drive device

Abstract

This invention relates to the field of aircraft technology, specifically to a drive device. The drive device includes: a housing having a receiving space and a first opening and a second opening communicating with the receiving space; a stator disposed in the receiving space and fixed to the inner wall of the housing; a rotor sleeved in the stator and electromagnetically connected to the stator, with a first end extending into the first opening; and a gear disposed in the receiving space, meshing with both the rotor and the output propeller shaft, with a first end extending outside the second opening and a driven component mounted on the first end of the output propeller shaft. In this invention, the power input to the rotor is reduced by the gear, and the output propeller shaft outputs speed and power to drive the driven component. This integrates the rotor and the reducer into a single housing, reducing the overall weight and volume of the device, effectively improving the load-bearing capacity for flight loads, reducing the output speed of high-power, high-speed motors, and making it suitable for propeller drives of large-tonnage aircraft.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a drive system. Background Technology

[0002] With the rapid development of the low-altitude economy, multi-rotor aircraft powered by electricity have broad market prospects. Currently, due to the relatively low power of direct-drive motors, large-tonnage electric aircraft typically require multiple low-power motors to drive the rotor blades simultaneously, resulting in a complex control system. While using high-power, high-torque motors could reduce the number of motors, their excessive weight and size would reduce the aircraft's payload and affect its performance. Summary of the Invention

[0003] This invention provides a drive device to solve the problem that existing high-power, high-torque motors are too heavy and bulky, and that direct mounting on aircraft would reduce the effective payload of the aircraft and affect its performance.

[0004] This invention provides a driving device, comprising:

[0005] The shell has a receiving space and a first opening and a second opening communicating with the receiving space; The stator is located in the receiving space and is fixed to the inner wall of the housing; The rotor is fitted inside the stator and is electromagnetically connected to the stator, with the first end of the rotor extending into the first opening; The gear is located in the receiving space and meshes with both the rotor and the output propeller shaft. The first end of the output propeller shaft extends out of the second opening, and the first end of the output propeller shaft is provided with a drive element.

[0006] Beneficial effects: This invention uses a rotor as the power input component of the drive device. The power input from the rotor is reduced by gears and finally output by the output propeller shaft to drive the driven component. Thus, the rotor and reducer are integrated into a single housing, reducing the overall weight and volume of the device, effectively improving the load-bearing capacity for flight loads, reducing the output speed of the high-power high-speed motor, increasing the output torque of the device, and making it suitable for propeller drives of large-tonnage aircraft.

[0007] In one alternative embodiment, the rotor and the output propeller shaft are coaxially arranged, and the axis of the gear is parallel to the axis of the rotor.

[0008] By placing the gear on one side of the rotor and output propeller shaft, the axial length of the housing is reduced while ensuring transmission reliability, thus reducing the overall length of the device in that direction and making the structure more compact.

[0009] In one alternative embodiment, the gear is a planetary gear, including a first tooth and a second tooth spaced apart along the axial direction of the housing. The first tooth meshes with the rotor, and the second tooth meshes with the output propeller shaft.

[0010] The first and second teeth mesh with the rotor and output propeller shaft respectively, achieving two-stage reduction through only one planetary gear. This results in a simple structure, low cost, and more reliable force transmission.

[0011] In one optional embodiment, the output propeller shaft includes a mounting portion and a connecting portion, wherein the mounting portion is provided with gear teeth that mesh with the second gear portion, and the connecting portion is connected to the drive component.

[0012] The purpose of providing a mounting part that meshes with the second tooth is to increase the reduction ratio and further improve the output torque.

[0013] In one optional embodiment, a first support bearing and a second support bearing are provided between the connecting part and the inner wall of the housing. The first support bearing is adapted to withstand radial force, and the second support bearing is adapted to withstand axial force.

[0014] The first and second support bearings ensure an effective rotational connection between the output propeller shaft and the housing. The first and second support bearings bear radial and axial forces respectively, and can withstand bending moments and axial loads transmitted from the driven components, resulting in more uniform and reliable force distribution.

[0015] In one alternative embodiment, a third support bearing and a fourth support bearing are provided between the planetary gear and the inner wall of the housing.

[0016] The planetary gears are rotated and connected to the housing via the third and fourth support bearings at both ends, ensuring the reliability of the transmission.

[0017] In one alternative embodiment, a third support bearing is disposed between the first tooth and the second tooth, and a fourth support bearing is disposed close to the stator.

[0018] Because the first and second teeth are meshed with the rotor and the output propeller shaft respectively, the force is relatively concentrated. Therefore, a third support bearing is added between them to prevent connection failure when the force is large.

[0019] In one alternative embodiment, a fifth support bearing and a sixth support bearing are provided between the rotor and the inner wall of the housing. The fifth support bearing is located near the gear, and the sixth support bearing is located in the first opening.

[0020] As the input end of the driving force, the rotor bears a large force, and the overall size and weight of the rotor are also large. In order to ensure the stability of force transmission, a fifth support bearing and a sixth support bearing are respectively set at both ends of the rotor to achieve a reliable connection between the rotor and the housing.

[0021] In one optional embodiment, the system further includes a first lubrication structure and a second lubrication structure, wherein the first lubrication structure is disposed at the stator and the second lubrication structure is disposed sequentially at the rotor, the gear and the output propeller shaft.

[0022] The stator, rotor, gears, and output propeller shaft each use a set of lubrication structures to ensure lubrication effectiveness and prevent lubrication failure.

[0023] In one alternative implementation, the component to be driven includes a blade.

[0024] The rotor drives the blades to rotate through gears and the output blade shaft, ensuring stable and reliable transmission. Attached Figure Description

[0025] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the driving device according to an embodiment of the present invention.

[0027] Explanation of reference numerals in the attached figures: 1. Housing; 101. Accommodation space; 102. First opening; 103. Second opening; 2. Stator; 3. Rotor; 301. Shaft; 302. Outer rotor; 4. Gear; 401. First tooth; 402. Second tooth; 5. Output propeller shaft; 501. Mounting part; 502. Connecting part; 6. Driven component; 7. First support bearing; 8. Second support bearing; 9. First bearing housing; 10. Third support bearing; 11. Fourth support bearing; 12. Second bearing housing; 13. Fifth support bearing; 14. Sixth support bearing; 15. Third bearing housing; 16. Fourth bearing housing; 17. Propeller hub. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] The following is combined Figure 1 Embodiments of the present invention are described.

[0030] According to an embodiment of the present invention, a drive device is provided for driving propeller blades in a large-tonnage aircraft, comprising: The housing 1 has a receiving space 101 and a first opening 102 and a second opening 103 communicating with the receiving space 101; Stator 2 is disposed in the receiving space 101 and fixed to the inner wall of the housing 1; The rotor 3 is sleeved in the stator 2 and is electromagnetically connected to the stator 2, and the first end of the rotor 3 extends into the first opening 102; Gear 4 is located in the receiving space 101 and is meshed with rotor 3 and output propeller shaft 5. The first end of output propeller shaft 5 extends outside the second opening 103, and the first end of output propeller shaft 5 is provided with a drive member 6.

[0031] like Figure 1 As shown, the housing 1 is typically a one-piece machined cuboid or cylinder made of metal, such as an alloy, possessing a certain compressive strength. The first opening 102 and the second opening 103 are positioned opposite each other at opposite ends of the length of the housing 1 to facilitate connection with the power component and the driven component 6. The stator 2 is positioned near the first opening 102 and is generally cylindrical, housing the rotor 3. A gap is reserved between the stator 2 and the rotor 3. The stator 2 can be fixed to the inner wall of the housing 1 using bolts or other fasteners. When energized, electromagnetic induction occurs between the stator 2 and the rotor 3, thereby driving the rotor 3 to rotate. The rotor 3 includes a centrally located rotating shaft 301 and an outer rotor 302 sleeved on the rotating shaft 301. The rotating shaft 301 and the outer rotor 302 are integrally formed. The first end of the rotating shaft 301 extends into the first opening 102 for easy connection with the power component, and the second end of the rotating shaft 301 extends into the middle of the housing 1. The rotating shaft 301 has a hollow structure to further reduce the weight of the device. Of course, the rotating shaft 301 can also be a solid structure, and no specific limitation is made here. The gear 4 is located near the second end of the rotating shaft 301 for easy connection and force transmission. The first end of the output propeller shaft 5 extends outside the second opening 103 for easy connection with the driven component 6, and the second end of the output propeller shaft 5 is located near the second end of the rotor 3 for easy connection with the gear 4.

[0032] Beneficial effects: The present invention uses rotor 3 as the power input component of the drive device. The power input from rotor 3 is reduced by gear 4 and finally output by output propeller shaft 5 to drive the driven component 6. Thus, rotor 3 and reducer are integrated into a housing 1, which reduces the overall weight and volume of the device, effectively improves the load-bearing capacity of flight loads, reduces the output speed of high-power high-speed motors, increases the output torque of the device, and is suitable for propeller drive of large-tonnage aircraft.

[0033] In one embodiment, the rotor 3 and the output propeller shaft 5 are coaxially arranged, and the axis of the gear 4 is parallel to the axis of the rotor 3.

[0034] like Figure 1 As shown, this embodiment only sets one gear 4. Of course, two or more gears 4 can also be set along the circumference of the housing 1 according to actual needs. In this case, it is necessary to ensure that the multiple gears 4 rotate synchronously and in the same direction so that the driving force is output stably.

[0035] In addition, as an alternative implementation, the output speed can be reduced by means of torque transmission, multi-stage planetary gear transmission or multi-stage cylindrical gear transmission, without specific limitations.

[0036] By placing gear 4 on one side of rotor 3 and output propeller shaft 5, the axial length of housing 1 is reduced while ensuring transmission reliability, thus reducing the overall length of the device in this direction and making the structure more compact.

[0037] In one embodiment, gear 4 is a planetary gear, including a first tooth 401 and a second tooth 402 spaced apart along the axial direction of housing 1. The first tooth 401 is meshed with rotor 3, and the second tooth 402 is meshed with output propeller shaft 5.

[0038] like Figure 1 As shown, the first tooth 401 is located near the rotor 3, and the second tooth 402 is located near the output propeller shaft 5. The diameter of the first tooth 401 is greater than the diameter of the second tooth 402, that is, the number of teeth of the first tooth 401 is greater than the number of teeth of the second tooth 402. This achieves a gradual decrease in output speed. Since the output power remains unchanged, the output torque increases.

[0039] The first tooth 401 and the second tooth 402 are respectively meshed with the rotor 3 and the output propeller shaft 5, achieving two-stage reduction through only one planetary gear. This design is simple, low-cost, and provides more reliable force transmission. Of course, two or more planetary gears can be spaced axially as needed.

[0040] In one embodiment, the output propeller shaft 5 includes a mounting portion 501 and a connecting portion 502. The mounting portion 501 is provided with gear teeth that mesh with the second gear portion 402, and the connecting portion 502 is connected to the drive member 6.

[0041] like Figure 1 As shown, the mounting part 501 is a frame with an opening. Gear teeth are provided on the inner wall of the frame. The second tooth 402 of the planetary gear extends into the frame to mesh with the mounting part 501. The connecting part 502 is a hollow cylinder extending beyond the second opening 103. Alternatively, multiple gear teeth can be provided circumferentially on the outer wall of the mounting part 501, meshing with the second tooth 402. However, the outer wall meshing structure is not as compact as the inner wall meshing structure. Nevertheless, the outer wall meshing structure can be used in specific situations, and the positional relationship between the two is not specifically limited here.

[0042] The purpose of providing a mounting part 501 that meshes with the second tooth 402 is to increase the reduction ratio and further improve the output torque. The mounting part 501 can be sleeved on the second tooth 402 or it can be set as a support frame. No specific limitation is made here.

[0043] In one embodiment, a first support bearing 7 and a second support bearing 8 are provided between the connecting part 502 and the inner wall of the housing 1. The first support bearing 7 is adapted to bear radial force, and the second support bearing 8 is adapted to bear axial force.

[0044] like Figure 1 As shown, since the diameter of the connecting part 502 is much smaller than the inner diameter of the housing 1, a first bearing seat 9 is provided at the position corresponding to the connecting part 502 on the housing 1. The first support bearing 7 and the second support bearing 8 are arranged axially at intervals in the first bearing seat 9.

[0045] The first support bearing 7 and the second support bearing 8 ensure an effective rotational connection between the output propeller shaft 5 and the housing 1. The first support bearing 7 and the second support bearing 8 bear radial force and axial force respectively, and can withstand the bending moment and axial load transmitted by the driven component, resulting in more uniform and reliable force distribution.

[0046] In one embodiment, a third support bearing 10 and a fourth support bearing 11 are provided between the planetary gear and the inner wall of the housing 1.

[0047] like Figure 1 As shown, a second bearing seat 12 is provided between the housing 1 and the rotor shaft 301 of the rotor 3. The second bearing seat 12 is located close to the second end of the rotor 3. A third support bearing 10 is provided on the second bearing seat 12, and a fourth support bearing 11 is provided between the inner wall of the housing 1 and the rotor shaft 301 of the rotor 3.

[0048] The planetary gears are rotatably connected to the inside of the housing 1 through the third support bearing 10 and the fourth support bearing 11 at both ends, ensuring the reliability of the transmission.

[0049] In one embodiment, the third support bearing 10 is disposed between the first tooth 401 and the second tooth 402, and the fourth support bearing 11 is disposed close to the stator 2.

[0050] A transition section is provided between the first tooth 401 and the second tooth 402, and the third support bearing 10 is provided on the transition section. The third support bearing 10 and the fourth support bearing 11 are respectively provided at the two ends of the planetary gear that are arranged opposite each other along the axial direction.

[0051] Since the first tooth 401 and the second tooth 402 are meshed with the rotor 3 and the output propeller shaft 5 respectively, the force is relatively concentrated. Therefore, a third support bearing 10 is added between the two to prevent connection failure when the force is large.

[0052] In one embodiment, a fifth support bearing 13 and a sixth support bearing 14 are provided between the rotor 3 and the inner wall of the housing 1. The fifth support bearing 13 is located near the gear 4, and the sixth support bearing 14 is located in the first opening 102.

[0053] To facilitate the installation of the fifth support bearing 13 and the sixth support bearing 14, a third bearing housing 15 and a fourth bearing housing 16 are also provided in the housing 1. The third bearing housing 15 and the rotating shaft 301 of the rotor 3 form the installation space for the fifth support bearing 13, and the fourth bearing housing 16 and the rotating shaft 301 of the rotor 3 form the installation space for the sixth support bearing 14.

[0054] As the input end of the driving force, rotor 3 bears a large force, and the overall volume and weight of rotor 3 are also large. In order to ensure the stability of force transmission, a fifth support bearing 13 and a sixth support bearing 14 are respectively set at both ends of rotor 3 to achieve a reliable connection between rotor 3 and housing 1.

[0055] In one embodiment, the system further includes a first lubrication structure and a second lubrication structure. The first lubrication structure is located at the stator 2, and the second lubrication structure is sequentially located at the rotor 3, the gear 4, and the output propeller shaft 5.

[0056] Both the first and second lubrication structures are oil channels, which are respectively located at the lubrication points of the stator 2, the rotor 3, the gear 4, and the output propeller shaft 5. In addition, the second lubrication structure is also located at the lubrication points of the first support bearing 7, the second support bearing 8, the third support bearing 10, the fourth support bearing 11, the fifth support bearing 13, and the sixth support bearing 14.

[0057] The stator 2, rotor 3, gear 4, and output propeller shaft 5 each use a set of lubrication structures to ensure lubrication effect and prevent lubrication failure.

[0058] In one embodiment, the drive element 6 includes a blade.

[0059] The rotor 3 drives the blades to rotate via the gear 4 and the output blade shaft 5, ensuring stable and reliable transmission. Multiple blades are connected to the output blade shaft 5 via a blade hub 17. The blade hub 17 has a mounting hole in the middle suitable for connecting to the output blade shaft 5, making it easier to connect multiple blades.

[0060] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A driving device, characterized in that, include: The shell (1) has a receiving space (101) and a first opening (102) and a second opening (103) communicating with the receiving space (101). The stator (2) is disposed in the receiving space (101) and fixed to the inner wall of the housing (1); The rotor (3) is fitted into the stator (2) and is electromagnetically connected to the stator (2), and the first end of the rotor (3) extends into the first opening (102); A gear (4) is provided in the receiving space (101) and is meshed with the rotor (3) and the output propeller shaft (5). The first end of the output propeller shaft (5) extends to the outside of the second opening (103), and a drive member (6) is provided on the first end of the output propeller shaft (5).

2. The driving device according to claim 1, characterized in that, The rotor (3) is coaxial with the output propeller shaft (5), and the axis of the gear (4) is parallel to the axis of the rotor (3).

3. The driving device according to claim 2, characterized in that, The gear (4) is a planetary gear, including a first tooth (401) and a second tooth (402) spaced apart along the axial direction of the housing (1). The first tooth (401) meshes with the rotor (3), and the second tooth (402) meshes with the output propeller shaft (5).

4. The driving device according to claim 3, characterized in that, The output propeller shaft (5) includes a mounting part (501) and a connecting part (502). The mounting part (501) is provided with gear teeth that mesh with the second gear part (402). The connecting part (502) is connected to the drive member (6).

5. The driving device according to claim 4, characterized in that, A first support bearing (7) and a second support bearing (8) are provided between the connecting part (502) and the inner wall of the housing (1). The first support bearing (7) is adapted to bear radial force, and the second support bearing (8) is adapted to bear axial force.

6. The driving device according to claim 3, characterized in that, A third support bearing (10) and a fourth support bearing (11) are provided between the planetary gear and the inner wall of the housing (1).

7. The driving device according to claim 6, characterized in that, The third support bearing (10) is disposed between the first tooth (401) and the second tooth (402), and the fourth support bearing (11) is disposed close to the stator (2).

8. The driving device according to any one of claims 1 to 7, characterized in that, A fifth support bearing (13) and a sixth support bearing (14) are provided between the rotor (3) and the inner wall of the housing (1). The fifth support bearing (13) is located close to the gear (4), and the sixth support bearing (14) is located in the first opening (102).

9. The driving device according to any one of claims 1 to 7, characterized in that, It also includes a first lubrication structure and a second lubrication structure. The first lubrication structure is located at the stator (2), and the second lubrication structure is located sequentially at the rotor (3), the gear (4), and the output propeller shaft (5).

10. The driving device according to any one of claims 1 to 7, characterized in that, The drive component (6) includes a blade.

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