CN113665837A

CN113665837A - Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of leading edge line

Info

Publication number: CN113665837A
Application number: CN202111116050.2A
Authority: CN
Inventors: 丁峰; 柳军; 周芸帆; 金亮
Original assignee: National University of Defense Technology
Current assignee: National University of Defense Technology
Priority date: 2021-09-23
Filing date: 2021-09-23
Publication date: 2021-11-19
Anticipated expiration: 2041-09-23
Also published as: CN113665837B

Abstract

A design method for a steering engine bulge based on a sharp-pointed Von Karman curve with equal shock wave intensity of a front edge line is characterized in that a horizontal projection molded line of the bulge front edge line is used as design input, the design conception that the shock wave intensity of each longitudinal section is the same is realized by arranging the same average compression angle on each longitudinal section of a windward surface of the bulge, namely the design of the longitudinal shock wave intensity of the windward surface of the steering engine bulge along the transverse direction is realized, meanwhile, a sharp-pointed Von Karman curve equation is selected to calculate the flow direction molded lines of each longitudinal section, and the windward shock wave appendage of the bulge is realized, so that the pneumatic resistance is reduced.

Description

Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of leading edge line

Technical Field

The invention relates to the technical field of aerodynamic shape design of hypersonic aircrafts, in particular to a method for designing a pointed von Karman curve steering engine bulge based on shock wave intensities of leading edge lines and the like.

Background

The hypersonic aerocraft is an aerocraft which has a flight Mach number of more than 5, takes an air suction type engine or a combined engine thereof as main power or is unpowered, can remotely fly in an atmosphere and a trans-atmosphere, and can be applied in various forms, such as a hypersonic cruise missile, a hypersonic gliding aerocraft, a hypersonic manned/unmanned airplane, an aerospace plane, a hypersonic wide-speed-range aerocraft and the like.

The wave rider configuration utilizes a shock wave compression principle (wave rider principle) to realize the pneumatic requirement of high lift-drag ratio under the condition of hypersonic flight, so that the wave rider becomes an ideal configuration of the hypersonic flight vehicle.

The wave carrier is usually selected an air rudder to realize aircraft control when being used as an aircraft body, when the air rudder is installed on the wave carrier body, in order to control the gap heat flow between the air rudder and the wave carrier body, thereby avoiding the ablation of a rudder shaft, satisfying the requirements of installation spaces of structural members such as a steering engine, and improving the problem that the rudder effect of the air rudder is reduced because of the flow of the surface layer attached to the wall surface of the wave carrier body, usually, the steering engine bulge mode is selected to reduce the gap heat flow of the rudder shaft, the installation spaces of the structural members such as the steering engine are improved, and the problem of the rudder effect of the air rudder is improved. Meanwhile, the addition of the steering engine bulge increases the resistance of the wave rider body, and in order to reduce the increase in the resistance of the wave rider body caused by the addition of the steering engine bulge, the steering engine bulge needs to be designed in a rectifying manner.

The invention patent application with the publication number of CN112199853A, 1/8/2021 discloses a winged missile with a steering engine bulge and an optimization design method of the bulge, and the design method of the windward side of the steering engine bulge of the invention patent is that a first leading edge line 1, a second leading edge line 2, a third leading edge line 3 and a fourth leading edge line 4 shown in figure 1 are combined to generate a first side surface 5, then a second side surface 6 is generated by the same method, and the windward side of the steering engine bulge is formed by the first side surface and the second side surface: on one hand, the design problem that longitudinal shock wave intensity is distributed in the spanwise direction is not considered on the windward side of the steering engine bulge constructed by the method, so that the shock wave intensity of the longitudinal section of the bulge is gradually increased from the symmetrical surface to two sides, and the problem that the distribution of aerodynamic heat load characteristics of the bulge on different longitudinal sections is uneven is caused; on the other hand, the power curve or the Von Karman curve is adopted as the front edge line of the steering engine bulge, and the initial inclination angles of the power curve or the Von Karman curve are both 90 degrees, so that the initial compression angle of the windward side of the steering engine bulge generated by designing the curves is 90 degrees, the shock wave separation problem can be caused, and the problems in the two aspects are not beneficial to reducing the problem of aircraft resistance increase caused by the additional installation of the steering engine bulge. For the convenience of the following description, the invention patent design method with the publication number of CN112199853A, which is published as 1 month and 8 days 2021, is simply referred to as the original steering engine bulge design method.

Disclosure of Invention

The original steering engine bulge design method does not consider the design problem that the longitudinal shock wave strength is distributed along the transverse direction, the shock wave strength of the longitudinal section of the bulge is gradually increased from the symmetrical surface to two sides, the problem that aerodynamic heat load characteristics of the bulge on different longitudinal sections are not uniformly distributed is caused, and on the other hand, the problem that the shock wave is separated from a body can be caused because the initial compression angle of the windward side of the steering engine bulge in the original steering engine bulge design method is 90 degrees. Aiming at the defects of the original steering engine bulge design method, the invention aims to provide a method for designing a steering engine bulge based on a sharp-pointed Von Karman curve with the shock wave intensity of a leading edge line and the like. The steering engine bulge with the same longitudinal section shock wave strength, uniform force-heat load characteristic distribution and attached frontal shock waves can be generated through the steering engine bulge, and the steering engine bulge and the wave rider body are integrally designed, so that the resistance of a steering engine bulge and wave rider body assembly is further reduced.

In order to realize the technical purpose of the invention, the following technical scheme is adopted:

a method for designing a pointed Von Karman curve steering engine bulge based on shock wave intensities of a leading edge line and the like comprises the following steps of:

generating a wave-rider fuselage;

under the condition that the width constraint condition of a steering engine bulge along the Z direction is met, designing a horizontal projection molded line of a front edge line of a windward side of the bulge, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;

under the condition of satisfying the height constraint condition of the steering engine bulge along the Y direction, designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located;

the method comprises the steps that the average compression angle of the longitudinal section of the windward side of each bulge is given, the rear edge point of the windward side of each bulge, corresponding to the front edge point of the windward side of each bulge, is solved according to the average compression angle of the longitudinal section of the windward side of each bulge and the Y-direction coordinate value of the horizontal section of the rear edge line of the windward side of each bulge, and all the rear edge points of the windward side of each bulge are smoothly connected to form the rear edge line of the windward side of each bulge;

solving to obtain the lengths of the longitudinal sections corresponding to the front edge points of the windward sides of the bulges along the X direction and the Y direction according to the front edge points of the windward sides of the bulges and the rear edge points of the windward sides of the bulges corresponding to the front edge points of the windward sides of the bulges;

obtaining a von Karman curve equation of the longitudinal section corresponding to each windward leading edge point of each bump according to the length of the longitudinal section corresponding to each windward leading edge point of each bump in the X direction and the Y direction and the coordinates of each windward leading edge point of each bump in the X direction and the Y direction;

giving initial compression angle delta of longitudinal section of windward side of bump₀Changing the longitudinal section Von Karman curve corresponding to the front edge point of the windward side of each bump into a combined line formed by a straight line segment and the Von Karman curve, namely the longitudinal section pointed Von Karman curve corresponding to the front edge point of the windward side of each bump;

taking each bulge windward leading edge point as a starting point, taking each bulge windward trailing edge point corresponding to each bulge windward leading edge point as an end point, respectively generating a group of discrete points by utilizing a von Karman curve equation of a longitudinal section corresponding to each bulge windward leading edge point along the X direction, and respectively and smoothly connecting the discrete points to form a bulge windward flow molded line; lofting the flow direction molded lines of all the bulge windward sides to generate bulge windward sides;

according to the length of an air rudder wing root, a rear edge point of a windward side of the bulge and a wave carrier body, determining a rear edge line of the upper surface of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge, a lower edge contour line of the left side surface of the bulge, a lower side contour line of a right side surface of a finished bulge, a left side contour line of a bottom surface of the bulge, a right side contour line of the bottom surface of the bulge and a lower edge contour line of the bottom surface of the bulge, and further determining the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge, wherein the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge jointly form a steering engine bulge, and the wave carrier body jointly form an integrated design configuration.

Furthermore, according to the flight condition and the size of the aircraft, the invention utilizes a design method of a osculating axisymmetric von Karman waverider to generate the waverider fuselage. The flight conditions of the aircraft comprise incoming flow Mach number, incoming flow static pressure and incoming flow static temperature, and the size of the aircraft body comprises the length and the width of the aircraft body. The invention discloses a method for designing an osculating axisymmetric von Karman waverider, which is disclosed by CN109573092B from the invention of patent application No. 6/30 of 2020.

Further, the horizontal projection molded lines of the front edge line of the windward side of the bump are uniformly dispersed from left to right to obtain N₁The horizontal projection type line discrete points of the front edge line of the windward side of each bump; projecting the horizontal projection type line discrete points of the leading edge line of each bump windward side to the upper surface of the wave rider body along the longitudinal section of each bump windward side to obtain N₁Front edge point of windward side of each bump, N₁The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.

Furthermore, the wave rider body generated by the invention is composed of a family of discrete points, the wave rider body is divided into a plurality of triangular mesh units, each triangular mesh unit is composed of three adjacent discrete points, and the upper surface of the wave rider body is composed of M triangular mesh units.

The method for determining the leading edge point of the windward side of the bump comprises the following steps: sequentially solving the horizontal projection type line discrete points P passing through the ith bulge windward side leading edge line_L,iAnd a line parallel to the Y axis and a wave-rider bodyIntersection point P of the plane where the jth triangular grid cell on the upper surface is located_c,j，i＝1,2...N₁J is 1,2.. M, and the intersection point P is determined_c,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judged_c,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point P_c,jNamely the leading edge point of the windward side of the ith bulge.

Furthermore, the invention relates to a longitudinal section corresponding to the leading edge point of the ith bulge on the windward side, wherein i is 1,2₁According to a straight line passing through the leading edge point of the windward side of the ith bulge and with the slope being the sine value of the average compression angle of the longitudinal section of the windward side of the bulge and the Y-direction coordinate value Y of the horizontal section where the trailing edge line of the windward side of the bulge is located_TSolving to obtain the X-direction coordinate value X of the rear edge point of the windward side of the bulge corresponding to the front edge point of the windward side of the ith bulge_T,iAnd obtaining the rear edge point of the windward side of the ith bulge.

Further, according to the length of the longitudinal section corresponding to the ith bulge windward front edge point along the X direction and the Y direction and the coordinates of the ith bulge windward front edge point along the X direction and the Y direction, the i-th longitudinal section von Karman curve is obtained on the longitudinal section corresponding to the ith bulge windward front edge point, and the i-th longitudinal section von Karman curve equation is as follows:

wherein L is_Y,i、L_X,iThe lengths of the longitudinal section corresponding to the front edge point of the windward side of the ith bulge along the X direction and the Y direction respectively_L,i、Y_L,iThe coordinate values of the leading edge point of the ith bulge windward side in the X direction and the Y direction are respectively, and X belongs to [ X ∈ [ ]_L,i,X_T,i]。

Further, the longitudinal section pointed von Karman curve corresponding to the leading edge point of the windward side of the ith bulge is obtained by the following method:

solving the leading edge point P passing through the ith bulge windward side_L,iAnd the slope is the longitudinal section of the windward side of the bulgeInitial compression angle delta₀Intersection point A of the sine value straight line and the i-th longitudinal section von Karman curve_iIntersection point A_iThe coordinate value in the X direction of (A) is X_A,i；

In the i-th longitudinal section von Karman curve, the coordinate value in the X direction is set at [ X ]_L,i,X_A,i]The inner part is a straight line segment, and the coordinate value in the X direction is [ X ]_A,i,X_T,i]The part inside the pin is a von Karman curve, so that the i-th longitudinal section von Karman curve is changed into a combined line formed by a straight line section and the von Karman curve, namely the i-th longitudinal section pointed von Karman curve, and the i-th longitudinal section pointed von Karman curve equation is as follows:

further, the initial compression angle delta of the longitudinal section of the windward side of the bump is₀The value range of (a) meets the following requirements:

δ₀the upper limit value of (d) is to ensure that the longitudinal section cusp von Karman curve is attached to the shock wave under the condition of the incoming current Mach number Ma, delta₀Must be smaller than the maximum wedge angle delta of the wedge to generate the accessory shock wave_mI.e. delta₀＜δ_m；

δ₀In order to ensure that the ith leading edge point P passes through the windward side of the bulge_L,iAnd the slope is the longitudinal section initial compression angle delta₀The intersection point A of the sine value straight line and the i-th longitudinal section Von Karman curve_i，δ₀Must be larger than the average compression angle delta, i.e. delta, of the longitudinal section of the windward side of the bump₀＞δ。

Furthermore, the wedge angle delta of the wedge of the invention is used for generating the maximum wedge angle delta of the attached shock wave_mThe following method was used:

solving according to the oblique shock wave theory to obtain the maximum shock wave angle beta corresponding to the incoming flow Mach number Ma_m，

Wherein γ is a specific heat ratio.

Solving and obtaining the maximum wedge angle delta of the attached shock wave generated by wedge by utilizing the oblique shock wave theory_m，

Further, according to the length of the wing root of the air vane, the position X of the cross section of the rear edge of the upper surface of the drum is set to be X_TAnd projecting the rear edge point of the windward side of the bulge to the cross section of the rear edge of the upper surface of the bulge at the corresponding longitudinal section of the rear edge point of the windward side of each bulge, generating the corresponding rear edge point of the upper surface of the bulge, and smoothly connecting the rear edge points of the upper surface of the bulge to form a rear edge line of the upper surface of the bulge.

Further, in the invention, a straight line segment formed by connecting the trailing edge point of the windward side of the 1 st bulge positioned at the leftmost side and the corresponding trailing edge point of the upper surface of the 1 st bulge is used as the left side contour line of the upper surface of the bulge, and the Nth bulge positioned at the rightmost side is used as the Nth contour line of the upper surface of the bulge₁The trailing edge point of the windward side of each bulge corresponds to the Nth point₁And a straight line segment formed by connecting the rear edge points of the upper surface of each bulge is used as the right contour line of the upper surface of each bulge.

Further, in the invention, the left side contour line of the upper surface of the bulge is equidistantly scattered to generate N₃The discrete points are called bulge upper surface left side contour points, and the bulge upper surface right side contour lines are equidistantly and discretely generated into N₃The discrete points are called contour points on the right side of the upper surface of the bulge;

projecting discrete points on the 1 st bulge windward side flow direction molded line on the leftmost bulge and the bulge upper surface left side contour point to the upper surface of the wave rider body along the longitudinal section to generate bulge left side surface lower edge contour points, and smoothly connecting all bulge left side surface lower edge contour points to form a bulge left side surface lower edge contour line; will be located at the rightmost N₁The discrete points on the windward side flow direction molded lines of the strip bulges and the right side contour point of the upper surface of the bulge are projected to the upper surface of the wave rider body along the longitudinal section to generate the right bulgeAnd the lower edge contour points of the right side surface of the bulge are smoothly connected to form a lower edge contour line of the right side surface of the bulge.

Will be N₃Left side contour line and Nth contour line of upper surface of each bump₃The straight line segment formed by connecting the contour points of the lower edge of the left side surface of each bulge is used as the left side contour line of the bottom surface of the bulge, and the Nth bulge is connected with the contour points of the lower edge of the left side surface of the bulge₃The contour point on the right side of the upper surface of each bulge and the Nth point₃And a straight line segment formed by connecting contour points of the lower edge of the right side surface of each bulge is used as a right side contour line of the bottom surface of the bulge.

And projecting the rear edge points of the upper surface of the bulge to the upper surface of the wave-rider body along the cross section to generate bulge bottom surface lower edge contour points, and smoothly connecting all bulge bottom surface lower edge contour points to form a bulge bottom surface lower edge contour line.

A closed plane consisting of a rear edge line of the windward side of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge and a rear edge line of the upper surface of the bulge is used as the upper surface of the bulge; a closed plane formed by the flow direction line of the windward side of the leftmost bulge, the left side contour line of the upper surface of the bulge, the lower edge line of the left side surface of the bulge and the left side contour line of the bottom surface of the bulge is used as the left side surface of the bulge; a closed plane formed by the flow direction molded line of the windward side of the most right bulge, the right side contour line of the upper surface of the bulge, the lower edge line of the right side surface of the bulge and the right side contour line of the bottom surface of the bulge is used as the right side surface of the bulge; and a closed plane consisting of the rear edge line of the upper surface of the bulge, the left side contour line of the bottom surface of the bulge, the right side contour line of the bottom surface of the bulge and the lower edge contour line of the bottom surface of the bulge is used as the bottom surface of the bulge.

In another aspect, the present invention provides a computer device comprising a memory and a processor, the memory storing a computer program, the processor implementing the following steps when executing the computer program:

generating a wave-rider fuselage;

designing a horizontal projection molded line of a front edge line of a windward side of the bulge based on the width constraint of the bulge of the steering engine along the Z direction, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;

designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located based on the height constraint of the steering engine bulge along the Y direction;

In another aspect, the present invention provides a computer readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of:

generating a wave-rider fuselage;

Compared with the prior art, the invention can produce the following technical effects: the invention takes the horizontal projection molded line of the front edge line of the bulge as the design input, and realizes the design idea that the shock wave intensity of each longitudinal section is the same by arranging the same average compression angle on each longitudinal section of the windward side of the bulge, namely, the design of the longitudinal shock wave intensity of the windward side of the bulge of the steering engine along the transverse direction is realized. Meanwhile, a sharp-pointed Von Karman curve equation is selected to calculate the flow direction molded lines of each longitudinal section, so that the shock wave attachment of the windward side of the bump is realized, and the aerodynamic resistance is reduced.

The steering engine bulge has the advantages that the shock wave strength of each longitudinal section is the same, the force-heat load characteristic distribution is uniform, and the shock wave of the windward side is attached, and the steering engine bulge and the wave rider body are integrally designed, so that the resistance of the combination of the steering engine bulge and the wave rider body is further reduced.

Drawings

FIG. 1 shows a schematic diagram of a design method of a windward side of an original steering engine bulge;

FIG. 2 illustrates aircraft flight conditions and fuselage dimensions;

FIG. 3 shows an isometric view of a waverider body and a rectangular coordinate system definition;

FIG. 4 shows a side view of a waverider body and a rectangular coordinate system definition;

FIG. 5 shows a top view of a waverider fuselage and a rectangular coordinate system definition;

FIG. 6 shows a family of discrete points (i.e., point clouds), triangular mesh cells, and a partial magnified view of a fuselage that constitutes a waverider volume;

FIG. 7 shows the horizontal projected profile of the leading edge line of the windward side of the bulge;

FIG. 8 shows the horizontal projection of the line discrete points of the leading edge line of the windward side of the bump;

FIG. 9 is a schematic diagram showing a process of projecting the discrete points of the horizontal projection profile of the leading edge line of the windward side of the ith bump to the upper surface of the wave-rider fuselage along a longitudinal section;

FIG. 10 is a schematic diagram illustrating the determination of the leading edge point of the windward side of the bulge;

FIG. 11 is a schematic diagram showing the intersection of the leading edge line of the windward side of the bump and the triangular mesh unit on the upper surface of the hull;

FIG. 12 is a schematic diagram of solving for a bulge windward leading edge line from a bulge windward leading edge line horizontal projection profile;

FIG. 13 is a schematic diagram showing the solution of the ith bump leading edge point to the ith bump trailing edge point from the ith bump leading edge point;

FIG. 14 is a schematic view showing a longitudinal cross-section corresponding to the ith bump leading edge point, the longitudinal cross-section being a plane passing through the ith bump leading edge point and being parallel to the XOY plane;

FIG. 15 shows a schematic view of the flow direction profile of the windward side of the bulge with the wave rider fuselage;

FIG. 16 is a schematic view of all of the bulge upwind flow profiles and discrete points on each of the bulge upwind flow profiles;

FIG. 17 shows the bulge windward side generated from the lofting of the molded lines for all bulge windward sides;

FIG. 18 is a schematic diagram showing the generation of the contour lines of the upper surface, left side, right side and bottom of the drum;

FIG. 19 is a left and rear perspective view of an integrated design configuration formed by a steering engine bulge and a wave rider body;

FIG. 20 is a front right perspective view of the integrated design configuration formed by the steering engine bulge and the wave rider body;

FIG. 21 illustrates an aircraft configuration in which a steering engine bulge and a waverider fuselage are combined with an air rudder;

FIG. 22 is a grid diagram illustrating numerical simulation of an integrated design configuration of a steering engine bulge and a waverider body on a longitudinal symmetry plane, which is obtained by the method of the present invention in an embodiment of the present invention;

fig. 23 shows numerical simulation results of the steering engine bulge and waverider body integrated design configuration obtained by the method of the present invention in 6 different longitudinal sections, where (a) represents the numerical simulation result of the longitudinal section with Z equal to 0 mm; (b) numerical simulation results representing a longitudinal section of 10 mm; (c) numerical simulation results representing Z20 mm; (d) table Z-numerical simulation results of 30 mm; (e) numerical simulation results representing Z40 mm; (f) numerical simulation results representing Z50 mm.

Reference numbers in the figures: 1 represents a first front edge line of the windward side of an original steering engine bulge; 2, a second front edge line of the windward side of the original steering engine bulge; 3, a third leading edge line of the windward side of the original steering engine bulge; 4, a fourth leading edge line of the windward side of the original steering engine bulge; 5, a first side surface of the windward side of the original steering engine bulge; 6 represents the second side surface of the windward side of the original steering engine bulge; 7 denotes the fuselage length; 8 denotes the fuselage width;9, flight conditions including an incoming flow mach number, an incoming flow static temperature and an incoming flow static temperature; x represents a longitudinal coordinate value of the rectangular coordinate system; y represents a normal direction coordinate value of the rectangular coordinate system; z represents a coordinate value in the transverse direction of the rectangular coordinate system; o represents the origin of coordinates of the rectangular coordinate system; 10, a horizontal projection profile of a leading edge line of the windward side of the bump; 11 represents the horizontal projection type line discrete point P of the leading edge line of the windward side of the ith bulge_L,i(ii) a 12 denotes the leading edge point P of the i-th bump on the windward side_L,i'; 13 denotes a horizontal projection type line discrete point P passing through the leading edge line of the i-th bump windward side_L,iAnd a line parallel to the Y axis; 14, a jth triangular grid unit on the upper surface of the wave-rider body is shown, and three vertexes of the jth triangular grid unit are a 1# discrete point 15, a 2# discrete point 16 and a 3# discrete point 17 respectively; 15 denotes the 1# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 16 represents the 2# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 17 denotes a 3# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 19 represents the average compression angle of the longitudinal section of the windward side of the bump; 20, a straight line which passes through the leading edge point of the windward side of the ith bulge and has the slope which is the sine value of the average compression angle of the longitudinal section of the windward side of the bulge; 21 represents a horizontal section where the trailing edge line of the windward side of the bump is located, and Y is equal to Y_T(ii) a 22 denotes the i-th bump windward side trailing edge point; 23 denotes the bulge windward side trailing edge line; 24 and 25 respectively represent coordinate values X in X direction and Y direction of the leading edge point of the i-th bump windward side_L,i、Y_L,i(ii) a 26 denotes the i-th longitudinal section von karman curve; 27 denotes the initial compression angle delta of the longitudinal section of the windward side of the bulge₀(ii) a 28 denotes the leading edge point P passing through the i-th bump on the windward side_L,iAnd the slope is the initial compression angle delta of the longitudinal section of the windward side of the bump₀A line of sine values; 29 denotes the leading edge point P passing through the windward side of the i-th bump_L,iAnd the slope is the initial compression angle delta of the longitudinal section of the windward side of the bump₀Intersection point A of the sine value straight line and the i-th longitudinal section von Karman curve_i(ii) a 30, the flow direction molded line of the ith bulge windward side, namely a pointed von Karman curve of the ith longitudinal section; 31 represents N₁The strip bulge is provided with a windward side flow profile; 32 denotes the position X ═ X of the cross section of the trailing edge of the upper surface of the drum_T(ii) a 33 represents the 1 st trailing edge point of the windward side of the bulge; 34 denotes the 1 st bump upper surface trailing point, which also denotes the Nth bump upper surface trailing point₃A left side contour point of the upper surface of each bulge; 35 denotes the Nth₁The rear edge point of the windward side of each bulge; 36 denotes the Nth₁The upper surface trailing point of each bump, which also represents the Nth point₃The right outline point of the upper surface of each bulge; 37 represents the leading edge point of the windward side of the 1 st bump, which also represents the lower edge contour point of the left side of the 1 st bump; 38 denotes the Nth₃The lower edge contour point of the left side surface of each bulge; 39 denotes the Nth₁The leading edge point of the windward side of each bulge also represents the lower edge contour point of the right side surface of the 1 st bulge; 40 denotes the Nth₃The lower edge contour point of the right side surface of each bulge; 41 denotes a steering engine bulge; 42 denotes a wave-rider body; and 43 denotes an air rudder.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

The invention provides a method for designing a pointed Von Karman curve steering engine bulge based on the shock wave intensity of a leading edge line and the like, which comprises the following steps of:

and S1, generating a waverider fuselage according to the flight condition and the fuselage size of the aircraft by using a osculating axisymmetric Von Karman waverider design method.

As shown in fig. 2, the flight conditions 9 include an incoming mach number, an incoming static pressure and an incoming static temperature, the size of the fuselage includes a fuselage length 7 and a fuselage width 8, and the osculating axisymmetric von karman wavelet design method is the osculating axisymmetric von karman wavelet design method disclosed in the invention patent CN109573092B, published as 2020, 6, 30.

The isometric view, the side view, the top view and the rectangular coordinate system of the wave-rider body generated in S1 according to an embodiment of the present invention are defined as shown in fig. 3, 4 and 5, wherein X represents the longitudinal coordinate value of the rectangular coordinate system; y represents a normal direction coordinate value of the rectangular coordinate system; z represents a coordinate value in the transverse direction of the rectangular coordinate system; and O represents the origin of coordinates of a rectangular coordinate system.

S2, under the condition that the width constraint condition of the steering engine bulge along the Z direction is met, designing a bulge windward front edge line horizontal projection molded line 10, obtaining a series of bulge windward front edge points through the bulge windward front edge line horizontal projection molded line 10, and smoothly connecting all bulge windward front edge points to form a bulge windward front edge line.

In an embodiment of the present invention, as shown in fig. 6, the wave rider body is formed by a family of discrete points (i.e., point clouds), the wave rider body is divided into a plurality of triangular mesh units, each triangular mesh unit is formed by three adjacent discrete points, and the upper surface of the wave rider body is formed by M triangular mesh units. As shown in fig. 6, the j-th triangular mesh unit 14 on the upper surface of the wave-rider body has three vertices of a # 1 discrete point 15, a # 2 discrete point 16, and a # 3 discrete point 17.

As shown in fig. 7, a horizontal projection molded line 10 of a front edge line of a windward side of a bulge is designed according to a width constraint condition of the bulge of the steering engine along the Z direction; as shown in fig. 8, the horizontal projection profile 10 of the leading edge line of the windward side of the bulge is uniformly dispersed, and the dispersion is N₁The horizontal projection type line discrete point of the windward leading edge line of each bump 11 represents the horizontal projection type line discrete point P of the windward leading edge line of the ith bump_L,i。

As shown in fig. 9, the ith bulge windward leading edge line horizontal projection type line discrete point 11 is projected to the upper surface of the wave-rider body along the longitudinal section thereof to generate the ith bulge windward leading edge point 12, and N is generated by the same method₁Front edge point of windward side of each bump, N₁The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.

As shown in fig. 10, in S2 according to an embodiment of the present invention, based on the ith bump windward leading edge line horizontal projection type line discrete point 11, the ith bump windward leading edge line horizontal projection type line discrete points P are sequentially solved_L,iAnd the intersection point P of the straight line 13 parallel to the Y axis and the plane where the jth triangular grid cell 14 on the upper surface of the wave-rider body is located_c,j，i＝1,2...N₁J is 1,2.. M, and the intersection point P is determined_c,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judged_c,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point P_c,jNamely the leading edge point 12 of the ith bump on the windward side.

Referring to fig. 11 and 12, fig. 11 shows a schematic diagram of intersection of a leading edge line of a windward side of a bump and a triangular mesh unit on the upper surface of a wave-rider body; FIG. 12 is a schematic diagram showing a solution of the bulge windward leading edge line from the bulge windward leading edge line horizontal projection profile.

S3, designing Y-direction coordinate value of horizontal section where rear edge line of windward side of bulge is located under the condition that height constraint condition of steering engine bulge along Y direction is met_T。

S4, setting the average compression angle 19 of the longitudinal section of the windward side of the bulge, and determining the Y-direction coordinate value Y of the average compression angle of the longitudinal section of the windward side of the bulge and the Y-direction coordinate value Y of the horizontal section 21 of the trailing edge line of the windward side of the bulge at the longitudinal section corresponding to the leading edge point of the windward side of each bulge_TAnd solving the rear edge points of the windward surfaces of the bulges corresponding to the front edge points of the windward surfaces of the bulges, and smoothly connecting the rear edge points of the windward surfaces of the bulges to form a rear edge line 23 of the windward surfaces of the bulges.

As shown in fig. 13, given the average compression angle δ of the longitudinal section of the windward side of the drum, at the longitudinal section corresponding to the leading edge point 12 of the ith drum, according to the straight line 20 passing through the leading edge point of the windward side of the ith drum and having the slope of the sine value of the average compression angle of the longitudinal section of the windward side of the drum and the Y-direction coordinate value Y of the horizontal section 21 where the trailing edge line of the windward side of the drum is located_TAnd solving to obtain a bulge windward side rear edge point corresponding to the ith bulge windward side front edge point, namely the ith bulge windward side rear edge point 22.

And S5, solving to obtain the lengths of the longitudinal sections corresponding to the front edge points of the windward surfaces of the bulges along the X direction and the Y direction according to the front edge points of the windward surfaces of the bulges and the rear edge points of the windward surfaces of the bulges corresponding to the front edge points of the windward surfaces of the bulges.

As shown in fig. 14, according to the coordinate value of the leading edge point 12 of the windward side of the ith bulge and the coordinate value of the trailing edge point 22 of the windward side of the ith bulge, the windward side of the ith bulge is solved and obtainedThe length L of the longitudinal section corresponding to the front edge point along the X direction and the Y direction_X,i、L_Y,i。

And S6, obtaining von Karman curve equations of the longitudinal sections corresponding to the front edge points of the windward surfaces of the bulges according to the lengths of the longitudinal sections corresponding to the front edge points of the windward surfaces of the bulges along the X direction and the Y direction and the coordinates of the front edge points of the windward surfaces of the bulges along the X direction and the Y direction.

In an embodiment of the present invention, S6 is implemented by the following method:

as shown in fig. 14, in the longitudinal section corresponding to the windward leading edge point of the ith bump, according to the lengths of the longitudinal section corresponding to the windward leading edge point of the ith bump along the X direction and the Y direction and the coordinates of the windward leading edge point of the ith bump along the X direction and the Y direction, the von karman curve of the ith longitudinal section is obtained, and the equation of the von karman curve of the ith longitudinal section is as follows:

wherein L is_Y,i、L_X,iThe lengths of the longitudinal section corresponding to the front edge point of the windward side of the ith bulge along the X direction and the Y direction respectively_L,i、Y_L,iThe coordinate values of the leading edge point of the ith bulge windward side in the X direction and the Y direction are respectively, and X belongs to [ X ∈ [ ]_L,i,X_T,i]. In FIG. 14, 24 and 25 represent coordinate values X in X and Y directions of the leading edge point of the i-th bump on the windward side, respectively_L,i、Y_L,i(ii) a And 26 denotes the i-th longitudinal cross-sectional von karman curve.

S7, giving the initial compression angle 27 of the longitudinal section of the windward surface of each bump, and changing the von Karman curve of the longitudinal section corresponding to the front edge point of the windward surface of each bump into a combined line formed by a straight line segment and the von Karman curve, namely the von Karman curve of the tip of the longitudinal section corresponding to the front edge point of the windward surface of each bump.

In an embodiment of the present invention, S7 is implemented by the following method:

in order to solve the problem of shock wave dislocation of the ith longitudinal section of the von Karman curve,a sharp treatment of the ith longitudinal cross-sectional von karman curve head is required. As shown in FIG. 14, the solution is passed through the ith bump leading edge point P on the windward side_L,iAnd the slope is the initial compression angle delta of the longitudinal section of the windward side of the bump₀The intersection A of the sine value straight line 28 with the i-th longitudinal section von Karman curve_iIntersection point A_iThe coordinate value in the X direction of (A) is X_A,i(ii) a 29 in FIG. 14 denotes the leading edge P passing through the i-th bump on the windward side_L,iAnd the slope is the initial compression angle delta of the longitudinal section of the windward side of the bump₀Intersection point A of the sine value straight line and the i-th longitudinal section von Karman curve_i。

in one embodiment of the invention, the initial compression angle delta of the longitudinal section of the windward side of the bump₀The value range of (a) needs to satisfy the following requirements:

In one embodiment of the invention, the wedge angle delta is the maximum angle at which the accessory shock wave is generated by the wedge_mThe following method was used:

Wherein γ represents the specific heat ratio.

S8, taking each bulge windward leading edge point as a starting point, taking each bulge windward trailing edge point corresponding to each bulge windward leading edge point as an end point, respectively generating a group of discrete points by utilizing a von Karman curve equation of a longitudinal section corresponding to each bulge windward leading edge point along the X direction, and respectively and smoothly connecting the discrete points to form a bulge windward flow profile; and (4) lofting the flow direction molded lines of all the windward surfaces of the bulges to generate the windward surfaces of the bulges.

Referring to fig. 14, a group of N-th bump wind-facing surface N is generated by using an ith longitudinal section cusp von karman curve equation along the X direction with an ith bump wind-facing surface leading edge point as a starting point and an ith bump wind-facing surface trailing edge point as an ending point₂The discrete points are formed by points, and the discrete points in the group are smoothly connected to form the ith bulge windward flow profile 30, namely the ith longitudinal section pointed von Karman curve.

Generating N in the same way₁The strip bulge is facing the profile 31 as shown in fig. 15 and 16. As shown in FIG. 17, N₁And (3) lofting the flow direction molded line 31 of the windward side of the strip bulge to generate the windward side of the bulge.

S9, determining a rear edge line of the upper surface of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge, a lower edge contour line of the left side surface of the bulge, a lower edge contour line of the right side surface of the formed bulge, a left side contour line of the bottom surface of the bulge, a right side contour line of the bottom surface of the bulge and a lower edge contour line of the bottom surface of the bulge according to the length of the wing root of the air rudder, the rear edge point of the windward surface of the bulge and the fuselage of the wave carrier, and further determining the windward surface of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge, wherein the windward surface of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge jointly form a steering engine bulge, and the fuselage of the steering engine and the wave carrier jointly form an integrated design configuration. In an embodiment of the present invention, S9 is implemented by the following steps:

s9.1, as shown in fig. 18, the position 32 of the cross section of the trailing edge of the upper surface of the bulge is set according to the length of the wing root of the air rudder, and the cross section X is equal to X_TAnd projecting the rear edge point of the windward side of the bulge onto the cross section of the rear edge of the upper surface of the bulge at the corresponding longitudinal section of the rear edge point of the windward side of each bulge, so as to generate the rear edge point of the upper surface of the bulge, wherein the rear edge points of the upper surface of the bulge form a rear edge line of the upper surface of the bulge.

S9.2, taking a straight line segment formed by the 1 st bulge windward side rear edge point 33 and the 1 st bulge upper surface rear edge point 34 as a bulge upper surface left side contour line 33-34, and taking the line segment as the N₁ Rear edge point 35 and Nth of windward side of each bump₁Straight line segments formed by rear edge points 36 of the upper surface of each bulge are used as the right contour lines 35-36 of the upper surface of each bulge.

S9.3, generating N by equidistant generating of left side contour lines 33-34 of the upper surface of the bulge₃The discrete points are called bulge upper surface left contour points, and N is generated by equidistant N of bulge upper surface right contour lines 35-36₃And the discrete points are called contour points on the right side of the upper surface of the bump.

S9.4, projecting discrete points on the windward side flow direction line of the 1 st bulge positioned at the leftmost side and contour points on the left side of the upper surface of the bulge to the upper surface of the wave rider body along a longitudinal section to generate contour points of the lower edge of the left side surface of the bulge, and smoothly connecting the contour points of the lower edge of the left side surface of the bulge to form contour lines 37-38 of the lower edge of the left side surface of the bulge; will be located at the rightmost N₁The discrete points on the windward side flow direction molded line of the strip bulge and the right side contour point of the upper surface of the bulge are projected to the upper surface of the wave rider body along the longitudinal sectionAnd generating bulge right side surface lower edge contour points, and smoothly connecting all bulge right side surface lower edge contour points to form bulge right side surface lower edge contour lines 39-40. In fig. 18, 37 represents the leading edge point of the 1 st bump on the windward side, and it also represents the lower edge contour point of the left side face of the 1 st bump; 38 denotes the Nth₃The lower edge contour point of the left side surface of each bulge; 39 denotes the Nth₁The leading edge point of the windward side of each bulge also represents the lower edge contour point of the right side surface of the 1 st bulge; 40 denotes the Nth₃The lower edge contour point of the right side surface of each bulge.

S9.5, adding₃Left side contour point 34 and Nth of upper surface of each bump₃Taking a straight line segment consisting of lower edge contour points 38 of the left side surface of each bulge as a left side contour line 34-38 of the bottom surface of the bulge, and taking the Nth bulge as a contour line₃Right side contour point 36 and Nth of upper surface of each bump₃Straight line segments formed by contour points 40 of the lower edge of the right side surface of each bulge are used as contour lines 36-40 of the right side of the bottom surface of each bulge.

And S9.6, projecting the rear edge points of the upper surface of the bulge to the upper surface of the wave rider body along the cross section to generate bulge bottom surface lower edge contour points, wherein all bulge bottom surface lower edge contour points form bulge bottom surface lower edge contour lines 38-40.

S9.7, taking a closed plane formed by a rear edge line 33-35 of the windward side of the bulge, a left side contour line 33-34 of the upper surface of the bulge, a right side contour line 35-36 of the upper surface of the bulge and a rear edge line 34-36 of the upper surface of the bulge as the upper surface of the bulge, and taking a closed plane formed by a flow direction molded line 37-33 of the windward side of the bulge, a left side contour line 33-34 of the upper surface of the bulge, a lower edge line 37-38 of the left side surface of the bulge and a left side contour line 34-38 of the bottom surface of the bulge as the left side surface of the bulge; will be N₁A closed plane formed by a strip bulge windward side flow direction molded line 39-35, a bulge upper surface right side contour line 35-36, a bulge right side surface lower edge line 39-40 and a bulge bottom surface right side contour line 36-40 is used as a bulge right side surface; and a closed plane consisting of a bulge upper surface back edge line 34-36, a bulge bottom surface left side contour line 34-38, a bulge bottom surface right side contour line 36-40 and a bulge bottom surface lower edge contour line 38-40 is used as the bulge bottom surface.

S9.8, the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge form a steering engine bulge, and the steering engine bulge and the wave rider body form an integrated design configuration.

As shown in fig. 19 and 20, the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge form a steering engine bulge, and the steering engine bulge 41 and the wave-rider body 42 form an integrated design; the configuration of the aircraft in which the air rudder 43 is installed on the upper surface of the bulge, the steering engine bulge and the wave rider body are integrally designed, and the air rudder 43 is combined together is shown in fig. 21.

The application case is as follows: according to the embodiment, the incoming flow Mach number is 10.0, the incoming flow static pressure is 1197.031Pa, and the incoming flow static temperature is 226.509K, the shape of the embodiment based on the sharp-pointed Von Karman curve steering engine bulge with the equal shock wave intensity of the leading edge line and the integrated design configuration of the wave rider body is generated by adopting the method provided by the embodiment, and the shape of the embodiment is numerically simulated.

Fig. 22 shows a numerical simulation grid of the steering engine bulge and the waverider body integrated design configuration in the longitudinal symmetry plane in the present embodiment, fig. 23 shows numerical simulation results of the steering engine bulge and the waverider body integrated design configuration in 6 different longitudinal sections in the present embodiment, where the parameter shown in the figure is a mach number of a flow field, where (a) represents a numerical simulation result of a longitudinal section with Z being 0 mm; (b) numerical simulation results representing a longitudinal section of 10 mm; (c) numerical simulation results representing Z20 mm; (d) table Z-numerical simulation results of 30 mm; (e) numerical simulation results representing Z40 mm; (f) numerical simulation results representing Z50 mm.

As can be seen from fig. 23, the shock wave forms of different longitudinal sections are basically the same as the flow field structure, which verifies that the steering engine bulge generated by the invention has the characteristics of the same shock wave intensity of each longitudinal section and the uniform distribution of force-heat load characteristics, and solves the design problem that the longitudinal shock wave intensity is not considered to be distributed along the transverse direction in the original steering engine bulge design method. Meanwhile, the shock waves with different longitudinal sections are appendage shock waves, so that the problem that the shock waves of the windward side of the original steering engine bulge are detached is solved.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for designing a pointed Von Karman curve steering engine bulge based on shock wave intensities of a leading edge line and the like is characterized by comprising the following steps of:

generating a wave-rider fuselage;

2. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 1, wherein: and generating a waverider body by using a osculating axisymmetric von Karman waverider design method according to the flight condition and the size of the aircraft.

3. The design method of the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line according to claim 1 or 2, wherein the design method comprises the following steps: uniformly dispersing the horizontal projection molded line of the leading edge line of the windward side of the bump from left to right to obtain N₁Horizontal projection type line dispersion of front edge line of windward side of each bulgePoint; projecting the horizontal projection type line discrete points of the leading edge line of each bump windward side to the upper surface of the wave rider body along the longitudinal section of each bump windward side to obtain N₁Front edge point of windward side of each bump, N₁The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.

4. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 3, wherein: the wave rider body is composed of a family of discrete points and is divided into a plurality of triangular grid units, each triangular grid unit is composed of three adjacent discrete points, and the upper surface of the wave rider body is composed of M triangular grid units.

5. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 4, wherein: sequentially solving the horizontal projection type line discrete points P passing through the ith bulge windward side leading edge line_L,iAnd the intersection point P of the straight line parallel to the Y axis and the plane where the jth triangular grid unit on the upper surface of the wave-rider body is located_c,j，i＝1,2...N₁J is 1,2.. M, and the intersection point P is determined_c,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judged_c,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point P_c,jNamely the leading edge point of the windward side of the ith bulge.

6. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 3, wherein: a longitudinal section corresponding to the leading edge point of the ith bulge on the windward side, wherein i is 1,2₁According to a straight line passing through the leading edge point of the windward side of the ith bulge and with the slope being the sine value of the average compression angle of the longitudinal section of the windward side of the bulge and the Y-direction coordinate value Y of the horizontal section where the trailing edge line of the windward side of the bulge is located_TSolving to obtain the X-direction coordinate value X of the rear edge point of the windward side of the bulge corresponding to the front edge point of the windward side of the ith bulge_T,iThereby obtainingThe i-th bulge is at the rear edge of the windward side.

7. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 6, wherein: obtaining an ith longitudinal section von Karman curve according to the lengths of the longitudinal section corresponding to the ith bulge windward leading edge point along the X direction and the Y direction and the coordinates of the ith bulge windward leading edge point along the X direction and the Y direction on the longitudinal section corresponding to the ith bulge windward leading edge point, wherein the ith longitudinal section von Karman curve equation is as follows:

8. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 7, wherein: the von Karman curve of the longitudinal section corresponding to the leading edge point of the windward side of the ith bulge is obtained by the following method:

solving the leading edge point P passing through the ith bulge windward side_L,iAnd the slope is the initial compression angle delta of the longitudinal section of the windward side of the bump₀Intersection point A of the sine value straight line and the i-th longitudinal section von Karman curve_iIntersection point A_iThe coordinate value in the X direction of (A) is X_A,i；

In the i-th longitudinal section von Karman curve, the coordinate value in the X direction is set at [ X ]_L,i,X_A,i]The inner part is a straight line segment, and the coordinate value in the X direction is [ X ]_A,i,X_T,i]The inner part uses von Karman curve, so that the i-th longitudinal section von Karman curve is changed into a combined line formed by a straight line section and the von Karman curve, namely the i-th longitudinal section von Karman curveTo the cross-sectional tip von karman curve, the ith longitudinal cross-sectional tip von karman curve equation is as follows:

9. the method for designing the sharp-pointed von Karman curve steering engine bump based on the constant shock intensity of the leading edge line according to any one of claims 1 to 8, wherein: initial compression angle delta of longitudinal section of windward side of bump₀The value range of (a) meets the following requirements:

δ₀maximum wedge angle delta smaller than that of accessory shock wave generated by wedge_mI.e. delta₀＜δ_m；

δ₀Greater than the average compression angle delta, i.e. delta, of the longitudinal section of the windward side of the bulge₀＞δ。

10. The method for designing the pointed von karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 9, wherein: maximum wedge angle delta for generating attached shock wave by wedge splitting_mThe following method was used:

Wherein gamma is the specific heat ratio;

11. The leading edge-based of claim 6A design method for a pointed Von Karman curve steering engine bulge with line equal shock wave intensity is characterized by comprising the following steps of: according to the length of the wing root of the air rudder, setting the cross section position X of the rear edge of the upper surface of the drum package to be X_TAnd projecting the rear edge point of the windward side of the bulge to the cross section of the rear edge of the upper surface of the bulge at the corresponding longitudinal section of the rear edge point of the windward side of each bulge, generating the corresponding rear edge point of the upper surface of the bulge, and smoothly connecting the rear edge points of the upper surface of the bulge to form a rear edge line of the upper surface of the bulge.

12. The method for designing the pointed von karman curve steering engine bump based on the constant shock intensity of the leading edge line as claimed in claim 11, wherein: a straight line section formed by connecting the trailing edge point of the windward side of the 1 st bulge positioned at the leftmost side with the corresponding trailing edge point of the upper surface of the 1 st bulge is used as the left side contour line of the upper surface of the bulge, and the Nth bulge positioned at the rightmost side₁The trailing edge point of the windward side of each bulge corresponds to the Nth point₁And a straight line segment formed by connecting the rear edge points of the upper surface of each bulge is used as the right contour line of the upper surface of each bulge.

13. The method for designing the pointed von karman curve steering engine bump based on the constant shock intensity of the leading edge line as claimed in claim 12, wherein: the left side contour line of the upper surface of the bulge is equidistantly dispersed to generate N₃The discrete points are called bulge upper surface left side contour points, and the bulge upper surface right side contour lines are equidistantly and discretely generated into N₃The discrete points are called contour points on the right side of the upper surface of the bulge;

projecting discrete points on the 1 st bulge windward side flow direction molded line on the leftmost bulge and the bulge upper surface left side contour point to the upper surface of the wave rider body along the longitudinal section to generate bulge left side surface lower edge contour points, and smoothly connecting all bulge left side surface lower edge contour points to form a bulge left side surface lower edge contour line; will be located at the rightmost N₁And projecting the discrete points on the windward side flow direction molded line of the strip bulge and the right side contour point of the upper surface of the bulge to the upper surface of the wave rider body along the longitudinal section to generate lower edge contour points of the right side surface of the bulge, and smoothly connecting the lower edge contour points of the right side surface of the bulge to form a lower edge contour line of the right side surface of the bulge.

14. The method for designing the pointed von karman curve steering engine bump based on the constant shock intensity of the leading edge line as claimed in claim 13, wherein: will be N₃Left side contour line and Nth contour line of upper surface of each bump₃The straight line segment formed by connecting the contour points of the lower edge of the left side surface of each bulge is used as the left side contour line of the bottom surface of the bulge, and the Nth bulge is connected with the contour points of the lower edge of the left side surface of the bulge₃The contour point on the right side of the upper surface of each bulge and the Nth point₃And a straight line segment formed by connecting contour points of the lower edge of the right side surface of each bulge is used as a right side contour line of the bottom surface of the bulge.

15. The method of any one of claims 11 to 14, wherein the method comprises designing a sharp von Karman curve steering engine bump based on a leading edge line isoshock intensity, wherein the method comprises: and projecting the rear edge points of the upper surface of the bulge to the upper surface of the wave-rider body along the cross section to generate bulge bottom surface lower edge contour points, and smoothly connecting all bulge bottom surface lower edge contour points to form a bulge bottom surface lower edge contour line.

16. The method for designing the pointed von Karman curve steering engine bulge based on the constant shock intensity of the leading edge line as claimed in claim 1, wherein: