Composite wing inspection unmanned aerial vehicle with liquid cooling heat dissipation structure

Abstract

The invention relates to the field of liquid cooling unmanned aerial vehicles, in particular to a composite wing inspection unmanned aerial vehicle with a liquid cooling heat dissipation structure, which comprises a composite wing unmanned aerial vehicle, a flow divider fixedly mounted on the outer side surface of the bottom of the composite wing unmanned aerial vehicle, and a cooling liquid tank movably sleeved on the edges of the two sides of the composite wing unmanned aerial vehicle, a plurality of sets of heat absorption hollow aluminum plates are fixedly connected to the inner side wall face of the cooling liquid box, and the two ends of each heat absorption hollow aluminum plate extend to the upper side surface and the lower side surface of the cooling liquid box correspondingly. When the composite wing unmanned aerial vehicle flies at a high speed, cooling liquid after heat absorption enters a cooling liquid box, and when the cooling liquid after heat absorption makes contact with a heat absorption hollow aluminum plate, a heat source is guided into the heat absorption hollow aluminum plate through a heat conduction material of the heat absorption hollow aluminum plate; when the air flow flows on the surface of the bottom layer of the cooling liquid box and makes contact with the surfaces of the flow suction protruding strips, the air flow is guided by the flow suction protruding strips.

Description

Technical Field

[0001] The present invention belongs to the technical field of liquid-cooled UAVs, in particular to a composite-wing inspection UAV with a liquid-cooled heat dissipation structure. Background Art

[0002] A compound-wing UAV refers to a perfect combination of fixed-wing and rotary-wing UAVs; a compound-wing UAV has the advantages of both types of UAVs. Fixed-wing UAVs have fast flight speed, high flight altitude, and long flight time, while rotary-wing UAVs have the characteristics of vertical take-off and landing, hovering, and flexibility.

[0003] A patent with publication number CN119611828A discloses a hydrogen fuel cell drone with a liquid cooling and heat dissipation structure, comprising a drone fuselage, a hydrogen fuel cell system, a heat sink arm with an internal cavity, a liquid distribution main pipe, a first water pump, a liquid flow pipe, a liquid return pipe, a propeller, a flow equalization mechanism, and a liquid collection main pipe. The coolant, after absorbing heat, is evenly distributed to each liquid distribution branch pipe through the flow equalization mechanism through the liquid distribution main pipe. The coolant then flows into the liquid flow pipe and liquid return pipe in the heat sink arm for heat dissipation, making full use of the rotor wind for heat convection heat dissipation. The coolant then circulates to the hydrogen fuel cell system through the liquid collection main pipe. The entire process uses water cooling for heat dissipation. At the same time, the water-cooled radiator is combined with the drone frame, and the drone frame arm is used as a radiator. This can reduce weight by eliminating additional radiator structures, fully utilizing the rotor wind for heat convection, and eliminating the heat dissipation fan components, thereby reducing weight while ensuring heat dissipation effect.

[0004] In the current existing technology, the existing large-scale composite wing inspection drone needs to fly for a long time, and during the long flight, a large amount of high-temperature heat source will be generated inside the composite wing inspection drone. The high-temperature heat source will accelerate the battery consumption rate, thereby shortening the battery life. In order to avoid the battery loss rate being too fast, coolant will be used to dissipate heat inside the composite wing inspection drone. However, as the temperature inside the coolant continues to rise, the heat absorption efficiency of the coolant will decrease, and the natural cooling rate of the coolant is relatively slow, thus making it impossible to effectively absorb heat.

[0005] To this end, the present invention provides a composite wing inspection drone with a liquid cooling and heat dissipation structure. Summary of the Invention

[0006] In order to make up for the deficiencies of the prior art, at least one technical problem raised in the background technology is solved.

[0007] The technical solution adopted by the present invention to solve its technical problems is: the composite wing inspection drone with a liquid cooling and heat dissipation structure described in the present invention comprises a composite wing inspection drone and a diverter fixedly installed on the outer surface of the bottom of the composite wing drone, a coolant tank movably sleeved on the edge positions on both sides of the composite wing drone, a plurality of groups of heat-absorbing hollow aluminum plates are fixedly connected to the inner wall surface of the coolant tank, the two ends of the heat-absorbing hollow aluminum plates extend to the upper and lower surfaces of the coolant tank respectively, the top surface of the coolant tank is provided with a trapezoidal drainage strip at the edge position of the top side of the heat-absorbing hollow aluminum plate, the bottom surface of the heat-absorbing hollow aluminum plate is provided with a suction convex strip at the bottom edge position of the coolant tank, the inner wall surface of the coolant tank is provided with a V-shaped differentiation strip at the middle position of the two groups of heat-absorbing hollow aluminum plates, and the top outer surface of the coolant tank is provided with a clamping groove at the middle position.

[0008] Preferably, a gas diversion chute is provided on one side surface of the composite wing UAV, a diversion cavity is opened on the inner wall surface of the gas diversion chute, an L-shaped exhaust pipe is fixedly connected to the bottom surface of the composite wing UAV, and one end of the L-shaped exhaust pipe extends to the inner wall surface of the diversion cavity.

[0009] Preferably, a liquid cooling box is fixedly installed on the bottom surface of the composite wing UAV, a heat-absorbing aluminum plate is fixedly connected to the bottom surface of the liquid cooling box, and a heat dissipation plate is fixedly connected to the bottom surface of the heat-absorbing aluminum plate.

[0010] Preferably, the interior of the liquid cooling box and the coolant tank is filled with coolant, a sealing sleeve is fixedly connected to the inner wall surface of the guide cavity, and a limiting sleeve is movably sleeved on the inner wall surface of the sealing sleeve.

[0011] Preferably, two transmission rods are fixedly connected to the two side surfaces of the limiting sleeve, and two groups of transmission fan blades are fixedly connected to the outer surfaces of the two transmission rods. One group of transmission fan blades is positioned on the inner wall of the guide cavity, and the other group of transmission fan blades is positioned inside the liquid cooling box.

[0012] Preferably, support frames are provided on both side surfaces of the composite wing UAV, multiple sets of composite rotor wings are provided on the top surface of the support frame, swing arms are provided on both side surfaces of the support frame, one side surface of the swing arm is fixedly connected to the outer surface of one end of the coolant tank, and fixing plates are fixedly connected to both side surfaces of the support frame.

[0013] Preferably, an elastic buffer wire is fixedly connected to the bottom surface of the fixed plate, and the other end of the elastic buffer wire is fixedly connected to the top surface of the coolant tank, and an electric motor is provided on both side surfaces of the support frame, and a turbine push arm is fixedly connected to the output end of the electric motor, and the outer surface of the turbine push arm is movably overlapped with the outer surface of the coolant tank.

[0014] Preferably, multiple groups of circulation drainage tubes are fixedly installed on the output end of the diverter, the other end of one group of circulation drainage tubes extends to the inner wall of the coolant tank, and the two ends of another group of circulation drainage tubes are respectively fixedly connected to the outer surfaces of the coolant tank and the liquid cooling box.

[0015] The beneficial effects of the present invention are as follows:

[0016] 1. The composite wing inspection drone with a liquid cooling and heat dissipation structure described in the present invention has a cooling liquid after absorbing heat, which enters the interior of the cooling liquid tank. When the cooling liquid after absorbing heat contacts the heat-absorbing hollow aluminum plate, the heat source is drained into the interior of the heat-absorbing hollow aluminum plate by utilizing the heat-conducting material of the heat-absorbing hollow aluminum plate. When the composite wing drone flies at high speed, the external airflow will differentiate and flow from the upper and lower surfaces of the cooling liquid tank. When the airflow flows on the bottom surface of the cooling liquid tank and contacts the surface of the suction rib, the airflow is guided by the suction rib to quickly enter the interior of the heat-absorbing hollow aluminum plate, thereby quickly draining and discharging the heat source accumulated inside the heat-absorbing hollow aluminum plate, so that the inner wall surface of the heat-absorbing hollow aluminum plate is always kept in a low temperature state, thereby increasing the effect of rapid heat source interaction between the cooling liquid and the heat-absorbing hollow aluminum plate.

[0017] 2. The composite wing inspection drone with a liquid-cooled heat dissipation structure described in the present invention, when the airflow flows rapidly on the top surface of the composite wing drone, the gas flows upward on the surface of the trapezoidal guide strips under the guidance of the trapezoidal guide strips. When the gas flows at high speed, the flow path is changed, which accelerates the flow speed of the gas, thereby causing the bottom surface of the gas to generate a low-pressure state at the edge position of the trapezoidal guide strips. The gas in the low-pressure state will generate a large suction force. Since the low-pressure position is located at the top edge position of the heat-absorbing hollow aluminum plate, the low-pressure environment generates a large suction force on the interior of the heat-absorbing hollow aluminum plate, so that the gas inside the heat-absorbing hollow aluminum plate is quickly discharged. Under the mutual cooperation with the heat-absorbing hollow aluminum plate, the gas inside the heat-absorbing hollow aluminum plate is quickly discharged, and the heat dissipation effect of the coolant inside the coolant tank is accelerated.

[0018] 3. The composite wing inspection drone with a liquid cooling and heat dissipation structure described in the present invention, when the composite wing drone is flying quickly, uses the gas diversion chute on the surface of one side of the composite wing drone to change the path of the oncoming gas, so that the gas slides on the surface of the gas diversion chute, and at the same time, a part of the high-speed flowing gas will flow into the interior of the guide cavity, and under the guidance of the guide cavity and the L-shaped exhaust pipe, it will flow parallel to the bottom surface of the composite wing drone, and at the same time cooperate with the heat-absorbing aluminum plate and the heat dissipation plate to absorb the heat source inside the liquid cooling box and transmit the heat source. When the airflow under the parallel high-speed flow intersperses the surface of the heat dissipation plate, it takes away the heat source on the outer surface of the heat dissipation plate and the heat-absorbing aluminum plate, so that the surface of the heat-absorbing aluminum plate and the heat dissipation plate is always kept below the internal temperature of the liquid cooling box, so that the waste heat of the coolant inside the liquid cooling box can always be transferred to the heat source through the heat-absorbing aluminum plate and the heat dissipation plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described below with reference to the accompanying drawings.

[0020] Figure 1 It is a perspective view of the present invention;

[0021] Figure 2 This is a bottom-up perspective view of the composite wing UAV of the present invention;

[0022] Figure 3 is a cutaway perspective view of the coolant tank of the present invention;

[0023] Figure 4 It is a partial perspective view of the coolant tank in the present invention;

[0024] Figure 5 is a cutaway perspective view of the composite wing UAV of the present invention;

[0025] Figure 6 This is a partially cutaway perspective view of the composite wing UAV of the present invention;

[0026] Figure 7 is a sectional perspective view of the support frame of the present invention;

[0027] Figure 8 It is a three-dimensional diagram of the turbine propulsion arm in the present invention.

[0028] In the figure: 11, composite wing UAV; a1, gas drainage chute; a2, guide cavity; a3, L-shaped exhaust pipe; a4, liquid cooling box; a5, heat-absorbing aluminum plate; a6, heat dissipation plate; a7, sealing sleeve; a8, limit sleeve; a9, transmission rod; a10, transmission fan blade; 111, support frame; 112, swing arm; 113, composite propeller; 114, fixing plate; 115, elastic buffer wire; 116, electric motor; 117, turbine propeller arm; 12, diverter; 121, circulation drainage pipe; 13, coolant tank; 131, trapezoidal drainage strip; 132, heat-absorbing hollow aluminum plate; 133, suction convex strip; 134, V-shaped differentiation strip; 135, snap-in groove. DETAILED DESCRIPTION

[0029] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below in conjunction with specific implementation methods.

[0030] like Figures 1 to 4 As shown, a composite wing inspection drone with a liquid cooling and heat dissipation structure according to an embodiment of the present invention includes a composite wing drone 11 and a diverter 12 fixedly mounted on the outer surface of the bottom of the composite wing drone 11, a coolant tank 13 movably sleeved on the edge positions on both sides of the composite wing drone 11, and a plurality of groups of heat-absorbing hollow aluminum plates 132 are fixedly connected to the inner wall surface of the coolant tank 13, and the two ends of the heat-absorbing hollow aluminum plates 132 extend to the upper and lower surfaces of the coolant tank 13 respectively. A trapezoidal drainage strip 131 is provided on the top surface of the coolant tank 13 and located at the edge position of one side of the top of the heat-absorbing hollow aluminum plate 132, a suction convex strip 133 is provided on the bottom surface of the heat-absorbing hollow aluminum plate 132 and located at the bottom edge position of the coolant tank 13, a V-shaped differentiation strip 134 is provided on the inner wall surface of the coolant tank 13 and located in the middle position between the two groups of heat-absorbing hollow aluminum plates 132, and a clamping groove 135 is provided on the top outer surface of the coolant tank 13 and located in the middle position.

[0031] The coolant after absorbing heat will enter the interior of the coolant tank 13. When the coolant after absorbing heat contacts the heat-absorbing hollow aluminum plate 132, the heat source is guided into the interior of the heat-absorbing hollow aluminum plate 132 by the heat-conducting material of the heat-absorbing hollow aluminum plate 132. When the composite wing UAV 11 is flying at high speed, the external airflow will differentiate and flow from the upper and lower surfaces of the coolant tank 13. When the airflow flows on the bottom surface of the coolant tank 13, when it contacts the surface of the suction rib 133, the airflow is guided by the suction rib 133 to quickly enter the interior of the heat-absorbing hollow aluminum plate 132, and then the heat source accumulated inside the heat-absorbing hollow aluminum plate 132 is quickly drained and discharged, so that the inner wall surface of the heat-absorbing hollow aluminum plate 132 is always kept at a low temperature, thereby increasing the effect of rapid heat source interaction between the coolant and the heat-absorbing hollow aluminum plate 132.

[0032] When the airflow flows rapidly on the top surface of the composite wing UAV 11, the gas flows upward on the surface of the trapezoidal drainage strip 131 under the guidance of the trapezoidal drainage strip 131. When the gas flow path is changed under high-speed flow, the flow speed of the gas will be accelerated, and the bottom surface of the gas will produce a low-pressure state at the edge position of the trapezoidal drainage strip 131. The gas in the low-pressure state will generate a large suction force. Since the low-pressure position is located at the top edge position of the heat-absorbing hollow aluminum plate 132, the low-pressure environment generates a large suction force on the inside of the heat-absorbing hollow aluminum plate 132, so that the gas inside the heat-absorbing hollow aluminum plate 132 is quickly discharged. With the mutual cooperation of the heat-absorbing hollow aluminum plate 132, the gas inside the heat-absorbing hollow aluminum plate 132 is quickly discharged, and the heat dissipation effect of the coolant inside the coolant tank 13 is accelerated.

[0033] like Figures 1 to 2 and Figure 5-Figure 6 As shown, a gas drainage chute a1 is provided on one side surface of the compound wing UAV 11, and a guide cavity a2 is opened on the inner wall surface of the gas drainage chute a1. An L-shaped exhaust pipe a3 is fixedly connected to the bottom surface of the compound wing UAV 11, and one end of the L-shaped exhaust pipe a3 extends to the inner wall surface of the guide cavity a2. A liquid cooling box a4 is fixedly installed on the bottom surface of the compound wing UAV 11, and a heat-absorbing aluminum plate a5 is fixedly connected to the bottom surface of the liquid cooling box a4, and a heat-absorbing aluminum plate a6 is fixedly connected to the bottom surface of the heat-absorbing aluminum plate a5.

[0034] When the composite wing UAV 11 is flying at high speed, the gas diversion chute a1 on one side surface of the composite wing UAV 11 is used to change the path of the oncoming gas, so that the gas slides on the surface of the gas diversion chute a1. At the same time, a part of the high-speed flowing gas will flow into the interior of the guide cavity a2, and under the guidance of the guide cavity a2 and the L-shaped exhaust pipe a3, it will flow parallel to the bottom surface of the composite wing UAV 11. At the same time, the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 are used to absorb the heat source inside the liquid cooling box a4 and transmit the heat source. When the parallel high-speed flow of air passes through the surface of the heat dissipation plate a6, it takes away the heat source on the outer surface of the heat dissipation plate a6 and the heat-absorbing aluminum plate a5, so that the surface of the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 is always kept below the internal temperature of the liquid cooling box a4, so that the waste heat of the coolant inside the liquid cooling box a4 can always be transferred through the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 to achieve the effect of heat source transfer.

[0035] like Figures 5 and 6As shown, the interior of the liquid cooling box a4 and the coolant tank 13 are filled with coolant, a sealing sleeve a7 is fixedly connected to the inner wall of the guide cavity a2, a limiting sleeve a8 is movably sleeved on the inner wall of the sealing sleeve a7, two transmission rods a9 are fixedly connected to the two side surfaces of the limiting sleeve a8, two groups of transmission blades a10 are fixedly connected to the outer surfaces of the two transmission rods a9, one group of transmission blades a10 is positioned on the inner wall of the guide cavity a2, and the other group of transmission blades a10 is positioned inside the liquid cooling box a4.

[0036] When the high-speed flowing gas passes through the guide cavity a2, the high-speed flowing gas will push the transmission blades a10 on the outer surface of the transmission rod a9, and cause the transmission blades a10 to stir inside the liquid cooling box a4, so that the liquid inside the liquid cooling box a4 is stirred, so that the low-temperature liquid after heat dissipation is mixed with the waste heat, so that the waste heat inside the coolant can be transferred and dissipated through the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 under the continuous stirring of the coolant, thereby continuously stirring the coolant and mixing the coolant at different temperatures.

[0037] like Figures 1 to 2 and Figure 7-Figure 8 As shown, a support frame 111 is provided on both side surfaces of the composite wing UAV 11, a plurality of composite spiral wings 113 are provided on the top surface of the support frame 111, a swing arm 112 is provided on both side surfaces of the support frame 111, one side surface of the swing arm 112 is fixedly connected to the outer surface of one end of the coolant tank 13, a fixing plate 114 is fixedly connected to the both side surfaces of the support frame 111, an elastic buffer wire 115 is fixedly connected to the bottom surface of the fixing plate 114, and the other end of the elastic buffer wire 115 is fixedly connected to the coolant tank 13 On the top surface of the support frame 111, electric motors 116 are provided on both side surfaces, and a turbine push arm 117 is fixedly connected to the output end of the electric motor 116. The outer surface of the turbine push arm 117 is movably overlapped on the outer surface of the coolant tank 13. A plurality of groups of circulation drainage pipes 121 are fixedly installed on the output end of the diverter 12, and the other end of one group of circulation drainage pipes 121 extends to the inner wall of the coolant tank 13, and the two ends of the other group of circulation drainage pipes 121 are respectively fixedly connected to the outer surfaces of the coolant tank 13 and the liquid cooling tank a4.

[0038] When the drone is flying, the electric motor 116 rotates the turbine propulsion arm 117. When the turbine propulsion arm 117 is deformed, the resulting changes will squeeze and push the surface of the coolant tank 13, and cause the coolant tank 13 to tilt from the surface of the support frame 111, thereby changing the contact range and contact angle between the coolant tank 13 and the outside air, so that the surface of the coolant tank 13 can always maintain the contact range and contact area with the outside air, thereby accelerating the entry of gas into the heat-absorbing hollow aluminum plate 132.

[0039] Working principle: the coolant after absorbing heat will enter the interior of the coolant tank 13. When the coolant after absorbing heat comes into contact with the heat-absorbing hollow aluminum plate 132, the heat source is drained into the interior of the heat-absorbing hollow aluminum plate 132 by utilizing the heat-conducting material of the heat-absorbing hollow aluminum plate 132. When the composite wing UAV 11 is flying at high speed, the external airflow will differentiate and flow from the upper and lower surfaces of the coolant tank 13. When the airflow flows on the bottom surface of the coolant tank 13, when it contacts the surface of the suction rib 133, the airflow is guided by the suction rib 133 to quickly enter the interior of the heat-absorbing hollow aluminum plate 132, and then the heat source accumulated inside the heat-absorbing hollow aluminum plate 132 is quickly drained and discharged, so that the inner wall surface of the heat-absorbing hollow aluminum plate 132 is always kept in a low temperature state, thereby increasing the effect of rapid heat source interaction between the coolant and the heat-absorbing hollow aluminum plate 132.

[0040] When the airflow flows rapidly on the top surface of the composite wing UAV 11, the gas flows upward on the surface of the trapezoidal drainage strip 131 under the guidance of the trapezoidal drainage strip 131. When the gas is flowing at high speed, the flow path is changed, which will accelerate the flow speed of the gas, thereby causing the bottom surface of the gas to produce a low-pressure state at the edge position of the trapezoidal drainage strip 131. The gas in the low-pressure state will generate a large suction force. Since the low-pressure position is located at the top edge position of the heat-absorbing hollow aluminum plate 132, the low-pressure environment generates a large suction force on the inside of the heat-absorbing hollow aluminum plate 132, so that the gas inside the heat-absorbing hollow aluminum plate 132 is quickly discharged. Under the mutual cooperation of the heat-absorbing hollow aluminum plate 132, the gas inside the heat-absorbing hollow aluminum plate 132 is quickly discharged, and the heat dissipation effect of the coolant in the coolant tank 13 is accelerated.

[0041] When the composite wing UAV 11 is flying at high speed, the gas diversion chute a1 on one side surface of the composite wing UAV 11 is used to change the path of the oncoming gas, so that the gas slides on the surface of the gas diversion chute a1. At the same time, a part of the high-speed flowing gas will flow into the interior of the guide cavity a2, and under the guidance of the guide cavity a2 and the L-shaped exhaust pipe a3, it will flow parallel to the bottom surface of the composite wing UAV 11. At the same time, the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 are used to absorb the heat source inside the liquid cooling box a4 and transmit the heat source. When the parallel high-speed flow of air passes through the surface of the heat dissipation plate a6, it takes away the heat source on the outer surface of the heat dissipation plate a6 and the heat-absorbing aluminum plate a5, so that the surface of the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 is always kept below the internal temperature of the liquid cooling box a4, so that the waste heat of the coolant inside the liquid cooling box a4 can always be transferred through the heat-absorbing aluminum plate a5 and the heat dissipation plate a6 to achieve the effect of heat source transfer.

[0042] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the foregoing embodiments. The foregoing embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. A composite wing inspection drone with a liquid cooling structure, comprising a composite wing drone (11), a diverter (12) fixedly mounted on the outer surface of the bottom of the composite wing drone (11), and a coolant tank (13) movably sleeved on the edges of both sides of the composite wing drone (11), characterized in that: A plurality of heat-absorbing hollow aluminum plates (132) are fixedly connected to the inner wall surface of the coolant tank (13), and the two ends of the heat-absorbing hollow aluminum plates (132) extend to the upper and lower surfaces of the coolant tank (13), respectively. A trapezoidal drainage strip (131) is provided on the top surface of the coolant tank (13) and at the edge position of one side of the top end of the heat-absorbing hollow aluminum plates (132). A suction convex strip (133) is provided on the bottom surface of the heat-absorbing hollow aluminum plates (132) and at the bottom edge position of the coolant tank (13). A V-shaped differentiation strip (134) is provided on the inner wall surface of the coolant tank (13) and at the middle position of the two groups of heat-absorbing hollow aluminum plates (132). A clamping groove (135) is provided on the top outer surface of the coolant tank (13) and at the middle position.

2. The composite wing inspection drone with a liquid cooling and heat dissipation structure according to claim 1, characterized in that: A gas drainage chute (a1) is provided on one side surface of the composite wing UAV (11), a drainage cavity (a2) is provided on the inner wall surface of the gas drainage chute (a1), an L-shaped exhaust pipe (a3) ​​is fixedly connected to the bottom surface of the composite wing UAV (11), and one end of the L-shaped exhaust pipe (a3) ​​extends to the inner wall surface of the drainage cavity (a2).

3. The composite wing inspection drone with a liquid cooling and heat dissipation structure according to claim 2, characterized in that: A liquid cooling box (a4) is fixedly mounted on the bottom surface of the composite wing UAV (11), a heat-absorbing aluminum plate (a5) is fixedly connected to the bottom surface of the liquid cooling box (a4), and a heat dissipation plate (a6) is fixedly connected to the bottom surface of the heat-absorbing aluminum plate (a5).

4. The composite wing inspection drone with a liquid cooling and heat dissipation structure according to claim 3, characterized in that: The interiors of the liquid cooling box (a4) and the cooling liquid box (13) are filled with cooling liquid, a sealing sleeve (a7) is fixedly connected to the inner wall surface of the guide cavity (a2), and a limiting sleeve (a8) is movably sleeved on the inner wall surface of the sealing sleeve (a7).

5. The composite wing inspection drone with a liquid cooling and heat dissipation structure according to claim 4, characterized in that: Two transmission rods (a9) are fixedly connected to the two side surfaces of the limiting sleeve (a8), and two groups of transmission blades (a10) are fixedly connected to the outer surfaces of the two transmission rods (a9). One group of transmission blades (a10) is arranged on the inner wall surface of the guide cavity (a2), and the other group of transmission blades (a10) is arranged inside the liquid cooling box (a4).

6. The composite wing inspection drone with a liquid cooling structure according to claim 5, characterized in that: Support frames (111) are provided on both side surfaces of the composite wing UAV (11), a plurality of composite spiral wings (113) are provided on the top surface of the support frame (111), swing arms (112) are provided on both side surfaces of the support frame (111), one side surface of the swing arm (112) is fixedly connected to the outer surface of one end of the coolant tank (13), and fixing plates (114) are fixedly connected to both side surfaces of the support frame (111).

7. The composite wing inspection drone with a liquid cooling structure according to claim 6, characterized in that: An elastic buffer wire (115) is fixedly connected to the bottom surface of the fixed plate (114), and the other end of the elastic buffer wire (115) is fixedly connected to the top surface of the coolant tank (13). Electric motors (116) are provided on both side surfaces of the support frame (111), and a turbine propulsion arm (117) is fixedly connected to the output end of the electric motor (116). The outer surface of the turbine propulsion arm (117) is movably overlapped with the outer surface of the coolant tank (13).

8. The composite wing inspection drone with a liquid cooling and heat dissipation structure according to claim 1, characterized in that: A plurality of groups of circulation drainage tubes (121) are fixedly mounted on the output end of the diverter (12), the other end of one group of the circulation drainage tubes (121) extending to the inner wall surface of the coolant tank (13), and the two ends of another group of the circulation drainage tubes (121) are respectively fixedly connected to the outer surfaces of the coolant tank (13) and the liquid cooling tank (a4).

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