An assembled heat dissipation device for unmanned helicopter

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, and specifically to an assembled heat dissipation device for an unmanned helicopter, comprising an air inlet hood, which is detachably mounted inside the unmanned helicopter, and the bottom of the air inlet hood extends to the bottom of the unmanned helicopter, the air inlet hood is a rectangular hollow structure without a cover, an air inlet is arranged at the bottom of the air inlet hood and on the side facing the head of the unmanned helicopter, an air outlet is arranged at the bottom of the air inlet hood and on the side facing the tail of the unmanned helicopter, and both the air inlet and the air outlet are located below the unmanned helicopter; the present invention realizes natural heat dissipation by airflow during flight through a unique design of the air inlet hood, and effectively improves the cooling effect of the heat dissipation plate, and secondly, since the motor and the battery are both arranged above the heat dissipation plate, the present invention can fully improve the heat dissipation efficiency of the aircraft power source and the power supply system without increasing the aircraft's flight energy consumption.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to an assembled heat dissipation device for an unmanned helicopter. Background Art

[0002] Nowadays, with the continuous development of unmanned helicopter technology in my country, unmanned helicopters are widely used in fields such as agronomy, meteorology, topographic exploration and military science. In the prior art, unmanned helicopters generally include mechanisms such as a cabin, fuselage, landing gear, power unit, transmission device, power supply system and rotor system. Among them, the power unit generally uses an electric motor, which transmits torque to the rotor system through the transmission device to control the operation of the rotor system, thereby controlling the flight direction and speed of the unmanned helicopter. The power supply system generally uses a rechargeable lithium battery to power the power unit and various electronic components inside the fuselage.

[0003] In the prior art, during the flight of an unmanned helicopter, the motor, battery, and electronic components inside the fuselage will generate heat, thereby increasing the temperature inside the fuselage. High temperature environment is one of the important factors that affect the operation of electronic products. Therefore, the heat dissipation effect of the unmanned helicopter directly affects the quality and safety performance of the product. At present, in response to the heat dissipation problem of unmanned helicopters, the traditional method is mainly to reduce the temperature by improving the heat dissipation efficiency of motors, lithium batteries, and electronic components, and optimizing the air flow design inside the fuselage. However, these methods often have certain shortcomings. For example, traditional heat dissipation methods mainly rely on increasing the heat dissipation area or using fans for forced cooling. Increasing the heat dissipation area will undoubtedly increase the weight of the aircraft, and using fans will increase the energy consumption of the aircraft and affect the aircraft's endurance.

[0004] In addition to the above-mentioned traditional heat dissipation methods, in the prior art, a patent with publication number CN209427043U proposes a heat dissipation structure for an unmanned helicopter, and the patented technical solution includes structures such as a heat dissipation fan, a heat dissipation water tank, a hose, a main propeller shaft, and a main propeller wheel. The technical solution is connected by a transmission between the main propeller shaft and the main propeller wheel, and the main propeller shaft and the heat dissipation fan are connected by a transmission between the main propeller wheel, so that when the engine transmits power to the unmanned helicopter, it can drive the heat dissipation fan to rotate through its own mechanical structure, and help the heat dissipation water tank to quickly dissipate heat after absorbing the engine heat through the hose. The patented technical solution drives the heat dissipation fan to rotate through the rotation of the propeller, without providing an additional power source, so it can improve the heat dissipation efficiency of the aircraft without increasing the energy consumption of the aircraft, and overcomes the defects of the traditional heat dissipation method.

[0005] However, the above heat dissipation method can only dissipate heat for the power source or a single component inside the aircraft, and cannot dissipate heat well for the electronic components and power supply system inside the aircraft; in addition, the above method will also increase the rotation resistance of the main propeller shaft, which may affect the flight stability. In order to overcome the various defects of the existing heat dissipation methods of unmanned helicopters, we propose an assembled heat dissipation device for unmanned helicopters. Summary of the invention

[0006] The object of the present invention is to provide an assembled heat dissipation device for an unmanned helicopter, so as to solve the problems raised in the above-mentioned background technology.

[0007] The present invention is realized by the following technical scheme: an assembled heat dissipation device for an unmanned helicopter, comprising: an air inlet cover, the air inlet cover is detachably mounted inside the unmanned helicopter, and the bottom of the air inlet cover extends to the bottom of the unmanned helicopter, the air inlet cover is a rectangular hollow coverless structure, the bottom of the air inlet cover and the side facing the head of the unmanned helicopter are provided with an air inlet, the bottom of the air inlet cover and the side facing the tail of the unmanned helicopter are provided with an air outlet, and the air inlet and the air outlet are both located below the unmanned helicopter;

[0008] A heat sink, the heat sink is located inside the air inlet hood and is fixedly connected to the air inlet hood, a plurality of heat sinks are protruding from the bottom surface of the heat sink, the arrangement direction of the heat sinks is consistent with the length direction of the air inlet hood, a motor compartment in the shape of a square tube is provided on the top surface of the heat sink, the motor compartment is used to place the motor of the unmanned helicopter, and the outer surface of the motor compartment is evenly provided with heat dissipation fins;

[0009] A battery compartment is integrally formed on the upper surface of the heat sink, an opening end of the battery compartment passes through the tail of the unmanned helicopter, a battery cover is detachably connected to the opening end of the battery compartment, and the battery cover is flush with the outer surface of the tail of the unmanned helicopter.

[0010] Optionally, first guide plates are symmetrically provided on the left and right ends of the lower surface of the heat sink and close to the air inlet, and the air inlet is located between the two first guide plates. A plurality of second guide plates are also provided on the lower surface of the heat sink and between the two first guide plates, and the arrangement directions of the second guide plates and the first guide plates are consistent with the length direction of the heat sink.

[0011] Optionally, two mounting holes are provided on the surface of the heat sink and between the two first guide plates, a rotating shaft is rotatably arranged in the two mounting holes, a guide plate is provided at the bottom end of the rotating shaft, a plurality of guide vanes are evenly arranged on the bottom surface of the guide plate, the length directions of the plurality of guide vanes are consistent, and a guide air duct is formed between two adjacent guide vanes.

[0012] Optionally, ventilation holes are symmetrically provided on the surface of the heat sink and on the left and right sides of the two guide plates, and a guide cover is provided on the lower surface of the heat sink and at the position of the ventilation holes. When the guide plate is consistent with the length direction of the heat sink, the guide cover is located on the side of the guide plate. When the guide plate maintains an angle of 45° with the length direction of the heat sink, the guide air duct located at the edge of the guide plate is aligned with the guide cover.

[0013] Optionally, the top of the rotating shaft extends out to the top of the heat sink and is fixedly mounted with a driven gear. A driving mechanism for controlling the rotation of the two driven gears is also provided above the heat sink. The driving mechanism includes an electric push rod and a double-sided rack. The electric push rod is fixedly arranged on the heat sink, and the movable end of the electric push rod is fixedly connected to the double-sided rack. The double-sided rack extends between the two driven gears, and the two driven gears are both meshed with the double-sided rack.

[0014] Optionally, a temperature sensor and a controller are further provided inside the air inlet hood, a signal output end of the temperature sensor is connected to the controller, and a signal output end of the controller is connected to the electric push rod.

[0015] Optionally, the ends of several second guide plates close to the air inlet are aligned and distributed, the other ends of several second guide plates extend to a position close to the guide plate, and the bottom ends of the second guide plates are in contact with the bottom surface of the air inlet cover.

[0016] Optionally, a plurality of exhaust holes are formed through the surface of the battery cover, and the exhaust holes are communicated with the interior of the unmanned helicopter.

[0017] Optionally, the mounting hole is in the shape of a stepped hole that is smaller at the top and larger at the bottom, the diameter of the guide plate matches the bottom diameter of the mounting hole, the guide plate is located inside the mounting hole, and the bottom surface of the guide plate is flush with the lower surface of the heat sink.

[0018] Optionally, a plurality of heat conducting plates are protrudingly formed on the top surface of the battery compartment, and an arrangement direction of the heat conducting plates is consistent with a length direction of the heat sink.

[0019] Compared with the prior art, the present invention provides an assembled heat dissipation device for an unmanned helicopter, which has the following beneficial effects:

[0020] 1. The present invention realizes natural heat dissipation by airflow during flight through a unique air inlet cover design, which effectively improves the cooling effect of the heat sink. Secondly, since the motor and the battery are both arranged above the heat sink, the present invention can fully improve the heat dissipation efficiency of the aircraft power source and the power supply system without increasing the aircraft's flight energy consumption.

[0021] 2. When the guide plate in the present invention keeps tilted with the second guide plate, part of the airflow can pass under the heat sink, and the other part of the airflow can enter the interior of the fuselage. Therefore, the present invention can control the direction of the airflow according to the specific situation, and at the same time dissipate heat for the power source, power supply system and electronic components inside the fuselage of the aircraft.

[0022] 3. When the guide plate in the present invention is kept perpendicular to the second guide plate, the guide plate will prevent the airflow from passing under the heat sink, thereby preventing the airflow from dissipating heat and cooling the internal components of the unmanned helicopter. This ensures that the internal temperature of the unmanned helicopter can be maintained when working in cold seasons or high altitudes, thereby reducing the adverse effects of low temperature weather on the power supply system.

[0023] 4. The heat dissipation device in the present invention is detachably connected to the bottom of the unmanned helicopter, so it is easy to disassemble and assemble. In addition, the open end of the battery compartment runs through the tail of the unmanned helicopter, so the present invention can remove the battery without disassembling the heat dissipation device, which is convenient for the inspection or replacement of the battery. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the structure of the unmanned helicopter of the present invention;

[0025] Figure 2 It is a schematic diagram of the structure of the heat dissipation device of the present invention;

[0026] Figure 3 It is a schematic diagram of the structure of the heat sink of the present invention;

[0027] Figure 4 This is a schematic diagram of the back structure of the heat sink of the present invention;

[0028] Figure 5 This is a schematic diagram of another state of the back side of the heat sink of the present invention;

[0029] Figure 6 This is a top view of the back side of the heat sink of the present invention;

[0030] Figure 7 A top view of the back side of the heat sink of the present invention in another state;

[0031] Figure 8 It is a cross-sectional view of the structure of the heat dissipation device of the present invention;

[0032] Fig. 9 This is a schematic diagram of the structure of the air inlet cover of the present invention;

[0033] Fig.10 It is a schematic diagram of the rotating shaft structure of the present invention;

[0034] Fig.11 It is a schematic diagram of the battery cover structure of the present invention.

[0035] In the figure: 100, unmanned helicopter; 200, air inlet cover; 201, air inlet; 202, air outlet; 300, heat sink; 301, heat sink; 302, motor compartment; 303, heat sink; 304, first guide plate; 305, second guide plate; 306, mounting hole; 307, rotating shaft; 308, guide plate; 309, guide vane; 310, vent; 311, guide cover; 312, driven gear; 313, electric push rod; 314, double-sided rack; 400, battery compartment; 401, battery cover; 402, exhaust hole; 403, heat conductive sheet; 500, controller; 501, temperature sensor. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] See also Figure 1 - Fig.11 , an assembled heat dissipation device for an unmanned helicopter, comprising an air inlet cover 200, a heat dissipation plate 300 and a battery compartment 400, wherein the air inlet cover 200 is detachably installed inside the unmanned helicopter 100, and the bottom of the air inlet cover 200 extends to the bottom of the unmanned helicopter 100, the air inlet cover 200 is a rectangular hollow coverless structure, the bottom of the air inlet cover 200 and the side facing the head of the unmanned helicopter 100 are provided with an air inlet 201, the bottom of the air inlet cover 200 and the side facing the tail of the unmanned helicopter 100 are provided with an air outlet 202, and the air inlet 201 and the air outlet 202 are both located below the unmanned helicopter 100; it should be noted here that the bottom of the unmanned helicopter 100 has an opening for inserting the air inlet cover 200, and the air inlet cover 200 and the unmanned helicopter 100 are fixedly connected by bolts. When the unmanned helicopter 100 is in flight, since the air inlet 201 faces forward and the air outlet 202 faces backward, air flow can enter the air inlet cover 200 through the air inlet 201 and then be discharged through the air outlet 202 .

[0038] Furthermore, the heat sink 300 is located inside the air inlet cover 200 and is fixedly connected to the air inlet cover 200. The bottom surface of the heat sink 300 is protrudingly formed with a plurality of heat sinks 301, such as Figure 4As shown, the arrangement direction of the heat sink 301 is consistent with the length direction of the air inlet cover 200, and the top surface of the heat sink 300 is provided with a motor compartment 302 in the shape of a square tube. The motor compartment 302 is used to place the motor of the unmanned helicopter 100, and the outer surface of the motor compartment 302 is evenly provided with heat dissipation fins 303; the heat sink 300 is made of aluminum alloy, which has good thermal conductivity, and the motor compartment 302 and the heat sink 300 are an integrally formed structure. It should be noted that when the motor is placed in the motor compartment 302, in order to better conduct heat, the side and bottom of the motor should be coated with thermal conductive silicone grease, so that the heat generated by the motor can be better transferred to the heat sink 300.

[0039] Furthermore, the battery compartment 400 is integrally formed and arranged on the upper surface of the heat sink 300, and the opening end of the battery compartment 400 passes through the tail of the unmanned helicopter 100, and the opening end of the battery compartment 400 is detachably connected to a battery cover 401, such as Figure 2 As shown, the battery cover 401 is flush with the outer surface of the tail of the unmanned helicopter 100. The battery compartment 400 is composed of four surfaces: left and right side walls, an upper end surface, and a front end surface. The battery compartment 400 and the heat sink 300 together form a space for accommodating batteries, and the front end surface of the battery compartment 400 has two conductive contacts for corresponding positive and negative electrodes of the battery.

[0040] In addition, it should be noted that the tail of the unmanned helicopter 100 has a through hole for inserting the open end of the battery compartment 400, which is not shown in the figure. When the battery cover 401 is closed on the open end of the battery compartment 400, the battery cover 401 is also embedded in the through hole, and the outer surface of the battery cover 401 is flush with the outer surface of the tail of the unmanned helicopter 100. At the same time, the battery cover 401 and the battery compartment 400 are fixed by clamping or bolting.

[0041] It is worth mentioning that during the flight of the unmanned helicopter 100, the heat generated by the motor and the battery will be transferred to the heat sink 300, and the air flow enters from the air inlet 201 and is discharged from the air outlet 202, so the air flow can take away the heat on the heat sink 300, thereby reducing the heating efficiency of the motor and the battery.

[0042] On the other hand, first guide plates 304 are symmetrically provided on the left and right ends of the lower surface of the heat dissipation plate 300 and close to the air inlet 201. Figure 4As shown, the air inlet 201 is located between the two first guide plates 304, and a plurality of second guide plates 305 are provided on the lower surface of the heat sink 300 and between the two first guide plates 304. The arrangement directions of the second guide plates 305 and the first guide plates 304 are consistent with the length direction of the heat sink 300. Specifically, the width of the air inlet 201 is smaller than the spacing between the two first guide plates 304, and the airflow entering from the air inlet 201 will completely enter between the two first guide plates 304; in addition, the bottom ends of the first guide plates 304 and the second guide plates 305 are both in contact with the inner bottom surface of the air inlet cover 200, and one end of the first guide plate 304 is also in contact with the front end surface of the air inlet cover 200, so as to prevent the airflow from leaking from the bottom of the guide plate and ensure that the airflow completely passes through the gap between the first guide plates 304 and the second guide plates 305.

[0043] Furthermore, two mounting holes 306 are formed on the surface of the heat sink 300 and between the two first guide plates 304. Figure 5 As shown, a rotating shaft 307 is rotatably arranged in two mounting holes 306, a guide plate 308 is arranged at the bottom end of the rotating shaft 307, and a plurality of guide vanes 309 are evenly arranged on the bottom surface of the guide plate 308. The length directions of the plurality of guide vanes 309 are consistent, and a guide air duct is formed between two adjacent guide vanes 309, and the bottom surface of the guide plate 308 is flush with the lower surface of the heat sink 300. Specifically, the mounting hole 306 is a stepped hole shape with a small top and a large bottom, the rotating shaft 307 is rotatably connected in the mounting hole 306 through a bearing, and the guide plate 308 matches the lower end diameter of the mounting hole 306. In addition, as shown in FIG. Figure 6 As shown, the distance between the farthest ends of the two guide plates 308 is consistent with the distance between the two first guide plates 304 .

[0044] In addition, it should be noted that the ends of the plurality of second guide plates 305 close to the air inlet 201 are aligned and distributed, and the other ends of the plurality of second guide plates 305 extend to the position close to the guide plate 308, and the distance between the second guide plates 305 and the guide plate 308 does not exceed 1 cm; therefore, the plurality of second guide plates 305 are of different lengths, and when the length of the guide plate 309 is consistent with the length direction of the second guide plate 305, the airflow flowing through the second guide plate 305 can completely enter the guide air duct. In addition, it should be noted that there is only a small gap between the guide plate 309 and the inner bottom surface of the air inlet cover 200, which is used to prevent the airflow from passing under the guide plate 309.

[0045] Furthermore, ventilation holes 310 are symmetrically provided on the surface of the heat dissipation plate 300 and located on the left and right sides of the two guide plates 308, and a guide cover 311 is provided on the lower surface of the heat dissipation plate 300 and located at the position of the ventilation holes 310. Figure 5As shown, when the guide plate 309 is aligned with the heat sink 300 in length direction, the guide cover 311 is located on the side of the guide plate 309. When the guide plate 309 maintains a 45° angle with the heat sink 300 in length direction, the guide air duct located at the edge of the guide plate 308 can be aligned with the guide cover 311. Figure 6 Specifically, there are two vents 310, the height of the air guide 311 is equal to the height of the air guide plate 309, and the side of the air guide 311 facing the air guide plate 308 is inclined. When part of the air guide duct is aligned with the air guide 311, the air flow can pass through the vents 310 and enter the top of the heat sink 300 through the action of the air guide 311, thereby helping to take away the heat inside the unmanned helicopter 100.

[0046] In addition, the top of the rotating shaft 307 extends to the top of the heat sink 300 and is fixedly mounted with a driven gear 312. A driving mechanism for controlling the rotation of the two driven gears 312 is also provided above the heat sink 300. The driving mechanism includes an electric push rod 313 and a double-sided rack 314. The electric push rod 313 is fixedly arranged on the heat sink 300. The movable end of the electric push rod 313 is fixedly connected to the double-sided rack 314. The double-sided rack 314 extends between the two driven gears 312, and the two driven gears 312 are both meshed with the double-sided rack 314. Therefore, the electric push rod 313 can directly control the forward and backward sliding of the double-sided rack 314, thereby indirectly controlling the relative rotation of the two guide plates 308 to adjust the direction of the guide vane 309.

[0047] Specifically, a temperature sensor 501 and a controller 500 are further provided inside the air inlet cover 200. The signal output end of the temperature sensor 501 is connected to the controller 500, and the signal output end of the controller 500 is connected to the electric push rod 313. A plurality of exhaust holes 402 are provided on the surface of the battery cover 401, such as Figure 8 As shown, the exhaust hole 402 is connected to the interior of the unmanned helicopter 100, and the exhaust hole 402 is used to exhaust the air inside the unmanned helicopter 100; the upper surface of the battery compartment 400 is also protruding with a plurality of heat conductive sheets 403, and the arrangement direction of the heat conductive sheets 403 is consistent with the length direction of the heat sink 300.

[0048] It should be noted that the temperature sensor 501 is set with a high temperature threshold. When the air temperature inside the unmanned helicopter 100 is higher than the high temperature threshold set by the temperature sensor 501, the temperature sensor 501 transmits a signal to the controller 500. The controller 500 controls the electric push rod 313 to operate, so that the guide plate 309 maintains a 45° angle with the length direction of the second guide plate 305, allowing part of the air to enter the top of the heat sink 300, thereby helping to take away the heat of the internal components of the unmanned helicopter 100.

[0049] It should be noted that the temperature sensor 501 is also set with a low temperature threshold. When the air temperature inside the unmanned helicopter 100 is lower than the set low temperature threshold, the controller 500 will control the electric push rod 313 to move, so that the guide vane 309 and the second guide plate 305 remain vertical. Figure 7 In the posture shown, the guide plate 309 will prevent external air from entering the bottom of the heat sink 300.

[0050] In summary, in the specific application process of this embodiment, in the initial state, the length direction of the guide plate 309 is consistent with the length direction of the second guide plate 305. At this time, the guide plate 309 does not affect the flow of air below the heat sink 300. The air enters from the air inlet 201 and is discharged from the air outlet 202, which is used to cool the heat sink 300 and reduce the heating efficiency of the motor and the battery. When the continuous flight time of the unmanned helicopter 100 continues to increase, the electronic components inside the unmanned helicopter 100 will also generate heat, and the heat inside the unmanned helicopter 100 will continue to increase. When its temperature exceeds the threshold of the temperature sensor 501, the controller 500 will control the electric push rod 313 to move, so that the guide plate 309 rotates 45°. At this time, part of the airflow entering the air inlet cover 200 continues to flow below the heat sink 300, while the other part of the airflow enters the top of the heat sink 300 through the vent 310 and is discharged from the exhaust hole 402 to take away the heat inside the unmanned helicopter 100.

[0051] In addition, when the unmanned helicopter 100 flies in a cold season, or when the unmanned helicopter 100 flies to a higher altitude area, the ambient temperature is low at this time, and the low temperature will inevitably affect the stability of the battery power supply and the battery life. Therefore, in this case, when the temperature is lower than the low temperature threshold of the temperature sensor 501, the controller 500 can control the guide plate 308 to rotate 90°, such as Figure 7 In the state shown, the guide plate 309 can prevent external air from entering the bottom of the heat sink 300, thereby avoiding the adverse effect of the low temperature environment on the battery power supply system.

[0052] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0053] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An assembled heat dissipation device for an unmanned helicopter, characterized in that: include: An air inlet cover (200), the air inlet cover (200) being detachably mounted inside the unmanned helicopter (100), and the bottom of the air inlet cover (200) extending below the unmanned helicopter (100), the air inlet cover (200) being a rectangular hollow structure without a cover, an air inlet (201) being provided at the bottom of the air inlet cover (200) and facing the head of the unmanned helicopter (100), and an air outlet (202) being provided at the bottom of the air inlet cover (200) and facing the tail of the unmanned helicopter (100), and both the air inlet (201) and the air outlet (202) being located below the unmanned helicopter (100); A heat sink (300), the heat sink (300) being located inside the air inlet cover (200) and fixedly connected to the air inlet cover (200), a plurality of heat sinks (301) being protrudingly formed on the bottom surface of the heat sink (300), the arrangement direction of the heat sinks (301) being consistent with the length direction of the air inlet cover (200), a motor compartment (302) in the shape of a square tube being provided on the top surface of the heat sink (300), the motor compartment (302) being used to accommodate the motor of the unmanned helicopter (100), and heat sink fins (303) being evenly provided on the outer surface of the motor compartment (302); a battery compartment (400), the battery compartment (400) being integrally formed and arranged on the upper surface of the heat dissipation plate (300), the opening end of the battery compartment (400) penetrating the tail of the unmanned helicopter (100), the opening end of the battery compartment (400) being detachably connected to a battery cover (401), the battery cover (401) being flush with the outer surface of the tail of the unmanned helicopter (100); First guide plates (304) are symmetrically provided on the left and right ends of the lower surface of the heat dissipation plate (300) and on one side close to the air inlet (201); the air inlet (201) is located between the two first guide plates (304); a plurality of second guide plates (305) are also provided on the lower surface of the heat dissipation plate (300) and between the two first guide plates (304); the arrangement directions of the second guide plates (305) and the first guide plates (304) are consistent with the length direction of the heat dissipation plate (300); Two mounting holes (306) are provided on the surface of the heat dissipation plate (300) and are located between the two first guide plates (304); a rotating shaft (307) is rotatably arranged in the two mounting holes (306); a guide plate (308) is provided at the bottom end of the rotating shaft (307); a plurality of guide vanes (309) are evenly arranged on the bottom surface of the guide plate (308); the length directions of the plurality of guide vanes (309) are consistent, and a guide air duct is formed between two adjacent guide vanes (309); Ventilation holes (310) are symmetrically provided on the surface of the heat sink (300) and located on the left and right sides of the two guide plates (308); a guide cover (311) is provided on the lower surface of the heat sink (300) and located at the position of the vents (310); when the guide plate (309) and the heat sink (300) are aligned in length direction, the guide cover (311) is located on the side of the guide plate (309); when the guide plate (309) and the heat sink (300) maintain an angle of 45° in length direction, the guide air duct located at the edge of the guide plate (308) is aligned with the guide cover (311); The top of the rotating shaft (307) extends above the heat sink (300) and is fixedly sleeved with a driven gear (312); a driving mechanism for controlling the rotation of the two driven gears (312) is also provided above the heat sink (300); the driving mechanism comprises an electric push rod (313) and a double-sided rack (314); the electric push rod (313) is fixedly arranged on the heat sink (300); the movable end of the electric push rod (313) is fixedly connected to the double-sided rack (314); the double-sided rack (314) extends between the two driven gears (312); and the two driven gears (312) are both meshed with the double-sided rack (314); A temperature sensor (501) and a controller (500) are also provided inside the air inlet cover (200); a signal output end of the temperature sensor (501) is connected to the controller (500), and a signal output end of the controller (500) is connected to the electric push rod (313).

2. The assembled heat dissipation device for an unmanned helicopter according to claim 1, characterized in that: The ends of the plurality of second guide plates (305) close to the air inlet (201) are aligned and distributed, the other ends of the plurality of second guide plates (305) are extended to a position close to the guide plate (308), and the bottom ends of the second guide plates (305) are in contact with the bottom surface of the air inlet cover (200).

3. The assembled heat dissipation device for an unmanned helicopter according to claim 1, characterized in that: A plurality of exhaust holes (402) are provided through the surface of the battery cover (401), and the exhaust holes (402) are communicated with the interior of the unmanned helicopter (100).

4. The assembled heat dissipation device for an unmanned helicopter according to claim 1, characterized in that: The mounting hole (306) is in the shape of a stepped hole that is smaller at the top and larger at the bottom; the diameter of the guide plate (308) matches the bottom diameter of the mounting hole (306); the guide plate (308) is located inside the mounting hole (306), and the bottom surface of the guide plate (308) is flush with the lower surface of the heat sink (300).

5. The assembled heat dissipation device for an unmanned helicopter according to claim 1, characterized in that: A plurality of heat conducting sheets (403) are protrudingly formed on the top surface of the battery compartment (400), and the arrangement direction of the heat conducting sheets (403) is consistent with the length direction of the heat dissipation plate (300).

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