Wheel and brake assembly for aircraft, and landing gear comprising such an assembly

Abstract

An aircraft wheel and brake assembly (50), comprising a wheel (10) equipped with a brake (20), the wheel (10) comprising a rim (12) and at least one web (14), the rim (12) having an axis of rotation (X) defining an axial direction, a first axial end (12A) and a second axial end (12B), the web (14) extending radially inward from the rim (12), at a distance from the first axial end (12A) and the second axial end (12B), the brake (20) comprising a plurality of discs (22) arranged on a first side (C1) of the web (14) and a plurality of actuators (24) configured to axially press the discs (22) together, the plurality of actuators (24) being arranged in whole or in part on a second side (C2) of the web (14), the second side (C2) of the web (14) being axially opposite the first side (C1) of the veil (14). Figure for the abstract: Fig. 2.

Description

Title of the invention: Wheel and brake assembly for aircraft, and landing gear comprising such an assembly Technical field

[0001] The present disclosure relates to a wheel and brake assembly for an aircraft, and to a landing gear comprising such an assembly.

[0002] By aircraft we mean any flying machine, for example an airplane, a drone or a helicopter. Prior art

[0003] The architecture of known landing gear brakes generally comprises a ring of actuators coupled to a fixed part relative to the wheel and cooperates with a plurality of discs directly accessible by the ring of actuators. The ring is generally arranged on an outer side of the wheel and projects axially from the wheel itself, while the discs are arranged between the wheel and the ring of actuators. However, these known brakes induce a certain space constraint within the aircraft when the landing gear is retracted into the fuselage. In particular, the space requirement of the brakes is one of the reasons why aircraft, and in particular airplanes, have a belly, which is a widened part on the lower part of the fuselage, generally for airplanes at the connection between the wings and the fuselage.Such a belly penalizes the aerodynamic efficiency of the aircraft, and induces aerodynamic drag which affects fuel consumption. There is therefore a need for a more compact aircraft landing gear brake. Statement of the invention

[0004] One embodiment relates to a wheel and brake assembly for an aircraft, comprising an aircraft wheel equipped with a brake, the aircraft wheel comprising a rim and at least one web, the rim being configured to receive a tire and having an axis of rotation defining an axial direction, a first axial end and a second axial end opposite the first axial end in the axial direction, the web extending radially inward from the rim, the web being arranged axially at a distance from the first axial end of the rim and at a distance from the second axial end of the rim, the brake comprising a plurality of discs arranged on a first side of the web and a plurality of actuators configured to axially press the discs of the plurality of discs together, the plurality of actuators being arranged in whole or in part on a second side of the web,the second side of the veil being axially opposite to the first side of the veil relative to the veil.

[0005] Hereinafter and unless otherwise indicated, “assembly” means “wheel and brake assembly for aircraft”.

[0006] Within the assembly, the brake is mounted on the wheel. The brake comprises one or more parts coupled directly or indirectly to the wheel, these parts sometimes being called moving parts or rotating parts or rotor parts. The brake comprises one or more parts configured to be coupled directly or indirectly to a fixed element, for example an axle or a leg of a landing gear, these parts sometimes being called fixed parts or stator parts. For example, the plurality of discs may comprise at least one rotor disc and at least one stator disc, the stator discs alternating with the rotor discs in the axial direction, the plurality of actuators being configured to axially press the rotor discs and the stator discs together so as to exert the friction necessary for braking in order to brake and / or block the rotation of the wheel during the landing of the aircraft equipped with such an assembly.

[0007] For example, the brake may comprise a single plurality of actuators configured to axially press the discs together. In other words, the brake may not comprise any other actuator for pressing the discs than the actuators of the plurality of actuators. For example, the actuators of the plurality of actuators may each be electric, i.e. configured to be actuated by electrical energy. Electric actuators may be well suited to the structure of the brake according to the present disclosure.

[0008] Hereinafter and unless otherwise indicated, by "the actuators" is meant "the actuators of the plurality of actuators". Hereinafter and unless otherwise indicated, by "the discs" is meant "the discs of the plurality of discs".

[0009] The actuators may be coupled to the wheel, for example mounted on the web and / or on the rim. The actuators may extend axially through the web. For example, the actuators may extend on the second side and the first side of the web.

[0010] Each of the actuators may comprise a fixed portion and a movable portion that is movable relative to the fixed portion of the actuator. The movable portion may be axially movable, and cooperate with the plurality of discs, for example with one disc of the plurality of discs, in order to axially press all of the discs of the plurality of discs against each other.

[0011] Such a configuration of the brake within the wheel can make it possible to optimize the space occupied by the brake within the wheel, and to avoid, or at least to limit, any axial bulk of the brake outside the bulk of the wheel, beyond the first and / or second axial end of the rim. Such a brake can therefore be relatively more compact than the brakes known from the state of the art. Moreover, such a brake structure can make it possible to dispense with certain elements present in the brakes known from the state of the art, such as for example the crown carrying the actuators, so that the overall mass of the brake according to the present disclosure can be reduced compared to these known brakes.

[0012] In some embodiments, the brake may include an axial stop secured to the rim, the plurality of discs being disposed axially between the plurality of actuators and the axial stop.

[0013] In other words, the discs are axially sandwiched between the axial stop and the actuators. The axial stop serves to absorb the axial compression forces exerted by the actuators on the discs. Such a configuration can make it possible to optimize the space occupied by the brake within the wheel, and can contribute to the compactness of the brake.

[0014] In some embodiments, the axial stop may have a plurality of projections, each projection of the plurality of projections extending radially inwardly from the rim, the projections of the plurality of projections being regularly distributed about the axis.

[0015] Such projections can make it possible to optimize the surface area of ​​cooperation between the discs and the stop while allowing a maximum of free space on the one hand for ventilation and cooling of the brake and on the other hand for reducing the mass of the brake. Such a stop can contribute to optimizing the space occupied by the brake within the wheel, and to the compactness of the brake.

[0016] In some embodiments, each of the plurality of actuators may axially traverse the web and have a piston cooperating with a disc of the plurality of discs.

[0017] Such a configuration can make it possible to optimize the space occupied by the brake within the wheel, and can contribute to the compactness of the brake.

[0018] In some embodiments, the veil may be openwork.

[0019] In other words, the web may include through holes, or openings, connecting the two sides of the web. Such openings can, on the one hand, optimize the mass of the wheel, and on the other hand, optimize the ventilation and cooling of the brake. This can contribute to optimizing the space occupied by the brake within the wheel, and to the compactness of the brake.

[0020] In some embodiments, each of the plurality of actuators may be electrical, the brake comprising a rotating electrical connection configured to be electrically connected to a fixed portion of an aircraft landing gear, for example a wheel axle or a landing gear leg, the fixed portion being fixed relative to the wheel.

[0021] For example, the rotating electrical connection may be a connection of the type brush. For example, an electrical bridge can electrically connect each of the actuators to a central ring or cylinder mechanically coupled to the wheel while the central cylinder is electrically connected, for example via a brush, to the fixed part of the landing gear. Such a configuration can be particularly reliable and can optimize the space occupied by the brake within the wheel, and the compactness of the brake.

[0022] In some embodiments, the plurality of disks may comprise at least two disks, for example at least three disks.

[0023] For example, if the number of disks is even and has the same number of rotor disks as stator disks, the actuators can cooperate with a rotor disk while the possible axial stop can cooperate with a stator disk. For example, if the number of disks is odd and has an additional rotor disk compared to the number of stator disks, the actuators can cooperate with a rotor disk while the possible axial stop can cooperate with a rotor disk.

[0024] Such a number of discs can make it possible to optimize the braking efficiency of the brake while preserving the space occupied within the wheel and the compactness of the brake.

[0025] In some embodiments, the brake may be fully housed within the wheel.

[0026] It is understood that in this case, the brake does not protrude axially outside the rim, i.e. does not extend axially from the web beyond the first axial end and beyond the second axial end of the rim. In other words, the brake extends axially from the first side of the web, from the web, at most to the first axial end of the rim, and from the second side of the web, from the web, at most to the second axial end of the rim.

[0027] This ensures that the brake is particularly compact. The axial size of the landing gear on which such an assembly is mounted will be imposed by the size of the tire mounted on the rim, the tire generally being wider in the axial direction than the rim.

[0028] In certain embodiments, the wheel may comprise a first cavity delimited axially by the first axial end of the rim and by the web, and a second cavity delimited axially by the second axial end of the rim and by the web, the plurality of discs being arranged, for example strictly arranged, within the first cavity, the plurality of actuators being arranged, for example strictly arranged, within the first cavity and the second cavity.

[0029] By "strictly arranged" is meant that the element in question extends axially at most, from the web, to the axial end of the rim delimiting the cavity.

[0030] Such a configuration can make it possible to reduce the size of the brake within the wheel, and to optimize the compactness of the brake.

[0031] One embodiment relates to a landing gear comprising a landing gear leg, a wheel axle mounted on the landing gear leg and an aircraft wheel and brake assembly according to any of the embodiments described herein mounted on the wheel axle, the plurality of discs being disposed relative to the web on the landing gear leg side.

[0032] The leg of a landing gear is the part that connects the axle carrying the wheel to the aircraft. The axle can extend perpendicular to the leg. By arranging the discs on the side of the leg, the actuators are arranged at least partly on the other side of the discs relative to the web and are freely accessible. In other words, the leg does not prevent access to the actuators. This makes it easier to inspect and maintain the actuators, without having to remove the wheel. Brief description of the drawings

[0033] The object of the present disclosure and its advantages will be better understood upon reading the detailed description given below of different embodiments given as non-limiting examples. This description refers to the appended pages of figures, in which:

[0034] [Fig.l] [Fig.l] represents an aircraft equipped with landing gear,

[0035] [Fig.2] [Fig.2] shows a detailed view of a landing gear of the aircraft of [Fig.l],

[0036] [Fig.3] [Fig.3] represents a view according to arrow III of [Fig.2], of the stop axial,

[0037] [Fig.4] [Fig.4] represents a view according to arrow III of [Fig.2], of the stop axial equipped with a heat shield,

[0038] [Fig.5] [Fig.5] represents a view along arrow V of [Fig.2], of the assembly wheel and brake,

[0039] [Fig.6] [Fig.6] represents a first variant of the assembly shown in the [Fig.2], and

[0040] [Fig.7] [Fig.7] represents a second variant of the assembly shown in the [Fig.2], Description of the embodiments

[0041] [Fig.l] shows an aircraft 100, in this example an airplane, comprising a landing gear that includes a front landing gear 80 and a rear landing gear 80. In this example, the rear landing gear 80 is equipped with an aircraft wheel and brake assembly 50. In this example, the aircraft 100 includes three landing gears 80 (only two being visible in [Fig.l]), but it may include more or fewer. In this example, each landing gear 80 includes a single assembly 50, but each landing gear 80 may include two or more sets 50. The landing gears 80 may all be identical, for example, comprise the same number of sets 50, or be different, for example, comprise a different number of sets 50.

[0042] A landing gear 80 is shown in more detail in [Fig. 2]. The landing gear 80 in this example comprises a leg 82 (or landing gear leg), an axle 84 (or wheel axle) mounted on the leg 82, and a single aircraft wheel and brake assembly 50 mounted on the axle 84.

[0043] In this example, the assembly 50 comprises an aircraft wheel 10 equipped with a brake 20, the wheel 10 comprising a rim 12 and at least one web 14. For example, when the aircraft is a business jet, the wheel 10 may comprise a single web (single-web structure), and when the aircraft is an airliner, the wheel 10 may comprise an inner half-wheel and an outer half-wheel. Each half-wheel may then in turn comprise a web 14. In other words, it may be considered that the wheel 10 comprises in this example at least two webs 14. According to a variant, the assembly 50 may comprise several aircraft wheels 10 each equipped with a brake 20.

[0044] The rim 12 is configured to receive a tire 40 and has an axis of rotation X defining an axial direction, a first axial end 12A and a second axial end 12B opposite the first axial end 12A in the axial direction, the web 14 extending radially, in the radial direction R, inwards from the rim 12, the web 14 being arranged axially at a distance from the first axial end 12A of the rim 12 and at a distance from the second axial end 12B of the rim 12. The brake 20 comprises a plurality of discs 22 arranged on a first side C1 of the web 14 and a plurality of actuators 24 configured to axially press the discs of the plurality of discs 22 together, the plurality of actuators 24 being arranged in whole or in part on a second side C2 of the web 14, the second side C2 of the web 14 being axially opposite the first side Cl of the web 14 relative to the web 14.The 40 tire may or may not be part of the 50 set.

[0045] Generally speaking, within the meaning of the present disclosure, within the assembly 50, the axial direction corresponds to the direction of the axis of rotation X of the wheel 10, which coincides with the axis of the axle 84, and a radial direction R is a direction perpendicular to the axis X. The azimuthal or circumferential direction C corresponds to the direction describing a ring around the axial direction. The circumferential direction C corresponds to the direction of rotation of the wheel 10 around the axis X. The three axial, radial and azimuthal directions correspond respectively to the directions defined by the coast, the radius and the angle in a cylindrical coordinate system. Unless otherwise specified, the adjectives “inner” and “outer” are used with reference to a radial direction so that the inner part (i.e. radially inner) of an element is closer to the axis X than the outer part (ie radially external) of the same element.

[0046] In this example, the wheel 10 has a hub 16. The wheel 10 is mounted on the axle 84 via two bearings 85, in this example ball or roller bearings, the bearings 85 being arranged radially between the axle 84 and the hub 16.

[0047] In this example, the wheel 10 may comprise two half-wheels 10-1 and 10-2, each half-wheel 10-1, 10-2 comprising respectively a half-rim 10-12, 10-22, a web 10-14, 10-24, and a half-hub 10-16, 10-26. The half-rim 10-12 has the first axial end 12A while the half-rim 10-22 has the second axial end 12B. The two half-wheels 10-1 and 10-2 are assembled together by bolts 15 axially engaged with the webs 10-14 and 10-24. Each half-hub 10-16, 10-26 cooperates with a single bearing 85. Any other wheel structure 10 is conceivable. Subsequently, the terms “wheel”, “rim”, “skid plate” and “hub” will respectively designate the entire wheel (i.e. the two half-wheels), the entire rim (i.e. the two half-rims), a single sail plate or at least two sails, and the entire hub (i.e. the two half-hubs).

[0048] In this example, the wheel 10 may comprise a first cavity V1 delimited axially by the first axial end 12A of the rim 12 and by the web 14, and a second cavity V2 delimited axially by the second axial end 12B of the rim 12 and by the web 14. The first cavity VI is arranged on the first side C1 of the web 14 while the second cavity V2 is arranged on the second side C2 of the web 14. In this example, the first and second cavities VI and V2 are both delimited radially on the inside by the hubs 16 and radially on the outside by the rim 12. As will be described in more detail below, the plurality of discs 22 is arranged, in this example strictly arranged, within the first cavity VI and the plurality of actuators 24 is arranged, in this example strictly arranged, within the first cavity VI and the second cavity V2. In this example, the brake 20 is fully housed within the wheel 10.

[0049] The brake 20 may comprise an axial stop 26 secured to the rim 12, the plurality of discs 22 being arranged axially between the plurality of actuators 24 and the axial stop 26. In this example, the axial stop 26 is mounted on the rim 12 by means of bolts 17. In this example, the bolts 17 extend radially and are engaged with the rim 12 and an annular flange 26A of the axial stop 26. In this example, the axial stop 26 is mounted on the first axial end 12A of the rim 12. In this example, the axial stop 26 has a plurality of projections 26B, each projection 26B extending radially inwardly from the rim 12 (see [Fig. 3]), the projections 26B of the plurality of projections 26B being regularly distributed around the X axis. In this example, the stop 26 has four projections 26B, but could, according to a variant, comprise less than four projections or more than four projections. In this example, the projections each have a plate shape extending in a plane perpendicular to the X axis, and of substantially triangular shape, one vertex of the triangle being oriented radially towards the inside of the rim 12 and the other two vertices being connected to the annular flange 26A. In this example, the flange 26A and the projections 26B form a single piece. A space 26C is provided between each pair of adjacent stops 26B in the circumferential direction. In this example, the spaces 26C all together have a cross shape centered on the X axis. In other words, the stop 26 can be considered as a disc in which a cross is provided forming a through hole forming the spaces 26C. These spaces 26C can facilitate ventilation and cooling of the brake 10.The spaces 26C may be provided with an openwork cover 28 forming a heat shield to protect the immediate environment of the brake 20 from excessive heat generated during braking. The openwork cover 28 may include a central circular through hole to reduce its size and receive, for example, a portion of a coupling element 30 described below.

[0050] The brake 20 may comprise only the plurality of discs 22, i.e. no other discs than the discs 22. The plurality of discs may comprise at least two discs 22 and at most eleven discs 22, for example at least three discs 22 and at most five discs 22. In the example of [Fig. 2], the brake 20 comprises an odd number of discs 22, for example five discs 22. In this example, in the axial direction, there is alternation of rotor discs 22A and stator discs 22B (it is noted that unless otherwise specified, the discs are designated generically by the reference sign “22”). The rotor discs 22A have on their radially external side at least one axial groove, for example a plurality of axial grooves, not shown, axially engaged with an axial rib 12C of the rim 12. The rotor discs 22A are thus coupled in rotation with the wheel 10.The stator discs 22B have on their radially inner side at least one axial groove, for example a plurality of axial grooves, not shown, axially engaged with an axial rib 30A of a coupling element 30 coupled in rotation with the axle 84. The coupling element 30 may be known to those skilled in the art under the terminology axle hand for the portion coupled to the axle 84 and torque tube for the portion coupled to the stator discs 22B. The stator discs 22B are fixed in rotation relative to the rotor discs 22A, the rotor discs 22A being able to rotate about the axis X relative to the stator discs 22B. All the discs 22 are axially movable along the ribs 12C or 30A. In this example, each stator disc 22B is axially sandwiched between two rotor discs 22A.In this example, the actuators 24 cooperate axially with a rotor disc 22A, and the axial stop 26A cooperates axially with another rotor disc 22A distinct from the rotor disc 22A with . which cooperates the plurality of actuators 24.

[0051] According to a variant shown in [Fig.7], the number of discs in the plurality of discs 22 may be even, and in this example equal to four, all the other elements being identical to the embodiment of [Fig.2]. In this example of [Fig.7], the plurality of discs 22 comprises two rotor discs 22A and two stator discs 22B, alternating in the axial direction. In this variant, the actuators 24 cooperate axially with a rotor disc 22A, and the axial stop 26A cooperates axially with a stator disc 22B.

[0052] During a braking phase, the actuators 24 described in more detail below axially press all of the discs 22 towards the axial stop 26, this compression generating friction between the rotor discs 22A and the stator discs 22B, this friction itself generating the braking force. For example, the discs 22 are made of carbon or metallic material, but not necessarily. In this example, the walls directly facing the discs 22 may be equipped with a coating 13 forming a heat shield.

[0053] In this example, the plurality of actuators 24 may comprise four actuators 24 (see [Fig.5]). According to a variant, the plurality of actuators may comprise more or less than four actuators. The actuators 24 are regularly distributed in the circumferential direction around the axis X. In this example, each of the actuators 24 of the plurality of actuators 24 passes axially through the web 14 and has a piston 24A cooperating with a disc 22 of the plurality of discs 22. In this example, each of the actuators has a fixed part 24B mounted on the web 14, for example via bolts 23, and a movable part, in this example the piston 24A, which is movable relative to the fixed part 24B. The piston 24A is axially movable and is configured to axially press, during braking operations, the disc 22 with which it is axially opposite, and to release the pressure exerted otherwise.In this example, the piston 24A exerts pressure on the discs when it is moved axially toward the axial stop 26, and releases the pressure when it is moved axially away from the axial stop 26.

[0054] In this example, each of the actuators 24 of the plurality of actuators 24 is electrical, the brake 20 comprising a rotating electrical connection 28 configured to be electrically connected to a fixed portion of the aircraft landing gear 80, for example the axle 84 or the leg 82, in the present example the leg 82, the fixed portion being fixed relative to the wheel 10. In this example, the rotating electrical connection 28 may comprise a central ring 28A and as many radial branches 28B as there are actuators 24, each radial branch 28B electrically connecting the central ring 28A to an actuator 24. The central ring 28A may be equipped with a brush connector 28C. The rotating electrical connection 28 is rotationally coupled with the wheel 10, and fixed relative to the actuators 24. The brush connector 28C provides the electrical connection between the leg 82 and the actuators 24. In this example, the brush connector 28C forms a ring which has at least one portion in contact in the axial direction with the leg 82. An electrical current supply circuit within the leg 82 to the brush connector is otherwise known to those skilled in the art and is not described. A control device for controlling the brake 20 and actuating the actuators 24 in order to actuate / release the braking is not shown, and may be of any type otherwise known to those skilled in the art.

[0055] With reference to [Fig.5], the veil 14 is perforated, and has a plurality of openings passing through 14A. Each opening 14A has in this example an ellipsoidal shape, the major axis of the ellipse being oriented radially. According to a variant, the openings 14A may have a different shape and / or a different orientation. In this example, there are four openings 14A, but according to a variant there may be more or less than four openings 14A. In this example, the openings 14A are regularly distributed circumferentially around the axis X. In this example, in the circumferential direction C, the openings 14A alternate with the actuators 24. In other words, in the circumferential direction C, a opening 14A is arranged between each pair of adjacent actuators 24.

[0056] In the example of [Fig.2], the discs 22 are arranged relative to the web 14 on the side opposite the leg 82. [Fig.6] represents a variant in which the discs 22 are arranged, relative to the web 14, on the side of the leg 82.

[0057] The assembly 50 of [Fig.6] is similar to the assembly 50 of [Fig.2], except that the coupling element 30' and the rotating electrical connection 28' are adapted for mounting on the leg 82 so that the discs 22 are arranged on the side of the leg 82. All other elements are not described again and have the same reference signs.

[0058] In this example, the axle 84 has a flange 84A on which the coupling element 30' is mounted, in this example via bolts 85. The coupling element 30' has in this example a counter-flange 31 for mounting the coupling element on the flange 84A.

[0059] The rotating electrical connection 28' is in this example configured to be electrically connected to the axle 84. In this example, the connection 28' has radial branches 28'B similar to the branches 28B of the example of [Fig.2], which are connected to a central ring 28'B carrying a brush connector 28'C which forms a ring in which the axle 84 is fitted. A circuit for supplying electrical current within the axle 84 to the brush connector 28'C is otherwise known to those skilled in the art and is not described.

[0060] Although the present invention has been described with reference to embodiments specific, it is obvious that modifications and changes may be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

Claims

1. A wheel and brake assembly for an aircraft (50), comprising an aircraft wheel (10) equipped with a brake (20), the aircraft wheel (10) comprising a rim (12) and at least one web (14), the rim (12) being configured to receive a tire (40) and having an axis of rotation (X) defining an axial direction, a first axial end (12A) and a second axial end (12B) opposite the first axial end (12A) in the axial direction, the web (14) extending radially inward from the rim (12), the web (14) being arranged axially at a distance from the first axial end (12A) of the rim (12) and at a distance from the second axial end (12B) of the rim (12), the brake (20) comprising a plurality of discs (22) arranged on a first side (Cl) of the web (14) and a plurality of actuators (24) configured to axially press the discs (22) of the plurality of discs (22) together,the plurality of actuators (24) being arranged in whole or in part on a second side (C2) of the web (14), the second side (C2) of the web (14) being axially opposite the first side (Cl) of the web (14) relative to the web (14).,

2. An aircraft wheel and brake assembly (50) according to claim 1, wherein the brake (20) comprises an axial stop (26) integral with the rim (12), the plurality of discs (22) being arranged axially between the plurality of actuators (24) and the axial stop (26).

3. An aircraft wheel and brake assembly (50) according to claim 2, wherein the axial stop (26) has a plurality of projections (26B), each projection (26B) of the plurality of projections (26B) extending radially inwardly from the rim (12), the projections (26B) of the plurality of projections (26B) being regularly distributed about the axis (X).

4. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 3, wherein each of the plurality of actuators (24) axially passes through the web (14) and has a piston (24A) cooperating with a disc (22) of the plurality of discs (22).

5. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 4, wherein the web (14) is perforated.

6. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 5, wherein each of the actuators (24) of the plurality of actuators (24) is electrical, the brake (20) comprising a rotating electrical connection (28, 28') configured to be electrically connected to a fixed part of an aircraft landing gear (80), for example a wheel axle (84) or a landing gear leg (82), the fixed part being fixed relative to the wheel (10).

7. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 6, wherein the plurality of discs (22) comprises at least two discs (22), for example at least three discs (22).

8. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 7, wherein the brake (20) is integrally housed within the wheel (10).

9. An aircraft wheel and brake assembly (50) according to any one of claims 1 to 8, wherein the wheel (10) comprises a first cavity (VI) axially delimited by the first axial end (12A) of the rim (12) and by the web (14), and a second cavity (V2) axially delimited by the second axial end (12B) of the rim (12) and by the web (14), the plurality of discs (22) being arranged, for example strictly arranged, within the first cavity (VI), the plurality of actuators (24) being arranged, for example strictly arranged, within the first cavity (VI) and the second cavity (V2).

10. A landing gear (80) comprising a landing gear leg (84), a wheel axle (84) mounted on the landing gear leg (82) and an aircraft wheel and brake assembly (50) according to any one of claims 1 to 9 mounted on the wheel axle (84), the plurality of discs (22) being disposed relative to the web (14) on the landing gear leg (82) side.

Images