Propulsion device and aircraft

Abstract

The utility model provides a propulsion device and an aircraft, the propulsion device comprises a motor, a movable blade assembly, a stationary blade frame assembly and a duct cylinder with an air duct, and the motor is installed in the air duct through the stationary blade frame assembly; the movable blade assembly is installed on a driving shaft of the motor, and the movable blade assembly is used for generating propulsive force when driven by the motor to rotate and guiding airflow to conduct air cooling heat dissipation on the motor. When the movable blade assemblies rotate, the aircraft can be jointly propelled to run through pushing force generated by rotation of the movable blade assemblies and pushing force generated by lift augmentation of the duct cylinders; the air flow entering the air duct can flow through the motor in an accelerated manner in the axial direction of the driving shaft of the motor, so that air-cooled heat dissipation of the motor is realized, and the heat dissipation efficiency of the motor is improved; and the structure is simple, and the weight is reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of motors, and in particular relates to a propulsion device and an aircraft. Background Art

[0002] The ducted fan of the aircraft is arranged inside the duct of the propulsion device, and the duct achieves the lift-increasing effect by suppressing the fan tip vortex. In the related art, the ducted fan usually uses a motor as a driver, which will generate a large amount of heat during operation. In this way, there will be a problem that the heat generated inside the motor is difficult to be discharged, which will make it difficult to increase the power of the ducted fan, and may even cause damage to the motor; therefore, in order to dissipate the heat of the running motor in time, it is often necessary to arrange a special heat dissipation structure for the motor in the duct, which will make the structure of the propulsion device complicated and the weight increased, which is not conducive to the lightweight of the propulsion device. In addition, the heat dissipation efficiency of the heat dissipation structure in the propulsion device in the related art is low, and it is difficult to meet the heat dissipation requirements of the motor. Utility Model Content

[0003] The utility model aims at the technical problems such as low heat dissipation efficiency of the motor of the propulsion device in the prior art, and provides a propulsion device and an aircraft.

[0004] In view of the above technical problems, an embodiment of the utility model provides a propulsion device, including a motor, a moving blade assembly, a stationary blade frame assembly, and a duct tube having an air duct, wherein the motor is installed in the air duct through the stationary blade frame assembly; the moving blade assembly is installed on the driving shaft of the motor, and the moving blade assembly is used to generate propulsion force when driven to rotate by the motor, and guide the airflow to cool the motor.

[0005] Optionally, the stationary blade frame assembly includes a stationary blade bracket and at least one stationary blade mounted on the stationary blade bracket; one end of the stationary blade away from the stationary blade bracket is connected to the inner wall of the air duct; and the motor is mounted on the stationary blade bracket.

[0006] Optionally, a receiving groove and a first through hole are provided on the stationary blade support; the first through hole is connected between the air duct and the receiving groove.

[0007] Optionally, the propulsion device further includes a supporting flange; the supporting flange is used to fix the motor in the accommodating groove.

[0008] Optionally, the propulsion device also includes a first fairing; the first fairing is installed on the stationary blade bracket through the supporting flange, and an air outlet is provided at one end of the first fairing away from the stationary blade bracket; the end of the accommodating groove away from the first through hole is connected to the air outlet.

[0009] Optionally, the motor comprises a rotor assembly, a housing provided with an installation space, and a stator assembly installed on the housing and located in the installation space; the stator assembly is sleeved on the rotor assembly and is rotatably connected to the rotor assembly; the housing is provided with a second through hole and a third through hole respectively connected to opposite sides of the installation space; the housing is connected to the stationary blade frame assembly;

[0010] The motor also includes a fan assembly connected to the rotor assembly, and the fan assembly is used to rotate with the rotor assembly to drive the air flow to pass through the second through hole and the installation space, and then flow out from the third through hole, thereby performing air cooling and heat dissipation on the heating element in the installation space.

[0011] Optionally, the impeller assembly includes an impeller hub having a fourth through hole, and impeller blades mounted on the outer side wall of the impeller hub; the impeller hub is fixedly mounted on the driving shaft of the rotor assembly; and the fourth through hole is connected to the second through hole.

[0012] Optionally, the propulsion device also includes a second fairing installed at the end of the impeller hub away from the motor; an air inlet is provided at the end of the second fairing away from the impeller hub; and the fourth through hole is connected to the air inlet at the end away from the motor.

[0013] Optionally, the rotor assembly includes a driving shaft, the fan assembly includes an axial flow fan fixedly sleeved on the driving shaft, and the axial flow fan is located on a side of the second through hole away from the installation space;

[0014] The axial flow fan is used to rotate along with the driving shaft to drive the air flow to flow out of the third through hole through the second through hole and the installation space.

[0015] Optionally, a rotating space connected to the installation space is provided in the stator assembly; the fan assembly further comprises a radial fan fixedly sleeved on the drive shaft, and the radial fan is located in the rotating space;

[0016] The radial fan is used to rotate along with the driving shaft to blow the airflow in the rotating space toward the stator assembly.

[0017] Optionally, the housing comprises an annular shell, a first end cover and a second end cover; the first end cover and the second end cover are respectively mounted at opposite ends of the annular shell; the annular shell, the first end cover and the second end cover enclose the installation space; the annular shell is connected to the stationary blade frame assembly;

[0018] The second through hole is arranged on the first end cover; and the third through hole is arranged on the second end cover.

[0019] Optionally, a heat conducting member is provided on the outer side wall of the annular shell.

[0020] An aircraft comprises the propulsion device.

[0021] The motor of the utility model comprises a motor, a moving blade assembly, a stationary blade frame assembly, and a duct tube having an air duct, wherein the motor is installed in the air duct through the stationary blade frame assembly; the moving blade assembly is installed on the driving shaft of the motor, and the moving blade assembly is used to generate propulsion force when driven to rotate by the motor, and guide airflow to cool the motor.

[0022] In the present invention, a moving blade assembly is installed on the driving shaft of the motor. In this way, when the motor is running and drives the moving blade assembly to rotate, on the one hand, a driving force can be generated by the rotation of the moving blade assembly, so that the driving force and the thrust generated by the duct lift can jointly propel the operation of the aircraft; on the other hand, the rotation of the moving blade assembly can accelerate the airflow entering the air duct along the axial direction of the driving shaft of the motor to flow through the motor, thereby quickly taking away the heat generated by the motor, realizing air cooling of the motor, and further improving the heat dissipation efficiency of the motor, which is beneficial to improving the continuous output power of the motor; in addition, in the present invention, the motor in the propulsion device can be installed in the air duct through a lightweight stationary blade frame assembly, and the length of the drive shaft can be set shorter to realize the installation of the moving blade assembly, and there is no need to specially set up other heat dissipation structures to dissipate heat from the motor. The structure is simple and the weight is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0024] Figure 1 It is a structural schematic diagram of a propulsion device provided in one embodiment of the utility model.

[0025] Figure 2 It is a structural schematic diagram of a motor provided in one embodiment of the utility model.

[0026] Figure 3 It is a structural schematic diagram of a radial fan of a motor provided in one embodiment of the utility model.

[0027] Figure 4 It is a structural schematic diagram of an annular housing of a motor provided in one embodiment of the utility model.

[0028] Figure 5 It is a structural schematic diagram of a first end cover of a motor provided in one embodiment of the utility model.

[0029] Figure 6 It is a schematic structural diagram of a second end cover of a motor provided in one embodiment of the utility model.

[0030] Figure 7 It is a structural schematic diagram of an axial flow fan of a motor provided in one embodiment of the utility model.

[0031] Figure 8 It is a structural schematic diagram of a propulsion device provided in yet another embodiment of the utility model.

[0032] Fig. 9 It is a structural schematic diagram of a propulsion device provided in yet another embodiment of the utility model.

[0033] Fig.10 It is a structural schematic diagram of a propulsion device provided in yet another embodiment of the utility model.

[0034] Fig.11 It is a structural schematic diagram of a propulsion device provided in yet another embodiment of the utility model.

[0035] Fig.12 It is a structural schematic diagram of a stationary blade frame assembly of a propulsion device provided in one embodiment of the utility model.

[0036] Fig.13 It is a structural schematic diagram of a moving blade assembly of a propulsion device provided in one embodiment of the utility model.

[0037] The reference numerals in the specification are as follows:

[0038] 100, motor; 110, rotor assembly; 111, drive shaft; 120, housing; 121, installation space; 122, annular housing; 123, first end cover; 1231, second through hole; 124, second end cover; 1241, third through hole; 125, heat conducting member; 130, stator assembly; 131, rotation space; 140, fan assembly; 141, axial flow fan; 142, radial flow fan; 200, Duct tube; 210, air duct; 300, stationary blade frame assembly; 310, stationary blade bracket; 311, receiving groove; 312, first through hole; 320, stationary blade; 400, supporting flange; 500, first fairing; 510, air outlet; 600, threading tube; 700, moving blade assembly; 710, moving blade hub; 711, fourth through hole; 720, moving blade; 800, second fairing; 810, air inlet. DETAILED DESCRIPTION

[0039] In order to make the technical problems, technical solutions and beneficial effects solved by the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0040] It should be understood that the directions or positional relationships indicated by terms such as "upper", "lower", "left", "right", "front", "back", and "middle" are based on the directions or positional relationships shown in the accompanying drawings and are only used to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation of the present invention.

[0041] like Figures 1 to 13 As shown, an embodiment of the utility model provides a propulsion device, including a motor 100, a moving blade assembly 700, a stationary blade frame assembly 300, and a duct tube 200 having an air duct 210; the motor 100 is installed in the air duct 210 through the stationary blade frame assembly 300; the moving blade assembly 700 is installed on the driving shaft 111 of the motor 100; the moving blade assembly 700 is used to generate a propulsion force when being driven to rotate by the motor 100, and guide the airflow to cool the motor 100.

[0042] In the utility model, the motor 100 is installed in the duct 200 through the stationary blade frame assembly 300. When the propulsion device is running, the motor 100 runs and generates heat under the action of the current. In this process, the motor 100 drives the moving blade assembly 700 to rotate, so that the airflow entering the air duct is accelerated along the axial direction of the drive shaft of the motor 100 to flow through the motor, thereby quickly taking away the heat generated by the motor 100, and realizing the air cooling and heat dissipation of the motor 100. It can be understood that the propulsion device can be used in an aircraft, and the propulsion device can be hoisted on the fuselage of the aircraft through the duct 200. The moving blade assembly 700 is located in the air duct 210, so that the moving blade assembly 700 can generate a propulsion force, so that the propulsion force and the thrust generated by the duct 200 are used to jointly propel the aircraft to operate. The radius of the moving blade assembly 700 can be set according to actual conditions, as long as it can be installed in the air duct 210 and rotate.

[0043] It is understandable that the stationary blade frame assembly 300 can adopt a lighter frame structure, so that while the motor 100 can be stably installed on the stationary blade frame assembly 300, the airflow passage area can be increased. After the motor is installed on the stationary blade frame assembly 300, the drive shaft 111 can directly extend out of the stationary blade frame assembly 300 and connect with the moving blade assembly 700, avoiding the need to extend the drive shaft 111 or the need for an additional connection mechanism between the drive shaft and the moving blade assembly 700, thereby simplifying the structure and reducing the weight of the propulsion device.

[0044] In the above-mentioned embodiment of the utility model, the moving blade assembly 700 is installed on the driving shaft of the motor 100. In this way, when the motor 100 is running and drives the moving blade assembly 700 to rotate, on the one hand, a driving force can be generated by the rotation of the moving blade assembly 700, so that the aircraft can be propelled by the driving force and the thrust generated by the lift of the duct tube 200; on the other hand, the rotation of the moving blade assembly 700 can make the airflow entering the air duct accelerate along the axial direction of the driving shaft of the motor 100 to flow through the motor, thereby quickly taking away the heat generated by the motor 100, realizing air cooling and heat dissipation of the motor 100, thereby improving the heat dissipation efficiency of the motor 100, and facilitating improving the continuous output power of the motor 100; in addition, in the utility model, the motor 100 in the propulsion device can be installed in the air duct 210 through the lightweight stationary blade frame assembly 300, and the length of the driving shaft can be set shorter to realize the installation of the moving blade assembly 700, and there is no need to set up other special heat dissipation structures to dissipate heat from the motor, and its structure is simple and the weight is reduced.

[0045] like Fig. 9 , Fig.10 and Fig.12 As shown, in one embodiment, the stationary blade frame assembly 300 includes a stationary blade bracket 310 and at least one stationary blade 320 mounted on the stationary blade bracket 310; one end of the stationary blade 320 away from the stationary blade bracket 310 is connected to the inner wall of the air duct 210; and the motor 100 is mounted on the stationary blade bracket 310. It can be understood that the stationary blade bracket 310 can accommodate the motor 100 inside it, and the drive shaft 111 can extend out of the stationary blade bracket 310 and directly connect with the moving blade assembly 700, avoiding the additional connection mechanism between the drive shaft 111 and the moving blade assembly 700, simplifying the connection structure, and reducing the weight of the motor 100. The stationary blades 320 can be symmetrically distributed in the air duct 210, so as to ensure the balance of the motor 100 during operation. The stationary blades 320 can be made of carbon fiber material with embedded aluminum alloy, so as to reduce the weight on the basis of ensuring the structural strength. The connection method between the stationary blade 320 and the duct 200 or the stationary blade bracket 310 includes but is not limited to one or more of bolt connection, riveting, welding or integral molding, as long as a firm connection is formed between the stationary blade 320 and the duct 200, and between the stationary blade 320 and the stationary blade bracket 310.

[0046] like Fig.10 and Fig.12As shown, in one embodiment, the stationary blade support 310 is provided with a receiving groove 311 and a first through hole 312; the first through hole 312 is connected between the air duct 210 and the receiving groove 311; the propulsion device further includes a support flange 400; the support flange 400 is used to fix the housing 120 of the motor 100 in the receiving groove 311. It can be understood that the receiving groove 311 is used to accommodate the motor 100. The first through hole 312 can be set on the stationary blade support 310 according to actual conditions, as long as it is connected between the air duct 210 and the receiving groove 311. The connection method between the motor 100 and the stationary blade support 310 includes but is not limited to one or more of bolt connection, riveting, welding or integral molding, as long as a stable connection is formed between the motor 100 and the stationary blade support 310. The supporting flange 400 can be connected to the stationary blade support 310 and cover the receiving groove 311, so as to further fix and press the motor 100 located in the receiving groove 311 in the receiving groove 311, thereby improving the connection stability of the motor 100.

[0047] like Figure 1 , Figure 8 and Fig. 9 As shown, in one embodiment, the propulsion device further includes a first fairing 500; the first fairing 500 is mounted on the stationary blade bracket 310 through the support flange 400, and an air outlet 510 is provided at one end of the first fairing 500 away from the stationary blade bracket 310; and the end of the receiving groove 311 away from the first through hole 312 is connected to the air outlet 510. It can be understood that the first fairing 500 is mounted on the stationary blade bracket 310 through the support flange 400, that is, the first fairing 500 is provided on the receiving groove 311. The size of the air outlet 510 can be set according to actual conditions, as long as it can be connected with the end of the receiving groove 311 away from the first through hole 312. The connection method of the first fairing 500 and the stationary blade bracket 310 includes but is not limited to one or more of bolt connection, riveting, welding or integral molding, as long as a stable connection is formed between the first fairing 500 and the stationary blade bracket 310. In one embodiment, a wire tube 600 for installing wires is provided on the first fairing 500 , and the wire tube 600 is connected between the first fairing 500 and the duct 200 .

[0048] like Figures 2 to 7As shown, the motor 100 includes a rotor assembly 110, a housing 120 provided with an installation space 121, and a stator assembly 130 installed on the housing 120 and located in the installation space 121; the stator assembly 130 is sleeved on the housing 120; the housing 120 is provided with a second through hole 1231 and a third through hole 1241 which are respectively connected to the opposite sides of the installation space 121; the housing 120 is connected to the stator frame assembly 300; the motor 100 also includes a fan assembly 140 connected to the rotor assembly 110, and the fan assembly 140 is used to rotate with the rotor assembly 110 to drive the airflow to pass through the second through hole 1231 and the installation space 121, and then flow out from the third through hole 1241, thereby cooling the heat generating element in the installation space 121.

[0049] It can be understood that the heating element includes but is not limited to the stator assembly 130 and / or the rotor assembly 110 of the motor 100, and as long as the heating element is located in the installation space 121, it can be cooled by the fan assembly 140. The first through hole 312 can be arranged at the end of the receiving slot 311 away from the motor 100 and corresponding to the second through hole 1231. Therefore, the third through hole 1241 is located at the end of the receiving slot 311 away from the first through hole 312. The third through hole 1241 is connected to the air outlet 510, and the air outlet 510 can discharge the airflow discharged from the third through hole 1241 into the propulsion device to avoid airflow blockage in the propulsion device.

[0050] In this embodiment, when the motor 100 is running, the motor 100 drives the impeller assembly 700 to rotate, so that the impeller assembly 700 can guide the airflow to cool the motor 100; at the same time, the fan assembly 140 follows the rotation of the rotor assembly 110, so that the airflow at one end of the second through hole 1231 away from the installation space 121 can be accelerated to enter the installation space 121 through the second through hole 1231, so as to cool the heating element in the installation space 121, and then flow out through the third through hole 1241.

[0051] In the above-mentioned embodiment of the utility model, the motor 100 is installed in the air duct 210 through the stationary blade frame assembly 300, so that when the motor 100 is running, the motor 100 can obtain a larger airflow in the air duct 210 to cool the motor 100; at the same time, by arranging a fan assembly 140 on the rotor assembly 110, and arranging a second through hole 1231 and a third through hole 1241 on the outer casing 120 that are connected to the opposite sides of the installation space 121, when the motor 100 is running, the fan assembly 140 can be used to drive the airflow to accelerate through the second through hole 1231 into the installation space 121, and then flow out from the third through hole 1241, so as to cool the heating element in the installation space 121, thereby improving the heat dissipation efficiency of the motor 100.

[0052] like Fig.13 As shown, in one embodiment, the impeller assembly 700 includes an impeller hub 710 having a fourth through hole 711, and a moving blade 720 mounted on the outer side wall of the impeller hub 710; the impeller hub 710 is fixedly mounted on the drive shaft 111 of the rotor assembly 110; and the fourth through hole 711 is connected to the second through hole 1231. It can be understood that the connection between the drive shaft 111 and the impeller hub 710 includes but is not limited to one or more of the following methods: snap connection (including spline connection, etc.), bolt connection, riveting, welding or integral molding, as long as a stable connection is formed between the drive shaft 111 and the impeller hub 710. The fourth through hole 711 can be set on the impeller hub 710 according to actual conditions, as long as it is connected to the second through hole 1231. Thus, the airflow can enter the second through hole 1231 through the fourth through hole 711. In one embodiment, the fourth through hole 711 and the second through hole 1231 are arranged opposite to each other, so that airflow can more conveniently enter the second through hole 1231 through the fourth through hole 711 .

[0053] like Figure 1 , Figure 8 and Fig. 9As shown, in one embodiment, the propulsion device further comprises a second fairing 800 mounted on the end of the impeller hub 710 away from the motor 100; the end of the second fairing 800 away from the impeller hub 710 is provided with an air inlet 810; the end of the fourth through hole 711 away from the motor 100 is connected to the air inlet 810. It can be understood that the second fairing 800 is provided on the impeller hub 710, that is, the second fairing 800 is provided on the fourth through hole 711. Therefore, the end of the second fairing 800 away from the impeller hub 710 is provided with an air inlet 810, and the fourth through hole 711 can be connected to the outside through the air inlet 810, so that the outside airflow can enter the fourth through hole 711 through the air inlet 810. The size of the air inlet 810 can be set according to actual conditions, as long as it can be connected with the end of the fourth through hole 711 away from the motor 100, and then connected with the second through hole 1231. The connection method between the second fairing 800 and the impeller hub 710 includes, but is not limited to, one or more of the methods of clamping, bolting, riveting, bonding or integral molding, as long as a firm connection is formed between the second fairing 800 and the impeller hub 710 .

[0054] like Figure 2 and Figure 7As shown, in one embodiment, the rotor assembly 110 includes a driving shaft 111, and the fan assembly 140 includes an axial flow fan 141 fixedly sleeved on the driving shaft 111, and the axial flow fan 141 is located on the side of the second through hole 1231 away from the installation space 121; the axial flow fan 141 is used to rotate with the driving shaft 111 to drive the airflow to flow out of the third through hole 1241 through the second through hole 1231 and the installation space 121. It can be understood that the axial flow fan 141 can push the airflow to flow in a direction parallel to the axis, that is, in this embodiment, the axial flow fan 141 can rotate with the driving shaft 111, thereby pushing the airflow to flow in a direction parallel to the driving shaft 111, and then can drive the airflow to flow out of the third through hole 1241 through the second through hole 1231 and the installation space 121. The distance between the axial flow fan 141 and the second through hole 1231 can be set according to actual conditions (such as the length requirement of the motor 100, etc.), and the radius of the axial flow fan 141 can also be set according to actual conditions (such as the demand for air intake, etc.), as long as the airflow can be driven to flow through the second through hole 1231 and the installation space 121 and out of the third through hole 1241. For example, the radius of the axial flow fan 141 can be greater than or equal to the maximum value of the distance between the second through hole 1231 and the drive shaft 111, so that the projection of the axial flow fan 141 on the housing 120 on one side of the second through hole 1231 can completely cover all the second through holes 1231, thereby improving the air intake efficiency.

[0055] like Figure 2 and Figure 3 As shown, in one embodiment, the stator assembly 130 is provided with a rotating space 131 connected to the installation space 121; the fan assembly 140 further includes a radial fan 142 fixedly sleeved on the drive shaft 111, and the radial fan 142 is located in the rotating space 131; the radial fan 142 is used to rotate with the drive shaft 111 to blow the airflow in the rotating space 131 toward the stator assembly 130. It can be understood that the radial fan 142 can push the airflow to flow in a direction perpendicular to the axis (that is, radial direction), that is, in this embodiment, as shown in FIG. Figure 2As shown, the radial fan 142 can rotate with the drive shaft 111, thereby pushing the airflow to flow in a direction perpendicular to the drive shaft 111, and then blowing the airflow in the rotating space 131 toward the stator assembly 130. The radial fan 142 can be a centrifugal fan. The radius of the radial fan 142 can be set according to actual conditions (such as the demand for air volume, etc.), as long as the radius of the radial fan 142 is less than or equal to the radius of the rotating space 131, so that the radial fan 142 can be installed in the rotating space 131, and then the airflow in the rotating space 131 can be blown toward the stator assembly 130. The distance between the radial fan 142 and the third through hole 1241 can also be set according to actual conditions (such as the specific position of the stator assembly 130 for heat dissipation). Specifically, since the axial flow fan 141 is used to drive the airflow to pass through the second through hole 1231 and enter the installation space 121, the axial flow fan 141 can mainly dissipate heat to the end of the stator assembly 130 facing the second through hole 1231. Therefore, the radial flow fan 142 can be arranged at the end of the stator assembly 130 away from the second through hole 1231, so that the radial flow fan 142 can blow the airflow to the end of the stator assembly 130 away from the second through hole 1231, and then dissipate heat therefrom. In this way, the opposite ends of the stator assembly 130 can be cooled by the axial flow fan 141 and the radial flow fan 142, respectively, thereby improving the heat dissipation effect.

[0056] like Figure 2 , Figure 4 , Figure 5 and Figure 6As shown, in one embodiment, the housing 120 includes an annular housing 122, a first end cover 123 and a second end cover 124; the first end cover 123 and the second end cover 124 are respectively installed at opposite ends of the annular housing 122; the annular housing 122, the first end cover 123 and the second end cover 124 enclose the installation space 121; the annular housing 122 is connected to the stationary blade frame assembly 300; the second through hole 1231 is provided on the first end cover 123; the third through hole 1241 is provided on the second end cover 124. It can be understood that the connection method between the first end cover 123 and the annular housing 122 includes but is not limited to one or more of the methods of screw connection, riveting, welding or integral molding. The connection method between the second end cover 124 and the annular housing 122 includes but is not limited to one or more of the methods of screw connection, riveting, welding or integral molding. The second through hole 1231 can be provided on the first end cover 123 by casting or machining. The third through hole 1241 can also be provided on the second end cover 124 by casting or machining. The second through hole 1231 can be provided on the first end cover 123 according to actual conditions, as long as it is connected to the installation space 121. In one embodiment, the second through hole 1231 can be provided opposite to the stator assembly 130 and / or the rotor assembly 110, so that the airflow can be directly blown to the stator assembly 130 and / or the rotor assembly 110 through the second through hole 1231. The third through hole 1241 can also be provided on the second end cover 124 according to actual conditions, as long as it is connected to the installation space 121.

[0057] like Figure 2 and Figure 4 As shown, in one embodiment, a heat conductor 125 is provided on the outer side wall of the annular housing 122. The heat conductor 125 may be a heat dissipation fin or heat pipe that increases the heat dissipation area of ​​the annular housing 122, thereby improving the heat dissipation efficiency of the annular housing 122. It can be understood that the stator assembly 130 is mounted on the housing 120, and when the motor 100 is running, the heat generated by the stator assembly 130 can be conducted to the housing 120. The heat conductor 125 is arranged on the outer side wall of the annular housing 122 away from the stator assembly 130, thereby increasing the heat dissipation area of ​​the annular housing 122. When the motor 100 drives the ducted fan to rotate, the airflow generated by the ducted fan passes through the heat conductor 125, thereby taking away the heat on the heat conductor 125, improving the heat dissipation effect, and avoiding heat accumulation on the annular housing 122. The shape of the heat conducting member 125 can be set as required, as long as the heat dissipation area of ​​the annular housing 122 can be increased, thereby improving the heat dissipation efficiency of the annular housing 122 .

[0058] In this embodiment, while the fan assembly 140 is used to cool the heating elements in the installation space 121, the stator assembly 130 installed on the annular shell 122 is also cooled by the heat conductor 125 arranged on the outer wall of the annular shell 122, thereby further improving the heat dissipation efficiency of the motor 100.

[0059] An embodiment of the utility model further provides an aircraft, comprising the propulsion device. The specific structure of the propulsion device can refer to the above embodiment, and will not be repeated here.

[0060] In the aircraft of the above-mentioned embodiment of the utility model, the moving blade assembly 700 of the propulsion device is installed on the driving shaft of the motor 100. In this way, when the motor 100 is running and drives the moving blade assembly 700 to rotate, on the one hand, a driving force can be generated by the rotation of the moving blade assembly 700, so that the aircraft can be driven by the driving force and the thrust generated by the lift of the duct tube 200; on the other hand, the rotation of the moving blade assembly 700 can make the airflow entering the air duct accelerate along the axial direction of the driving shaft of the motor 100 to flow through the motor, thereby quickly taking away the heat generated by the motor 100, realizing air cooling and heat dissipation of the motor 100, thereby improving the heat dissipation efficiency of the motor 100, and facilitating improving the continuous output power of the motor 100; in addition, in the utility model, the motor 100 in the propulsion device can be installed in the air duct 210 through the lightweight stationary blade frame assembly 300, and the length of the drive shaft can be set shorter to realize the installation of the moving blade assembly 700, and there is no need to set up other special heat dissipation structures to dissipate heat from the motor, and its structure is simple and the weight is reduced.

[0061] The above are merely embodiments of the propulsion device and aircraft of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. A propulsion device, characterized in that: It includes a motor, a moving blade assembly, a stationary blade frame assembly, and a duct tube with an air duct. The motor is installed in the air duct through the stationary blade frame assembly; the moving blade assembly is installed on the driving shaft of the motor; the moving blade assembly is used to generate propulsion when driven to rotate by the motor, and guide the airflow to cool the motor.

2. The propulsion device according to claim 1, characterized in that: The stationary blade frame assembly includes a stationary blade bracket and at least one stationary blade installed on the stationary blade bracket; one end of the stationary blade away from the stationary blade bracket is connected to the inner wall of the air duct; and the motor is installed on the stationary blade bracket.

3. The propulsion device according to claim 2, characterized in that: The stationary blade support is provided with a receiving groove and a first through hole; the first through hole is connected between the air duct and the receiving groove.

4. The propulsion device according to claim 3, characterized in that: The propulsion device also includes a supporting flange; the supporting flange is used to fix the motor in the accommodating groove.

5. The propulsion device according to claim 4, characterized in that: The propulsion device also includes a first fairing; the first fairing is installed on the stationary blade bracket through the supporting flange, and an air outlet is provided at one end of the first fairing away from the stationary blade bracket; the end of the accommodating groove away from the first through hole is connected to the air outlet.

6. The propulsion device according to claim 1, characterized in that: The motor comprises a rotor assembly, a housing provided with an installation space, and a stator assembly installed on the housing and located in the installation space; the stator assembly is sleeved on the rotor assembly and is rotatably connected to the rotor assembly; the housing is provided with a second through hole and a third through hole respectively connected to opposite sides of the installation space; the housing is connected to the stationary blade frame assembly; The motor also includes a fan assembly connected to the rotor assembly, and the fan assembly is used to rotate with the rotor assembly to drive the air flow to pass through the second through hole and the installation space, and then flow out from the third through hole, thereby performing air cooling and heat dissipation on the heating element in the installation space.

7. The propulsion device according to claim 6, characterized in that: The impeller assembly includes an impeller hub having a fourth through hole, and impeller blades mounted on the outer side wall of the impeller hub; the impeller hub is fixedly mounted on the driving shaft of the rotor assembly; the fourth through hole is connected to the second through hole.

8. The propulsion device according to claim 7, characterized in that: The propulsion device also includes a second fairing installed at the end of the impeller hub away from the motor; an air inlet is provided at the end of the second fairing away from the impeller hub; and the end of the fourth through hole away from the motor is connected to the air inlet.

9. The propulsion device according to claim 6, characterized in that: The rotor assembly includes a driving shaft, the fan assembly includes an axial flow fan fixedly sleeved on the driving shaft, and the axial flow fan is located on a side of the second through hole away from the installation space; The axial flow fan is used to rotate along with the driving shaft to drive the air flow to flow out of the third through hole through the second through hole and the installation space.

10. The propulsion device according to claim 9, characterized in that: The stator assembly is provided with a rotating space connected to the installation space; the fan assembly further comprises a radial fan fixedly sleeved on the drive shaft, and the radial fan is located in the rotating space; The radial fan is used to rotate along with the driving shaft to blow the airflow in the rotating space toward the stator assembly.

11. The propulsion device according to claim 6, characterized in that: The housing comprises an annular shell, a first end cover and a second end cover; the first end cover and the second end cover are respectively mounted at opposite ends of the annular shell; the annular shell, the first end cover and the second end cover enclose the installation space; the annular shell is connected to the stationary blade frame assembly; The second through hole is arranged on the first end cover; and the third through hole is arranged on the second end cover.

12. The propulsion device according to claim 11, characterized in that A heat conducting member is arranged on the outer side wall of the annular shell.

13. An aircraft, characterized in that: Comprising a propulsion device as claimed in any one of claims 1 to 12.

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