CN111942600A

CN111942600A - Boundary layer-free partition air inlet channel

Info

Publication number: CN111942600A
Application number: CN202010783737.0A
Authority: CN
Inventors: 刘博�; 宋勇; 李世秋; 谢文忠; 于红勇; 何国忠; 刘驰; 王荣; 童凯; 李晓飞
Original assignee: Sichuan Aerospace Zhongtian Power Equipment Co ltd
Current assignee: Sichuan Aerospace Zhongtian Power Equipment Co ltd
Priority date: 2020-08-06
Filing date: 2020-08-06
Publication date: 2020-11-17
Anticipated expiration: 2040-08-06
Also published as: CN111942600B

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

Boundary layer-free partition air inlet channel

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:

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 main surface 12 of the bulge, R10 rounding is arranged between the step surface and the bulge, R10 rounding is also arranged at the intersection of the upper step surface 112 and the lower step surface 111, the height of the main surface 12 of the bulge is 40mm, and the main surface 12 of the bulge 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

1. The utility model provides a no boundary layer separates way intake duct which characterized in that: including intake duct pipeline (3), lip (2) and the swell (1) of shaping as an organic whole in proper order, swell (1) including mutual shaping step face (11) and swell main face (12) as an organic whole, step face (11) are including last step face (112) and lower step face (111), the edge of lip (2) is equipped with the sweepback angle.

2. The boundary-layer-free baffled air intake duct of claim 1, wherein: the upper step surface (112) and the lower step surface (111) are both planes.

3. The boundary-layer-free baffled air scoop of claim 2, wherein: the included angles between the upper step surface (112) and the lower step surface (111) and the course direction are A.

4. The boundary-layer-free baffled air scoop of claim 3, wherein: the A is 30-45 degrees.

5. The boundary-layer-free baffled air intake duct of claim 1, wherein: 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).

6. The boundary-layer-free baffled air scoop of claim 5, wherein: the height of the main surface (12) of the bulge is 40 mm.

7. 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.