CN110705142A - Numerical simulation method for Ti/CFRP laminated plate structure under impact load - Google Patents
Numerical simulation method for Ti/CFRP laminated plate structure under impact load Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000004088 simulation Methods 0.000 title claims abstract description 19
- 239000004918 carbon fiber reinforced polymer Substances 0.000 title claims abstract 27
- 239000010936 titanium Substances 0.000 claims abstract description 64
- 239000002131 composite material Substances 0.000 claims abstract description 56
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 18
- 230000015556 catabolic process Effects 0.000 claims abstract description 13
- 238000006731 degradation reaction Methods 0.000 claims abstract description 13
- 239000012790 adhesive layer Substances 0.000 claims abstract description 8
- 239000011159 matrix material Substances 0.000 claims description 21
- 239000000835 fiber Substances 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 230000032798 delamination Effects 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 3
- 239000010410 layer Substances 0.000 claims description 3
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 230000002194 synthesizing effect Effects 0.000 description 1
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Abstract
The invention discloses a numerical simulation method for a structural impact process of a Ti/CFRP laminated plate, which is used for constructing a VUMAT subprogram of a composite material based on the stress-strain relation, a three-dimensional Hashin failure criterion and a Tan degradation criterion of the composite material; constructing a finite element grid model of a Ti/CFRP laminated plate structure and a hemispherical punch; constructing a material failure model of a titanium alloy plate and an adhesive layer in a Ti/CFRP laminated plate grid model; constructing an initial condition of the impact load; constructing boundary conditions of a Ti/CFRP laminated plate grid model; and combining the constructed VUMAT subprogram with the constructed model and conditions by using ABAQUS to obtain a numerical analysis model of the Ti/CFRP laminated plate structure under the impact load, and solving to obtain the contact force of the laminated plate structure and the damage failure area of the composite material. The method can simulate damage failure of the Ti/CFRP laminated plate structure in which forms occur under impact load and corresponding failure areas, and provides more accurate reference basis for the structural design of the Ti/CFRP laminated plate.
Description
Technical Field
The invention relates to the field of numerical simulation, in particular to a numerical simulation method of a Ti/CFRP laminated plate structure under an impact load.
Background
Compared with metal materials, the carbon fiber reinforced composite material (CFRP) has good mechanical properties such as light weight, high specific strength, high toughness, high temperature resistance, corrosion resistance and the like, and is widely applied to the fields of aviation, aerospace, weapons, ships, automobiles and the like. However, the composite material has a weak impact resistance and is easily damaged after an impact. In order to improve the impact resistance of the composite material, a metal plate is generally adhered to the surface of the composite material laminate by means of gluing or mechanical bonding, etc. to form a new laminate. A titanium alloy/carbon fiber (Ti/CFRP) composite laminate is a typical laminate, and when one side of a titanium alloy sheet is subjected to an impact load, kinetic energy of the impact load is transmitted from the titanium alloy sheet to the composite laminate, and although the titanium alloy sheet absorbs a part of the kinetic energy, the titanium alloy sheet may still damage the composite laminate without damaging the titanium alloy sheet, and in order to ensure safety and reliability of the Ti/CFRP laminate structure, the Ti/CFRP laminate structure subjected to the impact load must be analyzed. In a paper "Ti/CFRP/Ti sandwich structure high-speed impact numerical simulation research", butyl ice and the like adopt a composite material two-dimensional Hashin failure rule carried by ABAQUS software to simulate the damage failure of a composite material, but cannot obtain which forms of damage failure of the composite material occur specifically.
Disclosure of Invention
The invention aims to provide a numerical simulation method of a Ti/CFRP laminated plate structure under impact load.
The technical scheme for realizing the purpose of the invention is as follows: a numerical simulation method of a Ti/CFRP laminated plate structure under impact load comprises the following steps:
step 1, constructing a VUMAT subprogram of the composite material based on the stress-strain relationship, the three-dimensional Hashin failure criterion and the Tan degradation criterion of the composite material;
step 5, constructing boundary conditions of a Ti/CFRP laminated plate grid model;
and 6, combining the VUMAT subprogram constructed in the step 1 with the model and the condition constructed in the steps 2-4 by using ABAQUS to obtain a numerical analysis model of the Ti/CFRP laminated plate structure under the impact load, and solving to obtain the contact force of the laminated plate structure and the damage failure area of the composite material.
Compared with the prior art, the invention has the following remarkable advantages: the numerical analysis model of the Ti/CFRP laminated plate structure under the impact load is constructed based on the stress-strain relation, the three-dimensional Hashin failure criterion and the Tan degradation criterion of the composite material, so that the damage failure in which forms of the Ti/CFRP laminated plate structure under the impact load occurs and the corresponding failure area can be simulated, and a more accurate reference basis is provided for the design of the Ti/CFRP laminated plate structure.
Drawings
FIG. 1 is a schematic view of a finite element mesh model of a Ti/CFRP laminate structure according to the present invention.
FIG. 2 is a flow chart of the composite VUMAT subroutine of the present invention.
FIG. 3 is a schematic diagram of the lowest layer of the finite element mesh model of the composite plate in a tensile failure state of the matrix.
FIG. 4 is a graph of contact force of the punch of the present invention with a Ti/CFRP laminate structure.
Detailed Description
The scheme of the invention is further explained by combining the attached drawings and the embodiment.
A subprogram interface for customizing material attributes is provided for a user in finite element software ABAQUS, the user writes a VUMAT subprogram in Fortran software according to the constitutive relation of materials and corresponding material failure criteria, and associates a composite material grid model with the VUMAT subprogram according to the material subprogram interface of ABAQUS, so that the damage failure in which forms occur to a composite material and the failure area can be determined. Accordingly, the invention utilizes VUMAT subprogram to research the impact resistance of the Ti/CFRP laminated plate structure under the impact load, and provides a numerical simulation method of the Ti/CFRP laminated plate structure under the impact load based on a three-dimensional Hashin failure criterion and a Tan degradation criterion, as shown in figure 1, the specific steps are as follows:
step 1, compiling a VUMAT subprogram of the composite material based on the stress-strain relationship, the three-dimensional Hashin failure criterion and the Tan degradation criterion of the composite material, as shown in FIG. 2;
the VUMAT subprogram is a code written by a Fortran language according to a material subprogram interface provided by ABAQUS and allows a user to define a material model meeting own problems under the condition that the user cannot find a proper material model. Wherein the stress-strain relationship of the composite material is as follows:
c in formula (1)ijIs a stiffness coefficient, CijSatisfies Cij＝Cji，σ11、σ22、σ33Is the principal stress of the cell, τ12、τ23、τ13Is unit shear stress, epsilon11、ε22、ε33Is a unit principal strain, γ12、γ23、γ13Is the cell shear strain.
The stiffness matrix [ C ] can be obtained by inverting the compliance matrix [ S ], the expression of which is as follows:
wherein E is1、E2And E3Young modulus of the composite material laminated plate in the longitudinal direction (along the carbon fiber laying direction), the transverse direction and the normal direction; g12、G13And G23The shear modulus of the composite laminated board in the longitudinal direction, the transverse direction and the normal direction are respectively; v. of12、v13And v23Respectively, the poisson's ratio of the composite material laminated plate in the longitudinal direction, the transverse direction and the normal direction.
From the symmetry of the compliance matrix, one can obtain:
therefore, E according to the composite laminate1、E2、E3、G12、G13、G23、v12、v13、v23The flexibility matrix S can be obtained by the nine independent material parameters]For a compliance matrix [ S ]]The inverse is used to obtain the rigidity matrix [ C]Using a stiffness matrix [ C ]]May incorporate a cell strain εijAnd gammaijCalculating to obtain the unit stress sigmaijAnd τij. The unit stress is brought into a three-dimensional Hashin failure criterion, and whether the unit fails or not can be judged.
The failure of the composite material is judged by adopting a three-dimensional Hashin failure criterion, and seven failure modes are specifically described as follows:
1) fiber tensile failure (σ)11≥0)：
2) Fibre compression failure (sigma)11＜0)：
3) Elongation failure (σ) of matrix22+σ33≥0)：
4) Compression failure (σ) of matrix22+σ33≥0)：
5) Tensile delamination failure (σ)33≥0)：
6) Compressive delamination failure (σ)33＜0)：
7) Matrix-fiber shear failure (σ)11＜0)：
In the above formula XT、XCThe longitudinal tensile strength and the longitudinal compressive strength of the composite material laminated plate are respectively; y isT，YCThe transverse tensile strength and the transverse compressive strength of the unidirectional plate are respectively; s12、S13And S23The shear strength of the unidirectional plate in three directions. Stress σ of the cellijAnd τijAnd substituting equations (4) to (10), and if the result is greater than or equal to 1, indicating that the unit has corresponding failure.
If the composite unit fails, its nine material parameters will degrade. If fiber tensile failure occurs, the unit is considered to be completely failed, and if other six types of failure occur, the rigidity matrix and the unit stress of the composite material are recalculated according to the degraded material parameters. Composite stiffness degradation criteria Tan degradation criteria was chosen as shown in the following table:
TABLE 1 Tan stiffness degradation model
E′1、E′2、E′3、G′12、G′13、G′23、v′12、v′13、v′13The material parameters of the composite laminate after degradation are respectively.
firstly, establishing a Ti/CFRP laminated plate structure model and a hemispherical punch head model, wherein the Ti/CFRP laminated plate structure model comprises a titanium alloy plate, an adhesive layer and a carbon fiber composite material plate; then, carrying out grid discretization on each part in finite element pretreatment software Hypermesh to obtain a Ti/CFRP laminated plate structure and a finite element grid model of the hemispherical punch. The structure of the established Ti/CFRP laminated board and the hemispherical punch grid model are shown in figure 1, wherein the names of all parts are as follows: 1-a hemispherical punch; 2-a titanium alloy plate; 3, a glue layer; 4-carbon fiber composite board.
selecting a Johnson-Cook damage failure model to simulate the damage failure of the titanium alloy plate;
and selecting a bilinear constitutive model to simulate the damage failure of an adhesive layer between the titanium alloy plate and the composite material laminated plate.
the hemispherical punch is set as a rigid body, and the contact relationship between the hemispherical punch and the Ti/CFRP laminated plate is general contact.
Step 5, constructing boundary conditions of a Ti/CFRP laminated plate grid model;
and setting the three translational degrees of freedom and the three rotational degrees of freedom as 0 so as to restrict the three translational degrees of freedom and the three rotational degrees of freedom of all nodes at the edge of the grid model of the Ti/CFRP laminated plate structure.
And 6, synthesizing the numerical analysis model of the Ti/CFRP laminated plate structure under the impact load obtained in the steps 1-5, and solving to obtain the contact force of the laminated plate structure and the damage failure area of the composite material.
Embedding the VUMAT subprogram compiled in the step 1 into a structural grid model of the Ti/CFRP laminated plate through an ABAQUS subprogram interface, solving a numerical analysis model of the Ti/CFRP laminated plate structure under impact load by using an ABAQUS explicit dynamics solver, and extracting contact force of the laminated plate structure and damage failure area of the composite material.
Examples
To verify the validity of the scheme of the present invention, the following simulation experiment was performed. In the experiment, the titanium alloy plate is TC4, the glue line material is AralditeAV 138, and the composite laminated plate is HTS 40/977-2.
The finite element mesh model constructed according to the method of the present invention is shown in FIG. 1. Firstly establishing a Ti/CFRP laminated plate structure model and a hemispherical punch head model, completing the division of a hemispherical punch head, a titanium alloy plate, an adhesive layer and a composite material laminated plate by adopting a three-dimensional entity unit C3D8R in Hypermesh, setting the minimum unit size of the impacted area of the titanium alloy plate, the adhesive layer and the composite material laminated plate to be 1mm, and setting the minimum unit size of other areas to be 3mm, and obtaining 45234 three-dimensional entity units in total. The Ti/CFRP laminated plate and the hemispherical punch grid model are led into ABAQUS, a hemispherical punch is arranged in an interaction module of the ABAQUS to be a rigid body, and the contact relation between the hemispherical punch and the Ti/CFRP laminated plate is general contact. And giving initial kinetic energy of 4J, 6J and 8J to the rigid punch in the load module respectively, and constraining three translational degrees of freedom and three rotational degrees of freedom of all nodes of the edge of the grid model of the Ti/CFRP laminated plate structure. Embedding a composite material VUMAT subprogram into the finite element mesh model through a subprogram interface in a jobmodule to establish a numerical analysis model.
In this embodiment, an ABAQUS explicit dynamics solver is used to perform numerical simulation on a Ti/CFRP laminated plate structure numerical analysis model under impact load, and simulation results are shown in fig. 3 and 4. It can be seen from fig. 3 and 4 that the greater the initial kinetic energy of the punch, the greater the contact force of the punch with the Ti/CFRP laminate structure, and the greater the area of the composite laminate where matrix stretch failure occurs.
Claims (9)
1. A numerical simulation method of a Ti/CFRP laminated plate structure under impact load is characterized by comprising the following steps:
step 1, constructing a VUMAT subprogram of the composite material based on the stress-strain relationship, the three-dimensional Hashin failure criterion and the Tan degradation criterion of the composite material;
step 2, constructing a finite element grid model of the Ti/CFRP laminated plate structure and the hemispherical punch;
step 3, constructing a material failure model of the titanium alloy plate and the adhesive layer in the Ti/CFRP laminated plate grid model;
step 4, constructing an initial condition of the impact load;
step 5, constructing boundary conditions of a Ti/CFRP laminated plate grid model;
and 6, combining the VUMAT subprogram constructed in the step 1 with the model and the condition constructed in the steps 2-4 by using ABAQUS to obtain a numerical analysis model of the Ti/CFRP laminated plate structure under the impact load, and solving to obtain the contact force of the laminated plate structure and the damage failure area of the composite material.
2. The method of numerical simulation of a Ti/CFRP laminate structure under impact load as claimed in claim 1, wherein in step 1, the stress-strain relationship of the composite material is:
c in formula (1)ijIs a stiffness coefficient, CijSatisfies Cij＝Cji，σ11、σ22、σ33Is the principal stress of the cell, τ12、τ23、τ13Is unit shear stress, epsilon11、ε22、ε33Is a unit principal strain, γ12、γ23、γ13Is the cell shear strain;
the stiffness matrix [ C ] can be obtained by inverting the compliance matrix [ S ], the expression of which is as follows:
wherein E is1、E2And E3Respectively the Young modulus of the composite material laminated plate in the longitudinal direction, the transverse direction and the normal direction; g12、G13And G23The shear modulus of the composite laminated board in the longitudinal direction, the transverse direction and the normal direction are respectively; v. of12、v13And v23Longitudinal, transverse and normal Poisson ratios of the composite laminated plate are respectively;
from the symmetry of the compliance matrix, one can obtain:
therefore, E according to the composite laminate1、E2、E3、G12、G13、G23、v12、v13、v23Nine independent material parameters can obtain a flexibility matrix S]For a compliance matrix [ S ]]The inverse is used to obtain the rigidity matrix [ C]Using a stiffness matrix [ C ]]May incorporate a cell strain εijAnd gammaijCalculating to obtain the unit stress sigmaijAnd τij。
3. The numerical simulation method of a Ti/CFRP laminate structure under impact load as claimed in claim 2, wherein in step 1, the three-dimensional Hashin failure criterion defines seven failure modes, and the unit stress is brought into the three-dimensional Hashin failure criterion to determine whether the unit fails, and the seven failure modes are described as follows:
1) fiber tensile failure (σ)11≥0)：
2) Fibre compression failure (sigma)11＜0)：
3) Elongation failure (σ) of matrix22+σ33≥0)：
4) Compression failure (σ) of matrix22+σ33≥0)：
5) Tensile delamination failure (σ)33≥0)：
6) Compressive delamination failure (σ)33＜0)：
7) Matrix-fiber shear failure (σ)11＜0)：
In the above formula XT、XCThe longitudinal tensile strength and the longitudinal compressive strength of the composite material laminated plate are respectively; y isT，YCThe transverse tensile strength and the transverse compressive strength of the unidirectional plate are respectively; s12、S13And S23The unit stress sigma is the shear strength of the unidirectional sheet in three directionsijAnd τijAnd substituting equations (4) to (10), and if the result is greater than or equal to 1, indicating that the unit has corresponding failure.
4. The method of numerical simulation of a Ti/CFRP laminate structure under impact load of claim 3 wherein in step 1, Tan degradation criteria are as shown in the following table:
TABLE 1 Tan stiffness degradation model
E′1、E′2、E′3、G′12、G′13、G′23、v′12、v′13、v′13The material parameters of the composite laminate after degradation are respectively.
5. The numerical simulation method of a Ti/CFRP laminate structure under impact load according to claim 1, wherein in step 2, a Ti/CFRP laminate structure model and a hemispherical punch model are first established, wherein the Ti/CFRP laminate structure model comprises a titanium alloy plate, a glue layer, a carbon fiber composite plate; then, carrying out grid discretization on each part in finite element pretreatment software Hypermesh to obtain a Ti/CFRP laminated plate structure and a finite element grid model of the hemispherical punch.
6. The method of numerical simulation of a Ti/CFRP laminate structure under impact load of claim 1 wherein in step 3, a Johnson-Cook damage failure model is selected to simulate damage failure of the titanium alloy sheet and a bilinear constitutive model is selected to simulate damage failure of the bondline between the titanium alloy sheet and the composite laminate sheet.
7. The method for numerically simulating a Ti/CFRP laminated plate structure under impact load as claimed in claim 1, wherein in step 4, the hemispherical punch is set to be a rigid body, and the Contact relationship between the hemispherical punch and the Ti/CFRP laminated plate is General Contact.
8. The numerical simulation method of a Ti/CFRP laminate structure under impact load as claimed in claim 1, wherein in step 5, three translational degrees of freedom and three rotational degrees of freedom are set to 0 to constrain the three translational degrees of freedom and three rotational degrees of freedom of all nodes of the edge of the Ti/CFRP laminate structure grid model.
9. The method according to claim 1, wherein in step 6, the VUMAT subprogram is embedded into the grid model of the Ti/CFRP laminated plate structure through the ABAQUS subprogram interface, and the ABAQUS explicit dynamics solver is used to solve the numerical analysis model of the Ti/CFRP laminated plate structure under the impact load, so as to extract the contact force of the laminated plate structure and the damage failure area of the composite material.
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| CN113360972A (en) * | 2021-05-17 | 2021-09-07 | 哈尔滨理工大学 | Kaiwaite latticed shell impact simulation method with roof panel |
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| CN113360972A (en) * | 2021-05-17 | 2021-09-07 | 哈尔滨理工大学 | Kaiwaite latticed shell impact simulation method with roof panel |
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Application publication date: 20200117 |