CN113821963B - Compression buckling test method and equipment for laser welding wallboard structure - Google Patents
Compression buckling test method and equipment for laser welding wallboard structure Download PDFInfo
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- CN113821963B CN113821963B CN202111403904.5A CN202111403904A CN113821963B CN 113821963 B CN113821963 B CN 113821963B CN 202111403904 A CN202111403904 A CN 202111403904A CN 113821963 B CN113821963 B CN 113821963B
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Abstract
The invention provides a compression buckling test method and equipment for a laser welding wallboard structure, which comprises the following steps: constructing a first shell-solid model of a laser welded wallboard structure; dividing unit grids on the first shell-solid model, and applying elastic-plastic parameters of the material to the corresponding unit grids to obtain a second shell-solid model; setting displacement boundary conditions and a load application mode for the second shell-entity model, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; copying a second shell-entity model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-entity model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain the data information of the reaction force, the strain and the displacement in the compression buckling process of the wall plate structure. The invention can quantitatively research the compressive failure load, strain and displacement of the laser welding wall plate structure.
Description
Technical Field
The embodiment of the invention relates to the technical field of wallboard structure strength, in particular to a compression buckling test method and equipment for a laser welding wallboard structure.
Background
The development trend of future civil aircrafts is green, efficient and rapid, and compared with the traditional civil aircrafts, the requirements of the future civil aircrafts on weight reduction and emission reduction are more severe, so that the selection of lighter aircraft structural materials and a more reasonable structural connection form to realize the light weight of the aircrafts is more important. The double-side laser synchronous welding technology has become a great trend to replace the traditional riveting process, but the laser welding technology is still in a technical blank state in the related field, and particularly the compression and buckling performance test for the laser synchronous welding wall plate structure is basically zero. Therefore, it is an urgent technical problem in the art to develop a method and apparatus for testing compression buckling of a laser welded wall panel structure, which can effectively fill up the technical gap in the related art.
Disclosure of Invention
In view of the above problems in the prior art, embodiments of the present invention provide a method and an apparatus for testing compression buckling of a laser welded wall panel structure.
In a first aspect, embodiments of the present invention provide a method of compressive buckling testing for laser welded wall panel structures, comprising: constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; dividing a welding seam solid unit grid, a skin shell unit grid, a stringer shell unit grid, a frame shell unit grid and a fillet shell unit grid of a wallboard on the first shell-solid model, and applying elastic parameters and plastic parameters of materials to the corresponding unit grids to obtain a second shell-solid model; setting displacement boundary conditions and a load application mode for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; copying a second shell-entity model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-entity model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain the data information of the reaction force, the strain and the displacement in the compression buckling process of the wall plate structure.
On the basis of the content of the embodiment of the method, the method for testing the compression buckling of the laser welding wallboard structure provided by the embodiment of the invention comprises the following steps of dividing a welding seam solid unit grid, a skin shell unit grid, a stringer shell unit grid, a frame shell unit grid and a corner piece shell unit grid of a wallboard on a first shell-solid model: the solid unit grids are divided into eight-node and hexahedral solid units, and the skin shell unit grids, the long truss shell unit grids, the frame shell unit grids and the corner piece shell unit grids are divided into four-node and quadrilateral shell units; wherein the skin, stringers, frame and gussets are shell faces, and the webs of the stringers are located on the centerline of the cross-section of the weld.
On the basis of the content of the above method embodiment, the method for testing compression buckling of a laser welded wall panel structure provided in the embodiment of the present invention includes the following steps: the modulus of elasticity and the poisson's ratio of the material.
On the basis of the content of the above method embodiment, the compression buckling test method for the laser welding wall plate structure provided in the embodiment of the present invention includes that the plastic parameters of the material include:
wherein the content of the first and second substances,
is the true stress of the material and is,
is the engineering stress of the material and is,
is the engineering strain of the material.
On the basis of the content of the above method embodiment, the method for testing compression buckling of a laser welded wall panel structure provided in the embodiment of the present invention further includes:
wherein the content of the first and second substances,
is the true strain of the material.
On the basis of the content of the above method embodiment, the method for testing compression buckling of a laser welded wall panel structure provided in the embodiment of the present invention further includes:
wherein the content of the first and second substances,
is the true plastic strain of the material and,
is the true elastic strain of the material and E is the modulus of elasticity.
On the basis of the content of the above method embodiments, the method for testing compressive buckling of a laser welded wall panel structure provided in the embodiments of the present invention includes:
wherein the content of the first and second substances,
is the compressive residual stress of the material and,
is the peak value of the compressive residual stress of the material,
the peak value of tensile residual stress of the material, b the total width of the skin,
is the width of the tensile residual stress region of the material.
In a second aspect, embodiments of the present invention provide a compression buckling test apparatus for laser welded wall panel structures, comprising: the first main module is used for constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; the second main module is used for dividing the welding seam solid unit grids, the skin shell unit grids, the stringer shell unit grids, the frame shell unit grids and the corner piece shell unit grids of the wallboard on the first shell-solid model, and applying the elastic parameters and the plastic parameters of the materials to the corresponding unit grids to obtain a second shell-solid model; the third main module is used for setting displacement boundary conditions and load application modes for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; and the fourth main module is used for copying the second shell-solid model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-solid model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain the data information of the reaction force, the strain and the displacement in the compression buckling process of the wall plate structure.
In a third aspect, an embodiment of the present invention provides an electronic device, including:
at least one processor; and
at least one memory communicatively coupled to the processor, wherein:
the memory stores program instructions executable by the processor to invoke the program instructions to perform the method of compressive buckling testing for laser welded wall panel structures provided in any of the various implementations of the first aspect.
In a fourth aspect, embodiments of the invention provide a non-transitory computer readable storage medium storing computer instructions for causing a computer to perform a method of compressive buckling testing for laser welded wall panel structures as provided in any of the various implementations of the first aspect.
According to the method and the device for testing the compressive buckling of the laser welding wallboard structure, provided by the embodiment of the invention, the first shell-solid model of the laser welding wallboard structure is constructed, the unit grid and the parameters are loaded to obtain the second shell-solid model, the compressive buckling mode is obtained according to the second shell-solid model, the second shell-solid model is copied, the nonlinear buckling equation is solved to obtain the reaction force, strain and displacement data information in the compressive buckling process of the wallboard structure, the rapid modeling of the wallboard structures with different structure sizes in different laser welding states can be realized, the failure load is obtained through the extracted load-displacement curve of the wallboard structure, the in-plane strain information and the out-plane displacement information of the wallboard structure can be obtained, and the quantitative research on the compressive failure load, strain and displacement of the laser welding wallboard structure is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, a brief description will be given below to the drawings required for the description of the embodiments or the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a flowchart of a method for testing compression buckling of a laser welded wall panel structure according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of a compression buckling testing apparatus for a laser welded wall panel structure according to an embodiment of the present invention;
fig. 3 is a schematic physical structure diagram of an electronic device according to an embodiment of the present invention;
FIG. 4 is a schematic view of a geometric model of a laser welded wall panel structure according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the structure dimensions and the position of a strain gauge for laser welding according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a grid model of a laser welded wall panel structure provided by an embodiment of the present invention;
FIG. 7 is a schematic view of a compression test of a laser welded wall panel structure and load and displacement curves of a finite element model according to an embodiment of the present invention;
FIG. 8 is a graph of a compression test and strain versus effect of a finite element model of a laser welded wall panel structure at a skin location provided by an embodiment of the present invention;
FIG. 9 is a schematic illustration of the out-of-plane displacement effect of a test and finite element model for a laser welded wallboard structure when a failure load is reached, according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. In addition, technical features of various embodiments or individual embodiments provided by the present invention may be arbitrarily combined with each other to form a feasible technical solution, and such combination is not limited by the sequence of steps and/or the structural composition mode, but must be realized by a person skilled in the art, and when the technical solution combination is contradictory or cannot be realized, such a technical solution combination should not be considered to exist and is not within the protection scope of the present invention.
The embodiment of the invention provides a compression buckling test method for a laser welding wall plate structure, and with reference to fig. 1, the method comprises the following steps: constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; dividing a welding seam solid unit grid, a skin shell unit grid, a stringer shell unit grid, a frame shell unit grid and a fillet shell unit grid of a wallboard on the first shell-solid model, and applying elastic parameters and plastic parameters of materials to the corresponding unit grids to obtain a second shell-solid model; setting displacement boundary conditions and a load application mode for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; copying a second shell-entity model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-entity model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain the data information of the reaction force, the strain and the displacement in the compression buckling process of the wall plate structure.
Specifically, the boundary condition is a position constraint condition, and the actual clamping condition is simulated by constraining the degree of freedom in the X, Y, Z axis direction. The load loading mode is realized by adopting the side load or displacement control of the shell. The defect size was obtained by deformation measurement of the laser welded wallboard structure and entered into the model by the keyword statement of finite element software.
Based on the content of the foregoing method embodiment, as an optional embodiment, the method for testing compression buckling of a laser welded wallboard structure provided in the embodiment of the present invention includes, dividing a weld solid unit mesh, a skin shell unit mesh, a stringer shell unit mesh, a frame shell unit mesh, and a fillet shell unit mesh of a wallboard on a first shell-solid model, including: the solid unit grids are divided into eight-node and hexahedral solid units, and the skin shell unit grids, the long truss shell unit grids, the frame shell unit grids and the corner piece shell unit grids are divided into four-node and quadrilateral shell units; wherein the skin, stringers, frame and gussets are shell faces, and the webs of the stringers are located on the centerline of the cross-section of the weld.
Based on the content of the above method embodiment, as an alternative embodiment, the method for testing compression buckling of a laser welded wall plate structure provided in the embodiment of the present invention includes: the modulus of elasticity and the poisson's ratio of the material.
Based on the content of the above method embodiment, as an alternative embodiment, the method for testing compression buckling of a laser welded wall plate structure provided in the embodiment of the present invention includes:
wherein the content of the first and second substances,
is the true stress of the material and is,
is the engineering stress of the material and is,
is the engineering strain of the material.
Based on the content of the above method embodiment, as an alternative embodiment, the method for testing compression buckling of a laser welded wall plate structure provided in the embodiment of the present invention further includes:
wherein the content of the first and second substances,
is the true strain of the material.
Based on the content of the above method embodiment, as an alternative embodiment, the method for testing compression buckling of a laser welded wall plate structure provided in the embodiment of the present invention further includes:
wherein the content of the first and second substances,
is the true plastic strain of the material and,
is the true elastic strain of the material and E is the modulus of elasticity.
Based on the content of the above method embodiment, as an alternative embodiment, the method for testing compressive buckling of a laser welded wall plate structure provided in the embodiment of the present invention includes:
wherein the content of the first and second substances,
is the compressive residual stress of the material and,
is the peak value of the compressive residual stress of the material,
the peak value of tensile residual stress of the material, b the total width of the skin,
is the width of the tensile residual stress region of the material.
According to the compressive buckling test method for the laser welding wallboard structure, provided by the embodiment of the invention, the first shell-solid model of the laser welding wallboard structure is constructed, the unit grid and the parameters are loaded to obtain the second shell-solid model, the compressive buckling mode is obtained according to the second shell-solid model, the second shell-solid model is copied, the nonlinear buckling equation is solved to obtain the reaction force, strain and displacement data information in the compressive buckling process of the wallboard structure, the rapid modeling of the wallboard structures with different structure sizes in different laser welding states can be realized, the failure load is obtained through the extracted load-displacement curve of the wallboard structure, the in-plane strain information and the out-of-plane displacement information of the wallboard structure can be obtained, and the quantitative research on the compressive failure load, strain and displacement of the laser welding wallboard structure is realized.
The specific flow of the compression buckling test method for the laser welding wall plate structure provided by the embodiment of the invention is as follows: referring to a compression process schematic diagram shown in fig. 4, a compression buckling simulation example of a shell-solid coupling unit model of a wallboard structure composed of a skin and a stringer with a thickness of 2mm, a frame with a thickness of 1.27mm and corner pieces is adopted, a finite element calculation result and a test result are compared and analyzed, and a complete process (load/displacement is shown in an arrow direction in fig. 4) of the invention is explained in detail, wherein fig. 4 comprises a wallboard end face a, a free end B, a clamping end C and a free end D. The dimensions of the laser welded panel structure shown in fig. 5 were used to create a corresponding shell-solid geometric model, as shown in fig. 4. On the basis of the geometric model, a shell-solid coupling unit grid model of the laser welding wall plate structure is established, wherein the grid model is shown as figure 6, welding seams 8 are three-dimensional solid unit grids, and the rest parts are two-dimensional shell unit grids (such as stringers 7 and skin 6). On the basis of the grid model, a shell-entity coupling unit finite element model of a laser welding wall plate structure is established, elastic-plastic parameters of materials are respectively input into the model, position constraint conditions and a load loading mode are respectively input into the model, an analysis step of characteristic value buckling solution of the finite element model is established, and a characteristic value and a critical buckling load are solved.
Then, selecting a proper buckling mode and a corresponding characteristic value as initial conditions of nonlinear buckling solution, substituting defect size and residual stress into the model as initial conditions, substituting a load value slightly larger than critical buckling load into the model as a load loading mode, establishing an analysis step of nonlinear buckling solution of the finite element model, and solving reaction force, strain and displacement of the wallboard structure, wherein the positions of strain data are as shown in fig. 5, close to skin positions E1 to E3 near a stringer E, a stringer F, a stringer G and a stringer H, skin positions F1 to F3, skin positions G1 to G3, skin positions H1 to H3, and front and back equidistant distribution positions X1 to X3 between two frames and two adjacent stringers, the front and back distribution positions X1 'to X3', the front and back equidistant distribution positions Y1 to Y3 of the skin, The front and back equidistant distribution positions Y1 'to Y3' of the skin, the front and back equidistant distribution positions Z1 to Z3 of the skin, and the front and back equidistant distribution positions Z1 'to Z3' of the skin. The laser welding wallboard structure also comprises a corner piece 1, a frame 2, a stringer 3, a skin 4 and a frame 5 filled with epoxy resin.
And finally, extracting the reaction force, displacement and strain data information of the wallboard structure, and comparing and analyzing the reaction force, displacement and strain data information with the data result obtained by the test. Specifically, the test results are compared to the load, in-plane strain and out-of-plane displacement data of the finite element simulation results. Fig. 7 is a comparison of the compressive load and displacement curves for the test and finite element models (i.e., simulations) with initial buckling loads of 94.50kN and 107.90kN, respectively, with a 14% error, and failure loads of 227.50kN and 234.35kN, respectively, with a 3% error, wherein the test results present a break point for the loads where the rivet connecting the frame and the horn broke, while the finite element model did not take into account the fracture behavior of the rivet. Fig. 8 is a result of a compression test of the laser welded panel structure at the front-to-back equidistant positions Y1 to Y3 (the front-to-back equidistant positions Y1 'to Y3') of the skin and the positions E1 to E3 of the skin and a strain comparison of a finite element model, where the strains of the test and the finite element model are each split up when the initial buckling load is reached and the maximum tensile strain perpendicular to the stringer direction is present at the position E3 of the skin near the stringer E when the failure load is reached. Specifically, the upper left graph in fig. 8 is the strain obtained by the test of the skin positions Y1 to Y3(Y1 'to Y3'), the upper right graph is the strain obtained by the finite element model of the skin positions Y1 to Y3(Y1 'to Y3'), the lower left graph is the strain obtained by the test of the skin positions E1 to E3, and the lower right graph is the strain obtained by the finite element model of the skin positions E1 to E3. FIG. 9 is a comparison of the out-of-plane displacement of the test and finite element models for a laser welded panel structure at failure loads, with the same number of relief patterns on the skin between adjacent stringers, and with the largest out-of-plane deformation of the flanges of stringer E in all stringers occurring along the Y-axis negative direction. According to the load, strain and displacement data, the test result verifies the accuracy and effectiveness of the compression buckling finite element model of the laser welding wall plate structure of the shell-entity coupling unit. Specifically, the left half of fig. 9 is the out-of-plane displacement data obtained by the fringe projection profilometry means under test, and the right half is the out-of-plane displacement data obtained by the finite element model.
The implementation basis of the various embodiments of the present invention is realized by programmed processing performed by a device having a processor function. Therefore, in engineering practice, the technical solutions and functions thereof of the embodiments of the present invention can be packaged into various modules. Based on this reality, on the basis of the above embodiments, embodiments of the present invention provide a compression buckling testing apparatus for laser welded wall panel structures, which is used to perform the compression buckling testing method for laser welded wall panel structures in the above method embodiments. Referring to fig. 2, the apparatus includes: the first main module is used for constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; the second main module is used for dividing the welding seam solid unit grids, the skin shell unit grids, the stringer shell unit grids, the frame shell unit grids and the corner piece shell unit grids of the wallboard on the first shell-solid model, and applying the elastic parameters and the plastic parameters of the materials to the corresponding unit grids to obtain a second shell-solid model; the third main module is used for setting displacement boundary conditions and load application modes for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; and the fourth main module is used for copying the second shell-solid model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-solid model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain the data information of the reaction force, the strain and the displacement in the compression buckling process of the wall plate structure.
The compression buckling testing device for the laser welding wallboard structure provided by the embodiment of the invention adopts a plurality of modules in figure 2, a second shell solid model is obtained by constructing a first shell-solid model of a laser welded wallboard structure and loading the unit grids and parameters, obtaining a compression buckling mode according to the second shell-solid model, copying the second shell-solid model, solving a nonlinear buckling equation to obtain data information of reaction force, strain and displacement in the compression buckling process of the wall plate structure, the rapid modeling of wallboard structures with different structure sizes under different laser welding states can be realized, the failure load is obtained through the extracted load-displacement curve of the wallboard structure, and the in-plane strain information and the out-of-plane displacement information of the wallboard structure can be obtained, so that quantitative research on the compressive failure load, the strain and the displacement of the laser welding wallboard structure is realized.
It should be noted that, the apparatus in the apparatus embodiment provided by the present invention may be used for implementing methods in other method embodiments provided by the present invention, except that corresponding function modules are provided, and the principle of the apparatus embodiment provided by the present invention is basically the same as that of the apparatus embodiment provided by the present invention, so long as a person skilled in the art obtains corresponding technical means by combining technical features on the basis of the apparatus embodiment described above, and obtains a technical solution formed by these technical means, on the premise of ensuring that the technical solution has practicability, the apparatus in the apparatus embodiment described above may be modified, so as to obtain a corresponding apparatus class embodiment, which is used for implementing methods in other method class embodiments. For example:
based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a first sub-module for implementing the weld solid cell grid, skin shell cell grid, stringer shell cell grid, frame shell cell grid and fillet shell cell grid of the panel partitioning on the first shell-solid model, comprising: the solid unit grids are divided into eight-node and hexahedral solid units, and the skin shell unit grids, the long truss shell unit grids, the frame shell unit grids and the corner piece shell unit grids are divided into four-node and quadrilateral shell units; wherein the skin, stringers, frame and gussets are shell faces, and the webs of the stringers are located on the centerline of the cross-section of the weld.
Based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a second submodule for implementing elastic parameters of said material, comprising: the modulus of elasticity and the poisson's ratio of the material.
Based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a third submodule for implementing plastic parameters of the material, comprising:
wherein the content of the first and second substances,
is the true stress of the material and is,
is the engineering stress of the material and is,
is the engineering strain of the material.
Based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a fourth submodule for implementing a plasticity parameter of the material, further comprising:
wherein the content of the first and second substances,
is the true strain of the material.
Based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a fifth submodule for implementing the plasticity parameters of the material, further comprising:
wherein the content of the first and second substances,
is the true plastic strain of the material and,
is the true elastic strain of the material and E is the modulus of elasticity.
Based on the content of the above device embodiment, as an alternative embodiment, the compression buckling testing device for laser welding wall plate structure provided in the embodiment of the present invention further includes: a sixth submodule, configured to implement the residual stress, comprising:
wherein the content of the first and second substances,
is the compressive residual stress of the material and,
is the peak value of the compressive residual stress of the material,
the peak value of tensile residual stress of the material, b the total width of the skin,
is the width of the tensile residual stress region of the material.
The method of the embodiment of the invention is realized by depending on the electronic equipment, so that the related electronic equipment is necessarily introduced. To this end, an embodiment of the present invention provides an electronic apparatus, as shown in fig. 3, including: the system comprises at least one processor (processor), a communication Interface (communication Interface), at least one memory (memory) and a communication bus, wherein the at least one processor, the communication Interface and the at least one memory are communicated with each other through the communication bus. The at least one processor may invoke logic instructions in the at least one memory to perform all or a portion of the steps of the methods provided by the various method embodiments described above.
In addition, the logic instructions in the at least one memory may be implemented in software functional units and stored in a computer readable storage medium when sold or used as a stand-alone product. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the method embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present invention. Based on this recognition, each block in the flowchart or block diagrams may represent a module, a program segment, or a portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In this patent, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. A method of compression buckling testing for laser welded wall panel structures, comprising: constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; dividing a welding seam solid unit grid, a skin shell unit grid, a stringer shell unit grid, a frame shell unit grid and a fillet shell unit grid of a wallboard on the first shell-solid model, and applying elastic parameters and plastic parameters of materials to the corresponding unit grids to obtain a second shell-solid model; setting displacement boundary conditions and a load application mode for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; copying a second shell-entity model, inputting a compression buckling mode, a defect size and residual stress into the second shell-entity model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain data information of reaction force, strain and displacement in the compression buckling process of the wall plate structure; the residual stress includes:
wherein the content of the first and second substances,
is the compressive residual stress of the material and,
is the peak value of the compressive residual stress of the material,
the peak value of tensile residual stress of the material, b the total width of the skin,
is the width of the tensile residual stress region of the material.
2. The method of claim 1 for compression buckling testing of laser welded wall panel structures, wherein dividing the welded solid cell lattice, skin shell cell lattice, stringer shell cell lattice, frame shell cell lattice and fillet shell cell lattice of a wall panel on a first shell-solid model comprises: the solid unit grids are divided into eight-node and hexahedral solid units, and the skin shell unit grids, the long truss shell unit grids, the frame shell unit grids and the corner piece shell unit grids are divided into four-node and quadrilateral shell units; wherein the skin, stringers, frame and gussets are shell faces, and the webs of the stringers are located on the centerline of the cross-section of the weld.
3. The method of claim 2 wherein the elastic parameters of the material include: the modulus of elasticity and the poisson's ratio of the material.
4. The method of claim 3 for compression buckling testing of laser welded wall panel structures, wherein the plastic parameters of the material include:
wherein the content of the first and second substances,
is the true stress of the material and is,
is the engineering stress of the material and is,
is the engineering strain of the material.
5. The method of claim 4 for compression buckling testing of laser welded wall panel structures, wherein the plastic parameters of the material further comprise:
wherein the content of the first and second substances,
is the true strain of the material.
6. The method of claim 5 for compression buckling testing of laser welded wall panel structures, wherein the plastic parameters of the material further comprise:
wherein the content of the first and second substances,
is the true plastic strain of the material and,
is the true elastic strain of the material and E is the modulus of elasticity.
7. A compression buckling testing device for laser welded wall panel structures, comprising: the first main module is used for constructing a first shell-solid model of the laser welding wallboard structure according to the structural size of the laser welding wallboard; the second main module is used for dividing the welding seam solid unit grids, the skin shell unit grids, the stringer shell unit grids, the frame shell unit grids and the corner piece shell unit grids of the wallboard on the first shell-solid model, and applying the elastic parameters and the plastic parameters of the materials to the corresponding unit grids to obtain a second shell-solid model; the third main module is used for setting displacement boundary conditions and load application modes for the second shell-entity model, setting a buckling type analysis step, solving a characteristic value buckling equation, and calculating a characteristic value and a critical buckling load to obtain a compression buckling mode; the fourth main module is used for copying the second shell-solid model, inputting the compression buckling mode, the defect size and the residual stress into the second shell-solid model, setting RIKS analysis steps and historical output variables, and solving a nonlinear buckling equation to obtain data information of reaction force, strain and displacement in the compression buckling process of the wall plate structure; the residual stress includes:
wherein the content of the first and second substances,
is the compressive residual stress of the material and,
is the peak value of the compressive residual stress of the material,
the peak value of tensile residual stress of the material, b the total width of the skin,
is the width of the tensile residual stress region of the material.
8. An electronic device, comprising:
at least one processor, at least one memory, and a communication interface; wherein the content of the first and second substances,
the processor, the memory and the communication interface are communicated with each other;
the memory stores program instructions executable by the processor, the processor invoking the program instructions to perform the method of any of claims 1 to 6.
9. A non-transitory computer-readable storage medium storing computer instructions for causing a computer to perform the method of any one of claims 1 to 6.
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| Publication number | Priority date | Publication date | Assignee | Title |
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Non-Patent Citations (3)
| Title |
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| 《基于压磁磁场的深海管线钢疲劳损伤监测与评估方法研究》;顾益斌;《中国优秀博硕士学位论文全文数据库(博士)工程科技Ⅰ辑》;20210515;正文第104页 * |
| 《机身新型焊接加筋壁板压缩失稳载荷预估方法研究》;李振远;《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》;20170415;摘要、正文第1-46页 * |
| 李振远.《机身新型焊接加筋壁板压缩失稳载荷预估方法研究》.《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》.2017, * |
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