CN202624638U - Stamped intake hood of aircraft ventilation-cooling system - Google Patents
Stamped intake hood of aircraft ventilation-cooling system Download PDFInfo
- Publication number
- CN202624638U CN202624638U CN 201220270280 CN201220270280U CN202624638U CN 202624638 U CN202624638 U CN 202624638U CN 201220270280 CN201220270280 CN 201220270280 CN 201220270280 U CN201220270280 U CN 201220270280U CN 202624638 U CN202624638 U CN 202624638U
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- China
- Prior art keywords
- intake
- aircraft
- hood
- stamped
- 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.)
- Expired - Lifetime
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Abstract
The utility model belongs to the field of aviation and relates to a stamped intake hood for forced ventilation cooling and air intake of an aircraft system, namely a stamped intake hood of the aircraft ventilation-cooling system. The stamped intake hood is fixed on aircraft skin. The front end and the rear end of the stamped intake hood are communicated. The stamped intake hood is combined with the aircraft skin to form an air intake and an outlet. The rear outlet of the intake hood is smaller than the front air intake, so that a shrinkable hood is formed. The middle of the hood right faces to a cooling intake pipe. The rear opening of the intake hood can effectively balance intake efficiency and pneumatic resistance, and accordingly the pneumatic resistance is reduced while the intake efficiency of the aircraft system is guaranteed. In addition, the stamped intake hood is simple in processing technique and reliable in operation, and the problem that intake efficiency and pneumatic resistance of the traditional air intake cannot be guaranteed at the same is solved.
Description
Technical field
The utility model belongs to aviation field, relates to a kind of punching press airscoop shroud that is used for aircraft system forced ventilation cooling air inlet.
Background technology
Aircraft system often need be extracted the air admission system from the external world, and the admission port that adopts usually at present has embedded admission port of NACA and cat ear type ram intake.The embedded admission port of NACA is little to the influence of aircraft aerodynamic configuration, but intake efficiency is low; Cat ear type punching press airscoop shroud intake efficiency is high, but big to the aerodynamic configuration influence, aerodynamic drag is big.
Summary of the invention
The purpose of the utility model provides the aircraft ventilation cooling system punching press airscoop shroud that a kind of configuration is simple, little to the aerodynamic configuration influence, intake efficiency is high.
The technical scheme of the utility model is: a kind of aircraft ventilation cooling system punching press airscoop shroud; It is fixed on the aircraft skin, and its front and back end communicates, and being harmonious with aircraft skin forms admission port and outlet; Wherein, This airscoop shroud back outlet size forms and shrinks cover body less than the front end air inlet port dimensions, and the cover body interlude is over against the cooling air inlet pipe.
Described aircraft ventilation cooling system punching press airscoop shroud is the single cover body of one machine-shaping.
The cover body interlude adopts stream line pattern transition profile.
Advantage that the utlity model has and beneficial effect: the utility model is through in the airscoop shroud open rearward end, can active balance intake efficiency and aerodynamic drag, when guaranteeing the aircraft system intake efficiency, reduced aerodynamic drag.Simultaneously, the utility model processing technology is simple, and reliable operation has solved the difficult problem of taking into account of traditional admission port intake efficiency and aerodynamic drag.
Description of drawings
Fig. 1 is the structural representation of the utility model aircraft ventilation cooling system punching press airscoop shroud,
Wherein, 1-admission port, 2-cover body, 3-outlet, 4-aircraft skin, 5-cool off admission line.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described further:
See also Fig. 1, it is the structural representation of the utility model aircraft ventilation cooling system punching press airscoop shroud.Said aircraft ventilation cooling system punching press airscoop shroud is single cover body 2, is fixed on the aircraft skin 4 through bolt or rivet.This airscoop shroud front and back end communicates, and being harmonious with aircraft skin 4 forms admission port 1 and outlet 3, and interlude adopts the excessive profile of stream line pattern, over against cooling air inlet pipe 5, to reduce the influence to flowing.Wherein, this airscoop shroud back outlet size forms and shrinks cover body less than front end admission port 1 size.In addition, this airscoop shroud is one machine-shaping, makes simply, and cost is low.
During actual the use, airscoop shroud is fixed on the aircraft outer skin, and air-flow gets into from the front end import, and under the compression of shrinking cover body, pressure increases, and gets into the cooling air inlet pipe 5 of cover body below, has higher intake efficiency.The a part of air-flow that gets into from admission port simultaneously flows out from back outlet, reduces the aerodynamic drag that airscoop shroud causes, avoids in the airscoop shroud gaseous tension excessive and cause air inlet obstruction or overflow.
In addition, to concrete air inlet requirement, can import and export size through changing, the adjustment intake pressure is to reach best air inlet effect.
Claims (3)
1. an aircraft ventilation cooling system punching press airscoop shroud is characterized in that, is fixed on the aircraft skin; Its front and back end communicates; Being harmonious with aircraft skin forms admission port and outlet, and wherein, this airscoop shroud back outlet size is less than the front end air inlet port dimensions; Form and shrink cover body, and the cover body interlude is over against the cooling air inlet pipe.
2. aircraft ventilation cooling system punching press airscoop shroud according to claim 1 is characterized in that, is the single cover body of one machine-shaping.
3. aircraft ventilation cooling system punching press airscoop shroud according to claim 2 is characterized in that, the cover body interlude adopts stream line pattern transition profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220270280 CN202624638U (en) | 2012-06-08 | 2012-06-08 | Stamped intake hood of aircraft ventilation-cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220270280 CN202624638U (en) | 2012-06-08 | 2012-06-08 | Stamped intake hood of aircraft ventilation-cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202624638U true CN202624638U (en) | 2012-12-26 |
Family
ID=47377862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220270280 Expired - Lifetime CN202624638U (en) | 2012-06-08 | 2012-06-08 | Stamped intake hood of aircraft ventilation-cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202624638U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533271A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of heat dissipation ventilation lid and the aircraft with it |
| CN112351660A (en) * | 2020-11-20 | 2021-02-09 | 中国电子科技集团公司第二十九研究所 | Low-aerodynamic-resistance skin heat exchange device and design method thereof |
-
2012
- 2012-06-08 CN CN 201220270280 patent/CN202624638U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533271A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of heat dissipation ventilation lid and the aircraft with it |
| CN112351660A (en) * | 2020-11-20 | 2021-02-09 | 中国电子科技集团公司第二十九研究所 | Low-aerodynamic-resistance skin heat exchange device and design method thereof |
| CN112351660B (en) * | 2020-11-20 | 2023-04-14 | 中国电子科技集团公司第二十九研究所 | Low-aerodynamic-resistance skin heat exchange device and design method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |