WO2019204956A1

WO2019204956A1 - Power component of unmanned aerial vehicle, and unmanned aerial vehicle

Info

Publication number: WO2019204956A1
Application number: PCT/CN2018/084019
Authority: WO
Inventors: 王佳迪; 黄华; 肖乐
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2018-04-23
Filing date: 2018-04-23
Publication date: 2019-10-31
Also published as: CN110382356B; CN110382356A

Abstract

A power component (300) of an unmanned aerial vehicle, and an unmanned aerial vehicle. The power component (300) comprises: a propeller (1); a motor (2) fixedly connected to the propeller (1) and used for driving the propeller (1) to rotate; and an electronic speed control component (3) electrically connected to the motor (2) and used for controlling the motor (2) to rotate. The electronic speed control component (3) and the motor (2) are arranged vertically, and the propeller (1) is located above the electronic speed control component (3) and the motor (2). The electronic speed control component (3) is provided with a heat-radiating structure (31) provided towards the propeller (1). The propeller (1) is rotated to drive the air to flow to the heat-radiating structure (31). By disposing the heat-radiating structure (31) on the electronic speed control component (3), and by means of matching of the airflow and the heat-radiating structure (31) driven by rotation of the propeller (1), the heat in the electronic speed control component (3) can be taken away in time, and the stable operation of the electronic speed control component (3) is ensured. Moreover, the heat-radiating structure (31) is directly provided towards the propeller (1) for improving the heat-radiating speed. Furthermore, the existing fan is replaced with the power propeller (1) of the unmanned aerial vehicle to reduce the weight of the unmanned aerial vehicle increased by the fan, and reduce costs.

Description

Power components and drones of drones

Technical field

The invention relates to the field of drones, in particular to a power component and a drone of a drone.

Background technique

During the flight of the drone, the ESC is used as the driving component for driving the motor. The heat dissipation is very large, and it needs to be dissipated in time to avoid affecting the work of the ESC and the UAV flight is affected. Conventional heat dissipation structures require additional heat sinks such as heat sinks, heat pipes, and fans. If the above heat dissipation structure is used on the ESC, the whole opportunity increases the extra weight. However, drones are very sensitive to weight. The increase in weight will cause the drone's battery life to drop.

Summary of the invention

The invention provides a power component and a drone of a drone.

According to a first aspect of the present invention, a power assembly for a drone is provided, comprising:

propeller;

a motor fixedly coupled to the propeller for driving the propeller to rotate;

An electrical adjustment component electrically connected to the motor for controlling rotation of the motor;

Wherein the electric modulation assembly and the motor are arranged in a vertical arrangement, and the propeller is located above the electric modulation assembly and the motor;

The electric adjusting component is provided with a heat dissipating structure, the heat dissipating structure is disposed toward the propeller, and the propeller rotates to drive air to the heat dissipating structure.

According to a second aspect of the present invention, a drone includes a body, an arm connected to the body, and a power assembly, wherein the power assembly fixedly connects the arm away from the body At one end, to provide flight power to the drone, the power components include:

propeller;

a motor fixedly coupled to the propeller for driving the propeller to rotate;

It can be seen from the technical solutions provided by the embodiments of the present invention that the heat dissipation structure is arranged on the ESC assembly, and the heat of the ESC component can be taken away in time by the cooperation of the airflow and the heat dissipation structure driven by the rotation of the propeller to ensure the ESC. The components work steadily. Moreover, the heat dissipation structure is disposed directly toward the propeller to increase the speed of heat dissipation. Furthermore, replacing the existing fan with the power propeller of the drone itself reduces the weight that the fan brings to the drone and can reduce the cost.

DRAWINGS

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the present invention. Other drawings may also be obtained from those of ordinary skill in the art in view of the drawings.

1 is a schematic view showing the structure splitting of a power assembly according to an embodiment of the present invention;

Figure 2 is a perspective view of a power assembly in accordance with an embodiment of the present invention;

3 is a schematic view showing the structure splitting of an ESC assembly according to an embodiment of the present invention;

4 is a partial structural view of an unmanned aerial vehicle according to an embodiment of the present invention.

Reference mark:

100: the fuselage;

200: arm;

300: power component; 1: propeller; 2: motor; 21: drive shaft; 3: ESC assembly; 31: heat dissipation structure; 32: ESC housing; 321: upper housing; 322: lower housing; 33: drive Circuit; 4: motor base; 41: bushing; 42: motor mounting section; 43: avoidance slot.

detailed description

The technical solutions in the embodiments of the present invention are clearly and completely described in the following with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

The power module and the drone of the drone of the present invention will be described in detail below with reference to the accompanying drawings. The features of the embodiments and embodiments described below may be combined with each other without conflict.

1 to 3, an embodiment of the present invention provides a power assembly 300 of a drone, which may include a propeller 1, a motor 2, and an ESC assembly 3. The motor 2 is fixedly connected to the propeller 1 for driving the propeller 1 to rotate, thereby providing flight power to the drone. The electric adjusting component 3 is electrically connected to the motor 2 for controlling the rotation of the motor 2, and then driving the propeller 1 to rotate by the motor 2. It should be noted that the present embodiment can drive the motor 2 through the ESC assembly 3 to adopt the existing driving mode.

Further, in this embodiment, the ESC assembly 3 and the motor 2 are arranged in a vertical arrangement. For example, the ESC assembly 3 may be disposed above the motor 2, or the electric device may be The adjustment component 3 is disposed under the motor 2, and can be selected according to the installation requirements of the power component 300. And, the propeller 1 is located above the electric modulation assembly 3 and the motor 2.

The heat-dissipating component 3 of the embodiment is provided with a heat-dissipating structure 31. By providing the heat-dissipating structure 31 on the electrical-modulating component 3, the airflow and the heat-dissipating structure 31 are rotated by the rotation of the propeller 1 to take away the electrical component 3 in time. The heat ensures that the ESC assembly 3 works steadily. Specifically, when the drone is in operation, the motor 2 drives the propeller 1 to rotate, thereby causing the airflow to flow, and the airflow flows to the heat dissipation structure 31 to achieve heat dissipation to the ESC assembly 3. Moreover, by replacing the existing fan with the power propeller 1 of the drone itself, the weight of the fan to the drone is reduced, and the cost can be reduced. In this embodiment, the heat dissipation structure 31 is disposed toward the propeller 1 , and the propeller 1 rotates to drive air to the heat dissipation structure 31 . The heat dissipation structure 31 is disposed directly toward the propeller 1 to increase the speed of heat dissipation. Preferably, the heat dissipation structure 31 is disposed on the top of the ESC assembly 3.

1 and 3, the ESC assembly 3 can include an ESC housing 32 and a drive circuit 33. Wherein, the ESC housing 32 is coupled to the motor 2, for example, the ESC housing 32 can be secured to the motor 2 by snapping, threading or other securing means. The driving circuit 33 is electrically connected to the motor 2, and on the one hand, the driving circuit 33 can convert the control signal from the flight controller or other controller, and output a driving signal recognizable by the motor 2, thereby controlling the motor 2 The rotation, on the other hand, the drive circuit 33 is electrically connected to the battery of the drone so that the drive circuit 33 and the motor 2 provide operating power. In this embodiment, the ESC housing 32 is provided with a receiving cavity (not shown), and the driving circuit 33 is received in the receiving cavity. In order to prevent the driving circuit 33 from shaking, the driving circuit 33 of the embodiment is fixedly disposed in the receiving cavity. For example, the driving circuit 33 can be fixed on the inner sidewall of the ESC housing 32 by a fixing member. The driving circuit 33 is provided with electronic components (not shown), for example, a controller, a resistor, etc., and the heat dissipation source of the ESC assembly 3 of the present embodiment is mainly derived from the operation of the electronic components on the driving circuit 33. If the heat generated in the process is not dissipated in time, a large amount of heat is accumulated in the receiving cavity, and some electronic components may not work properly due to excessive temperature. In severe cases, some electronic components may be burned, causing a large Loss.

In this embodiment, the heat dissipation structure 31 is disposed on the outer casing. The heat dissipation structure 31 may be a heat dissipation hole or a heat dissipation component capable of dissipating heat, and the heat dissipation structure 31 may be selected according to different requirements. For example, in one embodiment, the heat dissipation structure 31 is a heat dissipation hole formed in the ESC housing 32, and the heat dissipation hole is in communication with the receiving cavity. During the flight of the drone, the rotation of the propeller 1 drives the air to the heat dissipation hole to enter the receiving cavity, and the air in the receiving cavity may be connected to the gap from the side of the outer casing or disposed on the outer casing. The exhaust hole is discharged to the outside of the receiving cavity, thereby reducing the temperature in the receiving cavity, and ensuring that the driving circuit 33 in the receiving cavity can operate normally. In this embodiment, the heat dissipation structure 31 is selected as a heat dissipation hole, and the weight of the power assembly 300 can be reduced, thereby reducing the weight of the drone and improving the endurance of the drone. In this embodiment, the heat dissipation hole is disposed at the top of the ESC housing 32 to increase the inflow of the air flow, thereby accelerating the heat dissipation speed of the receiving cavity. In addition, the size of the heat dissipation hole may be selected according to the requirement of the heat dissipation rate, which is not specifically limited in this embodiment.

It should be noted that when the drone is a plant protection drone, the heat dissipation structure 31 should not be selected as a heat dissipation hole. This is because the plant protection drone is generally disposed under the propeller 1 during the spraying operation. The syrup sprayed from the nozzle easily enters the accommodating cavity through the vent hole, causing damage to the electronic components on the drive circuit 33, causing loss to the user. However, for other types of drones, for example, aerial drones, the use of louvers as the heat dissipation structure 31 does not have the above effects.

In another embodiment, the heat dissipation structure 31 is a heat dissipation component, and the heat dissipation component may be formed of a heat conductive material. Among them, the heat conductive material can be selected as a heat conductive metal (such as aluminum, copper) or a heat conductive alloy. Through the cooperation of the heat dissipating component and the propeller 1, the airflow driven by the propeller 1 is rotated, and the heat of the heat dissipating component is taken away in time, so that the heat in the ESC assembly 3 is taken away in time to ensure stable operation of the ESC assembly 3. This embodiment only needs to add a heat-dissipating component with a small weight to the ESC assembly 3, and achieves an efficient heat dissipation requirement without adding a fan. Moreover, when the drone is a plant protection drone, the heat dissipating component can prevent the syrup from entering the accommodating cavity compared to the vent hole, thereby preventing the electronic component on the driving circuit 33 in the accommodating cavity from being damaged by water. Further, the heat dissipation structure 31 may be a heat dissipation fin or other heat dissipation structure.

In this embodiment, the heat dissipation structure 31 is taken as an example of the heat dissipation fins. In this embodiment, the heat dissipation fins are disposed outside the ESC housing 32. Optionally, the heat dissipation fins are disposed on the top of the ESC housing 32 to increase the possibility of air flow (air flow driven by the propeller 1 rotating) blowing toward the heat dissipation fins, thereby accelerating the heat dissipation of the ESC assembly 3. speed.

Further, the heat dissipation fins may be partially disposed outside the ESC housing 32, or the heat dissipation fins may be integrally disposed outside the ESC housing 32. For example, in an embodiment, the ESC housing 32 is made of a metal material (a metal material capable of conducting heat), and the heat dissipation fins are at least partially in direct contact with the ESC housing 32, and the heat dissipation fins pass through The ESC housing 32 exchanges heat with the air in the housing chamber to reduce the temperature in the housing chamber. Optionally, the heat dissipation fins are integrally disposed on the outside of the ESC housing 32, increasing a contact area between the heat dissipation fins and the air flow driven by the propeller 1 to accelerate the heat exchange of the heat dissipation fins, thereby Speed up the heat dissipation of the receiving cavity. Optionally, a part of the heat dissipation fin is disposed outside the ESC housing 32, and another portion is disposed in the receiving cavity, and the heat dissipation fin can directly heat the heat in the receiving cavity to the The outer portion of the outer casing 32 is described. Preferably, the heat dissipation fins located in the receiving cavity can be in direct contact with the electronic components with large heat generation to quickly lower the temperature of the corresponding electronic components.

In another embodiment, the ESC housing 32 is made of a non-metal material, and the heat dissipation fins at least partially extend into the receiving cavity. Since the non-metallic material has poor thermal conductivity, a part of the heat dissipation fin needs to be inserted into the receiving cavity, so that the heat of the air in the receiving cavity can be absorbed by the heat dissipation fin to realize the heat dissipation function.

The specific position of the heat dissipation fin of this embodiment can be set according to actual needs. In this embodiment, the heat dissipating fins are as far as possible away from the central axis of rotation of the motor 2, which is because the closer the propeller 1 is to the central axis of rotation, the lower the linear velocity. On the contrary, the farther away from the central axis of rotation, the greater the rotational linear velocity of the propeller 1, the higher the efficiency of the propeller 1, the faster the flow rate of the driven airflow, and the higher the heat dissipation efficiency of the heat dissipation fins, thereby improving the heat dissipation efficiency of the ESC assembly 3. . Preferentially, the heat dissipation fins are located on the side of the ESC housing 32. The heat dissipation fins are disposed on the side of the ESC housing 32, which can increase the possibility that the air flow (the air flow driven by the propeller 1) blows toward the heat dissipation fins, thereby accelerating the heat dissipation speed of the ESC assembly 3.

Optionally, the heat dissipation fins may be formed by forming a heat dissipation hole on the heat dissipation metal block. Among them, the density and depth of the heat dissipation holes formed on the heat dissipation metal block can comprehensively consider factors such as heat dissipation requirements and weight of the heat dissipation fins. The material of the heat dissipation metal block can be selected from aluminum or copper. Since the unmanned aerial vehicle is very sensitive to the weight, the material of the heat dissipating fin of the embodiment is preferably a light weight metal, so that the heat dissipation requirement for the ESC assembly 3 is achieved with less additional weight.

Referring to FIG. 1 , the heat dissipation fins extend toward the propeller 1 , and the airflow can contact the heat dissipation surface of the heat dissipation fins more, thereby improving heat dissipation efficiency. Preferably, the heat dissipating surface of the heat dissipating fin is approximately parallel to the central axis of rotation of the propeller 1.

In addition, in this embodiment, the heat dissipation fins may be integrally formed on the ESC housing 32. Of course, the heat dissipation fins may also be detachably mounted on the ESC housing 32 to facilitate heat dissipation fins. replace. Preferably, the heat dissipation fins are detachably mounted on the ESC housing 32. Further, the heat dissipation fins may be detachably connected to the ESC housing 32 by a snap connection, or the heat dissipation fins may be detachably connected to the ESC housing 32 by a quick release member. on.

Referring to FIG. 3, the ESC housing 32 can include an upper housing 321 and a lower housing 322 that mates with the upper housing 321 . The upper housing 321 and the lower housing 322 surround the receiving cavity. Specifically, the upper casing 321 and the lower casing 322 are fitted to each other to surround the receiving cavity. Of course, the composition of the ESC housing 32 is not limited to the above-described combination of the upper and lower structures, and the combination of the left and right structures may also be employed. In the left and right structural combination, the ESC housing 32 may include a left housing and a right housing that cooperates with the left housing, and the left housing and the right housing cover and cooperate to surround the forming body. The containment chamber.

This embodiment is described by taking an electric-acoustic casing 32 composed of a combination of upper and lower structures as an example. In the embodiment, the heat dissipation fins are disposed at an edge of the upper casing 321. Of course, the heat dissipating fins are not limited to be disposed at the edge of the upper casing 321 , and may be disposed at other positions of the upper casing 321 , and may also be disposed on the lower casing 322 . Preferably, the edge of the lower casing 322 is also provided with the heat dissipation fins, and the heat dissipation fins at the edge of the upper casing 321 cooperate with the heat dissipation fins at the edge of the lower casing 322 to rapidly lower the heat dissipation fins. The temperature of the containment chamber.

Further, the heat dissipation fins may include a plurality of the heat dissipation fins disposed on two sides of the upper casing 321 to discharge heat generated by the operation of the electronic components in the receiving cavity as soon as possible, thereby improving Cooling efficiency. Correspondingly, the heat dissipation fins are also disposed at corresponding positions of the lower casing 322 to cooperate with the plurality of heat dissipation fins on the upper casing 321 to accelerate heat dissipation.

1 and 2, the power assembly 300 may further include a motor base 4, and in the embodiment, the motor 2 and the ESC assembly 3 are both mounted on the motor base 4. The position at which the motor 2 and the ESC assembly 3 are mounted on the motor block 4 is determined according to the arrangement direction of the motor 2 and the ESC assembly 3. For example, in an embodiment, the ESC assembly 3 is located above the motor 2. The motor 2 is mounted on a lower surface of the motor mount 4, and the electric modulation assembly 3 is mounted on an upper surface of the motor mount 4. In the present embodiment, in order to drive the propeller 1 to rotate, the drive shaft 21 of the motor 2 passes through the ESC assembly 3 and is fixedly coupled to the propeller 1.

In another embodiment, the ESC assembly 3 is located below the motor 2. The motor 2 is mounted on an upper surface of the motor mount 4, and the electric modulation assembly 3 is mounted on a lower surface of the motor mount 4. Further, in the present embodiment, in order to drive the rotation of the propeller 1, the propeller 1 can be fixedly connected by the rotor case or the drive shaft 21 of the motor 2.

This embodiment is further described by taking the electric adjusting component 3 below the motor 2 as an example. Referring to FIG. 2, the heat dissipation structure 31 of the present embodiment is exposed outside the side of the motor base 4. Since the heat dissipation structure 31 is not blocked by the motor base 4, the motor base 4 does not affect the heat dissipation of the heat dissipation structure 31, and the air flow is improved ( The possibility that the air flow driven by the propeller 1 is blown toward the heat dissipation structure 31. Further, the side of the motor base 4 may be provided with a relief groove 43 in which the heat dissipation structure 31 is located. On the one hand, the escape groove 43 can protect the heat dissipation structure 31. Especially when the heat dissipation structure 31 is selected as the heat dissipation fin, the escape groove 43 can prevent the heat dissipation fin from being impacted by the air flow, so that the heat dissipation fin is mounted to the stability of the ESC assembly 3. Getting worse. On the other hand, the escape groove 43 can also guide the mounting of the heat dissipation structure 31 (here, the heat dissipation structure 31 is a heat dissipation member provided separately from the electric modulation unit 3).

1 and 4, the motor base 4 may include a sleeve 41 and a motor mounting portion 42 provided at one end of the sleeve 41. Wherein, the sleeve 41 is used for socketing with the arm 200 of the drone, thereby assembling the power assembly 300 to the arm 200 to provide flight power for the drone. In this embodiment, the sleeve 41 is sleeved away from one end of the motor mounting portion 42 and the sleeve 41 can be locked to the arm by a thread, a snap or a quick release component. At 200, a stable assembly of the power assembly 300 and the arm 200 is achieved. Optionally, the sleeve 41 and the motor mounting portion 42 are integrally formed to ensure the strength of the motor base 4. In addition, the ESC assembly 3 is electrically connected to the flight controller of the UAV through a wire (signal line), and the motor 2 is rotated by the cooperation of the flight controller and the ESC assembly 3 to drive the propeller 1 to rotate. Further, the ESC assembly 3 is also electrically connected to the battery of the UAV through a wire (power line) to provide operating power for the ESC assembly 3 and the motor 2. The wires (including the signal wires and the power wires) of the embodiment are electrically connected to the ESC assembly 3 after passing through the sleeve 41, that is, the wires are housed in the sleeve 41 to realize wirelessization of the outside of the UAV.

It is worth mentioning that the power assembly 300 of the above embodiment can be applied to a plant protection drone, an aerial drone, a surveying drone or other types of drones.

Referring to FIG. 4, an embodiment of the present invention further provides a drone, which may include a body 100, a arm 200 connected to the body 100, and a power assembly 300 of the above embodiment. The power assembly 300 is fixedly coupled to one end of the arm 200 away from the body 100 to provide flight power to the drone. The power assembly 300 of the present embodiment is fixedly connected to the one end of the arm 200 away from the body 100 by the motor base 4. For the specific installation, refer to the above embodiment, and details are not described herein again.

Further, the drone may include a flight controller disposed in the airframe 100, and the flight controller may be electrically connected to the ESC assembly 3 via a wire, through the flight controller and the ESC assembly 3 The cooperation of the drive motor 2 rotates to drive the propeller 1 to rotate.

Further, the drone may include a battery disposed on the body 100, the battery being electrically connected to the ESC assembly 3 through a wire, thereby being the ESC assembly 3 and the motor 2 Provide working power.

In the embodiment of the present invention, the drone may be a quadrotor unmanned aerial vehicle, but is not limited to a quadrotor unmanned aerial vehicle, and may be, for example, an eight-rotor unmanned aerial vehicle.

In the description of the present invention, "upper", "lower", "front", "rear", "left", "right" should be understood as forming the propeller 1, the motor 2 and the ESC assembly 3 from top to bottom. The "upper", "lower", "front", "rear", "left", "right" direction of the power assembly 300, or the formation of the propeller 1, the ESC assembly 3 and the motor 2 from top to bottom The "upper", "lower", "front", "back", "left", and "right" directions of the power assembly 300.

It should be noted that, in this context, relational terms such as first and second are used merely to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply such entities or operations. There is any such actual relationship or order between them. The terms "including", "comprising" or "comprising" or "comprising" are intended to include a non-exclusive inclusion, such that a process, method, article, or device that comprises a plurality of elements includes not only those elements but also other items not specifically listed Elements, or elements that are inherent to such a process, method, item, or device. An element that is defined by the phrase "comprising a ..." does not exclude the presence of additional equivalent elements in the process, method, item, or device that comprises the element.

The power components and the drone of the UAV provided by the embodiments of the present invention are described in detail above. The principles and implementations of the present invention are described in the specific examples. The description of the above embodiments is only for helping. The method of the present invention and its core idea are understood; at the same time, for those skilled in the art, according to the idea of the present invention, there are changes in the specific embodiments and application scopes. It should be understood that the invention is limited.

Claims

A power component of a drone, characterized in that it comprises:

propeller;

a motor fixedly coupled to the propeller for driving the propeller to rotate;

An electrical adjustment component electrically connected to the motor for controlling rotation of the motor;

Wherein the electric modulation assembly and the motor are arranged in a vertical arrangement, and the propeller is located above the electric modulation assembly and the motor;

The electric adjusting component is provided with a heat dissipating structure, the heat dissipating structure is disposed toward the propeller, and the propeller rotates to drive air to the heat dissipating structure.
The power assembly of claim 1 wherein said ESC assembly comprises an ESC housing coupled to said motor and a drive circuit for electrically connecting said motor, said ESC housing being provided with a drive circuit a receiving cavity, the driving circuit is received in the receiving cavity;

The heat dissipation structure is disposed on the outer casing.
The power module of claim 2, wherein the heat dissipation structure is a heat dissipation hole formed in the electrically adjustable outer casing, and the heat dissipation hole is in communication with the receiving cavity.
The power module of claim 2, wherein the heat dissipation structure is a heat dissipation fin, and the heat dissipation fin is disposed outside the electrically adjustable outer casing.
The power assembly of claim 4 wherein said heat sink fins are located on a side of said ESC housing.
The power assembly of claim 4 wherein said fins extend toward said propeller.
The power module according to claim 4, wherein the heat dissipation fin is formed by forming a heat dissipation hole in the heat dissipation metal block.
The power assembly of claim 4, wherein the ESC housing is made of a metal material, and the heat dissipation fins are at least partially in direct contact with the ESC housing.
The power assembly of claim 4, wherein the ESC housing is of a non-metallic material, and the heat dissipation fins at least partially extend into the receiving cavity.
The power assembly of claim 4, wherein the ESC housing comprises an upper housing and a lower housing that mates with the upper housing, wherein the upper housing and the lower housing Surrounding to form the receiving cavity;

The heat dissipation fin is disposed at an edge of the upper casing.
The power assembly according to claim 10, wherein the edge of the lower casing is also provided with the heat dissipation fin, the heat dissipation fin of the upper casing edge and the heat dissipation fin of the lower casing edge The film matches.
The power module according to claim 10, wherein the heat dissipation fins comprise a plurality of the heat dissipation fins mounted on opposite sides of the upper casing.
The power assembly of claim 1 further comprising a motor mount, said motor and said ESC assembly being mounted to said motor mount.
A power pack according to claim 13, wherein said motor is mounted on a lower surface of said motor block, said electric adjusting component is mounted on an upper surface of said motor block, and a drive shaft of said motor passes through After the ESC assembly, the propeller is fixedly connected.
A power pack according to claim 13, wherein said motor is mounted on an upper surface of said motor block, said electric adjusting component is mounted on a lower surface of said motor block, and a rotor case or drive of said motor A shaft is fixedly coupled to the propeller.
The power assembly of claim 15 wherein said heat dissipation structure is exposed outside of a side of said motor block.
The power module according to claim 16, wherein a side of the motor base is provided with a relief groove, and the heat dissipation structure is located in the escape groove.
The power assembly according to claim 15, wherein the motor base includes a sleeve and a motor mounting portion provided at one end of the sleeve, the sleeve being adapted to be sleeved with the arm of the drone, A wire is electrically connected to the electrical modulation assembly after passing through the sleeve.
An unmanned aerial vehicle comprising a fuselage and an arm coupled to the fuselage, further comprising a power assembly, wherein the power assembly is fixedly coupled to the end of the arm away from the fuselage, To provide flight power to the drone, the power components include:

propeller;

a motor fixedly coupled to the propeller for driving the propeller to rotate;

An electrical adjustment component electrically connected to the motor for controlling rotation of the motor;

Wherein the electric modulation assembly and the motor are arranged in a vertical arrangement, and the propeller is located above the electric modulation assembly and the motor;

The electric adjusting component is provided with a heat dissipating structure, the heat dissipating structure is disposed toward the propeller, and the propeller rotates to drive air to the heat dissipating structure.
The drone according to claim 19, wherein said ESC assembly comprises an ESC housing connected to said motor and a drive circuit for electrically connecting said motor, said ESC housing a receiving cavity, the driving circuit is received in the receiving cavity;

The heat dissipation structure is disposed on the outer casing.
The unmanned aerial vehicle of claim 20, wherein the heat dissipation structure is a heat dissipation hole formed in the electrically adjustable outer casing, and the heat dissipation hole is in communication with the receiving cavity.
The drone according to claim 20, wherein the heat dissipation structure is a heat dissipation fin, and the heat dissipation fin is disposed outside the electric adjustment housing.
The drone according to claim 22, wherein said heat dissipating fins are located on a side of said ESC housing.
The drone according to claim 22, wherein said fins extend toward said propeller.
The drone according to claim 22, wherein said heat dissipating fin is formed by forming a heat dissipation hole in the heat dissipating metal block.
The drone according to claim 22, wherein the ESC housing is made of a metal material, and the heat dissipation fins are at least partially in direct contact with the ESC housing.
The drone according to claim 22, wherein the ESC housing is made of a non-metal material, and the heat dissipation fins at least partially protrude into the receiving cavity.
The drone according to claim 22, wherein said ESC housing comprises an upper housing and a lower housing mating with said upper housing, wherein said upper housing and said lower housing Body surrounding forming the receiving cavity;

The heat dissipation fin is disposed at an edge of the upper casing.
The drone according to claim 28, wherein the edge of the lower casing is also provided with the heat dissipation fin, the heat dissipation fin of the upper casing edge and the heat dissipation of the lower casing edge The fins match.
The drone according to claim 28, wherein the heat dissipating fins comprise a plurality of the plurality of fins mounted on opposite sides of the upper casing.
The drone according to claim 19, wherein said power assembly further comprises a motor mount, said motor and said ESC assembly being mounted to said motor mount.
The drone according to claim 31, wherein said motor is mounted on a lower surface of said motor block, said electric adjusting component is mounted on an upper surface of said motor block, and said driving shaft of said motor is worn After passing through the ESC assembly, it is fixedly connected to the propeller.
The drone according to claim 31, wherein said motor is mounted on an upper surface of said motor block, said electric adjusting component is mounted on a lower surface of said motor block, said rotor case of said motor or The drive shaft is fixedly coupled to the propeller.
The drone according to claim 33, wherein said heat dissipating structure is exposed outside a side of said motor base.
The unmanned aerial vehicle according to claim 34, wherein a side of the motor base is provided with a relief groove, and the heat dissipation structure is located in the escape groove.
The drone according to claim 33, wherein the motor base comprises a sleeve and a motor mounting portion provided at one end of the sleeve, the sleeve being adapted to be sleeved with the arm of the drone The wire is electrically connected to the electrical modulation component after passing through the sleeve.
The drone according to claim 19, wherein said drone is a plant protection drone.