General cooling device for external task load of rotor unmanned aerial vehicle

Abstract

The application belongs to the technical field of rotor unmanned aerial vehicle heat dissipation, and discloses a general heat dissipation device for rotor unmanned aerial vehicle external task load, the fuselage of the rotor unmanned aerial vehicle is connected with a rotor through a support arm, and the general heat dissipation device comprises a load heat conduction plate and a phase change temperature equalization network; the load heat conduction plate is arranged between the task load and the fuselage of the rotor unmanned aerial vehicle; the phase change temperature equalization network comprises a heat pipe and a heat dissipation fin; the heat pipe comprises a zigzag heat pipe, one end of the zigzag heat pipe is a zigzag heat pipe evaporation section, the zigzag heat pipe evaporation section is connected with the load heat conduction plate, the other end of the zigzag heat pipe is a zigzag heat pipe condensation section, the zigzag heat pipe condensation section extends along the support arm to the rotor direction and is fixed to the lower side of the rotor, the heat dissipation fin is arranged on the outer side of the zigzag heat pipe condensation section, a plurality of zigzag heat pipes and heat dissipation fins form a radial phase change temperature equalization network; the heat generated by the task load is conducted to the zigzag heat pipe evaporation section through the load heat conduction plate, then is conducted to the zigzag heat pipe condensation section, and finally is radiated through the heat dissipation fin under the action of the wind field generated by the rotor.

Description

Technical Field

[0001] This invention belongs to the field of heat dissipation technology for rotary-wing unmanned aerial vehicles (UAVs), and mainly relates to a general heat dissipation device for external mission payloads of rotary-wing UAVs. Background Technology

[0002] With the rapid iteration and development of drone technology, it has been widely applied in various fields, driving the rapid growth of the drone market. Drones are increasingly used in agriculture, logistics, security, surveying, and emergency rescue, especially in the field of rotary-wing drones, where their flexibility and maneuverability make them the mainstay of the small and medium-sized drone market. As drone application scenarios continue to expand, the demand for external mission payloads is also increasing, such as high-resolution cameras, thermal imaging equipment, and radar. These devices generate a lot of heat during operation, and small drones themselves typically lack active cooling resources, often resulting in limited performance of external devices and even affecting mission stability and reliability due to overheating.

[0003] Currently, most small and medium-sized drones on the market rely primarily on passive cooling methods such as natural heat dissipation for their external devices, which cannot provide effective cooling support. This limitation severely restricts the application of drones in high-temperature environments and the improvement of their power output.

[0004] Therefore, there is an urgent need to design a universal heat dissipation device suitable for external mission payloads, providing a flexible and efficient heat dissipation platform for various high-power external devices on drones. Summary of the Invention

[0005] To address the problems in the prior art, this invention proposes a universal heat dissipation device for external mission payloads of rotary-wing UAVs. The top or bottom of the rotary-wing UAV is used as the mounting surface for the external mission payload. Heat is transferred from the mission payload to the underside of the rotor through a load heat transfer plate and a phase change heat equalization network. The high-speed vertical wind field generated by the rotor's rotation enables efficient forced convection heat dissipation through the phase change heat transfer network, thus removing the heat generated by the mission payload.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solution:

[0007] A universal heat dissipation device for an external mission payload of a rotary-wing unmanned aerial vehicle (UAV) is disclosed. The UAV's fuselage is connected to the rotor via a support arm. The device includes a payload heat transfer plate and a phase change heat equalization network. The payload heat transfer plate is disposed between the mission payload and the UAV's fuselage. The phase change heat equalization network includes heat pipes and heat dissipation fins. The heat pipes include zigzag heat pipes, one end of which is a zigzag heat pipe evaporation section connected to the payload heat transfer plate, and the other end is a zigzag heat pipe condensation section extending along the support arm towards the rotor and fixed to the underside of the rotor. The heat dissipation fins are disposed outside the zigzag heat pipe condensation section. Multiple zigzag heat pipes and heat dissipation fins form a radial phase change heat equalization network. The heat generated by the mission payload is conducted through the payload heat transfer plate to the zigzag heat pipe evaporation section, then to the zigzag heat pipe condensation section, and finally dissipated through the heat dissipation fins under the action of the wind field generated by the rotor.

[0008] Furthermore, the load heat transfer plate is a metal heat-conducting plate.

[0009] Furthermore, the load heat transfer plate is a VC heat exchange plate, which includes a VC heat exchange plate evaporation section and a VC heat exchange plate condensation section. The heat generated by the task load is conducted through the VC heat exchange plate evaporation section to the VC heat exchange plate condensation section, and then to the zigzag heat pipe evaporation section.

[0010] Furthermore, the zigzag heat pipe is adjustablely positioned on the underside of the rotor via a heat pipe fixing assembly.

[0011] Furthermore, the heat pipe fixing assembly includes a clamp, a rubber sleeve, a height adjustment pad, and a fixing bolt. The height adjustment pad is located at the bottom of the rotor. The rubber sleeve is fitted onto the zigzag heat pipe, and a clamp is installed on the rubber sleeve. The clamp is connected to the height adjustment pad through the fixing bolt.

[0012] Furthermore, the heat pipe also includes an annular heat pipe, which is connected to the zigzag heat pipe via an interconnecting fixing block. The heat dissipation fins are disposed on the annular heat pipe, and the annular heat pipe and the heat dissipation fins form an annular phase change homogenization network.

[0013] Furthermore, the annular heat pipe includes an evaporation section and a condensation section. The connection point between the annular heat pipe and the interconnecting fixing block is the evaporation section, and the space between two evaporation sections is the condensation section. The heat dissipation fins are disposed at the condensation section.

[0014] Furthermore, the interconnecting fixing block is made of metal.

[0015] Furthermore, an interface plate is provided between the load heat transfer plate and the task load, and the interface plate is coated with an interface material for reducing contact thermal resistance.

[0016] Furthermore, the load heat transfer plate and the mission load are located on the top or bottom of the rotorcraft UAV.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. This invention is beneficial to significantly improve the heat dissipation capacity of external mission loads. It utilizes a phase change heat transfer network to rapidly spread heat under the rotor, achieving efficient heat dissipation to the environment. Furthermore, the phase change heat distribution network and fins are closely attached to the rotor and located in a high wind speed zone, which can significantly improve the convective heat transfer coefficient and effectively enhance the overall heat dissipation capacity.

[0019] 2. This invention is conducive to achieving a lightweight and miniaturized design of the entire UAV platform. The phase change temperature equalization network is closely attached to the lower side of the rotor and has almost no impact on the shape envelope of the UAV, thus achieving a lightweight and miniaturized system.

[0020] 3. This invention helps improve the reliability of the temperature control system. It has no active cooling components, and the heat dissipation is efficient and reliable. As long as the UAV is flying normally, it can ensure a stable heat dissipation airflow. There is no possibility that the system will overheat and affect the mission execution due to the failure of active thermal control components.

[0021] 4. This invention helps reduce the power supply requirements of the temperature control system. There are no active cooling components, the system is designed for completely passive heat dissipation, and there are no power supply requirements. The power supply of the system can be used entirely for the flight platform and mission system.

[0022] 5. This invention enables multi-platform compatibility and improves economy. By adjusting the sliding position between the installation transition component and the heat pipe and the variety and quantity of adjustment pads according to the size of the UAV, it can be adapted to multiple UAV platforms, which helps to reduce the number of supporting equipment varieties.

[0023] 6. This invention can improve the efficiency of mission payload changeover, adapt to multiple mission payloads, and eliminate the need to redeploy heat dissipation devices when changing payloads, which is conducive to achieving efficient mission payload changeover between different missions and improving work efficiency. Attached Figure Description

[0024] Figure 1 This is an exploded view illustrating the installation process of Embodiment 1 of the present invention.

[0025] Figure 2 This is a schematic diagram illustrating the heat transfer and heat dissipation principle of Embodiment 1 of the present invention.

[0026] Figure 3 This is a schematic diagram of the installation and fixing of the phase change heat transfer network according to Embodiment 1 of the present invention.

[0027] Figure 4 This is a detailed installation diagram of the phase change heat transfer network according to Embodiment 1 of the present invention.

[0028] Figure 5 This is a schematic diagram of the load heat transfer plate and the task load installation in Embodiment 1 of the present invention.

[0029] Figure 6 This is an installation diagram of Embodiment 2 of the present invention.

[0030] Figure 7 This is a partial installation diagram of Embodiment 2 of the present invention.

[0031] Figure 8 This is an installation illustration of Embodiment 3 of the present invention.

[0032] in:

[0033] 1. Rotary-wing unmanned aerial vehicle (UAV) platform;

[0034] 2. Mission payload;

[0035] 3. Phase change heat transfer network;

[0036] 4. Interface panel;

[0037] 5. Load-bearing heat transfer plate;

[0038] 6. Heat pipe; 6-1. Zigzag heat pipe; 6-2. Annular heat pipe;

[0039] 7. Heat dissipation fins;

[0040] 8. Clamps;

[0041] 9. Rubber sleeve;

[0042] 10. Height adjustment pads;

[0043] 11. Fixing bolts;

[0044] 12. Load heat transfer plate mounting and fixing groove;

[0045] 13. Fixed points for mission load;

[0046] 14. Interconnected fixed blocks. Detailed Implementation

[0047] To better illustrate the present invention, the implementation process of the present invention will be described in detail below with reference to the accompanying drawings.

[0048] Example 1

[0049] like Figures 1-5 As shown, this is a general heat dissipation device for external mission payload of a rotary-wing UAV. The rotary-wing UAV 1 is an arbitrary type of multi-rotor UAV, also known as a multi-rotor UAV platform. Multi-rotors usually include three or more rotors. The rotors are connected to the fuselage of the rotary-wing UAV 1 through the support arms. The mission payload 4 is the external device of the rotary-wing UAV 1, which can be a high-resolution camera, thermal imaging equipment or radar, etc.

[0050] This embodiment uses a quadcopter drone as an example for specific explanation.

[0051] A general-purpose heat dissipation device for external mission payloads of rotary-wing unmanned aerial vehicles includes a payload heat transfer plate 5, an interface plate 4, and a phase change heat equalization network.

[0052] The mission payload 4 is suspended at the bottom of the rotorcraft drone 1. The load heat transfer plate 5 is made of a metal plate with good thermal conductivity, such as a copper plate or an aluminum plate, and is installed at the bottom of the rotorcraft drone 1. Structurally, it serves as an installation transition piece between the mission payload 4 and the rotorcraft drone 1. Functionally, it serves as a heat sink plate for the mission payload 4, playing the role of collecting and conducting the heat generated by the mission payload 4.

[0053] The load heat transfer plate 5 is provided with a plurality of recessed fixing slots 12 and task load fixing points 13 for installing different task loads 4. The task load fixing points 13 are distributed around the load heat transfer plate 5, and the recessed fixing slots 12 can be used to flexibly adjust the spacing between the fixing points to facilitate adaptation to different UAV platforms.

[0054] The interface plate 4 is coated with an interface material, such as thermally conductive gel, and is placed between the task load 4 and the load heat transfer plate 5 to reduce the contact thermal resistance between the two.

[0055] The phase change heat exchanger network includes heat pipes 6 for heat transfer and heat dissipation fins 7 for heat dissipation. The heat pipes 6 are zigzag heat pipes 6-1, and multiple heat pipes are arranged. One end of each heat pipe 6 is connected to the load heat transfer plate 5, and the other end extends along the support arm towards the rotor. It is adjustablely set on the lower side of the rotor by a heat pipe fixing assembly. The bending position of the zigzag heat pipe 6-1 is set according to the shape of the support arm. The heat dissipation fins 7 are arranged on the heat pipes 6. Small tooth height fins are selected to avoid the fins being too high, so that the cooling airflow cannot effectively enter the space between the teeth for heat dissipation under the condition of wind field changes. The tooth shape can be circular, rectangular, sawtooth, etc.

[0056] The zigzag heat pipe 6-1 and the heat dissipation fins 7 form a radial phase change temperature uniformity network, that is, with the load heat transfer plate 5 as the center, the zigzag heat pipe 6-1 and the heat dissipation fins 7 extend radially to the surrounding areas to dissipate heat.

[0057] It should be noted that the heat pipe 6 can be made using existing heat pipes. The inside of the heat pipe is filled with a low-boiling-point, volatile working liquid, and a liquid-absorbing core is provided on the pipe wall. The capillary is formed by a capillary porous material. The heat pipe 6 includes an evaporation section and a condensation section. The evaporation section is located inside the load heat transfer plate 5, while the condensation section is located on the lower side of the support arm and rotor. The heat dissipation fins 7 are located on the outer side of the condensation section. The heat generated by the task load 4 is transferred from the load heat transfer plate 5 to the evaporation section of the heat pipe 6. The working liquid in the capillary inside the pipe is heated and rapidly vaporizes. The vapor flows to the condensation section under the power of thermal diffusion, releases latent heat and becomes liquid, and then flows back to the evaporation section along the capillary porous material. The heat dissipation fins 7 absorb the latent heat and release it to the environment, thus completing the heat dissipation.

[0058] The load heat transfer plate 5 can be made of a metal plate with good thermal conductivity or an existing VC heat exchange plate. The evaporation section of the heat pipe 6 is embedded in the VC heat exchange plate to ensure good contact and facilitate heat transfer. The VC heat exchange plate is a vacuum cavity with a microstructure on the inner wall and is plate-shaped. When heat is conducted from the task load 4 to the evaporation area of ​​the VC heat exchange plate, the coolant in the cavity is heated and vaporized, absorbs heat energy and expands rapidly to fill the cavity until it contacts the heat pipe 6. Upon contact with the condenser, it condenses and releases heat, thereby transferring heat to the evaporation section of the heat pipe 6. The gas in the VC heat exchange plate condenses into liquid and flows back to the heat source through the capillary structure for the next cycle.

[0059] The heat pipe fixing assembly includes a clamp 8, a rubber sleeve 9, a height adjustment pad 10, and a fixing bolt 11. The height adjustment pad 10 is located at the bottom of the rotor. The rubber sleeve 9 is fitted onto the zigzag heat pipe 6-1, and the clamp 8 is installed on the rubber sleeve 9. The clamp 8 is connected to the height adjustment pad 10 by the fixing bolt 11. Figure 3 , 4 As shown, the fixed position of the zigzag heat pipe 6-1 can be adjusted along the direction of the arrow, and the height can be adjusted by changing the height of the height adjustment pad 10, which can realize two degrees of freedom to adapt to different situations.

[0060] like Figure 2 As shown, the heat transfer and heat dissipation process in this embodiment is as follows: Under the combined action of the load heat transfer plate 5 and the phase change temperature equalization network, the heat generated by the mission load 4 is transferred by the load heat transfer plate 5 and spreads outward. The heat is introduced into the lower side of the rotor along the heat pipe 6, as shown by the direction of the dashed arrow. Combined with the high-speed top-down wind field generated by the rotor during the operation of the rotor UAV 1, as shown by the solid arrow, the heat is carried away by the heat dissipation fins 7 through forced convection, and finally the heat dissipation of the mission load 4 is achieved.

[0061] Through the aforementioned universal heat dissipation device, the phase change temperature equalization network can achieve network coverage in the area below the rotor. The phase change temperature equalization network and heat dissipation fins occupy a very low ratio of the entire vertical projection area of ​​the rotor UAV 1, which does not affect the lift and maneuverability of the UAV. It can achieve efficient heat dissipation for external mission payload 4. At the same time, this universal heat dissipation device can be adapted to multiple platforms and multiple payloads, and can achieve rapid replacement of mission payload 4 according to different mission requirements.

[0062] Example 2

[0063] like Figures 6-7 As shown, compared with Embodiment 1, the difference is that the heat pipe 6 of the phase change heat exchanger network can also be a ring heat pipe 6-2, which is connected to the zigzag heat pipe 6-1 through the interconnecting fixing block 14. The interconnecting fixing block 14 is made of a metal with good thermal conductivity. The heat of the zigzag heat pipe 6-1 is transferred to the ring heat pipe 6-2 through the interconnecting fixing block 14. The part of the ring heat pipe 6-2 connected to the interconnecting fixing block 14 is the evaporation section of the ring heat pipe 6-2. The section between the two evaporation sections is the condensation section. The heat dissipation fins 7 are set at the condensation section of the ring heat pipe 6-2.

[0064] In other words, the annular heat pipe 6-2 and the heat dissipation fins 7 form an annular phase change temperature uniformity network, that is, the annular heat pipe 6-2 together with the heat dissipation fins 7 dissipates heat to the surrounding area with the load heat transfer plate 5 as the center.

[0065] The interconnected fixing block 14 enables the zigzag heat pipe 6-1 and the annular heat pipe 6-2 to be partially installed and conduct heat to each other, which greatly increases the heat dissipation area of ​​the phase change heat exchanger network and improves the overall heat dissipation capacity.

[0066] Example 3

[0067] like Figure 8 As shown, compared with Embodiment 1, the difference is that the mission payload 4 is installed and fixed on the top of the rotor drone 1. Correspondingly, the payload heat transfer plate 5 and the interface plate 4 are both installed on the top of the rotor drone 1. In order to avoid interference with the rotor, the zigzag heat pipe 6-1 of the phase change heat exchanger network extends down from the top of the rotor drone 1 and is fixed to the bottom of the rotor.

[0068] Finally, it should be noted that the above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. However, any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A universal heat dissipation device for external mission payload of a rotary-wing unmanned aerial vehicle (UAV), wherein the fuselage of the UAV (1) is connected to the rotor via a support arm, characterized in that, The system includes a load heat transfer plate (5) and a phase change heat equalization network. The load heat transfer plate (5) is set between the mission payload (4) and the fuselage of the rotor drone (1). The phase change heat equalization network includes heat pipes (6) and heat dissipation fins (7). The heat pipe (6) includes a zigzag heat pipe (6-1), one end of which is a zigzag heat pipe evaporation section connected to the load heat transfer plate (5), and the other end is a zigzag heat pipe condensation section, which extends along the support arm toward the rotor and is fixed to the underside of the rotor. The heat dissipation fins (7) are set outside the zigzag heat pipe condensation section. Multiple zigzag heat pipes (6-1) and heat dissipation fins (7) form a radial phase change heat equalization network. The heat generated by the mission payload (4) is conducted through the load heat transfer plate (5) to the zigzag heat pipe evaporation section, and then to the zigzag heat pipe condensation section. Finally, under the action of the wind field generated by the rotor, the heat is dissipated through the heat dissipation fins (7).

2. The universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, The load heat transfer plate (5) is a metal heat-conducting plate.

3. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, The load heat transfer plate (5) is a VC heat exchange plate, which includes a VC heat exchange plate evaporation section and a VC heat exchange plate condensation section. The heat generated by the task load (4) is conducted through the VC heat exchange plate evaporation section to the VC heat exchange plate condensation section, and then to the zigzag heat pipe evaporation section.

4. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, The zigzag heat pipe (6-1) is adjustablely mounted on the underside of the rotor via a heat pipe fixing assembly.

5. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 4, characterized in that, The heat pipe fixing assembly includes a clamp (8), a rubber sleeve (9), a height adjustment pad (10), and a fixing bolt (11). The height adjustment pad (10) is set at the bottom of the rotor. The rubber sleeve (9) is fitted on the zigzag heat pipe (6-1). The clamp (8) is set on the rubber sleeve (9). The clamp (8) is connected to the height adjustment pad (10) by the fixing bolt (11).

6. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, The heat pipe (6) also includes an annular heat pipe (6-2), which is connected to the zigzag heat pipe (6-1) through an interconnecting fixing block (14). The heat dissipation fins (7) are disposed on the annular heat pipe (6-2). The annular heat pipe (6-2) and the heat dissipation fins (7) form an annular phase change uniform temperature network.

7. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 6, characterized in that, The annular heat pipe (6-2) includes an annular heat pipe evaporation section and an annular heat pipe condensation section. The annular heat pipe evaporation section is where the interconnecting fixing block (14) is connected on the annular heat pipe (6-2). The annular heat pipe condensation section is between the two annular heat pipe evaporation sections. The heat dissipation fins (7) are located at the annular heat pipe condensation section.

8. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 6, characterized in that, The interconnecting fixing block (14) is made of metal.

9. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, An interface plate (4) is also provided between the load heat transfer plate (5) and the task load (4), and the interface plate (4) is coated with an interface material for reducing contact thermal resistance.

10. A universal heat dissipation device for external mission payloads of a rotary-wing unmanned aerial vehicle according to claim 1, characterized in that, The load heat transfer plate (5) and the mission payload (4) are located on the top or bottom of the rotary-wing UAV.

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