CN109720586A - A kind of boundary layer diverter - Google Patents
A kind of boundary layer diverter Download PDFInfo
- Publication number
- CN109720586A CN109720586A CN201711040024.XA CN201711040024A CN109720586A CN 109720586 A CN109720586 A CN 109720586A CN 201711040024 A CN201711040024 A CN 201711040024A CN 109720586 A CN109720586 A CN 109720586A
- Authority
- CN
- China
- Prior art keywords
- wasteway
- trim panel
- boundary layer
- air
- air entraining
- 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.)
- Pending
Links
Landscapes
- Superstructure Of Vehicle (AREA)
Abstract
The present invention discloses a kind of boundary layer diverter, the component including compositions such as trim panel, wasteway, overflow port and air entraining passages；The trim panel blocks air entraining passage and wasteway in the outside of wasteway, conformal with the shape of fuselage and air intake duct；Trim panel, wasteway and air entraining passage are mounted between airframe and air intake duct；Overflow port is the opening on trim panel.The present invention relates to the improvement to aircraft boundary layer diverter, belong to field of flight vehicle design.The principle of the invention is simple, it can be achieved that property is strong；The design and aircraft overall performance requirement of boundary-layer can be taken into account, moreover it is possible to provide cold air import for equipment in fuselage.
Description
Technical field
The invention belongs to Flight Vehicle Design professions, are related to the improvement to aircraft boundary layer diverter.
Background technique
The boundary layer diverter of dopey is arranged boundary-layer to fuselage two sides using wedge at present.Chinese utility model
Patent " airplane intake boundary-layer is let out except dress " sets 201320718948.1 applying date of the patent No.: 2013-11-10, main feature
It is to be equipped between air inlet road junction and fuselage every road, uses β glut angle every road front end, it is smooth by inside and outside circular arc respectively above and below every road
Connection guidance fuselage boundary-layer low energy air-flow is discharged from every road upper and lower surfaces.There are following defects for the design: fuselage, air inlet
U-clamp angle is formed between road and wedge, and then generates corner reflector effect, it is unfavorable to stealthing design；It also needs in fuselage simultaneously
Other positions design bleed ports.
Summary of the invention
It is an object of the invention to overcome deficiency in the prior art, propose that a kind of thinking is effective, it is low in cost and have
The boundary layer diverter that can be engineered, the boundary-layer isolation for taking into account middle dopey needs and stealthing design requirement, in boundary-layer flow
When measuring enough, using boundary-layer bleed to fuselage interior, used for airborne equipment.
Realizing the technical solution of above-mentioned purpose is:
A kind of boundary layer diverter, including trim panel 1, wasteway 2, overflow port 3 and air entraining passage 4；The air entraining passage 4 is located at centre,
One wasteway 2 of each setting is arranged in 4 two sides of air entraining passage；The trim panel 1 is in the outside of wasteway；The wasteway 2 is along two sides
Overflow port 3 is provided on trim panel 1 backward.
A kind of boundary layer diverter of the invention is mounted between airframe and air intake duct.
The trim panel 1 forms air entraining passage 4 and 2 two sides of wasteway along airframe and air intake duct and blocks.
The shape of the trim panel 1 and fuselage and air intake duct is conformal.
The air entraining passage 4 is rectangular inlet.
The wasteway 2 is rectangular inlet.
The present invention blocks air entraining passage and wasteway by trim panel, using Specular reflection principle by incident radar wave
Other directions are reflexed to, reflection radar intensity of wave is reduced；U-clamp angle between fuselage and air intake duct is changed into pipeline, that is, is overflow
Runner eliminates the angle transmitter effect at U-clamp angle, can further decrease reflection radar by the stealthy measure of cavity in wasteway
Intensity of wave；Boundary-layer air-flow can be led to fuselage interior by air entraining passage, used for airborne equipment, avoided opening up dedicated " cat ear " etc.
Bleed ports reduce radar strong scattering source.
Boundary layer diverter weight cost of the invention is small, can take into account the design requirement of boundary-layer and wanting for stealthing design
It asks, moreover it is possible to provide cold air import for equipment in fuselage.The configuration of the present invention is simple, it is easy to implement.It may be used on vehicle, ship simultaneously
Equal fields.
Detailed description of the invention
Fig. 1 is present invention installation implementation diagram.
Fig. 2 is relation schematic diagram between trim panel and other structures.
Fig. 3 is relation schematic diagram between wasteway 2, air entraining passage 4 and other structures.
Fig. 4 is wasteway 2 and 4 schematic diagram of air entraining passage.
Specific embodiment
Below with reference to an example of the present invention and attached drawing, the present invention is further described.
Embodiment 1
Referring to Fig. 1 to Fig. 4, a kind of boundary layer diverter of the present invention is mounted between airframe 5 and air intake duct 6, including trim panel
1, wasteway 2, overflow port 3 and air entraining passage 4；The air entraining passage 4 is located at centre, and one overflow of each setting is arranged in 4 two sides of air entraining passage
Road 2；The trim panel 1 is in the outside of wasteway；The wasteway 2 is provided with overflow port 3 along two sides on trim panel 1 backward.
The trim panel 1 blocks air entraining passage 4 and the formation of wasteway 2 along airframe 5 and air intake duct 6.The trim panel 1 and fuselage 5
It is conformal with the shape of air intake duct 6.
Embodiment 2
Referring to Fig. 1 to Fig. 4, boundary layer diverter of the invention is by the overflow of 4,2 rectangular inlets of air entraining passage of 1 rectangular inlet
The compositions such as the trim panel 1 on the outside of road 2, wasteway 2, the overflow port 3 on trim panel 1.2 wasteways 2 are in the left and right of air entraining passage 4 two
Side；The outside of left and right sides wasteway 2 has corresponding trim panel 1 to block respectively, and trim panel 1 is according to specific fuselage 5 and air inlet
The outer shape in road 6, it is conformal with fuselage 5 and air intake duct 6；Rectangle overflow port 3, left and right sides overflow are opened up on left and right sides trim panel 1
Road 2 is connected with corresponding overflow port 3 respectively.
Embodiment 3
A kind of boundary layer diverter of the present invention, is mounted between airframe 5 and air intake duct 6, including trim panel 1, wasteway 2, overflows
Head piece 3 and air entraining passage 4；The air entraining passage 4 is located at centre, and one wasteway 2 of each setting is arranged in 4 two sides of air entraining passage；The shaping
Plate 1 is in the outside of wasteway；The wasteway 2 is provided with overflow port 3 along two sides on trim panel 1 backward.1 edge of trim panel
Airframe 5 and air intake duct 6 block air entraining passage 4 and the formation of wasteway 2.The shape of trim panel 1 and fuselage 5 and air intake duct 6 is total
Shape.Wasteway 2 is shaped between fuselage 5 and air intake duct 6 by composite formed or sheet metal component riveting forming or metal casting.
Air entraining passage 4 is shaped between fuselage 5 and air intake duct 6 by composite formed or sheet metal component riveting forming or metal casting.
Claims (6)
1. a kind of boundary layer diverter, including trim panel (1), wasteway (2), overflow port (3) and air entraining passage (4)；The air entraining passage
(4) it is located at centre, one wasteway (2) of each setting is arranged in air entraining passage (4) two sides；The trim panel (1) is in the outside of wasteway；
The wasteway (2) is provided with overflow port (3) along two sides on trim panel (1) backward.
2. a kind of boundary layer diverter according to claim 1, which is characterized in that its be mounted on airframe and air intake duct it
Between.
3. a kind of boundary layer diverter according to claim 1, which is characterized in that the trim panel (1) along airframe and
Air intake duct forms air entraining passage (4) and wasteway (2) two sides and blocks.
4. a kind of boundary layer diverter according to claim 1, which is characterized in that the trim panel (1) and fuselage and air inlet
The shape in road is conformal.
5. a kind of boundary layer diverter according to claim 1, which is characterized in that the air entraining passage (4) is rectangular inlet.
6. a kind of boundary layer diverter according to claim 1, which is characterized in that the wasteway (2) is rectangular inlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711040024.XA CN109720586A (en) | 2017-10-30 | 2017-10-30 | A kind of boundary layer diverter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711040024.XA CN109720586A (en) | 2017-10-30 | 2017-10-30 | A kind of boundary layer diverter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109720586A true CN109720586A (en) | 2019-05-07 |
Family
ID=66293984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711040024.XA Pending CN109720586A (en) | 2017-10-30 | 2017-10-30 | A kind of boundary layer diverter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109720586A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002758A (en) * | 2021-04-02 | 2021-06-22 | 北京北航天宇长鹰无人机科技有限公司 | Heat dissipation air inlet cabin and use its unmanned aerial vehicle |
| CN113120244A (en) * | 2021-04-27 | 2021-07-16 | 成都飞机工业（集团）有限责任公司 | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1243782A2 (en) * | 2001-03-23 | 2002-09-25 | The Boeing Company | Double jet engine inlet |
| CN101417592A (en) * | 2007-10-26 | 2009-04-29 | 尤洛考普特公司 | Improvement for rotorcraft equipped with turboshaft engines |
| US20100051756A1 (en) * | 2006-12-12 | 2010-03-04 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
| CA2689176A1 (en) * | 2008-12-31 | 2010-06-30 | Rolls-Royce Corporation | Gas turbine engine with ejector |
| CN101813027A (en) * | 2010-03-29 | 2010-08-25 | 南京航空航天大学 | Bump air inlet method for realizing integration of unequal-strength wave system with forebody |
| CN102826229A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Air inlet partition of air vehicle |
| CN102923309A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Invisible air intake system |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN205738118U (en) * | 2016-06-22 | 2016-11-30 | 成都飞机工业（集团）有限责任公司 | A kind of the most double S curved intake ports with stealthy function |
-
2017
- 2017-10-30 CN CN201711040024.XA patent/CN109720586A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1243782A2 (en) * | 2001-03-23 | 2002-09-25 | The Boeing Company | Double jet engine inlet |
| US20100051756A1 (en) * | 2006-12-12 | 2010-03-04 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
| CN101417592A (en) * | 2007-10-26 | 2009-04-29 | 尤洛考普特公司 | Improvement for rotorcraft equipped with turboshaft engines |
| CA2689176A1 (en) * | 2008-12-31 | 2010-06-30 | Rolls-Royce Corporation | Gas turbine engine with ejector |
| CN101813027A (en) * | 2010-03-29 | 2010-08-25 | 南京航空航天大学 | Bump air inlet method for realizing integration of unequal-strength wave system with forebody |
| CN102826229A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Air inlet partition of air vehicle |
| CN102923309A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Invisible air intake system |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN205738118U (en) * | 2016-06-22 | 2016-11-30 | 成都飞机工业（集团）有限责任公司 | A kind of the most double S curved intake ports with stealthy function |
Non-Patent Citations (1)
| Title |
|---|
| 张华军: "TBCC进气道研究现状及其关键技术", 《空气动力学学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002758A (en) * | 2021-04-02 | 2021-06-22 | 北京北航天宇长鹰无人机科技有限公司 | Heat dissipation air inlet cabin and use its unmanned aerial vehicle |
| CN113120244A (en) * | 2021-04-27 | 2021-07-16 | 成都飞机工业（集团）有限责任公司 | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage |
| CN113120244B (en) * | 2021-04-27 | 2022-07-15 | 成都飞机工业（集团）有限责任公司 | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3031713B1 (en) | Aircraft wing rib | |
| CN101952169B (en) | Aircraft nacelle including an optimised ice treatment system | |
| US8074924B2 (en) | Low-noise aircraft, particularly at take-off and landing | |
| ITTO20110122A1 (en) | AIRCRAFT CONFIGURATION TO IMPROVED AERODYNAMIC PERFORMANCES. | |
| CN103935524B (en) | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct | |
| CN109720586A (en) | A kind of boundary layer diverter | |
| CN100497092C (en) | Backpack S-shaped inlet channel | |
| CN103939216B (en) | Embedded type air inlet channel using combined opening surface vortex control method | |
| CN103587704A (en) | Combined subsonic air intake device of aircraft | |
| CN107380457A (en) | A kind of stealthy unmanned plane dynamical system of Flying-wing | |
| WO2012141770A3 (en) | Laminar flow wing optimized for transonic and supersonic cruise aircraft | |
| CN111204445A (en) | Leading-edge slat for aircraft | |
| DE602007002897D1 (en) | AIRCRAFT WING ARRANGEMENT WITH AN ENGINE MOUNTING GEAR DEFINING A LATERAL AIRFLOW CHANNEL IN THE FRONT AREA | |
| CN107762633A (en) | Bullet high-performance Submerged Inlet and boundary-layer minimizing technology | |
| CN109334948A (en) | Without rudder face aircraft | |
| CN106197941B (en) | A kind of icing mnncl tcst wing model for aircraft certification verifying | |
| CN106762146B (en) | A kind of hot air anti-icing structure of engine guide vane | |
| WO2023077686A1 (en) | Aircraft flap | |
| CN204368436U (en) | Flat opening wind scoop | |
| CN107521651B (en) | Aircraft with a flight control device | |
| CN102826229A (en) | Air inlet partition of air vehicle | |
| CN113148105A (en) | Double-head wing body fusion low-detectable layout | |
| CA2548752C (en) | Method and device for suctioning the boundary layer | |
| CN209241307U (en) | Without rudder face aircraft | |
| CN103979100A (en) | Main landing gear fairing of general-purpose plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190507 |
|
| RJ01 | Rejection of invention patent application after publication |