Mooring unmanned aerial vehicle

Abstract

The invention relates to a mooring unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the mooring unmanned aerial vehicle comprises a fuselage, propellers, an airborne power supply device, a heat dissipation assembly, a power assembly and a transmission assembly; the heat dissipation assembly comprises a heat dissipation box, a movable plate and a heat exchange pipe. The power assembly provides a power source, and the transmission assembly can transmit power to the heat dissipation assembly, so that the movable plate can be driven to reciprocate in the direction close to or away from the airborne power supply device. The cooling liquid in the first heat dissipation cavity and the second heat dissipation cavity in the heat dissipation box can be circulated and exchanged, the heat absorption efficiency of the cooling liquid in the first heat dissipation cavity is improved, the heat dissipation efficiency of the cooling liquid in the second heat dissipation cavity is guaranteed, and therefore the heat dissipation efficiency of the mooring unmanned aerial vehicle can be improved, and the service life of the mooring unmanned aerial vehicle is prolonged. The defect that a traditional mooring unmanned aerial vehicle is low in heat dissipation efficiency is overcome.

Description

Technical Field

[0001] The present application relates to the technical field of drones, and in particular to a tethered drone. Background Art

[0002] A tethered drone is a type of drone that can be used in fields such as firefighting and agriculture. A tethered drone is connected to a ground power supply device via a cable to continuously supply power to the tethered drone's onboard power supply device, where the tethered drone's onboard power supply device is used to convert voltage.

[0003] In actual work, the onboard power supply device of the tethered drone can convert the 1500V high voltage electricity transmitted by the ground power supply equipment into 600V high voltage electricity. Since the onboard power supply device will generate a lot of heat during the voltage conversion process, if the heat is not dissipated in time, it is easy to affect the relevant components of the tethered drone, thereby affecting the working state of the tethered drone.

[0004] In the prior art, most conventional tethered drones dissipate heat by installing a heat sink on an onboard power supply device, but the heat dissipation efficiency is relatively low. Summary of the invention

[0005] In order to improve the heat dissipation efficiency of a tethered drone and improve the defect of low heat dissipation efficiency of a traditional tethered drone, the present application provides a tethered drone.

[0006] The present application provides a tethered drone, which adopts the following technical solution: A tethered drone, comprising: body; a propeller, the propeller being arranged on the fuselage; An onboard power supply device, the onboard power supply device being arranged on the fuselage; A heat dissipation component, the heat dissipation component includes a heat dissipation box, a movable plate and a heat exchange tube, the heat dissipation box is fixedly arranged on one side of the airborne power supply device, the movable plate is slidably arranged in the heat dissipation box, the movable plate can move in a direction close to or away from the airborne power supply device, the movable plate divides the heat dissipation box into a first heat dissipation cavity and a second heat dissipation cavity, the first heat dissipation cavity is located on a side of the heat dissipation box close to the airborne power supply device, the second heat dissipation cavity is located on a side of the heat dissipation box away from the airborne power supply device, the first heat dissipation cavity and the second heat dissipation cavity are both filled with coolant, one end of the heat exchange tube is connected to the first heat dissipation cavity, and the other end is connected to the second heat dissipation cavity; A power assembly, the power assembly being arranged on the fuselage and used for providing a power source for the movement of the movable plate toward or away from the onboard power supply device; A transmission assembly is arranged on the fuselage and is used to transmit the power provided by the power assembly to the movable plate, so as to drive the movable plate to reciprocate in a direction close to or away from the airborne power supply device.

[0007] By adopting the above technical solution, the power component can provide a power source for the transmission component, and the transmission component can transmit power to the moving plate, thereby driving the moving plate to reciprocate in the direction close to or away from the onboard power supply device; when the UAV is in normal operation, the onboard power supply device will generate heat, and the heat will first be transferred to the first heat dissipation cavity of the heat dissipation box, and then diffused to the second heat dissipation cavity. At this time, the heat of the coolant in the first heat dissipation cavity is greater than the heat of the coolant in the second heat dissipation cavity. As time goes on, the heat of the coolant in the first heat dissipation cavity gradually increases, and its heat absorption efficiency gradually decreases; when the moving plate moves toward the direction close to the onboard power supply device, the pressure in the second heat dissipation cavity decreases, and the pressure in the first heat dissipation cavity increases. Part of the coolant in the first heat dissipation cavity will move to the second heat dissipation cavity through the heat exchange tube under the action of the pressure difference; when the moving plate moves toward the direction away from the onboard power supply device , the pressure in the first heat dissipation chamber decreases, and the pressure in the second heat dissipation chamber increases. Part of the coolant in the second heat dissipation chamber will move to the first heat dissipation chamber through the heat exchange tube under the action of the pressure difference; thereby, by reciprocating the movable plate in the direction close to or away from the airborne power supply device, the coolant in the first heat dissipation chamber and the second heat dissipation chamber can be circulated and exchanged, and the low-temperature coolant flows from the second heat dissipation chamber into the first heat dissipation chamber, thereby reducing the temperature of the coolant in the first heat dissipation chamber and accelerating the heat absorption efficiency of the coolant in the first heat dissipation chamber; the high-temperature coolant flows from the first heat dissipation chamber into the second heat dissipation chamber, increasing the temperature of the coolant in the second heat dissipation chamber, and quickly dissipating the heat of the coolant through the second heat dissipation chamber in contact with the outside world, thereby ensuring the heat dissipation efficiency of the coolant in the second heat dissipation chamber; the first heat dissipation chamber and the second heat dissipation chamber work together to improve the heat dissipation effect of the airborne power supply device.

[0008] Optionally, the power assembly includes an air inlet duct and an air outlet duct; one end of the air inlet duct is located below the propeller, the air inlet duct is used to collect the airflow below the propeller, the end of the air inlet duct away from the propeller is fixedly connected to one end of the air outlet duct, the end of the air outlet duct away from the air inlet duct is connected to the transmission assembly, and the air outlet duct is used to transfer the airflow collected by the air inlet duct to the transmission assembly.

[0009] By adopting the above technical solution, when the drone is in operation, the propeller rotates, driving the air around the propeller to generate airflow, part of which can enter the air inlet duct, be transmitted to the air outlet duct through the air inlet duct, and then be transmitted to the transmission assembly.

[0010] Optionally, the transmission assembly includes a first transmission component and a second transmission component, the first transmission component includes an impeller and a first transmission rod, the impeller is located below one end of the air outlet duct away from the air inlet duct, the impeller can rotate under the action of the airflow discharged from the air outlet duct, the first transmission rod is located on the side of the impeller close to the heat dissipation assembly, and the first transmission rod is coaxially arranged with the impeller, one end of the first transmission rod is fixedly connected to the impeller, and the other end is connected to the second transmission component.

[0011] By adopting the above technical solution, the airflow discharged from the air outlet pipe will blow toward the impeller from above the impeller, thereby driving the impeller to rotate, and further driving the first transmission rod to rotate.

[0012] Optionally, the second transmission component includes a transmission tube and a transmission plate, the transmission tube is fixedly arranged on the fuselage and coaxially arranged with the impeller, the transmission plate is circular and coaxially arranged with the transmission tube, the transmission plate is arranged inside the transmission tube and can move along the length direction of the transmission tube, and one side of the transmission plate is fixedly connected to an end of the first transmission rod away from the impeller.

[0013] By adopting the above technical solution, when the first transmission rod rotates under the drive of the impeller, it can also drive the transmission plate to rotate inside the transmission pipe.

[0014] Optionally, the second transmission component also includes a transmission ball, a transmission groove is opened on the inner wall of the transmission tube, the transmission groove is arranged in an S shape along the circumference of the transmission tube, and the two ends of the transmission groove are connected to each other, the transmission ball is slidably arranged in the transmission groove along the length direction of the transmission groove, and the transmission plate is fixedly connected to the transmission ball; the first transmission rod is a telescopic rod.

[0015] By adopting the above technical solution, when the transmission plate rotates, it can drive the transmission ball to move in the direction of the transmission groove. At this time, since the transmission groove is S-shaped, the transmission ball not only makes a circumferential motion with the center of the transmission plate as the center of the circle, but also makes a reciprocating motion toward or away from the onboard power supply device at the same time, that is, it can drive the transmission plate to make a reciprocating motion toward or away from the onboard power supply device while rotating.

[0016] Optionally, the second transmission component also includes a second transmission rod, which is arranged inside the transmission tube and coaxially with the transmission tube, one end of the second transmission rod is rotationally connected to the side of the transmission plate away from the first transmission rod, and the other end is fixedly connected to the movable plate.

[0017] By adopting the above technical solution, when the transmission plate is making a reciprocating motion toward or away from the onboard power supply device, it can drive the second transmission rod to make a reciprocating motion toward or away from the onboard power supply device, thereby driving the movable plate to make a reciprocating motion toward or away from the onboard power supply device, thereby enabling the coolant in the first heat dissipation cavity and the second heat dissipation cavity to circulate and exchange.

[0018] Optionally, the power assembly further includes an air collecting ring, which is fixedly disposed at the top of the air inlet pipe and is funnel-shaped, and the bottom of the air collecting ring and the top of the air inlet pipe are adapted to each other in size.

[0019] By adopting the above technical solution, the air collecting ring can increase the airflow entering the air inlet pipe, thereby increasing the power transmitted by the power component to the transmission component.

[0020] Optionally, four propellers are provided along the circumference of the fuselage, and four heat dissipation components, four power components and four transmission components are also provided along the circumference of the fuselage, and they correspond one to one to each other.

[0021] By adopting the above technical solution, the heat dissipation efficiency of the airborne power supply device can be further improved.

[0022] Optionally, the first transmission component further includes a windproof shell, the windproof shell cover is arranged on the outside of the impeller, and the top and bottom of the windproof shell are both open.

[0023] By adopting the above technical solution, the windproof shell is conducive to accumulating the airflow blown out by the air outlet duct, thereby reducing power transmission loss.

[0024] In summary, the present application includes at least one of the following beneficial technical effects: Through the arrangement of the power component, the transmission component and the heat dissipation component, the power component can convert the airflow at the propeller into an effective power source, thereby transmitting the power to the heat dissipation component through the transmission component, thereby driving the movable plate to reciprocate in the direction of approaching or moving away from the airborne power supply device; thereby enabling the coolant in the first heat dissipation cavity and the second heat dissipation cavity to circulate and exchange, and the low-temperature coolant flows from the second heat dissipation cavity into the first heat dissipation cavity, thereby reducing the temperature of the coolant in the first heat dissipation cavity and accelerating the heat absorption efficiency of the coolant in the first heat dissipation cavity; the high-temperature coolant flows from the first heat dissipation cavity into the second heat dissipation cavity, thereby increasing the temperature of the coolant in the second heat dissipation cavity, and quickly dissipating the heat of the coolant through the second heat dissipation cavity in contact with the outside world, thereby ensuring the heat dissipation efficiency of the coolant in the second heat dissipation cavity; the first heat dissipation cavity and the second heat dissipation cavity work in coordination, thereby improving the heat dissipation effect of the airborne power supply device.

[0025] Through the setting of the air inlet duct and the air outlet duct, when the drone is in operation, the propeller rotates, driving the air around the propeller to generate airflow, part of which can enter the air inlet duct, be transmitted to the air outlet duct through the air inlet duct, and then be transmitted to the transmission assembly.

[0026] Through the arrangement of the impeller, the first transmission rod, the transmission tube, the transmission plate, the transmission ball and the second transmission rod, the airflow discharged from the air outlet pipe will blow toward the impeller from above the impeller, thereby driving the impeller to rotate, and then driving the first transmission rod to rotate, and at the same time driving the transmission plate to rotate inside the transmission tube; further, it can drive the transmission ball to move along the direction of the transmission groove. At this time, since the transmission groove is S-shaped, the transmission ball not only makes a circumferential motion with the center of the transmission plate as the center of the circle, but also makes a reciprocating motion toward or away from the on-board power supply device, that is, it can drive the transmission plate to make a reciprocating motion toward or away from the on-board power supply device while rotating. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the structure of an embodiment of the present application; Figure 2 is a partial cross-sectional schematic diagram of an embodiment of the present application; Figure 3 is a cross-sectional schematic diagram showing a transmission groove in an embodiment of the present application; Figure 4 yes Figure 3 A partial enlarged schematic diagram of part A.

[0028] Description of reference numerals: 1. Body; 2. Propeller; 3. Airborne power supply device; 4. heat dissipation assembly; 41. heat dissipation box; 42. first heat dissipation cavity; 43. second heat dissipation cavity; 44. moving plate; 45. heat exchange tube; 5. Power assembly; 51. Air inlet pipe; 52. Air outlet pipe; 53. Air collecting circle; 6. Transmission assembly; 61. First transmission component; 611. Impeller; 612. First transmission rod; 613. Wind shield; 62. Second transmission component; 621. Transmission pipe; 622. Transmission plate; 623. Transmission ball; 624. Second transmission rod; 625. Transmission groove. DETAILED DESCRIPTION

[0029] The following is combined with Figure 1-4 This application is described in further detail.

[0030] The present application embodiment discloses a tethered drone. Figure 1A tethered drone includes a fuselage 1, a propeller 2, an airborne power supply device 3, a heat dissipation component 4, a power component 5 and a transmission component 6; the propeller 2 is fixedly mounted on the fuselage 1, and four propellers 2 are evenly distributed along the circumference of the fuselage 1; the airborne power supply device 3 is fixedly mounted below the fuselage 1; a group of power components 5 is provided below each propeller 2, a group of transmission components 6 is provided on the side of each power component 5 close to the airborne power supply device 3, and a group of heat dissipation components 4 is provided between each transmission component 6 and the airborne power supply device 3. The power component 5 is used to provide a power source for the transmission component 6, the transmission component 6 is used to transmit power to the heat dissipation component 4, and the heat dissipation component 4 is used to dissipate the heat of the airborne power supply device 3.

[0031] Reference Figure 1 and Figure 2 The power assembly 5 includes an air inlet pipe 51, an air outlet pipe 52 and an air collecting circle 53, wherein the air inlet pipe 51 is arranged below the propeller 2, the length direction of the air inlet pipe 51 is parallel to the axial direction of the propeller 2, the top of the air inlet pipe 51 is located below the propeller 2, and the air inlet pipe 51 is used to collect the airflow below the propeller 2; the air collecting circle 53 is arranged at the top of the air inlet pipe 51, and is used to increase the air collection amount of the air inlet pipe 51, the air collecting circle 53 is funnel-shaped, and its cross-sectional area gradually decreases from top to bottom, and the size of its bottom is mutually adapted to the size of the top of the air inlet pipe 51; one end of the air outlet pipe 52 is fixedly connected to the bottom end of the air inlet pipe 51, and the other end is connected to the transmission assembly 6, and is used to transmit the airflow collected in the air inlet pipe 51 to the transmission assembly 6.

[0032] When the tethered drone is working normally, its propeller 2 is in a rotating state, and airflow is generated around the propeller 2. At this time, part of the airflow below the propeller 2 can be collected into the air inlet pipe 51 through the air collecting circle 53, and then enters the air outlet pipe 52 and is transmitted to the transmission component 6.

[0033] Reference Figure 2 and Figure 3 The transmission component 6 includes a first transmission component 61 and a second transmission component 62, wherein the first transmission component 61 is used to collect the airflow transmitted from the power component 5, and convert the airflow into power, and transmit it to the second transmission component 62, and the second transmission component 62 is used to transmit the power to the heat dissipation component 4.

[0034] Reference Figure 2 and Figure 3The first transmission component 61 includes an impeller 611, a first transmission rod 612 and a windproof shell 613, wherein the impeller 611 is arranged below the end of the air outlet pipe 52 away from the air inlet pipe 51, the first transmission rod 612 is a telescopic rod, which is arranged on the side of the impeller 611 close to the heat dissipation component 4, the first transmission rod 612 is coaxially arranged with the impeller 611, the end of the first transmission rod 612 close to the impeller 611 is fixedly connected to the center of the impeller 611, and the end away from the impeller 611 is connected to the second transmission component 62.

[0035] When the airflow in the air outlet pipe 52 is discharged, it can drive the impeller 611 to rotate, thereby driving the first transmission rod 612 to rotate.

[0036] Reference Figure 2 and Figure 3 The second transmission component 62 includes a transmission tube 621, a transmission plate 622, a transmission ball 623 and a second transmission rod 624; the transmission tube 621 is fixedly connected to the fuselage 1, the transmission tube 621 is coaxially arranged with the first transmission rod 612, and the transmission tube 621 is located between the impeller 611 and the airborne power supply device 3; the transmission plate 622 is circular and is also coaxially arranged with the first transmission rod 612, the transmission plate 622 is movably arranged in the transmission tube 621 along the length direction of the transmission tube 621, and the diameter size of the transmission plate 622 is mutually adapted to the inner diameter size of the transmission tube 621.

[0037] Reference Figure 2 and Figure 4 A transmission groove 625 is provided on the inner wall of the transmission tube 621. The transmission groove 625 is arranged in an S shape along the circumference of the transmission tube 621, and the two ends of the transmission groove 625 are connected to each other. The transmission ball 623 is slidably arranged in the transmission groove 625 along the length direction of the transmission groove 625, and the transmission ball 623 is fixedly connected to the transmission plate 622. When the transmission ball 623 slides in the transmission groove 625, the transmission plate 622 rotates with the sliding of the transmission ball 623, and reciprocates in the direction of approaching or moving away from the airborne power supply device 3; the second transmission rod 624 is also arranged inside the transmission tube 621 and is coaxially arranged with the transmission tube 621. The second transmission rod 624 is located between the transmission plate 622 and the heat dissipation component 4. The end of the second transmission rod 624 close to the transmission plate 622 is rotatably connected to the center of the transmission plate 622, and the end away from the transmission plate 622 is connected to the heat dissipation component 4.

[0038] When the first transmission rod 612 rotates, it can drive the transmission plate 622 to rotate together, thereby driving the transmission ball 623 to slide in the transmission groove 625, so that the transmission plate 622 can reciprocate along the length direction of the transmission tube 621 to approach or move away from the airborne power supply device 3 while rotating; thereby, it can drive the second transmission rod 624 to reciprocate along the length direction of the transmission tube 621 to approach or move away from the airborne power supply device 3.

[0039] Reference Figure 2 and Figure 3 The heat dissipation assembly 4 includes a heat dissipation box 41, a movable plate 44 and a heat exchange tube 45; the heat dissipation box 41 is fixedly arranged on one side of the airborne power supply device 3, and its interior is a cavity; the movable plate 44 is slidably arranged in the heat dissipation box 41, and the sliding direction is parallel to the length direction of the transmission tube 621, and the size of the movable plate 44 is mutually adapted to the size of the cavity in the heat dissipation box 41, and the movable plate 44 divides the cavity in the heat dissipation box 41 into a first heat dissipation cavity 42 and a second heat dissipation cavity 43, wherein the first heat dissipation cavity 42 is located on a side of the heat dissipation box 41 close to the airborne power supply device 3, and the second heat dissipation cavity 43 is located on a side of the heat dissipation box 41 away from the airborne power supply device 3; the end of the second transmission rod 624 away from the transmission plate 622 is fixedly connected to the movable plate 44.

[0040] Reference Figure 2 The first heat dissipation cavity 42 and the second heat dissipation cavity 43 are both filled with coolant; the heat exchange tube 45 is arranged at the bottom of the heat dissipation box 41, one end of which is connected to the first heat dissipation cavity 42, and the other end is connected to the second heat dissipation cavity 43.

[0041] When the second transmission rod 624 reciprocates along the length direction of the transmission tube 621 to approach or move away from the airborne power supply device 3, the second transmission rod 624 drives the movable plate 44 to also reciprocate along the length direction of the transmission tube 621 to approach or move away from the airborne power supply device 3; when the movable plate 44 moves toward the direction close to the airborne power supply device 3, the pressure in the second heat dissipation cavity 43 decreases, and the pressure in the first heat dissipation cavity 42 increases. Part of the coolant in the first heat dissipation cavity 42 will move to the second heat dissipation cavity 43 through the heat exchange tube 45 under the action of the pressure difference. When the movable plate 44 moves toward the direction away from the airborne power supply device 3, the pressure in the first heat dissipation cavity 42 decreases, and the pressure in the second heat dissipation cavity 43 increases. Part of the coolant in the second heat dissipation cavity 43 will move to the first heat dissipation cavity 42 through the heat exchange tube 45 under the action of the pressure difference, thereby realizing the circulation and exchange of the coolant in the first heat dissipation cavity 42 and the second heat dissipation cavity 43.

[0042] The implementation principle of a tethered drone in the embodiment of the present application is: When the drone is in normal operation, the onboard power supply device 3 will generate heat, which is first transferred to the heat sink 41, through the first heat dissipation cavity 42, and then through the second heat dissipation cavity 43. At this time, the heat of the coolant in the first heat dissipation cavity 42 is greater than the heat of the coolant in the second heat dissipation cavity 43. As time goes by, the heat of the coolant in the first heat dissipation cavity 42 gradually increases, and its heat absorption efficiency gradually decreases.

[0043] At this time, the propeller 2 is in working state, and airflow is generated around it. The airflow located below the propeller 2 can be collected into the air inlet pipe 51 through the wind collecting circle 53, and then enters the air outlet pipe 52 to be transmitted to the transmission assembly 6; then the airflow will be discharged through the end of the air outlet pipe 52 close to the transmission assembly 6, thereby driving the impeller 611 to rotate, and then driving the first transmission rod 612 to rotate; further driving the transmission plate 622 to rotate together, thereby driving the transmission ball 623 to slide in the transmission groove 625, so that the transmission plate 622 can reciprocate along the length direction of the transmission tube 621 while rotating, approaching or moving away from the airborne power supply device 3, and then can drive the second transmission rod 624 to reciprocate along the length direction of the transmission tube 621, approaching or moving away from the airborne power supply device 3; further, the second transmission rod 624 can drive the movable plate 44 to reciprocate along the length direction of the transmission tube 621, approaching or moving away from the airborne power supply device 3.

[0044] When the movable plate 44 moves toward the direction approaching the onboard power supply device 3, the pressure in the second heat dissipation cavity 43 decreases, and the pressure in the first heat dissipation cavity 42 increases. Under the action of the pressure difference, part of the coolant in the first heat dissipation cavity 42 will move to the second heat dissipation cavity 43 through the heat exchange tube 45. When the movable plate 44 moves toward the direction away from the onboard power supply device 3, the pressure in the first heat dissipation cavity 42 decreases, and the pressure in the second heat dissipation cavity 43 increases. Under the action of the pressure difference, part of the coolant in the second heat dissipation cavity 43 will move to the first heat dissipation cavity 42 through the heat exchange tube 45, thereby realizing the circulation and exchange of the coolant in the first heat dissipation cavity 42 and the second heat dissipation cavity 43.

[0045] The coolant in the first heat dissipation cavity 42 and the second heat dissipation cavity 43 circulates and exchanges, and the low-temperature coolant flows from the second heat dissipation cavity 43 into the first heat dissipation cavity 42, thereby reducing the temperature of the coolant in the first heat dissipation cavity 42 and accelerating the heat absorption efficiency of the coolant in the first heat dissipation cavity 42; the high-temperature coolant flows from the first heat dissipation cavity 42 into the second heat dissipation cavity 43, increasing the temperature of the coolant in the second heat dissipation cavity 43, and quickly dissipates the heat of the coolant through the second heat dissipation cavity 43 in contact with the outside world, thereby ensuring the heat dissipation efficiency of the coolant in the second heat dissipation cavity 43; the first heat dissipation cavity 42 and the second heat dissipation cavity 43 work in coordination, thereby improving the heat dissipation effect of the airborne power supply device 3.

[0046] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A tethered drone, characterized in that: include: Body (1); A propeller (2), wherein the propeller (2) is arranged on the fuselage (1); An onboard power supply device (3), the onboard power supply device (3) being arranged on the fuselage (1); A heat dissipation component (4), the heat dissipation component (4) comprising a heat dissipation box (41), a movable plate (44) and a heat exchange tube (45), the heat dissipation box (41) being fixedly arranged on one side of the airborne power supply device (3), the movable plate (44) being slidably arranged in the heat dissipation box (41), the movable plate (44) being able to move in a direction approaching or away from the airborne power supply device (3), the movable plate (44) dividing the heat dissipation box (41) into a first heat dissipation cavity (42) and a second heat dissipation cavity (43), the first heat dissipation cavity (42) being located on a side of the heat dissipation box (41) close to the airborne power supply device (3), the second heat dissipation cavity (43) being located on a side of the heat dissipation box (41) away from the airborne power supply device (3), the first heat dissipation cavity (42) and the second heat dissipation cavity (43) being both filled with cooling liquid, one end of the heat exchange tube (45) being in communication with the first heat dissipation cavity (42), and the other end being in communication with the second heat dissipation cavity (43); a power assembly (5), the power assembly (5) being arranged on the fuselage (1) and being used to provide a power source for the movement of the movable plate (44) towards or away from the onboard power supply device (3); A transmission assembly (6), wherein the transmission assembly (6) is arranged on the fuselage (1) and is used to transmit the power provided by the power assembly (5) to the movable plate (44), thereby driving the movable plate (44) to reciprocate in a direction approaching or moving away from the onboard power supply device (3).

2. The tethered drone according to claim 1, characterized in that: The power assembly (5) comprises an air inlet pipe (51) and an air outlet pipe (52); one end of the air inlet pipe (51) is located below the propeller (2), the air inlet pipe (51) is used to collect the airflow below the propeller (2), the end of the air inlet pipe (51) away from the propeller (2) is fixedly connected to one end of the air outlet pipe (52), the end of the air outlet pipe (52) away from the air inlet pipe (51) is connected to the transmission assembly (6), and the air outlet pipe (52) is used to transfer the airflow collected by the air inlet pipe (51) to the transmission assembly (6).

3. The tethered drone according to claim 2, characterized in that: The transmission assembly (6) comprises a first transmission component (61) and a second transmission component (62); the first transmission component (61) comprises an impeller (611) and a first transmission rod (612); the impeller (611) is located below one end of the air outlet pipe (52) away from the air inlet pipe (51); the impeller (611) is capable of rotating under the action of the airflow discharged from the air outlet pipe (52); the first transmission rod (612) is located on a side of the impeller (611) close to the heat dissipation component (4); the first transmission rod (612) and the impeller (611) are coaxially arranged; one end of the first transmission rod (612) is fixedly connected to the impeller (611), and the other end is connected to the second transmission component (62).

4. The tethered drone according to claim 3, characterized in that: The second transmission component (62) comprises a transmission tube (621) and a transmission plate (622); the transmission tube (621) is fixedly arranged on the body (1) and is coaxially arranged with the impeller (611); the transmission plate (622) is circular and is coaxially arranged with the transmission tube (621); the transmission plate (622) is arranged inside the transmission tube (621) and is movable along the length direction of the transmission tube (621); one side of the transmission plate (622) is fixedly connected to an end of the first transmission rod (612) away from the impeller (611).

5. The tethered drone according to claim 4, characterized in that: The second transmission component (62) further comprises a transmission ball (623); a transmission groove (625) is provided on the inner wall of the transmission tube (621); the transmission groove (625) is arranged in an S-shape along the circumference of the transmission tube (621); and two ends of the transmission groove (625) are connected to each other; the transmission ball (623) is slidably arranged in the transmission groove (625) along the length direction of the transmission groove (625); and the transmission plate (622) is fixedly connected to the transmission ball (623); and the first transmission rod (612) is a telescopic rod.

6. The tethered drone according to claim 5, characterized in that: The second transmission component (62) further comprises a second transmission rod (624), which is arranged inside the transmission tube (621) and coaxially arranged with the transmission tube (621), one end of the second transmission rod (624) being rotationally connected to a side of the transmission plate (622) away from the first transmission rod (612), and the other end of the second transmission rod (624) being fixedly connected to the movable plate (44).

7. The tethered drone according to claim 2, characterized in that: The power assembly (5) further comprises an air collecting ring (53), which is fixedly arranged at the top of the air inlet pipe (51) and is funnel-shaped, and the bottom of the air collecting ring (53) and the top of the air inlet pipe (51) are adapted to each other in size.

8. The tethered drone according to claim 1, characterized in that: Four propellers (2) are provided along the circumference of the fuselage (1), and four heat dissipation components (4), power components (5) and transmission components (6) are also provided along the circumference of the fuselage (1), and correspond to each other one by one.

9. The tethered drone according to claim 3, characterized in that: The first transmission component (61) further comprises a windproof shell (613), wherein the windproof shell (613) is arranged to cover the outside of the impeller (611), and the top and bottom of the windproof shell (613) are both open.

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