Composite materials are heterogeneous materials composed of at least two integrated components. Among the different types of composite materials, layered composite materials are quite common and are widely used for aircraft, spacecraft, wind turbine, automobile, marine, buildings, and safety equipment use cases. The Composite Materials Module, add-on to the COMSOL Multiphysics® software, includes built-in features and functionality specifically designed for studying layered composite structures. Fiber-reinforced plastics, laminated plates, and sandwich panels are a few common examples of layered composite materials.

### What Is a Composite Material?

Composite materials are stronger and lighter than conventional materials, which is why they have many potential use cases in diverse areas. For instance, some industries are developing “smart” composite materials, which could have sensing, actuation, computation, communication, and other functionality. Before it’s possible to design composite structures out of these materials, though, engineers must have a good understanding of their behavior.

#### Types of Composite Materials and Their Classification

There are several ways to classify composite materials, one of which is to categorize them based on the type of constituents, namely matrix and reinforcement. Based on the type of matrix material, composite materials can be classified into the following categories:

- Polymer matrix composites (PMC)
- Metal matrix composites (MMC)
- Ceramic matrix composites (CMC)
- Carbon and graphite matrix composites (CGMC)

Based on the reinforcement shape, composite materials can be classified into fibers, whiskers, and particulates.

*Examples of fiber, whisker, and particulate composites.*

#### Benefits and Challenges of Using Composite Materials

Composite materials offer a lot of advantages when compared to conventional metallic materials. Some of the key benefits are as follows:

- High strength-to-weight ratio
- High resistance to fatigue and corrosion degradation
- Improved friction and wear properties
- Low thermal conductivity and low coefficient of thermal expansion
- Ability to tailor material properties to meet design requirements

Since composite materials are manmade, there are also some challenges involved with using these materials. Some examples include the high cost of raw materials and fabrication, difficulty in reuse and disposal, difficulty in joining different components, and various types of failure modes. They also involve anisotropic materials, hence they are challenging to analyze.

#### Industries that Use Composite Materials

Due to the benefits mentioned above, the use of composite materials is widespread in areas like:

- Aircraft (e.g., wings and fuselages)
- Defense (e.g., tanks and submarines)
- Wind turbines (e.g., blades)
- Building and construction (e.g., doors, panels, frames, and bridges)
- Chemical engineering (e.g., pressure vessels, storage tanks, piping, and reactors)
- Automobiles and transportation (e.g., bicycle and automobile components)
- Marine and railway transportation (e.g., boat hulls and rail components)
- Consumer and sports goods (e.g., tennis rackets and golf club shafts)
- Electronics (e.g., distribution pillars and link boxes)
- Orthopedic aids
- Safety equipment

#### Fiber-Reinforced Plastics

Among other composite materials, fiber-reinforced plastics (FRPs) are quite popular these days. These materials typically consist of a fibrous part, which acts as the main load-carrying element, and a surrounding matrix/resin, which supports the fiber and transfers the load. The fibers are arranged in a specified orientation in each layer (or lamina) of the material. A number of such laminae are stacked to form a laminated composite material that can be used to build a structural component. Fibers for industrial uses are, in general, made of carbon, glass, aramid, or basalt. Based on the type of fiber material, the two most popular FRPs available and typically used in the industry are carbon-fiber-reinforced plastics (CFRP) and glass-fiber-reinforced plastics (GFRP), also known as fiberglass.

#### Types of Laminates

A composite laminate is defined as the stacking of two or more unidirectional layers/plies/laminae with a uniform or varied fiber orientation with respect to a reference direction. The laminae can be made of the same material or different ones and can have individual thicknesses. The stacking sequence is essentially defined by the fiber orientation in each ply with respect to the first axis of the laminate coordinate system.

*Stacking sequence (0/45/90/45/0) of an antisymmetric balanced laminate.*

Based on the stacking sequence, composite laminates can be classified into the following categories:

- Angle-ply laminate (e.g., 45/30/-45/-30)
- Cross-ply laminate (e.g., 0/90/0/90)
- Balanced laminate (e.g., 0/45/90/-45)
- Symmetric laminate (e.g., 45/30/30/45)
- Antisymmetric laminate (e.g., 45/30/-30/-45)

Analyzing a composite laminate can be rather challenging, as the geometric scale of fibers, plies, and laminates are quite different. That is the reason the complete analysis is performed at two levels or scales: micromechanics analysis and macromechanics analysis.

### Micromechanics (Fiber-Matrix Modeling)

This step deals with simulating either a single lamina or a typical unit cell that has a fiber surrounded by a matrix. The purpose of this step is to calculate the lamina’s homogenized material properties.

*Representative unit cell of a fiber composite layer having a 60% fiber volume fraction.*

#### About Cell Periodicity

In COMSOL Multiphysics®, the micromechanics analysis is performed using the *Cell Periodicity* node in the *Solid Mechanics* interface. It needs a 3D solid geometry of a unit cell with a fiber and matrix along with their material properties. This analysis, which is based on a representative volume element (RVE) technique, is performed for six load cases and material data for a homogenized material is created. To find out more, see the Micromechanics and Stress Analysis of a Composite Cylinder example.

*Von Mises stress distribution together with the deformation in a unit cell for six different load cases.*

### Macromechanics (Laminate Modeling)

This step deals with the modeling of a laminate that has many layers. The homogenized material properties of a lamina computed from the micromechanics analysis are used as input. The aim is to compute the response of a laminate under various loading conditions.

To model a composite laminate, the following properties need to be specified:

- Number of layers
- Homogenized material properties of each layer
- Orientation of the principal material directions
- Thickness of each layer
- Stacking sequence

*Cross section of a composite laminate showing the thickness and fiber orientation of each layer.*

#### Modeling Layered Materials in COMSOL Multiphysics®

To define the laminate properties discussed above in the Composite Materials Module, a *Layered Material* node is used. In this node, the required number of layers can be added, and inputs can be either directly entered in the table or loaded from a text file. Once the inputs are specified, it is possible to preview the cross section as well as the stacking sequence of the laminate. The *Layered Material* node, containing the laminate definition, can be saved in the material library and loaded at a later point in time.

*Example of a* Layered Material *node.*

Once the laminate is defined using the *Layered Material* node, it can be attached to the geometric boundaries through the *Layered Material Link* or *Layered Material Stack* node. While doing so, the laminate coordinate system as well as the position of the geometric surface with respect to the laminate are also defined. The laminate coordinate system is further used to interpret the stacking sequence and create a layerwise local coordinate system.

### Laminate Theories

Now that the laminate is defined and attached to geometric boundaries, let’s take a look at the laminate theories. The analysis of laminated composite shells is commonly based on one of three different theories:

- Equivalent single layer (ESL) theory
- Classical laminated plate theory (CLPT)
- First-order shear deformation laminated plate theory (FSDT)
- Higher-order shear deformation laminated plate theory

- Three-dimensional elasticity theory
- 3D elasticity theory
- Layerwise theory

- Multiple model methods

In COMSOL Multiphysics, ESL-FSDT and the layerwise theory are implemented.

#### Equivalent Single Layer Theory (ESL-FSDT)

In ESL-FSDT, homogenized material properties of the entire laminate are computed and equations are solved only at the midplane. This theory has a shell-like formulation with degrees of freedom (DOFs) in the form of three displacements and three rotations on the meshed boundary in 3D. This theory is suitable for thin to moderately thick laminates and can be used for finding the global response as gross deflections, eigenfrequencies, critical buckling load, and in-plane stresses. Compared to the layerwise theory, ESL-FSDT is computationally inexpensive; however, it requires a shear correction factor for thicker laminates.

*DOF nodes in ESL-FSDT.*

#### Layerwise Theory

In this theory, equations are solved also in the thickness direction; hence, it can be used for very thick laminates, including delaminated regions. This theory has a solid-like formulation with DOFs in the form of three displacements distributed also in the thickness direction. This theory is suitable for moderately thin to thick laminates and can be used to predict correct interlaminar stresses and delamination and to perform detailed damage analysis. It supports nonlinear material models and doesn’t require a shear correction factor, as opposed to ESL-FSDT.

*DOF nodes in the layerwise theory.*

From a formulation point of view, the layerwise theory is quite similar to the 3D elasticity theory; however, it has the following advantages over the latter theory:

- The laminate coordinate system and layer local coordinate system are easy to define
- In-plane and out-of-plane shape functions can have different orders
- There’s no need to build a 3D geometry with many thin layers
- In-plane finite element meshing is independent of the out-of-plane meshing
- The layerwise and interfacial data is easy to handle

#### Selecting an Appropriate Laminate Theory

Based on the above descriptions, a suitable laminate theory can be chosen. A simple rule of thumb is to choose a laminate theory based on the laminate aspect ratio, which is defined as the ratio of laminate length to the laminate thickness.

*Range of validity for the two laminate theories based on the laminate aspect ratio.*

### Physics Interfaces for Composite Materials

In COMSOL Multiphysics, composite laminates are analyzed either using the layerwise theory through the *Layered Shell* interface or using ESL-FSDT through the *Layered Linear Elastic Material in Shell* interface. Salient features of the *Layered Shell* and *Shell* interfaces are described below.

#### Mixed Shape Discretization

The *Layered Shell* interface allows for a different shape order in the base surface and thickness direction. The four mixed shape elements available are as follows:

- Quadratic-linear Lagrange
- Quadratic-linear serendipity
- Quadratic-cubic Lagrange
- Quadratic-cubic serendipity

The quadratic-linear shape is intended for faster simulation results, whereas the quadratic-cubic shape is good for more accuracy in through-thickness results.

*The mixed shape discretization elements in the* Layered Shell *interface.*

#### Layered Material Continuity

The *Layered Shell* interface allows you to join two laminates placed next to each other using the *Continuity* node. With this functionality, you can model a ply drop-off scenario.

*Different ways of setting up the continuity between two laminates placed side-by-side.*

#### Nonlinear Materials

It is possible to include nonlinear material models (for example, viscoelasticity, creep, and viscoplasticity) in a few or all of the layers of a laminate. This functionality is available in the *Layered Shell* interface.

#### A, B, D Matrix Computation

The standard stiffness and flexibility matrices can be evaluated using the *Layered Linear Elastic Material* node in the *Shell* interface. The four stiffness matrices available are:

- Extensional stiffness matrix (A)
- Bending-extensional stiffness matrix (B)
- Bending stiffness matrix (D)
- Shear stiffness matrix (As)

You can check out the Material Characteristics of Laminated Composite Shell example for more details.

### Postprocessing Tools for Composite Material Modeling

#### Layered Material Dataset

As the geometry contains only surfaces, the *Layered Material* dataset is used to display the results of the simulation on a geometry that has a finite thickness. With this dataset, you can increase or decrease the laminate thickness in the normal direction, which is useful for thin laminates. In addition, you can create surface plots, volume plots, slices plots, etc. in 3D.

*Various plots created using the* Layered Material *dataset.*

#### Layered Material Slice Plot

For composite laminates, the *Layered Material Slice* plot offers more freedom when making slices. Some of the instances where this plot is useful include creating a slice:

- Through one (or a couple of) layers
- Through many (or all) of the layers (note that you do not need to place the slices in the through-thickness direction)
- At a certain position in the layer, although not in the midplane

*Von Mises stress in the middle of each layer of a laminate, created using the* Layered Material Slice *plot.*

#### Through Thickness Plot

This plot is used to determine the variation of different quantities through the thickness of the laminate. You can choose one or several geometric points on the boundary. You also have the option to create a dataset of the cut points as well as to directly enter the point coordinates.

*Through-thickness variation of the transverse shear stress at one point in a laminate.*

### Failure Analyses of Composite Structures

#### First-Ply Failure

A first-ply failure analysis is possible in both laminate theories. It is performed using the *Safety* node under the *Linear Elastic Material* node. A number of failure criterion are supported; e.g., Tsai-Wu, Tsai-Hill, etc. You can refer to the Failure Prediction in a Laminated Composite Shell example for more details.

*Hoffman safety factor in different plies of a laminate.*

#### Buckling

Linear buckling is possible in both laminate theories; however, ESL-FSDT is more efficient in finding the critical buckling load factor as compared to the layerwise theory. It is possible to optimize a layup in order to maximize the critical buckling load. For more information, see the Buckling of a Composite Cylinder example.

*Example of the buckling of a composite cylinder. The four different mode shapes (diamond, axisymmetric, and two spirals) corresponding to different stacking sequences are shown.*

#### Delamination

Delamination modeling is possible using the layerwise theory. The *Thin Elastic Layer, Interface* node is used to model the delaminated zone. To learn more, check out the Forced Vibration Analysis of a Composite Laminate example.

*Left: Composite laminate with and without a delaminated region. Right: Von Mises stress distribution at 500 Hz when subjected to a bending load.*

### Multiphysics Analyses of a Composite Laminate

#### Joule Heating and Thermal Expansion

Joule heating and thermal expansion in composite structures can be modeled using the following physics interfaces:

*Electric Currents, Layered Shell**Heat Transfer in Shells**Layered Shell*

The coupling between different physics is defined using the following multiphysics coupling nodes:

*Electromagnetic Heating, Layered Shell**Thermal Expansion, Layered Shell**Temperature Coupling*

*Example of Joule heating and thermal expansion in a composite laminate. Left: Electric potential. Middle: Temperature distribution. Right: Von Mises stress distribution.*

You can refer to the Thermal Expansion of a Laminated Composite Shell example for more details.

#### Acoustics-Composite Interaction

Acoustics-composite interaction can be modeled using the following physics interfaces:

*Pressure Acoustics**Shell*>*Layered Linear Elastic Material*

The *Acoustic-Structure Boundary* multiphysics coupling node is used to define the interaction between the two physics.

*Example of an acoustics-composite interaction. Left: Sound pressure level in the air domain. Right: Von Mises stresses in a composite plate.*

#### Fluid-Composite Interaction

This interaction can be modeled using the following physics interfaces:

*Laminar Flow*

*Shell*>

*Layered Linear Elastic Material*

The *Fluid-Structure Interaction* multiphysics coupling node is used to define the interaction between the two physics.

*Example of a fluid-composite interaction. Left: Velocity magnitude of the fluid flow. Right: Von Mises stresses in a composite plate.*

### Wind Turbine Blade Example

Using the abovementioned functionality, a wind turbine composite blade is modeled. The blade considered here is 61.5 m long and the geometry has 19 different sections that are defined by airfoil shapes. The aim of the analysis is to find the stress distribution in the skin and spar under gravity and centrifugal forces. Also, the natural frequencies and mode shapes are computed at different speeds.

*Example of a wind turbine composite blade. The von Mises stress distribution in the skin and spar of the blade is shown.*

To try this example yourself, see the wind turbine composite blade model.

### Next Step

Find out more about the dedicated functionality for modeling composite structures in the Composite Materials Module. Contact COMSOL via the button below to evaluate the software.

## Comments (4)

## N DHANUNJAYARAO BORRA

February 26, 2019hello sir,

This is dhanunjay, I am doing micromechanics analysis by representative volume element method and periodic boundary conditions for the fiber of circular and elliptical cross-sections. I am able to perform both separately for different cross-sections if I try to solve in a single file by taking another component and all it is showing only one result and unable to connect the compared graphs between them. But I want both cross-sections to be done in a single file and also need to show the comparison in the form of graphs for the fiber volume fraction and material constants. So in this context, I am seeking your help in performing both RVE models in single file and need comparisons. I hope a positive reply from you. Thanking you very much.

## N DHANUNJAYARAO BORRA

February 26, 2019This is my mail id dhanunjayborra@gmail.com and you can send a reply to mail id also. If you want I can send .mph file also. Thank you.

## Anonymous

February 26, 2019Dear Dhanunjay,

It is possible to solve for two or more RVE models in a single file but in different components. The only limitation for now is that the homogeneous material created under global definition corresponds to any one of the RVE models. Apart from that, you can plot or derive any quantity from all the RVE models.

If you still face any issues, feel free to send your query and .mph file to support@comsol.com

Best regards,

Pawan Soami

## Peter Cendula

January 27, 2021Dear Pawan,

thanks for nice overview. I’m still stuck with version 5.2 at our university and I am wondering if it is possible to calculate bilayer bending by thermal expansion with the Shell interface in 5.2? I tried to add two shells, with one shell being offset by thickness to the other one, but I’m not getting the desired behavior.

Thank you

Peter