CN109649666A - A Hypersonic Inlet Flow Control Method Combining Boundary Layer Guidance and Suction - Google Patents

Abstract

Translated fromChinese

本发明公开一种边界层引导和抽吸结合的高超声速进气道流动控制方法，包括以下步骤：在高超声速进气道前体上形成边界层引导型面通过在边界层引导型面上产生的横向压力梯度，使流经边界层引导型面的气流的流动方向发生定向改变；控制作用在所述边界层引导型面上的横向压力梯度以将边界层引导到所述边界层引导型面的局部；在所述边界层引导型面的局部设置抽气孔。该方案解决了现有技术中抽吸性能低的问题，实现了有针对性的抽吸，并提高的抽吸性能。

The invention discloses a hypersonic air inlet flow control method combining boundary layer guidance and suction, comprising the following steps: forming a boundary layer guiding profile on a hypersonic air inlet precursor by generating a boundary layer guiding profile The lateral pressure gradient on the boundary layer guide profile changes directionally; the lateral pressure gradient acting on the boundary layer guide profile is controlled to guide the boundary layer to the boundary layer guide profile Part of the boundary layer guide profile; set the air extraction hole in the part of the boundary layer guide profile. The solution solves the problem of low suction performance in the prior art, realizes targeted suction, and improves suction performance.

Description

A kind of hypersonic inlet flow control method of boundary layer guidance and suction combination

Technical field

The present invention relates to hypersonic inlet technical field, especially a kind of boundary layer guides and aspirates the superb of combinationVelocity of sound inlet duct flow flowing control method.

Background technique

Boundary layer suction is considered as a kind of very effective inlet boundary layer flow control method.Boundary layer suction isSuction hole is arranged in finger on wall surface, and the pressure difference at through hole both ends extracts boundary layer airflow out, to keep boundary layer thinning.BoundaryLayer suction is made of suction hole, suction chamber and bleed-off system etc., and the course of work enters suction chamber through suction hole for boundary layer, thenIt is discharged by bleed-off system.Suction substantially reduces boundary layer thickness, and air intake duct capture flow quality is improved；Another partyFace, since boundary layer is thinning, the interference of air intake duct Shock/Boundary-Layer weakens, and intake duct starting performance also greatly improves.Currently, sideInterlayer liposuction technique has been widely used in surpassing/hypersonic inlet.

The boundary layer suction of the prior art includes suction hole, suction chamber, bleed-off system etc., and structure is relative complex, is increased simultaneouslyAircraft weight is added, suction chamber and bleed-off system also occupy the space of Vehicle nose.On the other hand, aircraft fuselage oneAs use composite material, large area punching can destroy the structural strength of material on wall surface.

For hypersonic inlet application No. is: 201710784957.3 Chinese patent literature proposes one kindPrecursor and Bump have been carried out integrated design by Bump/ precursor integrated design method, this method, are solved Bump substantially and are existedThe excessive problem of flow losses in hypersonic air-flow.Bump/ precursor integration air intake duct passes through the cross generated on Bump type faceIt is realized to barometric gradient and the row in boundary layer is moved, achieve preferable effect.But due to hypersonic flowing excessive velocities, laterallyRow moves apart from too long, and designs obtained Bump limited height, therefore this method moves the row of hypersonic boundary layer airflowAbility is weaker.

Pneumatic research and experiment, 2010,28 (4): 1-6 is " based on numerical simulation air intake duct suction flowing control optimization design[J] " Bump air intake duct is combined with boundary layer suction technology, the different installation site of suction socket is had studied to air intake ductThe influence of performance.Also there is the scheme that suction hole is arranged in the bottom side Bump in actual engineering design.These schemes are all by BumpCombine with liposuction technique, to further increase inlet flow capture quality.The method that Bump and air intake duct suction combineAbility is moved to the row in boundary layer to be obviously improved, but the mode of the two combination is also rested on mechanically combine at presentStage.The installation site for studying different suction holes in Bump air intake duct for the first selects one in multi-scheme of only comformingA preferably scheme, does not account for the flow feature of Bump air intake duct, has blindness.Suction hole is arranged in the bottom side BumpScheme is taken away boundary layer by suction hole in view of being accumulated in the bottom side Bump in boundary layer, and this scheme is applicable inIn moving more powerful supersonic speed Bump air intake duct to boundary layer row, and it is hypersonic under the conditions of Bump type face tend not to big portionPoint boundary layer row moves on to bottom side, therefore suction hole cannot play swabbing action well.

Summary of the invention

The present invention provides the hypersonic inlet flow control method that a kind of guidance of boundary layer and suction combine, for gramBoundary layer airflow row moves the defects of performance is weaker to clothes in the prior art, realizes the effect for effectively playing aspirating hole, improves boundary layerAir-flow row moves the purpose of performance.

To achieve the above object, the present invention proposes a kind of hypersonic inlet boundary layer flow flowing control method, including withLower step:

Step 1, boundary layer guide profile is formed on hypersonic inlet precursor, by the guide profile of boundary layerDirected change occurs for the transverse-pressure gradient of generation, the flow direction for flowing through the air-flow of boundary layer guide profile,；

Step 2, boundary layer is directed to by the transverse-pressure gradient that acts in the boundary layer guide profile describedThe part of boundary layer guide profile；

Step 3, in the local setting aspirating hole of the boundary layer guide profile.

Hypersonic inlet flow control method provided by the invention passes through what is be distributed to boundary layer guide profile pressureIt is well-designed, so that boundary layer guide profile is generated transverse-pressure gradient, to carry out active guidance to boundary layer airflow, makes boundaryLayer be directed separately under the action of transverse-pressure gradient boundary layer guide profile part (such as easily operated middle part andBottom), the position due to concentrating on boundary layer guide profile can form thicker boundary layer, in the thicker place arrangement in boundary layerSuction hole, realization targetedly effectively aspirate boundary layer.

Detailed description of the invention

In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show belowThere is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only thisSome embodiments of invention for those of ordinary skill in the art without creative efforts, can be withThe structure shown according to these attached drawings obtains other attached drawings.

Fig. 1 is the hypersonic inlet flowing control that the boundary layer guidance that the embodiment of the present invention one provides and suction combineLower jaw formula axialsymmetrical inlet schematic diagram in method；

Fig. 2 is Fig. 1 left view；

Fig. 3 is the top view of Fig. 1；

Fig. 4 is the hypersonic inlet flowing control that the boundary layer guidance that the embodiment of the present invention one provides and suction combineK in method_θWith theta function relation curve schematic diagram；

Fig. 5 is the hypersonic inlet flowing control that the boundary layer guidance that the embodiment of the present invention one provides and suction combineX=x in method₀Section inner boundary layer extends to distribution and puff profile band and determines schematic diagram.

The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.

Specific embodiment

Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, completeSite preparation description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.BaseEmbodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all itsHis embodiment, shall fall within the protection scope of the present invention.

It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute is only used in the embodiment of the present inventionIn explaining in relative positional relationship, the motion conditions etc. under a certain particular pose (as shown in the picture) between each component, if shouldWhen particular pose changes, then directionality instruction also correspondingly changes correspondingly.

In addition, the description for being such as related to " first ", " second " in the present invention is used for description purposes only, and should not be understood asIts relative importance of indication or suggestion or the quantity for implicitly indicating indicated technical characteristic.Define as a result, " first ",The feature of " second " can explicitly or implicitly include at least one of the features.In the description of the present invention, " multiple " containJustice is at least two, such as two, three etc., unless otherwise specifically defined.

In the present invention unless specifically defined or limited otherwise, term " connection ", " fixation " etc. shall be understood in a broad sense,For example, " fixation " may be a fixed connection, it may be a detachable connection, or integral；It can be mechanical connection, be also possible toElectrical connection can also be physical connection or wireless communication connection；It can be directly connected, the indirect phase of intermediary can also be passed throughEven, the connection inside two elements or the interaction relationship of two elements be can be, unless otherwise restricted clearly.For thisFor the those of ordinary skill in field, the specific meanings of the above terms in the present invention can be understood according to specific conditions.

It in addition, the technical solution between each embodiment of the present invention can be combined with each other, but must be general with this fieldBased on logical technical staff can be realized, it will be understood that when the combination of technical solution appearance is conflicting or cannot achieve thisThe combination of technical solution is not present, also not the present invention claims protection scope within.

The present invention proposes the hypersonic inlet flow control method of a kind of boundary layer guidance and suction combination.

Embodiment one

Referring to Fig. 1-5, the embodiment of the present invention provides the hypersonic inlet stream of a kind of boundary layer guidance and suction combinationFlowing control method, comprising the following steps:

Step 1, boundary layer guide profile is formed on hypersonic inlet precursor, thus in the guide profile of boundary layerTransverse-pressure gradient is generated, is oriented by the flow direction that transverse-pressure gradient flows through the air-flow of boundary layer guide profileChange；

By the working principle of supersonic speed Bump, the flow direction for flowing through the air-flow of boundary layer guide profile is orientedChange, precursor type face generates transverse-pressure gradient, to carry out active guidance to boundary layer airflow, the direction of guidance can be pre-Fixed, theoretically any direction is ok, and is also possible to being set according to actual design condition or that analysis obtains.Draw in boundary layerConductivity type face is a part of hypersonic aircraft precursor, and its role is to flow through the flowing of boundary layer guide profile overdraughtDirected change occurs for direction, and directed change here refers to flowing towards scheduled direction；And then boundary layer is influenced on boundaryThe distribution of thickness, is adjusted boundary layer thickness under the action of guide profile in boundary layer in layer guide profile；

Step 2, boundary layer is directed to by the transverse-pressure gradient that acts in the boundary layer guide profile describedThe part of boundary layer guide profile；

It can be any part in this local theory, be by being distributed to boundary layer guide profile pressure in the present embodimentIt is well-designed, so that boundary layer is directed separately to the middle part and bottom of boundary layer guide profile under the action of transverse-pressure gradientThen portion is respectively arranged suction hole in the two regions, realizes the suction to boundary layer.It is optimal for being arranged in the two positionsBecause being typically all only to be arranged in bottom, but hypersonic condition boundary layer is difficult bottom, place at middle part andBottom has carried out row respectively and has moved.This is also invention distinguishes in other importances.

In boundary layer, the distribution of boundary layer thickness can change under the action of guide profile.According to boundary layer in boundary layerCharacteristic distributions in guide profile determine puff profile band by given threshold, then on each puff profile band respectivelySuction hole is set.

Step 3, in the local setting aspirating hole of the boundary layer guide profile.In boundary layer, the part of guide profile canThicker boundary layer is formed, in the thicker place setting aspirating hole in boundary layer, the quantity of aspirating hole can be reduced, while improving pumpingAbsorption energy.

Preferably, include: the step of formation boundary layer guide profile in the step 1

Step 11, the pressure on each osculating plane is defined by functional relation using variable θ and x as independent variable；θ be exhibition toVariable, x are to flow to variable, the i.e. axial deflection of air intake duct.The ginseng on a two-dimensional surface is assured that by the two variablesNumber, flow field symmetrical for outer shaft, the osculating plane, which refers to, flows to section with the plane of symmetry angle o degree；Referring to Fig. 1, region 1 is sideInterlayer guide profile；Boundary layer guide profile is a part of hypersonic aircraft precursor, and its role is to flow through boundaryDirected change occurs for the flow direction of layer guide profile overdraught, and the plane where face 2 is the plane of symmetry, and the plane where face 3 isIt is in the osculating plane of θ with the plane of symmetry, point 4 is coordinate origin, while being also boundary layer guide profile starting point, and point 5 is at x=LPoint, while being also boundary layer guide profile terminating point, each osculating plane is defined with variable θ, for Tidal Flow, closelyFace refers to parallel with the plane of symmetry, and distance is that θ flows to section；Axisymmetric flow field is turned for inside/outside, osculating plane refers to is in the plane of symmetryθ angle flows to section.

Step 12, the functional relation of the pressure on each osculating plane and independent variable obtains each and opens up to scale factorPressure distribution curve on osculating plane；

Step 13, the corresponding flow field of pressure distribution curve is obtained based on the method for characteristic curves in each osculating plane；

Step 14, the flow field wall surface line in all osculating planes is subjected to curved surface setting-out, the type face of acquisition is drawn as boundary layerConductivity type face.

Preferably, the step 11 includes:

The intersection point 4 that coordinate origin is boundary layer guide profile start line and the plane of symmetry is defined, following functional relation is passed throughDefine the pressure on each osculating plane:

P (θ, x)=k_θy(x)+P₀ (1)

Wherein, P₀It is given value for the pressure value of coordinate origin；Independent variable x is abscissa, and value range is 0 < x < L,Middle L is boundary layer guide profile terminated line abscissa, that is, puts 5 abscissa；Y (x) is the function of x, meets the following conditions: with xIt is increased monotonically；It is 0 in coordinate origin functional value, i.e. y (0)=0；The symmetrical flow field of the outer shaft of θ indicates osculating plane locating for the flow fieldAngular range with the plane of symmetry is-θ_c<θ<θ_c, wherein θ_cFor given value；k_θIt is the function of θ to open up to scale factor；Due to heightSupersonic speed precursor needs to undertake a part of compression duty, therefore boundary layer guide profile flow field edge flows to pressure and constantly increases(boundary layer guide profile plays the role of compression to air-flow, so wall surface constantly increases along stroke pressure).

The step 12 includes:

By changing k_θ, controlling each and opening up to scale factor is k_θOsculating plane in pressure distribution curve, realize to pressurePower be distributed in exhibition to control, in boundary layer, guide profile forms transverse-pressure gradient, realizes guidance to boundary layer.

Preferably, the step 12 includes:

k_θAs θ increases monotone decreasing, by second dervative by k_θCurve is divided into following three sections:

θ is located at [0, θ₁] section when, k_θ" (θ) > 0, and k_θ(0)=1；

θ is located at [θ₁,θ₂] section when, k_θ"(θ)<0；

θ is located at [θ₂,θ_c] section when, k_θ" (θ) > 0, and k_θ(θ_c)=k_min, wherein k_minFor specified value, range is 0 < k_min<1；

k_θCurve first derivative at θ=0 is zero, θ=θ₁With θ=θ₂It is continuous to locate first derivative.

Preferably, k in each section_θSpecific functional relation includes the letters such as given polynomial type, trigonometric function type, exponential typeThe specific analytic expression of at least one of number relationship.

As a preferred embodiment of the present invention: for example given y (x) is the functional relation of parabolic, a in formulaThe compression of air-flow can be required to give according to practical precursor, value range is generally [0.01,1].

P (θ, x)=k_θ(ax²)+P₀ (2)

k_θIt is the function of θ to open up to scale factor.The present invention is by changing k_θ, realize to pressure be distributed in exhibition to controlSystem to form transverse-pressure gradient in boundary layer guide profile, and then realizes the guidance to boundary layer.Below to k_θWith θ'sFunctional relation is described.k_θAlong the direction θ monotone decreasing, curve can be divided into three sections by second dervative is positive and negative.First segment is[0,θ₁] section, there is k in this section_θ" (θ) > 0, meets k_θ(0)=1.Second segment is [θ₁,θ₂] section, k in this section_θ"(θ)<0.Third section is [θ₂,θ_c] section, there is k in this section_θ" (θ) > 0, meets k_θ(θ_c)=k_min, wherein k_minFor specified value, rangeFor 0 < k_min<1.In addition, k_θCurve first derivative at θ=0 is zero, θ=θ₁With θ=θ₂It is continuous to locate first derivative, to guaranteeLine smoothing.Concrete functional form can give polynomial type, trigonometric function type, exponential type etc. and specifically parse in each sectionFormula.

One specific implementation case: the given quadratic function distribution form in three sections takes θ₁=10, θ₂=25, θ_c=60；θ₁Corresponding k_θTake 0.8, k_min=0.6.Simultaneously curve meet it is above-mentioned required, equation number etc. under these conditionsIn variable number, the quadratic function expression formula in three sections can be thus solved.(directly solve equation or be converted into lineProperty algebraic solution can obtain totally 9 variables and 9 equations)

By k in each section_θValue is discrete along the direction θ, and discrete accuracy rating is [1 °, 10 °].It is obtained according to the solution of formula 1It is k that each, which is opened up to scale factor,_θOsculating plane in pressure distribution curve.

To osculating plane pressure controllable flow field calculation, given pressure distribution is solved based on the method for characteristic curves in each osculating planeThe corresponding flow field of curve.This method is this field publicly-owned technology, solution procedure can refer to application No. is: 201710784957.3Chinese patent literature and Beijing Higher Education Publishing House -2012 " aerodynamics [M] ".

It is that known two phases are solved using the method estimated-corrected based on there is the rotation method of characteristic curves in specific solution procedureThe downstream wall millet cake these two types unit process that the downstream inner of adjacent internal point selects, known upstream wall millet cake and adjacent inner are selected.SoThe corresponding entire flow field of pressure distribution curve and wall surface molded line are solved according to space step-by-step system afterwards.

The corresponding wall surface of pressure distribution curve in osculating plane is thus obtained.Then it solves according to the method all closeThe corresponding wall surface of pressure distribution curve in section.

The flow field wall surface line in all osculating planes is finally subjected to curved surface setting-out, obtained type face is boundary layer leading typeFace.

Preferably, the step 2 includes:

Step 21, numerical simulation is carried out to boundary layer guide profile, obtains boundary layer guide profile top thickness of boundary layer pointCloth.In k of the present invention_θSetting boundary layer close to θ₁<θ<θ₂And θ=θ_cRegion, boundary layer thickness extend to formed pairAnswer the first protrusion and the second protrusion.

The step 3 includes:

Step 31, the characteristic distributions according to boundary layer on boundary layer type face determine puff profile band by threshold value；

Step 32, suction hole is respectively set on each puff profile band.

Preferably, the step 31 includes:

Step 311, in the case that boundary layer leading type is not added in boundary layer, x=x₀The boundary layer thickness conduct in sectionT₀；

Step 312, for the first elevated regions of boundary layer, give proportional factor r 1, when boundary layer thickness meet T > r1 ×T₀When, assert the position on the first puff profile band；

For the second elevated regions of boundary layer, proportional factor r 2 is given, the boundary layer thickness at the position meets T > r2×T₀When, assert the position on the second puff profile band；

R1 and r2 is given value, and r1, r2 are all larger than zero, and r1 < r2；

Step 313, puff profile band position is carried out really perpendicular to the section in the direction x to each according to step 312Recognize, obtains the first puff profile band and the second puff profile band in entire boundary layer guide profile.

As a specific embodiment of the invention, (axial direction of air intake duct) arranges one in the guide profile of boundary layer in the x-directionSerial equidistantly to open up to section, section spacing value range is [10,100].

This, which sentences x=x, is confirmed to puff profile band position into section in each open up₀It is illustrated for section.With no addition boundary layer guide profile, identical x=x in the case of the Free Development of boundary layer₀The boundary layer thickness in section is as baseQuasi- thickness, is denoted as T_o。

For the first elevated regions of boundary layer, proportional factor r is given₁, when boundary layer thickness meets T > r₁·T_o, it is assumed thatThe position is on the first puff profile band.For the second elevated regions of boundary layer, proportional factor r is given₂, side at the positionThickness of boundary layer meets T > r₂·T_o, it is assumed that the position is on the second puff profile band.r₁And r₂For given value, passed through according to designIt tests, the two value range takes [0.5,2] proper, in general meets r₁<r₂。

Each is opened up to section according to the method and carries out confirmation of the puff profile with position, available entire sidePuff profile band in interlayer guide profile.

The first puff profile band and the second puff profile band are obtained in the guide profile of boundary layer as a result,.

One specific implementation case: x=x is provided₀Section inner boundary layer extend to distribution illustrate puff profileThe confirmation process of band.Boundary layer thickness extends apparent raised to forming two in figure.Numerical simulation obtains T in the section_o=0.58.Take r₁=0.9, take r₂=1.04, the puff profile band range for finally obtaining the first elevated regions is [10.2,28.8], is obtainedPuff profile band range to the second elevated regions is [48.0,58.6].

Preferably, the step 32 specifically includes:

Step 321, according to the area of given shape, suction area ratio and single suction hole, the sum of aspirating hole is obtainedAmount；Suction area ratio refers to that the area of the total suction hole percentage with area that accounts for puff profile, total area that aspirates are taken out divided by singleTotal hole count can be obtained in sucker area.

Step 322, the distribution form in hole can be by the way of array equidistant on puff profile band, it is of course possible to rootIt is arranged according to actual demand.Suction hole is laid respectively on each puff profile band according to the distribution form in hole.

The arrangement of suction hole is the publicly-owned technology in this field, and suction hole arrangement can be divided into two: determining suction hole shape,Quantity；The distribution form of given suction hole.

The shape of given bore first, suction hole can be circle, triangle, rectangle etc..Then give suction area ratio andThe area of single suction hole, suction area ratio refers to the area of the total suction hole percentage with area that accounts for puff profile, total to aspirateTotal hole count can be obtained divided by single suction hole area in area.

The distribution form in hole can be by the way of array equidistant on puff profile band, it is of course possible to according to practical needIt asks and is arranged.

The working principle of supersonic speed Bump is introduced hypersonic precursor design by the present invention, and precursor type face is made to generate laterally pressureForce gradient is distributed in boundary layer thickness in the guide profile of boundary layer and forms two to carry out active guidance to boundary layer airflowA protrusion, then in the place arrangement suction hole of protrusion, to realize that a kind of boundary layer suitable for hypersonic inlet is drawnLead the boundary layer flow flowing control method of cooperation suction.

Compared with traditional liposuction technique, under identical suction effect, suction hole of the present invention is less, suction chamberAlso smaller, be conducive to the damaged condition for reducing fuselage material structural strength, while also saving the space of aircraft interior；WithBump air intake duct is compared, and the present invention proposes boundary layer aiming at the problem that boundary layer row moves relative difficulty in hypersonic flowingThe boundary layer controllable way that guidance and suction match, solves the problems, such as this substantially；Cooperate with existing Bump and suctionControl mode is compared, and the present invention guides boundary layer, then targetedly taken out by precursor type face special designingIt inhales, the effect of suction hole can be played to a greater extent.By numerical simulation, it was demonstrated that the program is feasible.

The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all at thisUnder the inventive concept of invention, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/use indirectlyIt is included in other related technical areas in scope of patent protection of the invention.

Claims (9)

Translated fromChinese

1.一种边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，包括以下步骤：1. a hypersonic air inlet flow control method combining boundary layer guidance and suction, is characterized in that, comprises the following steps:步骤1，在高超声速进气道前体上形成边界层引导型面，通过在边界层引导型面上产生的横向压力梯度，使流经边界层引导型面的气流的流动方向发生定向改变；Step 1: A boundary layer guiding profile is formed on the precursor of the hypersonic inlet port, and the flow direction of the airflow flowing through the boundary layer guiding profile is directionally changed by the transverse pressure gradient generated on the boundary layer guiding profile;步骤2，通过作用在所述边界层引导型面上的横向压力梯度将边界层引导到所述边界层引导型面的局部；Step 2, guiding the boundary layer to a part of the boundary layer guiding profile through the lateral pressure gradient acting on the boundary layer guiding profile;步骤3，在所述边界层引导型面的局部设置抽气孔。Step 3, setting an air extraction hole in a part of the boundary layer guiding profile.2.如权利要求1所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤1中形成边界层引导型面的步骤包括：2. The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 1, wherein the step of forming the boundary layer guidance profile in step 1 comprises:步骤11，以变量x，θ为自变量通过函数关系定义每一个密切面上的压力；x为进气道轴向变量，对于外转轴对称流场，所述密切面指与对称面呈θ角度的流向切面；Step 11, using variables x and θ as independent variables to define the pressure on each close surface through a functional relationship; x is the axial variable of the intake port, and for the outer rotational axis symmetric flow field, the close surface refers to the symmetric plane at an angle of θ. the flow direction section;步骤12，根据每个密切面上的压力与自变量的函数关系，获得每一个展向比例因子的密切面上的压力分布曲线；Step 12, according to the functional relationship between the pressure and the independent variable on each approximation surface, obtain the pressure distribution curve on the approximation surface of each spanwise scaling factor;步骤13，在每个密切面内基于特征线法获得压力分布曲线对应的流场；Step 13, obtain the flow field corresponding to the pressure distribution curve based on the characteristic line method in each close surface;步骤14，将所有密切面内的流场壁面线进行曲面放样，获得的型面作为边界层引导型面。Step 14: Perform surface lofting of the flow field wall lines in all the close planes, and the obtained profile is used as the boundary layer guiding profile.3.如权利要求2所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤11包括：3. The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 2, wherein the step 11 comprises:定义坐标原点为边界层引导型面起始线与对称面的交点，通过下面的函数关系定义每个密切面上的压力:Define the origin of the coordinate as the intersection of the starting line of the boundary layer guiding profile and the symmetry plane, and define the pressure on each close surface through the following functional relationship:P(θ,x)＝k_θy(x)+P₀ (1)P(θ,x)=k_θ y(x)+P₀ (1)其中，P₀为坐标原点的压力值，为给定值；自变量x为横坐标，取值范围为0<x<L，其中L为边界层引导型面终止线横坐标；y(x)为x的函数，满足以下条件：随x单调增加；在坐标原点函数值为0，即y(0)＝0；θ针对外转轴对称流场表示该流场所处密切面与对称面的夹角，范围为-θ_c<θ<θ_c，其中θ_c为给定值；k_θ为展向比例因子，是θ的函数；Among them, P₀ is the pressure value at the origin of the coordinate, which is a given value; the independent variable x is the abscissa, and the value range is 0<x<L, where L is the abscissa of the boundary layer guiding profile termination line; y(x) is a function of x, which satisfies the following conditions: it increases monotonically with x; the function value at the coordinate origin is 0, that is, y(0)=0; , the range is -θ_c <θ<θ_c , where θ_c is a given value; k_θ is the spanwise scaling factor, which is a function of θ;所述步骤12包括：The step 12 includes:通过改变k_θ，每一个展向比例因子为k_θ的密切面内的压力分布曲线，实现对压力分布在展向的控制，在边界层引导型面形成横向压力梯度，实现对边界层的引导。By changing k_θ , each pressure distribution curve in the close plane with the spanwise scaling factor k_θ realizes the control of the pressure distribution in the spanwise direction, and forms a lateral pressure gradient on the boundary layer guiding profile to realize the guidance of the boundary layer. .4.如权利要求3所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤12包括：4. The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 3, wherein the step 12 comprises:k_θ随着θ增加单调递减，按二阶导数将k_θ曲线分为以下三段：k_θ decreases monotonically as θ increases, and the k_θ curve is divided into the following three segments according to the second derivative:θ位于[0,θ₁]区间时，k_θ"(θ)>0，且k_θ(0)＝1；When θ is in the interval [0, θ₁ ], k_θ "(θ)>0, and k_θ (0)=1;θ位于[θ₁,θ₂]区间时，k_θ"(θ)<0；When θ is in the interval [θ₁ ,θ₂ ], k_θ "(θ)<0;θ位于[θ₂,θ_c]区间时，k_θ"(θ)>0，且k_θ(θ_c)＝k_min，其中k_min为给定的值，范围为0<k_min<1；When θ is in the interval [θ₂ ,θ_c ], k_θ "(θ)>0, and k_θ (θ_c )=k_min , where k_min is a given value, and the range is 0<k_min <1;k_θ曲线在θ＝0处一阶导数为零，θ＝θ₁和θ＝θ₂处一阶导数连续。The first derivative of the kθ curve is zero at_θ =₀ , and the first derivative is continuous at θ=_θ1 and θ=θ2.5.如权利要求4所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，每个区间内k_θ具体函数关系包括给定多项式型、三角函数型、指数型中至少一种具体解析式。5. The hypersonic inlet flow control method combining boundary layer guidance and suction according to claim 4, wherein the specific functional relationship of k_θ in each interval includes a given polynomial type, a trigonometric function type, an exponential At least one specific analytical formula in the type.6.如权利要求5所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤2中边界层引导到所述边界层引导型面的局部包括：6 . The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 5 , wherein in the step 2, the boundary layer is guided to the part of the boundary layer guidance profile comprising:所述边界层厚度方向的变化集中在所述边界层引导型面沿展向的中部和底部；The change in the thickness direction of the boundary layer is concentrated in the middle and bottom of the boundary layer guiding profile along the span;所述步骤3包括：The step 3 includes:步骤31，根据边界层在边界层型面上的分布特点，通过阈值确定抽吸分布带；Step 31, according to the distribution characteristics of the boundary layer on the boundary layer profile, determine the suction distribution zone through a threshold;步骤32，在每一抽吸分布带上分别设置抽吸孔。Step 32, respectively setting suction holes on each suction distribution belt.7.如权利要求6所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤2包括：7. The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 6, wherein the step 2 comprises:步骤21，对边界层引导型面进行数值仿真，获得在靠近θ₁<θ<θ₂以及θ＝θ_c的区域，边界层厚度分布沿展向对应形成第一凸起和第二凸起。Step 21: Numerical simulation is performed on the boundary layer guiding profile, and it is obtained that in the region close to θ₁ <θ<θ₂ and θ=θ_c , the thickness distribution of the boundary layer correspondingly forms the first protrusion and the second protrusion along the span.8.如权利要求7所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤31包括：8. The hypersonic air inlet flow control method combining boundary layer guidance and suction according to claim 7, wherein the step 31 comprises:步骤311，边界层没有加入边界层引导型的情况下，x＝x₀时的垂直于x方向的截面的边界层厚度作为T₀；Step 311 , in the case where the boundary layer guide type is not added to the boundary layer, the thickness of the boundary layer of the section perpendicular to the x direction when x=x₀ is taken as T₀ ;步骤312，对于边界层第一凸起区域，给定比例因子r1，当边界层厚度满足T>r1×T₀时，认定该位置在第一抽吸分布带上；Step 312, for the first convex region of the boundary layer, given a scale factor r1, when the thickness of the boundary layer satisfies T>r1×T₀ , it is determined that the position is on the first suction distribution zone;对于边界层第二凸起区域，给定比例因子r2，当该位置处的边界层厚度满足T>r2×T₀时，认定该位置在第二抽吸分布带上；For the second convex area of the boundary layer, given the scale factor r2, when the thickness of the boundary layer at the position satisfies T>r2×T₀ , it is determined that the position is on the second suction distribution zone;r1和r2为给定值，r1，r2均大于零，且r1<r2；r1 and r2 are given values, both r1 and r2 are greater than zero, and r1<r2;步骤313，按照步骤312对每一个垂直于x方向的截面都进行抽吸分布带位置的确认，获得整个边界层引导型面上的第一抽吸分布带和第二抽吸分布带。Step 313 , according to step 312 , confirm the position of the suction distribution zone for each section perpendicular to the x-direction, and obtain the first suction distribution zone and the second suction distribution zone on the entire boundary layer guiding profile.9.根据权利要求6～8任一项所述的边界层引导和抽吸结合的高超声速进气道流动控制方法，其特征在于，所述步骤32包括：9 . The hypersonic intake port flow control method combining boundary layer guidance and suction according to any one of claims 6 to 8, wherein the step 32 comprises:步骤321，根据给定的形状、抽吸面积比和单个抽吸孔的面积，获得抽气孔的总数量；Step 321, according to the given shape, the suction area ratio and the area of a single suction hole, obtain the total number of suction holes;步骤322，根据孔的分布形式在每一抽吸分布带上分别布设抽吸孔。Step 322, according to the distribution form of the holes, respectively arrange suction holes on each suction distribution belt.