Heat dissipation system and unmanned aerial vehicle

Abstract

The utility model discloses a heat dissipation system and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The cooling system comprises a supporting frame, a shock absorber and at least two radiators, all the radiators are connected to the supporting frame, and the shock absorber is connected to the supporting frame and used for being directly or indirectly connected with a fuselage frame of the unmanned aerial vehicle. The at least two radiators are connected to the supporting frame, so that the integration level of the heat dissipation system is high. The supporting frame is connected with the fuselage frame of the unmanned aerial vehicle through the shock absorbers, so that vibration generated when the unmanned aerial vehicle flies can be absorbed by the shock absorbers to a certain extent, vibration transmitted to the radiator is reduced, and therefore the radiator is protected against damage caused by vibration. Compared with the mode that all the radiators are connected with the machine body frame, the heat dissipation system is high in integration degree and more convenient to assemble and disassemble. The unmanned aerial vehicle provided by the embodiment of the utility model comprises the heat dissipation system.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and more particularly, to a heat dissipation system and an unmanned aerial vehicle. Background Art

[0002] During the flight of an unmanned aerial vehicle, the engine generates a large amount of heat, which needs to be dissipated through a radiator. In the prior art, the radiator is usually directly connected and fixed to the fuselage frame of the unmanned aerial vehicle. The vibration generated during the flight of the unmanned aerial vehicle will be directly transmitted to the radiator, resulting in easy damage to the radiator. In addition, when the heat dissipation system includes at least two radiators, each radiator is respectively connected to the fuselage frame of the unmanned aerial vehicle, and the integration of the radiators is poor. Summary of the Utility Model

[0003] The purpose of the present application is to provide a heat dissipation system and an unmanned aerial vehicle, in which the heat dissipation system has better integration, and the radiator therein is not easily damaged due to the vibration of the unmanned aerial vehicle.

[0004] To achieve the above object, in a first aspect, the present application provides a heat dissipation system for use in an unmanned aerial vehicle, including a support frame, shock absorbers, and at least two radiators. Each radiator is connected to the support frame, and the shock absorbers are connected to the support frame and are used to directly or indirectly connect to the fuselage frame of the unmanned aerial vehicle.

[0005] In an alternative embodiment, the heat dissipation system includes two support frames spaced apart in a first direction. The two support frames are respectively connected to at least one shock absorber. Each radiator is arranged in a second direction, and each radiator is connected to the two support frames; wherein, the first direction is perpendicular to the second direction.

[0006] In an alternative embodiment, each end of each support frame in the second direction is respectively connected to a shock absorber.

[0007] In an alternative embodiment, the support frame includes a support body extending in the second direction. The support body is provided with shock absorber fixing holes for installing shock absorbers, and two edges of the support body spaced apart in the first direction are respectively provided with first reinforcing ribs.

[0008] In an alternative embodiment, at least one first reinforcing rib of the support frame is provided with radiator mounting holes, and the first reinforcing rib is connected to the radiator through the radiator mounting holes.

[0009] In an alternative embodiment, the heat dissipation system further includes a connecting frame. The connecting frame is arranged at the adjacent position of two adjacent radiators and is located on the side of the two radiators facing away from the support frame, and is connected to the two adjacent radiators.

[0010] In an alternative embodiment, the heat dissipation system further includes a fan. The fan is connected to the side of the connecting frame facing away from the radiator.

[0011] In an alternative embodiment, two adjacent radiators are arranged along a second direction, the axis of the fan is perpendicular to the second direction, and the movement space of the fan blades can be axially projected onto two adjacent radiators along the axis of the fan.

[0012] In an alternative embodiment, the connecting frame includes a connecting body extending along a first direction, two adjacent radiators are arranged along a second direction, the first direction is perpendicular to the second direction, a fan mounting hole is provided on the connecting body, the fan is connected to the connecting body through the fan mounting hole, connecting portions are respectively provided at both ends of the connecting body in the first direction, mounting portions are provided on both radiators, and the mounting portions and the connecting portions are connected by fasteners.

[0013] In an alternative embodiment, second reinforcing ribs are respectively provided at two edges of the connecting body spaced apart in the second direction.

[0014] In an alternative embodiment, the heat dissipation system further includes a connecting component, the connecting component is connected to the shock absorber, and the connecting component is used to connect to the fuselage frame.

[0015] In an alternative embodiment, the connecting component includes a hoop, and the support frame is connected to the fuselage frame of the drone through the shock absorber and the hoop.

[0016] In an alternative embodiment, at least two of the radiators include an oil-cooled radiator and an intercooler.

[0017] In a second aspect, the present application provides a drone, including a fuselage frame and the heat dissipation system according to any one of the foregoing embodiments, and the heat dissipation system is connected to the fuselage frame through a shock absorber.

[0018] The beneficial effects of the heat dissipation system provided by the embodiments of the present application include:

[0019] The heat dissipation system provided by the embodiment of the present application includes a support frame, shock absorbers, and at least two radiators. Each radiator is connected to the support frame, and the shock absorbers are connected to the support frame and are used to be directly or indirectly connected to the fuselage frame of the drone. By connecting at least two radiators to the support frame, the integration degree of the heat dissipation system is relatively high. The support frame is connected to the fuselage frame of the drone through shock absorbers, so that the vibration of the drone during flight can be absorbed by the shock absorbers to a certain extent, reducing the vibration transmitted to the radiators, thereby protecting the radiators from being damaged easily due to vibration. In addition, since multiple radiators are centrally installed on the support frame, when assembling the heat dissipation system, the radiators can be assembled to the support frame first, and then the support frame together with the radiators can be installed on the fuselage frame; when disassembling the heat dissipation system, multiple radiators together with the support frame can be removed from the fuselage frame. Compared with each radiator being separately connected to the fuselage frame, the heat dissipation system provided by the embodiment of the present application is more convenient to load and unload. The drone provided by the embodiment of the present application includes the above heat dissipation system, and thus also has the above beneficial effects.

[0020] Other features and advantages of the present application will be described in detail in the subsequent specific implementation part. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as a limitation of the scope. For those of ordinary skill in the art, other related drawings can also be obtained based on these drawings without creative efforts.

[0022] Figure 1 It is a schematic diagram of the heat dissipation system installed on the fuselage frame in an embodiment of the present application;

[0023] Figure 2 For Figure 1 the enlarged view of the partial area II in

[0024] Figure 3 It is a schematic diagram of the support frame in an embodiment of the present application;

[0025] Figure 4 It is a schematic diagram of the connection between the support frame and the first radiator and the second radiator in an embodiment of the present application;

[0026] Figure 5 It is a schematic diagram of the connecting frame in an embodiment of the present application.

[0027] Icons: 100 - fuselage frame; 110 - top beam; 120 - bottom beam; 200 - cooling system; 210 - support frame; 211 - support body; 212 - shock absorber fixing hole; 213 - first reinforcing rib; 214 - radiator mounting hole; 215 - first weight reduction hole; 220 - shock absorber; 230 - connecting component; 241 - first radiator; 242 - second radiator; 243 - support part; 244 - first mounting part; 245 - second mounting part; 246 - oil cooling pipe; 247 - intercooling pipe; 250 - connecting frame; 251 - connecting body; 252 - connecting part; 253 - radiator connection hole; 254 - second reinforcing rib; 255 - fan mounting hole; 256 - second weight reduction hole; 260 - fan; 300 - landing gear. Detailed implementation manners

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. The components of the embodiments of the present application described and illustrated herein can generally be arranged and designed in a variety of different configurations.

[0029] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of this application is usually placed during use. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present application. In addition, terms such as "first", "second", etc. are only used for descriptive distinction and cannot be understood as indicating or implying relative importance.

[0030] In the description of the present application, it should also be noted that unless otherwise clearly specified and limited, the terms "set", "connect" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances. It should be noted that, without conflict, the features in the embodiments of the present application can be combined with each other.

[0031] Existing drones have heat-generating components. Taking an unmanned helicopter as an example, its engine is a heat-generating component. The engine of an unmanned helicopter is usually an internal combustion engine. During operation, the engine inhales air for fuel combustion. During the operation of the engine, a large amount of heat is generated. If the heat cannot be effectively removed and accumulates inside the drone, it may cause the engine to overheat, which has a negative impact on its normal operation; and the overall high temperature inside the drone will also cause the electronic devices carried on the drone to malfunction. In the drones of related technologies, a heat dissipation system is provided to assist in heat dissipation, and the heat dissipation system includes multiple radiators to achieve different types of heat dissipation. For example, some radiators are used to dissipate heat from the cylinder block of the engine, some radiators are used to dissipate heat from compressed air, and some radiators are used to dissipate heat from the engine oil. In related technologies, each radiator is respectively connected to the fuselage frame of the drone. When the drone vibrates due to flight, the fuselage frame will transmit the vibration to the radiator, which easily causes the radiator to be damaged. Therefore, the reliability of the radiator is poor. Moreover, different radiators are independently connected to the fuselage frame of the drone, resulting in a low integration degree of the heat dissipation system. When removing the heat dissipation system from the fuselage frame, each radiator needs to be disassembled. Therefore, the heat dissipation system in related technologies also has the problem of inconvenient loading and unloading.

[0032] In order to improve the problems of poor reliability and low integration degree of the heat dissipation system in related technologies. An embodiment of the present application provides a heat dissipation system and a drone. Each radiator is installed on a support frame, and the support frame is connected to the fuselage frame through a shock absorber, which not only improves the integration degree of the heat dissipation system but also reduces the risk of the radiator being damaged due to vibration.

[0033] Figure 1 Schematic diagram of the heat dissipation system 200 installed on the fuselage frame 100 in an embodiment of the present application; Figure 2 For Figure 1 The enlarged view of the partial II in. As Figure 1 And Figure 2 As shown, the drone provided by the embodiment of the present application includes a fuselage frame 100 and a heat dissipation system 200 provided on the fuselage frame 100. The drone in this embodiment is an unmanned helicopter. In addition to the fuselage frame 100 and the heat dissipation system 200, the drone also includes a housing (not shown in the figure), an engine (not shown in the figure), a rotor assembly (not shown in the figure), a landing gear 300, etc. The fuselage frame 100 plays a role of a support structure, and each component can be installed and fixed through the fuselage frame 100.

[0034] In this embodiment, the fuselage frame 100 includes two top beams 110 spaced apart in the first direction (the direction of the ab arrow in the figure), and the two top beams 110 extend in the second direction (the direction of the cd arrow in the figure). In this embodiment, the first direction is the left - right direction of the drone, and the second direction is the front - back direction of the drone. Therefore, the first direction is perpendicular to the second direction. The heat dissipation system 200 is installed on the top beams 110 of the fuselage frame 100. Further, the landing gear 300 is arranged below the bottom beam 120 and is used to support the ground when the drone takes off and lands. The engine can be arranged in the space between the top beam 110 and the bottom beam 120.

[0035] In an embodiment of the present application, the heat dissipation system 200 includes a support frame 210, a shock absorber 220, and at least two radiators. Each radiator is connected to the support frame 210, and the shock absorber 220 is connected to the support frame 210 and is used to directly or indirectly connect to the fuselage frame 100 of the drone. In this embodiment, the heat dissipation system 200 further includes a connection component 230. The connection component 230 is connected to the shock absorber 220, and the connection component 230 is used to connect to the fuselage frame 100. The heat dissipation system 200 is connected to the fuselage frame 100 through the shock absorber 220. Specifically, the shock absorber 220 of the heat dissipation system 200 is indirectly connected to the top beam 110 of the fuselage frame 100 through the connection component 230.

[0036] Figure 3 It is a schematic diagram of the support frame 210 in an embodiment of the present application. Combining Figures 1 to 3 As shown, the heat dissipation system 200 includes two support frames 210. The two support frames 210 are spaced apart in the first direction. The two support frames 210 are respectively connected to at least one shock absorber 220. Each radiator is arranged in the second direction, and each radiator is connected to the two support frames 210. In this embodiment, the two support frames 210 correspond to the two top beams 110 of the fuselage frame 100 one by one, and the two support frames 210 are respectively connected to the two top beams 110 through the shock absorbers 220. The heat dissipation system 200 of this embodiment includes two radiators. For the convenience of representation, the two radiators are respectively named the first radiator 241 and the second radiator 242. In other embodiments, the heat dissipation system 200 may further include more radiators.

[0037] In this embodiment, a shock absorber 220 is connected to each end of the support frame 210 in the second direction, and the two shock absorbers 220 can support the support frame 210 well. The shock absorber 220 can be an elastic component, such as a rubber block, a spring, etc. When the fuselage frame 100 vibrates, the shock absorber 220 can generate a certain elastic deformation by itself, so as to absorb the amplitude of the fuselage frame 100 and reduce the vibration amount transmitted to the support frame 210. In other embodiments, the number of shock absorbers 220 provided on each support frame 210 can be increased or decreased as needed.

[0038] In this embodiment, the support frame 210 includes a support body 211 extending in the second direction. A shock absorber fixing hole 212 for installing the shock absorber 220 is provided on the support body 211. First reinforcing ribs 213 are respectively provided on two edges of the support body 211 spaced apart in the first direction. In this embodiment, by providing the two first reinforcing ribs 213, the anti-bending ability of the support frame 210 can be improved. Further, a plurality of first weight-reducing holes 215 are also provided on the support body 211 to reduce the weight of the support frame 210. Optionally, the support body 211 and the first reinforcing ribs 213 can be integrally formed.

[0039] Figure 4 It is a schematic connection diagram of the support frame 210, the first radiator 241, and the second radiator 242 in an embodiment of the present application. As Figure 3 and Figure 4 shown, in this embodiment, a radiator mounting hole 214 is provided on at least one of the first reinforcing ribs 213 of the support frame 210, and the first reinforcing rib 213 is connected to the radiator through the radiator mounting hole 214. Specifically, support portions 243 are provided on both the first radiator 241 and the second radiator 242, and the support portions 243 of the radiator are connected to the first reinforcing ribs 213 of the support frame 210 by screws.

[0040] Please refer to again Figure 2In this embodiment, the heat dissipation system 200 further includes a connecting frame 250, which is arranged adjacent to two adjacent heat sinks and located on the side of the two heat sinks away from the support frame 210, and connected to the two adjacent heat sinks. In this embodiment, the connecting frame 250 is arranged adjacent to the first heat sink 241 and the second heat sink 242, located on the side of the first heat sink 241 and the second heat sink 242 away from the support frame 210, and connected to the first heat sink 241 and the second heat sink 242. By providing the connecting frame 250, the integrity of the heat dissipation system 200 can be improved, and the reliability of the first heat sink 241 and the second heat sink 242 can be improved by connecting the first heat sink 241 and the second heat sink 242 together. In some abnormal cases, even if the connection between the first heat sink 241 or the second heat sink 242 and the support frame 210 is loose, due to the fixing effect of the connecting frame 250, it will not shake excessively on the support frame 210 or fall off from the support frame 210.

[0041] In the present embodiment, the heat dissipation system 200 further includes a fan 260, and the fan 260 is connected to the side of the connecting frame 250 away from the radiator. By providing the fan 260, the air flow around the radiator can be enhanced and the heat dissipation efficiency can be improved. In the present embodiment, the fan 260 is located on the side of the connecting frame 250 away from the first radiator 241 and the second radiator 242. The fan 260 in the present embodiment is an axial flow fan, and its axis is located adjacent to the first radiator 241 and the second radiator 242. The air outlet direction of the fan 260 can be toward the first radiator 241 and the second radiator 242, and can also be away from the first radiator 241 and the second radiator 242.

[0042] In this embodiment, two adjacent radiators (the first radiator 241 and the second radiator 242) are arranged along the second direction, the axis of the fan 260 is perpendicular to the second direction, and the movement space of the blades of the fan 260 can be projected onto the two adjacent radiators along the axial direction of the fan 260. In this embodiment, the axis of the fan 260 is also perpendicular to the first direction, so the extension direction of the axis of the fan 260 is the up and down direction of the drone (the direction of the arrow ef in the figure). The movement space of the blades of the fan 260 is a disc-shaped space, which can be projected onto the two adjacent radiators along the axial direction of the fan 260, which means that at least parts of the two radiators can be located in the blowing path or the suction path of the fan 260, and the stronger air convection can improve the heat dissipation effect of the radiator. In this embodiment, two radiators can be purged by one fan 260, which can save costs and improve the utilization rate of the fan 260; in other embodiments, a larger number of fans 260 can be set on the connecting frame 250, and the direction of the fan 260 can also be adjusted as needed, for example, two fans 260 are set to face the first radiator 241 and the second radiator 242 respectively.

[0043] Figure 5 This is a schematic diagram of the connecting frame 250 in an embodiment of the present application. Please refer to Figure 2 and Figure 5 In this embodiment, the connecting frame 250 includes a connecting body 251 extending in the first direction. A fan mounting hole 255 is provided on the connecting body 251, and the fan 260 is connected to the connecting body 251 through the fan mounting hole 255. Connecting parts 252 are respectively provided at both ends of the connecting body 251 in the first direction. Mounting parts are provided on both radiators, and the mounting parts and the connecting parts 252 are connected by fasteners. In this embodiment, first mounting parts 244 are respectively provided at both ends of the first radiator 241 in the first direction, and second mounting parts 245 are respectively provided at both ends of the second radiator 242 in the first direction. Matching holes are provided on both the first mounting part 244 and the second mounting part 245. Two radiator connecting holes 253 are provided on the connecting part 252, and the connecting part 252 is respectively connected to the first mounting part 244 and the second mounting part 245 through the two radiator connecting holes 253 and screws. Further, a second weight-reducing hole 256 is also provided on the connecting body 251 to reduce the overall weight of the connecting frame 250.

[0044] In this embodiment, second reinforcing ribs 254 are respectively provided at two edges of the connecting body 251 spaced apart in the second direction. The second reinforcing ribs 254 can improve the strength of the connecting frame 250 and enhance its anti-bending ability. Optionally, the connecting body 251, the connecting part 252 and the second reinforcing ribs 254 are integrally formed.

[0045] In this embodiment, the connecting assembly 230 includes a hoop. The support frame 210 is connected to the fuselage frame 100 of the unmanned aerial vehicle through the shock absorber 220 and the hoop, so as to fix the support frame 210 to the top beam 110 of the fuselage frame 100 and facilitate disassembly.

[0046] The first radiator 241 and the second radiator 242 can be used to achieve the same heat dissipation function or different heat dissipation functions. For example, in this embodiment, the first radiator 241 and the second radiator 242 have different functions. The first radiator 241 is an oil-cooled radiator for dissipating heat from the engine oil; the second radiator 242 is an intercooler for dissipating heat from the compressed air.

[0047] Specifically, the cooling system 200 further includes an oil cooling pipe 246. The first radiator 241, the oil cooling pipe 246, and the engine form an oil cooling loop for the engine oil to circulate. The engine oil absorbs heat in the engine, circulates along the oil cooling loop to the first radiator 241 outside the engine, and the first radiator 241 transfers the heat of the engine oil to the external air, causing the engine oil to cool down. The cooled engine oil then circulates back to the engine interior through the oil cooling pipe 246 for lubrication and heat absorption, thus forming a cycle.

[0048] In this embodiment, the drone further includes a turbocharger (not shown in the figure), and the cooling system 200 further includes an intercooling pipe 247. The intercooling pipe 247 is used to connect the turbocharger, the second radiator 242, and the intake port of the engine in series. Specifically, the second radiator 242 is connected in series between the intake port of the engine and the turbocharger. The second radiator 242 is used to cool the gas that has been pressurized by the turbocharger and enters the intake port of the engine. Specifically in this embodiment, the intake end of the second radiator 242 is connected to the turbocharger through the intercooling pipe 247, and the outlet end of the second radiator 242 is connected to the intake port of the engine through the intercooling pipe 247. The turbocharger increases the intake air volume of the engine in an active supercharging manner, thereby improving the power of the engine. Since the turbocharger does work on compressing the air, the compressed air will heat up, and the high-temperature air entering the engine will increase the heat load of the engine; and the higher the air temperature, the greater the pressure, which will inhibit the turbocharger from delivering high-pressure gas to the engine, restricting the intake air volume and making it difficult to further increase the engine power. In this embodiment, by cooling the high-temperature air output by the turbocharger, the temperature of the gas entering the engine can be reduced, the heat load of the engine can be reduced, and the intake air can also be increased to improve the power of the engine.

[0049] It should be understood that in other embodiments, the first radiator 241 and the second radiator 242 may also be radiators of other types and functions. For example, at least one of the first radiator 241 and the second radiator 242 is a water-cooled radiator, which forms a water-cooling cycle by connecting with a water-cooling pipe and is used to cool the cylinder block of the engine.

[0050] In summary, the embodiment of the present application provides a heat dissipation system 200 and a drone. The heat dissipation system 200 includes a support frame 210, a shock absorber 220, and at least two radiators. Each radiator is connected to the support frame 210, and the shock absorber 220 is connected to the support frame 210 and is used to directly or indirectly connect to the fuselage frame 100 of the drone. By connecting at least two radiators to the support frame 210, the integration degree of the heat dissipation system 200 is relatively high. The support frame 210 is connected to the fuselage frame 100 of the drone through the shock absorber 220, so that the vibration of the drone during flight can be absorbed by the shock absorber 220 to a certain extent, reducing the vibration transmitted to the radiator, thereby protecting the radiator from being damaged easily due to vibration. In addition, since multiple radiators are centrally installed on the support frame 210, when assembling the heat dissipation system 200, the radiators can be assembled on the support frame 210 first, and then the support frame 210 together with the radiators can be installed on the fuselage frame 100; when disassembling the heat dissipation system 200, multiple radiators together with the support frame 210 can be removed from the fuselage frame 100. Compared with the case where each radiator is separately connected to the fuselage frame 100, the heat dissipation system 200 provided by the embodiment of the present application is more convenient to load and unload. The drone provided by the embodiment of the present application includes the above heat dissipation system 200, so it also has the above beneficial effects.

[0051] The above is only the preferred embodiment of the present application and is not used to limit the present application. For those skilled in the art, various changes and modifications can be made to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A heat dissipation system, applied to a drone, characterized in that: It comprises a support frame, a shock absorber and at least two radiators, each of the radiators is connected to the support frame, and the shock absorber is connected to the support frame and is used to be directly or indirectly connected to the fuselage frame of the drone.

2. The heat dissipation system according to claim 1, characterized in that: The heat dissipation system includes two support frames, which are spaced apart in a first direction, and are respectively connected to at least one shock absorber. The radiators are arranged in a second direction, and each radiator is connected to the two support frames; wherein the first direction is perpendicular to the second direction.

3. The heat dissipation system according to claim 2, characterized in that: Each of the support frames is respectively connected to a shock absorber at both ends in the second direction.

4. The heat dissipation system according to claim 2, characterized in that: The support frame includes a support body extending along the second direction, the support body is provided with a shock absorber fixing hole for installing the shock absorber, and two edges of the support body spaced apart in the first direction are respectively provided with first reinforcing ribs.

5. The heat dissipation system according to claim 4, characterized in that: A radiator mounting hole is provided on at least one of the first reinforcing ribs of the support frame, and the first reinforcing rib is connected to the radiator through the radiator mounting hole.

6. The heat dissipation system according to any one of claims 1 to 5, characterized in that: The heat dissipation system further comprises a connecting frame, which is arranged adjacent to two adjacent radiators and located on a side of the two radiators away from the supporting frame, and is connected to the two adjacent radiators.

7. The heat dissipation system according to claim 6, characterized in that: The heat dissipation system further comprises a fan, and the fan is connected to a side of the connection frame away from the radiator.

8. The heat dissipation system according to claim 7, characterized in that: The two adjacent heat sinks are arranged along the second direction, the axis of the fan is perpendicular to the second direction, and the movement space of the fan blades can be projected onto the two adjacent heat sinks along the axial direction of the fan.

9. The heat dissipation system according to claim 7, characterized in that: The connecting frame includes a connecting body extending along a first direction, and two adjacent radiators are arranged along a second direction, the first direction is perpendicular to the second direction, a fan mounting hole is provided on the connecting body, and the fan is connected to the connecting body through the fan mounting hole, and connecting parts are respectively provided at both ends of the connecting body in the first direction, and mounting parts are provided on both radiators, and the mounting parts are connected to the connecting parts through fasteners.

10. The heat dissipation system according to claim 9, characterized in that: Two edges of the connection body spaced apart in the second direction are respectively provided with second reinforcing ribs.

11. The heat dissipation system according to any one of claims 1 to 5, characterized in that: The heat dissipation system further comprises a connecting component, wherein the connecting component is connected to the shock absorber and is used to connect to the fuselage frame.

12. The heat dissipation system according to claim 11, characterized in that: The connecting assembly comprises a hoop, and the supporting frame is connected to the fuselage frame of the UAV through the shock absorber and the hoop.

13. The heat dissipation system according to any one of claims 1 to 5, characterized in that: The at least two radiators include an oil cooling radiator and an intercooling radiator.

14. A drone, characterized in that: It comprises a fuselage frame and the heat dissipation system according to any one of claims 1 to 13, wherein the heat dissipation system is connected to the fuselage frame via the shock absorber.

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