Unmanned aerial vehicle shell assembly structure

Abstract

The invention discloses an unmanned aerial vehicle shell assembly structure and belongs to the technical field of unmanned aerial vehicles. The rear shell and the front shell are connected in a sealed mode through a first bolt to form a shell assembly, the front shell is provided with an engine combination face, one end of the input shaft assembly penetrates through the engine combination face and is sealed through a second oil seal, an output shaft assembly, a middle shaft assembly and an input shaft assembly are arranged in the shell assembly, and the input shaft assembly is meshed with the middle shaft assembly. The middle shaft assembly is meshed with the output shaft assembly, one end of the output shaft assembly is connected with the flange plate and sealed through a first oil seal, an exhaust labyrinth and a first oil duct are arranged on the rear shell, the exhaust labyrinth is communicated with the first oil duct, a vent valve is arranged on the rear shell and communicated with the exhaust labyrinth, and a second oil duct is arranged in the front shell and communicated with the first oil duct. By optimizing the structural design, the lubricating system and the exhaust system, improving the performance of the unmanned aerial vehicle and other aspects, comprehensive optimization and improvement of the unmanned aerial vehicle shell assembly structure are achieved, and a powerful guarantee is provided for stable operation and long-term use of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and specifically relates to a structure of an unmanned aerial vehicle housing assembly. Background Art

[0002] With the rapid development of technology, significant progress has been made in the intelligent and autonomous design direction of unmanned aerial vehicle technology. Relying on its unique advantages, unmanned aerial vehicles have been widely used in multiple fields. In the military field, unmanned aerial vehicles are used for various tasks such as reconnaissance, strikes, and logistics transportation. Their efficient and flexible characteristics have greatly improved the efficiency and accuracy of military operations. In the agricultural field, unmanned aerial vehicles have become powerful assistants for tasks such as pesticide spraying, sowing and fertilizing, and agricultural product transportation, effectively improving agricultural production efficiency and the quality of agricultural products. In addition, in the field of road traffic, unmanned aerial vehicles also play an important role, being used for intelligent monitoring of traffic flow, accident investigation, traffic guidance, as well as logistics and rescue, providing strong support for urban traffic management and emergency response.

[0003] However, with the continuous expansion and deepening of the application fields of unmanned aerial vehicles, higher requirements are placed on their performance. On the premise of meeting the functions of the unmanned aerial vehicle itself, the overall design needs to be simpler, more stable, lower in cost, and easier to repair to adapt to various complex environments and task requirements. Summary of the Invention

[0004] To solve the problems existing in the background art, the present invention provides a structure of an unmanned aerial vehicle housing assembly.

[0005] To achieve the above object, the present invention adopts the following technical solution: A structure of an unmanned aerial vehicle housing assembly includes a flange, a first oil seal, a rear housing, a front housing, a ventilation valve, an output shaft assembly, an intermediate shaft assembly, an input shaft assembly, an engine joint surface, a second oil seal, a first bolt, a first oil passage, a second oil passage, and an exhaust maze.

[0006] The rear housing and the front housing are hermetically connected by the first bolt to form a housing assembly. The front housing is provided with an engine joint surface. One end of the input shaft assembly passes through the engine joint surface and is radially sealed by the second oil seal. The output shaft assembly, the intermediate shaft assembly, and the input shaft assembly are rotatably arranged in the housing assembly. The input shaft assembly is meshed and connected with the intermediate shaft assembly. The intermediate shaft assembly is meshed and connected with the output shaft assembly. One end of the output shaft assembly is connected to the flange and is radially sealed by the first oil seal. The rear housing is provided with an exhaust maze and a first oil passage. The exhaust maze is communicated with the first oil passage. The rear housing is provided with a ventilation valve. The ventilation valve is communicated with the exhaust maze. The front housing is provided with a second oil passage. The second oil passage is communicated with the first oil passage.

[0007] The exhaust maze is provided with a second bolt, a maze cover plate, a slope, and a shallow groove.

[0008] The maze cover plate is fixed on the exhaust maze by the second bolt and forms a cavity. A slope and a shallow groove are provided in the cavity. Symmetrical through holes are provided between the shallow groove and the maze cover plate, and both through holes are communicated with the first oil passage.

[0009] The first oil passage is provided with a first oil baffle, a first oil inlet groove, a first oil return groove, a second oil baffle, a second oil inlet groove, a second oil return groove, a third oil inlet groove and a third oil return groove;

[0010] The first oil inlet groove and the first oil return groove are respectively arranged on both sides of the output shaft assembly. A first oil baffle is provided at the first oil inlet groove. The second oil inlet groove and the second oil return groove are respectively arranged on both sides of the intermediate shaft assembly. A second oil baffle is provided on the second oil inlet groove. The third oil inlet groove and the third oil return groove are respectively arranged on both sides of the input shaft assembly.

[0011] The second oil passage is provided with a third oil baffle, a fourth oil inlet groove, a fourth oil return groove, a fourth oil baffle, a fifth oil inlet groove, a fifth oil return groove, a sixth oil inlet groove and a sixth oil return groove;

[0012] The fourth oil inlet groove and the fourth oil return groove are arranged on both sides of the output shaft assembly. A third oil baffle is provided at the fourth oil inlet groove. The fifth oil inlet groove and the fifth oil return groove are respectively arranged on both sides of the intermediate shaft assembly. A fourth oil baffle is provided on the fifth oil inlet groove. The sixth oil inlet groove and the sixth oil return groove are respectively arranged on both sides of the input shaft assembly.

[0013] Compared with the prior art, the beneficial effects of the present invention are:

[0014] 1. Structural compactness and symmetry: The structure of the UAV housing assembly adopts a design of three coaxial lines arranged vertically, realizing the overall uniform symmetry of the airframe, effectively shortening the axial dimension, improving the structural compactness. This design not only optimizes the appearance of the UAV, but also improves its flight stability, reducing vibration and noise during power transmission.

[0015] 2. High-efficiency lubrication and cooling: The first oil passage and the second oil passage are layout-designed according to the rotation directions of the input shaft assembly, the intermediate shaft assembly and the output shaft assembly, ensuring the smooth flow of oil and high-efficiency lubrication. The setting of the oil baffle effectively blocks the oil from entering the areas where it is not desired, improving the lubrication efficiency and reducing oil waste. At the same time, the circulating flow of the oil also provides effective cooling for each component, reducing component wear and temperature, and extending the service life of the UAV.

[0016] 3. Stable exhaust and pressure balance: The coordinated work of the exhaust maze and the vent valve ensures the stability of the internal pressure of the UAV housing assembly. When the internal pressure of the housing assembly increases, the oil-gas mixture is discharged through the exhaust maze, avoiding affecting the performance of the UAV or causing damage due to excessive pressure. The vent valve can automatically open or close according to the change of the internal pressure of the housing assembly, maintaining the cleanliness and stability of the internal environment.

[0017] 4. Improve the performance of the drone: The three-axis realizes two-stage gear reduction, increasing the starting torque and enabling rapid response. At the same time, the use of simple mechanical structures and conventional materials reduces the manufacturing and design costs, improves stability, and reduces the maintenance costs. These advantages make the drone more convenient for commercialization and popularization, improve production efficiency, and reduce personnel risk operations.

[0018] In summary, through optimizing aspects such as structural design, lubrication system, exhaust system, and improving the performance of the drone, the present invention realizes the comprehensive optimization and improvement of the drone housing assembly structure, providing a strong guarantee for the stable operation and long-term use of the drone. Description of the Drawings

[0019] Figure 1 is the axial sectional view of the assembly structure of the present invention;

[0020] Figure 2 is the schematic diagram of the ventilation maze and oil circuit structure of the rear shell of the present invention;

[0021] Figure 3 is Figure 2 the partial enlarged view of part A of

[0022] Figure 4 is the schematic diagram of the oil circuit structure of the front shell of the present invention. Detailed Embodiments

[0023] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present invention.

[0024] This embodiment records a drone housing assembly structure, including a flange 1, a first oil seal 2, a rear shell 3, a front shell 5, a ventilation valve 4, an output shaft assembly 6, an intermediate shaft assembly 7, an input shaft assembly 8, an engine joint surface 9, a second oil seal 10, a first bolt 11, an oil passage 1, an oil passage 2, and an exhaust maze;

[0025] The rear housing 3 and the front housing 5 are hermetically connected by a first bolt 11 to form a housing assembly. An engine mating surface 9 is provided on the front housing 5. One end of the input shaft assembly 8 passes through the engine mating surface 9 and is radially sealed by a second oil seal 10, facilitating the driving connection between the input shaft assembly 8 and the engine. An output shaft assembly 6, an intermediate shaft assembly 7, and an input shaft assembly 8 are rotatably provided in the housing assembly. The three shafts are collinear and vertically arranged, achieving overall uniform symmetry of the body and shortening the axial dimension. The input shaft assembly 8 is meshed with the intermediate shaft assembly 7 to achieve primary speed reduction and torque increase. The intermediate shaft assembly 7 is meshed with the output shaft assembly 6 to achieve secondary speed reduction and torque increase. One end of the output shaft assembly 6 is connected to the flange 1 and is radially sealed by a first oil seal 2. The flange 1 is used to transmit torque outward to meet the starting torque requirements of the drone. An exhaust maze and a first oil passage are provided on the rear housing 3. The exhaust maze is communicated with the first oil passage, used to guide the discharge of oil and gas and the flow of oil. A vent valve 4 is provided on the rear housing 3 for exhausting to avoid excessive pressure in the cavity. The vent valve 4 is communicated with the exhaust maze. A second oil passage is provided in the front housing 5, and the second oil passage is communicated with the first oil passage.

[0026] The exhaust maze is provided with a second bolt 13, a maze cover plate 14, a slope 15, and a shallow groove 16;

[0027] The maze cover plate 14 is fixed on the exhaust maze by the second bolt 13 and forms a cavity. A slope 15 and a shallow groove 16 are provided in the cavity. The angle of the slope 15 is greater than the maximum designed elevation angle of the whole machine to ensure that the oil can smoothly flow back to the bottom of the cavity when the drone reaches the maximum elevation angle, avoiding oil storage. Symmetrical through holes are provided between the shallow groove 16 and the maze cover plate 14. The diameter of the through holes is precisely calculated to balance the exhaust requirement and the anti-choking oil performance. Both through holes are communicated with the first oil passage to prevent the oil from overflowing through the vent valve 4 due to choking oil.

[0028] The first oil passage is provided with a first oil baffle 17, a first oil inlet groove 18, a first oil return groove 19, a second oil baffle 20, a second oil inlet groove 21, a second oil return groove 23, a third oil inlet groove 24, and a third oil return groove 25;

[0029] The first oil inlet groove 18 and the first oil return groove 19 are respectively arranged on both sides of the output shaft assembly 6. A first oil baffle 17 is provided at the first oil inlet groove 18. The second oil inlet groove 21 and the second oil return groove 23 are respectively arranged on both sides of the intermediate shaft assembly 7. A second oil baffle 20 is provided on the second oil inlet groove 21. The third oil inlet groove 24 and the third oil return groove 25 are respectively arranged on both sides of the input shaft assembly 8.

[0030] The second oil passage is provided with a third oil baffle 26, a fourth oil inlet groove 27, a fourth oil return groove 28, a fourth oil baffle 29, a fifth oil inlet groove 30, a fifth oil return groove 31, a sixth oil inlet groove 32, and a sixth oil return groove 33;

[0031] The fourth oil inlet groove 27 and the fourth oil return groove 28 are arranged on both sides of the output shaft assembly 6. A third oil baffle 26 is provided on the fourth oil inlet groove 27. The fifth oil inlet groove 30 and the fifth oil return groove 31 are respectively arranged on both sides of the intermediate shaft assembly 7. A fourth oil baffle 29 is provided on the fifth oil inlet groove 30. The sixth oil inlet groove 32 and the sixth oil return groove 33 are respectively arranged on both sides of the input shaft assembly 8.

[0032] The first oil passage and the second oil passage are layout-designed according to the rotation directions of the input shaft assembly 8, the intermediate shaft assembly 7 and the output shaft assembly 6. The positions and directions of the oil inlet grooves and the oil return grooves are optimized to ensure the smooth flow of the oil fluid and the lubrication effect. The first oil baffle 17, the second oil baffle 20, the third oil baffle 26 and the fourth oil baffle 29 are all designed according to the rotation directions of the corresponding shafts to effectively block the oil fluid from entering the areas where it is not desired to enter, improve the lubrication efficiency and reduce the waste of the oil fluid.

[0033] In the structure of the UAV housing assembly, the first oil passage and the second oil passage constitute a key oil fluid circulation system. Their layout design closely revolves around the rotation directions of the input shaft assembly 8, the intermediate shaft assembly 7 and the output shaft assembly 6 to achieve efficient lubrication and cooling. When the UAV is operating, each shaft rotates at a high speed, driving the gears to mesh and transmit power. At this time, the first oil passage and the second oil passage work together to provide lubrication for each shaft and the gears. The oil fluid first enters the working area through the oil inlet grooves, such as the first oil inlet groove 18, the second oil inlet groove 21, the third oil inlet groove 24, the fourth oil inlet groove 27, the fifth oil inlet groove 30, and the sixth oil inlet groove 32, which are respectively located on one side of the output shaft assembly 6, the intermediate shaft assembly 7 and the input shaft assembly 8. Taking the output shaft assembly 6 as an example, the first oil inlet groove 18 and the fourth oil inlet groove 27 deliver the oil fluid to the periphery of the output shaft assembly 6 to lubricate the shaft and the related gears. During this process, the first oil baffle 17 and the third oil baffle 26 play an important role. They are designed according to the rotation direction of the output shaft assembly 6 to effectively block the oil fluid from entering the areas where it is not desired to enter, avoid the waste of the oil fluid, ensure that the oil fluid accurately flows to the parts that need lubrication, and improve the lubrication efficiency. Similarly, the oil inlet grooves and the oil baffles on both sides of the intermediate shaft assembly 7 and the input shaft assembly 8 work in the same way to ensure good lubrication of each shaft and the gears. After being lubricated, the oil fluid flows back through the oil return grooves. The first oil return groove 19, the second oil return groove 23, the third oil return groove 25, the fourth oil return groove 28, the fifth oil return groove 31, and the sixth oil return groove 33 are respectively arranged on one side of each shaft to collect the used oil fluid. These oil return grooves are connected to the first oil passage and the second oil passage, enabling the oil fluid to flow back to the oil fluid storage area smoothly, completing a complete cycle. During the entire oil fluid circulation process, the first oil passage and the second oil passage are interconnected to ensure the continuous flow of the oil fluid in the housing assembly, continuously provide lubrication and cooling for each component, reduce the wear and temperature of the components, and ensure the stable operation of the UAV.

[0034] During the operation of the drone, the pressure inside the housing assembly may increase due to reasons such as oil evaporation and gas thermal expansion. If the air is not exhausted in time, it may affect the performance of the drone or even cause damage. Therefore, the design of the exhaust system is crucial. It consists of components such as an exhaust maze and a ventilation valve 4 working together to ensure the stability of the pressure inside the housing assembly. The exhaust maze on the rear housing 3 is connected to the ventilation valve 4 and is a key part of the entire exhaust system. The exhaust maze is provided with bolt two 13, a maze cover plate 14, a slope 15, and a shallow groove 16. When the pressure inside the housing assembly increases, the oil-gas mixture is discharged through the exhaust maze. The oil-gas first enters the cavity formed by the maze cover plate 14 and the exhaust maze. The angle of the slope 15 in the cavity is greater than the maximum designed elevation angle of the whole machine. This design ensures that when the drone reaches the maximum elevation angle, the oil can smoothly flow back to the bottom of the cavity along the slope 15 under the action of gravity, avoiding the accumulation of oil in the exhaust maze. At the same time, symmetric through holes are provided between the shallow groove 16 and the maze cover plate 14. The diameter of the through holes is precisely calculated to effectively prevent the oil from overflowing through the ventilation valve 4 due to oil choking while ensuring smooth exhaust. The oil-gas mixture enters the first oil passage through these through holes and then is discharged from the housing assembly through the connection path between the first oil passage and the ventilation valve 4. The ventilation valve 4 plays a key regulatory role in the entire exhaust process. It can automatically open or close according to the change of the pressure inside the housing assembly. When the internal pressure exceeds the set value, the ventilation valve 4 opens to discharge the excess gas and avoid excessive pressure in the cavity. When the pressure returns to normal, the ventilation valve 4 closes to prevent external dust, impurities, etc. from entering the inside of the housing assembly and ensure the cleanliness and stability of the internal environment. Through the coordinated work of the exhaust maze and the ventilation valve 4, the drone housing assembly can timely discharge the excess gas inside, maintain pressure balance, and ensure the normal operation of the drone.

[0035] The structure of the drone housing assembly adopts a design with three axes collinear and vertically arranged, that is, the input shaft assembly, the intermediate shaft assembly, and the output shaft assembly are collinear and vertically arranged. This design achieves the overall uniform symmetry of the fuselage, effectively shortens the axial dimension, and improves the structural compactness. At the same time, the three-axis collinear design also helps to reduce vibration and noise during power transmission and improve the flight stability of the drone.

[0036] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent conditions of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed rights.

Claims

1. A drone housing assembly structure, characterized in that: It includes a flange (1), a first oil seal (2), a rear housing (3), a front housing (5), a ventilation valve (4), an output shaft assembly (6), an intermediate shaft assembly (7), an input shaft assembly (8), an engine mating surface (9), a second oil seal (10), a first bolt (11), a first oil passage, a second oil passage, and an exhaust maze; The rear housing (3) and the front housing (5) are hermetically connected by the first bolt (11) to form a housing assembly. The front housing (5) is provided with an engine mating surface (9). One end of the input shaft assembly (8) passes through the engine mating surface (9) and is radially sealed by the second oil seal (10). An output shaft assembly (6), an intermediate shaft assembly (7), and an input shaft assembly (8) are rotatably arranged in the housing assembly. The input shaft assembly (8) is meshed and connected with the intermediate shaft assembly (7), the intermediate shaft assembly (7) is meshed and connected with the output shaft assembly (6). One end of the output shaft assembly (6) is connected to the flange (1) and is radially sealed by the first oil seal (2). The rear housing (3) is provided with an exhaust maze and a first oil passage. The exhaust maze is communicated with the first oil passage. The rear housing (3) is provided with a ventilation valve (4), and the ventilation valve (4) is communicated with the exhaust maze. The front housing (5) is internally provided with a second oil passage, and the second oil passage is communicated with the first oil passage.

2. The structure of the drone housing assembly according to claim 1, wherein: The exhaust maze is provided with a second bolt (13), a maze cover plate (14), a slope (15), and a shallow groove (16); The maze cover plate (14) is fixed on the exhaust maze by the second bolt (13) to form a cavity. A slope (15) and a shallow groove (16) are arranged in the cavity. Symmetrical through holes are arranged between the shallow groove (16) and the maze cover plate (14), and both through holes are communicated with the first oil passage.

3. The structure of a drone housing assembly according to claim 1, characterized in that: The first oil passage is internally provided with a first oil baffle (17), a first oil inlet groove (18), a first oil return groove (19), a second oil baffle (20), a second oil inlet groove (21), a second oil return groove (23), a third oil inlet groove (24), and a third oil return groove (25); The first oil inlet groove (18) and the first oil return groove (19) are respectively arranged on both sides of the output shaft assembly (6). A first oil baffle (17) is arranged at the first oil inlet groove (18). The second oil inlet groove (21) and the second oil return groove (23) are respectively arranged on both sides of the intermediate shaft assembly (7). A second oil baffle (20) is arranged on the second oil inlet groove (21). The third oil inlet groove (24) and the third oil return groove (25) are respectively arranged on both sides of the input shaft assembly (8).

4. The structure of a drone housing assembly according to claim 1, wherein: The second oil passage is internally provided with a third oil baffle (26), a fourth oil inlet groove (27), a fourth oil return groove (28), a fourth oil baffle (29), a fifth oil inlet groove (30), a fifth oil return groove (31), a sixth oil inlet groove (32), and a sixth oil return groove (33); The fourth oil inlet groove (27) and the fourth oil return groove (28) are arranged on both sides of the output shaft assembly (6). A third oil baffle (26) is arranged at the fourth oil inlet groove (27). The fifth oil inlet groove (30) and the fifth oil return groove (31) are respectively arranged on both sides of the intermediate shaft assembly (7). A fourth oil baffle (29) is arranged on the fifth oil inlet groove (30). The sixth oil inlet groove (32) and the sixth oil return groove (33) are respectively arranged on both sides of the input shaft assembly (8).

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