CN111639451A - Refined modeling simulation method of two-dimensional plain woven fiber reinforced composite material - Google Patents
Refined modeling simulation method of two-dimensional plain woven fiber reinforced composite material Download PDFInfo
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Abstract
The invention belongs to the field of finite element simulation of fiber reinforced composite materials, and relates to a refined modeling simulation method of a two-dimensional plain woven fiber reinforced composite material; comprises (1) simplifying the microstructure of a two-dimensional plain woven composite material; (2) obtaining RVE geometric parameters; (3) establishing a geometric model; (4) setting a section attribute; (5) determining fiber tow performance parameters; (6) setting a material model; (7) defining a load condition and a boundary condition; (8) contact setting; (9) setting a control card and submitting calculation; the invention can simulate the mechanical response and failure process of the fiber and the matrix of the fiber reinforced composite material in more detail to obtain the micro processes of the fiber reinforced composite material such as interface cracking, fiber matrix damage and the like; the invention provides accurate reference for related structure design, reduces the actual experiment times of researchers, shortens the development period and reduces the design and development cost.
Description
Technical Field
The invention belongs to the field of finite element simulation of fiber reinforced composite materials, and relates to a refined modeling simulation method of a fiber reinforced composite material.
Background
Compared with the traditional metal structure, the Fiber Reinforced Plastic (FRP) has excellent mechanical properties such as light weight, high specific stiffness, good impact resistance, strong fatigue resistance and the like, and is currently widely applied to various fields such as national defense, aerospace, automobiles and the like. However, the process of damage and failure of the fiber reinforced composite material is very complicated, and intensive research on the mechanical response, the failure process and the prediction of the residual strength of the material becomes the research focus of related personnel.
In the research of fiber reinforced composite materials, the damage and failure processes of the fiber reinforced composite materials cannot be observed in detail by using a traditional mechanical experiment method, so that the combination of a mechanical experiment and a finite element analysis technology becomes a mainstream research mode. The finite element analysis scale of the composite material adopted in the current research is divided into a macro scale and a micro scale, and the two scales respectively explain the fiber reinforced composite material from different angles.
Due to the anisotropic characteristics of the fiber reinforced composite material, the fiber reinforced composite material is regarded as an equivalent homogeneous anisotropic material under the macroscopic scale, namely, a homogenization method is adopted to be equivalent to the composite material with complex material properties, and the setting can reflect the macroscopic damage and failure of the material. The defects are that the external shear stress can not be calculated, and the shear stratification can not be predicted; failure behaviors of all composition phases in a failure area cannot be accurately described; the micro-processes of interface cracking, fiber matrix destruction and the like of the fiber reinforced composite material cannot be simulated well.
In order to study the fiber reinforced composite material more deeply, the micro-scale finite element analysis has more advantages. And simulating the damage or failure process of the fiber reinforced composite material by using a proper finite element model so as to provide reference for experimental comparison and microscopic research. Two requirements are provided for the finite element model, namely high calculation precision and as short as possible calculation time. Meanwhile, the fiber reinforced composite material is in a mixed state consisting of fibers, a matrix (mostly adopting resin materials) and an interface phase on the microscopic level, and the microstructure is complex, so that the difficulty is high in the modeling process.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a refined modeling simulation method of a two-dimensional plain weave woven fiber reinforced composite material, which is based on the experiment in the document [1], establishes the working condition that a bullet breaks through a two-dimensional plain weave woven composite material laminated plate by using the method provided by the invention, is used for researching the out-of-plane damage and failure process of the material, and verifies the accuracy and the rationality of the modeling method by comparing the experiment result in the document [1], thereby verifying the rationality of the refined modeling method of the fiber reinforced composite material.
Reference [1] refers to Meyer, c.s., Haque, b.z.g., O' Brien, d.j., Getinet, n., Jian, h.y., Bonyi, e., & Gillespie Jr, j.w. (2018) Mesoscale basic mechanisms of single-layer w oven glass/epoxy composite.
The technical scheme adopted by the invention is as follows:
geometric data of each component of the composite material are obtained through experiments, a basic geometric model of a single fiber tow is established by utilizing three-dimensional modeling software CATIA, the basic geometric model is led into a Hypermesh platform for further modeling, finite element analysis pretreatment is completed, and then an LS-dyna finite element analysis software platform is used for simulation calculation.
CATIA and Hypermesh are software developed by foreign companies.
A refined modeling simulation method of a two-dimensional plain weave fiber reinforced composite material comprises the following steps:
(1) simplifying the microstructure of the two-dimensional plain woven composite material;
(2) obtaining RVE geometric parameters; RVE represents a volume unit;
(3) establishing a geometric model;
(4) setting a section attribute;
(5) determining fiber tow performance parameters;
(6) setting a material model;
(7) defining a load condition and a boundary condition;
(8) contact setting;
(9) setting control cards and submitting calculations.
In the technical scheme, the simplified two-dimensional plain weave composite material microstructure specifically refers to that:
determining the structural parameters of the individual RVEs in which the individual fiber tows simplify an elliptical cross-section with the major axis of the elliptical cross-section being l, and the overall thickness and width of the laminate, the recurring units are called the representative volume units RVEaMinor axis is lbThe distance between the central points of two adjacent tows is lg。
In the technical scheme, the RVE geometric parameter acquisition comprises the following steps:
a. processing the carbon fiber laminated plate;
b. obtaining geometric and dimensional parameters of a target area;
c. measurement of l in RVE units by Electron microscopya，lbAnd lg；
d. Measurement of the overall dimensions of the laminate: radius R and thickness H.
The geometric model is established according to the size and the position of the fiber tows obtained through experimental measurement, and the model is established through three-dimensional modeling software CATIA and finite element pretreatment software Hpermesh respectively; the method comprises the following steps:
a. geometric modeling:
establishing a geometric model of a single fiber tow in three-dimensional modeling software CATIA according to the size and the position of the fiber tow;
b. importing into Hypermesh to divide a body grid:
introducing a geometric model of a single fiber tow established in CATIA into Hypermesh, processing the single fiber tow through translation and rotation operations to obtain plain woven cloth consisting of a plurality of fiber tows, and then carrying out finite element gridding on the model;
drawing a body grid of the whole laminated plate, selecting a partial grid with interference between fibers and the laminated plate by adopting a penetrating command, and deleting the partial grid to obtain the geometric shape and the grid of the base body;
c. combining the fiber tow mesh with the matrix mesh to ensure that no mesh penetrates between the two.
The setting of the section attribute in the technical scheme refers to the step of establishing the section attribute by using a section attribute setting command Properties and endowing the section attribute to each component of the laminated plate; a solid isotropic cross-section is created, imparted to the hammer head member.
The technical scheme is that the determination of the performance parameters of the fiber tows refers to the determination of the tensile strength Y in the direction vertical to the fiber towstThe properties in the fiber tow perpendicular to the fiber (Y-axis) are the result of the interaction of the fiber with the matrix and are difficult to measure experimentally and need to be further determined by trial and error;
firstly, test data are obtained through a composite material plate projectile impact test, and meanwhile, a corresponding finite element simulation test is carried out, and continuous test is carried outError and modification of YtThe value of Y at this time, which finally makes the obtained simulation data coincide with the experimental datatThe values are used as the performance parameters in the vertical direction of the fiber tows.
The technical scheme is that the material setting model comprises the following contents:
a. base material arrangement
The matrix of the composite board is epoxy resin material, and mechanical property simulation is carried out by adopting 24 material MAT _ PIECEWISE _ LINEAR _ PLASTICITY, and the concrete meaning of MAT _ PIECEWISE _ LINEAR _ PLASTICITY is that the mechanical property of the multi-LINEAR elastoplastic material is set; the failure of the matrix is simulated by a keyword MAT _ ADD _ EROSION, the keyword MAT _ ADD _ EROSION means that the damage of the material is failed, and the specific failure criterion is as follows: when the stress of the matrix reaches the limit stress, the matrix fails and the unit is deleted;
b. arrangement of reinforcement material
The reinforcement of the composite board refers to fiber tows, and a No. 262 material MAT _ LAMINATED _ FRACTURE _ DAIMLER _ CAMANHO is adopted for simulation, and the specific meaning of MAT _ LAMINATED FRACTURE _ DAIMLER _ CAMANHO is the setting of the FRACTURE mechanical property of the laminated board;
c. bullet material arrangement
The bullet is simulated by using a 20 # material MAT _ RIGID, and the concrete meaning of the MAT _ RIGID is RIGID body material mechanical property setting.
In the technical scheme, the defining of the load condition and the boundary condition comprises the following steps:
a. load condition setting
Placing a ball with the mass of 1.03g and the diameter of 5.0mm right above the junction midpoint of the warp yarns and the weft yarns, setting the initial speed of the ball as V, and setting the initial speed direction as the Z-axis negative direction;
b. boundary condition setting
Taking the center of the sphere as the center to be a circular area with the diameter of 203mm directly, applying fixed constraint to nodes outside the area, and totally constraining six degrees of freedom of each node.
The contact arrangement in the technical scheme comprises the following steps:
a. contact property setting between bullet and composite material laminated plate
Simulating CONTACT attributes between the bullet and the two-dimensional plain woven composite laminate by using a keyword CONTACT _ AUTOMATIC _ SURFACE _ TO _ SURFACE, wherein the keyword CONTACT _ AUTOMATIC _ SURFACE _ TO _ SURFACE model SURFACE-SURFACE CONTACT attributes are set, and the friction coefficient is set TO be 0.3;
b. composite panel internal contact property setting
The internal CONTACT attribute of the laminated plate is simulated through a keyword (CONTACT _ AUTOMATIC _ SINGLE _ SURFACCE), the meaning of the keyword (CONTACT _ AUTOMATIC _ SINGLE _ SURFACCE) is set for the SURFACE CONTACT attribute of the model, and the friction coefficient is set to be 0.2.
In the technical scheme, the setting of the control card and the submitting calculation specifically refer to:
filling in the control card, and after the model is built, exporting model data to a Keyword file and submitting Ls-dyna to solve and calculate.
Compared with the prior art, the invention has the beneficial effects that:
1. compared with general macroscopic simulation analysis, the refined model obtained by the method can simulate the mechanical response and failure process of the fiber and the matrix of the fiber reinforced composite material in more detail, and obtain the microscopic processes of interface cracking, fiber matrix damage and the like of the fiber reinforced composite material.
2. The method provides accurate reference basis for related structure design, reduces the actual experiment times of researchers, shortens the development period and reduces the design and development cost.
Drawings
The invention is further described with reference to the accompanying drawings in which:
fig. 1 is an analysis flow of a refined modeling simulation method of a two-dimensional plain woven fiber reinforced composite material based on Ls-dyna.
FIG. 2 is a simplified schematic of a two-dimensional plain woven composite laminate fiber tow.
Fig. 3a is a method for obtaining a geometric cross section of a laminate according to an embodiment of the present invention.
Fig. 3b is a cross-sectional electron microscope of the laminate provided in the embodiment of the invention.
Figure 3c is a simplified diagram of the geometric cross-sectional dimensions of a laminate provided by an embodiment of the present invention.
Fig. 4 is a cross-section of a laminate finite element mesh provided by an embodiment of the present invention.
Fig. 5 is a schematic illustration and direction definition of a fiber tow structure provided by an embodiment of the present invention.
Fig. 6a is a top view of a loaded condition provided by an embodiment of the present invention.
FIG. 6b is a constraint boundary provided by an embodiment of the present invention.
Fig. 6c is a front view of a loading condition provided by an embodiment of the present invention.
FIG. 7 shows a schematic diagram of a method for determining Y according to an embodiment of the present inventiontThe next round measured the residual velocity.
Fig. 8 is a comparison of the residual velocity experiment and the simulation results at different initial velocities according to the embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention is further described in detail below with reference to the accompanying drawings and embodiments, and it should be understood that the specific embodiments described herein are only for explaining the present invention and are not intended to limit the present invention.
1. Microstructure simplification of two-dimensional plain woven composite material
The fiber tows in the two-dimensional plain woven composite laminate can be simplified into the structure shown in fig. 2, and are woven by interlacing warps and wefts. It can be seen that the two-dimensional woven fabric has good cycle times, generally referred to as Representative Volume Elements (RVEs), in which individual fiber tows can simplify an elliptical cross-section with the major axis of the elliptical cross-section being l, as shown in figure 3caMinor axis is lbThe distance between the central points of two adjacent tows is lg. Thus, only the structural parameters of a single RVE and the laminate total thickness and width need to be determined to obtain the geometric features of a refined model.
The objective is to determine dimensional parameters including overall RVE length on a macroscopic scale,Width, thickness, and microscopically the size of the individual fiber tows in the RVE: la、lb、lg。
RVE geometric parameter acquisition
To obtain specific values for each parameter in the RVE, the carbon fiber laminate is first processed. As shown in fig. 3a, the processed laminate was sliced to obtain samples for electron microscope experiments. In order to increase the conductivity of the sample and obtain a clear picture, a layer of conductive paint is sprayed on the surface. Then, the geometric and dimensional parameters of the target area are obtained through processes of clamping, focusing, observing, measuring and the like, and the experimental result of the cross section electron microscope of the sample piece is shown in fig. 3 b. Measurement of l in RVE units by Electron microscopya，lbAnd lgMeanwhile, in order to determine the number of the fiber tows, the whole size of the laminated plate is measured: radius R and thickness H.
3. Building a geometric model
According to the size and the position of the fiber tows obtained through experimental measurement, a geometric model of the single fiber tows is established in three-dimensional modeling software CATIA, and the geometric model is led into Hypermesh to divide a body grid. The plain weave finite element grid consisting of a plurality of fiber tows is obtained by processing the single fiber tows through operations such as translation, rotation and the like. The matrix cannot be directly generated due to the complex geometric distribution of the matrix. It is contemplated that the fibers and matrix together comprise a regular laminate. Thus, by first drawing the entire laminate volume grid, using the penetration command to select the partial grid where the fibers interfere with the laminate and deleting it, the base geometry and grid can be obtained, and finally combining the fiber tow grid with the base grid and ensuring that there is no grid penetration between them, as shown in fig. 4.
The key method in the generation process of the fine model geometric model comprises the following steps: and obtaining a finite element model of the matrix by adopting a mesh method for deleting the penetrated mesh.
4. Setting cross-sectional properties
Create section Properties using Properties (section property setting commands) and assign to laminate components; a solid isotropic cross-section is created, imparted to the hammer head member.
5. Determining mechanical property parameters of composite material plate
For the composite plate, the bearing capacity of the matrix in the fiber direction (X axis) is far greater than that of the matrix, so the main direction performance of the fiber tows can be considered to be consistent with the mechanical performance of the fibers; the properties in the fiber tow perpendicular to the fibers (Y-axis) are a result of the interaction of the fibers with the matrix and are difficult to measure experimentally and need to be further determined by trial and error.
Now, the determination of the tensile strength Y perpendicular to the direction of the fiber strands by trial and error is described in detailt: the method comprises the steps of shooting a composite material plate fixed on a specially designed test fixture by using a helium gun to launch steel shot, and obtaining the impact speed and the residual speed of the shot through a high-speed camera (the speed before the shot impacts the composite material plate is the impact speed, and the speed after the shot impacts the composite material plate is the residual speed). Meanwhile, finite element simulation reproduction is carried out on the experiment through a computer, in the simulation experiment, the impact speed of the projectile is a known input quantity, and the tensile strength Y is perpendicular to the direction of the fiber towstIs an unknown input quantity, needs to first assume a reasonable YtInputting the value into the simulation experiment, comparing the residual speed of the projectile obtained from the simulation experiment with the experimental data, and continuously adjusting YtValue until the residual velocities obtained by both experimental and simulation experiments are equal or within an acceptable range, at which point YtThe value is accepted as the tensile strength Y of the composite sheet perpendicular to the direction of the fiber towst。
6. Setting material model
The composite material plate generally adopts epoxy resin as a matrix material, the epoxy resin can be regarded as isotropic material, and is simulated by a No. 24 material model (the keyword MAT _ PIECEWISE _ LINEAR _ PLASTICITY in finite element software Ls-dyna), and the keyword MAT _ PIECEWISE _ LINEAR _ PLASTICITY means that the nonlinear elastoplastic material model is set. In order to realize the effect that the laminated plate is penetrated, the failure of the material needs to be considered, the failure of the substrate is simulated by a key word MAT _ ADD _ error, the key word MAT _ ADD _ error means that the material is damaged and failed, and the specific failure criteria are as follows: when the stress of the matrix reaches the limit stress, the matrix fails and the unit is deleted.
The material model is a mechanical model and can reflect the mechanical property response of a certain material. For example: the No. 24 material model and the mechanical model reflect the performance of the multi-linear elastic-plastic material. Not only can be used for epoxy resin, but also metal materials such as aluminum and the like with the same mechanical properties can be simulated by using a No. 24 material, and the difference between the two materials is only the difference of parameters (such as density, Poisson ratio, modulus and the like).
The matrix of the composite material is generally made of epoxy resin material, and for different grades of epoxy resin, the simulation can be realized by modifying the specific parameter setting of the No. 24 material.
The reinforcement of the composite board is mainly fiber tows, and the fiber tows comprise fibers and epoxy resin in tows, as shown in fig. 5. Therefore, the fiber tows still belong to anisotropic materials, and the No. 262 material (the key word of the material in finite element software Ls-dyna is MAT _ LAMINATED _ FRACTURE _ DAIMLER _ CAMANHO) is used for simulation, and the key word of MAT _ LAMINATED _ FRACTURE _ DAIMLER _ CAMANHO means the setting of the FRACTURE mechanical properties of the laminate.
The hammer (bullet) is set as a RIGID material without considering the deformation in the simulation, and a No. 20 material (the key word of the material in finite element software Ls-dyna is MAT _ RIGID) is used for simulation, and the key word MAT _ RIGID means the setting of the mechanical property of the RIGID material.
7. Definition of boundary conditions and load conditions
The refined model established in this example simulates the working condition that a bullet passes through the two-dimensional plain woven composite laminated board at high speed. As shown in FIG. 6a and FIG. 6c, a round ball with the mass of 1.03g and the diameter of 5.0mm is placed right above the connecting midpoint of the warp and the weft, the initial speed of the round ball is set to be V, and the initial speed direction is the Z-axis negative direction. Taking the center of the sphere as the center to be a circular area with the diameter of 203mm directly, applying fixed constraint to nodes outside the area (black part in figure 6 b), and totally constraining the six degrees of freedom of each node.
8. Contact attribute setting
The CONTACT setting was similar TO other drop hammer impact simulations, with the key word CONTACT AUTOMATIC SURFACE CONTACT TO SURFACE CONTACT property simulating the CONTACT property between the bullet and the two-dimensional plain woven composite laminate, and the coefficient of friction was set TO 0.3. The internal CONTACT properties of the laminate (including the base component and the fiber tow component) were simulated by the keyword CONTACT AUTOMATIC SINGLE SURFACE CONTACT property setting, and the friction coefficients were all set to 0.2.
9. Setting control cards and submitting calculations
For convenience of post-processing and result observation, corresponding control cards need to be filled in, and specific setting contents are shown in table 1. After the model is built, a Keyword file (Keyword file) is output, and the Keyword file contains model data and setting data. Submitted to Ls-dyna for solution calculation. Ls-dyna is a finite element analysis platform software.
TABLE 1 control card settings
Examples
The following will describe the implementation of the fine modeling of the fiber reinforced composite material by taking the construction of the two-dimensional plain woven composite material as an example.
1. Two-dimensional plain weave composite microstructure simplification and acquisition of geometric parameters in the examples, the geometric parameters of RVE model of two-dimensional plain weave composite are shown in table 2.
TABLE 2 RVE geometry parameters
Setting of Material models
The mechanical parameters of the SC-15 epoxy resin and the S-2 glass fiber in reference [1] are set as follows for each constituent material in the model, as shown in Table 3.
TABLE 3 Properties of the materials
III, determination of the Performance parameters of the fiber tows
As mentioned above, the mechanical properties of the fiber tow in the Y direction (Y)tValues) were obtained by trial and error. FIG. 7 shows that different Y are adopted under the condition that the bullet initial velocity V is 300m/stValue-corresponding residual velocity Vt. According to the experimental results, when the initial velocity was 300m/s, the residual velocity was 267 m/s. Thus, Yt190MPa should be taken as the basis for simulation model analysis.
IV, model verification at different initial speeds
The bullet initial velocity V is changed to obtain corresponding residual velocities, and compared with the experimental results of the document [1], the experimental results of the document [1] are that the bullet initial velocities are 300m/s, 350m/s, 400m/s and 450m/s respectively correspond to the residual velocities of 267m/s, 320m/s, 370m/s and 424m/s, and the experimental results and the simulation experimental results of the document [1] are as shown in FIG. 8. It can be seen that the experimental and simulation results are close, the error is within 5%, and the method belongs to an acceptable range.
V, deformation analysis and verification
Compared with a macroscopic model, the refined model can reflect the deformation, fracture failure and the like of the matrix and the fiber tows more accurately, and the deformation of the fiber reinforced composite laminated plate hit by bullets is analyzed by the model established in the embodiment.
The area near the contact of the bullet with the laminate was examined at an initial velocity of 300 m/s. It can be seen that the main load-bearing zone occurs in the fiber tow in the vicinity of the sphere as the center, and the fiber bundle located at the lowermost portion of the sphere is stretched by the tensile force first, while the tensile force is transmitted to the adjacent fiber bundle by the woven structure and the matrix bonding, which is accompanied by the generation and propagation of cracks in the fiber bundle. The laminate absorbs the kinetic energy of the bullet primarily by breaking the fiber bundle.
After penetration, the unit failure on both the upper and lower surfaces was compared. When a bullet passes through the laminate from the upper surface, the base of the upper surface is under compressive stress and the base of the lower surface is under tensile stress and the curvature of the bend is greater so that the base failure area of the upper surface is much smaller than the lower surface.
The diameter of the bullet is equivalent to the size of a long shaft of a single tow, only warp yarns and weft yarns which are in direct contact with the bullet are broken in the breakdown process, the adjacent fiber tows are not invalid and only move outwards, and simultaneously, the space between the fiber tows is obviously increased because the fiber tows are stretched and deformed under stress.
VI, conclusion
The invention mainly introduces a method for establishing a refined model of a fiber reinforced composite material, takes a bullet breakdown two-dimensional plain woven composite material laminated plate as an example, explains the steps for establishing the model, and carries out verification and analysis according to experimental results. The result shows that the established refined model can effectively simulate the mechanical response of the laminated plate, the micro damage mechanism of the fiber bundle tensile failure and the fiber bundle delamination on the substrate can be obtained through the simulation result, and the failure behavior of the two-dimensional plain woven composite laminated plate is reflected in detail. The method can provide technical support for further simulation analysis of the composite material.
The above description is only for the purpose of illustrating the present invention and the appended claims are not to be construed as limiting the scope of the invention, which is intended to cover all modifications, equivalents and improvements that are within the spirit and scope of the invention as defined by the appended claims. And those not described in detail in this specification are well within the skill of those in the art.
Claims (10)
1. A refined modeling simulation method of a two-dimensional plain weave fiber reinforced composite material is characterized by comprising the following steps:
(1) simplifying the microstructure of the two-dimensional plain woven composite material;
(2) obtaining RVE geometric parameters;
(3) establishing a geometric model;
(4) setting a section attribute;
(5) determining fiber tow performance parameters;
(6) setting a material model;
(7) defining a load condition and a boundary condition;
(8) contact setting;
(9) setting control cards and submitting calculations.
2. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 1, characterized in that:
the simplified two-dimensional plain weave composite material microstructure specifically refers to:
determining the structural parameters of the individual RVEs in which the individual fiber tows simplify an elliptical cross-section with the major axis of the elliptical cross-section being l, and the overall thickness and width of the laminate, the recurring units are called the representative volume units RVEaMinor axis is lbThe distance between the central points of two adjacent tows is lg。
3. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 2, characterized in that:
the RVE geometric parameters are obtained by the following steps:
a. processing the carbon fiber laminated plate;
b. obtaining geometric and dimensional parameters of a target area;
c. measurement of l in RVE units by Electron microscopya，lbAnd lg；
d. Measurement of the overall dimensions of the laminate: radius R and thickness H.
4. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 3, characterized in that:
the geometric model is established by respectively establishing a model through three-dimensional modeling software CATIA and finite element pretreatment software Hpermesh according to the size and the position of the fiber tows obtained through experimental measurement; the method comprises the following steps:
a. geometric modeling:
establishing a geometric model of a single fiber tow in three-dimensional modeling software CATIA according to the size and the position of the fiber tow;
b. importing into Hypermesh to divide a body grid:
introducing a geometric model of a single fiber tow established in CATIA into Hypermesh, processing the single fiber tow through translation and rotation operations to obtain plain woven cloth consisting of a plurality of fiber tows, and then carrying out finite element gridding on the model;
drawing a body grid of the whole laminated plate, selecting a partial grid with interference between fibers and the laminated plate by adopting a penetrating command, and deleting the partial grid to obtain the geometric shape and the grid of the base body;
c. combining the fiber tow mesh with the matrix mesh to ensure that no mesh penetrates between the two.
5. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 4, characterized in that:
setting the section attribute, namely creating the section attribute by using a section attribute setting command Properties and endowing the section attribute to each component of the laminated plate; a solid isotropic cross-section is created, imparted to the hammer head member.
6. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 5, characterized in that:
the determination of the performance parameters of the fiber tows refers to the determination of the tensile strength Y in the direction vertical to the fiber towstThe properties in the fibre tow perpendicular to the fibres are the result of the co-action of the fibres with the matrix and are difficult to measure experimentally, requiringFurther determining by a trial and error method;
firstly, test data are obtained through a composite material plate projectile impact test, corresponding finite element simulation tests are carried out simultaneously, and continuous trial and error and Y modification are carried outtThe value of Y at this time, which finally makes the obtained simulation data coincide with the experimental datatThe values are used as the performance parameters in the vertical direction of the fiber tows.
7. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 6, characterized in that:
the setting material model comprises the following contents:
a. base material arrangement
The matrix of the composite board is epoxy resin material, and mechanical property simulation is carried out by adopting 24 material MAT _ PIECEWISE _ LINEAR _ PLASTICITY, and the concrete meaning of MAT _ PIECEWISE _ LINEAR _ PLASTICITY is that the mechanical property of the multi-LINEAR elastoplastic material is set; the failure of the matrix is simulated by a keyword MAT _ ADD _ EROSION, the keyword MAT _ ADD _ EROSION means that the damage of the material is failed, and the specific failure criterion is as follows: when the stress of the matrix reaches the limit stress, the matrix fails and the unit is deleted;
b. arrangement of reinforcement material
The reinforcement of the composite board refers to fiber tows, and a No. 262 material MAT _ LAMINATED _ FRACTURE _ DAIMLER _ CAMANHO is adopted for simulation, and the specific meaning of MAT _ LAMINATED FRACTURE _ DAIMLER _ CAMANHO is the setting of the FRACTURE mechanical property of the laminated board;
c. bullet material arrangement
The bullet is simulated by using a 20 # material MAT _ RIGID, and the concrete meaning of the MAT _ RIGID is RIGID body material mechanical property setting.
8. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 7, characterized in that:
the defining of the load condition and the boundary condition includes the following:
a. load condition setting
Placing a ball with the mass of 1.03g and the diameter of 5.0mm right above the junction midpoint of the warp yarns and the weft yarns, setting the initial speed of the ball as V, and setting the initial speed direction as the Z-axis negative direction;
b. boundary condition setting
Taking the center of the sphere as the center to be a circular area with the diameter of 203mm directly, applying fixed constraint to nodes outside the area, and totally constraining six degrees of freedom of each node.
9. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 8, characterized in that:
the contact arrangement comprises the following steps:
a. contact property setting between bullet and composite material laminated plate
Simulating CONTACT attributes between the bullet and the two-dimensional plain woven composite laminate by using a keyword CONTACT _ AUTOMATIC _ SURFACE _ TO _ SURFACE, wherein the keyword CONTACT _ AUTOMATIC _ SURFACE _ TO _ SURFACE model SURFACE-SURFACE CONTACT attributes are set, and the friction coefficient is set TO be 0.3;
b. composite panel internal contact property setting
The internal CONTACT attribute of the laminated plate is simulated through a keyword (CONTACT _ AUTOMATIC _ SINGLE _ SURFACCE), the meaning of the keyword (CONTACT _ AUTOMATIC _ SINGLE _ SURFACCE) is set for the SURFACE CONTACT attribute of the model, and the friction coefficient is set to be 0.2.
10. The fine modeling simulation method of the two-dimensional plain woven fiber reinforced composite material according to claim 9, characterized in that:
the setting of the control card and the submitting calculation specifically refer to:
filling in the control card, and after the model is built, exporting model data to a Keyword file and submitting Ls-dyna to solve and calculate.
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