A method and device for designing a high-low Mach number double design point waverider forebody and internally turning variable inlet

Abstract

The application provides a high / low Mach number double-design-point-based waverider forebody / inner turning adjustable inlet design method and device, relates to the waverider forebody / inlet profile aerodynamic technical field, and comprises the following steps: acquiring a forebody shock wave and a waverider forebody and calculating forebody flow field parameters based on a given incoming flow design working condition; constructing an inner cone flow field to generate an inner cone shock wave based on the forebody flow field parameters; determining an inlet capture type line based on the forebody shock wave, the waverider forebody and the inner cone shock wave, and generating an inner turning inlet profile in the inner cone flow field; performing profile constraint and profile adjustment on the inner turning inlet profile to generate an inner turning adjustable inlet configuration, and jointly forming a forebody / inner turning adjustable inlet integrated configuration with the waverider forebody; and iteratively optimizing the forebody / inner turning adjustable inlet integrated configuration under the condition of a given low Mach number flow constraint. The scheme can solve the leakage problem of the inner turning inlet designed under the high Mach number design point working condition under the low Mach number working condition.

Description

Technical Field

[0001] This application relates to the field of aerodynamic technology for waverider forebody / inlet profile, and more specifically, to a design method and apparatus for a waverider forebody and an internally adjustable inlet based on dual design points of high and low Mach numbers. Background Technology

[0002] As the Mach number range of wide-speed-range aircraft continues to expand, no single power mode can meet the flight requirements. Therefore, wide-speed-range aircraft employing air-breathing combined propulsion systems have become a research hotspot in the future aerospace field. In air-breathing combined propulsion systems, the air intake, as a key component, needs to possess wide-speed-range capability to achieve speed and flow rate matching. Compared to conventional axisymmetric and two-dimensional air intakes, the internal rotating air intake has advantages such as strong compression capacity and small wetted area. Therefore, the adjustment system using the internal rotating air intake has broad application prospects. Currently, to achieve matching between different engine speeds and flow rates, the design of the internal rotating adjustable air intake is usually based on a high Mach number design point, precisely ensuring the flow rate requirements under high Mach number design point conditions. At low Mach numbers (outside the design point), excess flow is discharged by rotating the air intake compression surface to ensure air intake start-up. Generally, the higher the high Mach number design point, the more severe the start-up problem faced by the air intake at low Mach numbers, and the greater the discharge flow required to ensure air intake start-up. On the one hand, excessive leakage will reduce the actual utilization rate of the airflow captured and compressed by the intake duct profile; on the other hand, excessive rotation of the intake duct compression surface at an excessive angle will cause airflow expansion. Summary of the Invention

[0003] The embodiments of this application provide a design method and apparatus for a waverider forebody and an adjustable inlet based on dual design points of high and low Mach numbers. By combining traditional aerodynamic design methods with optimization methods, a forebody and adjustable inlet configuration that meets flow requirements over a wide speed range can be quickly obtained. The design process aims to improve the airflow capture utilization rate under low Mach number conditions and reduce the airflow expansion effect caused by the rotation of the splitter plate. This reduces the bleed demand at low Mach numbers and reduces the rotation angle of the splitter plate during bleed, thereby reducing the airflow expansion effect and improving the self-starting capability of the adjustable inlet.

[0004] Other features and advantages of this application will become apparent from the following detailed description, or may be learned in part from practice of this application.

[0005] According to a first aspect of the embodiments of this application, a design method for a waverider forebody and an internally adjustable inlet based on dual design points of high and low Mach numbers is provided, comprising: Based on the given incoming flow design conditions, the forebody shock wave and wave-riding forebody are obtained, and the forebody flow field parameters are calculated. Based on the aforementioned precursor flow field parameters, an inner cone flow field is constructed to generate an inner cone shock wave; The intake capture profile is determined based on the precursor shock wave, the wave-riding precursor, and the inner cone shock wave, and the inner cone intake profile is generated in the inner cone flow field. The internal rotating inlet profile is constrained and adjusted to generate an internal rotating adjustable inlet configuration, which together with the wave-riding forebody forms an integrated configuration of the forebody and the internal rotating adjustable inlet. Given flow constraints at low Mach numbers, the integrated configuration of the forebody and the internal adjustable inlet is iteratively optimized.

[0006] In some embodiments of this application, based on the foregoing scheme, the calculation of the precursor flow field parameters includes: The internal intake duct is located in the interval between the first and second cross sections of the waverider forebody flow field, and this interval is defined as a specific interval of the waverider forebody flow field. Calculate the average airflow parameters within a specific interval of the wave-riding forebody flow field.

[0007] In some embodiments of this application, based on the foregoing scheme, the step of constructing an inner cone flow field and generating an inner cone shock wave based on the precursor flow field parameters includes: Based on the given inflow conditions of the inner cone flow field and the parameters of the forebody flow field, the inner cone flow field is constructed and an inner cone shock wave is generated using the two-dimensional axisymmetric rotatable characteristic line method.

[0008] In some embodiments of this application, based on the foregoing scheme, determining the inlet capture profile based on the precursor shock wave, the waverider precursor, and the inner cone shock wave includes: After rotating the inner cone shock wave by a set angle, it intersects with the wave-riding forebody to form a forebody intersection line, and intersects with the forebody shock wave to form a shock wave intersection line; Given two sidewall profiles, the forebody intersection line, the shock wave intersection line, and the two sidewall profiles together form the intake capture profile.

[0009] In some embodiments of this application, based on the foregoing scheme, the shape of the intake duct capture profile can be changed by adjusting the position of the inner cone shock wave.

[0010] In some embodiments of this application, based on the foregoing scheme, the profile of the internal intake duct is constrained, including: Initial flow surfaces are generated by streamline tracing in the inner cone flow field based on the intersection line of the forebody. Given the predicted values ​​of streamline deviations at all discrete points along the intersection line of the precursor body, when the root mean square error of the streamline deviations at all discrete points... When formula (1) is satisfied, the surface constraint is completed; (1) in, It is a small constant. The first on the anterior body intersection line discrete points, This is the predicted value of the streamline deviation at this discrete point. This represents the total number of discrete points.

[0011] In some embodiments of this application, based on the foregoing scheme, the shape of the forebody intersection line is determined by the shape along the initial flow surface. The position of the inner cone shock wave changes due to axial translation.

[0012] In some embodiments of this application, the process of adjusting the surface based on the foregoing solution includes: On the inner intake duct profile after the profile constraint is applied, the streamlines located on the plane of symmetry are extended to both sides to form splitters, and the throat cross-section is designed to be rectangular.

[0013] In some embodiments of this application, based on the foregoing scheme, the iterative optimization of the integrated configuration of the forebody and the internal adjustable inlet, given the flow constraint at a low Mach number, includes: Viscous numerical simulation calculations were performed on the integrated configuration of the forebody and the internal adjustable intake under low Mach number conditions to obtain the actual airflow at the intake outlet. Based on actual working flow requirements, determine the required flow rate at low Mach numbers and give a flow rate constraint range; Determine whether the actual airflow at the intake outlet is within the flow constraint range. If not, readjust the position of the inner cone shock wave and recalculate the actual airflow at the intake outlet until the actual airflow at the intake outlet is within the flow constraint range.

[0014] According to a second aspect of the embodiments of this application, a waverider forebody and an internally adjustable inlet design device based on dual design points of high and low Mach numbers are provided, comprising: The calculation unit is used to obtain the forebody shock wave and wave-riding forebody based on the given incoming flow design conditions, and to calculate the forebody flow field parameters. The first generation unit is used to construct an inner cone flow field and generate an inner cone shock wave based on the forebody flow field parameters. The second generation unit is used to determine the intake duct capture profile based on the precursor shock wave, the wave-riding precursor and the inner cone shock wave, and to generate the inner turning intake duct profile in the inner cone flow field. The first constraint unit is used to constrain and adjust the profile of the inner rotating inlet to generate an adjustable inner rotating inlet configuration, and together with the wave-riding forebody, it forms an integrated configuration of the forebody and the adjustable inner rotating inlet. The second constraint unit is used to iteratively optimize the integrated configuration of the precursor and the internal adjustable inlet under a given flow constraint at a low Mach number.

[0015] The integrated configuration of the waverider forebody and the internal adjustable inlet generated in this application reduces the bleed-out requirements of the internal adjustable inlet during low Mach number start-up, improves the airflow capture utilization rate of the inlet under low Mach number conditions, reduces the rotation angle of the splitter plate during bleed-out, thereby weakening the airflow expansion effect and improving the self-starting capability of the internal adjustable inlet.

[0016] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings: Figure 1 A schematic flowchart of a design method for a waverider forebody and an internally adjustable inlet based on dual design points of high and low Mach numbers, according to an embodiment of this application, is shown. Figure 2 The diagram illustrates the implementation steps of an example of a design method for a waverider forebody and an internally adjustable inlet based on dual design points of high and low Mach numbers, according to an embodiment of this application. Figure 3 A schematic diagram of waverider generation and forebody flow field according to an embodiment of this application is shown; Figure 4 A schematic diagram of the internal cone flow field construction according to an embodiment of this application is shown; Figure 5 A schematic diagram of determining the capture profile according to an embodiment of this application is shown; Figure 6 A schematic diagram of the internal intake duct profile according to an embodiment of this application is shown; Figure 7 A schematic diagram of streamline deviation according to an embodiment of this application is shown; Figure 8 A schematic diagram of the adjustable pivot position according to an embodiment of this application is shown; Figure 9 A schematic diagram of an adjustable profile design according to an embodiment of this application is shown; Figure 10 An integrated configuration of a waverider forebody and an internally adjustable inlet is shown according to one embodiment of this application; Figure 11 A schematic diagram illustrating the definition of capture traffic utilization according to an embodiment of this application is shown; Figure 12 A block diagram of a waverider forebody and internally adjustable inlet design device based on dual design points of high and low Mach numbers, according to one embodiment of this application, is shown. Detailed Implementation

[0018] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided to make this application more comprehensive and complete, and to fully convey the concept of the exemplary embodiments to those skilled in the art.

[0019] Furthermore, the described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a thorough understanding of embodiments of this application. However, those skilled in the art will recognize that the technical solutions of this application can be practiced without one or more of the specific details, or other methods, components, apparatuses, steps, etc., can be employed. In other instances, well-known methods, apparatuses, implementations, or operations are not shown or described in detail to avoid obscuring various aspects of this application.

[0020] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0021] It should be noted that "multiple" in this article refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, or B alone. The character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of the embodiments of this invention 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 invention, and not all of them. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0023] The following detailed description of some embodiments of this application will be provided in conjunction with the accompanying drawings. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0024] See Figure 1 The diagram shows a flow chart of a waverider forebody and internally adjustable inlet design method based on high and low Mach number dual design points according to an embodiment of this application.

[0025] like Figure 1 As shown, a design method for a waverider forebody and an internally adjustable inlet based on dual design points of high and low Mach numbers is presented, specifically including steps S100 to S500.

[0026] refer to Figure 1 Step S100: Based on the given incoming flow design conditions, obtain the forebody shock wave and wave-riding forebody, and calculate the forebody flow field parameters.

[0027] Understandably, based on the given incoming flow design conditions, the forebody shock wave and waverider configuration can be obtained, and the waverider configuration can be used as the waverider forebody.

[0028] In some feasible embodiments, based on the foregoing scheme, the calculation of the precursor flow field parameters includes: The internal intake duct is located in the interval between the first and second cross sections of the waverider forebody flow field, and this interval is defined as a specific interval of the waverider forebody flow field. Calculate the average airflow parameters within a specific interval of the wave-riding forebody flow field.

[0029] Continue to refer to Figure 1 Step S200: Based on the precursor flow field parameters, construct the inner cone flow field to generate the inner cone shock wave.

[0030] In some feasible embodiments, based on the foregoing scheme, the step of constructing an inner cone flow field and generating an inner cone shock wave based on the precursor flow field parameters includes: Based on the given inflow conditions of the inner cone flow field and the parameters of the forebody flow field, the inner cone flow field is constructed and an inner cone shock wave is generated using the two-dimensional axisymmetric rotatable characteristic line method.

[0031] Continue to refer to Figure 1 Step S300: Determine the intake duct capture profile based on the precursor shock wave, the wave-riding precursor, and the inner cone shock wave, and generate the inner turning intake duct profile in the inner cone flow field.

[0032] In some feasible embodiments, based on the foregoing scheme, determining the inlet capture profile based on the precursor shock wave, the waverider precursor, and the inner cone shock wave includes: After rotating the inner cone shock wave by a set angle, it intersects with the wave-riding forebody to form a forebody intersection line, and intersects with the forebody shock wave to form a shock wave intersection line; Given two sidewall profiles, the forebody intersection line, the shock wave intersection line, and the two sidewall profiles together form the intake capture profile.

[0033] It should be noted that, in this embodiment, the shape of the intake duct capture profile can be changed by adjusting the position of the inner cone shock wave.

[0034] Continue to refer to Figure 1 In step S400, the inner rotating intake profile is constrained and adjusted to generate an inner rotating adjustable intake configuration, which together with the wave-riding forebody forms an integrated configuration of the forebody and the inner rotating adjustable intake.

[0035] In some feasible embodiments, based on the foregoing scheme, the profile of the inner intake duct is constrained, including: Initial flow surfaces are generated by streamline tracing in the inner cone flow field based on the intersection line of the forebody. Given the predicted values ​​of streamline deviations at all discrete points along the intersection line of the precursor body, when the root mean square error of the streamline deviations at all discrete points... When formula (1) is satisfied, the surface constraint is completed; (1) in, It is a small constant. The first on the anterior body intersection line discrete points, This is the predicted value of the streamline deviation at this discrete point. This represents the total number of discrete points.

[0036] It should be noted that, in this embodiment, the shape of the forebody intersection line is determined by the shape along the initial flow surface. The position of the inner cone shock wave changes due to axial translation.

[0037] In some feasible embodiments, the process of adjusting the surface based on the aforementioned scheme includes: On the inner intake duct profile after the profile constraint is applied, the streamlines located on the plane of symmetry are extended to both sides to form splitters, and the throat cross-section is designed to be rectangular.

[0038] Continue to refer to Figure 1 In step S500, given the flow constraint at a low Mach number, the integrated configuration of the precursor and the internal adjustable inlet is iteratively optimized.

[0039] In some feasible embodiments, based on the foregoing scheme, the iterative optimization of the integrated configuration of the forebody and the internal adjustable inlet, given the flow constraint at a low Mach number, includes: Viscous numerical simulation calculations were performed on the integrated configuration of the forebody and the internal adjustable intake under low Mach number conditions to obtain the actual airflow at the intake outlet. Based on actual working flow requirements, determine the required flow rate at low Mach numbers and give a flow rate constraint range; Determine whether the actual airflow at the intake outlet is within the flow constraint range. If not, readjust the position of the inner cone shock wave and recalculate the actual airflow at the intake outlet until the actual airflow at the intake outlet is within the flow constraint range.

[0040] Below is a specific example of this method.

[0041] like Figure 2 As shown, the example method includes the following steps: S1: Waverider generation and forebody flow field parameter calculation S1.1 Waverider Generation This example waverider generation references "(Ding Feng. Research on the Theory and Method of Integrated Internal and External Flow 'Full Waverider' Aerodynamic Design for Air-breathing Hypersonic Vehicles [D]. National University of Defense Technology. Changsha, Hunan. 2016) Chapter 3 Research on General Waverider Design Method", with the given flight flow design conditions as follows: flight altitude H = 29.05 km, Mach number =7.0Ma, incoming static pressure , incoming flow static temperature Angle of attack = Generate after giving the bottom projection profile. Figure 3 The waverider configuration shown is used as the waverider forebody. Viscous numerical simulations are then performed on this waverider configuration to obtain all flow parameters in the forebody flow field.

[0042] S1.2 Calculation of forebody flow field parameters The internal intake duct is positioned at the mid-section of the forebody flow field. and cross section Between these intervals, which constitute a specific region of the forebody flow field, the average airflow parameters within this interval are calculated, and the average airflow angle is... Mean Mach number = . Use this parameter as the input value for the subsequent design parameters of the inner cone flow field.

[0043] S2: Internal intake manifold profile generation S2.1 Constructing the internal cone flow field This example of the internal cone flow field design references the patent "Patent Application No. 201910325410.6 (“An Integrated Design Method for the Internal Rotating Waverider Forebody Inlet of a Supersonic Vehicle”), which employs a two-dimensional axisymmetric rotatable characteristic line method. Given the incoming flow parameters, the internal cone flow field and internal cone shock wave can be obtained. Adjusting the generatrix of the rotating body... abc The parameters can be adjusted to change the inner cone flow field and alter the shape of the inner cone shock wave. For example... Figure 4 The rotating body's generatrix abc From a quadratic curve ab and a cubic curve bc Composition, design parameters include points a coordinate a ( and inclination angle , b x-coordinate of point ( and inclination angle , c coordinates of the point c ( and inclination angle The main design parameter for the inner cone flow field is the incoming Mach number. = . Ma, that is . Ma represents the high Mach number design point for the intake duct selected in this case. Other parameters are based on static pressure. , incoming flow static temperature .

[0044] S2.2 Determine the intake capture profile like Figure 5 As shown, in order to match the flow angle behind the forebody shock wave, the aforementioned inner cone shock wave is rotated. The shock then intersects with the waverider and the forebody shock wave. The intersection of the waverider and the inner cone shock wave forms the forebody intersection line, and the intersection of the forebody shock wave and the inner cone shock wave forms the shock wave intersection line. Given two sidewall profiles, the forebody intersection line, the shock wave intersection line, and the sidewall profiles together constitute the inlet capture profile. Based on this profile, the inner conical inlet profile is generated using a streamline tracing method in the inner cone flow field, as shown below. Figure 6 It is worth noting that the shape of the intake capture profile can be changed by adjusting the position of the inner cone shock wave. In order to match the backflow angle of the forebody shock wave, the rotation angle of the inner cone shock wave remains unchanged, and only the position is changed by translation.

[0045] S3: Optimized and iterative design of integrated forebody and internally adjustable inlet configuration S3.1 Iterative optimization under surface constraints S3.1.1 Determination of Surface Constraints (1) The surface constraint design of this example is based on the reference "Integrated design of variable-geometric inward-turning inlet and waverider via accurate capture profile matching[J].Aerospace Science and Technology,2026,Vol.172: 111749". The initial flow surface is generated by streamline tracing in the inner cone flow field based on the forebody intersection line, as shown below. Figure 7 As shown, AA The cross-section is perpendicular to the incoming flow, and M and N are the contour lines on both sides of the initial flow surface. AA The intersection of the cross sections, PQ is a streamline that makes up the flow surface, and point Q is where the streamline flows to the cross section. AA streamline point at the location, AA The distance between point Q and MN on the cross section is denoted as the streamline deviation Δ at point Q. d The predicted values ​​for streamline deviations at all discrete points on the intersection line FI are: The iteration terminates when the root mean square error (RMSE) of the streamline deviations at all discrete points is sufficiently small, i.e., the following convergence condition is satisfied.

[0046] in It is a small constant. The first on the anterior body intersection line i discrete points, This step concludes the iteration with the predicted streamline deviation value for this discrete point. In this example, we take... , .

[0047] (2) Iteratively determine the shape of the intersection line of the precursor.

[0048] The shape of the forebody intersection line is obtained by following along x The position of the inner cone shock wave is changed by axial translation. The root mean square error is calculated after the final iteration. Therefore, it can be considered that the flow surface is at this point. AA The wall profile at the cross-section is approximately a straight line, which can meet the engineering requirements for the pivot design. The pivot position is as follows: Figure 8 As shown, the surface behind the pivot can rotate around the pivot.

[0049] S3.1.2 Adjustable Surface Design An adjustable profile is designed on the optimized flow surface. Streamlines located on the plane of symmetry are extended to both sides to form flow dividers. To meet geometric adjustment constraints and ensure the sealing of the flow channel, the throat cross-section is designed as rectangular. Comparison shows that the generated rotating surface has slight changes in profile on both sides compared to the original flow surface, but the profile change is smaller near the plane of symmetry, thus preserving the flow characteristics of the main flow region to the greatest extent. The rotating surface rotates around its axis to achieve flow regulation.

[0050] S3.1.3 Generation of an integrated configuration for the forebody and internally adjustable inlet At this point, the existing waverider and the internally adjustable intake duct together form an integrated configuration of the forebody and the internally adjustable intake duct. Viscous numerical simulation calculations are performed to obtain the actual airflow at the intake duct outlet. Based on the flow requirements of a certain type of TBCC engine during operation, this integrated configuration is scaled up to ensure that the actual airflow in the intake duct meets the engine requirements at the high Mach number design point of 7.0 Ma.

[0051] S3.2 Iterative Optimization of Flow Constraints S3.2.1 Calculate the actual airflow rate in the intake at low Mach numbers Based on the aforementioned integrated configuration of the precursor and the internally adjustable intake duct, viscous numerical simulation calculations were performed under low Mach number conditions to obtain the actual airflow rate at the intake duct outlet. This example selects... =3.4Ma, that is, 3.4Ma is the low Mach number design point of the intake selected in this example.

[0052] S3.2.2 Flow Constraint Determination Based on the flow requirements of a certain type of TBCC engine during operation, given a low Mach number ( Demand flow rate at 3.4 Ma and give the flow constraint range If the above calculations result in the actual airflow rate at the intake outlet... If the flow constraint interval is not met, the position of the inner cone shock wave is readjusted, and steps S2.2 to S3.2 are repeated until the actual airflow at the intake outlet is reached. The conditions of the flow constraint range are met. The final output is an integrated configuration of the waverider forebody and the internally adjustable inlet.

[0053] This example compares the performance of a conventional internal intake at low Mach numbers: (1) The integrated configuration of the waverider forebody and the internally adjustable inlet generated in this example has a high angle of attack. = The capture area was 0.3734. The ratio of the capture area to the intake throat area is 6.9 (i.e., the total contraction ratio is 6.9), and the design point for the integrated configuration at high Mach number is 7.0 Ma and the design point for low Mach number is 3.4 Ma.

[0054] For comparative analysis, given similar inlet capture profiles and ensuring angle of attack, = The capture area was 0.3734. The ratio of the capture area to the intake throat area is 6.9 (i.e., the total contraction ratio is 6.9), ensuring only a high Mach number design point of 7.0 Ma, and generating an internally adjustable intake through conventional surface modification methods.

[0055] Table 1 Comparison of self-starting Mach numbers

[0056] Results analysis: Under normal flow conditions, the integrated intake configuration of the waverider forebody and the internal adjustable intake in this implementation case starts normally at an incoming flow Mach number of 2.3 Ma, while the conventional internal adjustable intake can only start normally at an incoming flow Mach number of 4.0 Ma.

[0057] (2) The range of low Mach numbers is given ( =2.0Ma~4.0Ma), the intake duct capture flow utilization rate and related performance when a good supersonic flow field is established in the intake duct under the condition of flow passage.

[0058] Table 2. Utilization rate and related performance of conventional internal intake traps

[0059] Table 3. Inlet capture flow utilization and related performance in the integrated configuration of waverider forebody and internally adjustable inlet.

[0060] Results Analysis: Under normal flow conditions, the initial matching range of velocity and flow rate for the integrated configuration of the waverider forebody and the internal adjustable inlet in this implementation case is 3.4 Ma to 7.0 Ma. In the range of 2.0 Ma to 3.4 Ma, the inlet only needs a maximum of 3° of rotation of the splitter to ensure normal start-up of the inlet and the capture flow utilization rate is over 70%. In contrast, the initial matching range of velocity and flow rate for the conventional internal adjustable inlet is 4.0 Ma to 7.0 Ma. In the range of 2.0 Ma to 4.0 Ma, the inlet needs a maximum of 8° of rotation of the splitter to ensure normal start-up of the inlet. Moreover, as the Mach number decreases, the capture flow utilization rate of the inlet gradually decreases, and the capture flow utilization rate is only 38.44% at Ma 2.0.

[0061] Beneficial effects: Based on the above results, it can be seen that after flow constraint iteration, the initial matching range of velocity and flow of the integrated configuration of the forebody and the internal adjustable inlet is effectively widened. At the same time, the flow requirement can be met with a smaller profile adjustment angle in the low Mach number stage, which improves the airflow capture utilization rate, reduces the airflow expansion effect, and improves the self-starting capability of the internal adjustable inlet.

[0062] It should be noted that the optimization iterations in this example are based on the multi-science optimization platform Isight, employing the Multi-Island Genetic Algorithm (MIGA) for multi-objective optimization. The population size is set to 10, the number of islands to 10, the number of generations to 10, and the crossover rate to 0.9. For multi-objective optimization (MO) problems, Pareto optimization theory is introduced to seek the optimal solution set at the Pareto front. This implementation case represents one scenario within the optimal solution set.

[0063] Intake duct capture flow utilization rate definition: such as Figure 11 As shown, at low Mach, the rotating splitter discharges part of the airflow to ensure normal start-up of the intake. The flow rate entering the intake after passing through the lip section is the actual captured flow rate, denoted as . The flow rate passing through the throat section is the actual effective flow rate, denoted as . The intake duct capture flow utilization rate is defined as the actual effective flow rate. Compared with actual captured traffic ratio .

[0064] The following describes an embodiment of the apparatus described in this application, which can be used to execute a waverider forebody and internally adjustable inlet design method based on dual design points of high and low Mach numbers as described in the above embodiments of this application. For details not disclosed in the apparatus embodiments of this application, please refer to the embodiments of the method described in the above applications.

[0065] Reference Figure 12 As shown, a waverider forebody and internally adjustable inlet design device 1200 based on high and low Mach number dual design points according to an embodiment of this application includes: The calculation unit 1201 is used to obtain the forebody shock wave and wave-riding forebody based on the given incoming flow design conditions, and to calculate the forebody flow field parameters. The first generation unit 1202 is used to construct an inner cone flow field and generate an inner cone shock wave based on the forebody flow field parameters. The second generation unit 1203 is used to determine the intake duct capture profile based on the forebody shock wave, the wave-riding forebody, and the inner cone shock wave, and to generate the inner cone intake duct profile in the inner cone flow field. The first constraint unit 1204 is used to constrain and adjust the profile of the inner rotating inlet to generate an adjustable inner rotating inlet configuration, and together with the wave-riding forebody, form an integrated configuration of the forebody and the adjustable inner rotating inlet. The second constraint unit 1205 is used to iteratively optimize the integrated configuration of the forebody and the internal adjustable inlet under a given flow constraint at a low Mach number.

[0066] Other embodiments of this application will readily conceive of by those skilled in the art upon consideration of the specification and practice of the embodiments disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. It should be understood that this application is not limited to the precise structures described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.

Claims

1. A method for designing a high-low Mach number dual design point waverider forebody and internally turning variable inlet, characterized in that, include: Based on the given incoming flow design conditions, the forebody shock wave and wave-riding forebody are obtained, and the forebody flow field parameters are calculated. Based on the aforementioned precursor flow field parameters, an inner cone flow field is constructed to generate an inner cone shock wave; The intake capture profile is determined based on the precursor shock wave, the wave-riding precursor, and the inner cone shock wave, and the inner cone intake profile is generated in the inner cone flow field. The internal rotating inlet profile is constrained and adjusted to generate an internal rotating adjustable inlet configuration, which together with the wave-riding forebody forms an integrated configuration of the forebody and the internal rotating adjustable inlet. Given flow constraints at low Mach numbers, the integrated configuration of the forebody and the internal adjustable inlet is iteratively optimized. The calculation of the precursor flow field parameters includes: The internal intake duct is located in the interval between the first and second cross sections of the waverider forebody flow field, and this interval is defined as a specific interval of the waverider forebody flow field. Calculate the average airflow parameters within a specific range of the waverider forebody flow field; The process of constructing an inner cone flow field and generating an inner cone shock wave based on the forebody flow field parameters includes: Based on the given inflow conditions of the inner cone flow field and the parameters of the forebody flow field, the inner cone flow field is constructed and an inner cone shock wave is generated using the two-dimensional axisymmetric rotatable characteristic line method.

2. The method of claim 1, wherein, The determination of the inlet capture profile based on the precursor shock wave, the waverider precursor, and the inner cone shock wave includes: After rotating the inner cone shock wave by a set angle, it intersects with the wave-riding forebody to form a forebody intersection line, and intersects with the forebody shock wave to form a shock wave intersection line; Given two sidewall profiles, the forebody intersection line, the shock wave intersection line, and the two sidewall profiles together form the intake capture profile.

3. The method according to claim 2, characterized in that, The shape of the intake capture profile can be changed by adjusting the position of the inner cone shock wave.

4. The method according to claim 2, characterized in that, The surface constraint of the inner intake duct profile includes: Initial flow surfaces are generated by streamline tracing in the inner cone flow field based on the intersection line of the forebody. Given the predicted values ​​of streamline deviations at all discrete points along the intersection line of the precursor body, when the root mean square error of the streamline deviations at all discrete points... When formula (1) is satisfied, the surface constraint is completed; ；（1） in, It is a small constant. The first on the anterior body intersection line discrete points, This is the predicted value of the streamline deviation at this discrete point. This represents the total number of discrete points.

5. The method according to claim 4, characterized in that, The shape of the forebody intersection line is determined by the initial flow surface. The position of the inner cone shock wave changes due to axial translation.

6. The method according to claim 4, characterized in that, The process of adjusting the profile includes: On the inner intake duct profile after the profile constraint is applied, the streamlines located on the plane of symmetry are extended to both sides to form splitters, and the throat cross-section is designed to be rectangular.

7. The method according to claim 1, characterized in that, Given the flow constraint at a low Mach number, the iterative optimization of the integrated configuration of the forebody and the internal adjustable inlet includes: Viscous numerical simulation calculations were performed on the integrated configuration of the forebody and the internal adjustable intake under low Mach number conditions to obtain the actual airflow at the intake outlet. Based on actual working flow requirements, determine the required flow rate at low Mach numbers and give a flow rate constraint range; Determine whether the actual airflow at the intake outlet is within the flow constraint range. If not, readjust the position of the inner cone shock wave and recalculate the actual airflow at the intake outlet until the actual airflow at the intake outlet is within the flow constraint range.

8. A waverider forebody or internally adjustable inlet design device based on high and low Mach number dual design points, applied to the method as described in any one of claims 1-7, characterized in that, include: The calculation unit is used to obtain the forebody shock wave and wave-riding forebody based on the given incoming flow design conditions, and to calculate the forebody flow field parameters. The first generation unit is used to construct an inner cone flow field and generate an inner cone shock wave based on the forebody flow field parameters. The second generation unit is used to determine the intake duct capture profile based on the forebody shock wave, the wave-riding forebody, and the inner cone shock wave, and to generate the inner cone intake duct profile in the inner cone flow field. The first constraint unit is used to constrain and adjust the profile of the inner rotating inlet to generate an adjustable inner rotating inlet configuration, and together with the wave-riding forebody, it forms an integrated configuration of the forebody and the adjustable inner rotating inlet. The second constraint unit is used to iteratively optimize the integrated configuration of the precursor and the internal adjustable inlet under a given flow constraint at a low Mach number.

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