#### Transcript Stress - Dr. Brian Sullivan

### Micromechanics Macromechanics

Fibers Lamina Laminate Structure Matrix

### Micromechanics

The analysis of relationships between effective composite properties (i.e., stiffness, strength) and the material properties, relative volume contents, and geometric arrangement of the constituent materials.

### Micromechanics - Stiffness

1. Mechanics of materials models – Simplifying assumptions make it unnecessary to specify details of stress and strain distribution – fiber packing geometry is arbitrary. Use average stresses and strains.

### Micromechanics - Stiffness

2.

Theory of elasticity models “Actual” stress and strain distributions are used – fiber packing geometry taken into account.

a) Closed form solutions b) Numerical solutions such as finite element c) Variational methods (bounds)

### Volume Fractions

*v f*

*V f V c v m*

*V m V c*

fiber volume fraction matrix volume fraction Where

*V c v v*

*V f v*

*f V v V c*

*V m*

*v m*

void volume fraction

*V v v v*

1 (3.2) composite volume

### Weight Fractions

*w f*

*W f W c*

fiber weight fraction Where

*w m*

*W m W c*

matrix weight fraction

*W c*

*W f*

*W m*

composite weight Note: weight of voids neglected

### Densities

*W*

*W V c*

*W f*

density

*W m*

*c V c*

*f V f*

*m V m*

*c*

*f v f*

*m v m*

“Rule of Mixtures” for density (3.6)

Alternatively,

*c*

*w f*

1

*f*

*w m*

*m*

Eq. (3.2) can be rearranged as

*v v*

1

*W f*

*f*

*( W c*

*W f W c*

*c )*

*m*

(3.8) (3.9)

Above formula is useful for void fraction estimation from measured weights and densities.

Typical void fractions: Autoclaved cured composite: 0.1% - 1% Press cured w/o vacuum: 2 - 5%

Measurements typically involve weight fractions, which are related to volume fractions by and

*w f*

*W f W c*

*f V f*

*c V c*

*c f w m*

*W m W c*

*m V m c V c*

*m c v m v f*

(3.10) (3.12)

Representative area elements for idealized square and triangular fiber packing geometries.

Fiber s s Square array d s d s Triangular array

### Fiber volume fraction – packing geometry relationships

Square array:

*v f*

4

*d s*

2 When s=d,

*v f*

*v f*

max 4 0 .

785 (3.14) (3.15)

### Fiber volume fraction – packing geometry relationships

Triangular Array:

*v f*

2 3

*d s*

2 (3.16) When s=d,

*v f*

*v f*

max 2 3 0 .

907 (3.17)

### Fiber volume fraction – packing geometry relationships

•

**Real composites:**

Random fiber packing array Unidirectional: Chopped: 0 .

05 0 .

*v*

5

*f*

*v f*

0 .

4 0 .

8 Filament wound: close to theoretical

Photomicrograph of carbon/epoxy composite showing actual fiber packing geometry at 400X magnification

Voronoi cell and its approximation. (From Yang, H. and Colton, J.S. 1994.

*Polymer Composites*

, 51, 34–41. With permission.) Random nature of fiber packing geometry in real composites can be quantified by the use of the Voronoi cell. Each point within the space of a Voronoi cell for a particular fiber is closer to the center of that fiber than it is to the center of any other fiber s Voronoi cells Equivalent square cells, with Voronoi cell size, s

Typical histogram of Voronoi distances and corresponding Wiebull distribution for a thermoplastic matrix composite. (From Yang, H. and Colton, J.S. 1994.

*Polymer Composites*

, 51, 34–41. With permission.)

**Elementary Mechanics of Materials Models for Effective Moduli**

• Fiber packing array not specified – RVE consists of fiber and matrix blocks.

• Improved mechanics of materials models and elasticity models do take into account fiber packing arrays.

Assumptions: 1. Area fractions = volume fractions 2. Perfect bonding at fiber/matrix interface – no slip 3. Matrix is isotropic, fiber can be orthotropic 4. Fiber and matrix linear elastic 5. Lamina is macroscopically homogeneous, linear elastic and orthotropic

Concept of an Effective Modulus of an Equivalent Homogeneous Material.

Heterogeneous composite under varying stresses and strains

*d x*

3 2

*x*

3 2 2

*L*

2 Equivalent homogeneous material under average stresses and strains

*x*

3 Stress, 2 2 2 2 Stress

*x*

3 Strain, 2 2 Strain

Representative volume element and simple stress states used in elementary mechanics of materials models

Representative volume element and simple stress states used in elementary mechanics of materials models Longitudinal normal stress In-plane shear stress Transverse normal stress

Average stress over RVE: 1

*V*

*V*

*dV*

1

*A*

*A*

*dA*

Average strain over RVE: 1

*V*

*V*

*dV*

1

*A*

*A*

*dA*

Average displacement over RVE: 1

*V V*

*dV*

1

*A*

*A*

*dA*

(3.19) (3.20) (3.21)

### Longitudinal Modulus

longitudinal modulus E 1 .

Equilibrium:

*c*

1

*A*

1

*f*

1

*A f*

*m*

1

*A m*

(3.22) Note: fibers are often orthotropic.

Rearranging, we get “Rule of Mixtures” for longitudinal stress

**Static Equilibrium**

*c*

1

*f*

1

*v f*

*m*

1

*v m*

(3.23)

Hooke’s law for composite, fiber and matrix

**Stress – strain Relations**

*c*

1

*E*

1

*c*

1

*f*

1

*E f*

1

*f*

1

*m*

1

*E m*

*m*

1 So that:

*E*

1

*c*

1

*E f*

1

*f*

1

*v f*

*E m*

*m*

1

*v m*

(3.24) (3.25)

Assumption about average strains:

**Geometric Compatibility**

*c*

1

*f*

1

*m*

1 (3.26) Which means that,

*E*

1

*E f*

1

*v f*

*E m v m*

“Rule of Mixtures” – generally quite accurate – useful for design calculations (3.27)

Variation of composite moduli with fiber volume fraction Eq. 3.27

Eq. 3.40

Predicted

*E 1*

and

*E 2*

from elementary mechanics of materials models

Variation of composite moduli with fiber volume fraction Comparison of predicted and measured

*E 1*

for E-glass/polyester. (From Adams, R.D., 1987. Engineered Materials Handbook, Vol. 1, Composites, 206–217.)

### Strain Energy Approach

*U c*

*U f*

*U m*

(3.28) Where strain energy in composite, fiber and matrix are given by,

*U f U c*

1 2

*V c*

*c*

1

*c*

1

*dV*

1 2

*f V*

*f*

1

*f*

1

*dV*

1 2 1 2

*E*

1

*c*

1 2

*V c E f*

1

*f*

1 2

*V f*

(3.29a) (3.29b)

*U m*

1 2

*V m*

*m*

1

*m*

1

*dV*

1 2

*E m*

1

*m*

1 2

*V m*

(3.29c)

Strain energy due to Poisson strain mismatch at fiber/matrix interface is neglected.

Let the stresses in fiber and matrix be defined in terms of the composite stress as:

*f*

1

*a*

1

*c*

1 (3.30)

*m*

1

*b*

1

*c*

1 Subst. in “Rule of Mixtures” for longitudinal stress:

*c*

1

*f*

1

*v f*

*m*

1

*v m*

(3.23)

Or

*c*

1

*a*

1

*v f*

*b*

1

*v m*

*c*

1

*a*

1

*v f*

*b*

1

*v m*

1 (3.31) Combining (3.30), (3.24) & (3.29) in (3.28), 1

*E*

1

*a*

1 2

*v f E f*

1

*b*

1 2

*v m E m*

1 (3.32) Solving (3.31) and (3.32) simultaneously for E-glass/epoxy with known properties: Find a 1 and b 1 , then

*f m*

1 1 1 .

00

Representative volume element and simple stress states used in elementary mechanics of materials models Longitudinal normal stress In-plane shear stress Transverse normal stress

### Transverse Modulus

RVE under average stress

*c*

2 Response governed by transverse modulus

*E 2*

Geometric compatibility:

*c*

2

*f*

2

*m*

2 (3.34) From definition of normal strain,

*c*

2

*f*

2

*f c*

2

*L*

2 2

*L f*

*m*

2

*m*

2

*L m*

(3.35)

Thus, Eq.(3.34) becomes Or

*c*

2

*L*

2

*c*

2

*f*

2

*L f f*

2

*v f*

*m*

2

*L m*

*m*

2

*v m*

(3.36) (3.37) Where

*L L*

2

*f*

*v f*

,

*L L*

2

*m*

*v m*

, 1-D Hooke’s laws for transverse loading:

*c*

2

*f*

2

*E*

2

*E f*

2

*c*

2

*f*

2 (3.38)

*m*

2

*E m*

*m*

2

Where Poisson strains have been neglected. Combining (3.37) and (3.38),

*c*

2

*E*

2

*f*

2

*E f*

2

*v f*

*m*

2

*E m v m*

(3.39) Assuming that

*c*

2

*f*

2

*m*

2 We get 1

*E*

2

*v f E f*

2

*v m E m*

(3.40)

- “Inverse Rule of Mixtures” – Not very accurate - Strain energy approach for transverse loading, Assume,

*f*

2

*a*

2

*c*

2 (3.41)

*m*

2

*b*

2

*c*

2 Substituting in the compatibility equation (Rule of mixture for transverse strain), we get

*a*

2

*v f*

*b*

2

*v m*

1 (3.42)

*m*

2 in

*U c*

*U f*

*U m*

We get

*E*

2

*a*

2 2

*E f*

2

*v f*

*b*

2 2

*E m v m*

(3.28) (3.43) Solving (3.42) and (3.43) simultaneously for

*a 2*

and

*b 2*

, we get for E-glass/epoxy,

*f*

2

*m*

2 5 .

63

Representative volume element and simple stress states used in elementary mechanics of materials models Longitudinal normal stress In-plane shear stress Transverse normal stress

In-Plane Shear Modulus, G 12 • Using compatibility of shear displacement and assuming equal stresses in fiber and matrix: 1

*v f*

*v m*

(3.47)

*G*

12

*G f*

12

*G m*

(Not very accurate) Major Poisson’s Ratio,

*υ*

12 • Using compatibility in 1 and 2 directions: 12

*f*

12

*v f*

*m v m*

(3.45) (Good enough for design use)

### Design Equations

*E*

1

*E f*

1

*v f*

*E m v m*

12

*f*

12

*v f*

*m v m*

• Elementary mechanics of materials Equations derived for

*G 12*

and

*E 2*

are not very useful – need to develop improved models for

*G 12*

and

*E 2*

.

### Improved Mechanics of Materials Models for

*E 2*

### and

*G 12*

Mechanics of materials models refined by assuming a specific fiber packing array. Example: Hopkins – Chamis method of sub-regions RVE

Convert RVE with circular fiber to equivalent RVE having square fiber whose area is the same as the circular fiber.

RVE A s f A

**Sub Region A**

d s B s f B

**Sub Region B**

A A

**Sub Region A**

Division of representative volume element into sub regions based on square fiber having equivalent fiber volume fraction.

Equivalent Square Fiber:

*s f*

4

*d*

Size of RVE:

*s*

4

*v f d*

For Sub Region B:

*s f*

2 4

*d*

2 s s f (3.48) (3.49) s f

Following the procedure for the elementary mechanics of materials analysis of transverse modulus: 1

*E B*

2

*E*

1

*f*

2

*s s f*

*E*

1

*m s s m*

(3.50) but

*s f s*

So that

*v f*

;

*s m s*

1

*v f*

; (3.51)

*E B*

2 1

*v f*

1

*E*

*m E m E f*

2 (3.52)

For sub regions A and B in parallel, Or finally

*E*

2

*E B*

2

*s f s*

*E m s s m E*

2

*E m*

1

*v f*

1

*v f*

1

*v f E m*

Similarly,

*G*

12

*G m*

1

*v f*

1 (3.53)

*E f*

2 (3.54)

*v f*

1

*v f G m G f*

2

Simplified Micromechanics Equations (Chamis) Only used part of the analysis for sub region B in Eq. (3.52):

*E B*

2 1

*G*

12 1

*v f*

1

*E*

*m E m v f*

1

*G m*

*G m E f*

2

*G f*

12 (3.52) Fiber properties

*E f2*

and

*G f12*

from these equations.

in tables inferred

**Semi empirical Models**

Use empirical equations which have a theoretical basis in mechanics Halpin-Tsai Equations Where

*E*

2

*E E f f E m*

1

*v f*

1

*v f E m E m*

1 (3.63) (3.64)

2 for

*E 2*

of square array of circular fibers 1 for

*G 12*

Mixtures

Tsai-Hahn Stress Partitioning Parameters Get let

*m*

2 2

*f*

2 1

*E*

2

*v f*

1 2

*v m*

*v E f f*

2

*v m E m*

2 2 1 .

0 , (3.65) (3.66)

Transverse modulus for glass/epoxy according to Tsai-Hahn equation (Eq. 3.66). (From Tsai, S.W. and Hahn, H.T. 1980.

*Introduction to Composite Materials*

. Technomic Publishing Co., Lancaster, PA. With permission from Technomic Publishing Co.) Eq. 3.66

**Micromechanical Analysis of Composite Materials Using Elasticity Theory**

Micromechanical analysis of composite materials involve the development of analytical models for predicting macroscopic composite properties in terms of constituent material properties and information on geometry and loading. Analysis begins with the selection of a representative volume element, or RVE, which depends on the assumed fiber packing array in the composite .

Example: Square packing array RVE Matrix Fiber Due to double symmetry, we only need to consider one quadrant of RVE Fiber Matrix

• The RVE is then subjected to uniform stress or displacement along the boundary. The resulting boundary value problem is solved by either stress functions, finite differences or finite elements.

• Later in this course we will discuss specific examples of finite difference solutions and finite element solutions for micromechanics problems.