Modeling method for simulation model of woven composite material component
By superimposing the reinforced body beam unit model with the matrix solid unit model and establishing constraint equations, the problems of low modeling efficiency and limited accuracy of braided composite components in the prior art are solved, and a more efficient and accurate modeling process is achieved.
Patent Information
- Application Number
- CN202411482201.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-23
- Publication Date
- 2025-03-28
AI Technical Summary
The prior art has low efficiency and high accuracy in the modeling of numerical simulation models of braided composite material components, which leads to a complex and time-consuming modeling process.
By superimposing the reinforced beam unit model with the matrix solid unit model, a constraint equation is established to fix the position of the beam unit node relative to the matrix solid model, and the material constitutive of the overlapping area is corrected at the material constitutive level to form a more accurate simulation model.
It improves the modeling efficiency and quality during the design of braided composite components, reduces manpower and material investment, and enhances the accuracy of the modeling process.
Smart Images
Figure CN119720473A_ABST
Abstract
Description
Technical Field
[0002] The invention provides a modeling method for a braided composite material component simulation model, belonging to the field of engineering material design. Background Art
[0004] With the continuous improvement of lightweight and high-performance requirements for mechanical equipment, braided composite components are widely used in defense and civil industries such as aerospace, machinery, and automobiles. Good mechanical, acoustic, thermal and other service performance is an important indicator for evaluating the quality of composite structure design. How to obtain excellent design solutions at a lower cost has become a problem that designers have been exploring.
[0005] With the continuous development and maturity of computer hardware performance and numerical methods, numerical simulation technology has gradually become a commonly used technical means in product design, performance optimization and failure cause detection. Combined with experimental research, it has made great progress and is widely used in many fields of military and civilian industries.
[0006] The first condition for numerical simulation is to establish a reasonable numerical simulation model. The accuracy of the model directly determines the accuracy of the simulation results, and even the success or failure. Therefore, in the context of the large-scale application of braided composite materials in engineering practice, it is of great significance to carry out research on its efficient modeling technology.
[0007] The quality and efficiency of braided composite modeling are the basis and key to the performance simulation of composite components. Due to the diversity of braided composite component materials, the complexity of the spatial structure of the reinforcement and the geometric structure of the composite component, the modeling of its numerical simulation model is very complex and time-consuming. Existing methods mostly use three-dimensional software to model the braided composite reinforcement and its overlapping area, which requires a huge waste of manpower and material resources, and its accuracy is greatly affected by the designer's human factors. Summary of the invention
[0009] In response to the above problems, the present invention proposes a method for modeling a simulation model of a braided composite component, so as to improve the modeling efficiency and quality during the design of braided composite components.
[0010] To achieve the above object, the present invention provides a method for modeling a simulation model of a braided composite material component, comprising the following steps:
[0011] 1) Beam unit model and matrix solid unit model of woven composite components. The reinforcement beam unit model and the matrix solid unit model are superimposed. The two models are established based on the same coordinate system and their spatial positions overlap. The execution process of the superposition process is as follows: (a) for any beam unit node, search for its overlapping solid unit according to its spatial position; (b) establish constraint equations between the beam unit node and each node of the above-mentioned searched solid unit. The constraint equations are used to fix the position of the beam unit node relative to the matrix solid model. The constraint equations are as follows:
[0012] ; ; (1)
[0013] in, , , is the displacement of the jth (j=1, 2)th node of the i-th beam element in the x, y, z directions of the node coordinate system; N c is the shape function of the element coincident with the beam element node; , , is the displacement of the kth node of the element that coincides with the beam element node in the x, y, z directions of the nodal coordinate system, and n is the number of nodes of the coincident base element;
[0014] (c) Repeat (a) and (b) to establish constraint relationships between all beam element nodes and solid elements;
[0015] 2) Forming of the beam unit model of the braided composite reinforcement. In order to obtain the beam unit model of the reinforcement under the real geometric shape of the braided composite component, a forming rigid mold is added to the model. The mold form and size depend on the geometric structure and size of the braided composite component. After adding the mold, the surface contact between the mold and the inner wall of the component beam-solid unit model is established, and static analysis is performed to obtain the forming structure of the braided composite component, and then the reinforcement beam unit model after forming is obtained;
[0016] 3) Modeling of the solid unit model of woven composite components: Based on the reinforced beam unit model after forming, the reinforced solid unit model is established by considering the cross-sectional shape of the reinforced fiber. The reinforced solid unit model and the matrix solid unit model are established based on the same coordinate system and have the same spatial position, or the two overlap in space. Based on this, the constraint equations between the reinforced solid unit model and the matrix solid unit are established.
[0017] ; ; (2)
[0018] Among them, (u, v, w) are the displacements of the reinforcement nodes in the three directions of the global coordinate system when the braided composite material is loaded and deformed; , , ) is the displacement of each node of the matrix unit in the three directions of the global coordinate system when the braided composite material is loaded and deformed.
[0019] According to the modeling method of the simulation model of the woven composite material component, the reinforcement beam unit model is converted into a solid unit model, and the reinforcement fiber beam unit model has a structural form like a "fishbone", including a main beam and a sub-beam, and the ends of the main beam and the sub-beam are beam unit nodes. The main beam determines the spatial posture of the reinforcement fiber, and the sub-beam determines the cross-sectional shape of the reinforcement fiber. According to the different cross-sectional shapes, the size and plane layout of the sub-beam are different, and its cross-sectional shape is one of a circle, an ellipse, a rectangle, and an octagon.
[0020] According to the simulation modeling method of the braided composite component, the execution process of establishing the constraint equation between the reinforcement solid unit model and the matrix solid unit in step 3) is as follows: a) for each node of the reinforcement phase, first determine the matrix unit containing the node according to the node coordinates; (b) obtain the shape function of the matrix unit according to the coordinates of the node and each node of the matrix unit in the global coordinate system using formula (2); (c) calculate the displacement of the reinforcement node according to the displacement of each node of the matrix unit when the braided composite material is loaded and the shape function obtained in the previous step using formula (2), that is, establish a coupling equation to make the materials in the overlapping area of each phase meet the deformation coordination condition,
[0021] ; ; (3)
[0022] Where (x, y, z) is the coordinate of the augmented volume node in the global coordinate system; , , ) is the coordinate of each node of the matrix unit in the global coordinate system; m is the number of nodes of the matrix unit; is the shape function of the base unit.
[0023] 4 According to the simulation modeling method of the braided composite component, in step 3), according to the actual situation of the braided composite component, there is more matrix material in the overlapping area of the reinforcement and the matrix, and the geometric shape of this part of the matrix material is consistent with the reinforcement. Therefore, in order to obtain the performance of the real structure of the braided composite component, the material constitutive structure of the overlapping area is corrected at the material constitutive level. The correction method is as follows:
[0024] (4)
[0025] Among them, [D] C is the real stiffness matrix of the overlapping area material; [D] R is the stiffness matrix of the reinforcement in the overlapping area; [D] M is the stiffness matrix of the matrix in the overlapping area.
[0026] By means of the braided composite material modeling method of the present invention, the quality and efficiency of the braided composite material model are improved.
[0027] The method of the present invention increases displacement coupling calculation parameters and modeling and trimming processes through a computer component model, and the modeling process is more accurate. BRIEF DESCRIPTION OF THE DRAWINGS
[0029] Figure 1 is a flow chart of the modeling process of the present invention,
[0030] Figure 2 It is a process diagram of converting the reinforced beam unit model of the present invention into a solid unit model. Specific implementation methods
[0032] The specific process of the present invention is further described below:
[0033] The modeling method of the braided composite material component simulation model of the present invention is implemented based on a numerical simulation software platform (Ansys or Abaqus), and the modeling method is mainly divided into three steps:
[0034] 1) Modeling of beam-solid element model of woven composite components,
[0035] Taking advantage of the simple structure and bending deformation characteristics of the beam unit, it is used to establish a cylindrical model of the reinforcement, such as Figure 1 (a) shows the reinforced beam unit model. Figure 2 (a) The reinforcement beam unit model 1 (a) and the matrix solid unit model 1 (b) are superimposed. The two models are established based on the same coordinate system and their spatial positions overlap.
[0036] The execution process of the superposition process is:
[0037] (a) For any beam element node, search for its overlapping solid element according to its spatial position;
[0038] (b) Establish constraint equations between the beam unit nodes and the nodes of the above-mentioned search entity units. The constraint equations are used to fix the position of the beam unit nodes relative to the matrix entity model to ensure that they deform with the deformation of the matrix entity unit in step ②. The constraint equations are as follows:
[0039] ; ; (1)
[0040] in, , , is the displacement of the jth (j=1, 2)th node of the i-th beam element in the x, y, z directions of the node coordinate system; N c is the shape function of the element coincident with the beam element node; , , is the displacement of the kth node of the element that coincides with the beam element node in the x, y, z directions of the nodal coordinate system, and n is the number of nodes of the coincident base element.
[0041] (c) Repeat (a) and (b) to establish constraint relationships between all beam element nodes and solid elements.
[0042] 2) Forming of the braided composite reinforced beam unit model,
[0043] The main purpose of this step is to obtain the beam element model of the reinforcement body under the real geometric shape of the braided composite component. A forming rigid mold is added to the model. The mold form and size depend on the geometric structure and size of the braided composite component. After adding the mold, the surface contact between the mold and the inner wall of the component beam-solid element model is established, and static analysis is performed to obtain the forming structure of the braided composite component, such as Figure 1 (e) As shown. Then, the reinforced beam unit model after forming is obtained, and the Figure 1 (f) shown.
[0044] 3) Modeling of solid element model of braided composite components
[0045] Based on the reinforced beam unit model after forming, the cross-sectional shape of the reinforcement fiber (such as Figure 2 As shown in Figure 2), a reinforcement solid unit model is established, as Figure 1 (g) shown.
[0046] The method of converting the reinforced body beam unit model into a solid unit model, the reinforced body fiber beam unit model is as follows Figure 2 As shown in (a), its structure is like a "fishbone", including a main beam and a secondary beam, and the ends of the main beam and the secondary beam are beam unit nodes. The main beam determines the spatial position of the reinforcement fiber, and the secondary beam determines the cross-sectional shape of the reinforcement fiber. Depending on the cross-sectional shape, the size and plane layout of the secondary beam are different. Figure 2 Only hexagonal cross-sections are used as examples. Figure 2 As shown in (b), its cross-sectional shape can be various forms such as circular, elliptical, rectangular, octagonal, etc.
[0047] Considering the reinforcement and matrix solid unit models comprehensively, the two models are established based on the same coordinate system and have the same spatial position, or the two overlap in space. Based on this, the constraint equations between the reinforcement and matrix solid units are established.
[0048] The execution process is:
[0049] (a) For each node of the reinforcement phase, the matrix unit containing the node is first determined according to the node coordinates;
[0050] (b) according to the coordinates of the node and the nodes of the above-mentioned base unit in the global coordinate system, the shape function of the base unit is obtained by using formula (2);
[0051] (c) Based on the displacement of each node of the matrix unit when the braided composite material is loaded and the shape function obtained in the previous step, the displacement of the reinforcement node is calculated using formula (3), which is the coupling equation established to ensure that the materials in the overlapping areas of each phase meet the deformation coordination conditions.
[0052] ; ; (2)
[0053] Where (x, y, z) is the coordinate of the augmented volume node in the global coordinate system; , , ) is the coordinate of each node of the matrix unit in the global coordinate system; m is the number of nodes of the matrix unit; is the shape function of the base unit.
[0054] ; ; (3)
[0055] Among them, (u, v, w) are the displacements of the reinforcement nodes in the three directions of the global coordinate system when the braided composite material is loaded and deformed; , , ) is the displacement of each node of the matrix unit in the three directions of the global coordinate system when the braided composite material is loaded and deformed.
[0056] According to the actual situation of braided composite components, there is more matrix material in the overlapping area between the reinforcement and the matrix than in the actual situation, and the geometry of this part of the matrix material is consistent with the reinforcement. Therefore, in order to obtain the performance of the real structure of the braided composite component, the material constitutive structure of the overlapping area is modified at the material constitutive level. The modification method is as follows:
[0057] (4)
[0058] Among them, [D] C is the real stiffness matrix of the overlapping area material; [D] R is the stiffness matrix of the reinforcement in the overlapping area; [D] M is the stiffness matrix of the matrix in the overlapping area.
[0059] The final simulation model of the braided composite material component entity unit is as follows: Figure 1 (i) shown.
[0060] By means of the braided composite material modeling method of the present invention, the quality and efficiency of the braided composite material model are improved.
[0061] The method of the present invention increases displacement coupling calculation parameters and modeling and trimming processes through a computer component model, and the modeling process is more accurate.
Claims
1. A method for modeling a simulation model of a braided composite material component, characterized in that: The following steps are included: 1) Beam unit model and matrix solid unit model of woven composite components. The reinforcement beam unit model and the matrix solid unit model are superimposed. The two models are established based on the same coordinate system and their spatial positions overlap. The execution process of the superposition process is as follows: (a) for any beam unit node, search for its overlapping solid unit according to its spatial position; (b) establish constraint equations between the beam unit node and each node of the above-mentioned searched solid unit. The constraint equations are used to fix the position of the beam unit node relative to the matrix solid model. The constraint equations are as follows: ； ； （1） in, , , is the displacement of the jth (j=1, 2)th node of the i-th beam element in the x, y, z directions of the node coordinate system; N c is the shape function of the element coincident with the beam element node; , , is the displacement of the kth node of the element that coincides with the beam element node in the x, y, z directions of the node coordinate system, and n is the number of nodes of the coincident base element; (c) Repeat (a) and (b) to establish constraint relationships between all beam element nodes and solid elements; 2) Forming of the beam unit model of the braided composite reinforcement. In order to obtain the beam unit model of the reinforcement under the real geometric shape of the braided composite component, a forming rigid mold is added to the model. The mold form and size depend on the geometric structure and size of the braided composite component. After adding the mold, the surface contact between the mold and the inner wall of the component beam-solid unit model is established, and static analysis is performed to obtain the forming structure of the braided composite component, and then the reinforcement beam unit model after forming is obtained; 3) Modeling of the solid unit model of woven composite components: Based on the reinforced beam unit model after forming, the reinforced solid unit model is established by considering the cross-sectional shape of the reinforced fiber. The reinforced solid unit model and the matrix solid unit model are established based on the same coordinate system and have the same spatial position, or the two overlap in space. Based on this, the constraint equations between the reinforced solid unit model and the matrix solid unit are established. ； ； (2) Wherein, (u, v, w) is the displacement of the reinforcement node in the three directions of the global coordinate system when the braided composite material is loaded and deformed; , , ) is the displacement of each node of the matrix unit in the three directions of the global coordinate system when the braided composite material is loaded and deformed.
2. The method for modeling a simulation model of a braided composite material component according to claim 1, characterized in that: The structure of the reinforced fiber beam unit model is like a "fishbone", including a main beam and a sub-beam. The ends of the main beam and the sub-beam are beam unit nodes. The main beam determines the spatial posture of the reinforced fiber, and the sub-beam determines the cross-sectional shape of the reinforced fiber. According to the different cross-sectional shapes, the size and plane layout of the sub-beam are different. Its cross-sectional shape is one of circular, elliptical, rectangular, and octagonal.
3. The method for modeling a simulation model of a braided composite material component according to claim 1, characterized in that: The execution process of establishing the constraint equation between the reinforcement solid unit model and the matrix solid unit in step 3) is as follows: a) for each node of the reinforcement phase, first determine the matrix unit containing the node according to the node coordinates; (b) obtain the shape function of the matrix unit according to the coordinates of the node and each node of the above-mentioned matrix unit in the global coordinate system using formula (2); (c) calculate the displacement of the reinforcement node according to the displacement of each node of the matrix unit when the woven composite material is loaded and the shape function obtained in the previous step using formula (2), that is, establish a coupling equation to make the materials in the overlapping area of each phase meet the deformation coordination conditions. ; ； (3) Where (x, y, z) is the coordinate of the augmented volume node in the global coordinate system; , , ) is the coordinate of each node of the matrix unit in the global coordinate system; m is the number of nodes of the matrix unit; is the shape function of the base unit.
4. The method for modeling a simulation model of a braided composite material component according to claim 1, characterized in that: In step 3), according to the actual situation of the braided composite component, there is more matrix material in the overlapping area of the reinforcement and the matrix. The geometric shape of this part of the matrix material is consistent with the reinforcement. Therefore, in order to obtain the performance of the real structure of the braided composite component, the material constitutive structure of the overlapping area is corrected at the material constitutive level. The correction method is as follows （4） Among them, [D] C is the real stiffness matrix of the overlapping area material; [D] R is the stiffness matrix of the reinforcement in the overlapping area; [D] M is the stiffness matrix of the matrix in the overlapping area.