CN117272757A - Method and system for determining failure mechanical parameters of aluminum honeycomb material - Google Patents
Method and system for determining failure mechanical parameters of aluminum honeycomb material Download PDFInfo
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- 229910052782 aluminium Inorganic materials 0.000 title claims abstract description 373
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 title claims abstract description 373
- 239000000463 material Substances 0.000 title claims abstract description 258
- 238000000034 method Methods 0.000 title claims abstract description 43
- 238000012360 testing method Methods 0.000 claims abstract description 156
- 230000003068 static effect Effects 0.000 claims abstract description 150
- 238000006073 displacement reaction Methods 0.000 claims abstract description 148
- 238000004088 simulation Methods 0.000 claims abstract description 120
- 230000006835 compression Effects 0.000 claims abstract description 100
- 238000007906 compression Methods 0.000 claims abstract description 100
- 239000000178 monomer Substances 0.000 claims abstract description 80
- 238000011156 evaluation Methods 0.000 claims description 53
- 230000001413 cellular effect Effects 0.000 claims description 16
- 239000011148 porous material Substances 0.000 claims description 12
- 238000009864 tensile test Methods 0.000 claims description 7
- 238000012937 correction Methods 0.000 claims description 6
- 238000010586 diagram Methods 0.000 description 20
- 230000004888 barrier function Effects 0.000 description 8
- 238000012669 compression test Methods 0.000 description 8
- 238000004364 calculation method Methods 0.000 description 7
- 239000011888 foil Substances 0.000 description 5
- 239000010953 base metal Substances 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000009863 impact test Methods 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract
The invention discloses a method and a system for determining failure mechanical parameters of a honeycomb aluminum material, and relates to the technical field of honeycomb aluminum, wherein the method comprises the following steps: carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer; carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer; assigning the stress strain curve, the stress triaxial degree and the failure strain curve of the honeycomb aluminum base material to a honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading; and correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material in an iterative mode according to the test curve and the simulation curve until the iteration stop condition is met, and outputting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material. The invention improves the accuracy of determining the failure mechanical parameters of the honeycomb aluminum material.
Description
Technical Field
The invention relates to the technical field of honeycomb aluminum, in particular to a method and a system for determining failure mechanical parameters of a honeycomb aluminum material.
Background
The actual car collision experiment is generally composed of an automobile and a barrier, and the deformation of the barrier has an important influence on the experimental result. The deformable collision barrier is generally composed of honeycomb aluminum and a trolley, wherein the honeycomb aluminum is formed by rolling aluminum foils and bonding, the pore diameters of the honeycomb aluminum of different barriers are different, and the mechanical properties of the honeycomb aluminum can be realized within a certain range by changing the thickness, the pore diameter, the treatment process and other parameters of the aluminum foils. The honeycomb aluminum has the characteristics of light weight, good energy absorption and buffering capacity, simple structure and the like, and is widely applied to the deformable barrier in the automobile collision test. In the early design stage of the whole vehicle, the structure of the whole vehicle is optimized in a virtual simulation mode, and the accuracy of the honeycomb aluminum material in the simulation directly influences the accuracy of the collision simulation result.
The thickness of the honeycomb aluminum foil for the automobile collision barrier is generally between 0.05 and 0.2mm, the aluminum foil is easy to break under stress due to the thinner thickness, the force-displacement characteristic of the honeycomb aluminum foil is difficult to obtain by a traditional mechanical testing machine, and the material failure model is difficult to directly develop based on the sample piece cut out of the honeycomb aluminum material. If the material failure mechanical parameters are obtained through the honeycomb aluminum base material, the influence of the thinner thickness of the honeycomb aluminum and the processing technology on the material performance is difficult to consider, so that the failure characteristics of the honeycomb aluminum are difficult to accurately simulate in simulation. Aiming at the honeycomb aluminum barrier for automobile collision, if the parameters of the honeycomb aluminum material are not accurate enough, the accuracy of the automobile type collision simulation result is reduced.
Disclosure of Invention
The invention aims to provide a method and a system for determining failure mechanical parameters of an aluminum honeycomb material, which improve the accuracy of determining the failure mechanical parameters of the aluminum honeycomb material.
In order to achieve the above object, the present invention provides the following solutions:
a method for determining failure mechanical parameters of an aluminum honeycomb material, comprising:
carrying out a mechanical tensile test on a honeycomb aluminum base material sample of a target honeycomb aluminum material to obtain a stress strain curve of the honeycomb aluminum base material; taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material;
obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps; taking the stress triaxial degree and failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material;
carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer;
carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer;
Establishing a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material;
assigning the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
and correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material in an iterative mode according to the consistency between the static compressive force-displacement test curve and the static compressive force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stopping condition is met, and outputting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material.
Optionally, obtaining a stress triaxial degree and failure strain curve of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps specifically comprises:
carrying out mechanical stretching test on the honeycomb aluminum base material sample pieces with different gaps, and obtaining failure strain values of the honeycomb aluminum base material sample pieces through a digital image method;
Respectively establishing finite element models for the honeycomb aluminum base material sample pieces of different gaps;
performing stretching simulation according to stress-strain curves of the finite element models and the honeycomb aluminum base material samples to obtain stress triaxial of the honeycomb aluminum base material samples;
and obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material according to the failure strain value and stress triaxial degree of each honeycomb aluminum base material sample piece.
Alternatively, the static compression regime test of different stress states includes a full-width compressive stress static compression regime test and a plane shear stress static compression regime test;
the static compressive force-displacement test curves comprise a first static force-displacement test curve obtained from a full-width compressive stress static compression working condition test and a second static force-displacement test curve obtained from a planar shear stress static compression working condition test.
Optionally, according to the consistency between the static compressive force-displacement test curve and the static compressive force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve, correcting the current stress triaxial degree and the failure strain curve of the target cellular aluminum material in an iterative manner until the iteration stop condition is met, and outputting the current stress triaxial degree and the failure strain curve of the target cellular aluminum material, which specifically comprises:
Consistency evaluation is carried out on the static pressure force-displacement test curve and the static pressure force-displacement simulation curve to obtain a first consistency evaluation value;
judging whether the first consistency evaluation value is larger than a set evaluation value or not;
if the first consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the static compression force-displacement test curve and the current static compression force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model for respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
if the first consistency evaluation value is larger than the set evaluation value, carrying out consistency evaluation on the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve to obtain a second consistency evaluation value;
judging whether the second consistency evaluation value is larger than a set evaluation value or not;
if the second consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the dynamic impact force-displacement test curve and the current dynamic impact force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model for respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static stressed force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
And if the second consistency evaluation value is larger than the set evaluation value, outputting the current stress triaxial and failure strain curve of the target honeycomb aluminum material.
Alternatively, the aluminum honeycomb base material samples of the target aluminum honeycomb materials with different notches comprise an aluminum honeycomb base material sample with a notch of 5mm in radius, an aluminum honeycomb base material sample with a notch of 20mm in radius, an aluminum honeycomb base material sample with a center hole of 10mm in diameter, a 0-degree sheared aluminum honeycomb base material sample and a 45-degree sheared aluminum honeycomb base material sample.
Optionally, building a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material, which specifically comprises:
if the aperture of the honeycomb aluminum of the target honeycomb aluminum material is larger than or equal to a set value, establishing a honeycomb aluminum monomer finite element model according to the aperture size of the target honeycomb aluminum material;
if the aluminum honeycomb pore diameter of the target aluminum honeycomb material is smaller than a set value, establishing equivalent honeycomb pores of the target aluminum honeycomb material, wherein the side length L of the equivalent honeycomb pores 1 =n×l, the equivalent honeycomb holes have a thickness ofThe method comprises the steps of carrying out a first treatment on the surface of the Wherein N is a positive integer, L is the side length of the honeycomb holes of the target honeycomb aluminum material;
and building a honeycomb aluminum monomer finite element model according to the equivalent honeycomb holes.
Optionally, the set value is 40mm.
The invention also discloses a system for determining the failure mechanical parameters of the honeycomb aluminum material, which comprises the following steps:
the stress-strain curve determining module is used for carrying out a mechanical tensile test on a honeycomb aluminum base material sample of the target honeycomb aluminum material to obtain a stress-strain curve of the honeycomb aluminum base material; taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material;
the stress triaxial degree and failure strain curve determining module is used for obtaining a stress triaxial degree and failure strain curve of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps; taking the stress triaxial degree and failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material;
the static compression force-displacement test curve determining module is used for carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer;
the dynamic impact force-displacement test curve determining module is used for carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer;
The honeycomb aluminum monomer finite element model building module is used for building a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material;
the simulation curve determining module is used for assigning the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
and the stress triaxial degree and failure strain curve correction module is used for correcting the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material in an iterative mode according to the consistency between the static compression force-displacement test curve and the static compression force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stop condition is met, and outputting the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
according to the method, the stress-strain curve, the stress triaxial degree and the failure strain curve of the honeycomb aluminum base material are utilized, the stress-displacement test curve and the force-displacement simulation curve of the honeycomb aluminum monomer finite element model under different stress states of the honeycomb aluminum monomer model are combined, the stress triaxial degree and the failure strain curve are corrected, the corrected stress triaxial degree and the failure strain curve are used as the stress triaxial degree and the failure strain curve of the target honeycomb aluminum material failure, and the accuracy of the obtained stress triaxial degree and the failure strain curve of the target honeycomb aluminum material failure is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a method for determining failure mechanical parameters of an aluminum honeycomb material according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a method for determining failure mechanical parameters of an aluminum honeycomb material according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a sample of a honeycomb aluminum base material according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a stress-strain curve according to an embodiment of the present invention;
FIG. 5 is a schematic view of a notch R5 honeycomb aluminum base material sample provided in an embodiment of the present invention;
FIG. 6 is a schematic diagram of a notch R20 honeycomb aluminum base material sample provided in an embodiment of the present invention;
FIG. 7 is a schematic view of a center hole phi 10 honeycomb aluminum base material sample provided by an embodiment of the present invention;
FIG. 8 is a schematic view of a 0℃sheared honeycomb aluminum base material sample provided by an embodiment of the present invention;
FIG. 9 is a schematic diagram of a 45℃sheared honeycomb aluminum base material sample provided by an embodiment of the invention;
FIG. 10 is a graph showing stress triaxial and strain to failure of a honeycomb aluminum base material according to an embodiment of the present invention;
FIG. 11 is a 2-fold equivalent schematic diagram of a cellular aperture provided in an embodiment of the present invention;
FIG. 12 is a 3-fold equivalent schematic diagram of a cellular aperture provided by an embodiment of the present invention;
FIG. 13 is a schematic diagram of a finite element model of a honeycomb aluminum monomer according to an embodiment of the present invention;
FIG. 14 is a schematic diagram of coordinates of a finite element model of a honeycomb aluminum monomer according to an embodiment of the present invention;
FIG. 15 is a schematic diagram of static compression under full-width conditions according to an embodiment of the present invention;
FIG. 16 is a schematic view of LZ plane shear static compression provided by an embodiment of the present invention;
FIG. 17 is a schematic view of WZ plane shear static compression provided by an embodiment of the present invention;
FIG. 18 is a schematic diagram of a first static force-displacement test provided by an embodiment of the present invention;
fig. 19 is a schematic diagram of a second static force-displacement test curve obtained by an LZ plane shear static compression test according to an embodiment of the present invention;
FIG. 20 is a schematic diagram of a second static force-displacement test curve obtained by a WZ plane shear static compression test according to an embodiment of the present invention;
FIG. 21 is a schematic view of dynamic impact according to an embodiment of the present invention;
FIG. 22 is a graph showing a dynamic impact force-displacement test provided by an embodiment of the present invention;
FIG. 23 is a schematic diagram showing a comparison between a test curve and a simulation curve corresponding to a corrected full-width working condition according to an embodiment of the present invention;
FIG. 24 is a schematic diagram showing a comparison of a test curve and a simulation curve corresponding to the corrected LZ plane shear provided by the embodiment of the present invention;
FIG. 25 is a schematic diagram showing the comparison of the test curve and the simulation curve corresponding to the corrected WZ plane shear provided by the embodiment of the invention;
FIG. 26 is a schematic diagram showing the comparison of the test curves and the simulation curves corresponding to the modified dynamic impact according to the embodiment of the present invention;
FIG. 27 is a graph showing the modified stress triaxial and failure strain curve versus the simulation curve according to an embodiment of the present invention;
fig. 28 is a schematic structural diagram of a system for determining failure mechanical parameters of a cellular aluminum material according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a method and a system for determining failure mechanical parameters of an aluminum honeycomb material, which improve the accuracy of determining the failure mechanical parameters of the aluminum honeycomb material.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1 and 2, the method for determining the failure mechanical parameter of the aluminum honeycomb material provided in this embodiment includes the following steps.
Step 101: carrying out a mechanical tensile test on a honeycomb aluminum base material sample of a target honeycomb aluminum material to obtain a stress strain curve of the honeycomb aluminum base material; and taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material.
In step 101, dynamic tensile mechanical properties with strain rates of 1ps, 10ps, 100ps, 200ps and 500ps are tested during the mechanical tensile test.
Because the cellular aluminum is too thin and can be broken after slight stretching, accurate material parameters cannot be obtained through a tablet stretching test, taking 3003-grade cellular aluminum as an example, firstly selecting a 3003 aluminum alloy sample with the thickness of 2mm for stretching test, and respectively testing dynamic stretching mechanical properties of cellular aluminum base materials with strain rates of 1PS, 10PS, 100PS and 500PS as shown in figure 3, so as to obtain a stress-strain curve of the 3003 cellular aluminum base materials as shown in figure 4.
Step 102: obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps; and taking the stress triaxial degree and the failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material.
Wherein, the honeycomb aluminum base material sample and the honeycomb aluminum base material sample are both samples made of honeycomb aluminum materials for the automobile collision barrier.
The aluminum honeycomb base material samples of the target aluminum honeycomb materials of the different notches include an aluminum honeycomb base material sample having a notch of 5mm in radius (R5 mm), an aluminum honeycomb base material sample having a notch of 20mm in radius (R20 mm), an aluminum honeycomb base material sample having a center hole of 10mm in diameter (10 mm in center hole), an aluminum honeycomb base material sample sheared at 0 degrees, and an aluminum honeycomb base material sample sheared at 45 degrees, as shown in FIGS. 5 to 9, wherein R represents the radius of the notch, and phi represents the diameter of the center hole, wherein R25 represents the excessive rounded corner of the sample.
The step 102 specifically includes:
and carrying out mechanical stretching test on the honeycomb aluminum base material samples with different gaps, and obtaining the failure strain value of each honeycomb aluminum base material sample by a digital image method (Digital Image Correlation Method, DIC).
And respectively establishing finite element models for the honeycomb aluminum base material samples with different gaps.
Performing stretching simulation according to stress-strain curves of the finite element models and the honeycomb aluminum base material samples to obtain stress triaxial degrees of the honeycomb aluminum base material samples, wherein the method specifically comprises the following steps: inputting the stress-strain curve of the honeycomb aluminum base material sample into each finite element model, and reading the stress triaxial of the honeycomb aluminum base material sample with different notches according to simulation results.
Obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material according to the failure strain value and stress triaxial degree of each honeycomb aluminum base material sample piece, wherein the curves specifically comprise: by combining the failure strain values obtained by the DIC method, stress triaxial degree values and failure strain values of key feature points (points corresponding to triangles in fig. 10, namely failure strain values of different honeycomb aluminum base material samples) can be obtained. And performing interpolation fitting on the key characteristic points through polynomials to obtain stress triaxial degree and failure strain curves of the honeycomb aluminum base metal (3003 base metal), wherein the sample pieces with different gaps are shown in fig. 5-9, the stress triaxial degree and failure strain curves of the base metal are shown in fig. 10, the abscissa in fig. 10 is triaxial stress, and the ordinate is failure strain value.
Step 103: and carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer.
The static compression condition tests of different stress states comprise a full-width compression stress static compression condition test (WL plane full-width compression test) and a plane shear stress static compression condition test, wherein the plane shear stress static compression condition test is a first plane shear stress static compression condition test (LZ plane shear test) or a second plane shear stress static compression condition test (WZ plane shear test). And obtaining the static mechanical characteristic curve and the deformation mode of the honeycomb aluminum monomer through two compression tests. Wherein the directions of L, W and Z are shown in fig. 14.
The static stressed force-displacement test curve comprises a first static force-displacement test curve obtained from a full-width compressive stress static compression working condition test, a second static force-displacement test curve obtained from a plane shear stress static compression working condition test, and the second static force-displacement test curve is a second static force-displacement test curve obtained from a first plane shear stress static compression working condition test or a second static force-displacement test curve obtained from a second plane shear stress static compression working condition test.
Step 104: and carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer.
In step 104, a semicircular impact head test is performed by considering dynamic factors and complex stress states, and the impact head impacts the honeycomb aluminum monomer at a certain initial speed to obtain a dynamic mechanical characteristic curve and a deformation mode of the honeycomb aluminum monomer.
Step 105: and establishing a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material.
Step 105 specifically includes:
in order to ensure the calculation accuracy of the simulation model, at least 3 rows of grids are needed on the edge of each honeycomb aluminum, the calculation accuracy and the efficiency can be considered according to experience when the size of the honeycomb aluminum grids is 8mm, the side length of the honeycomb aluminum is 24mm, the calculation aperture is 41.6mm, and the aperture size is rounded to 40mm. When the aperture of the actual honeycomb aluminum is more than or equal to 40mm, the honeycomb aluminum monomer finite element model can be directly built without simplification.
For a single honeycomb structure with smaller aperture, if finite element modeling is performed according to a real object, a model grid is small, the calculation efficiency is low, and in order to consider simulation precision and calculation efficiency, reasonable equivalence needs to be performed on the honeycomb aperture.
If the aperture of the honeycomb aluminum of the target honeycomb aluminum material is larger than or equal to a set value, establishing a honeycomb aluminum monomer finite element model according to the aperture size of the target honeycomb aluminum material; the set value is 40mm.
If the aluminum honeycomb pore diameter of the target aluminum honeycomb material is smaller than a set value, establishing equivalent honeycomb pores of the target aluminum honeycomb material, wherein the side length L of the equivalent honeycomb pores 1 The dimensional relationship before and after the equivalent is known as follows, according to the principle that the cellular aluminum mass is the same:. The thickness of the equivalent honeycomb holes isThe method comprises the steps of carrying out a first treatment on the surface of the Wherein N is a positive integer, N is 2 or 3, L is the side length of the honeycomb hole of the target honeycomb aluminum material, L 1 Is equivalent to the side length of a honeycomb hole, T 1 Is the thickness of the equivalent honeycomb holes. Equivalent honeycomb holesAs shown in fig. 11 and 12.
And building a honeycomb aluminum monomer finite element model according to the equivalent honeycomb holes.
For example, the aperture of the original honeycomb aluminum is 15mm, the thickness is 0.2mm, the equivalent multiple N is 3, and the calculation formula is adoptedThe equivalent aluminum honeycomb had a pore diameter of 45mm and a thickness of 0.3mm. Fig. 12 is an equivalent schematic diagram of aluminum honeycomb. And (3) establishing a simulation model by using the equivalent honeycomb aluminum size, wherein the grids adopt quadrilateral shell grid units, each honeycomb aluminum side length at least ensures 3 rows of grids, and the honeycomb aluminum single finite element model is shown in fig. 13.
Step 106: and assigning the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve.
The static compression simulation in step 106 also includes two static compression working condition tests, specifically a full-width working condition compression stress static compression working condition test (WL plane full-width compression test) and a plane shear stress static compression working condition test, where the plane shear stress static compression working condition test is a first plane shear stress static compression working condition test (LZ plane shear test) or a second plane shear stress static compression working condition test (WZ plane shear test), to respectively obtain a first static force-displacement simulation curve and a second static force-displacement simulation curve. When the static compression working condition test of the plane shear stress is an LZ plane shear test, the static compression working condition test of the plane shear stress in the static compression simulation is also an LZ plane shear test, and when the static compression working condition test of the plane shear stress is a WZ plane shear test, the static compression working condition test of the plane shear stress in the static compression simulation is also a WZ plane shear test. Wherein the directions of L, W and Z are shown in fig. 14.
The static pressurized force-displacement simulation curves include a first static force-displacement simulation curve and a second static force-displacement simulation curve.
Taking the honeycomb aluminum with the size of 250 multiplied by 450mm as an example, designing static compression working condition tests of three different stress states aiming at honeycomb aluminum monomers, wherein the full-width working condition considers the compression stress of the honeycomb aluminum, the plane size of a pressure head of a static compression test machine is required to be more than 250 multiplied by 250mm, the honeycomb aluminum monomers can be completely covered, and the static compression speed is 100mm/min. The LZ plane shear test considers the shear stress of the bevel edge area of the honeycomb aluminum, and the size of the pressure head is required to cover half of the honeycomb aluminum monomer, and the static compression speed is 100mm/min. The WZ plane shear test considers the shear stress of the vertical edge of the honeycomb aluminum, and the size of the pressure head can cover half of the honeycomb aluminum monomer, and the static compression speed is 100mm/min. The static compression of the mechanical testing machine is used for obtaining a force-displacement curve of the static compression of the honeycomb aluminum monomer, the static compression schematic diagram is shown in fig. 15-17, and the force-displacement test curve is shown in fig. 18-20.
According to the method, a dynamic impact working condition test is designed for honeycomb aluminum monomers, one end of honeycomb aluminum (a honeycomb aluminum monomer model) is fixed, impact with certain initial speed is carried out on the other end, in order to comprehensively consider the dynamic compression and shearing stress of the honeycomb aluminum, an impact head is designed into a semicircular shape, the length is 150mm, the radius is 100mm, the central position of the impact head is located at the central position of the honeycomb aluminum, the initial impact speed of the impact head is set to be 10m/s, the impact head is made of solid steel, the strength is high, and the impact head is not deformed in the impact process. The acceleration or the stress of the impact head can be collected in the impact process to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum, wherein the dynamic impact is shown in figure 21, and the dynamic impact force-displacement test curve is shown in figure 22.
Step 107: and correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material in an iterative mode according to the consistency between the static compressive force-displacement test curve and the static compressive force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stopping condition is met, and outputting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material.
The correction method of the mechanical characteristic curve of the honeycomb aluminum monomer material comprises the following steps: correcting the-1 to 0 section (the-1 to 0 section of triaxial stress) of the stress triaxial degree and failure strain curve according to the full-width static compression deformation difference, correcting the 0 to 0.7 section (the 0 to 0.7 section of triaxial stress) of the second static force-displacement simulation curve obtained according to the LZ shearing test or the WZ shearing test, realizing the integral correction of the curve according to the dynamic impact test, and correcting the amplitude of the stress triaxial degree and failure strain curve according to the amplitude of the difference between the test and the simulation force-displacement curve, wherein the amplitude of the stress triaxial degree and failure strain curve is 1.2 times of the full-width static compression test force-displacement curve, and the 1.2 times of the-1 to 0 curve section of the stress triaxial degree and failure strain curve can be increased for trial calculation to judge whether the stress triaxial degree and the failure strain curve are consistent. The simulated force-displacement curve is corrected to be basically consistent with the test by modifying key characteristic numerical values of the stress triaxial and failure strain curve and scaling local curve, repeatedly adjusting and iterating, and the development of the failure mechanical parameters of the honeycomb aluminum monomer material is completed. The pair of simulation and test force-displacement of the honeycomb aluminum is shown in fig. 23-26, the curve including the triangle in fig. 23-26 is a simulation curve, the curve not including the triangle is a test curve, the corrected triaxial degree of stress and failure strain curve of the honeycomb aluminum and the triaxial degree of stress and failure strain curve of the base material are shown in fig. 27, the broken line in fig. 27 is the triaxial degree of stress and failure strain curve of the honeycomb aluminum single material, and the solid line is the triaxial degree of stress and failure strain curve of the base material.
Step 107 specifically includes:
and carrying out consistency evaluation on the static pressure force-displacement test curve and the static pressure force-displacement simulation curve to obtain a first consistency evaluation value.
And judging whether the first consistency evaluation value is larger than a set evaluation value.
And if the first consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the static compression force-displacement test curve and the current static compression force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve.
And if the first consistency evaluation value is larger than the set evaluation value, carrying out consistency evaluation on the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve to obtain a second consistency evaluation value.
And judging whether the second consistency evaluation value is larger than the set evaluation value.
And if the second consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the dynamic impact force-displacement test curve and the current dynamic impact force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model for respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static stressed force-displacement simulation curve and a dynamic impact force-displacement simulation curve.
And if the second consistency evaluation value is larger than the set evaluation value, outputting the current stress triaxial and failure strain curve of the target honeycomb aluminum material.
The evaluation value was set to 90%.
Wherein the consistency assessment includes a trend consistency assessment (Corridor Rating) and a Magnitude consistency assessment (Magnitrude Rating) in International organization for standardization (International Organization for Standardization, ISO) 18571, and a first consistency assessment value greater than the set assessment value means that the trend consistency assessment and the Magnitude consistency assessment are both greater than 90%.
The iteration stop condition means that the first consistency evaluation value is larger than the set evaluation value and the second consistency evaluation value is larger than the set evaluation value.
Correcting the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the static stressed force-displacement test curve and the current static stressed force-displacement simulation curve, wherein the method specifically comprises the following steps of: modifying-1 to 0 section of the current stress triaxial degree and the abscissa of the failure strain curve of the target honeycomb aluminum material according to a full-width static compression force-displacement test curve (a first static force-displacement test curve), and modifying 0 to 0.7 section of the current stress triaxial degree and the abscissa of the failure strain curve of the target honeycomb aluminum material according to the first static force-displacement test curve.
More specifically, when the ratio of the amplitude of the first static force-displacement test curve to the amplitude of the first static force-displacement simulation curve is n1, the amplitude of the curve segment corresponding to-1 to 0 of the triaxial degree of the current stress and the abscissa of the failure strain curve is divided by n1, and when the ratio of the amplitude of the second static force-displacement test curve to the amplitude of the second static force-displacement simulation curve is n2, the amplitude of the curve segment corresponding to 0 to 0.7 of the triaxial degree of the current stress and the abscissa of the failure strain curve is divided by n2.
Correcting the current stress triaxial and failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the dynamic impact force-displacement test curve and the current dynamic impact force-displacement simulation curve, wherein the method specifically comprises the following steps of: when the ratio of the amplitude of the dynamic impact force-displacement test curve to the amplitude of the current dynamic impact force-displacement simulation curve is n3 times, dividing the integral amplitude of the current stress triaxial degree and the failure strain curve by n3.
The principle of the method for determining the failure mechanical parameters of the honeycomb aluminum material in the embodiment is as follows: and (3) carrying out a mechanical property test of the unidirectional stretching sample piece on the honeycomb aluminum base material, and determining a stress strain curve of the honeycomb aluminum base material. According to the samples (honeycomb aluminum base material samples) of different gaps, determining basic failure mechanical parameters of the base material (honeycomb aluminum base material) by combining the finite element models of the samples, and obtaining a material failure model of the base material; secondly, judging whether to perform equivalent of the aperture size according to the size of the aperture of the honeycomb aluminum, and performing aperture equivalent on the actual size of the honeycomb aluminum based on the principle that the mass is the same and the integer multiple is equivalent for the honeycomb aluminum structure with smaller aperture, so as to establish a honeycomb aluminum monomer finite element model; carrying out compression tests of different stress states of the honeycomb aluminum monomer to obtain a force displacement characteristic curve of the monomer; and carrying the material failure mechanical parameters of the base material into the honeycomb aluminum monomer, and finishing the development of a failure model of the honeycomb aluminum monomer material through readjustment of the failure mechanical parameters.
The invention determines the equivalent principle of honeycomb aluminum based on the integral multiple simplification of the same mass and aperture, and better reserves the physical characteristics and the size parameters of the honeycomb aluminum. And (3) carrying out sample piece stretching tests of different gaps on the honeycomb aluminum base material, and combining finite element simulation of the sample piece to obtain a comprehensive and basic initial plate material failure model. By combining the structural characteristics of the honeycomb aluminum, three static compression working conditions and dynamic impact tests are designed, and the force-displacement curve and deformation modes of the honeycomb aluminum in different stress states can be fully displayed. The base material failure model is subjected to parameter correction by combining simulation and test, so that the high-precision honeycomb aluminum material failure model can be obtained, the improvement of the honeycomb aluminum simulation precision is realized, and the method has important significance for the accurate simulation of the automobile collision. The method has the advantages of strong universality, comprehensive system, simplicity, convenience, easiness in operation and the like, and is suitable for the development of failure models of honeycomb aluminum materials.
Example 2
As shown in fig. 28, the system for determining the failure mechanical parameter of the aluminum honeycomb material provided in this embodiment includes the following matters.
The stress-strain curve determining module 201 is configured to perform a mechanical tensile test on a sample of the honeycomb aluminum base material of the target honeycomb aluminum material to obtain a stress-strain curve of the honeycomb aluminum base material; and taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material.
The stress triaxial degree and failure strain curve determining module 202 is configured to obtain a stress triaxial degree and failure strain curve of the aluminum honeycomb base material based on aluminum honeycomb base material samples of target aluminum honeycomb materials with different notches; and taking the stress triaxial degree and the failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material.
And the static compression force-displacement test curve determining module 203 is used for performing static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer.
And the dynamic impact force-displacement test curve determining module 204 is used for performing a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer.
And the honeycomb aluminum monomer finite element model building module 205 is used for building a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material.
And the simulation curve determining module 206 is configured to assign the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target cellular aluminum material to the cellular aluminum monomer finite element model, and perform static compression simulation loading and dynamic impact simulation loading respectively to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve.
And the stress triaxial degree and failure strain curve correction module 207 is configured to correct the current stress triaxial degree and failure strain curve of the target aluminum honeycomb material in an iterative manner according to the consistency between the static stressed force-displacement test curve and the static stressed force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stop condition is satisfied, and output the current stress triaxial degree and failure strain curve of the target aluminum honeycomb material.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. A method for determining failure mechanical parameters of an aluminum honeycomb material, comprising:
carrying out a mechanical tensile test on a honeycomb aluminum base material sample of a target honeycomb aluminum material to obtain a stress strain curve of the honeycomb aluminum base material; taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material;
obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps; taking the stress triaxial degree and failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material;
carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer;
carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer;
establishing a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material;
assigning the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
And correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material in an iterative mode according to the consistency between the static compressive force-displacement test curve and the static compressive force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stopping condition is met, and outputting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material.
2. The method for determining mechanical parameters of failure of aluminum honeycomb material according to claim 1, wherein the method for obtaining the stress triaxial degree and failure strain curve of the aluminum honeycomb base material based on the aluminum honeycomb base material samples of the target aluminum honeycomb material with different notches specifically comprises:
carrying out mechanical stretching test on the honeycomb aluminum base material sample pieces with different gaps, and obtaining failure strain values of the honeycomb aluminum base material sample pieces through a digital image method;
respectively establishing finite element models for the honeycomb aluminum base material sample pieces of different gaps;
performing stretching simulation according to stress-strain curves of the finite element models and the honeycomb aluminum base material samples to obtain stress triaxial of the honeycomb aluminum base material samples;
And obtaining stress triaxial degree and failure strain curves of the honeycomb aluminum base material according to the failure strain value and stress triaxial degree of each honeycomb aluminum base material sample piece.
3. The method for determining mechanical parameters of failure of aluminum honeycomb material according to claim 1, wherein the static compression condition tests of different stress states comprise a full-width compression stress static compression condition test and a plane shear stress static compression condition test;
the static compressive force-displacement test curves comprise a first static force-displacement test curve obtained from a full-width compressive stress static compression working condition test and a second static force-displacement test curve obtained from a planar shear stress static compression working condition test.
4. The method for determining a failure mechanical parameter of a cellular aluminum material according to claim 3, wherein the method comprises the steps of correcting the current stress triaxial degree and the failure strain curve of the target cellular aluminum material in an iterative manner according to the consistency between the static compressive force-displacement test curve and the static compressive force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stop condition is satisfied, and outputting the current stress triaxial degree and the failure strain curve of the target cellular aluminum material, and specifically comprises the following steps:
Consistency evaluation is carried out on the static pressure force-displacement test curve and the static pressure force-displacement simulation curve to obtain a first consistency evaluation value;
judging whether the first consistency evaluation value is larger than a set evaluation value or not;
if the first consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the static compression force-displacement test curve and the current static compression force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model for respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
if the first consistency evaluation value is larger than the set evaluation value, carrying out consistency evaluation on the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve to obtain a second consistency evaluation value;
judging whether the second consistency evaluation value is larger than a set evaluation value or not;
if the second consistency evaluation value is not greater than the set evaluation value, correcting the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material according to the amplitude difference between the dynamic impact force-displacement test curve and the current dynamic impact force-displacement simulation curve, and returning to assign the current stress strain curve and the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model for respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static stressed force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
And if the second consistency evaluation value is larger than the set evaluation value, outputting the current stress triaxial and failure strain curve of the target honeycomb aluminum material.
5. The method of determining mechanical parameters for failure of aluminum honeycomb material according to claim 1, wherein the aluminum honeycomb base material samples of the target aluminum honeycomb material of different notches include an aluminum honeycomb base material sample of a notch having a radius of 5mm, an aluminum honeycomb base material sample of a notch having a radius of 20mm, an aluminum honeycomb base material sample having a center hole diameter of 10mm, a 0 degree sheared aluminum honeycomb base material sample, and a 45 degree sheared aluminum honeycomb base material sample.
6. The method for determining mechanical parameters of failure of an aluminum honeycomb material according to claim 1, wherein building a finite element model of an aluminum honeycomb monomer of the target aluminum honeycomb material comprises:
if the aperture of the honeycomb aluminum of the target honeycomb aluminum material is larger than or equal to a set value, establishing a honeycomb aluminum monomer finite element model according to the aperture size of the target honeycomb aluminum material;
if the aluminum honeycomb pore diameter of the target aluminum honeycomb material is smaller than a set value, establishing equivalent honeycomb pores of the target aluminum honeycomb material, wherein the side length L of the equivalent honeycomb pores 1 =n×l, the equivalent honeycomb holes have a thickness of The method comprises the steps of carrying out a first treatment on the surface of the Wherein N is a positive integer, L is the side length of the honeycomb holes of the target honeycomb aluminum material;
and building a honeycomb aluminum monomer finite element model according to the equivalent honeycomb holes.
7. The method of determining mechanical parameters for failure of an aluminum honeycomb material of claim 6, wherein the set point is 40mm.
8. A system for determining mechanical parameters for failure of a cellular aluminum material, comprising:
the stress-strain curve determining module is used for carrying out a mechanical tensile test on a honeycomb aluminum base material sample of the target honeycomb aluminum material to obtain a stress-strain curve of the honeycomb aluminum base material; taking the stress-strain curve of the honeycomb aluminum base material as the current stress-strain curve of the target honeycomb aluminum material;
the stress triaxial degree and failure strain curve determining module is used for obtaining a stress triaxial degree and failure strain curve of the honeycomb aluminum base material based on the honeycomb aluminum base material sample pieces of the target honeycomb aluminum materials with different gaps; taking the stress triaxial degree and failure strain curve of the honeycomb aluminum base material as the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material;
the static compression force-displacement test curve determining module is used for carrying out static compression working condition tests of different stress states on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a static compression force-displacement test curve of the honeycomb aluminum monomer;
The dynamic impact force-displacement test curve determining module is used for carrying out a dynamic impact working condition test on the honeycomb aluminum monomer model of the target honeycomb aluminum material to obtain a dynamic impact force-displacement test curve of the honeycomb aluminum monomer;
the honeycomb aluminum monomer finite element model building module is used for building a honeycomb aluminum monomer finite element model of the target honeycomb aluminum material;
the simulation curve determining module is used for assigning the current stress strain curve, the current stress triaxial degree and the failure strain curve of the target honeycomb aluminum material to the honeycomb aluminum monomer finite element model, and respectively carrying out static compression simulation loading and dynamic impact simulation loading to obtain a static compression force-displacement simulation curve and a dynamic impact force-displacement simulation curve;
and the stress triaxial degree and failure strain curve correction module is used for correcting the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material in an iterative mode according to the consistency between the static compression force-displacement test curve and the static compression force-displacement simulation curve and the consistency between the dynamic impact force-displacement test curve and the dynamic impact force-displacement simulation curve until the iteration stop condition is met, and outputting the current stress triaxial degree and failure strain curve of the target honeycomb aluminum material.
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