A gearbox transmission mechanism for a single-rotor plant protection UAV

Abstract

The present invention discloses a transmission mechanism of a gearbox for a single-rotor plant protection UAV, on which a main shaft is installed, a lubricating oil input port is provided at the upper left end of the main shaft, and a lubricating oil output port is provided at the lower right end of the main shaft. The transmission mechanism of the gearbox for a single-rotor plant protection UAV has the advantages of strong stability, high transmission efficiency, and diversified structural functionality. During the aircraft design process, the front end of the gearbox can convert the high speed and rotation direction of the engine through spiral bevel gears, and can also transfer part of the power to the tail rotor through the rear spiral bevel gear mechanism, so that the transmission efficiency of the engine fully meets the aircraft design and use requirements. At the same time, the mechanism concentrates the main transmission systems of the aircraft in the gearbox, which reduces the probability of aircraft resonance and makes the aircraft more stable.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a gearbox transmission mechanism of a single-rotor plant protection unmanned aerial vehicle. Background Art

[0002] The value-added drone has many advantages such as low cost, low loss, no pollution, reusability and high mobility, and plays a huge role in agriculture, such as sowing, spraying, insect control, etc.

[0003] The transmission mechanism of the unmanned helicopter is an important part of the unmanned helicopter. Most of the existing unmanned helicopters with a take-off weight of more than 150 kg use a gearbox to convert the engine output speed. At the same time, the design of the gearbox case is divided into two parts: the upper cover and the lower cover. This traditional design has the following defects:

[0004] 1). The gearbox plus the cantilever pulley mechanism will cause serious wear on the cantilever bearing installation. Long-term operation will cause the gearbox to wear, resulting in increased transmission clearance and reduced efficiency.

[0005] 2) At the same time, the gearbox is mostly an integrated upper cover, which is difficult to process and has poor economic efficiency.

[0006] 3) After the upper and lower covers of the gearbox are combined, they are connected and fixed to the frame with screws. Over time, the deformation of the frame directly causes deformation and displacement at the joint between the upper and lower covers of the gearbox, resulting in leakage of lubricating oil in the gearbox and poor structural stability.

[0007] To this end, we propose a gearbox transmission mechanism for a single-rotor plant protection UAV. Summary of the invention

[0008] In view of the shortcomings of the prior art, the present invention provides a gearbox transmission mechanism for a single-rotor agricultural drone, which solves the problem that the gearbox in the prior art is equipped with a cantilever pulley mechanism, which causes serious wear at the cantilever bearing installation point, and long-term operation causes wear of the gearbox, resulting in increased transmission clearance and reduced efficiency; at the same time, the gearbox is mostly an integrated upper cover, which is difficult to process and has poor economy; after the gearbox upper cover and lower cover are combined, they are connected and fixed to the frame with screws. As time goes by, the frame deforms, which directly causes deformation and displacement at the joint between the gearbox upper cover and the lower cover, resulting in leakage of lubricating oil in the gearbox and poor structural stability.

[0009] A single-rotor plant protection UAV gearbox transmission mechanism, a main shaft is installed on the transmission mechanism, a lubricating oil input port is opened at the left upper end of the main shaft, and a lubricating oil output port is opened at the right lower end of the main shaft, a bevel gear meshing part is provided on one side above the lubricating oil output port, and the transmission mechanism is composed of a large spiral bevel gear assembly, a gearbox support seat assembly, a gearbox upper cover assembly, a gearbox lower cover assembly, an input end front gear shaft assembly and an output end rear gear shaft assembly.

[0010] Preferably, the main shaft is installed in the middle position of the large spiral bevel gear assembly, and the large spiral bevel gear is installed on the right side of the large spiral bevel gear assembly.

[0011] Preferably, an exhalation bolt is installed in the middle position of the left side of the gearbox support seat assembly, and a dust ring is provided on the right side of the upper end of the gearbox support seat assembly, a deep groove ball bearing is installed at the lower end of the dust ring, the periphery of the gearbox support seat assembly has a support seat, and limiting steps are provided on both sides of the lower end of the gearbox support seat assembly.

[0012] Preferably, a limiting groove is provided at the top of the gearbox upper cover assembly, and an angular contact bearing is provided inside the limiting groove, an upper cover is provided on the right side of the angular contact bearing, and stainless steel sleeves are evenly installed around the gearbox upper cover assembly.

[0013] Preferably, a gearbox lower cover is installed on the gearbox lower cover assembly, and a first bearing and an oil drain screw are respectively installed on one side of the gearbox lower cover.

[0014] Preferably, first fixing threaded rings are installed on both sides of the middle of the input-end front gear shaft assembly, and a front gear shaft is installed on the input-end front gear shaft assembly, and a second bearing is sleeved on one side of the front gear shaft.

[0015] Preferably, second fixing threaded rings are installed on both sides of the middle of the output-end rear gear shaft assembly, and a rear gear shaft is installed on the input-end front gear shaft assembly, and a third bearing is sleeved on one side of the rear gear shaft.

[0016] Compared with the prior art, the present invention has the following beneficial effects: the transmission mechanism of the gearbox of the single-rotor plant protection UAV has the advantages of strong stability, high transmission efficiency, and diversified structural functionality. During the aircraft design process, the front end of the gearbox can convert the high speed and rotation direction of the engine through the spiral bevel gear, and can also transmit part of the power to the tail rotor through the rear spiral bevel gear mechanism, so that the transmission efficiency of the engine fully meets the aircraft design and use requirements. At the same time, the mechanism concentrates the main transmission system of the aircraft in the gearbox, which reduces the probability of aircraft resonance and makes the aircraft more stable. At the same time, the traditional gearbox upper cover is divided to reduce the processing difficulty; and a single-row angular contact bearing is adopted, and the traditional deep groove ball bearing is abandoned. The reasonably selected bearing is more suitable for the force mode of the box. At the same time, because the height of the box is reduced after the box is divided, the internal lubricating oil driven by the gearbox during operation can lubricate the single-row angular contact bearing, extending the life of the bearing; the gearbox lower cover is independently connected to the gearbox and does not participate in the fixing of the gearbox, which fundamentally solves the problem of gearbox oil leakage. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is an overall structural diagram of the transmission mechanism of the gearbox of the single-rotor plant protection UAV of the present invention;

[0018] Figure 2 For the present invention Figure 1 Schematic diagram of the structure at AA in the middle;

[0019] Figure 3 It is a schematic structural diagram of a large spiral bevel gear assembly of the present invention;

[0020] Figure 4 It is a structural schematic diagram of the gearbox support seat assembly of the present invention;

[0021] Figure 5 It is a structural schematic diagram of the gearbox upper cover assembly of the present invention;

[0022] Figure 6 It is a structural schematic diagram of the gearbox lower cover assembly of the present invention;

[0023] Figure 7 This is a schematic structural diagram of the front gear shaft assembly at the input end of the present invention;

[0024] Figure 8 This is a schematic diagram of the structure of the rear gear shaft assembly at the output end of the present invention;

[0025] In the figure: 1. main shaft; 2. lubricating oil input port; 3. lubricating oil output port; 4. bevel gear meshing point; 5. large spiral bevel gear assembly; 6. large spiral bevel gear; 7. gearbox support seat assembly; 8. exhalation bolt; 9. dust ring; 10. deep groove ball bearing; 11. support seat; 12. limit step; 13. gearbox upper cover assembly; 14. limit groove; 15. angular contact bearing; 16. upper cover; 17. stainless steel sleeve; 18. gearbox lower cover assembly; 19. gearbox lower cover; 20. first bearing; 21. drain screw; 22. input end front gear shaft assembly; 23. first fixed threaded ring; 24. second bearing; 25. front gear shaft; 26. output end rear gear shaft assembly; 27. second fixed threaded ring; 28. rear gear shaft; 29. ​​third bearing. DETAILED DESCRIPTION

[0026] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0027] See also Figure 1-8 A single-rotor plant protection UAV gearbox transmission mechanism, a main shaft 1 is installed on the transmission mechanism, a lubricating oil input port 2 is opened at the left upper end of the main shaft 1, and a lubricating oil output port 3 is opened at the right lower end of the main shaft 1, and a bevel gear meshing part 4 is provided on one side above the lubricating oil output port 3. The transmission mechanism is composed of a large spiral bevel gear assembly 5, a gearbox support seat assembly 7, a gearbox upper cover assembly 13, a gearbox lower cover assembly 18, an input end front gear shaft assembly 22 and an output end rear gear shaft assembly 26.

[0028] The main shaft 1 is installed in the middle position of the large spiral bevel gear assembly 5 , and a large spiral bevel gear 6 is installed on the right side of the large spiral bevel gear assembly 5 .

[0029] An exhalation bolt 8 is installed in the middle position of the left side of the gearbox support seat assembly 7, and a dust ring 9 is provided on the right side of the upper end of the gearbox support seat assembly 7, and a deep groove ball bearing 10 is installed on the lower end of the dust ring 9. The periphery of the gearbox support seat assembly 7 has a support seat 11, and limiting steps 12 are provided on both sides of the lower end of the gearbox support seat assembly 7.

[0030] A limiting groove 14 is provided at the top of the gearbox upper cover assembly 13 , and an angular contact bearing 15 is provided inside the limiting groove 14 . An upper cover 16 is provided on the right side of the angular contact bearing 15 , and stainless steel sleeves 17 are evenly installed around the gearbox upper cover assembly 13 .

[0031] A gearbox lower cover 19 is mounted on the gearbox lower cover assembly 18 , and a first bearing 20 and an oil drain screw 21 are respectively mounted on one side of the gearbox lower cover 19 .

[0032] First fixed threaded rings 23 are installed on both sides of the middle of the input end front gear shaft assembly 22 , and a front gear shaft 25 is installed on the input end front gear shaft assembly 22 , and a second bearing 24 is sleeved on one side of the front gear shaft 25 .

[0033] Second fixing threaded rings 27 are installed on both sides of the middle of the output end rear gear shaft assembly 26 , and a rear gear shaft 28 is installed on the input end front gear shaft assembly 22 , and a third bearing 29 is sleeved on one side of the rear gear shaft 28 .

[0034] It should be noted that the internal transmission structure of the gearbox of this value-protected drone consists of a gearbox support seat, a gearbox upper cover, a gearbox lower cover, a single-row angular contact bearing, a deep groove ball bearing, a gearbox main shaft, a main spiral bevel gear, front and rear gear shafts and sealing gaskets. A deep groove ball bearing with a dust ring is installed at the corresponding position in the gearbox support seat. The gearbox upper cover is reasonably equipped with a single-row angular contact bearing according to the force direction. At the same time, the outer end of the shell is provided with 4 mounting holes connected and fixed to the body, and the holes are inlaid with stainless steel sleeves. The gearbox lower cover is equipped with a deep groove ball bearing. The above three are assembled in sequence on the gearbox main shaft with large spiral bevel gears installed as required. The gear shaft assembly is composed of a gear shaft, a deep groove ball bearing and a sealing ring. After assembly, they are assembled on the gearbox upper cover. The front gear shaft assembly is the engine input end, and the rear gear shaft assembly is the tail shaft output end. An exhalation bolt is installed on the gearbox support seat, the upper cover is equipped with a refueling port, and the lower cover is provided with an oil drain hole fixed with a sealing screw. The large spiral bevel gear and the front and rear gear shafts form a first-stage reduction gear, which converts the engine output speed into the speed required by the aircraft main rotor through the front gear shaft combination, and changes the tail transmission speed through the rear gear shaft assembly. The gearbox housing is made of 7075 aluminum, which not only ensures strength but also reduces the overall weight. The main shaft is made of aviation high-quality material 30CrMnSiA. The gears and gear shafts inside the mechanism are made of 20CrMnTi integral carburizing and quenching processing to ensure the wear resistance and transmission accuracy of the gears. The design speed of the aircraft main rotor can be adjusted according to the engine speed and the gear ratio of the large gear and gear shaft. The speed of the tail rotor is also determined by adjusting the gear ratio of the bevel gear.

[0035] The transmission mechanism of the gearbox of the single-rotor plant protection UAV has the advantages of strong stability, high transmission efficiency, and diversified structural functionality. During the aircraft design process, the front end of the gearbox can convert the high speed and rotation direction of the engine through the spiral bevel gear, and can also transmit part of the power to the tail rotor through the spiral bevel gear mechanism at the back, so that the transmission efficiency of the engine fully meets the aircraft design and use requirements. At the same time, the mechanism concentrates the main transmission system of the aircraft in the gearbox, which reduces the probability of aircraft resonance and makes the aircraft more stable. At the same time, the traditional gearbox cover is divided to reduce the processing difficulty; and a single-row angular contact bearing is used, and the traditional deep groove ball bearing is abandoned. The reasonably selected bearing is more suitable for the force mode of the box. At the same time, because the height of the box is reduced after the distribution, the internal lubricating oil driven by the gearbox during operation can lubricate the single-row angular contact bearing, extending the life of the bearing; the gearbox cover is independently connected to the gearbox and does not participate in the fixing of the gearbox, which fundamentally solves the problem of gearbox oil leakage.

[0036] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A gearbox transmission mechanism for a single-rotor plant protection UAV, wherein a main shaft (1) is mounted on the transmission mechanism, and wherein: The left upper end of the main shaft (1) is provided with a lubricating oil input port (2), and the right lower end of the main shaft (1) is provided with a lubricating oil output port (3), and a bevel gear meshing portion (4) is provided on one side above the lubricating oil output port (3). The transmission mechanism is composed of a large spiral bevel gear assembly (5), a gearbox support seat assembly (7), a gearbox upper cover assembly (13), a gearbox lower cover assembly (18), an input end front gear shaft assembly (22), and an output end rear gear shaft assembly (26); The main shaft (1) is installed at the middle position of the large spiral bevel gear assembly (5), and a large spiral bevel gear (6) is installed on the right side of the large spiral bevel gear assembly (5); A limiting groove (14) is provided at the top of the gearbox upper cover assembly (13), and an angular contact bearing (15) is provided inside the limiting groove (14); an upper cover (16) is provided on the right side of the angular contact bearing (15), and stainless steel sleeves (17) are evenly installed around the gearbox upper cover assembly (13); The gearbox lower cover assembly (18) is provided with a gearbox lower cover (19), and a first bearing (20) and an oil drain screw (21) are respectively provided on one side of the gearbox lower cover (19); The large spiral bevel gear and the front and rear gear shafts form a first-stage reduction gear, which converts the engine output speed into the speed required by the aircraft's main rotor through the front gear shaft combination, and at the same time changes the tail drive speed through the rear gear shaft assembly.

2. The single-rotor plant protection UAV gearbox transmission mechanism according to claim 1 is characterized in that: An exhalation bolt (8) is installed at the middle position of the left side of the gearbox support seat assembly (7), and a dust ring (9) is arranged on the right side of the upper end of the gearbox support seat assembly (7), and a deep groove ball bearing (10) is installed at the lower end of the dust ring (9). The outer periphery of the gearbox support seat assembly (7) has a support seat (11), and both sides of the lower end of the gearbox support seat assembly (7) are provided with limiting steps (12).

3. The single-rotor plant protection UAV gearbox transmission mechanism according to claim 1 is characterized in that: First fixed threaded rings (23) are installed on both sides of the middle of the input end front gear shaft assembly (22), and a front gear shaft (25) is installed on the input end front gear shaft assembly (22), and a second bearing (24) is sleeved on one side of the front gear shaft (25).

4. The single-rotor plant protection UAV gearbox transmission mechanism according to claim 1, characterized in that: Second fixed threaded rings (27) are installed on both sides of the middle of the output end rear gear shaft assembly (26), and a rear gear shaft (28) is installed on the input end front gear shaft assembly (22), and a third bearing (29) is sleeved on one side of the rear gear shaft (28).

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