Heat dissipation structure and unmanned aerial vehicle

Abstract

The utility model discloses a heat dissipation structure and an unmanned aerial vehicle, the heat dissipation structure comprises a fuselage, the fuselage is provided with a heat dissipation cavity, the heat dissipation cavity is used for installing a heating assembly of the unmanned aerial vehicle, and the whole side of the fuselage is provided with heat dissipation ports communicated with the heat dissipation cavity. According to the technical scheme, the heat dissipation efficiency of the heat dissipation structure can be improved while the quality of the heat dissipation structure is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a heat dissipation structure and a unmanned aerial vehicle. Background Art

[0002] When a drone is working, the heat source inside it will generate a lot of heat. If this heat is not dissipated in time, the heat will accumulate and overheat, affecting the normal operation of the drone. Long-term overheating will cause damage to the drone or a reduction in its service life. Therefore, a part for heat dissipation is usually set on the drone.

[0003] In the current UAV heat dissipation structure, a cooling fan is installed to blow air towards the heat-generating circuit board to remove the heat. However, since the heat dissipation area of ​​the circuit board is not large enough, the amount of heat that can be removed by this circuit board direct blowing method is relatively limited. If the number of cooling fans is increased to improve the heat dissipation efficiency, the weight of the heat dissipation structure will increase, which will increase the energy consumption of the UAV. Utility Model Content

[0004] The main purpose of the utility model is to provide a heat dissipation structure, aiming to reduce the mass of the heat dissipation structure while improving the heat dissipation efficiency of the heat dissipation structure.

[0005] To achieve the above-mentioned purpose, the heat dissipation structure proposed in the utility model is used for an unmanned aerial vehicle, and the heat dissipation structure includes a fuselage, and the fuselage is provided with a heat dissipation cavity, and the heat dissipation cavity is used for installing the heat generating components of the unmanned aerial vehicle, and the entire side of the fuselage is provided with heat dissipation ports connected to the heat dissipation cavity.

[0006] Optionally, the heat dissipation cavity includes a first heat dissipation cavity and a second heat dissipation cavity that are interconnected, and the body includes an upper shell, a middle frame and a lower shell that are connected in sequence, so that the first heat dissipation cavity is formed between the upper shell and the middle frame, and the second heat dissipation cavity is formed between the middle frame and the lower shell.

[0007] Optionally, the heat dissipation port includes a lower heat dissipation port, a front heat dissipation port, a left heat dissipation port, a right heat dissipation port and a two-way heat dissipation port, the front heat dissipation port is arranged on the front side of the upper shell and / or the middle frame, the two-way heat dissipation port is arranged on the upper shell, the lower heat dissipation port is arranged on the lower side of the lower shell, and the left heat dissipation port and the right heat dissipation port are respectively arranged on the left and right sides of the middle frame.

[0008] Optionally, the left heat dissipation port and the right heat dissipation port are arranged close to the rear side of the fuselage.

[0009] Optionally, the heat-generating component includes a mainboard, and the front heat dissipation port is arranged opposite to the mainboard.

[0010] Optionally, the front heat dissipation port further includes a first front heat dissipation port and a second front heat dissipation port, the first front heat dissipation port is arranged at the front side of the upper shell, the second front heat dissipation port is arranged at the front side of the middle frame, and the second front heat dissipation port is arranged opposite to the mainboard.

[0011] Optionally, a mounting recess is provided on the front side of the middle frame, and the mounting recess is used for installing a gimbal assembly of the drone, and the second front heat dissipation port is provided on a side wall of the mounting recess.

[0012] Optionally, there are multiple second front heat dissipation openings, the mounting recess includes a first side wall and a second side wall that are bent and connected to each other, some of the second front heat dissipation openings are arranged on the first side wall, and some of the second front heat dissipation openings are arranged on the second side wall.

[0013] Optionally, the upper shell includes a top shell wall and a peripheral side wall arranged around the periphery of the top shell wall, the peripheral side wall is connected to the middle frame, the first front heat dissipation port is arranged on the front side of the peripheral side wall, and the bidirectional heat dissipation port is arranged on the top shell wall.

[0014] Optionally, the top shell wall includes a first section and two second sections arranged on opposite sides of the first section, the second sections are inclined in a direction away from the first section toward a direction close to the peripheral side wall, and the rear end of each second section is a guide section inclined from top to bottom in a direction close to the tail of the drone, and the two-way heat dissipation port is arranged in the guide section.

[0015] Optionally, each of the heat dissipation openings includes a plurality of heat dissipation holes arranged at intervals.

[0016] Optionally, vortex generators are provided on the left and right sides of the fuselage respectively.

[0017] Optionally, the vortex generator is configured as a vortex protrusion, and the vortex protrusion is arranged close to the rear side of the fuselage.

[0018] Optionally, when the UAV is in forward flight, the angle between the vortex protrusion and the horizontal plane approaches zero; and / or

[0019] The angle between the vortex protrusion and the bottom surface of the fuselage ranges from 30° to 45°.

[0020] The utility model also provides a drone, comprising a gimbal assembly, a heating assembly and the above-mentioned heat dissipation structure, wherein the gimbal assembly is installed on the front side of the fuselage, and the heating assembly is arranged in the heat dissipation cavity of the heat dissipation structure.

[0021] The above heat dissipation structure has at least the following beneficial effects:

[0022] The technical solution of the utility model adopts a heat dissipation structure including a fuselage, the fuselage is provided with a heat dissipation cavity, the heat dissipation cavity is used for installing the heating components of the drone, and all sides of the fuselage are provided with heat dissipation ports connected to the heat dissipation cavity. Specifically, since heat dissipation ports connected to the heat dissipation cavity are provided on all sides of the fuselage, during the flight of the UAV, no matter in which direction it flies, the air can flow into the heat dissipation cavity from the heat dissipation ports facing the flight direction along the airflow, thereby improving the efficiency of normal temperature air entering the heat dissipation cavity, and then increasing the air intake of normal temperature air in the heat dissipation cavity, and improving the heat dissipation efficiency of the heat dissipation structure; secondly, the air after heat exchange can flow out of the fuselage from another heat dissipation port opposite to the heat dissipation port through which the normal temperature air flows in or multiple heat dissipation ports connected to each other, thereby reducing the resistance of the heated air after heat exchange to be discharged from the fuselage, and improving the efficiency of the heated air to be discharged from the fuselage after heat exchange, thereby improving the heat dissipation efficiency of the heat dissipation structure, and the normal temperature air of the heat dissipation structure of the present scheme flows into the heat dissipation cavity from the heat dissipation port facing the flight direction, and the air after heat exchange flows out of the fuselage from another heat dissipation port opposite to the heat dissipation port through which the normal temperature air flows in or multiple heat dissipation ports connected to each other, and there is no need to set a heat dissipation fan, which can not only reduce costs, but also reduce the weight of the heat dissipation structure, thereby reducing the energy consumption of the UAV; it can be seen that the technical solution of the present utility model can reduce the weight of the UAV while improving the heat dissipation efficiency of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0024] Figure 1 This is a schematic structural diagram of a first perspective of an embodiment of the utility model drone;

[0025] Figure 2 This is a schematic diagram of the structure of the second viewing angle of the UAV of the utility model;

[0026] Figure 3 This is a schematic diagram of the structure of the UAV of the utility model from the third perspective;

[0027] Figure 4 This is a schematic diagram of the structure of the fourth viewing angle of the UAV of the utility model;

[0028] Figure 5 for Figure 1 A partial enlarged view of the middle A;

[0029] Figure 6 The figure is a schematic diagram of the explosion structure of the UAV of the utility model.

[0030] Description of Figure Numbers:

[0031]

[0032] The realization of the purpose, functional features and advantages of the utility model will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0034] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0035] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the utility model, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the utility model.

[0037] The utility model provides a heat dissipation structure.

[0038] Reference Figure 1 , Figure 3 , Figure 4 and Figure 6 In one embodiment of the utility model, the heat dissipation structure is used for a drone, and the heat dissipation structure includes a fuselage, and the fuselage is provided with a heat dissipation cavity, and the heat dissipation cavity is used for installing a heating component 600 of the drone, and heat dissipation ports connected to the heat dissipation cavity are provided on all sides of the fuselage.

[0039] Specifically, since heat dissipation ports connected to the heat dissipation cavity are provided on all sides of the fuselage, during the flight of the UAV, no matter in which direction it flies, the air can flow into the heat dissipation cavity from the heat dissipation ports facing the flight direction along the airflow, thereby improving the efficiency of normal temperature air entering the heat dissipation cavity, and then increasing the air intake volume of normal temperature air in the heat dissipation cavity, and improving the heat dissipation efficiency of the heat dissipation structure; secondly, the air after heat exchange can flow out of the fuselage from another heat dissipation port opposite to the heat dissipation port through which the normal temperature air flows in, or from a plurality of heat dissipation ports that are connected, thereby reducing the resistance of the heated air after heat exchange to be discharged from the fuselage, and improving the efficiency of the heated air to be discharged from the fuselage, thereby improving the heat dissipation efficiency of the heat dissipation structure; moreover, the normal temperature air of the heat dissipation structure of the present scheme flows into the heat dissipation cavity from the heat dissipation port facing the flight direction, and the air after heat exchange flows out of the fuselage from another heat dissipation port opposite to the heat dissipation port through which the normal temperature air flows in, and there is no need to set a heat dissipation fan, which can not only reduce the cost, but also reduce the weight of the heat dissipation structure, thereby reducing the energy consumption of the UAV; it can be seen that the technical solution of the present utility model can improve the heat dissipation efficiency of the UAV while reducing the weight of the UAV.

[0040] It should be noted that the full side of the fuselage refers to the front side, rear side, left side, right side, top side and bottom side of the fuselage.

[0041] The heating component 600 of the drone is arranged in the heat dissipation cavity, so that the normal temperature air can directly contact the heating component 600, thereby reducing the heat transfer path of the heating component 600 and further improving the heat dissipation efficiency of the heat dissipation structure.

[0042] Furthermore, the heat dissipation cavity includes a first heat dissipation cavity and a second heat dissipation cavity that are interconnected, and the fuselage includes an upper shell 100, a middle frame 200, and a lower shell 300 that are connected in sequence, so that a first heat dissipation cavity is formed between the upper shell 100 and the middle frame 200, and a second heat dissipation cavity is formed between the middle frame 200 and the lower shell 300; this can facilitate the installation and maintenance of the heating component 600. Of course, the utility model is not limited to this, and in other embodiments, the fuselage may also include an upper shell part and a lower shell part that cover each other to form a heat dissipation cavity between the upper shell part and the lower shell part, and the heating component is arranged in the lower shell part.

[0043] Optionally, the heat dissipation vents include a lower heat dissipation vent 520, a front heat dissipation vent 400, a left heat dissipation vent 530, a right heat dissipation vent 540 and a two-way heat dissipation vent 510, the front heat dissipation vent 400 is arranged on the front side of the upper shell 100 and / or the middle frame 200, the two-way heat dissipation vent 510 is arranged on the upper shell 100, the lower heat dissipation vent 520 is arranged on the lower side of the lower shell 300, and the left heat dissipation vent 530 and the right heat dissipation vent 540 are respectively arranged on the left and right sides of the middle frame 200; the lower heat dissipation vent 520, the front heat dissipation vent 400, the two-way heat dissipation vent 510, the left heat dissipation vent 530 and the right heat dissipation vent 540 are respectively arranged on the upper shell 100, the middle frame 200 and the lower shell 300 can be easily processed, and when one of the components is damaged, it is convenient for repair and replacement without replacing the entire shell.

[0044] Among them, the left heat dissipation port 530 and the right heat dissipation port 540 are arranged near the rear side of the fuselage. Since the flight inclination angle of the drone is generally between 0° and 45°, and it is generally in a forward flight state, that is, the air generally enters from the front heat dissipation port 400 and exits from the two-way heat dissipation port 510, the left heat dissipation port 530 or the right heat dissipation port 540, the left heat dissipation port 530 and the right heat dissipation port 540 are arranged near the rear side of the fuselage, so that the flow path of the normal temperature air in the heat dissipation cavity can be increased, that is, the heat exchange path is increased, thereby improving the utilization rate of the normal temperature air entering the heat dissipation cavity, and then improving the heat dissipation efficiency of the heat dissipation structure. Of course, the utility model is not limited to this. In other embodiments, the left heat dissipation port 530 and the right heat dissipation port 540 can also be arranged in the middle of the left and right sides of the middle frame 200.

[0045] Reference Figure 2 , Figure 5 and Figure 6 Optionally, the heating component 600 includes a main board 610, and the front heat dissipation port 400 is arranged opposite to the main board 610; in this way, when the drone flies forward, the wind flows from the front to the back, and the heat of the main board 610 generated inside the fuselage is directly brought out of the drone, thereby shortening the heat dissipation path and improving the heat dissipation efficiency of the main board 610.

[0046] It should be noted that the mainboard 610 refers to a circuit board, which is installed on a side of the middle frame 200 close to the lower shell 300 . The lower shell 300 is connected to the middle frame 200 to cover the mainboard 610 .

[0047] Furthermore, the heating component 600 also includes electronic components and batteries that generate heat inside the body. The electronic components and batteries are installed on the middle frame 200 and are located in the heat dissipation cavity. This allows normal temperature air to directly contact the heating component 600, shortening the heat dissipation path of the heating component 600, thereby improving the heat dissipation efficiency.

[0048] Furthermore, the front heat dissipation port 400 includes a first front heat dissipation port 410 and a second front heat dissipation port 420 (430), the first front heat dissipation port 410 is arranged on the front side of the upper shell 100, the second front heat dissipation port 420 (430) is arranged on the front side of the middle frame 200, and the second front heat dissipation port 420 (430) is arranged opposite to the mainboard 610. Since the flight inclination angle of the UAV is generally between 0° and 45°, and the UAV is generally in a forward flight state, that is, the front heat dissipation port 400 is generally in a wind intake state, the first front heat dissipation port 410 is arranged on the front side of the upper shell 100, and the second front heat dissipation port 420 (430) is arranged on the front side of the middle frame 200, so that the wind intake area of ​​the UAV during flight can be increased, thereby increasing the air intake volume of the heat dissipation cavity to improve the heat dissipation efficiency.

[0049] Optionally, a mounting recess 210 is provided on the front side of the middle frame 200, and the mounting recess 210 is used for mounting the gimbal assembly 800 of the drone, and the second front heat dissipation vent 420 (430) is provided on the side wall of the mounting recess 210; it can be understood that the gimbal assembly 800 is provided in the mounting recess 210, which can make the structure of the drone more compact. Of course, the utility model is not limited to this, and in other embodiments, the second front heat dissipation vent 420 (430) can also be provided on the end surface of the front side of the middle frame 200.

[0050] Optionally, there are multiple second front heat dissipation vents 420 (430), the mounting recess 210 includes a first side wall 211 and a second side wall 212 that are bent and connected to each other, part of the second front heat dissipation vents 420 are arranged on the first side wall 211, and part of the second front heat dissipation vents 430 are arranged on the second side wall 212. Since the flight inclination angle of the drone is generally between 0° and 45°, and it is generally in a forward flight state, that is, the front heat dissipation vents 400 are generally in a wind intake state, the second front heat dissipation vents 420 (430) are arranged on both the first side wall 211 and the second side wall 212 of the mounting recess 210 to increase the wind intake area, thereby increasing the efficiency of normal temperature air entering the heat dissipation cavity, thereby improving the heat dissipation efficiency. When the drone is in a backward flight state, the front heat dissipation vents 400 serve as air outlets, which can increase the efficiency of the air after heat exchange being discharged from the fuselage, and can also play the role of improving the heat dissipation efficiency.

[0051] Furthermore, the upper shell 100 includes a top shell wall 110 and a peripheral side wall 120 arranged around the periphery of the top shell wall 110, the peripheral side wall 120 is connected to the middle frame 200, the first front heat dissipation port 410 is arranged on the front side of the peripheral side wall 120, and the two-way heat dissipation port 510 is arranged on the top shell wall 110, so as to facilitate the connection between the upper shell 100 and the middle frame 200.

[0052] Optionally, the top shell wall 110 includes a first section 111 and two second sections 112 respectively arranged on opposite sides of the first section 111, the second section 112 is inclined in a direction away from the first section 111 toward a direction close to the peripheral side wall 120, and the rear end of each second section 112 is a guide section 112a inclined from the top to the bottom in a direction close to the tail of the drone, and the two-way heat dissipation port 510 is arranged in the guide section 112a. Since the guide section 112a has both an upwardly inclined side and a rearwardly inclined side, the two-way heat dissipation port 510 is arranged in the guide section 112a, which is conducive to the two-way heat dissipation port 510 to discharge or inhale air toward the rear side of the fuselage or toward the upper side of the fuselage, so that the structure of the heat dissipation structure can be more compact. Specifically, when the drone flies forward, the two-way heat dissipation port 510 can discharge air toward the rear side, and when the drone descends, the two-way heat dissipation port 510 can discharge air toward the upper side. In the second embodiment, the upper side surface of the upper housing 100 may also be provided with a heat dissipation port opening upward, and the rear side of the peripheral side wall 120 of the upper housing 100 may also be provided with a heat dissipation port opening rearward. In the third embodiment, the upper side surface of the upper housing 100 may also be provided with a heat dissipation port opening upward, and the rear side of the middle frame 200 may be provided with a heat dissipation port opening rearward.

[0053] Furthermore, the first section 111 is gradually inclined from the middle to the front side of the fuselage in a direction close to the middle frame 200, and the first section 111 is gradually inclined from the middle to the rear side of the fuselage in a direction close to the middle frame 200. The rear end of each second section 112 is a guide section 112a inclined from the top to the bottom in a direction close to the tail of the drone; in this way, the top surface of the fuselage can guide the air flow, thereby reducing the wind resistance of the drone when flying at high speed.

[0054] Optionally, the two-way heat dissipation vent 510 is arranged away from the front heat dissipation vent 400. Since the front heat dissipation vent 400 is arranged on the front side of the fuselage and the drone is generally in a forward flight state, the front heat dissipation vent 400 is generally in a wind intake state. The two-way heat dissipation vent 510 is arranged away from the front heat dissipation vent 400. This can increase the flow path of the normal temperature air in the heat dissipation cavity, that is, increase the heat exchange path, thereby improving the utilization rate of the normal temperature air entering the heat dissipation cavity, and then improving the heat dissipation efficiency of the heat dissipation structure.

[0055] Among them, each heat dissipation port includes a plurality of heat dissipation holes arranged at intervals. This dense arrangement of heat dissipation holes can prevent large particles of dust from entering the fuselage and damaging the drone components, thereby affecting the flight safety of the drone.

[0056] Reference Figure 2 , Figure 4 and Figure 5Optionally, vortex generators are respectively provided on the left and right sides of the fuselage. In this solution, since there are vortex generators on the left and right sides of the fuselage, when air flows through the fuselage, the vortex generators can destroy the air flow attached to the left and right sides of the fuselage, so that the air flow is not easy to tightly adhere to the left and right sides of the fuselage, thereby causing the air flowing through the left and right sides of the fuselage to generate vortices. If vortex generators are not provided, the airflow will flow along the left and right sides of the fuselage to the bottom surface of the fuselage and generate vortices on the back side of the fuselage. In this solution, vortex generators are provided on the left and right sides, and the vortex generated on the back side of the fuselage is generated on the left and right sides of the fuselage in advance, so that the pressure difference resistance formed by the top surface and the bottom surface of the fuselage is reduced, thereby increasing the flight speed of the UAV.

[0057] Furthermore, the vortex generator is arranged close to the rear side of the fuselage. This is because the UAV is generally in a forward flight state. Setting the vortex generator close to the rear side of the fuselage can better reduce the vortex on the back of the fuselage when the UAV flies forward, thereby reducing the pressure difference resistance formed by the top surface and the bottom surface of the fuselage, and is more conducive to increasing the flight speed of the UAV.

[0058] Furthermore, the vortex generator is configured as a vortex protrusion 700, and the vortex protrusion 700 is arranged near the rear side of the fuselage; the vortex protrusion 700 has a simple structure and is easy to process and manufacture, and the vortex protrusion 700 can destroy the air flow attached to the left and right sides of the fuselage, so that the air flow is not easy to tightly adhere to the left and right sides of the fuselage, thereby causing the air flowing through the left and right sides of the fuselage to generate vortices, reducing the pressure difference resistance between the windward side of the drone fuselage and the back side of the fuselage, which is conducive to increasing the flight speed of the drone. Of course, the utility model is not limited to this, and in some other embodiments, the vortex generator can also be configured as a vortex generating groove.

[0059] Optionally, when the UAV is in forward flight, the angle between the vortex protrusion 700 and the horizontal plane approaches zero, which can reduce the flight wind resistance.

[0060] The angle between the vortex protrusion 700 and the bottom surface of the fuselage ranges from 30° to 45°; this can better generate vortices in the airflow flowing through the left and right sides, and can reasonably reduce the pressure difference resistance between the windward side of the fuselage and the back side of the fuselage, avoiding the generation of vortices that are too large or too small.

[0061] The utility model also proposes an unmanned aerial vehicle, which includes a gimbal assembly 800, a heating assembly 600 and a heat dissipation structure. The specific structure of the heat dissipation structure refers to the above-mentioned embodiment. Since the heat dissipation structure adopts all the technical solutions of all the above-mentioned embodiments, it at least has all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be described one by one here; wherein, the gimbal assembly 800 is installed on the front side of the fuselage, and the heating assembly 600 is arranged in the heat dissipation cavity of the heat dissipation structure.

[0062] The above description is only an optional embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A heat dissipation structure for a drone, characterized in that: The heat dissipation structure is arranged on the fuselage, and the fuselage is provided with a heat dissipation cavity, and the heat dissipation cavity is used for installing the heat generating components of the drone, and the entire side of the fuselage is provided with heat dissipation ports connected with the heat dissipation cavity; The left side and the right side of the fuselage are respectively provided with vortex generators.

2. The heat dissipation structure according to claim 1, characterized in that: The heat dissipation cavity includes a first heat dissipation cavity and a second heat dissipation cavity that are interconnected, and the body includes an upper shell, a middle frame and a lower shell that are connected in sequence, so that the first heat dissipation cavity is formed between the upper shell and the middle frame, and the second heat dissipation cavity is formed between the middle frame and the lower shell.

3. The heat dissipation structure according to claim 2, characterized in that: The heat dissipation port includes a lower heat dissipation port, a front heat dissipation port, a left heat dissipation port, a right heat dissipation port and a two-way heat dissipation port. The front heat dissipation port is arranged on the front side of the upper shell and / or the middle frame, the two-way heat dissipation port is arranged on the upper shell, the lower heat dissipation port is arranged on the lower side of the lower shell, and the left heat dissipation port and the right heat dissipation port are respectively arranged on the left side and the right side of the middle frame.

4. The heat dissipation structure according to claim 3, characterized in that: The left heat dissipation opening and the right heat dissipation opening are arranged close to the rear side of the fuselage.

5. The heat dissipation structure according to claim 3, characterized in that: The heat generating component comprises a mainboard, and the front heat dissipation port is arranged opposite to the mainboard.

6. The heat dissipation structure according to claim 5, characterized in that: The front heat dissipation port also includes a first front heat dissipation port and a second front heat dissipation port, the first front heat dissipation port is arranged on the front side of the upper shell, the second front heat dissipation port is arranged on the front side of the middle frame, and the second front heat dissipation port is arranged opposite to the mainboard.

7. The heat dissipation structure according to claim 6, characterized in that: A mounting recess is provided on the front side of the middle frame, and the mounting recess is used for mounting a gimbal assembly of the drone, and the second front heat dissipation port is provided on a side wall of the mounting recess.

8. The heat dissipation structure according to claim 7, characterized in that: There are multiple second front heat dissipation openings, the mounting recess includes a first side wall and a second side wall that are bent and connected to each other, some of the second front heat dissipation openings are arranged on the first side wall, and some of the second front heat dissipation openings are arranged on the second side wall.

9. The heat dissipation structure according to claim 6, characterized in that: The upper shell includes a top shell wall and a peripheral side wall arranged around the periphery of the top shell wall, the peripheral side wall is connected to the middle frame, the first front heat dissipation port is arranged on the front side of the peripheral side wall, and the bidirectional heat dissipation port is arranged on the top shell wall.

10. The heat dissipation structure according to claim 9, characterized in that: The top shell wall includes a first section and two second sections arranged on opposite sides of the first section, the second sections are inclined in a direction away from the first section toward a direction close to the peripheral side wall, and the rear end of each second section is a guiding section inclined from the top to the bottom in a direction close to the tail of the drone, and the two-way heat dissipation port is arranged in the guiding section.

11. The heat dissipation structure according to claim 1, characterized in that: Each of the heat dissipation openings includes a plurality of heat dissipation holes arranged at intervals.

12. The heat dissipation structure according to claim 1, characterized in that: The vortex generator is configured as a vortex protrusion, and the vortex protrusion is arranged close to the rear side of the fuselage.

13. The heat dissipation structure according to claim 12, characterized in that: When the UAV is in forward flight, the angle between the vortex protrusion and the horizontal plane approaches zero; and / or The angle between the vortex protrusion and the bottom surface of the fuselage ranges from 30° to 45°.

14. A drone, characterized in that: It comprises a pan-tilt assembly, a heating assembly and a heat dissipation structure as claimed in any one of claims 1 to 13, wherein the pan-tilt assembly is mounted on the front side of the fuselage, and the heating assembly is arranged in the heat dissipation cavity of the heat dissipation structure.

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