CN111942600B - Boundary layer-free partition air inlet channel - Google Patents
Boundary layer-free partition air inlet channel Download PDFInfo
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- CN111942600B CN111942600B CN202010783737.0A CN202010783737A CN111942600B CN 111942600 B CN111942600 B CN 111942600B CN 202010783737 A CN202010783737 A CN 202010783737A CN 111942600 B CN111942600 B CN 111942600B
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- bulge
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- 238000005192 partition Methods 0.000 title description 5
- 230000000694 effects Effects 0.000 abstract description 14
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000000926 separation method Methods 0.000 abstract description 6
- 239000010410 layer Substances 0.000 description 16
- 238000011084 recovery Methods 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the technical field of aviation air inlets, in particular to a boundary layer-free air inlet with a separation channel, which is used for solving the problems that the boundary layer separation channel of the air inlet increases the windward area of an airplane, so that the aerodynamic resistance of the airplane is increased, the stealth performance of a radar is reduced, and the air inlet is difficult to manufacture in the prior art. The invention comprises an air inlet pipeline, a lip and an expansion bulge which are sequentially formed into a whole, wherein the expansion bulge comprises a step surface and an expansion bulge main surface which are mutually formed into a whole, the step surface comprises an upper step surface and a lower step surface, and the edge of the lip is provided with a sweepback angle. The invention cancels boundary layer separating channels, eliminates the angle transmitter effect of boundary layer separating channel electromagnetic waves, reduces the windward area and the resistance of the airplane, and is easier to manufacture; the lip and the bulge adopt the sweepback angle design, so that the electromagnetic wave mirror effect of the airplane in the main use posture is reduced, and the stealth effect of the lip is improved.
Description
Technical Field
The invention relates to the technical field of aviation air inlets, in particular to an air inlet without a boundary layer partition channel.
Background
The aircraft is an apparatus flying in the atmosphere or the space outside the atmosphere, and the aircraft flies by the static buoyancy of the air or the aerodynamic force generated by the relative motion of the air, and the high-speed aircraft is the most common aircraft in the air suction type aircraft and is widely applied.
The air inlet channel comprises an air inlet surface positioned at the front end of the air inlet channel, an air inlet channel inner channel extending backwards from the air inlet surface, a lip cover surrounding the air inlet channel surface, a machine body part connected with the air inlet channel surface, the air inlet surface comprises a first port surface positioned outside the machine body part and a second port surface positioned inside the machine body part, the lip cover comprises a main lip cover and side lip covers bent and extending from two sides of the main lip cover and connected with the machine body part, the front edge of the main lip cover comprises a central sharp point and a first sweepback edge extending towards the oblique back direction from the central sharp point, the front edge of the side lip cover comprises an intersection point intersected with the first edge and a second sweepback edge extending towards the oblique back direction from the intersection point, and the air inlet channel is separated from the machine body surface by arranging a special auxiliary surface layer partition and a partition plate so as to avoid sucking air flow in the machine body surface auxiliary surface layer.
However, the boundary layer separation channel increases the windward area of the airplane, forms a corner reflector of electromagnetic waves, increases the aerodynamic drag of the airplane, reduces the radar stealth performance, increases the weight and the structural complexity of the airplane, and makes the air inlet channel difficult to manufacture and high in manufacturing cost.
Disclosure of Invention
Based on the above problems, the present invention aims to: the utility model provides a no boundary layer separates a way intake duct for the boundary layer that solves among the prior art intake duct separates the way and has increased the aircraft area of facing the wind, thereby makes the aerodynamic drag of aircraft increase, and radar stealthy performance descends, and the difficult problem of making of intake duct. The invention cancels boundary layer separating channels, eliminates the angle transmitter effect of boundary layer separating channel electromagnetic waves, reduces the windward area and the resistance of the airplane, and is easier to manufacture; the lip and the bulge adopt the sweepback angle design, so that the electromagnetic wave mirror effect of the airplane in the main use posture is reduced, and the stealth effect of the lip is improved.
The invention specifically adopts the following technical scheme for realizing the purpose:
the utility model provides a no boundary layer separates passageway intake duct, includes intake duct pipeline, lip and the swell of shaping as an organic whole in proper order, the swell includes mutual shaping step face and swell main face as an organic whole, the step face includes step face and lower step face, the edge of lip is equipped with the back and sweeps the angle.
The upper step surface and the lower step surface are both planes. And the included angles between the upper step surface and the course and the included angles between the lower step surface and the course are A.
Preferably, A is 30-45 deg.
The main surface of the bulge is parallel to the course, and a round circle is arranged at the joint of the main surface of the bulge and the step surface.
The height of the main surface of the bulge is 40 mm.
The sweep angle comprises an overlooking sweep angle B and a front-view sweep angle C, the overlooking sweep angle B is 30-40 degrees, and the front-view sweep angle C is 12-20 degrees.
The invention has the following beneficial effects:
(1) according to the invention, the bulge is utilized to discharge the boundary layer low-energy airflow to two sides, so that the total pressure recovery coefficient of the air inlet channel is improved, the boundary layer separation channel is cancelled, the angle transmitter effect of the boundary layer separation channel electromagnetic waves is eliminated, and the windward area and the resistance of the airplane are reduced; the lip and the bulge adopt the sweepback angle design, so that the electromagnetic wave mirror effect of the airplane in the main use posture is reduced, and the stealth effect of the lip is improved.
(2) On the premise of ensuring that the total pressure recovery coefficient and the flow field distortion index of the air inlet channel meet the requirements, the aircraft air inlet channel is free of boundary layer separation channels, so that the aerodynamic resistance of the aircraft is reduced, and the stealth performance of the aircraft radar is improved.
(3) The bulge and the lip are simple in structure form and low in manufacturing difficulty, and the resistance of the airplane is further reduced.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic top view of the present invention;
FIG. 3 is a schematic front view of the present invention;
reference numerals: 1 bulge, 11 step surfaces, 111 lower step surfaces, 112 upper step surfaces, 12 bulge main surfaces, 2 lips and 3 inlet channel pipes.
Detailed Description
For a better understanding of the present invention by those skilled in the art, the present invention will be described in further detail below with reference to the accompanying drawings and the following examples.
Example 1:
as shown in fig. 1-3, a boundary-layer-free divided-channel air inlet comprises an air inlet channel 3, a lip 2 and a bulge 1 which are sequentially formed into a whole, wherein the bulge 1 comprises a step surface 11 and a bulge main surface 12 which are formed into a whole, the step surface 11 comprises an upper step surface 112 and a lower step surface 111, and the edge of the lip 2 is provided with a sweepback angle.
Wherein, the upper step surface 112 and the lower step surface 111 are both flat surfaces. The included angles between the upper step surface 112 and the lower step surface 111 and the heading direction are A, and A is preferably 30-45 degrees.
The main surface of the bulge 1 is parallel to the course, and the joint of the bulge main surface 12 and the step surface 11 is provided with a round shape.
The height of the bulge main surface 12 is 40 mm.
The sweep angle comprises an overlooking sweep angle B and a front-view sweep angle C, the overlooking sweep angle B is 30-40 degrees, and the front-view sweep angle C is 12-20 degrees. The so-called top-down sweep angle B is the sweep angle as seen from the top-down angle of the drawing, as shown in fig. 2; the so-called front sweep angle C is a sweep angle as viewed from the front of the drawing, as shown in fig. 3.
Because the surface of the airplane has boundary layer low-energy airflow with a certain thickness, the boundary layer low-energy airflow is discharged to two sides by using the bulge 1, and the step surface 11 and the course form a certain included angle, so that electromagnetic waves are reflected to two side directions through the step surface 11, the radar scattering sectional area is reduced, and the total pressure recovery coefficient of the air inlet channel is improved; the boundary layer channel is cancelled, and the angle transmitter effect of the boundary layer channel electromagnetic wave is eliminated; the lip 2 and the bulge 1 adopt the sweepback angle design, the electromagnetic wave mirror effect of the airplane in the main use posture is eliminated, the stealth effect of the lip 2 is achieved, the structural form of the bulge 1 is simpler, and the processing and the manufacturing are easier.
Example 2:
as shown in fig. 1-3, a boundary-layer-free divided-channel air inlet comprises an air inlet channel 3, a lip 2 and a bulge 1 which are sequentially formed into a whole, wherein the bulge 1 comprises a step surface 11 and a bulge main surface 12 which are formed into a whole, the step surface 11 comprises an upper step surface 112 and a lower step surface 111, and the edge of the lip 2 is provided with a sweepback angle.
The upper step surface 112 and the lower step surface 111 are both planes, the included angles between the upper step surface 112 and the heading direction and the included angles between the lower step surface 111 and the heading direction are both A, A is preferably 33 degrees, R10 rounding or other curve smooth transition is arranged between the step surface 11 and the bulge main surface 12, R10 rounding is arranged between the step surface and the machine body, R10 rounding is also arranged at the intersection of the upper step surface 112 and the lower step surface 111, the height of the bulge main surface 12 is 40mm, and the bulge main surface 12 is parallel to the heading direction.
The sweep angle comprises an overlook sweep angle B and an orthographic sweep angle C, the overlook sweep angle B is 33 degrees, and the orthographic sweep angle C is 17 degrees. The so-called top-down sweep angle B is the sweep angle as seen from the top-down angle of the drawing, as shown in fig. 2; the forward sweep angle C is a sweep angle viewed from the front of the drawing, and as shown in fig. 3, the lip on the front may be a double sweep structure or a single sweep structure. Therefore, the electromagnetic wave mirror effect of the lip 2 in the forward +/-30 degrees and pitching +/-10 degrees of the airplane can be eliminated, and a better stealth effect is achieved.
In addition, the design scheme of the air inlet in the two embodiments can be suitable for the airplane with the air inlet structures on two sides, and can also be suitable for the airplane with the air inlet structure on the back or the belly.
The above is an embodiment of the present invention. The above embodiments are illustrative of the present invention, and are not intended to limit the present invention, and any simple modified embodiments such as scaling, rounding or other curves or other transition ways, and changing the height of the boundary layer, etc. of the present embodiment are all within the scope of the present invention.
Claims (3)
1. The utility model provides a no boundary layer separates way intake duct which characterized in that: the device comprises an air inlet pipeline (3), a lip (2) and an expansion bump (1) which are sequentially formed into a whole, wherein the expansion bump (1) comprises a step surface (11) and an expansion bump main surface (12) which are formed into a whole, the step surface (11) comprises an upper step surface (112) and a lower step surface (111), a sweepback angle is arranged at the edge of the lip (2), and the lip on the front side is of a double sweepback structure or a single-direction sweepback structure;
the upper step surface (112) and the lower step surface (111) are both planes;
the included angles between the upper step surface (112) and the course and the included angles between the lower step surface (111) and the course are all A, and the A is 30-45 degrees;
the main surface (12) of the bulge is parallel to the course, and a round circle is arranged at the joint of the main surface (12) of the bulge and the step surface (11).
2. The boundary-layer-free baffled air intake duct of claim 1, wherein: the height of the main surface (12) of the bulge is 40 mm.
3. The boundary-layer-free baffled air intake duct of claim 1, wherein: the sweep angle comprises an overlooking sweep angle B and a front-view sweep angle C, the overlooking sweep angle B is 30-40 degrees, and the front-view sweep angle C is 12-20 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010783737.0A CN111942600B (en) | 2020-08-06 | 2020-08-06 | Boundary layer-free partition air inlet channel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010783737.0A CN111942600B (en) | 2020-08-06 | 2020-08-06 | Boundary layer-free partition air inlet channel |
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| Publication Number | Publication Date |
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| CN111942600A CN111942600A (en) | 2020-11-17 |
| CN111942600B true CN111942600B (en) | 2022-03-08 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113071689A (en) * | 2021-05-08 | 2021-07-06 | 上海甘石星经智能科技有限公司 | Air inlet channel of subsonic aircraft |
| CN115571351A (en) * | 2022-11-21 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Flying wing layout backpack air inlet channel with high-low speed performance and stealth performance |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5779189A (en) * | 1996-03-19 | 1998-07-14 | Lockheed Martin Corporation | System and method for diverting boundary layer air |
| US5749542A (en) * | 1996-05-28 | 1998-05-12 | Lockheed Martin Corporation | Transition shoulder system and method for diverting boundary layer air |
| CN101813027B (en) * | 2010-03-29 | 2013-04-10 | 南京航空航天大学 | Bump air inlet method for realizing integration of unequal-strength wave system with forebody |
| CN101798961B (en) * | 2010-03-29 | 2012-08-22 | 南京航空航天大学 | Two-stage beveled supersonic speed air inlet lip |
| US20160144972A1 (en) * | 2013-08-06 | 2016-05-26 | United Technologies Corporation | Blended Wing Body Boundary Layer Ingesting Inlet Design Integration |
| FR3022218B1 (en) * | 2014-06-12 | 2016-07-15 | Airbus Operations Sas | AIRCRAFT NACELLE COMPRISING AN ENHANCED AIR INTAKE |
| CN104590570B (en) * | 2014-11-19 | 2016-08-24 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of construction design method of inner equilibrium self adaptation bump inlet |
| JP6128568B2 (en) * | 2015-03-26 | 2017-05-17 | 株式会社Ｓｕｂａｒｕ | Aircraft intake structure |
| CN105649779B (en) * | 2016-01-29 | 2017-03-08 | 厦门大学 | The controlled bulge method for designing of transverse-pressure gradient |
| JP6689231B2 (en) * | 2017-04-11 | 2020-04-28 | 株式会社Ｓｕｂａｒｕ | Intake design method, intake design program, and intake design device |
| CN107215473B (en) * | 2017-06-08 | 2018-08-31 | 南京航空航天大学 | A kind of and integrated nothing of aircraft is every road Subsonic inlet |
| CN109899178A (en) * | 2019-03-08 | 2019-06-18 | 中国人民解放军国防科技大学 | Hypersonic air inlet channel with pre-compression device |
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