CN112149322B - Finite element analysis method for curing deformation of composite material reinforced structure - Google Patents
Finite element analysis method for curing deformation of composite material reinforced structure Download PDFInfo
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Abstract
The invention discloses a finite element analysis method for curing deformation of a composite material reinforced structure, which is characterized in that the whole curing process of a composite material is simulated based on an autoclave molding process, resin in the curing process comprises a rubber state and a glass state, different material attributes are given to the composite material under different resin states, and the conversion of the material attributes is completed through finite element software; and analyzing the curing deformation of different reinforcement structures to conclude the influence rule of the reinforcement on the deformation of different curved surface structures. According to the characteristics of the autoclave molding process, the whole curing process of the composite material is simulated, and the resin in the process is simplified into two states: the composite material is in a rubber state and a glass state, different material properties are given to the composite material under different resin states, and the conversion process of the material properties is completed through finite element software ABAQUS neutron program UMAT.
Description
Technical Field
The invention belongs to the technical field of fiber reinforced composite material member molding, and particularly relates to a finite element analysis method for curing deformation of a composite material reinforced structure.
Background
The composite material has the properties of high specific strength and specific rigidity, excellent corrosion resistance, fatigue resistance, strong designability, large-area integral forming and the like, and is widely applied to the fields of aerospace and the like. In the field of aviation, the amount and location of application of composite materials has become an important indicator of aircraft advancement. In recent years, with the rapid development of composite material technology and processing technology and detection and maintenance technology thereof, the use amount of the composite material on military and civil aircrafts is greatly increased.
A thermosetting resin-base fibre-reinforced composite material is prepared through mixing fibres and resin to form prepreg, spreading in a certain order, putting it in vacuum bag, putting it in hot-pressing tank, and solidifying at a certain temp and pressure.
Due to the influence of factors such as thermal expansion coefficients of fiber, resin, composite material and a mold, a formed composite material workpiece has a certain difference from an expected result, and the reason is that residual stress exists inside the composite material workpiece, so that the composite material workpiece is cured and deformed, the appearance precision of the composite material workpiece is seriously affected, the difficulty in processes such as assembly is caused, and the like, and the method is also one of main reasons for causing high cost of the composite material workpiece.
Therefore, the influence mechanism of the curing deformation of the composite material workpiece must be researched, so that the deformation of the composite material workpiece after curing is predicted, and the curing deformation of the composite material workpiece is reduced by correcting various parameters in the forming process. At present, various aviation institutes and host factories in China also gradually begin to research the appearance control technology of the composite material, and the application of the integrated structure of the fuselage composite material is just started.
Disclosure of Invention
The invention aims to provide a finite element analysis method for curing deformation of a composite material reinforced structure.
The invention is mainly realized by the following technical scheme:
a finite element analysis method for curing deformation of a composite material reinforced structure is characterized in that the whole curing process of the composite material is simulated based on an autoclave molding process, resin in the curing process comprises a rubber state and a glass state, different material attributes are given to the composite material under different resin states, and the conversion of the material attributes is completed through finite element software; and analyzing the curing deformation of different reinforcement structures, and summarizing to obtain the influence rule of the reinforcement on the deformation of different curved surface structures.
In order to better implement the invention, the method mainly comprises the following steps:
step S300: setting boundary conditions of a design shape model of the reinforced composite material structure according to a grid structure of the design shape model of the reinforced composite material structure;
step S400: setting a variable temperature field according to the temperature change in the curing process of the composite material, wherein the temperature field is consistent with the temperature field actually applied in the autoclave forming process;
step S500: compiling a subroutine according to the characteristics of the material property change in the temperature field in the step S400 and the constitutive relation of the material, and obtaining the deformation of the composite material caused by mechanical stress and thermal expansion in the curing process;
step S600: the shape of the member, i.e., the shape of the cured deformation of the member, is calculated from the boundary conditions and the deformation in step S300.
In order to better implement the present invention, further, in step S300, in order to ensure convergence of the model calculation process and obtain an accurate calculation result, the stiffness displacement of the reinforced curved surface typical part is defined; except the symmetry boundary conditions of all nodes on the symmetrical surfaces of the wall plate and the tool, the rigidity displacement limitation is carried out on a point on one surface of the reinforced curved surface typical part, the rigidity displacement in three directions needs to be fixed at the central point, the rigidity displacement in two directions only needs to be fixed at Y, Z at two points in the X direction, the expansion in the X direction is allowed, and the Y direction is the same.
To better practice the invention, further, the composite material is orthotropic, and the subroutine UMAT accomplishes the transition of the material properties of the composite material from a rubbery state to a glassy state, the final cure deformation of the composite material being due to the superposition of the deformations created in the rubbery and glassy states.
In order to better implement the present invention, further, in step S500, in order to simulate and predict the curing deformation of the composite material, the constitutive relation of stress-strain of the composite material single-layer plate under the global coordinate system is as follows:
C44＝G23
C55＝G13
C66＝G12
where [ Cij ] represents the stiffness matrix of the material, [ epsilon ] and [ sigma ] represent strains and stresses,
when the resin is in a rubber state, the rigidity of the composite material is relatively low, and the stress-strain relation is as follows:
σr＝Crεr
wherein epsilonrAnd σrThe strain and the stress of the composite material in a rubber state are represented, and Cr represents a rigidity matrix of the composite material;
when the resin is in the glassy state, the elastic modulus of the composite tends to be stable and greater than the modulus in the rubbery state, the stress and strain relationships are as follows:
σg＝Cgεg
wherein epsilongAnd σgComposite strain and stress, C, respectively, in the glassy stategRepresenting a stiffness matrix of the composite material;
the final curing deformation of the composite is therefore due to the superposition of deformations generated in the rubbery and glassy states:
εresidual＝εr+εg＝Cr -1σr+Cg -1σg。
in order to better implement the present invention, further, the following steps are further included before step S300:
step S100: establishing a design shape model of a reinforced composite material structure in finite element software;
step S200: and (5) dividing grids according to the characteristics of the design shape model of the reinforced composite material structure in the step (S100), and giving composite material layering to the model.
In order to better realize the invention, further, in step S100, the inner and outer molded surfaces of the typical part of the stiffened wall panel are extracted in the CATIA, and are cut according to the part line and the allowance line to obtain the inner and outer surfaces of the hollow structure, the corners of the ribs are also extracted only except the top surface and the side surfaces, and are stored in the universal standard igs format, and the geometric molded surface of the igs format is introduced into the Hypermesh for establishing the mesh model.
In order to better implement the present invention, further, in step S200, geometric cleaning is performed on the two-dimensional profile to remove irregular and unnecessary shared edges, and then surface segmentation is performed, so as to divide the two-dimensional profile into regular structural grids; selecting the surface to be divided, giving the type of the grid and the number of seeds, and dividing the two-dimensional grid.
In order to better implement the invention, further, the thickness of the ribbed curved surface typical part in the step S200 is 2.5mm, and the layering is [45/0/0/-45/90/0/-45/0/0/45 ]]SSymmetrically layering; in the process of creating the grid, the components are divided into 2 layers in total, and each layerA total of 10 basic fibre plies with a thickness of 1.25mm were included and a different set was created for each 1.25mm grid for subsequent ply placement.
In order to better realize the invention, further, the reinforcement influences the structural deformation from two aspects of rebound effect and bending rigidity, and the reinforcement can generate rebound deformation, thereby promoting the generation of deformation; the reinforcement increases the bending rigidity of the rib, thereby suppressing the generation of deformation.
The invention has the beneficial effects that:
the reinforced structure has different influences on the composite material structures with different curved surfaces, and the rebound effect of the reinforced structure can promote the solidification deformation of the structure; meanwhile, the longitudinal rigidity of the curved surface structure can be increased by adding the ribs, so that deformation is inhibited, and therefore, the deep research on the deformation of the reinforced rib on different curved surface composite material structures is of great significance. According to the characteristics of the autoclave molding process, the whole curing process of the composite material is simulated, and the resin in the process is simplified into two states: the composite material is in a rubber state and a glass state, different material attributes are given to the composite material under different resin states, the conversion process of the material attributes is completed through a finite element software ABAQUS neutron program UMAT, and the influence rule of reinforcement on the curing deformation of the curved surface structure of the composite material is researched and induced.
Drawings
FIG. 1 is a schematic view of an inner and outer profile model of a typical ribbed curved surface part;
FIG. 2 is a detailed view of ribs of a typical ribbed curved surface;
FIG. 3 is an inner profile of a stiffened curved surface representative piece after being re-segmented;
FIG. 4 is a two-dimensional grid of an inner profile after a typical stiffened curved surface is re-segmented;
FIG. 5 is a three-dimensional mesh model of a typical ribbed curved surface part;
FIG. 6 is a schematic view of a pattern section layup arrangement;
FIG. 7 is a boundary condition of symmetry for a mold symmetry plane;
FIG. 8 is a composite autoclave temperature field set up;
FIG. 9 is stress and strain during curing;
FIG. 10 is a deformed cloud with a single curvature surface with ribs;
FIG. 11 is a deformed cloud view of a single-curvature surface without ribbing;
FIG. 12 is a deformed cloud with ribbed double curvature surfaces;
fig. 13 is a deformed cloud image of a doubly curved surface without ribs.
Detailed Description
Example 1:
a finite element analysis method for curing deformation of a composite material reinforced structure mainly comprises the following steps:
(1) establishing a design shape model of a reinforced composite material structure in finite element software;
(2) dividing grids for the model according to the design shape model characteristics of the reinforced composite material structure;
(3) according to the actual process, endowing the model with composite material layering;
(4) setting boundary conditions of a design shape model of the reinforced composite material structure according to the grid structure;
(5) setting a changing temperature field according to the temperature change in the curing process of the composite material; the temperature field is consistent with the temperature field actually applied in the autoclave molding process.
(6) Compiling a subprogram according to the characteristic of the material property change in the temperature field and the constitutive relation of the material, wherein the subprogram is used for acquiring the deformation of the composite material caused by mechanical stress and thermal expansion in the curing process;
(7) calculating the shape of the member, namely the shape of the member which is solidified and deformed according to the boundary condition and the deformation;
(8) and by analyzing the curing deformation of different reinforcement structures, the influence rule of reinforcement on the deformation of different curved surface structures is summarized.
The reinforced structure has different influences on the composite material structures with different curved surfaces, and the rebound effect of the reinforced structure can promote the solidification deformation of the structure; meanwhile, the longitudinal rigidity of the curved surface structure can be increased by adding the ribs, so that deformation is inhibited, and therefore, the deep research on the deformation of the reinforced rib on different curved surface composite material structures is of great significance. According to the characteristics of the autoclave molding process, the whole curing process of the composite material is simulated, and the resin in the process is simplified into two states: the composite material is in a rubber state and a glass state, different material attributes are given to the composite material under different resin states, the conversion process of the material attributes is completed through a finite element software ABAQUS neutron program UMAT, and the influence rule of reinforcement on the curing deformation of the curved surface structure of the composite material is researched and induced.
Example 2:
a finite element analysis method for curing deformation of a composite material reinforced structure is disclosed, as shown in figures 1-13, a typical L-shaped structure with ribs is taken as a research object, the influence rule of the ribs on the curing deformation of the L-shaped structure is researched by using a finite element method, and the influence rule of different ribs on the curing deformation of a composite material component with a complex curved surface is summarized by changing the material properties of the ribs. The invention mainly comprises the following steps:
(1) and establishing a design shape model of the reinforced composite material structure in finite element software. According to the three-dimensional digital model of the typical part of the reinforced curved surface, the division of the grid, the establishment of the laying layer, the direction setting and the like are complex, the corner effect of the ribs is considered, the fine corner parts of the ribs need to be faithfully reconstructed and divided into regular structural grids, and the process is complicated and tedious, so that the establishment of the grid model is completed by means of third-party software Hypermesh with strong grid dividing function. Firstly, extracting the inner and outer molded surfaces of a typical reinforced wall plate in the CATIA, and cutting according to a part line, a margin line and the like to obtain the inner and outer surfaces of a hollow structure, as shown in figure 1. The corners of the ribs are likewise extracted only from their surfaces, except for the top and side surfaces, and are stored in the universal standard igs format, as shown in detail in fig. 2. And (4) importing the geometric molded surface in the igs format into Hypermesh to establish a grid model.
(2) And dividing grids for the model according to the design shape model characteristics of the reinforced composite material structure, and endowing the model with composite material layering. The embodiment of the invention is specifically as follows: the two-dimensional molded surface is geometrically cleaned, irregular and unnecessary shared edges are removed, and then surface segmentation is carried out, particularly in an area with large curvature, so that the two-dimensional molded surface is conveniently divided into regular structural grids. The re-segmented internal profile is shown in fig. 3. The two-dimensional mesh can be divided by selecting the surface to be divided, giving the mesh type and giving the seed number appropriately. As shown in fig. 4. The generation of the three-dimensional grid is complex, in order to ensure the quality of the grid, especially the grid at the corner of the rib, the operation may be quite delicate and complicated, the workload may be greatly increased along with the increase of the number of the rib, and the finally generated three-dimensional grid is as shown in fig. 5.
(3) According to the actual process, the model is given a composite lay-up. The embodiment of the invention is specifically as follows: the typical stiffened curved surface member of the present invention has a thickness of 2.5mm and a lay of [45/0/0/-45/90/0/-45/0/0/45 ]]SAnd (4) symmetrically layering. In the previous mesh creation process, the components were co-divided into 2 layers, each 1.25mm thick, containing a total of 10 basic fiber plies, and a different set was created for each 1.25mm mesh for subsequent ply placement. As shown in fig. 6.
(4) And setting boundary conditions of a design shape model of the reinforced composite material structure according to the grid structure. The embodiment of the invention is specifically as follows: in order to ensure the convergence of the model calculation process and obtain an accurate calculation result, the rigidity displacement of the typical part of the reinforced curved surface needs to be limited. Fig. 7 is a boundary condition definition of a tooling of a stiffened curved surface typical part, and in addition to the boundary conditions of symmetry of all nodes on a wall plate and a tooling symmetry plane, stiffness displacement limitation is performed on a plurality of points on one surface of the stiffened curved surface typical part, stiffness displacement in three directions needs to be fixed at a central point, and stiffness displacement in two directions only needs to be fixed at two points in the X direction Y, Z to allow expansion in the X direction, and the same principle holds in the Y direction.
(5) And setting a variable temperature field according to the temperature change in the composite material curing process. An embodiment of the present invention is specifically shown in fig. 8.
(6) And compiling a subprogram according to the characteristic of the material property change in the temperature field and the constitutive relation of the material, wherein the subprogram is used for acquiring the deformation of the composite material caused by mechanical stress and thermal expansion in the curing process. The embodiment of the invention is specifically as follows: in order to simulate and predict the curing deformation of the composite material, the stress-strain relationship of the composite material single-layer plate under a global coordinate system needs to be determined, the constitutive relationship is shown as follows,
C44＝G23
C55＝G13
C66＝G12
in which is [ Cij]Representing the stiffness matrix of the material, epsilon and sigma represent strain and stress. The resin exhibits two states during curing, a rubbery state and a glassy state, and figure 9 shows the stress and strain of the composite in both states. When the composite material is in a rubber state, the relation between stress and strain is represented by a stage I, in the process, the rigidity of the composite material is lower, and the relation between stress and strain is as followsShown in the figure:
σr＝Crεr
wherein epsilonrAnd σrComposite strains and stresses, C, representing the rubbery staterRepresenting the stiffness matrix of the composite.
The relationship between stress and strain when the resin is in the glassy state is represented by stage (ii) in fig. 9, at which the elastic modulus of the composite material tends to be stable and greater than the modulus in the rubbery state, as shown below:
σg＝Cgεg
wherein epsilongAnd σgComposite strain and stress in the glassy state are represented and Cg represents the stiffness matrix of the composite.
The final curing deformation of the composite is therefore due to the superposition of deformations generated in the rubbery and glassy states:
εresidual＝εr+εg＝Cr -1σr+Cg -1σg
(7) the method of the invention respectively carries out deformation prediction on the curved surfaces with single curvature and double curvature. Deformation of single-curvature surfaces with and without ribbing as shown in figures 10 and 11, the spring-back effect of the ribs themselves promotes deformation.
(8) Fig. 12 and 13 show deformation diagrams of a double-curvature curved surface structure with and without ribs. The deformation of the structure without the ribs is obviously larger than that of the structure with the ribs, and the ribs inhibit the deformation, mainly because the bending rigidity of the double-curvature curved surface is increased by the ribs, so that the deformation of the inhibitor is inhibited
(9) Theoretically, the ribs influence the structural deformation in two ways: spring back effect and bending stiffness. The ribs can be subjected to rebound deformation, so that the deformation is promoted; the ribs increase the bending rigidity of the ribs, thereby suppressing the generation of deformation. The method of the invention can be used for researching the influence rule of the ribs on the deformation of the structural curved surface according to the difference of the structural curved surface shape.
The reinforced structure has different influences on the composite material structures with different curved surfaces, and the rebound effect of the reinforced structure can promote the solidification deformation of the structure; meanwhile, the longitudinal rigidity of the curved surface structure can be increased by adding the ribs, so that deformation is inhibited, and therefore, the deep research on the deformation of the reinforced rib on different curved surface composite material structures is of great significance. According to the characteristics of the autoclave molding process, the whole curing process of the composite material is simulated, and the resin in the process is simplified into two states: the composite material is in a rubber state and a glass state, different material attributes are given to the composite material under different resin states, the conversion process of the material attributes is completed through a finite element software ABAQUS neutron program UMAT, and the influence rule of reinforcement on the curing deformation of the curved surface structure of the composite material is researched and induced.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (9)
1. A finite element analysis method for curing deformation of a composite material reinforced structure is characterized in that the whole curing process of the composite material is simulated based on an autoclave molding process, resin in the curing process comprises a rubber state and a glass state, different material attributes are given to the composite material under different resin states, and the conversion of the material attributes is completed through finite element software; the influence rule of the reinforcement on the deformation of different curved surface structures is obtained by analyzing the curing deformation of different reinforcement structures;
the composite material is an orthotropic composite material, the subprogram UMAT completes the conversion of the material property of the composite material from a rubber state to a glass state, and the final curing deformation of the composite material is the superposition of the deformation generated in the rubber state and the glass state; when the resin is in a rubber state, the rigidity of the composite material is relatively low, and the stress-strain relation is as follows:
σr＝Crεr
wherein epsilonrAnd σrThe strain and the stress of the composite material in a rubber state are represented, and Cr represents a rigidity matrix of the composite material;
when the resin is in the glassy state, the elastic modulus of the composite tends to be stable and greater than the modulus in the rubbery state, the stress and strain relationships are as follows:
σg＝Cgεg
wherein epsilongAnd σgComposite strain and stress, C, respectively, in the glassy stategRepresenting a stiffness matrix of the composite material;
the final curing deformation of the composite is therefore due to the superposition of deformations generated in the rubbery and glassy states:
εresidual＝εr+εg＝Cr -1σr+Cg -1σg。
2. a finite element analysis method of solidification deformation of a composite material reinforced structure according to claim 1, comprising the steps of:
step S300: setting boundary conditions of a design shape model of the reinforced composite material structure according to a grid structure of the design shape model of the reinforced composite material structure;
step S400: setting a variable temperature field according to the temperature change in the curing process of the composite material, wherein the temperature field is consistent with the temperature field actually applied in the autoclave forming process;
step S500: compiling a subroutine according to the characteristics of the material property change in the temperature field in the step S400 and the constitutive relation of the material, and obtaining the deformation of the composite material caused by mechanical stress and thermal expansion in the curing process;
step S600: the shape of the member, i.e., the shape of the cured deformation of the member, is calculated from the boundary conditions and the deformation in step S300.
3. The finite element analysis method for curing deformation of a composite material reinforced structure according to claim 2, wherein in step S300, in order to ensure the convergence of the model calculation process and obtain an accurate calculation result, the stiffness displacement of the reinforced curved surface typical member is defined; except the symmetry boundary conditions of all nodes on the symmetrical surfaces of the wall plate and the tool, the rigidity displacement limitation is carried out on a point on one surface of the reinforced curved surface typical part, the rigidity displacement in three directions needs to be fixed at the central point, the rigidity displacement in two directions only needs to be fixed at Y, Z at two points in the X direction, the expansion in the X direction is allowed, and the Y direction is the same.
4. A finite element analysis method for curing deformation of a composite material reinforced structure according to claim 2, wherein in step S500, for simulation and prediction of curing deformation of the composite material, the constitutive relation of stress-strain of the composite material single-layer plate in the global coordinate system is as follows:
C44＝G23
C55＝G13
C66＝G12
where [ Cij ] represents the stiffness matrix of the material and ε and σ represent strain and stress.
5. A finite element analysis method for solidification deformation of a composite material reinforced structure according to any one of claims 2 to 4, further comprising the following steps before step S300:
step S100: establishing a design shape model of a reinforced composite material structure in finite element software;
step S200: and (5) dividing grids according to the characteristics of the design shape model of the reinforced composite material structure in the step (S100), and giving composite material layering to the model.
6. The finite element analysis method of the solidification deformation of the composite material reinforced structure as claimed in claim 5, wherein in step S100, the inner and outer profiles of the typical member of the reinforced wall panel are extracted in the CATIA, and cut according to the part line and the allowance line to obtain the inner and outer surfaces of the hollow structure, the corners of the ribs are extracted only except the top surface and the side surface, and are stored in the universal standard igs format, and the geometric profile of the igs format is introduced into the Hypermesh for establishing the mesh model.
7. A finite element analysis method of solidification deformation of a composite material reinforced structure according to claim 5, wherein in step S200, the two-dimensional profile is first geometrically cleaned to remove irregular and unnecessary shared edges, and then surface segmentation is performed so as to divide the two-dimensional profile into regular structural grids; selecting the surface to be divided, giving the type of the grid and the number of seeds, and dividing the two-dimensional grid.
8. The method of claim 5A finite element analysis method for curing deformation of a composite material reinforced structure is characterized in that in the step S200, the thickness of a typical ribbed curved surface part is 2.5mm, and the layering is [45/0/0/-45/90/0/-45/0/0/45 ]]SSymmetrically layering; during the grid creation process, the components were grouped together into 2 layers, each 1.25mm thick, containing a total of 10 basic fiber plies, and a different set was created for each 1.25mm grid for subsequent ply placement.
9. The finite element analysis method for curing deformation of the composite material reinforced structure according to claim 1, wherein the reinforcement influences the structural deformation from both the rebound effect and the bending rigidity, and the reinforcement can generate the rebound deformation so as to promote the deformation; the reinforcement increases the bending rigidity of the rib, thereby suppressing the occurrence of deformation.
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