Device for axially locking a first tubular element fitting tightly into a second tubular element

Abstract

The invention relates to a device (100) for axially locking a first tubular element (20) fitting tightly into a second tubular element (E), the locking device comprising a tubular body (101) including an outer annular groove (101.2) in which a ring (102) is slidably mounted along a longitudinal axis (Y101) of the body between a locked position and a released position, the ring comprising a wheel (102.1) having a front face from which elastically deformable outer hooking claws (102.2) extend projecting axially between a state in which they project radially from the body and a state in which they are retracted into the body, and the groove in the body comprising a bottom (101.7) shaped to keep the claws in their projecting state when the ring is in the locked position, and to allow the claws to transition from the projecting state to the retracted state when the ring is in the released position.

Description

[0001]AXIAL LOCKING DEVICE FOR A FIRST TUBULAR ELEMENT RECEIVED FOR FITTING IN A SECOND TUBULAR ELEMENT Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies both to new types of aircraft and those currently in circulation, requiring the implementation of technological solutions to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change. Technological research efforts have already led to very significant improvements in the environmental performance of aircraft.All stakeholders in the sector are constantly working to improve energy efficiency. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental impacts with the aim of improving the energy efficiency of air transport. Consequently, the Applicant is constantly working to reduce its climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible to reduce the environmental footprint of its activity.This sustained research and development work relates to new generations of aircraft engines, the lightening of aircraft, in particular through the materials used and the lightened on-board equipment, the development of the use of electrical technologies to ensure propulsion, and, essential complements to technological progress, aeronautical biofuels. To this end, the invention is the result of technological research aimed at very significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft. For this purpose, the present invention relates to the field of mechanical assemblies and in particular to a device for axial locking of a first tubular element received for adjustment in a second tubular element, and in particular a member for driving in rotation an aircraft wheel received for adjustment in a landing gear axle.The invention also relates to a member for rotating an aircraft wheel equipped with such a locking device, to a wheel equipped with such a driving member, to a landing gear equipped with such a wheel, and to an aircraft equipped with such a landing gear. BACKGROUND OF THE INVENTION In the field of aviation, it is now planned to equip aircraft with members for rotating the wheels to allow the aircraft to move on the ground without using its powertrains. A driving member mounted on a landing gear is described in document FR-A-3024706. This driving member comprises an electric motor mounted at one end of an axle carrying the wheels of the landing gear to transmit a rotational torque to one of said wheels via a connecting interface.The mounting of the electric motor, in particular the connection of the motor casing to the axle, and the supply of electrical energy to the motor are relatively complex in practice. The mounting means must be compact and the supply means are very exposed. Indeed, the electric motor is installed in a very congested area of ​​the landing gear and subject to external aggressions. OBJECT OF THE INVENTION The invention therefore aims to propose a device allowing axial locking of two tubes in one another which is relatively compact and little exposed to external aggressions. SUMMARY OF THE INVENTION To this end, the invention proposes a device for axial locking of a first tubular element received in adjustment in a second tubular element.The locking device comprises a tubular body having an external annular groove in which a ring is slidably mounted along a longitudinal axis of the body between a locking position and a release position, the ring comprising a crown having a front face from which elastically deformable external hooking claws extend axially between a state projecting radially from the body and a state retracted towards the inside of the body, and the groove of the body comprising a bottom shaped to maintain the claws in their projecting state when the ring is in the locking position, and to allow the claws to pass from the projecting state to the retracted state when the ring is in the release position. According to a particular characteristic, the ring is returned to the locking position by a first spring.According to another particular characteristic, the body comprises at least one cable passage conduit opening onto a front face of the body. In particular, the cable passage conduit comprises at least one longitudinal slot opening onto the front face of the body, forming a notch. In particular, the cable passage conduit comprises a hole formed in the front face of the body. The invention also relates to a member for driving in rotation a wheel arranged to be pivotally mounted on an aircraft landing gear shaft about an axis, the drive member comprising a tubular element intended to be received in a fit manner in the axle, and such a locking device.The body of the locking device is mounted to move in translation along the axis in the tubular element between a retracted position in which the ring is in the locking position and a free end of the claws extends through an opening of the tubular element, projecting from an external surface of said tubular element, and an advanced position in which the ring is in the release position and the claws are in the retracted state, the free end of the claws bearing against an internal surface of the tubular element. In particular, the body of the locking device is returned to the retracted position by at least one second spring. The invention also relates to a wheel pivotally mounted on a shaft of an aircraft landing gear, the wheel being equipped with such a drive member. The invention also relates to an aircraft landing gear comprising an axle on which such a wheel is rotatably mounted.The axle comprises an internal annular groove arranged to receive and cooperate with the free end of the claws of the locking device when the drive member is in the connected position in the axle and the body of said locking device in the retracted position. The invention further relates to an aircraft comprising at least one such landing gear. BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood in the light of the following description, which is purely illustrative and non-limiting, and must be read in conjunction with the appended drawings, among which: [Fig. 1] Figure 1 is a simplified representation of an aircraft comprising main landing gears comprising wheels provided with a rotational drive member according to the invention; [Fig. 2] Figure 2 is a front view of one of the main landing gears of the aircraft illustrated in Figure 1; [Fig.3] Figure 3 is a perspective view of the axle and the drive member equipping the main landing gear illustrated in Figure 2; [Fig. 4] Figure 4 is an axial sectional view of the locking device, according to a particular embodiment of the invention, equipping the drive member illustrated in Figure 3; [Fig. 5] Figure 5 is a perspective view of the locking device illustrated in Figure 4; [Fig. 6A] Figure 6A is a sectional view of the locking device illustrated in Figure 5, in use; [Fig. 6B] Figure 6B is a view identical to Figure 6A, in which the locking device is inactive. DETAILED DESCRIPTION OF THE INVENTION The invention is described here in application to an aircraft wheel but other applications are of course conceivable.An aircraft A comprises, as illustrated in Figure 1, two main landing gears P each comprising a leg J ​​having a first end articulated on a structure S of the aircraft A and, opposite, a second end carrying wheels R, RM rotating about an axis Y on a tubular shaft or axle E. The leg J ​​is movable between a retracted position (not shown) and a deployed position illustrated here. Each of the wheels R, RM comprises a rim receiving a tire and is equipped with a brake. The rim is connected by a web to a hub mounted to rotate on the axle E about the axis Y. In a manner known per se, the brake comprises a stack of disks received in an annular space delimited by the rim and the hub. The stack of disks comprises alternating stator disks fixed in rotation relative to the axle E and rotor disks fixed in rotation relative to the rim.Hydraulic or electromechanical actuators are arranged on an actuator-carrying ring to exert a pressing force on the stack of discs. Each braking action performed by the pilot of aircraft A causes an increase in temperature of the brake discs and their immediate surroundings, requiring the provision of heat shields not detailed here. The brake is known in itself and will not be detailed further here. With reference to Figure 2, the leg J ​​is held in the deployed position by means of a bracing member comprising a first connecting rod B1 articulated on the structure S of aircraft A and a second connecting rod B2 articulated on the leg J ​​and on the first connecting rod B1. The first connecting rod B1 and the second connecting rod B2 are, in the deployed position, in a substantially aligned position.The leg J ​​comprises a box C articulated on the structure S of the aircraft A, and a rod T slidably mounted in the box C along an axis Z to form a shock absorber. The rod T carries at a lower end the axle E pivotally receiving the wheels R, RM. In a manner known per se, a main compass and a secondary compass (not shown here) allow the sliding of the rod T in the box C, while preventing the pivoting of the rod T around the axis Z, relative to the box C. The axle E is integral with the rod T so that said axle E is immobile with respect to said rod T. The axis Z is here substantially perpendicular to the axis Y. The landing gear will not be detailed further here. The RM wheels are said to be "motorized", that is to say equipped with a drive member 1 intended to move the aircraft A without using the main powertrains of the aircraft when it is on the ground.The following description relates to one of the motorized RM wheels, but all the motorized RM wheels of the aircraft A are identical here. With reference to Figure 3, the drive member 1 comprises a first element 10 of generally cylindrical shape and a second tubular element 20 extending coaxially projecting from the first element 10. The first element 10 and the second element 20 respectively constitute a motorization zone of the RM wheel and a zone of engagement of the drive member 1 in the axle E. The first element 10 comprises an electric motor 11 mounted at a free end of the axle E which is bordered by axial projections forming dog teeth E1 (Figure 3). The motor 11 comprises a stator 11.1 (visible in Figure 4) carrying electromagnetic coils on its periphery. The stator 11.1 is coupled to the axle E by the engagement of the dog teeth E1 of said axle E in housings provided in said stator 11.1, so that the stator 11.1 is, along the Y axis, rotationally connected to the axle E. The motor 11 also comprises a rotor mounted to rotate on the stator 11.1, here by means of bearings. The rotor comprises a drum carrying permanent magnets. The circulation, in the coils of the stator 11.1, of a current, adapted to create a rotating magnetic field, induces on the drum a mechanical torque driving said drum in rotation. When the drive member 1 is in position on the axle E, the axis of rotation of the rotor coincides with the Y axis of rotation of the wheel RM. The drum carries a plurality of tie rods 12 which extend parallel to the axis of rotation of the rotor. An interface member (not shown) extends between the tie rods 12 and the rim of the wheel RM to rotationally connect the drum of the rotor and the rim so as to transmit the torque of said rotor to said wheel RM.The first element 10 also comprises an electric fan 13 mounted on the motor 11 to create an air flow around the brake discs and around the motor 11 so as to accelerate the cooling of said brake discs and said motor 11 as well as their immediate surroundings. The second element 20 is integral with the stator 11.1 and is received in a fit in the axle E, said second element 20 extending here coaxially with respect to said axle E. A free end of the second element 20 carries a male electrical coupler 21 opening into a central orifice E2 formed in the axle E at the junction between the rod T and said axle E. The orifice E2 extends along an axis X perpendicular to the axis Y and to the axis Z and receives a female electrical coupler 30 adapted to receive the male electrical coupler 21 carried by the second element 20 of the drive member 1.A guidance system (not shown here) is provided on the female coupler 30 and on the second element 20 to ensure the correct alignment of the male coupler 21 and the female coupler 30 before their connection. An angular keying system (not shown here) is also provided on the female coupler 30 and on the second element 20 to ensure the correct angular orientation of the male coupler 21 and the female coupler 30 before their connection. The keying system can also be provided on the axle E.Electrical harnesses (or harnesses) supply current to the motor of the drive member 1 and the brake cooling fan 13, and send back signals from various sensors equipping the drive member 1 and / or landing gear management signals equipping the wheel RM, such as the rotation speed of the wheel RM, the tire pressure, the temperature of the brake discs, etc. These electrical harnesses comprise first electrical harnesses, not shown here, extending inside the second element 20 from the male coupler 21 into the cylindrical body 10, and second electrical harnesses 31, 32, 33 extending from the female coupler 30 and traveling along the main compass and the secondary compass to rise along the rod T to the structure S of the aircraft A. The second harnesses 31, 32, 33 are connected, via the male coupler 21, to the first beams.With reference to Figure 4, the second element 20 is equipped with an axial locking device 100 for locking the drive member 1 in a connected position in which the male coupler 21 is received in the female coupler 30. As illustrated in Figure 5, the locking device 100 comprises a tubular body 101 having a first end provided with a radially externally projecting collar 101.1, and a second end, opposite the first end, provided with an external annular groove 101.2 inside which a locking ring 102 is mounted movable in translation along a longitudinal axis Y101 of the body 101, between a release position (Figure 6B) and a locking position (illustrated in Figures 5 and 6A). The ring 102 is returned to the locking position by a first corrugated compression spring 103 extending in the groove 101.2, between the ring 102 and a side wall of said groove 101.2.As can be seen in Figure 4, the body 101 is here made in three parts 101a, 101b, 101c connected together by screws 101d. The body 101 comprises three longitudinal slots 101.3 symmetrically distributed around the axis Y101. The slots 101.3 extend parallel to the axis Y101 from the collar 101.1 to the second end and open onto a front face 101.4 of said second end, forming peripheral notches 101.5 which define first passages P1 for electrical harnesses. The slots 101.3 delimit three branches 101.6 connecting the collar 101.1 to the front face 101.4 which comprises a central hole 101.8 defining a second passage P2 for electrical harnesses. The ring 102 has a central axis substantially coincident with the longitudinal axis Y101 of the body 101, and comprises an annular crown 102.1 and three series of six identical blades 102.2 extending axially from a front face of the crown 102.1.The series of blades 102.2 are equally distributed around the axis Y101 and extend between the slots 101.3. The blades 102.2 have a free end comprising a relief 102.3 projecting radially towards the outside of the body, and are elastically deformable between a rest state (figure 6A) and a deformed state towards the inside of the body 101 (figure 6B) to form hooking claws. These hooking claws are said to be floating in that they are axially movable relative to the body 101. The groove 101.2 in which the ring 102 slides comprises a bottom 101.7 shaped to hold the blades 102.2 in their rest state when the ring 102 is in the locking position, and to allow the blades 102.2 to pass from the rest state to the deformed state when the ring 102 is in the release position. The locking device 100 is received in a fit manner in the second element 20 of the drive member 1.The body 101 of the locking device 100 is mounted to move in translation, along the Y axis, in the second element 20 between a retracted position in which the ring 102 is in the locking position and the reliefs 102.3 of the blades 102.2 extend through an opening 25 of the second element 20, projecting from an external surface of the second element 20 (figure 6A), and an advanced position in which the ring 102 is in the release position and the blades 102.2 are in a deformed state, the reliefs 102.3 of said blades bearing against an internal surface of the second element 20 (figure 6B). As illustrated in Figure 4, the body 101 is returned to the retracted position by second helical springs 104 symmetrically and equally distributed around the axis Y101, the second springs 104 having a first end bearing against the collar 101.1 and a second end, opposite the first end, bearing against the first element 10.The axle E comprises an internal annular groove E3 arranged to be substantially opposite the openings 25 of the second element 20 and to receive the reliefs 102.3 of the blades 102.2 of the locking device 100 when the drive member 1 is in the connected position and the body 101 of said locking device 100 in the retracted position, said reliefs 102.3 cooperating with a side wall E4 of the groove E3 under the action of the second springs 104. The assembly sequence of the drive member 1 in the axle E will now be detailed. After having checked the absence of electric current in the female coupler 30 housed in the axle E, a tool is positioned on the drive member 1 to take up its mass during its insertion into the axle E. The cooling fan 13 is then removed from the motor 11 so as to be able to access the locking device 100 and to exert on the collar 101.1 an axial thrust force bringing the body 101 from the retracted position to the advanced position, which causes the blades 102.2 to retract inside the second element 20. The reliefs 102.3 of the blades 102.2 then do not oppose the insertion of the second element 20 of the drive member 1 into the axle E. The second element 20 is then inserted into the axle E until the drive member 1 is brought into the connected position in which the male coupler 21 is received in the female coupler 30. By ceasing to exert the thrust force, the body 101 of the locking device 100 tends to return, under the action of the second springs 104, to its retracted position. The blades 102.2 then slide inside the body 101 until they return to their rest state in which the reliefs 102.3 of the blades 102.2 extend through the openings 25 of the second element 20 and are received in the groove E3 formed in the axle E.By continuing their return action, the second springs 104 tend to make the reliefs 102.3 cooperate with the side wall E4 of the groove E3 and then to exert on the stator 11.1 of the motor 11 an axial thrust force causing said stator 11.1 to be pressed against the dog teeth E1. The fan 13 can then be reassembled on the motor 11. The disassembly of the drive member 1 is carried out in the reverse direction of the assembly. Such a locking device 100 makes it possible in particular to: - axially hold the drive member 1 in the connected position; - transmit the torque delivered by the motor 11 to the wheel RM by the engagement of the dog teeth E1 of the axle E in the housings provided in the stator 11.1 of said motor 11; - keep the stator 11.1 of the motor 11 pressed against the dog teeth E1 of the axle E; - form a secure conduit for passing cables (electrical, hydraulic, etc.)), mechanical elements (connecting rod, lever, fixing, etc.), equipment (fan mounted in the axle, etc.); and - to ensure rapid and secure assembly / disassembly of the drive member 1, which facilitates maintenance operations. Each of the branches 101.6 of the body 101 is sized to withstand without failure the breakage of one of the other branches 101.6 and to guarantee the detection of said breakage during a scheduled inspection before a new breakage. The locking device 100 is thus designed according to the "fail-safe" principle. Of course, the invention is not limited to the embodiment described but encompasses any variant falling within the scope of the invention as defined by the claims. The number of parts constituting the body 101 of the locking device 100 may be less than or greater than three. The number of branches 101.6 constituting the body 101 of the locking device 100 may be less than or greater than three.The number of blades 102.2 may be different from that of the locking device 100 described. Although the return of the body 101 to the retracted position is here provided by second helical springs 104, it may also be provided by any elastic return means (wave springs, elastically deformable washers, etc.). The movement of the body 101 between the advanced position and the retracted position may also be provided by at least one actuator (screw, hydraulic cylinder, electric cylinder, etc.). Although the return of the ring 102 to the locking position is here provided by a first wave spring 103, it may also be provided by any elastic return means (helical spring, elastically deformable washers, etc.). The first wave spring 103 is optional. Although the motor 11 is here electric, it may be hydraulic.The first bundles are then formed of rigid pipes of pressurized hydraulic fluid intended for the motor 11, and the end of the second tubular element 20 carries a hydraulic coupler. Although here the end of the tubular element 20 of the drive member 1 carries a male coupler 21, it can on the contrary carry a female coupler adapted to receive a male coupler inserted into the axle E via the orifice E2 after insertion of the drive member 1 into said axle E. The dog teeth E1 bordering the free end of the axle E can be replaced by any mechanical means allowing said axle E to be coupled to the stator of the motor 11 (splines, key, etc.).

Claims

CLAIMS 1. Axial locking device (100) for a first tubular element (20) received for adjustment in a second tubular element (E), the locking device comprising a tubular body (101) having an external annular groove (101.2) in which a ring (102) is slidably mounted along a longitudinal axis (Y 101) of the body between a locking position and a release position, the ring comprising a crown (102.1) having a front face from which elastically deformable external hooking claws (102.2) project axially between a state projecting radially from the body and a state retracted towards the inside of the body, and the groove of the body comprising a bottom (101.7) shaped to maintain the claws in their projecting state when the ring is in the locking position, and to allow the claws to pass from the projecting state to the retracted state when the ring is in the release position.

2. Locking device (100) according to claim 1, in which the ring (102) is returned to the locking position by a first spring (103). 3.Locking device (100) according to any one of the preceding claims, wherein the body (101) comprises at least one cable passage conduit (P1, P2) opening onto a front face (101.4) of the body.

4. Locking device (100) according to claim 3, wherein the cable passage conduit (P1) comprises at least one slot (101.3). longitudinal opening onto the front face (101.4) of the body (101) forming a notch (101.5).

5. Locking device (100) according to claim 3, in which the cable passage conduit (P2) comprises a hole (101.8) formed in the front face (101.4) of the body (101).

6. A drive member (1) for rotating a wheel (RM) arranged to be pivotally mounted on an axle (E) of an aircraft landing gear about an axis (Y), the drive member comprising a tubular element (20) intended to be received for adjustment in the axle, and a locking device (100) according to any one of the preceding claims, the body (101) of the locking device being mounted movable in translation along the axis (Y) in the tubular element (20) between a retracted position in which the ring (102) is in the locking position and a free end (102.3) of the claws (102.2) extends through an opening (25) of the tubular element, projecting from an external surface of said tubular element, and an advanced position in which the ring (102) is in the released position and the claws (102.2) are in the retracted state, the free end of the claws bearing against an internal surface of the tubular element.

7. Drive member (1) according to claim 6, in which the body (101) of the locking device (100) is returned to the retracted position by at least one second spring (104).

8. Wheel (R. M ) pivotally mounted on a shaft (E) of an aircraft landing gear (P), the wheel being equipped with a drive member (1) according to claim 6 or 7.

9. Aircraft landing gear (P) comprising an axle (E) on which a wheel (RM) according to claim 8 is rotatably mounted, the axle (E) comprising an internal annular groove (E3) arranged to receive and cooperate with the free end (102.3) of the claws (102.2) of the locking device (100) when the drive member (1) is in the connected position in the axle (E) and the body (101) of said locking device (100) in the retracted position.

10. Aircraft (A) comprising at least one landing gear (P) according to claim 9.

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