinforce said alignment when the landing gear is in the other of the positions.
The invention relates to an aircraft landing gear comprising: a strut (12) intended to be articulated to a structure of the aircraft in order to be able to move between a deployed position and a retracted position, a brace strut (15); a lock link assembly (20) and an unlocking actuator (30) having a first end coupled to the lock link assembly and operable to bring about a misalignment of the links during retraction or deployment of the landing gear against the action of the elastic member. According to the invention, the unlocking actuator is of the dual acting type and the landing gear comprises means (31, 33) of coupling a second end of the unlocking actuator which cause a relative movement of said second end with respect to the strut so that, in one and the same action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of the positions and tends to reinforce said alignment when the landing gear is in the other of the positions.
The invention relates to an actuator comprising a cylinder (1) in which a rod (2) is mounted to slide, the actuator having a screw (8) extending inside the rod to co-operate with a nut (7) secured to the rod, the screw being driven in rotation by a motor (10), the actuator being characterized in that a hydraulic chamber (CH) filled with hydraulic fluid is arranged inside the actuator by means of a floating piston (20) sliding in sealed manner against the rod inside of the actuator, the hydraulic chamber being in fluid flow communication with an accumulator (21) via a solenoid valve (22) that is controllable between a closed state in which the chamber is isolated from the accumulator, and a fluid-passing state in which the hydraulic chamber and the accumulator are in communication, calibrated resistance being exerted against the passage of fluid from the chamber towards the accumulator.
B60G 15/12 - Resilient suspensions characterised by arrangement, location, or type of combined spring and vibration- damper, e.g. telescopic type having fluid spring and fluid damper
The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake 2 fitted to at least one braked wheel 1 of the aircraft, the brake 2 having friction members 3 and a plurality of electromechanical actuators 4, each actuator 4 comprising a pusher 5 suitable for being moved by means of an electric motor 6 to selectively apply a pressing force on the friction members 3. According to the invention, for a given braking operation, a total braking force to be applied against the friction members 3 of the brake is distributed in non-uniform manner amongst the actuators 4 of the brake, such that at least two actuators 4 apply respective different forces.
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
The invention concerns an aircraft electromechanical braking method comprising at least one electromechanical brake equipping at least one braked wheel of the aircraft, the brake including friction elements and a plurality of electromechanical actuators, each actuator including a plunger capable of being moved by means of an electric motor to selectively apply a pressure force on the friction elements. According to the invention, for a given braking force, the total force to be applied to the friction elements of the brake are distributed heterogeneously among the brake actuators, so that at least two actuators apply respectively distinct forces.
The invention concerns an electromechanical braking system for an aircraft comprising the means to control braking and at least one electromechanical brake equipping at least one braked wheel on the aircraft, the brake being equipped with friction elements and with at least one electromechanical actuator comprising a plunger capable of being moved by an electric motor, the actuator comprising in addition a blockage unit to block the plunger in place, the means to control being designed to make the braking system operate at least in controlled mode or in parked mode. According to the invention, the control means are designed to operate the braking system in a supplementary braking mode called a combined mode, in which the motor is activated to bring the plunger into a position in which it exerts a given maintenance pressure, then the blockage unit is activated, the motor being maintained activated to allow the plunger to develop force supplementary beyond the maintenance pressure.
The invention concerns a braking system architecture for an aircraft equipped with braked wheels by means of brakes with electromechanical activation, the braking system including controllers to distribute electrical power to the actuators in response to a braking instruction, each controller associated to actuators for the same brake. According to the invention, each controller includes an input to receive information about the rotation speed of the wheel braked by the actuators associated to the said controller, the controller comprising processing means to modulate the power transmitted to the actuators based on the rotation speed of the wheel in order to provide anti-slip protection.
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
The invention provides a method of mounting an aircraft wheel drive member (30) on an undercarriage having an axle (1) that carries the wheel and that is provided with a torque plate (3) having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support (10) that bears against an inside face of the torque plate opposite from its outside face against which a brake (2) is fitted, and of fitting the drive member on the support.
The invention concerns an assembly method for a drive unit in an aircraft wheel on landing gear with an axle bearing the wheel, and that is equipped with an axle casing with an outer face against which the brake may be applied, the method including the step of applying a support borne against an inner face of the axle casing which is opposite A, an outer face of the latter against which a brake is applied, and to apply the drive element on this support.
Assistance device for regulating a liquid electrolytic bath, including a basin for containing the bath and a support for metal components to be dissolved in the bath, this support arranged relative to the basin to selectively immerse the metal components in the bath contained in the basin. The support includes the means to measure a force depending on the mass of metal components borne by the support.
F16D 55/24 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with a plurality of axially-movable discs, lamellae, or pads, pressed from one side towards an axially-located member
F16D 65/28 - Actuating mechanisms for brakesMeans for initiating operation at a predetermined position arranged apart from the brake
The invention concerns an unlocking process for an aircraft wheel brake equipped with at least one electromechanical actuator including at least one electrical engine and a plunger moveable by the action of the engine, facing braking friction elements to selectively apply braking effort on the friction elements, the actuator being equipped with a locking element to lock the plunger in position at least after the actuator has been commanded to apply braking effort for parking. According to the invention, the unlocking process comprises the steps of: - connecting an external command box onto the brake, designed to act upon at least the locking element of the actuator; - using the external command box, command the locking element to unlock the plunger.
An analysis method for quantifying a level of cleanliness and/or activation of a surface (S) of an electrically conductive part (P). The method comprises: - positioning a counter-electrode (2) and the surface (S) of the part (P) in an electrolyte (1) containing ions; - using a generator (G) to apply electrical current at an electrical voltage (V) between the counter-electrode (2) and the surface (S) of the part (P) of which the level of cleanliness and/or activation is being sought; - measuring the change over time in the intensity (I) of the current flowing between the counter-electrode (2) and said surface (S) of the conductive part (P); - assessing a level of cleanliness and/or activation of the surface (S) on the basis of said measurement of the change in intensity (I).
An analysis method for quantifying a level of cleanliness and/or activation of a surface (S) of an electrically conductive part (P). The method comprises: - positioning a counter-electrode (2) and the surface (S) of the part (P) in an electrolyte (1) containing ions; - using a generator (G) to apply electrical current at an electrical voltage (V) between the counter-electrode (2) and the surface (S) of the part (P) of which the level of cleanliness and/or activation is being sought; - measuring the change over time in the intensity (I) of the current flowing between the counter-electrode (2) and said surface (S) of the conductive part (P); - assessing a level of cleanliness and/or activation of the surface (S) on the basis of said measurement of the change in intensity (I).
The invention concerns an aircraft wheel brake comprising actuator-carrier that bears at least one electromechanical actuator comprising a plunger, moveable in a direction parallel to a rotation axis of the wheel facing friction elements, to selectively apply a braking force on the friction elements, the actuator-carrier and the actuator comprising the means to guide the actuator when it is lifted on the actuator-carrier in a radial direction to a service position, the said guiding means creating a support apt to assure the transmission of the braking force from the actuator to the actuator-carrier, and the means to hold the actuator in its service position. According to the invention, the means to hold the actuator in position include a flange secured to the actuator-carrier to immobilise the actuator on the actuator-carrier in the service position.
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
73.
Device for guiding and holding a cable within a pipe
a) of the tube (12), the expandable clamp (13) being deployed so as to be blocked against the inside wall of the duct (4) in order to hold the tube (12) in the duct (4). The device serves to guide and hold the cable in the duct without damaging the duct.
The invention relates to an aircraft braking system comprising brakes with electromechanical braking actuators designed to selectively press associated stacks of disks to generate braking torque on the wheels associated to the aircraft; at least one control module receiving braking instructions and in response generating a braking command; at least one power module delivering phase currents to the actuator motors connected to the power module, in response to the braking command, so they may develop a braking force corresponding to the braking instructions. According to the invention, the control module comprises a digital processing stage and an analog processing stage.
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
Electric brake for an aircraft wheel including: - a support, made up of a torque tube and an actuator-carrier; - a stack 7 of disks, mounted around the torque tube; - electro-mechanical actuators borne by the actuator-carrier, each actuator comprising an electric motor and a plunger, the electric motor designed to move the plunger to face the stack of disks to selectively apply a braking force on the stack of disks; - the means to measure a temperature representative of the temperature in the stack of disks; characterised in that the means to measure the temperature includes at least one temperature sensor placed in the plunger of one of the electro-mechanical actuators so as to be in immediate proximity of the stack of disks when the plunger is brought into contact with the stack.
The invention relates to a steering actuator piston with a rack (6) for an aircraft landing gear (1). The piston comprises a body (18) made of light alloy having an externally threaded main section (11) ending at one end in a shoulder (12) and extended on the other end by a skirt (13), the body (18) having screwed to it a tapped bronze bushing (14) which on its external wall has at least one groove (16) to house a seal (22), the skirt having a drilling to accept a pin (15) that attaches the piston to the rack, the bushing (14) when in service extending between the shoulder and the pin (15) so that it is retained axially between the shoulder (12) and the pin (15).
The invention relates to a steering actuator piston with a rack (6) for an aircraft landing gear (1). The piston comprises a body (18) made of light alloy having an externally threaded main section (11) ending at one end in a shoulder (12) and extended on the other end by a skirt (13), the body (18) having screwed to it a tapped bronze bushing (14) which on its external wall has at least one groove (16) to house a seal (22), the skirt having a drilling to accept a pin (15) that attaches the piston to the rack, the bushing (14) when in service extending between the shoulder and the pin (15) so that it is retained axially between the shoulder (12) and the pin (15).
The invention concerns a control box to selectively deliver commands to receivers (8, 12), the box including: - a shaft (14) mounted to rotate around a rotation axis (X), while being capable of sliding along the said axis (X) between an idle position toward which it is recalled by recall means (24) and an active position; - the means for delivering commands (16, 11) cooperating with the shaft (14) to deliver commands based on an angular position of the shaft (14); - the means to drive the shaft in rotation (15); - security activation means (23) to make the shaft slide from the idle position in which anti-rotation means (27, 28) prevent the shaft from turning, to the active position in which the anti-rotation means (27, 28) allow free rotation of the shaft driven by the rotary drive means (15).
The invention concerns a ground maneuver device for an aircraft landing gear trap, including: - the means to maneuver (5, 12) the trap (4), - the means to fasten (6, 7, 10), comprising at least one unlocking actuator (8), - a control box (9) including the means to deliver orders (16) to selectively control the following sequences: - an opening sequence during which the unlocking actuator (8) is activated to deactivate the means to fasten (6, 7, 10), - a closing sequence during which the means to maneuver (5, 12) are activated to close the trap (4).
The invention concerns a direction control process for an adjustable part of an auxiliary aircraft landing gear, including the implementation of power assist to assist a direction actuator to an angular position instruction of the adjustable part, the power assist comprising an error calculation consisting in deducting a reference angle from the angular position instruction. According to the invention, the reference angle is an angle determined by calculation based on a longitudinal speed and a yaw rate of the aircraft.
The invention relates to a connection device of a geared motor to an aircraft wheel, comprising: - a casing which rotates a shaft, designed to be driven by the geared motor, the shaft having a grooved section on which a pinion is mounted to slide along a longitudinal axis of the shaft without rotation relative to the shaft; - a ring gear intended to be secured in rotation to the aircraft wheel; - the means to displace the pinion axially between a retracted position in which it is disengaged from the ring gear and an engaged position, in which the pinion meshes with the ring gear. According to the invention, the axial displacement means of the pinion comprise a hollow bolt/nut assembly extending around the shaft, one of the elements of the bolt/nut assembly being secured axially to the pinion, but prevented from turning by an anti-rotation unit, and the other element of the bolt/nut assembly being assembled to rotate in the casing, to be driven selectively by an electric motor, so that a rotation of the electric motor causes axial displacement of the pinion.
B60K 1/00 - Arrangement or mounting of electrical propulsion units
B60K 7/00 - Disposition of motor in, or adjacent to, traction wheel
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
F16H 3/30 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion without gears having orbital motion exclusively or essentially using gears that can be moved out of gear with gears shiftable only axially with driving and driven shafts not coaxial
F16H 63/04 - Final output mechanisms thereforActuating means for the final output mechanisms a single final output mechanism being moved by a single final actuating mechanism
82.
SYSTEM MANAGEMENT PROCESS FOR AIRCRAFT LANDING GEAR
The invention concerns an aircraft management process for aircraft comprising landing gear carrying a certain number of wheels that can brake, the aircraft comprising: - a manoeuvre system for landing gear comprising manoeuvre and fastening actuators for landing gear and associated traps, - a braking system comprising braking actuators for the aircraft wheels; - at least one control unit to control the movement of the landing gear and braking; - at least one maintenance housing to selectively control at least some of the actuators of the said systems while the aircraft is in off mode during maintenance operations of one or other of the systems. According to the invention, the process includes the step of activating the maintenance housing when the aircraft is in active mode to ensure that the actuators connected to the maintenance housing are activated, by means of the maintenance housing, specifically in the case of failure of the control unit.
Method for controlling an automated system (S) for applying a coating to a component (Pi), this automated system (S) comprising an articulated robot arm (1) and a spray head (T) provided with a spray nozzle (3), the method involving generating a command such: - that the spray head (T) is moved in a path (C) around a component (Pi) axis (B); and - that, along the entire path the nozzle (3) is oriented toward the component (Pi); and - that over a first portion (C1) of the path (C), a first side (K1) of the head is oriented toward a plane in which the component (Pi) is held; and - that over a second portion (C2) of the path (C1) a second side (K2) of the head (T) is oriented in the direction of said plane (P).
Aircraft landing gear strut (1) comprising a tubular part (3) to accept a shock absorber and an axle bearer part (2) situated at the end of the tubular part (3) and designed to accept a landing gear wheel support mechanism. The tubular part (3) and the axle bearer part (2) are made of metallic material different from one another, the tubular part (3) being made of a first metallic material and the axle bearer part (2) being made of a second metallic material, the tubular part (3) and the axle bearer part (2) being connected to one another by at least one weld (4).
Aircraft landing gear strut (1) comprising a tubular part (3) to accept a shock absorber and an axle bearer part (2) situated at the end of the tubular part (3) and designed to accept a landing gear wheel support mechanism. The tubular part (3) and the axle bearer part (2) are made of metallic material different from one another, the tubular part (3) being made of a first metallic material and the axle bearer part (2) being made of a second metallic material, the tubular part (3) and the axle bearer part (2) being connected to one another by at least one weld (4).
Method for controlling an automated system (S) for applying a coating to a component (Pi), this automated system (S) comprising an articulated robot arm (1) and a spray head (T) provided with a spray nozzle (3), the method involving generating a command such: - that the spray head (T) is moved in a path (C) around a component (Pi) axis (B); and - that, along the entire path the nozzle (3) is oriented toward the component (Pi); and - that over a first portion (C1) of the path (C), a first side (K1) of the head is oriented toward a plane in which the component (Pi) is held; and - that over a second portion (C2) of the path (C1) a second side (K2) of the head (T) is oriented in the direction of said plane (P).
The invention relates to an aircraft landing gear comprising a casing (401) in which a directable lower portion (402) is slidably mounted, and a directing member which is suitable for rotating the directable lower portion in response to a directing command. According to the invention, the directing device comprises an electrical motor (410) having at least one stator (411) and at least one rotor (413) which extend around the directable lower portion such that a rotational axis of the motor coincides with the swivel axis of the directable lower portion, the stator being secured to the casing and the rotor being rotatably secured to the directable lower portion.
The invention concerns an aircraft braking management process comprising at least one controllable brake to brake the aircraft when the aircraft is on the ground based on a braking instruction, characterised in that the process comprises a correction for the braking instruction based on a pitch angle of the aircraft during braking.
B60T 8/1755 - Brake regulation specially adapted to control the stability of the vehicle, e.g. taking into account yaw rate or transverse acceleration in a curve
B60T 8/24 - 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 vehicle inclination or change of direction, e.g. negotiating bends
The invention concerns a recalibration process for an aircraft landing gear comprising a housing in which an adjustable lower part is mounted to slide to counter a suspension force generated by a shock absorber, the landing gear being equipped with a controllable direction unit to pivot the adjustable lower part in response to an angular position instruction, the landing gear comprising in addition at least one angular position sensor designed to generate an electrical signal representing the angular position of the adjustable lower part which can be operated to control the direction unit; the process includes a stage to recalibrate the sensor's electrical signal to a specific calibration value when the adjustable lower part is in an indexed angular position while the aircraft is in flight and the landing gear is completely released.
The invention is relative to a process to activate landing gear fastening boxes and associated landing gear trap boxes in emergency mode in an aircraft, the fastening boxes comprising at least one supply port as well as at least one unlocking element operable when the port is supplied in pressurised fluid, the aircraft in addition featuring a hydraulic braking circuit. According to the invention, the process includes the installation of at least one deviation associated to an isolation valve onto the aircrafts braking circuit, kept in normal mode in a state of isolation and controllable to be placed in an open state in which at least some of the supply ports of the fastening boxes are supplied by the deviation in the braking circuit.
The invention relates to a method for measuring the thickness of a coating layer (Rev) of a part (P) that is formed on a substrate (Sub) of said part. The method comprises: supplying power to an induction means (Mind) using an AC electrical signal (S) in order to induce a magnetic field in the part (P); measuring at least one physical characteristic (Zn) that changes on the basis of the magnetic field (B) induced in the part (P); determining a first and second value of an indicator, which are determined from measurements of said physical characteristic that is produced when the electrical signal has first and second given frequencies, respectively; and then calculating the difference between the first and second value of the indicator, and determining the thickness (er) of the coating layer in accordance with said difference and with predetermined data that correlate the difference between values of the indicator with corresponding values of the thicknesses of the coating layer.
G01B 7/06 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring length, width, or thickness for measuring thickness
92.
METHOD FOR MEASURING THE THICKNESS OF A COATING LAYER BY INDUCING MAGNETIC FIELDS
The invention relates to a method for measuring the thickness of a coating layer (Rev) of a part (P) that is formed on a substrate (Sub) of said part. The method comprises: supplying power to an induction means (Mind) using an AC electrical signal (S) in order to induce a magnetic field in the part (P); measuring at least one physical characteristic (Zn) that changes on the basis of the magnetic field (B) induced in the part (P); determining a first and second value of an indicator, which are determined from measurements of said physical characteristic that is produced when the electrical signal has first and second given frequencies, respectively; and then calculating the difference between the first and second value of the indicator, and determining the thickness (er) of the coating layer in accordance with said difference and with predetermined data that correlate the difference between values of the indicator with corresponding values of the thicknesses of the coating layer.
G01B 7/06 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring length, width, or thickness for measuring thickness
93.
CONNECTION DEVICE FOR A MOTOR REDUCTION UNIT OF AN AIRCRAFT WHEEL, ALLOWING FOR SELECTIVE DRIVE BY THE MOTOR REDUCTION UNIT
The invention is relative to a connection device for a motor reduction unit of an aircraft wheel, comprising a casing causing the rotation of a shaft, designed to be driven by the motor reduction unit and upon which an idler gear is mounted by means of ball bearings; a sprocket intended to be secured in rotation to the aircraft wheel and arranged to be permanently engaged with the idler gear; and the means to secure the idler gear to the shaft in selective rotation. According to the invention, a smooth bearing is interposed between the shaft and the ball bearing of the idler gear.
The invention concerns a ground manoeuver device for a landing gear trap on an aircraft, the trap associated to the means to manoeuver the trap and the means to fasten the trap so that the trap is locked when it comes to a closed position, at least one electromechanical unlocking actuator arranged to act on the fastening means in order to deactivate them when the trap opens inflight. According to the invention, the device comprises control means, operable by an operator on the ground to control at least: - one opening sequence during which the electromechanical unlocking actuator is activated to deactivate the fastening means, - a closing sequence during which the means to manoeuver are activated to close the trap.
The invention relates to a device for coupling an actuator for controlling the landing gear of an aircraft to an aircraft structure, comprising: a lever (10;110) having a first end (10a;110a) to be pivotably connected onto the structure of the aircraft and a second end (10b;110b) onto which the actuator is pivotably connected; preloading means (11,12;112,122,123) engaging with the lever so as to return the latter toward a stable rest position which is occupied by the lever in the absence of a force passing through the actuator; and an abutment means (13;113) for defining at least one work position of the lever when the actuator is actuated.
The invention relates to a device for coupling an actuator for controlling the landing gear of an aircraft to an aircraft structure, comprising: a lever (10;110) having a first end (10a;110a) to be pivotably connected onto the structure of the aircraft and a second end (10b;110b) onto which the actuator is pivotably connected; preloading means (11,12;112,122,123) engaging with the lever so as to return the latter toward a stable rest position which is occupied by the lever in the absence of a force passing through the actuator; and an abutment means (13;113) for defining at least one work position of the lever when the actuator is actuated.
The invention relates to an anti-lofting deflector for landing gear bearing two wheels on an axle, and comprising: - a fixed support (5) intended in service to be fixed on a part of the landing gear bearing the axle so that it extends between the wheels and has a distal end behind the wheels; - a first flap (2) articulated to the support at the distal end thereof about a first axis of articulation (X1) substantially parallel to the axis; - a second flap (3) articulated to the first flap about a second axis of articulation (X2) substantially parallel to the first axis of articulation; a return member (11) positioned in such a way as to return the second flap against an end stop of the first flap preventing the second flap from aligning with the first flap, and as to return the first flap against an end stop of the fixed support preventing the first flap from folding against the support.
The invention relates to a method for manufacturing a rocker arm for the landing gear of an aircraft, including a body that is provided with a double yoke (24) comprising two flanges (19, 21) arranged parallel to a radial direction with respect to the body, comprising the steps of: forming a first mandrel; applying one or more first layers of braided fibers (11) onto the first mandrel; mounting, onto the thus-formed assembly a second mandrel element extending between the two flanges (19, 21) of the yoke (24) to be formed; applying one or more second layers of braided fibers (17) onto the thus-formed assembly; injecting a resin into the various layers (11, 17) and polymerizing said resin; and machining the thus-formed unfinished part, so as to form a notch that passes through the second braided layers (17) in order to separate the two flanges (19, 21) of the double yoke (24) from one another.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/24 - 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 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
The invention relates to a method for manufacturing a rocker arm for the landing gear of an aircraft, including a body that is provided with a double yoke (24) comprising two flanges (19, 21) arranged parallel to a radial direction with respect to the body, comprising the steps of: forming a first mandrel; applying one or more first layers of braided fibers (11) onto the first mandrel; mounting, onto the thus-formed assembly a second mandrel element extending between the two flanges (19, 21) of the yoke (24) to be formed; applying one or more second layers of braided fibers (17) onto the thus-formed assembly; injecting a resin into the various layers (11, 17) and polymerizing said resin; and machining the thus-formed unfinished part, so as to form a notch that passes through the second braided layers (17) in order to separate the two flanges (19, 21) of the double yoke (24) from one another.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/24 - 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 70/54 - Component parts, details or accessoriesAuxiliary operations
F16C 7/00 - Connecting-rods or like links pivoted at both endsConstruction of connecting-rod heads
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
F16C 7/02 - Constructions of connecting-rods with constant length
100.
PROCESS FOR MANUFACTURING A COMPOSITE, GENERALLY TRIANGULAR, STRUCTURAL PART
The invention relates to a process for manufacturing a composite element (25) comprising three arms (22, 23, 24) arranged in a triangle, comprising the operations of: manufacturing a woven three-dimensional preform of reinforcing fibres comprising through-slots delimiting two arms (22, 23) and two half-arms completely parallel and contiguous in pairs, each arm (22, 23) having one end via which it is connected to a half-arm and another end via which it is connected to the other arm (22, 23); shaping the preform by opening it out and by joining the two half-arms thereof together in order to configure it into a triangle; firmly attaching the half-arms to one another by stitching of reinforcing fibres; injecting the resin into this preform and polymerizing it.
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]
