Unmanned aerial vehicle engine control device and method

Abstract

The invention belongs to the technical field of engine control devices, and particularly relates to an unmanned aerial vehicle engine control device and method.The unmanned aerial vehicle engine control device comprises an engine body, a circulating cooling mechanism, a separation pressure mechanism, an air inlet cooling mechanism and a pair of closed cooling mechanisms, and a control box and a temperature sensor are fixedly installed on the engine body; a circulating cooling mechanism is fixedly installed on the upper side of the engine body and comprises a circulating containing bin. According to the unmanned aerial vehicle engine control device and method, through arrangement of corresponding mechanisms, the engine of the unmanned aerial vehicle can adapt to flight at various environment heights, the phenomenon that the engine is shut down due to overheating is reduced, the probability that the unmanned aerial vehicle falls off and is damaged is reduced, meanwhile, the situation that the temperature of the engine is too low is reduced, heat efficiency is more stable, and the service life of the unmanned aerial vehicle is prolonged. And the influence on the gas pressure in the cylinder is reduced, and the situation that the oil consumption is increased is correspondingly reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine control devices, and particularly relates to an engine control device and method for an unmanned aerial vehicle (UAV). Background Art

[0002] An engine is a machine that can convert other forms of energy into mechanical energy, including, for example, internal combustion engines, external combustion engines, jet engines, electric motors, etc. For example, an internal combustion engine usually converts chemical energy into mechanical energy. An engine is applicable to power generating devices and can also refer to the entire machine including the power device.

[0003] Currently, engines for UAVs mostly use natural air cooling for cooling. However, there is a large temperature difference between the ground and high altitudes. Only through natural air cooling, it is very difficult to fly at various environmental altitudes, which easily causes the engine to overheat and shut down, resulting in the dropping and damage of the UAV. When the engine temperature is too low, the thermal efficiency will also decrease synchronously, reducing the gas pressure in its cylinder and thus increasing fuel consumption.

[0004] The information disclosed in this background art section is only intended to enhance the overall understanding of the present invention and should not be regarded as an admission or any form of implication that this information constitutes prior art already known to those of ordinary skill in the art. Summary of the Invention

[0005] The purpose of the present invention is to provide an engine control device and method for a UAV, which can solve the problems that the existing natural air cooling method of the engine easily causes the engine to overheat and shut down, or the thermal efficiency decreases, resulting in increased fuel consumption.

[0006] To achieve the above purpose, the technical solution provided by a specific embodiment of the present invention is as follows:

[0007] An engine control device for a UAV, comprising: an engine body, a circulating cooling mechanism, a separating pressure mechanism, an intake air cooling mechanism, and a pair of closed cooling mechanisms;

[0008] A control box and a temperature sensor are fixedly installed on the engine body;

[0009] The circulating cooling mechanism is fixedly installed on the upper side of the engine body. The circulating cooling mechanism includes a circulating accommodation chamber, in which there is circulating coolant. A circulating partition plate is fixedly installed in the circulating accommodation chamber, and a circulating pressure piece is fixedly installed on the circulating partition plate. A circulating closed chamber is fixedly installed on the circulating accommodation chamber, and a circulating cooling plate is fixedly installed in the circulating closed chamber. A number of evenly distributed circulating vacuum chambers are fixedly installed in the circulating accommodation chamber;

[0010] The separating pressure mechanism is fixedly installed in the circulating accommodation chamber;

[0011] An air intake cooling mechanism is provided on the upper side of the circulating closed bin;

[0012] A pair of closed cooling mechanisms are fixedly installed on the upper side of the circulating closed bin.

[0013] In one or more embodiments of the present invention, positioning grooves matching the circulating pressure plates are drilled on the circulating partition plate, which can fix the positions of the circulating pressure plates, facilitate the installation of the circulating pressure plates, and improve the stability of the circulating pressure plates;

[0014] Circulating alcohol is provided in the circulating vacuum bin, which can be vaporized after absorbing the heat in the engine body, and can circulate between vaporization and liquefaction within the range of the circulating vacuum bin. After vaporization, it rises to the top of the circulating vacuum bin and is liquefied after the heat is absorbed by the circulating coolant;

[0015] A number of evenly distributed circulating contact fins are fixedly installed on the circulating vacuum bin, which can improve the speed of the circulating partition plate absorbing heat, improve the heat dissipation efficiency of the circulating vacuum bin, increase the heat absorption area of the circulating coolant, increase the contact area between the circulating coolant and the circulating vacuum bin, and improve the heating efficiency of the circulating coolant.

[0016] In one or more embodiments of the present invention, a number of evenly distributed circulating contact heat absorption rods are fixedly installed on the side of the circulating cooling plate close to the circulating partition plate, which can quickly cool the vaporized circulating coolant, can increase the contact area with the vaporized circulating coolant, and quickly absorb the heat in the vaporized circulating coolant;

[0017] A number of evenly distributed circulating air cooling fins are fixedly installed on the side of the circulating cooling plate away from the circulating contact heat absorption rods, which can quickly dissipate the heat on the surface of the circulating cooling plate after contacting the air, and enhance the heat dissipation efficiency of the circulating cooling plate.

[0018] In one or more embodiments of the present invention, the partition pressure mechanism includes a partition central axis rod, which can facilitate the rotation of the partition pressure plate, provide corresponding support for the rotation of the partition pressure plate, and provide a corresponding axis for the rotation of the partition pressure plate;

[0019] A partition pressure plate is rotatably installed outside the partition central axis rod, which can cooperate with the circulating partition plate to separate the spaces on the upper and lower sides of the circulating partition plate, so that the spaces on the upper and lower sides of the circulating partition plate do not interfere with each other. At the same time, when the liquefied circulating coolant in the space above the circulating partition plate converges to a certain extent, it will press down the partition pressure plate to open the partition pressure plate, so that the liquefied circulating coolant enters the space below the circulating partition plate;

[0020] A separating return spring is installed between the separating shaft rod and the separating pressure plate, which can support the separating pressure plate, prevent the separating pressure plate from rotating, and enable the separating pressure plate to quickly return to its original position after rotation;

[0021] A rotating groove matching the separating pressure plate is formed in the circulating pressure plate, which facilitates the installation of the separating pressure plate, enables the separating pressure plate to better cooperate with the circulating separating plate, and separates the space.

[0022] In one or more embodiments of the present invention, a separating positioning block is fixedly installed in the circulating accommodation bin, which can cooperate with the separating pressure plate to fix the separating pressure plate, reducing the probability of excessive rotation of the separating pressure plate affected by the separating return spring;

[0023] A separating attracting magnet is fixedly installed on the separating positioning block, which can attract the separating pressure plate, reducing the probability of rotation of the separating pressure plate. The separating attracting magnet matches the separating pressure plate.

[0024] In one or more embodiments of the present invention, the intake air cooling mechanism includes an intake air connecting bin, which connects the intake air guiding pipeline and the closed cooling bin, enabling the air in the closed cooling bin to enter the intake air guiding pipeline;

[0025] An intake air dust-proof net is fixedly installed in the intake air connecting bin, which can reduce the entry of external dust into the intake air guiding pipeline, improve the cleanliness above the circulating cooling plate, and prevent the heat dissipation effect of the circulating cooling plate from being affected;

[0026] An intake air guiding pipeline is installed between the intake air connecting bin and the circulating closed bin, which can connect the intake air connecting bin and the circulating closed bin, enable the air in the intake air connecting bin to enter the circulating closed bin, and facilitate the installation of the intake air fan. The intake air guiding pipeline penetrates through the intake air connecting bin and the circulating closed bin;

[0027] In one or more embodiments of the present invention, an intake air fan is provided in the intake air guiding pipeline, which can drive the air in the intake air guiding pipeline by rotation, enable the air in the intake air guiding pipeline to enter the circulating closed bin, and be discharged from the intake air exhaust net to form an air flow;

[0028] A pair of intake air brackets are installed between the intake air fan and the intake air guiding pipeline, which can position the intake air fan, ensure the balance of the intake air fan, improve the stability of the intake air fan, and the intake air fan penetrates through the intake air brackets and the intake air connecting bin;

[0029] An intake motor is fixedly installed on the intake communication bin, which improves the stability of the intake motor and can drive the rotation of the intake fan, providing corresponding power for the rotation of the intake fan. The intake motor is fixedly connected to the intake fan;

[0030] Intake and exhaust nets are fixedly installed on both sides of the circulation closed bin, which facilitates the discharge of air and provides a corresponding channel for the discharge of air. Exhaust grooves matching the intake and exhaust nets are drilled on the circulation closed bin.

[0031] In one or more embodiments of the present invention, the closed cooling mechanism includes a closed cooling bin, and air can enter the intake communication bin from the closed cooling bin. The closed cooling bin penetrates through the intake communication bin;

[0032] A number of evenly distributed closed rotating hinges are rotatably installed on the closed cooling bin, which can be rotated by control to close the closed cooling bin or open it at a certain angle;

[0033] A closed rotating pulley is fixedly installed on the closed rotating hinge, which can be driven by the closed sliding rack to rotate, and then drive the rotation of the closed rotating hinge. A closed sliding rack is slidably installed in the closed cooling bin, which can drive the rotation of the closed rotating pulley through friction;

[0034] A closed anti-wear pad is fixedly installed on one side of the closed sliding rack close to the closed rotating pulley, which improves the friction between the closed sliding rack and the closed rotating pulley and the precision of the closed sliding rack driving the closed rotating pulley.

[0035] In one or more embodiments of the present invention, a closed motor is fixedly installed on the closed cooling bin, which can drive the rotation of the closed power gear and provide corresponding power for the rotation of the closed power gear. The closed motor penetrates through the closed cooling bin;

[0036] A closed power gear is fixedly installed on the closed motor, which can drive the sliding of the closed sliding rack, enabling the closed sliding rack to better drive the rotation of multiple closed rotating pulleys. The closed power gear meshes with the closed sliding rack.

[0037] A method for controlling a drone engine, the method comprising: the temperature sensor constantly detecting the operating temperature of the engine body and transmitting it, the control box receiving the temperature data transmitted by the temperature sensor, the control box determining whether to start the intake cooling mechanism and the closed cooling mechanism, and sending instructions to the intake cooling mechanism and the closed cooling mechanism. After the intake cooling mechanism and the closed cooling mechanism are turned on, the heat dissipation of the circulating cooling mechanism can be enhanced, and the heat dissipation efficiency of the engine body can be improved. After the intake cooling mechanism and the closed cooling mechanism are turned off, the heat dissipation inside the engine body can be reduced.

[0038] Compared with the prior art, the drone engine control device and method of the present invention enable the engine of the drone to adapt to flights at various environmental altitudes through the setting of corresponding mechanisms, reduce the occurrence of engine overheating shutdown, reduce the probability of the drone falling and being damaged. At the same time, the situation of the engine temperature being too low is reduced, the thermal efficiency is more stable, the influence on the gas pressure in its cylinder is reduced, and the corresponding increase in fuel consumption is also reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments recorded in the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0040] Figure 1 It is a front elevation sectional view of a drone engine control device in an embodiment of the present invention;

[0041] Figure 2 For Figure 1 Schematic diagram of the structure at position A in

[0042] Figure 3 For Figure 1 Schematic diagram of the structure at position B in

[0043] Figure 4 For Figure 1 Schematic diagram of the structure at position C in

[0044] Figure 5 For Figure 1 Schematic diagram of the structure at position D in

[0045] Figure 6 For Figure 1 Schematic diagram of the structure at position E in

[0046] Figure 7 For Figure 1 Schematic diagram of the structure at position F in

[0047] Figure 8 A perspective view of the UAV engine control device in an embodiment of the present invention;

[0048] Figure 9 is Figure 8 A schematic structural view of the structure at position G in

[0049] Figure 10 A flowchart of the UAV engine control method in an embodiment of the present invention.

[0050] Main reference numeral description:

[0051] 1 - Engine body, 101 - Control box, 102 - Temperature sensor, 2 - Circulating cooling mechanism, 201 - Circulating storage bin, 202 - Circulating coolant, 203 - Circulating partition plate, 204 - Circulating pressure plate, 205 - Circulating closed bin, 206 - Circulating cooling plate, 207 - Circulating vacuum bin, 208 - Circulating alcohol, 209 - Circulating contact fin, 210 - Circulating contact heat absorption rod, 211 - Circulating air-cooled fin, 3 - Partition pressure mechanism, 301 - Partition central axis rod, 302 - Partition pressure plate, 303 - Partition rotary spring, 304 - Partition positioning block, 305 - Partition attracting magnet, 4 - Intake air cooling mechanism, 401 - Intake air connecting bin, 402 - Intake air dust-proof net, 403 - Intake air guiding pipeline, 404 - Intake air fan, 405 - Intake air bracket, 406 - Intake air motor, 407 - Intake air exhaust net, 5 - Enclosed cooling mechanism, 501 - Enclosed cooling bin, 502 - Enclosed rotating hinge, 503 - Enclosed rotating pulley, 504 - Enclosed sliding rack, 505 - Enclosed anti-wear pad, 506 - Enclosed motor, 507 - Enclosed driving gear. Detailed implementation manners

[0052] In order to enable those skilled in the art of the present technology to better understand the technical solutions in the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0053] As Figures 1 to 10 shown, the UAV engine control device in an embodiment of the present invention includes: an engine body 1, a circulating cooling mechanism 2, a partition pressure mechanism 3, an intake air cooling mechanism 4, and a pair of enclosed cooling mechanisms 5.

[0054] As Figures 1 to 8As shown in the figure, a control box 101 and a temperature sensor 102 are fixedly installed on the engine body 1. The control box 101 can control the opening and closing of the intake motor 406 and the closing motor 506, and can control the power of the intake motor 406 and the opening angle of the closing rotating hinge 502.

[0055] Among them, the temperature sensor 102 can detect the temperature of the engine body 1 at all times, providing a basis for the control box 101 to control the intake motor 406 and the closing motor 506.

[0056] As Figures 1 to 7 shown in the figure, a circulating cooling mechanism 2 is fixedly installed on the upper side of the engine body 1. The circulating cooling mechanism 2 includes a circulating accommodation chamber 201, which facilitates the accommodation of the circulating coolant 202 and provides a corresponding space for the accommodation of the circulating coolant 202.

[0057] Among them, the circulating accommodation chamber 201 is provided with a circulating coolant 202, which can absorb heat and vaporize, increasing the air pressure in the space below the circulating partition plate 203 and pushing open the circulating pressure piece 204. The vaporized circulating coolant 202 will enter the space above the circulating partition plate 203. After being cooled, the liquefied circulating coolant 202 will, due to gravity, press down the partition pressure plate 302 and flow back to the space below the circulating partition plate 203.

[0058] In addition, a circulating partition plate 203 is fixedly installed in the circulating accommodation chamber 201, which can separate the spaces on both sides of the circulating partition plate 203 and cooperate with the partition pressure plate 302 so that the spaces above and below the circulating partition plate 203 do not interfere with each other.

[0059] In addition, a circulating pressure piece 204 is fixedly installed on the circulating partition plate 203, which can be opened after the air pressure in the space below the circulating partition plate 203 increases. A circulating closed chamber 205 is fixedly installed on the circulating accommodation chamber 201, which can enclose the space of the circulating accommodation chamber 201 and at the same time facilitate the installation of the circulating cooling plate 206.

[0060] In addition, a circulating cooling plate 206 is fixedly installed in the circulating closed chamber 205, which can quickly dissipate the heat of the vaporized circulating coolant 202. A number of evenly distributed circulating vacuum chambers 207 are fixedly installed in the circulating accommodation chamber 201, which can accommodate the circulating alcohol 208.

[0061] As Figures 1 to 9 shown in the figure, a positioning groove matching the circulating pressure piece 204 is drilled on the circulating partition plate 203, which can fix the position of the circulating pressure piece 204, facilitating the installation of the circulating pressure piece 204 and improving the stability of the circulating pressure piece 204.

[0062] Among them, there is circulating alcohol 208 in the circulating vacuum chamber 207, which can be vaporized after absorbing the heat in the engine body 1 and can circulate between vaporization and liquefaction within the range of the circulating vacuum chamber 207. After vaporization, it rises to the top of the circulating vacuum chamber 207 and is liquefied after the heat is absorbed by the circulating coolant 202.

[0063] In addition, a number of evenly distributed circulating contact fins 209 are fixedly installed on the circulating vacuum chamber 207, which can improve the speed of the circulating partition plate 203 absorbing heat, improve the heat dissipation efficiency of the circulating vacuum chamber 207, increase the heat absorption area of the circulating coolant 202, increase the contact area between the circulating coolant 202 and the circulating vacuum chamber 207, and improve the heating efficiency of the circulating coolant 202.

[0064] As Figures 1 to 8 shown, a number of evenly distributed circulating contact heat absorption rods 210 are fixedly installed on the side of the circulating cooling plate 206 close to the circulating partition plate 203, which can quickly cool the vaporized circulating coolant 202, increase the contact area with the vaporized circulating coolant 202, and quickly absorb the heat in the vaporized circulating coolant 202.

[0065] Among them, a number of evenly distributed circulating air cooling fins 211 are fixedly installed on the side of the circulating cooling plate 206 far from the circulating contact heat absorption rods 210, which can quickly dissipate the heat on the surface of the circulating cooling plate 206 after contacting the air, enhancing the heat dissipation efficiency of the circulating cooling plate 206.

[0066] As Figures 1 to 5 shown, a partition pressure mechanism 3 is fixedly installed in the circulating accommodation chamber 201. The partition pressure mechanism 3 includes a partition central axis rod 301, which can facilitate the rotation of the partition pressure plate 302, provide corresponding support for the rotation of the partition pressure plate 302, and provide a corresponding axis for the rotation of the partition pressure plate 302.

[0067] Among them, a partition pressure plate 302 is rotatably installed outside the partition central axis rod 301, which can cooperate with the circulating partition plate 203 to separate the spaces on the upper and lower sides of the circulating partition plate 203, so that the spaces on the upper and lower sides of the circulating partition plate 203 will not interfere with each other. At the same time, when the liquefied circulating coolant 202 in the space above the circulating partition plate 203 converges to a certain extent, it will press down the partition pressure plate 302 to open the partition pressure plate 302, allowing the liquefied circulating coolant 202 to enter the space below the circulating partition plate 203.

[0068] In addition, a partition return spring 303 is installed between the partition central axis rod 301 and the partition pressure plate 302, which can support the partition pressure plate 302, prevent the partition pressure plate 302 from rotating, and enable the partition pressure plate 302 to quickly return to its original position after rotation.

[0069] In addition, a rotating groove matching the partition pressure plate 302 is formed in the circulating pressure plate 204, which facilitates the installation of the partition pressure plate 302 and enables the partition pressure plate 302 to better cooperate with the circulating partition plate 203 to partition the space.

[0070] As Figures 1 to 6 shown, a partition positioning block 304 is fixedly installed in the circulating accommodation bin 201, which can cooperate with the partition pressure plate 302 to fix the partition pressure plate 302 and reduce the probability of excessive rotation of the partition pressure plate 302 affected by the partition return spring 303.

[0071] Among them, a partition attracting magnet 305 is fixedly installed on the partition positioning block 304, which can attract the partition pressure plate 302 and reduce the probability of rotation of the partition pressure plate 302. The partition attracting magnet 305 matches the partition pressure plate 302.

[0072] As Figures 1 to 8 shown, an air intake cooling mechanism 4 is provided on the upper side of the circulating closed bin 205. The air intake cooling mechanism 4 includes an air intake connecting bin 401, which connects the air intake guiding pipeline 403 and the closed cooling bin 501, so that the air in the closed cooling bin 501 can enter the air intake guiding pipeline 403.

[0073] Among them, an air intake dust-proof net 402 is fixedly installed in the air intake connecting bin 401, which can reduce the entry of external dust into the air intake guiding pipeline 403, improve the cleanliness above the circulating cooling plate 206, and ensure that the heat dissipation effect of the circulating cooling plate 206 is not affected.

[0074] In addition, an air intake guiding pipeline 403 is installed between the air intake connecting bin 401 and the circulating closed bin 205, which can connect the air intake connecting bin 401 and the circulating closed bin 205, so that the air in the air intake connecting bin 401 can enter the circulating closed bin 205. At the same time, it facilitates the installation of the air intake fan 404. The air intake guiding pipeline 403 is arranged through the air intake connecting bin 401 and the circulating closed bin 205.

[0075] As Figures 1 to 7 shown, an air intake fan 404 is provided in the air intake guiding pipeline 403, which can drive the air in the air intake guiding pipeline 403 by rotation, so that the air in the air intake guiding pipeline 403 enters the circulating closed bin 205 and is discharged from the air intake and exhaust net 407 to form an air flow.

[0076] In addition, a pair of air intake brackets 405 are installed between the air intake fan 404 and the air intake guiding pipeline 403, which can position the air intake fan 404, ensure the balance of the air intake fan 404, improve the stability of the air intake fan 404, and the air intake fan 404 is arranged through the air intake brackets 405 and the air intake connecting bin 401.

[0077] In addition, an intake motor 406 is fixedly installed on the intake connection chamber 401, which improves the stability of the intake motor 406 and can drive the rotation of the intake fan 404, providing corresponding power for the rotation of the intake fan 404. The intake motor 406 is fixedly connected to the intake fan 404.

[0078] Wherein, intake and exhaust nets 407 are fixedly installed on both sides of the circulation closed chamber 205, facilitating the discharge of air and providing a corresponding passage for the discharge of air. An exhaust groove matching the intake and exhaust nets 407 is drilled on the circulation closed chamber 205.

[0079] As Figures 1 to 9 shown, a pair of closed cooling mechanisms 5 are fixedly installed on the upper side of the circulation closed chamber 205. The closed cooling mechanism 5 includes a closed cooling chamber 501. Air can enter the intake connection chamber 401 from the closed cooling chamber 501. The closed cooling chamber 501 is arranged through the intake connection chamber 401.

[0080] Wherein, a number of evenly distributed closed rotating hinges 502 are rotatably installed on the closed cooling chamber 501, which can be rotated by control to close the closed cooling chamber 501 or open it at a certain angle.

[0081] In addition, a closed rotating pulley 503 is fixedly installed on the closed rotating hinge 502, which can be driven by the closed sliding rack 504 to rotate, thereby driving the rotation of the closed rotating hinge 502. A closed sliding rack 504 is slidably installed in the closed cooling chamber 501, which can drive the rotation of the closed rotating pulley 503 through friction.

[0082] Wherein, a closed anti-wear pad 505 is fixedly installed on the side of the closed sliding rack 504 close to the closed rotating pulley 503, which improves the friction between the closed sliding rack 504 and the closed rotating pulley 503 and improves the precision of the closed sliding rack 504 driving the closed rotating pulley 503.

[0083] As Figures 1 to 10 shown, a closed motor 506 is fixedly installed on the closed cooling chamber 501, which can drive the rotation of the closed power gear 507 and provide corresponding power for the rotation of the closed power gear 507. The closed motor 506 is arranged through the closed cooling chamber 501.

[0084] In addition, a closed power gear 507 is fixedly installed on the closed motor 506, which can drive the sliding of the closed sliding rack 504, enabling the closed sliding rack 504 to better drive the rotation of a plurality of closed rotating pulleys 503. The closed power gear 507 is meshed with the closed sliding rack 504.

[0085] AsFigures 1 to 8 As shown, a method for controlling an unmanned aerial vehicle (UAV) engine, the method comprising: a temperature sensor 102 constantly detecting the operating temperature of the engine body 1 and transmitting it, a control box 101 receiving the temperature data transmitted by the temperature sensor 102, the control box 101 determining whether to activate an intake air cooling mechanism 4 and an enclosed cooling mechanism 5, and sending instructions to the intake air cooling mechanism 4 and the enclosed cooling mechanism 5. After the intake air cooling mechanism 4 and the enclosed cooling mechanism 5 are activated, the heat dissipation of a circulating cooling mechanism 2 can be enhanced, and the heat dissipation efficiency of the engine body 1 can be improved. After the intake air cooling mechanism 4 and the enclosed cooling mechanism 5 are closed, the heat dissipation inside the engine body 1 can be reduced.

[0086] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above-described exemplary embodiments, and without departing from the spirit or basic characteristics of the present invention, the present invention can be implemented in other specific forms. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present invention. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0087] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An unmanned aerial vehicle engine control device, characterized in that: include: An engine body, on which a control box and a temperature sensor are fixedly mounted; A circulating cooling mechanism is fixedly mounted on the upper side of the engine body, the circulating cooling mechanism comprises a circulating containing chamber, a circulating coolant is arranged in the circulating containing chamber, a circulating partition plate is fixedly mounted in the circulating containing chamber, a circulating pressure plate is fixedly mounted on the circulating partition plate, a circulating closed chamber is fixedly mounted on the circulating containing chamber, a circulating cooling plate is fixedly mounted in the circulating closed chamber, and a plurality of evenly distributed circulating vacuum chambers are fixedly mounted in the circulating containing chamber; A separation pressure mechanism is fixedly installed in the circulation containing chamber; An air intake cooling mechanism is provided on the upper side of the circulating closed chamber; A pair of closed cooling mechanisms are fixedly installed on the upper side of the circulating closed chamber.

2. The UAV engine control device according to claim 1, characterized in that: The circulation partition plate is provided with a positioning groove matching the circulation pressure plate, the circulation vacuum chamber is provided with circulation alcohol, and the circulation vacuum chamber is fixedly provided with a plurality of evenly distributed circulation contact fins.

3. The UAV engine control device according to claim 2, characterized in that: A plurality of evenly distributed circulating contact heat absorbing rods are fixedly installed on one side of the circulating cooling plate close to the circulating dividing plate, and a plurality of evenly distributed circulating air cooling fins are fixedly installed on one side of the circulating cooling plate away from the circulating contact heat absorbing rods.

4. The UAV engine control device according to claim 3, characterized in that: The separation pressure mechanism comprises a separation axis rod, a separation pressure plate is rotatably mounted outside the separation axis rod, a separation rotation spring is mounted between the separation axis rod and the separation pressure plate, and a rotation groove matching the separation pressure plate is bored on the circulation pressure plate.

5. The UAV engine control device according to claim 4, characterized in that: A separation positioning block is fixedly installed in the circulation containing bin, and a separation attraction magnet is fixedly installed on the separation positioning block. The separation attraction magnet matches the separation pressure plate.

6. The UAV engine control device according to claim 1, characterized in that: The air intake cooling mechanism includes an air intake connecting chamber, in which an air intake dust blocking net is fixedly installed, an air intake guide pipe is installed between the air intake connecting chamber and the circulation closed chamber, and the air intake guide pipe runs through the air intake connecting chamber and the circulation closed chamber.

7. The UAV engine control device according to claim 6, characterized in that: An intake fan is provided in the air intake guide duct, and a pair of air intake brackets are installed between the air intake fan and the air intake guide duct. The air intake fan passes through the air intake brackets and the air intake connecting chamber. An air intake motor is fixedly installed on the air intake connecting chamber, and the air intake motor is fixedly connected to the air intake fan. Air intake and exhaust nets are fixedly installed on both sides of the circulating closed chamber, and exhaust grooves matching the air intake and exhaust nets are opened on the circulating closed chamber.

8. The UAV engine control device according to claim 7, characterized in that: The closed cooling mechanism includes a closed cooling bin, which is arranged to penetrate the air intake connecting bin, and a plurality of evenly distributed closed rotating hinges are rotatably installed on the closed cooling bin, a closed rotating leather wheel is fixedly installed on the closed rotating hinge, a closed sliding gear rod is slidably installed in the closed cooling bin, and a closed anti-wear pad is fixedly installed on the side of the closed sliding gear rod close to the closed rotating leather wheel.

9. The UAV engine control device according to claim 8, characterized in that: A closed motor is fixedly mounted on the closed cooling bin, and the closed motor is arranged to penetrate the closed cooling bin. A closed power gear is fixedly mounted on the closed motor, and the closed power gear is meshed with a closed sliding gear rod.

10. A method for controlling an unmanned aerial vehicle engine, applied to the unmanned aerial vehicle engine control device according to any one of claims 1 to 9, characterized in that: The method includes: the temperature sensor constantly detects the operating temperature of the engine body and transmits it, the control box receives the temperature data transmitted by the temperature sensor, the control box determines whether to start the intake cooling mechanism and the closed cooling mechanism, and sends instructions to the intake cooling mechanism and the closed cooling mechanism. After the intake cooling mechanism and the closed cooling mechanism are turned on, the heat dissipation of the circulating cooling mechanism can be enhanced, and the heat dissipation efficiency of the engine body can be improved. After the intake cooling mechanism and the closed cooling mechanism are turned off, the heat dissipation in the engine body can be reduced.

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