CN206149689U - Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle - Google Patents

Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle Download PDF

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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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China
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unmanned plane
heat
thermal component
conducting
radiator
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CN201621025520.9U
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Chinese (zh)
Inventor
孙宏涛
杨建军
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Zerotech Beijing Intelligence Robot Co Ltd
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Zerotech Beijing Intelligence Robot Co Ltd
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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

Unmanned plane radiator structure and unmanned plane
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.
CN201621025520.9U 2016-08-31 2016-08-31 Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle Active CN206149689U (en)

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Application Number Priority Date Filing Date Title
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Cited By (2)

* Cited by examiner, † Cited by third party
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

Cited By (2)

* Cited by examiner, † Cited by third party
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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GR01 Patent grant
GR01 Patent grant
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

PE01 Entry into force of the registration of the contract for pledge of patent right