Supersonic two-dimensional inlet grid deformation method, device and equipment and storage medium

Abstract

The application relates to a supersonic two-dimensional inlet grid deformation method, device, equipment and storage medium. The method comprises the following steps: according to the influence range of supersonic two-dimensional inlet surface change on a flow field grid, the flow field grid is divided into three types of regions, i.e., a grid unchanged region, a grid translation region and a grid stretching region, and the displacement amount of the grid nodes in each type of region is calculated by using the shape parameters of the inlet configurations before and after deformation. The method does not need to separately calculate the displacement amount of the grid boundary, and does not need to establish the mapping relationship between the internal nodes and the boundary nodes of the grid, so that the deformation process of the supersonic two-dimensional inlet flow field grid is simplified, the method is simple and easy to understand, and the deformation efficiency of the supersonic two-dimensional inlet flow field grid is improved.

Description

Technical Field

[0001] This application relates to the field of engineering design technology, and in particular to a method, apparatus, device and storage medium for supersonic two-dimensional air intake mesh deformation. Background Technology

[0002] The supersonic inlet is a crucial component of a ramjet engine, playing a vital role in slowing down and pressurizing the incoming airflow, providing a stable flow rate and high-quality air to the combustion chamber, and its compression efficiency has a significant impact on the engine's performance. Thanks to the advantages of a simple two-dimensional inlet structure and wave system, most current ramjet engines utilize this type of inlet. Designing a high-compression-efficiency supersonic two-dimensional inlet is of great significance for improving ramjet engine performance.

[0003] Inlet duct optimization design is an effective method to obtain high-performance inlets. During the optimization design process, the use of mesh deformation technology can directly provide the flow field mesh corresponding to different design parameters, eliminating the need for model generation and mesh generation processes, simplifying the inlet duct optimization design process, and improving the efficiency and fault tolerance of inlet duct optimization design.

[0004] Current mesh deformation techniques include physical modeling, mathematical interpolation, and partial differential equation methods. When using existing methods for mesh deformation, the displacement of the flow field boundary mesh nodes is first calculated based on the change in shape. Then, a mapping relationship is established between the boundary mesh nodes and the internal mesh nodes. Finally, using this mapping relationship, the displacement of the internal mesh nodes is calculated from the displacement of the boundary mesh nodes and applied to the corresponding mesh nodes to obtain the flow field mesh after the shape change. This process is relatively complex and suitable for complex flow field meshes and deformations involving complex movements such as displacement, rotation, and oscillation at the boundary. The supersonic two-dimensional inlet mesh structure is simple, and changes in the inlet shape have little impact on the overall flow field mesh structure. Therefore, using current mesh deformation methods for supersonic two-dimensional inlet mesh deformation is quite complicated. Thus, existing techniques for supersonic two-dimensional inlet mesh deformation suffer from the disadvantages of complexity and low efficiency. Summary of the Invention

[0005] Therefore, it is necessary to provide a method, apparatus, device, and storage medium for supersonic two-dimensional inlet mesh deformation to address the aforementioned technical problems. This method can directly generate flow field meshes with other shape parameters based on a reference mesh, simplifying the process of supersonic two-dimensional inlet mesh deformation and improving the efficiency of two-dimensional inlet mesh deformation.

[0006] A method for deforming a supersonic two-dimensional air intake grid, the method comprising: Based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into a grid invariant region, a grid translation region, and a grid expansion region.

[0007] Based on the corresponding shape parameters of the reference mesh and the shape parameters after deformation, calculate the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region.

[0008] The nodes of the reference mesh are displaced according to the displacement amount to obtain the deformed mesh.

[0009] In one embodiment, based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into a grid-invariant region, a grid-translation region, and a grid-expansion region, including: The flow field is divided into multiple regions by the leading edge and lip of the air intake.

[0010] Based on the influence range of the intake duct profile change on the flow field grid and preset judgment conditions, the categories of all block regions are determined; among them, the outer edge of the intake duct leading edge is the grid-invariant region, the outer edge of the intake duct lip is the grid translation region, and the upstream and inner / outer compression regions of the intake duct are the grid expansion / contraction regions; the preset judgment conditions are: When changes in the intake duct profile have no effect on the flow field grid in this region, it is considered a grid-invariant region.

[0011] When the change in the air intake profile causes the flow field grid in that region to shift as a whole, it is called the grid shift zone.

[0012] When the boundary of this region changes with the shape of the air intake, and there is local stretching or compression at the boundary, it is called the grid stretching zone.

[0013] In one embodiment, based on the shape parameters corresponding to the reference mesh and the deformed shape parameters, the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region is calculated, including: Within the grid invariant region, the grid node coordinates remain unchanged, and the grid node displacement is 0.

[0014] Within the mesh translation zone, the mesh nodes translate along with the boundary, and all mesh nodes have the same displacement, which is equal to the boundary displacement.

[0015] Within the grid expansion zone, the boundary of the region deforms, and the displacement of the internal grid nodes is related to the boundary deformation. Based on the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the grid nodes within the region is calculated, and then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement. For the displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformation of the two boundaries before and after displacement. The weighting coefficient is determined by the distance between the grid node and the region boundary.

[0016] In one embodiment, the lateral displacement is:

[0017] in, This is the lateral displacement. and These are the x-coordinates of the left and right boundaries of the region before deformation, respectively. and These are the x-coordinates of the left and right boundaries of the deformed region, respectively. This represents the displacement caused by the change in the left boundary of the region. This represents the displacement caused by the change in the right boundary of the region. From grid nodes The distances to the left and right boundaries are determined. .

[0018] In one embodiment, the longitudinal displacement of a grid node is calculated based on its lateral coordinates before and after displacement, including: Determine the horizontal coordinate of the deformed grid node based on the lateral displacement before and after the node displacement.

[0019] According to grid nodes Using the x-coordinates before and after deformation, and the longitudinal boundary shapes of the region before and after deformation, calculate the projections of the mesh nodes onto the longitudinal boundary of the region before and after deformation; denote the projections of the mesh nodes onto the upper and lower boundaries of the region before deformation as follows: and The projections of the deformed mesh nodes onto the upper and lower boundaries of the region are denoted as follows: and .

[0020] Based on the projections of the mesh node onto the upper and lower boundaries before and after deformation, the longitudinal displacement of the mesh node is determined as follows:

[0021] in This represents the displacement at the upper boundary of the region. This represents the displacement at the lower boundary of the region. From grid nodes The distance from the upper and lower boundaries is determined. .

[0022] A supersonic two-dimensional air intake grid deformation device, the device comprising: The grid partitioning module is used to divide the supersonic two-dimensional inlet grid into a grid invariant region, a grid translation region, and a grid expansion region based on the influence range of the flow field grid on the inlet profile changes.

[0023] The mesh displacement calculation module is used to calculate the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region based on the corresponding shape parameters of the reference mesh and the shape parameters after deformation.

[0024] The mesh deformation module is used to perform displacement operations on the nodes of the reference mesh according to the displacement amount to obtain the deformed mesh.

[0025] In one embodiment, the grid partitioning module is further used to divide the flow field into multiple regions through the leading edge and lip of the inlet; and to determine the category of all regions based on the influence range of the inlet profile change on the flow field grid and preset judgment conditions; wherein, the outer side of the inlet leading edge is the grid invariant region, the outer side of the inlet lip is the grid translation region, and the upstream and inner / outer compression regions of the inlet are the grid expansion and contraction regions; the preset judgment conditions are: when the inlet profile change has no effect on the flow field grid of the region, it is the grid invariant region; when the inlet profile change causes the flow field grid of the region to be translated as a whole, it is the grid translation region; when the boundary of the region changes with the inlet profile change, and there is local stretching or compression at the boundary of the region, it is the grid expansion and contraction region.

[0026] In one embodiment, the grid displacement calculation module is further configured to: In the grid invariant region, where the grid node coordinates remain unchanged and the grid node displacement is 0; in the grid translation region, where the grid nodes translate with the boundary, all grid nodes have the same displacement, equal to the boundary displacement; and in the grid expansion region, where the region boundary deforms, the internal grid node displacement is related to the boundary deformation. Based on the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the grid nodes within the region is calculated, then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement. For a displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformations of the two boundaries before and after that direction. The weighting coefficient is determined by the distance between the grid node and the region boundary.

[0027] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program performing the following steps: Based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into the grid invariant region, the grid translation region, and the grid expansion region.

[0028] Based on the corresponding shape parameters of the reference mesh and the shape parameters after deformation, calculate the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region.

[0029] The nodes of the reference mesh are displaced according to the displacement amount to obtain the deformed mesh.

[0030] A computer-readable storage medium having a computer program stored thereon, the computer program performing the following steps when executed by a processor: Based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into the grid invariant region, the grid translation region, and the grid expansion region.

[0031] Based on the corresponding shape parameters of the reference mesh and the shape parameters after deformation, calculate the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region.

[0032] The nodes of the reference mesh are displaced according to the displacement amount to obtain the deformed mesh.

[0033] The aforementioned method, apparatus, equipment, and storage medium for deforming the supersonic two-dimensional inlet mesh include the following steps: Based on the influence range of the supersonic two-dimensional inlet profile changes on the flow field mesh, the flow field mesh is divided into three regions: a mesh-invariant region, a mesh-translation region, and a mesh-expansion region. The displacement of mesh nodes in each region is calculated using the shape parameters of the inlet configuration before and after deformation. This method eliminates the need to separately calculate the displacement of the mesh boundaries and establish a mapping relationship between internal mesh nodes and boundary nodes, simplifying the deformation process of the supersonic two-dimensional inlet flow field mesh. It is simple, easy to understand, and improves the deformation efficiency of the supersonic two-dimensional inlet flow field mesh. Attached Figure Description

[0034] Figure 1 This is a flowchart illustrating a supersonic two-dimensional air intake mesh deformation method in one embodiment; Figure 2 This is a schematic diagram of the reference mesh used in one embodiment; Figure 3 This is a schematic diagram of the grid region division of the supersonic two-dimensional inlet flow field in one embodiment; Figure 4 This is a schematic diagram of the displacement of the grid nodes in the expansion zone in another embodiment; Figure 5 This is a schematic diagram of the two-dimensional intake duct mesh before and after deformation in another embodiment; Figure 6 A structural block diagram of a supersonic two-dimensional air intake grid deformation device in one embodiment; Figure 7 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0036] In one embodiment, such as Figure 1 As shown, a method for deforming a supersonic two-dimensional air intake mesh is provided. This method should include the following steps: Step 100: Based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into the grid invariant region, the grid translation region, and the grid expansion region.

[0037] Specifically, the reference mesh used in this embodiment is as follows: Figure 2 As shown; the boundaries of the reference grid include the far-field boundary, the upper and lower wall boundaries of the inlet, and the inlet outlet boundary. A schematic diagram of the supersonic two-dimensional inlet flow field grid division is shown below. Figure 3 As shown, Figure 3 In the diagram, ① represents the region where the mesh remains unchanged, ② represents the region where the mesh is translated, and ③ represents the region where the mesh is stretched. Figure 3 The displacement of the grid nodes in the invariant zone of the middle grid is 0; the displacement of the left grid translation zone is only longitudinal, and the displacement is equal to the longitudinal displacement of the intake lip; the displacement of the right grid translation zone is the displacement of the intake lip.

[0038] Step 102: Based on the shape parameters corresponding to the reference mesh and the shape parameters after deformation, calculate the displacement of the mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region.

[0039] Step 104: Displace the nodes of the reference mesh according to the displacement to obtain the deformed mesh.

[0040] Specifically, based on the displacement, the mesh nodes of the reference mesh are displaced to obtain the deformed mesh. This method does not require separate calculation of the displacement of the mesh boundary nodes, nor does it require establishing a mapping relationship between boundary nodes and internal nodes. It is simple to understand and has high deformation efficiency.

[0041] The aforementioned method for deforming the supersonic two-dimensional inlet mesh includes: dividing the flow field mesh into three regions—a mesh-invariant region, a mesh-translation region, and a mesh-expansion region—based on the influence range of the supersonic two-dimensional inlet profile change on the flow field mesh; and calculating the displacement of mesh nodes in each region using the shape parameters of the inlet configuration before and after deformation. This method eliminates the need to separately calculate the displacement of the mesh boundary and establish a mapping relationship between internal mesh nodes and boundary nodes, simplifying the deformation process of the supersonic two-dimensional inlet flow field mesh. It is simple, easy to understand, and improves the deformation efficiency of the supersonic two-dimensional inlet flow field mesh.

[0042] In one embodiment, step 100 includes: dividing the flow field into multiple regions through the leading edge and lip of the inlet; judging the category of all regions based on the influence range of the inlet profile change on the flow field grid and preset judgment conditions; wherein, the outer side of the inlet leading edge is the grid-invariant region, the outer side of the inlet lip is the grid-translation region, and the upstream and inner / outer compression regions of the inlet are the grid-expansion region; the preset judgment conditions are: when the inlet profile change has no effect on the flow field grid of the region, it is the grid-invariant region; when the inlet profile change causes the flow field grid of the region to be translated as a whole, it is the grid-translation region; when the boundary of the region changes with the inlet profile change, and there is local stretching or compression at the boundary of the region, it is the grid-expansion region.

[0043] In one embodiment, step 102 includes: in the grid invariant region, the grid node coordinates remain unchanged, and the grid node displacement is 0; in the grid translation region, the grid nodes translate with the boundary, and all grid nodes have the same displacement, which is equal to the boundary displacement; in the grid expansion region, the region boundary deforms, and the internal grid node displacement is related to the boundary deformation; based on the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the grid nodes in the region is calculated, and then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement; for the displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformation of the two boundaries before and after displacement; the weighting coefficient is determined by the distance between the grid node and the region boundary.

[0044] Specifically, the calculation method for the grid displacement in different regions of the supersonic two-dimensional inlet flow field is as follows: (1) The grid invariant region is where the grid node coordinates do not change and the grid node displacement is 0. (2) Mesh translation zone: In this zone, the mesh nodes are translated along with the boundary, and the displacement of all mesh nodes is the same, which is equal to the displacement of the boundary. (3) Grid expansion and contraction zone: The boundary of this zone is deformed, and the displacement of the internal grid nodes is related to the boundary deformation. According to the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. This indicates that the lateral deformation of the grid nodes in the region is not affected by their ordinate. Therefore, the lateral and longitudinal deformations can be decoupled. First, the lateral displacement of the grid nodes in the region is calculated, and then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement. For the displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformations of the two boundaries before and after displacement. The weighting coefficient is determined by the distance between the grid node and the boundary of the region.

[0045] In one embodiment, the lateral displacement is:

[0046] in, This is the lateral displacement. and These are the x-coordinates of the left and right boundaries of the region before deformation, respectively. and These are the x-coordinates of the left and right boundaries of the deformed region, respectively. This represents the displacement caused by the change in the left boundary of the region. This represents the displacement caused by the change in the right boundary of the region. From grid nodes The distances to the left and right boundaries are determined. .

[0047] In one embodiment, calculating the longitudinal displacement of a grid node based on its lateral coordinates before and after displacement includes: determining the lateral coordinates of the deformed grid node based on the lateral displacement before and after displacement; and determining the lateral coordinates of the deformed grid node based on the lateral coordinates of the grid node. Using the x-coordinates before and after deformation, and the longitudinal boundary shapes of the region before and after deformation, calculate the projections of the mesh nodes onto the longitudinal boundary of the region before and after deformation; denote the projections of the mesh nodes onto the upper and lower boundaries of the region before deformation as follows: and The projections of the deformed mesh nodes onto the upper and lower boundaries of the region are denoted as follows: and Based on the projections of the mesh node onto the upper and lower boundaries before and after deformation, the longitudinal displacement of the mesh node is determined as follows:

[0048] in This represents the displacement at the upper boundary of the region. This represents the displacement at the lower boundary of the region. From grid nodes The distance from the upper and lower boundaries is determined. .

[0049] Specifically, the following section, with illustrations, explains in detail the calculation process of node displacement in the mesh scaling zone: (e.g.) Figure 4 As shown, the solid-lined box represents the region before deformation, and the dashed-lined box represents the region after deformation. The x-coordinates of the left and right boundaries of the region before deformation are respectively... and The x-coordinates of the left and right boundaries of the deformed region are respectively and For a specific grid node within the grid scaling region. The steps for calculating its displacement are as follows: (1) Based on the lip coordinates and length of the intake duct before and after deformation, give the abscissas of the left and right boundaries of the region before and after deformation. The coordinates before deformation are denoted as follows: and The deformed form is denoted as and .

[0050] (2) Calculate the lateral displacement The lateral displacement is the weighted sum of the displacements of the left and right boundaries before and after the deformation of the region, that is:

[0051] The first term represents the displacement of the left boundary of the region, the second term represents the displacement of the right boundary of the region, and the coefficients are... From grid nodes The distance to the left and right boundaries is determined, that is It is not difficult to see that the closer the grid nodes are to the right boundary, the better. The closer the value is to 0, the smaller the impact of the deformation on the nodes on the left boundary, while the greater the impact of the deformation on the nodes on the right boundary, and vice versa.

[0052] (3) Calculate the longitudinal boundary projection coordinates Get grid nodes After determining the lateral displacement, its deformed x-coordinate can be calculated as follows: According to grid nodes By analyzing the x-coordinates before and after deformation, and the longitudinal boundary shapes of the region before and after deformation, the projections of the mesh nodes onto the longitudinal boundary of the region before and after deformation can be calculated. Figure 4 As shown, where and These represent the projections of the mesh nodes before deformation onto the upper and lower boundaries of the region. and These are the projections of the deformed mesh nodes onto the upper and lower boundaries of the region, respectively.

[0053] (4) Calculate the longitudinal displacement By weighted summing of the deformations at the upper and lower boundaries, we can calculate... The longitudinal displacement is:

[0054] The first term represents the displacement at the upper boundary of the region, the second term represents the displacement at the lower boundary of the region, and the coefficients are... From grid nodes The distance from the upper and lower boundaries is determined, that is It is easy to see that the closer the grid nodes are to the lower boundary, the better. The closer the value is to 0, the smaller the impact of the upper boundary deformation on the nodes, while the larger the impact of the lower boundary deformation on the nodes, and vice versa. Obtain mesh nodes. After determining the longitudinal displacement, its deformed ordinate can be calculated as follows: .

[0055] Schematic diagram of the two-dimensional intake grid before and after deformation as shown below Figure 5 As shown, Figure 5 The original mesh is drawn with solid lines, while the deformed mesh is drawn with dashed lines. From Figure 5 As can be seen, the topology, shape of the mesh cells, and density of the mesh after deformation are consistent with those before deformation. The deformed mesh also has the same densification effect as the original mesh near the wall, indicating that the mesh deformation method proposed in this application can maintain the characteristics of the original mesh well while achieving mesh deformation.

[0056] It should be understood that, although Figure 1 The steps in the flowchart are shown sequentially as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order in which these steps are executed, and they can be performed in other orders. Figure 1 At least some of the steps in the process may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least some of the sub-steps or stages of other steps.

[0057] In one embodiment, such as Figure 6 As shown, a supersonic two-dimensional air intake mesh deformation device is provided, comprising: a mesh partitioning module, a mesh displacement calculation module, and a mesh deformation module, wherein: The grid partitioning module is used to divide the supersonic two-dimensional inlet grid into a grid invariant region, a grid translation region, and a grid expansion region based on the influence range of the inlet profile changes on the flow field grid. The mesh displacement calculation module is used to calculate the displacement of mesh nodes in the mesh invariant region, mesh translation region, and mesh expansion region based on the corresponding shape parameters of the reference mesh and the shape parameters after deformation. The mesh deformation module is used to displace the nodes of the reference mesh according to the displacement amount to obtain the deformed mesh.

[0058] In one embodiment, the grid partitioning module is further used to divide the flow field into multiple regions through the leading edge and lip of the inlet; and to determine the category of all regions based on the influence range of the inlet profile change on the flow field grid and preset judgment conditions; wherein, the outer side of the inlet leading edge is the grid invariant region, the outer side of the inlet lip is the grid translation region, and the upstream and inner and outer compression regions of the inlet are the grid expansion and contraction regions; the preset judgment conditions are: when the inlet profile change has no effect on the flow field grid of the region, it is the grid invariant region; when the inlet profile change causes the flow field grid of the region to be translated as a whole, it is the grid translation region; when the boundary of the region changes with the inlet profile change, and there is local stretching or compression at the boundary of the region, it is the grid expansion and contraction region.

[0059] In one embodiment, the grid displacement calculation module is further configured to: In the grid invariant region, where the grid node coordinates remain unchanged and the grid node displacement is 0; in the grid translation region, where the grid nodes translate with the boundary, all grid nodes have the same displacement, equal to the boundary displacement; and in the grid expansion region, where the region boundary deforms, the internal grid node displacement is related to the boundary deformation. Based on the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the grid nodes within the region is calculated, then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement. For a displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformations of the two boundaries before and after that direction. The weighting coefficient is determined by the distance between the grid node and the region boundary.

[0060] In one embodiment, the lateral displacement in the mesh displacement calculation module is:

[0061] in, This is the lateral displacement. and These are the x-coordinates of the left and right boundaries of the region before deformation, respectively. and These are the x-coordinates of the left and right boundaries of the deformed region, respectively. This represents the displacement caused by the change in the left boundary of the region. This represents the displacement caused by the change in the right boundary of the region. From grid nodes The distances to the left and right boundaries are determined. .

[0062] In one embodiment, the mesh displacement calculation module is further configured to determine the abscissa of the deformed mesh node based on the lateral displacement of the mesh node before and after displacement; based on the mesh node Using the x-coordinates before and after deformation, and the longitudinal boundary shapes of the region before and after deformation, calculate the projections of the mesh nodes onto the longitudinal boundary of the region before and after deformation; denote the projections of the mesh nodes onto the upper and lower boundaries of the region before deformation as follows: and The projections of the deformed mesh nodes onto the upper and lower boundaries of the region are denoted as follows: and Based on the projections of the mesh node onto the upper and lower boundaries before and after deformation, the longitudinal displacement of the mesh node is determined as follows:

[0063] in This represents the displacement at the upper boundary of the region. This represents the displacement at the lower boundary of the region. From grid nodes The distance from the upper and lower boundaries is determined. .

[0064] Specific limitations regarding the supersonic two-dimensional inlet mesh deformation device can be found in the limitations of the supersonic two-dimensional inlet mesh deformation method described above, and will not be repeated here. Each module in the aforementioned supersonic two-dimensional inlet mesh deformation device can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device in hardware form, or stored in the memory of a computer device in software form, so that the processor can call and execute the corresponding operations of each module.

[0065] In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 7 As shown, the computer device includes a processor, memory, network interface, display screen, and input devices connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The network interface is used to communicate with external terminals via a network connection. When executed by the processor, the computer program implements a supersonic two-dimensional air intake mesh deformation method. The display screen can be a liquid crystal display (LCD) or an e-ink display. The input devices can be a touch layer covering the display screen, buttons, a trackball, or a touchpad mounted on the computer device casing, or an external keyboard, touchpad, or mouse.

[0066] Those skilled in the art will understand that Figure 6The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0067] In one embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program, the processor executing the computer program to implement the steps in the above method embodiment.

[0068] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the steps in the above method embodiments.

[0069] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0070] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0071] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A method for deforming a supersonic two-dimensional air intake grid, characterized in that, The method includes: Based on the influence range of the inlet profile change on the flow field grid, the supersonic two-dimensional inlet grid is divided into a grid-invariant region, a grid-translation region, and a grid-expansion region. Specifically, the flow field is divided into multiple regions by the inlet leading edge and lip. The category of each region is determined based on the influence range of the inlet profile change on the flow field grid and preset judgment conditions. The outer side of the inlet leading edge is the grid-invariant region, the outer side of the inlet lip is the grid-translation region, and the upstream and inner / outer compression regions of the inlet are the grid-expansion regions. The preset judgment conditions are: when the inlet profile change has no effect on the flow field grid of this region, it is the grid-invariant region; when the inlet profile change causes the flow field grid of this region to translate as a whole, it is the grid-translation region; when the boundary of this region changes with the inlet profile change, and there is local stretching or compression at the boundary, it is the grid-expansion region. Based on the corresponding shape parameters of the baseline mesh and the deformed shape parameters, the displacement of mesh nodes in the mesh-invariant region, mesh-translation region, and mesh-expansion region is calculated. Specifically, in the mesh-invariant region, the coordinates of the mesh nodes do not change, and the displacement of the mesh nodes is 0. In the mesh-translation region, the mesh nodes translate with the boundary, and all mesh nodes have the same displacement, which is equal to the boundary displacement. In the mesh-expansion region, the region boundary deforms, and the displacement of the internal mesh nodes is related to the boundary deformation. According to the characteristics of the two-dimensional flow field mesh, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the mesh nodes in the region is calculated, and then the longitudinal displacement is calculated based on the lateral coordinates of the mesh nodes before and after displacement. For the displacement in a certain direction, the displacement of the internal mesh nodes in that direction is calculated by weighted summation of the deformation of the two boundaries before and after that direction. The weighting coefficient is determined by the distance between the mesh node and the region boundary. The nodes of the reference mesh are displaced according to the displacement amount to obtain the deformed mesh.

2. The method according to claim 1, characterized in that, The lateral displacement is: in, This is the lateral displacement. and These are the x-coordinates of the left and right boundaries of the region before deformation, respectively. and These are the x-coordinates of the left and right boundaries of the deformed region, respectively. This represents the displacement caused by the change in the left boundary of the region. This represents the displacement caused by the change in the right boundary of the region. From grid nodes The distances to the left and right boundaries are determined. .

3. The method according to claim 2, characterized in that, Calculate the longitudinal displacement based on the lateral coordinates of the mesh node before and after displacement, including: Determine the abscissa of the grid node after deformation based on the lateral displacement before and after the grid node displacement. According to grid nodes Using the x-coordinates before and after deformation, and the longitudinal boundary shapes of the region before and after deformation, calculate the projections of the mesh nodes onto the longitudinal boundary of the region before and after deformation; denote the projections of the mesh nodes onto the upper and lower boundaries of the region before deformation as follows: and The projections of the deformed mesh nodes onto the upper and lower boundaries of the region are denoted as follows: and ; Based on the projections of the mesh node onto the upper and lower boundaries before and after deformation, the longitudinal displacement of the mesh node is determined as follows: in, This represents the longitudinal displacement of the grid node. This represents the displacement at the upper boundary of the region. This represents the displacement at the lower boundary of the region. From grid nodes The distance from the upper and lower boundaries is determined. .

4. A supersonic two-dimensional air intake grid deformation device, characterized in that, The device includes: The grid partitioning module is used to divide the supersonic two-dimensional inlet grid into three regions: a grid-invariant region, a grid-translation region, and a grid-expansion region, based on the influence range of the inlet profile changes on the flow field grid. Specifically, it includes: dividing the flow field into multiple regions through the inlet leading edge and lip; and determining the category of each region based on the influence range of the inlet profile changes on the flow field grid and preset judgment conditions. The outer side of the inlet leading edge is the grid-invariant region, the outer side of the inlet lip is the grid-translation region, and the upstream and inner / outer compression regions of the inlet are the grid-expansion regions. The preset judgment conditions are: when the inlet profile changes have no effect on the flow field grid in this region, it is a grid-invariant region; when the inlet profile changes cause the flow field grid in this region to translate as a whole, it is a grid-translation region; and when the boundary of this region changes with the inlet profile changes, and there is local stretching or compression at the boundary, it is a grid-expansion region. The grid displacement calculation module is used to calculate the displacement of grid nodes in the grid invariant zone, grid translation zone, and grid expansion zone based on the corresponding shape parameters of the reference grid and the deformed shape parameters. Specifically, it includes: in the grid invariant zone, the grid node coordinates do not change, and the grid node displacement is 0; in the grid translation zone, the grid nodes translate with the boundary, and all grid nodes have the same displacement, which is equal to the boundary displacement; in the grid expansion zone, the region boundary deforms, and the internal grid node displacement is related to the boundary deformation. Based on the characteristics of the two-dimensional flow field grid, the divided region is quadrilateral or approximately quadrilateral, and the two lateral boundaries are straight lines before and after deformation. First, the lateral displacement of the grid nodes in the region is calculated, and then the longitudinal displacement is calculated based on the lateral coordinates of the grid nodes before and after displacement. For the displacement in a certain direction, the displacement of the internal grid nodes in that direction is calculated by weighted summation of the deformation of the two boundaries before and after that direction; the weighting coefficient is determined by the distance between the grid node and the region boundary. The mesh deformation module is used to perform displacement operations on the nodes of the reference mesh according to the displacement amount to obtain the deformed mesh.

5. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the method of any one of claims 1 to 3.

6. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method of any one of claims 1 to 3.

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