Bending of plates

File:BendingCircularPlate.png

Bending of an edge-clamped circular plate under the action of a transverse pressure. The left half of the plate shows the deformed shape, while the right half shows the undeformed shape. This calculation was performed using Ansys.

Bending of plates, or plate bending, refers to the deflection of a plate perpendicular to the plane of the plate under the action of external forces and moments. The amount of deflection can be determined by solving the differential equations of an appropriate plate theory. The stresses in the plate can be calculated from these deflections. Once the stresses are known, failure theories can be used to determine whether a plate will fail under a given load.

Bending of Kirchhoff-Love plates

File:PlateForcesMoments upd.png

Forces and moments on a flat plate.

In the Kirchhoff–Love plate theory for plates the governing equations are

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

and

$M_{\alpha\beta,\alpha\beta} - q = 0$

In expanded form,

$\cfrac{\partial N_{11}}{\partial x_1} + \cfrac{\partial N_{21}}{\partial x_2} = 0 ~;~~ \cfrac{\partial N_{12}}{\partial x_1} + \cfrac{\partial N_{22}}{\partial x_2} = 0$

and

$\cfrac{\partial^2 M_{11}}{\partial x_1^2} + 2\cfrac{\partial^2 M_{12}}{\partial x_1 \partial x_2} + \cfrac{\partial^2 M_{22}}{\partial x_2^2} = q$

where $q(x)$ is an applied transverse load per unit area, the thickness of the plate is $H=2h$, the stresses are $\sigma_{ij}$, and

$N_{\alpha\beta} := \int_{-h}^h \sigma_{\alpha\beta}~dx_3 ~;~~ M_{\alpha\beta} := \int_{-h}^h x_3~\sigma_{\alpha\beta}~dx_3~.$

The quantity $N$ has units of force per unit length. The quantity $M$ has units of moment per unit length.

For isotropic, homogeneous, plates with Young's modulus $E$ and Poisson's ratio $\nu$ these equations reduce to

$\nabla^2\nabla^2 w = -\cfrac{q}{D} ~;~~ D := \cfrac{2h^3E}{3(1-\nu^2)} = \cfrac{H^3E}{12(1-\nu^2)}$

where $w(x_1,x_2)$ is the deflection of the mid-surface of the plate.

In rectangular Cartesian coordinates,

$\cfrac{\partial^4 w}{\partial x_1^4} + 2\cfrac{\partial^4 w}{\partial x_1^2 \partial x_2^2} + \cfrac{\partial^4 w}{\partial x_2^4} = -\cfrac{q}{D} \,.$

Circular Kirchhoff-Love plates

The bending of circular plates can be examined by solving the governing equation with appropriate boundary conditions. These solutions were first found by Poisson in 1829. Cylindrical coordinates are convenient for such problems. Here $z$ is the distance of a point from the midplane of the plate.

The governing equation in coordinate-free form is

$\nabla^2 \nabla^2 w = -\frac{q}{D} \,.$

In cylindrical coordinates $(r, \theta, z)$,

$\nabla^2 w \equiv \frac{1}{r}\frac{\partial }{\partial r}\left(r \frac{\partial w}{\partial r}\right) + \frac{1}{r^2}\frac{\partial^2 w}{\partial \theta^2} + \frac{\partial^2 w}{\partial z^2} \,.$

For symmetrically loaded circular plates, $w = w(r)$, and we have

$\nabla^2 w \equiv \frac{1}{r}\cfrac{d }{d r}\left(r \cfrac{d w}{d r}\right) \,.$

Therefore, the governing equation is

$\frac{1}{r}\cfrac{d }{d r}\left[r \cfrac{d }{d r}\left\{\frac{1}{r}\cfrac{d }{d r}\left(r \cfrac{d w}{d r}\right)\right\}\right] = -\frac{q}{D}\,.$

If $q$ and $D$ are constant, direct integration of the governing equation gives us

$w(r) = -\frac{qr^4}{64 D} + C_1\ln r + \cfrac{C_2 r^2}{2} + \cfrac{C_3r^2}{4}(2\ln r - 1) + C_4$

where $C_i$ are constants. The slope of the deflection surface is

$\phi(r) = \cfrac{d w}{d r} = -\frac{qr^3}{16D} + \frac{C_1}{r} + C_2 r + C_3 r \ln r \,.$

For a circular plate, the requirement that the deflection and the slope of the deflection are finite at $r = 0$ implies that $C_1 = 0$. However, $C_3$ need not equal 0, as the limit of $r \ln r\,$ exists as you approach $r = 0$ from the right.

Clamped edges

For a circular plate with clamped edges, we have $w(a) = 0$ and $\phi(a) = 0$ at the edge of the plate (radius $a$). Using these boundary conditions we get

$w(r) = -\frac{q}{64 D} (a^2 -r^2)^2 \quad \text{and} \quad \phi(r) = \frac{qr}{16 D}(a^2-r^2) \,.$

The in-plane displacements in the plate are

$u_r(r) = -z\phi(r) \quad \text{and} \quad u_\theta(r) = 0 \,.$

The in-plane strains in the plate are

$\varepsilon_{rr} = \cfrac{d u_r}{d r} = -\frac{qz}{16D}(a^2-3r^2) ~,~~ \varepsilon_{\theta\theta} = \frac{u_r}{r} = -\frac{qz}{16D}(a^2-r^2) ~,~~ \varepsilon_{r\theta} = 0 \,.$

The in-plane stresses in the plate are

$\sigma_{rr} = \frac{E}{1-\nu^2}\left[\varepsilon_{rr} + \nu\varepsilon_{\theta\theta}\right] ~;~~ \sigma_{\theta\theta} = \frac{E}{1-\nu^2}\left[\varepsilon_{\theta\theta} + \nu\varepsilon_{rr}\right] ~;~~ \sigma_{r\theta} = 0 \,.$

For a plate of thickness $2h$, the bending stiffness is $D = 2Eh^3/[3(1-\nu^2)]$ and we have

$\begin{align} \sigma_{rr} &= -\frac{3qz}{32h^3}\left[(1+\nu)a^2-(3+\nu)r^2\right] \\ \sigma_{\theta\theta} &= -\frac{3qz}{32h^3}\left[(1+\nu)a^2-(1+3\nu)r^2\right]\\ \sigma_{r\theta} &= 0 \,. \end{align}$

The moment resultants (bending moments) are

$M_{rr} = -\frac{q}{16}\left[(1+\nu)a^2-(3+\nu)r^2\right] ~;~~ M_{\theta\theta} = -\frac{q}{16}\left[(1+\nu)a^2-(1+3\nu)r^2\right] ~;~~ M_{r\theta} = 0 \,.$

The maximum radial stress is at $z = h$ and $r = a$:

$\left.\sigma_{rr}\right|_{z=h,r=a} = \frac{3qa^2}{16h^2} = \frac{3qa^2}{4H^2}$

where $H := 2h$. The bending moments at the boundary and the center of the plate are

$\left.M_{rr}\right|_{r=a} = \frac{qa^2}{8} ~,~~ \left.M_{\theta\theta}\right|_{r=a} = \frac{\nu qa^2}{8} ~,~~ \left.M_{rr}\right|_{r=0} = \left.M_{\theta\theta}\right|_{r=0} = -\frac{(1+\nu) qa^2}{16} \,.$

Rectangular Kirchhoff-Love plates

File:RectangularPlateBending.svg

Bending of a rectangular plate under the action of a distributed force $q$ per unit area.

For rectangular plates, Navier in 1820 introduced a simple method for finding the displacement and stress when a plate is simply supported. The idea was to express the applied load in terms of Fourier components, find the solution for a sinusoidal load (a single Fourier component), and then superimpose the Fourier components to get the solution for an arbitrary load.

Sinusoidal load

Let us assume that the load is of the form

$q(x,y) = q_0 \sin\frac{\pi x}{a}\sin\frac{\pi y}{b} \,.$

Here $q_0$ is the amplitude, $a$ is the width of the plate in the $x$-direction, and $b$ is the width of the plate in the $y$-direction.

Since the plate is simply supported, the displacement $w(x,y)$ along the edges of the plate is zero, the bending moment $M_{xx}$ is zero at $x=0$ and $x=a$, and $M_{yy}$ is zero at $y=0$ and $y=b$.

If we apply these boundary conditions and solve the plate equation, we get the solution

$w(x,y) = \frac{q_0}{\pi^4 D}\,\left(\frac{1}{a^2}+\frac{1}{b^2}\right)^{-2}\,\sin\frac{\pi x}{a}\sin\frac{\pi y}{b} \,.$

Where D is the flexural rigidity

$D=\frac{Et^3}{12(1-\nu^2)}$

Analogous to flexural stiffness EI. We can calculate the stresses and strains in the plate once we know the displacement.

For a more general load of the form

$q(x,y) = q_0 \sin\frac{m \pi x}{a}\sin\frac{n \pi y}{b}$

where $m$ and $n$ are integers, we get the solution

$\text{(1)} \qquad w(x,y) = \frac{q_0}{\pi^4 D}\,\left(\frac{m^2}{a^2}+\frac{n^2}{b^2}\right)^{-2}\,\sin\frac{m \pi x}{a}\sin\frac{n \pi y}{b} \,.$

Navier solution

Let us now consider a more general load $q(x,y)$. We can break this load up into a sum of Fourier components such that

$q(x,y) = \sum_{m=1}^{\infty} \sum_{n=1}^\infty a_{mn}\sin\frac{m \pi x}{a}\sin\frac{n \pi y}{b}$

where $a_{mn}$ is an amplitude. We can use the orthogonality of Fourier components,

$\int_0^a \sin\frac{k\pi x}{a}\sin\frac{\ell \pi x}{a}\text{d}x = \begin{cases} 0 & k \ne \ell \\ a/2 & k = \ell \end{cases}$

to find the amplitudes $a_{mn}$. Thus we have, by integrating over $y$,

$\int_0^b q(x,y)\sin\frac{\ell\pi y}{b}\,\text{d}y = \sum_{m=1}^{\infty} \sum_{n=1}^\infty a_{mn}\sin\frac{m \pi x}{a} \int_0^b \sin\frac{n \pi y}{b} \sin\frac{\ell\pi y}{b}\,\text{d}y = \frac{b}{2}\sum_{m=1}^{\infty} a_{m\ell}\sin\frac{m \pi x}{a} \,.$

If we repeat the process by integrating over $x$, we have

$\int_0^b \int_0^a q(x,y)\sin\frac{k\pi x}{a}\sin\frac{\ell\pi y}{b}\,\text{d}x\text{d}y = \frac{b}{2}\sum_{m=1}^{\infty} a_{m\ell} \int_0^a \sin\frac{m \pi x}{a} \sin\frac{k\pi x}{a}\,\text{d}x = \frac{ab}{4} a_{k\ell} \,.$

Therefore,

$a_{mn} = \frac{4}{ab} \int_0^b \int_0^a q(x,y)\sin\frac{m\pi x}{a}\sin\frac{n\pi y}{b}\,\text{d}x\text{d}y \,.$

Now that we know $a_{mn}$, we can just superpose solutions of the form given in equation (1) to get the displacement, i.e.,

$\text{(2)} \qquad w(x,y) = \sum_{m=1}^\infty \sum_{n=1}^\infty \frac{a_{mn}}{\pi^4 D}\,\left(\frac{m^2}{a^2}+\frac{n^2}{b^2}\right)^{-2}\,\sin\frac{m \pi x}{a}\sin\frac{n \pi y}{b} \,.$

Uniform load

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Displacement ($w$)

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Stress ($\sigma_{xx}$)

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Stress ($\sigma_{yy}$)

Displacement and stresses along $x=a/2$ for a rectangular plate with $a=20$ mm, $b=40$ mm, $H=2h=0.4$ mm, $E=70$ GPa, and $\nu=0.35$ under a load $q_0 = -10$ kPa. The red line represents the bottom of the plate, the green line the middle, and the blue line the top of the plate.

Consider the situation where a uniform load is applied on the plate, i.e., $q(x,y) = q_0$. Then

$a_{mn} = \frac{4q_0}{ab} \int_0^a \int_0^b \sin\frac{m\pi x}{a}\sin\frac{n\pi y}{b}\,\text{d}x\text{d}y \,.$

Now

$\int_0^a \sin\frac{m\pi x}{a}\,\text{d}x = \frac{a}{m\pi}(1 - \cos m\pi)$

and

$\int_0^b \sin\frac{n\pi y}{b}\,\text{d}y = \frac{b}{n\pi}(1 - \cos n\pi)\,.$

We can use these relations to get a simpler expression for $a_{mn}$:

$a_{mn} = \frac{4q_0}{mn\pi^2}(1 - \cos m\pi)(1 - \cos n\pi) \,.$

Notice that $\cos m\pi = \cos n\pi = 1$ [ so $(1 - \cos m\pi) = (1 - \cos n\pi) = 0$ ] when $m$ and $n$ are even. Also, when both $m$ and $n$ are odd we have $\cos m\pi = \cos n\pi = -1$. Therefore we can get an even simpler expression for $a_{mn}$ for these special cases :

$a_{mn} = \begin{cases} 0 & m~\text{or}~n~\text{even}, \\ \cfrac{16q_0}{mn\pi^2} & m~\text{and}~n~\text{odd}\,. \end{cases}$

Plugging this expression into equation (2) and keeping in mind that only odd terms contribute to the displacement, we have

$\begin{align} w(x,y) & = \sum_{m=1}^\infty \sum_{n=1}^\infty \frac{16 q_0}{(2m-1)(2n-1)\pi^6 D}\,\left[\frac{(2m-1)^2}{a^2}+\frac{(2n-1)^2}{b^2}\right]^{-2}\\ & \qquad \qquad \quad \times \sin\frac{(2m-1) \pi x}{a}\sin\frac{(2n-1) \pi y}{b} \,. \end{align}$

The corresponding moments are given by

$\begin{align} M_{xx} & = -D\left(\frac{\partial^2 w}{\partial x^2} + \nu \frac{\partial^2 w}{\partial y^2}\right) \\ & = \sum_{m=1}^\infty \sum_{n=1}^\infty\frac{16 q_0}{(2m-1)(2n-1)\pi^4}\, \left[\frac{(2m-1)^2}{a^2}+\nu\frac{(2n-1)^2}{b^2}\right] \,\times\\ & \qquad \qquad \left[\frac{(2m-1)^2}{a^2}+\frac{(2n-1)^2}{b^2}\right]^{-2} \sin\frac{(2m-1) \pi x}{a}\sin\frac{(2n-1) \pi y}{b} \\ M_{yy} & = -D\left(\frac{\partial^2 w}{\partial y^2} + \nu \frac{\partial^2 w}{\partial x^2}\right) \\ & = \sum_{m=1}^\infty \sum_{n=1}^\infty\frac{16 q_0}{(2m-1)(2n-1)\pi^4}\, \left[\frac{(2n-1)^2}{b^2}+\nu\frac{(2m-1)^2}{a^2}\right] \,\times\\ & \qquad \qquad \left[\frac{(2m-1)^2}{a^2}+\frac{(2n-1)^2}{b^2}\right]^{-2} \sin\frac{(2m-1) \pi x}{a}\sin\frac{(2n-1) \pi y}{b} \,. \end{align}$

The stresses in the plate are

$\sigma_{xx} = \frac{3z}{2h^3}\,M_{xx} = \frac{12 z}{H^3}\,M_{xx} \quad \text{and} \quad \sigma_{yy} = \frac{3z}{2h^3}\,M_{yy} = \frac{12 z}{H^3}\,M_{yy} \,.$

Levy solution

Another approach was proposed by Levy in 1899. In this case we start with an assumed form of the displacement and try to fit the parameters so that the governing equation and the boundary conditions are satisfied.

Let us assume that

$w(x,y) = \sum_{m=1}^\infty Y_m(y) \sin \frac{m\pi x}{a} \,.$

For a plate that is simply supported at $x=0$ and $x=a$, the boundary conditions are $w=0$ and $M_{xx} = 0$. The moment boundary condition is equivalent to $\partial^2 w/\partial x^2 = 0$ (verify). The goal is to find $Y_m(y)$ such that it satisfies the boundary conditions at $y = 0$ and $y = b$ and, of course, the governing equation $\nabla^2 \nabla^2 w = q/D$.

Moments along edges

Let us consider the case of pure moment loading. In that case $q = 0$ and $w(x,y)$ has to satisfy $\nabla^2 \nabla^2 w = 0$. Since we are working in rectangular Cartesian coordinates, the governing equation can be expanded as

$\frac{\partial^4 w}{\partial x^4} + 2 \frac{\partial^4 w}{\partial x^2\partial y^2} + \frac{\partial^4 w}{\partial y^4} = 0 \,.$

Plugging the expression for $w(x,y)$ in the governing equation gives us

$\sum_{m=1}^\infty \left[\left(\frac{m\pi}{a}\right)^4 Y_m \sin\frac{m\pi x}{a} - 2\left(\frac{m\pi}{a}\right)^2 \cfrac{d^2 Y_m}{d y^2} \sin\frac{m\pi x}{a} + \frac{d^4Y_m}{dy^4} \sin\frac{m\pi x}{a}\right] = 0$

or

$\frac{d^4Y_m}{dy^4} - 2 \frac{m^2\pi^2}{a^2} \cfrac{d^2Y_m}{dy^2} + \frac{m^4\pi^4}{a^4} Y_m = 0 \,.$

This is an ordinary differential equation which has the general solution

$Y_m = A_m \cosh\frac{m\pi y}{a} + B_m\frac{m\pi y}{a} \cosh\frac{m\pi y}{a} + C_m \sinh\frac{m\pi y}{a} + D_m\frac{m\pi y}{a} \sinh\frac{m\pi y}{a}$

where $A_m, B_m, C_m, D_m$ are constants that can be determined from the boundary conditions. Therefore the displacement solution has the form

$w(x,y) = \sum_{m=1}^\infty \left[ \left(A_m + B_m\frac{m\pi y}{a}\right) \cosh\frac{m\pi y}{a} + \left(C_m + D_m\frac{m\pi y}{a}\right) \sinh\frac{m\pi y}{a} \right] \sin \frac{m\pi x}{a} \,.$

Let us choose the coordinate system such that the boundaries of the plate are at $x = 0$ and $x = a$ (same as before) and at $y = \pm b/2$ (and not $y=0$ and $y=b$). Then the moment boundary conditions at the $y = \pm b/2$ boundaries are

$w = 0 \,, -D\frac{\partial^2 w}{\partial y^2}\Bigr|_{y=b/2} = f_1(x) \,, -D\frac{\partial^2 w}{\partial y^2}\Bigr|_{y=-b/2} = f_2(x)$

where $f_1(x), f_2(x)$ are known functions. The solution can be found by applying these boundary conditions. We can show that for the symmetrical case where

$M_{yy}\Bigr|_{y=-b/2} = M_{yy}\Bigr|_{y=b/2}$

and

$f_1(x) = f_2(x) = \sum_{m=1}^\infty E_m\sin\frac{m\pi x}{a}$

we have

$w(x,y) = \frac{a^2}{2\pi^2 D}\sum_{m=1}^\infty \frac{E_m}{m^2\cosh\alpha_m}\, \sin\frac{m\pi x}{a}\, \left(\alpha_m \tanh\alpha_m \cosh\frac{m\pi y}{a} - \frac{m\pi y}{a}\sinh\frac{m\pi y}{a}\right)$

where

$\alpha_m = \frac{m\pi b}{2a} \,.$

Similarly, for the antisymmetrical case where

$M_{yy}\Bigr|_{y=-b/2} = -M_{yy}\Bigr|_{y=b/2}$

we have

$w(x,y) = \frac{a^2}{2\pi^2 D}\sum_{m=1}^\infty \frac{E_m}{m^2\sinh\alpha_m}\, \sin\frac{m\pi x}{a}\, \left(\alpha_m \coth\alpha_m \sinh\frac{m\pi y}{a} - \frac{m\pi y}{a}\cosh\frac{m\pi y}{a}\right) \,.$

We can superpose the symmetric and antisymmetric solutions to get more general solutions.

Uniform and symmetric moment load

For the special case where the loading is symmetric and the moment is uniform, we have at $y=\pm b/2$,

$M_{yy} = f_1(x) = \frac{4M_0}{\pi}\sum_{m=1}^\infty \frac{1}{2m-1}\,\sin\frac{(2m-1)\pi x}{a} \,.$

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Displacement ($w$)

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Bending stress ($\sigma_{yy}$)

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Transverse shear stress ($\sigma_{yz}$)

Displacement and stresses for a rectangular plate under uniform bending moment along the edges $y=-b/2$ and $y=b/2$. The bending stress $\sigma_{yy}$ is along the bottom surface of the plate. The transverse shear stress $\sigma_{yz}$ is along the mid-surface of the plate.

The resulting displacement is

$\begin{align} & w(x,y) = \frac{2M_0 a^2}{\pi^3 D}\sum_{m=1}^\infty \frac{1}{(2m-1)^3\cosh\alpha_m}\sin\frac{(2m-1)\pi x}{a} \times\\ & ~~ \left[ \alpha_m\,\tanh\alpha_m\cosh\frac{(2m-1)\pi y}{a} -\frac{(2m-1)\pi y}{a} \sinh\frac{(2m-1)\pi y}{a}\right] \end{align}$

where

$\alpha_m = \frac{\pi (2m-1)b}{2a} \,.$

The bending moments and shear forces corresponding to the displacement $w$ are

$\begin{align} M_{xx} & = -D\left(\frac{\partial^2 w}{\partial x^2}+\nu\,\frac{\partial^2 w}{\partial y^2}\right) \\ & = \frac{2M_0(1-\nu)}{\pi}\sum_{m=1}^\infty\frac{1}{(2m-1)\cosh\alpha_m}\,\times \\ & ~ \sin\frac{(2m-1)\pi x}{a} \,\times \\ & ~ \left[ -\frac{(2m-1)\pi y}{a}\sinh\frac{(2m-1)\pi y}{a} + \right. \\ & \qquad \qquad \qquad \qquad \left. \left\{\frac{2\nu}{1-\nu} + \alpha_m\tanh\alpha_m\right\}\cosh\frac{(2m-1)\pi y}{a} \right] \\ M_{xy} & = (1-\nu)D\frac{\partial^2 w}{\partial x \partial y} \\ & = -\frac{2M_0(1-\nu)}{\pi}\sum_{m=1}^\infty\frac{1}{(2m-1) \cosh\alpha_m}\,\times \\ & ~ \cos\frac{(2m-1)\pi x}{a} \, \times \\ & ~ \left[\frac{(2m-1)\pi y}{a}\cosh\frac{(2m-1)\pi y}{a} + \right. \\ & \qquad \qquad \qquad \qquad \left. (1-\alpha_m\tanh\alpha_m)\sinh\frac{(2m-1)\pi y}{a}\right] \\ Q_{zx} & = \frac{\partial M_{xx}}{\partial x}-\frac{\partial M_{xy}}{\partial y} \\ & = \frac{4M_0}{a}\sum_{m=1}^\infty \frac{1}{\cosh\alpha_m}\,\times \\ & ~ \cos\frac{(2m-1)\pi x}{a}\cosh\frac{(2m-1)\pi y}{a}\,. \end{align}$

The stresses are

$\sigma_{xx} = \frac{12z}{h^3}\,M_{xx} \quad \text{and} \quad \sigma_{zx} = \frac{1}{\kappa h}\,Q_{zx}\left(1 - \frac{4z^2}{h^2}\right)\,.$

Cylindrical plate bending

Cylindrical bending occurs when a rectangular plate that has dimensions $a \times b \times h$, where $a \ll b$ and the thickness $h$ is small, is subjected to a uniform distributed load perpendicular to the plane of the plate. Such a plate takes the shape of the surface of a cylinder.

Simply supported plate with axially fixed ends

For a simply supported plate under cylindrical bending with edges that are free to rotate but have a fixed $x_1$. Cylindrical bending solutions can be found using the Navier and Levy techniques.

Bending of thick Mindlin plates

For thick plates, we have to consider the effect of through-the-thickness shears on the orientation of the normal to the mid-surface after deformation. Mindlin's theory provides one approach for find the deformation and stresses in such plates. Solutions to Mindlin's theory can be derived from the equivalent Kirchhoff-Love solutions using canonical relations.

Governing equations

The canonical governing equation for isotropic thick plates can be expressed as

$\begin{align} & \nabla^2 \left(\mathcal{M} - \frac{\mathcal{B}}{1+\nu}\,q\right) = -q \\ & \kappa G h\left(\nabla^2 w + \frac{\mathcal{M}}{D}\right) = -\left(1 - \cfrac{\mathcal{B} c^2}{1+\nu}\right)q \\ & \nabla^2 \left(\frac{\partial \varphi_1}{\partial x_2} - \frac{\partial \varphi_2}{\partial x_1}\right) = c^2\left(\frac{\partial \varphi_1}{\partial x_2} - \frac{\partial \varphi_2}{\partial x_1}\right) \end{align}$

where $q$ is the applied transverse load, $G$ is the shear modulus, $D = Eh^3/[12(1-\nu^2)]$ is the bending rigidity, $h$ is the plate thickness, $c^2 = 2\kappa G h/[D(1-\nu)]$, $\kappa$ is the shear correction factor, $E$ is the Young's modulus, $\nu$ is the Poisson's ratio, and

$\mathcal{M} = D\left[\mathcal{A}\left(\frac{\partial \varphi_1}{\partial x_1} + \frac{\partial \varphi_2}{\partial x_2}\right) - (1-\mathcal{A})\nabla^2 w\right] + \frac{2q}{1-\nu^2}\mathcal{B} \,.$

In Mindlin's theory, $w$ is the transverse displacement of the mid-surface of the plate and the quantities $\varphi_1$ and $\varphi_2$ are the rotations of the mid-surface normal about the $x_2$ and $x_1$-axes, respectively. The canonical parameters for this theory are $\mathcal{A} = 1$ and $\mathcal{B} = 0$. The shear correction factor $\kappa$ usually has the value $5/6$.

The solutions to the governing equations can be found if one knows the corresponding Kirchhoff-Love solutions by using the relations

$\begin{align} w & = w^K + \frac{\mathcal{M}^K}{\kappa G h}\left(1 - \frac{\mathcal{B} c^2}{2}\right) - \Phi + \Psi \\ \varphi_1 & = - \frac{\partial w^K}{\partial x_1} - \frac{1}{\kappa G h}\left(1 - \frac{1}{\mathcal{A}} - \frac{\mathcal{B} c^2}{2}\right)Q_1^K + \frac{\partial }{\partial x_1}\left(\frac{D}{\kappa G h \mathcal{A}}\nabla^2 \Phi + \Phi - \Psi\right) + \frac{1}{c^2}\frac{\partial \Omega}{\partial x_2} \\ \varphi_2 & = - \frac{\partial w^K}{\partial x_2} - \frac{1}{\kappa G h}\left(1 - \frac{1}{\mathcal{A}} - \frac{\mathcal{B} c^2}{2}\right)Q_2^K + \frac{\partial }{\partial x_2}\left(\frac{D}{\kappa G h \mathcal{A}}\nabla^2 \Phi + \Phi - \Psi\right) + \frac{1}{c^2}\frac{\partial \Omega}{\partial x_1} \end{align}$

where $w^K$ is the displacement predicted for a Kirchhoff-Love plate, $\Phi$ is a biharmonic function such that $\nabla^2 \nabla^2 \Phi = 0$, $\Psi$ is a function that satisfies the Laplace equation, $\nabla^2 \Psi = 0$, and

$\begin{align} \mathcal{M} & = \mathcal{M}^K + \frac{\mathcal{B}}{1+\nu}\,q + D \nabla^2 \Phi ~;~~ \mathcal{M}^K := -D\nabla^2 w^K \\ Q_1^K & = -D\frac{\partial }{\partial x_1}\left(\nabla^2 w^K\right) ~,~~ Q_2^K = -D\frac{\partial }{\partial x_2}\left(\nabla^2 w^K\right) \\ \Omega & = \frac{\partial \varphi_1}{\partial x_2} - \frac{\partial \varphi_2}{\partial x_1} ~,~~ \nabla^2 \Omega = c^2\Omega \,. \end{align}$

Simply supported rectangular plates

For simply supported plates, the Marcus moment sum vanishes, i.e.,

$\mathcal{M} = \frac{1}{1+\nu}(M_{11}+M_{22}) = D\left(\frac{\partial \varphi_1}{\partial x_1}+\frac{\partial \varphi_2}{\partial x_2}\right) = 0 \,.$

In that case the functions $\Phi$, $\Psi$, $\Omega$ vanish, and the Mindlin solution is related to the corresponding Kirchhoff solution by

$w = w^K + \frac{\mathcal{M}^K}{\kappa G h} \,.$

Bending of Reissner-Stein cantilever plates

Reissner-Stein theory for cantilever plates leads to the following coupled ordinary differential equations for a cantilever plate with concentrated end load $q_x(y)$ at $x=a$.

$\begin{align} & bD \frac{\mathrm{d}^4w_x}{\mathrm{d}x^4} = 0 \\ & \frac{b^3D}{12}\,\frac{\mathrm{d}^4\theta_x}{\mathrm{d}x^4} - 2bD(1-\nu)\cfrac{d^2 \theta_x}{d x^2} = 0 \end{align}$

and the boundary conditions at $x=a$ are

$\begin{align} & bD\cfrac{d^3 w_x}{d x^3} + q_{x1} = 0 \quad,\quad \frac{b^3D}{12}\cfrac{d^3 \theta_x}{d x^3} -2bD(1-\nu)\cfrac{d \theta_x}{d x} + q_{x2} = 0 \\ & bD\cfrac{d^2 w_x}{d x^2} = 0 \quad,\quad \frac{b^3D}{12}\cfrac{d^2 \theta_x}{d x^2} = 0 \,. \end{align}$

Solution of this system of two ODEs gives

$\begin{align} w_x(x) & = \frac{q_{x1}}{6bD}\,(3ax^2 -x^3) \\ \theta_x(x) & = \frac{q_{x2}}{2bD(1-\nu)}\left[x - \frac{1}{\nu_b}\, \left(\frac{\sinh(\nu_b a)}{\cosh[\nu_b (x-a)]} + \tanh[\nu_b(x-a)]\right)\right] \end{align}$

where $\nu_b = \sqrt{24(1-\nu)}/b$. The bending moments and shear forces corresponding to the displacement $w = w_x + y\theta_x$ are

$\begin{align} M_{xx} & = -D\left(\frac{\partial^2 w}{\partial x^2}+\nu\,\frac{\partial^2 w}{\partial y^2}\right) \\ & = q_{x1}\left(\frac{x-a}{b}\right) - \left[\frac{3yq_{x2}}{b^3\nu_b\cosh^3[\nu_b(x-a)]}\right] \times \\ & \quad \left[6\sinh(\nu_b a) - \sinh[\nu_b(2x-a)] + \sinh[\nu_b(2x-3a)] + 8\sinh[\nu_b(x-a)]\right] \\ M_{xy} & = (1-\nu)D\frac{\partial^2 w}{\partial x \partial y} \\ & = \frac{q_{x2}}{2b}\left[1 - \frac{2+\cosh[\nu_b(x-2a)] - \cosh[\nu_b x]}{2\cosh^2[\nu_b(x-a)]}\right] \\ Q_{zx} & = \frac{\partial M_{xx}}{\partial x}-\frac{\partial M_{xy}}{\partial y} \\ & = \frac{q_{x1}}{b} - \left(\frac{3yq_{x2}}{2b^3\cosh^4[\nu_b(x-a)]}\right)\times \left[32 + \cosh[\nu_b(3x-2a)] - \cosh[\nu_b(3x-4a)]\right. \\ & \qquad \left. - 16\cosh[2\nu_b(x-a)] + 23\cosh[\nu_b(x-2a)] - 23\cosh(\nu_b x)\right]\,. \end{align}$

The stresses are

$\sigma_{xx} = \frac{12z}{h^3}\,M_{xx} \quad \text{and} \quad \sigma_{zx} = \frac{1}{\kappa h}\,Q_{zx}\left(1 - \frac{4z^2}{h^2}\right)\,.$

If the applied load at the edge is constant, we recover the solutions for a beam under a concentrated end load. If the applied load is a linear function of $y$, then

$q_{x1} = \int_{-b/2}^{b/2}q_0\left(\frac{1}{2} - \frac{y}{b}\right)\,\text{d}y = \frac{bq_0}{2} ~;~~ q_{x2} = \int_{-b/2}^{b/2}yq_0\left(\frac{1}{2} - \frac{y}{b}\right)\,\text{d}y = -\frac{b^2q_0}{12} \,.$

See also

• Bending
• Infinitesimal strain theory
• Kirchhoff–Love plate theory
• Linear elasticity
• Mindlin–Reissner plate theory
• Plate theory
• Stress (mechanics)
• Stress resultants
• Structural acoustics
• Vibration of plates