Heat dissipation structure for high-power load of unmanned aerial vehicle

Abstract

The invention relates to a heat dissipation structure of a high-power load of an unmanned aerial vehicle. The heat dissipation structure comprises an inner heat dissipation plate, an outer heat dissipation plate, a front ventilation opening, a rear heat dissipation opening, an inner heat dissipation flow channel and an outer heat dissipation flow channel. An inner heat dissipation plate and an outer heat dissipation plate are arranged on the two corresponding sides of the high-power load correspondingly, and the inner heat dissipation plate is located in the unmanned aerial vehicle body; the outer heat dissipation plate penetrates through the side wall of the unmanned aerial vehicle body and extends out of the unmanned aerial vehicle body; in the forward flight direction of the unmanned aerial vehicle, front ventilation openings and rear heat dissipation openings are symmetrically formed in the positions, on the front side and the rear side of the high-power load, of the side wall of the unmanned aerial vehicle body, the front ventilation openings, the outer heat dissipation plates and the rear heat dissipation openings communicate to form outer heat dissipation flow channels, and the front ventilation openings, the inner heat dissipation plates and the rear heat dissipation openings communicate to form inner heat dissipation flow channels. According to the cooling device, cooling equipment does not need to be additionally arranged, the ideal cooling effect can be achieved by conducting forced air cooling heat dissipation through the designed structure, the occupied space and loads are reduced, and the cooling device can serve as a preferable heat dissipation mode for the loads of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a heat dissipation structure of a high-power load of an unmanned aerial vehicle. Background Art

[0002] The size of the drone platform is limited, and the volume and weight of the high-power payload installed inside it will affect the flight capability of the drone, so there are high restrictions on the payload weight of the drone. The high-power payload is equivalent to a highly integrated electrical component, which is fixed in the box using a packaging process.

[0003] High-power loads have the characteristics of high power and high temperature when working, which will generate a lot of heat, thus affecting the flight of the drone. When the heat reaches a certain temperature, it will cause a certain degree of damage to itself and surrounding components, causing the drone to fail to work, and it may also pose a greater threat to the safety of the drone itself. Therefore, it is necessary to dissipate heat from high-power loads and other heat-generating components in a timely manner to ensure normal operating temperature. At present, the commonly used cooling technologies for airborne electronic equipment mainly include natural air cooling technology, forced air convection cooling technology, cold plate technology, liquid cooling technology, phase change evaporative cooling technology, thermoelectric cooling technology and heat pipe technology.

[0004] The use of natural air cooling is to remove heat by air flow generated by the temperature difference between the various parts of the system. It is a safe and reliable cooling method that does not require external power, but it cannot solve the cooling problem of heat flux density exceeding 0.8W / cm². For example, CN110082728B discloses a heat dissipation structure of a synthetic aperture radar array system on a drone, which directly sets multiple rows of heat dissipation teeth on the outer wall of the T / R component shell arranged in a row, combined with the grooves at both ends of the array frame, so that the natural wind during the flight of the drone can be fully cooled; however, the heat dissipation structure is aimed at the array system, and the heat generated by the system is far less than the heat generated during the working period of the high-power load, which is insufficient to meet the needs of installing high-power loads on drones, and there are still safety hazards.

[0005] After further development, liquid cooling and air cooling are used. Air cooling mainly uses fans to blow air for cooling, but fans need to occupy a certain space and part of the load. Liquid cooling is a cooling method that refrigerates by circulating cooling liquid. Liquid cooling requires adding liquid cooling channels when designing the array system structure. Not only does it require additional liquid cooling units, but it also has problems such as heavy weight, leakage, corrosion, etc. that affect safety and reliability. For example, CN212890967U discloses an internal circulation cooling device for plant protection drones, which uses a combination of air cooling components and water cooling components to achieve a good heat dissipation effect.

[0006] From this, it can be seen that the structural design of traditional heat dissipation generally requires external connection to other equipment, which will inevitably occupy the load weight or space of the drone, affect the installation or operation of high-power loads, reduce the installation space of other devices, and make it difficult to meet actual heat dissipation requirements.

[0007] In the existing technology, there are also methods of heat dissipation using the heat dissipation mesh of the heat dissipation cover, but the heat dissipation efficiency is low, and the heat of the high-power load cannot be quickly dissipated. The temperature of the high-power load is still high, and the probability of failure is still high. Phase change evaporation technology is suitable for short-term or intermittent working scenarios such as missile-borne platforms and pulse working systems, and is not suitable for UAV platforms carrying high-power loads. Thermoelectric cooling is a type of heat dissipation based on the Peltier effect that uses electricity for cooling. It not only consumes a large amount of platform power resources, but also has an unsatisfactory heat dissipation efficiency. Summary of the invention

[0008] In order to solve the problem that conventional heat dissipation measures require external devices, which will lead to large space occupation and increased load, the present invention provides a heat dissipation structure for high-power loads of unmanned aerial vehicles, which does not require external devices, avoids occupying a large space, reduces the load of the unmanned aerial vehicle, and can complete the heat dissipation of high-power loads only by relying on its own structure and natural air cooling.

[0009] To achieve the above purpose, the technical solution adopted by the present invention is: The heat dissipation structure of the high-power load of the UAV is used for heat dissipation and cooling of the high-power load on the inner wall of the UAV fuselage, including an inner heat dissipation plate, an outer heat dissipation plate, a front vent, a rear heat dissipation port, an inner heat dissipation channel, and an outer heat dissipation channel; An inner heat sink and an outer heat sink are respectively arranged on the two sides corresponding to the high-power load. The design of the double heat sink increases the heat dissipation area and effect. The inner heat sink is located inside the fuselage of the drone. The inner heat sink includes a substrate and a plurality of needle-shaped heat sinks arranged on the substrate. The outer heat sink passes through the side wall of the fuselage of the drone and extends to the outside of the fuselage of the drone, so as to facilitate direct contact with the outside air. The structure of the outer heat sink is the same as that of the inner heat sink, but the size is different. The front vents and rear heat dissipation vents are symmetrically provided on the side walls of the drone body on both sides of the front and rear of the high-power load along the forward flight direction of the drone. The front vents, the outer heat dissipation plate and the rear heat dissipation vents are connected to form the outer heat dissipation flow channel, and the front vents, the inner heat dissipation plate and the rear heat dissipation vents are connected to form the inner heat dissipation flow channel. High-speed airflow flows through the inner and outer heat dissipation flow channels at the same time, thereby quickly taking away heat.

[0010] Furthermore, the substrate of the inner heat sink and the substrate of the outer heat sink are respectively attached to the two side walls corresponding to the high-power load, and a heat-conducting layer is arranged between the substrate of the inner heat sink, the substrate of the outer heat sink and the side walls of the high-power load. The heat-conducting layer is a layer structure filled with a heat-conducting medium, which improves the heat transfer efficiency.

[0011] Furthermore, the thickness of the inner heat sink is greater than that of the outer heat sink, and the inner heat sink and the outer heat sink cooperate to clamp the high-power load. Both the inner heat sink and the outer heat sink are copper plate structures, and anti-oxidation layers are provided on the surfaces of the inner heat sink and the outer heat sink, thereby stabilizing the heat dissipation effect of the heat sink.

[0012] Furthermore, the substrate and the heat dissipation column are integrally formed, and the thickness d of the substrate is one of 2-4 mm, 4-6 mm, 6-8 mm, 8-10 mm and ≥10 mm.

[0013] Furthermore, a plurality of the heat dissipation columns are arranged in a rectangular array, the heat dissipation columns are a kind of prism or frustum structure, the heat dissipation columns are arranged perpendicular to the substrate, the large diameter end of the heat dissipation column is connected and fixed to the substrate, and the large diameter end of two adjacent heat dissipation columns is spaced w≥4mm, which improves the smoothness of air flow, and the inclination of the side surface of each heat dissipation column is 2~4°; The heat dissipation column of the external heat dissipation plate extends to the outside of the UAV fuselage, and the extension length is ≤5mm.

[0014] Furthermore, the thickness d of the substrate is 2-4 mm, the dimension λ of the large diameter end of the heat dissipation column is 1.5 mm, and the height h of the heat dissipation column is ≥ 6 mm; Or, the thickness d of the substrate is 4-6 mm, the dimension λ of the large diameter end of the heat dissipation column is 2 mm, and the height h of the heat dissipation column is ≥ 8 mm; Or, the thickness d of the substrate is 6-8 mm, the dimension λ of the large diameter end of the heat dissipation column is 2.5 mm, and the height h of the heat dissipation column is ≥ 8 mm; Or, the thickness d of the substrate is 8-10 mm, the large diameter end dimension λ of the heat dissipation column is 3 mm, and the height h of the heat dissipation column is ≥10 mm; Or, the thickness of the substrate d≥10 mm, the dimension λ of the large diameter end of the heat dissipation column is 4 mm, and the height of the heat dissipation column h≥10 mm.

[0015] Furthermore, the number of the front vents and the rear heat dissipation vents is at least two arranged in parallel front and back, thereby increasing the air circulation; the front vents are a fin-like structure bent in a “〉” shape, which facilitates the introduction of air into the interior of the UAV fuselage; the front vents and the rear heat dissipation vents have the same structure; the front vent openings and the rear heat dissipation vent openings are both oriented toward the high-power load; the angle θ of the front vent opening and the rear heat dissipation vent openings is in the range of 60°≤θ≤90°; the heights of the front vents and the rear heat dissipation vents are consistent with the high-power load height.

[0016] Furthermore, the outer heat dissipation channel is a linear channel structure, and the inner heat dissipation channel is a streamlined channel structure that is bent into an arc shape.

[0017] Through the above technical solution, the beneficial effects of the present invention are: The present invention has a reasonable structural design. An inner heat sink and an outer heat sink are arranged on both sides of a high-power load. The inner and outer heat sinks are detachably connected so that the heat sinks are suitable for high-power loads of different specifications and have good versatility. The inner and outer heat sinks cooperate to clamp the high-power load, which can increase the heat dissipation area of ​​the high-power load and improve the heat dissipation capacity. A heat-conducting layer is also arranged between the joint surfaces of the inner and outer heat sinks and the high-power load to ensure a closer contact between the three and improve the heat transfer efficiency.

[0018] When the high-power load of the present invention is working, the heat is transferred to the outer heat sink. Since the outer heat sink extends to the outside of the drone body and is exposed to the air, the high-speed airflow flows through the outer heat sink when the drone is flying, thereby taking away a large amount of heat. When the high-power load is working, the heat is transferred to the inner heat sink at the same time. Since the front vents and rear heat sinks are provided at the front and back of the drone body, the high-speed airflow enters the drone body from the front vents, flows through the inner heat sink, and finally flows out from the rear heat sink when the drone is flying, thereby achieving the purpose of heat dissipation.

[0019] The present invention uses high-speed airflow to flow into the inner heat dissipation channel and the outer heat dissipation channel at the same time. The inner heat dissipation channel guides the airflow to the inner heat dissipation plate, and the outer heat dissipation channel guides the airflow to the outer heat dissipation plate. The inner and outer heat dissipation plates are both provided with a plurality of needle-shaped heat dissipation columns. The heat dissipation columns have the characteristics of small size and light weight. The heat dissipation columns increase the contact area between the airflow and the heat dissipation plate. The heat dissipation plate with the heat dissipation columns has better heat dissipation performance and can quickly dissipate the heat emitted by the high-power load, greatly reducing the probability of failure of the drone's onboard equipment, and at the same time, it can also avoid overheating and damage of other electronic components inside the drone fuselage.

[0020] The heat dissipation structure adopted by the present invention has the characteristics of no moving parts, no power consumption, maintenance-free, compact structure and high reliability. It greatly reduces the additional devices and heat dissipation devices of the load besides the high-power load that the UAV platform has to carry, so that all the components that need to be integrated in the high-power load itself do not need to be cut or castrated, which can greatly enhance the tolerance of the UAV platform to the problem that many current high-power loads cannot be highly integrated, so that many high-power loads can be widely used in UAV platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a front view of the heat dissipation structure of the high-power load of the UAV of the present invention, and the arrow B in the figure points to the forward flight direction of the UAV.

[0022] Figure 2 The heat dissipation structure of the high-power load of the UAV of the present invention Figure 1 Cross-sectional view of high power load in the AA direction.

[0023] Figure 3 The invention discloses a schematic diagram of the installation of an inner heat sink, an outer heat sink and a high-power load of the heat dissipation structure of the high-power load of the UAV.

[0024] Figure 4 The heat dissipation structure of the high-power load of the UAV of the present invention Figure 3 A partial enlarged schematic diagram of .

[0025] Figure 5 It is a schematic diagram of the front vent of the heat dissipation structure of the high-power load of the UAV of the present invention.

[0026] Figure 6 It is a schematic diagram of the air flow status in the outer heat dissipation channel and the inner heat dissipation channel of the heat dissipation structure of the high-power load of the UAV of the present invention. The right-angle arrow in the figure points to the flow path of the airflow in the outer heat dissipation channel, and the triangular arrow points to the flow path of the airflow in the inner heat dissipation channel.

[0027] The numbers in the attached figure are: 1 UAV fuselage, 2 high-power load, 3 internal heat sink, 4 external heat sink, 5 front vent, 6 rear heat sink, 7 internal heat dissipation channel, 8 external heat dissipation channel, 9 substrate, 10 heat dissipation column, 11 thermal conductive layer. DETAILED DESCRIPTION

[0028] The specific implementation of the present invention is described in detail below with reference to the accompanying drawings: like Figure 1 to Figure 6 As shown, the heat dissipation structure of the high-power load of the UAV is used for heat dissipation and cooling of the high-power load 2 on the inner wall of the UAV fuselage 1. The high-power load 2 is installed on the inner wall of the UAV fuselage 1, and the high-power load 2 is encapsulated in a rectangular box, so that the high-power load 2 has a regular appearance, and the front of the UAV fuselage 1 is the nose part of the UAV.

[0029] The heat dissipation structure includes an inner heat dissipation plate 3, an outer heat dissipation plate 4, a front vent 5, a rear heat dissipation port 6, an inner heat dissipation channel 7, and an outer heat dissipation channel 8. The inner heat dissipation plate 3 and the outer heat dissipation plate 4 are respectively arranged on the two sides corresponding to the high-power load 2. The inner heat dissipation plate 3 and the outer heat dissipation plate 4 are both installed on the high-power load 2 by screws. After installation, the inner heat dissipation plate 3 and the outer heat dissipation plate 4 cooperate to clamp the high-power load 2, and the inner heat dissipation plate 3 and the outer heat dissipation plate 4 cooperate to achieve heat dissipation of the high-power load 2.

[0030] The inner heat sink 3 is located inside the drone body 1, and the thickness of the inner heat sink 3 is Greater than the thickness of the external heat sink 4 The external heat dissipation plate 4 passes through the side wall of the drone body 1 and extends to the outside of the drone body 1 , that is, a part of the external heat dissipation plate 4 is exposed outside the drone body 1 .

[0031] Both the inner heat sink 3 and the outer heat sink 4 can play a role in heat dissipation. Here, both the inner heat sink 3 and the outer heat sink 4 are copper plate structures, and the structure of the outer heat sink 4 is the same as that of the inner heat sink 3. Taking the structure of the inner heat sink 3 as an example, the inner heat sink 3 includes a substrate 9 and a plurality of needle-shaped heat sinks 10 arranged on the substrate 9. The substrate 9 and the heat sink 10 are integrally formed, and the plurality of heat sinks 10 are arranged in a rectangular array. The heat sink 10 is a kind of prism or truncated cone structure, and the inclination of the side surface of each heat sink 10 is 2~4°. Preferably, the inclination of the side surface of the heat sink 10 is 3°.

[0032] The heat dissipation column 10 is arranged perpendicular to the substrate 9, and the large diameter end of the heat dissipation column 10 is connected and fixed to the substrate 9. The large diameter ends of two adjacent heat dissipation columns 10 are spaced w ≥ 4 mm to ensure that there is enough spacing between the heat dissipation columns 10 to ensure smoothness of air flowing naturally through the heat dissipation columns 10, to ensure that the air can circulate quickly, and the heat emitted can be quickly taken away when the air flows through.

[0033] In order to increase the heat dissipation effect, the substrate 9 of the inner heat dissipation plate 3 and the substrate 9 of the outer heat dissipation plate 4 are respectively attached to the two side walls corresponding to the high-power load 2 to form a surface contact, which can increase the contact area between the inner heat dissipation plate 3, the outer heat dissipation plate 4 and the high-power load 2 and improve the heat transfer range. The heat dissipation column 10 of the outer heat dissipation plate 4 extends to the outside of the drone fuselage 1, and the extension length is ≤5mm, so that the heat dissipation column 10 of the outer heat dissipation plate 4 is partially exposed to the outside.

[0034] At the same time, a heat conducting layer 11 is arranged between the substrate 9 of the inner heat dissipation plate 3, the substrate 9 of the outer heat dissipation plate 4 and the side wall of the high-power load 2. The heat conducting layer 11 is a layer structure filled with a heat conducting medium. Here, the heat conducting medium can be thermally conductive silicone grease, and the heat conducting layer 11 can improve the heat transfer effect.

[0035] Since both the inner heat sink 3 and the outer heat sink 4 are in contact with the air, an anti-oxidation layer is provided on the surface of the inner heat sink 3 and the outer heat sink 4. The anti-oxidation layer is anodized on the surface of the heat sink, which can achieve the effect of anti-oxidation corrosion, improving radiation capacity and stabilizing heat dissipation.

[0036] In this embodiment, the substrate 9 has different thickness specifications. Specifically, the thickness d of the substrate 9 is 2-4 mm, 4-6 mm, 6-8 mm, 8-10 mm, and ≥10 mm. For different specifications of the substrate 9, the heat dissipation column 10 also has corresponding sizes, which is to reduce the thickness-to-height ratio of the heat dissipation column 10, so as to enhance the heat dissipation performance. The thickness-to-height ratio is the ratio of the thickness of the heat dissipation column 10 to the height.

[0037] When the thickness d of the substrate 9 is 2-4 mm, the dimension λ of the large diameter end of the heat dissipation column 10 is 1.5 mm, and the height h of the heat dissipation column 10 is ≥ 6 mm; When the thickness d of the substrate 9 is 4-6 mm, the dimension λ of the large diameter end of the heat dissipation column 10 is 2 mm, and the height h of the heat dissipation column 10 is ≥ 8 mm; When the thickness d of the substrate 9 is 6-8 mm, the dimension λ of the large diameter end of the heat dissipation column 10 is 2.5 mm, and the height h of the heat dissipation column 10 is ≥ 8 mm; When the thickness d of the substrate 9 is 8-10 mm, the dimension λ of the large diameter end of the heat dissipation column 10 is 3 mm, and the height h of the heat dissipation column 10 is ≥ 10 mm; When the thickness d of the substrate 9 is ≥10 mm, the dimension λ of the large diameter end of the heat dissipation column 10 is 4 mm, and the height h of the heat dissipation column 10 is ≥10 mm.

[0038] After the inner heat sink 3 and the outer heat sink 4 absorb heat, they dissipate the heat in the form of convection. In the process of convection heat dissipation, the heat dissipation area is mainly determined by the surface area of ​​the plurality of heat sinks 10. The larger the surface area, the better the heat dissipation effect; the smaller the surface area, the worse the heat dissipation effect. The denser and more numerous the heat sinks 10 per unit volume are, the larger the surface area for effective heat dissipation and the better the heat dissipation performance. Therefore, needle-shaped heat sinks 10 are used to enhance the heat dissipation performance by reducing the thickness-to-height ratio of the heat sinks 10. The smaller the thickness-to-height ratio means that the denser and more numerous the heat sinks 10 per unit volume can be, the larger the surface area for effective heat dissipation and the better the heat dissipation performance.

[0039] The heat dissipation structure dissipates heat through natural air cooling. Since the outer heat sink 4 is exposed to the outside, it can exchange heat with the air. In order to achieve contact between the air and the inner heat sink 3, front vents 5 and rear heat sinks 6 are respectively provided on the side walls of the UAV fuselage 1 on the front and rear sides of the high-power load 2. The front vents 5 and rear heat sinks 6 are arranged symmetrically front and back with the high-power load 2 as the center, and the front vents 5 and rear heat sinks 6 are arranged front and back along the forward flight direction of the UAV, that is, the air flow passes through the front vents 5 first and then passes through the rear heat sink 6.

[0040] In order to increase the ventilation volume, the number of the front vents 5 is at least two arranged in parallel front and back, and the same is true for the rear heat dissipation vents 6. In order to improve the air circulation and directionality, the front vents 5 are a fish fin-like structure bent in a "〉" shape, and the bend of the front vents 5 is an arc transition. The front vents 5 of this shape can better guide the airflow generated when the drone is flying to the inside of the drone body 1; the front vents 5 and the rear heat dissipation vents 6 have the same structure.

[0041] The height of the front vent 5 and the rear heat dissipation vent 6 is consistent with the height of the high-power load 2, and the height is H. The openings of the front vent 5 and the rear heat dissipation vent 6 are both oriented toward the high-power load 2, and the opening angles θ of the front vent 5 and the rear heat dissipation vent 6 are in the range of 60°≤θ≤90°. The appropriate opening angle θ avoids too small an angle, which will cause the lengths of both sides of the front vent 5 to be too long, resulting in a large amount of wind energy being wasted and unable to fully enter the drone fuselage 1 for heat dissipation; it also avoids too large an angle, which will cause insufficient pressure difference, and prevent a large amount of wind energy from entering the front vent 5, greatly reducing the heat dissipation efficiency.

[0042] The front vent 5, the outer heat dissipation plate 4 and the rear heat dissipation port 6 are connected to form an outer heat dissipation channel 8, which is a linear channel structure. The front vent 5, the inner heat dissipation plate 3 and the rear heat dissipation port 6 are connected to form an inner heat dissipation channel 7, which is a curved streamlined channel structure. The air flows through the outer heat dissipation channel 8 and the inner heat dissipation channel 7 at the same time, thereby performing an efficient cooling operation.

[0043] The principle of the present invention is: during the operation of the UAV, the heat emitted by the high-power load 2 is simultaneously transferred to the outer heat sink 4 and the inner heat sink 3, thereby improving the heat dissipation effect of the high-power load 2. When the UAV is flying, a high-speed airflow is formed, and the high-speed airflow takes away the heat on the surface of the outer heat sink 4 during the process of passing through the outer heat dissipation channel 8. At the same time, under the action of the front vents 5 and the rear heat dissipation vents 6, the high-speed airflow passes through the inner heat dissipation channel 7, and then takes away the heat on the surface of the inner heat sink 3, thereby achieving natural air cooling of the high-power load 2.

[0044] The air-cooling structure of the present invention is simple and reliable. It combines the front air vents 5 and the rear heat dissipation vents 6, the needle-shaped heat dissipation columns 10, the heat-conducting layer 11 and other efficient heat transfer means to optimize the heat dissipation structure to expand the heat dissipation area, increase the fluid disturbance and improve the heat dissipation capacity of the structure. It not only solves the problem of air-cooling equipment occupying part of the space, but also solves the overly complex design of the liquid cooling system, thereby reducing the complexity of the UAV structural design and greatly reducing the weight of the UAV. It not only reduces the loss of the engine, saves energy, and prolongs the service life of the UAV, but also allows the UAV to have more load to carry the high-power load 2, and can better achieve the goal of combining the high-power load 2 with the UAV.

[0045] The embodiments described above are only preferred embodiments of the present invention and are not intended to limit the scope of implementation of the present invention. Therefore, any equivalent changes or modifications made according to the structures, features and principles described in the patent scope of the present invention should be included in the scope of the patent application of the present invention.

Claims

1. A heat dissipation structure for a high-power load of an unmanned aerial vehicle, used for heat dissipation and cooling of a high-power load (2) on the inner wall of an unmanned aerial vehicle fuselage (1), characterized in that: It comprises an inner heat dissipation plate (3), an outer heat dissipation plate (4), a front vent (5), a rear heat dissipation port (6), an inner heat dissipation channel (7) and an outer heat dissipation channel (8); An inner heat sink (3) and an outer heat sink (4) are respectively arranged on two sides corresponding to the high-power load (2); the inner heat sink (3) is located inside the UAV fuselage (1); the inner heat sink (3) comprises a base plate (9) and a plurality of needle-shaped heat sink columns (10) arranged on the base plate (9); the outer heat sink (4) passes through the side wall of the UAV fuselage (1) and extends to the outside of the UAV fuselage (1); the structure of the outer heat sink (4) is the same as that of the inner heat sink (3); The front vents (5) and the rear heat dissipation vents (6) are symmetrically provided on the side walls of the UAV fuselage (1) on both sides of the front and rear of the high-power load (2) in the forward flight direction of the UAV. The front vents (5), the outer heat dissipation plate (4) and the rear heat dissipation vents (6) are connected to form the outer heat dissipation channel (8), and the front vents (5), the inner heat dissipation plate (3) and the rear heat dissipation vents (6) are connected to form the inner heat dissipation channel (7).

2. The heat dissipation structure of the UAV high-power load according to claim 1 is characterized in that: The substrate (9) of the inner heat dissipation plate (3) and the substrate (9) of the outer heat dissipation plate (4) are respectively attached to the two side walls corresponding to the high-power load (2); a heat-conducting layer (11) is provided between the substrate (9) of the inner heat dissipation plate (3), the substrate (9) of the outer heat dissipation plate (4) and the side wall of the high-power load (2); the heat-conducting layer (11) is a layer structure filled with a heat-conducting medium.

3. The heat dissipation structure of the high-power load of the UAV according to claim 1 is characterized in that: The thickness of the inner heat sink (3) is greater than that of the outer heat sink (4); the inner heat sink (3) and the outer heat sink (4) cooperate to clamp the high-power load (2); the inner heat sink (3) and the outer heat sink (4) are both copper plate structures; and an anti-oxidation layer is provided on the surface of the inner heat sink (3) and the outer heat sink (4).

4. The heat dissipation structure of a high-power load of an unmanned aerial vehicle according to claim 1, characterized in that: The substrate (9) and the heat dissipation column (10) are integrally formed, and the thickness d of the substrate (9) is one of 2-4 mm, 4-6 mm, 6-8 mm, 8-10 mm, and ≥10 mm.

5. The heat dissipation structure of the high-power load of the UAV according to claim 4 is characterized in that: A plurality of the heat dissipation columns (10) are arranged in a rectangular array, the heat dissipation columns (10) are of a prism or truncated cone structure, the heat dissipation columns (10) are arranged perpendicular to the substrate (9), the large diameter ends of the heat dissipation columns (10) are connected and fixed to the substrate (9), the large diameter ends of two adjacent heat dissipation columns (10) are spaced w ≥ 4 mm, and the inclination of the side surface of each heat dissipation column (10) is 2 to 4°; The heat dissipation column (10) of the external heat dissipation plate (4) extends to the outside of the drone body (1), with an extension length of ≤5 mm.

6. The heat dissipation structure of a high-power load of an unmanned aerial vehicle according to claim 5, characterized in that: The thickness d of the substrate (9) is 2-4 mm, the dimension λ of the large diameter end of the heat dissipation column (10) is 1.5 mm, and the height h of the heat dissipation column (10) is ≥ 6 mm; Or, the thickness d of the substrate (9) is 4-6 mm, the dimension λ of the large diameter end of the heat dissipation column (10) is 2 mm, and the height h of the heat dissipation column (10) is ≥ 8 mm; Or, the thickness d of the substrate (9) is 6-8 mm, the dimension λ of the large diameter end of the heat dissipation column (10) is 2.5 mm, and the height h of the heat dissipation column (10) is ≥ 8 mm; Or, the thickness d of the substrate (9) is 8-10 mm, the dimension λ of the large diameter end of the heat dissipation column (10) is 3 mm, and the height h of the heat dissipation column (10) is ≥10 mm; Alternatively, the substrate (9) has a thickness d≥10 mm, the heat dissipation column (10) has a large diameter end dimension λ of 4 mm, and the heat dissipation column (10) has a height h≥10 mm.

7. The heat dissipation structure of a high-power load of an unmanned aerial vehicle according to claim 1, characterized in that: The number of the front ventilation openings (5) and the rear heat dissipation openings (6) is at least two arranged in parallel front and back, the front ventilation opening (5) is a fish-fin-shaped structure bent into a "〉" shape, the front ventilation opening (5) and the rear heat dissipation opening (6) have the same structure, the openings of the front ventilation openings (5) and the rear heat dissipation openings (6) are both oriented toward the high-power load (2), the opening angles θ of the front ventilation openings (5) and the rear heat dissipation openings (6) are in the range of 60°≤θ≤90°, and the heights of the front ventilation openings (5) and the rear heat dissipation openings (6) are consistent with the height of the high-power load (2).

8. The heat dissipation structure of a high-power load of an unmanned aerial vehicle according to claim 1, characterized in that: The outer heat dissipation channel (8) is a linear channel structure, and the inner heat dissipation channel (7) is a streamlined channel structure that is bent into an arc shape.

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