Overview of Elasticity of Materials/Isotropic Response

This section covers linear isotropic response.

We now understand tensor relations and have established two tensors that we need for elasticity; $\mathit{\sigma }$ and $\mathit{\epsilon }$. In this chapter we will learn how to relate these to each other. In this particular section we will begin studying elasticity in the case of isotropic elasticity where we assume that all directions have the same material response.

Modulus of Elasticity

In earlier sections we learned that Hooke's Law can relate uniaxial loading to uniaxial strain:

${\sigma }_{11}=E{\epsilon }_{11}$ Template:Spaces[1]

Here, $E$ is the modulus of elasticity. Note that we picked the $x_1$ direction arbitrarily. It could have easily been $x_2$ or $x_3$, or any other direction in this crystal, and found the same material response, $E$. This is what comes from working with an isotropic solid.

Poisson's Ratio

When we load stress in the $x_1$ direction, there is also a natural contraction in the transverse directions, $x_2$ and $x_3$. This is expressed as Poisson's Ratio, $\nu$.

${\epsilon }_{22}={\epsilon }_{33}=-\nu {\epsilon }_{11}=-\frac{\nu {\sigma }_{11}}{E}$ Template:Spaces[2]

For a perfectly incompressible material, which means it conserves volume, we will have a Poisson's Ratio of 0.50. However, most real materials such as common metals have a Poisson's Ratio of around 0.33.

For linear elastic, isotropic materials, normal stresses will not induce shear strain and shear stress will not cause normal stress. In linear elasticity, the various contributions to strain can be superimposed. We can use the two above equations for the Modulus of Elasticity and Poisson's Ratio to determine that if a triaxial normal stress is applied, the strain will be:

$\begin{array}{cc}{\epsilon }_{11}& =\frac{{\sigma }_{11}}{E}-\frac{\nu {\sigma }_{22}}{E}-\frac{\nu {\sigma }_{33}}{E}\{\begin{array}{cc}{\epsilon }_{11}& =\frac{1}{E}[{\sigma }_{11}-\nu \left({\sigma }_{22}{\sigma }_{33}\right)]\\ {\epsilon }_{22}& =\frac{1}{E}[{\sigma }_{22}-\nu \left({\sigma }_{33}{\sigma }_{11}\right)]\\ {\epsilon }_{33}& =\frac{1}{E}[{\sigma }_{33}-\nu \left({\sigma }_{11}{\sigma }_{22}\right)]\end{array}\end{array}$ Template:Spaces[3-5]

Moving to shear relations, the shear stress and strain are related by the shear modulus, $G$.

${\sigma }_{12}=G{\gamma }_{12}=G2{\epsilon }_{12}$ Template:Spaces[6]

Again, due to the isotropic nature, this relation holds in all the other directions as well. These three constants of proportionality are sufficient to describe the isotropic linear response. They take typical values (for common engineering metals):

$\begin{array}{cc}50<& E<200GPa\\ 25<& G<75GPa\\ 0.25<& \nu <0.35\end{array}$

There are many other useful relations that we will summarize here. The Block Modulus, $K$, is the ratio of the hydrostatic pressure to the dilatation it produces:

$K=\frac{-p}{\mathrm{\Delta }}=\frac{{\sigma }_m}{\mathrm{\Delta }}=\frac{1}{\beta }$ Template:Spaces[7]

Where $-p$ is the hydrostatic pressure and $\beta$ is the compressibility.

Adding together Equations 3-5 for the triaxial normal strain, we get:

$\begin{array}{cc}\underset{\mathrm{\Delta }}{\underbrace{{\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33}}}& =\frac{1-2\nu }{E}(\underset{3{\sigma }_m}{\underbrace{{\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33}}})\\ \mathrm{\Delta }& =\frac{1-2\nu }{E}3{\sigma }_m\end{array}$ Template:Spaces[8]

Applying this to Equations 7 & 8 for the Block Modulus results in:

$K=\frac{{\sigma }_m}{\mathrm{\Delta }}=\frac{E}{3(1-2\nu )}$ Template:Spaces[9]

These next solutions are given without proof, because several advanced topics are used to show the relationships.

$G=\frac{E}{2(1+\nu )}$ Template:Spaces[10]

$E=\frac{9K}{1+3K/G}$ Template:Spaces[11]

$\nu =\frac{1-2G/3K}{2+2G/3K}$ Template:Spaces[12]

$G=\frac{3(1-2\nu )K}{2(1+\nu )}$ Template:Spaces[13]

$K=\frac{E}{9-3E/G}$ Template:Spaces[14]

The stress-strain relationships can be expressed in compact tensor notation:

${\epsilon }_{ij}=\frac{1+\nu }{E}{\sigma }_{ij}-\frac{\nu }{E}{\sigma }_{kk}{\delta }_{ij}$ Template:Spaces[15]

Looking specifically at a normal strain, ${\epsilon }_{22}$ for example:

${\epsilon }_{22}=\frac{1+\nu }{E}{\sigma }_{22}-\frac{\nu }{E}({\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33}){\delta }_{22}$

Similarly, for a shear strain, ${\epsilon }_{12}$, gets us:

${\epsilon }_{12}=\frac{1+\nu }{E}{\sigma }_{12}-\frac{\nu }{E}({\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33}){\delta }_{12}$

From $G=\frac{E}{2(1+\nu )}$, we find that:

$\begin{array}{cc}\frac{1+\nu }{E}& =\frac{1}{2G}\\ {\epsilon }_{12}& =\frac{1}{2G}{\sigma }_{12}\\ {\sigma }_{12}& =2G{\epsilon }_{12}\end{array}$

For a given stress state:

$\mathit{\sigma }=\left(\begin{array}{ccc}{\sigma }_{11}& {\sigma }_{12}& {\sigma }_{13}\\ {\sigma }_{21}& {\sigma }_{22}& {\sigma }_{23}\\ {\sigma }_{31}& {\sigma }_{32}& {\sigma }_{33}\end{array}\right)$

We can only write the strain tensor as:

$\mathit{\epsilon }=\left(\begin{array}{ccc}\frac{1}{E}({\sigma }_{11}-\nu ({\sigma }_{22}+{\sigma }_{33}))& \frac{{\sigma }_{12}}{2G}& \frac{{\sigma }_{13}}{2G}\\ \frac{{\sigma }_{12}}{2G}& \frac{1}{E}({\sigma }_{22}-\nu ({\sigma }_{33}+{\sigma }_{11}))& \frac{{\sigma }_{23}}{2G}\\ \frac{{\sigma }_{13}}{2G}& \frac{{\sigma }_{23}}{2G}& \frac{1}{E}({\sigma }_{33}-\nu ({\sigma }_{11}+{\sigma }_{22}))\end{array}\right)$ Template:Spaces[16]

So we have an expression for strain in terms of the applied load, the stress. This can certainly be useful for predicting the deformation to anticipate when loading in application. There is another application we are interested in. Given we deform a part, what stress does it feel? This answers questions such as, "how much can I bend this part before I reach the yield strength?" Basically, we want to take our existing solution and invert it.

To do this, we can take our first triaxial strain equation, Equation 3, and rearrange it:

$\begin{array}{cc}{\epsilon }_{11}& =\frac{{\sigma }_{11}}{E}-\frac{\nu {\sigma }_{22}}{E}-\frac{\nu {\sigma }_{33}}{E}\\ & +0=\frac{\nu {\sigma }_{11}}{E}-\frac{\nu {\sigma }_{11}}{E}\\ & =\frac{{\sigma }_{11}}{E}+\frac{\nu {\sigma }_{11}}{E}-\frac{\nu {\sigma }_{11}}{E}-\frac{\nu {\sigma }_{22}}{E}-\frac{\nu {\sigma }_{33}}{E}\end{array}$

And we arrive at:

$\begin{array}{cc}{\epsilon }_{11}& =\frac{1+\nu }{E}{\sigma }_{11}-\frac{\nu }{E}({\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33})\end{array}$ Template:Spaces[17]

We can additionally take our earlier equation for $\mathrm{\Delta }$, Equation 8, and rearrange it to get:

$\begin{array}{cc}\mathrm{\Delta }& =\frac{1-2\nu }{E}3{\sigma }_m\\ {\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33}& =\frac{1-2\nu }{E}({\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33})\end{array}$

And

${\sigma }_{11}+{\sigma }_{22}+{\sigma }_{33}=\frac{E}{1-2\nu }({\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33})$ Template:Spaces[18]

Then by substituting Equation 18 into Equation 17, we get:

$\begin{array}{cc}{\epsilon }_{11}& =\frac{1+\nu }{E}{\sigma }_{11}-\frac{\nu }{E}(\frac{E}{1+2\nu }({\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33}))\\ {\sigma }_{11}& ={\epsilon }_{11}\left(\frac{E}{1+\nu }\right)+\frac{E}{1+\nu }\frac{\nu }{E}\frac{E}{1-2\nu }({\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33})\end{array}$

Which becomes

$\begin{array}{cc}{\sigma }_{11}& =\left(\frac{E}{1+\nu }\right){\epsilon }_{11}+\frac{\nu E}{(1+\nu )(1-2\nu )}({\epsilon }_{11}+{\epsilon }_{22}+{\epsilon }_{33})\end{array}$ Template:Spaces[19]

Thinking about shear stress is simpler:

$\begin{array}{cc}{\sigma }_{12}& =2G{\epsilon }_{12}\end{array}$

Substituting in Equation 10 results in

$\begin{array}{cc}{\sigma }_{12}& =2\frac{E}{2(1+\nu )}{\epsilon }_{12}\end{array}$

Which becomes

$\begin{array}{cc}{\sigma }_{12}& =\left(\frac{E}{1+\nu }\right){\epsilon }_{12}\end{array}$ Template:Spaces[20]

Taking Equations 19 & 20 gives us the tensor expression for stress in terms of strain, which is:

${\sigma }_{ij}=\frac{E}{1+\nu }{\epsilon }_{ij}+\underset{\lambda }{\underbrace{\frac{\nu E}{(1+\nu )(1-2\nu )}}}{\epsilon }_{kk}{\delta }_{ij}$ Template:Spaces[21]

Here, $\lambda$ is the Lamé Constant. We can analyze these results and extract useful equations. We will begin by extracting the deviatoric and hydrostatic contributions to stress.

${\sigma }_{i^{\prime }j}=2G{\epsilon }_{i^{\prime }j}$ Template:Spaces[22]

We can show this is true by considering shear and normal components.

Shear:

${\sigma }_{1^{\prime }2}={\sigma }_{12}=\frac{E}{(1+\nu )}{\epsilon }_{12}=2G{\epsilon }_{12}=2G{\epsilon }_{1^{\prime }2}$

Normal:

$\begin{array}{cc}{\sigma }_{1^{\prime }1}& =\frac{2{\sigma }_{22}-{\sigma }_{22}-{\sigma }_{33}}{3}\\ & =\frac{1}{3}[2(2G{\epsilon }_{11}+\lambda {\epsilon }_{11}+\lambda {\epsilon }_{22}+\lambda {\epsilon }_{33})-(2G{\epsilon }_{22}+\lambda {\epsilon }_{11}+\lambda {\epsilon }_{22}+\lambda {\epsilon }_{33})-(2G{\epsilon }_{33}+\lambda {\epsilon }_{11}+\lambda {\epsilon }_{22}+\lambda {\epsilon }_{33})]\\ & =\frac{1}{3}(4G{\epsilon }_{11}-2G{\epsilon }_{22}-2G{\epsilon }_{33})\\ & =2G\frac{2{\epsilon }_{11}-{\epsilon }_{22}-{\epsilon }_{33}}{3}\\ & =2G{\epsilon }_{1^{\prime }1}\end{array}$

The relationship between the hydrostatic stress and the mean strain is:

${\sigma }_{ii}=\frac{E}{1-2\nu }{\epsilon }_{kk}=3K{\epsilon }_{kk}$ Template:Spaces[23]

Note that we've seen this expression several times before!

Simplified Cases

Plane stress ${\sigma }_{33}=0$.

Once again looking at our earlier triaxial strain equations, Equations 3 & 4, we will start by adding the first two together:

$\frac{\begin{array}{cc}{\epsilon }_{11}& =\frac{1}{E}[{\sigma }_{11}-\nu {\sigma }_{22}]=\frac{1}{E}{\sigma }_{11}-\frac{\nu }{E}{\sigma }_{22}\\ +\nu ({\epsilon }_{22}& =\frac{1}{E}[{\sigma }_{22}-\nu {\sigma }_{11}]=-\frac{\nu }{E}{\sigma }_{11}+\frac{1}{E}{\sigma }_{22})\end{array}}{{\epsilon }_{11}+\nu {\epsilon }_{22}=(\frac{1}{E}-\frac{{\nu }^2}{E}){\sigma }_{11}}\begin{array}{c}\\ \\ \to {\sigma }_{11}& =\frac{E}{1-{\nu }^2}({\epsilon }_{11}+\nu {\epsilon }_{22})\\ {\sigma }_{22}& =\frac{E}{1-{\nu }^2}({\epsilon }_{22}+\nu {\epsilon }_{11})\end{array}$

Plane stress encountered either as loaded sheet, or more likely a pressure vessel.

Another simplification is Plane Strain, where ${\epsilon }_{33}=0$, typically when one dimension is much greater than the other two so ${\epsilon }_{11}$ and ${\epsilon }_{22}$ are much greater than ${\epsilon }_{33}$, such as a long rod where strain along the length of the rod is constrained. Here, Equation 5 rearranges to:

$\begin{array}{cc}{\epsilon }_{33}& =\frac{1}{E}[{\sigma }_{33}-\nu ({\sigma }_{11}+{\sigma }_{22})]=0\\ {\sigma }_{33}& =\nu ({\sigma }_{11}+{\sigma }_{22})\end{array}$

Note that ${\sigma }_{33}$ does not equal zero just because ${\epsilon }_{33}$ equals zero. Substituting this ${\sigma }_{33}$ equation into Equations 3-5 yields us:

$\begin{array}{cc}{\epsilon }_{11}& =\frac{1}{E}[(1-{\nu }^2){\sigma }_{22}-\nu (1+\nu ){\sigma }_{11}]\\ {\epsilon }_{22}& =\frac{1}{E}[(1-{\nu }^2){\sigma }_{22}-\nu (1+\nu ){\sigma }_{11}]\end{array}$

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