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

Abstract

The invention relates to an aircraft internal and external flow integrated profile optimization method and device, equipment and a medium. The method comprises the following steps: firstly, dispersing a constructed three-dimensional computational domain of an aircraft internal and external drainage basin into a plurality of volume grids; then, according to the order of the numerical format, constructing a surface unit array containing a plurality of volume grid one-dimensional index information; partitioning the plurality of volume grids and then distributing the volume grids to a GPU for parallel processing; each GPU performs iterative calculation on the volume mesh through the discrete computational fluid mechanics equation, packages and transmits marked volume mesh physical quantities based on volume mesh one-dimensional index information contained in a surface unit array of an interface, and calculates mechanical properties; all mechanical properties are counted and optimized, and an optimal profile design scheme is obtained. According to the method, a one-dimensional index three-dimensional partitioning method is adopted, so that a GPU program can carry out multi-GPU simulation, the calculation of a larger-scale grid quantity is realized, and the calculation efficiency and precision are improved.

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 aircraft have important value for the future of ultra-fast transportation and have attracted more and more attention in the civilian field. The design of hypersonic aircraft can be divided into three parts: theoretical calculation, numerical simulation and experiment. When the structural parameters of the hypersonic aircraft are designed through theoretical calculation, they are first tested through numerical simulation to determine whether their various performance indicators meet the requirements, and then the structural parameters that meet the requirements are improved for experiment. It can be seen that high-precision numerical simulation can greatly reduce the number of experiments, thereby reducing design time and cost.

[0003] The role of numerical simulation in the design of hypersonic aircraft cannot be ignored. Through numerical simulation, engineers can simulate the behavior of aircraft under hypersonic conditions in a virtual environment and study key factors such as aerodynamic characteristics, thermodynamic effects, and structural stress. This enables the design team to have a more comprehensive understanding of the performance of the aircraft before actual manufacturing, and to make multiple modifications and optimizations in a virtual environment, greatly reducing the number of experiments. This not only improves the accuracy of the design, but also significantly reduces the design cycle and cost.

[0004] At present, the optimization design of hypersonic vehicles through computational fluid dynamics (CFD) has become a key technology to shorten the development cycle. Generally, when the computational fluid dynamics program based on the CPU is used for calculation, the three-dimensional grid with three-dimensional index is partitioned. However, due to the increasing requirements for calculation accuracy, it is necessary to accelerate the calculation based on the graphics processing unit (GPU), especially the cluster of multiple GPUs for ultra-large-scale calculations. Traditional three-dimensional indexing may make it difficult to directly find nearby volume grids, thus failing to give full play to the powerful parallel computing performance of GPU. 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-mentioned 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 of the flow domain 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, 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;

[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 through the discretized computational fluid dynamics equations, and based on the volume mesh one-dimensional index information contained in the surface unit array of the interface, packages and transfers 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;

[0011] The mechanical properties of the flow configuration inside the engine and the aerodynamic shape of the aircraft 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 field 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 inside the aircraft engine according to the design requirements of the aircraft; and

[0014] Design the aerodynamic shape of the aircraft;

[0015] Determine the three-dimensional calculation 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 calculation domain into a plurality of volume grids;

[0016] The aerodynamic shape of the aircraft is used as an 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 dividing interface, obtaining a physically adjacent volume mesh arrangement through the dividing interface, and marking related volume meshes according to the arrangement, including:

[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 a dividing interface;

[0021] Near the interface, possible arrangement modes that may occur when the first partition and the second partition are respectively transferred are recorded, and relevant volume grids are marked according to the arrangement modes.

[0022] In one embodiment, each body mesh is 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:

[0023] Divide each of the volume meshes equally 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 unit array of the interface.

[0025] In one of the embodiments, the volume grid associated with the interface is arranged along the positive direction of the coordinate axis.

[0026] An aircraft internal and external flow integrated profile 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, used to determine the order of the 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, used for partitioning the plurality of volume grids, and assigning the partitioned volume grids to the GPU for parallel processing; wherein, when partitioning, a dividing interface is determined, an arrangement mode of physically adjacent volume grids is obtained through the dividing interface, and related volume grids are marked according to the arrangement mode;

[0030] Iterative calculation module, used for each GPU to iteratively calculate the volume grid through the discretized computational fluid dynamics equation, and based on the volume grid one-dimensional index information contained in the surface unit array of the interface, the marked volume grid physical quantities are packaged and transferred, and the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume grid are calculated;

[0031] The performance optimization module is used to statistically analyze and optimize the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all body 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 implements the steps of any of the above methods when executed by a processor.

[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, and construct a surface unit array between the volume grids according to the order of the numerical format, 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, determine the interface, obtain the arrangement mode of physically adjacent volume grids through the interface, and mark the relevant volume grids according to the arrangement mode; 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, packages and transmits the marked volume grid physical quantities, and calculates the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume grid; the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in all volume grids are statistically analyzed and optimized to obtain the optimal design scheme for the integrated surface of the internal and external flows of the aircraft.

[0035] The present invention constructs a surface unit array, so that numerical flux and gradient can be constructed directly on the surface unit, which is more concise in calculation and improves calculation efficiency; according to the order of the numerical format, a surface unit array containing one-dimensional index information of several volume grids is constructed, and then the physically adjacent volume grid arrangement mode is obtained through the interface, and the label association is performed, so that the calculation of the corresponding numerical value can still be completed after being partitioned by the interface. By adopting the three-dimensional partitioning method of one-dimensional index, the GPU program can carry out multi-GPU simulation, thereby realizing the calculation of larger-scale grid volume and improving calculation 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 is a schematic diagram of the association between a one-dimensional index and a face in one embodiment;

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

[0039] Figure 4This is a schematic diagram of four-point partition value transmission in an 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 It is a structural block diagram of an aircraft internal and external flow integrated profile optimization device in one embodiment;

[0041] Figure 6 FIG. 4 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0043] It should be noted that in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0044] In the process of implementing the technology of this solution, the inventor found that the traditional data indexing method is a three-dimensional index, and its grid partitioning method is for three-dimensional grids with three-dimensional indexes. Through the three-dimensional index, 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 calculation accuracy and the increasing scale of calculations, it is necessary to accelerate calculations based on GPUs, especially clusters of multiple GPUs for ultra-large-scale calculations to obtain the lift and drag coefficients of aircraft or cars, so as to optimize the shape of the carrier and greatly speed up the development of aircraft or cars. For GPU computational fluid programs, if traditional three-dimensional indexing is used, even if the volume units are physically adjacent, due to the large difference between their index numbers, it may be 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 inventor provides a partition value transmission method for three-dimensional grids with one-dimensional indexes, which can provide fast and efficient parallel partitioning for grid organization calculation programs for surface associations, and can realize large-scale simulation calculations on GPU clusters to improve computing efficiency.

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

[0046] The following will describe the implementation of the present invention in detail with reference to the accompanying drawings in the embodiment diagram of the present invention.

[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 area inside and outside the aircraft, and discretize the three-dimensional computational domain into a plurality of volume grids.

[0049] It can be understood that before optimizing the aircraft surface, the spatial area for numerical simulation must be determined first. The three-dimensional computational domain of the flow field inside and outside the aircraft is mainly determined by the flow configuration inside the engine and the aerodynamic shape of the aircraft, which is used to simulate the fluid behavior around the aircraft. Then, the three-dimensional computational domain is divided into many small cubes or other geometric units in three-dimensional space through discretization. These volume grids cover the entire computational domain, and when solving, the problem can be decomposed into discrete equations on each grid unit.

[0050] In summary, the fluid dynamics equations can be converted into discrete form by discretizing the computational domain into a volume mesh, and then a computer algorithm is 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] It can be understood that in the computational fluid program based on GPU, in order to give full play to the parallel computing performance of GPU, the grid is to store all volume grids in a one-dimensional array, that is, to use a one-dimensional index. In order to solve this problem, the surface unit between adjacent grids is used to record the index number of the corresponding volume grid, and the required volume unit is directly recorded on the surface unit. In this way, it is easy to construct numerical flux and gradient on the surface unit.

[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. Figure 2 As shown, the surface element F 1 The four volume grids near it are recorded. To construct the flux of the fourth-order format, you can construct the surface cell array F 1 (i,i+N 1,i+N 2 ,i+N 3 ), the surface element array includes the one-dimensional index information of the four body grids corresponding to the fourth-order format, so that the simulation calculation of the fourth-order format can be performed. For example, to construct the flux of the second-order format, the surface element F 1 in(i+N 1 ) and (i+N 2 ), we can construct the array F before partitioning 1 (i+N 1 ,i+N 2 ), so as to perform simulation calculations in 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, a partitioning process of the fourth-order format is described in detail below, and 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 related 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, the traditional grid partitioning is aimed 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 combining the arrangement methods of the volume grids associated with the interfaces, so as to achieve one-dimensional indexing. Physically adjacent volume grids can also directly find nearby volume grids through simple indexing operations to complete the 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] It can be understood that the surface unit array of the interface has been constructed in step 204, and all volume grids belonging to the arrangement mode near the interface have been marked in step 206. Therefore, through the one-dimensional index information of the volume grid contained in the surface unit array, the physical quantity of the marked volume grid can be correctly transmitted, so as to calculate the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume grid.

[0059] Step 210, statistically analyzing the mechanical properties of the flow configuration inside the engine and the aerodynamic shape of the aircraft in all body grids and optimizing them, and obtaining 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, thereby finding the optimal design solution.

[0061] The above-mentioned aircraft internal and external flow integrated surface optimization method constructs a three-dimensional calculation domain of the aircraft internal and external flow domains, discretizes the three-dimensional calculation domain into a number of volume grids; determines the order of the numerical format, constructs 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; partitions the several volume grids, and distributes the partitioned volume grids to the GPU for parallel processing; wherein, when partitioning, determines the interface, obtains the arrangement mode of physically adjacent volume grids through the interface, and marks the relevant volume grids according to the arrangement mode; 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, packages and transmits the marked volume grid physical quantities, calculates the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in each volume grid; counts and optimizes the mechanical properties of the engine internal flow configuration and the aircraft aerodynamic shape in all volume grids, and obtains the optimal design scheme of the aircraft internal and external flow integrated surface.

[0062] The present invention constructs a surface unit array, so that numerical flux and gradient can be constructed directly on the surface unit, which is more concise in calculation and improves calculation efficiency; according to the order of the numerical format, a surface unit array containing one-dimensional index information of several volume grids is constructed, and then the physically adjacent volume grid arrangement mode is obtained through the interface, and the label association is performed, so that the calculation of the corresponding numerical value can still be completed after being partitioned by the interface. By adopting the three-dimensional partitioning method of one-dimensional index, the GPU program can carry out multi-GPU simulation, thereby realizing the calculation of larger-scale grid volume and improving calculation efficiency and accuracy.

[0063] In one embodiment, a three-dimensional computational domain of the flow field inside and outside the aircraft is constructed, and the three-dimensional computational domain is 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 flow field inside and outside 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 a number of volume grids.

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

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

[0068] The flight conditions of the aircraft are generally confirmed based on the purpose of use of the hypersonic aircraft and the actual technical requirements. Different purposes of use 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, a dividing interface is determined, an arrangement of physically adjacent volume meshes is obtained through the dividing interface, and related volume meshes are marked according to the arrangement, including:

[0070] Each body mesh is 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, the possible arrangement modes when the first partition and the second partition are respectively transferred are recorded, and the relevant volume grids are marked according to the arrangement modes.

[0072] In one embodiment, further, each body mesh is partitioned to obtain a first partition and a second partition, and the 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 volume mesh numbers of the first partition and the second partition, and the surface cell array of the interface is obtained.

[0075] Specifically, Figure 3 As shown in the figure, a schematic diagram of the grid partitioning of a complex structure is shown. For the convenience of explanation, the lines between two-dimensional grids are used here to represent the faces between two volume grids in three dimensions. In the figure, the grid is divided into two areas along the x direction according to the number of grids, where face1, face2, and face3 are typical surface units between volume grids 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 partition on the right. Therefore, the two volume meshes C' and D' need to be marked. Similarly, the corresponding surface unit 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 three-dimensional structure mesh, the mesh numbers belonging to the above 12 cases need to be marked respectively during partitioning. Then, when transferring values, the physical quantities of the mesh that need to be transferred are packaged, and the physical quantities to which the marked mesh belongs are packaged, and then the values ​​are transferred through 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. Moreover, 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, a device for optimizing the integrated internal and external flow profile of an aircraft 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 field 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, wherein 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; wherein, when partitioning, a dividing interface is determined, and the arrangement of physically adjacent volume meshes is obtained through the dividing interface, and the related volume meshes are marked according to the arrangement.

[0089] The iterative calculation module 408 is used for each GPU to iteratively calculate the volume grid through the discretized computational fluid dynamics equation, and based on the volume grid one-dimensional index information 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 flow configuration in the engine and the aerodynamic shape of the aircraft in each volume grid are calculated.

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

[0091] For the specific definition of the aircraft internal and external flow integrated surface optimization device, please refer to the definition of the aircraft internal and external flow integrated surface optimization method mentioned above, which will not be repeated here. Each module in the above-mentioned aircraft internal and external flow integrated surface optimization device can be implemented in whole or in part by software, hardware and their combination. The above-mentioned modules can be embedded in or independent of the processor in the computer device in the form of hardware, or can be stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[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 through a system bus. Among them, 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 internal and external flow integrated surface of the aircraft. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for optimizing the internal and external flow integrated surface 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 those shown in the figure, or combine certain components, or have a different arrangement of components.

[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, constructing a three-dimensional computational domain of the flow domain inside and outside the aircraft, and discretizing 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 related 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 flow configuration inside the engine and the aerodynamic shape of the aircraft in all body grids and optimizing them, and obtaining 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, and when the computer program is executed by a processor, the following steps are implemented:

[0101] Step 202, constructing a three-dimensional computational domain of the flow domain inside and outside the aircraft, and discretizing 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 related 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 flow configuration inside the engine and the aerodynamic shape of the aircraft in all body grids and optimizing them, and obtaining the optimal design scheme of the integrated internal and external flow profile of the aircraft.

[0106] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and 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. As an illustration and not limitation, RAM is available in many 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 may 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 only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached 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 of the flow domain 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, 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; 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 through the discretized computational fluid dynamics equations, and based on the volume mesh one-dimensional index information contained in the surface unit array of the interface, packages and transfers 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; The mechanical properties of the flow configuration inside the engine and the aerodynamic shape of the aircraft 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 of the flow field inside and outside the aircraft, and discretize the three-dimensional computational domain into a number of volume grids, including: Determine the flow configuration inside the aircraft engine according to the design requirements of the aircraft; and Design the aerodynamic shape of the aircraft; Determine the three-dimensional calculation 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 calculation domain into a plurality of volume grids; The aerodynamic shape of the aircraft is used as an 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 a dividing interface; Near the interface, possible arrangement modes that may occur when the first partition and the second partition are respectively transferred are recorded, and relevant 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 to obtain a first partition and a second partition, and using adjacent surfaces of the first partition and the second partition as interfaces, including: Divide each of the volume meshes equally 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 unit 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, used to determine the order of the 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, used for partitioning the plurality of volume grids, and assigning the partitioned volume grids to the GPU for parallel processing; wherein, when partitioning, a dividing interface is determined, an arrangement mode of physically adjacent volume grids is obtained through the dividing interface, and related volume grids are marked according to the arrangement mode; Iterative calculation module, used for each GPU to iteratively calculate the volume grid through the discretized computational fluid dynamics equation, and based on the volume grid one-dimensional index information contained in the surface unit array of the interface, the marked volume grid physical quantities are packaged and transferred, and the mechanical properties of the flow configuration in the engine and the aerodynamic shape of the aircraft in each volume grid are calculated; The performance optimization module is used to statistically analyze and optimize the mechanical properties of the flow configuration inside the engine and the aerodynamic shape of the aircraft in all body 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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