阅读说明：本技术 一种无人机电机的高性能散热装置 (High-performance heat dissipation device for motor of unmanned aerial vehicle ) 是由 杨振河 朱海军 韩玉华 于 2019-11-12 设计创作，主要内容包括：本发明公开了一种无人机电机的高性能散热装置,包括主体,所述主体上连接有端盖,所述主体内设有转轴,所述转轴的一端贯穿端盖的中心处设于主体的外侧,所述转轴上连接有第一限位板,所述第一限位板设于主体的内侧；本发明中的一种无人机电机的高性能散热装置,其具有良好的散热性能,使用者可以持续使用,提高工作效率,通过散热薄膜的设置,可以减少转子与定子之间的摩擦,延长使用寿命；通过液体蒸发吸热的远离,可以实现对电机内部进行散热,从而可以降低电机内的温度,使得电机不易温度过高而损坏；通过单向阀的设置,可以将液体重复利用,节省了一定的资源,使得使用者不需要频繁的注入液体,一定程度上减轻使用者的负担。(The invention discloses a high-performance heat dissipation device of an unmanned aerial vehicle motor, which comprises a main body, wherein an end cover is connected to the main body, a rotating shaft is arranged in the main body, one end of the rotating shaft penetrates through the center of the end cover and is arranged on the outer side of the main body, a first limiting plate is connected to the rotating shaft, and the first limiting plate is arranged on the inner side of the main body; the high-performance heat dissipation device for the motor of the unmanned aerial vehicle has good heat dissipation performance, can be continuously used by a user, improves the working efficiency, can reduce the friction between a rotor and a stator through the arrangement of the heat dissipation film, and prolongs the service life; the heat absorption is far away through the evaporation of the liquid, so that the heat dissipation can be realized in the motor, the temperature in the motor can be reduced, and the motor is not easy to damage due to overhigh temperature; through the setting of check valve, can save certain resource with liquid reuse for the user does not need frequent injection liquid, alleviates user's burden to a certain extent.)

1. The utility model provides a high performance heat abstractor of unmanned aerial vehicle motor, its characterized in that, includes main part (1), be connected with end cover (2) on main part (1), be equipped with pivot (3) in main part (1), the center department that the one end of pivot (3) runs through end cover (2) locates the outside of main part (1), be connected with first limiting plate (4) on pivot (3), the inboard of main part (1) is located to first limiting plate (4), be connected with bearing (5) on pivot (3), bearing (5) are located the downside of first limiting plate (4), the outside of bearing (5) is connected with permanent magnet (6), be connected with stator (7) on the inside wall of main part (1), stator (7) in-connection has coil (8) and wire (9), and interval arrangement between coil (8) and wire (9), one of end that end cover (2) was kept away from in pivot (3) is served and is connected with second limiting plate (10), be equipped with in the lateral wall of main part (1) and accomodate chamber (12), it is equipped with fin (14) in chamber (12) to accomodate, fin (14) and chamber (12) of accomodating are formed with cavity and exchange chamber (15), it has volatile liquid (13) to fill in the cavity.

2. The high-performance heat dissipation device of unmanned aerial vehicle motor of claim 1, characterized in that, the material of main part (1) and end cover (2) is the castable aluminium.

3. The high-performance heat dissipation device for the unmanned aerial vehicle motor, according to claim 1, wherein the material of the rotating shaft (3) is high-quality carbon steel, and the high-quality carbon steel is 45# steel.

4. The high-performance heat dissipation device for the unmanned aerial vehicle motor, according to claim 1, wherein the bearing (5) is made of roll bearing steel of roll 15.

5. The high-performance heat dissipation device of the unmanned aerial vehicle motor, according to claim 1, is characterized in that a heat dissipation film (11) is arranged between the permanent magnet (6) and the stator (7).

6. The high-performance heat dissipation device of the unmanned aerial vehicle motor, according to claim 1, characterized in that a one-way valve (16) is connected to the fin (14).

7. The high-performance heat dissipation device for the motor of the unmanned aerial vehicle as claimed in claim 1, wherein graphene (17) is connected between the main body (1) and the stator (7), and a through hole (18) matched with the graphene (17) is formed in the lower bottom wall of the main body (1).

8. The high-performance heat dissipation device for the unmanned aerial vehicle motor, according to claim 1, wherein the coil (8) is made of red copper, and the number of winding turns of the wire (9) is 8.

9. The high-performance heat sink for the motor of the unmanned aerial vehicle as claimed in claim 1, wherein the fins (14) have a density greater than water vapor and less than water.

10. The high-performance heat dissipation device for the motor of the unmanned aerial vehicle as claimed in claim 1, wherein the volatile liquid (13) is made of alcohol, water or other volatile liquid.

Technical Field

The invention relates to the technical field of heat dissipation devices, in particular to a high-performance heat dissipation device for an unmanned aerial vehicle motor.

Background

The equipment on the existing market is little to including household electrical appliances, digital products, projecting apparatus, and is big to including the lathe, heavily doing all can use heat abstractor to machinery, through heat abstractor's setting, can reduce the temperature in the equipment for equipment is difficult to damage because the temperature is too high, and current heat abstractor also makes manifold, include, fin, radiator etc. and its radiating mode is the diverse also, and radiating mode has the radiation heat dissipation, and the conduction heat dissipation, the convection current heat dissipation, the evaporation heat dissipation. Through the heat dissipation of multiple mode, can reach final heat dissipation purpose.

The cooling system is divided into air cooling and water cooling. An air cooling system using air as a cooling medium, and a water cooling system using a cooling liquid as a cooling medium. The water cooling system is generally composed of a water pump, a radiator, a cooling fan, a thermostat, a compensation water bucket, a machine body, a water jacket and other accessories. The radiator is responsible for cooling circulating water, a water pipe and radiating fins of the radiator are made of aluminum materials, the aluminum water pipe is made into a flat shape, the radiating fins are corrugated, the radiating performance is emphasized, the mounting direction is perpendicular to the air flowing direction, the wind resistance is small as much as possible, and the cooling efficiency is high. The coolant flows through the radiator core, and the air passes through the radiator core. The radiator is a heat exchanger because the hot coolant cools by radiating heat to the air, and because the cold air heats by absorbing the heat radiated by the coolant.

The current unmanned aerial vehicle motor lacks necessary heat abstractor in the use, relies on the nature heat dissipation, and its not only rate of heat dissipation is slow, and the radiating effect is also not enough obvious moreover, and unmanned aerial vehicle uses a period after, and the user needs the decommissioning, treats that motor cooling later side can continue to use, has just so caused the problem that user work efficiency is low.

Therefore, to above-mentioned technical problem, it is necessary to provide a high performance heat abstractor of unmanned aerial vehicle motor.

Disclosure of Invention

In view of this, the present invention provides a high performance heat dissipation device for an unmanned aerial vehicle motor, which has good heat dissipation performance, can be continuously used by a user, improves work efficiency, and can reduce friction between a rotor and a stator and prolong service life by arranging a heat dissipation film; the heat absorption is far away through the evaporation of the liquid, so that the heat dissipation can be realized in the motor, the temperature in the motor can be reduced, and the motor is not easy to damage due to overhigh temperature; through the setting of check valve, can save certain resource with liquid reuse for the user does not need frequent injection liquid, alleviates user's burden to a certain extent.

In order to achieve the above object, an embodiment of the present invention provides the following technical solutions:

the utility model provides a high performance heat abstractor of unmanned aerial vehicle motor, includes the main part, be connected with the end cover in the main part, be equipped with the pivot in the main part, the one end of pivot runs through the center department of end cover and locates the outside of main part, be connected with first limiting plate in the pivot, the inboard of main part is located to first limiting plate, be connected with the bearing in the pivot, the downside of first limiting plate is located to the bearing, the outside of bearing is connected with the permanent magnet, be connected with the stator on the inside wall of main part, stator in-connection has coil and wire, and interval arrangement between coil and the wire, the pivot is kept away from one of end cover and is served and be connected with the second limiting plate, be equipped with in the lateral wall of main part and accomodate the chamber, it has cavity and exchange chamber to accomodate the intracavity.

As a further improvement of the invention, the main body and the end cover are both made of wrought aluminum, so that the service lives of the main body and the end cover are easily prolonged.

As a further improvement of the invention, the material of the rotating shaft is high-quality carbon steel, and the high-quality carbon steel is 45# steel, so that the rotating shaft is not easy to generate heat and damage.

As a further improvement of the invention, the bearing is made of roll bearing steel of 15, so that the durability of the bearing is improved.

As a further improvement of the invention, a heat dissipation film is arranged between the permanent magnet and the stator, so that the friction between the permanent magnet and the stator is reduced.

As a further improvement of the invention, the fins are connected with one-way valves, so that the volatile liquid is easy to recycle.

As a further improvement of the invention, graphene is connected between the main body and the stator, and a through hole matched with the graphene is formed in the lower bottom wall of the main body, so that bottom heat dissipation is easily performed on the permanent magnet and the stator.

As a further improvement of the invention, the coil is made of red copper, and the number of winding turns of the lead is 8.

As a further improvement of the invention, the fins have a density greater than water vapor and less than water so that water vapor can pass through the fins and liquid cannot pass through the fins.

As a further improvement of the invention, the volatile liquid is made of alcohol, water or other volatile liquid, and is easy to evaporate and absorb heat.

The invention has the beneficial effects that: the high-performance heat dissipation device for the motor of the unmanned aerial vehicle has good heat dissipation performance, can be continuously used by a user, improves the working efficiency, can reduce the friction between a rotor and a stator through the arrangement of the heat dissipation film, and prolongs the service life; the heat absorption is far away through the evaporation of the liquid, so that the heat dissipation can be realized in the motor, the temperature in the motor can be reduced, and the motor is not easy to damage due to overhigh temperature; through the setting of check valve, can save certain resource with liquid reuse for the user does not need frequent injection liquid, alleviates user's burden to a certain extent.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a high-performance heat dissipation device of an unmanned aerial vehicle motor according to an embodiment of the present invention;

FIG. 2 is a schematic view of the structure at A in FIG. 1;

fig. 3 is a perspective view of a high-performance heat dissipation device of an unmanned aerial vehicle motor according to an embodiment of the present invention.

In the figure: 1. the heat-dissipating device comprises a main body, 2 parts of an end cover, 3 parts of a rotating shaft, 4 parts of a first limiting plate, 5 parts of a bearing, 6 parts of a permanent magnet, 7 parts of a stator, 8 parts of a coil, 9 parts of a lead, 10 parts of a second limiting plate, 11 parts of a heat-dissipating film, 12 parts of a containing cavity, 13 parts of volatile liquid, 14 parts of fins, 15 parts of an exchange cavity, 16 parts of a one-way valve, 17 parts of graphene and 18 parts of a through hole.

Detailed Description

In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the various drawings of the present invention, certain dimensions of structures or portions are exaggerated relative to other structures or portions for ease of illustration and, therefore, are used only to illustrate the basic structure of the subject matter of the present invention.

Terms such as "left", "right", and the like, used herein to denote relative spatial positions, are used for ease of description to describe one element or feature's relationship to another element or feature as illustrated in the figures. The spatially relative positional terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "to the right" of other elements or features would then be oriented "to the left" of the other elements or features. Thus, the exemplary term "right side" may encompass both left and right orientations. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

Referring to fig. 1 to 3, in an embodiment of the present invention, a high performance heat dissipation device for an unmanned aerial vehicle motor includes a main body 1, an end cover 2 connected to the main body 1, a rotating shaft 3, a bearing 5 mounted on the rotating shaft 3, a permanent magnet 6, a coil 8, and a lead 9.

Referring to fig. 3, an end cover 2 is connected to a main body 1, a rotating shaft 3 is arranged in the main body 1, one end of the rotating shaft 3 penetrates through the center of the end cover 2 and is arranged on the outer side of the main body 1, a first limiting plate 4 is connected to the rotating shaft 3, and the first limiting plate 4 is arranged on the inner side of the main body 1.

The main body 1 and the end cover 2 are made of wrought aluminum, so that the service lives of the main body 1 and the end cover 2 are easily prolonged, and the rotating shaft 3 is made of high-quality carbon steel which is 45# steel, so that the rotating shaft 3 is not easy to generate heat and damage.

Refer to fig. 1, be connected with bearing 5 in the pivot 3, bearing 5's material is for rolling the bearing steel of luo 15, improve bearing 5's durability, bearing 5 locates first limiting plate 4's downside, easily spacing bearing 5 and permanent magnet 6, bearing 5's the outside is connected with permanent magnet 6, be connected with stator 7 on the inside wall of main part 1, be equipped with radiating film 11 between permanent magnet 6 and the stator 7, reduce the friction of permanent magnet 6 and stator 7, stator 7 in-connection has coil 8 and wire 9, and interval arrangement between coil 8 and the wire 9, coil 8's material is red copper, the winding number of turns of wire 9 is 8 circles, pivot 3 is kept away from one of end cover 2 and is served and is connected with second limiting plate 10.

Referring to fig. 2, the side wall of the main body 1 is provided with a storage cavity 12, the storage cavity 12 is provided with fins 14 for easy heat exchange, the fins 14 are connected with one-way valves 16 for easy recycling of the volatile liquid 13, the fins 14 and the storage cavity 12 are formed with cavities and a exchange cavity 15, the cavities are filled with the volatile liquid 13, and the volatile liquid 13 is easy to evaporate and absorb heat, so that the cooling effect can be achieved.

Specifically, be connected with graphite alkene 17 between main part 1 and the stator 7, open on the lower diapire of main part 1 and chisel and have with graphite alkene 17 assorted through-hole 18, easily carry out the bottom heat dissipation to permanent magnet 6 and stator 7, volatile liquid 13's material is alcohol, water or other volatile liquid, easily evaporates the heat absorption, and the density of fin 14 is greater than vapor and is less than water, makes vapor can pass fin 14, and liquid can not pass fin 14.

The working principle is as follows: after the motor is powered on, the coil 8 and the lead 9 generate a magnetic field under the combined action, so that the permanent magnet 6 on the rotating shaft 3 can make magnetic induction line cutting motion in the magnetic field, the heat dissipation film 11 between the permanent magnet 6 and the stator 7 can reduce friction and prolong the service life of the motor, heat generated after the permanent magnet 6 and the stator 7 rub is transferred to the volatile liquid 13, the volatile liquid 13 starts to volatilize after being heated and becomes gas, the gas can enter the exchange cavity 15 through the fins 14, the volatile liquid 13 cannot pass through the fins 14, the volatile liquid 13 which becomes gas is liquefied when encountering the fins 14 and becomes liquid again, the liquid is replenished back to the cavity under the action of the check valve 16, so that the liquid can be recycled, the inside of the motor can be radiated, the graphene 17 in the main body 1 can also play a role of heat radiation, and the heat can flow out of the through hole 18, thus, the temperature in the main body 1 can be kept low and the main body can be used continuously.

According to the technical scheme, the invention has the following beneficial effects:

the high-performance heat dissipation device for the motor of the unmanned aerial vehicle has good heat dissipation performance, can be continuously used by a user, improves the working efficiency, can reduce the friction between a rotor and a stator through the arrangement of the heat dissipation film, and prolongs the service life; the heat absorption is far away through the evaporation of the liquid, so that the heat dissipation can be realized in the motor, the temperature in the motor can be reduced, and the motor is not easy to damage due to overhigh temperature; through the setting of check valve, can save certain resource with liquid reuse for the user does not need frequent injection liquid, alleviates user's burden to a certain extent.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.