A heat dissipation system for drones

Abstract

This specification discloses a heat dissipation system for an unmanned aerial vehicle (UAV), including a heat dissipation frame, an air duct cover, a cooling fan, and a dust filter. The heat dissipation frame is made of metal and includes a heat dissipation air duct body (with a first heat dissipation fin on its inner wall, overlapping the position of the air duct cover) and an outer mounting platform. The top is sealed by a first sealing gasket, and the bottom by a second sealing gasket, forming a sealed cavity. An air inlet is located at the front end of the heat dissipation air duct body, protected from water seepage by the sealing gasket. The air duct cover is fixed to the top of the frame by the sealing gasket, with a thermally conductive contact surface on its upper surface and a second heat dissipation fin on its lower surface, forming a heat dissipation path with the first heat dissipation fin. A dust filter is installed at the rear exhaust port of the heat dissipation frame, and the cooling fan is fixed to the air inlet, driving cool air to exchange heat through the two heat dissipation fins before exhausting it from the exhaust port.

Description

Technical Field

[0001] This utility model relates to the field of drone heat dissipation technology, and more specifically, to a drone heat dissipation system. Background Technology

[0002] With the widespread application of drones in aerial photography, agriculture, logistics, and rescue, their functions are becoming increasingly complex, leading to a significant increase in the power and heat generation of their internal components. For example, high-resolution aerial photography chips and the motors of agricultural drones generate a large amount of heat during operation. Insufficient heat dissipation will result in decreased component performance, shortened lifespan, and even malfunctions, such as reduced battery life at high temperatures.

[0003] Meanwhile, drones operate in complex and diverse environments, especially when flying in the rain. Rainwater can seep into the drone's interior, causing short circuits, and the humid environment can also affect heat dissipation. Traditional heat dissipation methods struggle to simultaneously meet the requirements of efficient heat dissipation and waterproofing. Therefore, it is necessary to develop a heat dissipation system for drones that combines efficient heat dissipation with waterproofing. Utility Model Content

[0004] This specification provides a heat dissipation system for a drone to overcome at least one technical problem existing in the related art.

[0005] According to an embodiment of this specification, a heat dissipation system for a drone is provided, comprising:

[0006] The heat dissipation frame, air duct cover, cooling fan, and dust filter; among which,

[0007] The heat dissipation frame is made of metal and consists of a heat dissipation duct body and an outer mounting platform. The heat dissipation duct body is located at the same position as the duct cover, and its inner wall is evenly distributed with first heat dissipation fins along the duct direction. The outer mounting platform is used to fix the internal components of the UAV and conduct heat to the heat dissipation duct body.

[0008] The top of the heat dissipation frame is sealed to the top cover of the drone body by a first sealing gasket, and the bottom is sealed to the body structure by a second sealing gasket, forming a sealed heat dissipation cavity;

[0009] The front end of the heat dissipation duct body is provided with an air inlet. The air inlet is sealed by pressing the air inlet gasket against the air duct interface of the machine body to prevent external moisture from seeping in.

[0010] The air duct cover is pressed and fixed to the top of the heat dissipation frame by the air duct sealing gasket. The upper surface of the air duct cover is provided with a second thermally conductive contact surface and a third thermally conductive contact surface that are in contact with the heat-generating elements of the UAV. The lower surface is provided with a second heat dissipation fin. The second heat dissipation fin and the first heat dissipation fin of the heat dissipation frame form a continuous heat dissipation path.

[0011] The rear end of the heat dissipation frame is provided with an air outlet, and a dustproof net is installed at the air outlet.

[0012] The cooling fan is fixed at the air inlet and drives cold air to flow in from the air inlet. After heat exchange between the first heat dissipation fins of the heat dissipation frame and the second heat dissipation fins of the air duct cover, the air is discharged from the air outlet.

[0013] In some optional embodiments, the first sealing gasket, the second sealing gasket, the air inlet sealing gasket, and the air duct sealing gasket are all planar compression structures made of rubber or foam.

[0014] In some optional embodiments, the lower surface of the heat dissipation frame is provided with a heat-conducting plane, which is used to fix the internal components of the UAV and conduct heat to the heat dissipation duct body.

[0015] In some alternative embodiments, the thermally conductive contact surface of the air duct cover and the second heat dissipation fin are integrally formed metal structures.

[0016] In some optional embodiments, the first heat dissipation fins of the heat dissipation frame are arranged perpendicular to the inner wall of the air duct, and the first heat dissipation fins and the second heat dissipation fins of the air duct cover are spatially staggered to increase the heat dissipation area.

[0017] In some alternative embodiments, the first heat dissipation fin is located on the inner wall of the heat dissipation duct body, and the second heat dissipation fin is located above the heat dissipation duct body. The two are distributed in a vertical layer, and the projections of the first heat dissipation fin and the second heat dissipation fin partially overlap on the horizontal plane.

[0018] The beneficial effects of the embodiments in this specification are as follows:

[0019] 1. In one embodiment of the technical solution of this application, the heat dissipation frame is made of metal to improve thermal conductivity. The heat-conducting contact surface of the air duct cover and the heat dissipation frame and the heat dissipation fins are made of integrated molding process, which can shorten the heat transfer path, reduce thermal resistance, and achieve a compact heat dissipation layout.

[0020] 2. In one embodiment of this application, a waterproof barrier is constructed using sealing gaskets. Specifically, the sealing structure between the heat dissipation frame and the upper and lower surfaces of the casing isolates external moisture, the air inlet sealing gasket blocks the water inlet path of the air duct, and the air duct cover sealing gasket prevents internal moisture from seeping out. The heat dissipation air duct maintains airflow with the outside environment while completely isolating the working environment of the heat-generating components from the outside.

[0021] 3. In one embodiment of the technical solution of this application, a planar compression sealing structure is used to replace the traditional O-ring seal. Waterproofing is achieved through the planar contact between the metal frame and the sealing gasket (rubber / foam material), which eliminates the complex sealing groove design, reduces the processing difficulty and assembly cost, and ensures the sealing reliability under dynamic environment.

[0022] 4. In one embodiment of the technical solution of this application, a cooling fan is configured to drive air circulation. Through the forced convection heat exchange between the heat dissipation fins and the flowing air, the heat dissipation efficiency can be significantly improved compared with the traditional passive heat dissipation method relying on the drone shell, which can meet the heat dissipation requirements of high-power components.

[0023] 5. In one embodiment of the technical solution of this application, the heat dissipation frame has the dual functions of heat dissipation and structural support. Its peripheral platform directly serves as the mounting carrier for internal components, reducing independent support structures and realizing modular integrated design, thereby reducing system weight and volume while ensuring heat dissipation performance.

[0024] It should be noted that the above-mentioned technical effects do not require that each embodiment of the technical solution achieve the above-mentioned technical effects simultaneously. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments or related technologies of this specification, the drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 A schematic diagram of the overall structure of a heat dissipation system for a drone provided in an embodiment of this specification;

[0027] Figure 2 A top view of the air duct cover in the heat dissipation system of the UAV provided in the embodiments of this specification;

[0028] Figure 3 A view of the lower surface of the air duct cover in the heat dissipation system of the UAV provided in the embodiments of this specification;

[0029] Figure 4 A view of the lower surface of the heat dissipation frame in the heat dissipation system of the UAV provided in the embodiments of this specification;

[0030] Figure 5 This is a three-dimensional structural diagram of the heat dissipation frame in the heat dissipation system of the UAV provided in the embodiments of this specification.

[0031] Wherein, 1 represents the cooling fan, 2 represents the first sealing gasket, 3 represents the heat dissipation frame, 301 represents the first thermally conductive contact surface, 302 represents the air inlet, 303 represents the first heat dissipation fin, 304 represents the air outlet, 4 represents the second sealing gasket, 5 represents the air inlet sealing gasket, 6 represents the air duct cover, 601 represents the second thermally conductive contact surface, 602 represents the third thermally conductive contact surface, 603 represents the second heat dissipation fin, 7 represents the air duct sealing gasket, and 8 represents the dustproof mesh. Detailed Implementation

[0032] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0033] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0034] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0035] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0036] This embodiment provides a heat dissipation system for a drone, which will be described below in conjunction with... Figures 1 to 5This heat dissipation system will be described in detail, such as... Figure 1 As shown, the structure may include a heat dissipation frame 3, an air duct cover 6, a heat dissipation fan 1, and a dust filter 8; wherein, the heat dissipation frame 3 is made of metal and is divided into a heat dissipation air duct body and an outer mounting platform; wherein, the heat dissipation air duct body and the air duct cover 6 are overlapped, and the inner wall of the body is evenly distributed with first heat dissipation fins 303 along the air duct direction; the outer mounting platform is used to fix the internal components of the UAV and conduct heat to the heat dissipation air duct body;

[0037] The top of the heat dissipation frame 3 is sealed to the top cover of the drone body by pressing together with the first sealing gasket 2, and the bottom is sealed to the body structure by pressing together with the second sealing gasket 4, forming a sealed heat dissipation cavity;

[0038] The front end of the heat dissipation duct body is provided with an air inlet 302. The air inlet 302 is sealed by pressing the air inlet sealing gasket 5 with the air duct interface of the machine body to prevent external moisture from seeping in.

[0039] The air duct cover 6 is pressed and fixed to the top of the heat dissipation frame 3 by the air duct sealing gasket 7. The upper surface of the air duct cover 6 is provided with a second thermally conductive contact surface 601 and a third thermally conductive contact surface 602 that are in contact with the heat-generating elements of the UAV, and the lower surface is provided with a second heat dissipation fin 603. The second heat dissipation fin 603 and the first heat dissipation fin 303 of the heat dissipation frame 3 form a continuous heat dissipation path.

[0040] The rear end of the heat dissipation frame 3 is provided with an air outlet 304, and a dustproof net 8 is installed at the air outlet 304.

[0041] The cooling fan 1 is fixed at the air inlet 302, driving cool air to flow in from the air inlet 302. After heat exchange with the first cooling fin 303 of the heat dissipation frame 3 and the second cooling fin 603 of the air duct cover plate 6, the air is discharged from the air outlet 304. The first cooling fin 303 is located inside the air duct of the heat dissipation frame 3, mainly used to improve the heat exchange efficiency between the airflow inside the air duct and the metal frame. Its distribution direction is consistent with the airflow direction in the air duct, extending longitudinally along the heat dissipation frame. The second cooling fin 603 is located on the lower surface of the air duct cover plate 6, connected to the upper surface of the air duct cover plate 6 through the second thermally conductive contact surface 601 and the third thermally conductive contact surface 602, conducting heat from the upper part of the cover plate to the interior of the air duct. Its distribution direction is perpendicular to the mounting surface of the air duct cover plate 6, intersecting with the airflow inside the air duct. The first heat dissipation fin 303 and the second heat dissipation fin 603 are arranged in a three-dimensional staggered pattern in space. This staggered layout can increase the heat dissipation surface area and guide the airflow to generate turbulence, thereby enhancing the thermal convection effect. The synergistic effect of the two allows the cold air to carry away the heat on the heat dissipation fins more efficiently when it flows in the air duct, thus meeting the high-power heat dissipation requirements of the drone.

[0042] The first thermally conductive contact surface 301 of the heat dissipation frame 3 can directly contact the heat-generating components. During drone operation, the components generate a large amount of heat. Thanks to its excellent thermal conductivity, the heat is conducted through the first thermally conductive contact surface 301 and further transferred into the air duct by the metal material properties of the heat dissipation frame and the structure of the heat dissipation fins. In the air duct, the flowing cool air exchanges heat with this heat, ultimately expelling the heat from the drone body, thus constructing a complete and efficient heat dissipation path. For example, for components with high heat generation, such as the drone's main control chip, the first thermally conductive contact surface 301 can quickly dissipate the heat generated by the chip, preventing the chip from degrading in performance or being damaged due to excessive temperature.

[0043] In the above scheme, the heat dissipation frame 3 can be made of metal (such as aluminum alloy), whose high thermal conductivity can quickly absorb and conduct the heat generated by the internal components of the UAV to the heat dissipation structure. The main body of the heat dissipation duct serves as the core heat dissipation area, with the first heat dissipation fins 303 evenly distributed along the duct direction on its inner wall. By increasing the contact area with the airflow, thermal convection can be enhanced. The peripheral mounting platform not only fixes the components but also serves as a heat conduction path to conduct the heat from the components to the main body of the heat dissipation duct, avoiding local overheating. From the perspective of the heat dissipation path of the entire heat dissipation system, heat is transferred to the main body of the duct through the thermally conductive plane of the metal frame, and then exchanged with the airflow through the fins, forming a complete heat dissipation chain of "components → frame → fins → airflow".

[0044] Meanwhile, the top of the heat dissipation frame 3 is pressed against the upper cover of the chassis via the first sealing gasket 2, and the bottom is pressed against the chassis structure via the second sealing gasket 4, forming a sealed heat dissipation cavity that can isolate external moisture. The air inlet sealing gasket 5 and the air duct sealing gasket 7 further prevent water from seeping into the internal hardware area from the air duct interface or cover gaps. The sealed cavity only allows airflow to circulate through a specific channel (air inlet 302 → air duct → air outlet 304), which not only achieves physical isolation between the hardware and the external environment, but also ensures the openness of the heat dissipation air duct and unobstructed airflow.

[0045] Meanwhile, the cooling fan 1 is fixed at the air inlet 302, forcibly driving cool air from the air inlet into the main body of the air duct. The first heat dissipation fins 303 (inner wall of the frame) are arranged parallel to the airflow direction to reduce wind resistance and guide the airflow to flow efficiently. The second heat dissipation fins 603 (located on the lower surface of the air duct cover plate 6) are perpendicular to the airflow direction and are staggered with the first fins, which can increase the turbulence effect and further improve the heat exchange efficiency.

[0046] When cold air flows over the heat dissipation fins, forced convection carries away the heat from the fin surface, and the air is finally discharged from the outlet 304. The second thermally conductive contact surface 601 and the third thermally conductive contact surface 602 of the air duct cover 6 directly contact the heat-generating element (such as a motor or battery), which can conduct heat to the second fin 603 below the cover, forming a continuous heat dissipation path with the first fin 303 in the frame, realizing the rapid transfer of heat from the element to the airflow. The dust filter 8 is installed at the outlet 304 to prevent foreign objects (such as dust and debris) from entering the air duct and avoid a decrease in heat dissipation efficiency due to blockage.

[0047] Based on the technical solutions described above, some more specific technical solutions are provided below, which will be elaborated on separately.

[0048] In the optional embodiment, the first sealing gasket 2, the second sealing gasket 4, the air inlet sealing gasket 5, and the air duct sealing gasket 7 are all planar compression structures, and the material is rubber or foam.

[0049] In this embodiment, the first sealing gasket 2, the second sealing gasket 4, the air inlet sealing gasket 5, and the air duct sealing gasket 7 all adopt a planar compression structure. Compared with the traditional O-ring sealing method, this structure can omit complex sealing grooves and waterproof ribs, thereby greatly reducing the difficulty of manufacturing and installation, and reducing production processes and costs. Specifically, the planar compression structure achieves sealing by the compression force between the planes. When the heat dissipation frame 3 is fitted with the upper cover of the fuselage, the fuselage structure, the air duct interface, and the air duct cover, the sealing gaskets only need to be placed between the corresponding planes, and an effective seal can be formed by compression. When the heat dissipation frame 3 is fitted with the upper cover of the fuselage, the first sealing gasket 2 is compressed between the two, which can effectively prevent external water from entering the heat dissipation frame 3; similarly, the second sealing gasket 4 can prevent external water intrusion when the heat dissipation frame 3 is fitted with the fuselage structure. This structure can also ensure the reliability of the seal. During the flight of the UAV, even if subjected to external forces such as vibration and impact, the planar compression sealing method can maintain a good sealing state and avoid water leakage due to loosening of the sealing structure.

[0050] Both rubber and foam possess excellent elasticity. When the sealing gaskets are subjected to planar pressure, they can elastically deform, tightly adhering to the sealing surface and filling tiny gaps to effectively prevent water penetration. Simultaneously, both rubber and foam exhibit a degree of water resistance, preventing them from easily becoming wet or damaged upon contact with moisture, thus maintaining their sealing performance over a long period. When flying drones in rainy weather or using them in humid environments, these sealing gaskets effectively resist external moisture erosion. Rubber and foam also provide cushioning; when the drone is subjected to vibration, they not only act as a sealant but also reduce the transmission of vibration between components, protecting internal parts.

[0051] Meanwhile, although these four types of sealing gaskets (first sealing gasket 2, second sealing gasket 4, air inlet sealing gasket 5, and air duct sealing gasket 7) are located in different positions, they form a complete waterproof system through the combined effect of a planar compression structure and rubber or foam material. Specifically, first sealing gasket 2 and second sealing gasket 4 can prevent external water from entering the heat dissipation frame as a whole; air inlet sealing gasket 5 can prevent water drawn in from the air duct from entering the internal structure; and air duct sealing gasket 7 can prevent water seepage from the heat dissipation air duct from causing hardware short circuits. Their coordinated action ensures that the heat dissipation system effectively protects the internal hardware of the drone from water damage while fulfilling its heat dissipation function, thus guaranteeing the stable operation of the drone.

[0052] In an optional embodiment, the lower surface of the heat dissipation frame 3 is provided with a heat-conducting plane, which is used to fix the internal components of the UAV and conduct heat to the heat dissipation duct body.

[0053] In this embodiment, a heat-conducting plane is provided on the lower surface of the heat dissipation frame 3. On the one hand, it can provide a stable mounting base for the internal components of the drone, ensuring that each component remains stable during the operation of the drone. On the other hand, it can serve as a key bridge for heat conduction, quickly and efficiently conducting the heat generated by the components to the main body of the heat dissipation duct, thereby achieving heat dissipation.

[0054] As mentioned in the first point above, the heat-conducting surface provides a flat and suitable mounting surface for components. Components can be securely fixed to the heat sink frame 3 using methods such as screw fastening or clip-on connections. This fixing method ensures the stability of the components while also guaranteeing close contact between the components and the heat-conducting surface, creating favorable conditions for heat conduction.

[0055] Regarding the second point mentioned earlier, when the internal components of a drone generate heat, the heat is first transferred to the heat-conducting surface in close contact with it. Because the heat-conducting surface is made of a material with good thermal conductivity, it can quickly absorb this heat and, thanks to its material properties, rapidly conduct it to the main body of the heat dissipation duct. In this process, the efficiency of heat transfer is affected by factors such as the thermal conductivity of the heat-conducting surface material, the contact area with the components, and the tightness of the contact. Typically, heat-conducting surfaces are made of materials with high thermal conductivity, such as aluminum alloys, to reduce thermal resistance and accelerate heat conduction. Furthermore, to further improve heat conduction efficiency, thermal interface materials such as thermal grease or thermal gel may be added between the heat-conducting surface and the components. These materials can fill tiny gaps, reducing the thermal resistance of media such as air, allowing heat to be conducted more smoothly from the components to the heat-conducting surface, and then from the heat-conducting surface to the main body of the heat dissipation duct.

[0056] Thus, on the one hand, the heat-conducting plane can promptly dissipate the heat generated by the components, preventing heat from accumulating around the components, effectively reducing the operating temperature of the components, improving the performance and stability of the components, and extending their service life; on the other hand, after the heat is conducted to the main body of the heat dissipation duct, the cooling fan 1 can drive the cold air to flow through the first heat dissipation fin 303 and the second heat dissipation fin 603 to achieve heat exchange and dissipate heat, completing the entire heat dissipation cycle.

[0057] In an optional embodiment, the thermally conductive contact surface 601 of the air duct cover 6 and the second heat dissipation fin 603 are integrally formed metal structures.

[0058] The one-piece molding process used in this embodiment eliminates the seams between the thermally conductive contact surface 601 and the second heat dissipation fin 603, forming a complete and continuous component. This seamless structure avoids the thermal resistance problems caused by gaps in traditional splicing methods. In traditional structures, heat transfer is hindered when encountering seams, leading to reduced heat dissipation efficiency. The one-piece molding design provides a smooth and unobstructed heat dissipation path, significantly improving the efficiency of heat transfer from the thermally conductive contact surface 601 to the second heat dissipation fin 603.

[0059] Meanwhile, in this embodiment, the integrally formed structural material can be a metal material, which can quickly absorb and conduct heat. For example, aluminum alloy has a high thermal conductivity. When the heat-conducting contact surface 601 comes into contact with the heat-generating element of the drone, it can quickly absorb the heat and then quickly transfer it to the second heat dissipation fin 603, so that the heat can be efficiently transferred in the heat dissipation system and dissipated in time.

[0060] In the entire heat dissipation system, the thermally conductive contact surface 601 is responsible for close contact with the heat-generating components of the drone to collect heat, while the second heat dissipation fin 603 dissipates the absorbed heat into the surrounding air by increasing the heat dissipation area. As a single, integrally formed metal structure, the two work closely together to efficiently complete the process from heat collection to dissipation. Together with the heat dissipation frame 3 and the cooling fan 1, they form a complete heat dissipation system. When the cooling fan 1 drives cool air in through the air inlet, the thermally conductive contact surface 601 and the second heat dissipation fin 603 transfer heat to the cool air, which then carries the heat out through the air outlet, achieving continuous heat dissipation and ensuring that the internal temperature of the drone remains within a reasonable range, guaranteeing stable operation of the drone.

[0061] In an optional embodiment, the first heat dissipation fins 303 of the heat dissipation frame 3 are arranged perpendicular to the inner wall of the air duct, and the first heat dissipation fins 303 and the second heat dissipation fins 603 of the air duct cover plate 6 are spatially staggered to increase the heat dissipation area.

[0062] In this embodiment, the first heat dissipation fins 303 of the heat dissipation frame 3 are arranged perpendicular to the inner wall of the air duct. This arrangement allows the heat dissipation fins to maximize contact with the cold air flowing within the air duct. From the perspective of heat transfer principles, the larger the contact area, the higher the heat exchange efficiency. When cold air flows within the air duct, the vertically arranged first heat dissipation fins 303 act like barriers, forcing the cold air to fully contact the fin surface. This not only increases the contact area between the cold air and the heat dissipation fins but also prolongs the residence time of the cold air between the fins, allowing heat to be transferred more fully from the heat dissipation fins to the air, thereby effectively improving heat dissipation efficiency.

[0063] Meanwhile, the first heat dissipation fin 303 and the second heat dissipation fin 603 are staggered, further expanding the heat dissipation area. Within a limited space, the staggered distribution avoids parallel overlap of the heat dissipation fins, allowing them to be more evenly distributed within the airflow channel. This layout increases the total surface area of ​​the heat dissipation fins, allowing more heat to be dissipated into the surrounding air. For example, when cold air flows through the staggered heat dissipation fins, the airflow path is disrupted, forming a more complex flow pattern, allowing the air to contact more fin surfaces, thereby carrying away more heat.

[0064] The three-dimensional staggered spatial distribution of the first and second heat dissipation fins 303 further promotes turbulence in the airflow within the duct. Compared to laminar flow, turbulence has stronger mixing capabilities and a higher heat transfer coefficient. In laminar flow, air molecules move relatively regularly, and a thermal boundary layer easily forms near the surface of the heat dissipation fins, hindering further heat transfer. Turbulence, however, disrupts this thermal boundary layer, allowing cool air to continuously wash over the surface of the heat dissipation fins, maintaining a higher temperature gradient and accelerating heat dissipation. Furthermore, turbulence allows heat to be distributed more evenly in the air, preventing localized heat accumulation and further improving the uniformity and efficiency of heat dissipation.

[0065] From the perspective of heat dissipation of the entire drone system, the heat sink fins work in conjunction with components such as the heat dissipation frame 3, the air duct cover 6, and the cooling fan 1 to achieve efficient heat dissipation for the drone. By increasing the heat dissipation area and enhancing heat exchange efficiency, the heat generated by the internal components of the drone can be quickly removed, preventing excessive temperature from causing performance degradation or damage to the components.

[0066] In an optional embodiment, the first heat dissipation fin 303 is located on the inner wall of the heat dissipation duct body, and the second heat dissipation fin 603 is located above the heat dissipation duct body. The two are distributed in a vertical layer, and the projections of the first heat dissipation fin 303 and the second heat dissipation fin 603 partially overlap on the horizontal plane.

[0067] In this embodiment, the first heat dissipation fin 303 is located on the inner wall of the main body of the heat dissipation duct. The inner wall of the duct is the direct contact area for airflow. When the cold air drawn in by the cooling fan flows within the duct, the first heat dissipation fin 303 can quickly transfer the heat it carries to the flowing cold air. By utilizing air convection heat transfer, the heat is efficiently carried out of the heat dissipation system. This arrangement utilizes the airflow characteristics within the duct, allowing heat to be quickly removed. The second heat dissipation fin 603 is located above the main body of the heat dissipation duct. Its position allows it to utilize the principle of rising hot air. During the rising process, the hot air comes into contact with the second heat dissipation fin, transferring heat to the fin. Heat dissipation is then achieved through natural convection or mixed convection with the cold air within the duct.

[0068] The two layers are arranged vertically, one above the other, which further increases the heat dissipation area and enhances the heat dissipation effect. Furthermore, their projections overlap on the horizontal plane, meaning that the two layers of heat dissipation fins can work together at the same horizontal position to conduct and dissipate heat more fully in that area, avoiding heat dissipation dead zones and allowing heat to be discharged from the heat dissipation system more evenly and efficiently, ensuring that the internal components of the drone operate in a suitable temperature environment.

[0069] In summary, the technical solution of this utility model has the following technical effects:

[0070] 1. In one embodiment of the technical solution of this application, the heat dissipation frame is made of metal to improve thermal conductivity. The heat-conducting contact surface of the air duct cover and the heat dissipation frame and the heat dissipation fins are made of integrated molding process, which can shorten the heat transfer path, reduce thermal resistance, and achieve a compact heat dissipation layout.

[0071] 2. In one embodiment of this application, a waterproof barrier is constructed using sealing gaskets. Specifically, the sealing structure between the heat dissipation frame and the upper and lower surfaces of the casing isolates external moisture, the air inlet sealing gasket blocks the water inlet path of the air duct, and the air duct cover sealing gasket prevents internal moisture from seeping out. The heat dissipation air duct maintains airflow with the outside environment while completely isolating the working environment of the heat-generating components from the outside.

[0072] 3. In one embodiment of the technical solution of this application, a planar compression sealing structure is used to replace the traditional O-ring seal. Waterproofing is achieved through the planar contact between the metal frame and the sealing gasket (rubber / foam material), which eliminates the complex sealing groove design, reduces the processing difficulty and assembly cost, and ensures the sealing reliability under dynamic environment.

[0073] 4. In one embodiment of the technical solution of this application, a cooling fan is configured to drive air circulation. Through the forced convection heat exchange between the heat dissipation fins and the flowing air, the heat dissipation efficiency can be significantly improved compared with the traditional passive heat dissipation method relying on the drone shell, which can meet the heat dissipation requirements of high-power components.

[0074] 5. In one embodiment of the technical solution of this application, the heat dissipation frame has the dual functions of heat dissipation and structural support. Its peripheral platform directly serves as the mounting carrier for internal components, reducing independent support structures and realizing modular integrated design, thereby reducing system weight and volume while ensuring heat dissipation performance.

[0075] It should be noted that the above-mentioned technical effects do not require that each embodiment of the technical solution achieve the above-mentioned technical effects simultaneously.

[0076] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A heat dissipation system for an unmanned aerial vehicle (UAV), characterized in that, It includes a heat dissipation frame (3), an air duct cover (6), a cooling fan (1), and a dust filter (8); among which, The heat dissipation frame (3) is made of metal and consists of a heat dissipation duct body and an outer mounting platform. The heat dissipation duct body coincides with the duct cover plate (6), and its inner wall is evenly distributed with first heat dissipation fins (303) along the duct direction. The outer mounting platform is used to fix the internal components of the UAV and conduct heat to the heat dissipation duct body. The top of the heat dissipation frame (3) is sealed to the top cover of the drone body by the first sealing gasket (2), and the bottom is sealed to the body structure by the second sealing gasket (4), forming a closed heat dissipation cavity; The front end of the heat dissipation duct body is provided with an air inlet (302). The air inlet (302) is sealed with the air duct interface of the machine body by the air inlet sealing gasket (5) to prevent external moisture from seeping in. The air duct cover (6) is pressed and fixed to the top of the heat dissipation frame (3) by the air duct sealing gasket (7). The upper surface of the air duct cover (6) is provided with a second thermally conductive contact surface (601) and a third thermally conductive contact surface (602) that are in contact with the heat-generating elements of the UAV. The lower surface is provided with a second heat dissipation fin (603). The second heat dissipation fin (603) and the first heat dissipation fin (303) of the heat dissipation frame (3) form a continuous heat dissipation path. The heat dissipation frame (3) has an air outlet (304) at its rear end, and a dustproof net (8) is installed at the air outlet (304); The cooling fan (1) is fixed at the air inlet (302) and drives cold air to flow in from the air inlet (302). After heat exchange with the first heat dissipation fin (303) of the heat dissipation frame (3) and the second heat dissipation fin (603) of the air duct cover (6), it is discharged from the air outlet (304).

2. The heat dissipation system for the UAV according to claim 1, characterized in that, The first sealing gasket (2), the second sealing gasket (4), the air inlet sealing gasket (5), and the air duct sealing gasket (7) are all planar compression structures, and the material is rubber or foam.

3. The heat dissipation system for the UAV according to claim 1, characterized in that, The lower surface of the heat dissipation frame (3) is provided with a heat-conducting plane, which is used to fix the internal components of the UAV and conduct heat to the heat dissipation duct body.

4. The heat dissipation system for the UAV according to claim 1, characterized in that, The heat-conducting contact surface (601) of the air duct cover (6) and the second heat dissipation fin (603) are integrally formed metal structures.

5. The heat dissipation system for the UAV according to claim 1, characterized in that, The first heat dissipation fins (303) of the heat dissipation frame (3) are arranged perpendicular to the inner wall of the air duct. The first heat dissipation fins (303) and the second heat dissipation fins (603) of the air duct cover plate (6) are arranged in a three-dimensional staggered distribution in space to increase the heat dissipation area.

6. The heat dissipation system for the UAV according to claim 1, characterized in that, The first heat dissipation fin (303) is located on the inner wall of the heat dissipation duct body, and the second heat dissipation fin (603) is located above the heat dissipation duct body. The two are distributed in a vertical direction, and the projections of the first heat dissipation fin (303) and the second heat dissipation fin (603) partially overlap on the horizontal plane.

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