CN109673139B

CN109673139B - Heat dissipation system and aircraft with same

Info

Publication number: CN109673139B
Application number: CN201910098293.4A
Authority: CN
Inventors: 张磊; 冯建刚; 唐尹
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2015-12-03
Filing date: 2015-12-03
Publication date: 2020-05-29
Anticipated expiration: 2035-12-03
Also published as: CN107211556A; CN107211556B; WO2017091997A1; CN109673139A

Abstract

The invention relates to a heat dissipation system, which comprises a substrate, a plurality of heat dissipation fins and a fan. The substrate is provided with a first surface and a second surface opposite to the first surface. The plurality of radiating fins are arranged on the first surface of the substrate. The fan has an air opening. The fan is arranged on one side of the first surface of the substrate. The air outlet of the fan is inclined relative to the first surface of the substrate, and the air outlet of the fan is inclined towards the radiating fins and the extending direction of the radiating fins. The invention also provides an aircraft with the heat dissipation system. The invention reduces the occupied size of the heat dissipation system in height, and the flow direction of the forced airflow provided by the fan is consistent with the extension direction of the heat dissipation fins/airflow channels, so that the wind resistance of the forced airflow provided by the fan is smaller when the forced airflow passes through the heat dissipation fins/airflow channels, and an effective heat dissipation channel is formed.

Description

Heat dissipation system and aircraft with same

Technical Field

The present disclosure relates to heat dissipation technologies, and particularly to a heat dissipation system and an aircraft having the same.

Background

With the development of electronic technology, the integration degree of chips is higher and higher, the size of the chips is smaller and smaller, and the heat flux density of the chips is higher and higher. When the chips are applied to miniaturized products, the narrow space structure in the products is not beneficial to heat dissipation of the chips. Temperature is a key factor influencing chip reliability, and as the temperature rises, the failure rate of the chip increases in a geometric multiple relationship. Therefore, how to quickly and effectively dissipate heat from the chip is an important factor for determining the reliability of the product.

At present, most of electronic products with high heat flux density are designed by an active heat dissipation scheme, the scheme adopts a mode of adding a fan and a radiator, the heat flux density of a chip is reduced by using the radiator, and then the heat on the radiator is dissipated by forced convection heat transfer of blowing a radiating fin of the radiator by using the fan, so that the aim of reducing the temperature of the chip is fulfilled.

However, if a fan and a heat sink are used in a narrow space inside a product, the fan layout is difficult, the air duct is not smooth, and an effective heat dissipation channel is difficult to form.

The aircraft, especially unmanned vehicles, sets up some chips in its fuselage, and the design of these chip heat dissipation schemes also receives the narrow and small influence in fuselage interior space.

Disclosure of Invention

In view of the above, it is desirable to provide a heat dissipation system with an effective heat dissipation channel and an aircraft having the same.

The invention relates to a heat dissipation system, comprising: base plate, a plurality of fin and fan. The substrate is provided with a first surface and a second surface opposite to the first surface. The plurality of radiating fins are arranged on the first surface of the substrate. The fan is provided with an air opening and is arranged on one side of the first surface of the substrate. The air outlet of the fan is inclined relative to the first surface of the substrate, and the air outlet of the fan is inclined towards the radiating fins and the extending direction of the radiating fins.

The invention also relates to a heat dissipation system comprising: a heat sink and a fan. The heat dissipation device comprises a plurality of airflow channels, and each airflow channel is provided with an airflow inlet. The fan is provided with an air opening which is arranged at one side of the heat dissipation device. The air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan is inclined towards the air flow inlets of the air flow channels and the extending direction of the air flow channels.

The invention also relates to an aircraft comprising: fuselage and cooling system. The fuselage includes: casing, accommodation space and heating element. The accommodating space is surrounded by the housing. The heating element is contained in the containing space. The heat dissipation system is used for dissipating heat generated by the heating element. The heat dissipation system is arranged in the accommodating space, and the heat dissipation system comprises: heat-conducting plate, a plurality of fin and fan. The heat conducting plate is attached to the heating element. The plurality of radiating fins are positioned on one side of the heat conducting plate and used for radiating heat absorbed by the heat conducting plate from the heating element. The fan is provided with an air opening and is arranged at one end of the radiating fins. The air outlet of the fan faces the radiating fins and inclines towards the extending direction of the radiating fins.

The invention also relates to an aircraft comprising: fuselage and cooling system. The fuselage includes: casing, accommodation space and heating element. The accommodating space is surrounded by the housing. The heating element is contained in the containing space. The heat dissipation system is used for dissipating heat generated by the heating element. The heat dissipation system is arranged in the accommodating space, and the heat dissipation system comprises: a heat sink and a fan. The heat dissipation device comprises a plurality of airflow channels, and each airflow channel is provided with an airflow inlet. The fan is provided with an air opening which is arranged on one side of the heat dissipation device. The air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan is inclined towards the air flow inlets of the air flow channels and the extending direction of the air flow channels.

Compared with the prior art, the invention adopts the wind inclined arrangement, thereby reducing the occupied size of the heat dissipation system in height. The air opening of the fan faces the radiating fin/airflow channel and inclines towards the extending direction of the radiating fin/airflow channel, so that the forced airflow provided by the fan is blown to the radiating fin/airflow channel, and the flowing direction of the forced airflow is consistent with the extending direction of the radiating fin/airflow channel, and therefore when the forced airflow provided by the fan passes through the radiating fin/airflow channel, the wind resistance is small, and an effective radiating channel is formed.

Further, each of the heat dissipation fins is curved along the extending direction thereof.

Further, the plurality of heat dissipation fins are located at the middle position of the first surface of the substrate.

Furthermore, each of the heat dissipation fins sequentially comprises a first heat dissipation part, a second heat dissipation part and a third heat dissipation part along the extension direction of the heat dissipation fin, and the extension direction of the second heat dissipation part and the extension direction of the third heat dissipation part are different from the extension direction of the first heat dissipation part.

Further, the air opening of the fan is close to the first heat dissipation part and far away from the third heat dissipation part.

Further, the second heat sink member is bent to connect the first heat sink member and the third heat sink member.

Further, the height of the second heat sink member is greater than the height of the first heat sink member and greater than the height of the third heat sink member.

Further, the first heat sink portions of the plurality of heat sinks are parallel to each other.

Further, a third heat dissipation part of the plurality of heat dissipation fins is radial along the extending direction.

Further, the heat dissipation system further comprises a plurality of other heat dissipation fins located on two sides of the plurality of heat dissipation fins, and the extending direction of the other heat dissipation fins is different from the extending direction of the heat dissipation fins.

Further, the heat dissipation system further includes:

the heat conducting plate is used for absorbing heat generated by the heating element and comprises a contact surface for being attached to the heating element and a joint surface for being combined with the second surface of the substrate;

and the heat pipe is positioned between the substrate and the heat conducting plate.

Furthermore, the heat conducting plate is provided with a plurality of accommodating grooves for accommodating the heating elements on one side of the contact surface of the heat conducting plate.

Further, the heat conductive plate is provided with a plurality of notches at its periphery.

Further, each airflow channel is bent.

Further, one end of each airflow channel, which is far away from the fan, is radial.

Further, the airflow inlets of the plurality of airflow channels are parallel to each other.

Further, the plurality of airflow channels are located between the plurality of fins.

Further, other airflow channels are arranged among the plurality of radiating fins, and the extending direction of the airflow channels is different from the extending direction of the other airflow channels.

Further, the fan is an axial fan.

Furthermore, the casing has an air inlet and an air outlet, the air outlet is the air outlet of the fan, the fan also has an air inlet, the air inlet corresponds to the air inlet, and the air outlet corresponds to one end of the radiating fin far away from the fan.

Further, the aircraft further comprises: another heating element and another heat sink. The other heat dissipation device comprises a base attached to the other heating element and a plurality of heat dissipation fins extending out of the base.

Further, the material of the shell is heat conduction material, and the heat dissipation fins contact with the shell.

Further, the housing is provided with a plurality of perforations.

Drawings

Fig. 1 is a schematic plan view of a heat dissipation system according to an embodiment of the present invention.

Fig. 2 is an exploded perspective view of a heat dissipation device of the heat dissipation system shown in fig. 1.

Fig. 3 is an assembled plan view of the heat dissipating device shown in fig. 2.

Fig. 4 is a schematic cross-sectional view of the heat dissipating device shown in fig. 3 taken along line IV-IV.

Fig. 5 is another schematic plan view of the heat dissipation system shown in fig. 1.

Fig. 6 is a further schematic plan view of the heat dissipation system shown in fig. 1.

FIG. 7 is a partially cut-away schematic illustration of an aircraft having a heat dissipation system provided by an embodiment of the present invention.

Fig. 8 is an enlarged view schematically showing a portion VIII in fig. 7.

Fig. 9 is an enlarged view of part IX in fig. 7.

Description of the main elements

Heat dissipation system 1

Fan 10

Outer casing 11

Wind tunnel 111

Inlet air 113

Wind outlet 115

Mounting frame 13

Rib 131

Heat sink 20

Heat conducting plate 21

Contact surface 211

Bonding surface 213

Groove 215

Notch 217

Accommodation groove 219

Heat pipe 23

First heat transfer section 231

Second heat transfer section 233

Third heat transfer section 235

Radiator 25

Substrate 251

First Table 2511

Second Table 2512

Fitting groove 2513

First side 2514

Second side 2515

Third side 2516

Fourth side 2517

Notch 2518

Heat sink 253

First heat sink 2531

Second heat sink 2532

Third fin 2533

First heat sink member 25331

Second heat sink component 25332

Third heat sink component 25333

Fourth heat sink 2534

First gas flow passage 2535

Second gas flow passage 2536

Third gas flow passage 2537

Gas inflow port 25371

Gas flow outlet 25372

Fourth airflow passage 2538

Fixed part 255

Fixing hole 2551

Aircraft 4

Fuselage 41

Case 411

Gas inlet 4111

Exhaust port 4113

Perforation 4115

Accommodating space 413

Arm 42

Rotor 43

Heating element 44

Fixing device 45

Heating element 46

Heat sink 47

Base 471

Heat sink 473

The following detailed description will further illustrate the invention in conjunction with the above-described figures.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1, an embodiment of the invention provides a heat dissipation system 1, where the heat dissipation system 1 is used for dissipating heat of an electronic component. The heat dissipation system 1 includes a fan 10 and a heat dissipation device 20 cooperating with the fan 10. The fan 10 is disposed obliquely with respect to the heat sink 20.

The fan 10 may be an axial fan or a radial fan. In this embodiment, the fan 10 is an axial fan. The fan 10 includes a housing 11, a mounting bracket 13, and an impeller (not shown). The housing 11 is hollow to form an air duct 111, and openings at two opposite ends of the air duct 111 form an inlet air 113 and an outlet air 115. The mounting bracket 13 is disposed in the air duct 111 and fixed to the housing 11 by a plurality of ribs 131. The impeller is accommodated in the air duct 111 and rotatably mounted to the mounting frame 13.

Referring to fig. 2 and 3, the heat dissipation device 20 includes a heat conduction plate 21, a heat pipe 23 combined with the heat conduction plate 21, and a heat sink 25 thermally connected to the heat conduction plate 21 and the heat pipe 23.

The heat conductive plate 21 includes a contact surface 211 and a bonding surface 213. The contact surface 211 is for contacting a heat generating component. The bonding surface 213 is used for bonding the radiator 25. The heat pipe 23 is accommodated in a groove 215 provided on one side of the bonding surface 213 of the heat plate 21. The groove 215 extends from the coupling surface 213 toward the contact surface 211 to have a certain depth. The shape of the groove 215 may be set according to the shape of the heat pipe 23, and may be a straight line type, a curved type, and when the groove is a curved type, it may be an S-shape, a C-shape, a U-shape, an M-shape, an N-shape, and the like. In this embodiment, the groove 215 is U-shaped.

The shape of the heat conducting plate 21 can be set according to actual needs. In this embodiment, the heat conducting plate 21 is polygonal. The heat conductive plate 21 is provided at the periphery thereof with a plurality of notches 217 to prevent the peripheral elements from interfering with the installation position of the heat conductive plate 21 when the heat conductive plate is installed to the heat generating element. The heat-conducting plate 21 further has a plurality of accommodating grooves 219 for accommodating the heating elements on the side of the contact surface 211. The receiving grooves 219 extend from the contact surface 211 toward the coupling surface 213 to have a certain depth. The depths of the plurality of receiving grooves 219 may be set to be the same or different according to the heights of the heating elements.

The heat conducting plate 21 is made of metal with good heat conducting property, such as copper, aluminum, etc., and may also be made of heat conducting graphite material or heat conducting carbon nano material. The heat conducting plate 21 may also be filled with a phase change medium, such as water, ethanol, ether, etc.

The heat pipe 23 is a metal pipe body filled with a phase change medium, and the phase change medium may be water, ethanol, ether, or the like.

The heat pipe 23 may be a circular pipe, a semi-circular pipe, a flat shape, etc. In this embodiment, the heat pipe 23 is flat and has two opposite parallel flat surfaces for attaching to the heat conducting plate 21 and the heat sink 25. The heat pipe 23 includes a first heat transfer section 231, a second heat transfer section 233, and a third heat transfer section 235. The second heat transfer section 233 extends outward from one end of the first heat transfer section 231. The third heat transfer section 235 extends outward from the other end of the first heat transfer section 231. In other words, the second heat transfer section 233 and the third heat transfer section 235 extend in a direction different from the end of the first heat transfer section 231.

In this embodiment, the heat pipe 23 is U-shaped corresponding to the groove 215. The first heat transfer section 231, the second heat transfer section 233 and the third heat transfer section together form a U-shaped structure of the heat pipe 23. The first heat transfer section 231 is linear. The second heat transfer section 233 is linear. The junction of the first heat transfer section 231 and the second heat transfer section 233 is connected smoothly with a curved surface. The third heat transfer segment 235 is linear. The connection between the first heat transfer section 231 and the third heat transfer section 235 is a curved surface. The second heat transfer section 233 is parallel to the third heat transfer section 235. The second heat transfer section 233 and the third heat transfer section 235 are substantially perpendicular to the first heat transfer section 231. In one embodiment, the length of the third heat transfer section 235 is less than the length of the second heat transfer section 233.

The thickness of the heat pipe 23 is greater than, equal to, or less than the depth of the groove 215. In this embodiment, the thickness of the heat pipe 23 is greater than or equal to the depth of the groove 215.

The heat sink 25 includes a substrate 251 and a plurality of heat dissipation fins 253 disposed on the substrate 251. The plurality of fins 253 form a plurality of airflow channels therebetween.

The substrate 251 is a metal plate with good thermal conductivity, and may also be a thermal conductive graphite plate or a thermal conductive carbon nano plate. The substrate 251 further extends outward with a plurality of fixing portions 255. The substrate 251 includes a first surface 2511 and a second surface 2512 opposite the first surface 2511. The substrate 251 may have an attaching groove 2513 (see fig. 4) on one side of the second surface 2512 thereof corresponding to the groove 215 of the heat conducting plate 21 for accommodating the heat pipe 23.

The shape of the substrate 251 may be a square, trapezoid, circle or other polygon. In this embodiment, the substrate 251 has a substantially square shape, and includes a first side 2514, a second side 2515, a third side 2516 opposite to the first side, and a fourth side 2517 opposite to the second side. In this embodiment, the second side 2515 is substantially parallel to the fourth side 2517. A plurality of notches 2518 are formed at the third side 2516 to prevent peripheral components from interfering with the installation position of the substrate 251 when the heat sink 20 is installed on a heat generating component. The first side 2514, the second side 2515, the third side 2516 and the fourth side 2517 are all connected to the first surface 2511 and the second surface 2512.

In this embodiment, each of the fixing portions 255 is disposed with a fixing hole 2551.

The plurality of heat sinks 253 are disposed on the first surface 2511 of the substrate 251. The plurality of fins 253 include fins of different shapes or placement directions. In this embodiment, the plurality of heat dissipation fins 253 includes a plurality of first heat dissipation fins 2531, a plurality of second heat dissipation fins 2532, a plurality of third heat dissipation fins 2533 and a plurality of fourth heat dissipation fins 2534.

The plurality of first heat dissipation fins 2531 are disposed at an end of the substrate 251 near the second side 2515. The plurality of first cooling fins 2531 are arranged in parallel and spaced apart from each other. First air flow passages 2535 are formed between adjacent first heat dissipation fins 2531. Each first heat sink 2531 is substantially parallel to the second side 2515. Each first heat sink 2531 extends from proximate the first side edge 2514 to proximate the third side edge 2516. Each of the first heat radiation fins 2531 is linear along the extending direction thereof. In this embodiment, a first heat sink 2531 is defined to extend from adjacent to the first side 2514 along a first direction.

The first airflow channel 2535 is linear and extends from near the first side 2514 along the second side 2515 to near the third side 2516 and is substantially parallel to the second side 2515. In this embodiment, the first flow path 2535 extends in a first direction from proximate the first side 2514.

The plurality of second heat dissipation fins 2532 are provided on the side of the substrate 251 close to the third side 2516. In this embodiment, the plurality of second heat dissipation fins 2532 are located between the first heat dissipation fin 2531 and the third heat dissipation fin 2533. The plurality of second heat radiation fins 2532 are disposed to be spaced apart from each other. Second airflow passages 2536 are formed between adjacent second heat radiation fins 2532. Each second fin 2532 extends in a direction from the second side edge 2515 toward the third side edge 2516 at an oblique angle relative to the second and

third side edges

2515 and 2516. Each second heat dissipation fin 2532 is disposed obliquely to the first heat dissipation fin 2531. An included angle is formed between the second heat dissipation fin 2532 and the first heat dissipation fin 2531. In this embodiment, the second heat sink 2532 is defined to extend from near the second side 2515 in a second direction. The second heat dissipation fins 2532 are slightly radial in a direction away from the first heat dissipation fins 2531. The lengths of the plurality of second cooling fins 2532 may be different. In this embodiment, the lengths of the second heat dissipation fins 2532 gradually increase along the third side 2516 toward the first side 2514, that is, the lengths of the second heat dissipation fins 2532 gradually increase from the edge of the substrate 251 toward the center.

The second flow path 2536 is linear and extends from a position near the second side 2515 toward the third side 2516 at an oblique angle to the second and

third sides

2515 and 2516. That is, the second gas flow path 2536 extends from near the second side edge 2515 in a substantially diagonal direction of the substrate 251. In this embodiment, the second flow path 2536 extends in a second direction from proximate the second side edge 2515. The second direction is different from the first direction. An included angle is formed between the second direction and the first direction.

The plurality of third heat dissipation fins 2533 are disposed at a middle position of the base plate 251. The plurality of third heat radiating fins 2533 are located between the second heat radiating fins 2532 and the fourth heat radiating fins 2534. Each third fin 2533 extends from an end of the first side 2514 adjacent to the second side 2515 to the fourth side 2517. That is, the third heat sink 2533 extends from an end of the first side 2514 close to the second side 2515 substantially in a diagonal direction of the substrate 251. The plurality of third cooling fins 2533 are spaced from each other, a third airflow channel 2537 is formed between adjacent third cooling fins 2533, and the third airflow channel 2537 extends from one end of the first side 2514 close to the second side 2515 to the fourth side 2517. Each of the third heat radiation fins 2533 has a curved shape along its extending direction. Each of the third heat dissipation fins 2533 sequentially includes a first heat dissipation portion 25331, a second heat dissipation portion 25332 extending outward from one end of the first heat dissipation portion 25331, and a third heat dissipation portion 25333 extending outward from the second heat dissipation portion 25332 along the extending direction thereof.

The first heat sink member 25331 is linear along its extension. The first heat sink piece 25331 of the third heat sink pieces 2533 is located near the first side 2514. In this embodiment, the first heat dissipation parts 25331 of the third heat dissipation fins 2533 are parallel to each other. In this embodiment, the first heat dissipation part 25331 of the plurality of third heat dissipation fins 2533 is parallel to the first heat dissipation fin 2531 and the second side 2515. The first heat sink component 25331 extends in a first direction from the first side edge 2514. In this embodiment, the first heat dissipating part 25331 of the third heat dissipating fins 2533 is perpendicular to the first side 2514. Each of the third heat radiating fins 2533 gradually increases in height along its extending direction. The third gas flow path 2537 forms a gas flow inlet 25371 at the first heat sink piece 25331.

The second heat sink member 25332 is curved in its direction of extension. The second heat sink member 25332 connects the first heat sink member 25331 and the third heat sink member 25333. The second heat sink piece 25332 of the plurality of third heat sink pieces 2533 is located approximately at the center of the substrate 251. The second heat dissipating parts 25332 of the third heat dissipating fins 2533 are parallel to each other or are slightly radial in the extending direction thereof. The second heat sink member 25332 extends in a direction different from the first direction, i.e., different from the direction in which the first heat sink member 25331 extends. The height of each second heat sink member 25332 is greater than the height of the first heat sink member 25331 and the third heat sink member 25333.

The third heat sink member 25333 is linear along its direction of extension. The third heat sink piece 25333 of the plurality of third heat sink pieces 2533 extends toward the fourth side 2517. The third heat sink member 25333 extends in a direction substantially diagonal to the substrate 251. The third heat sink member 25333 extends in a direction different from the first direction, i.e., different from the direction in which the first heat sink member 25331 extends. In this embodiment, the third heat dissipation parts 25333 of the plurality of third heat dissipation fins 2533 are radial in the extending direction thereof. In one embodiment, the third heat dissipation portion 25333 of the plurality of third heat dissipation fins 2533 forms an angle of 50-70 degrees with the first heat dissipation fin 2531 or the second side 2515. The third gas flow passage 2537 forms a gas flow outlet 25372 at the third heat sink piece 25333.

The third airflow channel 2537 is curved and extends from the end of the first side 2514 near the second side 2515 to the fourth side 2517. That is, the third airflow path 2537 is curved and extends from the end of the first side 2514 close to the second side 2515 in a substantially diagonal direction of the base 251. In this embodiment, the third airflow channel 2537 is defined to extend in a third direction from an end of the first side 2514 adjacent to the second side 2515. The third direction is a curved shape, which is different from the first direction and the second direction.

The plurality of fourth heat dissipation fins 2534 are located at the corners of the base 251 near the first side 2514 and the fourth side 2517. The plurality of fourth heat dissipation fins 2534 are positioned on one side of the third heat dissipation fins 2533. The plurality of fourth heat dissipation sheets 2534 are spaced from each other, and a fourth air flow channel 2538 is formed between adjacent fourth heat dissipation sheets 2534. In this embodiment, the plurality of fourth heat dissipation fins 2534 are parallel to each other. In this embodiment, the plurality of fourth heat dissipation fins 2534 are parallel to the first side 2514. In one embodiment, the lengths of the fourth heat dissipation fins 2534 are different.

The fourth flow path 2538 is linear and extends in a direction parallel to the first side 2514. In this embodiment, the fourth flow channel 2538 is defined to extend in a fourth direction. The fourth direction is different from the first direction, the second direction, and the third direction. The fourth direction is substantially perpendicular to the first direction.

Referring to fig. 4, when the heat dissipation device 20 is assembled, the heat pipe 23 is accommodated in the groove 215 of the heat conductive plate 21, and the second surface 2512 of the substrate 251 of the heat sink 25 is attached to the bonding surface 213 of the heat conductive plate 21. The heat pipe 23 is further accommodated in the attachment groove 2513 of the substrate 251 and is sandwiched between the heat conductive plate 21 and the substrate 251. In one embodiment, solder paste is applied to the grooves 215, the bonding grooves 2513, and between the heat conducting plate 21 and the substrate 251 to reduce thermal resistance between the heat conducting plate 21, the heat pipe 23, and the substrate 251.

Referring to fig. 1, 5 and 6, when the fan 10 and the heat sink 20 are assembled, the fan 10 is obliquely disposed at one side of the heat sink 20. The outlet 115 of the fan 10 is disposed obliquely with respect to the first surface 2511 of the substrate 251. The air outlet 115 of the fan 10 faces the heat sink 253 and is spaced from the heat sink 253, and the air inlet 113 of the fan 10 faces away from the heat sink 253. In this embodiment, the fan 10 is located near the second side 2515 corresponding to the first side 2514 of the substrate 251 of the heat sink 25, and the air outlet 115 thereof faces the first heat dissipation part 25331 of the third heat dissipation fin 2533, i.e., faces the air inlet 25371 of the third air flow passage 2537, and is inclined toward the extending direction of the third heat dissipation fin 2533 and the third air flow passage 2537.

Referring to fig. 5, an included angle of 12 degrees is formed between the air outlet 115 of the fan 10 and the second side 2515 and the fourth side 2517 of the substrate 251 of the heat sink 25, that is, the air outlet 115 of the fan 10 is inclined towards the substrate 251 and towards the extending direction of the first heat dissipating part 25331 of the third heat dissipating fin 2533.

Referring to fig. 6, an included angle between the air outlet 115 of the fan 10 and the first side 2514 of the substrate 251 of the heat sink 25 is 3 degrees, that is, the air outlet 115 of the fan 10 is inclined towards the substrate 251 and towards the extending directions of the second heat dissipating part 25332 and the third heat dissipating part 25333 of the third heat sink 2533.

In this way, the outlet 115 of the fan 10 is inclined toward the third heat sink 2533 and the extending direction of the third heat sink 2533, that is, the outlet 115 of the fan 10 is inclined toward the airflow inlet 25371 of the third airflow channel 2537 and the extending direction of the third airflow channel 2537.

In use, the thermally conductive plate 21 of the heat sink 20 of the heat dissipation system 1 absorbs heat from the heat generating elements. The heat pipes 23 of the heat dissipation device 20 absorb heat from the heat conductive plate 21 to further uniformly distribute the heat to the heat conductive plate 21. The heat conductive plate 21 and the heat pipe 23 transfer heat to the base 251 and the heat sink 253 of the heat sink 25 of the heat dissipation device 20. The fan 10 of the heat dissipation system 1 blows a forced airflow to the heat sink 253 through the air outlet 115. Since the outlet 115 of the fan 10 is inclined toward the third heat dissipation fins 2533 of the heat dissipation fins 253 and toward the extending direction of the third heat dissipation fins 2533, the forced airflow provided by the fan 10 mostly enters the third airflow passages 2537 between the third heat dissipation fins 2533, and a small portion of the forced airflow enters the first airflow passages 2535 between the first heat dissipation fins 2531, the second airflow passages 2536 between the second heat dissipation fins 2532, and the fourth airflow passages 2538 between the fourth heat dissipation fins 2534. The forced airflow entering the third airflow passage 2537 flows along the extending direction of the third heat dissipation fin 2533 and takes away the heat on the third heat dissipation fin 2533. Similarly, the airflow entering the first airflow channel 2535, the second airflow channel 2536 and the fourth airflow channel 2538 takes away the heat on the first heat sink 2531, the second heat sink 2532 and the fourth heat sink 2534.

Compared with the prior art, the fan 10 is disposed obliquely relative to the substrate 251, so that the fan 10 and the heat sink 20 occupy a small space. The air outlet 115 of the fan 10 faces the airflow inlet 25371 of the third airflow channel 2537 and is inclined to the third heat sink 2533 and the extending direction of the third airflow channel 2537 therebetween, so that the forced airflow provided by the fan 10 is blown to the third heat sink 2533, and the direction of the forced airflow is consistent with the extending direction of the third heat sink 2533 and the third airflow channel 2537, and thus, when the forced airflow provided by the fan 10 passes through the third heat sink 2533, most of heat generated by the heat generating element can be taken away, and the wind resistance is reduced, thereby forming an effective heat dissipation channel.

In addition, the second heat dissipating part 25332 of the third heat dissipating fin 2533 is curved along the extending direction thereof, so that the forced airflow provided by the fan 10 can more sufficiently exchange heat with the third heat dissipating fin 2533. The height of the second heat sink member 25332 is greater than the heights of the first heat sink member 25331 and the third heat sink member 25333, so that the heat exchange between the forced airflow provided by the fan 10 and the third heat sink members 2533 is further sufficient.

In addition, the first heat dissipation fin 2531 is located on one side of the third heat dissipation fin 2533, so that the forced airflow provided by the fan 10 is prevented from blowing out of the heat sink 25, and the utilization rate of the forced airflow provided by the fan 10 is improved.

In addition, the second heat sink 2532 and the fourth heat sink 2534 extend in different directions, so that part of the forced airflow provided by the fan 10 is directed to different positions of the heat sink 25, and heat dissipation is more effective.

In addition, the heat dissipation device 20 adopts the heat pipe 23, so that the heat absorbed by the heat conduction plate 21 is more uniformly distributed, and the local overheating phenomenon is avoided.

It is understood that the inlet air 113 of the fan 10 can face the heat sink 20, so that the heat absorbed by the heat sink 20 from the heat generating element is drawn out by the fan 10 through the inlet air 113, and the outlet air 115 of the fan 10 faces away from the heat sink 20.

Referring to fig. 7, an embodiment of the present invention provides an aircraft 4. The aircraft 4 comprises the heat dissipation system 1. The aircraft 4 includes a fuselage 41, a plurality of arms 42 extending outwardly from the fuselage 41, a plurality of rotors 43 mounted to the plurality of arms 42, and a heating element 44 located within the fuselage 41 (see fig. 8). The heat-generating component 44 may comprise one or more heat-generating electronic components.

The body 41 includes a housing 411 and an accommodating space 413 surrounded by the housing 411. The heating element 44 is disposed in the accommodating space 413. In one embodiment, the heating element 44 is mounted to a mounting plate. The accommodating space 413 is located between the mounting plate and the housing 411. In this embodiment, the accommodating space 413 is located at the bottom of the body 41.

An air inlet 4111 and an air outlet 4113 are disposed on opposite sides of the housing 411. An angle is formed between the inlet port 4111 and the outlet port 4113, which does not cause circulation of heat flow. The heat generating elements 44 are centrally distributed between the air inlet 4111 and the air outlet 4113. The housing 411 may further include a plurality of through holes 4115 corresponding to the accommodating space 413.

Referring to fig. 8, the heat conducting plate 21 of the heat dissipating device 20 of the heat dissipating system 1 is attached to the heating element 44. The heat conducting plate 21 and the heating element 44 may be further bonded by a heat conducting medium. The inlet air 113 of the fan 10 of the heat dissipation system 1 corresponds to the inlet air 4111 of the housing 411. An end of the heat dissipating device 20 away from the fan 10 is close to the exhaust 4113 of the housing 411. The fan 10 may be fixed to the housing 411 by a fixing device 45.

Referring to fig. 7 and 9, the aircraft 4 may further include another heating element 46 disposed in the accommodating space 413. The heat-generating component 46 may comprise one or more heat-generating electronic components. The aircraft 4 comprises a further heat sink 47 coupled to the heat-generating element 46. The heating element 46 is located at one side of the heating element 44 and the heat dissipation system 1. The heat generating element 46 is proximate to the exhaust 4113 of the housing 411.

Referring to fig. 9, the heat dissipation device 47 includes a base 471 and a plurality of heat dissipation fins 473 extending from the base 471. The base 471 is attached to the heat generating element 46. The base 471 and the heat generating element 44 may be further attached by a heat conducting medium. The base 471 may also have a plurality of receiving slots for receiving a plurality of electronic components of the heating element 46. The heat dissipation fins 473 face the housing 411 of the body 41. In this embodiment, the heat dissipation fins 473 contact the housing 411, and the housing 411 is made of a metal material or other heat conductive materials, such as a heat conductive carbon nanomaterial.

In use, the heating element 44 operates to generate heat. The heat-conducting plate 21 of the heat-dissipating device 20 of the heat-dissipating system 1 absorbs the heat generated by the heating element. The heat pipes 23 of the heat sink 20 absorb heat from the heat conductive plate 21 to further uniformly distribute the heat to the heat conductive plate 21. The heat conductive plate 21 and the heat pipe 23 transfer heat to the base 251 and the heat sink 253 of the heat sink 25 of the heat dissipation device 20. The fan 10 of the heat dissipation system 1 sucks air through the air inlet 4111 and the air inlet 113 of the housing 411 of the body 41, and blows a forced airflow to the heat sink 253 through the air outlet 115. Since the air outlet 115 of the fan 10 is inclined toward the third heat dissipation fins 2533 of the heat dissipation fins 253 and toward the extending direction of the third heat dissipation fins 2533, the forced airflow provided by the fan 10 mostly enters the third airflow passages 2537 between the third heat dissipation fins 2533, and a small portion enters the first airflow passages 2535 between the first heat dissipation fins 2531, the second airflow passages 2536 between the second heat dissipation fins 2532, and the fourth airflow passages 2538 between the fourth heat dissipation fins 2534. The forced airflow entering the third airflow passage 2537 flows along the extending direction of the third heat dissipation fin 2533 and takes away the heat on the third heat dissipation fin 2533. Similarly, the airflow entering the first airflow channel 2535, the second airflow channel 2536 and the fourth airflow channel 2538 takes away the heat on the first heat sink 2531, the second heat sink 2532 and the fourth heat sink 2534. The hot air flow passing through the heat sink 253 is exhausted out of the main body 41 through the exhaust port 4113 of the housing 411.

Likewise, the heat generating element 46 operates to generate heat, and the base 471 of the heat sink 47 absorbs heat from the heat generating element 46 and transfers the heat to the heat sink fins 473. The heat dissipating fins 473 dissipate heat to the outside and transfer a part of the heat to the housing 411 to be dissipated from the housing 411 to the outside of the body 41.

Compared with the prior art, the fan 10 is obliquely arranged relative to the base plate 251, so that the occupied size of the fan 10 and the heat dissipation device 20 in height is reduced, and the space in the body 41 is adapted or saved. The air outlet 115 of the fan 10 faces the airflow inlet 25371 of the third airflow channel 2537 and is inclined to the third heat sink 2533 and the extending direction of the third airflow channel 2537 therebetween, so that the forced airflow provided by the fan 10 is blown to the third heat sink 2533, and the direction of the forced airflow is consistent with the extending direction of the third heat sink 2533 and the third airflow channel 2537, and thus, when the forced airflow provided by the fan 10 passes through the third heat sink 2533, most of heat generated by the heat generating element can be taken away, and the wind resistance is small, thereby forming an effective heat dissipation channel.

Further, the air inlet 4111 of the housing 411 of the body 41 corresponds to the air inlet 113 of the fan 10, and the exhaust 4113 corresponds to the heat sink 25 far away from one end of the fan 10, so that the heat dissipation channel formed by the heat dissipation system 1 is smoother and more effective.

Further, the heating element 46 of the aircraft 4 adopts the heat dissipation device 47 to contact the housing 411 of the fuselage 41 for natural heat dissipation, so that on one hand, the heat dissipation area of the heat dissipation device 47 is enlarged, the heat dissipation device 47 can adopt a small size, and on the other hand, energy is saved.

It is understood that the inlet air 113 of the fan 10 is directed toward the heat dissipating device 20, so that the heat absorbed by the heat dissipating device 20 from the heat generating element 44 is drawn by the fan 10 through the inlet air 113, at this time, the outlet air 115 of the fan 10 is directed away from the heat dissipating device 20, the inlet air 4111 of the housing 411 corresponds to the outlet air 115, the hot air drawn by the fan 10 is exhausted out of the main body 41, and the outlet air 4113 is a cold air inlet.

In addition, it is obvious to those skilled in the art that other various corresponding changes and modifications can be made according to the technical idea of the present invention, and all such changes and modifications should fall within the scope of the claims of the present invention.

The application comprises the following technical scheme:

the technical scheme 1 is that the aircraft is characterized by comprising a fuselage, a plurality of arms extending outwards from the fuselage, a plurality of rotors mounted to the arms and a heating element positioned in the fuselage;

the machine body comprises a shell and an accommodating space surrounded by the shell, the heating element is arranged in the accommodating space, and the accommodating space is positioned at the bottom of the machine body;

wherein, the relative both sides of casing are equipped with air inlet and gas vent, the air inlet with form an angle between the gas vent, heating element distributes the air inlet with between the gas vent.

2. The aircraft according to claim 1, characterized in that: the heat dissipation device comprises a plurality of airflow channels, and each airflow channel is provided with an airflow inlet.

3. The aircraft according to claim 2, characterized in that: the heat dissipation device comprises a plurality of cooling fins, and the plurality of airflow channels are located among the plurality of cooling fins.

4. The aircraft according to claim 3, characterized in that: the fan is provided with an air opening and is arranged on one side of the heat dissipation device.

5. The aircraft according to claim 4, characterized in that: the air outlet is the air outlet of the fan, the fan is also provided with an air inlet, the air inlet corresponds to the air inlet, and the air outlet corresponds to one end, far away from the fan, of the radiating fin.

6. The aircraft according to claim 4, characterized in that: the air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan faces to the airflow inlet of the airflow channel and is oblique to the extending direction of the airflow channel.

7. The aircraft according to claim 2, characterized in that: each air flow channel is bent.

8. The aircraft according to claim 2, characterized in that: the end of the airflow channels far away from the fan is radial.

9. The aircraft according to claim 2, characterized in that: the airflow inlets of the plurality of airflow channels are parallel to each other.

10. The aircraft according to claim 3, characterized in that: and other airflow channels are arranged among the plurality of radiating fins, and the extending direction of the airflow channels is different from that of the other airflow channels.

11. The aircraft according to claim 2, characterized in that: the heat dissipating device further includes:

a heat conducting plate for absorbing heat generated from the heating element;

a heat pipe coupled to the heat conductive plate;

the radiating fin is positioned on one side of the heat conducting plate.

12. The aircraft of claim 11, wherein: the heat conducting plate is provided with a plurality of accommodating grooves for accommodating the heating elements on one side of the contact surface of the heat conducting plate.

13. The aircraft of claim 11, wherein: the periphery of the heat-conducting plate is provided with a plurality of notches

An aircraft according to claim 14, comprising a fuselage, a plurality of arms extending outwardly from the fuselage, a plurality of rotors mounted to the plurality of arms, a heat generating element located within the fuselage, and a heat sink coupled to the heat generating element;

the heat dissipation device comprises a base and a plurality of heat dissipation fins extending from the base, and the base is attached to the heating element;

the heat dissipation fins face to the shell of the machine body, the heat dissipation fins are in contact with the shell, and the shell is made of heat conduction materials;

the base of the heat dissipation device absorbs heat from the heating element and transfers the heat to the heat dissipation fins, and the heat dissipation fins dissipate the heat outwards, transfer part of the heat to the shell and dissipate the heat out of the machine body from the shell.

15. The aircraft of claim 14, wherein: the housing is provided with a plurality of perforations.

16. The aircraft of claim 14, wherein: the heat dissipation device comprises a plurality of airflow channels, and each airflow channel is provided with an airflow inlet.

17. The aircraft of claim 16, wherein: the aircraft comprises a fan with an air opening, and the air opening is arranged on one side of the heat dissipation device.

18. The aircraft of claim 17, wherein: the air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan is inclined towards the air flow inlets of the air flow channels and the extending direction of the air flow channels.

19. The aircraft of claim 16, wherein: each air flow channel is bent.

20. The aircraft of claim 17, wherein: the end of the airflow channels far away from the fan is radial.

21. The aircraft of claim 16, wherein: the airflow inlets of the plurality of airflow channels are parallel to each other.

22. The aircraft of claim 16, wherein: the heat dissipation device comprises a plurality of cooling fins, and the plurality of airflow channels are located among the plurality of cooling fins.

23. The aircraft of claim 22, wherein: and other airflow channels are arranged among the plurality of radiating fins, and the extending direction of the airflow channels is different from that of the other airflow channels.

24. The aircraft of claim 14, wherein: the heat dissipation device is provided with a plurality of accommodating grooves, the heating element comprises a plurality of electronic components, and the plurality of electronic component devices are accommodated in the accommodating grooves.

25. The aircraft of claim 24, wherein: the heat dissipation device further comprises a heat pipe.

An aircraft according to claim 26, comprising a fuselage, a plurality of arms extending outwardly from the fuselage, a plurality of rotors mounted to the plurality of arms, a heat generating component located within the fuselage, and a heat dissipation system for dissipating heat generated by the heat generating component;

the heat dissipation system is arranged in the accommodating space and comprises a fan, a heat conduction plate and a plurality of heat dissipation fins, and the heat conduction plate is attached to the heating element; the air outlet of the fan faces the plurality of radiating fins; the plurality of radiating fins are positioned on one side of the heat conducting plate and are used for radiating heat absorbed by the heat conducting plate from the heating element;

the radiating fins comprise a plurality of bent radiating fins, and the bent radiating fins are bent along the extending direction of the bent radiating fins.

27. The aircraft of claim 26, wherein: the air outlet of the fan inclines towards the extending direction of the plurality of bent radiating fins.

28. The aircraft of claim 26, wherein: each bent radiating fin sequentially comprises a first radiating part, a second radiating part and a third radiating part along the extending direction of the bent radiating fin, and the extending direction of the second radiating part and the third radiating part is different from the extending direction of the first radiating part.

29. The aircraft of claim 28, wherein: the air opening of the fan is close to the first heat dissipation part and far away from the third heat dissipation part.

30. The aircraft of claim 28, wherein: the second heat sink member is bent to connect the first heat sink member and the third heat sink member.

31. The aircraft of claim 28, wherein: the height of the second heat sink member is greater than the height of the first heat sink member and greater than the height of the third heat sink member.

32. The aircraft of claim 28, wherein: the first heat dissipation parts of the plurality of bent heat dissipation fins are parallel to each other.

33. The aircraft of claim 28, wherein: the third radiating part of the plurality of bent radiating fins is radial along the extending direction.

34. The aircraft of claim 26, wherein: the heat dissipation structure further comprises a plurality of other heat dissipation fins positioned on two sides of the plurality of bent heat dissipation fins, and the extending direction of the other heat dissipation fins is different from the extending direction of the bent heat dissipation fins.

35. The aircraft of claim 26, wherein: the heat conducting plate is provided with a plurality of accommodating grooves, the heating element comprises a plurality of electronic components, and the plurality of electronic component devices are accommodated in the accommodating grooves.

36. The aircraft of claim 26, wherein: the heat dissipation system further includes a heat pipe coupled to the heat conductive plate.

37. The aircraft of claim 26, wherein: the periphery of the heat conducting plate is provided with a plurality of notches for avoiding interference of surrounding elements of the heating element on the heat conducting plate.

Claims

1. An aircraft comprising a fuselage, a plurality of arms extending outwardly from the fuselage, a plurality of rotors mounted to the plurality of arms, and a heating element located within the fuselage;

wherein, the opposite two sides of the shell are provided with an air inlet and an air outlet, an angle is formed between the air inlet and the air outlet, the heating elements are distributed between the air inlet and the air outlet,

the aircraft also includes a heat sink comprising a plurality of airflow channels, including a curved airflow channel.

2. The aircraft of claim 1, wherein: each airflow channel has an airflow inlet.

3. The aircraft of claim 2, wherein: the heat dissipation device comprises a plurality of cooling fins, and the plurality of airflow channels are located among the plurality of cooling fins.

4. The aircraft of claim 3, wherein: the fan is provided with an air opening and is arranged on one side of the heat dissipation device.

5. The aircraft of claim 4, wherein: the air outlet is the air outlet of the fan, the fan is also provided with an air inlet, the air inlet corresponds to the air inlet, and the air outlet corresponds to one end, far away from the fan, of the radiating fin.

6. The aircraft of claim 4, wherein: the air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan faces to the airflow inlet of the airflow channel and is oblique to the extending direction of the airflow channel.

7. The aircraft of claim 4, wherein: one end of the bent airflow channel, which is far away from the fan, is radial.

8. The aircraft of claim 2, wherein: the air flow inlets of the curved air flow channels are parallel to each other.

9. The aircraft of claim 3, wherein: and other airflow channels are arranged among the plurality of radiating fins, and the extending direction of the airflow channels is different from that of the other airflow channels.

10. The aircraft of claim 2, wherein: the heat dissipating device further includes:

a heat conducting plate for absorbing heat generated from the heating element;

a heat pipe coupled to the heat conductive plate;

the heat radiating fin is positioned on one side of the heat conducting plate.

11. The aircraft of claim 10, wherein: the heat conducting plate is provided with a plurality of accommodating grooves for accommodating heating elements on one side of the contact surface.

12. The aircraft of claim 10, wherein: the periphery of the heat-conducting plate is provided with a plurality of notches.

13. An aircraft comprising a fuselage, a plurality of arms extending outwardly from the fuselage, a plurality of rotors mounted to the plurality of arms, a heat-generating element located within the fuselage, and a heat sink coupled to the heat-generating element;

the heat dissipation device comprises a plurality of air flow channels, wherein the plurality of air flow channels comprise bent air flow channels.

14. The aircraft of claim 13, wherein: the housing is provided with a plurality of perforations.

15. The aircraft of claim 13, wherein: each airflow channel has an airflow inlet.

16. The aircraft of claim 15, wherein: the aircraft comprises a fan with an air opening, and the air opening is arranged on one side of the heat dissipation device.

17. The aircraft of claim 16, wherein: the air opening of the fan is obliquely arranged relative to the heat dissipation device, and the air opening of the fan is inclined towards the air flow inlets of the air flow channels and the extending direction of the air flow channels.

18. The aircraft of claim 16, wherein: one end of the bent airflow channel, which is far away from the fan, is radial.

19. The aircraft of claim 15, wherein: the air flow inlets of the curved air flow channels are parallel to each other.

20. The aircraft of claim 15, wherein: the heat dissipation device comprises a plurality of cooling fins, and the plurality of airflow channels are located among the plurality of cooling fins.

21. The aircraft of claim 20, wherein: and other airflow channels are arranged among the plurality of radiating fins, and the extending direction of the airflow channels is different from that of the other airflow channels.

22. The aircraft of claim 13, wherein: the heat dissipation device is provided with a plurality of accommodating grooves, the heating element comprises a plurality of electronic components, and the plurality of electronic component devices are accommodated in the accommodating grooves.

23. The aircraft of claim 22, wherein: the heat dissipation device further comprises a heat pipe.

24. An aircraft comprising a fuselage, a plurality of arms extending outwardly from the fuselage, a plurality of rotors mounted to the plurality of arms, a heat-generating component located within the fuselage, and a heat dissipation system for dissipating heat generated by the heat-generating component;

25. The aircraft of claim 24, wherein: the air outlet of the fan inclines towards the extending direction of the plurality of bent radiating fins.

26. The aircraft of claim 24, wherein: each bent radiating fin sequentially comprises a first radiating part, a second radiating part and a third radiating part along the extending direction of the bent radiating fin, and the extending direction of the second radiating part and the third radiating part is different from the extending direction of the first radiating part.

27. The aircraft of claim 26, wherein: the air opening of the fan is close to the first heat dissipation part and far away from the third heat dissipation part.

28. The aircraft of claim 26, wherein: the second heat sink member is bent to connect the first heat sink member and the third heat sink member.

29. The aircraft of claim 26, wherein: the height of the second heat sink member is greater than the height of the first heat sink member and greater than the height of the third heat sink member.

30. The aircraft of claim 26, wherein: the first heat dissipation parts of the plurality of bent heat dissipation fins are parallel to each other.

31. The aircraft of claim 26, wherein: the third radiating part of the plurality of bent radiating fins is radial along the extending direction.

32. The aircraft of claim 24, wherein: the heat dissipation structure further comprises a plurality of other heat dissipation fins positioned on two sides of the plurality of bent heat dissipation fins, and the extending direction of the other heat dissipation fins is different from the extending direction of the bent heat dissipation fins.

33. The aircraft of claim 24, wherein: the heat conducting plate is provided with a plurality of accommodating grooves, the heating element comprises a plurality of electronic components, and the plurality of electronic component devices are accommodated in the accommodating grooves.

34. The aircraft of claim 24, wherein: the heat dissipation system further includes a heat pipe coupled to the heat conductive plate.

35. The aircraft of claim 24, wherein: the periphery of the heat conducting plate is provided with a plurality of notches for avoiding interference of surrounding elements of the heating element on the heat conducting plate.