Wide-speed-range waverider configuration based on constant volume deformation mode and design method

Abstract

The present disclosure relates to a wide-speed-range waverider configuration based on the iso-volume deformation mode, comprising a waverider surface arranged along a three-dimensional fixed leading edge line and a waverider unit, the waverider unit being provided with several different configuration state modes that can be switched, and the area of the waverider surface floating with different configuration state modes; wherein the three-dimensional fixed leading edge line of the waverider unit is completely consistent and the volume is equal in each configuration state mode; the waverider unit adjusts the waverider surface in real time by matching the inflow velocity, so as to realize the smooth transition of the waverider surface in the Mach number range of 5-15. The three-dimensional fixed leading edge line is extracted as a reference configuration in the above anti-wing double-back-sweep configuration; the three-dimensional fixed leading edge line is reconstructed by using a cubic quasi-uniform B-spline.

Description

Technical Field

[0001] This disclosure relates to the field of aerodynamic layout design technology for hypersonic vehicles, and more specifically, to a wide-velocity waverider shape and design method based on an equal-volume deformation method. Background Technology

[0002] Wide-velocity-range waveriders, with their unique "waveriding" effect—that is, using the leading-edge shock wave to confine high-pressure airflow to the lower surface to generate additional lift—exhibit a significant advantage in high lift-to-drag ratio during hypersonic flight, making them a research hotspot and core development direction in the aerospace field in recent years. Currently, the wide-velocity-range waverider technology solutions proposed globally mainly include various forms such as series-connected combined layouts, parallel modular designs, deformable waveriders, and fixed-planar-shape waveriders. Among them, deformable waveriders, because they can adjust their shape in real time to actively adapt to the flow field characteristics of different velocity ranges, are considered one of the most promising technology paths, especially in hypersonic vehicles with multi-mission profiles where there is an urgent need.

[0003] The mainstream design approach for existing deformable waveriders is based on the traditional tapered guide method. Its core logic is to design waverider shapes with the same leading edge at different Mach numbers, and then achieve shape deformation by discarding waverider surface segments adapted to high Mach numbers, or by using a combination of flexible skin and drive mechanism, etc., to adapt to speed changes. However, traditional cone-shaped waveriders have three inherent drawbacks: First, they cannot precisely control the volume of the waverider while strictly specifying the leading edge. Actual measurements show that the thickness difference of the waverider can reach more than 30% for different Mach numbers, and even exceeds 50% in extreme cases. Excessive deformation not only increases the fatigue loss of flexible materials, but also significantly increases the difficulty of structural design and sealing protection. Second, because sufficient space needs to be reserved in the deformation area, it is difficult to use it as an effective loading space, resulting in a volume utilization rate of generally less than 60%, causing a serious waste of valuable load space. Third, the lift-to-drag ratio performance advantage over a wide speed range is not obvious. In the commonly used cruise speed range of Ma=8~12, its lift-to-drag ratio is only 2%-5% higher than that of a fixed-shape waverider. In fact, the thin shape designed for low Mach numbers even shows better aerodynamic performance in some transition speed ranges (such as Ma=6-7), failing to reflect the core value of deformable design.

[0004] The emergence of waverider design methods with fixed leading-edge lines offers a technological possibility for solving the above problems. These methods can achieve basic consistency in shape across different velocity domains by precisely controlling the geometry of the leading-edge line. However, a complete isovolumetric deformation design system has not yet been formed in the current technology. Current research mostly focuses on performance optimization in a single velocity domain, or only achieves similarity of the leading-edge line rather than complete consistency, and cannot simultaneously take into account the synergistic optimization goals of leading-edge geometric consistency, volumetric stability, and aerodynamic performance across a wide velocity domain.

[0005] Therefore, there is an urgent need to develop a deformable waverider shape that can maintain the same leading edge and precisely equal volume across a wide speed range, so as to fundamentally reduce deformation costs, improve volume utilization, and achieve a balance between filling and lift-to-drag ratio requirements across a wide speed range. Summary of the Invention

[0006] To address the problems existing in the prior art, this disclosure proposes a wide-velocity-domain waverider shape and design method based on equal volume deformation, aiming to overcome at least one of the aforementioned technical problems. The technical solution adopted in this disclosure is as follows: In a first aspect, this disclosure provides a wide-velocity-domain waverider shape based on an isovolumetric deformation method, comprising: a waverider surface and waverider units arranged along a three-dimensional fixed leading edge line, wherein the waverider units are preset with several different shape state modes that can be switched, and the area of ​​the waverider surface floats with different shape state modes. Among them, the three-dimensional fixed leading edge lines of the waverider unit are completely consistent and have equal volume in each of the above-described shape state modes.

[0007] Preferably, the waverider unit adjusts the surface of the waverider in real time by matching the incoming flow velocity, thereby achieving a smooth transition of the waverider surface in the Mach number range of 5-15. Preferably, the three-dimensional fixed leading edge line and the anti-wing double-swept configuration are used as the reference shape for extraction.

[0008] Preferably, the three-dimensional fixed leading edge line is reconstructed using a cubic quasi-uniform B-spline.

[0009] Preferably, the baseline shape is: 8m in length, 9m in wingspan, 75° in the first sweep angle, 50° in the second sweep angle, and 0.8m in the wingtip elevation to form an upturned wing.

[0010] Preferably, the three-dimensional leading edge line is described by a B-spline curve.

[0011] Preferably, the surface area of ​​the waverider is between 32.01 and 32.98 m² under different shape configurations. 2 The area of ​​the waverider surface corresponding to each of the aforementioned shape states fluctuates between 2.5%.

[0012] Preferably, the number of all the shape state modes is three, namely Model-Ma5, Model-Ma10 and Model-Ma15.

[0013] Preferably, the Model-Ma5 corresponds to a Mach number of 5, a volume ratio τ of 0.1596, and volume matching is achieved by adjusting the shock angle of the conical flow. The shock angle β is 15.0°, and the corresponding surface area of ​​the waverider is 32.98m².

[0014] Preferably, the Model-Ma10 corresponds to a Mach number of 10, a volume ratio τ of 0.1596, and volume matching is achieved by adjusting the shock angle of the conical flow. The shock angle β is 10.868°, and the corresponding surface area of ​​the waverider is 32.17m².

[0015] Preferably, the Model-Ma15 corresponds to a Mach number of 15, a volume ratio τ of 0.1596, and volume matching is achieved by adjusting the shock angle of the conical flow. The shock angle β is 9.736°, and the corresponding surface area of ​​the waverider is 32.01m².

[0016] Preferably, the thickness of the central inner region of the Model-Ma5 is greater than that of the outer wing region, with a maximum thickness of 0.68m.

[0017] Preferably, Model-Ma10 and Model-Ma15 adopt a progressive thickness variation design to achieve smooth thickness changes.

[0018] Through the design of the thickness, Model-Ma5, Model-Ma10 and Model-Ma15 have good shock wave adhesion at the corresponding designed Mach number, and the leakage of high-pressure airflow on the lower surface is very small. Preferably, the planar shapes of each of the aforementioned shape states are consistent.

[0019] Preferably, in each of the aforementioned shape states, the aerodynamic focus position is concentrated between 69% and 71% of the total length of the waverider unit, and the longitudinal static stability margin formed by the aerodynamic focus position and the center of gravity position of the waverider unit (occupying 66.7% of the total length) is greater than 5%, thereby achieving longitudinal static stability without additional adjustment of the control surface.

[0020] Secondly, this disclosure provides a method for designing the shape of a wide-velocity waverider based on an equal-volume deformation method, applied to the aforementioned wide-velocity waverider shape, including the following steps: S100, the above anti-wing double-sweep configuration is used as the reference shape to extract the three-dimensional fixed leading edge line, and the three-dimensional fixed leading edge line is reconstructed by cubic quasi-uniform B-spline; S200. Based on the shape state mode Ma=5, determine the volume target, and by adjusting the shock angle β, design several shape state modes with equal volume corresponding to different Mach numbers. S300. Using computational fluid dynamics, the aerodynamic performance and wave-riding performance of the wave-rider unit in each of the above-described shape states are simulated and verified in a wide speed range. This is because the shock wave can attach well to the leading edge of the corresponding wide speed range wave-rider shape during flight in a wide speed range. S400: By adjusting the lower surface in real time to match the incoming flow velocity, the wide-speed-range waverider shape can achieve good waveriding characteristics under different flight conditions.

[0021] The beneficial effects of this disclosure are as follows: Through innovative isovolumetric deformation design, this disclosure can effectively balance the aerodynamic performance requirements under different speed ranges, significantly improve the lift-to-drag ratio characteristics, mission load adaptability and structural reliability of the vehicle in the full hypersonic speed range, provide core aerodynamic layout support for the engineering application of the next generation of hypersonic vehicles, and can be applied to hypersonic cruise missiles, space-to-space vehicles and transatmospheric transport vehicles with a flight Mach number covering a wide speed range of 5-15.

[0022] This disclosure uses a high-precision three-dimensional fixed leading edge line as a rigid reference boundary. By adjusting the design shock wave angle to change the flow field compression characteristics, a series of waverider units with completely consistent three-dimensional fixed leading edge lines and volume deviations of less than 1% are generated under different shape state modes corresponding to Mach numbers 5-15. By matching with the incoming flow velocity and adjusting the lower surface in real time, the shape of the wide-velocity waverider can be made to have good waveriding characteristics under different flight states, and maintain the stability of the planar shape and aerodynamic focus position during deformation.

[0023] Compared with the prior art, this disclosure has the following significant advantages: (1) Small deformation amplitude and stable volume: The three-dimensional fixed leading edge line of the shape state mode corresponding to each Mach number is completely consistent through coordinate calibration, the volume deviation is strictly controlled within 1%, the maximum difference in surface area of ​​the wave rider is only 2.5%, the maximum stretching / retraction amount of the flexible deformation method is significantly reduced compared with the traditional scheme, the structural design is less difficult, and the weight and cost are controllable. (2) High volume utilization: The design concept of "discarding the waverider surface" or "reserving deformation gap" in the traditional deformable scheme is completely abandoned. All the space inside the waverider is an effective loading space, which meets the loading requirements of large mission equipment such as high-precision guidance system and multi-mode warhead. (3) Excellent aerodynamic performance over a wide speed range: The maximum lift-to-drag ratio is stably maintained between 3.86 and 4.43 within the full design speed range of Ma=5~15; The consistency of the planar shape ensures that the aerodynamic focus position is concentrated between 69% and 71% of the total length in each state, resulting in good longitudinal stability. No additional adjustment of the control surface is required, reducing aerodynamic drag and control energy consumption. (4) Strong engineering applicability: The design method is closely integrated with computational fluid dynamics technology. By adjusting the shock angle parameters, it can be easily extended to the design of waveriders in other Mach number ranges of Ma=3-20. Applicable scenarios cover a variety of equipment such as tactical missiles and spaceplanes. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the specific embodiments of this disclosure or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the three-dimensional fixed leading edge line and surface of a wide-velocity waverider based on the equal volume deformation method described in Embodiment 1 of this disclosure.

[0026] Figure 2 It is the cross-section of the lower surface of a wide velocity domain waverider shape based on the equal volume deformation method described in Embodiment 1 of this disclosure at the flow direction positions of 25%, 50% and trailing edge sections (with x=0 representing the head vertex position); Figure 3 The lift coefficient, drag coefficient, and lift-to-drag ratio of Model-Ma5, Model-Ma10, and Model-Ma15 described in Embodiment 1 of this disclosure vary with Mach number at an angle of attack of 0°. Figure 4 This is a schematic diagram showing the variation of the aerodynamic focus with the angle of attack for Model-Ma5, Model-Ma10, and Model-Ma15 as described in Embodiment 1 of this disclosure when Ma=5, 10, and 15, respectively. Detailed Implementation

[0027] The present disclosure will now be described in detail with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in the present application can be combined with each other.

[0028] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this document.

[0029] Example 1: like Figure 1 As shown, this embodiment provides a wide-velocity-domain waverider shape based on an isovolumetric deformation method, including: a waverider surface and waverider units arranged along a three-dimensional fixed leading edge line. The waverider units are preset with several different shape state modes that can be switched. The area of ​​the waverider surface floats with different shape state modes. Among them, the three-dimensional fixed leading edge lines of the waverider unit are completely consistent and have equal volume in each of the above-described shape state modes.

[0030] Preferably, the waverider unit adjusts the surface of the waverider in real time by matching the incoming flow velocity, thereby achieving a smooth transition of the waverider surface in the Mach number range of 5-15.

[0031] It is understood that the waverider unit corresponds to multiple switchable shape state modes, and each shape state model is the shape model of the waverider unit in the corresponding state, that is, the shape state of the waverider unit in different states. During implementation, the waverider unit will switch / change between different shape state modes as the Mach number changes, thus allowing the shape of the waverider unit to change to a certain extent, and also allowing the surface area of ​​the waverider to fluctuate to a certain extent. Similarly, the design parameters and / or the surface area of ​​the waverider corresponding to each shape state mode are respectively the design parameters and / or the surface area of ​​the waverider unit in each shape state mode.

[0032] Preferably, the three-dimensional fixed leading edge line and the anti-wing double-swept configuration are used as the reference shape for extraction.

[0033] Preferably, the three-dimensional fixed leading edge line is reconstructed using a cubic quasi-uniform B-spline.

[0034] Preferably, such as Figure 1 As shown in (a), the baseline shape is: 8m in length, 9m in wingspan, 75° in the first sweep angle, 50° in the second sweep angle, and 0.8m in the wingtip elevation to form anhedral. The three-dimensional fixed leading edge line obtained here can be used to obtain the design curves in the close-cone method, namely the inlet capture curve (ICC) and the flow capture tube (FCT), by projecting them onto the top view and front view directions, respectively.

[0035] Understandably, the anhedral double-sweep configuration with excellent overall aerodynamic performance was selected as the baseline shape. This baseline shape was determined through multiple rounds of aerodynamic optimization, and the specific parameters are as follows: overall length 8m, wingspan 9m, first sweep angle 75° (corresponding to the inner wing section, enhancing high-speed stability), second sweep angle 50° (corresponding to the outer wing section, improving low-speed lift), and wingtip elevation of 0.8m to form anhedral characteristics to enhance roll stability.

[0036] Preferably, the three-dimensional leading edge line is described by a B-spline curve.

[0037] Preferably, the surface area of ​​the waverider is between 32.01 and 32.98 m² under different shape configurations. 2 The area of ​​the waverider surface corresponding to each of the aforementioned shape states fluctuates between 2.5%.

[0038] Preferably, the number of all the aforementioned shape state modes is three, namely Model-Ma5, Model-Ma10, and Model-Ma15; wherein, The Model-Ma5 corresponds to a Mach number of 5 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow. The shock angle β is 15.0°, and the corresponding surface area of ​​the waverider is 32.98 m². The Model-Ma10 corresponds to a Mach number of 10 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow, with a shock angle β of 10.868°, corresponding to a surface area of ​​32.17 m² for the waverider. The Model-Ma15 corresponds to a Mach number of 15 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow, with a shock angle β of 9.736°, and the corresponding surface area of ​​the waverider is 32.01 m².

[0039] Preferably, the thickness of the central inner region of the Model-Ma5 is greater than that of the outer wing region, with a maximum thickness of 0.68m.

[0040] Preferably, Model-Ma10 and Model-Ma15 adopt a progressive thickness variation design to achieve smooth thickness changes.

[0041] Through the design of the thickness, Model-Ma5, Model-Ma10 and Model-Ma15 have good shock wave adhesion at the corresponding designed Mach number, and the leakage of high-pressure airflow on the lower surface is very small. Preferably, the planar shapes of each of the aforementioned shape states are consistent.

[0042] Preferably, in each of the aforementioned shape states, the aerodynamic focus position is concentrated between 69% and 71% of the total length of the waverider unit, and the longitudinal static stability margin formed by the aerodynamic focus position and the center of gravity position of the waverider unit (occupying 66.7% of the total length) is greater than 5%, thereby achieving longitudinal static stability without additional adjustment of the control surface.

[0043] Working principle: The acquired ICC and FCT curves can be used as inputs. A waverider design method based on the close cone method with a fixed leading edge profile is used to generate corresponding shape state patterns for each waverider unit. Thus, the three-dimensional fixed leading edge line of the wide-velocity-range waverider shape is precisely the extracted anhedral double-swept configuration. Changing the shock wave angle can alter the volume corresponding to each shape state pattern while maintaining the same three-dimensional fixed leading edge line.

[0044] Specifically, corresponding shape state modes can be designed at Ma=5, 10, and 15 (unit: Mach). For example, at Ma=5, a shock angle β=15° is selected and named Model-Ma5. Then, referring to Model-Ma5 as the benchmark, shapes with the same volume are generated at Ma=10 and Ma=15 respectively. After testing, when generating the equal-volume shape Model-Ma10 at Ma=10, the shock angle β=10.868°; when generating the equal-volume shape Model-Ma15 at Ma=15, the shock angle β=9.736°.

[0045] Table 1 shows the specific design parameters for each external shape mode of the waverider unit, where the volumetric ratio τ = V 2 / 3 / S, where V is the volume and S is the projected area. The slight differences in the surface area of ​​the waverider under various shape modes primarily stem from minor adjustments to the surface morphology caused by the flow field compression effect, and do not affect the overall volume consistency. Comparison of waverider surfaces under different shape modes is shown in the figure. Figure 1 As shown in (b).

[0046] Table 1—Design parameters for each external shape mode

[0047] The aerodynamic performance of the waverider unit under various shape modes can be evaluated through computational fluid dynamics simulations. Numerical methods, such as the finite volume method, can be used to solve the three-dimensional compressible Navier-Stokes equations. Inviscid flux can be calculated using the Roe scheme; the weighted Green-Gauss formula reconstruction method can achieve second-order spatial accuracy. An improved Barth limiter can be selected as the gradient limiter to eliminate numerical overshoot and oscillations near computational breaks. Simultaneously, a local entropy correction method based on a pressure-assisted limiter is applied to avoid non-physical solutions. Viscous flux is calculated using a second-order central scheme. The turbulence model employs the widely used Menter SST. k-ω Two-equation model. The time direction can be solved using a second-order precision dual-time-step method, with implicit advancement via LU-SGS.

[0048] The computational platform can utilize CFD software, employing a partitioned structured grid with approximately 6.84 million grid cells to obtain the corresponding aerodynamic data. For example... Figure 3 As shown, the lift-drag performance of the three shape modes under zero angle of attack conditions is presented as a function of Mach number. With the same leading edge line and volume ratio, the drag coefficient of the waverider element at Ma=5 is larger than that at Ma=10 and Ma=15, while the lift coefficients are comparable. This results in the lift-drag ratio of Model-Ma5 being lower than that of Model-Ma10 and Model-Ma15 in all three modes. Figure 4 As stated above, when Ma=5, 10 and 15, the aerodynamic focus of each of the aforementioned shape state modes changes with the angle of attack. When the center of mass is uniformly set at 2 / 3 of the total length, all shape state modes maintain longitudinal static stability, and at the same Mach number, the positions of the aerodynamic focus are extremely close, concentrated in the range of 69% to 71% of the total length.

[0049] The wide-speed-range waverider shape formed by integrating the various shape state modes constitutes a complete deformation closed-loop control system, enabling smooth aerodynamic transitions at different Mach numbers: when the flight Mach number approaches 5 (4.5≤Ma<7.5), the waverider surface remains in its initial state, maintaining Model-Ma5 to obtain the optimal low-speed lift-to-drag ratio; when the Mach number enters the medium-speed range (7.5≤Ma<12.5), the waverider surface can be gradually deformed to Model-Ma10 using a flexible deformation method to adapt to the medium-compression flow field; when the Mach number reaches the high-speed range (Ma≥12.5), it is completely deformed into Model-Ma15 to match the characteristics of the strongly compressible flow field. Throughout the deformation process, the planar projection shape of the waverider remains absolutely consistent, with no change in key parameters such as its span and chord length, ensuring continuous consistency in longitudinal stability without the need for frequent adjustments to control surfaces such as the elevator.

[0050] Example 2: This embodiment provides a wide-velocity waverider shape design method based on equal volume deformation, which can be applied to the wide-velocity waverider shape described in Embodiment 1, including the following steps S100 to S400.

[0051] Step S100: Using the above anti-wing double-swept configuration as the reference shape, extract the three-dimensional fixed leading edge line, and then reconstruct the three-dimensional fixed leading edge line using cubic quasi-uniform B-splines.

[0052] Step S200: Determine the volume target based on the shape state mode Ma=5 (e.g., set τ=0.1596), and design several shape state modes with equal volume corresponding to different Mach numbers by adjusting the shock angle β.

[0053] Understandably, in step S200, the shape state mode corresponding to Mach 5 (i.e., Model-Ma5) is used as the baseline shape state mode because this state is the typical takeoff and landing transition velocity range for hypersonic vehicles, which places high demands on both volume and aerodynamic performance. The volume of the baseline waverider is accurately calculated using 3D modeling software. V 0 = 12.86 m³, planar projected area S =48.23m², define floor area ratio τ 0= V 0^(2 / 3) / S As a core indicator for volume control, it is calculated τ 0 = 0.1596. This value is used as the target for equal volume control. In the subsequent design of the shape state modes corresponding to different Mach numbers, the shock angle is adjusted to ensure that the deviation between the volume of each shape state mode and the reference volume does not exceed 1%, and the corresponding difference in the surface area of ​​the waverider is between 32.01 and 32.98 m². 2 This provides a foundation for the stable arrangement of mission payloads.

[0054] Step S300: Using computational fluid dynamics, the aerodynamic performance and wave-riding performance of the waverider unit in each of the described shape states are simulated and verified in a wide speed range. This is because the shock wave can attach well to the leading edge of the corresponding wide speed range waverider shape during flight in a wide speed range.

[0055] Understandably, in step S300, a waverider design method based on a closely spaced cone and a fixed leading edge profile can be used to design the shape state modes corresponding to the three typical hypersonic states of Mach numbers Ma=5, 10, and 15, respectively, resulting in Model-Ma5, Model-Ma10, and Model-Ma15. The leading edge lines of each element remain completely consistent. By precisely adjusting the design shock wave angle to change the flow field compression intensity, precise volume matching is achieved. The specific design features of each element are as follows: Model-Ma5 (Ma=5 element): Sets the shock wave angle of the conical flow. β =15.0°, directly generating a waverider shape that meets the reference volume. The waverider surface exhibits a design feature of "thick in the center and thin on the outer wing". The thickness of the central inner area is greater, providing a larger effective loading space. Ma=10 element (Model-Ma10): Based on an isovolumetric target, the shock angle is adjusted. β =10.868°. Compared with Model-Ma5, the thickness of this unit is reduced in the central inner region and slightly increased in the outer region, resulting in a more uniform overall thickness distribution; The Ma=15 element (Model-Ma15) is designed for strong compressive flow fields at higher Mach numbers. The shock angle is further optimized to β=9.736°, achieving precise volume matching. Its shape is highly similar to Model-Ma10, with a slightly reduced thickness on the inner central side and a largely identical outer side.

[0056] Step S400: By adjusting the lower surface in real time to match the incoming flow velocity, the wide-speed-range waverider shape can achieve good waveriding characteristics under different flight conditions.

[0057] It should be noted that the wide-speed-domain waverider shape design method described in Example 2 is only one method that can be used for the wide-speed-domain waverider shape described in Example 1, and does not mean that the wide-speed-domain waverider shape described in Example 1 must depend on the wide-speed-domain waverider shape design method described in Example 2.

[0058] In summary, the wide-velocity-range waverider shape and design method based on equal volume deformation provided in this disclosure can effectively balance the aerodynamic performance requirements under different velocity ranges through innovative equal volume deformation design. It significantly improves the lift-to-drag ratio characteristics, mission load adaptability and structural reliability of the vehicle in the full hypersonic velocity range, and provides core aerodynamic layout support for the engineering application of the next generation of hypersonic vehicles. It can be applied to wide-velocity-range hypersonic cruise missiles, space-to-space vehicles and transatmospheric transport vehicles with flight Mach numbers covering 5-15.

[0059] This disclosure uses a high-precision three-dimensional fixed leading edge line as a rigid reference boundary. By adjusting the design shock wave angle to change the flow field compression characteristics, a series of waverider units with completely consistent three-dimensional fixed leading edge lines and volume deviations of less than 1% are generated under different shape state modes corresponding to Mach numbers 5-15. By matching with the incoming flow velocity and adjusting the lower surface in real time, the shape of the wide-velocity waverider can be made to have good waveriding characteristics under different flight states, and maintain the stability of the planar shape and aerodynamic focus position during deformation.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this disclosure and not to limit them. Although this disclosure has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of this disclosure. Any modifications or equivalent substitutions that do not depart from the spirit and scope of this disclosure should be covered within the protection scope of the claims of this disclosure.

Claims

1. A wide-velocity waverider shape based on an isovolumetric deformation method, characterized in that, include: A waverider surface and waverider units are arranged along a three-dimensional fixed leading edge. The waverider units are preset with several different shape states that can be switched. The area of ​​the waverider surface floats with different shape states. Among them, the three-dimensional fixed leading edge lines of the waverider unit are completely consistent and have equal volumes in each of the said shape state modes; The waverider unit adjusts the surface of the waverider in real time by matching the incoming flow velocity, thereby achieving a smooth transition of the waverider surface in the Mach number range of 5-15.

2. The wide-velocity waverider shape according to claim 1, characterized in that, The three-dimensional fixed leading edge line and the anti-wing double-sweep configuration above the double-leading edge are used as the reference shape for extraction; The three-dimensional fixed leading edge line is reconstructed using cubic quasi-uniform B-splines.

3. The wide-velocity waverider shape according to claim 2, characterized in that, The baseline shape is as follows: overall length 8m, wingspan 9m, first sweep angle 75°, second sweep angle 50°, and wingtip elevation 0.8m to form an upturned wing.

4. The wide-velocity waverider shape according to claim 1, characterized in that, The three-dimensional leading edge line is described by a B-spline curve; The surface area of ​​the waverider ranges from 32.01 to 32.98 m² under different shape configurations. 2 The area of ​​the waverider surface corresponding to each of the aforementioned shape states fluctuates between 2.5%.

5. The wide-velocity waverider shape according to claim 4, characterized in that, The total number of all described shape state modes is three: Model-Ma5, Model-Ma10, and Model-Ma15; among them... The Model-Ma5 corresponds to a Mach number of 5 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow. The shock angle β is 15.0°, and the corresponding surface area of ​​the waverider is 32.98 m². The Model-Ma10 corresponds to a Mach number of 10 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow, with a shock angle β of 10.868°, corresponding to a surface area of ​​32.17 m² for the waverider. The Model-Ma15 corresponds to a Mach number of 15 and a volume ratio τ of 0.1596. Volume matching is achieved by adjusting the shock angle of the conical flow, with a shock angle β of 9.736°, and the corresponding surface area of ​​the waverider is 32.01 m².

6. The wide-velocity-range waverider shape according to claim 5, characterized in that, The thickness of the central inner region of the Model-Ma5 is greater than that of the outer wing region, with a maximum thickness of 0.68m.

7. The wide-velocity-range waverider shape according to claim 5, characterized in that, The Model-Ma10 and Model-Ma15 adopt a progressive thickness variation design to achieve smooth thickness changes.

8. The wide-velocity waverider shape according to claim 1, characterized in that, The planar shape of each of the aforementioned shape state modes is consistent.

9. The wide-velocity waverider shape according to claim 1, characterized in that, In each of the aforementioned shape states, the aerodynamic focus position is concentrated between 69% and 71% of the total length of the waverider unit. The longitudinal static stability margin formed by the aerodynamic focus position and the center of gravity position of the waverider unit is greater than 5%, thus achieving longitudinal static stability without additional adjustment of the control surface.

10. A method for designing the shape of a wide-velocity waverider based on an isovolumetric deformation method, applied to the wide-velocity waverider shape as described in any one of claims 1-9, characterized in that, Includes the following steps: S100, the above anti-wing double-swept configuration is used as the reference shape to extract the three-dimensional fixed leading edge line, and the three-dimensional fixed leading edge line is reconstructed by cubic quasi-uniform B-spline; S200. Based on the shape state mode Ma=5, determine the volume target, and by adjusting the shock angle β, design several shape state modes with equal volume corresponding to different Mach numbers. S300. Using computational fluid dynamics, the aerodynamic performance and wave-riding performance of the wave-rider unit in each of the above-described shape states are simulated and verified in a wide speed range. This is because the shock wave can attach well to the leading edge of the corresponding wide speed range wave-rider shape during flight in a wide speed range. S400: By adjusting the lower surface in real time to match the incoming flow velocity, the wide-speed-range waverider shape can achieve good waveriding characteristics under different flight conditions.

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