MSC Laminate Modeler Version 2008 User's Guide

MSC Laminate Modeler

Version 2008User’s Guide

Worldwide Webwww.mscsoftware.com

DisclaimerThis documentation, as well as the software described in it, is furnished under license and may be used only in accordance with the terms of such license.MSC.Software Corporation reserves the right to make changes in specifications and other information contained in this document without prior notice.The concepts, methods, and examples presented in this text are for illustrative and educational purposes only, and are not intended to be exhaustive or to apply to any particular engineering problem or design. MSC.Software Corporation assumes no liability or responsibility to any person or company for direct or indirect damages resulting from the use of any information contained herein.User Documentation: Copyright ©2008 MSC.Software Corporation. Printed in U.S.A. All Rights Reserved.This notice shall be marked on any reproduction of this documentation, in whole or in part. Any reproduction or distribution of this document, in whole or in part, without the prior written consent of MSC.Software Corporation is prohibited.The software described herein may contain certain third-party software that is protected by copyright and licensed from MSC.Software suppliers. Contains IBM XL Fortran for AIX V8.1, Runtime Modules, (c) Copyright IBM Corporation 1990-2002, All Rights Reserved. MSC, MSC/, MSC Nastran, MD Nastran, MSC Fatigue, Marc, Patran, Dytran, and Laminate Modeler are trademarks or registered trademarks of MSC.Software Corporation in the United States and/or other countries. NASTRAN is a registered trademark of NASA. PAM-CRASH is a trademark or registered trademark of ESI Group. SAMCEF is a trademark or registered trademark of Samtech SA. LS-DYNA is a trademark or registered trademark of Livermore Software Technology Corporation. ANSYS is a registered trademark of SAS IP, Inc., a wholly owned subsidiary of ANSYS Inc. ACIS is a registered trademark of Spatial Technology, Inc. ABAQUS, and CATIA are registered trademark of Dassault Systemes, SA. EUCLID is a registered trademark of Matra Datavision Corporation. FLEXlm is a registered trademark of Macrovision Corporation. HPGL is a trademark of Hewlett Packard. PostScript is a registered trademark of Adobe Systems, Inc. PTC, CADDS and Pro/ENGINEER are trademarks or registered trademarks of Parametric Technology Corporation or its subsidiaries in the United States and/or other countries. Unigraphics, Parasolid and I-DEAS are registered trademarks of UGS Corp. a Siemens Group Company. All other brand names, product names or trademarks belong to their respective owners.

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C o n t e n t sMSC Laminate Modeler User’s Guide

1 OverviewPurpose 2

MSC.Laminate Modeler Product Information 3

What is Included with this Product? 4

MSC.Laminate Modeler Integration with MSC.Patran 5

What is MSC.Laminate Modeler? 6

2 TutorialIntroduction 10

Composite Materials and Manufacturing Processes 11Composite Materials 11Common Material Forms 11Common Manufacturing Forms 12

Composites Design, Analysis and Manufacture 15The Development Process 15Requirements of CAE Tools for Composites Development 15Composites Development Within the MSC.Patran Environment 19

Draping Simulation (Developable Surfaces) 21Definition of Developable Surfaces 21Example of Waffle Plate 21Benefits of MSC.Laminate Modeler 23

Draping Simulation (Non-Developable Surfaces) 24Definition of Non-Developable Surfaces 24Benefits of MSC.Laminate Modeler 29

Building Models using Global Layers 30Global Layer Description of Layup 30Example of a Top Hat Section 31Benefits of MSC.Laminate Modeler 33

MSC Laminate Modeler User’s Guide

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Results Processing 34Recovering Results by Global Layer 34Example of a Top Hat Section 34Benefits of MSC.Laminate Modeler 37

Structural Optimization 38Introducing Iteration to the Development Process 38Example of a Torque Tube with a Cutout 38Benefits of MSC.Laminate Modeler 41

Glossary 42

3 Using MSC.Laminate ModelerProcedure 44

Element Library 46Supported Element Topologies 46Supported Element Types 46Supported Element Property Words 46

Initialization 48

Creating Materials 49Create LM_Material Add Form 51Modify LM_Material Form 52Show LM_Material Form 53Delete LM_Material Select Form 54

Creating Plies 55Create LM_Ply Add Form (Draping) 56Create LM_Ply Add Form (Projection) 68Modify LM_Ply Form 69Show LM_Ply Graphics Form 70Delete LM_Ply Select Form 71

Creating a Layup and an Analysis Model 72Create LM_Layup Add Form 73Modify LM_Layup Add Form 80Show LM_Layup Exploded View Form 81Show LM_Layup Cross Section Form 82Show LM_Layup Element Form 83Show LM_Layup Element Info Form 84Transform LM_Layup Mirror Form 85Delete LM_Layup Select Form 86

vCONTENTS

Creating Solid Elements and an Analysis Model 87Create Solid Elements LM_Layup Form 88

Creating Laminate Materials 89Create Laminate LM_Layup Form 90Show Laminate Form 92Delete Laminate Select Form 93Delete Property Set Select Form 94

Creating Sorted Results 95Create LM_Results LM_Ply Sort Form 96Create LM_Results Material ID Sort Form 97

Creating Failure Results 98Create LM_Results Failure Calc Form 99

Creating Design and Manufacturing Data 101Create Ply Book Layup Form 102

Importing Plies and Models 103Import Plies File Form 104Import Model File Form 105

Importing and Exporting Laminate Materials 106Import Laminate LAP Form 107Export Laminate LAP Form 108

Setting Options 109Set Export Options Form 110Set Display Options Form 112

Session File Support 116

Public PCL Functions 117

Data Files 125

4 Example:Laminated PlateOverview 128

Model Description 129

Modeling Procedure 130

Step-By-Step 132


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5 TheoryThe Geometry of Surfaces 140

The Fabric Draping Process 142

Results for Global Plies 151

Composite Failure Criteria 155

A Bibliography

Chapter 1: OverviewMSC Laminate Modeler User’s Guide

1 Overview

Purpose 2

MSC.Laminate Modeler Product Information 3

What is Included with this Product? 4

MSC.Laminate Modeler Integration with Patran 5

What is MSC.Laminate Modeler? 6

MSC Laminate Modeler User’s GuidePurpose

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PurposePatran comprises a suite of products written and maintained by MSC.Software Corporation. The core of the product suite is Patran, a finite element analysis pre and postprocessor. Patran also includes several optional products such as application modules, advanced postprocessing programs, tightly coupled solvers, and interfaces to third party solvers. This document describes one of these application modules. For more information on the Patran suite of products, see the Patran Reference Manual.

MSC.Laminate Modeler is a Patran module for aiding the design, analysis, and manufacture of laminated composite structures. The user can simulate the application of layers of reinforcing materials to selected areas of a surface to ensure that a design is realizable. Layers are then used to build up the composite construction in a manner that reflects the manufacture of the structure. Finite element properties and laminated materials are automatically generated so that accurate models of the structure can be evaluated rapidly. Alternative solutions can be compared to optimize the structure at an early stage of the development process.

3Chapter 1: OverviewMSC.Laminate Modeler Product Information

MSC.Laminate Modeler Product InformationMSC.Laminate Modeler is a product of MSC.Software Corporation. The program is available on all Patran supported platforms and allows identical functionality and file support across these platforms.

MSC Laminate Modeler User’s GuideWhat is Included with this Product?

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What is Included with this Product?The MSC.Laminate Modeler product includes all of the following items:

1. PCL command and library files which add the MSC.Laminate Modeler functionality definitions into Patran.

2. An external executable program for Layup manipulation and composite ply generation.3. This Application Preference User’s Guide is included as part of the product. An online version is

also provided to allow the user direct access to this information from within Patran.

5Chapter 1: OverviewMSC.Laminate Modeler Integration with Patran

MSC.Laminate Modeler Integration with PatranFigure 1-1 indicates how the MSC.Laminate Modeler library and associated programs fit into the Patran environment.

Figure 1-1 MSC.Laminate Modeler Integration with Patran Environment

MSC Laminate Modeler User’s GuideWhat is MSC.Laminate Modeler?

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What is MSC.Laminate Modeler?MSC.Laminate Modeler is a Patran module for aiding the design, analysis, and manufacture of laminated composite structures. By enabling the concept of concurrent engineering, MSC.Laminate Modeler allows the production of structures which take full advantage of these materials in the aerospace, automotive, marine, and other markets. The quality of the development process can be greatly improved because of the rigorous and repeatable manner in which MSC.Laminate Modeler defines fibre orientations.

MSC.Laminate Modeler incorporates two key functionalities: simulation of the manufacturing process, and storage and manipulation of composite data on the basis of global layers.

Process SimulationProcess simulation methods include draping of fabrics using various material and manufacturing options, in addition to the more conventional techniques of projecting fibre angles onto a surface. These options allow the use of MSC.Laminate Modeler for various production methods including manual layup of pre-preg materials, Resin Transfer Moulding (RTM) and filament winding. Furthermore, MSC.Laminate Modeler reflects the open systems philosophy of Patran and can cater to customized simulation methods developed by customers.

Composite Data ManagementAll data produced by the manufacturing simulation are stored together and referenced as a single data entity. This structured representation allows efficient data handling in the actual design environment. For example, to apply predefined layers to an analysis model, the user simply adds them to a table in a process which reflects the real-world manufacture of the finished component. Alternative layups can be generated and evaluated rapidly to allow the designer to optimize the composite structure using existing structural analysis tools. The process of defining layups is inherently traceable, unlike the situation in conventional composites analysis where data is reduced to an unstructured element-based level which has no physical analogy.

The functions available within MSC.Laminate Modeler allows the designer to visualize the manufacturing process and estimate the quantity of material involved. Representative analysis models of the component can be produced very rapidly to allow effective layup optimization. Finally, a “ply book” and other manufacturing data can be produced.

These functions promise a significant increase in the efficiency of the development process for high-performance composite structures.

7Chapter 1: OverviewWhat is MSC.Laminate Modeler?

MSC Laminate Modeler User’s GuideWhat is MSC.Laminate Modeler?

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Chapter 2: TutorialMSC Laminate Modeler User’s Guide

2 Tutorial

Introduction 10

Composite Materials and Manufacturing Processes 11

Composite Materials and Manufacturing Processes 11

Composites Design, Analysis and Manufacture 15

Draping Simulation (Developable Surfaces) 21

Draping Simulation (Non-Developable Surfaces) 24

Building Models using Global Layers 30

Results Processing 34

Structural Optimization 38

Glossary 42

MSC Laminate Modeler User’s GuideIntroduction

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IntroductionThis manual is intended to introduce the reader to the most common methods of composite manufacture, and define what is required of an effective tool for simultaneous composites engineering. Thereafter, some examples of the use of the MSC.Laminate Modeler are presented to illustrate the usefulness of this module in the composites development process.

11Chapter 2: TutorialComposite Materials and Manufacturing Processes

Composite Materials and Manufacturing Processes

Composite MaterialsComposite materials are composed of a mixture of two or more constituents, giving them mechanical and thermal properties which can be significantly better than those of homogeneous metals, polymers and ceramics. An important class of composite materials are filamentary composites which consist of long fibres embedded in a tough matrix. Materials of this type include graphite fibre/epoxy resin composites widely used in the aerospace industry, and glass fibre/polyester mixtures which have wide applicability in the marine and automotive markets. Because of their predominance in high-quality structures which need to be analyzed before manufacture, the term composite material will refer to a filamentary composite having a resin matrix in this document. Furthermore, it will be assumed that the composite is manufactured in distinct layers, which is appropriate for almost all filamentary composite materials.

By decreasing the characteristic size of the microstructure and providing large interface areas, the toughness of the composite material is improved significantly compared with that of a homogeneous solid made of the same material as the fibres. In addition, the manufacturing processes of many components can be simplified by applying the fibres to the component in a manner which is compatible with its geometry. These and other considerations mean that composite materials are an effective engineering material for many types of structure.

However, filamentary composite materials are often characterized by strongly anisotropic behavior and wide variations in mechanical properties which are a direct result of the manufacturing route for a component. In addition, the cost of a composite component is highly dependent on the way the fibres are applied to a surface. This means that designers must be aware of the consequences of manufacturing considerations from the beginning of the development phase.

Common Material FormsFilamentary composite materials are usually placed in components as tows (bundles of individual fibres) or as fabrics which have been processed in a separate operation.

TowsA large proportion of commercially-produced components are built up from layers of fibre tows laid parallel to each other. Each tow consists of a large number of individual fibres as each fiber is usually too thin to process effectively. For example, graphite tows typically contain between 1000 to 10000 fibres. Tows containing many fibres result in cheaper components at some expense of mechanical properties.

Composite structures built up from tows have the greatest volume fraction of fibres which usually lead to the most favorable theoretical mechanical properties. They are also characterized by extreme anisotropy. For example, the strength and stiffness of a resulting layer may be ten times greater in the direction of the fibres compared with an orthogonal direction.

MSC Laminate Modeler User’s GuideComposite Materials and Manufacturing Processes

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FabricsIndividual tows may also be woven or stitched into fabrics which are used to form the component. This method effectively allows much of the fibre preparation to be completed under controlled conditions, while components can be rapidly built up from fabric during the final stage of manufacture.

Composite structures built up from fabrics are generally easier to manufacture and exhibit superior toughness compared with those built up from tows, with some loss in ultimate mechanical properties.

MixedSome processing methods allow the user to mix tows and fabrics to achieve optimum performance. An example of this is a composite I-beam, where the shear-loaded web consists of a fabric, while the axially-loaded flanges have a high proportion of fibres oriented along the beam.

Common Manufacturing FormsComposite structures are manufactured using a wide variety of manufacturing routes. The ideal processing route for a particular structure will depend on the chosen fiber and matrix type, processing volume, quality required, and the form of the component. All these issues should be addressed right from the beginning of the development cycle for a component or structure.

A feature of almost all the manufacturing processes is that the fibres are formed into the final structure in layers. The thickness of each layer typically ranges between 0.125 mm (0.005”) for aerospace-grade pre-pregs up to several millimeters for woven rovings (say, 0.25”). This means that a component is usually built up of a large number of layers which may be oriented in different directions to achieve the desired structural response.

Another consequence of layer-based manufacturing is that a laminated area is usually thin compared with its area. This means that the dominant loads are in the plane of the fibres, and that classical lamination theory (which assumes that through-thickness stresses are negligible) and shell finite elements can be used to conduct representative analyses. In contrast, in particularly thick or curved skins, inter-laminar tensile and shear stresses can be significant. This can seriously compromise static and fatigue strength and may require the use of through-thickness reinforcement. Another consequence of thick laminates is that the analyst must use special thick shell or solid elements to model the stress fields correctly.

Wet LayupIn the wet layup process, fibres are placed on a mould surface in fabric form and manually wetted-out with resin. Wet layup is widely used to make large structures, like the hulls of small ships.

This process is amenable to high production rates but results in wide variations in quality. In particular, the inability to control the ratio of fibres to resin means that the mechanical properties of the laminate will vary from point-to-point and structure-to-structure.

13Chapter 2: TutorialComposite Materials and Manufacturing Processes

Pre-Preg LayupIn this process, tows or fabrics are impregnated with controlled quantities of resin before being placed on a mould. Pre-preg layup is typically used to make high-quality components for the aerospace industry.

This process results in particularly consistent components and structures. Because of this, pre-preg techniques are often associated with sophisticated resin systems which require curing in autoclaves under conditions of high temperature and pressure. However, the application of pre-preg layers to a surface is highly labor-intensive, and can only be automated for a small class of simple structures.

Compression MouldingCompression moulding describes the process whereby a stack of pre-impregnated layers are compressed between a set matched dies using a powerful press, and then cured while under compression. This method is often used to manufacture small quantities of high-quality components such as crash helmets and bicycle frames.

Due to the use of matched dies, the dimensional tolerances and mechanical properties of the finished component are extremely consistent. However, the requirement to trim the component after curing and the need for a large press means that this method is extremely expensive. Also, it is very difficult to make components where the plies drop off consistently within the component.

Resin Transfer Moulding (RTM) / Structural Reaction Injection Moulding (SRIM)Here, dry fibres are built up into intermediate preforms using tows and fabric held together by a thermoplastic binder. One or more preforms are then placed into a closed mould, after which resin is injected and cured to form a fully-shaped component of high quality and consistency. The in-mould cycle time for RTM is of the order of several minutes, while that for SRIM is measured in seconds.

As fibres are manipulated in a dry state, these processes provide unmatched design flexibility. RTM produces good-quality components efficiently but incurs high initial costs for tooling and development. As a result, there is often a cross-over point between pre-preg layup and RTM for the manufacture of high-quality components like spinners for aero engines. At a lower level, SRIM is used for the manufacture of automotive parts which have a lower volume fraction of fibres.

Filament WindingIn this method, tows are wet-out with resin before being wound onto a mandrel which is rotated in space. This process is used for cylindrical and spherical components such as pipes and pressure vessels.

Winding is inherently automated, so it allows consistent components to be manufactured cheaply. However, the range of component geometries amenable to this method is somewhat limited.

Automated Tow PlacementThis development of filament winding utilizes a computer-controlled 5-axis head to apply individual tows to a mandrel rotating in space. This allows the manufacture of complex surfaces, such as entire helicopter body shells with speed and precision.

MSC Laminate Modeler User’s GuideComposite Materials and Manufacturing Processes

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Of course, the equipment required for manufacture is extremely expensive, being of the order of $1 million. In addition, the possibilities for fibre placement are so controllable that no component can possibly make use of the capabilities of the process at present. However, the development of CAE tools for optimized design of composite structures will increase its usefulness in the future.

15Chapter 2: TutorialComposites Design, Analysis and Manufacture

Composites Design, Analysis and Manufacture

The Development ProcessThe development process for any component consists of design, analysis and manufacturing phases, which are sometimes undertaken by separate groups within large organizations. However, for composites, these functions are inextricably linked and must be undertaken simultaneously if the component is to be manufactured economically. Thus, the principles of concurrent engineering must be followed particularly closely for composites development.

In general, the development process incorporates three phases:

Conceptual Development - here, the development team generates a number of conceptual solutions based on their interpretation of the requirements and knowledge of composite materials and processes.

Outline Development - thereafter, surface geometry is defined, a preliminary layup determined and analysis undertaken. Based on the interpretation of analysis results, the outline design may be modified through several iterations before an acceptable solution is reached.

Detailed Development - detailed drawings of the structure and required tooling are prepared together with plans for production.

Requirements of CAE Tools for Composites DevelopmentThe outline development process is the most critical phase in refining a design solution. Composite components and structures can be an order of magnitude more complex than items made of homogeneous materials. It is, therefore, essential to automate many repetitive tasks using computer-based tools. Depending on the application, these tools should have one or more of the features defined below.

Integration of CAD/CAE/CAM SystemsIt is important to integrate all tools for composites engineering within a single environment to allow simultaneous development of a product (see Figure 2-1).

Furthermore, all design and manufacturing information should be readily transferable to and from a CAD system so that the intent of an optimized design can be realized.

MSC Laminate Modeler User’s GuideComposites Design, Analysis and Manufacture

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Figure 2-1 Integrated Composites Development Environment

Layer-Based ModelingThe fundamental requirement is that the CAE tools treat the composite structure in a manner which reflects the real-world structure. In particular, many conventional CAE tools store and manipulate data on the basis of laminate materials as shown in Figure 2-2. This representation means that the model becomes extremely complicated as soon as the layers making up the structure overlap. In contrast, all CAE tools should store the data describing the structure in terms of its constituent layers. This ensures that the construction is always representative of the manufacturing method, making the model easy to understand. Furthermore, changes are easily effected by adding and removing layers.


Figure 2-2 Comparison of Global Layer and Laminate Material Descriptions for a Simple Structure

Layer-Based Results ProcessingAny optimization during the development process is likely to involve the interpretation of results for various analyses. These results should be interpreted on the basis of layers, in the same way that the component is manufactured.

Furthermore, it should be possible to visualize results in the reference system of the material making up a layer, even where this reference system changes constantly over a surface.

Mass and Cost CalculationThe cost of composites materials are generally high. A CAE tool should allow the designer to interrogate the materials usage and approximate cost at any point in the development cycle.

Visualization ToolsSufficient visualization tools should be provided to ensure that the form of the structure is easily checked and communicated. Such tools would include the ability to interrogate the extent and orientation of


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layers, generate core samples at various points, generate cross sections along arbitrary lines, and generate a layer sequence table.

Manufacturing GuidesAny CAE tool should produce fool-proof manufacturing guides, so that the design and analyses components are actually manufactured. For structures manufactured from sheet materials, this could take the form of a “ply-book” which has a page for every layer. This should present the cutout shape, views of the three-dimensional moulded shape and other essential information.

Mould Surface and Insert Shape DefinitionTypically, layers will be placed on a male or female mould surface. If the mould tool is closed. The software should calculate the exact thickness of the laminate stack which has been defined. This should include the effect of thickening which can occur as woven material is sheared to conform to a surface. Thereafter, a second mould surface should be defined which is offset from the original surface by the correct amount.

It should also be possible to define a secondary mould surface, and automatically define the cutout shapes of individual plies required to fill the entire mould.

Materials Data ManagementBecause composite materials are generally anisotropic, and have more variability in their properties than homogeneous materials, it is important to store and manipulate materials data in a consistent manner throughout the design process. In particular, the same data should be used for all subsequent analyses, so that any change is reflected throughout the entire cycle.

The state of composite materials can also be highly dependent on temperature, moisture content, and even the degree of shear which might be induced in a manufacturing process. This means that all data should be stored as a function of state, and the correct information retrieved for any analysis.

Because of the wide variety of states possible, material property data will only be available for a few states. It is, therefore, necessary to interpolate material property data for intermediate states in a rational and repeatable manner. For example, if the properties of fabric are known when the warp and fill fibers are 90 and 60 degrees apart, the software should also calculate equivalent properties for 75 degrees separation.

Drape AnalysisA large proportion of composite structures are manufactured by placing essentially two-dimensional sheets of fabric onto three-dimensional surfaces. If the surface has curvature, then the shape of the sheet cannot be inferred directly from a projection of the surface onto a plane. Therefore, the draping simulation software must produce the cutout shape of the layer before it is applied to the surface.

If the surface is doubly-curved at any point, it is non-developable. In this case, the sheet material must shear in its plane to allow it to conform to the surface. The software must illustrate the degree of shearing in the sheet, and update the material property references to account for the changed material state. The


shearing also means that the orientation of the material changes dramatically over a curved surface. The correct orientations must therefore be passed through transparently to all relevant analysis codes.

Sheet material can be extremely expensive. Therefore, so-called nesting software should be used to minimize the material required by aligning and placing the cutouts in an optimum way.

Structural AnalysisAny composite part must be thoroughly analyzed to ensure that it will withstand service loads. Many composite components are relatively thin so that through-thickness stresses are low. This means that shell elements can be used to model the structure adequately. However, to model through-thickness stresses, solid elements must be used. For some problems, such as investigating through-thickness stresses at edges, many high-order elements will be required through the thickness of the laminate to model stresses at all reasonably.

A major concern with composite materials are their resistance to damage, as the degradation of the material is very complex and not well understood. It is, therefore, important that the structural analysis codes provide for modelling the initiation, growth and effects of defects.

Resin Flow AnalysisResin flow should be analyzed for processes such as RTM to ensure that pockets of air are not trapped in the moulding, causing defects. In addition, resin flow has a dominant effect on cycle time, with its ongoing effect on manufacturing cost.

Cure AnalysisThe curing of a composite component should be analyzed to determine the cycle time of the process. Also, it is essential to determine the extent of springback in the cured component.

Mould Tool AnalysisMould tool analysis is required to estimate deflections in the tool where small tolerances are required. The thermal behavior of the mould can also have a significant effect on the cutting of a composite component.

Composites Development Within the Patran EnvironmentThe Patran environment provides a rich core environment for the development of composite structures. Existing links are readily used to import geometry from leading CAD systems including CATDirect, CADDS 5, Unigraphics, Pro/ENGINEER and Euclid 3. Meshing and other general pre and postprocessing functions are available within Patran itself. Finally, the preference system enables the seamless use of a variety of analysis systems which would be useful for composites development.

MSC.MvisionMSC.Mvision allows the user to store and handle complex materials data such as that required for composites development.


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MSC.Laminate ModelerThe MSC.Laminate Modeler adds dedicated layer-based modeling and results processing functionality to Patran. This support greatly improves the ability of the user to define and modify representative composite structures, and then analyze their behavior using analysis packages supported by preferences.

The module also includes a drape simulation facility which can handle non-developable surfaces. This allows the user to understand the deformation required of a sheet of fabric to cover a surface, predicts realistic material orientations over individual elements, and produces cutout shapes for use by CAM systems.

Patran FEAThis general-purpose finite element analysis solver includes QUAD4/8 and TRI3/6 laminates shell elements which account for bending and extension deformation of a shell. The linear strain elements also model the transverse shear flexibility of the laminate.

HEX8/20 and WEDGE6/15 elements are available to model the flexibility of a laminate in all directions.

All composite elements provide the facility for inputting nonlinear material properties.

Patran CompositeThis specialized finite element analysis solver is used for detailed analysis of laminates with complex fibre geometry or unusual material behavior. It utilizes a family of elements with tri-cubic interpolation functions, with up to HEX64 topology. These allow the calculation of high stress gradients, such as occur at free edges or in components which suffer severe thermal stress during processing.

21Chapter 2: TutorialDraping Simulation (Developable Surfaces)

Draping Simulation (Developable Surfaces)

Definition of Developable SurfacesAn important subset of curved surfaces is developable surfaces. These surfaces can always be manufactured using sheet materials without the material needing to shear. At any point, there will be no curvature in one direction and maximum curvature in the orthogonal direction. Mathematically, this means that these surfaces are characterized by zero Gaussian curvature over their entire area. Cylinders are one example of developable surfaces found in many structures.

Note that all developable surfaces are ruled surfaces. However, not all ruled surfaces are developable. For example, a hyperbola of one sheet (such as a cooling tower shape) is not developable.

Although many CAD systems have provision for developing flat patterns from developable surfaces, the definition of material orientation is not trivial, particularly when the curvature is great.

The draping process for development is unique. That means that the cutout profile is always the same, and that definition of fibre orientation at any point uniquely describe the fibre orientations at all other points on the surface.

Example of Waffle PlateOne example of a developable surface with complex fibre orientations is a waffle plate used as a core for sandwich structures. A typical geometry for a circular sandwich structure is shown in Figure 2-3. As the core is predominantly loaded in shear, it would be if the majority of fibres lay in the +/-45 directions along the webs. However, if these directions are ideal for one web, they will obviously not be the same for other webs.

MSC Laminate Modeler User’s GuideDraping Simulation (Developable Surfaces)

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Figure 2-3 Geometry of a Curved Waffle Plate

The MSC.Laminate Modeler can be used to quantify the effect of varying fibre orientation both qualitatively and quantitatively. For example, if a piece of woven fabric is draped from the middle rib so that the average angle is +/-45 along the webs of the central rib, we see that the angle on the webs near the edge of the plate are more like 0/90. This latter direction will obviously result in poor shear stiffness and strength in this direction.

Having understood this limitation, the designer can then make an informed decision whether to specify a quai-isotropic layup for the whole of the waffle plate, or to make the waffle plate out of several different plies oriented in different directions. Both alternatives can be modeled and analyzed rapidly using the MSC.Laminate Modeler, and an informed choice made on the basis of analysis results.

23Chapter 2: TutorialDraping Simulation (Developable Surfaces)

Figure 2-4 Variation of Fibre Angles over Waffle Plate

Benefits of MSC.Laminate Modeler1. Visual feedback of fibre orientation.2. Accurate orientation data for analysis model.3. Exact flat-pattern generation.

MSC Laminate Modeler User’s GuideDraping Simulation (Non-Developable Surfaces)

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Draping Simulation (Non-Developable Surfaces)

Definition of Non-Developable SurfacesNon-developable surfaces are those which cannot be formed from sheet material without the material shearing in its plane. Surfaces of this type have curvatures in two different directions (they are therefore often called doubly-curved surfaces). Although these surfaces are usually more difficult to manufacture than flat or developable surfaces, their form gives them great stiffness and strength.

Because composite materials can often shear during the manufacturing process, they are more suitable for manufacturing these shapes than conventional materials like aluminium. This magnifies the advantage of laminated composite materials for many classes of structure.

Gaussian CurvatureThe extent of double curvature at any point is reflected in a value called the Gaussian curvature. This is the product of the curvatures in the principal directions at any point on a surface. The Gaussian curvature reveals many of the characteristics of a surface. Positive Gaussian curvature means that the surface is locally dome-shaped, with the curvatures in the same direction with respect to the surface normal. In contrast, negative Gaussian curvature implies saddle-shaped topology, with curvatures in opposite directions. Finally, zero Gaussian curvature is characteristic of a developable area.

Note that surfaces often have varying Gaussian curvature over their extent. As an example, a torus (donut) is saddle-shaped on the inside (negative Gaussian curvature) but dome-shaped on the outside (positive Gaussian curvature).

Gaussian curvature can be given a physical significance by drawing geodesic lines on a surface. (Geodesic lines are straight in the plane of the surface at any point; meridians are geodesic, but lines of latitude are constantly turning in one direction with respect to the surface.) A pair of lines which are initially parallel will tend to converge on surfaces of positive Gaussian curvature, but will diverge on a surface of negative Gaussian curvature. In contrast, the lines will remain parallel on the surface until they reach an edge if the surface is developable.

Another interpretation of Gaussian curvature is the extent of misfit in the surface. Consider a circular disk made up of several flat segments. This necessarily has zero Gaussian curvature even if it is bent along the joints between segments. However, if one of the segments is removed and the neighboring segments joined, the disk will adopt a dome-like shape which is indicative of positive Gaussian curvature. In contrast, adding a segment will result in the disk forming a saddle-like shape with negative Gaussian curvature.

Drape Simulation for Non-Developable SurfacesDraping of non-developable surfaces is an extremely difficult task. Essentially, this process involves extremely large geometric and, perhaps, material nonlinearities. A direct consequence of this is that there is no unique solution for the draping process. The draped shape is highly dependent on the point at which the draping starts, the directions in which the draping proceeds and the properties of the material itself. In addition, if there is interaction between different layers, friction between them would have a

25Chapter 2: TutorialDraping Simulation (Non-Developable Surfaces)

significant effect. A detailed analysis of the draping process for arbitrary geometries is therefore a considerable analysis task in itself.

This difficulty in analysis reflects a real-world difficulty in manufacturing complex composite components consistently. Engineering drawings of composite components typically specify fibre angles within a tolerance of 3 degrees. In practice, if there is significant curvature in a surface, the manufacturing tolerance could easily reach 15 degrees or more.

These problems can be mitigated to a large extent by limiting the degree of shear developed within reinforcing layers during the manufacturing process. The degree of shear is primarily dependent on the Gaussian curvature and the area of a layer. Therefore, a design incorporating two layers of excessive shear can be replaced by three smaller layers with less shear and greater quality. The MSC.Laminate Modeler employs a rapid draping module which allows the designer to investigate the likely degree of shear, and make rational engineering decisions on the basis of manufacturing simulations.

Whatever simulation process is used, two different levels of draping should be considered. Local Draping reflects the behavior of an infinitesimal material element applied to a point on a surface having general curvature. This is a material characteristic and is determined from tests on materials. In contrast, Global Draping considers how the many material elements are placed on a surface, and is dependent on the manufacturing process used.

Local Draping ModelsLocal draping is concerned with fitting a small section of material to a generally-curved surface. If the surface has nonzero Gaussian curvature, the material element must shear in its plane to conform to the surface. This deformation is highly dependent on the microstructure of the material. As a result, local shearing behavior can be regarded as a layer material property.

Figure 2-5 Scissor Draping Mechanism


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Figure 2-6 Slide Draping Mechanism

MSC.Laminate Modeler currently supports two local draping algorithms: scissor and slide draping. For scissor draping (Figure 2-5), an element of material which is originally square shears in a trellis-like mode about its vertices to form a rhombus. In particular, the sides of the material element remain of constant length. This type of deformation behavior is characteristic of woven fabrics which are widely used to manufacture highly-curved composite components.

For slide draping (Figure 2-6), two opposite sides of a square material element can slide parallel to each other while their separation remains constant. This is intended to model the application of parallel strips of material to a surface. It can also model, very simply, the relative sliding of adjacent tows making up a strip of unidirectional material.

When draping a given surface using the two different local draping algorithms, the shear in the layer builds up far more rapidly for the slide draping mechanism than for the scissor draping mechanism. This observation is compatible with actual manufacturing experience that woven fabrics are more suitable for draping curved surfaces than unidirectional pre-pregs.

For small deformations, the predictions of the different algorithms are practically identical. Therefore, it is suggested that the scissor draping algorithm be used in the first instance.

Global Draping ModelsGlobal draping is concerned with placing a real sheet of material onto a surface of general curvature. This is not a trivial task as there are infinite ways of doing this if the surface has nonzero Gaussian curvature at any point. Therefore, it is important to define procedures for the global draping simulation which are reproducible and reflect what can be manufactured in a production situation. As a result, global draping behavior can be regarded as a manufacturing, rather than material, property.

The MSC.Laminate Modeler currently supports three different global draping algorithms: Geodesic, Planar and Energy. For the Geodesic global draping option, principal axes are drawn away from the starting point along geodesic paths on the surface (i.e., the lines are always straight with respect to the surface). Once these principal axes are defined, there is then a unique solution for draping the remainder of the surface. This may be considered the most “natural” method and appropriate for conventional laminating methods. However, for highly-curved surfaces, the paths of geodesic lines are highly dependent on initial conditions and so the drape simulation must be handled with care.


For the Planar global draping option, the principal axes may be defined by the intersection of warp (and weft for scissor draping) planes which pass through the viewing direction. This method is appropriate where the body has some symmetry, or where the layup is defined on a space-centered rather than a surface-centered basis.

Finally, the Energy global draping option is provided for draping highly-curved surfaces where the manufacturing tolerances are necessarily greater. Here, the draping proceeds outwards from the start point, while the direction of draping is controlled by minimizing the shear strain energy along each edge.

Example of a Pressure VesselMany pressure vessels are made of composite materials, particularly via the filament winding process. However, it is often necessary to add woven reinforcements to the shell. In this case, it is vital to understand the mechanics of the draping process because the curvature of the surface varies so much. In particular, the body of a pressure vessel is developable and has zero gaussian curvature. In contrast, the ends have constant positive Gaussian curvature.

If draping begins at the pole of the vessel (Figure 2-7), the shear in the material increases rapidly away from the start point due to the severe curvature. The amount of shearing is indicated by the color of the draping pattern lines. Note that the degree of shear is zero along the principal axes, which are defined by geodesic lines.

The draping algorithm stops where the shear reaches the cutoff value for the material, or the override value defined in the Additional Controls form. This gives an indication of where the material would fold when being formed.


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Figure 2-7 Fibre Directions for Draping Starting at the Pole of the Vessel

To cover the same area, it is also possible to begin draping on the cylindrical part of the surface (Figure 2-8). Because this region is developable, there is no shear deformation until the end cap is reached. This means that the average degree of shear on the surface is much lower, which should lead to better quality and better mechanical performance.


Figure 2-8 Fiber Directions for Draping Starting on the Cylindrical Part of the Vessel

Benefits of MSC.Laminate Modeler1. Visual feedback of fibre orientation.2. Visual feedback of material shear.3. Orientation data for analysis model.4. Flat pattern generation.

MSC Laminate Modeler User’s GuideBuilding Models using Global Layers

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Building Models using Global Layers

Global Layer Description of LayupThe model is built up from predefined layers using a spreadsheet. This mirrors the use of layup tables in the final drawings of a component. The models are easily modified by defining, adding and deleting new layers to or from the layup.

Figure 2-9 Spreadsheet For Defining the Layup Using Predefined Layers

31Chapter 2: TutorialBuilding Models using Global Layers

Example of a Top Hat SectionA typical top-hat section subjected to pressure and bending load will be used to illustrate the building of models using global layers. The model itself consists of a total of 52 global layers arranged in 4 different laminates. To model this structure properly, using conventional methods, would require the definition of 11 different property regions containing between 16 and 48 layers each. This would be tedious to define, and almost impossible to modify if the user wished to conduct a rapid sensitivity analysis.

Figure 2-10 Geometry of the Top Hat Section

MSC Laminate Modeler User’s GuideBuilding Models using Global Layers

32

Figure 2-11 Lamination Specification of the Top Hat Section

In contrast, the MSC.Laminate Modeler user simply needs to define four layers which cover the areas of each laminate. Then, multiples of these layers are added to the model, using the layup spreadsheet. Because the surface is developable, it is permissible to use the Angular Offset option to modify the orientation of the plies at 45, 90 and -45 to the original layers. All the generation of representative property regions would be handled completely automatically by the software.

33Chapter 2: TutorialBuilding Models using Global Layers

Figure 2-12 Visualization of Geometry Covered by Layer_3

The greatest benefit would, of course, accrue if the model needed to be changed after a preliminary analysis. For example, the user may wish to define localized reinforcement at the attachment end of the section. This could be completed in a matter of minutes by defining additional layers and adding them to the layup.

Benefits of MSC.Laminate Modeler1. Rapid layer-based generation and modification of model.

MSC Laminate Modeler User’s GuideResults Processing

34

Results Processing

Recovering Results by Global LayerConventional systems present stresses on the basis of a particular layer on individual elements. If any element is reversed, or there are ply drop-offs on the surface, the produced results cannot be interpreted meaningfully.

In contrast, the MSC.Laminate Modeler rearranges analysis results stored in the database so that they refer to global layers defined in the layup spreadsheet. This means that the results for a physically meaningful piece of fabric are presented together. This is a unique capability for the majority of codes that store composite data on the basis of laminate materials.

Example of a Top Hat SectionFringe plots for stresses along the fibres are presented for global layers 1, 17, 21 and 33 for the top-hat section model. Using conventional post-processors, this would give misleading results due to the variation of layup over the model. In contrast, all stresses presented here are continuous, indicating that the correct results have been grouped for each global layer.

Figure 2-13

35Chapter 2: TutorialResults Processing

Figure 2-14 Layer Results

MSC Laminate Modeler User’s GuideResults Processing

36


37Chapter 2: TutorialResults Processing


Benefits of MSC.Laminate Modeler1. Flexible layer-based results processing.

MSC Laminate Modeler User’s GuideStructural Optimization

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Structural Optimization

Introducing Iteration to the Development ProcessThe ability to modify a composite model rapidly and asses results on a realistic basis opens up many opportunities for the optimization of composite structures. This is essential to compete with highly-optimized structures made of conventional materials, and bring the cost of composite structures down to a competitive level.

Example of a Torque Tube with a CutoutA tube subject to torsional loading and having a large cutout is representative of a number of structures, including the chassis of a single-seater racing car. A layup was defined, using two global layers covering the entire surface, and the rim around the cutout respectively as shown in Figure 2-17 and Figure 2-18.

Figure 2-17 Analysis Model of Torsion Tube

39Chapter 2: TutorialStructural Optimization

Figure 2-18 Stiffened Collar

Models were built with a uniform layup, and including layer_2 reinforcement around the cutout. Analyses were then conducted for both configurations. As shown in the deformation plot in Figure 2-19, the torsional load generates substantial out-of-plane deflections around the cutout. Therefore, it is to be expected that reinforcing the cutout edge will have a significant effect on the structural performance of the tube.

MSC Laminate Modeler User’s GuideStructural Optimization

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Figure 2-19 Deformed Shape of Analysis Model

The analysis results for both models are summarized in the table below.

This clearly shows that the addition of local reinforcing in highly-loaded areas can have an extremely significant effect on overall structural performance. By allowing the designer to quantify the effects of localized reinforcement, the MSC.Laminate Modeler will enable the development of more efficient structures.

Property Uniform Layup Reinforced Layup DifferenceLayup layer_1 (0/45/-45/90)

layer_1 (90/-45/45/0)layer_2 (0/45/-45/90)layer_1 (0/45/-45/90)layer_1 (90/-45/45/0)layer_2 (90/-45/45/0)

layer_2 (0/45/-45/90)layer_2 (90/-45/45/0)

Mass 4.826 kg 5.035 kg 0.209 kg (+4.3%)Rotation 0.143 0.118 -0.025 (-18%)Max. Deflection 2.817 mm 1.800 mm -1.017 mm(-36%)Max. Tensile Fiber Stress 165 MPa 122 MPa 43 MPa (-26%)Max. Compressive Fiber Stress

186 MPa 121 MPa 65 MPa (-35%)

41Chapter 2: TutorialStructural Optimization

Benefits of MSC.Laminate Modeler1. Rapid modify-analyze-interpret cycle allows optimization.

MSC Laminate Modeler User’s GuideGlossary

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Glossary(ISO 10303 equivalent terms in parentheses)

layer (Ply)

An area on a surface having consistent material properties, fiber orientation and thickness. A layer is analogous to one or more pieces of fabric which are applied to a surface adjacent to each other and in a similar way.

layup sequence (Layup_ply_table)

An assembly table which provides an ordered list of layers.

layup (Ply_laminate)

A collection of one or more layers which mate with one another.

Chapter 3: Using MSC.Laminate ModelerMSC Laminate Modeler User’s Guide

3 Using MSC.Laminate Modeler

Procedure 44

Element Library 46

Initialization 48

Creating Materials 49

Creating Plies 55

Creating a Layup and an Analysis Model 72

Creating Solid Elements and an Analysis Model 87

Creating Laminate Materials 89

Creating Sorted Results 95

Creating Failure Results 98

Creating Design and Manufacturing Data 101

Importing Plies and Models 103

Importing and Exporting Laminate Materials 106

Setting Options 109

Session File Support 116

Public PCL Functions 117

Data Files 125

MSC Laminate Modeler User’s GuideProcedure

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ProcedureThe MSC.Laminate Modeler is a specialized tool for the creation and visualization of a ply-based laminated composite model. An analysis model consisting of appropriate laminate materials and element properties can be generated automatically for a number of different analysis codes. Following analysis, specific composite results can be calculated to verify the performance of the model. The general process for generating a laminate composite model is as follows:

1. Create Homogeneous Materials (Patran)Materials are typically orthotropic, and the user should specify failure coefficients when defining materials.

2. Create Mesh (Patran)The surface on which the composite layup is to be built is defined by the shell elements of the finite element mesh in the Patran database. The user should generate a mesh of sufficient resolution for both drape simulation and analysis purposes. It is a requirement that the meshing is completed before starting a session. Use the tools in the Finite Element application to verify the element normals and the free edges of the model before creating a new Layup file.

3. Create Ply Materials (MSC.Laminate Modeler)These materials are analogous to raw ply materials and include a reference to a homogeneous material for specifying mechanical properties, as well as manufacturing related information like thickness.

4. Create Plies (MSC.Laminate Modeler)Create plies in a manner which reflects the manufacturing process.

5. Create a LM_Layup and an Analysis Model (MSC.Laminate Modeler)A layup, or sequence of plies, is defined, allowing the creation of corresponding laminate materials and element properties required to define an analysis mode..

6. Analyze (Patran and analysis code)The analysis is submitted in the usual way. The user may have to explicitly request layered composites results from the analysis code.

7. Create Results (MSC.Laminate Modeler)The user may sort results on the basis of physical plies or define new ones based on a failure analysis.

These operations are summarized schematically overleaf.

45Chapter 3: Using MSC.Laminate ModelerProcedure

Overview

Figure 3-1 Overview of MSC.Laminate Modeler Process

MSC Laminate Modeler User’s GuideElement Library

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Element LibraryStandard shell elements define the surfaces used in the MSC.Laminate Modeler module. The standard Patran geometry and mesh generation commands can be used to create a valid model.

The elements in the Patran database are used to define the draping surface in addition to acting as analysis elements

Supported Element Topologies

Figure 3-2 Element Types

After the laminate descriptions have been generated they are applied to the Finite Element model in a controlled manner. The user is allowed to select the type of element for the currently selected analysis preference.

Supported Element Types1. Property selection and generation has been significantly enhanced from previous versions.

MSC.Laminate Modeler is no longer restricted to generating the data for MSC’s own preferences. Any suitably customized database will allow the generation of the required laminate materials and properties.

2. Selection of the thermal composite elements is now possible because of the redesign.3. SAMCEF is supported by writing an external file for inclusion into the BACON BANQUE file.

Supported Element Property WordsThe routine for creating properties extracts the data from the database and compares it against values that are consistently used for the type of data required by MSC.Laminate Modeler.

The PROP_IDS that are recognized are:

47Chapter 3: Using MSC.Laminate ModelerElement Library

If the applicable data type for the prop_ids described is not available, then the MSC.Laminate Modeler cannot generate the required property cards.

PROP IDS DESCRIPTION DATA TYPEID_PROP_MATERIAL_NAME(13) Laminated material name generated by

MSC.Laminate Modeler.MATERIAL_ID(5)

ID_PROP_ORIENTATION_ANG(20) This will be set to 0.0. The Laminate materials are built to reflect the different relative angles.

REAL_SCALAR(1)

ID_PROP_ORIENTATION_SYS(21) This prop_id is used to allow the creation of additional reference coordinate frames. Users are prompted whether or not they wish to create the frames.

COORD_ID(9)

ID_PROP_ORIENTATION_AXIS(1079) The property call is made reflecting the occurrence of this prop_id.

INTEGER_SCALAR(3)

MSC Laminate Modeler User’s GuideInitialization

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InitializationThe initialization form controls the opening of the current MSC.Laminate Modeler database (Layup) file and the resultant display of the main Action Object Method control forms. To display the initialization form, select MSC.Laminate Modeler from the Tools menu.

49Chapter 3: Using MSC.Laminate ModelerCreating Materials

Creating MaterialsWhen using MSC.Laminate Modeler there are three levels of material generation.

1. Patran homogeneous materials should be generated using standard Patran functionality. These contain mechanical, thermal or physical data which can be manually input or imported Using Patran Materials (p. 10) in the Patran Materials Enterprise.

1. MSC.Laminate Modeler ply materials. These ply materials have thickness and manufacturing data in addition to a reference to an appropriate material in the Patran database. These ply materials are used to create plies in the MSC.Laminate Modeler module.

1. Patran laminate materials which are built up from Patran homogeneous materials by the MSC.Laminate Modeler software on the basis of the user-specified layup sequence, offsets and tolerances.

Patran Homogeneous Material DefinitionThe main description of the materials is done using the standard Patran methods of definition. The Materials form can be used to generate the required materials. Methods available include user input, external definition and Patran Materials.

MSC.Laminate Modeler Ply Material DefinitionThe homogeneous materials created, within the standard Patran form, are referenced within the MSC.Laminate Modeler Create LM_Material Add form to generate ply materials with extended property sets which include thickness and manufacturing data, such as the maximum strain allowable during draping.

Material Application TypesPly materials are categorized by the way in which they are applied to a selected surface. They reference particular types of Patran homogeneous materials.

• PaintedIsotropic materials are supported for Painting.

• Projected2D/3D orthotropic and anisotropic materials are supported for Projecting.

• Scissor Draped2D/3D orthotropic and anisotropic materials are supported for Scissor Draping.

• Slide Draped2D/3D orthotropic and anisotropic materials are supported for Slide Draping.

MSC Laminate Modeler User’s GuideCreating Materials

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Additional Ply Material Parameters• Thickness • The thickness of a single ply of the material before it is sheared.• Maximum Strain

The allowable strain value before the material “locks” (i.e., the material can no longer conform to the surface by shearing). This is measured in degrees.

• Initial Warp/Weft Angle This value describes the original undeformed angle between warp and weft yarns in a fabric. This value can be overridden on the Create LM_Ply Add, Additional Parameters form. This allows deformation of the fabric before it is placed on the model, which may achieve better draping. This angle is measured in degrees.

Paint Project Scissor SlideThickness Yes Yes Yes YesMaximum Strain No No Yes YesInitial Warp/Weft Angle No No Yes No


Create LM_Material Add FormThis form allows the user to generate MSC.Laminate Modeler ply materials which reference Patran homogenous materials and contain additional thickness and manufacturing data.


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Modify LM_Material Form


Show LM_Material Form


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Delete LM_Material Select Form

55Chapter 3: Using MSC.Laminate ModelerCreating Plies

Creating PliesWhat is a Ply?A ply is an area of LM_Material which is stored and manipulated as a single entity. A ply represents a piece of reinforcing fabric which is cut from sheet stock and placed on a mould during the manufacturing process. A ply is fully characterized by the LM_Material it is made of, the area it covers, and the way in which it is applied to the surface. The latter is particularly important for non-developable surfaces where there are many different ways of placing the fabric on a surface.

Figure 3-3 LM_Ply Description

Why use Plies?Plies allow easy manipulation of complex data when you assemble and/or modify the layers to form the complete layup. The physical representation of a ply is a piece of fabric.

MSC Laminate Modeler User’s GuideCreating Plies

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Create LM_Ply Add Form (Draping)

Note: When a ply is created, a group of the same name and containing the Area Definition entities is created.


Input Data Definitions

Start Point

This defines the starting point of the drape simulation process. It is analogous to the point at which a ply is first attached to a mould surface during manufacture. As the distortion usually increases away from the starting point, it is best to begin draping near the center of a region to minimize shear distortion. If the start point coordinates do not lie on the selected surface, the coordinates are projected onto the surface along the application direction vector. The start point must lie on the selected area.

Application Direction

The application direction defines the side of the surface area on which a ply is subsequently added when the final layup is defined. The “Top” of the surface covered by the ply is defined as the side on which the ply is originally applied when created. When defining a layup, the ply can be added to the “Top” or “Bottom” side of the mesh. It follows that the “Top” side is the same side as the application direction used to define the ply, whereas the “Bottom” side is the side opposite the application direction.

The concept of side is very important as composite structures are often built using molds or forms, limiting the side of application to a single direction. The plies of reinforcing fabric can be added to either the outside of a male mould or the inside of a female mould. When defining plies and a layup, it is useful to consider the manufacturing process.

The application direction is also used to project the start point and reference direction onto the surface.

Reference Direction

The reference direction is used to specify the initial direction of the fabric. The input vector is projected onto the surface along the application direction to define the principal warp axis of the material at the


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start point. Note that the direction of the material will usually change away from the starting point if the surface is curved.

Reference Angle

The principal warp axis of the material on the surface can be rotated from the reference direction by inputting a non-zero reference angle. This rotation is counterclockwise when viewed along the application direction.

Figure 3-4 Effect of Application Direction on Warp Orientation

Note that the application direction is used to project the start point and reference direction vector onto the selected surface. This means that the same start point and reference direction vector results in different values when projected onto the surface along different application directions, as shown in Figure 3-4. It follows that the start point and reference direction should be defined as close to the surface as practical, while the application direction should be defined as perpendicular to the surface as possible.


Figure 3-5 Projection of Reference Direction

Example of Starting Definitions


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This example shows the view as it would appear in the viewport in addition to the input that would appear on the Create LM_Ply Add form.

Axis TypeThe principal warp and weft axes are the paths the warp and weft fibers follow along the surface away from the start point. By defining the paths of the principal axes, it is possible to constrain the ply uniquely in the region bounded by the principal axes.

The principal axes can be defined in different ways:

• NoneNo principal axes are defined, draping proceeds using the extension method only.

• GeodesicThe principal axes are defined by geodesic lines from the start point.


• PlanarThe principal axes are defined by the intersection of planes defined by the start point, application direction and reference direction rotated about the application direction through the reference angle.

Extension Type

The extension type controls the draping process if no axis type is defined, or the draping extends beyond the region uniquely defined by the principal axes. In this case, the material cells on each edge are kinematically unconstrained, and so some extension type must be specified to control the extension of the fabric.

The extension mechanism can be defined in different ways:

• GeodesicThe fiber closest to the principal axis is identified and extended along the surface along a geodesic path. The adjacent fabric cells are then uniquely constrained.Note that the geodesic extension method yields an identical result to that produced using geodesic principal axes, followed by geodesic extension where necessary.

• EnergyThe mechanism defined by the free edge cells is rotated in such a way as to minimize the shear strain energy in that free edge, using the assumption that the shear load-deflection behavior is linear (this could be extended for nonlinear response).

• MaximumThe mechanism defined by the free edge cells is rotated in such a way as to minimize the maximum shear strain in that free edge.


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Additional Controls Form - Geometry


Additional Controls Form - Material


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Additional Controls Form - Boundaries


Figure 3-6 Split Example

Note: Avoid starting to drape near split definitions to prevent ambiguous draping results.


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Additional Controls Form - Order of Draping


Note: This capability is particularly useful when draping over a series of conical sections. First drape the most critical section, ensuring minimal shear. Thereafter, drape peripheral areas.


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Create LM_Ply Add Form (Projection)


Modify LM_Ply Form


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Show LM_Ply Graphics Form


Delete LM_Ply Select Form

Note: When an LM_Ply is deleted, the group of the same name created at LM_Ply creation time will also be deleted.

MSC Laminate Modeler User’s GuideCreating a Layup and an Analysis Model

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Creating a Layup and an Analysis ModelThe individual LM_Plies are used to define the model LM_Layup using the Create LM_Layup Add form. When this form is selected, a spreadsheet for the Layup definition and forms for the relevant tolerances can be accessed. The forms are described on the following pages.

These forms are used to create and maintain the analysis layup. As well as providing tools to modify and redefine the layup, the forms will generate the correct laminate materials and apply the correct properties to the model. If all other operations are complete (i.e., Loads/BC addition), the model is ready for analysis after these forms have been applied.

73Chapter 3: Using MSC.Laminate ModelerCreating a Layup and an Analysis Model

Create LM_Layup Add Form


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Layup Definition Form

The spreadsheet is used to specify which of the previously defined LM_Plies are used in the generation of the model LM_Layup. The form allows the selection and ordering of the required LM_Plies. Manipulation of the LM_Plies within the spreadsheet is used to create different stacking sequences and layups.

Select the specific LM_Ply from the definitions in the Existing LM_Plies frame The method of application of that LM_Ply to the existing layup is controlled by the LM_Layup Controls. Continue by Adding, Inserting, and Deleting LM_Plies until the LM_Layup is finished.

LM_Plies can be added to the layup at any time to reinforce the model between analyses. The ability to redefine laminates rapidly is one of the key features of the MSC.Laminate Modeler.

The spreadsheet works in two distinct but connected modes. They are called “Expanded” and “Compressed.” In expanded mode, the multiplier column on the spreadsheet is always set equal to 1. This enables you to work at the level of single LM_Plies and the Delete and Replace commands will only act on the single LM_Ply selected. In compressed mode, the Delete and Replace commands can be used to


do multiple “single actions” at the same time. For example, if a row is specified as having a multiplier of 10, then a replace instruction will replace all 10 rows with the new LM_Ply. The same is true for delete.

You can switch between the two methods at any time and take advantage of the quicker set up time of the stack building, while still being able to modify the LM_Ply sequence at the single LM_Ply level if required.

Make current definition a total definition.

Make the current definition symmetrical by copying LM_Plies.

Make the current definition symmetrical about the bottom LM_Ply.

Split the current definition in half.

Split the current definition in half as if the current definition is symmetrical about a mid-LM_Ply.

Cut data from selected spreadsheet cells.

Copy data from selected spreadsheet cells

Paste data cut or copied from selected spreadsheet cells


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Figure 3-7 Icons on LM_Layup Create Spreadsheet

Paste mirrored data cut or copied from selected spreadsheet cells

Undo the last command for the LM_Layup definition spreadsheet.


Offset Definition Form

Important: Ignore Offsets is required for analysis preferences like ABAQUS and Patran Advanced FEA which do not allow any offset definition for composite shells. This is not the same as having an offset = 0.0. An offset with a specified value will cause an error as it is interpreted as a set value.


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Select Element Type Form


Tolerance Definition Form


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Modify LM_Layup Add Form

As only a single layup is allowed in a single Layup file, the form for layup modification is identical to that for layup creation.


Show LM_Layup Exploded View Form

This capability allows the user to verify the definition and application direction of the plies defined in a layup.


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Show LM_Layup Cross Section Form

This capability allows the user to define cross-section plots of the plies defined in a layup.


Show LM_Layup Element Form

This capability allows the user to verify the resulting layup on individual elements. Visualization capabilities are similar to those provided by the Show Laminate function.


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Show LM_Layup Element Info Form


Transform LM_Layup Mirror Form

This capability allows the user to model a repeated unit of a symmetrical model, and mirror as appropriate to generate the full model. For example, only one half of a composite chassis may be modeled prior to mirroring the mesh and layup about the center plane.


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Delete LM_Layup Select Form

This form allows the user to delete the single layup defined in the current Layup file.

87Chapter 3: Using MSC.Laminate ModelerCreating Solid Elements and an Analysis Model

Creating Solid Elements and an Analysis ModelThe MSC.Laminate Modeler defines a ply layup on a 2D shell mesh. The majority of analyses can be conducted using shell elements as through-thickness effects are relatively insignificant. However, if the laminate is thick, and especially if the surface is curved, it may be necessary to use solid elements to model structural behavior adequately.

For these situations, the MSC.Laminate Modeler includes the capability to extrude shell elements through a distance equal to the laminate thickness. Furthermore, laminate materials and element properties can be created automatically to allow accurate analysis. If the analysis code does not support laminated solid elements, the laminate materials are converted to equivalent anisotropic materials for subsequent analysis.

MSC Laminate Modeler User’s GuideCreating Solid Elements and an Analysis Model

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Create Solid Elements LM_Layup Form

This capability allows the user to generate solid elements and the associated materials and element properties needed for detailed analysis of thick laminates.

89Chapter 3: Using MSC.Laminate ModelerCreating Laminate Materials

Creating Laminate MaterialsThe MSC.Laminate Modeler generates laminate materials and element properties when creating or modifying a layup, or when creating solid elements. Additional capabilities are provided for advanced users who need greater control over the creation of the analysis model. For example, when using MSC.Nastran, the user can align the laminate materials using several different methods such as using coordinate systems or specified vectors.

The procedure followed for generating an analysis model is as follows. The MSC.Laminate Modeler stores warp angle, weft angle and thickness data for every element making up a ply. When a layup is created, the total material definition on every element can be defined. By default, angle data is specified with respect to the first edge of every element.

The next step is to transform this angle data to the angle definition system required by the selected element type. For example, the projection of a vector onto each element may be used as the basis for defining laminate material orientations. This allows the program to calculate a corresponding laminate material on each element.

However, it is generally unwieldy to define a laminate material per element for large models which may contain over a hundred thousand elements. Hence, a sorting mechanism is invoked to identify a minimum number of materials within the user-defined tolerance.

The analysis model can become complicated due to the continuous variation of fiber direction over curved surfaces. Verification tools allow the user to show the layer thickness and orientations on any element in the model. This capability can be used even if conventional techniques have been used to define the composites model, or legacy analysis files have been imported into Patran.

MSC Laminate Modeler User’s GuideCreating Laminate Materials

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Create Laminate LM_Layup Form


Laminate Options Form

Preview Form


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Show Laminate Form


Delete Laminate Select Form


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Delete Property Set Select Form

95Chapter 3: Using MSC.Laminate ModelerCreating Sorted Results

Creating Sorted ResultsMost analysis codes which generate results for laminated composite materials define the layer results as the stacking sequence number with respect to the element orientation system. If there are ply drop-offs or elements are reversed, the stacking sequence number bears no direct relationship to the physical plies.

To overcome this problem, two results sorting procedures are supported. If the analysis model has been generated using laminate modeler, the results can be sorted quite simply using data stored in the Layup file. Otherwise, results can be sorted on the basis of underlying material IDs, if the ID is only used once on every element over a selected area.

MSC Laminate Modeler User’s GuideCreating Sorted Results

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Create LM_Results LM_Ply Sort Form

97Chapter 3: Using MSC.Laminate ModelerCreating Sorted Results

Create LM_Results Material ID Sort Form

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Creating Failure ResultsFailure indices according to various criteria can be calculated from layered results.

Note that these are based on calculated results and do not affect the analysis model itself. Therefore, they rely on the assumption of linearity and are only valid for first ply failure.

99Chapter 3: Using MSC.Laminate ModelerCreating Failure Results

Create LM_Results Failure Calc Form

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Material Allowables Form

101Chapter 3: Using MSC.Laminate ModelerCreating Design and Manufacturing Data

Creating Design and Manufacturing DataIt is important to integrate the design, analysis and manufacture of laminated composites. In particular, it is important that the model analyzed is equivalent to the manufactured part. Therefore, a ply book containing design and manufacturing data can be produced at any time.

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Create Ply Book Layup Form

103Chapter 3: Using MSC.Laminate ModelerImporting Plies and Models

Importing Plies and ModelsUsually, a new Layup file is created once a mesh has been finalized in the Patran database. If the user subsequently changes the mesh, the elements in the database and those in the Layup file no longer correspond. This can lead to errors because the elements selected in the viewport may not have the same IDs as those used for internal operations. For this reason, a warning is issued if the database mesh does not correspond to the Layup file mesh when opening a new Layup file.

In addition, it may be desirable to import plies from another Layup file, which may have a different element definition. For example, a draping simulation tool embedded in a CAD package could generate a Layup file which has no knowledge of the analysis mesh.

The Import Ply capability has been developed to allow users to remesh as required and also import of data from other draping systems. In order to do this, it is necessary to generate a mapping between the current mesh and the imported mesh. This mapping is calculated by element matching or piercing.

The MSC.Laminate Modeler first tires to find a direct match between current and imported elements by identifying elements with the same nodal coordinates. Where such a match is identified, the layup on the imported element can be transferred directly to the current element as necessary. The matching process is relatively fast.

Where a current element has no direct match, mapping is determined through piercing. Here, a normal vector is calculated at the centroid of each current element and any intersections with imported elements are calculated. If there are multiple intersections, that closest to the centroid is chosen. The distance between the centroid and intersection point is calculated, as is the angle between the current normal and the normal of the intersected imported element. If both the calculated distance and angle are less than the distance and angular tolerances respectively, the layup on the intersected element is mapped onto the current element. This piercing process is relatively slow due to the multiple calculations required.

In addition to ply import, it is also possible to import a complete composites model definition stored in a Layup file. This will copy the mesh and materials from the Layup file into a Patran database so that further operations like ply creation can be conducted as normal. This feature means that composite models can be transferred and stored by means of the Layup file alone.

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Import Plies File Form

105Chapter 3: Using MSC.Laminate ModelerImporting Plies and Models

Import Model File Form

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Importing and Exporting Laminate MaterialsThe MSC.Laminate Modeler generates laminate materials based on a ply layup. However, under certain circumstances, it is desirable to export or import laminate materials to or from specialized tools used for laminate analysis. The MSC.Laminate Modeler includes and interface to the LAP laminate analysis program developed by Anaglyph Ltd. (www.anaglyph.co.uk).

During preliminary design, the user can define a baseline laminate material within LAP and save this data in a text file. This information can be imported into Patran and referenced by element properties in the normal way. This basic laminate can be optimized for loading and manufacturing criteria using the tools within the MSC.Laminate Modeler.

Following analysis, the user can export laminate material and load information to LAP in order to examine and report stresses.

107Chapter 3: Using MSC.Laminate ModelerImporting and Exporting Laminate Materials

Import Laminate LAP Form

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Export Laminate LAP Form

109Chapter 3: Using MSC.Laminate ModelerSetting Options

Setting OptionsOptions for the display of graphical information in a viewport, and the export of manufacturing data, must be set before creating plies and layups.

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Set Export Options Form


Flat Pattern Example

Figure 3-8 Example Flat Pattern

The 2D flat pattern shape can be generated in different formats. The DXF format is typically used to drive nesting and cutting machines.

Note that the flat pattern shape does not indicate the edges of the fabric where the maximum strain value has been exceeded.


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Set Display Options Form


Additional Forms Controlling Ply and Layup Graphics


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Flat Pattern Display on Screen

Figure 3-9 Flat Pattern Displayed on Screen

The flat pattern shape is displayed on the screen perpendicular to the application direction arrow. The variation that occurred between the draped fabric on the model and the undeformed fabric shape can be seen.


Figure 3-10 Flat Pattern Displayed for Surface with Split Definition

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Session File SupportMSC.Laminate Modeler can be run from a session file if required. The session file should contain calls to the public PCL functions defined in the next section. These functions correspond to user interface forms in the usual way. If required, the contents of a session file can be modified manually before being replayed to change the layup.

Replaying a session file also allows the user to remesh surfaces if area selection is done by reference to geometrical entities, such as <Surface 4 8>. However, care must be taken with the selection of the start point and the reference direction to make sure that they correspond to the remeshed model.

Note that running a session file will be slightly different from undertaking an interactive run because the forms will not appear or be filled with the corresponding data.

It is also advisable to change the full path names for the files to just the file names. For example: “/usr/people/demo/test/testrun. Layup” becomes “testrun.Layup”.

Important: Session File edits.

117Chapter 3: Using MSC.Laminate ModelerPublic PCL Functions

Public PCL FunctionsThese functions correspond to user interface forms in the usual way. They can be used by running a session file, or calling them directly from other PCL functions. In either case, it is important that the PCL library <laminate_modeler.plb> is available to the session, and the executable <layup> is in the path

Begins a MSC.Laminate Modeler session using a new Layup file with the name <filename>.

Begins a MSC.Laminate Modeler session by opening an existing Layup file with the name <filename>.

Saves a copy of the current Layup file with the name <filename>.

p3cm.new ( <filename> )

Input:STRING <filename> Name of the new Layup file.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.

p3cm.open ( <filename> )

Input:STRING <filename> Name of the existing Layup file.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.

p3cm.save_as ( <filename> )

Input:STRING <filename> Name of the target Layup file.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine

is successful.

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Creates a new material

p3cm.create_material_add ( <type_name>, <material_name>, <analysis_material_name>, <thickness>, <max_strain>, <warp_weft_angle> )

Input:STRING <type-name> Application type.STRING <material_name> Material name.STRING <analysis_material_name> Analysis material name.REAL <thickness> Initial thickness of the ply material.REAL <max_strain> Maximum permissible strain of the ply material.REAL <warp_weft_angle> Initial angle between warp and weft fibres.Output:INTEGER <Return Value> Status return value. The value will be 0 if the

routine is successful.


Creates a new ply.

p3cm.create_ply_add ( <type_name>, <material_name>, <ply_name>, <start_pt>, <appliqueing>, <ref_dirn>, <ref_ang>, <warp_weft_angle>, <max_strain>, <step_length>, <axis_type>, <max_sweeps>, <bounds>, <area_str>, <split_str> )

Input:STRING <type_name> Application type.STRING <material_name> Ply material name.STRING <ply_name> Ply name.REAL ARRAY <start_pt> Coordinates of starting point.REAL ARRAY <appliqueing> Vector defining application direction.REAL ARRAY <ref_dirn> Vector defining the reference direction.REAL <ref_ang> Reference angle.REAL <warp_weft_angle> Initial angle between warp and weft fibres.REAL <max_strain> Maximum permissible strain of the ply material.REAL <step_length> Step length.INTEGER <axis_type> Axis type.INTEGER <max_sweeps> Maximum number of sweeps.REAL ARRAY <bounds> Maximum fabric bounds.STRING <area_str> Selected area.STRING <split_str> Split definition.Output:INTEGER <Return Value> Status return value. The value will be 0 if the



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Creates a new layup.

p3cm.create_layup_add (<num_plies>, <ply_names>, <type_names>, <instances>, <sides>, <offsets>, < num_offs>, <off_values>, < off_flags>, < off_starts>, <off_views>, < off_areas>, < num_tols>, <ang_tols>, <thick_tols>, <tol_areas>, <model_flag>, < element_type>, <solid_flag>, <bacon_flag> )

Input:INTEGER <num_plies> Number of plies.STRING ARRAY <ply-names> Ply names.STRING ARRAY <type_names> Application types.INTEGER ARRAY <instances> Instances.STRING ARRAY <sides> Side of application.REAL ARRAY <offsets> Angular offset values.INTEGER <num_offs> Number of offset regions defined.REAL ARRAY <off_values> Value of offset.STRING ARRAY <off_flags> Side of offset.REAL ARRAY <off_starts> Coordinates of starting points for offset definition.REAL ARRAY <off_views> Vectors defining view direction for offsets.STRING ARRAY <off_areas> Selected areas for offset definition.INTEGER <num_tols> Number of tolerance regions defined.REAL ARRAY <ang_tols> Angular tolerance values (degrees).REAL ARRAY <thick_tols> Thickness tolerance values(degrees).STRING ARRAY <tol_areas> Selected areas for tolerance definition.LOGICAL <model_flag> Generate analysis model.STRING <element_type> Selected element type.LOGICAL <solid_flag> Generate solid element file.LOGICAL <bacon_flag> Generate BACON command file.Output:INTEGER <Return Value> Status return value. The value will be 0 if the



Deletes an unused material.

Deletes an unused ply.

Creates sorted results.

p3cm.delete_material_name (<type_name>, <material_name> )

Input:STRING <type_name> Application type.STRING <material_name> Material name.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine

is successful.

p3cm.delete_ply_name (<type_name>, < ply_name> )

Input:STRING <type_name> Application type.STRING <ply_name> Ply name.Output:INTEGER <Return Value> Status return value. The value will be 0 if the


p3cm.create_results_sort (<res_names> )

Input:STRING ARRAY <res_names> A string array containing the loadcase name, subcase

name, primary label, secondary label and dummy layer name of result to be sorted.

Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine

is successful.


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Creates composite failure index results. These are stored in a text file and optional results in the Patran database.

p3cm.create_results_failure (<res_names>,<area>,<criterion>,<basis>,<num_mats>,<mat_names>,<mat_allows>,<name>,<ply_sort>,<ply_results>,<failure_index>,<reserve_factor>,<margin_safety>,<critical_component>,<critical_ply> )

Input:STRING ARRAY <res_names> A string array containing the loadcase name, subcase

name, primary label, secondary label and dummy layer name of result to be sorted.

STRING <area> A list of elements for which results are to be calculated.STRING <criterion> The name of the criterion to be used.STRING <basis> The basis to be used: "STRESS" or "STRAIN".INTEGER <num_mats> The number of material allowables.STRING ARRAY <mat_names> A <num_mats> array of material names.REAL ARRAY <mat_allows> A <num_mats>x<8> array of material allowables.STRING <name> Result name.LOGICAL <ply_sort> Flag to sort ply results by LM_Ply. (Not yet

implemented.)LOGICAL <ply_results> Flag to generate failure index, reserve factor, margin of

safety and critical component results for every ply in the Patran database. (Not yet implemented.)

LOGICAL <failure_index> Flag to generate failure index results in the Patran database. (Not yet implemented.)

LOGICAL <reserve_factor> Flag to generate failure index results in the Patran database. (Not yet implemented.)

LOGICAL <margin_safety> Flag to generate margin of safety results in the Patran database.

LOGICAL <critical_component> Flag to generate margin of safety results in the Patran database.

LOGICAL <critical_ply> Flag to generate critical ply results in the Patran database. Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.


Sets graphics options.

p3cm.set_graphics_options (<msg>, <ply_gr>, <layup_gr>, <view>, <init>, <maxstrn>, <area>, <cutout>, <pattern>, <offset>, <angles>, <offval>, <scale> )

Input:LOGICAL <msg> Display the message file.LOGICAL <ply_gr> Display the ply graphics control form.LOGICAL <layup_gr> Display the layup graphics control form.LOGICAL <view> Display the view direction arrow of a ply.LOGICAL <init> Display the reference direction arrow of a ply.LOGICAL <maxstrn> Display the maximum strain value of a ply.LOGICAL <area> Display the border of the selected area of a ply.LOGICAL <cutout> Display the 2D flat pattern of a ply.LOGICAL <pattern> Display the 3D draped pattern of a ply.LOGICAL <offset> Display the angles of the surface plies of a layup.LOGICAL <angles> Display the angles of a ply.REAL <offval> Offset value of the 2D flat pattern of a ply.REAL <scale> Scale value of the angles of the surface plies of a layup.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.


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Sets export options.

Deletes properties named <P3LM_prop_XXX> generated by the MSC.Laminate Modeler.

Deletes laminates named <laminate_XXX> generated by the MSC.Laminate Modeler.

p3cm.set_export_options (<pat>, <cut>, <mould>, <iges>, <dxf>, <post> )

Input:LOGICAL <pat> Export the 3D draped pattern.LOGICAL <cut> Export the 2D flat pattern.LOGICAL <mould> Export mould surface.LOGICAL <iges> Export files in IGES format.LOGICAL <dxf> Export files in DXF format.LOGICAL <post> Export files in postscript format.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.

p3cm.delete_properties_all ( )

Input:None.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.

p3cm.delete_laminates_all ( )

Input:None.Output:INTEGER <Return Value> Status return value. The value will be 0 if the routine is

successful.

125Chapter 3: Using MSC.Laminate ModelerData Files

Data FilesMSC.Laminate Modeler uses a variety of files to store and communicate the extensive data required for composites analysis. The file name prefix <filename> is set when entering the MSC.Laminate Modeler. The default prefix is the name of the database. For data files, additional suffices <.bak>, <.igs>, <.dxf> and <.ps> denote backup, IGES, DXF or postscript files respectively.

1. <filename>.Layup This is the external MSC.Laminate Modeler database.

2. <filename>.lm_msgThis message file is produced by the “layup” executable and provides a record of the ply application and manipulation processes. Any errors will always be reported in this file. This file can be displayed automatically after every user command by setting a toggle on the Set Display Options form.

3. <filename>.lm_mouldThis file contains mould surface data.

4. <filename>.lm_solidThis file contains data describing solid elements created by extruding the shell elements through the thickness of the plies.

5. <filename>.lm_baconThis file contains BACON (SAMCEF preprocessor) commands to build the analysis model.

6. <filename>.lm_reportThis file contains a text summary of the layup.

7. <filename>.lm_resultsThis file contains the results of a laminate failure analysis.

Important: Do not delete or modify this file manually.

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Chapter 4: Example:Laminated PlateMSC Laminate Modeler User’s Guide

4 Example:Laminated Plate

Overview 128

Model Description 129

Modeling Procedure 130

Step-By-Step 132

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OverviewThis example will show the use of MSC.Laminate Modeler by building and modifying a simple layup on a flat plate. The Functionality shown is extendable to general shapes.

129Chapter 4: Example:Laminated PlateModel Description

Model Description• L=Length = 10 units• H=Height = 6 Units

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Modeling ProcedureStep 1: Open a new database and set parameters

Step 2: Create a new empty group

131Chapter 4: Example:Laminated PlateModeling Procedure

Step 3: Construct the Patch

Step 4: Mesh the Patch

Use the Create action.

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Step-By-Step

133Chapter 4: Example:Laminated PlateStep-By-Step


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Chapter 5: TheoryMSC Laminate Modeler User’s Guide

5 Theory

The Geometry of Surfaces 140

The Fabric Draping Process 142

Results for Global Plies 151

Composite Failure Criteria 155

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The Geometry of SurfacesIntroductionComposite materials are typically made from sheets of materials whose thickness is very much smaller than their width. Therefore, an elementary understanding of surface geometry is essential in order to use these materials effectively.

For the purposes of engineering analyses, surfaces are generally divided into flat plates or curved shells. Compared with plate structures, shells generally exhibit superior strength and stiffness as a consequence of their curvature. Shells have traditionally been difficult to manufacture from conventional materials like aluminum, but are now readily built from plies of reinforcing fabrics which conform or drape relatively easily to surfaces of complex curvature. The potential for optimizing surface geometry leads to weight savings beyond those promised by the increase in mechanical performance alone.

The drapability of reinforcing materials results directly from their ability to shear, allowing the material to cling to surfaces without folding or tearing. It is important to understand the cause of material shear as this both changes the form of the material, and hence its mechanical properties, but also varies the alignment of the fibres with respect to the loads in the surface. The latter factor is especially vital in unidirectionally-reinforced materials where the strength and stiffness along the fibres may be more than ten times greater than in the transverse direction.

Effect of Gaussian CurvatureThe amount of shear distortion in a sheet of material is dependent on the degree of curvature of the surface and the size of the sheet. The curvature of the surface is conveniently measured by a scalar quantity called the “Gaussian curvature” which is the product of the curvature of the surface in two orthogonal principal directions. For example, the dome has positive Gaussian curvature because the sense of the curvature in two directions at 90 degrees is the same.

Gaussian curvature can be visualized easily by drawing geodesic lines on surfaces. (Geodesic lines are those that are straight in the plane of the surface, such as the meridian of a sphere.) A pair of lines which are parallel at some point will tend to converge, remain parallel or diverge on surfaces of positive, zero and negative curvature respectively.

In contrast, the cylinder has zero Gaussian Curvature as there is no curvature along its axis. All “developable” surfaces (i.e., those that can be rolled up from a flat sheet without the material shearing in its plane) necessarily have zero Gaussian Curvature over their entire area. Finally, a saddle which has curvature in two different directions, has a negative Gaussian curvature.

141Chapter 5: TheoryThe Geometry of Surfaces

Figure 5-1 Selected Shapes with Different Gaussian Curvature

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The Fabric Draping Process

The fabric draping process can be split into two sections:

1. A Local draping mechanism2. A Global draping procedure

Local DrapingLocal draping is concerned with fitting a small section of material to a generally curved surface. If the surface has nonzero Gaussian curvature, the material element must shear in its plane to conform to the surface. This deformation is highly dependent on the microstructure of the material. As a result, local shearing behavior can be regarded as a ply material property.

Figure 5-2 Scissor Draping Mechanism

Figure 5-3 Slide Draping Mechanism

MSC.Laminate Modeler currently supports two local draping algorithms: scissor and slide draping. For scissor draping, an element of material which is originally square shears in a trellis-like mode about its vertices to form a rhombus. In particular, the sides of the material element remain of constant length. This type of deformation behavior is characteristic of woven fabrics which are widely used to manufacture highly-curved composite components.

Note: Material Models for Draping.

143Chapter 5: TheoryThe Fabric Draping Process

For slide draping, two opposite sides of a square material element can slide parallel to each other while their separation remains constant. This is intended to model the application of parallel strips of material to a surface. It can also model, very simply, the relative sliding of adjacent tows making up a strip of unidirectional material.

When draping a given surface using the two different local draping algorithms, the shear in the plies builds up far more rapidly for the slide draping mechanism than for the scissor draping mechanism. This observation is compatible with actual manufacturing experience that woven fabrics are more suitable for draping curved surfaces than unidirectional pre-pregs.

For small deformations, the predictions of the different algorithms are practically identical. Therefore, it is suggested that the scissor draping algorithm be used in the first instance.

Global DrapingGlobal draping is concerned with placing a real sheet of material onto a surface of general curvature. This is not a trivial task as there are infinite ways of doing this if the surface has nonzero Gaussian curvature at any point. Therefore, it is important to define procedures for the global draping simulation which are reproducible and reflect what can be manufactured in a production situation. As a result, global draping behavior can be regarded as a manufacturing, rather than material, property.

MSC.Laminate Modeler currently supports three different global draping algorithms: Geodesic, Planar and Energy. For the Geodesic global draping option, principal axes are drawn away from the starting point along geodesic paths on the surface (i.e., the lines are always straight with respect to the surface). Once these principal axes are defined, there is then a unique solution for draping the remainder of the surface. This may be considered the most “natural” method and appropriate for conventional laminating methods. However, for highly-curved surfaces, the paths of geodesic lines are highly dependent on initial conditions and so the drape simulation must be handled with care.


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Figure 5-4 Geodesic Global Draping

For the Planar global draping option, the principal axes may be defined by the intersection of warp (and weft for scissor draping) planes which pass through the viewing direction. This method is appropriate where the body has some symmetry, or where the layup is defined on a space-centered rather than a surface-centered basis.


Figure 5-5 Planar Global Draping

Finally, the Energy global draping option is provided for draping highly-curved surfaces where the manufacturing tolerances are necessarily greater. Here, the draping proceeds outwards from the start point, while the direction of draping is controlled by minimizing the shear strain energy along each edge.

Figure 5-6 Energy Global Draping


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Note that all draping simulations are discrete and use a specific step length. A default value is calculated on the basis of the area of the selected region. This may be modified or overridden, using the step length databox on the Additional Controls/Geometry form.

The sections above relate only to how the fabric algorithm works internally. When the graphics are drawn to the screen, they are drawn in the same manner for all of the selected types, if applicable. The fabric drawing to the screen has no relevance to the method that the fabric generation routine executed. In particular, do not expect to see the fabric being drawn in a manner similar to the calculation method for the Energy Option.

Projected AnglesMSC.Laminate Modeler supports two different methods of projecting fiber angles onto a surface. In the first Planar method, the angles are defined by the intersection of parallel planes with the surface. Using the Axis method, axes are projected onto the elements and rotated as specified. The appropriate method will depend on the manufacturing process followed.

Figure 5-7 Plane X-Axis

Note: Step Length.

Note: Fabric Graphics.


Using the “Plane X-axis” option, a plane passing through the Z-axis and rotated through an angle α from the X-axis. The elemental material angle is the angle between the intersection of this plane, or one parallel to it, with the element and the first edge of the element.

“Plane Y-axis” uses plane through X-axis measured from Y-axis.

“Plane Z-axis” uses plane through Y-axis measured from Z-axis.

Figure 5-8 Projected X-axis

Using the “Project X-axis” option, the global X-axis is projected normally onto the element at the first node. This axis is then rotated through the reference angle α in the counter (anti-) clockwise direction from the viewing point. It is important to note that the element material angle θ is generally not equal the angle α.

“Project Y-axis” uses the Y-axis

“Project Z-axis” uses the Z-axis

MSC.Laminate Modeler also allows the user to define angles with respect to the element datum (i.e., the first edge of the element). This feature can also be used to visualize the relative orientation of elements where this is not immediately obvious, such as if the pave mesher is utilized.

Practical Restrictions On SurfacesThe draping simulation has been found to give realistic results for surfaces which are manufacturable using sheet materials. This is even true for surfaces having infinite curvature in a single direction (i.e.,


148

sharp edges). However, the simulation is likely to fail where it is physically impossible to drape a real sheet of material.

Geometrical features leading to poor draping include:

1. Excessive Gaussian Curvature. For example, the apex of a cone has extreme Gaussian curvature, and is therefore impossible to drape realistically. The user should use the Split Definition facility to cut the cone between its base and apex before simulating the drape.

2. Holes in Surfaces. It is recommended that holes be temporarily filled with dummy elements while a layup is being defined. If these elements are put in a separate Patran group, they can be excluded from the analysis by only analyzing the current group.

3. Incomplete Boundary Definition. Many surfaces, such as cylinders, do not have a complete boundary; draping will continue around the body until an internal program storage limit is reached. Define artificial boundaries using the split definition facility on the Create LM_Ply, Additional Controls, Definition form.


4. “T” Sections. These can be draped along three separate paths. The user must make sure that the correct elements are selected, and that a consistent definition of top and bottom surfaces is maintained. This prevent plies crossing over unexpectedly.


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151Chapter 5: TheoryResults for Global Plies

Results for Global PliesMSC.Laminate Modeler results can be rearranged to produce output for a single continuous piece of fabric rather than a local element-based ply-by-ply representation of the results. This feature is essential for proper results interpretation because a single piece of fabric may be represented by different ply numbers on different elements. The common approach to results processing is to produce results by ply number over a range of elements. This can lead to completely misleading results for typical components.The results rearrangement creates a new set of results in the database which uses the exact definition of a fabric on an element/ply-number scheme, allowing meaningful postprocessing as illustrated below.

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Example

Note: Results shown above are centroidal.

Spectrum was updated for each picture so contours were assigned per plot.

153Chapter 5: TheoryResults for Global Plies

As can be seen, the analysis references to plies can be in error. This rearrangement of results does not give “better” or “more accurate results” but provides a more realistic grouping of results. The functionality can be used to rearrange any results stored and referenced by plies in the database. For example, you could create failure criteria results using P/LAM or an in-house program, read the results into Patran, and then sort these results on the basis of global plies. The initial release of this functionality extracts and creates results at element centroids.

Some more simple examples can be used to help visualize the difference.

Note: All model dimensions are greatly exaggerated.

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Results at Multiple Sections Through a PlyThis initial version of the results manipulation always tries to operate on a single result per layer.

MSC.Laminate Modeler determines how many results there are per ply by a simple formula: the number of layer results from database divided by the maximum number of plies on any element.

If the value of this = 1 then MSC.Laminate Modeler uses that single value to create the new results.

If the value is > 1 then a further calculation is done to extract what should be a reasonable value.

For example:

155Chapter 5: TheoryComposite Failure Criteria

Composite Failure CriteriaFailure criteria for composite materials are significantly more complex than yield criteria for metals because composite materials can be strongly anisotropic and tend to fail in a number of different modes depending on their loading state and the mechanical properties of the material. While theories which reflect detailed mechanisms of failure are currently being developed, empirical criteria based on test data have been used for decades. These criteria have been incorporated in the MSC.Laminate Modeler to allow rapid evaluation of the strength of a structure according to the current industry standards. The user can also define custom criteria using PCL functions for use in specialized applications.

NomenclatureFailure criteria compare the loading state at a point (stress or strain) with a set of values reflecting the strength of the material at that point (often referred to as the material allowables). Both loading and strength values should be reflected in the same material coordinate system. For unidirectional materials, this is typically in the direction of the fibres. However, for woven and knitted fabrics , this direction is not obvious, and might change as the material is formed to shape.

In general, the load is represented by a full stress or strain tensor having six independent components. By convention, for lamina materials the material X axis lies in the direction of the warp fibres while the Z axis lies in the through-thickness direction of the sheet. Note than in Patran, shear strains are stored in tensor rather than engineering notation, and any experimental failure strengths should reflect this.

The strength of a composite can be expressed by an arbitrarily large number of values, depending on the complexity of the failure criterion. However, lamina materials, used in composites, are often assumed to be orthotropic; the through-thickness stresses or strains are ignored and it is assumed that there is negligible interaction between the different failure modes. The strength of the material can therefore be represented by seven independent variables:

In the Tsai-Wu criterion, these values have been supplemented by an interaction term which reflects the interdependence of failure modes due to loading along both the X and Y material directions.

STRESS σx,σy,σz,τxy,τyz,τxz

STRAIN εx,εy,εz,γxy,γyz,γxz

TX tensile strength along the X axis 0 < TXCX compressive strength along the X axis 0 < CXTY tensile strength along the Y axis 0 < TYCY compressive strength along the Y axis 0 < CYSXY shear strength in the XY plane 0 < SXYSYZ shear strength in the YZ plane 0 < SYZSXZ shear strength in the XZ plane 0 < SXZ

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Note that the above values can be applied to either stress or strain.

The form of the failure criterion is typically described as a mathematical function of the above variables which reaches the value of unity at failure as follows.

Failure Index = FI (load, strength) = 1

The strength of a structure can be given as a Strength Ratio (SR), which is the ratio by which the load must be factored to just fail. (Note that the Strength Ratio is not necessarily the reciprocal of the Failure Index.) Alternatively, the Margin of Safety (MoS), where MoS = SR - 1, is used.

Maximum CriterionThis criterion is calculated by comparing the allowable load with the actual strength for each component. Mathematically, it is defined by:

FI = max (σx/TX, -σx/CX, σy/TY, -σy/CY,

abs(τxy)/SXY, abs(γyz)/SYZ, abs(γxz)/SXZ)

In this case,

SR = 1/FI

Hill CriterionThe Hill criterion was one of the first attempts to develop a single formula to account for the widely different strengths in the various principal directions:

FI = FXX σx2 + FYY σy

2 + 2 FXY σx σy + FSS τxy2

where

Because this failure theory is quadratic:

SR = 1 / sqrt (FI)

IXY interaction between X and Y directions -1< IXY <1

FXX = 1/(TX TX) if σx >= 0

1/(CX CX) if σx <0

FYY = 1/(TY TY) if σy >= 0

1/(CY CY) if σy <0

FXY = -1/(2 TX TX) if σxσy >= 0

-1/(2 CX CX) if σxσy <0

FSS = 1 / (SXY SXY)


In the Laminate Modeler, the Tsai-Wu criterion for in-plane loads (representing fiber failure) has been supplemented by a maximum load theory for out-of-plane shear loads (representing matrix failure):

FI = max( abs(γyz)/SYZ, abs(γxz)/SXZ)

In this case,

SR = 1/FI

For every ply, the lower of the Margins of Safety for fibre and matrix failure is calculated and displayed.

Tsai-Wu CriterionThe Tsai-Wu failure criterion is an unashamed, empirical criterion based on the sum of the linear and quadratic invariants as follows:

where Fi and Fij are dependent on the material strengths. For the restrictions of lamina materials, this equation reduces to:

FI = FX σx + FY σy + FXX σx2 + FYY σy


where:

FX = 1/TX - 1/CX

FY = 1/TY - 1/CY

FXX = 1/(TX CX)

FYY = 1/(TY CY)

FXY = IXY sqrt(FXX FYY) = IXY / sqrt(TX CX TY CY)

FSS = 1 / (SXY SXY)

Because this failure theory is quadratic, the Strength Ratio (SR) = 1/FI. However, multiplying the failure criterion by SR and rearranging gives

a SR2 + b SR - 1 = 0

where

a = FXX σx2 + FYY σy


b = FX σx + FY σy

Therefore

SR = [-b + sqrt (b2 + 4a)] / 2a

Fi σi + Fij σi σj = 1 i,j = 1...6


158

In the Laminate Modeler, the Tsai-Wu criterion for in-plane loads (representing fiber failure) has been supplemented by a maximum load theory for out-of-plane shear loads (representing matrix failure):

FI = max( abs(γyz)/SYZ, abs(γxz)/SXZ )

In this case,

SR = 1/FI

For every ply, the lower of the Margins of Safety for fibre and matrix failure is calculated and displayed.

Extended Quadratic CriteriaThese criterion are identical to the Tsai-Wu criterion except for the calculation of the interaction coefficient FXY which is derived rather than obtained from experimental results.

HoffmanFXY = - 1 / (2 TX CX)

Hankinson

FXY = 0.5 / (1/(TX CX) + 1/(TY CY) - 1/SXY2)

Cowin

FXY = 1 / sqrt(TX CX TY CY) - 0.5 /SXY2

User-Defined CriterionThe user can write a custom PCL function to generate failure indices and margins of safety according to specialized failure criteria. For example, sophisticated failure criteria are being developed which incorporate a mixture of equations depending on the expected mode of failure. These could be expected to outperform simple criteria where there is a complex loading state, particularly within thick laminates.

To use this facility, the user should modify the function user() within the class p3CM_create_res_fail_user. A sample function based on the criteria of maximum loading is illustrated below. The function has input values of loading state and material strength data. The output values are the margin of safety, the critical component, and a failure index. The required function should be edited into a file “p3CM_create_res_fail_user.user.pcl.” This function must then be substituted for the default dummy function in the Laminate Modeler PCL library. To do this, save a backup copy of the existing laminate_modeler.plb, and issue the following commands in the command line:

!! LIBRARY ADD laminate_modeler.plb!! COMPILE p3CM_create_res_fail_user.user INTO laminate_modeler.plbThe PCL source code required to implement the maximum failure criteria follows as an example:CLASS p3CM_create_res_fail_user

FUNCTION user(res_array,mat_array,out_res_array)


REAL res_array() REAL mat_array() REAL out_res_array()

REAL sxx,syy,szz,sxy,syz,sxz REAL fxt,fxc,fyt,fyc,fs12,fs23,fs31 REAL margin,component,fi

REAL fi11t,fi11c,fi22t,fi22c,fi12,fi23,fi31

/* * Set input values. */ sxx = res_array(1) syy = res_array(2) szz = res_array(3) sxy = res_array(4) syz = res_array(5) sxz = res_array(6)

fxt = mat_array(1) fxc = mat_array(2) fyt = mat_array(3) fyc = mat_array(4) fs12 = mat_array(5) fs23 = mat_array(6) fs31 = mat_array(7)

/* * Check that failure values are reasonable. */ IF ( (fxt<=0.) || @ (fxc<=0.) || @ (fyt<=0.) || @ (fyc<=0.) || @ (fs12<=0.) || @ (fs23<=0.) || @ (fs31<=0.) ) THEN

user_message(“Ack”,4,”LAMMODEL”,”Failure strength values must be > 0.0”) RETURN

END IF

/* * Initialise variables. */ margin = 0.0 component = 1.0 fi = 1.0 sys_allocate_array(out_res_array,1,3) out_res_array(1) = 0.0 out_res_array(2) = 1.0 out_res_array(3) = 1.0


160

/* * Calculate strength ratios for each component. */ fi11t = sxx / fxt IF( fi < fi11t )THEN fi = fi11t margin = 1. / fi - 1 component = 11 ENDIF fi11c = -sxx / fxc IF( fi < fi11c )THEN fi = fi11c margin = 1. / fi - 1 component = -11 ENDIF fi22t = syy / fyt IF( fi < fi22t )THEN fi = fi22t margin = 1. / fi - 1 component = 22 ENDIF fi22c = -syy / fyc IF( fi < fi22c )THEN fi = fi22c margin = 1. / fi - 1 component = -22 ENDIF fi12 = mth_abs(sxy) / fs12 IF( fi < fi12 )THEN fi = fi12 margin = 1. / fi - 1 component = 12 ENDIF fi23 = mth_abs(syz) / fs23 IF( fi < fi23 )THEN fi = fi23 margin = 1. / fi - 1 component = 23 ENDIF fi31 = mth_abs(sxz) / fs31 IF( fi < fi31 )THEN fi = fi31 margin = 1. / fi - 1 component = 31 ENDIF /* * Set output values. */

out_res_array(1) = margin out_res_array(2) = component


out_res_array(3) = fi

END FUNCTION

END CLASS


162

Appendix A: Bibliography


A Bibliography

MSC Laminate Modeler User’s Guide164

Bibliography1. Bergsma, O.K. and Huisman, J. “Deep Drawing of Fabric Reinforced Thermoplastics,” in

Brebbia, C., et al., CAD in Composite Material Technology (Southampton, Computational Mechanics, 1988).

2. Bergsma, O.K. Deep Drawing of Fabric Reinforced Thermoplastics: Simulation and Experiment (Delft University of Technology, Department of Aerospace Engineering).

3. Calladine, C. Theory of Shell Structures, Chapter 5.4. Heisey, F.L., et al. “Three-Dimensional Pattern Drafting,” Textile Research Journal, November

1990, pp. 690-696.5. Collier, J.R., Collier, B.J., O’Toole, G. and Sargand, S.M. “Drape Prediction by Means of Finite-

Element Analysis,” J. Text. Inst., 1991, Vol. 82, No. 1, pp. 96-107.6. Heisey, F.L., and Haller, K.D. “Fitting Woven Fabric To Surfaces in Three Dimensions,” J. Text.

Inst., 1988, No. 2, pp. 250-263.7. Hinds, B.K., McCartney, J., and Woods ,G. “Pattern Development for Three Dimensional

Surfaces” (Queens University Belfast, Department of Mechanical and Manufacturing Engineering).

8. Kawabata, S. The Standardization and Analysis of Hand Evaluation, 2nd ed., (Osaka, Japan, The Textile Machinery Society of Japan, 1980).

9. Mack, C., and Taylor, H.M. “The Fitting of Woven Cloth to Surfaces,” J.Text. Inst., 1956, No. 47, pp. T477-88.

10. Mallon, P.J., O’Bradaigh, C.M., and Pipes, R.B. “Polymeric Diaphragm Forming of Complex-Curvature Thermoplastic Composite Parts,” Composites, Vol. 20, No. 1, Jan. 1989, pp.48-56.

11. Monaghan, M.R., Mallon, P.J., O’Bradaigh, C.M., and Pipes, R.B. “The Effect of Diaphragm Stiffness on the Quality of Diaphragm Formed Thermoplastic Composite Components,” The Journal of Thermoplastic Composite Materials, Vol. 3, July 1990, pp.202-215.

12. Okine, R.K. “Analysis of Forming Parts from Advanced Thermoplastic Composite Sheet Materials,” The Journal of Thermoplastic Composite Materials, Vol. 2, Jan. 1989, pp.50-77.

13. Potter, K.D. “The Influence of Accurate Stretch Data for Reinforcements on the Production of Complex Structural Mouldings -- Part 1. Deformation of Aligned Sheets & Fabrics,” Composites, July 1979, pp.161-167.

14. Potter, K.D. “The Influence of Accurate Stretch Data for Reinforcement on the Production of Complex Structural Mouldings -- Part 2. Deformation of Random Mats,” Composites, July 1979, pp. 168-173.

15. Potter, K.D. Deformation Mechanisms of Fibre Reinforcements and Their Influence on the Fabrication of Complex Structural Parts (London, Controller HMSO, 1980).

16. Robertson, R.E., et al. “Fiber Rearrangements During the Moulding of Continuous Fiber Composites. 1: Flat Cloth to a Hemisphere,” Polymer Composites, July 1981, Vol. 2, No. 3, pp. 126-131.

17. Skelton, J. Shear Of Woven Fabrics (Dedham MA, USA, FRL, 1979).

165Appendix A: Bibliography

18. Smiley, A.J., and Pipes, R.B. “Analysis of the Diaphragm Forming of Continuous Fiber Reinforced Thermoplastics,” The Journal of Thermoplastic Composite Materials, Vol. 1, Oct. 1988, pp. 298-321.

19. Stubbs, N., and Fluss, H. “A Space-truss Model for Plain-Weave Coated Fabrics,” Appl. Math. Modeling, Vol. 4, Part 1, Feb. 1980, pp. 51-58.

20. Tam, A.S., and Gutowski, T. “Ply-Slip During the Forming of Thermoplastic Composite Parts,” Journal of the ASCE Engineering Mechanics Division, Vol. 104, Part 5, Oct, 1978.

21. Testa, R.B., Stubbs, N., and Spillers, W.R. “Bilinear Model For Coated Square Fabrics,” The Journal of the ASCE Engineering Mechanics Division, Vol. 104, Part 5, Oct. 1978, pp. 1027-1042.

22. Van Der Weeen, F. “Algorithms For Draping Fabrics on Doubly-Curved Surfaces,” International Journal for Numerical Methods in Engineering, Vol. 31, 1991, pp. 1415-1426.

23. Van West, B.P., et al. The Draping and Consolidation of Commingled Fabrics (Delaware USA, Center for Composite Materials and Dept. of Mechanical Engineering, University of Delaware, 1990).

24. Wormersley, J.R. “The Application of Differential Geometry to the Study of the Deformation of Cloth Under Stress,” J. Text. Inst., 1937, pp.T97-112.

MSC Laminate Modeler User’s Guide166

MSC.Fatigue Quick Start Guide

I n d e xMSC Laminate Modeler User’s Guide

IndexIndex

Aanisotropic behavior, 11anisotropy, 11automated tow placement, 13

Bbottom, 57

CCAD systems, 19, 21CADDS 5, 19CATIA, 19composites data, 6compression moulding, 13conceptual design, 15core samples, 18cross sections, 18curved shells, 140

Ddegree of shear, 25detailed development, 15developable surfaces, 21dome-shaped surfaces, 24doubly-curved, 18doubly-curved surfaces, 24drape simulation, 20draping

global, 143local, 142scissor, 142slide, 143

Eenergy global draping, 27, 145Euclid 3, 19excessive Gaussian curvature, 148

Ffiber angles, 146

axis method, 146planar method, 146

filament winding, 6, 13filamentary composites, 11

fabrics, 11, 12glass fibre/polyester mixture, 11graphic fibre/epoxy resin, 11tows, 11

finite element analysis, 20flat plates, 140

GGaussian curvature, 24, 25, 140

negative, 24, 140positive, 24, 140zero, 140

geodesic global draping, 26, 143geodesic lines, 140global draping, 25, 26, 143

energy, 27, 145geodesic, 26, 143planar, 27, 144

Hholes in surfaces, 148

Iincomplete boundary definition, 148initial direction, 57initial direction vector, 58

Llamination theory, 12, 13layer, 42, 55


168

layer materials, 49painted, 49projected, 49scissor draped, 49slide draped, 49

layup, 42, 74layup ply table, 42layup sequence, 42layup table, 30LM_layer material, 55local draping, 25, 142

Mmanual layup, 6material generation, 49maximum strain, 50, 111mesh, 44, 57MSC.Mvision, 19MSC.Patran COMPOSITE, 20MSC.Patran FEA, 20

Nnesting software, 19non-developable, 18non-developable surfaces, 24, 55

Ooutline design, 15

Pplanar global draping, 27, 144ply, 42ply laminate, 42ply-book, 18pressure vessels, 27Pro/ENGINEER, 19production methods

filament winding, 6manual layup, 6resin transfer method (RTM), 6

Rresin flow, 19resin transfer moulding, 6, 13

RTM, 13ruled surfaces, 21

Ssaddle-shaped surfaces, 24sandwich structures, 21scissor draping, 26, 27, 142shell model, 46simulation, 6slide draping, 26, 143springback, 19SRIM, 13stacking sequences, 74step length, 146structural reaction injection moulding, 13

TT sections, 149thickness, 50top, 57top-hat section, 31

UUnigraphics, 19

Vview direction, 58

Wwaffle plate, 21warp, 144warp/weft angle, 50weft, 144wet layup, 12

Zzero Gaussian curvature, 21

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MSC Laminate Modeler Version 2008 User's Guide