A design method of internal-external flow integrated high-speed full-flow surface waverider aircraft

Abstract

The application discloses a kind of inner and outer flow integrated high-speed full-flow surface waverider aircraft design method, it is related to aerodynamic shape design field, comprising: S1, based on the constraint condition of incoming flow condition and axial symmetry curved surface cone, utilize characteristic line method to obtain two mutually matched first axial symmetry curved surface cone flow field, second axial symmetry curved surface cone flow field;S2, in two axial symmetry curved surface cone flow field, respectively construct upper waverider surface, lower waverider surface, precursor inlet of waverider aerodynamic configuration using streamer tracking method;S3, upper waverider surface, lower waverider surface and precursor inlet are assembled according to flow field characteristics, and the appearance structure of inner and outer flow integrated high-speed full-flow surface waverider aircraft is obtained.The application realizes the design of high-speed air-breathing waverider configuration from the level of theoretical method, all components are designed using flow surface and the flow field between each component is matched, which provides a very effective and efficient method and technical support for designing waverider configuration meeting engineering practical requirements.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic shape design. More specifically, this invention relates to a design method for a high-speed, full-flow-surface waverider aircraft that integrates internal and external flow. Background Technology

[0002] High-speed aerodynamic technology, especially the design technology of high-speed aerodynamic shapes, serves as a pioneer in the development of high-speed technology, determining both its direction and progress. Therefore, extensive research has been conducted both domestically and internationally on high-speed aerodynamic design technology. Examples include the aerodynamic shape design technologies for high-speed aircraft such as the X-51, X-43, and Trijet proposed in recent years. These aircraft employ integrated design technology for the forebody and air intake, using geometric modifications to achieve compatibility between the forebody and air intake, as well as between the forebody / air intake and the aircraft fuselage. However, these geometric modifications inevitably compromise the aerodynamic performance of the forebody / air intake to some extent. Building on this, domestic researchers have proposed integrated external cone waverider forebody / air intake design technologies and integrated internal cone waverider forebody / air intake design technologies. These technologies address the integration issue of the forebody / air intake using aerodynamic methods. However, the integration of the forebody air intake with the aircraft fuselage remains a challenge. Currently, most integrated designs of the forebody air intake and aircraft fuselage employ the CTS parametric method. This mathematically descriptive method is beneficial for the parametric optimization of the fuselage and offers high flexibility, but it involves a large computational load and is constrained by the dimensions of the optimization parameters and the optimization method, resulting in drawbacks such as high computational cost and the optimization results only having local optima. Furthermore, the use of aerodynamic methods to achieve forebody air intake integration largely focuses on solving the problem of integrating the aircraft's compression surface with the forebody air intake, and its engineering practicality is not strong.

[0003] The patent "Design Method for Hypersonic Integrated Internal and External Flow Full Waverider Aircraft" presents a design method for a waverider with coupled internal and external flows. This patent, through streamline tracing, obtains a fully coupled waverider aircraft with windward-facing waveriding. The key feature of this method is its "full waveriding," meaning that the windward flow field of the aircraft designed based on this method completely inherits the structure of the waverider. This method solves the problem of mutual interference between the waverider and the inlet flow field, realizing a windward-facing, coupled waverider design. It should be noted that this method focuses on solving the integration of the aircraft's compression surface and the forebody inlet; its leeward side uses free-flow surfaces as constraints. Further improvements are needed in its engineering practicality. Specifically, the patent "Design Method for Hypersonic Integrated Internal and External Flow Full Waverider Aircraft" has the following problems:

[0004] Firstly, the information such as the leading edge line and shock wave line between different components is directly given through geometric constraints. This method can only obtain part of the flow field of the aerodynamic shape (windward side and air intake) in the design, and it is difficult to customize the flow field of the leeward side according to the needs.

[0005] Secondly, the emphasis is on the concept of full wave riding, which means that the on-demand customization of the flow field is only focused on the design of the windward side, without involving the geometric constraints of the leeward side and the customized requirements of the flow.

[0006] Third, the leading edge shock wave of the reference flow field on the windward side and the leading edge shock wave of the reference flow field in the inlet share the same shock wave. The coupling between the front body and the inlet makes it difficult to achieve dual customization of geometry and flow. Furthermore, the leading edge shock wave of the aircraft and the shock wave at the lip of the inlet intersect at the lip, and flow field interference is very likely to occur under different angles of attack. Summary of the Invention

[0007] One object of the present invention is to solve at least the above-mentioned problems and / or defects, and to provide at least the advantages described below.

[0008] To achieve these objectives and other advantages of the present invention, a design method for a high-speed, full-flow-surface waverider vehicle integrating internal and external flow is provided, comprising:

[0009] S1. Based on the incoming flow conditions and the constraints of the axisymmetric surface cone, the flow fields of the first and second axisymmetric surface cones, which are matched with each other, are obtained using the method of characteristics.

[0010] S2. In two axisymmetric curved surface cone flow fields, the upper wavefront, lower wavefront, and forebody inlet of the wave-riding aerodynamic shape are constructed respectively using the streamline tracing method.

[0011] S3. Assemble the upper wavefront, lower wavefront, and forebody air intake according to the flow field characteristics to obtain the external structure of a high-speed full-flow surface waverider aircraft with integrated internal and external flow.

[0012] The construction of the forebody air intake includes: a top compression surface of the air intake, a bottom compression surface of the isolation section, and an outer envelope surface of the air intake lip.

[0013] Preferably, in S1, the incoming flow conditions include: static pressure. PS 0. Static temperature TS 0. Total pressure PT 0. Total temperature TT 0. Incoming Mach number Ma 0;

[0014] The constraints include: the volume of the first axisymmetric cone, the length of the first axisymmetric axis corresponding to the first axisymmetric cone, and the radius of the base circle of the first axisymmetric cone, i.e., the first trailing edge section circle. R 1;

[0015] The volume of the second axisymmetric cone, the length of the second axisymmetric axis corresponding to the second axisymmetric cone, and the radius of the base circle of the second axisymmetric cone, i.e., the circle of the third trailing edge section.R 3;

[0016] The methods for generating the first axisymmetric surface cone flow field and the second axisymmetric surface cone flow field are as follows:

[0017] S101. Select the type of generatrix of the axisymmetric surface cone;

[0018] S102. Based on the generatrix type and constraint conditions of the axisymmetric surface cone, obtain the corresponding first axisymmetric surface cone and second axisymmetric surface cone;

[0019] S103. Based on their respective axisymmetric surface cones and incoming flow conditions, the flow fields of the first and second axisymmetric surface cones and the corresponding first shock wave surface are obtained using the method of characteristics. SW 1. Second shock surface SW 2;

[0020] S104, the first shock wave surface SW The intersection of 1 and the first trailing edge section circle is defined as the second trailing edge section circle and the second shock surface. SW The intersection of 2 and the third trailing edge section circle is defined as the fourth trailing edge section circle.

[0021] Preferably, in S2, the method for obtaining the superior wavefront and inferior wavefront is as follows:

[0022] S2110. The second axisymmetric surface cone flow field is moved relative to the first axisymmetric surface cone flow field to obtain the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile.

[0023] S2120. Starting from a series of discrete points on the leading edge profile, and taking the first trailing edge shock profile as the shock profile, the forward streamline tracing is carried out in the first axisymmetric curved surface cone flow field to obtain the upper wave surface of the aerodynamic shape of the full-flow surface waverider.

[0024] S2130. Starting from the discrete point cluster on the projection curve corresponding to the leading edge profile, and taking the second trailing edge shock profile as the trailing edge shock profile of the lower wave surface, the lower wave surface is obtained by forward streamline tracing in the second axisymmetric curved surface cone flow field.

[0025] Preferably, the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile are obtained in the following manner:

[0026] S2111. Align the centers of the second trailing edge section circle and the fourth trailing edge section circle and place them in the same plane;

[0027] S2112. Fix the first axisymmetric curved surface cone flow field, and move the second axisymmetric curved surface cone flow field upwards by a distance along the vertical direction of the second axis of symmetry. d make SW 1 and SW 2 intersect, the distance d It is characterized by the following formula:

[0028]

[0029] In the above formula, R 2 is the radius of the second trailing edge section circle. R 4 is the radius of the fourth trailing edge section circle;

[0030] S2113, in SW 1 and SW When the two circles intersect, the intersection point of the second trailing edge section circle and the fourth trailing edge section circle is... A , B Connected line segments AB Defined as an intersecting chord, the length of the intersecting chord b It refers to the width of the aerodynamic shape of a high-speed, full-flow-surface waverider aircraft that integrates internal and external flows. SW 1 and SW The spatial intersection line formed by the two intersecting points is defined as the leading edge profile line;

[0031] After the intersecting chord divides the second trailing edge section circle, the upper circular arc segment located above the intersecting chord is defined as the first trailing edge shock profile.

[0032] After the intersecting chord divides the fourth trailing edge section circle, the upper circular arc segment located above the intersecting chord is defined as the second trailing edge shock profile.

[0033] Preferably, in S2, the method for obtaining the forebody air intake is as follows:

[0034] S2210. Starting from the discrete point clusters on the projection curve of the leading edge profile, and taking the arc segment of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, the forward streamline tracing is carried out in the flow field of the axisymmetric outer cone inlet to obtain the top compression surface of the inlet.

[0035] S2220. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and taking the leading edge arc segment of the inlet lip as the shock wave profile of the inlet trailing edge, the forward streamline tracing is performed in the axisymmetric outer cone inlet flow field to obtain the bottom compression surface of the isolation section.

[0036] S2230. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and using the second trailing edge shock profile as the trailing edge shock profile of the outer envelope surface of the inlet lip, the forward streamline tracing is performed in the second axisymmetric curved surface cone flow field to obtain the outer envelope surface of the inlet lip.

[0037] Preferably, in S2210, the axisymmetric outer cone inlet flow field is constructed within the second axisymmetric curved cone flow field, which is the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field. Given the compression form of the axisymmetric outer cone inlet wall, the compression surface of the axisymmetric outer cone inlet and the corresponding axisymmetric outer cone inlet flow field are generated using the method of characteristics.

[0038] Preferably, the specific process for obtaining the flow field of the axisymmetric outer cone inlet is as follows:

[0039] S2211, will SW 2. The projection on the symmetry plane of the forebody inlet is defined as... SW 2 busbars SW The intersection of the generatrix of the second axisymmetric surface cone and the generatrix of the second axisymmetric surface cone is defined as the cone vertex of the second axisymmetric surface cone;

[0040] S2212, in SW The distance from the second axis of symmetry on the second generatrix is ​​equal to the radius of the reference inlet capture circle. R c The point is taken as the leading edge point of the axisymmetric outer cone intake lip;

[0041] S2213. In the flow field of the second axisymmetric curved surface cone, iterate the leftward characteristic line starting from the leading edge point, and define the intersection of the leftward characteristic line and the generatrix of the second axisymmetric curved surface cone as the endpoint of the shock wave dependent domain at the leading edge of the axisymmetric outer cone inlet.

[0042] S2214, The distance between the cone vertex and the leading edge point... SW The generatrix is ​​defined as closed line I. The generatrix of the second axisymmetric surface cone between the cone apex and the endpoint of the leading edge shock wave dependent domain is defined as closed line II. The left-moving characteristic line between the leading edge point and the endpoint of the leading edge shock wave dependent domain is defined as closed line III. The closed region constructed by closed lines I, II, and III serves as the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field.

[0043] S2215. Using the method of characteristics, with the closed line III as the initial condition, and given the compression form of the axisymmetric external conical inlet wall, obtain the compression surface of the axisymmetric external conical inlet and the corresponding flow field of the axisymmetric external conical inlet.

[0044] Preferably, S2 also includes:

[0045] S2010, based on the given R c The capture surface of the inlet is constructed within the second axisymmetric curved conical flow field. The construction process is as follows:

[0046] S2011, the center of the circle passing through the fourth trailing edge section. O2. The vertical plane perpendicular to the fourth trailing edge section circle is defined as the symmetry plane of the forebody air intake.

[0047] On the right view of the fourth trailing edge section circle, with O Starting from point 2, two rays are generated that are symmetrical about the front intake duct. The intersection points of the two rays and the corresponding projection curves of the leading edge profile are the left vertex and the right vertex of the leading edge, respectively.

[0048] S2012, align the center of the reference intake capture circle with... O 2. The intersections of the two rays with the reference intake duct capture circle are defined as the left vertex I and right vertex I of the leading edge of the intake duct lip, respectively.

[0049] S2013. The projected curve has curve segment I between the left and right vertices. The reference intake capture circle has curve segment II between the left and right vertices. The left ray has straight line segment I between the left and left vertices, and the right ray has straight line segment II between the right and right vertices. The closed region formed by curve segment I, curve segment II, straight line segment I, and straight line segment II is the capture surface of the intake, and the area of ​​the capture surface... S c It is characterized by the following formula:

[0050]

[0051] In the above formula, θ c The forebody intake fan annulus angle is formed by the left and right rays. r ( θ ) represents the polar coordinate function expression of the projection curve. θ It is a polar coordinate variable.

[0052] Preferably, in S2210, the method for obtaining the top compression surface of the intake is as follows: taking the discrete point cluster on curve segment I as the starting point, and taking the arc segment at the leading edge of the intake lip between the left vertex I and the right vertex I as the shock wave profile at the trailing edge of the intake, the forward streamline tracing is performed in the flow field of the axisymmetric outer cone intake to obtain the corresponding streamline cluster, and the streamline cluster forms the top compression surface of the intake.

[0053] The present invention has at least the following beneficial effects:

[0054] Firstly, this invention employs multiple reference flow field streamline tracing techniques to obtain a novel chin-type air-breathing high-speed aircraft. All components of this air-breathing high-speed aircraft adopt flow surface design and flow field matching between components, resulting in a wave-riding aircraft aerodynamic shape that has no approximation in aerodynamic theory.

[0055] Secondly, this invention realizes the design of a high-speed air-breathing waverider shape from a theoretical and methodological perspective. The air-breathing waverider designed using this method has a shock surface that is completely attached to the body in the design state, which has a good isolation effect on the high and low pressure difference between the upper and lower surfaces of the external flow. It is easier to design an aircraft with high volumetric efficiency, high lift-to-drag ratio, and simpler flow field.

[0056] Third, this invention achieves decoupled design of lift-to-drag ratio, sealing shock surface, upper and lower multiplication surface, front air intake, and volume ratio within a certain range;

[0057] Fourth, the present invention provides a highly effective and efficient method and technical guarantee for designing waverider configurations that meet the actual engineering requirements in terms of lift-to-drag ratio, volume ratio, structural feasibility, and flow field asymmetry.

[0058] Other advantages, objectives and features of the present invention will become apparent in part from the following description, and in part from those skilled in the art through study and practice of the invention. Attached Figure Description

[0059] Figure 1 This is a schematic diagram of the first axisymmetric curved surface cone corresponding to S01 in an embodiment of the present invention;

[0060] Figure 2 This refers to the first axisymmetric conical flow field and shock wave surface corresponding to S01 in this embodiment of the invention. SW A schematic diagram of 1;

[0061] Figure 3 This is a schematic diagram of the second axisymmetric curved surface cone corresponding to S01 in an embodiment of the present invention;

[0062] Figure 4 This refers to the second axisymmetric curved surface conical flow field and the second shock wave surface corresponding to S01 in this embodiment of the invention. SW Schematic diagram of 2;

[0063] Figure 5 This is a schematic diagram of the flow field of the first axisymmetric curved surface cone and the flow field of the second axisymmetric curved surface cone when the second trailing edge section circle corresponding to S02 in the embodiment of the present invention is in the same plane and the center of the circle coincides;

[0064] Figure 6 This is a schematic diagram of the first axisymmetric surface cone flow field and the second axisymmetric surface cone flow field when the second axisymmetric surface cone flow field corresponding to S02 in this embodiment of the invention is translated upward relative to the first axisymmetric surface cone flow field;

[0065] Figure 7 This is a schematic diagram showing the relative positions of the first trailing edge shock profile and the second trailing edge shock profile corresponding to S02 in this embodiment of the invention.

[0066] Figure 8 This is a schematic diagram of the projection curve of the leading edge profile corresponding to S02 and the first trailing edge shock wave profile in an embodiment of the present invention.

[0067] Figure 9 This is a schematic diagram of the superior wavefront obtained by the streamline tracing method corresponding to S03 in this embodiment of the invention;

[0068] Figure 10 This is the three-dimensional digital model of the superior wave surface and the first axisymmetric curved surface cone shock surface obtained by the streamline tracing method in S03 of this invention;

[0069] Figure 11 This is a schematic diagram of the intake duct capture surface construction process corresponding to S04 in this embodiment of the invention;

[0070] Figure 12 This is a schematic diagram of the design process of the leading shock wave dependent domain of the axisymmetric external conical inlet flow field corresponding to S05 in the embodiment of the present invention, the compression surface of the axisymmetric external conical inlet and the corresponding axisymmetric external conical inlet flow field, and the flow field in the isolation section of the axisymmetric external conical inlet corresponding to S06 in the embodiment of the present invention.

[0071] Figure 13 This is a schematic diagram of the design process of the top compression surface of the intake corresponding to S07 in this embodiment of the invention;

[0072] Figure 14 This is a schematic diagram of the design process of the bottom compression surface of the isolation section corresponding to S08 in this embodiment of the invention;

[0073] Figure 15 This is a schematic diagram of the design process of the outer envelope surface of the intake duct lip corresponding to S09 in this embodiment of the invention;

[0074] Figure 16 This is a schematic diagram of the wavefront design process corresponding to S10 in this embodiment of the invention;

[0075] Figure 17 This is the design result of the aerodynamic shape of the high-speed full-flow surface waverider aircraft with integrated internal and external flow obtained in S11 of the present invention;

[0076] Among them, the length of the first axis of symmetry -1, the circle of the first trailing edge section -2, the generatrix of the first axisymmetric surface cone -3, the flow field of the first axisymmetric surface cone -4, and the shock surface of the first axisymmetric surface cone ( SW1)-5, Second trailing edge section circle -6, Length of the symmetry center axis of the second axisymmetric curved surface cone -7, Third trailing edge section circle -8, Generatrix of the second axisymmetric curved surface cone -9, Flow field of the second axisymmetric curved surface cone -10, Shock surface of the second axisymmetric curved surface cone -11, Fourth trailing edge section circle -12, Intersecting chord -13, Leading edge profile -14, Projected curve -15, First trailing edge shock profile -16, Second trailing edge shock profile -17, Superior wave surface -18, Intersection line -19, Left vertex -20, Right vertex -21, Left vertex I -22, Right vertex I -23, Generatrix of the second shock surface SW2 -24, Cone vertex -25, Leading edge point -26, End point of the leading edge shock wave dependence domain -27, Compression surface of the axisymmetric outer cone inlet -28, Shock wave reflected from the lip of the axisymmetric outer cone inlet -29, Point P- 30. End point of upper wall of isolation section - 31. End point of lower wall of isolation section - 32. Arc segment of leading edge of intake duct lip - 33. Compression surface of top of intake duct - 34. Trailing edge curve of top of isolation section - 35. Left vertex II - 36. Right vertex II - 37. Compression surface of bottom of isolation section - 38. Trailing edge curve of bottom of isolation section - 39. Left vertex III - 40. Right vertex III - 41. Left intersection point of second trailing edge shock wave - 42. Right intersection point of second trailing edge shock wave - 43. Outer envelope surface of intake duct lip - 44. Trailing edge curve of outer envelope surface of intake duct lip - 45. Left vertex IV - 46. Right vertex IV - 47. End point of left side - 48. End point of right side - 49. Left side surface of second wavefront - 50. Right side surface of second wavefront - 51. Lower wavefront - 52. Trailing edge curve of lower wavefront - 53. Detailed Implementation

[0077] The present invention will now be described in further detail with reference to the accompanying drawings, so that those skilled in the art can implement it based on the description.

[0078] This invention provides a design method for a high-speed, full-surface waverider aircraft integrating internal and external flow characteristics. By decoupling the flow fields of the upper and lower waverider surfaces and the forebody inlet within two mutually matched, theoretically and numerically optimized axisymmetric curved surface conical flow fields, the upper waverider surface, lower waverider surface, and forebody inlet are obtained independently using the streamline tracing method. The upper waverider surface, lower waverider surface, and forebody inlet are then assembled according to the flow field characteristics to obtain the aerodynamic shape of a high-speed, air-breathing, full-surface waverider aircraft with complete internal and external waverider characteristics, compression characteristics, lift-to-drag ratio, volumetric efficiency, and engineering feasibility. The operational steps are as follows:

[0079] S01. Based on the incoming flow conditions and the constraint conditions of the axisymmetric surface cone, the flow fields of the first and second axisymmetric surface cones are obtained using the method of characteristics.

[0080] Furthermore, the specific operating procedure for S01 is as follows:

[0081] S0101. Given the incoming flow conditions, including: static pressure PS 0. Static temperature TS 0. Total pressure PT 0. Total temperature TT 0. Incoming Mach number Ma 0;

[0082] S0102. Given the constraint conditions of the axisymmetric surface cone, including:

[0083] The volume of the first axisymmetric cone, the length of the first axisymmetric axis corresponding to the first axisymmetric cone, and the radius of the base circle (i.e., the first trailing edge section circle) of the first axisymmetric cone. R 1;

[0084] The volume of the second axisymmetric cone, the length of the second axisymmetric axis corresponding to the second axisymmetric cone, and the radius of the base circle of the second axisymmetric cone (i.e., the circle of the third trailing edge section). R 3;

[0085] S0103. Select one curve from commonly used axisymmetric curve types as the type of the first axisymmetric surface cone generatrix and the second axisymmetric surface cone generatrix, respectively. Commonly used axisymmetric curve types include: quasi-isentropic compression, pressure distribution law, Mach number distribution law, von Kármán curve, and minimum resistance curve.

[0086] S0104. Based on the constraints in S0102 and the selected generatrix type in S0103, obtain the first axisymmetric surface cone and the second axisymmetric surface cone respectively.

[0087] S0105. Based on the incoming flow conditions in S0101 and the first axisymmetric surface cone in S0104, the flow field of the first axisymmetric surface cone and the first shock surface are obtained by numerical calculation using the method of characteristics. SW 1. Second shock surface SW 2. Radius of the circle at the second trailing edge section R 2. The second trailing edge section circle and the first trailing edge section circle are in the same plane and have the same center. O 1 is the center of both the first trailing edge section circle and the second trailing edge section circle;

[0088] Based on the incoming flow conditions of S0101 and the second axisymmetric surface cone of S0104, the flow field of the second axisymmetric surface cone and the second shock surface are obtained by numerical calculation using the method of characteristics. SW 2. Second shock surface SW 2. The radius of the circle at the fourth trailing edge. R 4. The fourth trailing edge section circle and the third trailing edge section circle are in the same plane and have the same center. O 2 is the center of both the third trailing edge section circle and the fourth trailing edge section circle;

[0089] S02. The second axisymmetric surface cone flow field is moved relative to the first axisymmetric surface cone flow field to obtain the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile.

[0090] Furthermore, the specific operating procedure for S02 is as follows:

[0091] S0201. Place the second trailing edge section circle and the fourth trailing edge section circle in the same plane, and set the center of the second trailing edge section circle... O 1 and the center of the fourth trailing edge section circle O 2 overlap;

[0092] S0202. The position of the first axisymmetric curved surface cone flow field is fixed, and the second axisymmetric curved surface cone flow field is moved upwards along the vertical direction of the second axis of symmetry by a distance. d Ensure shock wave surface SW 1 and the second shock surface SW The second trailing edge section circle and the fourth trailing edge section circle intersect to form two intersection points. A , B Connecting intersections A , B The line segments are intersecting chords, and the length of the intersecting chords is the width of the aerodynamic shape of the integrated internal and external flow high-speed full-flow surface waverider aircraft. b ;

[0093] distance traveled d Based on the width of the aerodynamic shape of the integrated internal and external flow high-speed full-flow surface waverider aircraft b Determined by formula (1):

[0094] (1)

[0095] in, R 2 is the radius of the second trailing edge section circle. R 4 is the radius of the fourth trailing edge section circle;

[0096] S0203, Shock surface SW 1 and the second shock surface SW The spatial intersection line formed by the two intersections is the leading edge profile of the wave-riding surface. The projection of the leading edge profile along the first axis of symmetry of the first axisymmetric surface cone onto the second trailing edge section circle yields the projection curve of the leading edge profile.

[0097] S0204. The intersecting chord divides the second trailing edge section circle into an upper circular arc segment located above the intersecting chord and a lower circular arc segment located below the intersecting chord. The upper circular arc segment is the first trailing edge shock profile.

[0098] The intersecting chord divides the fourth trailing edge section circle into an upper circular arc segment above the intersecting chord and a lower circular arc segment below the intersecting chord. The lower circular arc segment is the second trailing edge shock profile.

[0099] S03. Starting from a series of discrete points on the leading edge profile, and taking the first trailing edge shock profile as the shock profile, the forward streamline tracing is carried out in the first axisymmetric curved surface cone flow field to obtain the upper wave surface of the aerodynamic shape of the full-flow surface waverider.

[0100] Furthermore, S03 starts with the discrete point clusters on the leading edge profile and uses the first trailing edge shock profile as the superimposed wavefront trailing edge shock profile. Streamlines are traced in the first axisymmetric curved surface cone flow field along the direction close to the second trailing edge cross-section circle to obtain the streamline clusters starting from the aforementioned discrete points. These streamline clusters form the superimposed wavefront.

[0101] S04. Given the radius of the reference intake capture circle, adjust the fan ring angle of the forebody intake. θ c Construct the intake's trapping surface within the second axisymmetric curved conical flow field, and increase its area. S c To meet design goals, in practical applications, the capture surface is an input parameter or a requirement parameter. It is calculated and compared with the input. The capture surface is mainly controlled by the radius and angle, that is, by adjusting the radius and fan-ring angle of the capture circle to iteratively meet the capture area requirements.

[0102] Furthermore, the specific operating procedure for S04 is as follows:

[0103] S0401, the center of the circle passing through the fourth trailing edge section. O 2. The vertical plane perpendicular to the fourth trailing edge section circle is the symmetry plane of the front air intake. On the right view of the fourth trailing edge section circle, with the center of the fourth trailing edge section circle as the reference point... O Starting from point 2, generate two rays symmetrical about the symmetrical plane of the forebody air intake. The ray located to the left of the symmetrical plane of the forebody air intake is the left ray, and the ray located to the right of the symmetrical plane of the forebody air intake is the right ray. The intersection of the left ray and the projection curve is the left vertex of the leading edge of the air intake, and the intersection of the right ray and the projection curve is the right vertex of the leading edge of the air intake.

[0104] S0402, The radius of the given reference inlet capture circle R c The center of the reference intake capture circle and the center of the fourth trailing edge section circle O 2. When the left ray intersects with the reference intake duct capture circle, the left vertex I of the leading edge of the intake duct lip is obtained; when the right ray intersects with the reference intake duct capture circle, the right vertex I of the leading edge of the intake duct lip is obtained.

[0105] S0403. The closed area formed by the curve segment I between the left vertex of the projection curve and the right vertex of the leading edge of the air intake, the curve segment II between the left vertex I of the leading edge of the air intake lip and the right vertex I of the leading edge of the air intake lip, the straight line segment I between the left vertex of the left ray and the left vertex I of the leading edge of the air intake lip, and the straight line segment II between the right vertex of the right ray and the right vertex I of the leading edge of the air intake lip is the capture surface of the air intake.

[0106] S0404, the intake duct capture area is determined by formula (2):

[0107] (2)

[0108] in, S c The capture area of ​​the air intake. R c The radius of the reference intake capture circle. θ c The acute angle formed by the left and right rays is the fan-ring angle of the forebody intake. r ( θ ) represents the polar coordinate function expression of the projection curve. θ It is a polar coordinate variable.

[0109] S05. Construct the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field within the second axisymmetric curved surface cone flow field. Given the compression form of the axisymmetric outer cone inlet wall, generate the compression surface of the axisymmetric outer cone inlet and the corresponding axisymmetric outer cone inlet flow field using the method of characteristics.

[0110] Furthermore, the specific operating procedure for S05 is as follows:

[0111] S0501, The projection of the second shock surface SW2 onto the symmetry plane of the forebody inlet described in S0401 is the generatrix of the second shock surface SW2, and the intersection of the generatrix of SW2 and the generatrix of the second axisymmetric curved surface cone is the cone vertex of the second axisymmetric curved surface cone.

[0112] S0502, On the generatrix of the second shock wave surface SW2, find a distance from the second axis of symmetry equal to the radius of the reference inlet capture circle. R c The point is the leading edge of the lip of the axisymmetric outer cone intake;

[0113] S0503. In the second axisymmetric curved surface cone flow field, iterate the leftward characteristic line starting from the leading edge point of the axisymmetric outer cone inlet lip. The intersection of the leftward characteristic line and the generatrix of the second axisymmetric curved surface cone is the end point of the shock wave dependent domain at the leading edge of the axisymmetric outer cone inlet.

[0114] S0504. Define the second shock surface SW2 generatrix between the cone vertex of the second axisymmetric curved surface cone and the leading edge point of the axisymmetric outer cone inlet lip as closed line I, define the second axisymmetric curved surface cone generatrix between the cone vertex and the endpoint as closed line II, define the leftward characteristic line between the leading edge point of the axisymmetric outer cone inlet lip and the endpoint of the leading edge shock wave dependent domain of the axisymmetric outer cone inlet as closed line III. Closed line I, closed line II, and closed line III constitute a closed region, namely the leading edge shock wave dependent domain of the flow field of the axisymmetric outer cone inlet.

[0115] When designing the compression flow field of an axisymmetric external cone inlet that matches the wave rider, it is necessary to ensure that the shock wave dependence domain at the leading edge of the axisymmetric external cone inlet remains unchanged.

[0116] S0505. Using the characteristic line method, with the left-moving characteristic line between the leading edge point of the axisymmetric outer cone inlet lip and the end point of the shock wave dependent domain at the leading edge of the axisymmetric outer cone inlet as the initial condition, and given the compression form of the axisymmetric outer cone inlet wall, the compression surface of the axisymmetric outer cone inlet and the corresponding flow field of the axisymmetric outer cone inlet are obtained.

[0117] S06. Given the upper wall shape and flow parameter distribution of the axisymmetric outer cone inlet isolation section, the flow field of the axisymmetric outer cone inlet isolation section can be obtained by using the characteristic line method. The flow field of the axisymmetric outer cone inlet and the flow field of the axisymmetric outer cone inlet isolation section together constitute the reference flow field of the axisymmetric outer cone inlet.

[0118] Furthermore, the specific operating procedure for S06 is as follows:

[0119] S0601. The shock wave reflected from the lip of the axisymmetric outer cone intake, starting from the leading edge point of the lip, intersects the compression surface of the axisymmetric outer cone intake at point P.

[0120] S0602. Using the backflow parameters of the shock wave reflected from the lip of the axisymmetric external conical inlet as boundary conditions, given the shape of the upper wall and the distribution of flow parameters of the isolation section of the axisymmetric external conical inlet located between the intersection point P and the termination point of the upper wall of the isolation section, the flow field of the isolation section of the axisymmetric external conical inlet located between the leading edge point of the lip of the axisymmetric external conical inlet and the termination point of the lower wall of the isolation section is obtained by using the method of characteristics.

[0121] S07. Starting from the discrete point clusters on the projection curve of the leading edge profile, and taking the arc segment of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, the forward streamline tracing is performed in the reference flow field of the axisymmetric outer cone inlet to obtain the top compression surface of the inlet.

[0122] Furthermore, the specific operating procedure for S07 is as follows:

[0123] S0701. Starting from the discrete point cluster on the curve segment between the left vertex and the right vertex of the leading edge of the inlet, the arc segment of the leading edge of the inlet lip between the left vertex I and the right vertex I of the leading edge of the inlet lip is taken as the shock wave profile of the trailing edge of the inlet. By tracing the streamlines in the reference flow field of the axisymmetric outer cone inlet, the streamline cluster starting from the above discrete points can be obtained. These streamline clusters form the compression surface at the top of the inlet.

[0124] S0702. The plane parallel to the trailing edge section of the second axisymmetric curved surface cone and passing through the termination points of the upper and lower walls of the isolation section is the trailing edge section of the intake duct. The intersection of the top compression surface of the intake duct and the trailing edge section of the intake duct forms the top trailing edge curve of the isolation section. The intersection of the top trailing edge curve of the isolation section and the left ray is the left vertex II of the top trailing edge curve of the isolation section. The intersection of the top trailing edge curve of the isolation section and the right ray is the right vertex II of the top trailing edge curve of the isolation section.

[0125] S08. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and taking the leading edge arc segment of the inlet lip as the shock wave profile of the inlet trailing edge, the forward streamline tracing is performed in the axisymmetric outer cone inlet flow field to obtain the bottom compression surface of the isolation section.

[0126] Furthermore, the specific operating procedure for S08 is as follows:

[0127] S0801. Starting from the discrete point cluster on the leading edge arc segment of the lip between the left vertex I and the right vertex I, and taking the leading edge arc segment of the inlet lip between the left vertex I and the right vertex I as the shock wave profile of the inlet trailing edge, the streamline tracing in the axisymmetric outer cone inlet flow field can be carried out in the forward streamline tracing to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the bottom compression surface of the isolation section.

[0128] S0802. The bottom compression surface of the isolation section intersects with the rear edge section of the intake duct to obtain the bottom trailing edge curve of the isolation section. The bottom trailing edge curve of the isolation section intersects with the left ray to obtain the left vertex III of the bottom trailing edge curve of the isolation section. The bottom trailing edge curve of the isolation section intersects with the right ray to obtain the right vertex III of the bottom trailing edge curve of the isolation section.

[0129] S09. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and using the second trailing edge shock wave profile as the trailing edge shock wave profile of the outer envelope surface of the inlet lip, the forward streamline tracing is performed in the second axisymmetric curved surface cone flow field to obtain the outer envelope surface of the inlet lip.

[0130] Furthermore, the specific operating procedure for S09 is as follows:

[0131] S0901. The left ray intersects with the second trailing edge shock profile to obtain the left intersection point of the second trailing edge shock. The right ray intersects with the second trailing edge shock profile to obtain the rear intersection point of the second trailing edge shock. The intersection point of the left side of the second trailing edge shock and the intersection point of the right side of the second trailing edge shock divide the second trailing edge shock profile into three parts: the second trailing edge shock profile located between the intersection point of the left side of the second trailing edge shock and the intersection point of the right side of the second trailing edge shock; the second trailing edge shock profile located between the left end point of the projection curve of the leading edge profile and the intersection point of the left side of the second trailing edge shock; and the second trailing edge shock profile located between the right end point of the projection curve of the leading edge profile and the intersection point of the right side of the second trailing edge shock.

[0132] S0902. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip between the left vertex I and the right vertex I, the second trailing edge shock profile between the left intersection point and the right intersection point of the second trailing edge shock wave is taken as the trailing edge shock profile of the outer envelope surface of the inlet lip. In the second axisymmetric curved surface cone flow field, forward streamline tracing is performed to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the outer envelope surface of the inlet lip.

[0133] S0903, the outer envelope surface of the intake lip intersects with the plane containing the third trailing edge section circle to obtain the trailing edge curve of the outer envelope surface of the intake lip. The trailing edge curve of the outer envelope surface of the intake lip intersects with the left ray to obtain the left vertex IV of the trailing edge curve of the outer envelope surface of the intake lip. The trailing edge curve of the outer envelope surface of the intake lip intersects with the right ray to obtain the right vertex IV of the trailing edge curve of the outer envelope surface of the intake lip.

[0134] S10. Starting from the discrete point cluster on the projection curve of the leading edge profile, and taking the second trailing edge shock profile as the trailing edge shock profile of the lower wave surface, the lower wave surface is obtained by forward streamline tracing in the second axisymmetric curved surface cone flow field.

[0135] Furthermore, the specific operating procedure for S10 is as follows:

[0136] S1001. Starting from the discrete point cluster on the projection curve of the leading edge profile between the left vertex of the leading edge of the inlet and the left end point of the leading edge profile projection curve, the second trailing edge shock profile between the left end point of the leading edge profile projection curve and the left end point of the second trailing edge shock is used as the trailing edge shock profile of the left side of the lower wavefront profile. In the second axisymmetric curved surface cone flow field, forward streamline tracing is performed to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the left side of the lower wavefront profile.

[0137] S1002. Starting from the discrete point cluster on the projection curve of the leading edge profile between the right apex of the leading edge of the inlet and the right end point of the leading edge profile projection curve, the second trailing edge shock profile between the right end point of the leading edge profile projection curve and the right side intersection point of the second trailing edge shock is taken as the trailing edge shock profile of the right side profile of the lower wave surface. In the second axisymmetric curved surface cone flow field, forward streamline tracing is performed to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the right side profile of the lower wave surface.

[0138] S1003, the left side profile of the lower wavefront and the right side profile of the lower wavefront constitute the lower wavefront. The lower wavefront intersects with the third trailing edge section circle to obtain the trailing edge curve 53 of the lower wavefront.

[0139] S11, the upper wavefront, the lower wavefront, the top compression surface of the inlet, the bottom compression surface of the isolation section, and the outer envelope surface of the inlet lip form a closed area, which is the aerodynamic shape of the high-speed full-flow surface waverider aircraft with integrated internal and external flow.

[0140] Furthermore, the specific operating procedure for S11 is as follows:

[0141] The aerodynamic shape of the high-speed full-flow-surface waverider aircraft, which integrates internal and external flow, is composed of a closed region consisting of the following flow surfaces: upper waverider surface, lower waverider surface, top compression surface of the inlet, bottom compression surface of the isolation section, and outer envelope surface of the inlet lip.

[0142] Example:

[0143] A design method for a high-speed, full-flow-surface waverider vehicle integrating internal and external flow, the specific technical solution of which includes:

[0144] S01. Based on the incoming flow conditions and the constraint conditions of the axisymmetric surface cone, the flow fields of the first and second axisymmetric surface cones are obtained using the method of characteristics.

[0145] like Figure 1 and Figure 2 As shown, under given incoming flow conditions, the following are given: the volume of the first axisymmetric surface cone, the length 1 of the first axis of symmetry, and the radius of the base circle of the first axisymmetric surface cone (i.e., the first trailing edge section circle 2). R 1. Using numerical and theoretical methods, the generatrix of the first axisymmetric surface cone is generated. 3. Using the method of characteristics, the flow field of the first axisymmetric surface cone and the shock surface of the first axisymmetric surface cone are obtained. (The shock surface of the first axisymmetric surface cone is abbreviated as the first shock surface.) SW 1)5, First axisymmetric surface cone shock surface ( SW 1) The intersection of circle 5 and the first trailing edge section circle 2 is a circle. Define this circle as the second trailing edge section circle 6, and the radius of this circle is... R 2.

[0146] like Figure 3and Figure 4 As shown, under given incoming flow conditions, the following parameters are given: volume of the second axisymmetric surface cone, length 7 of the central axis of symmetry of the second axisymmetric surface cone, and radius of the base circle of the second axisymmetric surface cone (i.e., the circle of the third trailing edge section 8). R 3. Using numerical and theoretical methods, the generatrix 9 of the second axisymmetric surface cone is generated. Using the method of characteristics, the flow field 10 of the second axisymmetric surface cone and the shock surface of the second axisymmetric surface cone (the shock surface of the second axisymmetric surface cone is abbreviated as the second shock surface) are obtained. SW 2) 11, the intersection of this circle with the third trailing edge section circle 8 is a circle, defined as the fourth trailing edge section circle 12, with a radius of . R 4.

[0147] like Figures 5-8 As shown in Figure S02, the flow field of the second axisymmetric curved surface cone is moved relative to the flow field of the first axisymmetric curved surface cone to obtain the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile. The specific operation procedure is as follows:

[0148] Place the second trailing edge section circle 6 and the fourth trailing edge section circle 12 in the same plane, and coincide the centers of the two trailing edge section circles. Fix the position of the first axisymmetric surface cone flow field, and deviate the second axisymmetric surface cone flow field upwards by a certain distance in the vertical direction of the second axisymmetric surface cone symmetry axis 7. This distance is the length of the line connecting the center of the second trailing edge section circle 6 and the center of the fourth trailing edge section circle 12. d While ensuring the first axisymmetric curved surface cone shock surface ( SW 1)5. Second axisymmetric surface cone shock wave surface ( SW 2) Given that 11 intersects, the intersection of the second trailing edge section circle 6 and the fourth trailing edge section circle 12 results in the endpoint being... A , B The intersecting chord 13 of the two points forms an arc segment located above and below the intersecting chord 13. The length of the intersecting chord 13 is the width of the hypersonic inhalation wave-riding aerodynamic shape that integrates internal and external flow. b ;

[0149] First axisymmetric surface cone shock surface ( SW 1)5 and the second axisymmetric curved surface cone shock wave surface ( SW 2) The spatial intersection line formed by the intersection of 11 is the leading edge profile 14. The leading edge profile 14 is projected along the direction of the central axis 1 of the first axisymmetric curved surface cone onto the plane containing the second trailing edge section circle 6, resulting in a line with the two endpoints of the intersecting chord 13 as the starting points. A and the end point B The projection curve 15 is defined as the projection curve 15 of the leading edge profile 14;

[0150] The intersecting chord 13 divides the second trailing edge section circle 6 into an upper arc segment above the intersecting chord and a lower arc segment below the intersecting chord, and selects the upper arc segment as the first trailing edge shock profile 16; the intersecting chord 13 divides the fourth trailing edge section circle 12 into an upper arc segment above the intersecting chord and a lower arc segment below the intersecting chord, and selects the lower arc segment as the second trailing edge shock profile 17;

[0151] The vertical deviation of the center axis 1 of the first axisymmetric surface cone and the center axis 7 of the second axisymmetric surface cone. d The constraint condition must be met: this distance must be less than the radius of the second trailing edge section circle. R 2 and the radius of the fourth trailing edge section circle R The sum of 4, that is:

[0152] (1)

[0153] The vertical deviation of the center axis 1 of the first axisymmetric surface cone and the center axis 7 of the second axisymmetric surface cone. d The width of the aerodynamic shape is mainly referenced from the integrated internal and external flow high-speed full-flow surface waverider aircraft. b Sure.

[0154] like Figure 9 As shown, S03, starting from a series of discrete points on the leading edge profile, and using the first trailing edge shock profile as the shock profile, forward streamline tracing is performed within the first axisymmetric curved surface cone flow field to obtain the upper wavefront of the aerodynamic shape of the full-surface waverider. The specific operation procedure is as follows:

[0155] Starting from the discrete point cluster on the projection curve 15 of the leading edge profile 14, and under the constraint of the first trailing edge shock profile 16, the streamline clusters starting from the discrete points are obtained by forward streamline tracing within the first axisymmetric curved surface cone flow field 4. These streamline clusters form the superimposed wave surface 18, and the intersection line 19 of the superimposed wave surface 18 and the second trailing edge section circle 6.

[0156] Superior wavefront 18 and first axisymmetric curved cone shock surface ( SW 1) A 3D digital model of 5, such as Figure 10 As shown.

[0157] The specific process for obtaining the upper waverider surface 18 by the streamline tracing method can be found in the patent application CN202310898025.7, "A Three-Dimensional Leading Edge Customizable Streamline Tracing Waverider Design Method", which will not be detailed here.

[0158] like Figure 11 As shown in Figure S04, given the radius of the reference inlet capture circle, the capture surface of the inlet is constructed within the second axisymmetric curved surface conical flow field. The specific construction process is as follows:

[0159] The center of circle 12 passing through the fourth trailing edge section O The vertical plane of section 2 is the plane of symmetry (hereinafter referred to as the front intake symmetry plane), with the center of the fourth trailing edge section circle. O Starting from point 2, generate two rays symmetrical about the plane of symmetry of the forebody air intake. The ray located to the left of the plane of symmetry of the forebody air intake is referred to as the left ray, and the ray located to the right of the plane of symmetry of the forebody air intake is referred to as the right ray. Define the angle between the left ray and the right ray. θ c The fan ring angle of the forebody intake duct. The intersection of the left ray and the projection curve 15 of the leading edge profile 14 is defined as the left vertex 20 of the intake duct leading edge, and the intersection of the right ray and the projection curve 15 of the leading edge profile 14 is defined as the right vertex 21 of the intake duct leading edge.

[0160] Define the center of the intake fan ring arc and the center of the fourth trailing edge section circle 12. O 2 coincide, and the radius is R c The endpoint of the fan-ring arc located on the left side of the symmetry plane of the forebody air intake is defined as the left vertex I22 of the leading edge of the air intake lip, and the left vertex I22 of the leading edge of the air intake lip is located on the left ray. The endpoint of the fan-ring arc located on the right side of the symmetry plane of the forebody air intake is defined as the right vertex I23 of the leading edge of the air intake lip, and the right vertex I23 of the leading edge of the air intake lip is located on the right ray.

[0161] The intake capture section consists of a closed region formed by the following curves: the projection curve 15 of the leading edge profile 14, which is the curve segment between the left vertex 20 and the right vertex 21 of the leading edge of the intake; the intake fan-shaped arc between the left vertex I22 and the right vertex I23 of the leading edge of the intake lip; the straight line segment of the left ray between the left vertex 20 and the left vertex I22 of the leading edge of the intake; and the straight line segment of the right ray between the right vertex 21 and the right vertex I23 of the leading edge of the intake.

[0162] Inlet capture area S c This refers to the area of ​​the enclosed region, which is calculated as follows: Assume the radius of the reference intake capture circle is... R c The polar coordinate function expression of the projection curve 15 of the leading edge profile 14 is: r = r ( θ If the area of ​​the enclosed region is such that the area is calculated using the following integral form:

[0163] (2)

[0164] Therefore, the area of ​​the enclosed region can be seen. S c Only with θ c and R c Relevant. Under certain intake duct capture area requirements. θ c and R c It presents a one-to-one correspondence, given θ c The intake capture area can be calculated. S c The corresponding requirements R c Similarly, given a reference inlet capture circle radius... R c It is possible to find the unique corresponding one. θ c horn.

[0165] like Figure 12 As shown in Figure S05, the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field is constructed within the second axisymmetric curved surface cone flow field. Given the compression form of the axisymmetric outer cone inlet wall, the compression surface of the axisymmetric outer cone inlet and the corresponding axisymmetric outer cone inlet flow field are generated using the method of characteristics.

[0166] The projection of the second shock surface SW2 onto the symmetry plane of the forebody inlet is the generatrix 24 of the second shock surface SW2. The intersection of the generatrix 24 of the second shock surface SW2 and the generatrix 9 of the second axisymmetric curved surface cone is the cone vertex 25 of the second axisymmetric curved surface cone.

[0167] On the second shock wave surface SW2 generatrix 24, find a distance from the center axis 7 of the second axisymmetric curved surface cone that is equal to the radius of the intake fan ring arc. R c The point is referred to as the leading edge point 26 of the axisymmetric outer cone inlet lip. Within the second axisymmetric curved cone flow field 10, a leftward characteristic line is iterated from the leading edge point 26 of the axisymmetric outer cone inlet lip. This leftward characteristic line intersects the second axisymmetric curved cone generatrix 9 at a point, referred to as the ending point 27 of the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field.

[0168] The design of the axisymmetric external conical inlet flow field to match the waverider requires ensuring that the closed region flow field composed of the following three curve segments remains unchanged: the second shock surface SW2 generatrix 24 between the cone vertex 25 of the second axisymmetric curved surface cone and the leading edge point 26 of the axisymmetric external conical inlet lip; the second axisymmetric curved surface cone generatrix 9 between the cone vertex 25 of the second axisymmetric curved surface cone and the ending point 27 of the leading edge shock wave dependence domain of the axisymmetric external conical inlet; and the left-moving characteristic line configuration between the leading edge point 26 of the axisymmetric external conical inlet lip and the ending point 27 of the leading edge shock wave dependence domain of the axisymmetric external conical inlet flow field are used as the leading edge shock wave dependence domain of the axisymmetric external conical inlet flow field.

[0169] Using the method of characteristics, with the left-moving characteristic line between the leading edge point 26 of the axisymmetric outer conical inlet lip and the ending point 27 of the leading edge shock wave dependence domain of the axisymmetric outer conical inlet as the initial value line, given the compression form of the axisymmetric outer conical inlet wall (wall pressure distribution, wall Mach number distribution, isentropic compression of wall shape, etc.), the compression surface 28 of the axisymmetric outer conical inlet and the corresponding compression flow field of the axisymmetric outer conical inlet can be generated.

[0170] The specific process for the compression form of the axisymmetric external cone inlet wall can be found in patent application number CN202310898025.7, "A Three-Dimensional Leading Edge Customizable Streamline Tracing Waverider Design Method", which will not be elaborated here.

[0171] like Figure 12 As shown in Figure S06, given the upper wall shape and flow parameter distribution of the axisymmetric outer conical inlet isolation section, the flow field of the axisymmetric outer conical inlet isolation section can be obtained using the characteristic line method. The specific operation procedure is as follows:

[0172] The axisymmetric external conical inlet lip reflected shock wave 29, originating from the leading edge point 26 of the axisymmetric external conical inlet lip, intersects the axisymmetric external conical inlet compression surface 28 at a single point. P 30.

[0173] Using the airflow parameters after wave 29 of the shock wave reflected from the lip of the axisymmetric external cone inlet as boundary conditions, and assuming the isolation section of the axisymmetric external cone inlet is located at the intersection point... P The shape of the upper wall between 30 and the termination point 31 of the upper wall of the isolation section, as well as the distribution of flow parameters (pressure distribution, Mach number distribution), can be obtained using the method of characteristics. The flow field in the axisymmetric outer cone inlet isolation section between the leading edge point 26 of the lip of the axisymmetric outer cone inlet and the termination point 32 of the lower wall of the isolation section can be obtained.

[0174] The flow field of the axisymmetric outer cone inlet and the flow field of the axisymmetric outer cone inlet isolation section together constitute the reference flow field of the axisymmetric outer cone inlet.

[0175] like Figure 13As shown, S07, starting from the discrete point cluster on the projection curve of the leading edge profile, and taking the arc segment of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, forward streamline tracing is performed in the flow field of the axisymmetric outer cone inlet to obtain the compression surface at the top of the inlet. The specific operation procedure is as follows:

[0176] Starting from the discrete point cluster on the curve segment of the projection curve 15 of the leading edge profile 14 located between the left vertex 20 and the right vertex 21 of the leading edge of the inlet, and taking the arc segment 33 of the leading edge of the inlet lip located between the left vertex I22 and the right vertex I23 of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, the streamline cluster starting from the above discrete points can be obtained by tracing the streamlines in the reference flow field of the axisymmetric outer cone inlet. These streamline clusters form the compression surface 34 at the top of the inlet.

[0177] Define the plane parallel to the trailing edge section of the second axisymmetric curved cone and passing through the termination point 31 of the upper wall of the axisymmetric outer cone intake isolation section and the termination point 32 of the lower wall of the isolation section as the trailing edge section of the intake. Then, the top compression surface 31 of the forebody intake and the trailing edge section of the forebody intake intersect at a curve, which is simply called the top trailing edge curve 35 of the isolation section. The top trailing edge curve 35 of the isolation section intersects with the left ray at a point, which is simply called the left vertex II 36 of the top trailing edge curve 35 of the isolation section. The top trailing edge curve 35 of the isolation section intersects with the right ray at a point, which is simply called the right vertex II 37 of the top trailing edge curve II 35 of the isolation section.

[0178] The specific process of obtaining the top compression surface 34 of the intake duct by the streamline tracing method can be referred to in the asymmetric double wave configuration design method based on the close method of patent application number CN202310916988.5, which will not be described in detail here.

[0179] like Figure 14 As shown in Figure S08, starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and taking the leading edge arc segment of the inlet lip as the shock wave profile of the inlet trailing edge, forward streamline tracing is performed within the axisymmetric outer cone inlet flow field to obtain the compression surface at the bottom of the isolation section. The specific operation procedure is as follows:

[0180] Starting from the discrete point cluster on the arc segment 33 of the leading edge of the inlet lip between the left vertex I22 and the right vertex I23 of the leading edge of the inlet lip, and taking the arc segment 33 of the leading edge of the inlet lip between the left vertex I22 and the right vertex I23 of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, the streamline cluster starting from the above discrete points can be obtained by tracing the forward streamlines in the axisymmetric outer cone inlet flow field. These streamline clusters form the bottom compression surface 38 of the isolation section.

[0181] The bottom compression surface 38 of the isolation section intersects the rear edge section of the intake duct at a curve, referred to as the bottom trailing edge curve 39 of the isolation section. The bottom trailing edge curve 39 of the isolation section intersects the left ray at a point, referred to as the left vertex Ⅲ40 of the top trailing edge curve 39 of the isolation section. The bottom trailing edge curve 39 of the isolation section intersects the right ray at a point, referred to as the right vertex Ⅲ41 of the bottom trailing edge curve 39 of the isolation section.

[0182] The specific process of obtaining the bottom compression surface 38 of the isolation section by the streamline tracing method can be referred to in the asymmetric double wave configuration design method based on the close method of patent application number CN202310916988.5, which will not be described in detail here.

[0183] like Figure 15 As shown in Figure S09, starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and using the second trailing edge shock profile as the trailing edge shock profile of the outer envelope surface of the inlet lip, forward streamline tracing is performed within the second axisymmetric curved surface cone flow field to obtain the outer envelope surface of the inlet lip. The specific operation procedure is as follows:

[0184] The left ray intersects the second trailing edge shock profile 17 at a point, referred to as the left intersection point 42 of the second trailing edge shock. The right ray intersects the second trailing edge shock profile 17 at a point, referred to as the right intersection point 43 of the second trailing edge shock. The left intersection point 42 and the right intersection point 43 of the second trailing edge shock divide the second trailing edge shock profile 17 into three parts: the second trailing edge shock profile located between the left intersection point 42 and the right intersection point 43 of the second trailing edge shock; the second trailing edge shock profile located between the left termination point 48 of the leading edge profile projection curve 15 and the left intersection point 42 of the second trailing edge shock; and the second trailing edge shock profile located between the right termination point 49 of the leading edge profile projection curve 15 and the right intersection point 43 of the second trailing edge shock.

[0185] Starting from the discrete point cluster on the leading edge arc segment 33 of the inlet lip between the left vertex I22 and the right vertex I23 of the leading edge of the inlet lip, the second trailing edge shock profile located between the left intersection point 42 and the right intersection point 43 of the second trailing edge shock wave is taken as the trailing edge shock profile of the outer envelope surface of the inlet lip. By tracing the streamlines in the second axisymmetric curved surface cone flow field, the streamline cluster starting from the above discrete points can be obtained. These streamline clusters form the outer envelope surface 44 of the inlet lip.

[0186] The outer envelope surface 44 of the intake lip intersects the plane containing the circle 8 of the third trailing edge section at a curve, referred to as the trailing edge curve 45 of the outer envelope surface of the intake lip. The trailing edge curve 45 of the outer envelope surface of the intake lip intersects the left ray at a point, referred to as the left vertex IV46 of the trailing edge curve 45 of the outer envelope surface of the intake lip. The trailing edge curve 45 of the outer envelope surface of the intake lip intersects the right ray at a point, referred to as the right vertex IV47 of the trailing edge curve 45 of the outer envelope surface of the intake lip.

[0187] The specific process for obtaining the outer envelope surface 44 of the intake lip can be found in the asymmetric double wave configuration design method based on the close method, patent application number CN202310916988.5, and will not be described here.

[0188] like Figure 16 As shown, starting from the discrete point cluster on the projection curve of the leading edge profile (S10), and using the second trailing edge shock profile as the trailing edge shock profile of the lower wavefront, the lower wavefront is obtained by forward streamline tracing within the second axisymmetric curved surface cone flow field. The specific operation procedure is as follows:

[0189] Starting with the discrete point cluster on the leading edge profile projection curve 15 located between the left vertex 20 of the capturing leading edge and the left end point 48 of the leading edge profile projection curve 15, the second trailing edge shock profile 17 between the left end point 48 of the leading edge profile projection curve 15 and the left intersection point 42 of the second trailing edge shock wave is used as the trailing edge shock profile of the left side surface of the second wave-multiplying surface. In the second axisymmetric curved surface cone flow field, forward streamline tracing is performed to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the left side surface 50 of the second wave-multiplying surface.

[0190] Starting from the discrete point cluster on the leading edge profile projection curve 15 located between the right side point 21 of the capturing leading edge and the right side termination point 49 of the leading edge profile projection curve 15, the second trailing edge shock profile 17 between the right side termination point 49 of the leading edge profile projection curve 15 and the right side intersection point 43 of the second trailing edge shock wave is used as the trailing edge shock profile of the right side profile of the second wave-multiplying surface. In the second axisymmetric curved surface cone flow field, forward streamline tracing is performed to obtain the streamline cluster starting from the above discrete points. These streamline clusters form the right side profile 51 of the second wave-multiplying surface.

[0191] The left side profile 50 of the second wavefront and the right side profile 51 of the second wavefront constitute the lower wavefront 52. The lower wavefront intersects the third trailing edge section circle 8 at a curve, which is defined as the trailing edge curve 53 of the lower wavefront.

[0192] The specific process for obtaining the lower waverider surface 52 using the streamline tracing method can be found in a three-dimensional leading edge customizable streamline tracing waverider design method with patent application number CN202310898025.7, and will not be described here.

[0193] like Figure 17 As shown, in S11, the upper wavefront 18, the lower wavefront 52 (the left side profile 50 of the second wavefront and the right side profile 51 of the second wavefront), the top compression surface 34 of the inlet, the bottom compression surface 38 of the isolation section, and the outer envelope profile 44 of the inlet lip are combined into a closed area to obtain the aerodynamic shape of the high-speed full-flow surface waverider aircraft with integrated internal and external flow.

[0194] The full-flow surface design method presented in this embodiment focuses on the design of all flow surfaces (i.e., all geometric surfaces including the waverider fuselage / wing, the inner and outer flow regions of the forebody inlet, and the leeward fuselage / wing). Specifically, the forebody inlet, windward surface (i.e., upper waverider surface), and leeward surface (i.e., lower waverider surface) of the aircraft are all obtained through flow field customization and streamline tracing. The geometric and flow characteristics of all flow surfaces can be customized as needed through the design of the reference flow field and then assembled using streamlines. This solves both the integrated design problem of the aircraft's compression surface and forebody inlet and the customized flow problem of the coupled leeward surface. The specific effects are as follows:

[0195] Firstly, the method described in this patent firstly conducts reference flow field design to meet the requirements of loading space, waverider flow field structure, and air intake characteristics. Then, based on the geometric constraint relationship between the reference flow fields, information such as the windward side, leeward side, forebody air intake, leading edge line of the outer compression surface of the air intake lip, and shock wave line are generated. Streamline assembly and flow domain matching are performed in sequence for the constraints, thereby forming a high-speed full-flow surface waverider design method that integrates internal and external flows.

[0196] Secondly, the design is more flexible due to the greater variety of reference flow fields. In the design method described in this patent, in order to simultaneously customize the geometric and flow characteristics of the windward and leeward sides, the method for obtaining the three-dimensional leading edge line of the waverider is no longer directly given. Instead, the intersection line generated by the shock wave surfaces of the windward and leeward reference flow fields is used as the three-dimensional leading edge line. Through this method, the decoupled design of the windward and leeward flow fields can be achieved. Theoretically, this method is applicable to the design of any reference flow field and has universality.

[0197] Furthermore, this invention decouples the leading-edge shock wave of the windward reference flow field from the leading-edge shock wave of the inlet reference flow field, thereby achieving a decoupling design between the windward wave-riding fuselage shock surface and the inlet sealing shock surface. This also decouples the geometric constraints of the windward front body from the flow field constraints of the inlet. This method allows for control of the intersection position of the leading-edge shock wave and the inlet lip shock wave.

[0198] Therefore, this invention designs multiple reference flow fields that meet the overall geometric, volumetric, and flow requirements. By understanding the wave system structure, flow matching, and constraint relationships between the shock surfaces around the aircraft in different reference flow fields, it obtains the geometric relationships of the aerodynamic frontal surface, leeward surface, forebody inlet, and lip leading edge lines and shock lines. Using these as input, it conducts the design of various flow surfaces of a high-speed, full-flow-surface waverider aircraft integrating internal and external flows. This method, by relaxing the constraints of the aerodynamic frontal line and shock lines, achieves matching between arbitrary flow fields, resulting in a wider range of applicability, greater flexibility, and a larger design space.

[0199] The above solution is merely an illustration of a preferred example and is not limited thereto. When implementing this invention, appropriate substitutions and / or modifications can be made according to the user's needs.

[0200] Although embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and embodiments. It can be applied to various fields suitable for the present invention. Other modifications can be readily made by those skilled in the art. Therefore, without departing from the general concept defined by the claims and their equivalents, the present invention is not limited to the specific details and examples shown and described herein.

Claims

1. A design method for a high-speed full-flow surface waverider vehicle integrating internal and external flow, characterized in that, include: S1. Based on the incoming flow conditions and the constraints of the axisymmetric surface cone, the flow fields of the first and second axisymmetric surface cones, which are matched with each other, are obtained using the method of characteristics. S2. In two axisymmetric curved surface cone flow fields, the upper wavefront, lower wavefront, and forebody inlet of the wave-riding aerodynamic shape are constructed respectively using the streamline tracing method. S3. Assemble the upper wavefront, lower wavefront, and forebody air intake according to the flow field characteristics to obtain the external structure of a high-speed full-flow surface waverider aircraft with integrated internal and external flow. The construction of the forebody inlet includes: a top compression surface of the inlet, a bottom compression surface of the isolation section, and an outer envelope surface of the inlet lip. The top compression surface of the inlet is obtained by forward streamline tracing within the flow field of the axisymmetric outer cone inlet. The specific process for obtaining the flow field of the axisymmetric outer cone inlet is as follows: S2211, the second shock wave surface SW 2. The projection onto the symmetry plane of the forebody inlet is defined as the second shock surface. SW 2nd busbar, second shock surface SW The intersection of the generatrix of the second axisymmetric surface cone and the generatrix of the second axisymmetric surface cone is defined as the cone vertex of the second axisymmetric surface cone; S2212, at the second shock wave surface SW The distance from the second axis of symmetry on the second generatrix is ​​equal to the radius of the reference inlet capture circle. R c The point is taken as the leading edge point of the axisymmetric outer cone intake lip; S2213. In the flow field of the second axisymmetric curved surface cone, iterate the leftward characteristic line starting from the leading edge point, and define the intersection of the leftward characteristic line and the generatrix of the second axisymmetric curved surface cone as the endpoint of the shock wave dependent domain at the leading edge of the axisymmetric outer cone inlet. S2214, the second shock surface between the cone apex and the leading edge point. SW The generatrix is ​​defined as closed line I. The generatrix of the second axisymmetric surface cone between the cone apex and the endpoint of the leading edge shock wave dependent domain is defined as closed line II. The left-moving characteristic line between the leading edge point and the endpoint of the leading edge shock wave dependent domain is defined as closed line III. The closed region constructed by closed lines I, II, and III serves as the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field. S2215. Using the method of characteristics, with the closed line III as the initial condition, given the compression form of the axisymmetric external cone inlet wall, the compression surface of the axisymmetric external cone inlet and the corresponding flow field of the axisymmetric external cone inlet are obtained. S2 also includes: S2010, based on the given R c The capture surface of the inlet is constructed within the second axisymmetric curved conical flow field. The construction process is as follows: S2011, the center of the circle passing through the fourth trailing edge section. O 2. The vertical plane perpendicular to the fourth trailing edge section circle is defined as the symmetry plane of the forebody air intake. On the right view of the fourth trailing edge section circle, with O Starting from point 2, two rays are generated that are symmetrical about the front intake duct. The intersection points of the two rays and the corresponding projection curves of the leading edge profile are the left vertex and the right vertex of the leading edge, respectively. S2012, align the center of the reference intake capture circle with... O 2. The intersections of the two rays with the reference intake duct capture circle are defined as the left vertex I and right vertex I of the leading edge of the intake duct lip, respectively. S2013. The projected curve has curve segment I between the left and right vertices. The reference intake capture circle has curve segment II between the left and right vertices. The left ray has straight line segment I between the left and left vertices, and the right ray has straight line segment II between the right and right vertices. The closed region formed by curve segment I, curve segment II, straight line segment I, and straight line segment II is the capture surface of the intake, and the area of ​​the capture surface... S c It is characterized by the following formula: In the above formula, θ c The forebody intake fan annulus angle is formed by the left and right rays. r ( θ ) represents the polar coordinate function expression of the projection curve. θ It is a polar coordinate variable.

2. The design method for a high-speed full-flow surface waverider vehicle integrating internal and external flow as described in claim 1, characterized in that, In S1, the incoming flow conditions include: static pressure PS 0. Static temperature TS 0. Total pressure PT 0. Total temperature TT 0. Incoming Mach number Ma 0; The constraints include: the volume of the first axisymmetric cone, the length of the first axisymmetric axis corresponding to the first axisymmetric cone, and the radius of the base circle of the first axisymmetric cone, i.e., the first trailing edge section circle. R 1; The volume of the second axisymmetric cone, the length of the second axisymmetric axis corresponding to the second axisymmetric cone, and the radius of the base circle of the second axisymmetric cone, i.e., the circle of the third trailing edge section. R 3; The methods for generating the first axisymmetric surface cone flow field and the second axisymmetric surface cone flow field are as follows: S101. Select the type of generatrix of the axisymmetric surface cone; S102. Based on the generatrix type and constraint conditions of the axisymmetric surface cone, obtain the corresponding first axisymmetric surface cone and second axisymmetric surface cone; S103. Based on their respective axisymmetric surface cones and incoming flow conditions, the flow fields of the first and second axisymmetric surface cones and the corresponding first shock wave surface are obtained using the method of characteristics. SW 1. Second shock surface SW 2; S104, the first shock wave surface SW The intersection of 1 and the first trailing edge section circle is defined as the second trailing edge section circle and the second shock surface. SW The intersection of 2 and the third trailing edge section circle is defined as the fourth trailing edge section circle.

3. The design method for a high-speed full-flow surface waverider aircraft integrating internal and external flow as described in claim 2, characterized in that, In S2, the method for obtaining the superposition wavefront and the underposition wavefront is as follows: S2110. The second axisymmetric surface cone flow field is moved relative to the first axisymmetric surface cone flow field to obtain the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile. S2120. Starting from a series of discrete points on the leading edge profile, and taking the first trailing edge shock profile as the shock profile, the forward streamline tracing is carried out in the first axisymmetric curved surface cone flow field to obtain the upper wave surface of the aerodynamic shape of the full-flow surface waverider. S2130. Starting from the discrete point cluster on the projection curve corresponding to the leading edge profile, and taking the second trailing edge shock profile as the trailing edge shock profile of the lower wave surface, the lower wave surface is obtained by forward streamline tracing in the second axisymmetric curved surface cone flow field.

4. The design method for a high-speed full-flow surface waverider aircraft integrating internal and external flow as described in claim 3, characterized in that, The method for obtaining the leading edge profile, the first trailing edge shock profile, and the second trailing edge shock profile is as follows: S2111. Align the centers of the second trailing edge section circle and the fourth trailing edge section circle and place them in the same plane; S2112. Fix the first axisymmetric curved surface cone flow field, and move the second axisymmetric curved surface cone flow field upwards by a distance along the vertical direction of the second axis of symmetry. d make SW 1 and SW 2 intersect, the distance d It is characterized by the following formula: In the above formula, R 2 is the radius of the second trailing edge section circle. R 4 is the radius of the fourth trailing edge section circle; S2113, in SW 1 and SW When the two circles intersect, the intersection point of the second trailing edge section circle and the fourth trailing edge section circle is... A , B Connected line segments AB Defined as an intersecting chord, the length of the intersecting chord b It refers to the width of the aerodynamic shape of a high-speed, full-flow-surface waverider aircraft that integrates internal and external flows. SW 1 and SW The spatial intersection line formed by the two intersecting points is defined as the leading edge profile line; After the intersecting chord divides the second trailing edge section circle, the upper circular arc segment located above the intersecting chord is defined as the first trailing edge shock profile. After the intersecting chord divides the fourth trailing edge section circle, the lower circular arc segment located above the intersecting chord is defined as the second trailing edge shock profile.

5. The design method for a high-speed full-flow surface waverider vehicle integrating internal and external flow as described in claim 4, characterized in that, In S2, the method for obtaining the forebody air intake is as follows: S2210. Starting from the discrete point clusters on the projection curve of the leading edge profile, and taking the arc segment of the leading edge of the inlet lip as the shock wave profile of the trailing edge of the inlet, the forward streamline tracing is carried out in the flow field of the axisymmetric outer cone inlet to obtain the top compression surface of the inlet. S2220. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and taking the leading edge arc segment of the inlet lip as the shock wave profile of the inlet trailing edge, the forward streamline tracing is performed in the axisymmetric outer cone inlet flow field to obtain the bottom compression surface of the isolation section. S2230. Starting from the discrete point cluster on the leading edge arc segment of the inlet lip, and using the second trailing edge shock profile as the trailing edge shock profile of the outer envelope surface of the inlet lip, the forward streamline tracing is performed in the second axisymmetric curved surface cone flow field to obtain the outer envelope surface of the inlet lip.

6. The design method for a high-speed full-flow surface waverider vehicle integrating internal and external flow as described in claim 5, characterized in that, In S2210, the axisymmetric outer cone inlet flow field is constructed within the second axisymmetric curved cone flow field, which is the leading edge shock wave dependent domain of the axisymmetric outer cone inlet flow field. Given the compression form of the axisymmetric outer cone inlet wall, the compression surface of the axisymmetric outer cone inlet and the corresponding axisymmetric outer cone inlet flow field are generated using the method of characteristics.

7. The design method for a high-speed full-flow surface waverider vehicle integrating internal and external flow as described in claim 1, characterized in that, In S2210, the method for obtaining the top compression surface of the inlet is as follows: taking the discrete point cluster on curve segment I as the starting point, and taking the arc segment of the leading edge of the inlet lip between the left vertex I and the right vertex I as the shock wave profile of the trailing edge of the inlet, the forward streamline tracing is performed in the flow field of the axisymmetric outer cone inlet to obtain the corresponding streamline cluster, and the streamline cluster forms the top compression surface of the inlet.

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