Water-cooling planetary speed reduction power system for aircraft

Abstract

The water-cooling planetary speed reduction power system for the aircraft comprises an inner rotor motor, the upper end of the inner rotor motor is sequentially connected with a motor upper end cover and a planetary speed reducer end cover through bolts, and the lower end of the inner rotor motor is connected with a motor lower end cover through bolts; a water cooling sleeve is connected between the planetary reducer end cover and the motor lower end cover, the motor upper end cover and the inner rotor motor are inserted into the inner side of the water cooling sleeve, a motor output shaft of the inner rotor motor is connected with a planetary reducing mechanism, and the planetary reducing mechanism is installed on the inner side of the motor upper end cover. And a planet carrier of the planetary reducing mechanism is connected with a flange plate. A high-speed inner rotor motor and planetary speed reduction are adopted, the same power and torque of an outer rotor motor can be achieved, and the overall mass is lighter than that of the outer rotor motor with the same power and torque.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft power systems, and in particular to a water-cooled planetary reduction power system for aircraft. Background Art

[0002] The power system of an aircraft is a key component, responsible for providing flight power and ensuring the stability and control of the aircraft. The design of an aircraft power system needs to comprehensively consider multiple factors such as power output, weight, efficiency, and thermal management. Since aircraft are sensitive to the quality of power, especially for multi-rotors, reducing the mass of a single motor will significantly reduce the weight of the entire aircraft. At present, the aircraft power system mainly uses an outer rotor motor, which has a low speed, high torque, is generally flat, and adopts an air-cooled structure. The disadvantage of this outer rotor structure is that it is not sealed, has a heavy structural mass, and is large in size. Summary of the invention

[0003] In view of the above technical problems in the related art, the present invention provides a water-cooled planetary reduction power system for an aircraft, which can solve the above problems.

[0004] To achieve the above technical objectives, the technical solution of the present invention is implemented as follows: A water-cooled planetary reduction power system for an aircraft comprises an inner rotor motor, the upper end of the inner rotor motor is connected to a motor upper end cover and a planetary reducer end cover in sequence by bolts, the lower end of the inner rotor motor is connected to a motor lower end cover by bolts, a water cooling jacket is connected between the planetary reducer end cover and the motor lower end cover, the motor upper end cover and the inner rotor motor are plugged into the inner side of the water cooling jacket, the motor output shaft of the inner rotor motor is connected to a planetary reduction mechanism, the planetary reduction mechanism is installed on the inner side of the motor upper end cover, and the planetary carrier of the planetary reduction mechanism is connected to a flange.

[0005] Furthermore, the outer side of the shell of the motor stator of the inner rotor motor is processed with evenly distributed grooves and bosses, and the lower end of the boss is provided with a notch, and two grooves adjacent to the notch are connected through the notch.

[0006] Furthermore, a groove 2 and a boss 2 having the same structure as the groove 1 and the boss 1 are processed on the outer wall of the upper end cover of the motor, and the groove 1 is connected to the groove 2.

[0007] Furthermore, a plurality of grooves 1 are provided on the end cover of the planetary reducer, wherein the grooves 1 are staggered with the notches, and the grooves 1 are connected to two adjacent grooves 2.

[0008] Furthermore, the outer wall of the water cooling jacket is processed with grooves for increasing heat dissipation.

[0009] Furthermore, the lower end surface of the lower end cover of the motor is connected to two cooling water joints, the two cooling water joints are respectively a water inlet joint and a water outlet joint, and the two cooling water joints are respectively connected to a groove.

[0010] Furthermore, the inner gear ring of the planetary reduction mechanism is embedded and installed on the inner side of the upper end cover of the motor, the lower end of the planetary carrier is connected to the upper end cover of the motor through a bearing, and a deep groove ball bearing, a thrust ball bearing, and a rotary oil seal are installed in sequence between the upper end of the planetary carrier and the planetary reducer end cover.

[0011] Furthermore, the planetary reduction mechanism includes a sun gear, which is mounted on the motor output shaft through a spline, and four planetary gears are evenly distributed between the inner ring gear and the sun gear. A bearing 2 is installed at the upper and lower ends of each planetary gear, and a shaft is installed inside the bearing 2.

[0012] Furthermore, a shaft sleeve is installed at both upper and lower ends of the shaft, the shaft is connected to the planetary frame through the shaft sleeve, and the upper and lower ends of the shaft extending out of the planetary frame are respectively provided with shaft steps and retaining springs.

[0013] Furthermore, one end of the planetary carrier extending out of the planetary reducer end cover is a protruding connecting portion, which has a hexagonal structure. A threaded hole is provided in the middle of the protruding connecting portion. The flange is inserted into the protruding connecting portion and locked by a shaft head, and the shaft head is threadedly connected to the threaded hole.

[0014] Furthermore, a plurality of threaded holes 2 for connecting to the motor body are provided on the lower end surface of the lower end cover of the motor.

[0015] Beneficial effects of the present invention: The present application adopts a high-speed inner rotor motor and a planetary reduction gear, which can achieve the same power and torque as an outer rotor motor, but the overall mass is lighter than an outer rotor motor of the same power and torque. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] The present invention is further described in detail below with reference to the accompanying drawings.

[0018] Figure 1 This is a longitudinal section of a water-cooled planetary deceleration power system for an aircraft according to an embodiment of the present invention. Figure 1 ; Figure 2 This is a longitudinal section of a water-cooled planetary deceleration power system for an aircraft according to an embodiment of the present invention. Figure 2 ; Figure 3 It is a transverse cross-sectional view of a water-cooled planetary reduction power system for an aircraft according to an embodiment of the present invention.

[0019] In the figure: 1. Planetary reduction mechanism; 1-1. Planet carrier; 2. Shaft; 2-1. Shaft step; 3. Bearing 1; 4. Sun gear; 5. Bearing 2; 6. Circlip; 7. Deep groove ball bearing; 8. Thrust ball bearing; 9. Planet gear; 10. Bushing; 11. Inner rotor motor; 11-1. Motor stator; 11-1-1. Groove 1; 11-1-2. Boss 1; 11-1-3. Notch; 11-2. Motor output shaft ; 12. Lower end cover of motor; 12-1. Threaded hole 2; 13. Upper end cover of motor; 14. Cooling water joint; 20. Water cooling jacket; 20-1. Groove 2; 21. End cover of planetary reducer; 21-1. Groove 1; 23. Combined gasket; 24. Internal gear ring; 25. Rotary oil seal; 27. Flange; 28. Shaft head; 29. ​​Sealing ring 3; 31. Bolt 2; 32. Sealing ring 1; 34. Sealing ring 2. DETAILED DESCRIPTION

[0020] The following will be combined with the accompanying 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 belong to the scope of protection of the present invention.

[0021] like Figure 1-3 As shown, according to the present invention, a water-cooled planetary reduction power system for an aircraft is disclosed, comprising an inner rotor motor 11, wherein the upper end of the inner rotor motor 11 is sequentially connected to a motor upper end cover 13 and a planetary reducer end cover 21 by bolts, and the lower end of the inner rotor motor 11 is connected to a motor lower end cover 12 by bolts, a water cooling jacket 20 is connected between the planetary reducer end cover 21 and the motor lower end cover 12, the motor upper end cover 13 and the inner rotor motor 11 are plugged into the inner side of the water cooling jacket 20, the motor output shaft 11-2 of the inner rotor motor 11 is connected to a planetary reduction mechanism 1, the planetary reduction mechanism 1 is installed on the inner side of the motor upper end cover 13, and the planetary carrier 1-1 of the planetary reduction mechanism 1 is connected to a flange 27.

[0022] Embodiment 1: In the present application, the motor stator 11-1, the motor upper end cover 13, and the planetary reducer end cover 21 are connected by bolt one, and the motor stator 11-1 and the motor lower end cover 12 are connected by bolt two 31. The bolts use a combined gasket 23 for sealing when connecting. A planetary reduction mechanism 1 is installed on the inner side of the motor upper end cover 13. The inner gear ring 24 of the planetary reduction mechanism 1 is embedded and fixedly installed on the inner side of the motor upper end cover 13. Sealing rings are provided between the various components for sealing. For example, a sealing ring 1 32 is provided between the water cooling jacket 20 and the planetary reducer end cover 21, and between the water cooling jacket 20 and the motor lower end cover 12. A sealing ring 2 34 is provided between the motor upper end cover 13 and the inner rotor motor 11, and between the motor upper end cover 13 and the inner gear ring 24. A sealing ring 3 29 is provided between the inner gear ring 24 and the planetary reducer end cover 21, and so on.

[0023] Embodiment 2: In the present application, the motor stator 11-1, the motor upper end cover 13, the water cooling jacket 20 on the outside of the motor, the planetary reducer end cover 21, and the motor lower end cover 12 are assembled together to form a circulating water channel for water cooling of the motor. Specifically, a plurality of evenly distributed grooves 11-1-1 and a plurality of bosses 11-1-2 are processed on the outer side of the shell of the motor stator 11-1, wherein half of the bosses 11-1-2 have notches 11-1-3 at the lower ends, and the bosses 11-1-2 with notches 11-1-3 and the bosses without notches 11-1-3 are provided with notches 11-1-3. The boss 11-1-2 with the notch 11-1-3 is arranged at intervals (the boss 11-1-2 without the notch 11-1-3 is provided with a threaded hole for connecting the motor lower end cover 12), and the two grooves 11-1-1 adjacent to the notch 11-1-3 are connected through the notch 11-1-3. The outer wall of the motor upper end cover 13 is processed with a groove 2 and a boss 2 with the same structure as the groove 11-1-1 and the boss 11-1-2, and the groove 11-1-1 and the groove 2 are connected. A groove 21-1 is provided on the planetary reducer end cover 21, and the groove 21-1 is staggered with the notch 11-1-3, and the groove 21-1 is connected with two adjacent grooves 2, and two cooling water joints 14 are connected to the lower end surface of the motor lower end cover 12, and the two cooling water joints 14 are respectively an inlet joint and an outlet joint, and the two cooling water joints 14 are connected with the groove 11-1-1, so that the cooling water enters a groove 11-1-1 from the inlet joint. , flows into the adjacent groove 2 through the connected groove 2 and groove 1 21-1, then flows into the adjacent groove 11-1-1, and then enters another groove 11-1-1 through the notch 11-1-3. According to the above flow process, it circulates from the water outlet joint. In order to increase heat dissipation, the outer wall of the water cooling jacket 20 is processed with a groove 20-1 for increasing heat dissipation. The water cooling structure makes the heat dissipation effect good when the motor is working, can effectively control the motor temperature within a reasonable range, and can improve the working efficiency of the motor.

[0024] Embodiment three: In the present application, the inner gear ring 24 of the planetary reduction mechanism 1 is embedded and installed on the inner side of the upper end cover 13 of the motor. The lower end of the planetary carrier 1-1 is connected to the upper end cover 13 of the motor through a bearing 1-3. A deep groove ball bearing 7, a thrust ball bearing 8, and a rotary oil seal 25 are installed in sequence between the upper end of the planetary carrier 1-1 and the planetary reducer end cover 21. The planetary reduction mechanism 1 includes a sun gear 4, which is installed on the motor output shaft 11-2 through a spline. Four planetary gears 9 are evenly distributed between the inner gear ring 24 and the sun gear 4. A bearing 25 is installed at the upper and lower ends of each planetary gear 9. A shaft 2 is installed inside the bearing 25, and a shaft sleeve 10 is installed at the upper and lower ends of the shaft 2 (the axial displacement of the outer ring of the bearing 25 is limited by the step of the planetary wheel 9, and the axial displacement of the inner ring of the bearing 25 is limited by the shaft sleeve 10). The shaft 2 is connected to the planetary carrier 1-1 through the shaft sleeve 10, and the upper and lower ends of the shaft 2 extending out of the planetary carrier 1-1 are respectively provided with a shaft step 2-1 and a retaining spring 6 (the shaft step 2-1 is a part of the shaft 2, overlapped on the planetary carrier 1-1, and the retaining spring 6 is connected to the lower end of the shaft 2, and the relative movement of the shaft 2 and the planetary carrier 1-1 is limited by the shaft step 2-1 and the retaining spring 6).

[0025] Embodiment 4: The end of the planet carrier 1-1 extending out of the planet reducer end cover 21 in the present application is a protruding connection part, which is a hexagonal structure. The flange 27 is inserted into the protruding connection part and supported and limited by a step surface, and then the shaft head 28 is threadedly connected in the threaded hole 1. The flange 27 is pressed by the shaft head 28, so that the tension generated by the rotation of the rotor can be transmitted to the protruding connection part of the planet carrier 1-1 through the flange 27. The protruding connection part of the planet carrier 1-1 transmits the tension to the housing of the planetary reduction power system through the thrust ball bearing 8. A plurality of threaded holes 12-1 for connecting to the body are provided on the lower end surface of the lower end cover of the motor, which are used to fix and install the entire power system, so that the tension generated by the rotor can be transmitted to the body structure.

[0026] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A water-cooled planetary deceleration power system for an aircraft, characterized in that: The invention comprises an inner rotor motor (11), wherein the upper end of the inner rotor motor (11) is connected to a motor upper end cover (13) and a planetary reducer end cover (21) in sequence by bolts, the lower end of the inner rotor motor (11) is connected to a motor lower end cover (12) by bolts, a water cooling jacket (20) is connected between the planetary reducer end cover (21) and the motor lower end cover (12), the motor upper end cover (13) and the inner rotor motor (11) are plugged into the inner side of the water cooling jacket (20), the motor output shaft (11-2) of the inner rotor motor (11) is connected to a planetary reduction mechanism (1), the planetary reduction mechanism (1) is mounted on the inner side of the motor upper end cover (13), and the planetary carrier (1-1) of the planetary reduction mechanism (1) is connected to a flange (27).

2. The water-cooled planetary reduction power system for an aircraft according to claim 1, characterized in that: The outer side of the shell of the motor stator (11-1) of the inner rotor motor (11) is processed with a plurality of evenly distributed grooves (11-1-1) and a plurality of bosses (11-1-2), wherein half of the bosses (11-1-2) have notches (11-1-3) at their lower ends, the bosses (11-1-2) with the notches (11-1-3) and the bosses (11-1-2) without the notches (11-1-3) are arranged at intervals, and two grooves (11-1-1) adjacent to the notches (11-1-3) are connected via the notches (11-1-3).

3. A water-cooled planetary deceleration power system for an aircraft according to claim 2, characterized in that: A groove 2 and a boss 2 having the same structure as the groove 1 (11-1-1) and the boss 1 (11-1-2) are processed on the outer wall of the motor upper end cover (13), and the groove 1 (11-1-1) and the groove 2 are connected.

4. A water-cooled planetary deceleration power system for an aircraft according to claim 3, characterized in that: A plurality of grooves 1 (21-1) are provided on the planetary reducer end cover (21); the grooves 1 (21-1) and the notches (11-1-3) are staggered, and the grooves 1 (21-1) are connected to two adjacent grooves 2.

5. A water-cooled planetary deceleration power system for an aircraft according to claim 4, characterized in that: The outer side wall of the water cooling jacket (20) is processed with a second groove (20-1) for increasing heat dissipation.

6. A water-cooled planetary deceleration power system for an aircraft according to claim 5, characterized in that: The lower end surface of the motor lower end cover (12) is connected to two cooling water joints (14), the two cooling water joints (14) being a water inlet joint and a water outlet joint, respectively, and the two cooling water joints (14) are respectively connected to a groove 1 (11-1-1).

7. The water-cooled planetary reduction power system for aircraft according to claim 1, characterized in that: The inner gear ring (24) of the planetary reduction mechanism (1) is embedded and installed on the inner side of the upper end cover (13) of the motor; the lower end of the planetary carrier (1-1) is connected to the upper end cover (13) of the motor via a bearing 1 (3); a deep groove ball bearing (7), a thrust ball bearing (8), and a rotary oil seal (25) are installed in sequence between the upper end of the planetary carrier (1-1) and the planetary reducer end cover (21).

8. The water-cooled planetary reduction power system for aircraft according to claim 7, characterized in that: The planetary reduction mechanism (1) comprises a sun gear (4), the sun gear (4) being mounted on the motor output shaft (11-2) via a spline, four planetary gears (9) being evenly distributed between the inner gear ring (24) and the sun gear (4), a second bearing (5) being mounted at the upper and lower ends of each of the planetary gears (9), and a shaft (2) being mounted inside the second bearing (5).

9. The water-cooled planetary reduction power system for aircraft according to claim 8, characterized in that: A shaft sleeve (10) is installed at both upper and lower ends of the shaft (2); the shaft (2) is connected to the planetary frame (1-1) via the shaft sleeve (10); and shaft steps (2-1) and retaining springs (6) are respectively provided at the upper and lower ends of the shaft (2) extending out of the planetary frame (1-1).

10. The water-cooled planetary reduction power system for aircraft according to claim 9, characterized in that: One end of the planet carrier (1-1) extending out of the planetary reducer end cover (21) is a protruding connection portion, the protruding connection portion is a hexagonal structure, a threaded hole 1 is provided in the middle of the protruding connection portion, the flange (27) is plugged into the protruding connection portion and locked by a shaft head (28), and the shaft head (28) is threadedly connected to the threaded hole 1.

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