Aircraft internal and external flow integrated surface optimization method, device, equipment and medium

Abstract

The present application relates to an integrated surface optimization method, device, equipment and medium for internal and external flow of an aircraft. First, the three-dimensional computational domain of the constructed internal and external flow domain of the aircraft is discretized into a plurality of volume grids; then, a surface cell array containing one-dimensional index information of the plurality of volume grids is constructed according to the order of the numerical format; the plurality of volume grids are partitioned and distributed to GPUs for parallel processing; each GPU iteratively calculates the volume grids through the discretized computational fluid dynamics equations, and based on the one-dimensional index information of the volume grids contained in the surface cell array of the interface, the marked volume grid physical quantities are packaged and transmitted to calculate the mechanical properties; all mechanical properties are counted and optimized to obtain the optimal surface design scheme. The present invention adopts a three-dimensional partitioning method with one-dimensional indexing, so that the GPU program can carry out multi-GPU simulation, thereby realizing the calculation of larger-scale grid quantities and improving computational efficiency and accuracy.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft performance optimization, and in particular to a method, device, equipment and medium for optimizing the integrated internal and external flow profile of an aircraft. Background Art

[0002] Hypersonic vehicles hold significant value for the future of ultra-fast transportation and are attracting increasing attention in the civilian sector. The design of hypersonic vehicles can be divided into three phases: theoretical calculation, numerical simulation, and experimentation. Once the structural parameters of a hypersonic vehicle are designed through theoretical calculation, numerical simulation is first performed to verify whether its performance indicators meet the requirements. Then, improved structural parameters that meet the requirements are refined for experimental testing. High-precision numerical simulation can significantly reduce the number of experiments, thereby reducing design time and costs.

[0003] Numerical simulation plays an essential role in hypersonic vehicle design. Through numerical simulation, engineers can simulate the behavior of an aircraft under hypersonic conditions in a virtual environment, studying key factors such as aerodynamic characteristics, thermodynamic effects, and structural stresses. This enables the design team to gain a more comprehensive understanding of the vehicle's performance before actual manufacturing. Numerical simulation also allows for multiple modifications and optimizations in a virtual environment, significantly reducing the number of experiments. This not only improves design accuracy but also significantly reduces design cycle time and costs.

[0004] Currently, optimizing the design of hypersonic vehicles using computational fluid dynamics (CFD) has become a key technology for shortening development cycles. Typically, CPU-based CFD programs partition three-dimensional grids using a three-dimensional index. However, increasing demands for computational accuracy necessitate accelerated computations based on graphics processing units (GPUs), particularly multi-GPU clusters for ultra-large-scale computations. Traditional three-dimensional indexing can make it difficult to directly locate nearby volumetric grids, thus failing to fully utilize the powerful parallel computing capabilities of GPUs. Summary of the Invention

[0005] Based on this, it is necessary to provide a three-dimensional grid partitioning method using one-dimensional storage to address the above technical problems, which can directly find nearby grids through simple index operations, give full play to the powerful parallel computing performance of GPU, and improve the computing efficiency and accuracy of the integrated internal and external flow surface optimization method, device, equipment and medium of the aircraft.

[0006] A method for optimizing an integrated internal and external flow profile of an aircraft, comprising:

[0007] Constructing a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretizing the three-dimensional computational domain into a plurality of volume grids;

[0008] Determining the order of the numerical format, and constructing a surface unit array between volume grids according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume grids;

[0009] Partitioning the plurality of volume grids, and assigning the partitioned volume grids to a GPU for parallel processing; wherein, when partitioning, determining a dividing interface, obtaining an arrangement of physically adjacent volume grids through the dividing interface, and marking related volume grids according to the arrangement;

[0010] Each GPU iteratively calculates the volume mesh using the discretized computational fluid dynamics equations. Based on the volume mesh one-dimensional index information contained in the surface cell array of the interface, the physical quantities of the marked volume mesh are packaged and transferred to calculate the mechanical properties of the flow configuration within the engine and the aerodynamic shape of the aircraft in each volume mesh.

[0011] The mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all body grids are statistically analyzed and optimized to obtain the optimal design scheme for the integrated internal and external flow surface of the aircraft.

[0012] In one embodiment, a three-dimensional computational domain of the flow area inside and outside the aircraft is constructed, and the three-dimensional computational domain is discretized into a plurality of volume grids, including:

[0013] Determine the flow configuration within the aircraft engine based on the aircraft design requirements; and

[0014] Design the aerodynamic shape of the aircraft;

[0015] Determine a three-dimensional computational domain of the flow domain inside and outside the aircraft according to the flow configuration inside the engine and the aerodynamic shape of the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids;

[0016] The aerodynamic shape of the aircraft is used as the initial condition, and initial physical quantities are set in each body grid.

[0017] In one embodiment, designing the aerodynamic shape of an aircraft includes:

[0018] The flight conditions of the aircraft are determined, and the aerodynamic shape of the aircraft is designed according to the flight conditions.

[0019] In one embodiment, when partitioning, determining a partition interface, obtaining a physically adjacent volume mesh arrangement through the partition interface, and marking related volume meshes according to the arrangement include:

[0020] Partitioning each body mesh into a first partition and a second partition, and using adjacent surfaces of the first partition and the second partition as interfaces;

[0021] Near the interface, possible arrangement modes of the first partition and the second partition when values ​​are transferred are recorded, and related volume grids are marked according to the arrangement modes.

[0022] In one embodiment, each body mesh is partitioned into a first partition and a second partition, and adjacent surfaces of the first partition and the second partition are used as interfaces, including:

[0023] Divide each volume mesh into a first partition and a second partition, and use adjacent surfaces of the first partition and the second partition as interfaces;

[0024] According to the order of the numerical format, the interface is associated with the corresponding volume mesh quantities of the first partition and the second partition to obtain a surface cell array of the interface.

[0025] In one embodiment, the volume grids associated with the interface are arranged along the positive direction of the coordinate axis.

[0026] An aircraft internal and external flow integrated surface optimization device, the device comprising:

[0027] A grid discretization module is used to construct a three-dimensional computational domain of the flow field inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids;

[0028] a one-dimensional index construction module, configured to determine an order of a numerical format, and construct a surface unit array between volume grids according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume grids;

[0029] a partition processing module, configured to partition the plurality of volume meshes and assign the partitioned volume meshes to a GPU for parallel processing; wherein, when partitioning, a partitioning interface is determined, an arrangement of physically adjacent volume meshes is obtained through the partitioning interface, and related volume meshes are marked according to the arrangement;

[0030] The iterative calculation module is used by each GPU to iteratively calculate the volume mesh through the discretized computational fluid dynamics equations. Based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, the marked volume mesh physical quantities are packaged and transferred, and the mechanical properties of the flow configuration within the engine and the aerodynamic shape of the aircraft in each volume mesh are calculated;

[0031] The performance optimization module is used to statistically analyze and optimize the mechanical properties of the engine's internal flow configuration and the aircraft's aerodynamic shape in all volume grids to obtain the optimal design scheme for the integrated internal and external flow surface of the aircraft.

[0032] A computer device comprises a memory and a processor, wherein the memory stores a computer program, and the processor implements the steps of any one of the above methods when executing the computer program.

[0033] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of any one of the methods described above.

[0034] The above-mentioned method, device, equipment and medium for optimizing the integrated surface of internal and external flows of an aircraft construct a three-dimensional calculation domain of the internal and external flow domains of the aircraft, discretize the three-dimensional calculation domain into a number of volume grids; determine the order of the numerical format, construct a surface unit array between the volume grids according to the order of the numerical format, and the surface unit array includes a number of one-dimensional index information of the volume grids; partition the several volume grids, and distribute the partitioned volume grids to the GPU for parallel processing; wherein, when partitioning, the interface is determined, the arrangement of physically adjacent volume grids is obtained through the interface, and the relevant volume grids are marked according to the arrangement; each GPU iteratively calculates the volume grid through the discretized computational fluid dynamics equation, and based on the one-dimensional index information of the volume grid contained in the surface unit array of the interface, the marked volume grid physical quantities are packaged and transmitted, and the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in each volume grid are calculated; the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids are statistically calculated and optimized to obtain the optimal design scheme for the integrated surface of internal and external flows of the aircraft.

[0035] The present invention constructs a surface cell array, allowing the construction of numerical fluxes and gradients directly on the surface cells, making computations simpler and improving efficiency. Based on the order of the numerical format, a surface cell array containing one-dimensional index information for several volume meshes is constructed. The physically adjacent volume meshes are then arranged using interfaces, and labeled and associated, allowing the calculation of corresponding values ​​to be completed even after being partitioned by the interface. By adopting a three-dimensional partitioning method with one-dimensional indexing, GPU programs can perform multi-GPU simulations, enabling the calculation of larger-scale meshes and improving computational efficiency and accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 A schematic diagram of a process for optimizing an integrated internal and external flow profile of an aircraft in one embodiment;

[0037] Figure 2 Schematic diagram of association between a one-dimensional index and a face in one embodiment;

[0038] Figure 3 A schematic diagram of a structural grid partitioning of a complex shape in one embodiment;

[0039] Figure 4Schematic diagram of four-point partition value transmission in one embodiment; Figure 4 (a) is a schematic diagram of the first four-point partition value transmission method; Figure 4 (b) is a schematic diagram of the second four-point partition value transmission method; Figure 4 (c) is a schematic diagram of the third four-point partition value transmission method;

[0040] Figure 5 This is a structural block diagram of an integrated internal and external flow profile optimization device for an aircraft in one embodiment;

[0041] Figure 6 FIG. 1 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0043] It should be noted that the terms "first," "second," and so on, used in this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features being referred to. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this disclosure, "plurality" means at least two, such as two or three, unless otherwise specifically defined.

[0044] In the process of implementing the technology of this solution, the inventors found that the traditional data indexing method is three-dimensional indexing, and its grid partitioning method is all for three-dimensional grids with three-dimensional indexing. Through the three-dimensional indexing, each volume grid can find one or more adjacent volume grids to calculate flux and gradient. This partitioning method is very suitable for CPU-based computational fluid dynamics programs. However, due to the increasingly high requirements for computational accuracy and the increasing scale of calculations, GPU-based computational acceleration is needed. In particular, clusters of multiple GPUs are needed to perform ultra-large-scale calculations to obtain the lift and drag coefficients of aircraft or cars, thereby optimizing the vehicle shape and significantly accelerating the development of aircraft or cars. For GPU computational fluid dynamics programs, if traditional three-dimensional indexing is used, even physically adjacent volume cells may have large differences in their index numbers, which may make it difficult to directly find nearby volume grids through simple indexing operations. In order to give full play to the parallel computing performance of GPUs, the inventors provide a partitioning and value transfer method for three-dimensional grids with one-dimensional indexing, which can provide fast and efficient parallel partitioning for surface-related grid organization calculation programs, and can realize large-scale simulation calculations on GPU clusters, improving computing efficiency.

[0045] It is worth noting that the present invention is not only applicable to the aerospace field, but also to the automotive, shipbuilding, water conservancy, meteorology and other technical fields. When performing calculations, it is sufficient to appropriately change the corresponding configurations and parameters.

[0046] The following describes the embodiments of the present invention in detail with reference to the accompanying drawings.

[0047] In one embodiment, Figure 1 As shown, a method for optimizing the integrated internal and external flow profile of an aircraft is provided, comprising the following steps:

[0048] Step 202: construct a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids.

[0049] It's understandable that before optimizing an aircraft's surface, the spatial region for numerical simulation must first be determined. This is primarily determined by analyzing the flow configuration within the engine and the aerodynamic shape of the aircraft to determine the three-dimensional computational domain within and outside the aircraft, used to simulate the fluid behavior around the aircraft. This three-dimensional computational domain is then divided into numerous small cubes or other geometrically shaped units in three-dimensional space through discretization. These volume meshes cover the entire computational domain, allowing the problem to be decomposed into discrete equations for each grid cell during solution.

[0050] In summary, the fluid dynamics equations can be converted into discrete form by discretizing the computational domain into a volume mesh, and then computer algorithms are used to solve these equations in each small area.

[0051] Step 204 : determining the order of the numerical format, and constructing a surface unit array between volume meshes according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume meshes.

[0052] As you can understand, in GPU-based computational fluidics programs, to fully utilize the GPU's parallel computing capabilities, all volume meshes are stored in a one-dimensional array, using one-dimensional indexing. To address this issue, the surface cells between adjacent meshes are used to record the index number of the corresponding volume mesh, and the required volume cells are directly recorded on the surface cells. This makes it easy to construct numerical fluxes and gradients on the surface cells.

[0053] For numerical formats of different calculation orders, the surface unit needs to record different numbers of grids. For example, the second-order format requires two grids, the fourth-order format requires four grids, the sixth-order format requires six grids, and so on. For example, for the fourth-order format, Figure 2As shown, the surface element F1 records the four volume meshes near it. To construct the flux of the fourth-order format, you can construct the surface element array F1(i,i+N1,i+N2,i+N3). This surface element array includes the one-dimensional index information of the four volume meshes corresponding to the fourth-order format, so that you can perform simulation calculations of the fourth-order format. For example, to construct the flux of the second-order format, the surface element F1 is between (i+N1) and (i+N2). You can construct the array F1(i+N1,i+N2) before partitioning, so as to perform simulation calculations of the second-order format.

[0054] It is worth noting that in order to facilitate understanding of the grid partitioning method of the three-dimensional grid with one-dimensional index proposed in the present invention, the partitioning process of the fourth-order format is explained in detail below. The ideas of the partitioning methods of other orders are consistent with the fourth order.

[0055] Step 206 , partitioning the plurality of volume meshes and assigning the partitioned volume meshes to the GPU for parallel processing; wherein, when partitioning, determining the interface, obtaining the arrangement of physically adjacent volume meshes through the interface, and marking the relevant volume meshes according to the arrangement.

[0056] It can be understood that in step 204, by adding a surface cell array to the volume grid of the one-dimensional index, the computational fluid dynamics equation can be solved. However, traditional grid partitioning is targeted at three-dimensional indexing, and there is no corresponding grid partitioning method for one-dimensional indexing. This embodiment proposes to associate adjacent volume grids through interfaces, and to mark the related volume grids by arranging and combining the volume grids associated with the interfaces. This allows physically adjacent volume grids to directly find nearby volume grids through simple indexing operations when performing one-dimensional indexing, completing value transfer.

[0057] In step 208, each GPU iteratively calculates the volume mesh through the discretized computational fluid dynamics equations, and based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, packages and transmits the physical quantities of the marked volume mesh, and calculates the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume mesh.

[0058] As can be understood, step 204 has already constructed the surface cell array of the interface, and step 206 has marked all volume meshes in the vicinity of the interface that belong to this arrangement. Therefore, using the one-dimensional index information of the volume meshes contained in the surface cell array, the physical quantities of the marked volume meshes can be accurately transferred, thereby calculating the mechanical properties of the engine flow configuration and the aircraft aerodynamic shape in each volume mesh.

[0059] Step 210 , statistically analyzing the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids and optimizing them, to obtain the optimal design scheme of the integrated internal and external flow profile of the aircraft.

[0060] It can be understood that by continuously modifying the geometric configuration of the flow configuration inside the engine and the aerodynamic shape of the aircraft, the process from step 204 to step 208 is repeated, so that the mechanical properties of the flow configuration inside the engine and the aerodynamic shape of the aircraft in each body grid meet the design requirements, so as to find the optimal design solution.

[0061] The above-mentioned method for optimizing the integrated surface of internal and external flows of an aircraft constructs a three-dimensional calculation domain of the internal and external flow domains of the aircraft and discretizes the three-dimensional calculation domain into a number of volume grids; determines the order of the numerical format, and constructs a surface unit array between the volume grids according to the order of the numerical format, wherein the surface unit array includes a number of one-dimensional index information of the volume grids; partitions the number of volume grids and distributes the partitioned volume grids to the GPU for parallel processing; wherein, when partitioning, the interface is determined, the arrangement of physically adjacent volume grids is obtained through the interface, and the relevant volume grids are marked according to the arrangement; each GPU iteratively calculates the volume grid through the discretized computational fluid dynamics equation, and based on the one-dimensional index information of the volume grid contained in the surface unit array of the interface, the marked volume grid physical quantities are packaged and transmitted, and the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in each volume grid are calculated; the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids are statistically calculated and optimized to obtain the optimal design scheme of the integrated surface of internal and external flows of the aircraft.

[0062] The present invention constructs a surface cell array, allowing the construction of numerical fluxes and gradients directly on the surface cells, making computations simpler and improving efficiency. Based on the order of the numerical format, a surface cell array containing one-dimensional index information for several volume meshes is constructed. The physically adjacent volume meshes are then arranged using interfaces, and labeled and associated, allowing the calculation of corresponding values ​​to be completed even after being partitioned by the interface. By adopting a three-dimensional partitioning method with one-dimensional indexing, GPU programs can perform multi-GPU simulations, enabling the calculation of larger-scale meshes and improving computational efficiency and accuracy.

[0063] In one embodiment, a three-dimensional computational domain of the flow area inside and outside the aircraft is constructed and discretized into a plurality of volume grids, including:

[0064] According to the design requirements of the aircraft, determine the flow configuration inside the aircraft's engine; and design the aircraft's aerodynamic shape.

[0065] The three-dimensional computational domain of the internal and external flow areas of the aircraft is determined according to the flow configuration inside the engine and the aerodynamic shape of the aircraft, and the three-dimensional computational domain is discretized into several volume grids.

[0066] The aerodynamic shape of the aircraft is used as the initial condition, and the initial physical quantities are set in each body grid.

[0067] In one embodiment, further, designing the aerodynamic shape of the aircraft includes: determining flight conditions of the aircraft, and designing the aerodynamic shape of the aircraft according to the flight conditions.

[0068] The flight conditions of an aircraft are generally confirmed based on the purpose of use of the hypersonic aircraft and the actual technical requirements. Different purposes require different flight altitudes, speeds, and maneuvering conditions, and different degrees of compromise must be made based on the current technological status.

[0069] In one embodiment, when partitioning, determining a partition interface, obtaining a physically adjacent volume mesh arrangement through the partition interface, and marking related volume meshes according to the arrangement include:

[0070] The meshes of each body are partitioned into a first partition and a second partition, and the adjacent surfaces of the first partition and the second partition are used as interfaces.

[0071] Near the interface, record the possible arrangements of the first partition and the second partition when transferring values ​​respectively, and mark the relevant body grids according to the arrangements.

[0072] In one embodiment, each body mesh is further partitioned to obtain a first partition and a second partition, and adjacent surfaces of the first partition and the second partition are used as interfaces, including:

[0073] Each body mesh is equally divided into a first partition and a second partition, and the adjacent surfaces of the first partition and the second partition are used as interfaces;

[0074] According to the order of the numerical format, the interface is associated with the corresponding number of volume meshes of the first partition and the second partition, and the surface element array of the interface is obtained.

[0075] Specifically, if Figure 3 Figure 1 shows a schematic diagram of the mesh partitioning of a complex structure. For ease of illustration, the lines between two-dimensional meshes are used to represent the faces between two volume meshes in 3D. The figure shows the mesh divided into two equal regions along the x-direction, with face1, face2, and face3 representing typical face elements between volume meshes near the interface.

[0076] like Figure 4 (a) shows the partition diagram of face1, where the interface is the surface unit. In the figure, for the first partition A and B on the left, the values ​​of the two volume meshes C' and D' associated with them need to be transferred from the corresponding two volume meshes C and D in the right partition. Therefore, the two volume meshes C' and D' need to be marked. Similarly, the corresponding surface elements The values ​​of the two volume grids A′ and B′ associated with the two volume grids C and D on the right need to be transferred from the corresponding two volume grids A and B in the left partition, and the two volume grids A′ and B′ need to be marked. Figure 4 (b) and Figure 4 (c) Two other typical surface element partitioning methods are given.

[0077] In order to ensure that the volume meshes on both sides of the interface can be well associated after constructing the one-dimensional index, all possible arrangements of the two volume meshes A and B in the first partition, the two volume meshes C and D in the second partition, and A′, B′, C′, and D′ that need to be transferred are enumerated, as shown in Table 1.

[0078] Table 1 Possible arrangements of four-point associations on the interface

[0079] Serial number Arrangement 1 <![CDATA[A 1 B 1 C 2 D 2 ]]> 2 <![CDATA[A 2 B 2 C 1 D 1 ]]> 3 <![CDATA[A 1 B 1 C 1 D 2 ]]> 4 <![CDATA[A 2 B 2 C 2 D 1 ]]> 5 <![CDATA[A 1 B 2 C 2 D 2 ]]> 6 <![CDATA[A 2 B 1 C 1 D 1 ]]> 7 <![CDATA[A 1 B 2 C 1 D 1 <!-- 6 -->]]> 8 <![CDATA[A 2 B 1 C 2 D 2 ]]> 9 <![CDATA[A 1 B 1 C 2 D 1 ]]> 10 <![CDATA[A 2 B 2 C 1 D 2 ]]> 11 <![CDATA[A 1 B 2 C 1 D 2 ]]> 12 <![CDATA[A 2 B 1 C 2 D 1 ]]>

[0080] As can be seen from the table, there are a total of 12 arrangements for the fourth-order format when performing interface association, where the superscripts 1 and 2 represent the first partition and the second partition.

[0081] After obtaining all possible arrangements of the 3D structure mesh, the mesh numbers belonging to the 12 cases mentioned above need to be marked during partitioning. Then, when transferring values, the physical quantities of the mesh to be transferred are packaged together with the physical quantities belonging to the marked meshes, and the values ​​are transferred via MPI.

[0082] In one embodiment, the volume meshes associated with the interface are arranged along the positive direction of the coordinate axis.

[0083] It is understandable that Figure 2 As shown, for the fourth-order format provided in this embodiment, each face mesh must be associated with two volume meshes on the left and right sides of the face, and because the face has a unique normal vector pointing in the positive direction of the coordinate axis, the four volume meshes associated with the interface are always arranged along the positive direction of the coordinate axis.

[0084] It should be understood that although Figure 1 The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. In addition, Figure 1At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed 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 part of the sub-steps or stages of other steps.

[0085] In one embodiment, Figure 5 As shown, an aircraft internal and external flow integrated surface optimization device is provided, comprising: a grid discretization module 402, a one-dimensional index construction module 404, a partition processing module 406, an iterative calculation module 408 and a performance optimization module 410, wherein:

[0086] The grid discretization module 402 is used to construct a three-dimensional computational domain of the flow area inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids.

[0087] The one-dimensional index construction module 404 is used to determine the order of the numerical format and construct a surface unit array between volume meshes according to the order of the numerical format. The surface unit array includes one-dimensional index information of a plurality of volume meshes.

[0088] The partition processing module 406 is used to partition a plurality of volume meshes and distribute the partitioned volume meshes to the GPU for parallel processing. When partitioning, the partition interface is determined, the arrangement of physically adjacent volume meshes is obtained through the partition interface, and the relevant volume meshes are marked according to the arrangement.

[0089] The iterative calculation module 408 is used for each GPU to iteratively calculate the volume mesh through the discretized computational fluid dynamics equations, and based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, it packages and transmits the marked volume mesh physical quantities to calculate the mechanical properties of the flow configuration within the engine and the aerodynamic shape of the aircraft in each volume mesh.

[0090] The performance optimization module 410 is used to calculate and optimize the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids to obtain the optimal design scheme of the integrated internal and external flow surface of the aircraft.

[0091] The specific definitions of the aircraft internal and external flow integrated surface optimization device can be found in the definitions of the aircraft internal and external flow integrated surface optimization method described above and will not be repeated here. Each module within the aforementioned aircraft internal and external flow integrated surface optimization device can be implemented in whole or in part via software, hardware, or a combination thereof. Each of these modules can be embedded in or independent of a processor within a computer device in hardware form, or stored in a computer device memory in software form, allowing the processor to call and execute the corresponding operations of each module.

[0092] In one embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as follows: Figure 6 As shown. The computer device includes a processor, a memory, a network interface and a database connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store optimization data of the integrated internal and external flow profile of the aircraft. The network interface of the computer device is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, a method for optimizing the integrated internal and external flow profile of the aircraft is implemented.

[0093] Those skilled in the art will understand that Figure 6 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0094] In one embodiment, a computer device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and when the processor executes the computer program, the following steps are implemented:

[0095] Step 202: construct a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids.

[0096] Step 204 : determining the order of the numerical format, and constructing a surface unit array between volume meshes according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume meshes.

[0097] Step 206 , partitioning the plurality of volume meshes and assigning the partitioned volume meshes to the GPU for parallel processing; wherein, when partitioning, determining the interface, obtaining the arrangement of physically adjacent volume meshes through the interface, and marking the relevant volume meshes according to the arrangement.

[0098] In step 208, each GPU iteratively calculates the volume mesh through the discretized computational fluid dynamics equations, and based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, packages and transmits the physical quantities of the marked volume mesh, and calculates the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume mesh.

[0099] Step 210 , statistically analyzing the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids and optimizing them, to obtain the optimal design scheme of the integrated internal and external flow profile of the aircraft.

[0100] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0101] Step 202: construct a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids.

[0102] Step 204 : determining the order of the numerical format, and constructing a surface unit array between volume meshes according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume meshes.

[0103] Step 206 , partitioning the plurality of volume meshes and assigning the partitioned volume meshes to the GPU for parallel processing; wherein, when partitioning, determining the interface, obtaining the arrangement of physically adjacent volume meshes through the interface, and marking the relevant volume meshes according to the arrangement.

[0104] In step 208, each GPU iteratively calculates the volume mesh through the discretized computational fluid dynamics equations, and based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, packages and transmits the physical quantities of the marked volume mesh, and calculates the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume mesh.

[0105] Step 210 , statistically analyzing the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids and optimizing them, to obtain the optimal design scheme of the integrated internal and external flow profile of the aircraft.

[0106] Those skilled in the art will appreciate that all or part of the processes in the above-mentioned embodiments can be implemented by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0107] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, 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.

[0108] The above-described embodiments merely represent several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present application, and such modifications and improvements are intended to fall within the scope of protection of the present application. Therefore, the scope of protection of the present application shall be determined by the appended claims.

Claims

1. A method for optimizing the integrated internal and external flow profile of an aircraft, characterized in that: include: Constructing a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretizing the three-dimensional computational domain into a plurality of volume grids; Determining the order of the numerical format, and constructing a surface unit array between volume grids according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume grids; Partitioning the plurality of volume grids, and assigning the partitioned volume grids to a GPU for parallel processing; wherein, when partitioning, determining a dividing interface, obtaining an arrangement of physically adjacent volume grids through the dividing interface, and marking related volume grids according to the arrangement; Each GPU iteratively calculates the volume mesh using the discretized computational fluid dynamics equations. Based on the volume mesh one-dimensional index information contained in the surface cell array of the interface, the physical quantities of the marked volume mesh are packaged and transferred to calculate the mechanical properties of the flow configuration within the engine and the aerodynamic shape of the aircraft in each volume mesh. The mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all body grids are statistically analyzed and optimized to obtain the optimal design scheme for the integrated internal and external flow surface of the aircraft.

2. The method for optimizing the integrated internal and external flow profile of an aircraft according to claim 1, characterized in that: Construct a three-dimensional computational domain for the flow areas inside and outside the aircraft, and discretize the three-dimensional computational domain into several volume grids, including: Determine the flow configuration within the aircraft engine based on the aircraft design requirements; and Design the aerodynamic shape of the aircraft; Determine a three-dimensional computational domain of the flow domain inside and outside the aircraft according to the flow configuration inside the engine and the aerodynamic shape of the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids; The aerodynamic shape of the aircraft is used as the initial condition, and initial physical quantities are set in each body grid.

3. The method for optimizing the integrated internal and external flow profile of an aircraft according to claim 2, characterized in that: Design the aerodynamic shape of the aircraft, including: The flight conditions of the aircraft are determined, and the aerodynamic shape of the aircraft is designed according to the flight conditions.

4. The method for optimizing the integrated internal and external flow profile of an aircraft according to any one of claims 1 to 3, characterized in that: When partitioning, determining a dividing interface, obtaining a physically adjacent volume mesh arrangement through the dividing interface, and marking related volume meshes according to the arrangement, including: Partitioning each body mesh into a first partition and a second partition, and using adjacent surfaces of the first partition and the second partition as interfaces; Near the interface, possible arrangement modes of the first partition and the second partition when values ​​are transferred are recorded, and related volume grids are marked according to the arrangement modes.

5. The method for optimizing the integrated internal and external flow profile of an aircraft according to claim 4, characterized in that: Partitioning each body mesh into a first partition and a second partition, and using adjacent surfaces of the first partition and the second partition as interfaces, including: Divide each volume mesh into a first partition and a second partition, and use adjacent surfaces of the first partition and the second partition as interfaces; According to the order of the numerical format, the interface is associated with the corresponding volume mesh quantities of the first partition and the second partition to obtain a surface cell array of the interface.

6. The method for optimizing the integrated internal and external flow profile of an aircraft according to claim 5, characterized in that: The volume grids associated with the interface are arranged along the positive direction of the coordinate axis.

7. An integrated internal and external flow profile optimization device for an aircraft, characterized in that: The device comprises: A grid discretization module is used to construct a three-dimensional computational domain of the flow field inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids; a one-dimensional index construction module, configured to determine an order of a numerical format, and construct a surface unit array between volume grids according to the order of the numerical format, wherein the surface unit array includes one-dimensional index information of a plurality of volume grids; a partition processing module, configured to partition the plurality of volume meshes and assign the partitioned volume meshes to a GPU for parallel processing; wherein, when partitioning, a partitioning interface is determined, an arrangement of physically adjacent volume meshes is obtained through the partitioning interface, and related volume meshes are marked according to the arrangement; The iterative calculation module is used by each GPU to iteratively calculate the volume mesh through the discretized computational fluid dynamics equations. Based on the one-dimensional index information of the volume mesh contained in the surface cell array of the interface, the marked volume mesh physical quantities are packaged and transferred, and the mechanical properties of the flow configuration within the engine and the aerodynamic shape of the aircraft in each volume mesh are calculated; The performance optimization module is used to statistically analyze and optimize the mechanical properties of the engine's internal flow configuration and the aircraft's aerodynamic shape in all volume grids to obtain the optimal design scheme for the integrated internal and external flow surface of the aircraft.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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