Design method of high ultrasonic speed skating and patrol integrated double waverider aircraft

Abstract

The invention discloses a design method of a high-ultrasonic-speed skating and patrolling integrated double-waverider aircraft, and relates to a hypersonic-speed aircraft forebody / air inlet channel. According to the large-range efficient flight requirement of a novel trajectory scheme of a hypersonic gliding-cruising aircraft, a gliding and patrol integrated hypersonic aircraft configuration is designed and comprises a cruising-level aerodynamic profile based on the flow direction double waverider principle and a gliding-level aerodynamic profile based on the minimum wave resistance outer cone approximation theory. The two stages of pneumatic molded surfaces are subjected to waverider design of respective design points and are combined in a symmetrical form, the gliding-stage pneumatic molded surface on the back of the aircraft in the gliding reentry stage downwards performs unpowered gliding range extension, and the cruising-stage pneumatic molded surface of the aircraft in the cruising stage is overturned downwards; in a designed inner / outer flow integrated axial symmetry reference flow field, an outer waverider wall surface and an inner waverider air inlet channel which are generated through streamline tracking provide a good waverider characteristic for a cruising stage. And a new thought is introduced for realizing the design of excellent flight performance of wide speed domain and extensive airspace of the hypersonic-speed fixed-geometry aircraft configuration.

Description

Technical Field

[0001] The present invention relates to the field of near-space hypersonic aircraft integrated design, and in particular to a design method for a hypersonic glide / cruise integrated dual waverider aircraft in which both the glide stage and the cruise stage aerodynamic surfaces achieve waveriding characteristics in the glide / cruise phase. Background Art

[0002] Hypersonic near-space vehicles are a type of aircraft that fly at hypersonic speeds in near-space. Their flight altitude is between that of aviation vehicles and space vehicles. They are in the combat blind spot of air defense weapons and orbital interceptors, and their military application value is enormous.

[0003] The important strategic significance of near-space has promoted the development of spacecraft for this space. This type of aircraft can be divided into two types according to whether it carries power: unpowered gliding and powered cruise. These two aircraft have their own advantages and disadvantages. For unpowered gliding aircraft, it does not carry fuel and engines, the structural design and aerodynamic layout are relatively simple, and the flight test is easy to achieve, but the lack of power leads to poor maneuverability; for powered hypersonic cruise aircraft, it can achieve maneuverability during flight, the control performance is improved, and the aircraft range can be extended. Traditional powered hypersonic cruise aircraft are sent to more than 100 kilometers outside the atmosphere by boosters and then reenter ballistically. This causes problems such as excessive inclination of the perigee track, excessive overload, and poor thermodynamic environment. Based on the shortcomings of the two flight schemes, the IH plan proposed by the United States combines the advantages of gliding and cruising flight schemes. The aircraft using this flight scheme carries a power system, glides unpowered at hypersonic speed, and starts the ramjet engine at the end of the gliding stage for cruise flight, improving the maneuverability of the aircraft at the end of the flight trajectory.

[0004] The proposal of new near-space flight schemes has put forward higher requirements for the aerodynamic performance of aircraft. In order to meet the needs in this field, near-space aircraft usually adopt an aerodynamic configuration with excellent lift-to-drag ratio (Hu Weijun, Zhou Jun. Analysis of interception strategies and interception weapon capabilities of near-space aircraft [J]. Modern Defense Technology, 2012, 40 (1).). Among them, waverider aircraft, with its excellent aerodynamic performance, has shown a broader prospect in future engineering applications. At present, there are many studies on gliding and cruising flight schemes, and some have successfully completed flight demonstrations. However, the waverider aerodynamic layout limited to "single-point design" is difficult to meet the requirements of the new ballistic scheme of hypersonic gliding-cruising aircraft to always maintain excellent aerodynamic performance in a wide speed range and pan-airspace. The current mainstream method of meeting the performance requirements of multiple working points through variable geometry configuration is effective, but it also significantly increases the structural complexity and body mass, thus forming an obstacle to the realization of efficient flight. In summary, it is urgent to carry out research on glide-cruise integrated waverider aircraft. At present, only a few scholars have conducted research on the design of waverider aircraft that combines two flight schemes, aiming to achieve efficient flight in a large range. Ding Feng designed a configuration that can have waveriding performance at two different Machs based on the cone-guided theory (Ding Feng. Research on the design method of two-stage waverider for hypersonic glide-cruise [D]: [Master]. Changsha: National University of Defense Technology: 2012.), but the shock wave exit profile of the cone-guided method can only be an arc, and the shape of the inlet entrance is limited, which is not conducive to the integrated design of the waverider and the inlet. Wang Qingwen of the National University of Defense Technology adopted a two-stage waverider design based on the tangent cone theory, and proposed a design idea of ​​achieving high Mach number waveriding through an aerodynamic shape with a fairing in the gliding stage, and achieving low Mach number waveriding with a waverider forebody after discarding the fairing in the cruise stage (Wang Qingwen. Design of two-stage waverider based on tangent theory [D]. Changsha: National University of Defense Technology, 2015). Although these studies have made important progress, there are still some limitations in practical applications. For example, most studies focus more on the design of external flow waveriders, ignoring the internal flow research in actual mission flight requirements. In addition, the design of a two-stage waverider with a piggyback combination faces multiple challenges, including shock wave interference between the two stages, mutual interference between internal and external flows, and negative effects such as increased drag due to the increase in frontal area. These problems limit the overall performance optimization of the design. Summary of the invention

[0005] The purpose of the present invention is to provide a design method for a hypersonic glide-cruise integrated dual waverider aircraft. Taking into account the above-mentioned problems existing in the prior art and the advantages of the back air intake layout in terms of high lift-to-drag ratio and the effect of reducing the temperature gradient brought about by the weaker shock wave intensity at the back at a positive angle of attack, the present invention aims at the requirements for excellent aerodynamic performance of hypersonic glide-cruise aircraft under wide speed range and pan-airspace conditions, and innovatively proposes a method of designing the back of the aircraft as a glide-level aerodynamic surface and combining the other half with a cruise-level aerodynamic surface based on the concept of "glide-cruise integrated". This design of a hypersonic glide-cruise integrated aircraft realizes the dual waverider characteristics of the glide and cruise stages, and meets the aerodynamic performance requirements of each flight stage by flipping the two-stage surface, in order to introduce new ideas for improving the efficient flight design of fixed geometry two-stage aerospace vehicles.

[0006] In the design method of the hypersonic glide-cruise integrated dual waverider aircraft described in the present invention, the integrated configuration is composed of a gliding-level aerodynamic surface and a cruise-level aerodynamic surface; it is worth noting that the cruise-level aerodynamic surface is divided into a waverider forebody and an inward-turning air inlet of the inner flow part, and an aircraft waverider wing of the outer flow part; the inner-retracting air inlet is provided with a compression surface of the air inlet, a lip of the air inlet, a shoulder of the air inlet and an isolation section of the air inlet.

[0007] The present invention comprises the following steps:

[0008] (1) Design of the internal / external flow integrated axisymmetric reference flow field of the cruise-class aerodynamic surface: According to the requirements of the new ballistic scheme of the hypersonic glide-cruise vehicle, Mach 7 is used as the design reference Mach number of the internal / external flow integrated axisymmetric reference flow field; According to the mission requirements of the cruise vehicle, that is, according to the airflow pre-compressibility and volume ratio of the forebody, a suitable shock wave generator is designed, and the axisymmetric flow field is solved by the curved streamline characteristic line method (MOCC) to ensure the stability and efficiency of the flow field; According to the inlet capture flow demand, the generated axisymmetric flow field is divided into internal and external, the external part includes the external flow field between the outer cone shock wave and the generator; the internal part includes the external cone flow field of the waverider forebody and the internal cone flow field of the inlet; Among them, the outer cone flow field is also a part between the outer cone shock wave and the generator. The inner cone shock wave curve is defined on the basis of the outer cone flow field, and the inner cone flow field is also solved by the curved streamline characteristic line method to obtain the inner cone flow field. Finally, the internal and external flow fields are integrated to design the internal / external flow integrated axisymmetric reference flow field;

[0009] (2) Design the forebody of the internal flow part and the inner turning inlet of the cruise-class aerodynamic profile: Define the FCT (Flow Capture and Transformation) curve of the cruise-class aerodynamic profile and divide it into the internal flow / external flow design part according to the capture flow requirement. Then combine the FCT curve of the internal flow part with the given inner turning inlet capture profile. Streamline tracing in the internal / external flow integrated axisymmetric reference flow field obtains the waverider wall surface and the inner turning inlet compression profile surface as the forebody of the inner turning inlet. The inlet cover wall and the isolation section are generated by geometric transition to ensure the continuity of structural strength and aerodynamic performance.

[0010] (3) Design the waverider wall of the cruise-class aerodynamic profile: trace the FCT curve of the external flow section in the axisymmetric reference flow field of the integrated internal / external flow to obtain the waverider wing of the aircraft;

[0011] (4) Design of axisymmetric reference flow field of the glide-stage aerodynamic surface: According to the requirements of the new ballistic scheme of the hypersonic glide-cruise vehicle, Mach 10 is used as the design reference Mach number for constructing the axisymmetric reference flow field; based on the minimum wave resistance outer cone approximation theory, a low-drag axisymmetric minimum wave resistance shock wave generator that meets the volume requirements is designed and generated. The axisymmetric reference flow field is calculated and solved by the curved streamline characteristic line method;

[0012] (5) Design of the glide-stage aerodynamic surface: The back of the integrated configuration, i.e., the glide-stage aerodynamic surface, is also designed as a waverider wall, and shares the same three-dimensional leading edge with the cruise-stage aerodynamic surface. The corresponding inlet capture profile is calculated based on the three-dimensional leading edge, and after being discretized, the streamlines are traced in each kissing surface in the axisymmetric reference flow field using the kissing theory. The streamlines in each kissing surface are combined to form the glide-stage aerodynamic surface. The cruise-stage and glide-stage aerodynamic surfaces are symmetrically geometrically spliced ​​to ultimately obtain a glide-cruise integrated hypersonic vehicle configuration.

[0013] In step (2), the forebody and the inward-turning air inlet of the inner flow part of the designed cruise-level aerodynamic surface can realize "flow double waveriding", that is, the leading edge of the forebody and the leading edge of the air inlet lip of the aircraft can both be attached to the shock wave surface, and the integration of the two will not destroy its waveriding characteristics.

[0014] In step (5), the designed gliding stage aerodynamic surface is specifically: when generating the gliding stage aerodynamic surface structure, it adopts the same leading edge profile as the cruise stage to perform streamline tracking in the gliding stage axisymmetric flow field; the gliding and cruise integrated hypersonic aircraft configuration can maintain good wave riding characteristics at the design points of the gliding and cruise stages.

[0015] In step (1) and step (4), the governing equations of the bending shock wave theory are as follows:

[0016]

[0017] Among them, p is pressure, δ is flow angle, μ is Mach angle, ρ is density, V is stream velocity, w is circumferential velocity, γ is specific heat ratio, j is judgment factor, s is streamline, l is characteristic line, φ is circumferential angle, P is the derivative of pressure along streamline, D is the derivative of flow angle along streamline, y is the ordinate in Cartesian coordinate system, and a is local sound speed.

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

[0019] The bulge forebody designed and generated in the axisymmetric reference flow field model with both internal and external flow fields can achieve effective displacement of the incoming flow boundary layer; the glide-cruise integrated hypersonic aircraft designed by the present invention can achieve excellent wave-riding characteristics in both the glide and cruise stages in the new ballistic scheme by flipping the profile. It not only effectively improves the aerodynamic performance of the aircraft under the full working envelope, thereby achieving efficient flight in a wide speed range and pan-airspace, but also meets the requirements of volume ratio, and its structural design is more in line with the development needs of future aircraft. Specifically, the new ballistic scheme is in an unpowered gliding state when loaded. The glide-cruise integrated hypersonic aircraft configuration is back-down, and the belly air inlet is weakened by the heat flow. The wave-riding gliding-stage aerodynamic surface makes the gliding stage have excellent lift-drag characteristics. Entering the cruise stage, the "flow-direction double wave-rider" cruise-stage aerodynamic surface flipped downward also provides good wave-riding characteristics for the cruise stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of a new trajectory scheme for a hypersonic glide-cruise vehicle.

[0021] Figure 2 It is a schematic diagram of the design principle of the external flow field in the internal / external flow integrated axisymmetric basic flow field.

[0022] Figure 3 It is a schematic diagram of the design principle of the internal flow field in the internal / external flow integrated axisymmetric basic flow field.

[0023] Figure 4 It is the design principle diagram of the aerodynamic surface of the cruise stage of a semi-model configuration of a hypersonic vehicle with integrated gliding and cruising functions.

[0024] Figure 5 It is a side view of the aerodynamic surface of the cruise stage of a semi-model configuration of a hypersonic aircraft with integrated gliding and cruising capabilities.

[0025] Figure 6 It is a three-axis measurement of the aerodynamic surface of the cruise stage of a semi-model configuration of a hypersonic aircraft with integrated gliding and cruising functions.

[0026] Figure 7It is the design principle diagram of the aerodynamic surface of the gliding stage of a half-model configuration of a hypersonic vehicle with integrated gliding and patrolling.

[0027] Figure 8 This is a front view of the half-model configuration of the integrated gliding and patrolling hypersonic aircraft.

[0028] Fig. 9 It is a three-dimensional view of the half-model configuration of the integrated gliding and cruising hypersonic aircraft.

[0029] The marks in the figure are as follows: 1 represents the outer cone shock wave generator of the cruise-level aerodynamic profile, 2 represents the forebody shock wave, 3 represents the incident shock wave of the inlet, 4 represents the FCT curve of the cruise-level aerodynamic profile, 5 represents the design area of ​​the internal flow part of the cruise-level aerodynamic profile, 6 represents the design area of ​​the external flow part of the cruise-level aerodynamic profile, 7 represents the capture line of the upper lip of the inlet, 8 represents the capture line of the lower lip of the inlet, 9 represents the capture line of the side wall of the inlet, 10 represents the forebody leading edge line of the internal flow part, 11 represents the upper lip of the inlet, 12 represents the lower lip of the inlet, and 13 represents the side wall of the inlet Leading edge line, 14 represents the waverider wall of the internal flow part as the forerunner of the inward-turned air inlet, 15 represents the air inlet throat section, 16 represents the inner contraction surface of the air inlet, 17 represents the air inlet isolation section, 18 represents the air inlet outer cover wall, 19 represents the forerunner leading edge line of the external flow part, 20 represents the waverider wing of the cruise stage of the aircraft, 21 represents the minimum wave resistance shock wave generator of the gliding stage aerodynamic surface, 22 represents the three-dimensional shock wave surface of the gliding stage aerodynamic surface, 23 represents the three-dimensional leading edge of the gliding stage aerodynamic surface, 24 represents the air inlet capture line of the gliding stage aerodynamic surface, and 25 represents the gliding stage aerodynamic surface. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the following embodiments will further illustrate the present invention in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0031] Since the design of the integrated gliding and cruising hypersonic aircraft is highly symmetrical, only half of the model will be used for explanation below.

[0032] See also Figures 1 to 9 A method for designing a hypersonic gliding and patrolling dual waverider aircraft, the main steps of which include:

[0033] 1. Design of the internal / external integrated axisymmetric reference flow field of the cruise-level aerodynamic profile: Based on the mission requirements of the new trajectory scheme of the hypersonic glide-cruise aircraft, the present invention takes the incoming Mach number Ma7 and the flight altitude 28km as the design point to design the following: Figure 1 , 2The internal and external flow fields are combined to form an integrated axisymmetric reference flow field of internal and external flow. First, the basic flow field of the external flow is generated by the shock wave generator 1. Specifically, a convex curve OA passing through the origin of the coordinate system is defined as the shock wave generator 1, and the curve expression is defined by the following formula 1, where: represents the inclination angle at the origin of the coordinate system, represents the inclination angle at point A, and The axial and radial distances represent point A. The generator forms a forebody shock wave 2, and the flow field between the forebody shock wave 2 and the generator 1, that is, the basic flow field of the external flow, is calculated using the curved streamline characteristic line method.

[0034] (1)

[0035] On the basis of the external flow field, a cubic curve CD is defined as the incident shock wave 3 of the inlet, and the curve expression is as follows: Equation 2. Then, the inviscid flow field is solved by the curved streamline characteristic line method in the area behind the shock wave, and the internal flow basic flow field consisting of the external compression area OCD, the shock wave dependent domain CDE and the isentropic compression area DEFG is generated. The specific design process is as follows: the starting positions C and D of the incident shock wave 3 of the inlet are specified in the external flow basic flow field. The curved streamline characteristic line method is used to solve the shock wave dependent domain CDE, and the incoming flow conditions of the incident shock wave 3 of the inlet are determined by interpolation calculation in the external flow basic flow field. According to the predetermined Mach number distribution, the isentropic compression section DEFG is determined in the flow field, and then the basic flow field of internal and external flow integration is obtained.

[0036] (2)

[0037] 2. Design the front body and inner turning inlet of the inner flow part of the cruise-level aerodynamic surface: Define the FCT curve 4 of the cruise-level aerodynamic surface design, and divide it into the inner flow part design area 5 and the outer flow part design area 6 according to the capture flow requirement. First, the inner flow part aerodynamic surface is designed, specifically: Figure 3 The capture profiles of the upper and lower lips of the inner-turned inlet shown are obtained by scaling the forebody shock wave contour line 2, and the scaling ratio is Figure 2 The starting and ending positions of the incident shock wave are determined, such as the lower lip capture profile 8 by narrowing The capture line 7 of the upper lip is similarly obtained, and the straight line connecting points c and f is the capture line 9 of the side wall of the inlet. The FCT curve of the internal flow part and the capture line of the inward turning inlet entrance designed above are projected forward onto the forebody shock surface 2 and the incident shock surface 3 respectively, and the forebody leading edge line 10 of the internal flow part and the upper lip line 11, the lower lip line 12 and the sidewall leading edge line 13 of the inward turning inlet are obtained. The forebody leading edge line of the internal flow part is discretized and streamlined in the axisymmetric internal / external flow reference flow field to generate a series of streamlines, and these streamlines are lofted into flow surfaces to obtain the waverider wall 14 as the forebody of the inward turning inlet; the capture line of the inward turning inlet entrance is discretized and streamlined until the inlet throat section 15 (i.e. b'-c'-d'-e'), and the section position is determined by L1 and L2. At this time, the envelope surface formed by the obtained streamline cluster is the inner contraction profile 16 of the inner-turned air inlet. The air inlet isolation section 17 is designed by a geometric transition method of equal straight stretching, and the length of the isolation section is determined by L1, L2 and L3. The air inlet cover wall 18 is also generated by a geometric transition method.

[0038] 3. Design the waverider wall of the outflow part of the cruise-level aerodynamic profile: project the FCT curve of the outflow part forward onto the forebody shock surface to obtain the forebody leading edge line 19 of the outflow part, and then discretize it in the axisymmetric internal / external flow reference flow field to obtain the waverider wing 20 as the aircraft by streamline tracing. At this point, the design of the cruise-level aerodynamic profile is completed.

[0039] 4. Design of axisymmetric reference flow field of glide-stage aerodynamic profile: According to the mission requirements of the new ballistic scheme of hypersonic glide-cruise aircraft, Ma10 is used as the design point of axisymmetric reference flow field. Based on the minimum wave resistance outer cone approximation theory, the present invention adopts the minimum wave resistance generatrix equation derived by combining the variational method under the given coordinate conditions of the maximum cross-section and the bottom of the missile body proposed by Wang Zhongyuan, where x m is the horizontal coordinate of the maximum cross section of the projectile, a1 and a2 are Lagrange multipliers, and H(x) is the source intensity function, which is taken as the product of the cross-sectional radius y and y'. A low-resistance axisymmetric minimum wave resistance shock wave generator 21 that meets the volume requirements is designed and generated. The generator equation is shown in formula (3), and H(x) is the source intensity function. The generator can generate an axisymmetric three-dimensional shock wave surface 22, as well as an inviscid flow field between the three-dimensional shock wave surface and the minimum resistance cone. The axisymmetric reference flow field is calculated and solved by the curved streamline characteristic line method.

[0040] (3)

[0041] (5) Design of gliding-stage aerodynamic surface: The back of the aircraft configuration, i.e., the gliding-stage aerodynamic surface, is also designed as a waverider wall, and it shares a three-dimensional leading edge with the cruise-stage aerodynamic surface. According to the following formula (4), T is the unit tangent vector at the discrete leading edge point of the current three-dimensional leading edge; uin is the free stream velocity vector; is the effective shock angle, which is defined as the angle of the straight line connecting the front and end points of a curved shock wave, and approximates the shock angle of the curved shock wave; is the angle between the tangent plane where the discrete leading edge point of the three-dimensional leading edge is located and the z-axis; D is the angle between the bottom projection of the tangent vector at the discrete leading edge point of the current three-dimensional leading edge and the y-axis; L L represents the projection distance of the discrete leading edge points of the three-dimensional leading edge on the bottom surface of the waverider; L It represents the horizontal projection distance between the discrete leading edge point of the current three-dimensional leading edge and the bottom surface of the waverider body. The inlet capture profile 24 of the gliding-stage aerodynamic profile is designed by determining the three-dimensional leading edge 23 of the gliding-stage aerodynamic profile and introducing the effective shock wave angle. After the parameters such as the inlet capture profile are discretized, the streamlines are tracked in each tangent surface using the tangent theory in the axisymmetric reference flow field. The streamlines in each tangent surface are combined to form the gliding-stage aerodynamic profile 25. The two-stage aerodynamic profiles are symmetrically geometrically spliced ​​to finally obtain the gliding-cruising integrated hypersonic aircraft configuration.

[0042] (4)

[0043] The present invention includes a waveriding design of two-stage aerodynamic surfaces, wherein the cruise-stage aerodynamic surface includes a waverider forebody and an inward-turning air inlet of the inner flow portion and a waverider wing of the outer flow portion. The cruise-stage aerodynamic surface designed in an axisymmetric flow field integrating inner and outer flows has its entire lower surface completely "riding" on a three-dimensional external compression shock wave, and has good full waveriding characteristics; the three-dimensional internal contraction shock wave seals the full flow capture of the three-dimensional internal contraction air inlet. The gliding-stage aerodynamic surface designed based on the minimum wave resistance outer cone approximation theory also strictly rides the wave at the design point. Aiming at the requirements for excellent aerodynamic performance of hypersonic gliding-cruising aircraft under wide speed range and pan-airspace conditions, the present invention innovatively proposes a method of designing the back of the aircraft as a gliding-stage aerodynamic surface and combining it with the other half of the cruise-stage aerodynamic surface based on the concept of "gliding and cruising in one". This integrated gliding and cruising hypersonic aircraft design achieves dual-wave characteristics in the gliding and cruising phases, and meets the aerodynamic performance requirements of each flight phase by flipping the two-stage surface, in order to introduce new ideas for improving the efficient flight design of fixed geometry two-stage aerospace vehicles.

[0044] The above embodiments are only preferred embodiments of the present invention and cannot be considered to limit the scope of the present invention. All equivalent changes and improvements made within the scope of the present invention should still fall within the scope of the present invention.

Claims

1. Design method of hypersonic glide-cruise dual waverider aircraft, characterized by The following steps are involved: (1) Design the internal / external flow integrated axisymmetric reference flow field of the cruise-level aerodynamic surface: According to the requirements of the new ballistic scheme of the hypersonic glide-cruise vehicle, Ma7 is used as the design point of the internal / external flow integrated axisymmetric reference flow field; according to the mission requirements of the cruise vehicle, that is, according to the airflow pre-compressibility and volume ratio of the forebody, a suitable shock wave generator is designed, and the axisymmetric flow field is solved by the curved streamline characteristic line method; according to the inlet capture flow demand, the generated axisymmetric flow field is divided into an internal and an external part, the external part includes the external flow field between the outer cone shock wave and the generator; the internal part includes the internal flow field composed of the outer cone flow field of the waverider forebody and the inner cone flow field of the inlet; The outer cone flow field is also a part between the outer cone shock wave and the generating body. The inner cone shock wave curve is defined on the basis of the outer cone flow field. The inner cone flow field is also obtained by solving the curved streamline characteristic line method of the curved shock wave theory. Finally, an axisymmetric benchmark flow field integrating internal and external flows was designed; (2) Design the forebody of the inner flow part of the cruise-stage aerodynamic profile and the inner-turning inlet: Define the FCT curve of the cruise-stage aerodynamic profile and divide it into the inner / outer flow design part according to the capture flow requirement. Then, the FCT curve of the inner flow part and the given inner-turning inlet capture profile are traced in the axisymmetric inner flow reference flow field to obtain the waverider wall surface and the inner-turning inlet compression profile surface as the forebody of the inner-turning inlet. The inlet cover wall surface and the isolation section are generated by geometric transition. (3) Design the waverider wall of the cruise-level aerodynamic profile: trace the FCT curve of the outflow part in the axisymmetric outflow reference flow field to obtain the waverider wing of the aircraft; (4) Design of axisymmetric reference flow field of the glide-stage aerodynamic surface: According to the requirements of the new ballistic scheme of the hypersonic glide-cruise vehicle, Ma10 is used as the design point of the axisymmetric reference flow field; based on the minimum wave resistance outer cone approximation theory, a low-drag axisymmetric minimum wave resistance shock wave generator that meets the volume requirements is designed and generated. The axisymmetric reference flow field is calculated and solved by the curved streamline characteristic line method of the curved shock wave theory; (5) Design of the glide-stage aerodynamic surface: The back of the integrated configuration, i.e., the glide-stage aerodynamic surface, is also designed as a waverider wall and shares the same leading edge with the cruise-stage aerodynamic surface. The inlet capture profile of the glide-stage aerodynamic surface is designed based on the solved three-dimensional leading edge combined with the effective shock wave angle method. After being discretized, the streamlines in each kissing surface are traced in the axisymmetric reference flow field using the kissing theory. The streamlines in each kissing surface are combined to form the glide-stage aerodynamic surface. The two-stage aerodynamic surfaces are symmetrically geometrically spliced ​​to finally obtain the glide-cruise integrated hypersonic aircraft configuration.

2. The design method of the hypersonic gliding and cruising dual waverider aircraft as claimed in claim 1, characterized in that In step (2), the forebody and the inward-turning air inlet of the inner flow portion of the designed cruise-level aerodynamic profile are used to realize "flow-directed double waveriding", that is, the leading edge of the forebody and the leading edge of the air inlet lip of the aircraft can both be attached to the shock wave surface, and the integration of the two will not damage the waveriding characteristics.

3. The design method of the hypersonic gliding and cruising dual waverider aircraft as claimed in claim 1, characterized in that In step (5), the glide stage aerodynamic surface is designed, specifically: when generating the glide stage aerodynamic surface structure, the same leading edge profile as the cruise stage is used to perform streamline tracking in the glide stage axisymmetric flow field; the glide-cruise integrated hypersonic aircraft configuration can maintain good wave-riding characteristics at both the glide and cruise stage design points.

4. The design method of a hypersonic gliding and cruising dual waverider aircraft as claimed in claim 1, characterized in that In step (1) and step (4), the governing equations of the bending shock wave theory are as follows: Among them, p is pressure, δ is flow angle, μ is Mach angle, ρ is density, V is stream velocity, w is circumferential velocity, γ is specific heat ratio, j is judgment factor, s is streamline, l is characteristic line, φ is circumferential angle, P is the derivative of pressure along streamline, D is the derivative of flow angle along streamline, y is the ordinate in Cartesian coordinate system, and a is local sound speed.

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