Nonlinear finite elements/Axial bar finite element solution

Axially loaded bar: The Finite Element Solution

The finite element method is a type of Galerkin method that has the following advantages:

1. The functions ${\phi }_i$ are found in a systematic manner.
2. The functions ${\phi }_i$ are chosen such that they can be used for arbitrary domains.
3. The functions ${\phi }_i$ are piecewise polynomials.
4. The functions ${\phi }_i$ are non-zero only on a small part of the domain.

As a result, computations can be done in a modular manner that is suitable for computer implementation.

Discretization

The first step in the finite element approach is to divide the domain into elements and nodes, i.e., to create the finite element mesh.

Let us consider a simple situation and divide the rod into 3 elements and 4 nodes as shown in Figure 6.

File:DistAxialMesh.png Figure 6. Finite element mesh and basis functions for the bar.

Shape functions

The functions ${\phi }_i$ have special characteristics in finite element methods and are generally written as $N_i$ and are called basis functions, shape functions, or interpolation functions.

Therefore, we may write

$\begin{array}{cc}{K}_{ij}& =\underset{0}{\overset{L}{\int }}\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx\\ f_j& =\underset{0}{\overset{L}{\int }}{N}_j𝐪dx+{N_j𝑹|}_{x=L}.\end{array}$

The finite element basis functions are chosen such that they have the following properties:

1. The functions $N_i$ are bounded and continuous.
2. If there are $n$ nodes, then there are $n$ basis functions - one for each node. There are four basis functions for the mesh shown in Figure 6.
3. Each function $N_i$ is nonzero only on elements connected to node $i$.
4. $N_i$ is 1 at node $i$ and zero at all other nodes.

Stiffness matrix

Let us compute the values of $K_{ij}$ for the three element mesh. We have

$\begin{array}{cc}{K}_{ij}& =\underset{0}{\overset{L}{\int }}\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx\\ & =\underset{0}{\overset{x_2}{\int }}\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx+\underset{x_2}{\overset{x_3}{\int }}\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx+\underset{x_3}{\overset{L}{\int }}\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx\\ & \equiv \underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_j}{dx}AE\frac{d{N}_i}{dx}dx\end{array}$

The components of $𝐊$ are

$\begin{array}{cc}{K}_{11}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_1}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_1}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_1}{dx}AE\frac{d{N}_1}{dx}dx\\ K_{12}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_1}{dx}dx\\ K_{13}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_1}{dx}dx\\ K_{14}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_1}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_1}{dx}dx\\ K_{22}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_2}{dx}dx\\ K_{23}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_2}{dx}dx\\ K_{24}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_2}{dx}dx\\ K_{33}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_3}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_3}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_3}{dx}dx\\ K_{34}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_3}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_3}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_3}{dx}dx\\ K_{44}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_4}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_4}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_4}{dx}dx.\end{array}$

The matrix $𝐊$ is symmetric, so we don't need to explicitly compute the other terms.

From Figure 6, we see that $N_1$ is zero in elements 3 and 4, $N_2$ is zero in element 4, $N_3$ is zero in element 1, and $N_4$ is zero in elements 1 and 2. The same holds for $d{N}_i/dx$.

Therefore, the coefficients of the $𝐊$ matrix become

$\begin{array}{cc}{K}_{11}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_1}{dx}AE\frac{d{N}_1}{dx}dx;K_{12}=\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_1}{dx}dx;K_{13}=0;K_{14}=0\\ K_{22}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_2}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_2}{dx}AE\frac{d{N}_2}{dx}dx;K_{23}=\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_2}{dx}dx;K_{24}=0\\ K_{33}& =\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_3}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_3}{dx}AE\frac{d{N}_3}{dx}dx;K_{34}=\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_3}{dx}dx\\ K_{44}& =\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_4}{dx}AE\frac{d{N}_4}{dx}dx.\end{array}$

We can simplify our calculation further by letting $N_k^e$ be the shape functions over an element $e$. For example, the shape functions over element $2$ are $N_1^2$ and $N_2^2$ where the local nodes $1$ and $2$ correspond to global nodes $2$ and $3$, respectively. Then we can write,

$\begin{array}{cc}{K}_{11}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_1^1}{dx}AE\frac{d{N}_1^1}{dx}dx;K_{12}=\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2^1}{dx}AE\frac{d{N}_1^1}{dx}dx;K_{13}=0;K_{14}=0\\ K_{22}& =\underset{{\mathrm{\Omega }}_1}{\int }\frac{d{N}_2^1}{dx}AE\frac{d{N}_2^1}{dx}dx+\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_1^2}{dx}AE\frac{d{N}_1^2}{dx}dx;K_{23}=\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_2^2}{dx}AE\frac{d{N}_1^2}{dx}dx;K_{24}=0\\ K_{33}& =\underset{{\mathrm{\Omega }}_2}{\int }\frac{d{N}_2^2}{dx}AE\frac{d{N}_2^2}{dx}dx+\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_1^3}{dx}AE\frac{d{N}_1^3}{dx}dx;K_{34}=\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_2^3}{dx}AE\frac{d{N}_1^3}{dx}dx\\ K_{44}& =\underset{{\mathrm{\Omega }}_3}{\int }\frac{d{N}_2^3}{dx}AE\frac{d{N}_2^3}{dx}dx.\end{array}$

Let $K_{kl}^e$ be the part of the value of $K_{ij}$ that is contributed by element $e$. The indices $kl$ are local and the indices $ij$ are global. Then,

$\begin{array}{cc}{K}_{11}& =K_{11}^1;K_{12}=K_{12}^1;K_{13}=0;K_{14}=0\\ K_{22}& =K_{22}^1+K_{11}^2;K_{23}=K_{12}^2;K_{24}=0\\ K_{33}& =K_{22}^2+K_{11}^3;K_{34}=K_{12}^3\\ K_{44}& =K_{22}^3\\ \end{array}$

We can therefore see that if we compute the stiffness matrices over each element and assemble them in an appropriate manner, we can get the global stiffness matrix $𝐊$.

Stiffness matrix for two-noded elements

For our problem, if we consider an element $e$ with two nodes, the local hat shape functions have the form

$N_1^e(𝐱)=\frac{{𝐱}_2-𝐱}{h_e};N_2^e(𝐱)=\frac{𝐱-{𝐱}_1}{h_e}$

where $h_e$ is the length of the element.

Then, the components of the element stiffness matrix are

$\begin{array}{cc}{K}_{11}^e& =\underset{x_1}{\overset{x_2}{\int }}\frac{d{N}_1^e}{dx}AE\frac{d{N}_1^e}{dx}dx=\underset{x_1}{\overset{x_2}{\int }}(-\frac{1}{h_e})AE(-\frac{1}{h_e})dx=\frac{AE}{h_e}\\ K_{12}^e& =\underset{x_1}{\overset{x_2}{\int }}\frac{d{N}_2^e}{dx}AE\frac{d{N}_1^e}{dx}dx=\underset{x_1}{\overset{x_2}{\int }}\left(\frac{1}{h_e}\right)AE(-\frac{1}{h_e})dx=-\frac{AE}{h_e}\\ K_{22}^e& =\underset{x_1}{\overset{x_2}{\int }}\frac{d{N}_2^e}{dx}AE\frac{d{N}_2^e}{dx}dx=\underset{x_1}{\overset{x_2}{\int }}\left(\frac{1}{h_e}\right)AE\left(\frac{1}{h_e}\right)dx=\frac{AE}{h_e}\end{array}$

In matrix form,

${𝐊}^e=\frac{AE}{h_e}\left[\begin{array}{cc}1& -1\\ -1& 1\end{array}\right]$

The components of the global stiffness matrix are

$\begin{array}{cc}{K}_{11}& =\frac{AE}{h_1};K_{12}=-\frac{AE}{h_1};K_{13}=0;K_{14}=0\\ K_{22}& =\frac{AE}{h_1}+\frac{AE}{h_2};K_{23}=-\frac{AE}{h_2};K_{24}=0\\ K_{33}& =\frac{AE}{h_2}+\frac{AE}{h_3};K_{34}=-\frac{AE}{h_3}\\ K_{44}& =\frac{AE}{h_3}\\ \end{array}$

In matrix form,

$𝐊=AE\left[\begin{array}{cccc}\frac{1}{h_1}& -\frac{1}{h_1}& 0& 0\\ & \frac{1}{h_1}+\frac{1}{h_2}& -\frac{1}{h_2}& 0\\ & & \frac{1}{h_2}+\frac{1}{h_3}& -\frac{1}{h_3}\\ \text{Symm.}& & & \frac{1}{h_3}\end{array}\right]$

Load vector

Similarly, for the load vector $𝐟$, we have

$\begin{array}{cc}{f}_j& =\underset{0}{\overset{L}{\int }}{N}_j𝐪dx+{N_j𝑹|}_{x=L}\\ & =\underset{{\mathrm{\Omega }}_1}{\int }{N}_j𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_j𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_j𝐪dx+{N_j𝑹|}_{x=L}\end{array}$

The components of the load vector are

$\begin{array}{cc}{f}_1& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_1𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_1𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_1𝐪dx+{N_1𝑹|}_{x=L}\\ f_2& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_2𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_2𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_2𝐪dx+{N_2𝑹|}_{x=L}\\ f_3& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_3𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_3𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_3𝐪dx+{N_3𝑹|}_{x=L}\\ f_4& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_4𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_4𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_4𝐪dx+{N_4𝑹|}_{x=L}\end{array}$

Once again, since $N_1$ is zero in elements 2 and 3, $N_2$ is zero in element 3, $N_3$ is zero in element 1, and $N_4$ is zero in elements 1 and 2, we have

$\begin{array}{cc}{f}_1& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_1𝐪dx+{N_1𝑹|}_{x=L}\\ f_2& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_2𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_2𝐪dx+{N_2𝑹|}_{x=L}\\ f_3& =\underset{{\mathrm{\Omega }}_2}{\int }{N}_3𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_3𝐪dx+{N_3𝑹|}_{x=L}\\ f_4& =\underset{{\mathrm{\Omega }}_3}{\int }{N}_4𝐪dx+{N_4𝑹|}_{x=L}\end{array}$

Now, the boundary $𝐱=L$ is at node 4 which is attached to element 3. The only non-zero shape function at this node is $N_4$. Therefore, we have

$\begin{array}{cc}{f}_1& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_1𝐪dx\\ f_2& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_2𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_2𝐪dx\\ f_3& =\underset{{\mathrm{\Omega }}_2}{\int }{N}_3𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_3𝐪dx\\ f_4& =\underset{{\mathrm{\Omega }}_3}{\int }{N}_4𝐪dx+{N_4𝑹|}_{x=L}\end{array}$

In terms of element shape functions, the above equations can be written as

$\begin{array}{cc}{f}_1& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_1^1𝐪dx=f_1^1\\ f_2& =\underset{{\mathrm{\Omega }}_1}{\int }{N}_2^1𝐪dx+\underset{{\mathrm{\Omega }}_2}{\int }{N}_1^2𝐪dx=f_2^1+f_1^2\\ f_3& =\underset{{\mathrm{\Omega }}_2}{\int }{N}_2^2𝐪dx+\underset{{\mathrm{\Omega }}_3}{\int }{N}_1^3𝐪dx=f_2^2+f_1^3\\ f_4& =\underset{{\mathrm{\Omega }}_3}{\int }{N}_2^3𝐪dx+{N_2^3𝑹|}_{x=L}=f_2^3+𝑹\end{array}$

The above shows that the global load vector can also be assembled from the element load vectors if we use finite element shape functions.

Load vector for two-noded elements

Using the linear shape functions discussed earlier and replacing $𝐪$ with $a𝐱$, the components of the element load vector ${𝐟}^e$ are

$\begin{array}{cc}{f}_1^e& =\underset{x_1}{\overset{x_2}{\int }}{N}_1^{e}a𝐱dx=\underset{x_1}{\overset{x_2}{\int }}\left(\frac{x_2-x}{h_e}\right)a𝐱dx=\frac{a}{h_e}(\frac{x_2(x_2^2-x_1^2)}{2}-\frac{x_2^3-x_1^3}{3})\\ f_2^e& =\underset{x_1}{\overset{x_2}{\int }}{N}_2^{e}a𝐱dx=\underset{x_1}{\overset{x_2}{\int }}\left(\frac{x-x_1}{h_e}\right)a𝐱dx=-\frac{a}{h_e}(\frac{x_1(x_2^2-x_1^2)}{2}-\frac{x_2^3-x_1^3}{3})\end{array}$

In matrix form, the element load vector is written

${𝐟}^e=\frac{a}{h_e}\left[\begin{array}{c}\frac{x_2(x_2^2-x_1^2)}{2}-\frac{x_2^3-x_1^3}{3}\\ \frac{x_2^3-x_1^3}{3}-\frac{x_1(x_2^2-x_1^2)}{2}\end{array}\right]$

Therefore, the components of the global load vector are

$\begin{array}{cc}{f}_1& =\frac{a}{h_1}(\frac{x_2(x_2^2-x_1^2)}{2}-\frac{x_2^3-x_1^3}{3})\\ f_2& =\frac{a}{h_1}(\frac{x_2^3-x_1^3}{3}-\frac{x_1(x_2^2-x_1^2)}{2})+\frac{a}{h_2}(\frac{x_3(x_3^2-x_2^2)}{2}-\frac{x_3^3-x_2^3}{3})\\ f_3& =\frac{a}{h_2}(\frac{x_3^3-x_2^3}{3}-\frac{x_2(x_3^2-x_2^2)}{2})+\frac{a}{h_3}(\frac{x_4(x_4^2-x_3^2)}{2}-\frac{x_4^3-x_3^3}{3})\\ f_4& =\frac{a}{h_3}(\frac{x_4^3-x_3^3}{3}-\frac{x_3(x_4^2-x_3^2)}{2})+𝑹\end{array}$

Displacement trial function

Recall that we assumed that the displacement can be written as

${𝐮}_h(𝐱)=a_1{\phi }_1(𝐱)+a_2{\phi }_2(𝐱)+\dots +a_n{\phi }_n(𝐱)=\sum _{i=1}^n{a}_i{\phi }_i(𝐱).$

If we use finite element shape functions, we can write the above as

${𝐮}_h(𝐱)=a_1{N}_1(𝐱)+a_2{N}_2(𝐱)+\dots +a_n{N}_n(𝐱)=\sum _{i=1}^n{a}_i{N}_i(𝐱)$

where $n$ is the total number of nodes in the domain. Also, recall that the value of $N_i$ is 1 at node $i$ and zero elsewhere. Therefore, we have

$\begin{array}{cc}{u}_1& :={𝐮}_h({𝐱}_1)=a_1{N}_1({𝐱}_1)+a_2{N}_2({𝐱}_1)+\dots +a_n{N}_n({𝐱}_1)=a_1\\ u_2& :={𝐮}_h({𝐱}_2)=a_1{N}_1({𝐱}_2)+a_2{N}_2({𝐱}_2)+\dots +a_n{N}_n({𝐱}_2)=a_2\\ ⋮\\ u_n& :={𝐮}_h({𝐱}_n)=a_1{N}_1({𝐱}_n)+a_2{N}_2({𝐱}_n)+\dots +a_n{N}_n({𝐱}_n)=a_n\\ \end{array}$

Therefore, the trial function can be written as

${𝐮}_h(𝐱)=u_1{N}_1(𝐱)+u_2{N}_2(𝐱)+\dots +u_n{N}_n(𝐱)=\sum _{i=1}^n{u}_i{N}_i(𝐱)$

where $u_i$ are the nodal displacements.

Finite element system of equations

If all the elements are assumed to be of the same length $h$, the finite element system of equations ($𝐊𝐚=𝐟$) can then be written as

$\frac{AE}{h}\left[\begin{array}{cccc}1& -1& 0& 0\\ -1& 2& -1& 0\\ 0& -1& 2& -1\\ 0& 0& -1& 1\end{array}\right]\left[\begin{array}{c}{u}_1\\ u_2\\ u_3\\ u_4\end{array}\right]=\frac{a}{h}\left[\begin{array}{c}(\frac{x_2(x_2^2-x_1^2)}{2}-\frac{x_2^3-x_1^3}{3})\\ (\frac{x_2^3-x_1^3}{3}-\frac{x_1(x_2^2-x_1^2)}{2})+(\frac{x_3(x_3^2-x_2^2)}{2}-\frac{x_3^3-x_2^3}{3})\\ (\frac{x_3^3-x_2^3}{3}-\frac{x_2(x_3^2-x_2^2)}{2})+(\frac{x_4(x_4^2-x_3^2)}{2}-\frac{x_4^3-x_3^3}{3})\\ (\frac{x_4^3-x_3^3}{3}-\frac{x_3(x_4^2-x_3^2)}{2})+𝑹\frac{h}{a}\end{array}\right]$

Essential boundary conditions

To solve this system of equations we have to apply the essential boundary condition $𝐮=0$ at $𝐱=0$. This is equivalent to setting $u_1=0$. The reduced system of equations is

$\frac{AE}{h}\left[\begin{array}{ccc}2& -1& 0\\ -1& 2& -1\\ 0& -1& 1\end{array}\right]\left[\begin{array}{c}{u}_2\\ u_3\\ u_4\end{array}\right]=\frac{a}{h}\left[\begin{array}{c}(\frac{x_2^3-x_1^3}{3}-\frac{x_1(x_2^2-x_1^2)}{2})+(\frac{x_3(x_3^2-x_2^2)}{2}-\frac{x_3^3-x_2^3}{3})\\ (\frac{x_3^3-x_2^3}{3}-\frac{x_2(x_3^2-x_2^2)}{2})+(\frac{x_4(x_4^2-x_3^2)}{2}-\frac{x_4^3-x_3^3}{3})\\ (\frac{x_4^3-x_3^3}{3}-\frac{x_3(x_4^2-x_3^2)}{2})+𝑹\frac{h}{a}\end{array}\right]$

This system of equations can be solved for $u_2$, $u_3$, and $u_4$. Let us do that.

Assume that $A$, $E$, $L$, $a$, and $R$ are all equal to 1. Then $x_1=0$, $x_2=1/3$, $x_3=2/3$, $x_4=1$, and $h=1/3$. The system of equations becomes

$\left[\begin{array}{ccc}2& -1& 0\\ -1& 2& -1\\ 0& -1& 1\end{array}\right]\left[\begin{array}{c}{u}_2\\ u_3\\ u_4\end{array}\right]=\left[\begin{array}{c}0.037\\ 0.074\\ 0.383\end{array}\right]⟹\left[\begin{array}{c}{u}_1\\ u_2\\ u_3\\ u_4\end{array}\right]=\left[\begin{array}{c}0.0\\ 0.494\\ 0.951\\ 1.333\end{array}\right]$

Computing element strains and stresses

From the above, it is clear that the displacement field within an element $e$ is given by

${𝐮}^e=u_1^e{N}_1^e(𝐱)+u_2^e{N}_2^e(𝐱).$

Therefore, the strain within an element is

${\mathit{\epsilon }}^e=\frac{\partial {𝐮}^e}{\partial x}=u_1^e\frac{\partial N_1^e}{\partial x}+u_2^e\frac{\partial N_2^e}{\partial x}.$

In matrix notation,

${\mathit{\epsilon }}^e={𝐁}^e{𝐮}^e=\left[\frac{\partial N_1^e}{\partial x}\frac{\partial N_2^e}{\partial x}\right]\left[\begin{array}{c}{u}_1^e\\ u_2^e\end{array}\right]=[-\frac{1}{h}\frac{1}{h}]\left[\begin{array}{c}{u}_1^e\\ u_2^e\end{array}\right]$

The stress in the element is given by

${\mathit{\sigma }}^e=E{\mathit{\epsilon }}^e.$

For our discretization, the element stresses are

$\begin{array}{cc}{\mathit{\sigma }}^1& =1.48\\ {\mathit{\sigma }}^2& =1.37\\ {\mathit{\sigma }}^3& =1.15\end{array}$

A plot of this solution is shown in Figure 7.

File:AxialBarFemDisp.png Figure 7(a). FEM vs exact solutions for displacements of an axially loaded bar.

File:AxialBarFemSig.png Figure 7(b). FEM vs exact solutions for stresses in an axially loaded bar.

Matlab code

The finite element code (Matlab) used to compute this solution is given below.

    function AxialBarFEM
      
      A = 1.0;
      L = 1.0;
      E = 1.0;
      a = 1.0;
      R = 1.0;
    
      e = 3;
      h = L/e;
      n = e+1;
      for i=1:n
        node(i) = (i-1)*h;
      end
      for i=1:e
        elem(i,:) = [i i+1];
      end
     
      K = zeros(n);
      f = zeros(n,1);
      for i=1:e
        node1 = elem(i,1);
        node2 = elem(i,2);
        Ke = elementStiffness(A, E, h);
        fe = elementLoad(node(node1),node(node2), a, h);
        K(node1:node2,node1:node2) = K(node1:node2,node1:node2) + Ke;
        f(node1:node2) = f(node1:node2) + fe;
      end
    
      f(n) = f(n) + R;
   
      Kred = K(2:n,2:n);
      fred = f(2:n);
   
      d = inv(Kred)*fred;
   
      dsol = [0 d'];
   
      fsol = K*dsol';
      sum(fsol)
    
      figure;
      p0 = plotDisp(E, A, L, R, a);
      p1 = plot(node, dsol, 'ro--', 'LineWidth', 3); hold on;
      legend([p0 p1],'Exact','FEM');
   
      for i=1:e
        node1 = elem(i,1);
        node2 = elem(i,2);
        u1 = dsol(node1);
        u2 = dsol(node2);
        [eps(i), sig(i)] = elementStrainStress(u1, u2, E, h);
      end
 
      figure;
      p0 = plotStress(E, A, L, R, a);
      for i=1:e
        node1 = node(elem(i,1));
        node2 = node(elem(i,2));
        p1 = plot([node1 node2], [sig(i) sig(i)], 'r-','LineWidth',3); hold on;
      end
      legend([p0 p1],'Exact','FEM');

    function [p] = plotDisp(E, A, L, R, a)

      dx = 0.01;
      nseg = L/dx;
      for i=1:nseg+1
        x(i) = (i-1)*dx;
        u(i) = (1/(6*A*E))*(-a*x(i)^3 + (6*R + 3*a*L^2)*x(i));
      end
      p = plot(x, u, 'LineWidth', 3); hold on;
      xlabel('x', 'FontName', 'palatino', 'FontSize', 18);
      ylabel('u(x)', 'FontName', 'palatino', 'FontSize', 18);
      set(gca, 'LineWidth', 3, 'FontName', 'palatino', 'FontSize', 18);

    function [p] = plotStress(E, A, L, R, a)

      dx = 0.01;
      nseg = L/dx;
      for i=1:nseg+1
        x(i) = (i-1)*dx;
        sig(i) = (1/(2*A))*(-a*x(i)^2 + (2*R + a*L^2));
      end
      p = plot(x, sig, 'LineWidth', 3); hold on;
      xlabel('x', 'FontName', 'palatino', 'FontSize', 18);
      ylabel('\sigma(x)', 'FontName', 'palatino', 'FontSize', 18);
      set(gca, 'LineWidth', 3, 'FontName', 'palatino', 'FontSize', 18);

    function [Ke] = elementStiffness(A, E, h)

      Ke = (A*E/h)*[[1 -1];[-1 1]];
 
    function [fe] = elementLoad(node1, node2, a, h)

      x1 = node1;
      x2 = node2;

      fe1 = a*x2/(2*h)*(x2^2-x1^2) - a/(3*h)*(x2^3-x1^3);
      fe2 = -a*x1/(2*h)*(x2^2-x1^2) + a/(3*h)*(x2^3-x1^3);
      fe = [fe1;fe2];

    function [eps, sig] = elementStrainStress(u1, u2, E, h)

      B = [-1/h 1/h];
      u = [u1; u2];
      eps = B*u
      sig = E*eps;

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