CN113378298B - Hypersonic-velocity double-cone wave-rider gliding aircraft and aerodynamic shape design method - Google Patents

Hypersonic-velocity double-cone wave-rider gliding aircraft and aerodynamic shape design method Download PDF

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CN113378298B
CN113378298B CN202110667555.1A CN202110667555A CN113378298B CN 113378298 B CN113378298 B CN 113378298B CN 202110667555 A CN202110667555 A CN 202110667555A CN 113378298 B CN113378298 B CN 113378298B
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fillet
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CN113378298A (en
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杨雨欣
李涛
吴昌聚
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Zhejiang University ZJU
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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Abstract

The invention discloses a hypersonic-speed double-cone wave-rider gliding aircraft and a pneumatic appearance design method. The pneumatic profile comprises a biconic upper and lower surface, a biconic profile, a rounded transition between the upper and lower bodies, and an arrangement of control rudders. The molded line of the upper surface and the lower surface of the double cone isCSTSuperposition of curve and exponential function, conversion of standard equation in which the biconical contour line is exponential function, the fillet curve between upper and lower surface contour lines is circle, and the control surface contour line isCSTAnd (4) superposition of standard equations of curves and circles and a linear function. The aerodynamic shape obtained by the design method of the invention has the typical characteristics of the aerodynamic layout of a real aircraft, is suitable for flying in the near space with high Mach number, and the control rudder can be retracted in the double cones and popped up when needed, thereby increasing the stability in high-altitude extremely-high-speed flying. The whole aerodynamic shape can be completely described by the mathematical expression analysis, the aircraft shape can be conveniently and quickly changed according to the design requirement, and the iterative requirement of the aircraft optimization design on the aerodynamic shape is met.

Description

Hypersonic-velocity double-cone wave-rider gliding aircraft and aerodynamic shape design method
Technical Field
The invention relates to a hypersonic-speed double-cone wave-rider gliding aircraft and a pneumatic appearance design method, and belongs to the technical field of optimization design of aircrafts.
Background
After the hypersonic gliding aircraft reaches high altitude by utilizing the boosting rocket, the hypersonic gliding aircraft performs unpowered gliding flight at the high altitude at extremely high speed, and during the gliding flight, the hypersonic gliding aircraft mainly depends on aerodynamic lift force to overcome self gravity for flight, so that the hypersonic gliding aircraft is required to have good aerodynamic shape so as to realize long-distance stable flight. When the shape of the aircraft is optimized to carry out pneumatic design, the pneumatic shape needs to be iteratively designed, the aircraft needs to be parameterized and modeled for conveniently and quickly changing the shape of the aircraft, and parameters selected by modeling need to have certain physical significance, so that the shape obtained by optimization is closer to the actual requirement. In addition, the aerodynamic performance of the traditional single-cone gliding aircraft is obviously reduced when the traditional single-cone gliding aircraft flies at a very high speed at high altitude, and a new aerodynamic shape form needs to be explored in order to ensure that the hypersonic aircraft has good aerodynamic performance when the hypersonic aircraft flies at a high mach number at high altitude.
Disclosure of Invention
In order to solve the problems, the invention provides a hypersonic-velocity double-cone wave-rider gliding aircraft and a pneumatic appearance design method. The aerodynamic shape obtained by the design method provided by the invention has the typical characteristics of the aerodynamic layout of a real aircraft, and has a waverider-like characteristic when the near space flies at a high Mach number, the upper surface pressure is lower than the incoming flow pressure, the lower surface pressure is higher than the incoming flow pressure, and the aircraft has a high lift-drag ratio due to a large pressure difference between the upper surface and the lower surface. The edge reduces heat flow through round angle passivation, alleviates the solar heat protection degree of difficulty. When the aircraft flies to a certain height from high altitude, the control rudder pops out to control the aircraft, and the stability of the aircraft flying at high altitude and extremely high speed is improved. Meanwhile, the whole aerodynamic layout can be completely described by the analysis of a mathematical expression, all variables in the expression have corresponding physical meanings, the appearance of the aircraft can be conveniently and quickly changed according to design requirements, and the iterative requirement on the aerodynamic appearance in the optimized design is met.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a hypersonic speed double-cone wave-rider gliding aircraft is characterized in that the aerodynamic appearance comprises double-cone upper and lower surfaces, a double-cone profile, fillet transition between an upper machine body and a lower machine body, a control rudder, a fillet and smooth transition between the control rudder, the upper surface and the fillet; the control rudders are three in number, can be retracted in the double cones, and are positioned on the upper surfaces of the double cones when being popped up, and the other two control rudders are positioned on the round corners; the biconical upper and lower surface profile lines are the superposition of a CST (Class function/Shape function Transformation, based on a type function/Shape function Transformation technology) curve and an exponential function, the biconical profile line is the exponential function, the fillet curve between the upper and lower surface profile lines is the Transformation of a standard equation of a circle, and the control surface profile line is the superposition of the CST curve, the standard equation of the circle and a linear function.
The double cone is divided into a first cone and a second cone, and the conversion from the first cone to the second cone is realized by changing the upper half cone angle and the lower half cone angle; each cone is divided into a plurality of sections, each section being described by upper and lower surface profiles; the upper surface profile line and the lower surface profile line are expressed by a functional expression formed by eleven variables, namely a first cone upper half-cone angle, a first cone lower half-cone angle, a second cone upper half-cone angle, a second cone lower half-cone angle, a first cone length, a second cone length, an upper surface profile line control parameter, a lower surface profile line control parameter, a double cone profile curve control parameter, a fillet radius and a bottom surface width; the coordinate expression of the points on the profile line of the upper and lower surfaces of the first cone is as follows:
Figure BDA0003117495340000021
wherein i is the number of the cross section, liIs the normal distance between the ith cross section and the end head, L1Is a first taper length, WiThe maximum width of the ith cross section, up corresponds to the upper surface, abbreviated as u, down corresponds to the lower surface, abbreviated as l, Nu、NdFor control parameters of upper and lower surface profiles, RiIs the fillet radius at the ith cross section,
Figure BDA0003117495340000022
the molded line heights of the upper surface and the lower surface of the ith cross section are shown,
Figure BDA0003117495340000023
the expression of (a) is:
Figure BDA0003117495340000024
Figure BDA0003117495340000025
wherein the content of the first and second substances,
Figure BDA0003117495340000026
respectively an upper half cone angle and a lower half cone angle of the first cone;
the coordinate expression of the point on the second cone upper and lower surface molded line is as follows:
Figure BDA0003117495340000031
wherein L is the total length of the double cones,
Figure BDA0003117495340000032
is the profile height W of the upper and lower surfaces of the last section of the first cone1maxThe width of the last section.
The biconical contour line is expressed by an exponential function, and the coordinate expression of the biconical contour line is as follows:
Figure BDA0003117495340000033
wherein, Wmax＝W2maxThe maximum width of the double cone is at the end of the second cone, and the profile functions of the first cone and the second cone double cone are the same.
The fillet and the upper and lower surfaces between smooth transition, from the end to the bottom fillet between radius linear growth, the fillet coordinate expression is:
Figure BDA0003117495340000034
wherein, y1、
Figure BDA0003117495340000035
Respectively are the y values of the first point and the last point of the upper surface profile line and the lower surface profile line,
Figure BDA0003117495340000036
is the z value of the first point of the upper surface profile.
The hypersonic speed double-cone wave-rider gliding aircraft passes through the height and the position q of a rudder1Position q2Three parameters describe the shape of the control rudder, and the expression of the points on the control rudder and the parallel part of the double cones is as follows:
Figure BDA0003117495340000041
where R is the radius of the rudder apex circle, R ═ RmaxThe expression of the point on the rudder of the part connected with the double cone is as follows:
Figure BDA0003117495340000042
a method for designing the aerodynamic appearance of the hypersonic-velocity double-cone wave-rider gliding aircraft comprises the following steps:
1) determining the expressions of the molded lines and the contour lines of the upper surface and the lower surface of the biconical cone according to the parameters;
2) determining an expression of a fillet according to the fillet parameter;
3) determining a rudder expression based on the upper surface profile expression and the lower surface profile expression in the step 1) and determining an elevator expression based on the fillet expression in the step 2) according to control rudder parameters;
4) determining the control surface according to the control rudder expression obtained in the step 3).
The design method comprises the steps of changing the upper half cone angle and the lower half cone angle as well as the length of the first cone and the length of the second cone to realize the transition from the first cone to the second cone, determining the height of each section through the upper half cone angle, the lower half cone angle and x, and determining the maximum width of the molded line of the upper surface and the lower surface of each section through a contour line function.
In step 1), the value of x is from 0 to L1Traversing to obtain a plurality of upper and lower surface molded lines; for each x, let y be from
Figure BDA0003117495340000043
To
Figure BDA0003117495340000044
And traversing to obtain points forming each molded line to generate an upper surface and a lower surface.
In the step 2), a left round corner and a right round corner are determined by a semicircle intersected with the upper surface contour line and the lower surface contour line, and a round corner curve is obtained by traversing alpha from 0 to pi.
In the step 3), each control rudder is divided into a part rudder which is parallel to the double cones and a part rudder which is connected with the double cones to express the molded surface, the curve of the part of the rudder which is connected with the double cones and the curve of the part which is parallel to the double cones are determined through the expression, and corresponding points are sequentially connected to generate the whole control surface.
Compared with the prior art, the invention has the beneficial effects that:
the aerodynamic shape obtained by the design method provided by the invention completely has the typical characteristics of the aerodynamic layout of a real aircraft, and meanwhile, the whole aerodynamic shape can be completely described by the analysis of a mathematical expression, so that the aircraft shape can be conveniently and quickly changed, and the iterative requirement on the aerodynamic shape in the optimization design is met.
The aerodynamic shape obtained by the design method has a large volume, and because the lower surface pressure is increased sharply and the upper surface pressure is smaller than the incoming flow pressure, the aircraft has certain wave-rider characteristics, and the aircraft obtains a high lift-drag ratio because the pressure difference between the upper surface and the lower surface is large. The edges of the aircraft are passivated through round corners, so that heat flow is effectively reduced, and the heat-proof difficulty is relieved. The flight resistance and the heat flow are reduced when the control rudder contracts, and the transverse stability and the course stability are enhanced when the control rudder needs to pop up, so that the control of the aircraft under the high-altitude extremely-high-speed flight is facilitated.
Drawings
FIG. 1 is a schematic diagram of an example generated by a method of aerodynamic profile design for a hypersonic double-cone ride-wave gliding aircraft.
FIG. 2 is a schematic view of the aerodynamic profile of a hypersonic double-cone wave-rider gliding aircraft.
FIG. 3 is a schematic side view of the parameters.
FIG. 4 is a schematic view of the parameters of a double cone.
FIG. 5 is a schematic view of bottom surface parameters.
Fig. 6 is a schematic diagram of the control rudder and its parameters.
Fig. 7 is an enlarged view of the bottom of the control rudder.
Fig. 8 is an enlarged schematic view of the control rudder bottom and fillet.
FIG. 9 is a schematic diagram of generation of a bicone from contour lines and upper and lower surface contour lines.
FIG. 10 is a diagram showing the rule of change of contour parameters.
FIG. 11 is a graph showing the variation of the parameters of the upper surface profile.
FIG. 12 is a graph showing the variation of the profile parameters of the lower surface.
FIG. 13 is a schematic diagram showing the variation of the upper and lower surface profiles of a hypersonic double-cone wave-rider glider at different cross-sectional positions.
FIG. 14 is a pressure ratio cloud diagram of an example hypersonic double-cone wave-rider gliding aircraft.
FIG. 15 is a heat flux cloud diagram of an example hypersonic double-cone wave-rider gliding aircraft.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1-2, the aerodynamic profile of the hypersonic-velocity double-cone wave-rider gliding aircraft comprises a first cone 1, a second cone 2, a double-cone upper surface 3, a double-cone lower surface 4, a double-cone contour line 5, a fillet 6 and a control rudder 7.
The molded lines of the upper and lower surfaces of the biconical model are the superposition of a CST curve and an exponential function, the biconical contour lines are the exponential function, the fillet curve between the molded lines of the upper and lower surfaces is the transformation of a standard equation of a circle, and the molded line of the control surface is the superposition of the CST curve, the standard equation of the circle and a linear function.
As shown in fig. 3, the double cone is divided into a first cone 1 and a second cone 2, and the first cone 1 is transformed into the second cone 2 by changing the upper half cone angle and the lower half cone angle. As shown in fig. 9, each cone is divided into a plurality of sections, each section being described by a top and bottom surface profile. The upper surface profile line and the lower surface profile line pass through the first cone upper half cone angle
Figure BDA0003117495340000061
First cone lower half cone angle
Figure BDA0003117495340000062
Second taper upper half-cone angle
Figure BDA0003117495340000063
Second half cone angle
Figure BDA0003117495340000064
First taper length L1Second taper length L2Top surface profile control parameter NuLower surface profile control parameter NdAnd a function expression formed by eleven variables including a biconical profile curve control parameter n, a fillet radius R and a bottom surface width W is represented, and the physical significance of each parameter is shown in figures 3-8. The upper and lower surface profiles of the plurality of cross sections are generated from the function as shown in fig. 13, and finally the aircraft is formed as shown in fig. 9.
As shown in fig. 3, it can be seen that the physical meaning of the upper half-cone angle is the angle between the midpoint connecting line of the upper surface profile and the horizontal line, and the lower half-cone angle is the angle between the midpoint connecting line of the lower surface profile and the horizontal line. The profile curve control parameter n controls the shape of the 5, fig. 10 shows a change rule curve of n, and it can be seen from the figure that the larger the value of n, the flatter the profile, the sharper the biconical tip, and the larger the heat flow of the tip; the smaller the n value is, the smoother the contour line is, the blunter the end head is, the more natural the transition is, and the more favorable the reduction of the heat flow on the surface of the aircraft is. Top surface profile control parameter NuThe shape of the upper surface profile is controlled, and the figure 11 is taken as NuThe shape of the upper surface profile varies at different values, as can be seen with NuThe curve is increased, the two sides of the curve are protruded downwards more and more, and the curve is in an increasingly obvious 'thin and high' shape. Lower surface profile control parameter NlControl is the profile shape of the lower surface, and FIG. 12 is a graph taking NuThe shape of the lower surface profile varies with different values, NlThe smaller the curve, the closer the curve is to a square, NlThe closer to 1, the closer the curve is to parabolic.
The transition from the first cone 1 to the second cone 2 is realized by changing the angle of the upper half cone and the angle of the lower half cone, the height of each section is determined by the angle of the upper half cone and the angle of the lower half cone and x, and the maximum width of the molded line of the upper surface and the lower surface of each section is determined by a contour line function. And after the physical meanings of the parameters are clarified, giving out a function expression of each parting line.
The coordinate expression of the point on the first conical upper and lower surface profile is:
Figure BDA0003117495340000065
wherein i is the number of the cross section, liIs the normal distance between the i-th cross section and the end head, L1Is a first taper length, WiIs the maximum width of the i-th section. "up" corresponds to the upper surface, abbreviated as u, and "down" corresponds to the lower surface, abbreviated as l. N is a radical ofu、NdFor control parameters of upper and lower surface profiles, RiIs the fillet radius at the ith cross section,
Figure BDA0003117495340000071
is the height of the molded lines of the upper and lower surfaces of the ith cross section,
Figure BDA0003117495340000072
the expression of (a) is:
Figure BDA0003117495340000073
Figure BDA0003117495340000074
wherein the content of the first and second substances,
Figure BDA0003117495340000075
respectively an upper half cone angle and a lower half cone angle of the first cone.
The coordinate expression of the point on the second taper upper and lower surface molded line is as follows:
Figure BDA0003117495340000076
wherein L is the total length of the double cones,
Figure BDA0003117495340000077
the height of the molded line of the upper surface and the lower surface of the last section of the first cone W1maxThe width of the last section.
The biconical contour line is expressed by an exponential function, the maximum width of each section is equal to twice the maximum value of the absolute value of the y coordinate of the biconical contour line at the current position, and the coordinate expression of the biconical contour line is as follows:
Figure BDA0003117495340000078
wherein, Wmax＝W2maxThe maximum width of the double cone is at the end of the second cone, and the first cone and the second cone profile function are the same.
Smooth transition is passed through fillet 6 between the upper and lower surface, and 6 are variable radius fillets, and fillet radius is 0 in the end position, and is the biggest at the bottom radius, and fillet radius uniform variation from the end to the bottom. Corresponding each cross-section and for passing through the fillet between the upper and lower surface profile line and pass through, the fillet angle is pi, and each cross-section department fillet coordinate expression is:
Figure BDA0003117495340000081
wherein, y1、
Figure BDA0003117495340000082
Respectively the y values of the first point and the last point of the molded lines of the upper surface and the lower surface in each section,
Figure BDA0003117495340000083
is the z value of the first point of the upper surface profile.
The control rudders 7 are three in total and are composed of two elevators in the horizontal direction and two direction rudders connected to the upper surface in the vertical direction. Control rudder capable of contractingWithin the double cone, it springs out when required. The profile of the aircraft is described by the molded lines of the upper surface and the lower surface, the biconical contour lines and the fillet curves when the control rudder contracts, and the molded line of the control rudder surface is added on the original basis after the control rudder is popped up. The profile of the control surface passes through the height Pl of the control and the position 1 (q)1) Position 2 (q)2) Three parameters are described, wherein the expression of the point on the rudder parallel to the bicone is:
Figure BDA0003117495340000084
where R is the radius of the rudder apex circle, R ═ Rmax. The expression for the point on the rudder where the bicone meets is:
Figure BDA0003117495340000085
according to the above section line expression, the aerodynamic profile of the aircraft is generated by the following steps:
1) determining the expressions of the molded lines and the contour lines of the upper surface and the lower surface of the biconical cone according to the parameters;
2) determining an expression of a fillet according to the fillet parameter;
3) determining a rudder expression based on the upper surface profile expression and the lower surface profile expression in the step 1) according to the control rudder parameters, and determining an elevator expression based on the fillet expression in the step 2);
4) determining the control surface according to the control rudder expression obtained in the step 3).
In step 1), the value of x is from 0 to L1And traversing to obtain a plurality of upper and lower surface molded lines, wherein the upper surface molded lines are combined to form a biconical upper surface 3, and the lower surface molded lines are combined to form a biconical lower surface 4. At each cross-section, let y be from
Figure BDA0003117495340000091
To
Figure BDA0003117495340000092
And traversing to obtain all points on the upper surface contour and the lower surface contour. In step 2)And determining a left fillet and a right fillet by using a semicircle intersected with the profile lines of the upper surface and the lower surface, and traversing alpha from 0 to pi to obtain a fillet curve.
In the step 3), each control rudder is divided into a rudder parallel to a bicone and a rudder connected with the bicone to express a profile, a curve of the part, connected with the bicone, of the lower part of the rudder and a curve of the part, connected with the bicone, of the bicone are determined through a control surface profile expression, and corresponding points are connected in sequence to generate the whole control surface.
The aerodynamic shape obtained by the design method provided by the invention completely has the typical characteristics of the aerodynamic layout of a real aircraft, and meanwhile, the whole aerodynamic shape can be completely described by the analysis of a mathematical expression, so that the aircraft shape can be conveniently and quickly changed, and the iterative requirement on the aerodynamic shape in the optimization design is met.
The aircraft obtained by the design method has better aerodynamic characteristics, and a flow field pressure ratio cloud chart obtained by CFD numerical calculation of an example obtained by the design method is shown in figure 14. As can be seen from the figure, the upper surface pressure ratio of the aircraft is smaller than 1, which shows that the upper surface shock wave is tightly attached to the object surface, and the lower surface pressure ratio is 2-3, namely the upper surface pressure is obviously lower than the lower surface pressure. The pressure of the incoming flow passing through the aircraft is sharply increased on the lower surface, the pressure of the upper surface is smaller than the pressure of the incoming flow due to the fact that the shock wave is attached to the body, and the pressure difference between the upper surface and the lower surface is large, so that the aircraft has certain wave-rider characteristics, and a high lift-drag ratio is obtained. Fig. 15 shows a cloud of surface heat flows of the aircraft, and it can be seen from the cloud that, in addition to the higher heat flows at the ends of the aircraft, the surface heat flows are significantly reduced at the transition positions of the upper and lower surfaces due to the existence of the fillets, thereby effectively relieving the difficulty of heat protection. The table is the aerodynamic coefficient of the example, and the fact that the aircraft has a high lift-drag ratio and a low pitching moment coefficient can be seen, which shows that the aerodynamic shape obtained by the design method effectively enhances the stability of the transverse direction and the course direction and is beneficial to controlling the aircraft in high-altitude extremely-high-speed flight.
Figure BDA0003117495340000093
The embodiments in the above description can be further combined or replaced, and the embodiments are only described as preferred examples of the present invention, and do not limit the concept and scope of the present invention, and various changes and modifications made to the technical solution of the present invention by those skilled in the art without departing from the design concept of the present invention belong to the protection scope of the present invention. The scope of the invention is given by the appended claims and any equivalents thereof.

Claims (7)

1. A hypersonic speed bipyramid class takes advantage of ripples gliding aircraft which characterized in that: the pneumatic appearance comprises a double-cone upper surface, a double-cone profile, fillet transition between an upper machine body and a lower machine body, and smooth transition between a control rudder, a fillet and the control rudder, the upper surface and the fillet; the control rudders are three in number, can be retracted in the double cones, and are positioned on the upper surfaces of the double cones when being popped up, and the other two control rudders are positioned on the round corners;
the biconical upper and lower surface molded lines are the superposition of a CST curve and an exponential function, the biconical contour line is the exponential function, a fillet curve between the upper and lower surface molded lines is the transformation of a standard equation of a circle, and the control surface molded line is the superposition of the CST curve, the standard equation of the circle and a linear function;
the double cone is divided into a first cone and a second cone, and the conversion from the first cone to the second cone is realized by changing the upper half cone angle and the lower half cone angle; each cone is divided into a plurality of sections, each section being described by upper and lower surface profiles; the upper surface profile and the lower surface profile are expressed by a function expression consisting of eleven variables, namely a first cone upper half-cone angle, a first cone lower half-cone angle, a second cone upper half-cone angle, a second cone lower half-cone angle, a first cone length, a second cone length, an upper surface profile control parameter, a lower surface profile control parameter, a double cone profile curve control parameter, a fillet radius and a bottom surface width; the coordinate expression of the points on the profile line of the upper and lower surfaces of the first cone is as follows:
Figure FDA0003639582000000011
wherein i is the number of the cross section, liIs the normal distance between the ith cross section and the end head, L1Is a first taper length, WiIs the maximum width of the i-th cross section, RiIs the fillet radius of the ith section, the upper surface of the aircraft is abbreviated as u, and the lower surface of the aircraft is abbreviated as l, Nu、NlFor the control parameters of the upper and lower surface profiles,
Figure FDA0003639582000000012
the molded line height of the upper and lower surfaces of the ith cross section, wherein
Figure FDA0003639582000000013
The expression of (a) is:
Figure FDA0003639582000000014
Figure FDA0003639582000000015
Figure FDA0003639582000000016
respectively an upper half cone angle and a lower half cone angle of the first cone;
the coordinate expression of the point on the second cone upper and lower surface molded line is as follows:
Figure FDA0003639582000000021
wherein L is the total length of the double cones,
Figure FDA0003639582000000022
is the profile height W of the upper and lower surfaces of the last section of the first cone1maxThe width of the last section of the first cone.
2. The hypersonic speed double-cone wave rider glider of claim 1, wherein: the biconical contour line is expressed by an exponential function, and the coordinate expression of the biconical contour line is as follows:
Figure FDA0003639582000000023
wherein the parameter n is a profile curve control parameter; w is a group ofmax＝W2maxThe first cone and the second cone have the same profile function.
3. The hypersonic speed double-cone wave rider glider of claim 2, wherein: the fillet and the upper and lower surfaces are in smooth transition, and the coordinate expression of the fillet is as follows:
Figure FDA0003639582000000024
wherein, y1、
Figure FDA0003639582000000025
The y values of the first point and the last point of the upper surface profile line and the lower surface profile line are respectively;
Figure FDA0003639582000000026
is the z value of the first point of the upper surface profile.
4. The aerodynamic profile design method of the hypersonic speed double-cone wave-rider gliding aircraft as claimed in claim 3, wherein: the method comprises the following steps:
1) determining the expressions of the molded lines and the contour lines of the upper surface and the lower surface of the biconical cone according to the parameters;
2) determining an expression of a fillet according to the fillet parameter;
3) determining a rudder expression based on the upper surface profile expression and the lower surface profile expression in the step 1) according to the control rudder parameters, and determining an elevator expression based on the fillet expression in the step 2);
4) determining the control surface according to the control rudder expression obtained in the step 3).
5. The design method according to claim 4, wherein: the transition from the first cone to the second cone is realized through the change of the upper half cone angle, the lower half cone angle, the length of the first cone and the length of the second cone, the height of each section is determined through the upper half cone angle, the lower half cone angle and x, and the maximum width of the molded line of the upper surface and the lower surface of each section is determined through a contour line function.
6. The design method according to claim 4, wherein: in step 1), the value of x is from 0 to L1Traversing to obtain a plurality of upper and lower surface molded lines; for each x, let y be from
Figure FDA0003639582000000031
To
Figure FDA0003639582000000032
And traversing to obtain points forming each molded line to generate an upper surface and a lower surface.
7. The design method according to claim 4, wherein: in the step 2), a left round corner and a right round corner are determined by a semicircle intersected with the upper surface contour line and the lower surface contour line, and a round corner curve is obtained by traversing alpha from 0 to pi.
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