CN206155766U - Aircraft water conservancy diversion natural cooling system - Google Patents
Aircraft water conservancy diversion natural cooling system Download PDFInfo
- Publication number
- CN206155766U CN206155766U CN201621173542.XU CN201621173542U CN206155766U CN 206155766 U CN206155766 U CN 206155766U CN 201621173542 U CN201621173542 U CN 201621173542U CN 206155766 U CN206155766 U CN 206155766U
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- China
- Prior art keywords
- aircraft
- water conservancy
- conservancy diversion
- utility
- cooling system
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- 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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Abstract
The utility model discloses an aircraft water conservancy diversion natural cooling system, including installing the girder pipe on the organism, the middle part of girder pipe be equipped with the water conservancy diversion mouth, girder pipe for tubulose hollow structure, the girder pipe install in the intermediate position at organism top, and extend to the both sides of organism. The utility model discloses middle part at girder pipe is equipped with the water conservancy diversion mouth, and through this water conservancy diversion mouth, the smooth and easy leading -in girder intraduct of quick air current when flying before the aircraft that can be better carries out the natural wind cooling, solution that can be better girder pipe inner structure's heat dissipation problem, do not influence the flight performance of aircraft simultaneously yet, make the structure of aircraft reach the optimization.
Description
Technical field
The utility model is related to aircraft cooling system technical field, it particularly relates to a kind of aircraft water conservancy diversion nature
Cooling system.
Background technology
At present, with regard to aircraft cooling mainly by air-cooled and two kinds of water-cooled, wherein air-cooled and be divided into natural air cooled and strong
System is air-cooled, and air blast cooling needs dynamic, complex structure.Natural air cooled effect is typically poor.Water-cooled is typically followed using forced water
Ring is cooled down, complex structure, for small aircraft, increases additional weight larger.
Utility model content
The purpose of this utility model is to provide a kind of aircraft water conservancy diversion Cooling System, to overcome currently available technology to deposit
Above-mentioned deficiency.
To realize above-mentioned technical purpose, what the technical solution of the utility model was realized in：
A kind of aircraft water conservancy diversion Cooling System, including the crossbeam pipe being installed on body, in described crossbeam pipe
Portion is provided with flow-guiding mouth.
Preferably, described crossbeam pipe is tubular, hollow structure.
Preferably, described crossbeam pipe is installed on the centre position at the top of body, and extends to the both sides of body.
After above-mentioned technical proposal, the utility model has following beneficial effect：The utility model is in crossbeam pipe
Middle part is provided with flow-guiding mouth, by the flow-guiding mouth, preferably quick flow when flying before aircraft can smoothly be imported into crossbeam pipe
Inside carries out natural wind cooling, can preferably resolve the heat dissipation problem of crossbeam pipe internal structure, while nor affecting on aircraft
Flying quality, make being optimal of structure of aircraft.
Description of the drawings
In order to be illustrated more clearly that the utility model embodiment or technical scheme of the prior art, below will be to embodiment
Needed for the accompanying drawing to be used be briefly described, it should be apparent that, drawings in the following description are only of the present utility model
Some embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can be with according to this
A little accompanying drawings obtain other accompanying drawings.
Fig. 1 is a kind of front view of aircraft water conservancy diversion Cooling System of the utility model embodiment；
Fig. 2 is a kind of side view of aircraft water conservancy diversion Cooling System of the utility model embodiment；
In figure：1st, crossbeam pipe；2nd, flow-guiding mouth；3rd, body.
Specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, all other embodiment that those of ordinary skill in the art are obtained all belongs to
In the scope of the utility model protection.
As shown in Figure 1-2, a kind of aircraft water conservancy diversion Cooling System described in the utility model embodiment, including installation
Crossbeam pipe 1 on body 3, the middle part of described crossbeam pipe 1 is provided with flow-guiding mouth 2, wherein, described crossbeam pipe 1 is that tubulose is empty
Core structure.
In one embodiment, described crossbeam pipe 1 is installed on the centre position at the top of body 3, and to the two of body
Side extends.
Other structures can be installed inside crossbeam pipe of the present utility model, but need to keep air-flow when other structures are installed
Can also circulate from the flow-guiding mouth of crossbeam pipe to crossbeam pipe two ends.
The utility model is mainly made up of crossbeam pipe 1, flow-guiding mouth 2 and body 3, during crossbeam pipe 1 is located at the top of body
Between.By the flow-guiding mouth, preferably quick flow when flying before aircraft can smoothly be imported and carry out inside crossbeam pipe nature
Air cooling, can preferably resolve the heat dissipation problem of crossbeam pipe internal structure, while nor affecting on the flying quality of aircraft, make
Being optimal of structure of aircraft.
Aircraft is in flight course, and air-flow is extremely important for aircraft, the flow velocity of the air-flow of aircraft surface
Than very fast.For this purpose, the outline airflow design of aircraft is extremely important, the air-flow of aircraft surface can neither be affected, can not
Affect the performance of aircraft.Air-flow in the middle of smooth entrance crossbeam pipe, and is discharged, entirely by flow-guiding mouth 2 from crossbeam pipe two ends
The smoothly loop of air-flow stroke one, by the effect of air-flow, reaches the effect to being cooled down inside crossbeam pipe.Whole water conservancy diversion
The aerodynamic configuration for being designed with aerodynamic principle, not affecting aircraft of mouth.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Within the spirit and principle of utility model, any modification, equivalent substitution and improvements made etc. should be included in the utility model
Protection domain within.
Claims (3)
1. a kind of aircraft water conservancy diversion Cooling System, it is characterised in that including the crossbeam pipe being installed on body, described is big
Flow-guiding mouth is provided with the middle part of beam pipe.
2. a kind of aircraft water conservancy diversion Cooling System according to claim 1, it is characterised in that described crossbeam pipe is
Tubular, hollow structure.
3. a kind of aircraft water conservancy diversion Cooling System according to claim 2, it is characterised in that described crossbeam Guan An
Loaded on the centre position at the top of body, and extend to the both sides of body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173542.XU CN206155766U (en) | 2016-11-03 | 2016-11-03 | Aircraft water conservancy diversion natural cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173542.XU CN206155766U (en) | 2016-11-03 | 2016-11-03 | Aircraft water conservancy diversion natural cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206155766U true CN206155766U (en) | 2017-05-10 |
Family
ID=58657031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621173542.XU Active CN206155766U (en) | 2016-11-03 | 2016-11-03 | Aircraft water conservancy diversion natural cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206155766U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110318856A (en) * | 2019-07-12 | 2019-10-11 | 青岛未来创新高新技术有限公司 | The intelligent temperature control system and its implementation of unmanned vehicle engine |
-
2016
- 2016-11-03 CN CN201621173542.XU patent/CN206155766U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110318856A (en) * | 2019-07-12 | 2019-10-11 | 青岛未来创新高新技术有限公司 | The intelligent temperature control system and its implementation of unmanned vehicle engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230816 Address after: Room 202, No. 11 Dexing Lane, Chong'an District, Wuxi City, Jiangsu Province, 214000 Patentee after: Yang Haiyan Address before: 215100 Qianghua Road, Huayang village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee before: HELIPELLER GENERAL AIRCRAFT CO.,LTD. |