Propeller suitable for low-altitude vehicle

Abstract

The utility model discloses a propeller suitable for a low-altitude vehicle. The propeller comprises a middle supporting piece and a propeller body, the main shaft penetrates through the middle supporting piece; the first propeller blade assembly sleeves one end of the main shaft; the second propeller blade assembly sleeves the other end of the main shaft; the two connecting pieces are used for connecting the main shaft with the first propeller blade assembly and connecting the main shaft with the second propeller blade assembly; one protective cover is connected to the first propeller blade assembly, and the other protective cover is connected to the second propeller blade assembly; one motor assembly is connected to the middle supporting piece and the first propeller blade assembly, and the other motor assembly is connected to the middle supporting piece and the second propeller blade assembly; the technical problems that the steering torque generated by the forward propeller blade and the reverse propeller blade cannot be balanced, the rotation speed ratio needs to be adjusted, the structure is relatively complex, the structural reliability is relatively poor, the noise is relatively large, the stability is relatively poor, and the service life is relatively short are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a propeller suitable for low-altitude vehicles. Background Art

[0002] Aircraft related to the low-altitude sector can be divided into helicopters, drones, and eVTOLs (Electric Vertical Take-off and Landing Vehicles). With its three key features: electrification, vertical take-off and landing, and passenger capability, eVTOLs are expected to become the optimal vehicle for the low-altitude economy.

[0003] Among them, multiple propellers or fans are distributed on the wings or fuselage of the eVTOL, which together form a propulsion system to provide power (lift) for the eVTOL. Currently, common propulsion systems use a single motor and a single blade to provide power. The rotating propeller will assign a large reverse torque to the fuselage, seriously affecting the flight stability of the fuselage. To offset the reverse torque, it is often necessary to add additional devices to the fuselage or cross-distribute positive and reverse propellers to balance the fuselage torque (clockwise rotation is positive propeller, counterclockwise rotation is reverse propeller). This will increase the cost and difficulty of design and production.

[0004] For example, the Chinese patent application number is 202210250543.3, and the subject name of the patent is "Existing technology of coaxial reversible axial flux motor and drone", and the Chinese patent application number is 202120779343.8, and the subject name of the patent is "Existing technology of a coaxial reversible axial flux motor for electric aircraft". Both of them propose a reversible axial motor with forward and reverse output, and the torque offsets each other, which increases the motor power density and torque-to-weight ratio, and reduces motor loss. However, there are still some shortcomings:

[0005] 1. In the prior art of Chinese patent application No. 202210250543.3, the subject name of the patent is coaxial reversible axial flux motor and drone;

[0006] Two shafts (the first and second shafts) are used. The shafts and the rotor are fixed by a rotor sleeve. The motor drives the rotor to rotate, which drives the shaft to rotate, while the housing remains stationary. The structure of the upper and lower shafts is inconvenient to assemble, and the coaxiality of the two shafts is difficult to ensure. During operation, the upper and lower shafts are easily misaligned due to rotational vibration, resulting in increased noise and vibration.

[0007] The propeller blades are mounted on a shaft that drives the blades to rotate. During operation, the torque generated by the blades' rotation is small, so the motor must reach a higher speed to generate the required torque. First, increasing the speed increases noise. Second, increasing the speed further exacerbates the misalignment of the upper and lower shafts.

[0008] 2. In the prior art of Chinese patent application No. 202120779343.8, the subject name of the patent is a coaxial reverse axial flux motor for electric aircraft;

[0009] The forward rotor housing 100 is fixed to the forward rotating shaft 200, and the forward propeller blade is connected to the forward driving member fixing plate 300 on the forward rotating shaft 200. The forward rotor housing 100 drives the forward rotating shaft 200 and the forward propeller blade to rotate forward. The motor housing 400 is connected to the reverse propeller blade, and the motor housing 400 drives the reverse propeller blade to rotate reversely. The forward rotor housing 100 is inside the motor housing 400, and the two do not contact each other. Such a structure can achieve forward and reverse output, and uses a single shaft. In order to support the structure, a bearing is provided. Near one end of the reverse propeller blade, a bearing 500 with a large radius surrounds a bearing 600 with a small radius. The bearing 500 with a large radius is spaced apart from the bearing 600 with a small radius. The concentricity of the two is difficult to ensure.

[0010] The support bearing 700 near one end of the forward propeller blade (the support bearing 700 is used to connect the forward rotating shaft 200 and the motor housing 400) has its inner and outer rings rotating in opposite directions, which doubles the relative speed. This accelerates the wear of the bearing balls and reduces their service life.

[0011] The forward rotor housing 100 and the motor housing 400 have different radii and different moments of inertia during rotation, and the reverse torques generated by each cannot completely offset each other. It is necessary to adjust the speed ratio through the internal control system to completely offset the reverse torques, which increases the complexity of the control system, the structure is relatively complex, and the production process is cumbersome, making it unsuitable for large-scale industrial production. Utility Model Content

[0012] In response to the above-mentioned deficiencies in the related art, the purpose is to provide a propeller suitable for low-altitude vehicles to solve the technical problems in the related art, such as the unbalanced steering torque generated by the forward and reverse propeller blades, the need to adjust the speed ratio, the relatively complex structure, the relatively poor structural reliability, the relatively high noise, the relatively poor stability, and the relatively short service life;

[0013] The technical solution to achieve the purpose is: a propeller suitable for low-altitude vehicles, comprising:

[0014] intermediate support members;

[0015] a main shaft, which is passed through the intermediate support and tightly matched with the intermediate support, and both ends of the main shaft protrude from the outside of the intermediate support;

[0016] a first propeller blade assembly, sleeved on one end of the main shaft and spaced apart from the intermediate support member;

[0017] a second propeller blade assembly, sleeved on the other end of the main shaft and spaced apart from the intermediate support member, wherein the second propeller blade assembly rotates in a direction opposite to that of the first propeller blade assembly;

[0018] Two connecting members are symmetrically arranged, one connecting member connects the main shaft and the first propeller blade assembly, and the other connecting member connects the main shaft and the second propeller blade assembly;

[0019] Two shields are symmetrically arranged, one shield is connected to the first propeller blade assembly and covers one of the connecting parts, and the other shield is connected to the second propeller blade assembly and covers the other of the connecting parts;

[0020] And two motor assemblies are symmetrically arranged, one motor assembly is connected to the intermediate support and the first propeller blade assembly, and the other motor assembly is connected to the intermediate support and the second propeller blade assembly, the motor assembly is linked to the first propeller blade assembly to rotate forward or reverse with the main shaft and the connecting member as the rotation center, and the motor assembly is linked to the second propeller blade assembly to rotate reverse or forward with the main shaft and the connecting member as the rotation center.

[0021] Furthermore, the intermediate support member includes a main housing, wherein the middle portion of the main housing is sleeved on the main shaft and tightly matched with the main shaft, and the main housing has two first grooves, which are symmetrically spaced and used to connect a portion of the motor assembly;

[0022] and a ring body connected to the outer edge of the main shell and used for connecting the low-altitude vehicle.

[0023] Furthermore: the first propeller blade assembly and the second propeller blade assembly have the same structure, and both include: a first end cover, a first stepped through hole is provided in the middle of the first end cover, the first stepped through hole is sleeved on the end of the main shaft, and is used to set the connecting member and connect the shield, and the first end cover is also provided with a second groove, the second groove is spaced apart from the first stepped through hole, and is used to connect to another part of the motor assembly;

[0024] A plurality of side connection clips are spaced apart and arranged on the outer edge of the first end cover;

[0025] A plurality of first blades are arranged one-to-one with the side connecting clamp, one end of the first blade is clamped in the side connecting clamp, and the other end is away from the side connecting clamp;

[0026] and a plurality of locking members connecting the side connecting clamp and the first fan blade.

[0027] Further: the side connecting clamp includes: two convex plates, one end of the convex plate is connected to the outer edge of the first end cover, and the other end is away from the outer edge of the first end cover, and there is a card slot between the convex plates, and the card slot accommodates one end of the first fan blade.

[0028] Furthermore: the locking member includes: a fastening pin, which is plugged into the convex plate and the first fan blade; and a first screw, which is spaced apart from the fastening pin and connects the convex plate and the first fan blade.

[0029] Further: the connecting member includes: a first bearing connected to the first stepped through hole, connecting the main shaft and the first end cover;

[0030] a bearing pressure plate, disposed at the first stepped through hole, pressing the outer ring of the first bearing;

[0031] A plurality of second screws are arranged at intervals and are threadedly connected to the first end cover to press the bearing pressure plate;

[0032] a shaft sleeve, disposed at the first stepped through hole, sleeved on the main shaft, and resting against the inner ring of the first bearing;

[0033] A locking nut connected to the main shaft to press the sleeve;

[0034] And an axle pin is plugged into the axle through hole on the main shaft to block the locking nut.

[0035] Furthermore: the shield includes: a first plug-in end, which is a circular ring structure and is used to be plugged into the first stepped through hole; and a first cover body, which is a conical structure and is connected to the first plug-in end.

[0036] Furthermore: the motor assembly includes: a first stator, arranged in the first groove; and a first rotor, arranged in the second groove, spaced apart from the first stator.

[0037] Further: the intermediate support member includes: at least two partitions;

[0038] an injection molded body connecting the partition and a portion of the motor assembly;

[0039] and a buckle wrapped around the injection molded body for connecting the low-altitude carrier.

[0040] Furthermore: the first propeller blade assembly and the second propeller blade assembly have the same structure, and both include: a second end cover, a second stepped through hole is provided in the middle of the second end cover, the second stepped through hole is sleeved on the end of the main shaft, and is used to set the connecting member, and one side of the second end cover is connected to the shield, and the other side has a third groove, and the third groove is used to connect to another part of the motor assembly;

[0041] and a plurality of second blades connected to the outer edge of the second end cover at intervals.

[0042] Further: the connecting member includes: a second bearing, arranged at the second stepped through hole, connecting the main shaft and the second end cover;

[0043] a third bearing, disposed at the second stepped through hole, spaced apart from the second bearing, connecting the main shaft and the second end cover, and in contact with the injection molded body, with the inner ring thereof pressed by the injection molded body;

[0044] A pressing sleeve, which is sleeved on the main shaft and presses the inner ring of the second bearing;

[0045] and a locking pin, which is plugged into the pressing sleeve and the main shaft to connect the pressing sleeve and the main shaft.

[0046] Furthermore: the shield includes: a second plug-in end, which is a circular ring structure and is used to be plugged into one side of the second end cover; and a second cover body, which is a hemispherical structure and is connected to the second plug-in end.

[0047] Furthermore: the motor assembly includes: a second stator, which, together with the partition, is molded as a whole by the injection molding body, and the partition separates the second stator, and one side edge of the partition protrudes from the outer edge of the second stator;

[0048] and a second rotor, which is arranged in the third groove and spaced apart from the second stator.

[0049] The above technical solution has the following beneficial effects: a propeller suitable for low-altitude vehicles, compared with the related art, is provided with an intermediate support member, a main shaft, a first propeller blade assembly, a second propeller blade assembly, a connecting member, a shield and a motor assembly;

[0050] The intermediate support and the main shaft form a reliable support structure, which is conducive to connecting and supporting other components;

[0051] The shield forms a barrier protection to prevent dust and other substances from entering the connector, and can also reduce the volatilization of lubricating grease at the connector, thereby improving stability;

[0052] The motor assembly is linked to the first propeller blade assembly to rotate forward (reverse) with the main shaft and the connecting member as the rotation center, and the motor assembly is linked to the second propeller blade assembly to rotate reverse (forward) with the main shaft and the connecting member as the rotation center. Since the main shaft is in a fixed state, the rotation direction of the first propeller blade assembly is opposite to the rotation direction of the second propeller blade assembly, and the steering torque generated can offset the balance, without adjusting the speed ratio. The structure is relatively simple, the structural reliability is relatively good, the noise is relatively small, the stability is relatively good, and the service life is relatively long;

[0053] This overcomes the technical problems that the steering torque generated by the forward propeller blades and the reverse propeller blades cannot be balanced, the speed ratio needs to be adjusted, the structure is relatively complex, the structural reliability is relatively poor, the noise is relatively loud, the stability is relatively poor, and the service life is relatively short. The steering torque generated by the forward propeller blades and the reverse propeller blades can be balanced, the speed ratio does not need to be adjusted, the structure is relatively simple, the structural reliability is relatively good, the noise is relatively low, the stability is relatively good, the service life is relatively long, and the technical effect of having good power density, torque density and load ratio is achieved, which is practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Figure 1 This is one of the final assembly exploded views;

[0055] Figure 2 for Figure 1 Schematic diagram of the combined structure;

[0056] Figure 3 for Figure 2 A partial cross-sectional view of

[0057] Figure 4 One of the structural diagrams of the main axis;

[0058] Figure 5 This is the second exploded view of the final assembly;

[0059] Figure 6 for Figure 5 Schematic diagram of the assembled structure;

[0060] Figure 7 for Figure 6 A partial cross-sectional view of

[0061] Figure 8 It is a partial cross-sectional view of the prior art;

[0062] In the figure: 10. Intermediate support member, 11. Main shell, 11-1. First groove, 11-2. First wire outlet, 12. Ring body, 101. Partition, 102. Injection molding body, 103. Buckle, 103-1. Second wire outlet, 20. Main shaft, 21. Shaft through hole, 30. First propeller blade assembly, 31. First end cover, 31-1. First stepped through hole, 31-2. Second groove, 32. Side connecting clamp, 32-1. Protruding plate, 32-11. Slot, 33. First blade, 34. Locking member, 34-1. Fastening pin, 34-2. First screw, 301. Second end cover, 301-1. Second stepped through hole, 301-2. Third groove, 302. Second blade, 40. Second propeller Blade assembly, 50. Connector, 51. First bearing, 52. Bearing pressure plate, 53. Second screw, 54. Bushing, 55. Locking nut, 56. Axle pin, 501. Second bearing, 502. Third bearing, 503. Press sleeve, 504. Locking pin, 60. Protective cover, 61. First plug end, 62. First cover body, 601. Second plug end, 602. Second cover body, 70. Motor assembly, 71. First stator, 72. First rotor, 701. Second stator, 702. Second rotor, 100. Forward rotor housing, 200. Forward rotating shaft, 300. Forward drive member fixing plate, 400. Motor housing, 500. Bearing with large radius, 600. Bearing with small radius, 700. Support bearing. DETAILED DESCRIPTION

[0063] In order to make the content easier to understand, the following is a further detailed description based on specific embodiments and in conjunction with the accompanying drawings;

[0064] A propeller suitable for low-altitude vehicles solves the technical problems in related technologies such as the unbalanced steering torque generated by the forward and reverse propeller blades, the need to adjust the speed ratio, the relatively complex structure, the relatively poor structural reliability, the relatively high noise, the relatively poor stability, and the relatively short service life. The propeller can be manufactured and used, and achieves the positive effects of balancing the steering torque generated by the forward and reverse propeller blades, not requiring adjustment of the speed ratio, having a relatively simple structure, relatively good structural reliability, relatively low noise, relatively good stability, and a relatively long service life, and having good power density, torque density, and load ratio. The overall concept is as follows:

[0065] One implementation method:

[0066] like Figure 1 、 Figure 2 、 Figure 5 、 Figure 6 、 Figure 8 As shown; A propeller suitable for a low-altitude vehicle, comprising:

[0067] Intermediate support 10;

[0068] The main shaft 20 is passed through the intermediate support 10 and is tightly fitted with the intermediate support 10, and both ends of the main shaft 20 protrude from the outside of the intermediate support 10;

[0069] A first propeller blade assembly 30 is sleeved on one end of the main shaft 20 and spaced apart from the intermediate support member 10;

[0070] a second propeller blade assembly 40, which is sleeved on the other end of the main shaft 20 and spaced apart from the intermediate support member 10; and a rotation direction of the second propeller blade assembly 40 is opposite to that of the first propeller blade assembly 30;

[0071] Two connecting members 50 are symmetrically arranged, one connecting member 50 connects the main shaft 20 and the first propeller blade assembly 30, and the other connecting member 50 connects the main shaft 20 and the second propeller blade assembly 40;

[0072] Two shields 60 are symmetrically arranged, one shield 60 is connected to the first propeller blade assembly 30 and covers one of the connecting members 50, and the other shield 60 is connected to the second propeller blade assembly 40 and covers the other of the connecting members 50;

[0073] and two motor assemblies 70, symmetrically arranged, one of the motor assembly 70 being connected to the intermediate support 10 and the first propeller blade assembly 30, and the other of the motor assembly 70 being connected to the intermediate support 10 and the second propeller blade assembly 40, the motor assembly 70 being linked to the first propeller blade assembly 30 to rotate forward or reverse with the main shaft 20 and the connecting member 50 as the rotation center, and the motor assembly 70 being linked to the second propeller blade assembly 40 to rotate forward or reverse with the main shaft 20 and the connecting member 50 as the rotation center;

[0074] Specifically, during implementation, the intermediate support member 10 and the main shaft 20 form a reliable support structure that facilitates the connection and support of other components;

[0075] The shield 60 forms a barrier to prevent dust and the like from entering the connector 50 , and can also reduce the volatilization of lubricating grease at the connector 50 , thereby improving stability.

[0076] The motor assembly 70 drives the first propeller blade assembly 30 to rotate forward (reverse) with the main shaft 20 and the connecting member 50 as the rotation center. The motor assembly 70 drives the second propeller blade assembly 40 to rotate reverse (forward) with the main shaft 20 and the connecting member 50 as the rotation center. Since the main shaft 20 is in a fixed state, the rotation direction of the first propeller blade assembly 30 is opposite to the rotation direction of the first propeller blade assembly 40. The generated steering torque can offset the balance, and there is no need to adjust the speed ratio. The structure is relatively simple, the structural reliability is relatively good, the noise is relatively low, the stability is relatively good, and the service life is relatively long.

[0077] Another embodiment:

[0078] like Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 As shown; in implementation, the intermediate support member 10 includes: a main housing 11, the middle position of the main housing 11 is sleeved on the main shaft 20, tightly fitting with the main shaft 20, and the main housing 11 has two first grooves 11-1, the first grooves 11-1 are symmetrically spaced, and the first grooves 11-1 are used to connect with a part of the motor assembly 70; and a ring body 12, connected to the outer edge of the main housing 11, for connecting with the low-altitude vehicle;

[0079] The intermediate support member 10 is made of a lightweight and high-strength material such as aluminum alloy or aluminum-magnesium alloy, and the main shell 11 and the ring body 12 are integrally formed, so the structural reliability is relatively good;

[0080] The ring body 12 is connected to a low-altitude carrier by inserting bolts (the carrier refers to a carrying tool, and the carrier is a common structure in the prior art, such as a box-shaped carrier, a vehicle-shaped carrier, an aircraft fuselage-shaped carrier, etc.), and installation and disassembly are relatively convenient;

[0081] The main housing 11 also has a first wire outlet 11-2, which is convenient for passing the wires on the first stator 71 out;

[0082] The main shaft 20 is a stepped shaft, and the main shaft 20 is tightly fitted with the intermediate support member 10 (the two have an interference fit). The main shaft 20 is in a fixed state, and together with the intermediate support member 10, forms a reliable support structure, so that the first propeller blade assembly 30 and the second propeller blade assembly 40 have better stability during rotation, relatively low noise, and relatively long service life;

[0083] The main shaft 20 is provided with a shaft through hole 21, which is a round through hole, which is convenient for inserting the shaft pin 56 and is relatively easy to assemble;

[0084] Among them, the first propeller blade assembly 30 and the second propeller blade assembly 40 have the same structure, both of which include: a first end cover 31, a first stepped through hole 31-1 is provided in the middle position of the first end cover 31, the first stepped through hole 31-1 is sleeved on the end of the main shaft 20, and is used to set the connecting member 50 to connect the shield 60, and the first end cover 31 is also provided with a second groove 31-2, the second groove 31-2 is spaced apart from the first stepped through hole 31-1, and is used to connect another part of the motor assembly 70; a plurality of side connecting clamps 32 are spaced apart on the outer edge of the first end cover 31; a plurality of first fan blades 33 are arranged one-to-one with the side connecting clamps 32, one end of the first fan blade 33 is clamped in the side connecting clamp 32, and the other end is away from the side connecting clamp 32; and a plurality of locking members 34 are connected to the side connecting clamp 32 and the first fan blade 33;

[0085] The first end cover 31 has a circular shape;

[0086] A first stepped through hole 31 - 1 is provided, which is convenient for arranging the connecting member 50 and the connecting shield 60 ;

[0087] The second groove 31 - 2 is provided to facilitate accommodating the first rotor 72 , making full use of the space and having a relatively simple structure;

[0088] The side connecting clamp 32 includes: two protruding plates 32-1, one end of each protruding plate 32-1 is connected to the outer edge of the first end cover 31, and the other end is away from the outer edge of the first end cover 31. A slot 32-11 is defined between the protruding plates 32-1, and the slot 32-11 accommodates one end of the first fan blade 33. There are four side connecting clamps 32; the protruding plates 32-1 are rectangular plate-shaped structures and are integrally formed with the first end cover 31; the slot 32-11 facilitates accommodating one end of the first fan blade 33, making assembly relatively convenient.

[0089] The number of the first blades 33 is four;

[0090] The locking member 34 includes: a fastening pin 34-1, which is plugged into the protruding plate 32-1 and the first fan blade 33; and a first screw 34-2 is arranged at an interval with the fastening pin 34-1 to connect the protruding plate 32-1 and the first fan blade 33; there are four locking members 34; the fastening pin 34-1 is a pin shaft in the prior art, which is plugged into the protruding plate 32-1 and the first fan blade 33 to connect the protruding plate 32-1 and the first fan blade 33; the first screw 34-2 is a hexagon socket bolt threadedly connected to the protruding plate 32-1 and passes through one end of the first fan blade 33 to connect the protruding plate 32-1 and the first fan blade 33; the provision of the locking member 34 has good connection reliability, the first fan blade 33 will not be disengaged, and installation and disassembly are relatively convenient;

[0091] The first propeller blade assembly 30 and the second propeller blade assembly 40 have the same structure. When the first propeller blade assembly 30 rotates forward (reverse), the second propeller blade assembly 40 rotates reverse (forward). The generated steering torque can offset the balance, and there is no need to adjust the speed ratio. The stability is relatively good.

[0092] The connecting member 50 includes: a first bearing 51 connected to the first stepped through hole 31-1, connecting the main shaft 20 and the first end cover 31; a bearing pressure plate 52, provided at the first stepped through hole 31-1, pressing the outer ring of the first bearing 51; a plurality of second screws 53, spaced apart and threadedly connected to the first end cover 31, pressing the bearing pressure plate 52; a sleeve 54, provided at the first stepped through hole 31-1, sleeved on the main shaft 20, abutting the inner ring of the first bearing 51; a locking nut 55, connected to the main shaft 20, pressing the sleeve 54; and a shaft pin 56, plugged into the shaft through hole 21 on the main shaft 20, blocking the locking nut 55;

[0093] The first bearing 51 is a common structure in the prior art, such as a double-row angular contact ball bearing, which is used to connect the main shaft 20 and the first end cover 31. The connection reliability is good, and the first end cover 31 can rotate smoothly.

[0094] The bearing pressure plate 52 is a circular plate-shaped structure;

[0095] The second screw 53 is a hexagon socket bolt, which is threadedly connected to the first end cover 31 to press the bearing pressure plate 52, so that the bearing pressure plate 52 can press the outer ring of the first bearing 51 to prevent the first bearing 51 from moving at the first stepped through hole 31-1. The structural reliability is relatively good;

[0096] The shaft sleeve 54 is sleeved on the main shaft 20 and abuts against the inner ring of the first bearing 51 to limit the inner ring of the first bearing 51 and prevent the first bearing 51 from moving. The structural reliability is relatively good.

[0097] The inner and outer rings of the first bearing 51 are limited. When the first propeller blade assembly 30 and the second propeller blade assembly 40 rotate, the outer ring of the first bearing 51 rotates together with the first propeller blade assembly 30 and the second propeller blade assembly 40, while the inner ring does not move. This provides relatively good stability and prevents the first propeller blade assembly 30 and the second propeller blade assembly 40 from shaking.

[0098] The two first bearings 51 are symmetrically connected to the main shaft 20, and the coaxiality is relatively good, thereby improving stability;

[0099] The locking nut 55 is a hexagonal nut that is threadedly connected to the main shaft 20 and presses the sleeve 54 so that the sleeve 54 can be positioned at the inner ring of the first bearing 51;

[0100] The shaft pin 56 is a common structure in the prior art, such as a cotter pin, which is inserted into the shaft through hole 21 to form a barrier to prevent the locking nut 55 from loosening;

[0101] A connecting member 50 is provided to facilitate connection between the main shaft 20 and the first propeller blade assembly 30, and to facilitate connection between the main shaft 20 and the second propeller blade assembly 40, making assembly relatively convenient;

[0102] The shield 60 includes: a first plug end 61 having a circular ring structure for plugging into the first stepped through hole 31-1; and a first cover body 62 having a conical structure for connecting to the first plug end 61. The first plug end 61 and the first cover body 62 are integrally formed, and the first plug end 61 is plugged into and tightly fitted with the first stepped through hole 31-1, making assembly relatively convenient.

[0103] The shield 60 is provided to provide a barrier and protection to prevent dust and the like from entering the connecting member 50 , and can also reduce the volatilization of lubricating grease in the connecting member 50 (the rotation of the first propeller blade assembly 30 and the second propeller blade assembly 40 accelerates air circulation, which in turn accelerates the volatilization of lubricating grease), thereby avoiding dry grinding at the first bearing 51 and improving stability;

[0104] The motor assembly 70 includes: a first stator 71 disposed in the first groove 11 - 1 ; and a first rotor 72 disposed in the second groove 31 - 2 and spaced apart from the first stator 71 .

[0105] The first stator 71 is interference-fitted in the first groove 11-1. The first stator 71 and the main housing 11 do not move relative to each other, resulting in relatively good structural reliability, full utilization of space, and a relatively compact structure. The two first stators 71 are separated by the main housing 11, which can prevent mutual interference of magnetic fields and ensure the performance of the motor assembly 70. The first rotor 72 is tightly fitted in the second groove 31-2 or bonded with glue, fully utilizing space and having a relatively compact structure.

[0106] The motor assembly 70 is a conventional structure in the prior art, and is used to drive the first propeller blade assembly 30 to rotate forward (or reverse) about the main shaft 20 and the connecting member 50, and to drive the second propeller blade assembly 40 to rotate reverse (or forward) about the main shaft 20 and the connecting member 50. The rotational inertia generated by the rotation of the first propeller blade assembly 30 and the second propeller blade assembly 40 is the same, so the reverse torque can be offset, resulting in a relatively simple internal control system and a more compact structure.

[0107] Another embodiment:

[0108] like Figure 5、 Figure 6 、 Figure 7 As shown; in implementation, the intermediate support member 10 includes: at least two partitions 101; an injection molded body 102, connecting the partition 101 and a portion of the motor assembly 70; and a buckle 103, wrapped around the injection molded body 102, for connecting the low-altitude carrier;

[0109] The partition 101 is a steel plate, which not only ensures structural strength, but also separates the second stator 701 to prevent magnetic field interference, thereby ensuring the performance of the motor assembly 70;

[0110] The partition 101 and the second stator 701 are sealed as a whole by the injection molded body 102, and the structural reliability is relatively good and the assembly is relatively convenient;

[0111] One side edge of the partition 101 protrudes from the outer edge of the second stator 701, which is conducive to positioning the buckle 103 and the connection reliability is relatively good;

[0112] The buckle 103 is wrapped around the injection molded body 102, and together with the injection molded body 102, the partition 101 and the second stator 701, forms a relatively integral whole, with relatively high structural strength and relatively easy assembly;

[0113] The buckle 103 also has a second wire outlet 103-1, which is convenient for passing the wires on the second stator 701 out;

[0114] The shaft 20 is a stepped shaft. The main shaft 20 is tightly fitted with the intermediate support member 10 (interference fit). The main shaft 20 is in a fixed state and forms a reliable support structure together with the intermediate support member 10. This makes the first propeller blade assembly 30 and the second propeller blade assembly 40 more stable during rotation, with relatively low noise and a relatively long service life.

[0115] The first propeller blade assembly 30 and the second propeller blade assembly 40 have the same structure and both include: a second end cover 301, a second stepped through hole 301-1 is formed in the middle of the second end cover 301, the second stepped through hole 301-1 is sleeved on the end of the main shaft 20 and is used to set the connecting member 50, and one side of the second end cover 301 is connected to the shield 60, and the other side has a third groove 301-2, the third groove 301-2 is used to connect to another part of the motor assembly 70; and a plurality of second blades 302 are connected to the outer edge of the second end cover 301 at intervals;

[0116] The second end cover 301 has a circular shape;

[0117] There are four second blades 302 , which are integrally formed with the second end cover 301 ;

[0118] The second stepped through hole 301-1 is provided to facilitate the installation of the connector 50 and facilitate assembly.

[0119] The third groove 301-2 is provided to facilitate connection with the second rotor 702, making full use of space and having a relatively simple structure;

[0120] The first propeller blade assembly 30 and the second propeller blade assembly 40 have the same structure. When the first propeller blade assembly 30 rotates forward (reverse), the second propeller blade assembly 40 rotates reverse (forward). The generated steering torque can offset the balance, and there is no need to adjust the speed ratio. The stability is relatively good.

[0121] The connecting member 50 includes: a second bearing 501, which is provided at the second stepped through hole 301-1 and connects the main shaft 20 and the second end cover 301; a third bearing 502, which is provided at the second stepped through hole 301-1 and is spaced apart from the second bearing 501, connects the main shaft 20 and the second end cover 301, and contacts the injection molded body 102, and is pressed by the injection molded body 102 at its inner ring; a pressing sleeve 503, which is sleeved on the main shaft 20 and presses the inner ring of the second bearing 501; and a locking pin 504, which is plugged into the pressing sleeve 503 and the main shaft 20 and connects the pressing sleeve 503 and the main shaft 20;

[0122] The second bearing 501 or the third bearing 502 is a common structure in the prior art, such as a deep groove ball bearing, which is used to connect the main shaft 20 and the first propeller blade assembly 30, and to connect the main shaft 20 and the second propeller blade assembly 40. The structure has good reliability, allowing the first propeller blade assembly 30 and the second propeller blade assembly 40 to rotate smoothly.

[0123] The pressing sleeve 503 presses the inner ring of the second bearing 501, so that the second bearing 501 is positioned and the second bearing 501 will not be separated from the main shaft 20, and the structural reliability is relatively good;

[0124] The locking pin 504 is a common structure in the prior art, such as a cylindrical pin, which makes the connection between the pressing sleeve 503 and the main shaft 20 more reliable and prevents the pressing sleeve 503 from being separated from the main shaft 20;

[0125] The combination of the second bearing 501, the third bearing 502, the pressing sleeve 503 and the locking pin 504 facilitates assembly, enabling the first propeller blade assembly 30 and the second propeller blade assembly 40 to rotate smoothly. Furthermore, the first propeller blade assembly 30 and the second propeller blade assembly 40 will not fly out during rotation, and thus have relatively good stability.

[0126] The shield 60 includes: a second plug end 601, which is a circular ring structure and is used to plug into one side of the second end cover 301; and a second cover body 602, which is a hemispherical structure and is connected to the second plug end 601;

[0127] The second plug end 601 and the second cover body 602 are integrally formed, and the second plug end 601 is plugged and tightly fitted with the second end cover 301, so the assembly is relatively convenient;

[0128] The shield 60 provides a barrier and protection to prevent dust and the like from entering the connecting member 50 , and can also reduce the volatilization of lubricating grease from the connecting member 50 (the rotation of the first propeller blade assembly 30 and the second propeller blade assembly 40 accelerates air circulation, which in turn accelerates the volatilization of lubricating grease), thereby avoiding dry grinding at the second bearing 501 and the third bearing 502 and improving stability;

[0129] The motor assembly 70 includes: a second stator 701, which is integrally encapsulated with the partition 101 by the injection molding body 102, and the partition 101 separates the second stator 701, with one side edge of the partition 101 protruding from the outer edge of the second stator 701; and a second rotor 702, which is disposed in the third groove 301-2 and spaced apart from the second stator 701.

[0130] The second rotor 702 is tightly fitted in the third groove 301 - 2 and forms a relatively integral body with the second end cover 301 , making full use of space and having a relatively compact structure;

[0131] The motor assembly 70 is a conventional structure in the prior art, and is used to drive the first propeller blade assembly 30 to rotate forward (or reverse) about the main shaft 20 and the connecting member 50, and to drive the second propeller blade assembly 40 to rotate reverse (or forward) about the main shaft 20 and the connecting member 50. The rotational inertia generated by the rotation of the first propeller blade assembly 30 and the second propeller blade assembly 40 is the same, so the reverse torque can be offset, resulting in a relatively simple internal control system and a more compact structure.

[0132] In the description, it should be understood that the terms "upper", "lower", "left", "right", "front", "back", etc. indicating directions or positional relationships are based on the positional relationships shown in the drawings and are only used to facilitate or simplify the description, and do not necessarily indicate specific directions. The operating procedures described in the embodiments are not absolute steps for use and may be adjusted accordingly in actual use.

[0133] Unless otherwise defined, the technical or scientific terms used herein shall have the ordinary meanings understood by persons of ordinary skill in the relevant art. The terms "first," "second," and similar words used in the specification and claims do not denote any order, quantity, or importance, but are merely used to distinguish different components. Similarly, the terms "a" or "an" and similar words do not necessarily indicate a limit on quantity, but rather indicate the presence of at least one, which shall be determined based on the content of the embodiments.

[0134] The above is only a preferred specific implementation method, but the scope of protection is not limited to this. Any technician familiar with this technical field can make equivalent replacements or changes based on the technical solutions and inventive concepts within the disclosed technical scope, which should be covered by the scope of protection.

Claims

1. A propeller suitable for low-altitude vehicles, characterized in that: include: an intermediate support member (10); A main shaft (20) is passed through the intermediate support member (10) and is tightly fitted with the intermediate support member (10), and both ends of the main shaft (20) protrude outside the intermediate support member (10); A first propeller blade assembly (30) is sleeved on one end of the main shaft (20) and is spaced apart from the intermediate support member (10); a second propeller blade assembly (40) sleeved on the other end of the main shaft (20) and spaced apart from the intermediate support member (10); the rotation direction of the second propeller blade assembly (40) is opposite to the rotation direction of the first propeller blade assembly (30); Two connecting members (50) are symmetrically arranged, one connecting member (50) connects the main shaft (20) and the first propeller blade assembly (30), and the other connecting member (50) connects the main shaft (20) and the second propeller blade assembly (40); Two shields (60) are symmetrically arranged, one shield (60) is connected to the first propeller blade assembly (30) and covers one connecting member (50), and the other shield (60) is connected to the second propeller blade assembly (40) and covers the other connecting member (50); and two motor assemblies (70) symmetrically arranged, one motor assembly (70) being connected to the intermediate support member (10) and the first propeller blade assembly (30), and the other motor assembly (70) being connected to the intermediate support member (10) and the second propeller blade assembly (40), the motor assembly (70) being linked to the first propeller blade assembly (30) to rotate forward or reverse with the main shaft (20) and the connecting member (50) as the rotation center, and the motor assembly (70) being linked to the second propeller blade assembly (40) to rotate reverse or forward with the main shaft (20) and the connecting member (50) as the rotation center.

2. A propeller suitable for low-altitude vehicles according to claim 1, characterized in that: The intermediate support member (10) comprises: a main housing (11), wherein the middle position of the main housing (11) is sleeved on the main shaft (20) and is tightly matched with the main shaft (20), and the main housing (11) has two first grooves (11-1), the first grooves (11-1) are symmetrically spaced, and the first grooves (11-1) are used to connect a part of the motor assembly (70); and a ring body (12) connected to the outer edge of the main shell (11) and used for connecting to the low-altitude vehicle.

3. The propeller suitable for low-altitude vehicles according to claim 2, characterized in that: The first propeller blade assembly (30) and the second propeller blade assembly (40) have the same structure, and both include: a first end cover (31), a first stepped through hole (31-1) at a middle position of the first end cover (31), the first stepped through hole (31-1) being sleeved on the end of the main shaft (20) for arranging the connecting member (50) and connecting the shield (60), and a second groove (31-2) is further provided on the first end cover (31), the second groove (31-2) being spaced apart from the first stepped through hole (31-1) and being used for connecting another part of the motor assembly (70); A plurality of side connection clamps (32) are arranged at intervals on the outer edge of the first end cover (31); A plurality of first blades (33) are arranged one-to-one with the side connection clamp (32), one end of the first blade (33) is clamped in the side connection clamp (32), and the other end is away from the side connection clamp (32); and a plurality of locking members (34) connecting the side connection clamp (32) and the first fan blade (33).

4. The propeller suitable for low-altitude vehicles according to claim 3, characterized in that: The side connection clamp (32) comprises: two convex plates (32-1), one end of the convex plate (32-1) is connected to the outer edge of the first end cover (31), and the other end is away from the outer edge of the first end cover (31), and a clamping groove (32-11) is provided between the convex plates (32-1), and the clamping groove (32-11) accommodates one end of the first fan blade (33).

5. The propeller suitable for low-altitude vehicles according to claim 4, characterized in that: The locking member (34) comprises: a fastening pin (34-1) plugged into the convex plate (32-1) and the first fan blade (33); and a first screw (34-2) spaced apart from the fastening pin (34-1) and connecting the convex plate (32-1) and the first fan blade (33).

6. The propeller suitable for low-altitude vehicles according to claim 5, characterized in that: The connecting member (50) comprises: a first bearing (51), connected to the first stepped through hole (31-1), connecting the main shaft (20) and the first end cover (31); A bearing pressure plate (52) is provided at the first stepped through hole (31-1) and presses the outer ring of the first bearing (51); A plurality of second screws (53) are spaced apart and threadedly connected to the first end cover (31) to press the bearing pressure plate (52); A shaft sleeve (54) is provided at the first stepped through hole (31-1), sleeved on the main shaft (20), and abutting against the inner ring of the first bearing (51); A locking nut (55) is connected to the main shaft (20) and presses the shaft sleeve (54); And an axle pin (56) is plugged into the axle through hole (21) on the main shaft (20) to block the locking nut (55).

7. The propeller suitable for low-altitude vehicles according to claim 6, characterized in that: The shield (60) comprises: a first plug end (61) having a circular ring structure, used for plugging into the first stepped through hole (31-1); and a first shield body (62) having a conical structure, connected to the first plug end (61).

8. The propeller suitable for low-altitude vehicles according to claim 7, characterized in that: The motor assembly (70) comprises: a first stator (71) disposed in the first groove (11-1); and a first rotor (72) disposed in the second groove (31-2) and spaced apart from the first stator (71).

9. The propeller suitable for low-altitude vehicles according to claim 1, characterized in that: The intermediate support member (10) comprises: at least two partitions (101); An injection molded body (102) connecting the partition (101) and a portion of the motor assembly (70); and a buckle (103) wrapped around the injection molded body (102) for connecting to the low-altitude vehicle.

10. The propeller suitable for low-altitude vehicles according to claim 9, characterized in that: The first propeller blade assembly (30) and the second propeller blade assembly (40) have the same structure, both comprising: a second end cover (301), a second stepped through hole (301-1) at a middle position of the second end cover (301), the second stepped through hole (301-1) being sleeved on the end of the main shaft (20) for arranging the connecting member (50), and one side of the second end cover (301) being connected to the shield (60), and the other side having a third groove (301-2), the third groove (301-2) being used to connect to another part of the motor assembly (70); and a plurality of second blades (302) connected at intervals to the outer edge of the second end cover (301).

11. The propeller suitable for low-altitude vehicles according to claim 10, characterized in that: The connecting member (50) comprises: a second bearing (501), arranged at the second stepped through hole (301-1), connecting the main shaft (20) and the second end cover (301); a third bearing (502), arranged at the second stepped through hole (301-1), spaced apart from the second bearing (501), connecting the main shaft (20) and the second end cover (301), and in contact with the injection molded body (102), with the inner ring of the third bearing (502) being pressed by the injection molded body (102); A pressing sleeve (503) is sleeved on the main shaft (20) to press the inner ring of the second bearing (501); and a locking pin (504) plugged into the pressing sleeve (503) and the main shaft (20) to connect the pressing sleeve (503) and the main shaft (20).

12. The propeller suitable for low-altitude vehicles according to claim 11, characterized in that: The shield (60) comprises: a second plug end (601) having a circular ring structure, used for plugging with one side of the second end cover (301); and a second cover body (602) having a hemispherical structure, connected to the second plug end (601).

13. The propeller suitable for low-altitude vehicles according to claim 12, characterized in that: The motor assembly (70) comprises: a second stator (701), which, together with the partition (101), is molded into a whole by the injection molding body (102), and the partition (101) separates the second stator (701), and an edge of one side of the partition (101) protrudes from the outer edge of the second stator (701); and a second rotor (702) disposed in the third groove (301-2) and spaced apart from the second stator (701).

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