CN204368436U - Flat opening wind scoop - Google Patents
Flat opening wind scoop Download PDFInfo
- Publication number
- CN204368436U CN204368436U CN201420813900.3U CN201420813900U CN204368436U CN 204368436 U CN204368436 U CN 204368436U CN 201420813900 U CN201420813900 U CN 201420813900U CN 204368436 U CN204368436 U CN 204368436U
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- China
- Prior art keywords
- wind scoop
- flow guiding
- aircraft skin
- aircraft
- front flow
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Abstract
The utility model relates to a kind of flat opening wind scoop, comprise front flow guiding plate (1) and rear deflecting plate (2), front flow guiding plate (1) and aircraft skin (4) angle are 10 ° ~ 25 °, length is suitable with aircraft skin Opening length, rear deflecting plate (2) and aircraft horizontal plane angle are 10 ° ~ 45 °, have two side (3) between front flow guiding plate (1) and rear deflecting plate (2).The utility model brings a technical leap for the design of engine bay ventilation cooling system admission port, make engine bay ventilation cool admission port to be all embedded under aircraft skin, eliminate former punching press wind scoop and be placed in the form resistance brought outside aircraft skin, eliminate former punching press wind scoop and be placed in the front radar area brought outside covering.
Description
Technical field
The utility model relates to technical field of aerospace, relates to a kind of flat opening wind scoop.
Background technology
In airplane design, if engine bay ventilation cooling system need introduce cooling-air from aircraft, traditional mode adopts punching type wind scoop to draw cold air from aircraft to enter machinery space.Punching type wind scoop is that cold air is introduced a kind of bleed mode in aircraft by incoming flow punching press effect by a kind of being placed in outside aircraft skin.Along with present generation aircraft is especially more and more higher to the requirement of rebecca Stealth Fighter to the raising of flight performance requirement, punching type wind scoop is placed in outside aircraft skin can bring extra aerodynamic drag, punching press wind scoop shape itself is pipeline, has highlighted the shortcoming that its front radar return is strong.Engine bay ventilation cooling system is in the urgent need to a kind of novel bleed form, this bleed mode should meet the requirement of engine bay ventilation amount, can reduce or eliminate the extra aerodynamic drag brought to aircraft again, reducing simultaneously or eliminating this bleed mode is the front radar area that aircraft brings.
Summary of the invention
In order to reduce conventional ones wind scoop aerodynamic drag, improve the shortcoming that punching press wind scoop stealth capabilities is weak, the utility model, for the weak point in prior art, provides one and can eliminate extra aerodynamic drag, can eliminate again the novel flat opening wind scoop of punching press wind scoop stealth capabilities.
In order to achieve the above object, the utility model provides a kind of flat opening wind scoop, comprise front flow guiding plate (1) and rear deflecting plate (2), front flow guiding plate (1) and aircraft skin (4) angle are 10 ° ~ 25 °, length is suitable with aircraft skin Opening length, rear deflecting plate (2) and aircraft horizontal plane angle are 10 ° ~ 45 °, have two side (3) between front flow guiding plate (1) and rear deflecting plate (2).
Further, above-mentioned covering opening size scope is along course: 80mm ~ 400mm, perpendicular to course on covering: 60mm ~ 200mm.
Further, above-mentioned front flow guiding plate and aircraft horizontal plane angle are 15 ° ~ 18 °.
Further, above-mentioned rear deflecting plate and aircraft horizontal plane angle are 15 ° ~ 30 °.
Beneficial effect: the utility model brings a technical leap for the design of engine bay ventilation cooling system admission port, make engine bay ventilation cool admission port to be all embedded under aircraft skin, eliminate former punching press wind scoop and be placed in the form resistance brought outside aircraft skin, eliminate former punching press wind scoop and be placed in the front radar area brought outside covering.
Accompanying drawing illustrates:
Fig. 1 is the flat opening wind scoop structural representation according to the utility model proposes;
The utility model that Fig. 2 is installs and uses structural representation;
1: front flow guiding plate, 2: rear deflecting plate, 3: sidewall, 4: covering is illustrated, 5: air, 6: machinery space is illustrated.
Detailed description of the invention:
Details and the service condition of the flat opening wind scoop of foundation the utility model is described in detail below in conjunction with Figure of description.
The flat opening wind scoop of the one that the utility model provides, comprise front flow guiding plate 1 and rear deflecting plate 2, front flow guiding plate and aircraft skin 4 angle are 10 ° ~ 25 °, length is suitable with aircraft skin Opening length, rear deflecting plate 2 is 10 ° ~ 45 ° with aircraft skin angle, have two side 3 between front flow guiding plate 1 and rear deflecting plate 2, two side 3 is vertical with aircraft skin 4, forms hollow oblique parallelepiped structure between two side 3 and front flow guiding plate 1, rear deflecting plate 2.
The opening size of flat opening wind scoop on covering is determined on a case-by-case basis, and generally according to aircaft configuration ability to bear, its range of sizes is long 80mm ~ 400mm, wide 60mm ~ 200mm.
In actual use, if above-mentioned front flow guiding plate 1 and aircraft skin 4 horizontal plane angle are 15 ° ~ 18 °, then better effects if.
Same, rear deflecting plate 2 is 15 ° ~ 30 ° with aircraft skin 4 angle, then effect is better.
Fig. 1 is flat opening wind scoop profile signal of the present utility model.It is arranged on aircraft skin when using by the utility model, and as shown in Figure 2, cold air 5 is surperficial through flat opening wind scoop inflow engine cabin 6 from aircraft skin.
Flat opening wind scoop one end described in the utility model is connected with aircraft skin, rounding off between front flow guiding plate 1 and covering 4, be connected by flange with aircraft skin inside and obtained by strengthening rib strip and support, the cold air 5 outside machine is imported in machinery space 6 by cavity.
The utility model brings a technical leap for the design of engine bay ventilation cooling system admission port, make engine bay ventilation cool admission port to be all embedded under aircraft skin, eliminate former punching press wind scoop and be placed in the extra aerodynamic drag brought outside aircraft skin, eliminate former punching press wind scoop and be placed in the front radar area brought outside covering.
Claims (4)
1. a flat opening wind scoop, it is characterized in that: comprise front flow guiding plate (1) and rear deflecting plate (2), front flow guiding plate (1) and aircraft skin (4) angle are 10 ° ~ 25 °, length is suitable with aircraft skin Opening length, rear deflecting plate (2) and aircraft horizontal plane angle are 10 ° ~ 45 °, have two side (3) between front flow guiding plate (1) and rear deflecting plate (2).
2. flat opening wind scoop according to claim 1, is characterized in that: covering opening size scope is along course: 80mm ~ 400mm, perpendicular to course on covering: 60mm ~ 200mm.
3. flat opening wind scoop according to claim 1, is characterized in that: front flow guiding plate and aircraft horizontal plane angle are 15 ° ~ 18 °.
4. flat opening wind scoop according to claim 1, is characterized in that: rear deflecting plate and aircraft horizontal plane angle are 15 ° ~ 30 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420813900.3U CN204368436U (en) | 2014-12-19 | 2014-12-19 | Flat opening wind scoop |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420813900.3U CN204368436U (en) | 2014-12-19 | 2014-12-19 | Flat opening wind scoop |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204368436U true CN204368436U (en) | 2015-06-03 |
Family
ID=53324678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420813900.3U Active CN204368436U (en) | 2014-12-19 | 2014-12-19 | Flat opening wind scoop |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204368436U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730701A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Secondary flow system capable of changing secondary flow inlet area |
| CN106995049A (en) * | 2017-03-23 | 2017-08-01 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft body structure |
| CN109649667A (en) * | 2018-12-20 | 2019-04-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method of ventilation of aircraft engine nacelle |
-
2014
- 2014-12-19 CN CN201420813900.3U patent/CN204368436U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730701A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Secondary flow system capable of changing secondary flow inlet area |
| CN106995049A (en) * | 2017-03-23 | 2017-08-01 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft body structure |
| CN109649667A (en) * | 2018-12-20 | 2019-04-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method of ventilation of aircraft engine nacelle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |
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| CP01 | Change in the name or title of a patent holder |