Propeller and aircraft

Abstract

The utility model discloses a propeller and an aircraft, and relates to the technical field of aircrafts. The propeller comprises a propeller hub; the paddle is rotatably matched with the paddle mounting hole through a first bearing, a matching hole is formed in the end face of the end, close to the containing hole, of the paddle, and the central axis of the matching hole and the central axis of the paddle mounting hole are collinear; the connecting piece is arranged in the containing hole and fixedly connected with the propeller hub, at least part of the connecting piece directly faces the propeller blade mounting hole and protrudes to form a core shaft part, the core shaft part extends into the matching hole so as to be rotatably connected with the propeller blade through a second bearing, and part of the second bearing is fixedly connected with the propeller blade; the central axis of the mandrel part and the central axis of the paddle mounting hole are collinear; and the axial limiting piece is fixedly connected to the core shaft part, and the axial limiting piece is matched with the other part of the second bearing to limit the axial movement of the propeller blades relative to the propeller hub along the propeller blade mounting holes. The overall weight of the propeller can be reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a propeller and an aircraft. Background Art

[0002] For helicopters, rotorcraft or eVTOL (electric Vertical Take-off and Landing) with tilt-rotor configuration, the propeller is the component that ultimately generates thrust or lift.

[0003] A propeller consists of a hub and blades. To achieve variable pitch, the blades are mounted to the hub via bearings. The blades and bearings are connected via bolts. This connection method, to ensure the strength and reliability of the blade-hub connection, inevitably increases the size and weight of the bearings significantly. Utility Model Content

[0004] The main purpose of the utility model is to provide a propeller and an aircraft, aiming to solve the technical problem in the related art that the connection method between the hub and the blades causes the size and weight of the bearing to increase sharply.

[0005] To achieve the above-mentioned purpose, the present invention provides a propeller comprising:

[0006] A propeller hub is defined in which a receiving hole is defined, and an outer peripheral wall of the propeller hub is provided with a blade mounting hole connected to the receiving hole;

[0007] a blade rotatably engaged with the blade mounting hole via a first bearing, a mating hole being defined on an end surface of the blade adjacent to the receiving hole, and a central axis of the mating hole being collinear with a central axis of the blade mounting hole;

[0008] a connecting member disposed in the receiving hole and fixedly connected to the hub, at least a portion of the connecting member facing the blade mounting hole and protruding to form a core shaft portion, the core shaft portion extending into the mating hole and rotatably connected to the blade via a second bearing, a portion of the second bearing being fixedly connected to the blade, and a central axis of the core shaft portion being collinear with a central axis of the blade mounting hole; and

[0009] An axial limiter is fixedly connected to the core shaft portion and is adapted to cooperate with another portion of the second bearing to limit the axial movement of the blade relative to the hub along the blade mounting hole.

[0010] In one embodiment, the second bearings include at least two, and the at least two second bearings are spaced apart from each other along the axial direction of the blade mounting hole;

[0011] The at least two second bearings include an outermost second bearing close to the axial limiter, and the outermost second bearing cooperates with the axial limiter to limit the axial movement of the blade relative to the hub along the blade mounting hole.

[0012] In one embodiment, the propeller further includes a bearing sleeve, which is detachably fixed in the matching hole. The bearing sleeve defines a bearing mounting hole that passes through the bearing sleeve along the axial direction of the blade mounting hole. The bearing sleeve has a first axial positioning portion at one end facing the receiving hole, and a second axial positioning portion at one end away from the receiving hole. All second bearings are mounted between the first axial positioning portion and the second axial positioning portion.

[0013] The core shaft portion extends into the bearing mounting hole and extends out from one end of the bearing tube away from the accommodating hole, and the axial limiting member is arranged on the portion of the core shaft extending out of the bearing mounting hole.

[0014] In one embodiment, a first sleeve is disposed between any two adjacent second bearings.

[0015] In one embodiment, the bearing cartridge comprises:

[0016] A barrel body with two axial ends open, wherein at least a portion of an inner peripheral wall of one end of the barrel body close to the accommodating hole protrudes in the radial direction of the barrel body to form a first axial positioning portion; and

[0017] The end cover is detachably fixed to one end of the barrel body away from the accommodating hole, and the end cover includes a first cylindrical portion, which extends into the barrel body to form a second axial positioning portion.

[0018] In one embodiment, the end cover is provided with an end cover hole, and an end of the core shaft portion away from the receiving hole passes through the end cover hole;

[0019] The axial limiting member is located on a side of the end cover facing away from the cylinder body.

[0020] In one embodiment, the propeller further comprises:

[0021] The second sleeve is sleeved on the core shaft portion, and one end of the second sleeve abuts against the outermost second bearing, and the other end of the second sleeve abuts against the axial limiting member.

[0022] In one embodiment, the axial limiter comprises:

[0023] an axial limiting body, the axial limiting body being threadedly connected to the core shaft portion and cooperating with the outermost second bearing; and

[0024] The anti-loosening component is arranged at the axial limiting body and passes through the axial limiting body and the core shaft portion.

[0025] In one embodiment, the connecting member further includes a cover portion, which is disposed in the receiving hole, faces the blade mounting hole, and is connected to the receiving hole wall at the blade mounting hole.

[0026] Part of the surface of the end surface of one side of the cover portion facing the blade mounting hole protrudes to form a core shaft portion;

[0027] A portion of the surface of one side end surface of the cover plate portion facing the blade mounting hole protrudes to form a second cylindrical portion, and the second cylindrical portion extends into the blade mounting hole and abuts against the first bearing.

[0028] In one embodiment, the first bearing is a radial bearing; and / or the second bearing is a thrust bearing.

[0029] In addition, the present invention also provides an aircraft, which includes:

[0030] Aircraft body; and

[0031] At least one propeller as described above is provided on the aircraft body.

[0032] In one embodiment, the aircraft is an electric vertical take-off and landing aircraft.

[0033] One or more technical solutions proposed in this utility model have at least the following technical effects:

[0034] Compared to the related art in which the hub and the blades are directly connected through bearings and bolt groups, in the propeller proposed by the present invention, while the blades are rotatably matched with the blade mounting holes through the first bearing, the hub also includes a connecting piece that is directly opposite to the blade mounting hole. The connecting piece has a core shaft portion that extends into the matching hole on the end face of the blade, and the core shaft portion and the blade are rotatably matched through the second bearing. In this way, part of the second bearing is fixedly connected to the blade, and the other part cooperates with the axial limiter on the core shaft portion to realize axial constraint on the blade and transmission of axial load. The first bearing is mainly used to transmit the radial load between the hub and the blade, thereby reducing the size and weight of the first bearing. In addition, combined with the hollow structure of the blade, the size and weight of the hub and the blade handle portion can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0036] Figure 1A schematic diagram of the structure of the propeller provided by the utility model;

[0037] Figure 2 This is an enlarged schematic diagram of the bearing cylinder of the propeller provided by the present invention;

[0038] Figure 3 This is an enlarged schematic diagram of the axial limit member of the propeller provided by the present invention.

[0039] Description of Figure Numbers:

[0040] 100. Hub; 101. Blade mounting hole; 200. Blade; 210. Blade handle; 220. Blade blade; 211. Matching hole; 300. Connector; 310. Cover plate portion; 311. Second cylindrical portion; 320. Core shaft portion; 400. Axial limit member; 410. Axial limit body; 420. Anti-loosening member; 500. First bearing; 600. Second bearing; 610. Outermost second bearing; 700. Bearing cylinder; 701. Bearing mounting hole; 710. Cylinder body; 711. First axial positioning portion; 720. End cover; 721. End cover hole; 722. First cylindrical portion; 800. First sleeve; 900. Second sleeve.

[0041] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0042] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0043] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0044] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited to "first" and "second" may explicitly or implicitly include at least one of such features. In addition, if "and / or" or "and / or" appears in the full text, its meaning includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme in which A and B are satisfied at the same time. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0045] For helicopters, rotorcraft or eVTOL (electric Vertical Take-off and Landing) with tilt-rotor configuration, the propeller in its thrust assembly is the component that ultimately generates thrust or lift.

[0046] See also Figure 1 This embodiment provides a propeller, which includes a hub 100, blades 200, a connecting member 300 and an axial limit member 400.

[0047] Among them, the hub 100 defines a receiving hole, and the outer peripheral wall of the hub 100 is provided with a blade mounting hole 101 connected to the receiving hole; the blade 200 is rotatably matched with the blade mounting hole 101 through the first bearing 500, and the end surface of the blade 200 close to the receiving hole is provided with a matching hole 211, and the central axis of the matching hole 211 is collinear with the central axis of the blade mounting hole 101; the connecting member 300 is arranged in the receiving hole and is fixedly connected to the hub 100, and at least a portion of the connecting member 300 is directly opposite to the blade mounting hole. The mounting hole 101 protrudes to form a core shaft portion 320, the core shaft portion 320 extends into the matching hole 211 and is rotatably connected to the blade through the second bearing 600, a portion of the second bearing 600 is fixedly connected to the blade 200, and the center axis of the core shaft portion 320 is colinear with the center axis of the blade mounting hole 101; the axial limit member 400 is fixedly connected to the core shaft portion 320, and cooperates with another portion of the second bearing 600 to limit the axial movement of the blade 200 relative to the hub 100 along the blade mounting hole 101.

[0048] Specifically, the hub 100 is the part where each blade 200 is mounted and combined. On the outer peripheral wall of the hub 100, multiple blades 200 are evenly mounted through multiple evenly arranged blade mounting holes 101. The hub 100 is a hollow structure, and its internal space is constructed to accommodate holes ( Figure 1 The receiving hole is located on the left side of the cross-sectional area of ​​the middle hub 100. A pitch-changing assembly that drives the blades 200 to rotate about their pitch-changing axes is installed in the receiving hole. Of course, the pitch-changing assembly can be completely or partially located in the receiving hole, and this embodiment is not limited thereto.

[0049] The propeller blade includes a shaft 210 and a blade 220. The shaft 210 is inserted into the blade mounting hole 101, and the blade 220 is eccentrically connected to the portion of the shaft 210 that is exposed from the hub 100. To achieve pitch control, a first bearing 500 is installed between the shaft 210 and the wall of the blade mounting hole 101. Of course, corresponding axial positioning structures are provided on the outer peripheral walls of the blade mounting hole 101 and the shaft 210 to achieve axial positioning of the first bearing 500.

[0050] It should be noted that in this embodiment, the paddle handle 210 is a hollow shaft structure, that is, the inner end surface of the paddle handle 210 (the end surface adjacent to the receiving hole) is provided with a mating hole 211. The central axis of the mating hole 211 is approximately collinear with the central axis of the paddle handle 210, that is, it should be approximately collinear with the central axis of the blade mounting hole 101.

[0051] In addition, hub 100 is provided with a connector 300. Multiple connectors 300 may be provided, with their number matching the number of blade mounting holes 101 and corresponding one-to-one with each other. Alternatively, a single connector 300 may be provided. In this case, connector 300 is configured as an annular member coaxially arranged with hub 100, such that a portion of the annular member directly faces each blade mounting hole 101. The following description will be based on an example in which the number of connectors 300 matches the number of blade mounting holes 101 and corresponds one-to-one with each other.

[0052] A portion of the connector 300 is fixedly connected to the sidewall of the receiving hole, thereby securing it within the hub 100. Another portion of the connector 300 faces the corresponding blade mounting hole 101, and a portion of its surface protrudes to form a core shaft portion 320. The central axis of the core shaft portion 320 is approximately colinear with the central axis of the blade mounting hole 101. Therefore, when the blade handle 210 is inserted into the blade mounting hole 101, the core shaft portion 320 simultaneously extends into the mating hole 211. Furthermore, as the blade handle 210 rotates relative to the core shaft portion 320, the pitch changes. Therefore, a second bearing 600 is also mounted between the core shaft portion 320 and the sidewall of the mating hole 211. Portions of the second bearing 600, such as the outer ring, are fixedly connected to the blade handle 210, while another portion of the second bearing 600, such as the inner ring, fits over the core shaft portion 320 and is constrained by an axial stopper 400. It is worth mentioning that the core shaft portion 320 can be a part of the connecting member 300, and can also be a component fixed to the connecting member 300 by means of threaded connection or the like.

[0053] It is understood that, because blades 200 tend to move centrifugally during propeller rotation, axial stopper 400 is primarily used to prevent the blades from separating from hub 100. Therefore, axial stopper 400 is fixedly connected to core shaft portion 320 and engages with second bearing 600 within mating hole 211, for example, radially outwardly of second bearing 600 in the radial direction of hub 100 to restrict outward movement of second bearing 600. Thus, when blade handle 210 tends to separate outward from hub 100, blade handle 210 will drive second bearing 600 outward from hub 100. However, because second bearing 600 is blocked by axial stopper 400 on core shaft portion 320, blade handle 210 remains within blade mounting hole 101 of hub 100. It is understood that axial stopper 400 may be configured as a structure such as a shoulder on core shaft portion 320, or as a component such as a shaft end baffle or locking nut.

[0054] It is not difficult to see that, compared to the related art in which the hub 100 and the blade 200 are directly connected via a bearing and a bolt assembly, in this embodiment, while the blade 200 is rotatably engaged with the blade mounting hole 101 via the first bearing 500, the hub 100 also includes a connector 300 that partially faces the blade mounting hole 101. The connector 300 has a core shaft portion 320 that extends into the mating hole 211 on the end surface of the blade 200. The core shaft portion 320 and the blade 200 are rotatably engaged via the second bearing 600. In this way, a portion of the second bearing 600 is fixedly connected to the blade 200, while the other portion, via the axial stopper 400 on the core shaft portion 320, axially constrains the blade 200 and transmits the axial load. The first bearing 500 is primarily used to transmit the radial load between the hub 100 and the blade, thereby reducing the size and weight of the first bearing 500. In addition, the hollow structure of the blade 200 can reduce the weight of the handle 210 of the blade 200 .

[0055] Understandably, when a single second bearing 600 transmits axial loads, the weight and size of the second bearing 600 will increase accordingly to achieve higher structural strength and reliability, but this will make it difficult to install within the mating hole 211 of the propeller shaft 210. Therefore, in one embodiment, at least two second bearings 600 are included, and the at least two second bearings 600 are spaced apart from each other along the axial direction of the blade mounting hole 101. The at least two second bearings 600 include an outermost second bearing 610 adjacent to the axial stop 400. The outermost second bearing 610 cooperates with the axial stop 400 to limit the axial movement of the blade 200 relative to the hub 100 along the blade mounting hole 101.

[0056] Specifically, multiple second bearings 600 are sequentially spaced apart on the core shaft portion 320 along the axial direction of the blade mounting hole 101 (the axial direction of the core shaft portion 320). Furthermore, portions (e.g., the outer ring) of each second bearing 600 are fixedly connected to the shaft 210. Thus, compared to a single second bearing 600, the multiple second bearings 600 can collaboratively share the axial load between the core shaft and the shaft 210, thereby reducing the size and weight of a single second bearing 600. Of course, it is understood that each second bearing 600 has corresponding axial positioning structures to ensure axial positioning of each second bearing 600 on the core shaft portion 320.

[0057] It is worth noting that the outermost second bearing 610 (closest to blade 220) cooperates with axial stopper 400 to limit axial movement of blade 200 relative to hub 100 along blade mounting hole 101. For example, the end surface of its inner ring, facing away from the receiving hole, abuts against axial stopper 400. Furthermore, since the other second bearings 600 each have their own axial positioning structures and are stationary relative to core shaft portion 320, axial stopper 400 limits the axial movement of all second bearings 600 in blade mounting hole 101, thereby limiting the axial movement of blade 200 relative to hub 100 along blade mounting hole 101.

[0058] It is understood that the fixed connection between the second bearing 600 portion, such as the outer ring, and the blade 200 can be achieved by the outer ring being fixedly connected to the wall of the mating hole 211 via a bolt assembly, or by the outer ring of each second bearing 600 being threadedly connected to the wall of the mating hole 211. Obviously, the individual connection of each second bearing 600 to the blade 200 complicates installation. Therefore, in one embodiment, the propeller further includes a bearing cartridge 700. The bearing cartridge 700 is removably secured within the mating hole 211. The bearing cartridge 700 defines a bearing mounting hole 701 extending axially through the bearing cartridge 700 along the blade mounting hole 101. The end of the bearing cartridge 700 facing the receiving hole has a first axial locating portion 711, and the end of the bearing cartridge 700 facing away from the receiving hole has a second axial locating portion. All second bearings are mounted between the first axial locating portion 711 and the second axial locating portion. The core shaft portion 320 extends into the bearing mounting hole 701 and extends from an end of the bearing cylinder 700 away from the accommodating hole. The axial limiting member 400 is disposed at the portion of the core shaft portion 320 extending from the bearing mounting hole 701 .

[0059] Specifically, the connection between the blade handle 210 and all second bearings 600 is achieved through the bearing sleeve 700. The bearing sleeve 700 is a cylindrical member, and the central axis of the bearing sleeve 700 is collinear with the central axis of the matching hole 211. The bearing sleeve 700 is also a hollow structure, that is, the bearing sleeve 700 defines a bearing mounting hole 701 that passes through the bearing sleeve 700 along the axial direction of the blade mounting hole 101. All second bearings 600 are located in the bearing mounting hole 701, and the central axes of all second bearings 600, the core shaft portion 320, and the bearing sleeve 700 are approximately collinear. At this time, the core shaft portion 320 extends from the end face of the bearing sleeve 700 close to the receiving hole into the bearing mounting hole 701 and extends from the end of the bearing sleeve 700 away from the receiving hole. Then, the axial limit member 400 is set on the portion of the core shaft portion 320 that extends out of the bearing mounting hole 701. Of course, as before, the end surface of the inner ring of the outermost second bearing 610 (closest to the blade 220 ) in the bearing tube 700 , which is away from the accommodating hole, abuts against the axial limit member 400 .

[0060] Thus, when installing the propeller provided by this embodiment, the second bearing 600 and the bearing cartridge 700 are integrally mounted on the core shaft portion 320. Since all second bearings 600 are axially positioned on the core shaft portion 320, and compared to the bearing cartridge 700, the entire second bearing 600 is axially limited by the first axial positioning portion 711 and the second axial positioning portion of the bearing cartridge 700 at both ends, the core shaft portion 320, all second bearings 600, and the bearing cartridge 700 are considered as a single unit that moves axially in the blade mounting hole 101. This unit is then placed into the mating hole 211 of the blade shaft 210, and the bearing cartridge 700 is fixedly connected to the blade shaft 210. This secures the outer rings of all second bearings 600 to the blade shaft 210, thereby improving installation efficiency.

[0061] The bearing sleeve 700 and the matching hole 211 of the propeller shaft 210 are shaft-hole matched. Therefore, the fixed connection between the bearing sleeve 700 and the propeller shaft 210 can be achieved by a tapered sleeve, a threaded connection, an adapter sleeve connection, etc. Of course, since the propeller requires a higher fixing force and reliability, a threaded connection is preferably used.

[0062] In addition, the axial positioning structure of the second bearing 600 on the core shaft portion 320 can be a structure such as a shoulder or a collar designed on the core shaft portion 320. Alternatively, to facilitate the removal and installation of the second bearing in the bearing cartridge 700, in one embodiment, a first sleeve 800 is provided between any two adjacent second bearings 600.

[0063] Specifically, the core shaft portion 320 can be constructed as a straight shaft, eliminating the need for a shoulder, collar, or other structures. The first sleeve 800 is positioned within the bearing mounting hole 701 and sleeved onto the core shaft portion 320 . One end surface of the first sleeve 800 abuts against the inner race of one of any two adjacent second bearings 600 , and the other end surface of the first sleeve 800 abuts against the inner race of the other of any two adjacent second bearings 600 .

[0064] Thus, when installing the second bearing 600, the second bearing 600 and the first sleeve 800 are alternately mounted on the core shaft portion 320. Similarly, when removing the second bearing 600, the second bearing 600 and the first sleeve 800 are alternately removed from the core shaft portion 320. This significantly improves the efficiency of installing and removing the second bearing 600.

[0065] Furthermore, in one embodiment, the bearing cartridge 700 includes a cartridge body 710 with two axially open ends, and an end cap 720. At least a portion of the inner circumferential wall of the cartridge body 710 at one end adjacent to the receiving hole protrudes radially from the cartridge body 710 to form a first axial positioning portion 711. The end cap 720 is detachably secured to the end of the cartridge body 710 distal from the receiving hole and includes a first cylindrical portion 722 that extends into the cartridge body 710 to form a second axial positioning portion.

[0066] Specifically, see Figure 1 and Figure 2 One axial end of the barrel body 710 is open and covered by an end cap 720, while at least a portion of the inner circumferential wall of the other axial end protrudes radially along the barrel body 710 to form a radial projection, thereby forming a step at the other axial end of the barrel body 710. In one example, the radial projection can be an annular projection. Furthermore, the outer edge of the end cap 720 is removably secured to the end surface of one axial end of the barrel body 710 using fasteners such as screws or bolts. The projection of the end cap 720 toward one end surface of the barrel body 710 forms a first cylindrical portion 722. The outer diameter of the first cylindrical portion 722 is approximately equal to the inner diameter of the barrel body 710, allowing the first cylindrical portion 722 to extend into the barrel body 710, forming a step with the inner wall of the barrel body 710. In this way, the steps at both axial ends of the barrel body 710 form an axial positioning structure, with the radial projection forming the first axial positioning portion 711 and the first cylindrical portion 722 forming the second axial positioning portion. Among them, since the end face of the first sleeve 800 abuts against the inner ring of the second bearing 600, the first axial positioning portion 711 can abut against the outer ring of the innermost second bearing, and the second axial positioning portion can abut against the outer ring of the outermost second bearing 610.

[0067] It is not difficult to see that in this embodiment, the bearing cylinder 700 is composed of two parts, so that during installation, the cylinder body 710 can be first installed on the core shaft portion 320, and then the second bearing 600 and the first sleeve 800 can be alternately installed on the core shaft portion 320 and pushed into the cylinder body 710, and then the cylinder body 710 is covered by the end cover 720 to achieve axial positioning of the second bearing 600.

[0068] It is understood that, as an option in this embodiment, the axial stopper 400 can be disposed within the bearing sleeve 700. It is readily apparent that, since the inner and outer rings of the outermost second bearing 610 are constrained by the axial stopper 400 and the end cap 720, respectively, disposing the axial stopper 400 within the bearing sleeve 700 would increase the thickness and weight of the end cap 720. Therefore, as another option in this embodiment, the end cap 720 is provided with an end cap hole 721, through which the end of the core shaft portion 320, distal from the receiving hole, passes; the axial stopper 400 is located on the side of the end cap 720 facing away from the sleeve body 710.

[0069] It is not difficult to see that when the axial limit member 400 is located outside the end cover 720, the thickness and weight of the end cover 720 can be reduced, thereby reducing the overall weight of the propeller.

[0070] Furthermore, when the axial stopper 400 is positioned outside the end cap 720, the axial stopper 400 may interfere with the end cap 720, or the clearance between the axial stopper 400 and the end cap 720 may be small in the axial direction of the core shaft portion 320, thereby hindering the assembly and disassembly of the axial stopper 400. Therefore, in one embodiment, the propeller further includes a second sleeve 900. The second sleeve 900 is sleeved on the core shaft portion 320, with one end of the second sleeve 900 abutting the outer ring of the outermost second bearing 610, and the other end of the second sleeve 900 abutting the axial stopper 400.

[0071] Specifically, see Figure 3 The second sleeve 900 is sleeved on the core shaft portion 320, and one end passes through the end cover hole 721 and extends into the bearing tube 700 until it abuts the outer ring of the outermost second bearing 610. The other end of the second sleeve 900 is located on the outside of the end cover hole 721 and abuts the axial limit member 400. In this way, through the second sleeve 900, the end cover and the axial limit member 400 are staggered in the axial direction of the blade mounting hole to facilitate the installation of the two.

[0072] In one embodiment, the axial limiting member 400 includes an axial limiting body 410 and an anti-loosening member 420. The axial limiting body 410 is threadedly connected to the core shaft portion 320, and the axial limiting body 410 cooperates with the outermost second bearing 610; the anti-loosening member 420 is arranged at the axial limiting body 410 and passes through the axial limiting body 410 and the core shaft portion 320.

[0073] Specifically, the axial limiting body 410 can be constructed as a nut, an axial end baffle, or the like, such as a centrifugal nut, to provide axial limitation. In addition, the axial limiting body 410 is further provided with an anti-loosening member 420, such as an anti-loosening screw or a pin, to prevent the axial limiting body 410 from loosening.

[0074] See also Figure 3 In a specific embodiment, the axial limiting body 410 cooperates with the outermost second bearing 610 through the second sleeve 900 . At this time, the other end of the second sleeve 900 abuts against the axial limiting body 410 .

[0075] It is understandable that the connector 300 can be constructed as a frame or other structure fixedly mounted in the hub 100. Alternatively, in one embodiment, the connector 300 further includes a cover portion 310, which is disposed in the receiving hole. The cover portion 310 directly faces the blade mounting hole 101 and is connected to the receiving hole wall at the blade mounting hole 101. Part of the surface of the cover portion 310 on one side of the end surface facing the blade mounting hole 101 protrudes to form a core shaft portion 320. Another part of the surface of the cover portion 310 on one side of the end surface facing the blade mounting hole 101 protrudes to form a second cylindrical portion 311. The second cylindrical portion 311 extends into the blade mounting hole 101 and abuts against the first bearing 500.

[0076] Specifically, the outer edge of the cover plate portion 310 can be fixed to the hub 100 and cover the blade mounting hole 101 by fasteners such as screws and bolts, thereby achieving separation of the internal and external spaces of the hub 100. In addition, a portion of the surface of the end face of the cover plate portion 310 on one side facing the blade mounting hole 101 protrudes to form the core shaft portion 320, so that the connector 300 is an integrally formed part, thereby improving its structural strength. In addition, another portion of the surface of the end face of the cover plate portion 310 on one side facing the blade mounting hole 101 protrudes to form the second cylindrical portion 311. When the cover plate portion 310 covers the blade mounting hole 101, the second cylindrical portion 311 can extend into the blade mounting hole 101 as an axial positioning structure of the first bearing 500, thereby achieving axial positioning of the first bearing 500.

[0077] See also Figure 1 In one example, first bearings 500 include two. The inner ring of the outer first bearing abuts the shoulder of the outer circumferential wall of shaft 210, while the outer ring of the outer first bearing abuts the outer step of the mounting hole of hub 100. One end face of the outer ring of the inner first bearing abuts the outer step of blade mounting hole 101, and the other end face abuts second cylindrical portion 311. Of course, the inner ring of the inner first bearing can also be axially positioned by a structure such as a shoulder on shaft 210.

[0078] It is not difficult to see that the connector 300 in this embodiment realizes the transmission of axial load in the hub 100 and the axial positioning of the first bearing 500 through the integrated design of the cover portion 310 and the core shaft portion 320, thereby improving the integration of components.

[0079] Both first bearing 500 and second bearing 600 can be thrust bearings. Alternatively, as previously described, second bearing 600 is fixedly connected to blade 200 and, through axial stopper 400 on core shaft portion 320, provides axial constraint on the blade and transfers axial load. First bearing 500 is primarily used to transfer radial loads between hub 100 and the blade. Therefore, first bearing 500 is a radial bearing, and / or second bearing 600 is a thrust bearing.

[0080] In addition, the present invention also provides an aircraft, which includes an aircraft body; and at least one propeller as described above, wherein the propeller is arranged on the aircraft body.

[0081] The specific structure of the propeller refers to the above embodiments. Since the aircraft adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, which will not be described one by one here.

[0082] The aircraft may be a drone or an electric vertical take-off and landing aircraft eVTOL.

[0083] The above are merely exemplary embodiments of the present invention and are not intended to limit the patent scope of the present invention. All equivalent structural transformations made using the contents of the present invention specification and drawings under the technical concept of the present invention, or direct / indirect applications in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A propeller, characterized in that: include: a propeller hub, wherein a receiving hole is defined in the propeller hub, and a blade mounting hole communicating with the receiving hole is formed on an outer peripheral wall of the propeller hub; a blade, the blade being rotatably engaged with the blade mounting hole via a first bearing, a mating hole being formed on an end surface of the blade adjacent to the receiving hole, and a central axis of the mating hole being collinear with a central axis of the blade mounting hole; a connecting member, the connecting member being disposed in the accommodating hole and fixedly connected to the hub, at least a portion of the connecting member being opposite the blade mounting hole and protruding to form a core shaft portion, the core shaft portion extending into the mating hole and being rotatably connected to the blade via a second bearing, a portion of the second bearing being fixedly connected to the blade, and a central axis of the core shaft portion being collinear with a central axis of the blade mounting hole; and An axial limiter is fixedly connected to the core shaft portion, and cooperates with another portion of the second bearing to limit the axial movement of the blade relative to the hub along the blade mounting hole.

2. The propeller according to claim 1, wherein: The second bearings include at least two, and the at least two second bearings are spaced apart from each other along the axial direction of the blade mounting hole; The at least two second bearings include an outermost second bearing close to the axial limiter, and the outermost second bearing cooperates with the axial limiter to limit the axial movement of the blade relative to the hub along the blade mounting hole.

3. The propeller according to claim 2, characterized in that The propeller further comprises: a bearing sleeve, the bearing sleeve being detachably fixed in the matching hole, the bearing sleeve defining a bearing mounting hole extending axially through the bearing sleeve along the blade mounting hole, the bearing sleeve having a first axial positioning portion at one end facing the accommodating hole, and a second axial positioning portion at one end away from the accommodating hole, all second bearings being mounted between the first axial positioning portion and the second axial positioning portion; The core shaft portion extends into the bearing mounting hole and extends from one end of the bearing tube away from the accommodating hole, and the axial limiting member is arranged at the portion of the core shaft portion extending from the bearing mounting hole.

4. The propeller according to claim 3, characterized in that A first sleeve is arranged between any two adjacent second bearings.

5. The propeller according to claim 4, characterized in that The bearing sleeve includes: a barrel body with openings at both axial ends, wherein at least a portion of an inner peripheral wall of one end of the barrel body close to the accommodating hole protrudes radially from the barrel body to form the first axial positioning portion; and The end cover is detachably fixed to an end of the barrel body away from the accommodating hole, and the end cover includes a first cylindrical portion, and the first cylindrical portion extends into the barrel body to form the second axial positioning portion.

6. The propeller according to claim 5, characterized in that The end cover is provided with an end cover hole, and one end of the core shaft portion away from the receiving hole passes through the end cover hole; Wherein, the axial limiting member is located on a side of the end cover away from the cylinder body.

7. The propeller according to claim 6, characterized in that The propeller further comprises: The second sleeve is sleeved on the core shaft portion, and one end of the second sleeve abuts against the outermost second bearing, and the other end of the second sleeve abuts against the axial limiting member.

8. The propeller according to any one of claims 2 to 7, characterized in that The axial limiting member includes: an axial limiting body, wherein the axial limiting body is threadedly connected to the core shaft portion and cooperates with the outermost second bearing; and An anti-loosening component is provided at the axial limiting body and passes through the axial limiting body and the core shaft portion.

9. The propeller according to any one of claims 1 to 7, characterized in that The connecting member further includes a cover portion, which is arranged in the accommodating hole, the cover portion facing the blade mounting hole, and connected to the accommodating hole wall at the blade mounting hole; wherein, a portion of the surface of the cover portion facing the end surface of one side of the blade mounting hole protrudes to form the core shaft portion, and a portion of the surface of the cover portion facing the end surface of one side of the blade mounting hole protrudes to form a second cylindrical portion, and the second cylindrical portion extends into the blade mounting hole and abuts against the first bearing; and / or The first bearing is a radial bearing; and / or The second bearing is a thrust bearing.

10. An aircraft, characterized in that: The aircraft comprises: Aircraft body; and At least one propeller according to any one of claims 1 to 9, wherein the propeller is arranged on the aircraft body.

11. The aircraft according to claim 10, wherein: The aircraft is an electric vertical take-off and landing aircraft.

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