Static aeroelastic coupling simulation method, device, equipment and medium based on displacement difference

Abstract

The present application discloses a static aeroelastic coupling simulation method, device, equipment and medium based on displacement difference, which relates to the field of coupling simulation, including: obtaining a first aerodynamic load and a second aerodynamic load, determining the aerodynamic load difference and the current surface aerodynamic load of the elastic model, determining the structural finite element mesh and the structural surface mesh, mapping the current surface aerodynamic load to the structural surface mesh, and obtaining the structural surface aerodynamic load; determining the target displacement based on the structural surface aerodynamic load, the structural finite element mesh and the structural surface mesh, correcting the target displacement to obtain the corrected displacement, and judging whether the difference between the corrected displacements of two adjacent calculations is less than a preset threshold; if not, determining the current surface aerodynamic load of the elastic model, and jumping back to the step of constructing the structural finite element model until the difference is less than the preset threshold, and judging that the static aeroelastic coupling simulation calculation result of the aircraft converges. In this way, the error of static aeroelastic coupling simulation is reduced.

Description

Technical Field

[0001] The present invention relates to the field of coupling simulation, and in particular to a static aeroelastic coupling simulation method, device, equipment and medium based on displacement difference. Background Art

[0002] At present, aircraft design has a trend towards lightweight structures such as composite materials to reduce the weight of the entire aircraft structure, improve fuel efficiency and range, and make aircraft more flexible. Considering the coupling between wing aerodynamics / structures in all design stages can better improve the performance of aircraft and reduce design and manufacturing costs. There are currently three main methods for the coupling between flexible wing aerodynamics / structures: numerical simulation, wind tunnel test, and aerial flight test. Among them, the wind tunnel test has extremely high measurement accuracy due to its high fit to the actual flight conditions, but the wind tunnel test measurement technology is difficult and the experimental cost is high. In order to reduce the experimental cost and reduce the difficulty of measuring experimental data, the wind tunnel model of the aircraft often uses a scaled model of the full-size model of the aircraft, which also causes the stiffness of the model itself to increase exponentially. When conducting wind tunnel tests related to aeroelasticity, the elastic data is often distorted, so the wind tunnel test cannot accurately describe the aeroelastic state of the aircraft. However, the rigid wind tunnel test conducted on the scaled model can obtain more accurate data.

[0003] In order to reduce the cost of experiments and ensure the safety of experimenters, with the rapid development of computer technology and computing methods, computational fluid dynamics has developed into an efficient and high-resolution numerical analysis tool. At present, the static aeroelastic coupling simulation method based on CFD (Computational Fluid Dynamics) mainly adopts the direct coupling of pneumatics and structure. When performing aerodynamic / structural coupling simulation, due to factors such as aircraft modeling errors, grid discretization errors, and coupling surface data transmission errors, the calculation results deviate from the correct results, affecting the accuracy of aircraft performance evaluation. Summary of the invention

[0004] In view of this, the purpose of the present invention is to provide a static aeroelastic coupling simulation method, device, equipment and medium based on displacement difference, which can optimize the error generated by the aerodynamic displacement calculation in the numerical simulation process, thereby greatly reducing the error of static aeroelastic coupling simulation and improving the accuracy of the simulation results. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a static aeroelastic coupling simulation method based on displacement difference, comprising:

[0006] Acquire a first aerodynamic load of the aircraft in a rigid shape based on experimental data and a second aerodynamic load of the aircraft in a rigid shape based on data simulation calculation, and determine an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load;

[0007] Determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, construct a structural finite element model of the elastic model, so as to determine a structural finite element mesh and a structural surface mesh based on the structural finite element model, and map the current surface aerodynamic load to the structural surface mesh to obtain a structural surface aerodynamic load;

[0008] Determine a target displacement of a flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh and the structure surface mesh, correct the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determine whether a difference between two adjacent calculated corrected displacements is less than a preset threshold;

[0009] If not, the current surface aerodynamic load of the elastic model corresponding to the aircraft is determined using the corrected displacement corresponding to the current calculation, and the process jumps again to the step of constructing a structural finite element model of the elastic model until the difference is less than the preset threshold value, and it is determined that the static aeroelastic coupling simulation calculation results of the aircraft converge.

[0010] Optionally, the step of obtaining a first aerodynamic load of the aircraft in a rigid shape based on experimental data and a second aerodynamic load of the aircraft in a rigid shape based on data simulation calculation includes:

[0011] constructing a rigid scaled model of the aircraft according to the size of the aircraft and the wind tunnel performance, and performing a wind blowing test on the rigid scaled model in a wind tunnel, so as to obtain a first aerodynamic load of the aircraft under a rigid shape based on experimental data by measurement;

[0012] A rigid data model is constructed based on the wind tunnel model of the aircraft, the flow field corresponding to the rigid data model is discretized by grid, the discretized grid is obtained, and the discretized grid is numerically calculated by computational fluid dynamics method to obtain the second aerodynamic load of the aircraft under the rigid shape calculated based on data simulation.

[0013] Optionally, mapping the current surface aerodynamic load to the structure surface mesh to obtain the structure surface aerodynamic load includes:

[0014] A first mapping relationship between the flow field mesh surface and the structure surface mesh is determined, and a current surface aerodynamic load is mapped to the structure surface mesh according to the first mapping relationship to obtain the structure surface aerodynamic load.

[0015] Optionally, the determining the target displacement of the flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh and the structure surface mesh includes:

[0016] Calculating the surface displacement of the elastic model under the action of the aerodynamic load on the surface of the structure by a computational structural dynamics method based on the structural finite element mesh and the structural surface mesh;

[0017] A second mapping relationship between the structure surface mesh and the flow field mesh surface is determined, and the surface displacement is mapped to the flow field mesh surface based on the second mapping relationship to obtain a target displacement of the flow field mesh surface.

[0018] Optionally, the using the aerodynamic load difference to correct the target displacement to obtain a corrected displacement includes:

[0019] determining a ratio of the aerodynamic load differential to a stiffness matrix;

[0020] The sum of the ratio and the target displacement is determined as the corrected displacement.

[0021] Optionally, the determining the current surface aerodynamic load of the elastic model corresponding to the aircraft by using the corrected displacement corresponding to the current calculation includes:

[0022] The grid corresponding to the elastic model is updated using the corrected displacement corresponding to the current calculation, and the current surface aerodynamic load of the elastic model corresponding to the aircraft is determined based on the corresponding updated grid.

[0023] Optionally, after determining whether the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold, the method further includes:

[0024] If the difference between the corrected displacements corresponding to two adjacent calculations is less than the preset threshold, it is directly determined that the static aeroelastic coupling simulation calculation result of the aircraft is converged.

[0025] In a second aspect, the present application discloses a static aeroelastic coupling simulation device based on displacement difference, comprising:

[0026] an aerodynamic load difference determination module, used to obtain a first aerodynamic load of the aircraft under a rigid shape based on experimental data and a second aerodynamic load of the aircraft under a rigid shape based on data simulation calculation, and determine an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load;

[0027] an aerodynamic load determination module, used to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, construct a structural finite element model of the elastic model, so as to determine a structural finite element mesh and a structural surface mesh based on the structural finite element model, and map the current surface aerodynamic load to the structural surface mesh to obtain the structural surface aerodynamic load;

[0028] a judgment module, configured to determine a target displacement of a flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh, and the structure surface mesh, to correct the target displacement using the aerodynamic load difference to obtain a corrected displacement, and to judge whether a difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold;

[0029] The jump module is used to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft using the corrected displacement corresponding to the current calculation, and jump again to the step of constructing the structural finite element model of the elastic model until the difference is less than the preset threshold, and determine that the static aeroelastic coupling simulation calculation result of the aircraft converges.

[0030] In a third aspect, the present application discloses an electronic device, comprising:

[0031] Memory, used to store computer programs;

[0032] A processor is used to execute the computer program to implement the static aeroelastic coupling simulation method based on displacement difference as described above.

[0033] In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program, wherein the computer program, when executed by a processor, implements the static aeroelastic coupling simulation method based on displacement difference as described above.

[0034] The present application first obtains a first aerodynamic load of an aircraft under a rigid shape based on experimental data and a second aerodynamic load of an aircraft under a rigid shape based on data simulation calculation, and determines the aerodynamic load difference between the first aerodynamic load and the second aerodynamic load; then determines the current surface aerodynamic load of the elastic model corresponding to the aircraft, and constructs a structural finite element model of the elastic model, so as to determine a structural finite element grid and a structural surface grid based on the structural finite element model, and maps the current surface aerodynamic load to the structural surface grid to obtain a structural surface aerodynamic load; then determines a target displacement of the flow field grid surface based on the structural surface aerodynamic load, the structural finite element grid and the structural surface grid, corrects the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determines whether the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold; finally, if not, determines the current surface aerodynamic load of the elastic model corresponding to the aircraft using the corrected displacement corresponding to the current calculation, and jumps back to the step of constructing the structural finite element model of the elastic model until the difference is less than the preset threshold, and determines that the static aeroelastic coupling simulation calculation result of the aircraft converges. It can be seen that the present application corrects the displacement by the displacement difference corresponding to the experimental results and the numerical results under the rigid shape, so as to correct the error caused by the aerodynamic displacement calculation in the numerical simulation process, thereby greatly reducing the error of the static aeroelastic coupling simulation and improving the accuracy of the simulation results. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0036] Figure 1 A flow chart of a static aeroelastic coupling simulation method based on displacement difference disclosed in this application;

[0037] Figure 2 A schematic diagram of a model of a trapezoidal wing disclosed in the present application;

[0038] Figure 3 A schematic diagram of a surface grid disclosed in this application;

[0039] Figure 4 A schematic diagram of a discrete rear surface grid disclosed in this application;

[0040] Figure 5 A schematic diagram of a mapping relationship disclosed in this application;

[0041] Figure 6 This is another schematic diagram of mapping relationship disclosed in this application;

[0042] Figure 7 A schematic diagram of a convergence curve for static aeroelastic calculation of a trapezoidal wing disclosed in the present application;

[0043] Figure 8 A schematic diagram of the structure of a static-aeroelastic coupling simulation device based on displacement difference disclosed in the present application;

[0044] Fig. 9 This is a structural diagram of an electronic device disclosed in this application. DETAILED DESCRIPTION

[0045] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] At present, the static aeroelastic coupling simulation method based on CFD mainly adopts the method of direct coupling between pneumatics and structure. When performing aerodynamic / structural coupling simulation, due to factors such as aircraft modeling error, grid discretization error, coupling surface data transmission error, etc., the calculation results deviate from the correct results, affecting the accuracy of aircraft performance evaluation. In order to solve the above technical problems, the present application discloses a static aeroelastic coupling simulation method, device, equipment and medium based on displacement difference, which can optimize the error generated by the calculation of aerodynamic displacement in the numerical simulation process, thereby greatly reducing the error of static aeroelastic coupling simulation and improving the accuracy of simulation results.

[0047] See also Figure 1 As shown, the embodiment of the present invention discloses a static aeroelastic coupling simulation method based on displacement difference, comprising:

[0048] Step S11, obtaining a first aerodynamic load of the aircraft under a rigid shape based on experimental data and a second aerodynamic load of the aircraft under a rigid shape based on data simulation calculation, and determining an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load.

[0049] In this embodiment, the present application first manufactures a rigid scaled model of the aircraft according to the size of the aircraft model and the wind tunnel performance, and conducts a wind test in a wind tunnel with the rigid scaled model, and obtains the first aerodynamic load of the aircraft under the rigid shape based on the experimental data by measurement. At the same time, a rigid digital model identical to the wind tunnel model is established, and the flow field around the digital model is discretized by mesh. The discretized mesh is numerically calculated using the finite volume method (CFD method) to obtain the second aerodynamic load of the aircraft under the rigid shape calculated by numerical simulation. After obtaining the first aerodynamic load and the second aerodynamic load, the difference in aerodynamic load change under the rigid shape based on the experimental data and the numerical calculation is calculated:

[0050] ;

[0051] in, is the aerodynamic load difference; is the first aerodynamic load; is the second aerodynamic load.

[0052] Step S12: determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, construct a structural finite element model of the elastic model, so as to determine the structural finite element mesh and the structural surface mesh based on the structural finite element model, and map the current surface aerodynamic load to the structural surface mesh to obtain the structural surface aerodynamic load.

[0053] In this embodiment, a full-scale elastic model of the aircraft is first established, and the flow field around it is discretized to obtain a discrete grid. and the surface mesh of this discretized mesh Finally, the finite volume method (CFD method) is used to calculate the current surface aerodynamic load of the elastic model Then, a structural finite element model of the elastic model is constructed, and the structural finite element model is discretized using tetrahedron and hexahedron elements to generate a structural finite element mesh. and its structural surface mesh . Then, the aerodynamic load on the elastic model surface needs to be mapped to the structural mesh surface. In this process, the flow field surface mesh is established through the RBF (Radial Basis Function) method, the nearest projection method, etc. and structural surface mesh A first mapping relationship is defined between the two, and the current surface aerodynamic load is mapped to the structure surface mesh according to the first mapping relationship to obtain the structure surface aerodynamic load.

[0054] Step S13, determining a target displacement of the flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh and the structure surface mesh, correcting the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determining whether a difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold.

[0055] In this embodiment, in the process of determining the target displacement of the flow field mesh surface based on the aerodynamic load on the structure surface, the structural finite element mesh and the structural surface mesh, the surface displacement of the elastic model under the aerodynamic load on the structure surface is first calculated by the computational structural dynamics method based on the structural finite element mesh and the structural surface mesh. That is, the aerodynamic load on the structure surface is loaded onto the finite element model, and the displacement of the structure under the load is calculated by the CSD (Computational Structural Dynamics) method. Then, the second mapping relationship between the structural surface mesh and the flow field mesh surface is determined, and the surface displacement is mapped to the flow field mesh surface based on the second mapping relationship to obtain the target displacement of the flow field mesh surface. Specifically, the structural surface mesh is established by using the RBF method, the nearest projection method, etc. and the flow surface grid The mapping relationship between them is based on which the displacement of the elastic model is calculated. Mapping onto the flow surface , and obtain the displacement of the flow field surface grid .

[0056] After obtaining the target displacement of the flow field surface mesh, the displacement of the elastic model numerical simulation is corrected. Specifically, the displacement of the flow field surface mesh is obtained based on the difference in aerodynamic loads under the rigid shape based on experimental data and numerical calculations. Correction is performed to obtain the displacement of the corrected elastic model numerical simulation The correction method is as follows:

[0057] ;

[0058] in, is the corrected displacement; is the displacement of the flow field surface grid; is the aerodynamic load difference; K is the stiffness matrix.

[0059] After the correction, it is necessary to determine whether the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold.

[0060] Step S14: If not, the current surface aerodynamic load of the elastic model corresponding to the aircraft is determined using the corrected displacement corresponding to the current calculation, and the process jumps back to the step of constructing a structural finite element model of the elastic model until the difference is less than the preset threshold value, and it is determined that the static aeroelastic coupling simulation calculation result of the aircraft converges.

[0061] In this embodiment, if the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold, it is determined that the static aeroelastic coupling simulation calculation results of the aircraft have converged. However, if the difference between the corrected displacements corresponding to two adjacent calculations is greater than or equal to the preset threshold, it is necessary to first use the corrected displacement corresponding to the current calculation to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, that is, use the corrected displacement corresponding to the current calculation to update the grid corresponding to the elastic model, and determine the current surface aerodynamic load of the elastic model corresponding to the aircraft based on the corresponding updated grid. Then jump back to the step of constructing the structural finite element model of the elastic model, recalculate the corrected displacement according to the updated surface aerodynamic load, and then determine again whether the difference between the corrected displacements corresponding to two adjacent calculations is less than the preset threshold, until the static aeroelastic coupling simulation calculation results of the aircraft converge, and all processes are completed.

[0062] The present application first obtains a first aerodynamic load of an aircraft under a rigid shape based on experimental data and a second aerodynamic load of an aircraft under a rigid shape based on data simulation calculation, and determines the aerodynamic load difference between the first aerodynamic load and the second aerodynamic load; then determines the current surface aerodynamic load of the elastic model corresponding to the aircraft, and constructs a structural finite element model of the elastic model, so as to determine a structural finite element grid and a structural surface grid based on the structural finite element model, and maps the current surface aerodynamic load to the structural surface grid to obtain a structural surface aerodynamic load; then determines a target displacement of the flow field grid surface based on the structural surface aerodynamic load, the structural finite element grid and the structural surface grid, corrects the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determines whether the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold; finally, if not, determines the current surface aerodynamic load of the elastic model corresponding to the aircraft using the corrected displacement corresponding to the current calculation, and jumps back to the step of constructing the structural finite element model of the elastic model until the difference is less than the preset threshold, and determines that the static aeroelastic coupling simulation calculation result of the aircraft converges. It can be seen that the present application corrects the displacement by the displacement difference corresponding to the experimental results and the numerical results under the rigid shape, so as to correct the error caused by the aerodynamic displacement calculation in the numerical simulation process, thereby greatly reducing the error of the static aeroelastic coupling simulation and improving the accuracy of the simulation results.

[0063] Based on the previous embodiment, it can be seen that the present application discloses a static aeroelastic coupling simulation method based on displacement difference. Next, the static aeroelastic coupling simulation method based on displacement difference will be described in detail in combination with specific application scenarios.

[0064] This application firstly considers the size of the trapezoidal wing and the wind tunnel performance, and the model of the trapezoidal wing is as follows Figure 2 As shown in the figure, a rigid scaled model of a trapezoidal wing is manufactured, and a wind test is carried out in a wind tunnel using this model to obtain the aerodynamic load of the aircraft under the rigid shape by measuring Then, a rigid digital model identical to the wind tunnel model is established, and the flow field around the digital model is discretized by mesh. The discretized mesh is numerically calculated using the finite volume method (CFD method) to obtain the aerodynamic load of the aircraft under the rigid shape. .

[0065] Secondly, the difference in aerodynamic load change is calculated based on the aerodynamic load of the rigid shape experimental data and the aerodynamic load based on the rigid numerical calculation. Then a full-scale elastic model is established, and the surrounding flow field is discretized using a structural grid to obtain a discrete grid and a surface grid of the discrete grid. The surface grid is as follows: Figure 3 As shown, the finite volume method (CFD method) is finally used to calculate the current surface aerodynamic load of the elastic model.

[0066] Then, a structural finite element model of the elastic model is established, and the digital model is discretized using tetrahedral elements to generate a structural finite element mesh and its surface mesh. The surface mesh after discretization is as follows: Figure 4 Then, the mapping relationship between the flow field surface grid and the structure surface grid is established. According to the mapping relationship, the current surface aerodynamic load of the calculated elastic model is mapped to the structure surface to obtain the aerodynamic load. The mapping relationship is as follows: Figure 5 Then, the surface displacement of the elastic model of the structure under the aerodynamic load is calculated based on the structural finite element mesh and its surface mesh.

[0067] Then the displacement of the elastic model surface is mapped to the flow field mesh surface to obtain the displacement of the flow field surface mesh. The specific mapping relationship is as follows: Figure 6 Then, the displacement of the flow field surface grid needs to be corrected using the difference in aerodynamic load changes to obtain the corrected displacement of the elastic model numerical simulation.

[0068] Finally, it is determined whether the displacement between two adjacent calculations is less than a certain threshold. If so, it is determined to be converged and the process ends. If not, it is necessary to use the corrected displacement corresponding to the current calculation to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, and jump back to the step of building a finite element model until it is determined that the displacement between two adjacent calculations is less than a certain threshold, that is, the calculation result converges. The convergence curve of the static aeroelastic calculation of the trapezoidal wing is as follows: Figure 7 shown.

[0069] It can be seen that the present application corrects the displacement by the displacement difference corresponding to the experimental results and the numerical results under the rigid shape, so as to correct the error caused by the aerodynamic displacement calculation in the numerical simulation process, thereby greatly reducing the error of the static aeroelastic coupling simulation and improving the accuracy of the simulation results.

[0070] See also Figure 8 As shown, the embodiment of the present invention discloses a static aeroelastic coupling simulation device based on displacement difference, comprising:

[0071] an aerodynamic load difference determination module 11, for obtaining a first aerodynamic load of the aircraft under a rigid shape based on experimental data and a second aerodynamic load of the aircraft under a rigid shape based on data simulation calculation, and determining an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load;

[0072] an aerodynamic load determination module 12, for determining the current surface aerodynamic load of the elastic model corresponding to the aircraft, constructing a structural finite element model of the elastic model, so as to determine a structural finite element mesh and a structural surface mesh based on the structural finite element model, and mapping the current surface aerodynamic load to the structural surface mesh to obtain the structural surface aerodynamic load;

[0073] A judgment module 13 is used to determine a target displacement of a flow field mesh surface based on the aerodynamic load on the structure surface, the structural finite element mesh and the structure surface mesh, correct the target displacement using the aerodynamic load difference to obtain a corrected displacement, and judge whether a difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold;

[0074] The jump module 14 is used to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft using the corrected displacement corresponding to the current calculation, and jump again to the step of constructing the structural finite element model of the elastic model until the difference is less than the preset threshold value, and determine that the static aeroelastic coupling simulation calculation result of the aircraft converges.

[0075] The present application first obtains a first aerodynamic load of an aircraft under a rigid shape based on experimental data and a second aerodynamic load of an aircraft under a rigid shape based on data simulation calculation, and determines the aerodynamic load difference between the first aerodynamic load and the second aerodynamic load; then determines the current surface aerodynamic load of the elastic model corresponding to the aircraft, and constructs a structural finite element model of the elastic model, so as to determine a structural finite element grid and a structural surface grid based on the structural finite element model, and maps the current surface aerodynamic load to the structural surface grid to obtain a structural surface aerodynamic load; then determines a target displacement of the flow field grid surface based on the structural surface aerodynamic load, the structural finite element grid and the structural surface grid, corrects the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determines whether the difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold; finally, if not, determines the current surface aerodynamic load of the elastic model corresponding to the aircraft using the corrected displacement corresponding to the current calculation, and jumps back to the step of constructing the structural finite element model of the elastic model until the difference is less than the preset threshold, and determines that the static aeroelastic coupling simulation calculation result of the aircraft converges. It can be seen that the present application corrects the displacement by the displacement difference corresponding to the experimental results and the numerical results under the rigid shape, so as to correct the error caused by the aerodynamic displacement calculation in the numerical simulation process, thereby greatly reducing the error of the static aeroelastic coupling simulation and improving the accuracy of the simulation results.

[0076] In some specific embodiments, the aerodynamic load difference determination module 11 may specifically include:

[0077] a first aerodynamic load acquisition unit, configured to construct a rigid scaled model of the aircraft according to the size of the aircraft and the wind tunnel performance, and to perform a wind blowing test on the rigid scaled model in a wind tunnel, so as to obtain a first aerodynamic load of the aircraft under a rigid shape based on the experimental data by measurement;

[0078] The second aerodynamic load acquisition unit is used to build a rigid data model based on the wind tunnel model of the aircraft, discretize the flow field corresponding to the rigid data model, obtain the discretized grid, and perform numerical calculation on the discretized grid through computational fluid dynamics method to obtain the second aerodynamic load of the aircraft under the rigid shape calculated based on data simulation.

[0079] In some specific embodiments, the aerodynamic load determination module 12 may specifically include:

[0080] The structure surface aerodynamic load acquisition unit is used to determine a first mapping relationship between the flow field grid surface and the structure surface grid, and map the current surface aerodynamic load to the structure surface grid according to the first mapping relationship to obtain the structure surface aerodynamic load.

[0081] In some specific embodiments, the determination module 13 may specifically include:

[0082] A surface displacement calculation unit, used for calculating the surface displacement of the elastic model under the action of the aerodynamic load on the surface of the structure by a computational structural dynamics method based on the structural finite element mesh and the structural surface mesh;

[0083] The target displacement acquisition unit is used to determine a second mapping relationship between the structure surface grid and the flow field grid surface, and map the surface displacement to the flow field grid surface based on the second mapping relationship to obtain a target displacement of the flow field grid surface.

[0084] In some specific embodiments, the determination module 13 may specifically include:

[0085] a ratio determination unit, used to determine the ratio of the aerodynamic load difference to the stiffness matrix;

[0086] The corrected displacement determining unit is used to determine the sum of the ratio and the target displacement as the corrected displacement.

[0087] In some specific embodiments, the jump module 14 may specifically include:

[0088] The current surface aerodynamic load determination unit is used to update the grid corresponding to the elastic model using the corrected displacement corresponding to the current calculation, and determine the current surface aerodynamic load of the elastic model corresponding to the aircraft based on the corresponding updated grid.

[0089] In some specific embodiments, the device may further include:

[0090] The judgment result execution module is used to directly judge that the static aeroelastic coupling simulation calculation result of the aircraft has converged if the difference between the corrected displacements corresponding to two adjacent calculations is less than the preset threshold.

[0091] Furthermore, the present application also discloses an electronic device. Fig. 9 This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content in the diagram cannot be regarded as any limitation on the scope of use of the present application.

[0092] Fig. 9A schematic diagram of the structure of an electronic device 20 provided in an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the static aeroelastic coupling simulation method based on displacement difference disclosed in any of the aforementioned embodiments. In addition, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0093] In this embodiment, the power supply 23 is used to provide working voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs and is not specifically limited here.

[0094] In addition, the memory 22 as a carrier for storing resources may be a read-only memory, a random access memory, a disk or an optical disk, etc. The resources stored thereon may include an operating system 221, a computer program 222, etc., and the storage method may be temporary storage or permanent storage.

[0095] The operating system 221 is used to manage and control the hardware devices and computer program 222 on the electronic device 20, and may be Windows Server, Netware, Unix, Linux, etc. In addition to the computer program that can be used to complete the static aeroelastic coupling simulation method based on displacement difference performed by the electronic device 20 disclosed in any of the aforementioned embodiments, the computer program 222 may further include computer programs that can be used to complete other specific tasks.

[0096] Furthermore, the present application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the static aeroelastic coupling simulation method based on displacement difference disclosed above is implemented. For the specific steps of the method, reference may be made to the corresponding contents disclosed in the above embodiments, and no further description will be given here.

[0097] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0098] Professionals may further appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described in the above description according to function. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0099] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be implemented directly using hardware, a software module executed by a processor, or a combination of the two. The software module may be placed in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.

[0100] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0101] The technical solution provided by the present application is introduced in detail above. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. At the same time, for general technicians in this field, according to the idea of ​​the present application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. A static aeroelastic coupling simulation method based on displacement difference, characterized in that: include: Acquire a first aerodynamic load of the aircraft in a rigid shape based on experimental data and a second aerodynamic load of the aircraft in a rigid shape based on data simulation calculation, and determine an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load; Determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, construct a structural finite element model of the elastic model, so as to determine a structural finite element mesh and a structural surface mesh based on the structural finite element model, and map the current surface aerodynamic load to the structural surface mesh to obtain a structural surface aerodynamic load; Determine a target displacement of a flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh and the structure surface mesh, correct the target displacement using the aerodynamic load difference to obtain a corrected displacement, and determine whether a difference between two adjacent calculated corrected displacements is less than a preset threshold; If not, the current surface aerodynamic load of the elastic model corresponding to the aircraft is determined by using the corrected displacement corresponding to the current calculation, and the process is jumped again to the step of constructing a structural finite element model of the elastic model until the difference is less than the preset threshold value, and it is determined that the static aeroelastic coupling simulation calculation result of the aircraft converges; The method of correcting the target displacement by using the aerodynamic load difference to obtain a corrected displacement includes: determining a ratio of the aerodynamic load differential to a stiffness matrix; The sum of the ratio and the target displacement is determined as the corrected displacement.

2. The static-aeroelastic coupling simulation method based on displacement difference according to claim 1 is characterized in that: The method of obtaining a first aerodynamic load of the aircraft under a rigid shape based on experimental data and a second aerodynamic load of the aircraft under a rigid shape based on data simulation calculation includes: constructing a rigid scaled model of the aircraft according to the size of the aircraft and the wind tunnel performance, and performing a wind blowing test on the rigid scaled model in a wind tunnel, so as to obtain a first aerodynamic load of the aircraft under a rigid shape based on experimental data by measurement; A rigid data model is constructed based on the wind tunnel model of the aircraft, the flow field corresponding to the rigid data model is discretized by grid, the discretized grid is obtained, and the discretized grid is numerically calculated by computational fluid dynamics method to obtain the second aerodynamic load of the aircraft under the rigid shape calculated based on data simulation.

3. The static-aeroelastic coupling simulation method based on displacement difference according to claim 1 is characterized in that: Mapping the current surface aerodynamic load to the structure surface grid to obtain the structure surface aerodynamic load includes: A first mapping relationship between the flow field mesh surface and the structure surface mesh is determined, and a current surface aerodynamic load is mapped to the structure surface mesh according to the first mapping relationship to obtain the structure surface aerodynamic load.

4. The static aeroelastic coupling simulation method based on displacement difference according to claim 1 is characterized in that: The step of determining the target displacement of the flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh and the structure surface mesh comprises: Calculating the surface displacement of the elastic model under the action of the aerodynamic load on the surface of the structure by a computational structural dynamics method based on the structural finite element mesh and the structural surface mesh; A second mapping relationship between the structure surface mesh and the flow field mesh surface is determined, and the surface displacement is mapped to the flow field mesh surface based on the second mapping relationship to obtain a target displacement of the flow field mesh surface.

5. The static-aeroelastic coupling simulation method based on displacement difference according to claim 1 is characterized in that: The method of determining the current surface aerodynamic load of the elastic model corresponding to the aircraft by using the corrected displacement corresponding to the current calculation includes: The grid corresponding to the elastic model is updated using the corrected displacement corresponding to the current calculation, and the current surface aerodynamic load of the elastic model corresponding to the aircraft is determined based on the corresponding updated grid.

6. The static-aeroelastic coupling simulation method based on displacement difference according to any one of claims 1 to 5, characterized in that: After determining whether the difference between the corrected displacements corresponding to two consecutive calculations is less than a preset threshold, the method further includes: If the difference between the corrected displacements corresponding to two adjacent calculations is less than the preset threshold, it is directly determined that the static aeroelastic coupling simulation calculation result of the aircraft is converged.

7. A static aeroelastic coupling simulation device based on displacement difference, characterized in that: include: an aerodynamic load difference determination module, used to obtain a first aerodynamic load of the aircraft under a rigid shape based on experimental data and a second aerodynamic load of the aircraft under a rigid shape based on data simulation calculation, and determine an aerodynamic load difference between the first aerodynamic load and the second aerodynamic load; an aerodynamic load determination module, used to determine the current surface aerodynamic load of the elastic model corresponding to the aircraft, construct a structural finite element model of the elastic model, so as to determine a structural finite element mesh and a structural surface mesh based on the structural finite element model, and map the current surface aerodynamic load to the structural surface mesh to obtain the structural surface aerodynamic load; a judgment module, configured to determine a target displacement of a flow field mesh surface based on the aerodynamic load on the structure surface, the structure finite element mesh, and the structure surface mesh, to correct the target displacement using the aerodynamic load difference to obtain a corrected displacement, and to judge whether a difference between the corrected displacements corresponding to two adjacent calculations is less than a preset threshold; A jump module, for determining the current surface aerodynamic load of the elastic model corresponding to the aircraft by using the corrected displacement corresponding to the current calculation, and re-jumping to the step of constructing the structural finite element model of the elastic model, until the difference is less than the preset threshold value, and determining that the static aeroelastic coupling simulation calculation result of the aircraft converges; The judging module comprises: a ratio determination unit, used to determine the ratio of the aerodynamic load difference to the stiffness matrix; The corrected displacement determining unit is used to determine the sum of the ratio and the target displacement as the corrected displacement.

8. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the static aeroelastic coupling simulation method based on displacement difference as described in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that: Used to store a computer program, wherein when the computer program is executed by a processor, the static aeroelastic coupling simulation method based on displacement difference according to any one of claims 1 to 6 is implemented.

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