CN102514715A - Cooling channel of motor - Google Patents
Cooling channel of motor Download PDFInfo
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- CN102514715A CN102514715A CN2011104289765A CN201110428976A CN102514715A CN 102514715 A CN102514715 A CN 102514715A CN 2011104289765 A CN2011104289765 A CN 2011104289765A CN 201110428976 A CN201110428976 A CN 201110428976A CN 102514715 A CN102514715 A CN 102514715A
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- cooling
- cooling channel
- gallery
- fuselage
- motor
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Abstract
The invention relates to a cooling channel of a motor, which comprises an unmanned plane body and a cooling channel body, wherein the cooling channel body communicated with the motor is arranged on the unmanned plane body. The cooling channel body comprises an air inlet, a channel and an air outlet, wherein the air inlet of the cooling channel body is arranged at a plane head position at the front end of the plane body and opens forwards, the air outlet of the cooling channel body is arranged on the plane body above plane wings and opens upwards, the air inlet is communicated with the air outlet through the channel in the plane body, and the radiating channel is communicated with the motor installed in the plane body. The cooling channel of the motor is scientific in design, simple in structure, wide in application and low in cost, uses a simple through groove structure for radiating, and uses air flow for accelerating radiating, so that radiating performance is effectively improved, and normal work of airborne equipment is not affected. The cooling channel of the motor is small in structure occupied space, light in weight, high in reliability and attractive in appearance due to the fact that plane body modeling is not damaged.
Description
Technical field
The invention belongs to the unmanned plane field, relate to radiator structure, especially a kind of engine cooling passage.
Background technology
Maturation gradually along with the robot airplane technology; And the continuous development of UAV control equipment and unmanned plane carrying equipment, the application of unmanned plane constantly enlarges, and can be widely used at present like fields such as line data-logging, military surveillance, geographical information collection, aerial high-risk operations; Adopt unmanned plane to patrol and examine and to increase safety factor greatly; Increase the inspection number of times that cruises, reduce the cost of operation management, improve efficiency of operation; And operation is simpler, dependable performance, has better economic benefit and social benefit.Conventional fixed-wing layout unmanned plane stability is high, can carry as two-way camera take photo by plane, multiple airborne equipments such as The Cloud Terrace shooting, position fixing system, realization to target setting follow the tracks of, location, remote control, remote measurement and digital communication.
Unmanned plane is in the process of carrying out aerial mission, and driving engine constantly produces heat in continuous working, need in time heat to be discharged; Present unmanned plane is to rely on air-cooled and the lubricating oil cooling, and radiator structure is employed in that the position near driving engine directly is shaped on louvre on the fuselage, and heat is discharged through louvre; The position of louvre is arranged on the wing below; Or at the head rear one-week interval is arranged, the hot gas of being discharged by louvre can disturb the video recording picture pick-up device of lift-launch, influences data acquisition; And the direct radiating effect of louvre is not ideal enough, and influences the aesthetic of unmanned plane overall appearance.
Through retrieval, do not find related patent U.S. Patent No..
Summary of the invention
The objective of the invention is to overcome the weak point of prior art, a kind of design science, engine cooling passage simple in structure, widely applicable, lower-cost are provided.
The present invention solves its technical matters and takes following technical scheme to realize:
A kind of engine cooling passage; Comprise unmanned aerial vehicle body and cooling-gallery; On unmanned aerial vehicle body, be shaped on the cooling-gallery that is communicated with driving engine; It is characterized in that: said cooling-gallery comprises ventilation inlet, passage and exhaust outlet, the ventilation inlet of cooling-gallery built in the head position of front fuselage and opening forward, the exhaust outlet of cooling-gallery on the fuselage of wing top and opening upwards; Ventilation inlet communicates through the passage in fuselage with exhaust outlet, and this heat dissipation channel is communicated with the driving engine that is installed in the fuselage.
And the inside face of said passage is made as smooth cambered surface.
And said cooling-gallery is two and the fuselage both sides of symmetry above wing.
Advantage of the present invention and good effect are:
1, this cooling-gallery is positioned on the fuselage of wing top; Various data acquisition equipments such as the pick up camera that unmanned plane carries, photographic camera are installed in the unmanned plane below; The hot blast of effectively having avoided vent to discharge has influence on the normal operation of equipment, guarantees the data acquisition effect.
2, this cooling-gallery structure comprises the heat dissipation channel that make the fuselage both sides; In the unmanned plane during flying process; Air gets into heat dissipation channel by the ventilation inlet in fuselage the place ahead; Discharge via exhaust outlet through driving engine and the heat that carries engine producing, utilize " siphonic effect " of air to strengthen air current flow and more help engine radiating, quicken substracted heat.
3, the ventilation inlet of this cooling-gallery is arranged on front fuselage, and radiating groove connects fuselage, and air-flow can directly pass, and has reduced the fuselage wind area, has reduced the suffered resistance of unmanned plane during flying, helps to promote the airworthiness of unmanned plane, makes flight smooth more.
4, design science of the present invention, simple in structure, widely applicable, cost is lower; Through simple groove structure heat radiation, utilize air flows to quicken heat radiation, effectively promote heat dispersion; Avoid influencing the normal operation of airborne equipment; That structure takes up room is little, light weight, reliability are high, and does not destroy fuselage model, good looking appearance.
Description of drawings
Fig. 1 is a structural front view of the present invention;
Fig. 2 is the cooling-gallery part part sectional view of Fig. 1;
Fig. 3 is the birds-eye view of Fig. 1;
Fig. 4 is the cooling-gallery part part sectional view of Fig. 3.
The specific embodiment
Below in conjunction with accompanying drawing and through specific embodiment the present invention is made further detailed description, following examples are descriptive, are not determinate, can not limit protection scope of the present invention with this.
A kind of engine cooling passage comprises unmanned aerial vehicle body 1 and cooling-gallery, on unmanned aerial vehicle body, is shaped on the cooling-gallery that is communicated with driving engine 6, and innovative point of the present invention is:
Said cooling-gallery comprises ventilation inlet 4, passage 5 and exhaust outlet 3; The ventilation inlet of cooling-gallery built in the head position of front fuselage and opening forward; The exhaust outlet of cooling-gallery on the fuselage of wing 2 tops and opening upwards; Ventilation inlet communicates through the passage in fuselage with exhaust outlet, and this heat dissipation channel is communicated with the driving engine that is installed in the fuselage.
In order to help quickening air current flow and reduce flight resistance more, the inside face of said passage is made as smooth cambered surface.
In order to guarantee better thermal diffusivity, said cooling-gallery is two and the fuselage both sides of symmetry above wing.
Principle of work of the present invention is:
In the unmanned plane during flying process; Air gets into cooling-gallery by the ventilation inlet in fuselage the place ahead; Discharge via exhaust outlet through driving engine and the heat that carries engine producing, and utilize " siphonic effect " of air to strengthen the heat radiation of air current flow boost engine, quicken substracted heat.
Claims (3)
1. engine cooling passage; Comprise unmanned aerial vehicle body and cooling-gallery; On unmanned aerial vehicle body, be shaped on the cooling-gallery that is communicated with driving engine; It is characterized in that: said cooling-gallery comprises ventilation inlet, passage and exhaust outlet, the ventilation inlet of cooling-gallery built in the head position of front fuselage and opening forward, the exhaust outlet of cooling-gallery on the fuselage of wing top and opening upwards; Ventilation inlet communicates through the passage in fuselage with exhaust outlet, and this heat dissipation channel is communicated with the driving engine that is installed in the fuselage.
2. engine cooling passage according to claim 1 is characterized in that: the inside face of said passage is made as smooth cambered surface.
3. engine cooling passage according to claim 1 is characterized in that: said cooling-gallery is two and the fuselage both sides of symmetry above wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104289765A CN102514715A (en) | 2011-12-19 | 2011-12-19 | Cooling channel of motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104289765A CN102514715A (en) | 2011-12-19 | 2011-12-19 | Cooling channel of motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102514715A true CN102514715A (en) | 2012-06-27 |
Family
ID=46285883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104289765A Pending CN102514715A (en) | 2011-12-19 | 2011-12-19 | Cooling channel of motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102514715A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104883863A (en) * | 2015-06-25 | 2015-09-02 | 深圳飞马机器人科技有限公司 | Copper pipe heat radiation device of unmanned plane |
| CN106712707A (en) * | 2017-03-23 | 2017-05-24 | 北京航空航天大学 | Heat-dissipation and thermoelectric generation device for solar cell panel of high-altitude aircraft |
| CN106828947A (en) * | 2017-03-22 | 2017-06-13 | 北京航空航天大学 | A kind of high-altitude vehicle solar panel and propeller motor combined radiating device |
| CN108767472A (en) * | 2018-03-30 | 2018-11-06 | 彩虹无人机科技有限公司 | A kind of air-cooled radome of airborne suspension type |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2112727A (en) * | 1935-08-30 | 1938-03-29 | Armstrong Whitworth Co Eng | Cooling of aircraft engines |
| GB514128A (en) * | 1937-11-03 | 1939-10-31 | Bayerische Motoren Werke Ag | Method and devices for cooling air-cooled internal combustion engines mounted in gondolas or the like of aircraft, particularly those operating pusher propellers or of which one operates a pusher propeller and the other a tractor propeller |
| GB2369161A (en) * | 2000-11-20 | 2002-05-22 | Ajoy Kumar Kundu | Spinner for a propeller |
| EP1327758A2 (en) * | 2002-01-09 | 2003-07-16 | Airbus Deutschland GmbH | Air intake for an aircraft auxiliary power unit |
| KR20110121226A (en) * | 2010-04-30 | 2011-11-07 | 한국항공우주산업 주식회사 | Duct structure for cooling engine |
| CN202429355U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Engine cooling channel |
-
2011
- 2011-12-19 CN CN2011104289765A patent/CN102514715A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2112727A (en) * | 1935-08-30 | 1938-03-29 | Armstrong Whitworth Co Eng | Cooling of aircraft engines |
| GB514128A (en) * | 1937-11-03 | 1939-10-31 | Bayerische Motoren Werke Ag | Method and devices for cooling air-cooled internal combustion engines mounted in gondolas or the like of aircraft, particularly those operating pusher propellers or of which one operates a pusher propeller and the other a tractor propeller |
| GB2369161A (en) * | 2000-11-20 | 2002-05-22 | Ajoy Kumar Kundu | Spinner for a propeller |
| EP1327758A2 (en) * | 2002-01-09 | 2003-07-16 | Airbus Deutschland GmbH | Air intake for an aircraft auxiliary power unit |
| KR20110121226A (en) * | 2010-04-30 | 2011-11-07 | 한국항공우주산업 주식회사 | Duct structure for cooling engine |
| CN202429355U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Engine cooling channel |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104883863A (en) * | 2015-06-25 | 2015-09-02 | 深圳飞马机器人科技有限公司 | Copper pipe heat radiation device of unmanned plane |
| CN106828947A (en) * | 2017-03-22 | 2017-06-13 | 北京航空航天大学 | A kind of high-altitude vehicle solar panel and propeller motor combined radiating device |
| CN106712707A (en) * | 2017-03-23 | 2017-05-24 | 北京航空航天大学 | Heat-dissipation and thermoelectric generation device for solar cell panel of high-altitude aircraft |
| CN108767472A (en) * | 2018-03-30 | 2018-11-06 | 彩虹无人机科技有限公司 | A kind of air-cooled radome of airborne suspension type |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120627 |