CN111898295A - Finite element modeling method of variable-rigidity composite laminated plate - Google Patents
Finite element modeling method of variable-rigidity composite laminated plate Download PDFInfo
- Publication number
- CN111898295A CN111898295A CN202010662044.6A CN202010662044A CN111898295A CN 111898295 A CN111898295 A CN 111898295A CN 202010662044 A CN202010662044 A CN 202010662044A CN 111898295 A CN111898295 A CN 111898295A
- Authority
- CN
- China
- Prior art keywords
- laminated plate
- fiber
- curve
- finite element
- shell unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/26—Composites
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a finite element modeling method of a variable-rigidity composite laminated plate, which is implemented by programming through Python and PCL languages, directly extracting information of fiber angles and nodes of a laminated plate shell unit in a finite element model established by a Patran finite element through an operation file, calculating a central node coordinate of each shell unit, if the size of the shell unit is smaller, approximately regarding the fiber angle of the point as the fiber angle of the unit, and finally endowing the fiber angle of each shell unit with shell unit attributes again according to a set curve track to implement fiber curve laying of the laminated plate. And (3) utilizing a variable stiffness laminated plate model obtained by combining Patran and Python, submitting the model to Nastran for solving analysis, and performing visualization processing through Patran introduction. The method combines two programming languages of Python and PCL, does not need to use other platforms, and utilizes Patran to realize finite element modeling of the variable-rigidity laminated plate.
Description
Technical Field
The invention relates to a modeling method of a variable-rigidity composite laminated plate, in particular to a modeling method of a variable-rigidity composite laminated plate based on Patran and Python.
Background
The traditional composite material has excellent mechanical properties of large specific stiffness, high specific strength and strong designability, and is widely applied to the fields of aerospace, mechanical buildings, transportation tools and medical instruments. The composite material is the most promising and vital material meeting the needs of modern development and science, and gradually becomes a substitute material of metal alloy. The use of high-strength light-weight composite materials can reduce the structural mass and the fuel oil loss, and the use amount of the composite materials is continuously increased in both civil and military aspects along with the intensive research on the manufacturing and forming technologies of the composite materials. At present, composite materials applied in the aerospace field mainly comprise three types, namely a metal matrix, a resin matrix and a ceramic matrix, wherein the resin matrix carbon fiber reinforced composite materials are most widely applied and can be classified according to structural forms, and the composite materials can be further divided into a layered composite material, a three-dimensional woven composite material and an interlayer composite material.
To further enhance the designability of composites to improve structural efficiency, the concept of variable stiffness composites has emerged. The traditional composite material laminated plate adopts a fiber linear laying process, so that the excellent performance of fibers is not fully exerted, the fiber angle in a single layer of the variable-rigidity composite material laminated plate is continuously changed, and the structural rigidity is changed by planning a fiber tow path, so that the structure force transmission path is more effectively arranged, the stress distribution is optimized, and the aims of reducing the structural quality and improving the structural efficiency are fulfilled. With the development of automated fiber placement technology, composite laminates of varying stiffness have been produced by a curvilinear lay-up method. In order to better apply the variable stiffness composite material to practical engineering application, the research on the mechanical property of the variable stiffness composite material becomes increasingly important, and the current research methods for the variable stiffness composite material are mainly divided into the following two methods: (1) an analytical method; the analytic method is high in calculation efficiency and suitable for an initial design stage, but has more limitations on research problems, an analysis model needs to be simplified, and compared with a traditional composite laminated plate, a calculation result of the variable-rigidity laminated plate is more complex. (2) A finite element method; the variable stiffness composite laminate finite element method, as well as the analysis of conventional laminates, disperses the entire lay-up of the laminate into a number of grid cells. Although the fiber bundles in each single layer of the laminated plate are continuous, in the finite element, the grid cell size is small, so that the fiber laying angle can be assumed to be piecewise continuous, and the laying angle corresponding to each cell is constant, so that the smaller the cell size, the smaller the error of the finite element model from the actual tow curve path.
In the prior published technical document "storage tank diaphragm structure design and analysis system developed by Patran two times" ("Hunan Tan university science and science Collection, 2016, No. 1), a metal diaphragm storage tank design and analysis system is developed by using a secondary development tool PCL (PanCommand language) of MSC. However, when the method of performing secondary development of software by combining multiple languages is used, some programs need to be modified according to the compatibility requirement between the software, which may cause some unnecessary errors and affect the subsequent research progress.
Because the existing finite element software such as ANSYS, MSC.Patran, ABAQUS and the like can complete the simulation of the laminated plate paved with linear fibers, and for the modeling of the variable stiffness laminated plate, the software does not have a corresponding curve layering modeling module, so the modeling can not be directly carried out in the finite element software, and the variable stiffness analysis model can be established only by using other software or carrying out secondary development on the finite element software, which is troublesome and troublesome.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides a finite element modeling method of a variable-rigidity composite laminated plate; the modeling method is programmed through Python and PCL languages, information of fiber angles and nodes of the laminated plate shell unit in a finite element model established by a Patran finite element is directly extracted through running a script file, the central node coordinate of each shell unit is calculated, if the size of the shell unit is small enough, the fiber angle of the point can be approximately regarded as the fiber angle of the unit, and finally the fiber angle of each shell unit is endowed again according to a set curve track to realize the fiber curve laying of the laminated plate. Then, the model is submitted to Nastran for solving and analysis, and visualized processing is carried out through Patran introduction. The method combines two programming languages of Python and PCL, does not need to help other platforms, and only utilizes Patran to realize finite element modeling of the variable-rigidity laminated plate.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a finite element modeling method of a variable-rigidity composite laminated plate is characterized by comprising the following steps of:
step 1, finishing linear laying by finite element software Patran under the modeling condition of the software to obtain a complete normal-rigidity laminated plate model; in the geometric modeling process, a local coordinate system is required to be established in the geometric center of the model according to a set curve fiber path, and shell unit node output is set to serve as a reference coordinate system;
step 2, compiling a script file by using Python aiming at the laminated plate obtained by straight line laying to obtain the node coordinates and the fiber angle information of the shell unit, simultaneously selecting a fiber curve path, and realizing curve laying of the laminated plate according to a curve laying track and a fiber laying form;
a. when a reference path and a curve layering implementation mode are selected, curve layering is carried out on each single layer of the laminated plate, if a specific single layer needs to be subjected to curve layering, the single layer needing to be modified can be selected through layer-by-layer judgment, and straight curve mixed layering can be achieved;
b. the variable stiffness modeling is realized by a method of extracting node information of a shell unit through a script file to endow a fiber angle again; if the former is not a laminate but a cylindrical structure, the method can be used as long as the lay-up is in the form of a laminate, and proper conversion is required to realize the curve lay-up of the fibers;
step 3, calculating the corresponding fiber angle of the midpoint of each shell unit according to the set fiber curve path and the implementation mode of curve layering for the extracted model information, and giving the shell unit fiber angle again to obtain a variable-stiffness laminated plate model; the calculation mode is realized by the following formula:
θ(x)＝T0+2|x|(T1-T0)/a
in the formula, θ represents a fiber angle, T0Indicating the angle of the fibre, T, at the starting position1Representing the fiber angle at a first point, x representing the x coordinate value of the midpoint of the shell element, a representing the laminate side length;
and 4, performing post-processing by using a variable stiffness laminated plate model obtained by combining Patran and Python through finite element software Nastran to obtain a corresponding mechanical property analysis result.
Advantageous effects
The finite element modeling method of the variable-rigidity composite laminated plate provided by the invention is characterized in that programming is carried out through Python and PCL languages, information of fiber angles and nodes of a laminated plate shell unit in a finite element model established by a Patran finite element is directly extracted through an operation file, a central node coordinate of each shell unit is calculated, if the size of the shell unit is smaller, the fiber angle of the point can be approximately regarded as the fiber angle of the unit, and finally the fiber angle of each shell unit is endowed with shell unit attributes again according to a set curve track, so that fiber curve laying of the laminated plate is realized. And (3) utilizing a variable stiffness laminated plate model obtained by combining Patran and Python, submitting the model to Nastran for solving analysis, and performing visualization processing through Patran introduction.
According to the finite element modeling method of the variable-stiffness composite material laminated plate, the script file is written through Python, any subprogram or third-party software platform except the finite element Patran is not needed, and finite element modeling of the variable-stiffness laminated plate can be realized by using Patran.
Drawings
The finite element modeling method of the variable stiffness composite laminated plate of the invention is further described in detail with reference to the accompanying drawings and embodiments.
Fig. 1 is a schematic block diagram of the present invention.
FIG. 2 is a flow chart of a finite element modeling method for a variable stiffness composite laminate of the present invention.
Detailed Description
The embodiment is a finite element modeling method of a variable-rigidity composite laminated plate.
Referring to fig. 1 and 2, the finite element modeling method of the variable stiffness composite laminate of the present embodiment is based on the above operation steps of the variable stiffness laminate, and the following provides a specific embodiment of a variable stiffness laminate in which the ply [ ± <30/0> ] s is used and the curve ply is implemented by using a translation method.
Firstly, a complete laminated plate model with four layers is established in Patran according to the general steps, wherein the layering angles of four single layers are randomly given, and the model file is generated by submitting analysis. The fiber angle of the curve layering is <30/0>, namely the fiber angle of the middle of a single layer is 30 degrees, the fiber angle of the edge is 0 degrees, the fiber angle is symmetrical about the midpoint, and for the convenience of calculation, a local coordinate system is established at the midpoint of the laminated plate model, so that the model is symmetrical about the center.
And secondly, compiling a Python script file, and extracting node information and fiber angles of the shell units in the original model. The translation method includes the number of each shell unit, the number of four nodes corresponding to the shell unit, and the x coordinate of each node, and the parallel method needs to extract the y coordinate of each node in addition to the previous information. And defining a translation method core function in a Python script, wherein the purpose is to calculate the average value of x coordinates of four nodes of the shell unit, the reference path and the curve fiber planning path have different modes, and the function definition is also different. In the embodiment, the fiber laying is carried out by adopting a translation method, namely, a reference fiber path is moved equidistantly along the direction vertical to the fiber angle change axis, and the subsequent fiber path completely replicates the behavior of the reference fiber path.
And thirdly, calling a function, calculating the fiber angle through the written Python script program, and respectively giving the fiber angle to each shell unit to finish the laying of the fiber curve. Recalculating the fiber angle of each shell unit according to the angle change rule of the curve fiber path and combining the characteristics of a translation method, and giving the shell unit attributes again to ensure that the fiber angle of the whole laminated plate model is <30/0>, namely realizing fiber curve laying to obtain the variable-stiffness laminated plate; the calculation mode is realized by the following formula:
θ(x)＝T0+2|x|(T1-T0)/a
where θ represents the fiber angle, T0Indicating the angle of the fibre, T, at the starting position1The fiber angle at the first point is indicated, x represents the x coordinate value of the center point of the shell unit, and a represents the side length of the laminate.
Meanwhile, it should be noted that when writing Python code, the space therein cannot be deleted without authorization, the space in the code is fixed, and is a fixed format of a unit attribute card in a model file, and can be identified by Patran and Nastran.
And fourthly, submitting the variable stiffness model obtained in the third step to finite element software Nastran for subsequent solving analysis processing to obtain a corresponding mechanical property analysis result.
Claims (1)
1. A finite element modeling method of a variable-rigidity composite laminated plate is characterized by comprising the following steps of:
step 1, finishing linear laying by finite element software Patran under the modeling condition of the software to obtain a complete normal-rigidity laminated plate model; in the geometric modeling process, a local coordinate system is required to be established in the geometric center of the model according to a set curve fiber path, and shell unit node output is set to serve as a reference coordinate system;
step 2, compiling a script file by using Python aiming at the laminated plate obtained by straight line laying to obtain the node coordinates and the fiber angle information of the shell unit, simultaneously selecting a fiber curve path, and realizing curve laying of the laminated plate according to a curve laying track and a fiber laying form;
a. when a reference path and a curve layering implementation mode are selected, curve layering is carried out on each single layer of the laminated plate, if a specific single layer needs to be subjected to curve layering, the single layer needing to be modified can be selected through layer-by-layer judgment, and straight curve mixed layering can be achieved;
b. the variable stiffness modeling is realized by a method of extracting node information of a shell unit through a script file to endow a fiber angle again; if the former is not a laminate but a cylindrical structure, the method can be used as long as the lay-up is in the form of a laminate, and proper conversion is required to realize the curve lay-up of the fibers;
step 3, calculating the corresponding fiber angle of the midpoint of each shell unit according to the set fiber curve path and the implementation mode of curve layering for the extracted model information, and giving the shell unit fiber angle again to obtain a variable-stiffness laminated plate model; the calculation mode is realized by the following formula:
θ(x)＝T0+2|x|(T1-T0)/a
in the formula, θ represents a fiber angle, T0Indicating the angle of the fibre, T, at the starting position1Representing the fiber angle at a first point, x representing the x coordinate value of the midpoint of the shell element, a representing the laminate side length;
and 4, performing post-processing by using a variable stiffness laminated plate model obtained by combining Patran and Python through finite element software Nastran to obtain a corresponding mechanical property analysis result.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010662044.6A CN111898295A (en) | 2020-07-10 | 2020-07-10 | Finite element modeling method of variable-rigidity composite laminated plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010662044.6A CN111898295A (en) | 2020-07-10 | 2020-07-10 | Finite element modeling method of variable-rigidity composite laminated plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111898295A true CN111898295A (en) | 2020-11-06 |
Family
ID=73192237
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010662044.6A Pending CN111898295A (en) | 2020-07-10 | 2020-07-10 | Finite element modeling method of variable-rigidity composite laminated plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111898295A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112507587A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Variable-stiffness composite material structure optimization design method oriented to compression stability |
| CN112861304A (en) * | 2020-12-04 | 2021-05-28 | 中国航空工业集团公司成都飞机设计研究所 | Variable-stiffness composite material structure design method for compression stability |
| CN112949144A (en) * | 2021-03-30 | 2021-06-11 | 湖州中科晟合信息科技有限公司 | Method for determining fiber path direction of composite material plate |
| CN113158515A (en) * | 2021-03-31 | 2021-07-23 | 中国飞机强度研究所 | Method for quickly establishing defect-containing laminated plate cylinder parametric model |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103177138A (en) * | 2011-12-23 | 2013-06-26 | 上海汽车集团股份有限公司 | Flanging finite element modeling method |
| CN103353916A (en) * | 2012-09-10 | 2013-10-16 | 中国航空工业集团公司科学技术委员会 | Method for post-processing engineering-based composite material laminated board ply after optimization |
| US20150142149A1 (en) * | 2013-11-15 | 2015-05-21 | Collier Research and Development Corporation | Method and computer-based tool for composite-structure fabrication design |
| EP3107018A2 (en) * | 2015-06-19 | 2016-12-21 | Penso Holdings Ltd. | Method for use in the analysis of a composite component and a design tool |
| CN107220461A (en) * | 2017-06-26 | 2017-09-29 | 大连理工大学 | A kind of variation rigidity composite panel shell structure effectively optimizing method |
| CN107729659A (en) * | 2017-10-19 | 2018-02-23 | 吴尘瑾 | Laminate laying processing method and processing device |
| CN108363828A (en) * | 2017-12-28 | 2018-08-03 | 中国空间技术研究院 | A kind of modeling method of variation rigidity composite material |
| US10140388B1 (en) * | 2014-11-16 | 2018-11-27 | The Boeing Company | System and method for designing composite laminates using lamination parameters |
-
2020
- 2020-07-10 CN CN202010662044.6A patent/CN111898295A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103177138A (en) * | 2011-12-23 | 2013-06-26 | 上海汽车集团股份有限公司 | Flanging finite element modeling method |
| CN103353916A (en) * | 2012-09-10 | 2013-10-16 | 中国航空工业集团公司科学技术委员会 | Method for post-processing engineering-based composite material laminated board ply after optimization |
| US20150142149A1 (en) * | 2013-11-15 | 2015-05-21 | Collier Research and Development Corporation | Method and computer-based tool for composite-structure fabrication design |
| US10140388B1 (en) * | 2014-11-16 | 2018-11-27 | The Boeing Company | System and method for designing composite laminates using lamination parameters |
| EP3107018A2 (en) * | 2015-06-19 | 2016-12-21 | Penso Holdings Ltd. | Method for use in the analysis of a composite component and a design tool |
| CN107220461A (en) * | 2017-06-26 | 2017-09-29 | 大连理工大学 | A kind of variation rigidity composite panel shell structure effectively optimizing method |
| CN107729659A (en) * | 2017-10-19 | 2018-02-23 | 吴尘瑾 | Laminate laying processing method and processing device |
| CN108363828A (en) * | 2017-12-28 | 2018-08-03 | 中国空间技术研究院 | A kind of modeling method of variation rigidity composite material |
Non-Patent Citations (3)
| Title |
|---|
| TANG SIXUN 等: "The FEM Model Driven Method of the Static Performance Calculation for Gas Joumal Bearing by Python", 《2018 IEEE INTERNATIONAL CONFERENCE ON MECHATRONICS AND AUTOMATION (ICMA)》 * |
| TAO HUANG 等: "Finite Element Analysis on Plastic Deformation Behaviors of Ti-3Al-2.5V Tubes under Axial Compression", 《KEY ENGINEERING MATERIALS》 * |
| 薛彩虹 等: "复合材料风电叶片有限元建模和屈曲稳定性分析", 《玻璃钢/复合材料》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112507587A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Variable-stiffness composite material structure optimization design method oriented to compression stability |
| CN112861304A (en) * | 2020-12-04 | 2021-05-28 | 中国航空工业集团公司成都飞机设计研究所 | Variable-stiffness composite material structure design method for compression stability |
| CN112861304B (en) * | 2020-12-04 | 2022-06-28 | 中国航空工业集团公司成都飞机设计研究所 | Variable-stiffness composite material structure design method for compression stability |
| CN112949144A (en) * | 2021-03-30 | 2021-06-11 | 湖州中科晟合信息科技有限公司 | Method for determining fiber path direction of composite material plate |
| CN113158515A (en) * | 2021-03-31 | 2021-07-23 | 中国飞机强度研究所 | Method for quickly establishing defect-containing laminated plate cylinder parametric model |
| CN113158515B (en) * | 2021-03-31 | 2024-06-07 | 中国飞机强度研究所 | Method for quickly establishing cylindrical parameterized model of laminated plate with defects |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111898295A (en) | Finite element modeling method of variable-rigidity composite laminated plate | |
| JP7058902B2 (en) | High-speed coordinated optimization method for plate-wound shell structure of hybrid fiber composite material | |
| CN107451307B (en) | Method for multi-scale calculation of equivalent stiffness matrix of complex composite structure | |
| CN108984910B (en) | A kind of parametric modeling method of Three-Dimensional Braided Composites | |
| US8655627B2 (en) | Determining a distribution of multiple layers of a composite material within a structural volume | |
| Dillinger | Static aeroelastic optimization of composite wings with variable stiffness laminates | |
| KR101200167B1 (en) | Analysis system and method for composite materials | |
| CN106682336A (en) | Modeling method for structural finite element model | |
| CN108647386A (en) | A kind of optimization design method applied to FRP anticollisions girder construction/material | |
| CN112182933A (en) | Modeling and optimal design method of variable-rigidity composite material cylindrical shell | |
| CN112507587A (en) | Variable-stiffness composite material structure optimization design method oriented to compression stability | |
| CN111859747B (en) | Layered quantification method based on damage mapping finite element grid | |
| Littell et al. | Effect of microscopic damage events on static and ballistic impact strength of triaxial braid composites | |
| CN107368660B (en) | A kind of analysis method of predetermined period lattice material yield surface | |
| CN110110480A (en) | A kind of carbon fiber bumper anti-collision girder construction optimum design method considering laying compatibility | |
| CN112528537A (en) | Variable-stiffness composite material structure analysis method for compression stability | |
| Xu et al. | Process integration and optimization of ICME carbon fiber composites for vehicle lightweighting: a preliminary development | |
| CN110728081B (en) | Composite material layering sequence optimizing system | |
| CN116306140A (en) | Composite material fiber direction simulation modeling method | |
| Tian et al. | Buckling optimization of curvilinear fiber-reinforced composite structures using a parametric level set method | |
| CN113011014B (en) | Composite material layering optimization method and system | |
| CN110941922A (en) | Simulation method for predicting damage between composite laminated plate layers and between fiber bands | |
| CN108595724A (en) | Composite material revolving meber design method | |
| CN114912306A (en) | Modeling method of 2.5D woven composite material flat plate structure multi-scale model | |
| Sachdeva et al. | Stress Development Analysis within Composite Laminate for Different Layup Orientations |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| AD01 | Patent right deemed abandoned |
Effective date of abandoning: 20221206 |
|
| AD01 | Patent right deemed abandoned |