CN206149689U - Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN206149689U CN206149689U CN201621025520.9U CN201621025520U CN206149689U CN 206149689 U CN206149689 U CN 206149689U CN 201621025520 U CN201621025520 U CN 201621025520U CN 206149689 U CN206149689 U CN 206149689U
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- Prior art keywords
- unmanned plane
- heat
- thermal component
- conducting
- radiator
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- 210000003284 Horns Anatomy 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 12
- 241000143392 Oar Species 0.000 claims description 6
- 238000001816 cooling Methods 0.000 abstract 3
- 230000020169 heat generation Effects 0.000 abstract 1
- 239000000463 material Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 210000002356 Skeleton Anatomy 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminum Chemical compound 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[Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N copper Chemical compound 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[Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound 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[C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 230000001141 propulsive Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicium dioxide Chemical compound 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O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Abstract
The utility model provides an unmanned aerial vehicle heat radiation structure includes: the heat conduction parts and with the cooling parts of heat conduction parts hot link, at least a part of fuselage casing that lies in unmanned aerial vehicle of heat conduction parts, cooling parts is located outside the fuselage casing, and be located the part that generates heat in the fuselage casing passes through the heat conduction parts with the cooling parts hot link. This application also provides the unmanned aerial vehicle including above -mentioned unmanned aerial vehicle heat radiation structure. The utility model provides a heat radiation structure can carry the radiating efficiency of high heat generation part, can not influence the atmospheric pressure collection of unmanned aerial vehicle structural strength and barometer sensor again.
Description
Technical field
The utility model is related to unmanned plane radiator structure and the unmanned plane with the unmanned plane radiator structure.
Background technology
Previous unmanned plane is not provided with special housing, and it is mostly skeleton, and each module board is mounted in box modules housing
Interior, box modules housing is fixed on unmanned plane skeleton.Because unmanned plane has control chip, driving chip, picture processing chip etc.
The big part of heating, it usually needs heat abstractor is set and is radiated for it, such as radiated in box modules opening in shell, or perforate
Radiator fan is installed to be radiated.
With the improvement of technology, the unmanned plane for being provided with housing is occurred in that, the typically body shell in unmanned plane is arranged
Air vent, using unmanned plane screw produce air-flow by air vent into body shell flow through heat generating components flow out again it is logical
Air holes is taken away heat and is radiated.But the needs to radiate, the less words air-flow of its air vent cannot be flowed into effectively takes away heat
Amount, can affect unmanned plane structural strength if air vent is excessive, and can affect in unmanned plane for measuring the gas of flying height
The normal barometric pressure collection of pressure flowmeter sensor, so as to affect unmanned plane highly to control degree of stability.
Utility model content
In view of this, it is necessary to a kind of can effectively reducing is provided and is arranged caused by air vent on the casing of unmanned plane
Adverse effect, and the unmanned plane radiator structure of the radiating effect of unmanned plane heat generating components can be strengthened and using the radiator structure
Unmanned plane.
The utility model provides a kind of unmanned plane radiator structure, including：Conducting-heat elements；It is hot linked with the conducting-heat elements
Thermal component；Wherein, at least a portion of the conducting-heat elements is located in the body shell of unmanned plane, and the thermal component is located at
Outside the body shell, and the heat generating components in the body shell is by the conducting-heat elements and thermal component warm
Connection.
On the other hand the utility model provides a kind of unmanned plane including above-mentioned unmanned plane radiator structure.
Compared with prior art, the unmanned plane radiator structure and unmanned plane that the utility model is provided has advantages below：By
Radiated by the thermal component being set directly at outside the body shell of unmanned plane in unmanned plane radiator structure of the present utility model, and
Air vent radiating need not be set on the housing of unmanned plane, so as to the radiator structure can improve the radiating effect of heat generating components
Rate, does not interfere with the air pressure acquisition of unmanned plane structural strength and air pressure flowmeter sensor again.
Description of the drawings
By the detailed description for reading hereafter preferred embodiment, various other advantages and benefit is common for this area
Technical staff will be clear from understanding.Accompanying drawing is only used for illustrating the purpose of preferred embodiment, and is not considered as to this practicality
New restriction.And in whole accompanying drawing, it is denoted by the same reference numerals identical part.
The schematic diagram of the unmanned planes of unmanned plane radiator structure of the Fig. 1 to provide with first embodiment of the present utility model；
Fig. 2 actual airflow range schematic diagrames for causing when being the propeller works of unmanned plane of the present utility model；
The schematic diagram of the unmanned planes of unmanned plane radiator structure of the Fig. 3 to provide with second embodiment of the present utility model；
The unmanned plane schematic diagram of unmanned plane radiator structures of the Fig. 4 to provide with 3rd embodiment of the present utility model；
Fig. 5 is the partial enlarged drawing of Fig. 4；
The unmanned plane schematic diagram of unmanned plane radiator structures of the Fig. 6 to provide with fourth embodiment of the present utility model；
The unmanned plane schematic diagram of unmanned plane radiator structures of the Fig. 7 to provide with the 5th embodiment of the present utility model.
Illustrate：
The heat generating components 140 of unmanned plane 100,200,300,400,500
The screw 160 of unmanned plane radiator structure 110,210,310,410,510
The surfaces of revolution 162 of conducting-heat elements 112,212,312,412,512
The horn 180 of thermal component 114,214,314,414,514
The horn housing 190 of fin 1141,3141,5141
The surfaces of revolution diameter D of heating surface 1142,4142,5142
The airflow range radial dimension H of heat conduction extension 516
Body shell 120
Specific embodiment
The illustrative embodiments of the disclosure are more fully described below with reference to accompanying drawings.Although showing this public affairs in accompanying drawing
The illustrative embodiments opened, it being understood, however, that may be realized in various forms the disclosure and the reality that should not be illustrated here
The mode of applying is limited.On the contrary, there is provided these embodiments are able to be best understood from the disclosure, and can be by this public affairs
The scope opened it is complete convey to those skilled in the art.
Fig. 1 is referred to, the utility model first embodiment provides a kind of unmanned plane radiator structure 110 and with the unmanned plane
The unmanned plane 100 of radiator structure 110, the unmanned plane radiator structure 110 includes：Conducting-heat elements 112 and the conducting-heat elements 112
Hot linked thermal component 114, wherein, at least a portion of the conducting-heat elements 112 is located at the body shell of unmanned plane 100
In 120, the thermal component is located at outside the body shell, and the heat generating components 140 in the body shell 120 passes through
The conducting-heat elements 112 are thermally coupled with the thermal component 114.
Specifically, the heat generating components 140 can be master controller core, image processor chip or driver chip.It is described
Conducting-heat elements 112 partly can be located in the body shell 120, be preferably entirely located in the body shell 120, when described
After conducting-heat elements 112 are entirely located in body shell 120, the impact of the aerodynamic arrangement to unmanned plane 100 can be reduced.The heat conduction
Part 112 contacts the heat generating components 140, and the conducting-heat elements 112 through the body shell 120 with positioned at the machine
The thermal component 114 outside body housing 120 is contacted, specifically, the conducting-heat elements 112 are by being opened in the body shell
120 hole contacts with the thermal component 114.In the present embodiment, the both sides of the body shell 120 are provided with radiating part
Part 114, and the two ends of the conducting-heat elements 112 by be opened in the hole of the both sides of the body shell 120 respectively with positioned at institute
The thermal component 114 for stating the both sides of body shell 120 is contacted.The conducting-heat elements 112 are fully contacted with the heat generating components 140,
It can be sheet, bar-shaped etc., and it is made up of the higher material of thermal conductivity factor, can be the materials such as aluminium, copper, silica gel, graphite.Enter
One step ground, the body shell 120 also can be made up of the higher material of thermal conductivity factor so that the heat of the heat generating components 140
Also further can be radiated by the body shell 120, therefore, the material of the body shell 120 can be with the conducting-heat elements
112 material is identical, and the conducting-heat elements 112 and the body shell 120 can be integrally formed.
The screw 160 of the unmanned plane 100 is arranged on the horn 180 being connected with the body shell 120.Refer to
Fig. 2, when the screw 160 rotates, the screw 160 produces downward air-flow, and the rotation of screw 160 is not only
The lower zone that can directly cover in the surfaces of revolution 162 of the screw 160 produces air-flow, can also cause the screw 160
The neighboring area of the lower zone that the surfaces of revolution 162 is directly covered produces air-flow, i.e., the actual airflow that described screw 160 causes
Diameter Ds of the radial dimension H of scope more than the surfaces of revolution 162.Wherein, the surfaces of revolution 162 refer to Fig. 1 shown in the spiral shell
Rotation oar is the circle that radius is constituted, and is not necessarily referring to the whole plane at the place of screw 160.The thermal component 114 is located at the spiral shell
When rotation oar 160 rotates in the flow area that causes, so as to when the unmanned plane 100 is in state of flight, the heat generating components
140 heat is conducted to the thermal component 114 by the conducting-heat elements 112, and the gas that the rotation of the screw 160 is produced
Stream flows through the thermal component 114 to promote the further radiating of the thermal component 114.
In the present embodiment, the thermal component 114 includes multiple fin 1141 be arrangeding in parallel, the plurality of fin
1141 end is connected with each other, and the end surface being connected with each other constitutes the heating surface 1142 of the thermal component 114.It is described
Heat is directly conducted to the fin 1141 by conducting-heat elements 112 by the heating surface 1142.Specifically, the heat-conducting part
Part 112 can contact at least a portion of the heating surface 1142.The plurality of fin 1141 be arrangeding in parallel is perpendicular to the spiral shell
The surfaces of revolution 162 of rotation oar 160, and the surfaces of revolution 162 of the screw 160 is along perpendicular to the direction of the surfaces of revolution 162
Projection at least partly covers the thermal component 114.The fin 1141 is made up of the material with preferable heat conductivility,
Can be aluminium, copper or steel etc..
When the unmanned plane 100 is in state of flight, the heat of the heat generating components 140 is conducted by conducting-heat elements 112
To the thermal component 114, the rotation of the screw 160 produces air-flow, and the air-flow directly flows through fin 1141, takes away heat
Amount, and due to the screw 160 rotate produce airflow direction generally downward, the airflow direction with directly in the spiral
The orientation of the fin 140 of the lower section of oar 160 is basically identical, so that the air-flow can fully by the radiating
Piece 140, and high efficiency and heat radiation.
Fig. 3 is referred to, second embodiment of the invention provides unmanned plane radiator structure 210 and with the unmanned plane radiator structure
210 unmanned plane 200, the unmanned plane radiator structure 210 includes thermal component 214 and conducting-heat elements 212.The second embodiment
It is essentially identical with first embodiment, differ only in：The surfaces of revolution 162 of the screw 160 is along perpendicular to the surfaces of revolution 162
The projection in direction is misaligned with the thermal component 214, that is, be spaced a preset distance, therefore, the surfaces of revolution of the screw 160
The 162 any positions for not covering the thermal component 214.The surfaces of revolution edge with the screw 160 of the thermal component 214
It is the circular arc consistent with the edge of the projection perpendicular to the adjacent edge of the projection in the direction of the surfaces of revolution 162, so
Structure can ensure that in the case where the surfaces of revolution 162 of the screw 160 does not cover any position of the thermal component 214,
In the flow area that the screw 160 causes, the area of dissipation for making the thermal component 214 is maximized.Above-mentioned pre- spacing
Determine from the airflow range caused when being rotated according to the screw 160, as long as the part of the thermal component 214 is arranged at the spiral shell
Within airflow range caused by rotation oar 160, the air-flow is by the thermal component 214 carrying out to the thermal component
Radiating.Further, since the lower section of the screw does not have any object to stop its air-flow, so as to the screw propulsive efficiency compared with
Height, simultaneously as the thermal component 214 is still arranged in the airflow range of the screw, therefore the air-flow remains to stream
Cross the thermal component 214 to promote the thermal component 214 to radiate.
Fig. 4-5 are referred to, third embodiment of the invention provides a kind of unmanned plane radiator structure 310 and dissipates with the unmanned plane
The unmanned plane 300 of heat structure 310, the unmanned plane radiator structure 310 includes thermal component 314 and conducting-heat elements 312, the radiating
Part 314 includes multi-disc fin 3141 arranged in parallel.The present embodiment is essentially identical with second embodiment, is also described
The surfaces of revolution 162 of screw 160 along the edge of the projection perpendicular to the direction of the surfaces of revolution 162 and the thermal component 314 not
Overlap, that is, be spaced a preset distance, its difference is that the fin 3141 of the thermal component 314 is parallel to the screw
160 surfaces of revolution 162, and the thermal component 314 with the surfaces of revolution 162 of the screw 160 along perpendicular to the rotation
The edge that the projection in the direction in face 162 is adjacent is the circular arc consistent with the edge of the projection.
When the unmanned plane 300 is in state of flight, the downdraught and horizontal that the rotation of the screw 160 is produced
Blade tip flows through the thermal component 314, so that the air-flow can fully pass through the thermal component 314, and efficiently
Radiating.
Fig. 6 is referred to, fourth embodiment of the invention provides a kind of unmanned plane radiator structure 410 and with the unmanned plane radiating
The unmanned plane 400 of structure 410, the radiator structure 410 includes the thermal component 414 with heating surface 4142 and conducting-heat elements 412.
The fourth embodiment is essentially identical with second embodiment, differs only in, and the conducting-heat elements 412 of the radiator structure 410 are piece
Shape, wherein the heat generating components 140 of the unmanned plane 400, the conducting-heat elements 412 and the heating surface 4142 are parallel successively setting
Put.The radiator structure 410 can be only arranged at the side of the unmanned plane 400 or relative both sides, in the present embodiment, described
Heat generating components 140, and the setting side of the radiator structure 410 of the both sides are respectively provided near relative two side of unmanned plane 400
Formula is identical.
Fig. 7 is referred to, the embodiment of the utility model the 5th provides a kind of unmanned plane radiator structure 510 and with the unmanned plane
The unmanned plane 500 of radiator structure 510.5th embodiment is essentially identical with first embodiment, and its difference is, the unmanned plane
Radiator structure 510 further includes heat conduction extension 516 in addition to including conducting-heat elements 512 and thermal component 514.
Specifically, the heat conduction extension 516 is from the conducting-heat elements in the body shell 120 of the unmanned plane 500
On 512 horns 180 that the unmanned plane outside body shell 120 is extended to by being opened in the hole of the unmanned plane 500, and should
Heat conduction extension 516 contacts the thermal component 514, wherein, the heat conduction extension 516 and the conducting-heat elements 512 are integrally
Shaping.
Additionally, the unmanned plane 500 can further include the horn housing 190 for accommodating horn 180, the radiating part
Part 514 is arranged at outside the horn housing 190, and the heat conduction extension 516 is by being opened in the hole of the horn housing 190
Contact is arranged at the thermal component 514 on the horn housing 190.
The thermal component 514 includes multiple fin 5141 be arrangeding in parallel, the end phase of the plurality of fin 5141
Connect, and the end surface being connected with each other constitutes the heating surface 5142 of the thermal component 514, and the heat conduction extension
Heat is directly conducted to the fin 5141 by 516 by the heating surface 5142, specifically, the heat conduction extension 516
At least a portion of the accessible heating surface 5142.In the present embodiment, the plurality of fin 5141 be arrangeding in parallel hangs down
Directly cover along the projection perpendicular to the direction of the surfaces of revolution 162 in the surfaces of revolution 162 of screw 160, and the surfaces of revolution 162
Cover the thermal component 514.
The above, only the utility model preferably specific embodiment, but protection domain of the present utility model is not
Be confined to this, any those familiar with the art the invention discloses technical scope in, the change that can be readily occurred in
Change or replace, all should be included within the scope of the present invention.Therefore, protection scope of the present invention should be described with claim
Protection domain be defined.
Claims (17)
1. a kind of unmanned plane radiator structure, including：
Conducting-heat elements；
With the hot linked thermal component of the conducting-heat elements；
Characterized in that, at least a portion of the conducting-heat elements is located in the body shell of unmanned plane, the thermal component position
Outside the body shell, and the heat generating components in the body shell is by the conducting-heat elements and the thermal component
It is thermally coupled.
2. unmanned plane radiator structure according to claim 1, it is characterised in that at least a portion position of the thermal component
In the airflow range caused when the screw of the unmanned plane rotates.
3. unmanned plane radiator structure according to claim 1, it is characterised in that the conducting-heat elements contact the heating part
Part, and the conducting-heat elements are by being opened in the radiating parts of the Kong Eryu of the body shell outside the body shell
Part is contacted.
4. unmanned plane radiator structure according to claim 3, it is characterised in that the relative both sides of the body shell are equal
Be provided with the thermal component, and the two ends of the conducting-heat elements by be opened in the hole of the body shell both sides respectively with position
Thermal component in the body shell both sides is contacted.
5. unmanned plane radiator structure according to claim 3, it is characterised in that described in the end thereof contacts of the conducting-heat elements
Heat generating components, the other end is contacted by being opened in the hole of the body shell with the thermal component.
6. unmanned plane radiator structure according to claim 5, it is characterised in that the conducting-heat elements are sheet, and described
The heating surface of heat generating components, the conducting-heat elements and the thermal component is parallel successively to be stacked.
7. unmanned plane radiator structure according to claim 1, it is characterised in that further include：Heat conduction extension, this is led
Hot extension contacts the conducting-heat elements and the horn of unmanned plane outside body shell is extended to from the conducting-heat elements, and
The heat conduction extension contacts the thermal component.
8. unmanned plane radiator structure according to claim 7, it is characterised in that the conducting-heat elements and the heat conduction extend
Portion is integrally formed.
9. unmanned plane radiator structure according to claim 7, it is characterised in that the unmanned plane is further included for holding
Receive the horn housing of the horn, the heat conduction extension is arranged in the horn housing, and the thermal component is arranged at institute
State outside horn housing, and the heat conduction extension is contacted by being arranged at the hole of the horn housing with the thermal component.
10. the unmanned plane radiator structure according to claim 1-9 any one, it is characterised in that the thermal component bag
Include the fin that multi-disc be arranged in parallel and end is connected with each other.
11. unmanned plane radiator structures according to claim 10, it is characterised in that the fin perpendicular to it is described nobody
The surfaces of revolution of the screw of machine.
12. unmanned plane radiator structures according to claim 11, it is characterised in that the rotation of the screw of the unmanned plane
Face covers at least a portion of the thermal component.
13. unmanned plane radiator structures according to claim 11, it is characterised in that the rotation of the screw of the unmanned plane
Face is spaced a preset distance along the projection perpendicular to the direction of the surfaces of revolution with the thermal component.
14. unmanned plane radiator structures according to claim 13, it is characterised in that the thermal component with the spiral
The edge of the surfaces of revolution of oar is circular arc perpendicular to the adjacent edge of the projection in the direction of the surfaces of revolution.
15. unmanned plane radiator structures according to claim 10, it is characterised in that the fin parallel to it is described nobody
The surfaces of revolution of the screw of machine.
16. unmanned plane radiator structures according to claim 15, it is characterised in that the rotation of the screw of the unmanned plane
Projection of the edge in face perpendicular to the direction of the surfaces of revolution is spaced a preset distance with the thermal component.
17. a kind of unmanned planes, it is characterised in that including the unmanned plane radiator structure described in claim 1-16 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621025520.9U CN206149689U (en) | 2016-08-31 | 2016-08-31 | Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621025520.9U CN206149689U (en) | 2016-08-31 | 2016-08-31 | Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019095591A1 (en) * | 2017-11-20 | 2019-05-23 | 浙江杭一电器有限公司 | Heat dissipation system for use with unmanned aerial vehicle-mounted device |
| CN110831854A (en) * | 2017-06-16 | 2020-02-21 | 高通股份有限公司 | Multi-rotor aerial unmanned aerial vehicle with vapor chamber |
-
2016
- 2016-08-31 CN CN201621025520.9U patent/CN206149689U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110831854A (en) * | 2017-06-16 | 2020-02-21 | 高通股份有限公司 | Multi-rotor aerial unmanned aerial vehicle with vapor chamber |
| WO2019095591A1 (en) * | 2017-11-20 | 2019-05-23 | 浙江杭一电器有限公司 | Heat dissipation system for use with unmanned aerial vehicle-mounted device |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle Effective date of registration: 20180102 Granted publication date: 20170503 Pledgee: XinDa national equity investment fund (Shanghai) partnership (limited partnership) Pledgor: Zero degree intelligence control (Beijing) intelligent Science and Technology Ltd.|Chongqing Zerotech Intelligent Technology Co., Ltd. Registration number: 2017990001217 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |