CN105756765B - Unmanned vehicle engine cooling mechanism - Google Patents
Unmanned vehicle engine cooling mechanism Download PDFInfo
- Publication number
- CN105756765B CN105756765B CN201610101070.5A CN201610101070A CN105756765B CN 105756765 B CN105756765 B CN 105756765B CN 201610101070 A CN201610101070 A CN 201610101070A CN 105756765 B CN105756765 B CN 105756765B
- Authority
- CN
- China
- Prior art keywords
- heat dissipating
- dissipating housing
- gas outlet
- fan
- engine
- 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.)
- Expired - Fee Related
Links
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/14—Arrangements for cooling or ventilating wherein gaseous cooling medium circulates between the machine casing and a surrounding mantle
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P5/00—Pumping cooling-air or liquid coolants
- F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P5/00—Pumping cooling-air or liquid coolants
- F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
- F01P5/04—Pump-driving arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P5/00—Pumping cooling-air or liquid coolants
- F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
- F01P5/06—Guiding or ducting air to, or from, ducted fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P2050/00—Applications
- F01P2050/20—Aircraft engines
Abstract
The invention discloses a kind of unmanned vehicle engine cooling mechanisms, belong to unmanned vehicle engine technical field of heat dissipation.The unmanned vehicle engine cooling mechanism includes sleeve structure, engine and fan；Fan and engine are arranged in sleeve structure；Engine is connect with fan.Unmanned vehicle engine cooling mechanism of the present invention can radiate to engine, and radiating efficiency is high, ensure that the safety of engine.
Description
Technical field
The present invention relates to unmanned vehicle engine technical field of heat dissipation, in particular to a kind of unmanned vehicle engine cooling mechanism.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without cockpit on machine, but the equipment such as automatic pilot, presetting apparatus are installed.On ground, naval vessels or
Machine tool remote control station personnel track it, are positioned, are remotely controlled, telemetering and Digital Transmission by the equipment such as radar.It can be in radio
It takes off as conventional airplane under remote control or is launched with booster rocket, aerial launch can also be taken to by machine tool and flown.Recycling
When, the mode automatic Landing as conventional airplane landing mission can be used, can also be recycled by remote control parachute or block.It can
It is reused several times.So unmanned plane is very high for engine calls, but unmanned vehicle engine in use, does not have at present
There is good radiator, cause unmanned plane that cannot use for a long time, indicating oven temperature of engine will lead between mutual moving parts
Fit clearance reduces, and interferes the proper motion of parts, even causes movement parts stuck when serious, generates security risk.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of pair of engines to radiate, and radiating efficiency is high, ensure that
The unmanned vehicle engine cooling mechanism of the safety of engine.
In order to solve the above technical problems, being mounted on fuselage the present invention provides a kind of unmanned vehicle engine cooling mechanism；
Cooling mechanism includes sleeve structure, engine and fan；The fan and the engine are arranged in the sleeve structure；Institute
Engine is stated to connect with the fan；The sleeve structure includes the first heat dissipating housing and the second heat dissipating housing；First heat dissipating housing
It is connect with second heat dissipating housing；The fan and the engine are arranged in first heat dissipating housing and second heat dissipating housing
It is interior；First heat dissipating housing and second heat dissipating housing form air inlet and outlet side；The air inlet is located on the fuselage
Side；The outlet side is located at the fuselage two sides.
Further, the fan is arranged below the air inlet.
Further, the fan area is greater than the air inlet open area.
Further, the outlet side includes the first gas outlet and the second gas outlet；First gas outlet and described
Two gas outlets are located at the fuselage two sides.
Further, the area of first gas outlet and second gas outlet is greater than or equal to the one of air inlet open area
Half.
Further, first heat dissipating housing and second heat dissipating housing form the first air duct and the second air duct；Described
One air duct one end is connect with the air inlet, and the other end is connect with first gas outlet；Second air duct one end with it is described
Air inlet connection, the other end are connect with second gas outlet.
Further, the first cooling fin and the second cooling fin are provided on the engine；The first cooling fin setting
In first air duct；Second cooling fin is arranged in second air duct.
Further, first cooling fin and the second cooling fin close-packed arrays.
Further, unmanned vehicle engine cooling mechanism of the present invention further includes dust cover, and the dust cover is separately positioned on
On the air inlet, the first gas outlet and the second gas outlet.
The fan and engine of unmanned vehicle engine cooling mechanism provided by the invention are arranged in sleeve structure, engine
Connect with fan, driven by engine fan movement, sleeve structure include the first heat dissipating housing and the second heat dissipating housing, the first heat dissipating housing with
The connection of second heat dissipating housing, fan and engine are arranged in the first heat dissipating housing and the second heat dissipating housing, and fan transports outside air
Into the first heat dissipating housing and the second heat dissipating housing, makes air quickly through engine, take away heat of engine, radiating efficiency is high, protects
The safety of engine is demonstrate,proved.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of unmanned vehicle engine cooling mechanism provided in an embodiment of the present invention；
Fig. 2 is the structural schematic diagram of suit mechanism provided in an embodiment of the present invention.
Specific embodiment
Referring to Fig. 1-2, the embodiment of the invention provides a kind of unmanned vehicle engine cooling mechanisms, including sleeve structure, hair
Motivation 3 and fan 2.Sleeve structure includes the first heat dissipating housing and the second heat dissipating housing.First heat dissipating housing and the second heat dissipating housing pass through spiral shell
It tethers and connects.First heat dissipating housing and the second heat dissipating housing form air inlet 1 and outlet end.Air inlet 1 is located at the body upper.Outlet
End is located at fuselage two sides.The lower section of air inlet 1 is arranged in fan 2.The area of fan 2 is greater than the area of air inlet 1.Fan 2 with
Engine 3 drives fan 2 to work by axis connection, engine 3, does not need separately to set engine again for fan.Outlet side includes the
One gas outlet 8 and the second gas outlet 9.First gas outlet 8 and the second gas outlet 9 are located at fuselage two sides, avoid by first
The thermal current of gas outlet 8 and the discharge of the second gas outlet 9 is sucked by air inlet.The area of first gas outlet 8 and the second gas outlet 9 is big
In or equal to 1 area of air inlet half.First heat dissipating housing and the second heat dissipating housing form the first air duct 4 and the second air duct 5.First
4 one end of air duct is connect with air inlet 1, and the other end is connect with the first gas outlet 8.Second air duct, 5 one end is connect with air inlet 1, separately
One end is connect with the second gas outlet 9.The first cooling fin 6 and the second cooling fin 7 are provided on engine 3.The setting of first cooling fin 6
In the first air duct 4.Second cooling fin 7 is arranged in the second air duct 5.7 close-packed arrays of first cooling fin 6 and the second cooling fin.
Unmanned vehicle engine cooling mechanism of the present invention further includes dust cover.Dust cover be separately positioned on air inlet 1, the first gas outlet 8 and
On second gas outlet 9.
When using unmanned vehicle engine cooling mechanism of the present invention.Fan 2 and engine 3 are passed through into axis connection.By fan 2
And engine 3 is placed in the first heat dissipating housing.Second heat dissipating housing is connect by bolt with the first heat dissipating housing.Start engine 3, band
Dynamic fan 2 works.Fan 2 rotates, and forms low-pressure area above fan 2.Air passes through air inlet 1 under the action of atmospheric pressure
Into in the first heat dissipating housing and the second heat dissipating housing.The first air duct 4 and second formed due to the first heat dissipating housing and the second heat dissipating housing
5 space of air duct is small, and the area of the first gas outlet 8 and the second gas outlet 9 is greater than or equal to the half of 1 area of air inlet, makes
The air of sucking is quickly through the first air duct 4 and the second air duct 5.7 close-packed arrays of first cooling fin 6 and the second cooling fin, make sky
Gas faster passes through the first cooling fin 6 and the second cooling fin 7 takes away heat.Hot-air is gone out by the first gas outlet 8 and second
Port 9 is discharged, and reduces the temperature of engine 3.
The fan and engine of unmanned vehicle engine cooling mechanism provided by the invention are arranged in sleeve structure, engine
Connect with fan, driven by engine fan movement, sleeve structure include the first heat dissipating housing and the second heat dissipating housing, the first heat dissipating housing with
The connection of second heat dissipating housing, fan and engine are arranged in the first heat dissipating housing and the second heat dissipating housing, and fan transports outside air
Into the first heat dissipating housing and the second heat dissipating housing, makes air quickly through engine, take away heat of engine, radiating efficiency is high, protects
The safety of engine is demonstrate,proved.
It should be noted last that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it,
Although being described the invention in detail referring to example, those skilled in the art should understand that, it can be to the present invention
Technical solution be modified or replaced equivalently, without departing from the spirit and scope of the technical solution of the present invention, should all cover
In the scope of the claims of the present invention.
Claims (1)
1. a kind of unmanned vehicle engine cooling mechanism, is mounted on fuselage；It is characterised by comprising: sleeve structure, engine
(3) and fan (2)；The fan (2) and the engine (3) are arranged in the sleeve structure；The engine (3) and institute
It states fan (2) and passes through axis connection；The sleeve structure includes the first heat dissipating housing and the second heat dissipating housing；First heat dissipating housing and institute
The second heat dissipating housing is stated to be bolted；The fan and engine setting are dissipated in first heat dissipating housing and described second
In heat cover；First heat dissipating housing and second heat dissipating housing form air inlet (1) and outlet side；The air inlet (1) is located at
The body upper；The outlet side is located at the fuselage two sides；Fan (2) setting is below the air inlet (1)；Institute
Fan (2) area is stated greater than the air inlet (1) area；The first cooling fin and the second cooling fin are provided on the engine；
When the fan rotates, low-pressure area is formed above the fan；First heat dissipating housing and the second heat dissipating housing formed the first air duct and
Second air duct；First air duct one end is connect with air inlet, and the other end is connect with the first gas outlet；Second air duct one end and air inlet
Connection, the other end are connect with the second gas outlet；First cooling fin is arranged in the first air duct；Second cooling fin is arranged in the second wind
In road；First cooling fin and the second cooling fin close-packed arrays；
The outlet side includes the first gas outlet (8) and the second gas outlet (9)；First gas outlet (8) and described second go out
Port (9) is located at the fuselage two sides；The area of first gas outlet (8) and second gas outlet (9) is all larger than
Or it is equal to the half of air inlet (1) area；First heat dissipating housing and second heat dissipating housing form the first air duct (4) and second
Air duct (5)；Described first air duct (4) one end is connect with the air inlet (1), and the other end is connect with first gas outlet (8)；
Described second air duct (5) one end is connect with the air inlet (1), and the other end is connect with second gas outlet (9)；Further include:
Dust cover, the dust cover are separately positioned on the air inlet (1), on the first gas outlet (8) and the second gas outlet (9)；
Wherein, start engine, drive fan work；Fan rotation, forms low-pressure area above fan；Air is in atmospheric pressure
Under the action of entered in the first heat dissipating housing and the second heat dissipating housing by air inlet；Since the first heat dissipating housing and the second heat dissipating housing are formed
The first air duct and the second duct space it is small, and the area of first gas outlet (8) and second gas outlet (9) is big
In or be equal to air inlet (1) area half, make sucking air quickly through the first air duct and the second air duct；First cooling fin
And the second cooling fin close-packed arrays, make that air faster passes through the first cooling fin and the second cooling fin takes away heat；Hot-air
It is discharged by the first gas outlet and the second gas outlet, reduces the temperature of engine.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013208930936 | 2013-12-31 | ||
| CN201320893093 | 2013-12-31 | ||
| CN201410008773.4A CN103754374B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410008773.4A Division CN103754374B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105756765A CN105756765A (en) | 2016-07-13 |
| CN105756765B true CN105756765B (en) | 2019-11-12 |
Family
ID=50521750
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410008773.4A Expired - Fee Related CN103754374B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
| CN201610101070.5A Expired - Fee Related CN105756765B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
| CN201610102385.1A Expired - Fee Related CN105667813B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410008773.4A Expired - Fee Related CN103754374B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610102385.1A Expired - Fee Related CN105667813B (en) | 2013-12-31 | 2014-01-08 | Unmanned vehicle engine cooling mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN103754374B (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754374B (en) * | 2013-12-31 | 2016-06-29 | 湖北易瓦特科技股份有限公司 | Unmanned vehicle engine cooling mechanism |
| CN104691768B (en) * | 2014-07-16 | 2017-01-18 | 安阳全丰航空植保科技有限公司 | Volute type air centralization cooler for engine of agricultural unmanned helicopter |
| CN104802998A (en) * | 2015-04-25 | 2015-07-29 | 亳州市智航航空植保科技有限公司 | Air-cooled engine for unmanned plant protection aircraft |
| WO2016172947A1 (en) * | 2015-04-30 | 2016-11-03 | 深圳市大疆创新科技有限公司 | Thermal management system and thermal management method, and unmanned aerial vehicle for application of the thermal management system |
| EP3892535A1 (en) * | 2015-06-01 | 2021-10-13 | SZ DJI Technology Co., Ltd. | Segmented propulsion unit arm for an unmanned aerial vehicle |
| WO2016192022A1 (en) * | 2015-06-01 | 2016-12-08 | SZ DJI Technology Co., Ltd. | System, kit, and method for dissipating heat generated by a motor assembly |
| CN105217048B (en) * | 2015-09-28 | 2017-08-29 | 易瓦特科技股份公司 | Flexible exhaust passage with cooling system |
| CN105253312B (en) * | 2015-09-28 | 2017-08-25 | 易瓦特科技股份公司 | Flexible exhaust passage with dynamic balance system |
| CN105217045B (en) * | 2015-09-28 | 2017-09-05 | 易瓦特科技股份公司 | Depopulated helicopter with heat shield |
| CN105253311B (en) * | 2015-09-28 | 2017-08-08 | 易瓦特科技股份公司 | Depopulated helicopter |
| CN105217047B (en) * | 2015-09-28 | 2017-09-29 | 易瓦特科技股份公司 | Flexible exhaust passage with heat shield |
| CN106043680B (en) * | 2016-07-28 | 2019-03-19 | 易瓦特科技股份公司 | Aero-engine |
| CN108428912B (en) * | 2017-02-13 | 2024-01-09 | 江苏氢太新能源有限公司 | Unmanned aerial vehicle capable of adjusting air temperature in inner cavity of fuselage and working method thereof |
| CN106907267A (en) * | 2017-03-10 | 2017-06-30 | 西安天问智能科技有限公司 | Engine cooling system and rotor craft |
| CN206865924U (en) | 2017-05-19 | 2018-01-09 | 深圳市大疆创新科技有限公司 | Unmanned plane and radiator structure |
| CN109229398A (en) * | 2018-08-30 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of piggyback pod having active heat removal function |
| CN110015435B (en) * | 2019-04-12 | 2021-08-03 | 亿航智能设备（广州）有限公司 | Electric aircraft, heat dissipation system, method, equipment and storage medium thereof |
| CN112165831B (en) * | 2020-09-14 | 2022-08-09 | 中国运载火箭技术研究院 | Be applied to integrated controller and aircraft of aircraft |
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- 2014-01-08 CN CN201410008773.4A patent/CN103754374B/en not_active Expired - Fee Related
- 2014-01-08 CN CN201610101070.5A patent/CN105756765B/en not_active Expired - Fee Related
- 2014-01-08 CN CN201610102385.1A patent/CN105667813B/en not_active Expired - Fee Related
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| US6575402B1 (en) * | 2002-04-17 | 2003-06-10 | Sikorsky Aircraft Corporation | Cooling system for a hybrid aircraft |
| CN200964893Y (en) * | 2006-10-16 | 2007-10-24 | 冯政杰 | Engine |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN105667813B (en) | 2018-12-11 |
| CN105756765A (en) | 2016-07-13 |
| CN103754374A (en) | 2014-04-30 |
| CN105667813A (en) | 2016-06-15 |
| CN103754374B (en) | 2016-06-29 |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
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| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant after: Ewatt Technology Co.,Ltd. Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant before: Ewatt Technology Co.,Ltd. |
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| COR | Change of bibliographic data | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191112 Termination date: 20220108 |