Aviation power motor and assembling method thereof

Abstract

The invention discloses an aviation power motor which comprises a shell, a stator installed on the inner side of the shell, a rotor installed on the inner side of the stator, a hollow shaft installed on the inner side of the rotor, a waterproof bearing installed in the hollow shaft, an annular water seal installed between the top of the hollow shaft and the shell, and an annular shaft installed on the top of the hollow shaft. The top of the annular shaft is provided with a plurality of uniformly arranged propeller blades, the tops of the propeller blades are provided with propeller pressing rings, the center of the annular shaft is provided with an antenna sensor fixing seat, the bottom of the antenna sensor fixing seat penetrates through the shell, and the top of the antenna sensor fixing seat is provided with an antenna sensor.

Description

Technical Field

[0001] This invention belongs to the field of aviation power motor technology, specifically relating to an aviation power motor and its assembly method. Background Technology

[0002] As a core power component of equipment such as UAVs and light aircraft, aviation power motors often operate in harsh environments with conditions such as high-altitude high-speed airflow, water mist erosion, sand and dust impact, and mechanical vibration. This places extremely high demands on the motor's protection performance, structural compactness, and operational reliability. Currently, most existing aviation power motors adopt traditional open or semi-closed shaft system structures. During motor operation, impurities such as water mist, sand, and mechanical debris from the external environment can easily penetrate into the motor through the gap between the shaft system and the housing, causing faults such as stator winding insulation layer damage and rotor bearing jamming. This severely shortens the motor's service life and reduces its environmental adaptability and reliability. Summary of the Invention

[0003] In view of the problems raised in the background art above, the purpose of the present invention is to provide an aircraft power motor and its assembly method.

[0004] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows: An aircraft power motor includes a housing, a stator mounted inside the housing, a rotor mounted inside the stator, a hollow shaft mounted inside the rotor, a waterproof bearing mounted inside the hollow shaft, an annular water seal between the top of the hollow shaft and the housing, an annular shaft mounted on the top of the hollow shaft, a plurality of evenly arranged propeller blades mounted on the top of the annular shaft, propeller pressure rings mounted on the top of the plurality of propeller blades, an antenna sensor mounting base disposed at the center of the annular shaft, the bottom of the antenna sensor mounting base penetrating the housing, and an antenna sensor mounted on the top of the antenna sensor mounting base.

[0005] Furthermore, the housing includes a base, an outer shell is mounted on the top outer side of the base, and a top cover is mounted on the top of the outer shell. This structural design facilitates subsequent assembly.

[0006] Further specifying, a column is mounted at the top center of the base, the waterproof bearing is rotatably mounted on the column, a through hole is provided at the center of the column, and the bottom of the antenna sensor mounting base is disposed within the through hole. The base and the column are integrally formed, and several locking feet are installed at the bottom of the base. This structural design facilitates the installation of the waterproof bearing while providing installation space for the antenna sensor mounting base.

[0007] Furthermore, the outer surface of the housing is provided with a plurality of evenly arranged heat dissipation fins. This structural design facilitates heat dissipation.

[0008] Furthermore, the top cover has a central clearance hole, within which the hollow shaft and waterproof bearing are housed. A sealing groove is located on the lower side of the top cover near the clearance hole, and the annular water seal is installed within the sealing groove. This structural design facilitates installation and use without causing interference.

[0009] Further specifying, the annular shaft has several through holes around its circumference, the propeller blade has mounting holes at corresponding through holes, and the propeller pressure ring has assembly holes at corresponding mounting holes. Bolts are installed inside the assembly holes, with the bottom of the bolts passing through the mounting holes and through holes and extending into the hollow shaft. The hollow shaft has matching threaded holes at corresponding bolt locations, and the bottom of the bolts is locked into the threaded holes. This structural design ensures the fixed installation of the propeller blades.

[0010] Furthermore, the stator is fixedly mounted on the inner wall of the housing via an interference fit. This structural design effectively suppresses the relative displacement between the stator and the housing, and the tightness of the interference fit can withstand the centrifugal force at high speeds, preventing the stator from loosening.

[0011] Furthermore, the antenna sensor is fixedly mounted to the end face of the antenna sensor mounting base using bolts. This structural design achieves a fixed installation effect.

[0012] Furthermore, the waterproof bearing is a double-sided contact sealed deep groove ball bearing. This structural design provides excellent sealing performance.

[0013] An assembly method for an aircraft power motor, characterized by comprising the following steps: S1: Place the outer shell on the top outside of the base, ensuring that the outer shell fits snugly against the base and confirming that the base and the column are integrally molded structures; S2: The stator is fixedly installed on the inner wall of the housing using an interference fit. During installation, ensure that the stator and the housing fit tightly without any looseness. Rotate the waterproof bearing onto the column to ensure smooth rotation of the bearing. Then, put the hollow shaft on the outside of the waterproof bearing and install the rotor on the outside of the hollow shaft. Adjust the rotor position to maintain a preset gap between it and the stator to ensure that the gap is uniform. S3: Embed the annular water seal into the sealing groove of the top cover, confirm that the annular water seal is installed flat and without offset, and then install the top cover on the top of the outer shell. After the top cover is installed, the hollow shaft and the waterproof bearing are placed together in the clearance hole of the top cover, and the annular water seal between the top of the hollow shaft and the top cover is in a sealed state. S4: Install the annular shaft on top of the hollow shaft, then install the propeller blades on top of the annular shaft, aligning the mounting hole with the through hole. Place the propeller pressure ring on top of several propeller blades, aligning the assembly hole, mounting hole, and through hole. Finally, insert the bottom of the bolt through the assembly hole, mounting hole, and through hole in sequence and extend it into the threaded hole inside the hollow shaft to complete the fixing of the propeller assembly. S5: Finally, the antenna sensor is fixed to the end face of the antenna sensor mounting base with bolts. Tighten the bolts to ensure that the antenna sensor is installed firmly. Then, the bottom of the antenna sensor mounting base is installed on the aircraft through the propeller pressure ring, the ring shaft and the through hole, thus completing the installation of the entire aviation power motor.

[0014] The beneficial effects of this invention are as follows: 1. This invention forms a double waterproof structure by combining a waterproof bearing inside the hollow shaft with an annular water seal, effectively preventing external water mist, debris, dust and other impurities from entering the core components of the motor. This significantly improves the reliability and environmental adaptability of the motor in complex aviation environments such as humid and rainy conditions, and extends the service life of the equipment.

[0015] 2. This invention adopts a coaxial design for the stator, rotor, hollow shaft, and annular shaft, combined with the uniform arrangement of propeller blades and the fastening structure of the propeller pressure ring, to ensure that the electromagnetic energy of the motor can be efficiently converted into the mechanical power of the propeller, thus meeting the high efficiency requirements of aviation equipment for power output.

[0016] 3. While ensuring high protection and high reliability, this invention allows for the installation of components such as navigation lights on the hollow shaft, significantly improving space utilization. Furthermore, the coaxial arrangement of the hollow shaft and the antenna sensor mounting base integrates power output and sensor monitoring functions without increasing the radial dimension of the motor, thus improving the performance. Attached Figure Description

[0017] The present invention can be further illustrated by the non-limiting embodiments given in the accompanying drawings; Figure 1 This is a schematic diagram of the shaft side structure of an aircraft power motor according to an embodiment of the present invention; Figure 2 This is a schematic cross-sectional view of an aircraft power motor according to an embodiment of the present invention; Figure 3 This is an enlarged structural diagram of point A of an aircraft power motor according to an embodiment of the present invention; The symbols for the main components are explained below: 1. Housing; 2. Stator; 3. Rotor; 4. Hollow shaft; 5. Waterproof bearing; 6. Annular water seal; 7. Annular shaft; 8. Propeller blade; 9. Propeller pressure ring; 10. Antenna sensor mounting base; 11. Antenna sensor; 12. Base; 13. Housing; 14. Top cover; 15. Column; 16. Through hole; 17. Locking foot; 18. Heat dissipation fins; 19. Clearance hole; 20. Sealing groove; 21. Through hole; 22. Mounting hole; 23. Assembly hole; 24. Threaded hole. Detailed Implementation

[0018] To enable those skilled in the art to better understand the present invention, the technical solution of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0019] Example 1, such as Figure 1 , Figure 2 and Figure 3 As shown, an aviation power motor has a stator 2 installed inside the housing 1, a rotor 3 installed inside the stator 2, a hollow shaft 4 installed inside the rotor 3, a waterproof bearing 5 installed inside the hollow shaft 4, an annular water seal 6 installed between the top of the hollow shaft 4 and the housing 1, an annular shaft 7 installed on the top of the hollow shaft 4, a plurality of evenly arranged propeller blades 8 installed on the top of the annular shaft 7, a propeller pressure ring 9 installed on the top of the plurality of propeller blades 8, an antenna sensor mounting base 10 provided at the center of the annular shaft 7, the bottom of the antenna sensor mounting base 10 penetrating the housing 1, and an antenna sensor 11 installed on the top of the antenna sensor mounting base 10.

[0020] In this embodiment, after the motor starts, the stator 2 is supplied with three-phase alternating current to generate a rotating magnetic field. Under the action of electromagnetic force, the rotor 3 drives the hollow shaft 4 to rotate synchronously on the outside of the waterproof bearing 5. The hollow shaft 4 drives the propeller blade 8 to rotate at high speed through the annular shaft 7, generating lift or thrust to propel the aviation equipment. During this process, the waterproof bearing 5 and the annular water seal 6 form a double protection to prevent rainwater, fog and other substances from entering the motor and damaging the components. The antenna sensor 11 collects data such as the position and attitude of the equipment in real time and transmits it to the external control terminal to provide data support for the stable operation of the equipment.

[0021] During installation, the stator 2 is first installed inside the housing 1, and then the rotor 3 is fitted inside the stator 2. The hollow shaft 4 is connected and fixed inside the rotor 3. The axis of the hollow shaft 4 is aligned with the axis of the housing 1, stator 2, and rotor 3 to achieve coaxial rotation. A waterproof bearing 5 is embedded inside the hollow shaft 4 to provide stable support while preventing external moisture from entering the motor. An annular water seal 6 is installed at the connection between the top of the hollow shaft 4 and the housing 1. Its inner side is tightly fitted with the hollow shaft 4, and its outer side is fixed to the housing 1 to further enhance the axial waterproof sealing effect. The top of the hollow shaft 4 is fixed with an annular shaft 7 by a threaded connection. Propeller blades 8 are evenly arranged radially on the circumference of the annular shaft 7 and are axially pressed and fixed with a propeller clamping ring 9 to prevent the propeller blades from falling off during high-speed rotation. The antenna sensor mounting base 10 is set at the center of the annular shaft 7 and passes through the housing 1 to be installed on the aircraft. The antenna sensor 11 is fixedly installed on its top, and components such as navigation lights can be installed above the hollow shaft 4, greatly improving space utilization.

[0022] Example 2, as Figure 1 and Figure 2 As shown, this embodiment adds the following structure based on embodiment 1: the housing 1 includes a base 12, an outer shell 13 is installed on the top outer side of the base 12, and a top cover 14 is installed on the top of the outer shell 13.

[0023] In this embodiment, the housing 1 is composed of a base 12, an outer shell 13 and a top cover 14 forming a complete closed frame. The base 12 serves as a load-bearing foundation, and the outer shell 13 is fastened to its top outer side by bolts. The outer shell 13 has a cylindrical structure, and the top cover 14 is matched and installed on the top. The three together form a protective space for the internal components.

[0024] Example 3, as Figure 2 As shown, this embodiment adds the following structure based on embodiment 2: a column 15 is installed at the top center of the base 12, a waterproof bearing 5 is rotatably installed on the column 15, a through hole 16 is provided at the center of the column 15, the bottom of the antenna sensor fixing seat 10 is set in the through hole 16, the base 12 and the column 15 are integrally formed, and several locking feet 17 are installed at the bottom of the base 12.

[0025] In this embodiment, a column 15 is integrally formed at the top center of the base 12. The column 15 and the base 12 are cast from the same metal material to ensure structural strength. A waterproof bearing 5 is rotatably mounted on the column 15 by interference fit. At the same time, a through hole 16 is provided along the axial direction at the center of the column 15. The bottom of the antenna sensor mounting base 10 is adapted to be inserted into the through hole 16 to realize the built-in fixation of the antenna sensor. Locking feet 17 are evenly distributed on the bottom of the base 12 for detachable fixation between the housing 1 and the mounting surface.

[0026] Example 4, as Figure 1 As shown, this embodiment adds the following structure to the embodiment 2: the outer surface of the outer shell 13 is provided with a plurality of uniformly arranged heat dissipation fins 18.

[0027] In this embodiment, by setting heat dissipation fins 18, the internal heat can be dissipated through the heat dissipation fins 18 during use, and heat dissipation can be carried out quickly.

[0028] Example 5, as Figure 2 and Figure 3 As shown, this embodiment adds the following structure based on embodiment 2: the top cover 14 has a clearance hole 19 in the center, the hollow shaft 4 and the waterproof bearing 5 are set in the clearance hole 19, and the lower side of the top cover 14 has a sealing groove 20 near the clearance hole 19, and the annular water seal 6 is installed in the sealing groove 20.

[0029] In this embodiment, the top cover 14 is provided with a clearance hole 19 at the center corresponding to the position of the column 15. The upper parts of the hollow shaft 4 and the waterproof bearing 5 are both set in the clearance hole 19 to avoid interference during installation. The lower side of the top cover 14 is provided with an annular sealing groove 20 near the edge of the clearance hole 19. The annular water seal 6 is interference-fitted into the sealing groove 20 to achieve dynamic sealing cooperation with the hollow shaft 4.

[0030] Example 6, as Figure 2 and Figure 3 As shown, this embodiment adds the following structure based on embodiment 1: the annular shaft 7 has several through holes 21 around its circumference; the propeller blade 8 has mounting holes 22 at the corresponding through holes 21; the propeller pressure ring 9 has assembly holes 23 at the corresponding mounting holes 22; a bolt is installed inside the assembly hole 23; the bottom of the bolt passes through the mounting hole 22 and the through hole 21 in sequence and extends into the hollow shaft 4; the hollow shaft 4 has matching threaded holes 24 at the corresponding bolts; and the bottom of the bolt is locked and installed in the threaded holes 24.

[0031] In this embodiment, the bolt passes through the assembly hole 23 of the propeller pressure ring 9, the mounting hole 22 of the propeller blade 8, and the through hole 21 of the annular shaft 7 in sequence, and is finally locked with the threaded hole 24 of the hollow shaft 4, forming a multi-node, fully fitted fixing system. This effectively avoids the problem of component loosening caused by vibration in traditional connection methods. Furthermore, the coaxiality design of the through hole 21, mounting hole 22, assembly hole 23, and threaded hole 24 eliminates the need for repeated calibration during bolt installation, allowing assembly personnel to complete the operation with just a conventional wrench.

[0032] Example 7, as Figure 2 As shown, this embodiment adds the following structure to the embodiment 1: the stator 2 is fixedly installed on the inner wall of the housing 1 by interference fit.

[0033] In this embodiment, the relative displacement between the stator 2 and the housing 1 can be effectively suppressed during installation, and the tightness of the interference fit can withstand the centrifugal force at high speeds, preventing the stator 2 from loosening. Example 8, as Figure 2 As shown, this embodiment adds the following structure to the embodiment 1: the antenna sensor 11 is fixedly assembled to the end face of the antenna sensor mounting base 10 by bolts.

[0034] In this embodiment, the antenna sensor 11 is fixed to the end face of the antenna sensor mounting base 10 by bolts, forming a rigid connection structure that can effectively resist external interference such as vibration and impact. When the antenna sensor 11 malfunctions or needs to be upgraded or replaced, there is no need to damage the structure of the mounting base 10; the sensor can be disassembled simply by unscrewing the bolts.

[0035] Example 9, as Figure 2 As shown, this embodiment adds the following structure to the embodiment 1: the waterproof bearing 5 is a double-sided contact sealed deep groove ball bearing.

[0036] In this embodiment, the waterproof bearing 5 adopts a double-sided contact sealing structure, which can effectively prevent moisture, dust, mud and other impurities from entering the housing 1, thus achieving a good sealing effect.

[0037] An assembly method for an aircraft power motor, characterized by comprising the following steps: S1: Fit the outer shell 13 onto the top outer side of the base 12, ensuring that the outer shell 13 and the base 12 are connected and fit together, and confirming that the base 12 and the column 15 are integrally formed structures; S2: The stator 2 is fixedly installed on the inner wall of the housing 1 using an interference fit. During the installation process, ensure that the stator 2 and the housing 1 fit tightly without any signs of loosening. Rotate the waterproof bearing 5 onto the column 15 to ensure that the bearing rotates smoothly. Then, put the hollow shaft 4 on the outside of the waterproof bearing 5 and install the rotor 3 on the outside of the hollow shaft 4. Adjust the position of the rotor 3 to maintain a preset gap with the stator 2 and ensure that the gap is uniform. S3: Embed the annular water seal 6 into the sealing groove 20 of the top cover 14, confirm that the annular water seal 6 is installed flat and without offset, and then install the top cover 14 on the top of the outer shell 13. After the top cover 14 is installed, the hollow shaft 4 and the waterproof bearing 5 are placed together in the clearance hole 19 of the top cover 14, and the annular water seal 6 between the top of the hollow shaft 4 and the top cover 14 is in a sealed state. S4: Install the annular shaft 7 on top of the hollow shaft 4, then install the propeller blades 8 on top of the annular shaft 7, aligning the mounting hole 22 with the through hole 21. Cover the top of several propeller blades 8 with the propeller pressure ring 9, aligning the assembly hole 23, the mounting hole 22, and the through hole 21. Finally, insert the bottom of the bolt through the assembly hole 23, the mounting hole 22, and the through hole 21 in sequence and extend it into the threaded hole 24 inside the hollow shaft 4 to complete the fixing of the propeller assembly. S5: Finally, the antenna sensor 11 is fixedly mounted on the end face of the antenna sensor mounting base 10 with bolts. Tighten the bolts to ensure that the antenna sensor 11 is installed firmly. Then, the bottom of the antenna sensor mounting base 10 is installed on the aircraft through the propeller pressure ring 9, the annular shaft 7 and the through hole 16, thus completing the installation of the entire aviation power motor.

[0038] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. An aeronautical power motor comprising a casing (1), characterized in that: The inside of the shell (1) is provided with a stator (2), the inside of the stator (2) is provided with a rotor (3), the inside of the rotor (3) is provided with a hollow shaft (4), the inside of the hollow shaft (4) is provided with a waterproof bearing (5), the top of the hollow shaft (4) and the shell (1) are provided with an annular water seal (6), the top of the hollow shaft (4) is provided with an annular shaft (7), the top of the annular shaft (7) is provided with a plurality of uniformly arranged propeller blades (8), the top of the plurality of propeller blades (8) is provided with a propeller pressing ring (9), the center of the annular shaft (7) is provided with an antenna sensor fixing seat (10), the bottom of the antenna sensor fixing seat (10) penetrates the shell (1), and the top of the antenna sensor fixing seat (10) is provided with an antenna sensor (11).

2. An aeronautical power motor according to claim 1, characterized in that: The shell (1) comprises a base (12), the top outer side of the base (12) is provided with a shell (13), and the top of the shell (13) is provided with a top cover (14).

3. An aeronautical power motor according to claim 2, characterized in that: The top center of the base (12) is provided with a stand (15), the waterproof bearing (5) is rotatably installed on the stand (15), the center of the stand (15) is provided with a through hole (16), the bottom of the antenna sensor fixing seat (10) is arranged in the through hole (16), and the base (12) and the stand (15) are arranged in an integral molding structure, and the bottom of the base (12) is provided with a plurality of locking feet (17).

4. An aeronautical power motor according to claim 3, characterized in that: The outer surface of the shell (13) is provided with a plurality of uniformly arranged heat dissipation fins (18).

5. An aeronautical power motor according to claim 4, characterized in that: The center of the top cover (14) is provided with a clearance hole (19), the hollow shaft (4) and the waterproof bearing (5) are arranged in the clearance hole (19), the lower side of the top cover (14) is provided with a sealing groove (20) close to the clearance hole (19), and the annular water seal (6) is arranged in the sealing groove (20).

6. An aeronautical power motor according to claim 5, characterized in that: The circumference of the annular shaft (7) is provided with a plurality of through holes (21), the propeller blades (8) are provided with mounting holes (22) corresponding to the through holes (21), the propeller pressing ring (9) is provided with assembly holes (23) corresponding to the mounting holes (22), the assembly holes (23) are internally provided with bolts, the bottom of the bolts penetrates the mounting holes (22) and the through holes (21) in sequence and extends into the hollow shaft (4), the hollow shaft (4) is provided with a matching threaded hole (24) corresponding to the bolt, and the bottom of the bolt is locked and installed in the threaded hole (24).

7. An aeronautical power motor according to claim 6, characterized in that: The stator (2) is fixedly installed on the inner wall surface of the shell (1) through interference fit.

8. An aeronautical power motor according to claim 7, characterized in that: The antenna sensor (11) is fixedly assembled on the end face of the antenna sensor fixing seat (10) through bolts.

9. An aeronautical power motor according to claim 8, characterized in that: The waterproof bearing (5) is a double-sided contact type sealing deep groove ball bearing.

10. A method of assembling an aeronautical power machine according to any one of claims 1 to 9, characterized in that: The method comprises the following steps: S1: The shell (13) is sleeved on the top outer side of the base (12), the shell (13) is connected and fitted with the base (12), and it is confirmed that the base (12) and the stand (15) are in an integral molding structure; S2: The stator (2) is fixedly installed on the inner wall surface of the shell (1) in an interference fit manner, and the stator (2) is ensured to be tightly attached to the shell (1) without looseness during installation. The waterproof bearing (5) is rotatably installed on the stand (15), the bearing is ensured to rotate smoothly, the hollow shaft (4) is sleeved outside the waterproof bearing (5), the rotor (3) is installed outside the hollow shaft (4), and the position of the rotor (3) is adjusted to keep a predetermined gap between the rotor (3) and the stator (2), and the gap is ensured to be uniform; S3: The annular water seal (6) is embedded in the sealing groove (20) of the top cover (14), and it is confirmed that the annular water seal (6) is installed flat without deviation. Then the top cover (14) is installed on the top of the shell (13), and after the installation of the top cover (14) is completed, the hollow shaft (4) and the waterproof bearing (5) are arranged in the hollow hole (19) of the top cover (14), and the annular water seal (6) between the top of the hollow shaft (4) and the top cover (14) is in a sealed state; S4: The annular shaft (7) is installed on the top of the hollow shaft (4), and the propeller blades (8) are installed on the top of the annular shaft (7), so that the mounting hole (22) is aligned with the through hole (21). The propeller pressing ring (9) is covered on the top of the plurality of propeller blades (8), so that the assembly hole (23), the mounting hole (22) and the through hole (21) are aligned, and finally the bottom of the bolt is sequentially threaded through the assembly hole (23), the mounting hole (22) and the through hole (21) and extended into the threaded hole (24) in the hollow shaft (4), completing the fixation of the propeller assembly; S5: Finally, the antenna sensor (11) is fixedly assembled on the end surface of the antenna sensor fixing seat (10) by bolts, the bolts are tightened to ensure that the antenna sensor (11) is firmly installed, and the bottom of the antenna sensor fixing seat (10) is installed on the aircraft through the propeller pressing ring (9), the annular shaft (7) and the through hole (16), thereby completing the installation of the entire aviation power motor.

Images