Full Multi-Wavelet Inviscid-Viscoid Flow Integration and Design Method Based on Local Deflection Kiss-Cutting Theory

Abstract

The present invention relates to an all-waverider internal-external flow integration and design method based on the local deflection and tangential cutting theory, comprising the following steps: (1) designing an external compression shock wave flow field and discretizing the fundamental wave surface, and applying the local deflection and tangential cutting theory to solve the flow characteristics at each discrete point of the shock wave; (2) designing an internal compression shock wave surface to obtain the intersection line between the internal and external compression shock waves; and back-designing the leading edge of the waverider body through the intersection line; (3) solving and obtaining the waverider surface in the shock wave flow field according to the leading edge of the waverider body; (4) designing the side profile of the inlet shock wave on the internal contraction shock wave surface according to the leading edge of the waverider body to generate a three-dimensional internal turning inlet; (5) designing the full-waverider back profile according to the leading edge of the waverider body and the side profile of the inlet shock wave. While retaining the advantages of the three-dimensional internal turning inlet itself, the present invention adopts a shock wave flow field solving method with high calculation accuracy to complete the precise design of the waverider, realizing the efficient internal-external flow integration of the waverider and the three-dimensional internal turning inlet.

Description

Technical Field

[0001] The present invention relates to the technical field of hypersonic vehicle internal-external flow integration, and particularly relates to a full-waverider internal-external flow integration and design method based on the local deflection and tangency theory. Background Art

[0002] In recent years, mankind has made great progress in the field of hypersonic flight technology and will surely continue to advance towards the goal of new hypersonic flight in the future. It can be found from the publicly available research that the aerodynamic design of hypersonic vehicles has received extensive attention from researchers.

[0003] The aerodynamic shape of a hypersonic vehicle is one of the key factors determining its ability to achieve efficient and wide-speed-range flight. An aerodynamic shape design with a high lift-to-drag ratio is expected to enable the hypersonic vehicle to fly efficiently, at high speed, and with high stability. The waverider, with its excellent lift-to-drag ratio characteristics, is widely used as the forebody part of hypersonic vehicles. The waverider design method based on a curved shock wave involves streamline tracing in the curved shock wave flow field to obtain the waverider surface. The curved shock wave flow field solved by this method ignores the lateral flow factor, and the accuracy of the designed waverider surface needs to be improved. The local deflection and tangency theory is a method for solving the shock wave flow field that takes lateral flow into account. The waverider designed using this theory has higher accuracy and is of great significance for the geometric design of a full three-dimensional waverider. The three-dimensional internal compression inlet has been intensively studied by domestic and foreign scholars due to its excellent air capture ability and compression efficiency.

[0004] A large number of studies have shown that the internal-external flow integration technology is one of the cores in the development of hypersonic vehicles, and efficient internal-external flow integration design is of great significance for the development of hypersonic vehicles. Efficient internal-external flow integration design is not simply a compromise between the airframe and the inlet. Without a reasonable internal-external flow integration design method, even if an efficient waverider and inlet are designed, it is difficult to give full play to their excellent characteristics after integration, and instead, problems such as a decline in the overall performance of the hypersonic vehicle may occur. Therefore, it is necessary to achieve efficient internal-external flow integration design to fully utilize the aerodynamic characteristics of the waverider and the three-dimensional internal compression inlet. Summary of the Invention

[0005] Aiming at the deficiencies of the existing technology, the present invention aims to propose an all-waverider internal-external flow integration and design method based on the local deflection and tangential cutting theory. While retaining the advantages of the three-dimensional internal turning inlet itself, the local deflection and tangential cutting theory is applied to solve the curved shock wave with higher precision and design the waverider part. To achieve the efficient integration design of the waverider and the inlet, the lip part of the three-dimensional internal turning inlet is used as the connection part between the waverider and the three-dimensional internal turning inlet, effectively avoiding the mutual interference between the internal and external compression shock waves and reducing the capture of low-speed airflow by the three-dimensional internal turning inlet. This method has important research significance for the field of internal-external flow integration technology of hypersonic aircraft.

[0006] The present invention is realized through the following technical solutions.

[0007] An all-waverider internal-external flow integration and design method based on the local deflection and tangential cutting theory, the method comprising the following steps:

[0008] (1) Design the external compression shock wave flow field and discretize the fundamental wave surface, and apply the local deflection and tangential cutting theory to solve the flow characteristics at each discrete point of the shock wave.

[0009] (2) Design the internal compression shock wave surface to obtain the intersection line between the internal and external compression shock waves. Reverse design the leading edge of the waverider body through the intersection line.

[0010] (3) Solve and obtain the waverider surface in the shock wave flow field according to the leading edge of the waverider body.

[0011] (4) Design the side profile of the inlet shock wave generation on the internal contraction shock wave surface according to the leading edge of the waverider body to generate a three-dimensional internal turning inlet.

[0012] (5) Design the back profile of the all-waverider according to the leading edge of the waverider body and the side profile of the inlet shock wave generation.

[0013] In the said step (1), the designed external compression shock wave flow field is obtained by solving the external compression elliptic cone shock wave surface, and the external compression elliptic cone shock wave surface is strictly symmetric along the spanwise direction. The external compression elliptic cone shock wave surface is discretized into several points, and the geometric centers of the external compression elliptic cone shock wave surface corresponding to the discrete points of the external compression elliptic cone shock wave surface are all located on the geometric central axis of the external compression elliptic cone shock wave surface. Along the direction of the hypersonic air flow, the heights of the curvature centers corresponding to different discrete points of the external compression elliptic cone shock wave surface are different, and the connecting line of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface does not coincide with the geometric central axis of the external compression elliptic cone shock wave surface. In addition, along the direction of the hypersonic air flow, at different spanwise positions of the external compression elliptic cone shock wave surface, the connecting lines of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface are not coaxial. Due to the characteristics of the cross-flow of the air flow, the hypersonic air flow deflects, and the positions of the discrete points of the external compression elliptic cone shock wave surface are different in the spanwise direction. Connect adjacent shock wave discrete points, and through the connecting line of the discrete points of the external compression elliptic cone shock wave surface, design the micro tangent meridional plane of the discrete points of the external compression elliptic cone shock wave surface on the external compression elliptic cone shock wave surface. Solve the shock wave flow field by the conventional method, and obtain the external compression waverider surface according to the designed waverider leading edge.

[0014] In the said step (2), select the intersection point of the internal and external flow shock waves on the external compression elliptic cone shock wave surface, and inverse design the internal compression tangent shock wave surface at this point, and make it intersect with the external compression elliptic cone shock wave surface to obtain the intersection line between the internal and external flow compression shock wave surfaces. Design a vertical meridional plane in the direction of the hypersonic air flow to cut the intersection line between the internal and external flow compression shock wave surfaces to obtain the profile line of the shock wave receiving side of the three-dimensional internal turning inlet. The profile line of the shock wave receiving side of the three-dimensional internal turning inlet is projected on the trailing surface of the external compression elliptic cone shock wave surface, and inverse design the projected profile line of the waverider body leading edge. The projection of the projected profile line of the waverider body leading edge along the reverse direction of the hypersonic air flow is the waverider leading edge, which includes the profile line of the shock wave receiving side of the three-dimensional internal turning inlet and the leading edge of the waverider body wing. The leading edge of the waverider body wing is connected to the profile line of the shock wave receiving side of the three-dimensional internal turning inlet and fits on the external compression elliptic cone shock wave surface.

[0015] In the said step (3), according to the waverider leading edge obtained in step (2), and adopt the solution method in step (1) to obtain the external compression waverider surface.

[0016] In the step (4), connect the two end points on both sides of the shock wave receiving side profile of the three-dimensional internal turning inlet, and stretch it along the hypersonic airflow direction to obtain the horizontal meridian plane. Mirror the shock wave receiving side profile of the three-dimensional internal turning inlet through the horizontal meridian plane to obtain the mirror curve of the shock wave receiving side of the three-dimensional internal turning inlet. The projection of the mirror curve of the shock wave receiving side of the three-dimensional internal turning inlet on the internal compression tangent shock wave surface is the shock wave generating side profile of the three-dimensional internal turning inlet. The shock wave generating side profile and the shock wave receiving side profile of the three-dimensional internal turning inlet are the inlet profiles of the three-dimensional internal turning inlet, and the shock wave generating side profile and the shock wave receiving side profile of the three-dimensional internal turning inlet are attached to the internal compression tangent shock wave surface. The inlet profiles of the three-dimensional internal turning inlet adopt streamline tracking and geometric modification techniques in the internal compression tangent shock wave flow field to obtain the internal compression surface of the three-dimensional internal turning inlet. The tail surface of the internal compression surface of the three-dimensional internal turning inlet is the throat of the three-dimensional internal turning inlet, and the edge of the throat is the throat profile of the three-dimensional internal turning inlet. The throat profile of the three-dimensional internal turning inlet is a three-dimensional closed curve. Stretch it to the same vertical plane along the hypersonic airflow direction, and expand the throat profile of the three-dimensional internal turning inlet by means of geometric transition to generate the isolator of the three-dimensional internal turning inlet. During the geometric transition of the throat profile of the three-dimensional internal turning inlet, the outlet of the isolator of the three-dimensional internal turning inlet is converted into a circular shape. The expansion process is manifested as an increase in the projected area of the throat profile of the three-dimensional internal turning inlet along the hypersonic airflow direction.

[0017] In the step (5), along the hypersonic airflow direction, stretch the leading edge of the waverider wing and the shock wave generating side profile of the inlet to the same distance position as the tail end of the external compression waverider profile to form the full waverider back profile, and the tail is the full waverider tail surface. When the hypersonic airflow flows through the integration of the internal and external flows of the full waverider, the three-dimensional internal turning inlet captures the hypersonic airflow without any pre-compression effect of the forebody on the hypersonic airflow, preventing the generation of the boundary layer and avoiding the intake of the boundary layer by the three-dimensional internal turning inlet, effectively improving the quality of the airflow captured by the three-dimensional internal turning inlet.

[0018] Compared with the prior art, the advantages of the present invention are:

[0019] The present invention aims to propose an integrated internal and external flow design method for a full waverider based on the theory of local deflection and tangential cutting. While retaining the advantages of the three-dimensional internal turning inlet, a shock wave flow field solution method with high computational accuracy is adopted to complete the precise design of the waverider and achieve the efficient integration of the internal and external flows of the waverider and the three-dimensional internal turning inlet. In the integrated internal and external flow design method for a full waverider based on the theory of local deflection and tangential cutting proposed by the present invention, the three-dimensional internal turning inlet adopts a direct intake flow capture method, effectively preventing the three-dimensional internal turning inlet from capturing the boundary layer; the shock intersection of the internal and external flow compression shock waves is moved backward to the lip of the three-dimensional internal turning inlet, effectively avoiding the capture of low-energy flow caused by the mutual interference between the internal and external flow compression shock waves. Both the waverider body and the three-dimensional internal turning inlet designed by this integrated internal and external flow method can "ride" on the surface of the internal and external flow compression shock waves, having the characteristics of a full waverider. Description of the Drawings

[0020] The drawings described herein are used to provide a further understanding of the present invention and form a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the present invention.

[0021] Figure 1 It is a design drawing of an external compression elliptical cone shock wave surface;

[0022] Figure 2 It is a schematic diagram of solving the shock wave by applying the local deflection and tangential cutting method;

[0023] Figure 3 It is a schematic diagram of the internal and external flow compression shock waves;

[0024] Figure 4 It is a schematic diagram of the design principle of the connection line between the waverider body and the three-dimensional internal turning inlet;

[0025] Figure 5 It is a schematic diagram of the waverider surface of the waverider body;

[0026] Figure 6 It is a schematic diagram of the design principle of the inlet profile;

[0027] Figure 7 It is a side view of the structure of the lower surface of the waverider body and the three-dimensional internal turning inlet;

[0028] Figure 8 It is a schematic diagram of the overall structure of the integrated internal and external flows of the full waverider;

[0029] Figure 9 It is a bottom view of the integrated internal and external flows of the full waverider;

[0030] Figure 10 It is a half-sectional view of the integrated internal and external flows of the full waverider.

[0031] The markings in the figure are as follows: 1 represents the outer compression elliptic cone shock wave surface, 2 represents the geometric center of the outer compression elliptic cone shock wave surface, 3 represents the curvature center of the outer compression elliptic cone shock wave surface, 4 represents the connecting line of the curvature centers in the flow direction of the discrete points on the outer compression elliptic cone shock wave surface, 5 represents the profile line of the outer compression elliptic cone shock wave surface, 6 represents the geometric center axis of the outer compression elliptic cone shock wave surface, 7 represents the connecting line of the curvature centers in the spanwise direction of the discrete points on the outer compression elliptic cone shock wave surface, 8 represents the discrete points on the outer compression elliptic cone shock wave surface, 9 represents the radius of curvature of the discrete points on the outer compression elliptic cone shock wave surface, 10 represents the hypersonic airflow, 11 represents the leading edge of the waverider, 12 represents the outer compression waverider surface, 13 represents the connecting line of the discrete points on the outer compression elliptic cone shock wave surface, 14 represents the slightly tangent meridian plane of the discrete points on the outer compression elliptic cone shock wave surface, 15 represents the inner compression tangent shock wave surface, 16 represents the intersection line between the inner and outer flow compression shock wave surfaces, 17 represents the vertical meridian plane, 18 represents the profile line of the shock wave receiving side of the three-dimensional internal turning inlet, 19 represents the projected profile line of the leading edge of the waverider airframe, 20 represents the leading edge of the wing of the waverider airframe, 21 represents the horizontal meridian plane, 22 represents the mirror curve of the shock wave receiving side of the three-dimensional internal turning inlet, 23 represents the profile line of the shock wave generating side of the three-dimensional internal turning inlet, 24 represents the inner compression surface of the three-dimensional internal turning inlet, 25 represents the profile line of the throat of the three-dimensional internal turning inlet, 26 represents the isolator of the three-dimensional internal turning inlet, 27 represents the outlet of the isolator of the three-dimensional internal turning inlet, 28 represents the back surface of the full waverider, 29 represents the tail surface of the full waverider. Specific implementation mode

[0032] The following will elaborate on the implementation mode of the present invention in conjunction with the drawings and embodiments, so as to fully understand how the present invention applies technical means to solve technical problems and achieve the implementation process of the effects, and implement it accordingly.

[0033] The main implementation methods of the full waverider internal and external flow integration and design method based on the local deflection tangent theory include the following steps:

[0034] (1) Design the external compression shock wave flow field and discretize the fundamental wave surface. Apply the local deflection and tangency theory to solve the flow characteristics at each discrete point of the shock wave. The designed external compression shock wave flow field is obtained by solving the external compression elliptic cone shock wave surface 1, and the external compression elliptic cone shock wave surface 1 is strictly symmetric along the spanwise direction. Discretize the external compression elliptic cone shock wave surface 1 into several points. The geometric center 2 of the external compression elliptic cone shock wave surface corresponding to the discrete point 8 of the external compression elliptic cone shock wave surface is located on the geometric center axis 6 of the external compression elliptic cone shock wave surface. Along the flow direction of the hypersonic air flow 10, the height of the curvature center corresponding to different discrete points 8 of the external compression elliptic cone shock wave surface is different, and the connecting line 4 of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface does not coincide with the geometric center axis 6 of the external compression elliptic cone shock wave surface. In addition, along the flow direction of the hypersonic air flow 10, at different spanwise positions of the external compression elliptic cone shock wave surface 1, the connecting lines 4 of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface are not coaxial. Due to the characteristics of the cross-flow of the air flow, the hypersonic air flow 10 deflects, and the positions of the discrete points 8 of the external compression elliptic cone shock wave surface are different in the spanwise direction. Connect adjacent shock wave discrete points, and design the micro-tangency meridian plane 14 of the discrete points of the external compression elliptic cone shock wave surface through the connecting line 13 of the discrete points of the external compression elliptic cone shock wave surface on the external compression elliptic cone shock wave surface 1. Solve the shock wave flow field by conventional methods, and obtain the external compression waverider surface 12 according to the designed waverider leading edge 11.

[0035] (2) Design the internal compression shock wave surface and obtain the intersection line between the internal and external compression shock waves. Reverse design the leading edge of the waverider airframe through the intersection line. Select the intersection point of the internal and external flow shock waves on the external compression elliptic cone shock wave surface 1, and reverse design the internal compression tangency shock wave surface 15 at this point, which intersects with the external compression elliptic cone shock wave surface 1 to obtain the intersection line 16 between the internal and external flow compression shock wave surfaces. Design the vertical meridian plane 17 in the flow direction of the hypersonic air flow 10 to cut the intersection line 16 between the internal and external flow compression shock wave surfaces to obtain the profile line 18 of the shock wave receiving side of the three-dimensional internal turning inlet. Project the profile line 18 of the shock wave receiving side of the three-dimensional internal turning inlet on the trailing surface of the external compression elliptic cone shock wave surface 1, and reverse design the projected profile line 19 of the leading edge of the waverider airframe. The projection of the projected profile line 19 of the leading edge of the waverider airframe along the reverse flow direction of the hypersonic air flow 10 is the waverider leading edge 11, which includes the profile line 18 of the shock wave receiving side of the three-dimensional internal turning inlet and the leading edge 20 of the waverider airframe wing. The leading edge 20 of the waverider airframe wing is connected to the profile line 18 of the shock wave receiving side of the three-dimensional internal turning inlet and fits on the external compression elliptic cone shock wave surface 1.

[0036] (3) According to the waverider leading edge 11 obtained in step (2), and use the solution method in step (1) to obtain the external compression waverider surface 12.

[0037] (4) Based on the leading edge of the waverider body, design the side profile line for generating the inlet shock on the inner contraction shock surface to generate a three-dimensional inward-turning inlet. Connect the two end points on both sides of the shock wave receiving side profile line 18 of the three-dimensional inward-turning inlet, and stretch it along the flow direction of the hypersonic airflow 10 to obtain the horizontal meridian plane 21. Mirror the shock wave receiving side profile line 18 of the three-dimensional inward-turning inlet through the horizontal meridian plane 21 to obtain the mirror curve 22 of the shock wave receiving side of the three-dimensional inward-turning inlet. The projection of the mirror curve 22 of the shock wave receiving side of the three-dimensional inward-turning inlet on the inner compression tangent shock surface 15 is the side profile line 23 for generating the shock wave of the three-dimensional inward-turning inlet. The side profile line 23 for generating the shock wave of the three-dimensional inward-turning inlet and the shock wave receiving side profile line 18 of the three-dimensional inward-turning inlet are the inlet profile lines of the three-dimensional inward-turning inlet, and the side profile line 23 for generating the shock wave of the three-dimensional inward-turning inlet and the shock wave receiving side profile line 18 of the three-dimensional inward-turning inlet are fitted on the inner compression tangent shock surface 15. The inlet profile lines of the three-dimensional inward-turning inlet adopt streamline tracking and geometric modification techniques in the inner compression tangent shock wave flow field to obtain the inner compression surface 24 of the three-dimensional inward-turning inlet. The tail surface of the inner compression surface 24 of the three-dimensional inward-turning inlet is the throat of the three-dimensional inward-turning inlet, and the edge of the throat is the throat profile line 25 of the three-dimensional inward-turning inlet. The throat profile line 25 of the three-dimensional inward-turning inlet is a three-dimensional closed curve. Stretch it to the same vertical plane along the flow direction of the hypersonic airflow 10, and expand the throat profile line 25 of the three-dimensional inward-turning inlet by means of geometric transition to generate the isolator 26 of the three-dimensional inward-turning inlet. During the geometric transition of the throat profile line 25 of the three-dimensional inward-turning inlet, the outlet 27 of the isolator of the three-dimensional inward-turning inlet is converted into a circular shape. The expansion process is manifested as an increase in the projected area of the throat profile line 25 of the three-dimensional inward-turning inlet along the flow direction of the hypersonic airflow 10.

[0038] (5) Based on the leading edge of the waverider body and the side profile line for generating the inlet shock, design the full waverider back surface 28. Along the flow direction of the hypersonic airflow 10, stretch the leading edge 20 of the waverider body wing and the side profile line for generating the inlet shock to the same distance position as the tail end of the outer compression waverider surface 12 to form the full waverider back surface 28, and the tail is the full waverider tail surface 29. When the hypersonic airflow 10 flows through the integrated internal and external flow of the full waverider, the three-dimensional inward-turning inlet captures the hypersonic airflow 10, without any pre-compression effect of the forebody on the hypersonic airflow 10, preventing the generation of the boundary layer and avoiding the intake of the boundary layer by the three-dimensional inward-turning inlet, effectively improving the quality of the airflow captured by the three-dimensional inward-turning inlet.

[0039] The beneficial effects of the present invention are as follows: The present invention aims to propose an integrated internal and external flow design method for a full waverider based on the local deflection and kissing cut theory. While retaining the advantages of the three-dimensional internal turning inlet, a shock wave flow field solution method with high calculation accuracy is adopted to complete the precise design of the waverider and achieve the efficient integration of the internal and external flows of the waverider and the three-dimensional internal turning inlet. In the integrated internal and external flow design method for a full waverider based on the local deflection and kissing cut theory proposed by the present invention, the three-dimensional internal turning inlet adopts a direct intake flow capture method, effectively preventing the three-dimensional internal turning inlet from capturing the boundary layer; the shock intersection of the internal and external flow compression shock waves is shifted to the lip of the three-dimensional internal turning inlet, which can effectively avoid the capture of low-energy flow caused by the mutual interference between the internal and external flow compression shock waves. Both the waverider body and the three-dimensional internal turning inlet designed by this integrated internal and external flow method can "ride" on the surface of the internal and external flow compression shock waves, having the characteristics of a full waverider.

[0040] The above description is only for the best embodiments of the present invention and should not be construed as a limitation of the claims. The present invention is not limited to the above embodiments, and its specific structure allows for changes. All changes made within the scope of the protection of the independent claims of the present invention are within the scope of protection of the present invention.

Claims

1. An integrated internal and external flow and design method of all multiplier waves based on the local deflection kiss-cut theory, characterized in that It includes the following steps: (1) Design the external compression shock wave flow field and discretize the fundamental wave surface, and apply the local deflection tangency theory to solve the flow characteristics at each discrete point of the shock wave; In the step (1), the designed external compression shock wave flow field is obtained by solving the external compression elliptic cone shock wave surface, and the external compression elliptic cone shock wave surface is strictly symmetric along the spanwise direction; discretize the external compression elliptic cone shock wave surface into several points, and the geometric centers of the external compression elliptic cone shock wave surface corresponding to the discrete points of the external compression elliptic cone shock wave surface are all located on the geometric central axis of the external compression elliptic cone shock wave surface; along the direction of the hypersonic air flow, the heights of the curvature centers corresponding to different discrete points of the external compression elliptic cone shock wave surface are different, and the connection line of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface does not coincide with the geometric central axis of the external compression elliptic cone shock wave surface; along the direction of the hypersonic air flow, at different spanwise positions of the external compression elliptic cone shock wave surface, the connection lines of the curvature centers in the flow direction of the discrete points of the external compression elliptic cone shock wave surface are not coaxial; due to the characteristics of the lateral air flow, the hypersonic air flow deflects, and the positions of the discrete points of the external compression elliptic cone shock wave surface are different in the spanwise direction; connect adjacent shock wave discrete points, and design the micro-tangency meridian plane of the discrete points of the external compression elliptic cone shock wave surface through the connection line of the discrete points of the external compression elliptic cone shock wave surface; solve the shock wave flow field, and obtain the external compression waverider surface according to the designed leading edge of the waverider; (2) Design the internal compression shock wave surface, obtain the intersection line between the internal and external compression shock waves, and inversely design the leading edge of the waverider airframe through the intersection line; In the step (2), select the intersection point of the internal and external flow shock waves on the external compression elliptic cone shock wave surface, inversely design the internal compression tangency shock wave surface at this point, and intersect with the external compression elliptic cone shock wave surface to obtain the intersection line between the internal and external flow compression shock wave surfaces; design a vertical meridian plane in the direction of the hypersonic air flow to cut the intersection line between the internal and external flow compression shock wave surfaces to obtain the profile line of the shock wave receiving side of the three-dimensional internal turning inlet; project the profile line of the shock wave receiving side of the three-dimensional internal turning inlet on the trailing surface of the external compression elliptic cone shock wave surface, and inversely design the projected profile line of the leading edge of the waverider airframe; the projection of the projected profile line of the leading edge of the waverider airframe along the reverse direction of the hypersonic air flow is the leading edge of the waverider, including the profile line of the shock wave receiving side of the three-dimensional internal turning inlet and the leading edge of the waverider airframe wing, and the leading edge of the waverider airframe wing is connected to the profile line of the shock wave receiving side of the three-dimensional internal turning inlet and fits on the external compression elliptic cone shock wave surface; (3) Solve and obtain the waverider surface in the shock wave flow field according to the leading edge of the waverider airframe; (4) Design the profile line of the shock wave generating side of the inlet on the internal compression shock wave surface according to the leading edge of the waverider airframe, and generate a three-dimensional internal turning inlet; In the said step (4), connect the two end points on both sides of the shock wave receiving side profile of the three-dimensional inward-turning inlet, and stretch it along the hypersonic airflow direction to obtain a horizontal meridian plane; mirror the shock wave receiving side profile of the three-dimensional inward-turning inlet through the horizontal meridian plane to obtain the shock wave receiving side mirror curve of the three-dimensional inward-turning inlet. The projection of the shock wave receiving side mirror curve of the three-dimensional inward-turning inlet on the internal compression tangent shock wave surface is the shock wave generating side profile of the three-dimensional inward-turning inlet; the shock wave generating side profile and the shock wave receiving side profile of the three-dimensional inward-turning inlet are the inlet profiles of the three-dimensional inward-turning inlet, and the shock wave generating side profile and the shock wave receiving side profile of the three-dimensional inward-turning inlet are fitted on the internal compression tangent shock wave surface; the inlet profiles of the three-dimensional inward-turning inlet adopt streamline tracking and geometric modification techniques in the internal compression tangent shock wave flow field to obtain the internal compression surface of the three-dimensional inward-turning inlet; the end surface of the internal compression surface of the three-dimensional inward-turning inlet is the throat of the three-dimensional inward-turning inlet, and the edge of the throat is the throat profile of the three-dimensional inward-turning inlet; the throat profile of the three-dimensional inward-turning inlet is a three-dimensional closed curve, which is stretched to the same vertical plane along the hypersonic airflow direction, and the throat profile of the three-dimensional inward-turning inlet is expanded by geometric transition to generate the isolator of the three-dimensional inward-turning inlet; during the geometric transition of the throat profile of the three-dimensional inward-turning inlet, the outlet of the isolator of the three-dimensional inward-turning inlet is converted into a circular shape. (5) Design the full-waverider back surface according to the leading edge of the waverider body and the shock wave generating side profile of the inlet. In the said step (5), stretch the leading edge of the waverider body wing and the shock wave generating side profile of the inlet along the hypersonic airflow direction to the same distance position as the end of the external compression waverider profile to form the full-waverider back surface, and the tail is the full-waverider end surface.

2. The all-multiwave internal and external flow integration and design method based on the local deflection kiss-cut theory according to claim 1, characterized in that In step (3), according to the waverider leading edge obtained in step (2), and adopt the solution method in step (1) to obtain the external compression waverider profile.

3. The full waverider internal and external flow integration and design method based on the local deflection kissing theory according to claim 1 is characterized in that: In step (4), the expansion process is manifested as an increase in the projected area of the throat profile of the three-dimensional inward-turning inlet along the hypersonic airflow direction.

4. The integrated internal and external flow of all multiplier waves and design method based on the local deflection kiss-cut theory according to claim 1, characterized in that, In step (5), when the hypersonic airflow flows through the full-waverider internal and external flow integration, the three-dimensional inward-turning inlet captures the hypersonic airflow, without any pre-compression effect of the forebody on the hypersonic airflow, preventing the generation of the boundary layer, and avoiding the intake of the boundary layer by the three-dimensional inward-turning inlet, effectively improving the quality of the airflow captured by the three-dimensional inward-turning inlet.

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