CN107451309B - Method for multi-scale calculation of equivalent thermal expansion coefficient of complex composite material structure - Google Patents
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Abstract
The invention provides a method for calculating equivalent thermal expansion coefficients of a complex composite material structure in multiple scales, which adopts a scale separation method to separate three-scale structures of macroscopic scale, microscopic scale and microscopic scale, and respectively establishes various scale analysis models according to the geometric characteristics of different scale models; the three-scale problem is transformed into two multi-scale problems: and (3) analyzing the macroscopic-microscopic multi-scale problem and the microscopic-microscopic multi-scale problem sequentially aiming at the two multi-scale problems, and finally returning the equivalent modulus obtained by the microscopic multi-scale problem to the macroscopic multi-scale problem. The defects of low calculation efficiency and poor precision of the traditional structure analysis method are overcome, and the efficiency and precision of the prediction of the structural performance of the composite material are effectively improved, so that the method can be used for guiding the production, research and development and other work of the composite material. The invention can be applied to the structural design and analysis of complex composite materials in the aerospace field and the structural design thermal and mechanical analysis problems in other composite material engineering fields.
Description
Technical Field
The invention relates to the field of composite material design, in particular to a method for analyzing and designing a complex composite material structure, and specifically relates to a method for calculating the equivalent thermal expansion coefficient of the complex composite material structure in a multi-scale mode.
Background
The composite material has the characteristics of light weight, high strength, strong designability and the like, and is widely applied to structural devices of aerospace. In order to research the performance of the composite material and improve the use efficiency of the composite material structural member, scholars at home and abroad put forward a large number of theories for predicting the behavior of the composite material in the last hundred years because the composite material has a complex structure. The core of the method is to determine the distribution of physical quantities such as internal displacement and temperature of the structure by solving a control equation, thereby completing the prediction of material performance.
At present, the performance prediction methods of composite materials are mainly classified into four types:
the first category is analytical methods, and the methods represented by the first category include: sparse method, Mori-Tanaka method, self-consistent method, generalized self-consistent method. The method solves the problem of single inclusion or multiple inclusions in an infinite matrix to obtain the relation between far-field strain and single inclusion average strain, thereby obtaining the effective modulus of the material. The method is simple in theory, but due to the fact that a certain boundary exists in an actual composite material, a certain error is generated in a calculation result due to the boundary effect, in addition, a part of analysis methods are only suitable for the composite material which is simple in structure and low in volume fraction, and therefore the method is limited in performance prediction of the composite material.
The second category is semi-analytical methods, which are represented by transform field analysis. The method adopts an explicit constitutive relation in mesoscopic view to link macroscopic and mesoscopic fields, needs to give a homogenization and localization rule, and has very many internal variables required by the equivalent constitutive relation for multiphase materials and nonlinear heterogeneous materials, thereby limiting the application of the method.
The third category is a numerical method, which represents a numerical homogenization method, and converts the composite material into a multi-scale analysis problem, and establishes a connection between a macroscopic integral point and a microscopic volume representing unit through a localization and homogenization method, so as to complete the prediction of the material performance.
However, the existing multi-scale method only considers information of two scales, and as most composite materials adopt a form of layering, the microscopic scale of the materials is not a simple combination form of fibers and a matrix, but a combination form of a plurality of fibers and a matrix, and the layering angle of the fibers and the arrangement form of the fibers at each time can greatly influence the performance of the macroscopic material. In addition, most of multi-scale analysis software user development is developed by foreign aerospace scientific research institutions, the software is not disclosed to the outside for various reasons, and most of programs for academic research limit the application of the programs in the engineering field due to the problems of precision, calculation cost and the like.
Disclosure of Invention
In order to avoid the defects of the prior art, the invention provides a method for multi-scale calculation of equivalent thermal expansion coefficients of a complex composite material structure, wherein a three-scale model for composite material structure analysis is adopted in the method, and the method takes the microscopic structure and microstructure into consideration, so that the calculation accuracy of a macroscopic result is improved; in addition, the method is realized by secondary development of commercial finite element software ABAQUS, so that the universality is increased, and the large-scale engineering problem can be better solved.
The technical scheme of the invention is as follows:
the method for multi-scale calculation of the equivalent thermal expansion coefficient of the complex composite material structure is characterized by comprising the following steps of: the method comprises the following steps:
step 1: establishing a macroscopic finite element analysis model according to the actual scale of the composite material, wherein a material coordinate system (X) of the macroscopic finite element analysis model is1,X2,X3) (ii) a Obtaining a physical model of the composite material mesoscopic structure through a microscopic CT scanning experiment, establishing a mesoscopic finite element model according to the volume fraction of the physical model of the composite material mesoscopic structure, the geometric characteristics and the arrangement form of a reinforcing phase and a matrix phase, the defect position, the number of layers and the information of layer angle, and recording the material coordinate system of the mesoscopic finite element model as (Y)1,Y2,Y3) (ii) a Obtaining a physical model of the composite material micro unit cell through an electron microscope experiment, establishing a micro finite element model according to the volume fraction, the shape and the defect position of the reinforced phase of the composite material micro unit cell physical model, and recording a material coordinate system of the micro finite element model as (Z)1,Z2,Z3) (ii) a Wherein Y isi＝Xi/ξ，Zi＝YiThe/η, i is 1,2,3 and ξ which are respectively a bridging coefficient between macroscopic scale and microscopic scale and satisfy ξ<<1，η<<1；
Step 2: giving material properties to the micro finite element model according to the composite material to be calculated;
and step 3: dividing the multi-scale analysis into two steps, firstly, obtaining the equivalent thermal expansion coefficient of the microscopic scale through microscopic-microscopic two-scale analysis; according to the equivalent thermal expansion coefficient of the microscopic scale, obtaining the equivalent thermal expansion coefficient of the macroscopic structure through macroscopic-microscopic two-scale analysis:
step 3.1: the calculation formula for the homogenization of the microscopic equivalent thermoelastic constant is as follows:
step 3.2: calculating the equivalent thermoelastic constant as
The calculation formula for obtaining the equivalent thermal expansion coefficient is
Step 3.3: after the thermal expansion coefficient of the equivalent microscopic finite element model in the step 3.2 is obtained, the equivalent thermal expansion coefficient of each layer of the microscopic finite element model is obtained according to the layer angle of each layer in the microscopic finite element model and the classic laminated plate theory, and the thermal expansion coefficients of the microscopic finite element model are assembled according to the equivalent thermal expansion coefficient of each layer to form a thermal expansion coefficient matrix:
wherein, TtThe transition matrix of each layer of the mesoscopic model is shown, t is 1,2 … n,
the thermal expansion coefficient of the single-layer layering of the mesoscopic model under the global coordinate system,
thermal expansion for microscopic finite element modelA coefficient matrix;
step 3.4: and (3) endowing the microscopic finite element model thermal expansion coefficient matrix obtained in the step (3) to a macroscopic finite element analysis model, and applying load to the macroscopic finite element analysis model to obtain the response of the macroscopic finite element analysis model.
Advantageous effects
The three-scale composite material analysis method provided by the invention has the beneficial effects that:
1. the method utilizes a multi-scale method, fully considers the influence of the geometrical morphology of the microscopic and microscopic structures on the macroscopic structure in the analysis process of the composite material, has better precision compared with the traditional analysis means of the composite material, and can determine the damage mechanism by observing the stress distribution change of the microscopic structure for judging damage and failure.
2. By establishing the three-scale model, the influence of the fiber direction and the ply thickness factor on the whole thermal expansion coefficient is considered during the calculation of the equivalent property of the composite material, and the thickness of the microscale ply and the fiber direction factor are ignored in the traditional two-scale method. And therefore has better accuracy than the conventional multi-scale method.
3. The three-scale method can be realized through secondary development based on the ABAQUS platform, and has better applicability, thereby promoting the application of the multi-scale method in the field of engineering material calculation.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: a computational flow diagram of the invention;
FIG. 2: a geometric model of a pressure vessel of some type in an embodiment;
FIG. 3: a cross-sectional view of the pressure vessel;
FIG. 4: the microscopic appearance of the prefabricated body under CT scanning;
FIG. 5: simplified microscopic finite element model;
FIG. 6: the microscopic appearance of the non-woven fabric under CT scanning;
FIG. 7: calculating a model by needling and net tire microcosmic;
FIG. 8: a weftless fabric microcosmic calculation model;
FIG. 9: pressure vessel boundary conditions.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
In the embodiment, the performance calculation of equivalent materials of a certain type of pressure vessel is taken as an example, the implementation is performed according to the technical scheme of the invention, and a detailed implementation process is given.
Step 1: the pressure container is made of carbon/carbon composite materials, and the prefabricated body with a microscopic structure is formed by combining non-woven fabrics, plus or minus 45-degree layers, and 0-degree and 90-degree layers. According to the practical size of the calculation example, the cylinder is 20mm long as shown in fig. 2 and 3. Establishing a macroscopic finite element analysis model of the pressure vessel in commercial finite element software ABAQUS, wherein the material coordinate system of the macroscopic finite element analysis model is (X)1,X2,X3). And respectively obtaining real microscopic models and microscopic models of the pressure container structure through CT scanning and electron microscope scanning. As shown in fig. 4 and 6.
The basic form of the microstructure mesomonas can be determined from the analysis of the microstructure micrograph of the needled carbon/carbon composite preform. The mesoscopic unit cell is formed by laying a plurality of pieces of non-woven cloth with different ply angles and a composite net tire in a laminated manner, and is reinforced in the thickness direction by needling a fiber bundle. The web fibers are randomly distributed in the plane and thus are an in-plane quasi-isotropic material. The needling is similar to the net tire and also belongs to isotropic materials. The fiber arrangement of the 0-degree non-woven cloth, the annular 90-degree non-woven cloth and the oblique non-woven cloth is compact, and the fiber volume fraction is large. A mesoscopic finite element model is built accordingly, as shown in FIG. 5. The microscopic finite element model material coordinate system is marked as (Y)1,Y2,Y3)。
According to the displayTwo volume fractions of the material are obtained by micro scanning, two microscopic unit cells are established in ABAQUS finite element software, the fiber volume fraction of the unit cell 1 is 50%, and the microscopic unit cells are used for simulating a net blank with less fiber content and a needled microscopic finite element model, as shown in figure 7. The unit cell 2 with a volume fraction of 81% was used to simulate a micro finite element model of a laid fabric with a relatively compact fiber, as shown in FIG. 8. The microscopic finite element model material coordinate system is noted as (Z)1,Z2,Z3)。
Yi＝Xi/ξ，Zi＝YiThe/η, i is 1,2,3 and ξ which are respectively a bridging coefficient between macroscopic scale and microscopic scale and satisfy ξ<<1，η<<1。
Step 2: and giving the material properties of the micro finite element model according to the composite material needing to be calculated.
And step 3: dividing multi-scale analysis into two steps, firstly, obtaining the equivalent material attribute of the microscopic scale through microscopic-microscopic two-scale analysis; and obtaining the equivalent material attribute of the macrostructure through macroscopic-microscopic two-scale analysis according to the equivalent material attribute of the microscopic scale.
When the calculated equivalent material performance is an equivalent stiffness matrix, the specific steps of step 3 are as follows:
step 3.1: tie constraints are imposed in ABAQUS to achieve the application of periodic boundary conditions such that corresponding facet displacements are the same. Under the condition of periodic assumption, the displacement gradual expansion of the micro finite element model is substituted into an elastic mechanics control equation
Obtaining a microscopic equivalent rigidity expression:
wherein the content of the first and second substances,
the upper corner mark represents a micro finite element model, the lower corner mark represents the directions of 6 different stresses,
the lower corner marks k, l represent the directions of 3 different displacements,
the upper corner of the graph represents the homogenization of the micro finite element model, the lower corner represents 6 different directions in the stiffness matrix, Y represents the unit cell volume,
for the microscopic displacement characteristic function, k, l, corresponding to the displacement, represent the directions of 3 different displacement characteristic functions, CijklIs the elastic modulus, delta, of a single component materialmkIs the Kronecker tensor, and satisfies:
in the embodiment, 6 linear disturbance analysis steps are set in the ABAQUS, so that the loading of the heat load in different directions (11, 22, 33, 12, 13 and 23) is completed.
Step 3.2: and (3) converting the microscopic equivalent rigidity expression in the step 3.1 into:
wherein the content of the first and second substances,
represents the magnitude of the equivalent thermal strain,
Δ T is the unit temperature change, in terms of the unit coefficient of thermal expansion.
After the analysis results of the microscopic unit cells in all directions are homogenized, the equivalent thermal loads are unit 1 loads, so that the equivalent material properties of the microstructure are obtained after homogenization, such as tables 1 and 2, and the microscopic analysis is finished.
Table 1: equivalent stiffness matrix of needling and net tire micro model obtained by multi-scale method
Table 2: equivalent stiffness matrix of weftless fabric obtained by microscopic multi-scale method
Step 3.3: after obtaining the equivalent microscopic finite element model stiffness matrix in the step 3.2, obtaining the equivalent stiffness matrix of each layer of the microscopic finite element model according to the layer laying angle of each layer in the microscopic finite element model and the classical laminated plate theory, and assembling the stiffness matrix of the microscopic finite element model according to the equivalent stiffness matrix to form a total stiffness matrix:
wherein, TtThe transition matrix of each layer of the mesoscopic model is shown, t is 1,2 … n,
is a stiffness matrix of a single-layer layering of a mesoscopic model under a global coordinate system,
and (4) forming a total rigidity matrix of the microscopic finite element model.
In this example, the 45 ° degree ply material properties are shown in table 4, the-45 ° degree ply material properties are shown in table 5, the 90 ° ply material properties are shown in table 3, and the mesoscopic nozzle pressure vessel equivalent material properties are shown in table 6.
Table 3: equivalent modulus of mesoscopic 90-degree laid fabric obtained after coordinate transformation
Table 4: equivalent modulus of mesoscopic 45-degree laid fabric obtained after coordinate transformation
Table 5: the mesoscopic-45-degree weftless fabric equivalent modulus is obtained after coordinate transformation
Table 6: mesoscopic model equivalent stiffness matrix obtained by multi-scale method
Step 3.4: and (3) endowing the total rigidity matrix of the microscopic finite element model obtained in the step (3) to a macroscopic finite element analysis model, and applying a load to the macroscopic finite element analysis model, wherein in the embodiment, a load of 50MPa in the direction of 2 is applied to the left end face of the macroscopic finite element model, and the three-direction displacement and the corner of the right end faces 11, 22 and 33 are restrained as shown in figure 9, so that the response of the macroscopic finite element analysis model is obtained.
When the calculated equivalent material performance is the equivalent heat conduction coefficient, the specific steps of the step 3 are as follows:
step 3.1: under the condition of periodic assumption, the temperature gradual expansion of the micro finite element model is brought into a steady-state heat conduction control equation
Obtaining a microscopic equivalent heat conduction coefficient expression:
wherein the content of the first and second substances,
represents the micro-model heat conduction coefficient, the upper corner mark represents the micro-scale, the lower corner mark represents 3 different directions, p represents the material density, Y represents the unit cell volume, Q represents the internal heat flow density,
representing micro model temperature boundary conditions; deltajpRepresenting the Kronecker tensor;
step 3.2: and (3) converting the microscopic equivalent heat conductivity coefficient expression in the step 3.1 into:
wherein the content of the first and second substances,
represents the magnitude of the equivalent thermal strain,
is the unit coefficient of thermal expansion, Δ T is the unit change in temperature;
step 3.3: after obtaining the equivalent microscopic finite element model heat conduction coefficient matrix in the step 3.2, obtaining the equivalent heat conduction coefficient matrix of each layer of the microscopic finite element model according to the layer laying angle of each layer in the microscopic finite element model and the classical laminated board theory, and assembling the heat conduction coefficient matrix of the microscopic finite element model according to the equivalent microscopic finite element model heat conduction coefficient matrix to form a total heat conduction coefficient matrix:
wherein, TtThe transition matrix of each layer of the mesoscopic model is shown, t is 1,2 … n,
is a heat conduction coefficient matrix of a single-layer laying layer of the mesoscopic model under a global coordinate system,
a total heat conduction coefficient matrix of the microscopic finite element model;
step 3.4: and (3) endowing the total heat conduction coefficient matrix of the microscopic finite element model obtained in the step (3) to a macroscopic finite element analysis model, and applying a load to the macroscopic finite element analysis model to obtain the response of the macroscopic finite element analysis model.
When the calculated equivalent material performance is the equivalent thermal expansion coefficient, the specific steps of step 3 are as follows:
step 3.1: considering the thermoelastic boundary value problem in the periodic assumption, the strain is expressed as:
wherein the content of the first and second substances,
in order to achieve a microscopic total strain,
in order to be a micro-mechanical strain,
is the microscopic coefficient of thermal expansion. The constitutive equation for the thermoelastic boundary value problem is therefore:
recording microscopic thermoelastic constant tensor
Is composed of
So that the constitutive equation can be written as
Apart from the strain and constitutive equations, the governing equations for the thermoelastic boundary value problem are identical to those for the elastomechanical boundary value problem. Thus, groupObtaining the micro boundary value problem of the thermoelastic coefficient in the derivation process of solving the equivalent stiffness matrix and the equivalent heat conduction coefficient
Wherein, θ represents the microscopic thermoelastic characteristic function to be solved in the thermal expansion problem, and has the following relation with the characteristic function χ in the solved microscopic equivalent stiffness matrix:
finally obtaining a homogenization calculation formula of the microscopic equivalent thermoelastic constant:
step 3.2: calculating the equivalent thermoelastic constant as
The calculation formula for obtaining the equivalent thermal expansion coefficient is
Step 3.3: after the thermal expansion coefficient of the equivalent microscopic finite element model in the step 3.2 is obtained, the equivalent thermal expansion coefficient of each layer of the microscopic finite element model is obtained according to the layer angle of each layer in the microscopic finite element model and the classic laminated plate theory, and the thermal expansion coefficients of the microscopic finite element model are assembled according to the equivalent thermal expansion coefficient of each layer to form a thermal expansion coefficient matrix:
wherein, TtThe transition matrix of each layer of the mesoscopic model is shown, t is 1,2 … n,
the thermal expansion coefficient of the single-layer layering of the mesoscopic model under the global coordinate system,
a microscopic finite element model thermal expansion coefficient matrix is obtained;
step 3.4: and (3) endowing the microscopic finite element model thermal expansion coefficient matrix obtained in the step (3) to a macroscopic finite element analysis model, and applying load to the macroscopic finite element analysis model to obtain the response of the macroscopic finite element analysis model.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (1)
1. A method for multi-scale calculation of equivalent thermal expansion coefficient of a complex composite material structure is characterized by comprising the following steps: the method comprises the following steps:
step 1: establishing a macroscopic finite element analysis model according to the actual scale of the composite material, wherein a material coordinate system (X) of the macroscopic finite element analysis model is1,X2,X3) (ii) a Obtaining a physical model of the composite material mesoscopic structure through a microscopic CT scanning experiment, establishing a mesoscopic finite element model according to the volume fraction of the physical model of the composite material mesoscopic structure, the geometric characteristics and the arrangement form of a reinforcing phase and a matrix phase, the defect position, the number of layers and the information of layer angle, and recording the material coordinate system of the mesoscopic finite element model as (Y)1,Y2,Y3) (ii) a Obtaining a physical model of the composite material micro unit cell through an electron microscope experiment, and increasing the physical model according to the composite material micro unit cellEstablishing a micro finite element model by the volume fraction, the shape and the defect position of the strong phase, and recording the material coordinate system of the micro finite element model as (Z)1,Z2,Z3) (ii) a Wherein Y isi＝Xi/ξ，Zi＝YiThe/η, i is 1,2,3 and ξ which are respectively a bridging coefficient between macroscopic scale and microscopic scale and satisfy ξ<<1，η<<1；
Step 2: giving material properties to the micro finite element model according to the composite material to be calculated;
and step 3: dividing the multi-scale analysis into two steps, firstly, obtaining the equivalent thermal expansion coefficient of the microscopic scale through microscopic-microscopic two-scale analysis; according to the equivalent thermal expansion coefficient of the microscopic scale, obtaining the equivalent thermal expansion coefficient of the macroscopic structure through macroscopic-microscopic two-scale analysis:
step 3.1: the calculation formula for the homogenization of the microscopic equivalent thermoelastic constant is as follows:
step 3.2: calculating the equivalent thermoelastic constant as
The calculation formula for obtaining the equivalent thermal expansion coefficient is
Wherein
Represents the microscopic equivalent thermoelastic constant, Y represents the unit cell volume,
is the elastic tensor of the single component material at the microscopic scale, αklRepresenting the coefficient of thermal expansion of the single component material at the microscopic scale,
θkas a function of microscopic thermal expansion displacement characteristics, ylRepresents a coordinate component, εklIn order to be the strain tensor,
is an equivalent stiffness matrix of the mesoscopic model under a local coordinate system,
is the equivalent coefficient of thermal expansion;
step 3.3: after the thermal expansion coefficient of the equivalent microscopic finite element model in the step 3.2 is obtained, the equivalent thermal expansion coefficient of each layer of the microscopic finite element model is obtained according to the layer angle of each layer in the microscopic finite element model and the classic laminated plate theory, and the thermal expansion coefficients of the microscopic finite element model are assembled according to the equivalent thermal expansion coefficient of each layer to form a thermal expansion coefficient matrix:
wherein, TtThe transition matrix of each layer of the mesoscopic model is shown, t is 1,2 … n,
the thermal expansion coefficient of the single-layer layering of the mesoscopic model under the global coordinate system,
a microscopic finite element model thermal expansion coefficient matrix is obtained;
step 3.4: and (3) endowing the microscopic finite element model thermal expansion coefficient matrix obtained in the step (3) to a macroscopic finite element analysis model, and applying load to the macroscopic finite element analysis model to obtain the response of the macroscopic finite element analysis model.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103091352A (en) * | 2013-01-28 | 2013-05-08 | 河海大学 | Multiscale prediction method of coefficients of thermal expansion of common cement paste in early stages |
| CN103105485A (en) * | 2013-01-28 | 2013-05-15 | 河海大学 | Hardened ordinary cement paste thermal expansion coefficient multiscale predication method |
| US8862437B1 (en) * | 2010-03-30 | 2014-10-14 | The Boeing Company | Multi-scale modeling of composite structures |
-
2016
- 2016-05-31 CN CN201610373892.9A patent/CN107451309B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8862437B1 (en) * | 2010-03-30 | 2014-10-14 | The Boeing Company | Multi-scale modeling of composite structures |
| CN103091352A (en) * | 2013-01-28 | 2013-05-08 | 河海大学 | Multiscale prediction method of coefficients of thermal expansion of common cement paste in early stages |
| CN103105485A (en) * | 2013-01-28 | 2013-05-15 | 河海大学 | Hardened ordinary cement paste thermal expansion coefficient multiscale predication method |
Non-Patent Citations (2)
| Title |
|---|
| 基于多尺度模型的复合材料层合板性能预测;谢桂兰等;《材料导报》;20140331(第6期);全文 * |
| 复合材料热/力学性能的双尺度渐进分析;唐绍锋;《中国博士学位论文全文数据库 工程科技I辑》;20110531;全文 * |
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