CN114896709B - Integrated design method for front straight lip inlet with sharp front edge type triangular waverider - Google Patents

Integrated design method for front straight lip inlet with sharp front edge type triangular waverider Download PDF

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CN114896709B
CN114896709B CN202210829737.9A CN202210829737A CN114896709B CN 114896709 B CN114896709 B CN 114896709B CN 202210829737 A CN202210829737 A CN 202210829737A CN 114896709 B CN114896709 B CN 114896709B
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air inlet
plane
waverider
line
precursor
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CN114896709A (en
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余安远
黎崎
吴杰
马志成
乐嘉陵
王�锋
李姝源
杨辉
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Institute of Aerospace Technology of China Aerodynamics Research and Development Center
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Abstract

The invention provides an integrated design method for a straight lip inlet of a sharp front edge triangular waverider-like front body, which relates to the field of aerodynamic internal and external flow coupling design and comprises the following steps: (1) designing a binary plane reference flow field; (2) Constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating and positioning the characteristic molded lines on the tangential plane according to the edge line of the sharp front edge type triangular waverider precursor; (3) Constructing an air inlet on a tangential plane parallel to a meridian plane according to an air inlet compression plane reference configuration, compressing and horizontally positioning compression plane profiles of the air inlet on the tangential plane, and combining a set of the compression plane profiles with a precursor characteristic profile to obtain a sharp front edge triangular waverider-like precursor straight lip air inlet integrated configuration in an air inlet width range; (4) And generating a straight lip inlet integrated configuration of the front body of the sharp front edge type triangular waverider in the full-width range. The invention fills the design gap of the hypersonic-speed IgLa-type aircraft forebody air inlet passage.

Description

Integrated design method for front straight lip inlet with sharp front edge type triangular waverider
Technical Field
The invention relates to the field of aerodynamic internal and external flow coupling design, in particular to an integrated design method for a front straight lip inlet with a sharp leading edge triangular waverider.
Background
Compared with the conventional lifting body configuration, the waverider configuration has a higher lift-drag ratio and is an ideal choice for designing the hypersonic aircraft forebody. Meanwhile, the lower surface of the waverider has precompression function and good capture function for free incoming flow, and is a natural precursor coupled with an air inlet channel. The wave rider forebody and the air inlet channel are designed in a coupling mode in aerodynamic and geometric modes, and therefore the wave rider forebody/the air inlet channel should be designed in an integrated mode.
And the method is technically developed in the field of precursor/air inlet integrated design, for example, the X-51A adopts a design scheme of integrating a waverider with a binary compression air inlet, and the HTV3 aircraft adopts a design scheme of integrating the waverider with a three-dimensional internal compression air inlet. A great deal of research work is also done in the aspect of integral design of a wave carrier and an air inlet in China, wang Junji and the like design a hypersonic wave carrier precursor/air inlet integral precursor model with parallel air inlet at the belly based on a binary mixed pressure type hypersonic air inlet and a close cone wave carrier, and numerical simulation researches the aerodynamic characteristics of the model under different flight Mach numbers and attack angles; he Xuzhao, et al, have developed an integrated design technique for an inlet duct of a precursor of a close inner cone waverider based on a design method for the close inner cone waverider; the Xiaohong et al establishes a method for calculating the post-wave flow field by the estimation of the shock wave surface, designs an intersecting cone model capable of generating three closed conical shock waves, generates a comparison model of a wave-rider precursor with three closed shock waves and a wave-rider precursor with two plane shock waves of one closed shock wave on the basis of the intersecting cone model, respectively performs full three-dimensional flow field calculation on the two wave-rider precursors and the air inlet channel integrated model, and researches the pneumatic performance of the two models in different flight states. These research efforts and proposed design methods have led to the development of integrated design methods for flat-leading or flat-leading-edge-like waverider forebody/binary inlets and profiled forebody/internal-turn inlets.
In the prior art, a design method of a waverider air inlet mainly adopts a reference flow field, streamline extraction and osculating method. The current osculating method is associated with an inner-turning inlet design, and is often called a close axisymmetric method; while the streamline extraction is closely related to the reference flow field. In fact, the close axisymmetric method and the reference flow field selection axisymmetric inner cone flow field support each other.
The close axisymmetric method is a main method for popularizing a two-dimensional axisymmetric flow field to a three-dimensional flow field. A typical example of the application of this method is the design of an internal-turning inlet (e.g., REST inlet, i.e., a rebraglar to-lean-Shape Transition inlet), where the compression profile on each section of the airfoil is derived from streamlines at different locations in the same flow field.
The gas inlet channels with the forebody are divided into a lifting body forebody/gas inlet channel and an axisymmetrical forebody/gas inlet channel. The main types of precursors at present are: a flat front edge lifting body precursor, a pointed lifting body precursor and a special-shaped precursor. The design types of the air inlet channel are mainly as follows: a rectangular/quasi-rectangular air inlet, an axisymmetric air inlet and an inward turning air inlet. Often times, the buoyant body precursor can be combined with a waverider concept to form a waverider precursor design. Obtaining different forms of solutions of the precursor/air inlet channel of the wave-rider lifting body according to different combination modes of the precursor and the air inlet channel of the wave-rider lifting body: straight leading edge rider precursor/rectangular inlet (e.g., X-43A configuration), axisymmetric outer cone rider precursor/inner-turn inlet (e.g., HSSW configuration), shaped precursor/inner-turn inlet (e.g., triJet configuration), curved leading edge precursor/rectangular inlet (e.g., zircon configuration), sharp leading edge lift precursor/inner-turn inlet (e.g., SR-72 configuration), and sharp leading edge lift precursor/rectangular inlet (e.g., igLa configuration).
Of these riser/inlet solutions, a sharp leading edge/rectangular inlet configuration is of interest. The design approach for this type of configuration has not been disclosed, and it is assumed that it is likely that the binary inlet design is decoupled from the precursor design and configured geometrically in a butt-joint manner, and thus the design is most likely unable to take into account the trapping performance of the inlet. The sharp front edge lifting body configuration is particularly suitable for the high supersonic speed condition because the sharp front edge lifting body configuration has the advantage of reducing resistance. If the drag reduction advantage of the sharp leading edge is kept in the design, the high lift force and high capture characteristics of the waverider are fully utilized in the design of the front body, and the front body and the rectangular air inlet are integrally designed, a design method of the waverider front body/quasi-rectangular air inlet with high lift-drag ratio and high capture performance can be established, and the problem to be solved by the invention is solved.
The defects of the prior art are as follows: as shown in the IgLa configuration, in order to reduce the flight resistance, the forebody of some aircraft has a tapered feature, and the forebody appears in a sharp triangle or a triangle-like shape, and after the forebody is integrated with the rectangular inlet channel of the abdomen, the lip leading edge of the inlet channel can still maintain a straight leading edge. Although neither the design nor the aerodynamic performance of the precursor/inlet is disclosed, it is considered from the integration performance that the precursor/inlet should be a fully coupled integrated design in aerodynamic terms, and there are many possible design methods, but if there is a waverider precursor/inlet integration design that satisfies the above-mentioned geometric characteristics, the integration configuration obtained under the above-mentioned strong geometric constraints is necessarily a high-performance precursor/inlet configuration. On the premise that no design method is available or disclosed yet, how to design the tip triangle or tip-like triangle wave-multiplying precursor/rectangular-like air inlet under the strong geometric constraint is a technical problem in front of designers.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: (1) designing a reference flow field of the integrated waverider design of the precursor inlet channel; (2) shape control of a sharp triangular or cusp-like triangular waverider precursor having a sharp leading edge; (3) and (4) determining the similarity ratio and the position of the parallel osculating plane and the characteristic line.
In order to solve the technical problems, the invention provides a similar scaling method for a binary plane reference flow field, an edge contour line and a parallel osculating plane characteristic line, thereby providing an integrated design method for a front body straight lip inlet channel of a sharp leading edge type triangular waverider, and solving the design problem of a front body inlet channel of a hypersonic-speed type IgLa aircraft. The method adopts a binary plane compression flow field as a reference flow field, combines a tangential surface characteristic line similar scaling method parallel to a meridian plane, designs a precursor into a triangle-like shape by an edge contour line method, designs a lip of an abdomen rectangular-like air inlet into a straight front edge, designs the self-multiplication of the air inlet at a design point, and forms an integrated configuration together with the precursor.
In order to achieve the purpose, the technical scheme of the invention is as follows:
an integrated design method for a sharp front edge triangular waverider-like forebody straight lip inlet comprises the following steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to an air inlet compression plane reference configuration, scaling and horizontally moving and positioning compression plane profiles of the air inlet on the tangential plane, and combining a set of the compression plane profiles with a precursor characteristic profile to obtain a sharp front edge triangular multiplier wave-like precursor straight lip air inlet integrated configuration in an air inlet width range;
and S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Further, in the step S1, the binary planar reference flow field is designed specifically as follows:
s11, distributing waves for the external compression flow field by adopting a shock wave and isentropic wave system according to design parameters;
s12, designing an internal compression flow field by adopting a straight lip cover single wave system;
s13, obtaining a reference flow field which sequentially comprises three characteristic molded lines, namely a back free flow molded line OA, a compression surface molded line OB and a shock wave molded line OC from top to bottom;
s14, stretching the reference flow field perpendicular to a paper surface, namely a meridian plane and the like, to obtain a three-dimensional reference flow field taking a wave surface as a plane shock wave and a corresponding three-dimensional reference configuration, wherein the three-dimensional reference flow field comprises the following steps:
s1401, equivalently stretching the back free flow line OA perpendicular to the paper surface to obtain a free flow surface, and forming a back of a three-dimensional reference structure;
s1402, the compression surface line OB is vertical to the paper surface and the like and is stretched to obtain a precursor compression surface, and a bottom surface of a three-dimensional reference configuration is formed;
and S1403, stretching the shock wave line OC vertical to the paper surface to obtain a shock wave plane, and forming a wave plane of the three-dimensional reference configuration.
Further, in step S2, a sharp leading edge type triangular waverider precursor is obtained, specifically:
s21, controlling the shape of the sharp leading edge type triangular waverider precursor through an edge contour line, wherein the shape comprises the following steps:
s2101, obtaining a top view of the waverider precursor from above the three-dimensional reference configuration;
s2102, setting a triangular shape like a sharp leading edge on a top view, setting the shape of a side edge by using a mathematical method, and obtaining an edge projection line MON with a vertex O and end points M and N respectively, wherein M and N are symmetrical about OC, and OC is a symmetrical axis of MON;
s2103, projecting a projection line MON of the edge of the sharp leading edge type triangular waverider forebody to the forebody shock wave surface to obtain an edge contour line of the sharp leading edge type triangular waverider forebody;
s22, constructing a tangential plane with the extending direction parallel to the meridian plane according to the edge contour line MON of the tip leading edge type triangular waverider precursor and the three-dimensional reference configuration, and comprising the following steps:
s2201, forming a meridian plane OABC which sequentially comprises a back free flow type line OA, a compression plane type line OB and a shock wave type line OC from top to bottom, and forming a MONC shock wave plane which is a wave multiplication plane and is perpendicular to the lower plane of the meridian plane OABC;
s2202, translating the meridian plane OABC along OM or ON to enable O 1 、O 2 … always fall ON OM or ON, so as to obtain a series of tangential planes O parallel to meridian plane 1 A 1 B 1 C 1 、O 2 A 2 B 2 C 2 、…；
S2203, obtaining three molded lines O on each osculating plane 1 A 1 、O 1 B 1 、O 1 C 1 ，O 2 A 2 、O 2 B 2 、O 2 C 2 …, and O 1 A 1 ∥O 2 A 2 ∥…∥OA、O 1 B 1 ∥O 2 B 2 ∥…∥OB、O 1 C 1 ∥O 2 C 2 ∥…∥OC；
S23, forming a sharp front edge type triangular waverider precursor by the characteristic line set on the osculating plane, wherein the method comprises the following steps:
s2301, forming a back free-flow profile O 1 A 1 、O 2 A 2 、O 3 A 3 … to form the back surface of the wave multiplication precursor, i.e. the upstream surface;
s2302, compressing profile line O 1 B 1 、O 2 B 2 、O 3 B 3 … to form a bottom surface of the waverider precursor, i.e. a compression surface;
s2303, exciting the wave type line O 1 C 1 、O 2 C 2 、O 3 C 3 5363 and … to form a shock wave surface, i.e. the plane of the multiplied shock wave.
Further, in step S3, an integrated configuration of the front straight lip inlet with the sharp leading edge-like triangular waverider in the width range of the inlet is obtained, which specifically includes:
s31, designing the air inlet channel and the sharp front edge type triangular waverider precursor integrally, wherein the designing comprises the following steps:
s3101, an outer compression surface OD of the air inlet channel is collinear with a sharp front edge type triangular wave-multiplication precursor compression surface line OB, so that geometric integration of the precursor and the air inlet channel on the compression surface is realized;
s3102, the multiplied shock wave surface of the external compression shock wave of the air inlet and the sharp leading edge type triangular waverider precursor is intersected on the lip line of the air inlet at the point F, so that the aerodynamic integrated waverider design of the sharp leading edge type triangular waverider precursor and the air inlet is realized;
s3103, obtaining an air inlet compression surface reference flow field which sequentially comprises a back free flow molded line OA, an outer compression surface molded line ODB, an air inlet upper wall molded line ODE, a lower wall molded line FG, a shock wave molded line OFC and a lip point F on the shock wave molded line from top to bottom;
s32, constructing an air inlet channel on a tangential plane parallel to the meridian plane, and comprising:
s3201, constructing a meridian plane OFCBA including a back free flow molded line OA, an outer compression surface molded line ODB and a shock wave molded line OFC, and forming a lower plane MONC wave-multiplying plane vertical to the meridian plane OFCBA;
s3202, determining the capture height of the air inlet according to the capture flow and the capture width of the air inlet, and determining the position of a lip point F on the shock wave molded line OFC according to the capture height of the air inlet;
s3203, constructing a tangential plane profile of the straight lip inlet integrated structure of the sharp leading edge type triangular waverider-derived front body according to the meridian plane OFCBA and the edge profile MON of the sharp leading edge type triangular waverider-derived front body, wherein the tangential plane profile comprises the following components:
s320301, dividing the edge contour line MON into two sections, wherein one section is within the capture width range of the air inlet, and the rest are outside the capture width range of the air inlet;
s320302, when the air inlet channel capture width is not the same, generating a waverider configuration outside the air inlet channel capture width according to the steps S22 and S23;
s320303, when the width of the air inlet is within the range, generating a tight section molded line according to the following steps:
a. within the width range of the air inlet, any point O is selected on the contour line MON 1 O, O 1 And the tangential plane parallel to the meridian plane intersects with the lip line at F 1 Dot, F 1 Is positioned on the lip line and the shock plane MONC to obtain the shock wave profile line O of the current osculating plane 1 F 1 ；
The meridian lines on the meridian plane are arranged along FF 1 Is translated to F 1 Point by point to obtain peroxy O 1 A section of a point; on the current section of osculating with F 1 For reference point, the profile line related to the air inlet on the current osculating plane is all divided by a factor O 1 F 1 Updating the/OF similar scaling to obtain the back free flow profile O on the current osculating plane 1 A 1 Outer compression profile line O 1 D 1 B 1 Upper wall profile O of air inlet duct 1 D 1 E 1 Lower wall profile F 1 G 1 Shock line O 1 F 1 C 1 ；
b. Traversing the contour line MON in the width of the air inlet, obtaining a tangent plane passing through the On point for any one point On of the contour line MON, and changing the scaling factor into O n F n OF obtaining PerO n Back free flow line O of point dense section n A n Outer compression surface profile line O n D n B n Upper wall profile O of air inlet duct n D n E n Lower wall profile F n G n Shock line O n F n C n N is the nth point on the contour line MON within the width range of the air inlet, and n is more than or equal to 2;
s33, within the width range of the air inlet, combining the molded lines on all the osculating planes to obtain the integrated configuration of the front straight lip air inlet with the sharp front edge type triangular waverider within the width range of the air inlet.
Further, in step S4, an integrated configuration of a front straight lip inlet with a sharp leading edge-like triangular waverider in a full-width range is generated, specifically:
s41, combining the configuration inside the width of the air inlet channel with the configuration of the precursor outside the width of the air inlet channel;
s42, stretching the outer wall surface of the lip cover within the width range of the air inlet along the lip opening line;
s43, generating side plates on two sides of an inner channel of the air inlet channel;
and S44, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
The invention can achieve the following effects: (1) the front edge of the precursor adopts a sharp front edge, so that the resistance of the aircraft can be effectively reduced; (2) the precursor adopts a waverider design, so that the lift characteristic of the precursor can be further improved; (3) the front body and the air inlet channel are integrally designed and jointly multiplied by waves, so that the aerodynamic performance of the whole configuration is improved, and the capture performance of the air inlet channel is effectively improved; (4) the common wave multiplied by the front body and the air inlet channel is a plane shock wave, so that the lip opening front edge line is kept straight and is possible and necessary; (5) the lip of the air inlet is designed into a straight front edge, which is more beneficial to the processing and the heat-proof structure design. The technology of the invention adopts a two-dimensional precursor air inlet integrated characteristic line as a meridian plane reference line, adopts a top view projection to control the edge profile of a sharp leading edge type triangular precursor, constructs each section according to a parallel close idea, and uses the shock wave length corresponding to an air inlet on the section as a size target, thereby developing the integrated design of a sharp leading edge type triangular waverider precursor straight lip air inlet, solving the design problem of a hypersonic aerocraft precursor air inlet of a similar IgLa configuration, and enabling the configuration to have the advantages of large lifting force of a waverider and high flow capture of the waverider air inlet compared with the IgLa configuration.
Drawings
Fig. 1 is a schematic diagram of a binary planar reference flow field corresponding to step S1 of the present invention.
Fig. 2 is a schematic diagram of the profile of the reference flow field corresponding to step S13 in the present invention.
Fig. 3 is a schematic diagram of a front contour line of a sharp leading edge type triangular waverider corresponding to step S21 of the present invention.
Fig. 4 is a schematic view of a meridian plane of the sharp leading edge triangular waverider-like precursor corresponding to step S2201 of the present invention.
Fig. 5 is a schematic diagram of a tangential plane with the spanwise direction parallel to the meridian plane and a sharp leading-edge triangle-like waverider precursor corresponding to steps S22 and S23 of the present invention.
Fig. 6 is a schematic view of the integrated design of the air inlet channel and the sharp leading edge triangular waverider-like precursor corresponding to step S31 in the present invention.
Fig. 7 is a schematic diagram of the air inlet channel constructed on the tangential plane parallel to the meridian plane in step S32 according to the present invention.
Fig. 8 shows an integrated configuration of a sharp leading edge triangle-like waverider-like forebody straight lip inlet in the full width range corresponding to step S4.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention.
The invention is described in further detail below with reference to the following figures and embodiments:
example 1
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to the reference configuration of the compression plane of the air inlet, compressing and horizontally positioning the compression plane profile of the air inlet on the tangential plane, and combining the set of the compression plane profile and the precursor characteristic profile to obtain the integrated configuration of the sharp front edge triangular waverider-like precursor straight lip air inlet in the width range of the air inlet;
and S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Example 2
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s1 specifically comprises the following steps:
s11, distributing waves for the external compression flow field by adopting a shock wave and isentropic wave system according to design parameters;
s12, designing an internal compression flow field by adopting a straight lip cover single wave system;
s13, obtaining a reference flow field which sequentially comprises three characteristic molded lines, namely a back free flow molded line OA, a compression surface molded line OB and a shock wave molded line OC from top to bottom;
s14, stretching the reference flow field perpendicular to a paper surface, namely a meridian plane and the like, to obtain a three-dimensional reference flow field taking a wave surface as a plane shock wave and a corresponding three-dimensional reference configuration, wherein the three-dimensional reference flow field comprises the following steps:
s1401, equivalently stretching the back free flow line OA perpendicular to the paper surface to obtain a free flow surface, and forming a back of a three-dimensional reference structure;
s1402, the compression surface line OB is vertical to the paper surface and the like and is stretched to obtain a precursor compression surface, and a bottom surface of a three-dimensional reference configuration is formed;
and S1403, stretching the shock wave molded line OC vertical to the paper surface to obtain a shock wave plane, and forming a wave multiplication plane of the three-dimensional reference configuration.
S2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, zooming and translating and positioning the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge triangle-like waverider precursor, and forming the sharp leading edge triangle-like waverider precursor by the collection of the characteristic molded lines;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to an air inlet compression plane reference configuration, scaling and horizontally moving and positioning compression plane profiles of the air inlet on the tangential plane, and combining a set of the compression plane profiles with a precursor characteristic profile to obtain a sharp front edge triangular multiplier wave-like precursor straight lip air inlet integrated configuration in an air inlet width range;
and S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Example 3
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s2 specifically comprises the following steps:
s21, controlling the shape of the sharp leading edge type triangular waverider precursor through an edge contour line, wherein the shape comprises the following steps:
s2101, obtaining a top view of the waverider precursor from above the three-dimensional reference configuration;
s2102, setting a triangular shape like a sharp leading edge on a top view, setting the shape of a side edge by using a mathematical method, and obtaining an edge projection line MON with a vertex O and end points M and N respectively, wherein M and N are symmetrical about OC, and OC is a symmetrical axis of MON;
s2103, projecting a projection line MON of the edge of the sharp leading edge type triangular waverider forebody to the forebody shock wave surface to obtain an edge contour line of the sharp leading edge type triangular waverider forebody;
s22, constructing a tangential plane with the expansion direction parallel to the meridian plane according to the edge contour line MON and the three-dimensional reference configuration of the tip-leading edge type triangular waverider-like precursor, and comprising the following steps of:
s2201, forming a meridian plane OABC which sequentially comprises a back free flow type line OA, a compression plane type line OB and a shock wave type line OC from top to bottom, and forming a MONC shock wave plane which is a wave multiplication plane and is perpendicular to the lower plane of the meridian plane OABC;
s2202, translating the meridian plane OABC along OM or ON to enable O 1 、O 2 … always fall ON OM or ON, so as to obtain a series of tangential planes O parallel to meridian plane 1 A 1 B 1 C 1 、O 2 A 2 B 2 C 2 、…；
S2203, obtaining three molded lines O on each osculating plane 1 A 1 、O 1 B 1 、O 1 C 1 ，O 2 A 2 、O 2 B 2 、O 2 C 2 …, and O 1 A 1 ∥O 2 A 2 ∥…∥OA、O 1 B 1 ∥O 2 B 2 ∥…∥OB、O 1 C 1 ∥O 2 C 2 ∥…∥OC；
S23, forming a sharp front edge type triangular waverider precursor by the characteristic line set on the osculating plane, wherein the method comprises the following steps:
s2301, forming a back free-flow profile O 1 A 1 、O 2 A 2 、O 3 A 3 … to form the back surface of the wave multiplication precursor, i.e. the upstream surface;
s2302 to compress profile line O 1 B 1 、O 2 B 2 、O 3 B 3 … to form the bottom surface of the wave rider precursor, namely the compression surface;
s2303, exciting the wave type line O 1 C 1 、O 2 C 2 、O 3 C 3 … to form a shock surface, i.e., a plane of the multiplied shock.
S3, constructing an air inlet on a tangential plane parallel to a meridian plane according to the reference configuration of the compression plane of the air inlet, compressing and horizontally positioning the compression plane profile of the air inlet on the tangential plane, and combining the set of the compression plane profile and the precursor characteristic profile to obtain the integrated configuration of the sharp front edge triangular waverider-like precursor straight lip air inlet in the width range of the air inlet;
and S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Example 4
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to an air inlet compression plane reference configuration, scaling and horizontally moving and positioning compression plane profiles of the air inlet on the tangential plane, and combining a set of the compression plane profiles with a precursor characteristic profile to obtain a sharp front edge triangular multiplier wave-like precursor straight lip air inlet integrated configuration in an air inlet width range;
s3 specifically comprises the following steps:
s31, designing the air inlet channel and the sharp front edge type triangular waverider precursor integrally, wherein the designing comprises the following steps:
s3101, an outer compression surface OD of the air inlet channel is collinear with a sharp front edge type triangular wave-multiplication precursor compression surface line OB, so that geometric integration of the precursor and the air inlet channel on the compression surface is realized;
s3102, the multiplied shock wave surface of the external compression shock wave of the air inlet and the sharp leading edge type triangular waverider precursor is intersected on the lip line of the air inlet at the point F, so that the aerodynamic integrated waverider design of the sharp leading edge type triangular waverider precursor and the air inlet is realized;
s3103, obtaining an air inlet compression surface reference flow field which sequentially comprises a back free flow molded line OA, an outer compression surface molded line ODB, an air inlet upper wall molded line ODE, a lower wall molded line FG, a shock wave molded line OFC and a lip point F on the shock wave molded line from top to bottom;
s32, constructing an air inlet channel on a tangential plane parallel to the meridian plane, and comprising:
s3201, constructing a meridian plane OFCBA including a back free flow profile OA, an outer compression plane profile ODB and a shock wave profile OFC, and a lower plane MONC wave multiplication plane vertical to the meridian plane OFCBA;
s3202, determining the capture height of the air inlet according to the capture flow and the capture width of the air inlet, and determining the position of a lip point F on the shock wave molded line OFC according to the capture height of the air inlet;
s3203, constructing a tangential plane profile of the straight lip inlet integrated structure of the sharp leading edge type triangular waverider-derived front body according to the meridian plane OFCBA and the edge profile MON of the sharp leading edge type triangular waverider-derived front body, wherein the tangential plane profile comprises the following components:
s320301, dividing the edge contour line MON into two sections, wherein one section is within the capture width range of the air inlet, and the rest are outside the capture width range of the air inlet;
s320302, when the air inlet channel capture width is not the same, generating a waverider configuration outside the air inlet channel capture width according to the steps S22 and S23;
s320303, when the width of the air inlet is within the range, generating a tight section molded line according to the following steps:
a. within the width range of the air inlet, any point O is selected on the contour line MON 1 O to O 1 And the tangential plane parallel to the meridian plane intersects with the lip line at F 1 Dot, F 1 Is positioned on the lip line and on the shock plane MONC to obtain the shock wave molded line O of the current osculating plane 1 F 1 ；
The meridian lines on the meridian plane are arranged along FF 1 Translate to F 1 Point by point to obtain peroxy O 1 A section of a point; on the current section of osculating with F 1 For reference point, the profile lines related to the air inlet on the current osculating plane are all divided by a factor O 1 F 1 Updating the/OF similar scaling to obtain the back free flow profile O on the current osculating plane 1 A 1 Outer compression surface profile line O 1 D 1 B 1 Upper wall profile O of air inlet duct 1 D 1 E 1 Lower wall profile F 1 G 1 Shock wave line O 1 F 1 C 1 ；
b. Traversing the contour line MON in the width of the air inlet, obtaining a tangent plane passing through the On point for any point On of the contour line MON, and changing the scaling factor into O n F n OF obtaining PerO n Back free flow line O of point dense section n A n Outer compression profile line O n D n B n Upper wall profile O of air inlet duct n D n E n Lower wall profile F n G n Shock wave line O n F n C n N is the nth point on the contour line MON within the width range of the air inlet, and n is more than or equal to 2;
s33, within the width range of the air inlet, combining the molded lines on all the osculating planes to obtain the integrated configuration of the front straight lip air inlet with the sharp front edge type triangular waverider within the width range of the air inlet.
And S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Example 5
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to the reference configuration of the compression plane of the air inlet, compressing and horizontally positioning the compression plane profile of the air inlet on the tangential plane, and combining the set of the compression plane profile and the precursor characteristic profile to obtain the integrated configuration of the sharp front edge triangular waverider-like precursor straight lip air inlet in the width range of the air inlet;
and S4, generating an integrated structure of the front straight lip inlet of the sharp front edge type triangular waverider in a full-width range.
S4 specifically comprises the following steps:
s41, combining the configuration inside the width of the air inlet channel with the configuration of the precursor outside the width of the air inlet channel;
s42, stretching the outer wall surface of the lip cover within the width range of the air inlet along the lip line;
s43, generating side plates on two sides of an inner channel of the air inlet channel;
and S44, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
Example 6
The embodiment provides an integrated design method for a front straight lip inlet with a sharp leading edge and a triangular waverider, which comprises the following design steps:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s11, distributing waves to the external compression flow field by adopting a shock wave and isentropic wave system according to design parameters;
s12, designing an internal compression flow field by adopting a straight lip cover single wave system;
s13, obtaining a reference flow field which sequentially comprises three characteristic molded lines, namely a back free flow molded line OA, a compression surface molded line OB and a shock wave molded line OC from top to bottom;
s14, stretching the reference flow field perpendicular to a paper surface, namely a meridian plane and the like, to obtain a three-dimensional reference flow field taking a wave surface as a plane shock wave and a corresponding three-dimensional reference configuration, wherein the three-dimensional reference flow field comprises the following steps:
s1401, equivalently stretching the back free flow line OA perpendicular to the paper surface to obtain a free flow surface, and forming a back of a three-dimensional reference structure;
s1402, the compression surface line OB is vertical to the paper surface and the like and is stretched to obtain a precursor compression surface, and a bottom surface of a three-dimensional reference configuration is formed;
and S1403, stretching the shock wave molded line OC vertical to the paper surface to obtain a shock wave plane, and forming a wave multiplication plane of the three-dimensional reference configuration.
S2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s21, controlling the shape of the sharp leading edge type triangular waverider precursor through an edge contour line, wherein the shape comprises the following steps:
s2101, a plan view of the waverider precursor viewed from above the three-dimensional reference configuration;
s2102, setting a sharp leading edge triangle-like shape on a top view, setting a side edge shape by using a mathematical method, and obtaining an edge projection line MON with a vertex O and end points M and N respectively, wherein M and N are symmetrical about OC, and OC is a symmetrical axis of MON;
s2103, projecting a projection line MON of the edge of the sharp leading edge type triangular waverider forebody to the forebody shock wave surface to obtain an edge contour line of the sharp leading edge type triangular waverider forebody;
s22, constructing a tangential plane with the expansion direction parallel to the meridian plane according to the edge contour line MON and the three-dimensional reference configuration of the tip-leading edge type triangular waverider-like precursor, and comprising the following steps of:
s2201, forming a meridian plane OABC which sequentially comprises a back free flow type line OA, a compression plane type line OB and a shock wave type line OC from top to bottom, and forming a MONC shock wave plane which is a wave multiplication plane and is perpendicular to the lower plane of the meridian plane OABC;
s2202 translating the meridian plane OABC along OM or ON so that O 1 、O 2 … always fall ON OM or ON, so as to obtain a series of tangential planes O parallel to meridian plane 1 A 1 B 1 C 1 、O 2 A 2 B 2 C 2 、…；
S2203, obtaining three molded lines O on each osculating plane 1 A 1 、O 1 B 1 、O 1 C 1 ，O 2 A 2 、O 2 B 2 、O 2 C 2 …, and O 1 A 1 ∥O 2 A 2 ∥…∥OA、O 1 B 1 ∥O 2 B 2 ∥…∥OB、O 1 C 1 ∥O 2 C 2 ∥…∥OC；
S23, forming a sharp front edge type triangular waverider precursor by the characteristic line set on the osculating plane, wherein the method comprises the following steps:
s2301, forming a back free-flow profile O 1 A 1 、O 2 A 2 、O 3 A 3 … to form the back surface of the wave multiplication precursor, i.e. the upstream surface;
s2302, compressing profile line O 1 B 1 、O 2 B 2 、O 3 B 3 … to form a bottom surface of the waverider precursor, i.e. a compression surface;
s2303, exciting the wave type line O 1 C 1 、O 2 C 2 、O 3 C 3 5363 and … to form a shock wave surface, i.e. the plane of the multiplied shock wave.
S3, constructing an air inlet on a tangential plane parallel to a meridian plane according to the reference configuration of the compression plane of the air inlet, compressing and horizontally positioning the compression plane profile of the air inlet on the tangential plane, and combining the set of the compression plane profile and the precursor characteristic profile to obtain the integrated configuration of the sharp front edge triangular waverider-like precursor straight lip air inlet in the width range of the air inlet;
s31, designing the air inlet channel and the sharp front edge type triangular waverider precursor integrally, wherein the designing comprises the following steps:
s3101, an outer compression surface OD of the air inlet channel is collinear with a sharp front edge type triangular wave-multiplication precursor compression surface line OB, so that geometric integration of the precursor and the air inlet channel on the compression surface is realized;
s3102, the multiplied shock wave surface of the external compression shock wave of the air inlet and the sharp leading edge type triangular waverider precursor is intersected on the lip line of the air inlet at the point F, so that the aerodynamic integrated waverider design of the sharp leading edge type triangular waverider precursor and the air inlet is realized;
s3103, obtaining an air inlet compression surface reference flow field which sequentially comprises a back free flow molded line OA, an outer compression surface molded line ODB, an air inlet upper wall molded line ODE, a lower wall molded line FG, a shock wave molded line OFC and a lip point F on the shock wave molded line from top to bottom;
s32, constructing an air inlet channel on a tangential plane parallel to the meridian plane, and comprising:
s3201, constructing a meridian plane OFCBA including a back free flow molded line OA, an outer compression surface molded line ODB and a shock wave molded line OFC, and forming a lower plane MONC wave-multiplying plane vertical to the meridian plane OFCBA;
s3202, determining the capture height of the air inlet according to the capture flow and the capture width of the air inlet, and determining the position of a lip point F on the shock wave molded line OFC according to the capture height of the air inlet;
s3203, constructing a tangential plane profile of the straight lip inlet integrated structure of the sharp leading edge type triangular waverider-derived front body according to the meridian plane OFCBA and the edge profile MON of the sharp leading edge type triangular waverider-derived front body, wherein the tangential plane profile comprises the following components:
s320301, dividing the edge contour line MON into two sections, wherein one section is within the capture width range of the air inlet, and the rest are outside the capture width range of the air inlet;
s320302, when the air inlet channel capture width is not the same, generating a waverider configuration outside the air inlet channel capture width according to the steps S22 and S23;
s320303, when the width of the air inlet is within the range, generating a tight tangent plane molded line according to the following steps:
a. within the width of the inlet, an arbitrary point O is selected on the profile MON 1 O to O 1 And the tangential plane parallel to the meridian plane intersects with the lip line at F 1 Point, F 1 Is positioned on the lip line and on the shock plane MONC to obtain the shock wave molded line O of the current osculating plane 1 F 1 ；
The meridian lines on the meridian plane are arranged along FF 1 Is translated to F 1 Point by point to obtain peroxy O 1 A section of a spot; on the current section of osculating with F 1 For reference point, the profile lines related to the air inlet on the current osculating plane are all divided by a factor O 1 F 1 Updating the/OF similar scaling to obtain the back free flow profile O on the current osculating plane 1 A 1 Outer compression surface profile line O 1 D 1 B 1 Upper wall profile O of air inlet duct 1 D 1 E 1 Lower wall profile F 1 G 1 Shock line O 1 F 1 C 1 ；
b. Traversing the contour line MON in the width of the air inlet, obtaining a tangent plane passing through the On point for any one point On of the contour line MON, and changing the scaling factor into O n F n OF obtaining PerO n Back free flow line O of point dense section n A n Outer compression surface profile line O n D n B n Upper wall profile O of air inlet duct n D n E n Lower wall profile F n G n Shock line O n F n C n N is the nth point on the contour line MON within the width range of the air inlet, and n is more than or equal to 2;
s33, within the width range of the air inlet, combining the molded lines on all the osculating planes to obtain the integrated configuration of the front straight lip air inlet with the sharp front edge type triangular waverider within the width range of the air inlet.
And S4, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
S41, combining the configuration inside the width of the air inlet channel with the configuration of the precursor outside the width of the air inlet channel;
s42, stretching the outer wall surface of the lip cover within the width range of the air inlet along the lip opening line;
s43, generating side plates on two sides of an inner channel of the air inlet channel;
and S44, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
The following description is made with reference to the accompanying drawings:
FIG. 1 is a schematic view of a binary planar reference flow field corresponding to step S1 of the present invention; as shown in fig. 1, the reference flow field is a binary planar compression integrated flow field. The integrated flow field is divided into an outer compression flow field and an inner compression flow field, the outer compression flow field can adopt a shock wave + isentropic wave system for wave matching, or a multichannel shock wave system for wave matching, but the first compression of the outer compression flow field comes from a wave rider precursor, so that the precursor and the outer compression of the air inlet channel form an integrated design; the wave matching of the internal compression flow field can also adopt shock wave + iso-entropy wave or multi-channel shock wave to carry out wave matching. The external flow field adopts a design method of 'shock wave + iso-entropy wave', and the method can ensure that the compression surface of the precursor and the air inlet channel is naturally and smoothly transited; to simplify the non-critical portion, the internal flow field of the present invention uses a straight lip mask simplex wave system design (its lip leading edge line will also be straight).
FIG. 2 is a schematic view of a reference flow field profile corresponding to step S13 of the present invention; as shown in fig. 2, the reference flow field is stretched backward from the point O along the free flow direction, so as to obtain a reference flow field including a back free flow profile OA, a compression profile OB, and a shock profile OC in this order from top to bottom.
FIG. 3 is a schematic diagram of a front contour line of a sharp leading edge type triangular waverider corresponding to step S21 of the present invention; as shown in fig. 3, a top view of the waverider precursor viewed from above the three-dimensional reference pattern is provided, a sharp leading edge triangle-like shape is provided in the top view, and a side edge shape is mathematically provided to control the sharp leading edge triangle-like waverider shape. The invention adopts a second-order Bezier curve for control, firstly sets a point O and a point M (or a point N which is a symmetrical point of the point M), then sets a tangent direction at the point O, sets a tangent direction at the point M (or the point N), and takes the intersection point of two tangents as a Bezier line control point, thereby obtaining the projection of the sharp leading edge type triangular waverider precursor edge MON in a top view.
And projecting the projection line of the sharp leading edge type triangular waverider precursor edge to the precursor shock wave surface along the plane view direction to obtain an edge contour line of the sharp leading edge type triangular waverider precursor.
FIG. 4 is a schematic meridian plane of a sharp leading edge triangle-like waverider corresponding to step S2201; as shown in fig. 4, a meridian plane and a shock wave plane of the sharp leading edge type triangular waverider precursor are given. The plane OABC is a meridian plane, and the meridian plane comprises three characteristic lines: OA is a back free flow profile, OB is a compression profile, OC is a shock profile, and a plane MONC perpendicular to the plane OABC in the figure is a shock plane (plane where OM, ON and OC are located).
FIG. 5 is a schematic diagram of a truncated pyramid and a sharp leading-edge triangle-like waverider precursor with the spanwise direction parallel to the meridian plane according to steps S22 and S23 of the present invention; as shown in fig. 5, a tangential plane whose spanwise direction is parallel to the meridian plane is constructed, and the characteristic lines on the tangential plane are combined to obtain a tip-leading-edge triangle-like waverider precursor.
a. Translating the meridian plane OABC along the OM to make the point O always fall on the OM, thereby obtaining a series of tangential planes O parallel to the meridian plane 1 A 1 B 1 C 1 、O 2 A 2 B 2 C 2 、…。
b. Three characteristic lines O on each osculating plane 1 A 1 、O 1 B 1 、O 1 C 1 ，O 2 A 2 、O 2 B 2 、O 2 C 2 …, three characteristic lines OA, OB, OC, respectively, parallel to each other and to the meridian plane.
c. Mixing O with 1 A 1 、O 2 A 2 、O 3 A 3 … to obtain the back surface of the wave-rider precursor, namely the free flow surface; mixing O with 1 B 1 、O 2 B 2 、O 3 B 3 … to obtain the lower surface of the wave multiplication precursor, namely the compression surface; in fact, mixing O 1 C 1 、O 2 C 2 、O 3 C 3 … are combined to obtain the multiplied stimulusThe wavefront, and thus the precursor configuration and the multiplied shock wave, is obtained.
FIG. 6 is a schematic diagram illustrating the integrated design of the air inlet channel and the sharp leading edge triangular waverider-like precursor in step S31; as shown in fig. 6, the integrated design of the inlet and the waverider precursor is represented by:
an outer compression surface OD of the air inlet channel is collinear with a sharp front edge type triangular waverider precursor compression surface molded line OB, so that the geometric integration of the precursor and the air inlet channel on the compression surface is realized;
and the compression shock wave outside the air inlet channel and the precursor shock wave are crossed on the lip line where the point F is positioned, so that the integrated wave rider design of the precursor and the air inlet channel on the pneumatic aspect is realized.
And obtaining a reference flow field structure of the compression surface of the air inlet passage, wherein a lip cover outer wall profile FH is also given.
FIG. 7 is a schematic view of the present invention in which the air inlet channel is constructed on the tangential plane parallel to the meridian plane in step S32; as shown in fig. 7, the inlet channels are constructed in tangential planes parallel to the meridian plane:
the precursor inlet meridian profile is illustrated. The plane OFCBA is the meridian plane of the integrated configuration, and MON is the shock plane (also the shock plane of the inlet channel) multiplied by the precursor. On the meridian plane OFCBA plane, the characteristic lines included are respectively: a back free flow surface profile OA, an integrally configured precursor outer compression surface profile ODB, a shock surface profile OFC. Where point F is determined by the capture height of the precursor inlet channel, which is determined by the capture flow of the inlet channel in combination with the capture width.
According to the meridian plane reference configuration of the air inlet and the side edge line OM (or ON) of the front body, a section line of a tangent plane of the front body straight lip air inlet integrated configuration of the sharp front edge type triangular waverider is constructed.
The OM is divided into two sections, one section is within the width range of the air inlet, and the rest is outside the width range of the air inlet. When the air inlet width range is out of the range, the wave rider configuration is generated according to the steps S23 and S24. When the width of the air inlet channel is within the range, the dense section molded line is generated according to the following steps.
a. Let O 1 Setting O for any point on OM within the width range of the air inlet 1 And the tangential plane parallel to the meridian plane intersects with the lip line at F 1 . Then F 1 Necessarily on the lip line, i.e. on the plane of the shock wave, thus O 1 F 1 Namely the shock wave profile of the current osculating plane.
b. All molded lines on the current meridian plane are along FF 1 Is translated to F 1 Point to obtain the current pass O 1 A section of a point; on the current section of osculating with F 1 For reference point, the profile lines related to the air inlet on the current osculating plane are all divided by a factor O 1 F 1 the/OF is updated by similar scaling, and then various profiles (such as wall profile O) OF the upper air inlet channel OF the current dense section are obtained 1 D 1 E 1 、F 1 G 1 Shock line O 1 F 1 ）。
c. In the width range of the air inlet, another point O is taken on the OM 2 Repeating the above process (scaling factor to O) 2 F 2 OF) to obtain the inlet profile on the other osculating plane. The air inlet molded lines on all the osculating planes (the molded line on the width position of the air inlet is O) are obtained by traversing each osculating plane in the width of the air inlet n D n E n 、F n G n 、O n F n ，n≥2）。
Within the width range of the air inlet, the molded lines of the air inlet on all the osculating planes are combined to obtain the integrated configuration of the front straight lip air inlet with the sharp front edge type triangular waverider within the width range of the air inlet.
Fig. 8 shows an integrated configuration of a sharp leading edge triangle-like waverider-like front body straight lip inlet in the full width range corresponding to step S4. As shown in fig. 8, a full-width, sharp-leading-edge triangle-like waverider-like front body straight lip inlet integrated configuration is generated:
the configuration within the width of the air inlet channel and the front body configuration outside the width of the air inlet channel are combined, the outer wall surface of the lip cover is stretched within the width range of the air inlet channel along the lip line (so that the outer wall surface of the lip cover is a regular profile), and meanwhile, the side plates on two sides of the channel in the air inlet channel are generated, and the integrated configuration of the front body straight lip air inlet channel with the sharp front edge type triangular waverider within the whole width range is obtained.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and scope of the present invention as defined in the appended claims.

Claims (1)

1. A method for integrally designing a straight lip inlet of a front body of a sharp leading edge type triangular waverider is characterized by comprising the following steps of:
s1, designing a binary plane reference flow field to obtain three characteristic molded lines including a back free flow molded line, a compression surface molded line and a shock wave molded line on a meridian plane;
s2, constructing a tangential plane with the spanwise direction parallel to the meridian plane, and zooming and translating the characteristic molded lines on the tangential plane according to the edge lines of the sharp leading edge type triangular waverider precursor, wherein the characteristic molded lines are integrated to form the sharp leading edge type triangular waverider precursor;
s3, constructing an air inlet on a tangential plane parallel to a meridian plane according to the reference configuration of the compression plane of the air inlet, compressing and horizontally positioning the compression plane profile of the air inlet on the tangential plane, and combining the set of the compression plane profile and the precursor characteristic profile to obtain the integrated configuration of the sharp front edge triangular waverider-like precursor straight lip air inlet in the width range of the air inlet;
s4, generating a straight lip inlet integrated configuration of the front body of the sharp front edge type triangular waverider in the full-width range;
the binary plane reference flow field design in the step S1 specifically includes:
s11, distributing waves for the external compression flow field by adopting a shock wave and isentropic wave system according to design parameters;
s12, designing an internal compression flow field by adopting a straight lip cover single wave system;
s13, obtaining a reference flow field which sequentially comprises three characteristic molded lines, namely a back free flow molded line OA, a compression surface molded line OB and a shock wave molded line OC from top to bottom;
s14, stretching the reference flow field perpendicular to a paper surface, namely a meridian plane and the like, to obtain a three-dimensional reference flow field taking a wave surface as a plane shock wave and a corresponding three-dimensional reference configuration, wherein the three-dimensional reference flow field comprises the following steps:
s1401, equivalently stretching the back free flow line OA perpendicular to the paper surface to obtain a free flow surface, and forming a back of a three-dimensional reference structure;
s1402, the compression surface line OB is vertical to the paper surface and the like and is stretched to obtain a precursor compression surface, and a bottom surface of a three-dimensional reference configuration is formed;
s1403, stretching a shock wave molded line OC vertical to a paper surface to obtain a shock wave plane, and forming a wave plane of a three-dimensional reference configuration;
in step S2, a sharp leading edge type triangular waverider precursor is formed, specifically:
s21, controlling the shape of the sharp leading edge type triangular waverider precursor through an edge contour line, wherein the shape comprises the following steps:
s2101, obtaining a top view of the waverider precursor from above the three-dimensional reference configuration;
s2102, setting a triangular shape like a sharp leading edge on a top view, setting the shape of a side edge by using a mathematical method, and obtaining an edge projection line MON with a vertex O and end points M and N respectively, wherein M and N are symmetrical about OC, and OC is a symmetrical axis of MON;
s2103, projecting an edge projection line MON of the sharp leading edge type triangular waverider precursor to a front body shock wave surface to obtain an edge contour line of the sharp leading edge type triangular waverider precursor;
s22, constructing a tangential plane with the extending direction parallel to the meridian plane according to the edge projection line MON of the tip leading edge type triangular waverider precursor and the three-dimensional reference configuration, and comprising the following steps:
s2201, forming a meridian plane OABC which sequentially comprises three molded lines including a back free flow molded line OA, a compression surface molded line OB and a shock wave molded line OC from top to bottom, and forming a plane MONC shock wave surface which is perpendicular to the meridian plane OABC and is a wave multiplication surface;
s2202 translating the meridian plane OABC along OM or ON so that O 1 、O 2 … always fall ON OM or ON, so as to obtain a series of tangential planes O parallel to meridian plane 1 A 1 B 1 C 1 、O 2 A 2 B 2 C 2 、…；
S2203, obtaining three molded lines O on each osculating plane 1 A 1 、O 1 B 1 、O 1 C 1 ，O 2 A 2 、O 2 B 2 、O 2 C 2 …, and O 1 A 1 ∥O 2 A 2 ∥…∥OA、O 1 B 1 ∥O 2 B 2 ∥…∥OB、O 1 C 1 ∥O 2 C 2 ∥…∥OC；
S23, forming a sharp front edge type triangular waverider precursor by the characteristic line set on the osculating plane, wherein the method comprises the following steps:
s2301, forming a back free-flow profile O 1 A 1 、O 2 A 2 、O 3 A 3 … to form the back surface of the wave rider precursor, i.e. the upstream surface;
s2302 to compress profile line O 1 B 1 、O 2 B 2 、O 3 B 3 … to form a bottom surface of the waverider precursor, i.e. a compression surface;
s2303, exciting the wave type line O 1 C 1 、O 2 C 2 、O 3 C 3 … to form a shock wave surface, i.e. a multiplied shock wave plane;
in the step S3, an integrated configuration of a sharp leading edge type triangular waverider front body straight lip inlet in the width range of the inlet is obtained, which specifically comprises the following steps:
s31, designing the air inlet channel and the sharp front edge type triangular waverider precursor integrally, wherein the designing comprises the following steps:
s3101, an outer compression surface OD of the air inlet channel is collinear with a sharp front edge type triangular wave-multiplication precursor compression surface line OB, so that geometric integration of the precursor and the air inlet channel on the compression surface is realized;
s3102, the multiplied shock wave surface of the sharp front edge type triangular waverider forebody intersects the multiplied shock wave surface of the sharp front edge type triangular waverider forebody on the lip line of the air inlet at the point F, so that the integrated waverider design of the sharp front edge type triangular waverider forebody and the air inlet in the pneumatic direction is realized;
s3103, obtaining an air inlet compression surface reference flow field which sequentially comprises a back free flow molded line OA, an outer compression surface molded line ODB, an air inlet upper wall molded line ODE, a lower wall molded line FG, a shock wave molded line OFC and a lip point F on the shock wave molded line from top to bottom;
s32, constructing an air inlet channel on a tangential plane parallel to the meridian plane, and comprising:
s3201, constructing a meridian plane OFCBA including a back free flow molded line OA, an outer compression surface molded line ODB and a shock wave molded line OFC, and forming a lower plane MONC wave-multiplying plane vertical to the meridian plane OFCBA;
s3202, determining the capture height of the air inlet according to the capture flow and the capture width of the air inlet, and determining the position of a lip point F on the shock wave molded line OFC according to the capture height of the air inlet;
s3203, constructing a tangential plane profile of the straight lip inlet integrated structure of the sharp leading edge type triangular waverider-derived front body according to the meridian plane OFCBA and the edge profile MON of the sharp leading edge type triangular waverider-derived front body, wherein the tangential plane profile comprises the following components:
s320301, dividing the edge contour line MON into two sections, wherein one section is within the capture width range of the air inlet, and the rest are outside the capture width range of the air inlet;
s320302, when the air inlet channel capture width is not the same, generating a waverider configuration outside the air inlet channel capture width according to the steps S22 and S23;
s320303, when the width of the air inlet is within the range, generating a tight section molded line according to the following steps:
a. within the width of the inlet, an arbitrary point O is selected on the profile MON 1 O, O 1 And the tangential plane parallel to the meridian plane intersects with the lip line at F 1 Point, F 1 Is positioned on the lip line and on the shock plane MONC to obtain the shock wave molded line O of the current osculating plane 1 F 1 ；
The meridian lines on the meridian plane are arranged along FF 1 Is translated to F 1 Point by point to obtain peroxy O 1 A section of a spot; on the current section of osculating with F 1 For reference point, the profile lines related to the air inlet on the current osculating plane are all divided by a factor O 1 F 1 Updating the/OF similar scaling to obtain the back free flow profile O on the current osculating plane 1 A 1 Outer compression surface profile line O 1 D 1 B 1 Upper wall profile O of air inlet duct 1 D 1 E 1 Lower wall profile F 1 G 1 Shock wave line O 1 F 1 C 1 ；
b. Traversing the contour line MON in the width of the air inlet, and for any point O on the contour line MON n To obtain peroxy O n The tangent plane of the point, scaling factor becomes O n F n OF obtaining PerO n Back free flow line O of point dense section n A n Outer compression profile line O n D n B n Upper wall profile O of air inlet duct n D n E n Lower wall profile F n G n Shock wave line O n F n C n N is the nth point on the contour line MON within the width range of the air inlet, and n is more than or equal to 2;
s33, combining the molded lines on all the osculating planes within the width range of the air inlet to obtain an integrated configuration of the front straight lip air inlet with the sharp front edge type triangular waverider within the width range of the air inlet;
in step S4, a straight lip inlet integrated configuration of the sharp leading edge type triangular waverider-like precursor in the full-width range is generated, specifically:
s41, combining the configuration inside the width of the air inlet and the configuration of the precursor outside the width of the air inlet;
s42, stretching the outer wall surface of the lip cover within the width range of the air inlet along the lip opening line;
s43, generating side plates on two sides of an inner channel of the air inlet channel;
and S44, generating a straight lip inlet integrated structure of the front body of the sharp front edge type triangular waverider in the full-width range.
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