CN107211556A

CN107211556A - Cooling system and the aircraft with cooling system

Info

Publication number: CN107211556A
Application number: CN201580069093.6A
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: 2017-09-26
Anticipated expiration: 2035-12-03
Also published as: CN109673139B; CN107211556B; WO2017091997A1; CN109673139A

Abstract

A kind of cooling system and the aircraft with the cooling system.Cooling system (1), including substrate (251), multiple fin (253) and fan (10)；The substrate (251) has first surface (2511) and the second surface (2512) relative with the first surface (2511), and the multiple fin (253) is located at the first surface (2511) of the substrate；The fan (10) has air port, the fan (10) is arranged at the side of the first surface (2511) of the substrate (251), the air port of the fan (10) is tilted relative to the first surface (2511) of the substrate (251), and the air port of the fan (10) is tilted towards the multiple fin (253) and to the bearing of trend of the multiple fin (253).Reduce the occupancy size of cooling system in height, the pressure air current flow direction that fan is provided is consistent with the bearing of trend of the fin/gas channel, so that the pressure air-flow that fan is provided is when by the fin/gas channel, windage is smaller, forms effective heat dissipation channel.

Description

Cooling system and aircraft with cooling system

Technical field

The present invention relates to a heat dissipation technology more particularly to a kind of cooling system and the aircraft with the cooling system.

Background technique

With the development of electronic technology, the integration degree of chip is higher and higher, and chip size is smaller and smaller, and the heat flow density of chip is also higher and higher therewith.In the product that these chips are applied to miniaturization, interiors of products narrow space structure is unfavorable for the heat dissipation of chip.Temperature is to influence the key factor of chip reliability, and as the temperature rises, the crash rate of chip can increase at the relationship of geometric multiple.Therefore, how fast and effeciently to radiate to chip, be an important factor for determining product reliability.

At present, the electronic product of similar high heat flux density, major part has carried out the conceptual design of active heat removal, this scheme adds the mode of radiator using fan, the heat flow density of chip is reduced using radiator, then it blows forced-convection heat transfer as the cooling fin of radiator using fan the heat on radiator sheds, to achieve the purpose that reduce chip temperature.

However, the small space of interiors of products adds the mode of radiator according to fan, it often is faced with fan layout difficulty, air duct has some setbacks, it is difficult to form the such technical problem of effective heat dissipation channel.

Some chips are arranged in aircraft especially unmanned vehicle, fuselage interior, and the design of these chip cooling schemes is also influenced by fuselage interior narrow space.

Summary of the invention

In view of this, it is necessary to provide a kind of cooling system with effective heat dissipation channel and the aircraft with the cooling system.

The present invention relates to a kind of cooling systems, comprising: substrate, multiple cooling fins and fan.The substrate has first surface and the second surface opposite with the first surface.The multiple cooling fin is set to the first surface of the substrate.The fan has air port, is set to the side of the first surface of the substrate.The air port of the fan is tilted relative to the first surface of the substrate, and the air port of the fan is tilted towards the multiple cooling fin and to the extending direction of the multiple cooling fin.

The invention further relates to a kind of cooling systems, comprising: radiator and fan.The radiator includes multiple airflow channels, and each airflow channel has an air flow inlet.The fan has air port, is set to the side of the radiator.The air port of the fan is obliquely installed relative to the radiator, the air port of the fan towards the multiple airflow channel air flow inlet and tilted to the extending direction of the airflow channel.

The invention further relates to a kind of aircraft, comprising: fuselage and cooling system.The fuselage includes: shell, accommodating space and heater element.The accommodating space is surrounded by the shell.The heater element is contained in the accommodating space.The cooling system is used to distribute the heat that the heater element generates.In the accommodating space, the cooling system includes: heat-conducting plate, multiple cooling fins and fan for the cooling system setting.The heat-conducting plate fits in the heater element.The multiple cooling fin is located at the heat-conducting plate side, the heat absorbed for distributing the heat-conducting plate from the heater element.The fan has air port, is set to one end of the multiple cooling fin.The air port of the fan is tilted towards the multiple cooling fin and to the extending direction of the multiple cooling fin.

The invention further relates to a kind of aircraft, comprising: fuselage and cooling system.The fuselage includes: shell, accommodating space and heater element.The accommodating space is surrounded by the shell.The heater element receiving is in the accommodating space.The cooling system, the heat generated for distributing the heater element.In the accommodating space, the cooling system includes: radiator and fan for the cooling system setting.The radiator includes multiple airflow channels, and each airflow channel has air flow inlet.The fan has air port, is set to the side of the radiator.The air port of the fan is obliquely installed relative to the radiator, the air port of the fan towards the multiple airflow channel air flow inlet and tilted to the extending direction of the airflow channel.

Compared with prior art, the present invention is obliquely installed using wind, reduces the occupancy size of cooling system in height.The air port of the fan is tilted towards the cooling fin/airflow channel and to the extending direction of the cooling fin/airflow channel, so that the pressure air-flow that fan provides blows to the cooling fin/airflow channel, and make to force air current flow direction consistent with the extending direction of the cooling fin/airflow channel, pressure air-flow to make fan provide is when by the cooling fin/airflow channel, windage is smaller, forms effective heat dissipation channel.

Further, each cooling fin is in Curved along its extending direction.

Further, the multiple cooling fin is located at the medium position of the substrate first surface.

Further, each cooling fin extends along direction successively and includes the first radiating part, the second radiating part and third radiating part, and the extending direction of second radiating part and the third radiating part is different from the extending direction of first radiating part.

Further, the air port of the fan is close to first radiating part, and the separate third radiating part.

Further, second radiating part connects first radiating part and the third radiating part in Curved.

Further, the height of second radiating part is greater than the height of first radiating part, and is greater than the height of the third radiating part.

Further, the first radiating part of the multiple cooling fin is parallel to each other.

Further, it is radial to extend along direction for the third radiating part of the multiple cooling fin.

Further, the cooling system further includes other multiple cooling fins positioned at the multiple cooling fin two sides, and the extending direction of other cooling fins is different from the extending direction of the cooling fin.

Further, the cooling system further include:

Heat-conducting plate, for absorbing the heat of heater element generation, including the contact surface for being bonded with heater element and the faying face in conjunction with the second substrate surface；

Heat pipe, between the substrate and the heat-conducting plate.

Further, the heat-conducting plate is arranged multiple for accommodating the accommodation groove of heater element in the side of its contact surface.

Further, multiple recesses are arranged in the periphery of the heat-conducting plate.

Further, each airflow channel is in Curved.

Further, the one end of the multiple airflow channel far from the fan is radial.

Further, the air flow inlet of the multiple airflow channel is parallel to each other.

Further, the multiple airflow channel is between the multiple cooling fin.

Further, also there are other airflow channels, the extending direction of the airflow channel is different from the extending direction of other airflow channels between the multiple cooling fin.

Further, the fan is tube-axial fan.

Further, the shell has air inlet and exhaust outlet, and the air port is the air outlet of the fan, and the fan also has air inlet, and the air inlet corresponds to the air inlet, and the exhaust outlet corresponds to the one end of the cooling fin far from the fan.

Further, the aircraft further include: another heater element and another radiator.Another radiator includes the multiple radiating fins for being bonded the pedestal of another heater element and extending from the pedestal.

Further, the material of the shell is Heat Conduction Material, and the radiating fin contacts the shell.

Further, the shell is equipped with multiple perforation.

Detailed description of the invention

Fig. 1 is an a kind of floor map of cooling system that embodiment of the present invention provides.

Fig. 2 is the perspective exploded view of the radiator of cooling system shown in FIG. 1.

Fig. 3 is the combination view of radiator shown in Fig. 2.

Fig. 4 is the diagrammatic cross-section along IV-IV line of radiator shown in Fig. 3.

Fig. 5 is another floor map of cooling system shown in FIG. 1.

Fig. 6 is the another floor map of cooling system shown in FIG. 1.

Fig. 7 is the partial schematic sectional view for the aircraft with cooling system that embodiment of the present invention provides.

Fig. 8 is the enlarged drawing schematic diagram of the part VIII in Fig. 7.

Fig. 9 is the enlarged drawing schematic diagram of the part IX in Fig. 7.

Main element symbol description

Cooling system	1
Fan	10
Shell	11
Air duct	111
Air inlet	113
Air outlet	115
Mounting rack	13
Rib	131
Radiator	20
Heat-conducting plate	21
Contact surface	211
Faying face	213
Groove	215
Recess	217
Accommodation groove	219
Heat pipe	23
First heat transfer segment	231
Second heat transfer segment	233
Third heat transfer segment	235
Radiator	25
Substrate	251
First surface	2511
Second surface	2512
Fitting groove	2513
First side	2514
Second side	2515
Third side	2516
Four side	2517
Recess	2518
Cooling fin	253
First cooling fin	2531
Second cooling fin	2532
Third cooling fin	2533
First radiating part	25331
Second radiating part	25332
Third radiating part	25333
4th cooling fin	2534
First airflow channel	2535
Second airflow channel	2536
Third airflow channel	2537
Air flow inlet	25371
Air stream outlet	25372
4th airflow channel	2538
Fixed part	255
Fixation hole	2551
Aircraft	4
Fuselage	41
Shell	411
Air inlet	4111
Exhaust outlet	4113
Perforation	4115
Accommodating space	413
Horn	42
Rotor	43
Heater element	44
Fixed device	45
Heater element	46
Radiator	47
Pedestal	471
Radiating fin	473

The present invention that the following detailed description will be further explained with reference to the above drawings.

Specific embodiment

Following will be combined with the drawings in the embodiments of the present invention, and technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, every other embodiment obtained by those of ordinary skill in the art without making creative efforts, shall fall within the protection scope of the present invention.

It should be noted that it can be directly on another component or there may also be components placed in the middle when component is referred to as " being fixed on " another component.When a component is considered as " connection " another component, it can be directly to another component or may be simultaneously present component placed in the middle.When a component is considered as " being set to " another component, it, which can be, is set up directly on another component or may be simultaneously present component placed in the middle.Term as used herein "vertical", "horizontal", "left" and "right" and similar statement are for illustrative purposes only.

Unless otherwise defined, 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.Term as used herein in the specification of the present invention, which is only for the purpose of describing specific embodiments, is not intended to limit the present invention.Term " and or " used herein includes any and all combinations of one or more related listed items.

Referring to Fig. 1, embodiment of the present invention provides a kind of cooling system 1, the cooling system 1 is for radiating to electronic component.The cooling system 1 includes fan 10 and the radiator 20 with the fan 10 cooperation.The relatively described radiator 20 of the fan 10 is obliquely installed.

The fan 10 can be tube-axial fan or radial fan.In the present embodiment, the fan 10 is tube-axial fan.The fan 10 includes shell 11, mounting rack 13 and impeller (not shown).The hollow formation air duct 111 of the shell 11, the opposite end of the air duct 111 are open to form air inlet 113 and air outlet 115.The mounting rack 13 is set in the air duct 111 and by the fixation of multiple ribs 131 and the shell 11.The impeller is contained in the air duct 111 and is rotatably mounted to the mounting rack 13.

Fig. 2 and Fig. 3 are please referred to, the radiator 20 includes heat-conducting plate 21, the heat pipe 23 combined with the heat-conducting plate 21 and the radiator 25 connecting with the heat-conducting plate 21 and 23 thermal conductivity of the heat pipe.

The heat-conducting plate 21 includes contact surface 211 and faying face 213.The contact surface 211 is used for contact heating element.The faying face 213 is used in conjunction with the radiator 25.213 side of faying face of the heat-conducting plate 21 is equipped with the groove 215 for accommodating the heat pipe 23.The groove 215 extends from the faying face 213 towards 211 direction of contact surface and has certain depth.The shape of the groove 215 can be correspondingly arranged according to the shape of the heat pipe 23, can be linear type, flexure type, can be S-shaped, C-shaped, U-shaped, M shape, N shape etc. when for flexure type.In the present embodiment, the groove 215 is in U-shape.

The shape of the heat-conducting plate 21 can be arranged according to actual needs.In the present embodiment, the heat-conducting plate 21 is polygon.The periphery of the heat-conducting plate 21 is equipped with multiple recesses 217, and the installation site to heat-conducting plate 21 to avoid peripheral element when being installed on heater element forms interference.211 side of contact surface of the heat-conducting plate 21 is additionally provided with the accommodation groove 219 of multiple receiving heater elements.The multiple accommodation groove 219 extends from the contact surface 211 towards 213 direction of faying face and has certain depth.The depth of the multiple accommodation groove 219 may be configured as identical or different according to the height of heater element.

The material of the heat-conducting plate 21 is the good metal of heating conduction, such as copper, aluminium, can also be heat conductivity graphite material or conductive hot carbon nano material.Also phase change medium, such as water, ethyl alcohol, ether can be filled inside the heat-conducting plate 21.

The heat pipe 23 is the internal metal tube for being filled with phase change medium, and the phase change medium can be water, ethyl alcohol, ether etc..

The heat pipe 23 can be tubular, semi-circle tubular, pancake etc..In this implementation, the heat pipe 23 is pancake, with two opposite parallel flat surfaces, for being bonded with the heat-conducting plate 21 and the radiator 25.The heat pipe 23 includes the first heat transfer segment 231, the second heat transfer segment 233 and third heat transfer segment 235.Second heat transfer segment 233 extends outwardly from one end of first heat transfer segment 231.The third heat transfer segment 235 extends outwardly from the other end of first heat transfer segment 231.In other words, the extending direction of second heat transfer segment 233 and the third heat transfer segment 235 is different from the end of first heat transfer segment 231 direction.

In the present embodiment, the shape of the corresponding above-mentioned groove 215 of the heat pipe 23 is in U-shape.First heat transfer segment 231, second heat transfer segment 233 and the third heat transfer segment collectively form the U-shaped structure of the heat pipe 23.First heat transfer segment 231 is linear.Second heat transfer segment 233 is linear.The round and smooth connection in curved surface of the junction of first heat transfer segment 231 and the second heat transfer segment 233.The third heat transfer segment 235 is linear.The round and smooth connection in curved surface of the junction of first heat transfer segment 231 and the third heat transfer segment 235.Second heat transfer segment 233 is parallel to the third heat transfer segment 235.Second heat transfer segment 233 and the third heat transfer segment 235 are approximately perpendicular to first heat transfer segment 231.In one embodiment, the length of the third heat transfer segment 235 is less than the length of second heat transfer segment 233.

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

The radiator 25 includes substrate 251 and the multiple cooling fins 253 being set on the substrate 251.Multiple airflow channels are formed between the multiple cooling fin 253.

The substrate 251 is the good metal plate of heating conduction, can also be heat conductive graphite plate body or conductive hot carbon nano plate body.The substrate 251 extends further out multiple fixed parts 255.The substrate 251 includes first surface 2511 and the second surface 2512 opposite with the first surface 2511.The substrate 251 can set fitting groove 2513 (please referring to Fig. 4) in the groove 215 that the side of its second surface 2512 corresponds to the heat-conducting plate 21, for accommodating the heat pipe 23.

The shape of the substrate 251 can be rectangular, trapezoidal, round or other polygons.In the present embodiment, the substrate 251 is substantially square comprising first side 2514, second side 2515, the third side 2516 opposite with the first side and the four side 2517 opposite with the second side.In the present embodiment, the second side 2515 is roughly parallel to the four side 2517.Multiple recesses 2518 are set at the third side 2516, and peripheral element forms interference to the installation site of the substrate 251 when being installed on heater element to avoid the radiator 20.The first side 2514, second side 2515, third side 2516 and four side 2517 are all connected with the first surface 2511 and second surface 2512.

In the present embodiment, each fixed part 255, which is set to, fixation hole 2551.

The multiple cooling fin 253 is arranged on 251 first surface 2511 of substrate.The cooling fin of different shape or placement direction that the multiple cooling fin 253 includes.In the present embodiment, the multiple cooling fin 253 includes multiple first cooling fins 2531, multiple second cooling fins 2532, multiple third cooling fins 2533 and multiple 4th cooling fins 2534.

The multiple first cooling fin 2531 is set to the substrate 251 close to one end of the second side 2515.The multiple first cooling fin 2531, which is parallel to each other, is spaced setting.The first airflow channel 2535 is formed between adjacent first cooling fin 2531.Every one first cooling fin 2531 is roughly parallel to the second side 2515.Every one first cooling fin 2531 extends at the third side 2516 from from the first side 2514.Every one first cooling fin 2531 extends along direction and is of a straight line type.In the present embodiment, defines the first cooling fin 2531 and extended in a first direction from from the first side 2514.

First airflow channel 2535 is linear, extends close at the third side 2516 from the close first side 2514 along 2515 direction of second side and is roughly parallel to the second side 2515.In the present embodiment, first airflow channel 2535 is extended in a first direction from from first side 2514.

The multiple second cooling fin 2532 is set to the substrate 251 close to the side of the third side 2516.In the present embodiment, the multiple second cooling fin 2532 is between first cooling fin 2531 and the third cooling fin 2533.The multiple second cooling fin 2532 is spaced apart from each other setting.The second airflow channel 2536 is formed between adjacent second cooling fin 2532.Every one second cooling fin 2532 extends along from the second side 2515 towards the direction of the third side 2516 and the relatively described second side 2515 and the inclined angle in the third side 2516.Every one second cooling fin 2532 is inclined to set relative to first cooling fin 2531.It has angle between second cooling fin 2532 and first cooling fin 2531.In the present embodiment, defines second cooling fin 2532 and extend in a second direction from from the second side 2515.The multiple second cooling fin 2532 is slightly radial along the direction far from first cooling fin 2531.The length of the multiple second cooling fin 2532 can not be identical.In the present embodiment, the length of the multiple second cooling fin 2532 is gradually increased along the direction of third side 2516 towards the first side 2514, that is, the length of the multiple second cooling fin 2532 is gradually increased from the edge of the substrate 251 to center position.

Second airflow channel 2536 is linear, from the direction from the second side 2515 towards the third side 2516 and the relatively described second side 2515 and the extension of the inclined angle in the third side 2516.That is, second airflow channel 2536 substantially extends along the diagonal direction of the substrate 251 from from the second side 2515.In the present embodiment, second airflow channel 2536 extends in a second direction from from the second side 2515.The second direction is different from the first direction.There is an angle between the second direction and the first direction.

The multiple third cooling fin 2533 is set to the medium position of the substrate 251.The multiple third cooling fin 2533 is between second cooling fin 2532 and the 4th cooling fin 2534.Each third cooling fin 2533 extends to the four side 2517 close to one end of the second side 2515 from the first side 2514.That is, the third cooling fin 2533 substantially extends along the diagonal direction of the substrate 251 from the first side 2514 close to one end of the second side 2515.The multiple third cooling fin 2533 is spaced apart from each other setting, third airflow channel 2537 is formed between adjacent third cooling fin 2533, the third airflow channel 2537 extends to from the four side 2517 from the first side 2514 close to one end of the second side 2515.Each third cooling fin 2533 extends along direction in curved shape.Each third cooling fin 2533 extends along direction successively and includes one first radiating part 25331, from outwardly extending second radiating part in described first radiating part, 25331 one end 25332 and one from the outwardly extending third radiating part 25333 of second radiating part 25332.

It is linear that first radiating part 25331 extends along direction.First radiating part 25331 of the multiple third cooling fin 2533 is close to the first side 2514.In the present embodiment, the first radiating part 25331 of the multiple third cooling fin 2533 is parallel to each other.In the present embodiment, the first radiating part 25331 of the multiple third cooling fin 2533 is parallel to first cooling fin 2531 and the second side 2515.First radiating part 25331 extends in a first direction from the first side 2514.In the present embodiment, the first radiating part 25331 of the multiple third cooling fin 2533 is perpendicular to the first side 2514.The height of each third cooling fin 2533 extends along direction and gradually increases.The third airflow channel 2537 forms air flow inlet 25371 at first radiating part 25331.

Second radiating part 25332 extends along direction in Curved.Second radiating part 25332 connects first radiating part 25331 and the third radiating part 25333.Second radiating part 25332 of the multiple third cooling fin 2533 is located substantially at the middle part of the substrate 251.Second radiating part 25332 of the multiple third cooling fin 2533 is parallel to each other or to extend along direction slightly radial.The extending direction of second radiating part 25332 is different from first direction, that is, different from the extending direction of the first radiating part 25331.The height of every one second radiating part 25332 is greater than the height of first radiating part 25331 and the third radiating part 25333.

It is linear that the third radiating part 25333 extends along direction.The third radiating part 25333 of the multiple third cooling fin 2533 extends to the four side 2517.The diagonal of the substantially described substrate 251 of the extending direction of the third radiating part 25333.The extending direction of the third radiating part 25333 is different from the first direction, that is, different from the extending direction of the first radiating part 25331.In the present embodiment, it is radial that the third radiating part 25333 of the multiple third cooling fin 2533 extends along direction.In one embodiment, the third radiating part 25333 of the multiple third cooling fin 2533 and first cooling fin 2531 or the angle of second side 2515 are 50-70 degree.The third airflow channel 2537 forms air stream outlet 25372 at the third radiating part 25333.

The third airflow channel 2537 is in Curved, and extends to the four side 2517 from the first side 2514 close to one end of the second side 2515.That is, the third airflow channel 2537 is in Curved, and substantially extend along the diagonal direction of the substrate 251 from the first side 2514 close to one end of the second side 2515.In the present embodiment, defines the third airflow channel 2537 and extend from the first side 2514 close to one end of the second side 2515 along third direction.The third direction is in Curved, different from the first direction, second direction.

The multiple 4th cooling fin 2534 is located at the substrate 251 close to the corner of the first side 2514 and the four side 2517.The multiple 4th cooling fin 2534 is located at the side of the third cooling fin 2533.The multiple 4th cooling fin 2534 is spaced apart from each other setting, forms the 4th airflow channel 2538 between adjacent 4th cooling fin 2534.In the present embodiment, the multiple 4th cooling fin 2534 is parallel to each other.In this implementation, the multiple 4th cooling fin 2534 is parallel to the first side 2514.In one embodiment, the length of the multiple 4th cooling fin 2534 is not identical.

4th airflow channel 2538 is linear, extends along the direction for being parallel to the first side 2514.In the present embodiment, defines the 4th airflow channel 2538 and extend along fourth direction.The fourth direction is different from the first direction, second direction and third direction.The fourth direction is approximately perpendicular to the first direction.

Please refer to Fig. 4, when assembling the radiator 20, the heat pipe 23 is contained in the groove 215 of the heat-conducting plate 21, and the second surface 2512 of the substrate 251 of the radiator 25 is bonded the faying face 213 of the heat-conducting plate 21.The heat pipe 23 is further contained in the fitting groove 2513 of the substrate 251, and is folded between the heat-conducting plate 21 and the substrate 251.In one embodiment, it is coated with tin cream in the groove 215, the fitting groove 2513 and between the heat-conducting plate 21 and the substrate 251, for reducing the thermal resistance between the heat-conducting plate 21, the heat pipe 23 and the substrate 251.

Fig. 1, Fig. 5 and Fig. 6 are please referred to, when assembling the fan 10 and the radiator 20, the fan 10 is obliquely placed in the side of the radiator 20.The air outlet 115 of the fan 10 is obliquely installed relative to the first surface 2511 of the substrate 251.The air outlet 115 of the fan 10 has certain distance towards the cooling fin 253, and with the cooling fin 253, and the air inlet 113 of the fan 10 deviates from the cooling fin 253.In the present embodiment, the fan 10 corresponds to the first side 2514 of the substrate 251 of the radiator 25 at the second side 2515, first radiating part 25331 of its air outlet 115 towards the third cooling fin 2533, i.e. towards the air flow inlet 25371 of the third airflow channel 2537, and tilted to the extending direction of the third cooling fin 2533, third airflow channel 2537.

Please refer to Fig. 5, the second side 2515 of the substrate 251 of the air outlet 115 of the fan 10 and the radiator 25, four side 2517 are at 12 degree of angle, that is, the air outlet 115 of the fan 10 is tilted towards the substrate 251 and to the extending direction of the first radiating part 25331 of the third cooling fin 2533.

Please refer to Fig. 6, the first side 2514 of the substrate 251 of the air outlet 115 of the fan 10 and the radiator 25 is at 3 degree of angle, that is, the air outlet 115 of the fan 10 is tilted towards the substrate 251 and to the extending direction of the second radiating part 25332 of the third cooling fin 2533 and third radiating part 25333.

So, the air outlet 115 of the fan 10 is tilted towards the third cooling fin 2533 and to the extending direction of the third cooling fin 2533, that is, the air outlet 115 of fan 10 towards the third airflow channel 2537 air flow inlet 25371 and to the extending direction of the third airflow channel 2537 tilt.

In use, the heat-conducting plate 21 of the radiator 20 of the cooling system 1 absorbs heat from heater element.The heat pipe 23 of the radiator 20 absorbs heat from the heat-conducting plate 21 and even heat is further distributed in the heat-conducting plate 21.The heat-conducting plate 21 and the heat pipe 23 transfer heat to the substrate 251 and cooling fin 253 of the radiator 25 of the radiator 20.The fan 10 of the cooling system 1 will force air-flow to blow to the cooling fin 253 via its air outlet 115.Due to the fan 10 air outlet 115 towards the cooling fin 253 third cooling fin 2533 and to the extending direction of the third cooling fin 2533 tilt, what the fan 10 provided forces air-flow largely to enter the third airflow channel 2537 between the third cooling fin 2533, and small part enters the 4th airflow channel 2538 between the first airflow channel 2535 between first cooling fin 2531, the second airflow channel 2536 and the 4th cooling fin 2534 between the second cooling fin 2532.Pressure air-flow into the third airflow channel 2537 flows along 2533 extending direction of third cooling fin and takes away the heat on the third cooling fin 2533.Equally, the heat on first cooling fin 2531, the second cooling fin 2532 and the 4th cooling fin 2534 is taken away into the air-flow of first airflow channel 2535, the second airflow channel 2536 and the 4th airflow channel 2538.

Compared with the existing technology, the fan 10 is obliquely installed relative to the substrate 251, so that the fan 10 occupies little space with the radiator 20.The air outlet 115 of the fan 10 is towards the air flow inlet 25371 of the third airflow channel 2537 and the extending direction of third airflow channel 2537 to the third cooling fin 2533 and therebetween tilts, so that the pressure air-flow that fan 10 provides blows to third cooling fin 2533, and make to force airflow direction consistent with the extending direction of the third cooling fin 2533 and third airflow channel 2537, pressure air-flow to make fan 10 provide is when by the third cooling fin 2533, most of heat of heater element generation can be taken away, and windage reduces, form effective heat dissipation channel.

In addition, the second radiating part 25332 of the third cooling fin 2533 extends along direction in Curved, so that the heat exchange of pressure air-flow and third cooling fin 2533 that the fan 10 provides is more abundant.The height of second radiating part 25332 is greater than the height of first radiating part 25331 and the third radiating part 25333, and the heat exchange of the pressure air-flow and third cooling fin 2533 that provide the fan 10 is further abundant.

In addition, first cooling fin 2531 is located at the side of the third cooling fin 2533, the pressure air-flow for avoiding the fan 10 from providing is blowed to except the radiator 25, so that the utilization rate for the pressure air-flow that fan 10 provides is improved.

In addition, second cooling fin 2532 and the 4th cooling fin 2534 extend in different directions, so that the part that the fan 10 provides forces air-flow to be oriented to the different places of the radiator 25, so that it is more effective to radiate.

In addition, the radiator 20 uses heat pipe 23, so that the distribution that the heat of the absorption of heat-conducting plate 21 is more uniform, avoids hot-spot phenomenon.

Understandably, the air inlet 113 of the fan 10 can be towards the radiator 20, so that the heat that the radiator 20 is absorbed from heater element is aspirated away via the air inlet 113 by the fan 10, at this point, the air outlet 115 of the fan 10 deviates from the radiator 20.

Referring to Fig. 7, an embodiment of the present invention provides a kind of aircraft 4.The aircraft 4 includes the cooling system 1.The aircraft 4 includes fuselage 41, the heater element 44 (please referring to Fig. 8) from the outwardly extending multiple horns 42 of the fuselage 41, installation to multiple rotors 43 of the multiple horn 42 and in the fuselage 41.The heater element 44 may include one or more heating electronic components.

The fuselage 41 includes shell 411 and the accommodating space 413 surrounded by the shell 411.The heater element 44 is placed in the accommodating space 413.In one embodiment, the heater element 44 is installed on mounting plate.The accommodating space 413 is between the mounting plate and the shell 411.In the present embodiment, the accommodating space 413 is located at the bottom of the fuselage 41.

The opposite sides of the shell 411 is equipped with air inlet 4111 and exhaust outlet 4113.Shape at an angle, not will cause the circulation of hot-fluid between the air inlet 4111 and the exhaust outlet 4113.44 integrated distribution of heater element is between the air inlet 4111 and exhaust outlet 4113.Multiple perforation 4115 can be further arranged in corresponding 413 position of accommodating space of the shell 411.

Please refer to Fig. 8, the heat-conducting plate 21 of the radiator 20 of the cooling system 1 conforms to the heater element 44.It can be also further bonded by heat-conducting medium between the heat-conducting plate 21 and the heater element 44.The air inlet 4111 of the corresponding shell 411 of the air inlet 113 of the fan 10 of the cooling system 1.Exhaust outlet 4113 of the one end of the radiator 20 far from the fan 10 close to the shell 411.The fan 10 can be fixed on the shell 411 by fixed device 45.

Fig. 7 and Fig. 9 are please referred to, the aircraft 4 may also include another heater element 46 being placed in the accommodating space 413.The heater element 46 may include one or more heating electronic components.The aircraft 4 includes another radiator 47 for being bound to the heater element 46.The heater element 46 is located at the side of the heater element 44 and the cooling system 1.Exhaust outlet 4113 of the heater element 46 close to the shell 411.

Please refer to Fig. 9, the radiator 47 includes pedestal 471 and multiple radiating fins 473 from the pedestal 471 extension.The pedestal 471 conforms to the heater element 46.It can be also further bonded by heat-conducting medium between the pedestal 471 and the heater element 44.The pedestal 471 can also set multiple containers, for accommodating multiple electronic components of the heater element 46.Shell 411 of the radiating fin 473 towards fuselage 41.In the present embodiment, the radiating fin 473 contacts the shell 411, and the shell 411 is metal material or other Heat Conduction Materials, such as conductive hot carbon nano material.

In use, the heater element 44 works and generates heat.The heat-conducting plate 21 of the radiator 20 of the cooling system 1 absorbs the heat that heater element generates.The heat pipe 23 of the radiator 20 absorbs heat from heat-conducting plate 21 and even heat is further distributed in the heat-conducting plate 21.The heat-conducting plate 21 and the heat pipe 23 transfer heat to the substrate 251 and cooling fin 253 of the radiator 25 of the radiator 20.The fan 10 of the cooling system 1 will force air-flow to blow to the cooling fin 253 via 113 air-breathing of air inlet 4111 and its air inlet of the shell 411 of the fuselage 41 via its air outlet 115.Due to the fan 10 air outlet 115 towards the cooling fin 253 third cooling fin 2533 and to the extending direction of the third cooling fin 2533 tilt, what the fan 10 provided forces air-flow largely to enter the third airflow channel 2537 between the third cooling fin 2533, and small part enters the 4th airflow channel 2538 between the first airflow channel 2535 between first cooling fin 2531, the second airflow channel 2536 and the 4th cooling fin 2534 between the second cooling fin 2532.Pressure air-flow into the third airflow channel 2537 flows along 2533 extending direction of third cooling fin and takes away the heat on the third cooling fin 2533.Equally, the heat on first cooling fin 2531, the second cooling fin 2532 and the 4th cooling fin 2534 is taken away into the air-flow of first airflow channel 2535, the second airflow channel 2536 and the 4th airflow channel 2538.It is discharged outside the fuselage 41 by the thermal current of the cooling fin 253 by the exhaust outlet 4113 of the shell 411.

Similarly, the heater element 46 works and generates heat, and the pedestal 471 of the radiator 47 absorbs heat from heater element 46 and transfers heat to the radiating fin 473.The radiating fin 473 distributes heat outward, and a part of heat transfer to the shell 411 is distributed by the shell 411 to outside the fuselage 41.

Compared with the existing technology, the fan 10 is obliquely installed so that the fan 10 and the radiator 20 reduce occupancy size in height relative to the substrate 251, adapts to or save space in the fuselage 41.The air outlet 115 of the fan 10 is towards the air flow inlet 25371 of the third airflow channel 2537 and the extending direction of third airflow channel 2537 to the third cooling fin 2533 and therebetween tilts, so that the pressure air-flow that fan 10 provides blows to third cooling fin 2533, and make to force airflow direction consistent with the extending direction of the third cooling fin 2533 and third airflow channel 2537, pressure air-flow to make fan 10 provide is when by the third cooling fin 2533, most of heat of heater element generation can be taken away, and windage is smaller, form effective heat dissipation channel.

Further, the air inlet 113 of the corresponding fan 10 of the air inlet 4111 of 41 shell 411 of fuselage, the corresponding described one end of radiator 25 far from the fan 10 of exhaust outlet 4113, so that the heat dissipation channel that the cooling system 1 is formed is more smoothly effectively.

Further, the heater element 46 of the aircraft 4 contacts the shell 411 of the fuselage 41 using radiator 47, carries out natural heat dissipation, on the one hand expands the heat dissipation area of radiator 47, so that small size can be used in the radiator 47, the energy is on the other hand saved.

Understandably, the air inlet 113 of the fan 10 can be towards the radiator 20, so that the heat that the radiator 20 is absorbed from the heater element 44 is aspirated via the air inlet 113 by the fan 10, at this time, the air outlet 115 of the fan 10 deviates from the radiator 20, the air inlet 4111 of the shell 411 then corresponds to the air outlet 115, and the hot-air that the fan 10 is aspirated is discharged outside the fuselage 41, and the exhaust outlet 4113 is then cold air air inlet.

In addition, for those of ordinary skill in the art, various other changes and modifications can be made in accordance with the technical idea of the present invention, and all these changes and deformation all should belong to the protection scope of the claims in the present invention.

Claims

A kind of cooling system, comprising:

Substrate has first surface and the second surface opposite with the first surface；And

Multiple cooling fins, set on the first surface of the substrate；And

Fan, has air port, and the fan is set to the side of the first surface of the substrate；

It is characterized by: the air port of the fan is tilted relative to the first surface of the substrate, the air port of the fan is tilted towards the multiple cooling fin and to the extending direction of the multiple cooling fin.
Cooling system as described in claim 1, it is characterised in that: each cooling fin is in Curved along its extending direction.
Cooling system as claimed in claim 2, it is characterised in that: the cooling fin is located at the middle position of the substrate first surface.
Cooling system as claimed in claim 2, it is characterized by: it includes the first radiating part, the second radiating part and third radiating part that each cooling fin, which extends along direction successively, the extending direction of second radiating part and the third radiating part is different from the extending direction of first radiating part.
Cooling system as claimed in claim 4, it is characterised in that: the air port of the fan is close to first radiating part, and the separate third radiating part.
Cooling system as claimed in claim 5, it is characterised in that: second radiating part connects first radiating part and the third radiating part in Curved.
Cooling system as claimed in claim 6, it is characterised in that: the height of second radiating part is greater than the height of first radiating part, and is greater than the height of the third radiating part.
Cooling system as claimed in claim 6, it is characterised in that: the first radiating part of the multiple cooling fin is parallel to each other.
Cooling system as claimed in claim 6, it is characterised in that: it is radial that the third radiating part of the multiple cooling fin extends along direction.
Cooling system as described in claim 1, it is characterised in that: further include other multiple cooling fins positioned at the multiple cooling fin two sides, the extending direction of other cooling fins is different from the extending direction of the cooling fin.
Cooling system as described in claim 1, it is characterised in that: further include:

Heat-conducting plate, for absorbing the heat of heater element generation, including the contact surface for being bonded with heater element and the faying face in conjunction with the second substrate surface；

Heat pipe, between the substrate and the heat-conducting plate.
Cooling system as claimed in claim 11, it is characterised in that: the heat-conducting plate is arranged multiple for accommodating the accommodation groove of heater element in the side of its contact surface.
Cooling system as claimed in claim 11, it is characterised in that: multiple recesses are arranged in the periphery of the heat-conducting plate.
A kind of cooling system, comprising:

Radiator, including multiple airflow channels, each airflow channel have air flow inlet；And

Fan has air port, is set to the side of the radiator；

It is characterized by: the air port of the fan is obliquely installed relative to the radiator, the air port of the fan towards the airflow channel air flow inlet and tilted to the extending direction of the airflow channel.
Cooling system as claimed in claim 14, it is characterised in that: each airflow channel is in Curved.
Cooling system as claimed in claim 15, it is characterised in that: the one end of the multiple airflow channel far from the fan is radial.
Cooling system as claimed in claim 15, it is characterised in that: the air flow inlet of the multiple airflow channel is parallel to each other.
Cooling system as claimed in claim 15, it is characterised in that: the radiator includes multiple cooling fins, and the multiple airflow channel is between the multiple cooling fin.
Cooling system as claimed in claim 18, it is characterised in that: also there are other airflow channels, the extending direction of the airflow channel is different from the extending direction of other airflow channels between the multiple cooling fin.
Cooling system as claimed in claim 18, it is characterised in that: the radiator further include:

Heat-conducting plate, for absorbing the heat of heater element generation；

Heat pipe is bound to the heat-conducting plate；

The cooling fin is located at the heat-conducting plate side.
Cooling system as claimed in claim 20, it is characterised in that: the heat-conducting plate is arranged multiple for accommodating the accommodation groove of heater element in the side of its contact surface.
Cooling system as claimed in claim 20, it is characterised in that: multiple recesses are arranged in the periphery of the heat-conducting plate.
Cooling system as claimed in claim 15, it is characterised in that: the fan is tube-axial fan.
A kind of aircraft, comprising:

Fuselage, comprising:

Shell；

Accommodating space is surrounded by the shell；And

Heater element is contained in the accommodating space；And

Cooling system, the heat generated for distributing the heater element；

It is characterized by: the cooling system setting is in the accommodating space, the cooling system includes:

Heat-conducting plate fits in the heater element；

Multiple cooling fins are located at the heat-conducting plate side, the heat absorbed for distributing the heat-conducting plate from the heater element；And

Fan has air port, is set to one end of the multiple cooling fin；

The air port of the fan is tilted towards the multiple cooling fin and to the extending direction of the multiple cooling fin.
Aircraft as claimed in claim 24, it is characterized by: the shell has air inlet and exhaust outlet, the air port is the air outlet of the fan, and the fan also has air inlet, the air inlet corresponds to the air inlet, and the exhaust outlet corresponds to the one end of the cooling fin far from the fan.
Aircraft as claimed in claim 25, it is characterised in that: each cooling fin extends along direction in Curved.
Aircraft as claimed in claim 26, it is characterized by: it includes the first radiating part, the second radiating part and third radiating part that each cooling fin, which extends along direction successively, the extending direction of second radiating part and the third radiating part is different from the extending direction of first radiating part.
Aircraft as claimed in claim 27, it is characterised in that: the air outlet of the fan is close to first radiating part, and the separate third radiating part.
Aircraft as claimed in claim 28, it is characterised in that: second radiating part connects first radiating part and the third radiating part in Curved.
Aircraft as claimed in claim 28, it is characterised in that: the height of second radiating part is greater than the height of first radiating part, also greater than the height of the third radiating part.
Aircraft as claimed in claim 28, it is characterised in that: the first radiating part of the multiple cooling fin is parallel to each other.
Aircraft as claimed in claim 28, it is characterised in that: it is radial that the third radiating part of the multiple cooling fin extends along direction.
Aircraft as claimed in claim 24, it is characterised in that: further include other multiple cooling fins positioned at the multiple cooling fin two sides, the extending direction of other cooling fins is different from the extending direction of the cooling fin.
Aircraft as claimed in claim 24, it is characterised in that: the heat-conducting plate is equipped with multiple accommodation grooves, and the heater element includes being contained in the accommodation groove with multiple electronic components, the multiple electronic component device.
Aircraft as claimed in claim 24, it is characterised in that: the cooling system further includes heat pipe, and the heat pipe is bound to the heat-conducting plate.
Aircraft as claimed in claim 24, it is characterised in that: multiple recesses are arranged in the periphery of the heat-conducting plate, for avoiding interference of the surrounding component of heater element to the heat-conducting plate.
Aircraft as claimed in claim 24, it is characterised in that: further include:

Another heater element；

Radiator, including the multiple radiating fins for being bonded the pedestal of another heater element and extending from the pedestal.
Aircraft as claimed in claim 37, it is characterised in that: the material of the shell is Heat Conduction Material, and the radiating fin contacts the shell.
Aircraft as claimed in claim 37, it is characterised in that: the shell is equipped with multiple perforation.
A kind of aircraft, comprising:

Fuselage, comprising:

Shell；

Accommodating space is surrounded by the shell；And

Heater element, receiving is in the accommodating space；And

Cooling system, the heat generated for distributing the heater element；

It is characterized by: the cooling system setting is in the accommodating space, the cooling system includes:

Radiator, including multiple airflow channels, each airflow channel have air flow inlet；And

Fan has air port, is set to the side of the radiator；

The air port of the fan is obliquely installed relative to the radiator, the air port of the fan towards the multiple airflow channel air flow inlet and tilted to the extending direction of the airflow channel.
Aircraft as claimed in claim 40, it is characterized by: the shell has air inlet and exhaust outlet, the air port is the air outlet of the fan, and the fan also has air inlet, the air inlet corresponds to the air inlet, and the exhaust outlet corresponds to the one end of the cooling fin far from the fan.
Aircraft as claimed in claim 41, it is characterised in that: each airflow channel is in Curved.
Aircraft as claimed in claim 42, it is characterised in that: the one end of the multiple airflow channel far from the fan is radial.
Aircraft as claimed in claim 42, it is characterised in that: the air flow inlet of the multiple airflow channel is parallel to each other.
Aircraft as claimed in claim 42, it is characterised in that: the radiator includes multiple cooling fins, and the multiple airflow channel is between the multiple cooling fin.
Aircraft as claimed in claim 45, it is characterised in that: also there are other airflow channels, the extending direction of the airflow channel is different from the extending direction of other airflow channels between the multiple cooling fin.
Aircraft as claimed in claim 40, it is characterised in that: the radiator is equipped with multiple accommodation grooves, and the heater element includes multiple electronic components, and the multiple electronic component device is contained in the accommodation groove.
Aircraft as claimed in claim 40, it is characterised in that: the radiator further includes heat pipe.
Aircraft as claimed in claim 40, it is characterised in that: further include:

Another heater element；And

Another radiator, the pedestal for being bonded another heater element including one and the multiple radiating fins extended from the pedestal.
Aircraft as claimed in claim 49, it is characterised in that: the material of the shell is Heat Conduction Material, and the radiating fin contacts the shell.
Aircraft as claimed in claim 40, it is characterised in that: the shell is equipped with multiple perforation.