CN219809064U

CN219809064U - Heat radiation system and unmanned aerial vehicle

Info

Publication number: CN219809064U
Application number: CN202321970363.9U
Authority: CN
Inventors: 梁玉成; 王金林; 刘焯
Original assignee: Beijing Hangyi Technology Co ltd
Current assignee: Beijing Hangyi Technology Co ltd
Priority date: 2023-07-25
Filing date: 2023-07-25
Publication date: 2023-10-10
Anticipated expiration: 2033-07-25

Abstract

The utility model discloses a heat dissipation system and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The heat radiation system comprises a liquid cooling heat radiation assembly, an intercooling heat radiation assembly and an oil cooling heat radiation assembly. The liquid cooling radiator and the liquid cooling pipe of the liquid cooling radiating component form a liquid cooling loop for circulating cooling liquid, and the liquid cooling loop is used for absorbing heat from the engine. The intercooler is used to cool the gas that is boosted by the turbocharger to enter the intake port of the engine. The oil cooling radiator and the oil cooling pipe of the oil cooling radiating component are used for forming an oil cooling loop together with the engine for engine oil circulation, and the oil cooling radiator is used for cooling the engine oil. The heat dissipation system comprises three different heat dissipation components, and is used for jointly dissipating heat of the engine or medium (such as engine oil and air) entering the engine, so that the engine can be effectively prevented from being overheated, and the stable operation of the unmanned aerial vehicle can be maintained. The unmanned aerial vehicle engine and the heat dissipation system comprising the unmanned aerial vehicle engine are provided.

Description

Heat radiation system and unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a heat dissipation system and an unmanned aerial vehicle.

Background

In the driving process of the unmanned aerial vehicle, the engine can generate more heat, and the heat dissipation system is generally arranged to dissipate heat of the engine of the unmanned aerial vehicle so as to avoid abnormal operation caused by overheating. However, the existing heat dissipation system has a single heat dissipation mode, so that the heat dissipation effect is poor.

Disclosure of Invention

The utility model aims to provide a heat dissipation system and an unmanned aerial vehicle, which have better heat dissipation performance.

Embodiments of the present utility model are implemented as follows:

in a first aspect, the present utility model provides a heat dissipation system applied to an unmanned aerial vehicle, the unmanned aerial vehicle including an engine, the engine being provided with an intake port and a turbocharger, comprising:

the liquid cooling heat dissipation assembly comprises a liquid cooling radiator and a liquid cooling pipe, wherein the liquid cooling radiator and the liquid cooling pipe form a liquid cooling loop for circulating cooling liquid, the cooling liquid is used for absorbing heat from an engine of the unmanned aerial vehicle, and the liquid cooling radiator is used for cooling the cooling liquid;

an intercooler assembly including an intercooler for cooling gas pressurized by the turbocharger to enter an intake port of the engine;

the oil cooling heat dissipation assembly comprises an oil cooling radiator and an oil cooling pipe, wherein the oil cooling radiator and the oil cooling pipe are used for forming an oil cooling loop with an engine for engine oil circulation, and the oil cooling radiator is used for cooling engine oil.

In an alternative embodiment, the heat dissipation system further comprises a fan for dissipating heat from at least one of the liquid-cooled radiator, the intercooler radiator, and the oil-cooled radiator.

In an alternative embodiment, the intercooler further comprises an intercooler pipe connected to the intercooler for connecting the turbocharger, the intercooler and the intake port of the engine in series.

In an optional embodiment, the unmanned aerial vehicle further comprises a casing, the engine and the heat dissipation system are both arranged in the casing, at least one heat dissipation window is arranged on the casing, and the liquid cooling radiator, the middle cooling radiator and the oil cooling radiator correspond to the heat dissipation window in position.

In an optional embodiment, the unmanned aerial vehicle further comprises a frame body arranged in the shell, the shell is connected to the frame body, and the liquid cooling radiator, the middle cooling radiator and the oil cooling radiator are sequentially arranged at the top of the frame body; the heat dissipation window comprises an upper heat dissipation window arranged at the top of the shell, and the positions of the liquid cooling radiator, the middle cooling radiator and the oil cooling radiator correspond to the positions of the upper heat dissipation window.

In an alternative embodiment, the liquid cooling heat dissipation assembly further comprises a cooling liquid overflow kettle arranged on the liquid cooling pipe, and a cooling liquid filling port is arranged at the top of the machine shell and used for exposing a kettle opening of the cooling liquid overflow kettle.

In an alternative embodiment, the liquid-cooled radiator, the intercooler radiator and the oil-cooled radiator are arranged in sequence from the rear to the front in the front-rear direction of the unmanned aerial vehicle.

In a second aspect, the present utility model provides an unmanned aerial vehicle, comprising an engine, a chassis, and a heat dissipation system according to any of the embodiments of the first aspect.

In an alternative embodiment, the air outlet direction of the fan faces the heat dissipation window.

In an alternative embodiment, the enclosure includes a front shell, a rear shell, an upper shell, and two side shells spaced apart in the left-right direction of the unmanned aerial vehicle, the front shell, the rear shell, and the upper shell are all detachably connected with the two side shells, and the front shell and the rear shell are spaced apart in the front-rear direction of the unmanned aerial vehicle.

In an alternative embodiment, an upper heat dissipation window is arranged on the upper shell, and a first guide fin is arranged in the upper heat dissipation window and used for guiding air flow outside the shell into the shell.

In an alternative embodiment, the outside of the upper shell is provided with an air inlet structure, the air inlet structure forms an air inlet communicated with the inside of the shell, and the air inlet faces the front of the unmanned aerial vehicle.

In an alternative embodiment, the air inlet structure further forms an air inlet channel communicating the air inlet with the interior of the housing, and a first filter is disposed in the air inlet channel to filter air entering the interior of the housing through the air inlet channel.

In an alternative embodiment, the front housing is provided with a front heat dissipation window communicating with the interior of the housing.

In an alternative embodiment, a second filter is disposed within the front heat dissipation window to filter air entering the interior of the cabinet through the front heat dissipation window.

In an alternative embodiment, a second deflector fin is disposed in the front heat dissipation window, and the second deflector fin is used for guiding the air flow outside the front shell into the machine shell.

In an alternative embodiment, the rear housing is provided with a rear heat dissipation window communicating with the interior of the housing.

In an alternative embodiment, a third filter is disposed within the rear heat dissipation window.

In an alternative embodiment, a third guide fin is disposed in the rear heat dissipation window, and the third guide fin is used for guiding the airflow inside the rear shell to flow out of the machine shell.

In an alternative embodiment, the unmanned aerial vehicle is a tandem twin-rotor unmanned helicopter.

The embodiment of the utility model has the beneficial effects that:

the heat radiation system comprises a liquid cooling heat radiation component, an intercooling heat radiation component and an oil cooling heat radiation component. The liquid cooling heat dissipation assembly comprises a liquid cooling radiator and a liquid cooling pipe, wherein the liquid cooling radiator and the liquid cooling pipe form a liquid cooling loop for cooling liquid to circulate, the cooling liquid is used for absorbing heat from the engine, and the cooling liquid releases heat when carrying heat to flow through the liquid cooling radiator. The intercooler serves to cool the gas that is supercharged by the turbocharger to enter the intake port of the engine, thereby avoiding excessive heat load caused by the too high temperature of the compressed gas entering the engine. The oil cooling heat dissipation assembly comprises an oil cooling radiator and an oil cooling pipe, wherein the oil cooling radiator and the oil cooling pipe are used for forming an oil cooling loop with an engine for engine oil circulation, and the oil cooling radiator is used for cooling engine oil. Because the heat dissipation system comprises three different heat dissipation components, the heat dissipation system can jointly dissipate heat of an engine or a medium (such as engine oil and air) entering the engine, can effectively avoid overheat of the engine and maintains stable operation of the unmanned aerial vehicle.

The unmanned aerial vehicle provided by the utility model comprises the engine, the shell and the heat radiation system, so that the problem of overheating is not easy to occur, and the unmanned aerial vehicle can maintain stable operation for a long time.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic view of a unmanned aerial vehicle fuselage in an embodiment of the present utility model;

FIG. 2 is a schematic view of an unmanned aircraft fuselage with an upper shell removed in accordance with an embodiment of the present utility model;

FIG. 3 is a schematic view of an assembly of a fuselage frame, a heat dissipation system, and an engine at a first perspective in accordance with an embodiment of the present utility model;

FIG. 4 is a schematic view of an assembly of a fuselage frame, a heat dissipation system, and an engine at a second perspective in accordance with an embodiment of the present utility model;

FIG. 5 is a schematic view of an upper shell in an embodiment of the utility model;

FIG. 6 is a schematic diagram of an air intake structure 110 according to an embodiment of the present utility model;

FIG. 7 is a schematic view of a front housing 400 in accordance with an embodiment of the present utility model;

fig. 8 is a schematic view of a rear housing 500 in an embodiment of the utility model.

Icon 100-case; 101-front rotor opening; 102-rear rotor opening; 110-an upper shell; 111-an air intake structure; 112-air inlet; 113-an intake passage; 114-a first filter; 115-upper heat dissipation window; 116-first deflector fins; 117-reinforcing the beam; 118-a coolant filler; 120-side shells; 130-front shell; 131-front heat dissipation window; 132-a second filter; 133-second deflector fins; 134-radar window; 140-backshells; 141-a rear heat dissipation window; 142-a third filter; 143-third deflector fins; 144-indicator lights; 200-fuselage frames; 300-engine; 310-a turbocharger; 400-liquid cooling radiator; 410-liquid-cooled tube; 420-a fan; 500-intercooler; 510-a middle cooling tube; 600-oil-cooled radiator; 610-oil-cooled tube; 620-an engine oil pot; 700-landing gear.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present utility model and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

Existing unmanned engines are typically internal combustion engines that intake air for fuel combustion during operation. During engine operation, a large amount of heat is generated. If the heat is not effectively removed, the heat accumulated in the unmanned aerial vehicle can cause overheat of the engine, and the normal operation of the engine is negatively influenced; and the whole temperature in the unmanned aerial vehicle is too high, so that the electronic device carried on the unmanned aerial vehicle can be failed. The unmanned aerial vehicle of the related art is provided with a heat dissipation system to assist in heat dissipation, but the heat dissipation form in the related art is single, for example, a heat dissipation hole is formed in a machine shell, and the engine cylinder body is directly purged and cooled by adopting air cooling or cooled by adopting water cooling. However, the heat dissipation effect of the single type is limited, and the effect of reducing the heat load of the engine is not obvious enough.

Therefore, the embodiment of the utility model provides a heat dissipation system and an unmanned aerial vehicle carrying the heat dissipation system, which are used for assisting in heat dissipation of an engine by arranging various heat dissipation components of different types, so that the heat load of the engine is reduced, overheating is avoided, and the unmanned aerial vehicle can stably operate for a long time.

Fig. 1 is a schematic view of a unmanned aerial vehicle fuselage in an embodiment of the present utility model; FIG. 2 is a schematic view of the unmanned aerial vehicle body with the upper shell 110 removed according to an embodiment of the present utility model; FIG. 3 is a schematic diagram illustrating an assembly of a fuselage frame 200, a heat dissipation system, and an engine 300 at a first perspective in accordance with an embodiment of the present utility model; fig. 4 is a schematic diagram illustrating an assembly of the frame 200, the heat dissipation system, and the engine 300 at a second viewing angle according to an embodiment of the present utility model. As shown in fig. 1 to 4, the unmanned aerial vehicle provided in the present embodiment includes a chassis 100, a fuselage frame 200, an engine 300, a heat dissipation system, a landing gear 700, and a propeller (omitted in the drawings). The frame 200, the engine 300 and the heat dissipation system are arranged in the casing 100, the propeller is arranged outside the casing 100 and is in transmission connection with the engine 300 through a transmission mechanism, and an air inlet port and a turbocharger 310 are arranged on the engine 300. Specifically, the unmanned aerial vehicle of this embodiment is a tandem double-rotor unmanned helicopter, which has two propellers that are disposed at intervals in the front-rear direction of the unmanned aerial vehicle. Front and rear ends of the casing 100 are provided with a front rotor opening 101 and a rear rotor opening 102, respectively, the front rotor opening 101 being used for mounting a front rotor assembly, and the rear rotor opening 102 being used for mounting a rear rotor assembly. Landing gear 700 is located below the fuselage, and is attached to the fuselage frame 200 for supporting the ground during takeoff and landing of the unmanned aerial vehicle.

In the embodiment of the present utility model, the enclosure 100 includes a front shell 130, a rear shell 140, an upper shell 110, and two side shells 120, where the two side shells 120 are spaced apart in the left-right direction of the unmanned aerial vehicle, and the front shell 130, the rear shell 140, and the upper shell 110 are detachably connected (e.g., linked by screws) to the two side shells 120, and the front shell 130 and the rear shell 140 are spaced apart in the front-rear direction of the unmanned aerial vehicle. The front and rear directions of the unmanned aerial vehicle are the front and rear directions of the unmanned aerial vehicle during normal cruising flight, and correspond to directions indicated by arrows a and b in the figure respectively; the left and right directions of the unmanned aerial vehicle are the directions of the left and right sides of the unmanned aerial vehicle during normal cruising flight, and correspond to the directions indicated by arrows c and d in the figure respectively; the up and down directions of the unmanned aerial vehicle are consistent with the extending direction of the axis of the rotor wing of the unmanned aerial vehicle, and the up and down directions respectively correspond to directions indicated by arrows e and f in the figure. The front case 130, the rear case 140, the upper case 110, and the two side cases 120 together define a cavity, and the body frame 200, the engine 300, and the heat dissipation system are enclosed in the cavity, thereby protecting the body frame 200, the engine 300, and the heat dissipation system. Meanwhile, the shell 100 has a better pneumatic appearance, and can reduce the resistance of the unmanned aerial vehicle during flight.

In the embodiment of the present utility model, the body frame 200 functions as a skeleton in the unmanned aerial vehicle, and the casing 100 is connected to the body frame 200. The engine 300 and the heat dissipation system are both provided to the body frame 200.

The heat dissipation system comprises a liquid cooling heat dissipation assembly, an intercooling heat dissipation assembly and an oil cooling heat dissipation assembly. The liquid cooling heat dissipation assembly is used for performing auxiliary heat dissipation on the cylinder body of the engine 300, the intercooling heat dissipation assembly is used for cooling gas to be introduced into the engine 300, and the oil cooling heat dissipation assembly is used for cooling engine oil. Three different types of heat dissipating components can reduce the thermal load of engine 300 from multiple angles, avoiding overheating thereof.

In the present embodiment, the liquid-cooled radiator assembly includes a liquid-cooled radiator 400 and a liquid-cooled tube 410, the liquid-cooled radiator 400 and the liquid-cooled tube 410 form a liquid-cooled loop in which a cooling liquid for absorbing heat from the engine 300 is circulated, and the liquid-cooled radiator 400 is used for cooling the cooling liquid. In the present embodiment, the liquid cooling pipe 410 is in contact with the engine 300, and the cooling liquid absorbs heat from the engine 300 when passing through the liquid cooling pipe 410 in contact with the engine 300 during circulation of the cooling liquid in the liquid cooling loop, and transfers heat to the surrounding air through the liquid cooling radiator 400 when the cooling liquid having absorbed a large amount of heat passes through the liquid cooling radiator 400, thus achieving heat dissipation of the engine 300. And the part of the hot air having absorbed the heat can flow out of the casing 100 through the heat dissipation window formed in the casing 100. The liquid-cooled radiator 400 of the present embodiment has a chamber for circulating a cooling liquid; optionally, heat dissipation fins may be disposed on the inner surface and/or the outer surface of the liquid-cooled radiator 400, thereby increasing the heat transfer area and improving the heat dissipation efficiency. The cooling liquid flowing in the liquid cooling heat dissipation assembly can be water or other fluid media.

Further, the heat dissipation system further includes a fan 420, and the fan 420 is configured to dissipate heat from at least one of the liquid-cooled radiator 400, the intercooler 500, and the oil-cooled radiator 600. Optionally, in this embodiment, the fan 420 is used to dissipate heat from the liquid-cooled radiator 400. The fan 420 can enhance the air flow around the liquid-cooled radiator 400, thereby increasing the speed of the air flow to take away the heat in the liquid-cooled radiator 400, and thus improving the heat dissipation efficiency.

In this embodiment, the liquid-cooled radiator 400 is disposed on top of the body frame 200. The fan 420 is an axial flow fan, the fan 420 is disposed on the heat radiating fins of the liquid cooling radiator 400, the air suction side of the fan 420 faces the liquid cooling radiator 400 downward, and the air outlet side of the fan 420 faces upward. The above arrangement can suck the hot air around the liquid-cooled radiator 400 and convey the hot air toward the top of the casing 100.

Further, the liquid cooling heat dissipation assembly further comprises a cooling liquid overflow kettle (not shown in the figure) arranged on the liquid cooling pipe 410, wherein a cooling liquid filling port 118 is arranged at the top of the casing 100, the cooling liquid filling port 118 is used for exposing a kettle opening of the cooling liquid overflow kettle, and the cooling liquid overflow kettle is used for filling cooling liquid. Specifically, in this embodiment, the coolant overflow kettle may be located at the top of the body frame 200 and have a kettle mouth facing upward, and the upper case 110 of the cabinet 100 is provided with a coolant filler port 118.

In the present embodiment, the intercooler assembly includes an intercooler 500, the intercooler 500 being used to cool the gas pressurized by the turbocharger 310 to enter the intake port of the engine 300. Further, the intercooler assembly further includes an intercooler pipe 510 connected to the intercooler 500, and the intercooler pipe 510 is used to connect the turbocharger 310, the intercooler 500, and the intake port of the engine 300 in series. Specifically, intercooler 500 is connected in series between an intake port of engine 300 and turbocharger 310, and intercooler 500 is used to cool gas that is pressurized by turbocharger 310 to enter the intake port of engine 300. Specifically, in the present embodiment, the air intake end of the intercooler 500 communicates with the turbocharger 310 through the intercooler pipe 510, and the air outlet end of the intercooler 500 communicates with the air intake port of the engine 300 through the intercooler pipe 510.

The turbocharger 310 increases the intake air amount of the engine 300 by means of active supercharging, thereby increasing the power of the engine 300. Because turbocharger 310 applies work to air compression, the compressed air may warm up, while high temperature air entering engine 300 may increase the thermal load of engine 300; and the higher the air temperature, the higher the pressure, which inhibits turbocharger 310 from delivering high-pressure gas to engine 300, so that the amount of intake air is limited and the power of engine 300 is difficult to further increase. In the present embodiment, the temperature of the gas entering the engine 300 can be reduced by cooling the high-temperature air output from the turbocharger 310, the thermal load of the engine 300 can be reduced, and the intake air can be increased, thereby increasing the power of the engine 300.

The intercooler 500 radiates heat by adopting an air-cooled cooling mode, and the temperature of the air inside the intercooler 500 is reduced by the air flow outside the intercooler 500. In the present embodiment, the intercooler 500 is disposed at the top end of the body frame 200, side by side with the liquid-cooled radiator 400. Optionally, a plurality of heat dissipating fins may be disposed on the inner side and/or the outer side of the intercooler 500 to increase the heat transfer area and improve the heat dissipation efficiency.

The oil-cooled radiator assembly includes an oil-cooled radiator 600 and an oil-cooled tube 610, the oil-cooled radiator 600, the oil-cooled tube 610, and the engine 300 forming an oil-cooled loop through which engine oil circulates, the oil-cooled radiator 600 being configured to cool engine oil. The engine oil absorbs heat in the engine 300, circulates along an oil-cooled loop to the oil-cooled radiator 600 outside the engine 300, and the oil-cooled radiator 600 transfers the heat of the engine oil to the outside air, so that the engine oil is cooled. The cooled engine oil is circulated along the oil cooling pipe 610 to the inside of the engine 300 for lubrication and heat absorption. In this embodiment, the oil cooling assembly further includes an oil can 620 disposed in the oil cooling loop, and engine oil is cooled by the oil cooling radiator 600, and then enters the oil can 620 to operate the engine 300, thereby forming a cycle. The sump 620 may be provided with a sump opening that may be opened or closed to facilitate replenishment of engine oil. In the present embodiment, the oil cooler 600 is also disposed at the top of the frame 200, and is disposed in parallel with the liquid-cooled radiator 400 and the intercooler 500.

In this embodiment, at least one heat dissipation window is disposed on the casing 100, and the positions of the liquid cooling radiator 400, the intercooler 500, and the oil cooling radiator 600 correspond to the positions of the heat dissipation windows. By such arrangement, the distance between each radiator (the liquid cooling radiator 400, the intercooler radiator 500 and the oil cooling radiator 600) and the radiating window can be reduced, the strength of gas convection near the radiator can be enhanced, so that high-temperature air flow absorbing heat from the radiator can be sent out from the radiating window as soon as possible, or the air flow entering from the radiating window can be directly purged to the radiator, thereby accelerating heat radiation.

In the present embodiment, the liquid-cooled radiator 400, the intercooler 500, and the oil-cooled radiator 600 are disposed in this order on top of the body frame 200. The heat dissipation window on the casing 100 includes an upper heat dissipation window 115 formed on the top of the casing 100, and the positions of the liquid cooling radiator 400, the middle cooling radiator 500 and the oil cooling radiator 600 correspond to those of the upper heat dissipation window 115. Optionally, the air outlet direction of the fan 420 faces the heat dissipation window, and when the fan 420 is used for dissipating heat from the liquid cooling radiator 400, the fan 420 is disposed on the liquid cooling radiator 400, and the air outlet direction of the fan 420 faces the upper heat dissipation window 115. In the present embodiment, the liquid-cooled radiator 400, the intercooler 500, and the oil-cooled radiator 600 are arranged in this order from the rear to the front in the front-rear direction of the unmanned aerial vehicle.

It should be appreciated that in alternative embodiments, the fans 420 may be disposed on each of the liquid-cooled radiator 400, the intercooler 500, and the oil-cooled radiator 600, and any one or more of the liquid-cooled radiator 400, the intercooler 500, and the oil-cooled radiator 600 may be configured to dissipate heat by the fans 420.

Fig. 5 is a schematic view of an upper shell 110 according to an embodiment of the present utility model. As shown in fig. 5, in the present embodiment, an upper heat dissipation window 115 is provided on the upper case 110. The upper heat dissipation window 115 communicates the inside and the outside of the cabinet 100, and can enhance gas exchange between the inside and the outside of the cabinet 100, thereby enhancing heat dissipation. The upper heat dissipation window 115 is located above each heat sink to face each heat sink in the up-down direction, so that the air flow entering from the upper heat dissipation window 115 can sweep each heat sink to take away heat.

The air inlet structure 111 is arranged on the outer side of the upper shell 110, the air inlet structure 111 forms an air inlet 112 communicated with the interior of the shell 100, and the air inlet 112 faces the front of the unmanned aerial vehicle. By providing the air inlet structure 111 and arranging the air inlet 112 towards the front of the unmanned aerial vehicle, the unmanned aerial vehicle can be enabled to be in cruise flight, and air flow is poured into the casing 100 through the air inlet 112. A large amount of external air flow enters the cabinet 100 to facilitate heat dissipation inside the cabinet 100. In this embodiment, the air inlet 112 is located in front of the upper heat dissipation window 115 along the front-rear direction of the unmanned aerial vehicle, so that the air flow entering through the air inlet 112 can purge each radiator, thereby taking away heat.

Fig. 6 is a schematic view of an air intake structure 111 according to an embodiment of the present utility model. As shown in fig. 5 and 6, the air inlet structure 111 is a cylinder, the cylinder extends along the front-back direction of the unmanned aerial vehicle, the front end of the cylinder forms an air inlet 112, and the rear end is communicated with an opening formed in the upper shell 110, so that the air inlet 112 is communicated with the interior of the casing 100.

Further, the air intake structure 111 forms an air intake passage 113 communicating the air intake 112 with the interior of the casing 100, and a first filter 114 is disposed in the air intake passage 113 to filter air entering the interior of the casing 100 through the air intake passage 113. By providing the first filter 114, it is possible to prevent foreign matters such as dust and leaves from entering the casing 100 along with the airflow, and thus, the operation of the unmanned aerial vehicle is affected. Optionally, the first filter 114 is a wire mesh; in other embodiments, the first filter 114 may be a grating or other member with a certain filtering and intercepting function.

Further, a plurality of first guide fins 116 are disposed in the upper heat dissipation window 115, and the first guide fins 116 are used for guiding the air flow outside the upper shell 110 into the casing 100, so as to enhance the air convection intensity in the casing 100, and further enhance the heat dissipation effect. Specifically, the first fin 116 is in a slat shape, the length direction of the first fin is consistent with the left-right direction of the unmanned aerial vehicle, and the plurality of first fins 116 are arranged at intervals along the front-rear direction of the unmanned aerial vehicle. In the front-rear direction of the unmanned aerial vehicle, the front side edge of the first fin 116 is located closer to the outside of the upper heat dissipation window 115 than the rear side edge, in other words, the first fin 116 is inclined downward from front to rear, so that when the unmanned aerial vehicle is flying at cruise, the air flow near the upper heat dissipation window 115 is easy to enter the enclosure 100 through the upper heat dissipation window 115 under the effect of the air flow of the first fin 116. Optionally, first deflector fin 116 is integrally formed with upper shell 110.

In the present embodiment, the upper case 110 is provided with a coolant filler port 118. The coolant fill port 118 is adapted to expose a port of a coolant overflow kettle, thereby facilitating filling of the engine 300 with coolant. In the present embodiment, the upper heat dissipation window 115 is divided into two areas, the two areas of the upper heat dissipation window 115 are spaced apart in the front-rear direction of the unmanned aerial vehicle, and the coolant filler 118 is located between the two areas of the upper heat dissipation window 115. The upper heat dissipation window 115 is further internally provided with a reinforcing beam 117, the reinforcing beam 117 extends along the front-back direction of the unmanned aerial vehicle, the front end of the reinforcing beam 117 is connected to the side wall of the upper heat dissipation window 115, and the reinforcing beam 117 is further connected with a part of the first guide fins 116. By providing the reinforcing beam 117 and the first fin 116 in the upper heat dissipation window 115, the strength of the upper case 110 can be enhanced, and the strength of the upper case 110 is prevented from being greatly reduced due to the provision of the oversized upper heat dissipation window 115.

As shown in fig. 5, in the embodiment of the present utility model, one end of the upper case 110 and the front case 130 together enclose a front rotor opening 101, the other end of the upper case 110 and the rear case 140 together enclose a rear rotor opening 102, the front rotor opening 101 is used for mounting a front rotor assembly, and the rear rotor opening 102 is used for mounting a rear rotor assembly. Specifically, in this embodiment, the front end of the upper shell 110 has a semicircular notch for enclosing the front rotor opening 101 together with the front shell 130; the rear end of the upper shell 110 also has a semi-circular notch for co-enclosing the rear rotor opening 102 with the rear shell 140. Front rotor opening 101 is used to mount a front rotor assembly and rear rotor opening 102 is used to mount a rear rotor assembly.

Fig. 7 is a schematic view of the front case 130 according to an embodiment of the present utility model. Referring to fig. 1 and 7, in the present embodiment, one end of the front case 130 is connected to the upper case 110, and the other end of the front case 130 extends downward and rearward of the unmanned aerial vehicle. Specifically, one end (upper end) of the front shell 130 has a semicircular notch, and the end is connected to the upper shell 110 and encloses the front rotor opening 101 together with the upper shell 110. The other end of the front shell 130 extends towards the lower rear of the unmanned aerial vehicle, and the front shell 130 is obliquely arranged, so that the unmanned aerial vehicle has a better pneumatic appearance, and the flight resistance of the unmanned aerial vehicle is reduced.

The front case 130 is provided with a front heat dissipation window 131 communicating with the inside of the cabinet 100. The front heat dissipation window 131 is disposed on the windward side of the front shell 130, and when the unmanned aerial vehicle travels, air flow can flow into the casing 100 from the front heat dissipation window 131, so as to enhance heat dissipation of components in the casing 100. Specifically, in this embodiment, the front heat dissipation window 131 is divided into two parts, one part faces directly in front of the unmanned aerial vehicle, and the other part faces obliquely to the lower front of the unmanned aerial vehicle.

Further, a second filter 132 is provided in the front heat dissipation window 131 to filter air entering the inside of the cabinet 100 through the front heat dissipation window 131. By providing the second filter 132, it is possible to prevent foreign matters such as dust and leaves from entering the casing 100 along with the airflow, and to influence the operation of the unmanned aerial vehicle. Optionally, the second filter 132 is a wire mesh; in other embodiments, the second filter 132 may be a grating or other member with a certain filtering and intercepting function.

Further, a second fin 133 is disposed in the front heat dissipation window 131, and the second fin 133 is used for guiding the air flow outside the front case 130 into the casing 100. Specifically, the second fin 133 is disposed at a portion of the front heat dissipation window 131 facing downward and forward. When the airflow blows across the surface of the front case 130, the airflow flows along the lower rear direction, and by providing the second guide fins 133, the airflow outside the front case 130 can be guided to enter the casing 100 through the front heat dissipation window 131, thereby enhancing convection inside the casing 100 and enhancing heat dissipation effect. In addition, the second guide fin 133 also has an advantage of enhancing the structural strength of the front case 130.

Further, a radar window 134 is provided on the front case 130. A laser radar may be disposed inside the front case 130, and a detection beam of the laser radar may pass through the radar window 134 to achieve detection. A transparent baffle may be disposed at radar window 134 to protect the lidar while allowing the radar probe light to pass. Optionally, the baffle material is glass.

Fig. 8 is a schematic view of the rear case 140 according to an embodiment of the present utility model. Referring to fig. 1 and 8, in the present embodiment, one end of the rear case 140 is connected to the upper case 110, and the other end of the rear case 140 extends toward the lower front of the unmanned aerial vehicle. Specifically, the rear shell 140 has a semicircular notch at one end (upper end) thereof, which is connected to the upper shell 110 and encloses the rear rotor opening 102 together with the upper shell 110. The other end of the rear shell 140 extends to the lower front of the unmanned aerial vehicle, and the rear shell 140 is obliquely arranged, so that the unmanned aerial vehicle has a better pneumatic appearance, the flying resistance of the unmanned aerial vehicle is reduced, the rear shell 140 and the front shell 130 are approximately symmetrical in shape, and the front and rear balance of the unmanned aerial vehicle is facilitated.

The rear case 140 is provided with a rear heat dissipation window 141 communicating with the inside of the cabinet 100. When the unmanned aerial vehicle travels, high-temperature air flow inside the cabinet 100 may flow out of the rear heat dissipation window 141, thereby taking heat away. In particular, in the present embodiment, the rear heat dissipation window 141 includes two portions, one portion facing the right rear of the unmanned aerial vehicle and the other portion facing the lower rear of the unmanned aerial vehicle obliquely.

Further, a third filter 142 is disposed in the rear heat dissipation window 141. By providing the third filter 142, it is possible to prevent foreign matters such as dust and leaves from entering the casing 100, and to influence the operation of the unmanned aerial vehicle. Optionally, the third filter 142 is a wire mesh; in other embodiments, the third filter 142 may be a grating or other member with a certain filtering and intercepting function.

Further, a third fin 143 is disposed in the rear heat dissipation window 141, and the third fin 143 is used for guiding the air flow inside the rear case 140 to flow outside the chassis 100. Specifically, the third fin 143 is disposed at a portion of the rear heat dissipation window 141 facing downward and rearward. When the air flows along the inner surface of the rear case 140, the third guide fins 143 can guide the air flow inside the rear case 140 to flow out of the casing 100 through the rear heat dissipation window 141, thereby increasing the efficiency of taking away the heat inside the casing 100 and enhancing the heat dissipation effect. In addition, third deflector fin 143 also has the advantage of enhancing the structural strength of rear housing 140.

Further, an indicator light 144 is provided on the rear case 140. In the present embodiment, the indicator lamp 144 is disposed within the rear heat dissipation window 141, specifically, embedded in a portion of the rear heat dissipation window 141 facing the right rear. The outer contour of the indicator light 144 is matched with the contour of the rear heat dissipation window 141, so that the installation stability is guaranteed, and the indicator light 144 is in a hollowed-out design and cannot excessively influence the air outlet of the rear heat dissipation window 141. By embedding the indicator light 144 in the rear heat dissipation window 141, the device can be made more compact while ensuring a better aerodynamic profile.

When the unmanned aerial vehicle provided by the embodiment of the utility model flies at cruising, air flow can enter the shell 100 of the unmanned aerial vehicle through the upper heat dissipation window 115 and the front heat dissipation window 131. The cold air entering from the upper heat dissipation window 115 and the front heat dissipation window 131 can purge the oil-cooled radiator 600, the middle-cooled radiator 500 and the liquid-cooled radiator 400 in sequence, so that the heat dissipation effect of the three radiators is enhanced. The air flow entering from the front heat dissipation window 131 can pass through each radiator and the engine 300 in order from the front, thereby taking away the heat of each radiator and the engine 300. The air having absorbed the heat may be finally discharged outside the cabinet 100 through the rear heat dissipation window 141. By disposing the oil-cooled radiator 600, the intercooler 500, and the liquid-cooled radiator 400 on top of the fuselage frame 200 and providing the upper heat dissipation window 115 and the air intake structure 111 corresponding thereto, the heat dissipation performance of the unmanned aerial vehicle can be significantly improved, avoiding the risk of overheating.

In summary, the heat dissipation system of the present utility model includes a liquid cooling heat dissipation assembly, an intermediate cooling heat dissipation assembly, and an oil cooling heat dissipation assembly. The liquid cooling heat dissipation assembly includes a liquid cooling heat sink 400 and a liquid cooling tube 410, wherein the liquid cooling heat sink 400 and the liquid cooling tube 410 form a liquid cooling loop for circulating a cooling liquid, the cooling liquid is used for absorbing heat from the engine 300, and the cooling liquid releases heat when carrying heat through the liquid cooling heat sink 400. The intercooler 500 is used to cool the gas that is pressurized by the turbocharger 310 to enter the intake port of the engine 300, thereby avoiding excessive heat load caused by excessive temperature of the compressed gas entering the engine 300. The oil-cooled radiator assembly comprises an oil-cooled radiator 600 and an oil-cooled pipe 610, wherein the oil-cooled radiator 600 and the oil-cooled pipe 610 are used for forming an oil-cooled loop for circulating engine oil with the engine 300, and the oil-cooled radiator 600 is used for cooling the engine oil. Because the heat dissipation system comprises three different heat dissipation components, the heat dissipation system can jointly dissipate heat of the engine 300 or a medium (such as engine oil and air) entering the engine 300, so that the engine 300 can be effectively prevented from being overheated, and the stable operation of the unmanned aerial vehicle can be maintained.

The unmanned aerial vehicle provided by the utility model comprises the engine 300, the shell 100 and the heat radiation system, so that the problem of overheating is not easy to occur, and the unmanned aerial vehicle can maintain stable operation for a long time.

The above description is only of the preferred embodiments of the present utility model and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims

1. A heat dissipation system for an unmanned aerial vehicle, the unmanned aerial vehicle comprising an engine, the engine being provided with an intake port and a turbocharger, comprising:

an intercooler assembly comprising an intercooler for cooling gas pressurized by a turbocharger to enter an intake port of the engine;

the oil cooling heat dissipation assembly comprises an oil cooling radiator and an oil cooling pipe, wherein the oil cooling radiator and the oil cooling pipe are used for forming an oil cooling loop for engine oil circulation with the engine, and the oil cooling radiator is used for cooling the engine oil.

2. The heat removal system of claim 1, further comprising a fan for removing heat from at least one of the liquid-cooled radiator, the intercooler radiator, and the oil-cooled radiator.

3. The heat removal system of claim 1, wherein the intercooler further comprises an intercooler pipe connected to the intercooler, the intercooler pipe being used to connect the turbocharger, the intercooler, and an intake port of the engine in series.

4. A heat dissipating system according to any of claims 1-3, wherein the unmanned aerial vehicle further comprises a housing, wherein the engine and the heat dissipating system are both arranged in the housing, wherein at least one heat dissipating window is arranged on the housing, and wherein the liquid-cooled radiator, the intercooler radiator and the oil-cooled radiator correspond to the positions of the heat dissipating windows.

5. The heat removal system of claim 4, wherein the unmanned aerial vehicle further comprises a fuselage frame disposed within the chassis, the chassis being connected to the fuselage frame, the liquid-cooled radiator, the intercooler radiator, and the oil-cooled radiator being disposed in sequence on top of the fuselage frame; the heat dissipation window comprises an upper heat dissipation window arranged at the top of the shell, and the positions of the liquid cooling radiator, the middle cooling radiator and the oil cooling radiator correspond to the positions of the upper heat dissipation window.

6. The heat dissipation system of claim 4, wherein the liquid cooled heat dissipation assembly further comprises a coolant overflow kettle disposed on the liquid cooled tube, the top of the housing being provided with a coolant fill port for exposing a kettle mouth of the coolant overflow kettle.

7. The heat removal system of any one of claims 1-3, wherein the liquid-cooled radiator, the intercooler radiator, and the oil-cooled radiator are arranged in sequence from back to front in a front-to-back direction of the unmanned aerial vehicle.

8. An unmanned aerial vehicle comprising an engine, a chassis, and the heat dissipation system of any of claims 1-7.

9. The unmanned aerial vehicle of claim 8, wherein the chassis comprises a front shell, a rear shell, an upper shell, and two side shells spaced apart in a left-right direction of the unmanned aerial vehicle, the front shell, the rear shell, and the upper shell each being detachably connected to two of the side shells, the front shell and the rear shell being spaced apart in a front-rear direction of the unmanned aerial vehicle.

10. The unmanned aerial vehicle of claim 9, wherein an upper heat dissipation window is provided on the upper shell, and a first deflector fin is provided in the upper heat dissipation window, the first deflector fin being configured to direct an air flow outside the enclosure into the enclosure.

11. The unmanned aerial vehicle of claim 9, wherein the outside of the upper shell is provided with an air intake structure that forms an air intake that communicates with the interior of the enclosure, the air intake being directed toward the front of the unmanned aerial vehicle.

12. The unmanned aerial vehicle of claim 11, wherein the air intake structure further forms an air intake passage that communicates the air intake with the interior of the enclosure, the air intake passage having a first filter disposed therein to filter air entering the interior of the enclosure through the air intake passage.

13. The unmanned aerial vehicle of any of claims 9-12, wherein the front shell is provided with a front heat dissipation window that communicates with the interior of the chassis.

14. The unmanned aerial vehicle of claim 13, wherein a second filter is disposed within the front heat dissipation window to filter air entering the interior of the enclosure through the front heat dissipation window.

15. The unmanned aerial vehicle of claim 13, wherein a second deflector fin is disposed within the front heat dissipation window, the second deflector fin being configured to direct an airflow outside the front shell into the enclosure.

16. The unmanned aerial vehicle of any of claims 9-12, wherein the rear housing is provided with a rear heat dissipation window that communicates with the interior of the chassis.

17. The unmanned aerial vehicle of claim 16, wherein a third filter is disposed within the rear heat dissipation window.

18. The unmanned aerial vehicle of claim 16, wherein a third deflector fin is disposed within the rear heat dissipation window, the third deflector fin being configured to direct airflow inside the rear enclosure to outside the enclosure.

19. The unmanned aerial vehicle of any of claims 8-12, wherein the unmanned aerial vehicle is a tandem twin-rotor unmanned helicopter.