阅读说明：本技术 航空电机 (Aviation motor ) 是由 张博 李彦祥 刘立军 张腾 卢彬 高跃 刘栋良 邓春志 于 2021-05-28 设计创作，主要内容包括：本发明公开了航空电机,涉及电机技术领域,所述罩体套设在转轴的外周,所述罩体内侧壁设有磁钢,所述第一端盖设有扇叶,所述扇叶和罩体之间具有出风口；所述第二端盖具有第一通风口和第二通风口,所述第一通风口位于罩体和铁芯之间,所述第二通风口位于转轴和铁芯之间,所述出风口分别与第一通风口和第二通风口连通。转轴转动带动第一端盖上的扇叶转动,扇叶转动产生风压,风压将空气从第二端盖的第一通风口和第二通风口进入电机内部,空气由第一通风口进入罩体内部,带走磁钢表面的热量,由出风口排出；同时空气由第二通风口进入铁芯内部,带走缠绕在铁芯上的绕组产生的热量,由出风口排出,使电机内部的热量得到显著降低。(The invention discloses an aviation motor, and relates to the technical field of motors, wherein a cover body is sleeved on the periphery of a rotating shaft, magnetic steel is arranged on the inner side wall of the cover body, a fan blade is arranged on a first end cover, and an air outlet is formed between the fan blade and the cover body; the second end cover is provided with a first ventilation opening and a second ventilation opening, the first ventilation opening is located between the cover body and the iron core, the second ventilation opening is located between the rotating shaft and the iron core, and the air outlet is communicated with the first ventilation opening and the second ventilation opening respectively. The rotating shaft rotates to drive the fan blades on the first end cover to rotate, the fan blades rotate to generate wind pressure, the wind pressure enables air to enter the motor from the first ventilation opening and the second ventilation opening of the second end cover, the air enters the cover body from the first ventilation opening, heat on the surface of the magnetic steel is taken away, and the air is discharged from the air outlet; meanwhile, air enters the iron core from the second air inlet, takes away heat generated by a winding wound on the iron core and is discharged from the air outlet, so that the heat in the motor is remarkably reduced.)

1. The aviation motor is characterized by comprising a stator assembly and a rotor assembly, wherein the rotor assembly comprises a first end cover, a cover body and a rotating shaft, the first end cover is respectively connected with the rotating shaft and the cover body, the cover body is sleeved on the periphery of the rotating shaft, magnetic steel is arranged on the inner side wall of the cover body, the first end cover is provided with fan blades, and an air outlet is formed between the fan blades and the cover body;

stator module includes iron core and second end cover, the iron core is installed on the second end cover, the iron core cover is established in the pivot periphery, cover the body cover and establish in the iron core periphery, the winding has on the iron core, the second end cover has first vent and second vent, first vent is located between the cover body and the iron core, the second vent is located between pivot and the iron core, the air outlet communicates with first vent and second vent respectively.

2. The aero-motor as claimed in claim 1, wherein the fan blades are in a shape of a straight plate.

3. The aero-motor as claimed in claim 1, wherein the fan blades are distributed along a circumference of the first end surface, and the number of the fan blades is an odd number.

4. The aviation motor of claim 1, wherein an air guide cover is disposed between the rotating shaft and the iron core, the air guide cover is sleeved on the outer periphery of the iron core, and one end of the air guide cover covers a part of the second ventilation opening.

5. The aero-motor according to claim 4, wherein a support frame is arranged between the wind scooper and the rotating shaft, the rotating shaft is mounted on the support frame through a bearing, the support frame is mounted on the second end face, and the support frame penetrates through the wind scooper to be matched with the iron core.

6. The aircraft motor of claim 5, wherein the support frame comprises a support cylinder and support rods distributed along the circumference of the support cylinder, the support rods are matched with the iron core, and hollow cavities are arranged in the support rods.

7. The aircraft motor as claimed in claim 6, wherein one end of the support rod is mounted on the support cylinder, the other end of the support rod is provided with a clamping protrusion, and the iron core is provided with a clamping groove matched with the clamping protrusion.

8. The aircraft motor as claimed in claim 4, wherein the iron core is provided with heat dissipation fins on the inner side wall close to the wind scooper, and the heat dissipation fins are distributed along the circumference of the iron core.

9. An aircraft electric motor according to claim 8, wherein the width of the heat sink tapers from one end mounted on the core to the other.

10. The aircraft motor of claim 6, wherein the outer wall of the support cylinder is provided with reinforcing ribs distributed along the circumference of the support cylinder.

Technical Field

The invention relates to the technical field of motors, in particular to an aviation motor.

Background

The aero-motor generally needs to meet the requirements of high power, small volume and light weight, namely the requirement of high power density. The design of high power density can make the heat load of motor higher, can produce a large amount of heat energy when the motor operation, if these heat energy can not in time be taken away, can directly lead to serious problems such as motor insulation decline, insulation breakdown, permanent magnet demagnetization. Therefore, the problem of heat dissipation of the aviation motor with high power density is very important. At present, a motor with high power density is cooled by a liquid cooling mode commonly used, wherein cooling media such as water, oil and the like, however, the liquid cooling mode needs to additionally carry a pump source and a system of water or oil, and if the liquid cooling mode is used on an aviation motor, the problems of overlarge volume and heavy weight of the aviation motor are directly caused.

Disclosure of Invention

1. Technical problem to be solved by the invention

The invention provides an aviation motor, aiming at the technical problems that the size of the aviation motor is overlarge and the weight of the aviation motor is heavier due to a motor cooling system, and the heat in the motor is obviously reduced on the premise of not increasing the size of the motor.

2. Technical scheme

In order to solve the problems, the technical scheme provided by the invention is as follows: an aviation motor comprises a stator assembly and a rotor assembly, wherein the rotor assembly comprises a first end cover, a cover body and a rotating shaft, the first end cover is respectively connected with the rotating shaft and the cover body, the cover body is sleeved on the periphery of the rotating shaft, magnetic steel is arranged on the inner side wall of the cover body, fan blades are arranged on the first end cover, and an air outlet is formed between the fan blades and the cover body; stator module includes iron core and second end cover, the iron core is installed on the second end cover, the iron core cover is established in the pivot periphery, cover the body cover and establish in the iron core periphery, the winding has on the iron core, the second end cover has first vent and second vent, first vent is located between the cover body and the iron core, the second vent is located between pivot and the iron core, the air outlet communicates with first vent and second vent respectively.

Optionally, the fan blades are straight plates.

Optionally, the fan blades are distributed along the circumference of the first end face, and the number of the fan blades is odd.

Optionally, an air guide cover is arranged between the rotating shaft and the iron core, the air guide cover is sleeved on the periphery of the iron core, and one end of the air guide cover covers part of the second ventilation opening.

Optionally, a support frame is arranged between the wind scooper and the rotating shaft, the rotating shaft is mounted on the support frame through a bearing, the support frame is mounted on the second end face, and the support frame penetrates through the wind scooper to be matched with the iron core.

Optionally, the support frame includes a support section of thick bamboo and the bracing piece that distributes along a support section of thick bamboo circumference, bracing piece and iron core cooperation, and have well cavity in the bracing piece.

Optionally, one end of the supporting rod is mounted on the supporting cylinder, the other end of the supporting rod is provided with a clamping protrusion, and the iron core is provided with a clamping groove matched with the clamping protrusion.

Optionally, the iron core is provided with cooling fins on an inner side wall close to the air guide cover, and the cooling fins are distributed along the circumference of the iron core.

Optionally, the width of the heat sink decreases gradually from one end mounted on the core to the other end.

Optionally, the outer wall of the support cylinder is provided with reinforcing ribs, and the reinforcing ribs are distributed along the circumference of the support cylinder.

3. Advantageous effects

Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:

(1) when the aviation motor provided by the embodiment of the application is used, the rotating shaft rotates to drive the fan blades on the first end cover to rotate, the fan blades rotate to generate wind pressure, air enters the motor from the first ventilation opening and the second ventilation opening of the second end cover by the wind pressure, the air enters the cover body from the first ventilation opening, takes away heat on the surface of the magnetic steel and is discharged from the air outlet; meanwhile, air enters the iron core from the second air inlet, takes away heat generated by a winding wound on the iron core and is discharged from the air outlet, and on the premise of not increasing the size of the motor, the heat in the motor is remarkably reduced.

(2) The aviation motor that this application embodiment provided, well cavity design can effectively reduce motor weight, makes motor weight reduce to lightest under the condition of guaranteeing intensity.

(3) The aviation motor that this application embodiment provided, draw-in groove and card protruding cooperation make bracing piece and iron core interference pressure equipment together, ensure motor moment transmission.

Drawings

Fig. 1 is a sectional view of an aero-motor according to an embodiment of the present invention.

Fig. 2 is a schematic view of a first vent and a second vent of an aero-motor according to an embodiment of the present invention.

Fig. 3 is a schematic partial view of an iron core of an aero-motor according to an embodiment of the present invention.

Fig. 4 is a bracket and a partial schematic view of an aero-motor according to an embodiment of the present invention.

Fig. 5 is a schematic view of a fan blade of an aero-motor according to an embodiment of the present invention.

The figures are numbered: 1. a rotor assembly; 11. a first end cap; 111. a fan blade; 112. an air outlet; 12. a cover body; 121. magnetic steel; 13. a rotating shaft; 2. a stator assembly; 21. an iron core; 211. a card slot; 212. a heat sink; 22. a second end cap; 221. a first vent; 222. a second vent; 23. a winding; 24. a wind scooper; 25. a support frame; 251. a support cylinder; 2511. reinforcing ribs; 252. a support bar; 2521. a hollow cavity; 2522. clamping convex; 26. and a bearing.

Detailed Description

For a further understanding of the present invention, reference will now be made in detail to the embodiments illustrated in the drawings.

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings. The terms first, second, and the like in the present invention are provided for convenience of describing the technical solution of the present invention, and have no specific limiting effect, but are all generic terms, and do not limit the technical solution of the present invention. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. The technical solutions in the same embodiment and the technical solutions in different embodiments can be arranged and combined to form a new technical solution without contradiction or conflict, and the technical solutions are within the scope of the present invention.

Example 1

With reference to fig. 1-5, the aviation motor of this embodiment includes a stator assembly 2 and a rotor assembly 1, where the rotor assembly 1 includes a first end cover 11, a cover 12 and a rotating shaft 13, the first end cover 11 is connected to the rotating shaft 13 and the cover 12, the cover 12 is sleeved on the periphery of the rotating shaft 13, magnetic steel 121 is disposed on the inner side wall of the cover 12, the first end cover 11 is provided with a fan blade 111, and an air outlet 112 is disposed between the fan blade 111 and the cover 12; stator module 2 includes iron core 21 and second end cover 22, iron core 21 installs on second end cover 22, iron core 21 cover is established in pivot 13 periphery, cover body 12 cover is established in iron core 21 periphery, the winding has winding 23 on the iron core 21, second end cover 22 has first vent 221 and second vent 222, first vent 221 is located between cover body 12 and the iron core 21, second vent 222 is located between pivot 13 and the iron core 21, air outlet 112 communicates with first vent 221 and second vent 222 respectively. When the motor is used, the rotating shaft 13 rotates to drive the fan blades 111 on the first end cover 11 to rotate, the fan blades 111 rotate to generate wind pressure, the wind pressure enables air to enter the motor from the first ventilation opening 221 and the second ventilation opening 222 of the second end cover 22, the air enters the cover body 12 from the first ventilation opening 221, heat on the surface of the magnetic steel 121 is taken away, and the air is discharged from the air outlet 112; meanwhile, air enters the inside of the iron core 21 through the second ventilation opening 222, takes away heat generated by the winding 23 wound on the iron core 21, and is discharged through the ventilation opening 112, so that the heat inside the motor is remarkably reduced on the premise of not increasing the volume of the motor.

Example 2

With reference to fig. 1 to 5, compared with the technical solution of embodiment 1, the aero-motor of this embodiment may be improved as follows: the fan blades 111 are straight plates. When the rotating shaft 13 rotates counterclockwise or clockwise, the straight fan blades 111 can keep the air volume and the air pressure unchanged.

Example 3

With reference to fig. 1 to 5, compared with the technical solution of embodiment 1 or 2, the aero-motor of this embodiment may be improved as follows: the fan blades 111 are distributed along the circumference of the first end face, and the number of the fan blades 111 is odd. If even number of symmetrically-shaped blades 111 are adopted, the balance is not well adjusted, the system is easy to resonate, if the material of the blades cannot resist fatigue caused by vibration, the blades or the spindle can be broken, and the odd number of blades 111 are more stable in rotation.

Example 4

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 3, the aero-motor of this embodiment may be improved as follows: an air guiding cover 24 is arranged between the rotating shaft 13 and the iron core 21, the air guiding cover 24 is sleeved on the periphery of the iron core 21, and one end of the air guiding cover 24 covers part of the second ventilation opening 222. The wind scooper 24 is cylindrical, and when wind enters, the wind inlet area of the second wind inlet 222 is small, so that the wind pressure is increased, the flow rate of the wind inlet is further increased, the heat dissipation efficiency is improved, and the heat dissipation effect is increased.

Example 5

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 4, the aero-motor of this embodiment may be improved as follows: a support frame 25 is arranged between the wind scooper 24 and the rotating shaft 13, the rotating shaft 13 is mounted on the support frame 25 through a bearing 26, the support frame 25 is mounted on the second end face, and the support frame 25 penetrates through the wind scooper 24 to be matched with the iron core 21. The support frame 25 is matched with the iron core 21 to ensure the torque transmission of the motor.

Example 6

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 5, the aero-motor of this embodiment may be improved as follows: the supporting frame 25 includes a supporting cylinder 251 and supporting rods 252 distributed along the circumference of the supporting cylinder 251, the supporting rods 252 are engaged with the iron core 21, and a hollow cavity 2521 is formed in the supporting rods 252. In other embodiments, the hollow cavity 2521 may also be rectangular, a waist-shaped hole or hexagonal, and the hollow cavity 2521 may be designed to effectively reduce the weight of the motor, so as to reduce the weight of the motor to the lightest value while ensuring the strength.

Example 7

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 6, the aero-motor of this embodiment may be improved as follows: one end of the supporting rod 252 is mounted on the supporting cylinder 251, the other end of the supporting rod 252 has a locking protrusion 2522, and the iron core 21 has a locking groove 211 matched with the locking protrusion 2522. The locking slot 211 is matched with the locking protrusion 2522, so that the supporting rod 252 and the iron core 21 are pressed together in an interference fit manner, and the torque transmission of the motor is ensured. The end of the support rod 252 that is engaged with the iron core 21 may be an arc surface, and the locking protrusion 2522 may be rectangular, triangular, or hexagonal.

Example 8

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 7, the aero-motor of this embodiment may be improved as follows: the inner side wall of the iron core 21 close to the wind scooper 24 is provided with cooling fins 212, and the cooling fins 212 are distributed along the circumference of the iron core 21. The heat dissipation fins 212 increase the heat dissipation area and improve the heat dissipation efficiency.

Example 9

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 8, the aero-motor of this embodiment may be improved as follows: the width of the heat sink 212 is gradually reduced from one end mounted on the core 21 to the other end. The heat sink 212 is a cone, so that natural convection is formed between the upper part and the lower part of the heat sink 212, which is beneficial to air circulation and heat dissipation, and can rapidly take away heat generated by the winding 23, and the heat dissipation efficiency is high. The heat sink 212 may have protrusions, which may be circular, square or other shapes, and the arrangement of the protrusions may further increase the heat dissipation area.

Example 10

With reference to fig. 1 to 5, compared with any of the technical solutions of embodiments 1 to 9, the aero-motor of this embodiment may be improved as follows: the outer wall of the supporting cylinder 251 is provided with reinforcing ribs 2511, and the reinforcing ribs 2511 are distributed along the circumference of the supporting cylinder 251. The reinforcing ribs 2511 can enhance the strength of the support frame 25, and the end faces of the reinforcing ribs 2511 can be perforated, so that the support frame 25 can be conveniently installed on the second end face by using screws.

The present invention and its embodiments have been described above schematically, without limitation, and what is shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. Therefore, if the person skilled in the art receives the teaching, without departing from the spirit of the invention, the person skilled in the art shall not inventively design the similar structural modes and embodiments to the technical solution, but shall fall within the scope of the invention.