阅读说明：本技术 一种埋入式隐身外形进气道 (Embedded type invisible air inlet channel ) 是由 郝璐 郭晓铛 刘雪松 张亚坤 于 2021-11-18 设计创作，主要内容包括：本发明属于飞行器进气道领域,具体涉及一种埋入式隐身外形进气道。该进气道包括唇口、通道进口段和通道出口段,唇口外形为类多边形唇口外形,通道进口段为低散射外形腔体。应用该埋入式隐身外形进气道,可有效降低进气道雷达散射量截面积,同时保持高总压恢复系数和小的流场畸变,实现隐身/流场一体化设计,从外形上解决进气道前向雷达隐身问题,大幅提升飞行器隐身性能。(The invention belongs to the field of aircraft air inlet channels, and particularly relates to an embedded invisible air inlet channel. The inlet channel comprises a lip, a channel inlet section and a channel outlet section, wherein the lip is in a polygon-like lip shape, and the channel inlet section is a low-scattering shape cavity. The buried stealth appearance air inlet channel is applied, the radar scattering amount sectional area of the air inlet channel can be effectively reduced, meanwhile, high total pressure recovery coefficient and small flow field distortion are kept, stealth/flow field integrated design is achieved, the problem that the air inlet channel is hidden towards a radar is solved in appearance, and stealth performance of an aircraft is greatly improved.)

1. The utility model provides a stealthy appearance intake duct of formula of buryying which characterized in that: the air inlet channel comprises an air inlet channel lip (1), a channel inlet section (2) and a channel outlet section (4), wherein the channel inlet section (2) and the channel outlet section (4) use an air inlet channel minimum section (3) as an interface, and the air inlet channel adopts scattering characteristics and flow field characteristics to be optimized.

2. An embedded stealthy profile inlet according to claim 1, characterized in that the inlet lip (1) cross-sectional profile is one of a goose egg-shaped, a hexagon-like, and a triangle-like cross-section.

3. An embedded stealth profile inlet according to claim 2, characterized in that the inlet lip (1) is parameterised in shape by S₁: lip leading edge central arc segment S₂: lip front edge and side transition arc segment S₃: transition arc section of lip rear edge and side edge, S₄: lip trailing edge central arc, L₁: lip front edge straight line segment, L₂: straight line segment at lip side, L₃: lip trailing edge straight line segment, α: lip leading edge sweep angle, β: included angle between lip side edge and lip central axisγ: a lip trailing edge sweep angle; performing expression, wherein:

S₁simultaneously with L₁The arc length is 0-500 mm;

S₂simultaneously with L₁、L₂Tangent, and the arc length range is 0-1000 mm;

S₃simultaneously with L₂、L₃Tangent, and the arc length range is 0-1000 mm;

S₄simultaneously with L₃The y axis is tangent, and the arc length range is 0-1000 mm;

L₁the length range is 0-1000 mm determined by the butt joint width of the air inlet channel and the surface of the aircraft;

L₂the length range is 0-2500 mm, and the length range is determined by a longitudinal control line of an outlet section channel, the height of an aircraft and the installation position of an air inlet channel;

L₃: the length range is 0-1000 mm determined by the butt joint width of the air inlet channel and the surface of the aircraft;

α according to L₁、L₂The length range is determined, and the angle range is 0-80 degrees;

beta according to L₁、L₂、L₃The length range is determined, and the angle range is 0-80 degrees;

gamma according to L₂、L₃The length range is determined, and the angle range is 0-80 degrees;

the shape of the lip of the air inlet channel is constrained by the total length l of the lip and the total width h of the lip, and S₁、S₂、S₃、S₄、L₁、L₂、L₃The parameters alpha, beta and gamma satisfy L₁sinα+L₂cosβ+L₃L and L are sin gamma ≤₁cosα+L₂sinβ+L₃cosγ≤h。

4. An embedded stealth profile air inlet according to claim 1, characterized in that the minimum cross-section (3) of the air inlet is circular, elliptical, square, rectangular or triangular, the minimum cross-section is a fixed profile constraint, and the area and shape of the minimum cross-section are determined by the engine performance requirements.

5. An embedded stealth profile inlet according to claim 1, characterized in that said channel inlet section (2) is of parametric stealth profile design; wherein, the shape of the channel inlet section (2) is restricted by the minimum cross section (3) of the inlet channel and the shape of the lip (1) and uses CL₁: longitudinal section upper boundary line, CL, of the channel inlet section₂: lower boundary line of longitudinal section of the channel inlet section, in which CL₁、CL₂Are all tangent to the aircraft surface; CL₁Respectively aligning the two parts of the straight line segment and the rounding curve, and fusing and transiting the rounding curve and the surface of the aircraft; CL₂In the form of a second or third order curve, the end of which merges with the aircraft surface.

6. An embedded stealth profile inlet according to claim 1, characterized in that the profile of the channel outlet section (4) is designed to meet the requirements of the power system without developing a stealth profile.

7. The buried stealth profile air inlet according to any one of claims 1 to 6, designed according to the following steps:

(1) carrying out parametric modeling on the shape of the air inlet;

(2) carrying out gridding treatment on the air inlet channel model;

(3) calculating and analyzing a scattered field of the air inlet channel;

(4) analyzing the air inlet passage internal and external flow through joint calculation;

(5) and (4) carrying out comprehensive optimization design on the stealth/flow field.

8. The embedded stealth profile air inlet according to claim 7, wherein the comprehensive optimization design analysis method for scattering characteristics and flow field characteristics comprises the following specific steps:

the first step is as follows: parametric modeling of air inlet duct shape

According to project requirements and constraint conditions, the minimum cross section (3) and the lip (1) area of the air inlet are swept, and a line of the minimum cross section (3) of the air inlet is generatedAnd the basic contour line of the lip (1), set S₁、S₂、S₃、S₄、L₁、L₂、L₃Alpha, beta, gamma parameters; according to the curve of the lip (1) and the minimum section line, generating a longitudinal line of the inlet section of the channel, and setting CL₁、CL₂A parameter; sweeping the outlet section (4) of the air inlet channel to generate a longitudinal line and an outlet section line of the outlet section (4) of the channel; generating an inner surface curved surface of the air inlet by a curve passing network to form an air inlet appearance model;

the second step is that: air inlet channel model gridding treatment

Making section lines on the air inlet passage outline model, generating grid nodes with the density meeting the requirements on each section line, and outputting surface grid files required by radar scattering cross section (RCS) analysis and flow field analysis;

the third step: inlet duct scattered field computational analysis

Carrying out scattering characteristic simulation calculation on the generated surface grid file, and carrying out calculation on a lip edge diffraction field by applying methods such as geometric diffraction, physical diffraction, equivalent electromagnetic flow and the like; calculating the scattering characteristics of the air inlet channel by using methods such as a ray tracing method, a full wave algorithm and the like, and outputting an air inlet RCS;

the fourth step: inlet and outlet flow combined analysis

And carrying out flow field characteristic simulation calculation on the generated surface grid file. When the internal and external flow joint calculation is carried out, a numerical calculation method based on an N-S equation and a proper turbulence model is adopted, and flow field characteristic information such as total pressure recovery coefficient, flow field distortion and the like is output;

the fifth step: stealth/flow field comprehensive optimization design and verification

The method comprises the steps of taking shape parameters of a lip (1) and a channel inlet section (2) as design variables, taking flow field characteristics meeting the working requirements of an engine as constraint conditions, developing stealth/flow field comprehensive optimization design, adopting an optimization method based on a Kriging approximate model and a genetic algorithm to solve and optimize, obtaining a stealth shape meeting total pressure recovery coefficients and flow field distortion indexes, and verifying the stealth performance of an air inlet channel through RCS simulation or RCS test.

Technical Field

The invention belongs to the technical field of aircraft stealth, and particularly relates to an embedded stealth appearance air inlet channel based on stealth/flow field comprehensive optimization design.

Background

The air inlet channel is one of the most main radar scattering sources in the forward direction of the aircraft, the stealth performance and the battlefield survival rate of the aircraft are influenced, and stealth measures are required to reduce the RCS of the aircraft.

The patent ZL201911154550.8 discloses a cavity structure scheme for applying wave-absorbing materials in a partition mode based on cavity electromagnetic scattering characteristics; the patent CN201710889740.9 discloses a high-temperature air inlet with heat-insulating stealth and infrared stealth multifunctional layers and a preparation method thereof, wherein the high-temperature air inlet consists of a wave-transmitting layer, a heat-insulating stealth layer, an electromagnetic shielding layer and a low-emissivity coating; the patent of an electromagnetic stealth sleeve structure for the inner wall surface of an air inlet (application number: 202010047064.2) discloses an electromagnetic stealth sleeve structure in which a wave-absorbing coating or a PMI foam layer is filled in a gap between a wave-transmitting inner wall surface and a main structure of the air inlet. The defect of the patent is that the stealth function of the air inlet channel is realized by applying stealth materials inside the air inlet channel, so that the weight increment and the cost increase are brought.

Disclosure of Invention

The invention aims to overcome the defects in the prior art, provides an embedded invisible air inlet, and solves the problems of high cost and large weight increment caused by application of invisible materials in the air inlet.

The embedded stealth appearance air inlet disclosed by the invention has the advantages that on the premise of meeting the total pressure recovery coefficient and the flow field distortion index, the stealth performance of the air inlet is realized through parameterized stealth appearance optimization design, and the additional weight increase and cost caused by application of stealth materials are avoided.

The technical scheme of the invention is as follows:

an embedded hidden-profile air inlet is provided, wherein the air inlet is divided into a lip, an inlet channel section and an outlet channel section, and the inlet channel section and the outlet channel section use the minimum cross section of the air inlet as an interface. The air inlet channel adopts a comprehensive optimization design of scattering characteristics and flow field characteristics.

The lip of the air inlet adopts a parameterized stealth appearance design and has a low scattering appearance characteristic. The cross section of the lip mouth can be in a goose egg shape, a hexagon-like shape, a triangle-like shape and other unconventional special-shaped cross sections.

When the shape of the inlet lip is parameterized, S is used₁、S₂、S₃、S₄、L₁、L₂、L₃And alpha, beta, gamma and the like. S₁: lip leading edge central arc segment S₂: lip front edge and side transition arc segment S₃: transition arc section of lip rear edge and side edge, S₄: lip trailing edge central arc, L₁: lip front edge straight line segment, L₂: straight line segment at lip side, L₃: lip trailing edge straight line segment, α: lip leading edge sweep angle, β: lip side and lip central axis contained angle, gamma: a lip trailing edge sweep angle; wherein S is₁Simultaneously with L₁The arc length is 0-500 mm; s₂Simultaneously with L₁、L₂Tangent, and the arc length range is 0-1000 mm; s₃Simultaneously with L₂、L₃Tangent, and the arc length range is 0-1000 mm; s₄Simultaneously with L₃The y axis is tangent, and the arc length range is 0-1000 mm; l is₁The length range is 0-1000 mm determined by the butt joint width of the air inlet channel and the surface of the aircraft; l is₂The length range is 0-2500 mm, and the length range is determined by a longitudinal control line of an outlet section channel, the height of an aircraft and the installation position of an air inlet channel; l is₃: the length range is 0-1000 mm determined by the butt joint width of the air inlet channel and the surface of the aircraft; α according to L₁、L₂The length range is determined, and the angle range is 0-80 degrees; beta according to L₁、L₂、L₃The length range is determined, and the angle range is 0-80 degrees; gamma according to L₂、L₃The length range is determined, and the angle range is 0-80 degrees.

The shape of the lip of the air inlet channel is constrained by the total length l of the lip and the total width h of the lip, and S₁、S₂、S₃、S₄、L₁、L₂、L₃The parameters alpha, beta and gamma satisfy L₁sinα+L₂cosβ+L₃L and L are sin gamma ≤₁cosα+L₂sinβ+L₃cosγ≤h。

The minimum cross section of the air inlet channel can be in the shape of a circle, an ellipse, a square, a rectangle, a triangle and the like, the minimum cross section is constrained by a fixed shape, and the area and the shape of the minimum cross section are determined by the performance requirement of the engine.

The inlet section of the air inlet channel adopts a parameterized stealth appearance design. Wherein the shape of the inlet section of the channel is restricted by the minimum interface of the inlet channel and the shape of the lip, and is usedCL₁: longitudinal section upper boundary line, CL, of the channel inlet section₂: the lower boundary line of the longitudinal section of the channel inlet section is expressed by equal parameters. Wherein, CL₁、CL₂Are all tangent to the aircraft surface; CL₁Respectively aligning the two parts of the straight line segment and the rounding curve, and fusing and transiting the rounding curve and the surface of the aircraft; CL₂In the form of a second or third order curve, the end of which merges with the aircraft surface.

The typical cross section shape of the outlet section of the channel of the air inlet channel and the appearance characteristic of the outlet section are designed to meet the requirement of a power system, and the invisible appearance design is not carried out.

The comprehensive optimization design of the scattering characteristic and the flow field characteristic is analyzed according to the following steps:

(1) carrying out parametric modeling on the shape of the air inlet;

(2) carrying out gridding treatment on the air inlet channel model;

(3) calculating and analyzing a scattered field of the air inlet channel;

(4) analyzing the air inlet passage internal and external flow through joint calculation;

(5) and (4) carrying out comprehensive optimization design on the stealth/flow field.

The comprehensive optimization design analysis method for the scattering characteristics and the flow field characteristics of the air inlet channel comprises the following specific steps of:

the first step is as follows: parametric modeling of air inlet duct shape

According to project requirements and constraint conditions, the minimum cross section and the lip area of the air inlet channel are swept, a minimum cross section line and a basic lip contour line of the air inlet channel are generated, and S is set₁、S₂、S₃、S₄、L₁、L₂、L₃Parameters such as alpha, beta, gamma and the like; generating a longitudinal line of the inlet section of the channel according to the lip curve and the minimum section line, and setting CL₁、CL₂The like; and (4) sweeping the outlet section of the air inlet channel to generate a longitudinal line and an outlet section line of the outlet section of the channel. And generating the curved surface of the inner surface of the air inlet by the curve passing network to form an air inlet appearance model.

The second step is that: air inlet channel model gridding treatment

And (3) making section lines on the air inlet channel shape model, generating grid nodes with the density meeting the requirements on each section line, and outputting surface grid files required by radar scattering cross section (RCS) analysis and flow field analysis.

The third step: inlet duct scattered field computational analysis

And carrying out scattering characteristic simulation calculation on the generated surface grid file. The lip edge diffraction field can be calculated by applying geometric diffraction, physical diffraction, equivalent electromagnetic flow and other methods; the scattering characteristics of the air inlet channel can be calculated by methods such as ray tracing, full wave algorithm and the like, and the RCS of the air inlet channel is output.

The fourth step: inlet and outlet flow combined analysis

And carrying out flow field characteristic simulation calculation on the generated surface grid file. And in the process of internal and external flow joint calculation, a numerical calculation method based on an N-S equation and a proper turbulence model is adopted, and flow field characteristic information such as total pressure recovery coefficient, flow field distortion and the like is output.

The fifth step: stealth/flow field comprehensive optimization design

The method comprises the steps of taking shape parameters of a lip and a channel inlet section as design variables, taking flow field characteristics meeting working requirements of an engine as constraint conditions, developing comprehensive stealth/flow field optimization design, adopting an optimization method based on a Kriging approximate model and a genetic algorithm to solve and optimize, obtaining a stealth shape meeting total pressure recovery coefficient and flow field distortion index, and verifying stealth performance of an air inlet channel through RCS simulation or RCS test.

Compared with the prior art, the invention has the beneficial effects that:

the invention provides an embedded invisible shape air inlet, which deviates radar scattering echoes from a key threat direction through the shape parameterization design of an air inlet lip and a channel inlet section, realizes the forward RCS reduction of the air inlet, realizes the design of the channel outlet section of the air inlet to meet the requirements of a power system, and realizes high total pressure recovery coefficient and low flow field distortion index. The design method disclosed by the invention is suitable for the design of stealth appearance schemes of various embedded air inlets, and can achieve the beneficial effects of reducing forward radar echo and avoiding structure weight increase and cost increase under the condition of meeting the working requirements of an engine.

Drawings

FIG. 1 is a typical buried stealth profile air intake model;

FIG. 2 is a graphical depiction of an embedded inlet lip profile parameterization;

FIG. 3 is a graphical depiction of the inlet section profile of an embedded inlet channel.

FIG. 4 is a typical goose egg-shaped lip port stealth profile;

FIG. 5 is a typical pseudo-hexagonal lip port stealth profile;

FIG. 6 is a hidden shape of a typical triangular-like lip inlet;

1. an inlet lip; 2. an inlet section of the inlet channel; 3. minimum cross section of air inlet channel; 4. and an outlet section of the air inlet channel.

Detailed Description

The invention is further described with reference to the following figures and specific embodiments.

Example 1

The first step is as follows: parametric modeling of air inlet duct shape

According to project requirements and constraint conditions, sweeping the minimum cross section 3 and lip 1 areas of the air inlet, generating the minimum cross section 3 line and lip 1 basic contour line of the air inlet, and setting S₁、S₂、S₃、S₄、L₁、L₂、L₃Alpha, beta, gamma and other parameters, wherein alpha and gamma are 20 DEG, and S₁、S₂、S₃、S₄All are tangent fillets. The shape of the inlet lip 1 is constrained by the total length l of the lip 1 and the total width h of the lip 1, wherein l is 450mm, and h is 147mm, so that the shape of the quasi-hexagonal lip 1 is obtained; generating a longitudinal line of a channel inlet section 2 according to a curve of a lip 1 and a line of a minimum section 3, and setting CL₁、CL₂The like; and (4) sweeping the outlet section 4 of the air inlet channel to generate a longitudinal line and an outlet section line of the outlet section 4 of the channel. And generating a curved surface of the inner surface of the air inlet by the curve passing network to form a model of the shape of the air inlet with the quasi-hexagonal lip 1.

The second step is that: air inlet channel model gridding treatment

And (3) making section lines on the shape model of the air inlet, carrying out equidistant section point taking on the air inlet at intervals of 10mm from the edge of 1 lip of the air inlet, generating grid nodes with the density meeting the requirements on each section line, and outputting a surface grid file required by radar scattering cross section (RCS) analysis and flow field analysis.

The third step: inlet duct scattered field computational analysis

And carrying out scattering characteristic simulation calculation on the generated surface grid file. Calculating the lip edge diffraction field by using a physical diffraction method; and (4) applying a full wave algorithm method to the scattering characteristics of the air inlet channel to carry out calculation and outputting the RCS of the air inlet channel.

The fourth step: inlet and outlet flow combined analysis

And carrying out flow field characteristic simulation calculation on the generated surface grid file. And in the process of internal and external flow joint calculation, a numerical calculation method based on an N-S equation and a proper turbulence model is adopted, and flow field characteristic information such as total pressure recovery coefficient, flow field distortion and the like is output.

The fifth step: stealth/flow field comprehensive optimization design and verification

And (3) taking the shape parameters of the lip 1 and the channel inlet section 2 as design variables, taking the flow field characteristics meeting the working requirements of the engine as constraint conditions, developing the stealth/flow field comprehensive optimization design, and solving and optimizing by adopting an optimization method based on a Kriging approximate model and a genetic algorithm to obtain the quasi-hexagonal lip 1 stealth shape air inlet channel. Through flow field characteristic analysis, the total pressure recovery coefficient of the quasi-hexagonal lip 1 air inlet channel in the cruising state of the aircraft is 0.95-0.97, the flow field distortion is small, and the quasi-hexagonal lip 1 air inlet channel has good pneumatic performance; through an RCS test of an air inlet channel model, the mean value of forward RCS of S wave band of the profile air inlet channel is lower than-18 dBsm, and the mean value of forward RCS of X wave band is lower than-22 dBsm.

Example 2

The first step is as follows: parametric modeling of air inlet duct shape

According to project requirements and constraint conditions, sweeping the minimum cross section 3 and lip 1 areas of the air inlet, generating the minimum cross section 3 line and lip 1 basic contour line of the air inlet, and setting S₁、S₂、S₃、S₄、L₁、L₂、L₃Alpha, beta, gamma and other parameters, wherein alpha is 75 degrees, gamma is 20 degrees, and S is₁、S₂、S₄Are all tangent fillets，L₂、S₃Beta is 0, the shape of the inlet lip 1 is constrained by the total length l of the lip 1 and the total width h of the lip 1, l is 525mm, and h is 155mm, so that the triangle-like lip outer 1 shape is obtained; generating a longitudinal line of a channel inlet section 2 according to a curve of a lip 1 and a line of a minimum section 3, and setting CL₁、CL₂The like; and (4) sweeping the outlet section 4 of the air inlet channel to generate a longitudinal line and an outlet section line of the outlet section 4 of the channel. And generating a curved surface of the inner surface of the air inlet by the curve passing network to form a shape model of the triangular-like lip air inlet.

The second step is that: air inlet channel model gridding treatment

And (3) making section lines on the air inlet channel appearance model, carrying out equidistant section point taking on the air inlet channel at intervals of 15mm, generating grid nodes with the density meeting the requirements on each section line, and outputting surface grid files required by radar scattering cross section (RCS) analysis and flow field analysis.

The third step: inlet duct scattered field computational analysis

And carrying out scattering characteristic simulation calculation on the generated surface grid file. Calculating the lip edge diffraction field by using methods such as geometric diffraction; and (4) applying methods such as a full wave algorithm and the like to the scattering characteristics of the channel of the air inlet channel to carry out calculation, and outputting the RCS of the air inlet channel.

The fourth step: inlet and outlet flow combined analysis

And carrying out flow field characteristic simulation calculation on the generated surface grid file. And in the process of internal and external flow joint calculation, a numerical calculation method based on an N-S equation and a proper turbulence model is adopted, and flow field characteristic information such as total pressure recovery coefficient, flow field distortion and the like is output.

The fifth step: stealth/flow field comprehensive optimization design

And (3) taking the shape parameters of the lip 1 and the channel inlet section 2 as design variables, taking the flow field characteristics meeting the working requirements of the engine as constraint conditions, developing the stealth/flow field comprehensive optimization design, and solving and optimizing by adopting an optimization method based on a Kriging approximate model and a genetic algorithm to obtain the triangular-like lip 1 stealth shape air inlet channel.

Through flow field calculation verification, the total pressure recovery coefficient of the triangular-like lip 1 air inlet channel in the cruise state of the aircraft is 0.96-0.97, the flow field distortion is small, and the aerodynamic performance is good; through an RCS test of an air inlet channel model, the mean value of forward RCS of S wave band of the profile air inlet channel is lower than-20 dBsm, and the mean value of forward RCS of X wave band is lower than-26 dBsm.

Example 3

The first step is as follows: parametric modeling of air inlet duct shape

According to project requirements and constraint conditions, sweeping the minimum cross section 3 and lip 1 areas of the air inlet, generating the minimum cross section 3 line and lip 1 basic contour line of the air inlet, and setting S₁、S₂、S₃、S₄、L₁、L₂、L₃Alpha, beta, gamma, etc., wherein L₁、L₂、L₃Take 0, S₁、S₂、S₃、S₄The shapes of the inlet lip 1 are all tangent transition, the total length l of the lip 1 and the total width h of the lip 1 are restricted, wherein l is 550mm, and h is 550mm, so that the shape of the goose egg-shaped lip 1 is obtained; generating a longitudinal line of a channel inlet section 2 according to a curve of a lip 1 and a line of a minimum section 3, and setting CL₁、CL₂The like; and (4) sweeping the outlet section of the air inlet channel to generate a longitudinal line and an outlet section line of the outlet section 4 of the channel. And generating a curved surface of the inner surface of the air inlet by the curve passing network to form an appearance model of the air inlet with the goose egg-shaped lip 1.

The second step is that: air inlet channel model gridding treatment

And (3) making section lines on the air inlet channel appearance model, carrying out equidistant section point taking on the air inlet channel at intervals of 25mm, generating grid nodes with the density meeting the requirements on each section line, and outputting surface grid files required by radar scattering cross section (RCS) analysis and flow field analysis.

The third step: inlet duct scattered field computational analysis

And carrying out scattering characteristic simulation calculation on the generated surface grid file. Calculating by applying equivalent electromagnetic flow and other methods to a lip edge diffraction field; and (4) calculating the scattering characteristic of the channel of the air inlet by using a ray tracing method, and outputting the RCS of the air inlet.

The fourth step: inlet and outlet flow combined analysis

And carrying out flow field characteristic simulation calculation on the generated surface grid file. And in the process of internal and external flow joint calculation, a numerical calculation method based on an N-S equation and a proper turbulence model is adopted, and flow field characteristic information such as total pressure recovery coefficient, flow field distortion and the like is output.

The fifth step: stealth/flow field comprehensive optimization design

And (3) taking the shape parameters of the lip 1 and the channel inlet section 2 as design variables, taking the flow field characteristics meeting the working requirements of the engine as constraint conditions, developing the stealth/flow field comprehensive optimization design, and solving and optimizing by adopting an optimization method based on a Kriging approximate model and a genetic algorithm to obtain the goose egg-shaped lip 1 stealth shape air inlet channel. Through flow field calculation verification, the total pressure recovery coefficient of the goose egg-shaped lip 1 air inlet channel in the cruising state of the aircraft is 0.94-0.97, and the flow field distortion is small; through simulation of the RCS of the air inlet channel, the mean value of the forward RCS of the S wave band of the profile air inlet channel is lower than-20 dBsm, and the mean value of the forward RCS of the X wave band is lower than-23 dBsm.