Water-cooling planetary speed reduction power system for aircraft

Abstract

The utility model discloses a water-cooling planetary reduction power system for an aircraft, which 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 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 utility model relates to the technical field of aircraft power systems, in particular to a water-cooled planetary reduction power system for aircraft. Background Art

[0002] An aircraft's powertrain is a critical component, responsible for providing flight propulsion and ensuring stability and control. The design of an aircraft's powertrain requires comprehensive consideration of multiple factors, including power output, weight, efficiency, and thermal management. Because aircraft are sensitive to power quality, especially for multi-rotors, reducing the mass of a single motor significantly reduces the overall weight of the aircraft. Currently, aircraft powertrains primarily utilize external rotor motors, which offer low speed, high torque, and are typically flat and air-cooled. The disadvantages of this external rotor structure are its lack of sealing, heavy weight, and bulk. Utility Model Content

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

[0004] In order to achieve the above technical purpose, the technical solution of the utility model is implemented as follows:

[0005] A water-cooled planetary reduction power system for an aircraft includes 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.

[0006] Furthermore, the outer side of the housing of the motor stator of the inner rotor motor is processed with evenly distributed grooves and bosses, the lower end of the boss is provided with a notch, and the two grooves adjacent to the notch are connected through the notch.

[0007] 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 and the groove 2 are connected.

[0008] Furthermore, a plurality of grooves 1 are provided on the end cover of the planetary reducer. The grooves 1 are staggered with the notches, and the grooves 1 are connected to two adjacent grooves 2.

[0009] Further, the outer side wall of the water-cooling jacket is processed with grooves for enhancing heat dissipation.

[0010] Further, two cooling water connectors are connected to the lower end surface of the lower end cover of the motor. The two cooling water connectors are respectively a water inlet connector and a water outlet connector, and the two cooling water connectors are respectively communicated with a first groove.

[0011] Further, the internal gear ring of the planetary reduction mechanism is embedded and installed inside the upper end cover of the motor. The lower end of the planet carrier is connected to the upper end cover of the motor through a first bearing. A deep groove ball bearing, a thrust ball bearing, and a rotary oil seal are sequentially installed between the upper end of the planet carrier and the planetary reducer end cover.

[0012] Further, the planetary reduction mechanism includes a sun gear. The sun gear is installed on the output shaft of the motor through a spline. Four planet gears are evenly distributed between the internal gear ring and the sun gear. A second bearing is installed at both the upper and lower ends of each planet gear, and a shaft is installed inside the second bearing.

[0013] Further, shaft sleeves are installed at both the upper and lower ends of the shaft. The shaft is connected to the planet carrier through the shaft sleeves. Shaft steps and circlips are respectively provided at the upper and lower ends of the shaft extending out of the planet carrier.

[0014] Further, one end of the planet carrier extending out of the planetary reducer end cover is an extended connection part. The extended connection part has a hexagonal structure. A first threaded hole is opened in the middle of the extended connection part. The flange plate is inserted on the extended connection part and locked by a shaft head. The shaft head is threadedly connected to the first threaded hole.

[0015] Further, a plurality of second threaded holes for connecting the machine body are opened on the lower end surface of the lower end cover of the motor.

[0016] The beneficial effects of the present utility model: This application adopts a high-speed inner rotor motor and planetary reduction, and can achieve the same power and torque as an outer rotor motor, but the overall mass is lighter than that of an outer rotor motor with the same power and torque. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] The following further describes the present utility model in detail according to the drawings.

[0019] Figure 1It is the longitudinal section of a water-cooled planetary reduction power system for an aircraft according to an embodiment of the present invention Figure I ;

[0020] Figure 2 It is the longitudinal section of a water-cooled planetary reduction power system for an aircraft according to an embodiment of the present invention Figure II ;

[0021] Figure 3 It is the cross-sectional view of a water-cooled planetary reduction power system for an aircraft according to an embodiment of the present invention

[0022] In the figure:

[0023] 1. Planetary reduction mechanism; 1-1. Planet carrier; 2. Shaft; 2-1. Shaft step; 3. First bearing; 4. Sun gear; 5. Second bearing; 6. Snap ring; 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. First groove; 11-1-2. First boss; 11-1-3. Notch; 11-2. Motor output shaft; 12. Lower end cover of the motor; 12-1. Second threaded hole; 13. Upper end cover of the motor; 14. Cooling water joint; 20. Water-cooled sleeve; 20-1. Second groove; 21. End cover of the planetary reducer; 21-1. First groove; 23. Combination gasket; 24. Internal gear ring; 25. Rotary oil seal; 27. Flange; 28. Shaft head; 29. Third seal ring; 31. Second bolt; 32. First seal ring; 34. Second seal ring Specific embodiments

[0024] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present 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 belong to the scope of protection of the present invention

[0025] Such as Figures 1-3As shown in the figure, a water-cooled planetary reduction power system for an aircraft is disclosed according to the present utility model, which includes an inner rotor motor 11. The upper end of the inner rotor motor 11 is sequentially connected with a motor upper end cover 13 and a planetary reducer end cover 21 by bolts. The lower end of the inner rotor motor 11 is connected with 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 inserted into the inner side of the water-cooling jacket 20. The motor output shaft 11-2 of the inner rotor motor 11 is connected with a planetary reduction mechanism 1. The planetary reduction mechanism 1 is installed inside the motor upper end cover 13. The planet carrier 1-1 of the planetary reduction mechanism 1 is connected with a flange 27.

[0026] Embodiment 1:

[0027] In this application, the motor stator 11-1, the motor upper end cover 13, and the planetary reducer end cover 21 are connected by bolt 1. The motor stator 11-1 and the motor lower end cover 12 are connected by bolt 2 31. A combined gasket 23 for sealing is used when connecting the bolts. A planetary reduction mechanism 1 is installed inside the motor upper end cover 13. The internal gear ring 24 of the planetary reduction mechanism 1 is fixedly installed inside the motor upper end cover 13 by embedding. Sealing rings are provided between all components for sealing. For example, 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. 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 internal gear ring 24. Sealing ring 3 29 is provided between the internal gear ring 24 and the planetary reducer end cover 21, and so on.

[0028] Embodiment 2:

[0029] In this 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 grooves 11-1-1 and a plurality of bosses 11-1-2 are evenly distributed on the outside 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 11-1-2 are notched. 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. The groove 11-1-1 and the groove 2 are connected. A groove 21-1 is provided on the planetary reducer end cover 21. The groove 21-1 is staggered with the notch 11-1-3, and the groove 21-1 is connected to two adjacent grooves 2. Two cooling water joints 14 are connected to the lower end surface of the motor lower end cover 12. The two cooling water joints 14 are respectively an inlet joint and an outlet joint. Both cooling water joints 14 are connected to 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 passes through the notch 11-1-3 into another groove 11-1-1. 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.

[0030] Example 3:

[0031] In this application, the internal gear ring 24 of the planetary reduction mechanism 1 is embedded and installed inside the upper end cover 13 of the motor. The lower end of the planet carrier 1-1 is connected to the upper end cover 13 of the motor through the first bearing 3. Between the upper end of the planet carrier 1-1 and the planetary reducer end cover 21, a deep groove ball bearing 7, a thrust ball bearing 8, and a rotary oil seal 25 are installed in sequence. The planetary reduction mechanism 1 includes a sun gear 4, and the sun gear 4 is installed on the motor output shaft 11-2 through a spline. Four planet gears 9 are evenly distributed between the internal gear ring 24 and the sun gear 4. A second bearing 5 is installed at both the upper and lower ends of each planet gear 9, and a shaft 2 is installed inside the second bearing 5. Shaft sleeves 10 are installed at both the upper and lower ends of the shaft 2 (wherein the axial displacement of the outer ring of the second bearing 5 is restricted by the step of the planet gear 9, and the axial displacement of the inner ring of the second bearing 5 is restricted by the shaft sleeve 10). The shaft 2 is connected to the planet carrier 1-1 through the shaft sleeve 10. Shaft steps 2-1 and snap rings 6 are respectively provided at both the upper and lower ends of the shaft 2 extending out of the planet carrier 1-1 (the shaft step 2-1 is a part of the shaft 2 and overlaps on the planet carrier 1-1, and the snap ring 6 is connected to the lower end of the shaft 2. The relative movement between the shaft 2 and the planet carrier 1-1 is restricted by the shaft step 2-1 and the snap ring 6).

[0032] Embodiment 4:

[0033] In this application, one end of the planet carrier 1-1 extending out of the planetary reducer end cover 21 is an extended connection part, and the extended connection part has a hexagonal structure. The flange 27 is inserted on the extended connection part and supported and limited by a stepped surface. Then, a shaft head 28 is threadedly connected in the first threaded hole, and the flange 27 is pressed by the shaft head 28. The tension generated during the rotation of the rotor can be transmitted to the extended connection part of the planet carrier 1-1 through the flange 27. The extended 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 second threaded holes 12-1 for connecting the fuselage are opened on the lower end surface of the lower end cover of the motor, which are used for fixedly installing the entire power system, and can realize transmitting the tension generated by the rotor to the fuselage structure.

[0034] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A water-cooled planetary reduction 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, 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).

2. The water-cooled planetary reduction power system for an aircraft according to claim 1, characterized in that, The outer side of the housing 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 through the notches (11-1-3).

3. A water-cooled planetary reduction 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. The water-cooled planetary reduction 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. The water-cooled planetary reduction 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. The water-cooled planetary reduction power system for an aircraft according to claim 5, wherein, 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) are respectively a water inlet joint and a water outlet joint, 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 an aircraft according to claim 1, characterized in that, The inner gear ring (24) of the planetary reduction mechanism (1) is embedded in 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 sequentially installed between the upper end of the planetary carrier (1-1) and the planetary reducer end cover (21).

8. A water-cooled planetary reduction power system for an aircraft according to claim 7, characterized in that, The planetary reduction mechanism (1) includes a sun gear (4), the sun gear (4) is installed on the motor output shaft (11-2) through a spline, and four planetary gears (9) are evenly distributed between the internal gear ring (24) and the sun gear (4). A bearing two (5) is installed at both the upper and lower ends of each planetary gear (9), and a shaft (2) is installed inside the bearing two (5).

9. A water-cooled planetary reduction power system for an aircraft according to claim 8, characterized in that, Shaft sleeves (10) are installed at both the upper and lower ends of the shaft (2). The shaft (2) is connected to the planet carrier (1-1) through the shaft sleeves (10). Shaft steps (2-1) and snap rings (6) are respectively provided at the upper and lower ends of the shaft (2) extending out of the planet carrier (1-1).

10. A water-cooled planetary reduction power system for an 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 an extended connecting part, the extended connecting part has a hexagonal structure, and a threaded hole one is opened in the middle of the extended connecting part. The flange plate (27) is inserted on the extended connecting part and locked by a shaft head (28), and the shaft head (28) is threadedly connected to the threaded hole one.

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