Nonlinear finite elements/Homework 8/Solutions

Problem 1: Plate Bending

Given:

Consider the flat plate shown in Figure 1.

File:KirchhoffPlate.png Figure 1. Flat plate

Transverse normals are defined as the straight lines perpendicular to the midsurface.

If we assume that the plate is thin, the Kirchhoff-Love hypothesis holds, i.e.,

• Transverse normals remain straight.
• Transverse normals remain normal to the midsurface.
• Transverse normals are inextensible.

Solutions

Part 1

The displacement field that satisfies the Kirchhoff-Love hypothesis is given by

$\begin{array}{cc}{u}_1(x_1,x_2,x_3)& =u_1^0(x_1,x_2)-x_3{u}_{3,1}^0\\ u_2(x_1,x_2,x_3)& =u_2^0(x_1,x_2)-x_3{u}_{3,2}^0\\ u_3(x_1,x_2,x_3)& =u_3^0(x_1,x_2)\end{array}$

where $u_i^0$ are the displacements of the midsurface.

Write the expanded form of the above equations after making the following substitutions.

$\text{(2)}\begin{array}{cc}& x:=x_1;y:=x_2;z:=x_3\\ & u:=u_1;v:=u_2;w:=u_3\\ & u_0:=u_1^0;v_0:=u_2^0;w_0:=u_3^0.\end{array}$

After making the substitutions we get

$\begin{array}{cc}u(x,y,z)& =u_0(x,y)-z{w}_{0,1}\\ v(x,y,z)& =v_0(x,y)-z{w}_{0,2}\\ w(x,y,z)& =w_0(x,y)\end{array}$

The expanded form is

$\begin{array}{cc}u(x,y,z)& =u_0(x,y)-z\frac{\partial w_0}{\partial x}\\ v(x,y,z)& =v_0(x,y)-z\frac{\partial w_0}{\partial y}\\ w(x,y,z)& =w_0(x,y)\end{array}$

Part 2

Assume that the plate undergoes infinitesimal strains and rotations. Then the strain-displacement relations are

$\mathit{\epsilon }=\frac{1}{2}[\mathrm{\nabla }𝐮+(\mathrm{\nabla }𝐮{)}^T].$

Show that, in terms of the midsurface displacements, the strain-displacement relations can be written in index notation as

$\begin{array}{cc}{\epsilon }_{\alpha \beta }& =\frac{1}{2}(u_{\alpha ,\beta }^0+u_{\beta ,\alpha }^0)-x_3{u}_{3,\alpha \beta }^0\\ {\epsilon }_{\alpha 3}& =0\\ {\epsilon }_{33}& =0\end{array}$

where $\alpha =1,2$ and $\beta =1,2$.

The strain-displacement relations in index notation are

${\epsilon }_{ij}=\frac{1}{2}[u_{i,j}+u_{j,i}]$

where $i,j=1,2,3$. If the indices $\alpha$ and $\beta$ run from 1 to 2, we can write the above strain-displacement relations as

$\begin{array}{cc}{\epsilon }_{\alpha \beta }& =\frac{1}{2}[u_{\alpha ,\beta }+u_{\beta ,\alpha }]\\ {\epsilon }_{\alpha 3}={\epsilon }_{3\alpha }& =\frac{1}{2}[u_{\alpha ,3}+u_{3,\alpha }]\\ {\epsilon }_{33}& =\frac{1}{2}[u_{3,3}+u_{3,3}]=u_{3,3}\end{array}$

The displacements are given by

$\begin{array}{cc}{u}_1& =u_1^0-x_3{u}_{3,1}^0\\ u_2& =u_2^0-x_3{u}_{3,2}^0\\ u_3& =u_3^0\end{array}$

If the index $\alpha$ runs from 1 to 2, the displacements can be written as

$\begin{array}{cc}{u}_{\alpha }& =u_{\alpha }^0-x_3{u}_{3,\alpha }^0\\ u_3& =u_3^0\end{array}$

The partial derivatives of the displacements are (since $u_1^0,u_2^0,u_3^0$ are functions only of $x_1$ and $x_2$)

$\begin{array}{cc}{u}_{\alpha ,\beta }& =u_{\alpha ,\beta }^0-x_3{u}_{3,\alpha \beta }^0\\ u_{\alpha ,3}& =u_{\alpha ,3}^0-x_3{u}_{3,\alpha 3}^0=0\\ u_{3,\alpha }& =u_{3,\alpha }^0=0\\ u_{3,3}& =u_{3,3}^0=0\end{array}$

Therefore,

$\begin{array}{cc}{\epsilon }_{\alpha \beta }& =\frac{1}{2}[u_{\alpha ,\beta }^0+u_{\beta ,\alpha }^0]-x_3{u}_{3,\alpha \beta }^0\\ {\epsilon }_{\alpha 3}={\epsilon }_{3\alpha }& =0\\ {\epsilon }_{33}& =0\end{array}$

Part 3

The internal virtual work in the plate is given by (using index notation)

$\delta W_{\text{int}}=\underset{{\mathrm{\Omega }}_0}{\int }\left(\underset{-h}{\overset{h}{\int }}{\sigma }_{\alpha \beta }\delta {\epsilon }_{\alpha \beta }d{x}_3\right)d{\mathrm{\Omega }}_0.$

Note that if a component of the strain tensor is zero, then the variation of that strain component is also zero.

Show that the internal virtual work can be written as

$\text{(3)}\delta W_{\text{int}}=\underset{{\mathrm{\Omega }}_0}{\int }(N_{\alpha \beta }\delta {\epsilon }_{\alpha \beta }^0+M_{\alpha \beta }\delta {\epsilon }_{\alpha \beta }^1)d{\mathrm{\Omega }}_0$

where

$\begin{array}{cc}{N}_{\alpha \beta }& =\underset{-h}{\overset{h}{\int }}{\sigma }_{\alpha \beta }d{x}_3\\ M_{\alpha \beta }& =\underset{-h}{\overset{h}{\int }}{x}_3{\sigma }_{\alpha \beta }d{x}_3\\ {\epsilon }_{\alpha \beta }^0& =\frac{1}{2}(u_{\alpha ,\beta }^0+u_{\beta ,\alpha }^0)\\ {\epsilon }_{\alpha \beta }^1& =-u_{3,\alpha \beta }^0.\end{array}$

Write down the expanded form of equation (3).

The strains are given by

${\epsilon }_{\alpha \beta }=\frac{1}{2}[u_{\alpha ,\beta }^0+u_{\beta ,\alpha }^0]-x_3{u}_{3,\alpha \beta }^0={\epsilon }_{\alpha \beta }^0+x_3{\epsilon }_{\alpha \beta }^1$

Therefore, the variations of the strains are

$\delta {\epsilon }_{\alpha \beta }=\delta {\epsilon }_{\alpha \beta }^0+x_3\delta {\epsilon }_{\alpha \beta }^1$

The internal virtual work is

$\begin{array}{cc}\delta W_{\text{int}}& =\underset{{\mathrm{\Omega }}_0}{\int }\left[\underset{-h}{\overset{h}{\int }}{\sigma }_{\alpha \beta }(\delta {\epsilon }_{\alpha \beta }^0+x_3\delta {\epsilon }_{\alpha \beta }^1)d{x}_3\right]d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Omega }}_0}{\int }[\delta {\epsilon }_{\alpha \beta }^0\underset{-h}{\overset{h}{\int }}{\sigma }_{\alpha \beta }d{x}_3+\delta {\epsilon }_{\alpha \beta }^1\underset{-h}{\overset{h}{\int }}{x}_3{\sigma }_{\alpha \beta }d{x}_3]d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Omega }}_0}{\int }[\delta {\epsilon }_{\alpha \beta }^0{N}_{\alpha \beta }+\delta {\epsilon }_{\alpha \beta }^1{M}_{\alpha \beta }]d{\mathrm{\Omega }}_0\end{array}$

Therefore,

$\delta W_{\text{int}}=\underset{{\mathrm{\Omega }}_0}{\int }(N_{\alpha \beta }\delta {\epsilon }_{\alpha \beta }^0+M_{\alpha \beta }\delta {\epsilon }_{\alpha \beta }^1)d{\mathrm{\Omega }}_0$

The expanded form of the above equation is

$\begin{array}{cc}\delta W_{\text{int}}=\underset{{\mathrm{\Omega }}_0}{\int }(& N_{11}\delta {\epsilon }_{11}^0+N_{12}\delta {\epsilon }_{12}^0+N_{21}\delta {\epsilon }_{21}^0+N_{22}\delta {\epsilon }_{22}^0+\\ & M_{11}\delta {\epsilon }_{11}^1+M_{12}\delta {\epsilon }_{12}^1+M_{21}\delta {\epsilon }_{21}^1+M_{22}\delta {\epsilon }_{22}^1)d{\mathrm{\Omega }}_0\end{array}$

or,

$\begin{array}{cc}\delta W_{\text{int}}=\underset{{\mathrm{\Omega }}_0}{\int }(& N_{11}\delta {\epsilon }_{11}^0+2N_{12}\delta {\epsilon }_{12}^0+N_{22}\delta {\epsilon }_{22}^0+\\ & M_{11}\delta {\epsilon }_{11}^1+2M_{12}\delta {\epsilon }_{12}^1+M_{22}\delta {\epsilon }_{22}^1)d{\mathrm{\Omega }}_0\end{array}$

Part 4

The equilibrium equations for the plate can be written as

$\begin{array}{cc}\frac{\partial N_{xx}}{\partial x}+\frac{\partial N_{xy}}{\partial y}& =0\\ \frac{\partial N_{xy}}{\partial x}+\frac{\partial N_{yy}}{\partial y}& =0\\ \frac{{\partial }^2{M}_{xx}}{\partial x^2}+2\frac{{\partial }^2{M}_{xy}}{\partial x\partial y}+\frac{{\partial }^2{M}_{yy}}{\partial y^2}+𝒩(u_0,v_0,w_0)+q& =0\end{array}$

where

$𝒩(u_0,v_0,w_0)=\frac{\partial }{\partial x}(N_{xx}\frac{\partial w_0}{\partial x}+N_{xy}\frac{\partial w_0}{\partial y})+\frac{\partial }{\partial y}(N_{xy}\frac{\partial w_0}{\partial x}+N_{yy}\frac{\partial w_0}{\partial y}).$

Write the above equations in index notation.

The equilibrium equations are (written using indices $1,2,3$):

$\begin{array}{cc}& N_{11,1}+N_{12,2}=0\\ & N_{21,1}+N_{22,2}=0\\ & M_{11,11}+2M_{12,12}+M_{22,22}+{(N_{11}{u}_{3,1}^0+N_{12}{u}_{3,2}^0)}_{,1}+{(N_{21}{u}_{3,1}^0+N_{22}{u}_{3,2}^0)}_{,2}+q=0\end{array}$

Using the summation convention, we get

$\begin{array}{cc}& N_{1\beta ,\beta }=0\\ & N_{2\beta ,\beta }=0\\ & M_{\alpha \beta ,\alpha \beta }+{\left(N_{1\beta }{u}_{3,\beta }^0\right)}_{,1}+{\left(N_{2\beta }{u}_{3,\beta }^0\right)}_{,2}+q=0\end{array}$

The first two equations can then be written as

$N_{\alpha \beta ,\beta }=0$

and the third equation can be written as

$M_{\alpha \beta ,\alpha \beta }+{\left(N_{\alpha \beta }{u}_{3,\beta }^0\right)}_{,\alpha }+q=0$

Therefore the equilibrium equations in index notation are

$\begin{array}{cc}& N_{\alpha \beta ,\beta }=0\\ & M_{\alpha \beta ,\alpha \beta }+{\left(N_{\alpha \beta }{u}_{3,\beta }^0\right)}_{,\alpha }+q=0\end{array}$

Part 5

Show that in index-free Gibbs notation the equilibrium equations for the plate can be written as

$\begin{array}{cc}\mathrm{\nabla }\bullet 𝑵& =\mathrm{𝟎}\text{(4)}\\ \mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)+\mathrm{\nabla }\bullet (𝑵\bullet \mathrm{\nabla }{u}_3^0\mathit{)}+q& =0\text{(5)}\end{array}$

where

$\begin{array}{cccc}𝑵& =N_{\alpha \beta }{𝐞}_{\alpha }\otimes {𝐞}_{\beta };& 𝑴& =M_{\alpha \beta }{𝐞}_{\alpha }\otimes {𝐞}_{\beta }\\ \mathrm{\nabla }\phi & ={\phi }_{,\alpha }{𝐞}_{\alpha };& \mathrm{\nabla }𝐯& =v_{\alpha ,\beta }{𝐞}_{\alpha }\otimes {𝐞}_{\beta };& \mathrm{\nabla }𝑺& =S_{\alpha \beta ,\gamma }{𝐞}_{\alpha }\otimes {𝐞}_{\beta }\otimes {𝐞}_{\gamma }\\ \mathrm{\nabla }\bullet 𝐯& =v_{\alpha ,\alpha };& \mathrm{\nabla }\bullet 𝑺& =S_{\alpha \beta ,\beta }{𝐞}_{\alpha };& \mathrm{\nabla }\bullet 𝑻& =T_{\alpha \beta \gamma ,\gamma }{𝐞}_{\alpha }\otimes {𝐞}_{\beta }\end{array}$

and $\alpha =1,2$, $\beta =1,2$, and $\gamma =1,2$.

Equation (4) in index notation is

$\mathrm{\nabla }\bullet 𝑵=N_{\alpha \beta ,\beta }{𝐞}_{\alpha }=\mathrm{𝟎}⟹N_{\alpha \beta ,\beta }=0$

The above equations have been shown to be equivalent to the first two equilibrium equations in the previous part.

Let us now look at equation (5). Let

$𝐩:=\mathrm{\nabla }\bullet 𝑴⟹p_{\alpha }{𝐞}_{\alpha }=M_{\alpha \beta ,\beta }{𝐞}_{\alpha }$

Then

$\mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)=\mathrm{\nabla }\bullet 𝐩=p_{\alpha ,\alpha }=M_{\alpha \beta ,\alpha \beta }$

For the next term, let

$𝐰:=\mathrm{\nabla }{u}_3^0⟹w_{\alpha }{𝐞}_{\alpha }=u_{3,\alpha }^0{𝐞}_{\alpha }⟹w_{\alpha }=u_{3,\alpha }^0$

Then,

$𝐪:=𝑵\bullet \mathrm{\nabla }{u}_3^0=𝑵\bullet 𝐰⟹q_{\alpha }{𝐞}_{\alpha }=N_{\alpha \beta }{w}_{\beta }{𝐞}_{\alpha }=N_{\alpha \beta }{u}_{3,\beta }^0{𝐞}_{\alpha }$

Hence

$\mathrm{\nabla }\bullet (𝑵\bullet \mathrm{\nabla }{u}_3^0\mathit{)}=\mathrm{\nabla }\bullet 𝐪=q_{\alpha ,\alpha }=(N_{\alpha \beta }{u}_{3,\beta }^0{)}_{,\alpha }$

Therefore, equation (5) can be written as

$M_{\alpha \beta ,\alpha \beta }+(N_{\alpha \beta }{u}_{3,\beta }^0{)}_{,\alpha }+q=0$

The above equation has been shown to be equivalent to the third equilibrium equations in the previous part.

Part 6

Derive the symmetric weak forms of the equilibrium equations starting with equations (4) and (5). Use the coordinate-free Gibbs notation in your derivation.

For equation 4, we multiply the equation by a vector weighting function ${𝐰}_1$ and integrate over the midsurface ${\mathrm{\Omega }}_0$. Then,

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }{𝐰}_1\bullet (\mathrm{\nabla }\bullet 𝑵)d{\mathrm{\Omega }}_0& =0\end{array}$

Using the identity

$\mathrm{\nabla }\bullet ({𝑺}^T\bullet 𝐯)=𝐯\bullet (\mathrm{\nabla }\bullet 𝑺)+𝑺:(\mathrm{\nabla }𝐯)$

we get

${𝐰}_1\bullet (\mathrm{\nabla }\bullet 𝑵)=\mathrm{\nabla }\bullet ({𝑵}^T\bullet {𝐰}_1)-𝑵:(\mathrm{\nabla }{𝐰}_1)$

From the symmetry to the stress tensor $𝑵={𝑵}^T$. Hence,

${𝐰}_1\bullet (\mathrm{\nabla }\bullet 𝑵)=\mathrm{\nabla }\bullet (𝑵\bullet {𝐰}_1)-𝑵:(\mathrm{\nabla }{𝐰}_1)$

Therefore

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }{𝐰}_1\bullet (\mathrm{\nabla }\bullet 𝑵)d{\mathrm{\Omega }}_0& =\underset{{\mathrm{\Omega }}_0}{\int }\mathrm{\nabla }\bullet (𝑵\bullet {𝐰}_1)d{\mathrm{\Omega }}_0-\underset{{\mathrm{\Omega }}_0}{\int }𝑵:(\mathrm{\nabla }{𝐰}_1)d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (𝑵\bullet {𝐰}_1)d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }𝑵:(\mathrm{\nabla }{𝐰}_1)d{\mathrm{\Omega }}_0\end{array}$

where $𝐧$ is the normal to the boundary ${\mathrm{\Gamma }}_0$ of the midsurface.

Hence the symmetric weak form of the first equation is

$\underset{{\mathrm{\Omega }}_0}{\int }𝑵:\mathrm{\nabla }{𝐰}_{1}d{\mathrm{\Omega }}_0=\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (𝑵\bullet {𝐰}_1)d{\mathrm{\Gamma }}_0$

For equation 5, we multiply the equation by a scalar weighting function $w_2$ and integrate over the midsurface ${\mathrm{\Omega }}_0$. Then,

$\underset{{\mathrm{\Omega }}_0}{\int }{w}_2[\mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)+\mathrm{\nabla }\bullet (𝑵\bullet \mathrm{\nabla }{u}_3^0\mathit{)}+q]d{\mathrm{\Omega }}_0=0$

Using the identity,

$\mathrm{\nabla }\bullet (\phi 𝐯)=\phi (\mathrm{\nabla }\bullet 𝐯)+𝐯\bullet (\mathrm{\nabla }\phi )$

we get

$w_2[\mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)]=\mathrm{\nabla }\bullet [w_2(\mathrm{\nabla }\bullet 𝑴)]-(\mathrm{\nabla }\bullet 𝑴)\bullet (\mathrm{\nabla }{w}_2)$

Therefore,

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }{w}_2[\mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)]d{\mathrm{\Omega }}_0& =\underset{{\mathrm{\Omega }}_0}{\int }\mathrm{\nabla }\bullet [w_2(\mathrm{\nabla }\bullet 𝑴)]d{\mathrm{\Omega }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(\mathrm{\nabla }\bullet 𝑴)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet [w_2(\mathrm{\nabla }\bullet 𝑴)]d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(\mathrm{\nabla }\bullet 𝑴)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }{w}_2[𝐧\bullet (\mathrm{\nabla }\bullet 𝑴)]d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(\mathrm{\nabla }\bullet 𝑴)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\end{array}$

In order to have natural BCs directly in terms of moments, we have to perform a similar set of operations the last term above. Thus,

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }(\mathrm{\nabla }\bullet 𝑴)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0& =\underset{{\mathrm{\Omega }}_0}{\int }\mathrm{\nabla }\bullet [𝑴\bullet (\mathrm{\nabla }{𝒘}_2\mathit{)}\mathit{]}d{\mathrm{\Omega }}_0-\underset{{\mathrm{\Omega }}_0}{\int }𝑴:[\mathrm{\nabla }(\mathrm{\nabla }{w}_2)]d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet [𝑴\bullet (\mathrm{\nabla }{w}_2)]d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }𝑴:[\mathrm{\nabla }(\mathrm{\nabla }{w}_2)]d{\mathrm{\Omega }}_0\end{array}$

Hence,

$\underset{{\mathrm{\Omega }}_0}{\int }{w}_2\mathrm{\nabla }\bullet (\mathrm{\nabla }\bullet 𝑴)d{\mathrm{\Omega }}_0=\underset{{\mathrm{\Gamma }}_0}{\int }\{w_2𝐧\bullet (\mathrm{\nabla }\bullet 𝑴)-𝐧\bullet 𝑴\bullet (\mathrm{\nabla }{w}_2)\}d{\mathrm{\Gamma }}_0+\underset{{\mathrm{\Omega }}_0}{\int }𝑴:\left(\mathrm{\nabla }\mathrm{\nabla }{w}_2\right)d{\mathrm{\Omega }}_0$

Similarly,

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }{w}_2[\mathrm{\nabla }\bullet (𝑵\bullet \mathrm{\nabla }{u}_3^0\mathit{)}]d{\mathrm{\Omega }}_0& =\underset{{\mathrm{\Omega }}_0}{\int }\mathrm{\nabla }\bullet [w_2(𝑵\bullet \mathrm{\nabla }{u}_3^0\mathit{)}\mathit{]}d{\mathrm{\Omega }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(𝑵\bullet \mathrm{\nabla }{u}_3^0)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet [w_2(𝐝ot𝑵\mathrm{\nabla }{u}_3^0)]d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(𝑵\bullet \mathrm{\nabla }{u}_3^0)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\\ & =\underset{{\mathrm{\Gamma }}_0}{\int }{w}_2[𝐧\bullet (𝑵\bullet \mathrm{\nabla }{u}_3^0)]d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Omega }}_0}{\int }(𝑵\bullet \mathrm{\nabla }{u}_3^0)\bullet (\mathrm{\nabla }{w}_2)d{\mathrm{\Omega }}_0\end{array}$

Therefore, the symmetric weak form of the second equation is

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }& [(𝑵\bullet \mathrm{\nabla }{u}_3^0)\bullet \mathrm{\nabla }{w}_2-𝑴:\left(\mathrm{\nabla }\mathrm{\nabla }{w}_2\right)]d{\mathrm{\Omega }}_0=\\ & \underset{{\mathrm{\Omega }}_0}{\int }{w}_{2}qd{\mathrm{\Omega }}_0+\underset{{\mathrm{\Gamma }}_0}{\int }[w_2\{𝐧\bullet (\mathrm{\nabla }\bullet 𝑴)+𝐧\bullet 𝑵\bullet \mathrm{\nabla }{u}_3^0\}-𝐧\bullet (𝑴\bullet \mathrm{\nabla }{w}_2)]d{\mathrm{\Gamma }}_0\end{array}$

Using the distributive law for vectors

$(𝐚+𝐛)\bullet 𝐜=𝐚\bullet 𝐜+𝐛\bullet 𝐜$

we can also write the symmetric weak form for the second equation as:

$\begin{array}{cc}\underset{{\mathrm{\Omega }}_0}{\int }& [(𝑵\bullet \mathrm{\nabla }{u}_3^0)\bullet \mathrm{\nabla }{w}_2-𝑴:\left(\mathrm{\nabla }\mathrm{\nabla }{w}_2\right)]d{\mathrm{\Omega }}_0=\\ & \underset{{\mathrm{\Omega }}_0}{\int }{w}_{2}qd{\mathrm{\Omega }}_0+\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (\mathrm{\nabla }\bullet 𝑴+𝑵\bullet \mathrm{\nabla }{u}_3^0)w_{2}d{\mathrm{\Gamma }}_0-\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (𝑴\bullet \mathrm{\nabla }{w}_2)d{\mathrm{\Gamma }}_0\end{array}$

Part 7

Write down the natural boundary conditions in Gibbs notation.

From the expressions for the weak form, the weighted natural boundary conditions are

$\begin{array}{cc}& \underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (𝐝ot𝑵{𝐰}_1)d{\mathrm{\Gamma }}_0\\ & \underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (\mathrm{\nabla }\bullet 𝑴+𝑵\bullet \mathrm{\nabla }{u}_3^0)w_{2}d{\mathrm{\Gamma }}_0\\ & -\underset{{\mathrm{\Gamma }}_0}{\int }𝐧\bullet (𝐝ot𝑴\mathrm{\nabla }{w}_2)d{\mathrm{\Gamma }}_0\end{array}$

Therefore, the natural boundary conditions are:

$\begin{array}{ccc}\text{Boundary Membrane Forces}& & 𝐧\bullet 𝑵\\ \text{Boundary Transverse Forces}& & 𝐧\bullet (\mathrm{\nabla }\bullet 𝑴+𝑵\bullet \mathrm{\nabla }{u}_3^0)\\ \text{Boundary Moments}& & 𝐧\bullet 𝑴\end{array}$

Part 8

What are the essential boundary conditions that can be applied to the plate?

The essential boundary conditions that can be applied are

$\begin{array}{ccc}\text{Boundary Membrane Displacements}& & u_1^0,u_2^0\\ \text{Boundary Transverse Displacements}& & u_3^0\\ \text{Boundary Out-of-plane Rotations}& & \mathrm{\nabla }{u}_3^0\end{array}$

Problem 2: Transient Heat Conduction

Given:

The model problem shown in Figure 6.

File:NFE HW8Prob2.png Figure 6. Container with burning high energy material.

A 4340 steel casing is used to contain a solid high energy (HE) material. The HE material reacts on the inner (star-shaped) surface and generates gases. Since the gases are confined, the temperature of the gases increases according to the ideal gas law ($PV=nRT$).

The inner radius of the steel casing is 5 cm. The outer radius of the steel casing is 6 cm. The inner and outer radii of the star shaped region are 4 cm and 2 cm, respectively.

The high energy material has properties: Density = 1200 kg/m$3^{}$, Young's modulus = 1 GPa, Poisson's ratio = 0.49, Coefficient of thermal expansion = 1.2$\times$10${-4}^{}$ /K, Thermal Conductivity = 5 W/m-K, Specific Heat Capacity = 1000 J/kg-K.

The burn-surface does not change position. The temperature is the same at all points on the burn surface. The temperature at the burn surface increases exponentially with time according to the relation

$T=T_0+A\exp (Bt)$

where $T_0$ is the initial temperature (300 K), $T$ is the temperature at time $t$, $A=2$ K, and $B=3$ K/s.

Solution

The properties of normalized 4340 steel from Matweb are

Density	7850 kg/m$3^{}$	0.284 lbm/in$3^{}$
Young's Modulus	205 GPa	29.7$\times$10$6^{}$ psi
Poisson's Ratio	0.29	0.29
CTE	12.6$\times$10${-6}^{}$ /K	7$\times$10${-6}^{}$/F
Thermal Conductivity	44.5 W/m-K	309 BTU-in/hr-ft$2^{}$-F
Specific Heat Capacity	475 J/kg-K	0.114 BTU/lb-F

Part 1

Assume that the initial temperature of the steel and the HE material is 300 K. Also assume that there is no heat flux on the external surface of the steel casing. Plot the temperature contours and stresses in the two materials at $t=1$ s and $t=2$ s.

The temperature contours for the two materials are shown in Figure 7. The low thermal conductivity of the HE material leads to a slow rate of diffusion of heat into the material. Therefore, the steel casing sees no change in temperature. However, the casing does deform due to the deformation of the HE material.

File:NFE HW8Prob2 a 1s Temp.jpg Figure 7(a). Temperature contours for no flux BC at t = 1 sec. Units are degrees K.

File:NFE HW8Prob2 a 2s Temp.jpg Figure 7(b). Temperature contours for no flux BC at t = 2 sec. Units are degrees K.

The stress contours for the two materials are shown in Figures 8, 9, 10, and 11. The principal stress ${\sigma }_1$ is tensile in the steel casing and reaches a values of around 200 MPa (close to its yield point). In the HE material, ${\sigma }_1$ is compressive in some regions and tensile in others and reaches values well beyond the ulimate tensile strength of the material inside some elements.

File:NFE HW8Prob2 a 1s Sig1.jpg Figure 8(a). First Principal Stress contours for no flux BC at t = 1 sec. Units are Pa.

File:NFE HW8Prob2 a 2s Sig1.jpg Figure 8(b). First Principal Stress contours for no flux BC at t = 2 sec. Units are Pa.

File:NFE HW8Prob2 a 1s Sig2.jpg Figure 9(a). Second Principal Stress contours for no flux BC at t = 1 sec. Units are Pa.

File:NFE HW8Prob2 a 2s Sig2.jpg Figure 9(b). Second Principal Stress contours for no flux BC at t = 2 sec. Units are Pa.

File:NFE HW8Prob2 a 1s Sig3.jpg Figure 10(a). Third Principal Stress contours for no flux BC at t = 1 sec. Units are Pa.

File:NFE HW8Prob2 a 2s Sig3.jpg Figure 10(b). Third Principal Stress contours for no flux BC at t = 2 sec. Units are Pa.

File:NFE HW8Prob2 a 1s SigXY.jpg Figure 11(a). Shear Stress contours for no flux BC at t = 1 sec. Units are Pa.

File:NFE HW8Prob2 a 2s SigXY.jpg Figure 11(b). Shear Stress contours for no flux BC at t = 2 sec. Units are Pa.

The ANSYS input file used for this problem is given below. The preprocessing stage is shown in the PDF file NFE_HW8Prob2Ans.pdf.

File:NFE HW8Prob2Ans.pdf Figure 12. Preprocessing ANSYS input.

The solution stage is shown below:

!
! Solve
!
/solu
antype, trans
timint, off, struc
cnvtol, heat
cnvtol, f
autots, on
solcontrol, on
!
! Initial condition
!
ic, all, temp, 300
!
! Time stepping
!
time, 2
deltim, 0.1
outres, all, 10
solve
finish

Part 2

Assume that the initial temperature of the steel and the HE material is 300 K. Also assume that the external surface of the steel casing is maintained at 300 K. Plot the temperature contours and stresses in the two materials at $t=1$ s and $t=2$ s.

The temperature distribution from the previous problem suggests that the heat flux at the external surface is zero if the outside is maintained at 300 K (because of the low thermal conductivity of the HE material.) We don't expect to see any significant difference in the temperature and stress distributions.

Problem 3: Explicit Finite Elements

Given:

Figure 13(a) shows a beam that is built-in at one and loaded at the other. Figure 13(b) shows a plate that is built-in at one end and loaded at the other. The load that is applied is transient and has the form shown in Figure 13(c).

File:NFE HW8Prob3.png Figure 13(a) and (b). Built-in cantilevered beam and plate.

File:NFE HW8Prob3 1.png Figure 13(c). Load curve.

Assume that the beam and the plate are made of 4340 steel. The beam has dimensions 12 in. $\times$ 0.25 in. $\times$ 0.25 in. The plate has dimensions 12 in. $\times$ 0.25 in. $\times$ 6 in.

Simulate the problem for 10 secs. using LS-DYNA or some other explicit FE code. Use beam elements for the beam and shell elements for the plate. Use an element size of 2 in. for the beam and 2 in. $\times$ 2 in. for the shell.

Solution

Part 1

Plot the displacement of the end of the beam as a function of time.

Figure 14 shows the displacement of the end of the beam as a function of time. Some numerical damping appears to occur if Hughes-Liu beam elements are used with 2$\times$2 quadrature.

File:NFE HW8Prob3 1 Disp.png Figure 14. Displacement (in) of the end of the beam as a function of time (secs).

Part 2

Plot the axial stress at two points on the top of the beam as a function of time.

Figure 15 shows the axial stress at a Gauss point near the top of the beam for elements 2 and 5.

File:NFE HW8Prob3 1 Sig2.png Figure 15 (a). Axial stress (psi) at element 2 at the top of the beam as a function of time (secs).

File:NFE HW8Prob3 1 Sig5.png Figure 15 (b). Axial stress (psi) at element 5 at the top of the beam as a function of time (secs).

The LS-Dyna keyword file for the beam is shown below.

*keyword
*title
HW8Prob3_1.k - cantilever beam
*control_termination
10
*database_binary_d3plot
0.1
*database_history_node
1, 2, 3, 4, 5, 6, 7
*database_nodout
0.1
*database_history_beam
1, 2, 3, 4, 5, 6
*database_elout
0.1
*part
steel beam
1,1,1
*section_beam
1, 1, 0.833, 2.0, 0.0
0.25, 0.25, 0.25, 0.25, 0.0, 0.0
*mat_elastic
1, 0.284, 29.7e6, 0.29
*node
1, 0, 0, 0, 7, 7
2, 2.0, 0, 0, 0, 0
3, 4.0, 0, 0, 0, 0
4, 6.0, 0, 0, 0, 0
5, 8.0, 0, 0, 0, 0
6, 10.0, 0, 0, 0, 0
7, 12.0, 0, 0, 0, 0
8, 5.0, 1.0, 0, 0, 0
*element_beam
1, 1, 1, 2, 8, 0, 0, 0, 0, 2
2, 1, 2, 3, 8, 0, 0, 0, 0, 2
3, 1, 3, 4, 8, 0, 0, 0, 0, 2
4, 1, 4, 5, 8, 0, 0, 0, 0, 2
5, 1, 5, 6, 8, 0, 0, 0, 0, 2
6, 1, 6, 7, 8, 0, 0, 0, 0, 2
*load_node_point
7, 2, 1, 1.0
*define_curve
1
0.0, 0.0
0.1, 200.0
0.2, 200.0
0.25, 0.0
10.0, 0.0
*end

Part 3

Plot the displacement of the end of the plate as a function of time.

Figure 16 shows the displacement of the end of the plate as a function of time. Hughes-Liu shell elements with 3 integration points are used.

File:NFE HW8Prob3 2 Disp.png Figure 16. Displacement of the end of the plate as a function of time.

Part 4

Plot the axial stress at two points on the top of the plate as a function of time.

Figure 17 shows the axial stress at a Gauss point near the top of the plate for elements 8 and 11.

File:NFE HW8Prob3 2 Sig8.png Figure 17(a). Axial stress at element 8 at the top of the plate as a function of time.

File:NFE HW8Prob3 2 Sig11.png Figure 17(b). Axial stress at element 11 at the top of the plate as a function of time.

The LS-Dyna keyword file for the beam is shown below.

*keyword
*title
HW8Prob3_2 - bending of shell element
*control_termination
10
*database_binary_d3plot
0.1
*database_history_node_set
2
*database_nodout
0.1
*database_history_shell_set
1
*database_elout
0.1
*part
steel shell
1,1,1
*section_shell
1, 1, 0.833, 3.0, 0.0
0.25, 0.25, 0.25, 0.25, 0.0, 0.0
*mat_elastic
1, 0.284, 29.7e6, 0.29
*node
1,0,0,0
2,2,0,0
3,4,0,0
4,6,0,0
5,8,0,0
6,10,0,0
7,12,0,0
8,0,2,0
9,2,2,0
10,4,2,0
11,6,2,0
12,8,2,0
13,10,2,0
14,12,2,0
15,0,4,0
16,2,4,0
17,4,4,0
18,6,4,0
19,8,4,0
20,10,4,0
21,12,4,0
22,0,6,0
23,2,6,0
24,4,6,0
25,6,6,0
26,8,6,0
27,10,6,0
28,12,6,0
*set_node_list
1
1, 8, 15, 22
*set_node_list
2
7, 14, 21, 28
*element_shell
1,1,1,2,9,8
2,1,2,3,10,9
3,1,3,4,11,10
4,1,4,5,12,11
5,1,5,6,13,12
6,1,6,7,14,13
7,1,8,9,16,15
8,1,9,10,17,16
9,1,10,11,18,17
10,1,11,12,19,18
11,1,12,13,20,19
12,1,13,14,21,20
13,1,15,16,23,22
14,1,16,17,24,23
15,1,17,18,25,24
16,1,18,19,26,25
17,1,19,20,27,26
18,1,20,21,28,27
*set_shell_list
1
8, 11
*boundary_spc_set
1, 0, 1, 1, 1, 1, 1, 1
*load_node_set
2, 3, 1, 1.0
*define_curve
1
0.0, 0.0
0.1, 200.0
0.2, 200.0
0.25, 0.0
10.0, 0.0
*end