CN109819624A - A kind of cooling system for unmanned aerial vehicle onboard equipment - Google Patents
A kind of cooling system for unmanned aerial vehicle onboard equipment Download PDFInfo
- Publication number
- CN109819624A CN109819624A CN201711157507.8A CN201711157507A CN109819624A CN 109819624 A CN109819624 A CN 109819624A CN 201711157507 A CN201711157507 A CN 201711157507A CN 109819624 A CN109819624 A CN 109819624A
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- vehicle onboard
- onboard equipment
- radiating area
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000001816 cooling Methods 0.000 title claims abstract description 57
- 230000017525 heat dissipation Effects 0.000 claims description 13
- 239000007788 liquid Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 5
- 238000005286 illumination Methods 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Landscapes
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The present invention relates to unmanned plane field of radiating, disclose a kind of cooling system for unmanned aerial vehicle onboard equipment, including multiple rotors for being distributed in main body surrounding, the radiating area for being used for unmanned aerial vehicle onboard equipment cooling is formed between multiple rotors, the range area of the radiating area is S=π R2- π r2, the center of multiple rotors is P and is located on same circumference, the center of circle of the circumference is O, the formed diameter of a circle of rotor wing rotation is L, the distance between O and P are l, r is l-L/2, R l+L/2.The present invention has the following advantages and effects: this programme utilizes new mechanical structure, effectively reduces unmanned plane quality and volume, effectively promotes the mobility of unmanned plane.
Description
Technical field
The present invention relates to a kind of unmanned planes, more specifically, it relates to a kind of heat dissipation system for unmanned aerial vehicle onboard equipment
System.
Background technique
With the continuous development of unmanned air vehicle technique, it is gradually widely used in every field, for example is taken photo by plane, even
Logistics etc..Currently, many unmanned planes have had circled high overhead positioning and desired trajectory flight function, at the same time, according to
Application demand is further equipped with lighting system on some unmanned planes.
Currently, the Chinese patent that notification number is CN2063583U discloses a kind of self illumination unmanned plane, including main body,
More rotors being set on the main body, and be connected to the lighting device on the downside of the main body, the self illumination without
Man-machine further includes the liquid cooling apparatus for radiating to the lighting device, and the liquid cooling apparatus includes being set to the host
Liquid-cooling heat radiation row on body, the exchange part being set on the lighting device, and it is respectively communicated with the exchange part and the liquid
The conduit of cold heat dissipation row.
This self illumination unmanned plane structure is simple, but in actual use, liquid cooling apparatus is in order to illumination
Device is sufficiently radiated, and volume, the quality of liquid cooling apparatus are often larger.Unmanned plane needs to take bulky liquid cooling apparatus
Flight, it is necessary to be just able to achieve using the biggish unmanned plane of volume.In rescue site, bulky unmanned plane is more heavy,
Mobility is lower, while energy consumption is larger, and practicability is lower.
Summary of the invention
In view of the deficienciess of the prior art, the invention reside in provide a kind of heat dissipation system for unmanned aerial vehicle onboard equipment
System forms radiating area by rotor and radiates to host pendant, reach and reduce unmanned plane quality, reduce volume, promoted motor-driven
The purpose of property.
To achieve the above object, the present invention provides the following technical scheme that a kind of heat dissipation for unmanned aerial vehicle onboard equipment
System is formed between multiple rotors and is dissipated for unmanned aerial vehicle onboard equipment including multiple rotors for being distributed in main body surrounding
The radiating area of heat, the range area of the radiating area are S=π R2- π r2, and the center of multiple rotors is P and is located at same circle
Zhou Shang, the center of circle of the circumference are O, and the formed diameter of a circle of rotor wing rotation is L, and the distance between O and P are l, r l-
L/2, R l+L/2.
By using above-mentioned technical proposal, each rotor is rotated along the center P of itself, generates downward wind, Duo Gexuan
After the wing rotates together, stronger downward wind can be generated in radiating area, it is scattered so as to be carried out to unmanned aerial vehicle onboard equipment
Heat eliminates the setting of liquid cooling apparatus, so that the unmanned plane of small volume also can be to the same of unmanned aerial vehicle onboard equipment cooling
When drive unmanned aerial vehicle onboard equipment rise and fall, effectively improve the mobility and practicability of unmanned plane.
The present invention is further arranged to: further including the cooling fin connecting with unmanned aerial vehicle onboard equipment, the cooling fin and nothing
Man-machine airborne equipment is located in radiating area.
By using above-mentioned technical proposal, the heat of unmanned aerial vehicle onboard equipment is transmitted on cooling fin, and cooling fin is placed in scattered
In hot-zone, cooling fin can be radiated, can effectively be promoted to unmanned aerial vehicle onboard in the wind to cooling fin in radiating area
The radiating efficiency of equipment.
The present invention is further arranged to: further include heat-conducting piece, one end of the heat-conducting piece is placed in radiating area, the other end with
Unmanned aerial vehicle onboard equipment connection outside radiating area.
By using above-mentioned technical proposal, unmanned aerial vehicle onboard equipment is placed in outside radiating area, and the heat transfer of generation is to leading
On warmware, in the wind to heat-conducting piece in radiating area, to heat-conducting piece heat dissipation, cooling, unmanned aerial vehicle onboard equipment is radiated.
The present invention is further arranged to: further include cooling fin, the one end of the heat-conducting piece far from unmanned aerial vehicle onboard equipment with
The cooling fin connection.
By using above-mentioned technical proposal, cooling fin is placed in radiating area, in the wind to cooling fin in radiating area, is made
Cooling fin, which can quickly realize heat-conducting piece, to radiate, to further promote the radiating efficiency of unmanned aerial vehicle onboard equipment.
In conclusion the invention has the following advantages:
After rotor wing rotation, downward wind is generated, drives unmanned plane mobile, multiple rotor rotationals, the wind in radiating area can be real
Now to the heat spreading function of unmanned aerial vehicle onboard equipment, to eliminate the setting of liquid cooling apparatus, effectively reduce unmanned plane quality and
Volume makes unmanned equipment to also can be realized effective heat dissipation to unmanned aerial vehicle onboard equipment on the unmanned plane of smaller size smaller
There are stronger mobility and practicability.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of embodiment 1；
Fig. 2 is S range schematic diagram in the present invention；
Fig. 3 is the structural schematic diagram of embodiment 2；
Fig. 4 is the structural schematic diagram of embodiment 3；
Fig. 5 is the structural schematic diagram of embodiment 4.
Appended drawing reference: 1, main body；2, unmanned aerial vehicle onboard equipment；3, rotor；4, cooling fin；5, heat-conducting piece.
Specific embodiment
Referring to attached drawing, the present invention will be further described.
Embodiment 1: a kind of cooling system for unmanned aerial vehicle onboard equipment, as shown in Figure 1, on unmanned plane there are four settings
Rotor 3.This four rotors 3 are located at the surrounding of main body 1.Each rotor 3 is shown in Fig. 2 along the center P(of itself) rotation, downwards
The movement of main body 1 is realized in blowing.The center P(of this four rotors 3 is shown in Fig. 2) it is located on the same circumference, the center of circle of the circumference
Fig. 2 is seen for O().It is that L(is shown in Fig. 2 that the rotation of rotor 3, which is formed by diameter of a circle).As shown in Fig. 2, the distance between O and P are l.
Annular region shown in Fig. 2 is radiating area of the present invention, and cross-sectional area is S=π R2- π r2, wherein r is
L-L/2, R l+L/2.
As shown in Figure 1, unmanned aerial vehicle onboard equipment 2 is lighting apparatus (such as LED light) or communication equipment (such as signal transceiver).
Unmanned aerial vehicle onboard equipment 2 is placed in the following position directly of radiating area.It is realized by the wind in radiating area to unmanned aerial vehicle onboard equipment 2
Heat dissipation.
To effectively reduce volume, the quality of unmanned plane, unmanned plane is made to possess preferable practicability and mobility.
Embodiment 2: as shown in figure 3, a kind of cooling system for unmanned aerial vehicle onboard equipment, difference with embodiment 1 it
It is in further including cooling fin 4.
Cooling fin 4 can be made of either aluminum or copper.Cooling fin 4 is fixedly connected with unmanned aerial vehicle onboard equipment 2.And it will heat dissipation
Piece 4 and unmanned aerial vehicle onboard equipment 2 are placed in radiating area.The heat that unmanned aerial vehicle onboard equipment 2 generates quickly is transmitted to cooling fin 4
On, when in the wind to cooling fin 4 in radiating area, the cooling to cooling fin 4 can be realized, unmanned aerial vehicle onboard is set to realize
Standby 2 heat dissipation.
When wind in radiating area is blown to simultaneously in cooling fin 4 and unmanned aerial vehicle onboard equipment 2, equally it may be implemented to unmanned plane
The cooling of airborne equipment 2.
Embodiment 3: as shown in figure 4, a kind of cooling system for unmanned aerial vehicle onboard equipment, difference with embodiment 1 it
It is in further including heat-conducting piece 5.
Heat-conducting piece 5 can be the heat conducting pipe being made of either aluminum or copper.Unmanned aerial vehicle onboard equipment is placed in outside radiating area, it will
One end of heat-conducting piece 5 is fixed in unmanned aerial vehicle onboard equipment, and the other end is placed in radiating area.The mistake of unmanned aerial vehicle onboard equipment work
It generates heat in journey, in heat transfer to heat-conducting piece 5, is dispersed the heat on heat-conducting piece 5 rapidly by the wind in radiating area, it is real
Now to the cooling of heat-conducting piece 5, to realize the heat dissipation to unmanned aerial vehicle onboard equipment.
Embodiment 4: as shown in figure 5, a kind of cooling system for unmanned aerial vehicle onboard equipment, difference with embodiment 1 it
It is in further including cooling fin 4, heat-conducting piece 5.
One end of heat-conducting piece 5 is fixed in unmanned aerial vehicle onboard equipment, the other end is fixedly connected with cooling fin 4.Unmanned plane
Airborne equipment generates heat when working, heat is transmitted on cooling fin 4 by heat-conducting piece 5.
In use, unmanned aerial vehicle onboard equipment is placed in outside radiating area, cooling fin 4 is placed in radiating area.In radiating area
Wind to cooling fin 4 on when, realize heat dissipation to cooling fin 4, reduce the temperature of cooling fin 4.In unmanned aerial vehicle onboard equipment
During continuing working, heat is sustainable to be transported on cooling fin 4, and is dispersed in radiating area, is not easy unmanned plane on-hook
Because heat is difficult to break down due to dispersing.While reducing unmanned plane weight and volume to reach, realize to unmanned aerial vehicle onboard
The heat spreading function of equipment, mobility with higher and practicability.
It is also possible to which heat-conducting piece 5 and cooling fin 4 are placed in radiating area simultaneously, realize to heat-conducting piece 5 and cooling fin 4
While radiate.
The above is only a preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-mentioned implementation
Example, all technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that for the art
Those of ordinary skill for, several improvements and modifications without departing from the principles of the present invention, these improvements and modifications
It should be regarded as protection scope of the present invention.
Claims (4)
1. a kind of cooling system for unmanned aerial vehicle onboard equipment, including multiple rotors (3) for being distributed in main body (1) surrounding,
It is characterized in that: forming the radiating area for unmanned aerial vehicle onboard equipment (2) heat dissipation, the radiating area between multiple rotors (3)
Range area be S=π R2- π r2, the centers of multiple rotors (3) is P and is located on same circumference, the center of circle of the circumference
For O, it is L that the rotor (3), which rotates formed diameter of a circle, and the distance between O and P are l, r l-L/2, R l+L/2.
2. a kind of cooling system for unmanned aerial vehicle onboard equipment according to claim 1, it is characterized in that: further including and nothing
The cooling fin (4) of man-machine airborne equipment (2) connection, the cooling fin (4) and unmanned aerial vehicle onboard equipment (2) are located in radiating area.
3. a kind of cooling system for unmanned aerial vehicle onboard equipment according to claim 1, it is characterized in that: further including thermally conductive
One end of part (5), the heat-conducting piece (5) is placed in radiating area, and the unmanned aerial vehicle onboard equipment (2) outside the other end and radiating area is even
It connects.
4. a kind of cooling system for unmanned aerial vehicle onboard equipment according to claim 3, it is characterized in that: further including heat dissipation
Piece (4), the heat-conducting piece (5) connect far from the one end of unmanned aerial vehicle onboard equipment (2) with the cooling fin (4).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711157507.8A CN109819624A (en) | 2017-11-20 | 2017-11-20 | A kind of cooling system for unmanned aerial vehicle onboard equipment |
| PCT/CN2018/078783 WO2019095591A1 (en) | 2017-11-20 | 2018-03-13 | Heat dissipation system for use with unmanned aerial vehicle-mounted device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711157507.8A CN109819624A (en) | 2017-11-20 | 2017-11-20 | A kind of cooling system for unmanned aerial vehicle onboard equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109819624A true CN109819624A (en) | 2019-05-28 |
Family
ID=66539313
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711157507.8A Pending CN109819624A (en) | 2017-11-20 | 2017-11-20 | A kind of cooling system for unmanned aerial vehicle onboard equipment |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109819624A (en) |
| WO (1) | WO2019095591A1 (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
| KR101660464B1 (en) * | 2015-09-04 | 2016-10-24 | 주식회사 그리폰 다이나믹스 | Motor boom having radiator |
| CN206149689U (en) * | 2016-08-31 | 2017-05-03 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle |
| CN106628216A (en) * | 2016-12-01 | 2017-05-10 | 何小峰 | Illumination unmanned aerial vehicle |
| CN106672225A (en) * | 2016-12-27 | 2017-05-17 | 昆山优尼电能运动科技有限公司 | Cooling air path system of unmanned aerial vehicle |
| CN206358377U (en) * | 2017-01-09 | 2017-07-28 | 深圳市万景华科技有限公司 | Self illumination unmanned plane |
| CN207652875U (en) * | 2017-11-20 | 2018-07-24 | 浙江杭一电器有限公司 | A kind of cooling system for unmanned aerial vehicle onboard equipment |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206384143U (en) * | 2016-12-27 | 2017-08-08 | 昆山优尼电能运动科技有限公司 | Unmanned plane cooling system |
| CN206644992U (en) * | 2017-03-31 | 2017-11-17 | 湖南人文科技学院 | A kind of small-sized unmanned plane of excellent radiation performance |
-
2017
- 2017-11-20 CN CN201711157507.8A patent/CN109819624A/en active Pending
-
2018
- 2018-03-13 WO PCT/CN2018/078783 patent/WO2019095591A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
| KR101660464B1 (en) * | 2015-09-04 | 2016-10-24 | 주식회사 그리폰 다이나믹스 | Motor boom having radiator |
| CN206149689U (en) * | 2016-08-31 | 2017-05-03 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle heat radiation structure and unmanned aerial vehicle |
| CN106628216A (en) * | 2016-12-01 | 2017-05-10 | 何小峰 | Illumination unmanned aerial vehicle |
| CN106672225A (en) * | 2016-12-27 | 2017-05-17 | 昆山优尼电能运动科技有限公司 | Cooling air path system of unmanned aerial vehicle |
| CN206358377U (en) * | 2017-01-09 | 2017-07-28 | 深圳市万景华科技有限公司 | Self illumination unmanned plane |
| CN207652875U (en) * | 2017-11-20 | 2018-07-24 | 浙江杭一电器有限公司 | A kind of cooling system for unmanned aerial vehicle onboard equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019095591A1 (en) | 2019-05-23 |
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