A buried air intake

Abstract

A buried air inlet comprises an air inlet (1), an air outlet (2), a side edge (3), an inner channel (4), a low-energy flow discharge port (5), a low-energy flow discharge channel (6), a front guide surface (7), a rear guide surface (8) and a vortex low-energy flow guide (9), wherein the front guide surface (7) is provided with a vortex low-energy flow guide (9), the rear of the vortex low-energy flow guide (9) is provided with an inner channel (4), low-energy flow discharge ports (5) are symmetrically provided on both sides of the inner channel (4), the low-energy flow discharge port (5) is connected to the low-energy flow discharge channel (6), and the rear guide surface (8) is provided behind the inner channel (4). The present invention effectively reduces the boundary layer low-energy flow flowing into the buried air inlet, improves the airflow quality sucked into the buried air inlet, thereby improving the total pressure recovery coefficient of the buried air inlet and reducing the outlet distortion index.

Description

Technical Field

[0001] The present invention relates to the field of aircraft aerodynamic technology, and in particular to a buried air inlet. Background Art

[0002] A buried air inlet is an air inlet with no protruding parts and the inlet is buried in the aircraft. The buried air inlet has a small frontal area and a small radar scattering area, so its headwind resistance is small and its stealth performance is good. At the same time, the buried air inlet is integrated with the missile body / fuselage, effectively reducing the size of the aircraft, which is conducive to the placement, carrying and box-type launch of the aircraft. However, since the inlet of the buried air inlet is completely placed in the boundary layer of the missile body / fuselage, it cannot use the incoming flow ram pressure to inhale air, and only relies on the pressure gradient of the front lip perpendicular to the incoming flow direction and the vortex generated by the side edges to inhale air. Therefore, the buried air inlet will inhale a large amount of boundary layer. At the same time, the side edge vortex can easily lead to large airflow mixing losses, which makes the total pressure loss of the buried air inlet and the outlet cross-sectional flow field distortion larger.

[0003] Patent CN102249004 discloses an aircraft using a buried air inlet, which is provided with a blowing slot and a high-pressure chamber on the body for blowing away the boundary layer; Patent CN10194570 discloses a buried air inlet based on vortex discharge and an aircraft using the air inlet, which is provided with a pair of air release grooves on the side walls of the inner channel, and the vortices and low-energy flows in the inner channel are released through the air release grooves, and the side edge vortices cannot be discharged, or the side edge vortices are suppressed from entering the inner channel, thereby resulting in large distortion of the outlet flow field. Summary of the Invention

[0004] The technical problem solved by the present invention is to provide a buried air intake duct to solve the problems in the above-mentioned background technology.

[0005] The technical problem solved by the present invention is achieved by adopting the following technical solutions:

[0006] A buried air inlet comprises an air inlet (1), an air outlet (2), a side edge (3), an inner channel (4), a low-energy flow discharge port (5), a low-energy flow discharge channel (6), a front guide surface (7), a rear guide surface (8) and a vortex low-energy flow guide (9), wherein the front guide surface (7) is provided with a vortex low-energy flow guide (9), the inner channel (4) is provided behind the vortex low-energy flow guide (9), low-energy flow discharge ports (5) are symmetrically provided on both sides of the inner channel (4), the low-energy flow discharge port (5) is connected to the low-energy flow discharge channel (6), and the rear guide surface (8) is provided behind the inner channel (4).

[0007] Furthermore, the front guide surface (7) is divided into a front guide surface upstream (17) and a front guide surface downstream (18) with the inner channel inlet (16) of the inner channel (4) as a boundary, and the front guide surface upstream (17) is located in front of the front guide surface downstream (18) along the heading direction, and the vortex low-energy flow guide (9) has a tetrahedral structure, is located above the front guide surface upstream (17), and is symmetrical about the symmetric plane of the inlet;

[0008] The vortex low-energy flow guide (9) includes a discharge bottom surface (10), a diverter surface (11), two discharge side surfaces (12) and a discharge top surface (13). The discharge bottom surface (10) is in contact with the front guide surface (7). The most downstream position of the discharge bottom surface (10) is located upstream of the inner channel inlet (16). The discharge bottom surface (10) is in the shape of a triangular structure. The diverter surface (11) is an arc-shaped surface perpendicular to the front guide surface (7). Its height is equal to the boundary layer of the incoming flow. The thickness of the diverter surface (11) is located upstream of the upstream of the front guide surface (17), and the distance from the inner channel inlet (16) is 1 / 3 of the flow length of the upstream of the front guide surface (17). The highest point of the diverter surface (11) is lower than the air inlet (1). The low-energy flow entering the channel from the front lip flows through the diverter surface (11) of the vortex low-energy flow guide (9) and is divided into two paths and flows to the low-energy flow discharge port (5) respectively, and is discharged from the air inlet through the low-energy flow discharge channel (6).

[0009] Furthermore, the embedded air inlet is applied to a UAV, and the two discharge side surfaces (12) are planes perpendicular to the front guide surface (7). The discharge side surfaces (12) are symmetrical about the symmetry plane of the air inlet. The discharge side surfaces (12) can induce vortices to suppress the entry of the vortices of the side edges (3), that is, the vortices generated by the inlet side edges (3) and the low-energy flow of the boundary layer sucked in by them cannot enter the inner channel (4). Even if they enter, they can be directly discharged through the low-energy flow discharge port (5);

[0010] Furthermore, the discharge surface (13) includes an upstream plane (14) and a downstream plane (15), and the acute angle formed by the upstream plane (14) and the plane of the air inlet (1) is smaller than the acute angle formed by the downstream plane (15) and the plane of the air inlet (1), thereby effectively reducing the resistance. The upstream plane (14) is an isosceles triangle structure, and the downstream plane (15) is an isosceles trapezoid structure. The upstream plane (14) and the downstream plane (15) transition smoothly, and the downstream plane (15) transitions smoothly to the upstream of the front guide surface (17). The high-energy fluid in the mainstream area flows into the inner channel (4) through the discharge surface (13).

[0011] Furthermore, the discharge side surface (12) connects the diversion surface (11) and the low-energy flow discharge outlet (5) located on the same side. The low-energy flow discharge outlet (5) is a rounded rectangular structure. The area of ​​a single low-energy flow discharge outlet (5) is 1 / 6 of the area of ​​the inner channel inlet (16), and is symmetrically opened with respect to the symmetric plane of the air inlet. The low-energy flow discharge outlet (5) is located behind the inner channel inlet (16) along the heading direction, distributed on both sides of the inner channel inlet (16), and the distance from the inner channel inlet (16) is 1 / 40 of the flow length of the inner channel (4); two low-energy flow discharge channels (6) are respectively connected to the low-energy flow discharge outlet (5), located downstream of the low-energy flow discharge outlet (5), and are symmetrically opened with respect to the symmetric plane of the air inlet. The cross-sectional area of ​​the low-energy flow discharge channel (6) increases continuously.

[0012] Furthermore, the embedded air inlet is applied to an aircraft with stealth requirements, and the two discharge side surfaces (12) are set as multi-level planes perpendicular to the front guide surface (7) to improve the stealth performance of the aircraft; at the same time, the inlet of the rear guide surface (8) is set as a zigzag structure to meet the injection requirements.

[0013] Furthermore, the embedded air inlet is applied to an aircraft with ejection requirements, and a tail cabin (20), an engine (21) and an ejection nozzle (22) are added. The two discharge side surfaces (12) are set as arc surfaces perpendicular to the front guide surface (7). The air outlet (2) is connected to the inlet of the engine (21). The low-energy flow discharge channel (6) is connected to the tail cabin (20). The ejection nozzle (22) is provided on the tail cabin (20). The vortex low-energy flow flowing through the low-energy flow discharge channel (6) flows to the tail cabin (20). The temperature of this part of the fluid is relatively low, so as to cool the space of the tail cabin (20), and further flows through the ejection nozzle (22) and is discharged from the aircraft.

[0014] Beneficial effects: The present invention arranges a vortex low-energy flow guide on the front guide surface of the air inlet. The low-energy flow entering the channel from the front lip flows through the diverter surface of the vortex low-energy flow guide and is divided into two paths and flows to the low-energy flow discharge port respectively, and is discharged from the air inlet through the low-energy flow discharge channel; at the same time, the discharge side of the vortex low-energy flow guide can induce vortexes to inhibit the entry of side edge vortices, that is, the vortexes generated by the inlet side edges and the boundary layer low-energy flow sucked in by them cannot enter the inner channel, and even if they enter, they can be directly discharged through the low-energy flow discharge port; the high-energy fluid in the mainstream area flows into the inner channel through the discharge surface, effectively reducing the boundary layer low-energy flow flowing into the submerged air inlet, improving the airflow quality sucked into the submerged air inlet, thereby improving the total pressure recovery coefficient of the submerged air inlet and reducing the outlet distortion index. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the overall structure of a conventional UAV in a preferred embodiment of the present invention.

[0016] Figures 2 and 3This is a schematic diagram of the air intake structure of a conventional UAV in a preferred embodiment of the present invention.

[0017] Figure 4 This is a schematic diagram of the effect of applying a preferred embodiment of the present invention to a conventional drone.

[0018] Figure 5 It is a schematic diagram of the overall structure of an aircraft with stealth requirements in a preferred embodiment of the present invention.

[0019] Figures 6 and 7 This is a schematic diagram of the air inlet structure of an aircraft with stealth requirements in a preferred embodiment of the present invention.

[0020] Figure 8 The figure is a schematic diagram of the overall structure of an aircraft with ejection requirements in a preferred embodiment of the present invention.

[0021] Figures 9 and 10 The figure is a schematic diagram of the air inlet structure of an aircraft with ejection requirements in a preferred embodiment of the present invention.

[0022] Figure 11 It is a schematic diagram of the flow trajectory of the vortex low-energy flow applied to an aircraft with injection requirements in a preferred embodiment of the present invention.

[0023] Illustration:

[0024] Figure 4 In the figure, a is the high-energy flow in the mainstream area, b is the side edge entrainment vortex, c is the device-induced vortex, d is the low-energy flow, and e is the incoming flow;

[0025] Figure 11 In the figure, m is the flow discharged from the ejector nozzle, and n is the flow of low-energy flow in the tail cabin. DETAILED DESCRIPTION

[0026] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below with reference to specific illustrations. Example

[0027] See also Figures 1 to 4The embedded air inlet shown is applied to a UAV, comprising an air inlet (1), an air outlet (2), two side edges (3), an inner channel (4), two low-energy flow discharge ports (5), two low-energy flow discharge channels (6), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12), a discharge top surface (13), an upstream plane (14), a downstream plane (15), an inner channel inlet (16), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12), a discharge top surface (13), an upstream plane (14), a downstream plane (15), an inner channel inlet (16), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12), a discharge top surface (13), a front guide surface (14), a rear guide surface ... front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a front guide surface (7), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a front guide surface (10), a front guide surface (10), a front guide surface (11), a front guide surface (11), a front guide surface (11 An upstream guide surface (17), a downstream front guide surface (18) and a drone (19), wherein the air inlet (1) is embedded in the drone (19), and the front guide surface (7) is divided into an upstream front guide surface (17) and a downstream front guide surface (18) with the inner channel inlet (16) as the boundary, and the upstream front guide surface (17) is located in front of the downstream front guide surface (18) along the heading direction, and the vortex low-energy flow guide (9) is a tetrahedron-like structure, located above the upstream front guide surface (17), and symmetrical about the symmetric plane of the air inlet;

[0028] The vortex low-energy flow guide (9) includes a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12) and a discharge top surface (13). The discharge bottom surface (10) is in contact with the front guide surface (7). The most downstream position of the discharge bottom surface (10) is located upstream of the inner channel inlet (16). The discharge bottom surface (10) is in the shape of a triangular structure. The diversion surface (11) is an arc-shaped surface perpendicular to the front guide surface (7). Its height is the thickness of the incoming flow boundary layer. The surface (11) is located upstream of the upstream of the front guide surface (17), and the distance from the inner channel inlet (16) is 1 / 3 of the flow length of the upstream of the front guide surface (17). The highest point of the diverter surface (11) is lower than the air inlet (1). The low-energy flow entering the channel from the front lip flows through the diverter surface (11) of the vortex low-energy flow guide (9) and is divided into two paths and flows to the low-energy flow discharge port (5) respectively, and is discharged from the air inlet through the low-energy flow discharge channel (6); the two discharge side surfaces (12) are vertical. In the plane of the front guide surface (7), the discharge side surface (12) is symmetrical with respect to the symmetric plane of the air inlet. The discharge side surface (12) can induce vortices to suppress the entry of the vortices of the side edge (3), that is, the vortices generated by the inlet side edge (3) and the low-energy flow of the boundary layer sucked in by them cannot enter the inner channel (4). Even if they enter, they can be directly discharged through the low-energy flow discharge port (5); the discharge upper surface (13) includes an upstream plane (14) and a downstream plane (15). The acute angle formed by the upstream plane (14) and the plane of the air inlet (1) is smaller than the acute angle formed by the downstream plane (15) and the plane of the air inlet (1), thereby effectively reducing the resistance. The upstream plane (14) is an isosceles triangle structure, and the downstream plane (15) is an isosceles trapezoid structure. The upstream plane (14) and the downstream plane (15) are smoothly transitioned, and the downstream plane (15) and the upstream of the front guide surface (17) are smoothly transitioned. The high-energy fluid in the mainstream area flows into the inner channel (4) through the discharge upper surface (13).

[0029] The discharge side surface (12) connects the diversion surface (11) and the low-energy flow discharge outlet (5) located on the same side. The low-energy flow discharge outlet (5) is a rounded rectangular structure. The area of ​​a single low-energy flow discharge outlet (5) is 1 / 6 of the area of ​​the inner channel inlet (16) and is symmetrically opened with respect to the symmetric plane of the air inlet. The low-energy flow discharge outlet (5) is located behind the inner channel inlet (16) along the heading direction and is distributed on both sides of the inner channel inlet (16). The distance from the inner channel inlet (16) is 1 / 40 of the flow length of the inner channel (4). Two low-energy flow discharge channels (6) are respectively connected to the low-energy flow discharge outlet (5), are located downstream of the low-energy flow discharge outlet (5), and are symmetrically opened with respect to the symmetric plane of the air inlet. The cross-sectional area of ​​the low-energy flow discharge channel (6) increases continuously. Example

[0030] See also Figures 5-7 The embedded air inlet shown is applied to an aircraft with stealth requirements, comprising an air inlet (1), an air outlet (2), two side edges (3), an inner channel (4), two low-energy flow discharge ports (5), two low-energy flow discharge channels (6), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a discharge bottom surface (10), a diverter surface (11), a discharge side surface (12), a discharge top surface (13), an upstream plane (14), a downstream plane ( 15), an inner channel inlet (16), an upstream of a front guide surface (17), a downstream of a front guide surface (18) and an aircraft (19), the air inlet (1) is embedded in the aircraft (19), the front guide surface (7) is divided into an upstream of a front guide surface (17) and a downstream of a front guide surface (18) with the inner channel inlet (16) as a boundary, the upstream of the front guide surface (17) is located in front of the downstream of the front guide surface (18) along the heading direction, and based on the ejection requirement, the inlet of the rear guide surface (8) is set to a zigzag structure;

[0031] The vortex low-energy flow guide (9) is in a tetrahedral shape and is located above the upstream of the front guide surface (17) and is symmetrical about the symmetry plane of the air inlet. The vortex low-energy flow guide (9) includes a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12) and a discharge top surface (13). The discharge bottom surface (10) is in contact with the front guide surface (7). The most downstream position of the discharge bottom surface (10) is located upstream of the inner channel inlet (16). The discharge bottom surface (10) is in a triangular shape. The diversion surface (11) is perpendicular to the The front guide surface (7) is an arc-shaped surface, and its height is the thickness of the incoming flow boundary layer. The diverter surface (11) is located upstream of the front guide surface upstream (17), and the distance from the inner channel inlet (16) is 1 / 3 of the flow length of the front guide surface upstream (17). The highest point of the diverter surface (11) is lower than the air inlet (1). The low-energy flow entering the channel from the front lip flows through the diverter surface (11) of the vortex low-energy flow guide (9) and is divided into two paths and flows to the low-energy flow discharge port (5) respectively, and is discharged from the air inlet through the low-energy flow discharge channel (6). In order to improve the stealth performance of the aircraft, the two discharge side surfaces (12) are set as multi-level planes perpendicular to the leading guide surface (7). The discharge side surfaces (12) are symmetrical about the symmetric plane of the air inlet. The discharge side surfaces (12) can induce vortices to suppress the entry of the vortex of the side edge (3), that is, the vortex generated by the inlet side edge (3) and the boundary layer low-energy flow sucked in by it cannot enter the inner channel (4). Even if it enters, it can be directly discharged through the low-energy flow discharge port (5); the discharge surface (13) includes an upstream plane (14) and a downstream plane (15), the acute angle formed by the upstream plane (14) and the plane of the air inlet (1) is smaller than the acute angle formed by the downstream plane (15) and the plane of the air inlet (1), thereby effectively reducing the resistance. The upstream plane (14) is an isosceles triangle structure, and the downstream plane (15) is an isosceles trapezoid structure. The upstream plane (14) and the downstream plane (15) transition smoothly, and the downstream plane (15) transitions smoothly with the upstream of the front guide surface (17). The high-energy fluid in the mainstream area flows into the inner channel (4) through the discharge surface (13).

[0032] The discharge side surface (12) connects the diversion surface (11) and the low-energy flow discharge outlet (5) located on the same side. The low-energy flow discharge outlet (5) is a rounded rectangular structure. The area of ​​a single low-energy flow discharge outlet (5) is 1 / 6 of the area of ​​the inner channel inlet (16) and is symmetrically opened with respect to the symmetric plane of the air inlet. The low-energy flow discharge outlet (5) is located behind the inner channel inlet (16) along the heading direction and is distributed on both sides of the inner channel inlet (16). The distance from the inner channel inlet (16) is 1 / 40 of the flow length of the inner channel (4). Two low-energy flow discharge channels (6) are respectively connected to the low-energy flow discharge outlet (5) and are located downstream of the low-energy flow discharge outlet (5). They are symmetrically opened with respect to the symmetric plane of the air inlet. The cross-sectional area of ​​the low-energy flow discharge channel (6) gradually increases. Example

[0033] See also Figures 8-11The embedded air inlet shown is applied to an aircraft with ejection requirements, comprising an air inlet (1), an air outlet (2), two side edges (3), an inner channel (4), two low-energy flow discharge ports (5), two low-energy flow discharge channels (6), a front guide surface (7), a rear guide surface (8), a vortex low-energy flow guide (9), a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12), a discharge top surface (13), an upstream plane (14), a downstream plane (15), an inner channel inlet (16), and a front guide surface. The front guide surface (17) is connected to the upstream portion of the front guide surface (17), the downstream portion of the front guide surface (18), the aircraft fuselage (19), the tail cabin (20), the engine (21) and the ejector nozzle (22), the air inlet (1) is embedded in the aircraft fuselage (19), the air outlet (2) is connected to the inlet of the engine (21), the front guide surface (7) is divided into the upstream portion of the front guide surface (17) and the downstream portion of the front guide surface (18) with the inlet of the inner channel (16) as the boundary, the upstream portion of the front guide surface (17) is located in front of the downstream portion of the front guide surface (18) along the course direction, and the low-energy flow discharge channel (6) leads to the tail cabin (20);

[0034] The vortex low-energy flow guide (9) is in a tetrahedral shape and is located above the upstream of the leading guide surface (17). It is symmetrical about the symmetry plane of the air inlet. The vortex low-energy flow guide (9) includes a discharge bottom surface (10), a diversion surface (11), two discharge side surfaces (12) and a discharge top surface (13). The discharge bottom surface (10) is in contact with the leading guide surface (7). The most downstream position of the discharge bottom surface (10) is located upstream of the inner channel inlet (16). The discharge bottom surface (10) is in a triangular shape. The diversion surface (11) is perpendicular to the leading guide surface. The flow surface (7) is an arc-shaped surface, and its height is the thickness of the incoming flow boundary layer. The splitter surface (11) is located upstream of the front guide surface of the air inlet, and the distance from the inner channel inlet (16) is 1 / 3 of the flow length of the upstream (17) of the front guide surface. The highest point of the splitter surface (11) is lower than the air inlet (1). The low-energy flow entering the channel from the front lip flows through the splitter surface (11) of the vortex low-energy flow guide (9) and is divided into two paths and flows to the low-energy flow discharge port (5) respectively, and then discharges from the air inlet through the low-energy flow discharge channel (6) and flows to the tail cabin (20); The two discharge side surfaces (12) are arc-shaped surfaces perpendicular to the front guide surface (7). The discharge side surfaces (12) are symmetrical about the symmetric plane of the air inlet. The discharge side surfaces (12) can induce vortices to suppress the entry of the vortices of the side edges (3). That is, the vortices generated by the inlet side edges (3) and the boundary layer low-energy flows sucked therein cannot enter the inner channel (4). Even if they enter, they can be directly discharged through the low-energy flow discharge port (5) and flow to the tail cabin (20) through the low-energy flow discharge channel (6); the discharge upper surface (13) includes an upstream plane (14) and a lower plane (15). The upstream plane (15) and the acute angle formed by the upstream plane (14) and the inlet (1) plane are smaller than the acute angle formed by the downstream plane (15) and the inlet (1) plane, thereby effectively reducing the resistance. The upstream plane (14) is an isosceles triangle structure, and the downstream plane (15) is an isosceles trapezoid structure. The upstream plane (14) and the downstream plane (15) are smoothly transitioned, and the downstream plane (15) and the upstream of the front guide surface (17) are smoothly transitioned. The high-energy fluid in the mainstream area flows into the inner channel (4) through the discharge surface (13);

[0035] The discharge side surface (12) connects the diversion surface (11) and the low-energy flow discharge outlet (5) located on the same side. The low-energy flow discharge outlet (5) is a rounded rectangle. The area of ​​a single low-energy flow discharge outlet (5) is 1 / 5 of the area of ​​the inner channel inlet (16). The low-energy flow discharge outlet (5) is symmetrically opened about the symmetric plane of the air inlet. The low-energy flow discharge outlet (5) is located behind the inner channel inlet (16) along the heading direction and is distributed on both sides of the inner channel inlet (16). The distance from the inner channel inlet (16) is 1 / 40 of the flow length of the inner channel (4). The low-energy flow discharge channels (6) are respectively connected to the low-energy flow discharge port (5), are located downstream of the low-energy flow discharge port (5), and are symmetrically opened with respect to the symmetric plane of the air inlet. The cross-sectional area of ​​the low-energy flow discharge channel (6) gradually increases. The vortex low-energy flow flowing through the low-energy flow discharge channel (6) flows toward the tail cabin (20). The temperature of this part of the fluid is relatively low, and the space of the tail cabin (20) can be cooled. The fluid further flows through the ejector nozzle (22) and is discharged from the aircraft, thereby also playing the role of increasing thrust and reducing infrared radiation.

[0036] The simulation results of the above-mentioned embedded inlet show that, compared with the conventional embedded inlet, under the conditions of the incoming flow Mach number of 0.60, the incoming flow angle of attack of 2 degrees, and the inlet outlet Mach number of 0.32, the inlet total pressure recovery coefficient is increased from 0.92 to 0.945, and the comprehensive distortion index is reduced from 2.75% to 2.1%. Based on practical experience, when the inlet total pressure recovery coefficient increases by 1%, the aircraft speed increases by 1% under the same other conditions. The good inlet performance and reduced fuel consumption can effectively improve the aircraft's performance. Range; Based on practical experience, for every 1% increase in the total pressure recovery coefficient of the inlet, the aircraft range increases by 2% on the basis of the same fuel volume. On the basis of the same range, less fuel can be loaded, effectively reducing the weight of the aircraft; at the same time, the vortex low-energy flow deflector is set on the front guide surface, which can effectively block the engine inlet fan blades and enhance the stealth effect of the power unit; the exhaust gas of the inlet is discharged by the ejector nozzle, thereby realizing the cooling of the engine compartment, while playing the role of increasing thrust and reducing infrared radiation, further improving the stealth performance of the aircraft.

Claims

1. A buried air inlet, comprising an air inlet (1), an air outlet (2), a side edge (3), an inner channel (4), a low-energy flow discharge port (5), a low-energy flow discharge channel (6), a front guide surface (7), a rear guide surface (8) and a vortex low-energy flow guide (9), characterized in that: A vortex low-energy flow guide (9) is provided on the front guide surface (7), an inner channel (4) is provided behind the vortex low-energy flow guide (9), low-energy flow discharge ports (5) are symmetrically provided on both sides of the inlet of the inner channel (4), the low-energy flow discharge ports (5) are connected to the low-energy flow discharge channel (6), and a rear guide surface (8) is provided behind the inner channel (4); The leading guide surface (7) is divided into an upstream leading guide surface (17) and a downstream leading guide surface (18) with the inner channel inlet (16) of the inner channel (4) as a boundary. The upstream leading guide surface (17) is located in front of the downstream leading guide surface (18) along the heading direction. The vortex low-energy flow guide (9) has a tetrahedral structure, is located above the upstream leading guide surface (17), and is symmetrical about the symmetric plane of the inlet. The vortex low-energy flow guide (9) includes a discharge bottom surface (10), a diverter surface (11), two discharge side surfaces (12) and a discharge top surface (13), wherein the discharge bottom surface (10) is in contact with the front guide surface (7), the most downstream position of the discharge bottom surface (10) is located upstream of the inner channel inlet (16), the diverter surface (11) is located upstream of the front guide surface upstream (17), and the highest point of the diverter surface (11) is lower than the air inlet (1). The low-energy flow entering the channel from the front lip flows through the diverter surface (11) of the vortex low-energy flow guide (9) and is divided into two paths and flows to the low-energy flow discharge port (5) respectively, and is discharged from the air inlet through the low-energy flow discharge channel (6).

2. The embedded air intake according to claim 1, characterized in that: The discharge bottom surface (10) is in the shape of a triangular structure.

3. The embedded air intake according to claim 1, characterized in that: The distance between the diverter surface (11) and the inner channel inlet (16) is 1 / 3 of the flow length of the upstream (17) of the front guide surface.

4. The embedded air intake according to claim 1, characterized in that: The discharge surface (13) includes an upstream plane (14) and a downstream plane (15), and the acute angle formed by the upstream plane (14) and the plane of the air inlet (1) is smaller than the acute angle formed by the downstream plane (15) and the plane of the air inlet (1).

5. The embedded air intake according to claim 1, characterized in that: The discharge side surface (12) connects the diversion surface (11) and the low-energy flow discharge port (5) located on the same side.

6. The embedded air intake according to claim 1, characterized in that: The low-energy flow discharge outlet (5) is located behind the inner channel inlet (16) along the course direction and is distributed on both sides of the inner channel inlet (16).

7. The embedded air intake according to claim 1, characterized in that: The cross-sectional area of ​​the low-energy flow discharge channel (6) increases continuously.

8. The embedded air intake according to any one of claims 1 to 7, characterized in that: The embedded air inlet is used in a UAV, and the two discharge side surfaces (12) are planes perpendicular to the front guide surface (7).

9. The embedded air intake according to any one of claims 1 to 7, characterized in that: The embedded air inlet is applied to an aircraft with stealth requirements, and the two discharge side surfaces (12) are arranged as multi-level planes perpendicular to the front guide surface (7).

10. The embedded air intake according to claim 9, characterized in that: The inlet of the rear guide surface (8) is configured as a sawtooth structure.

11. The embedded air intake according to any one of claims 1 to 7, characterized in that: The embedded air inlet is applied to an aircraft with ejection requirements, wherein a tail cabin (20), an engine (21) and an ejection nozzle (22) are added, and two discharge side surfaces (12) are set as arc surfaces perpendicular to the front guide surface (7), the air outlet (2) is connected to the inlet of the engine (21), the low-energy flow discharge channel (6) is connected to the tail cabin (20), and an ejection nozzle (22) is provided on the tail cabin (20), and the vortex low-energy flow flowing through the low-energy flow discharge channel (6) flows to the tail cabin (20) to cool the space of the tail cabin (20), and further flows through the ejection nozzle (22) to be discharged from the aircraft.

Images