Kirchhoff–Love plate theory

The Kirchhoff–Love theory of plates is a two-dimensional mathematical model that is used to determine the stresses and deformations in thin plates subjected to forces and moments. This theory is an extension of Euler-Bernoulli beam theory and was developed in 1888 by Love^[1] using assumptions proposed by Kirchhoff. The theory assumes that a mid-surface plane can be used to represent a three-dimensional plate in two-dimensional form.

The following kinematic assumptions that are made in this theory:^[2]

• straight lines normal to the mid-surface remain straight after deformation
• straight lines normal to the mid-surface remain normal to the mid-surface after deformation
• the thickness of the plate does not change during a deformation.

Let the position vector of a point in the undeformed plate be ${\displaystyle \mathbf {x} }$. Then

${\displaystyle \mathbf {x} =x_{1}{\boldsymbol {e}}_{1}+x_{2}{\boldsymbol {e}}_{2}+x_{3}{\boldsymbol {e}}_{3}\equiv x_{i}{\boldsymbol {e}}_{i}\,.}$

The vectors ${\displaystyle {\boldsymbol {e}}_{i}}$ form a Cartesian basis with origin on the mid-surface of the plate, ${\displaystyle x_{1}}$ and ${\displaystyle x_{2}}$ are the Cartesian coordinates on the mid-surface of the undeformed plate, and ${\displaystyle x_{3}}$ is the coordinate for the thickness direction.

Let the displacement of a point in the plate be ${\displaystyle \mathbf {u} (\mathbf {x} )}$. Then

${\displaystyle \mathbf {u} =u_{1}{\boldsymbol {e}}_{1}+u_{2}{\boldsymbol {e}}_{2}+u_{3}{\boldsymbol {e}}_{3}\equiv u_{i}{\boldsymbol {e}}_{i}}$

This displacement can be decomposed into a vector sum of the mid-surface displacement ${\displaystyle u_{\alpha }^{0}}$ and an out-of-plane displacement ${\displaystyle w^{0}}$ in the ${\displaystyle x_{3}}$ direction. We can write the in-plane displacement of the mid-surface as

${\displaystyle \mathbf {u} ^{0}=u_{1}^{0}{\boldsymbol {e}}_{1}+u_{2}^{0}{\boldsymbol {e}}_{2}\equiv u_{\alpha }^{0}{\boldsymbol {e}}_{\alpha }}$

Note that the index ${\displaystyle \alpha }$ takes the values 1 and 2 but not 3.

Then the Kirchhoff hypothesis implies that

If ${\displaystyle \varphi _{\alpha }}$ are the angles of rotation of the normal to the mid-surface, then in the Kirchhoff-Love theory

${\displaystyle \varphi _{\alpha }=w_{,\alpha }^{0}}$

Note that we can think of the expression for ${\displaystyle u_{\alpha }}$ as the first order Taylor series expansion of the displacement around the mid-surface.

The original theory developed by Love was valid for infinitesimal strains and rotations. The theory was extended by von Kármán to situations where moderate rotations could be expected.

For the situation where the strains in the plate are infinitesimal and the rotations of the mid-surface normals are less than 10° the strain-displacement relations are

${\displaystyle {\begin{aligned}\varepsilon _{\alpha \beta }&={\frac {1}{2}}\left({\frac {\partial u_{\alpha }}{\partial x_{\beta }}}+{\frac {\partial u_{\beta }}{\partial x_{\alpha }}}\right)\equiv {\frac {1}{2}}(u_{\alpha ,\beta }+u_{\beta ,\alpha })\\\varepsilon _{\alpha 3}&={\frac {1}{2}}\left({\frac {\partial u_{\alpha }}{\partial x_{3}}}+{\frac {\partial u_{3}}{\partial x_{\alpha }}}\right)\equiv {\frac {1}{2}}(u_{\alpha ,3}+u_{3,\alpha })\\\varepsilon _{33}&={\frac {\partial u_{3}}{\partial x_{3}}}\equiv u_{3,3}\end{aligned}}}$

where ${\displaystyle \beta =1,2}$ as ${\displaystyle \alpha }$.

Using the kinematic assumptions we have

Therefore, the only non-zero strains are in the in-plane directions.

The equilibrium equations for the plate can be derived from the principle of virtual work. For a thin plate under a quasistatic transverse load ${\displaystyle q(x)}$ pointing towards positive ${\displaystyle x_{3}}$ direction, these equations are

${\displaystyle {\begin{aligned}&{\cfrac {\partial N_{11}}{\partial x_{1}}}+{\cfrac {\partial N_{21}}{\partial x_{2}}}=0\\&{\cfrac {\partial N_{12}}{\partial x_{1}}}+{\cfrac {\partial N_{22}}{\partial x_{2}}}=0\\&{\cfrac {\partial ^{2}M_{11}}{\partial x_{1}^{2}}}+2{\cfrac {\partial ^{2}M_{12}}{\partial x_{1}\partial x_{2}}}+{\cfrac {\partial ^{2}M_{22}}{\partial x_{2}^{2}}}=-q\end{aligned}}}$

where the thickness of the plate is ${\displaystyle 2h}$. In index notation,

where ${\displaystyle \sigma _{\alpha \beta }}$ are the stresses.

Derivation of equilibrium equations for small rotations

For the situation where the strains and rotations of the plate are small the virtual internal energy is given by ${\displaystyle {\begin{aligned}\delta U&=\int _{\Omega ^{0}}\int _{-h}^{h}{\boldsymbol {\sigma }}:\delta {\boldsymbol {\epsilon }}~dx_{3}~d\Omega =\int _{\Omega ^{0}}\int _{-h}^{h}\sigma _{\alpha \beta }~\delta \varepsilon _{\alpha \beta }~dx_{3}~d\Omega \\&=\int _{\Omega ^{0}}\int _{-h}^{h}\left[{\frac {1}{2}}~\sigma _{\alpha \beta }~(\delta u_{\alpha ,\beta }^{0}+\delta u_{\beta ,\alpha }^{0})-x_{3}~\sigma _{\alpha \beta }~\delta w_{,\alpha \beta }^{0}\right]~dx_{3}~d\Omega \\&=\int _{\Omega ^{0}}\left[{\frac {1}{2}}~N_{\alpha \beta }~(\delta u_{\alpha ,\beta }^{0}+\delta u_{\beta ,\alpha }^{0})-M_{\alpha \beta }~\delta w_{,\alpha \beta }^{0}\right]~d\Omega \end{aligned}}}$ where the thickness of the plate is ${\displaystyle 2h}$ and the stress resultants and stress moment resultants are defined as ${\displaystyle N_{\alpha \beta }:=\int _{-h}^{h}\sigma _{\alpha \beta }~dx_{3}~;~~M_{\alpha \beta }:=\int _{-h}^{h}x_{3}~\sigma _{\alpha \beta }~dx_{3}}$ Integration by parts leads to ${\displaystyle {\begin{aligned}\delta U&=\int _{\Omega ^{0}}\left[-{\frac {1}{2}}~(N_{\alpha \beta ,\beta }~\delta u_{\alpha }^{0}+N_{\alpha \beta ,\alpha }~\delta u_{\beta }^{0})+M_{\alpha \beta ,\beta }~\delta w_{,\alpha }^{0}\right]~d\Omega \\&+\int _{\Gamma ^{0}}\left[{\frac {1}{2}}~(n_{\beta }~N_{\alpha \beta }~\delta u_{\alpha }^{0}+n_{\alpha }~N_{\alpha \beta }~\delta u_{\beta }^{0})-n_{\beta }~M_{\alpha \beta }~\delta w_{,\alpha }^{0}\right]~d\Gamma \end{aligned}}}$ The symmetry of the stress tensor implies that ${\displaystyle N_{\alpha \beta }=N_{\beta \alpha }}$. Hence, ${\displaystyle \delta U=\int _{\Omega ^{0}}\left[-N_{\alpha \beta ,\alpha }~\delta u_{\beta }^{0}+M_{\alpha \beta ,\beta }~\delta w_{,\alpha }^{0}\right]~d\Omega +\int _{\Gamma ^{0}}\left[n_{\alpha }~N_{\alpha \beta }~\delta u_{\beta }^{0}-n_{\beta }~M_{\alpha \beta }~\delta w_{,\alpha }^{0}\right]~d\Gamma }$ Another integration by parts gives ${\displaystyle \delta U=\int _{\Omega ^{0}}\left[-N_{\alpha \beta ,\alpha }~\delta u_{\beta }^{0}-M_{\alpha \beta ,\beta \alpha }~\delta w^{0}\right]~d\Omega +\int _{\Gamma ^{0}}\left[n_{\alpha }~N_{\alpha \beta }~\delta u_{\beta }^{0}+n_{\alpha }~M_{\alpha \beta ,\beta }~\delta w^{0}-n_{\beta }~M_{\alpha \beta }~\delta w_{,\alpha }^{0}\right]~d\Gamma }$ For the case where there are no prescribed external forces, the principle of virtual work implies that ${\displaystyle \delta U=0}$. The equilibrium equations for the plate are then given by ${\displaystyle {\begin{aligned}N_{\alpha \beta ,\alpha }&=0\\M_{\alpha \beta ,\alpha \beta }&=0\end{aligned}}}$ If the plate is loaded by an external distributed load ${\displaystyle q(x)}$ that is normal to the mid-surface and directed in the positive ${\displaystyle x_{3}}$ direction, the external virtual work due to the load is ${\displaystyle \delta V_{\mathrm {ext} }=\int _{\Omega ^{0}}q~\delta w^{0}~d\Omega }$ The principle of virtual work ${\displaystyle \delta U=\delta V_{\mathrm {ext} }}$ then leads to the equilibrium equations ${\displaystyle {\begin{aligned}N_{\alpha \beta ,\alpha }&=0\\M_{\alpha \beta ,\alpha \beta }+q&=0\end{aligned}}}$

The boundary conditions that are needed to solve the equilibrium equations of plate theory can be obtained from the boundary terms in the principle of virtual work. In the absence of external forces on the boundary, the boundary conditions are

${\displaystyle {\begin{aligned}n_{\alpha }~N_{\alpha \beta }&\quad \mathrm {or} \quad u_{\beta }^{0}\\n_{\alpha }~M_{\alpha \beta ,\beta }&\quad \mathrm {or} \quad w^{0}\\n_{\beta }~M_{\alpha \beta }&\quad \mathrm {or} \quad w_{,\alpha }^{0}\end{aligned}}}$

Note that the quantity ${\displaystyle n_{\alpha }~M_{\alpha \beta ,\beta }}$ is an effective shear force.

The stress-strain relations for a linear elastic Kirchhoff plate are given by

${\displaystyle {\begin{aligned}\sigma _{\alpha \beta }&=C_{\alpha \beta \gamma \theta }~\varepsilon _{\gamma \theta }\\\sigma _{\alpha 3}&=C_{\alpha 3\gamma \theta }~\varepsilon _{\gamma \theta }\\\sigma _{33}&=C_{33\gamma \theta }~\varepsilon _{\gamma \theta }\end{aligned}}}$

Since ${\displaystyle \sigma _{\alpha 3}}$ and ${\displaystyle \sigma _{33}}$ do not appear in the equilibrium equations it is implicitly assumed that these quantities do not have any effect on the momentum balance and are neglected. The remaining stress-strain relations, in matrix form, can be written as

${\displaystyle {\begin{bmatrix}\sigma _{11}\\\sigma _{22}\\\sigma _{12}\end{bmatrix}}={\begin{bmatrix}C_{11}&C_{12}&C_{13}\\C_{12}&C_{22}&C_{23}\\C_{13}&C_{23}&C_{33}\end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}}$

Then,

${\displaystyle {\begin{bmatrix}N_{11}\\N_{22}\\N_{12}\end{bmatrix}}=\int _{-h}^{h}{\begin{bmatrix}C_{11}&C_{12}&C_{13}\\C_{12}&C_{22}&C_{23}\\C_{13}&C_{23}&C_{33}\end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}dx_{3}=\left\{\int _{-h}^{h}{\begin{bmatrix}C_{11}&C_{12}&C_{13}\\C_{12}&C_{22}&C_{23}\\C_{13}&C_{23}&C_{33}\end{bmatrix}}~dx_{3}\right\}{\begin{bmatrix}u_{1,1}^{0}\\u_{2,2}^{0}\\{\frac {1}{2}}~(u_{1,2}^{0}+u_{2,1}^{0})\end{bmatrix}}}$

and

${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=\int _{-h}^{h}x_{3}~{\begin{bmatrix}C_{11}&C_{12}&C_{13}\\C_{12}&C_{22}&C_{23}\\C_{13}&C_{23}&C_{33}\end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}dx_{3}=-\left\{\int _{-h}^{h}x_{3}^{2}~{\begin{bmatrix}C_{11}&C_{12}&C_{13}\\C_{12}&C_{22}&C_{23}\\C_{13}&C_{23}&C_{33}\end{bmatrix}}~dx_{3}\right\}{\begin{bmatrix}w_{,11}^{0}\\w_{,22}^{0}\\w_{,12}^{0}\end{bmatrix}}}$

The extensional stiffnesses are the quantities

${\displaystyle A_{\alpha \beta }:=\int _{-h}^{h}C_{\alpha \beta }~dx_{3}}$

The bending stiffnesses (also called flexural rigidity) are the quantities

${\displaystyle D_{\alpha \beta }:=\int _{-h}^{h}x_{3}^{2}~C_{\alpha \beta }~dx_{3}}$

The Kirchhoff-Love constitutive assumptions lead to zero shear forces. As a result, the equilibrium equations for the plate have to be used to determine the shear forces in thin Kirchhoff-Love plates. For isotropic plates, these equations lead to

${\displaystyle Q_{\alpha }=-D{\frac {\partial }{\partial x_{\alpha }}}(\nabla ^{2}w^{0})\,.}$

Alternatively, these shear forces can be expressed as

${\displaystyle Q_{\alpha }={\mathcal {M}}_{,\alpha }}$

where

${\displaystyle {\mathcal {M}}:=-D\nabla ^{2}w^{0}\,.}$

If the rotations of the normals to the mid-surface are in the range of 10${\displaystyle ^{\circ }}$ to 15${\displaystyle ^{\circ }}$, the strain-displacement relations can be approximated as

${\displaystyle {\begin{aligned}\varepsilon _{\alpha \beta }&={\tfrac {1}{2}}(u_{\alpha ,\beta }+u_{\beta ,\alpha }+u_{3,\alpha }~u_{3,\beta })\\\varepsilon _{\alpha 3}&={\tfrac {1}{2}}(u_{\alpha ,3}+u_{3,\alpha })\\\varepsilon _{33}&=u_{3,3}\end{aligned}}}$

Then the kinematic assumptions of Kirchhoff-Love theory lead to the classical plate theory with von Kármán strains

${\displaystyle {\begin{aligned}\varepsilon _{\alpha \beta }&={\frac {1}{2}}(u_{\alpha ,\beta }^{0}+u_{\beta ,\alpha }^{0}+w_{,\alpha }^{0}~w_{,\beta }^{0})-x_{3}~w_{,\alpha \beta }^{0}\\\varepsilon _{\alpha 3}&=-w_{,\alpha }^{0}+w_{,\alpha }^{0}=0\\\varepsilon _{33}&=0\end{aligned}}}$

This theory is nonlinear because of the quadratic terms in the strain-displacement relations.

If the strain-displacement relations take the von Karman form, the equilibrium equations can be expressed as

${\displaystyle {\begin{aligned}N_{\alpha \beta ,\alpha }&=0\\M_{\alpha \beta ,\alpha \beta }+[N_{\alpha \beta }~w_{,\beta }^{0}]_{,\alpha }+q&=0\end{aligned}}}$

For an isotropic and homogeneous plate, the stress-strain relations are

${\displaystyle {\begin{bmatrix}\sigma _{11}\\\sigma _{22}\\\sigma _{12}\end{bmatrix}}={\cfrac {E}{1-\nu ^{2}}}{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}\,.}$

where ${\displaystyle \nu }$ is Poisson's Ratio and ${\displaystyle E}$ is Young's Modulus. The moments corresponding to these stresses are

${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&{1-\nu }\end{bmatrix}}{\begin{bmatrix}w_{,11}^{0}\\w_{,22}^{0}\\w_{,12}^{0}\end{bmatrix}}}$

In expanded form,

${\displaystyle {\begin{aligned}M_{11}&=-D\left({\frac {\partial ^{2}w^{0}}{\partial x_{1}^{2}}}+\nu {\frac {\partial ^{2}w^{0}}{\partial x_{2}^{2}}}\right)\\M_{22}&=-D\left({\frac {\partial ^{2}w^{0}}{\partial x_{2}^{2}}}+\nu {\frac {\partial ^{2}w^{0}}{\partial x_{1}^{2}}}\right)\\M_{12}&=-D(1-\nu ){\frac {\partial ^{2}w^{0}}{\partial x_{1}\partial x_{2}}}\end{aligned}}}$

where ${\displaystyle D=2h^{3}E/[3(1-\nu ^{2})]=H^{3}E/[12(1-\nu ^{2})]}$ for plates of thickness ${\displaystyle H=2h}$. Using the stress-strain relations for the plates, we can show that the stresses and moments are related by

${\displaystyle \sigma _{11}={\frac {3x_{3}}{2h^{3}}}\,M_{11}={\frac {12x_{3}}{H^{3}}}\,M_{11}\quad {\text{and}}\quad \sigma _{22}={\frac {3x_{3}}{2h^{3}}}\,M_{22}={\frac {12x_{3}}{H^{3}}}\,M_{22}\,.}$

At the top of the plate where ${\displaystyle x_{3}=h=H/2}$, the stresses are

${\displaystyle \sigma _{11}={\frac {3}{2h^{2}}}\,M_{11}={\frac {6}{H^{2}}}\,M_{11}\quad {\text{and}}\quad \sigma _{22}={\frac {3}{2h^{2}}}\,M_{22}={\frac {6}{H^{2}}}\,M_{22}\,.}$

For an isotropic and homogeneous plate under pure bending, the governing equations reduce to

${\displaystyle {\frac {\partial ^{4}w^{0}}{\partial x_{1}^{4}}}+2{\frac {\partial ^{4}w^{0}}{\partial x_{1}^{2}\partial x_{2}^{2}}}+{\frac {\partial ^{4}w^{0}}{\partial x_{2}^{4}}}=0\,.}$

Here we have assumed that the in-plane displacements do not vary with ${\displaystyle x_{1}}$ and ${\displaystyle x_{2}}$. In index notation,

${\displaystyle w_{,1111}^{0}+2~w_{,1212}^{0}+w_{,2222}^{0}=0}$

and in direct notation

which is known as the biharmonic equation. The bending moments are given by

${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}w_{,11}^{0}\\w_{,22}^{0}\\w_{,12}^{0}\end{bmatrix}}}$

Derivation of equilibrium equations for pure bending

For an isotropic, homogeneous plate under pure bending the governing equations are ${\displaystyle {\begin{aligned}N_{\alpha \beta ,\alpha }&=0\implies N_{11,1}+N_{21,2}=0~,~~N_{12,1}+N_{22,2}=0\\M_{\alpha \beta ,\alpha \beta }&=0\implies M_{11,11}+2M_{12,12}+M_{22,22}=0\end{aligned}}}$ and the stress-strain relations are ${\displaystyle {\begin{bmatrix}\sigma _{11}\\\sigma _{22}\\\sigma _{12}\end{bmatrix}}={\cfrac {E}{1-\nu ^{2}}}{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}}$ Then, ${\displaystyle {\begin{bmatrix}N_{11}\\N_{22}\\N_{12}\end{bmatrix}}={\cfrac {2hE}{(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}u_{1,1}^{0}\\u_{2,2}^{0}\\{\frac {1}{2}}~(u_{1,2}^{0}+u_{2,1}^{0})\end{bmatrix}}}$ and ${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}w_{,11}^{0}\\w_{,22}^{0}\\w_{,12}^{0}\end{bmatrix}}}$ Differentiation gives ${\displaystyle {\begin{aligned}N_{11,1}&={\cfrac {2hE}{(1-\nu ^{2})}}\left(u_{1,11}^{0}+\nu ~u_{2,21}^{0}\right)~;~~N_{22,2}={\cfrac {2hE}{(1-\nu ^{2})}}\left(\nu ~u_{1,12}^{0}+u_{2,22}^{0}\right)\\N_{12,1}&={\cfrac {hE(1-\nu )}{(1-\nu ^{2})}}\left(u_{1,21}^{0}+u_{2,11}^{0}\right)~;~~N_{12,2}={\cfrac {hE(1-\nu )}{(1-\nu ^{2})}}\left(u_{1,22}^{0}+u_{2,12}^{0}\right)\end{aligned}}}$ and ${\displaystyle {\begin{aligned}M_{11,11}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\left(w_{,1111}^{0}+\nu ~w_{,2211}^{0}\right)\\M_{22,22}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\left(\nu ~w_{,1122}^{0}+w_{,2222}^{0}\right)\\M_{12,12}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}(1-\nu )~w_{,1212}^{0}\end{aligned}}}$ Plugging into the governing equations leads to ${\displaystyle {\begin{aligned}&u_{1,11}^{0}+\nu ~u_{2,21}^{0}+{\tfrac {1}{2}}(1-\nu )\left(u_{1,22}^{0}+u_{2,12}^{0}\right)=0\\&\nu ~u_{1,12}^{0}+u_{2,22}^{0}+{\tfrac {1}{2}}(1-\nu )\left(u_{1,21}^{0}+u_{2,11}^{0}\right)=0\\&w_{,1111}^{0}+\nu ~w_{,2211}^{0}+2(1-\nu )~w_{,1212}^{0}+\nu ~w_{,1122}^{0}+w_{,2222}^{0}=0\end{aligned}}}$ Since the order of differentiation is irrelevant we have ${\displaystyle u_{1,12}^{0}=u_{1,21}^{0}}$, ${\displaystyle u_{2,21}^{0}=u_{2,12}^{0}}$, and ${\displaystyle w_{,2211}^{0}=w_{,1212}^{0}=w_{,1122}^{0}}$. Hence ${\displaystyle {\begin{aligned}&u_{1,11}^{0}+{\tfrac {1}{2}}(1-\nu )~u_{1,22}^{0}+{\tfrac {1}{2}}(1+\nu )~u_{2,12}^{0}=0\\&u_{2,22}^{0}+{\tfrac {1}{2}}(1-\nu )~u_{2,11}^{0}+{\tfrac {1}{2}}(1+\nu )~u_{1,12}^{0}=0\\&w_{,1111}^{0}+2~w_{,1212}^{0}+w_{,2222}^{0}=0\end{aligned}}}$ In direct tensor notation, the governing equation of the plate is ${\displaystyle \nabla ^{2}\nabla ^{2}w=0}$ where we have assumed that the displacements ${\displaystyle u_{1}^{0},u_{2}^{0}}$ are constant.

If a distributed transverse load ${\displaystyle q(x)}$ pointing along positive ${\displaystyle x_{3}}$ direction is applied to the plate, the governing equation is ${\displaystyle M_{\alpha \beta ,\alpha \beta }=-q}$. Following the procedure shown in the previous section we get^[3]

In rectangular Cartesian coordinates, the governing equation is

${\displaystyle w_{,1111}^{0}+2\,w_{,1212}^{0}+w_{,2222}^{0}={\cfrac {q}{D}}}$

and in cylindrical coordinates it takes the form

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

Solutions of this equation for various geometries and boundary conditions can be found in the article on bending of plates.

Derivation of equilibrium equations for transverse loading

For a transversely loaded plate without axial deformations, the governing equation has the form ${\displaystyle M_{\alpha \beta ,\alpha \beta }=q\implies M_{11,11}+2M_{12,12}+M_{22,22}=q}$ where ${\displaystyle q}$ is a distributed transverse load (per unit area). Substitution of the expressions for the derivatives of ${\displaystyle M_{\alpha \beta }}$ into the governing equation gives ${\displaystyle -{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\left[w_{,1111}^{0}+2\,w_{,1212}^{0}+w_{,2222}^{0}\right]=q\,.}$ Noting that the bending stiffness is the quantity ${\displaystyle D:={\cfrac {2h^{3}E}{3(1-\nu ^{2})}}}$ we can write the governing equation in the form ${\displaystyle \nabla ^{2}\nabla ^{2}w=-{\frac {q}{D}}\,.}$ In cylindrical coordinates ${\displaystyle (r,\theta ,z)}$, ${\displaystyle \nabla ^{2}w\equiv {\frac {1}{r}}{\frac {\partial }{\partial r}}\left(r{\frac {\partial w}{\partial r}}\right)+{\frac {1}{r^{2}}}{\frac {\partial ^{2}w}{\partial \theta ^{2}}}+{\frac {\partial ^{2}w}{\partial z^{2}}}\,.}$ For symmetrically loaded circular plates, ${\displaystyle w=w(r)}$, and we have ${\displaystyle \nabla ^{2}w\equiv {\frac {1}{r}}{\cfrac {d}{dr}}\left(r{\cfrac {dw}{dr}}\right)\,.}$

Under certain loading conditions a flat plate can be bent into the shape of the surface of a cylinder. This type of bending is called cylindrical bending and represents the special situation where ${\displaystyle u_{1}=u_{1}(x_{1}),u_{2}=0,w=w(x_{1})}$. In that case

${\displaystyle {\begin{bmatrix}N_{11}\\N_{22}\\N_{12}\end{bmatrix}}={\cfrac {2hE}{(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}u_{1,1}^{0}\\0\\0\end{bmatrix}}}$

and

${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}w_{,11}^{0}\\0\\0\end{bmatrix}}}$

and the governing equations become^[3]

${\displaystyle {\begin{aligned}N_{11}&=A~{\cfrac {\mathrm {d} u}{\mathrm {d} x_{1}}}\quad \implies \quad {\cfrac {\mathrm {d} ^{2}u}{\mathrm {d} x_{1}^{2}}}=0\\M_{11}&=-D~{\cfrac {\mathrm {d} ^{2}w}{\mathrm {d} x_{1}^{2}}}\quad \implies \quad {\cfrac {\mathrm {d} ^{4}w}{\mathrm {d} x_{1}^{4}}}={\cfrac {q}{D}}\\\end{aligned}}}$

The dynamic theory of thin plates determines the propagation of waves in the plates, and the study of standing waves and vibration modes.

The governing equations for the dynamics of a Kirchhoff-Love plate are

where, for a plate with density ${\displaystyle \rho =\rho (x)}$,

${\displaystyle J_{1}:=\int _{-h}^{h}\rho ~dx_{3}=2~\rho ~h~;~~J_{3}:=\int _{-h}^{h}x_{3}^{2}~\rho ~dx_{3}={\frac {2}{3}}~\rho ~h^{3}}$

and

${\displaystyle {\dot {u}}_{i}={\frac {\partial u_{i}}{\partial t}}~;~~{\ddot {u}}_{i}={\frac {\partial ^{2}u_{i}}{\partial t^{2}}}~;~~u_{i,\alpha }={\frac {\partial u_{i}}{\partial x_{\alpha }}}~;~~u_{i,\alpha \beta }={\frac {\partial ^{2}u_{i}}{\partial x_{\alpha }\partial x_{\beta }}}}$

Derivation of equations governing the dynamics of Kirchhoff-Love plates

The total kinetic energy (more precisely, action of kinetic energy) of the plate is given by ${\displaystyle K=\int _{0}^{T}\int _{\Omega ^{0}}\int _{-h}^{h}{\cfrac {\rho }{2}}\left[\left({\frac {\partial u_{1}}{\partial t}}\right)^{2}+\left({\frac {\partial u_{2}}{\partial t}}\right)^{2}+\left({\frac {\partial u_{3}}{\partial t}}\right)^{2}\right]~\mathrm {d} x_{3}~\mathrm {d} A~\mathrm {d} t}$ Therefore, the variation in kinetic energy is ${\displaystyle \delta K=\int _{0}^{T}\int _{\Omega ^{0}}\int _{-h}^{h}{\cfrac {\rho }{2}}\left[2\left({\frac {\partial u_{1}}{\partial t}}\right)\left({\frac {\partial \delta u_{1}}{\partial t}}\right)+2\left({\frac {\partial u_{2}}{\partial t}}\right)\left({\frac {\partial \delta u_{2}}{\partial t}}\right)+2\left({\frac {\partial u_{3}}{\partial t}}\right)\left({\frac {\partial \delta u_{3}}{\partial t}}\right)\right]~\mathrm {d} x_{3}~\mathrm {d} A~\mathrm {d} t}$ We use the following notation in the rest of this section. ${\displaystyle {\dot {u}}_{i}={\frac {\partial u_{i}}{\partial t}}~;~~{\ddot {u}}_{i}={\frac {\partial ^{2}u_{i}}{\partial t^{2}}}~;~~u_{i,\alpha }={\frac {\partial u_{i}}{\partial x_{\alpha }}}~;~~u_{i,\alpha \beta }={\frac {\partial ^{2}u_{i}}{\partial x_{\alpha }\partial x_{\beta }}}}$ Then ${\displaystyle \delta K=\int _{0}^{T}\int _{\Omega ^{0}}\int _{-h}^{h}\rho \left({\dot {u}}_{\alpha }~\delta {\dot {u}}_{\alpha }+{\dot {u}}_{3}~\delta {\dot {u}}_{3}\right)~\mathrm {d} x_{3}~\mathrm {d} A~\mathrm {d} t}$ For a Kirchhof-Love plate ${\displaystyle u_{\alpha }=u_{\alpha }^{0}-x_{3}~w_{,\alpha }^{0}~;~~u_{3}=w^{0}}$ Hence, ${\displaystyle {\begin{aligned}\delta K&=\int _{0}^{T}\int _{\Omega ^{0}}\int _{-h}^{h}\rho \left[\left({\dot {u}}_{\alpha }^{0}-x_{3}~{\dot {w}}_{,\alpha }^{0}\right)~\left(\delta {\dot {u}}_{\alpha }^{0}-x_{3}~\delta {\dot {w}}_{,\alpha }^{0}\right)+{\dot {w}}^{0}~\delta {\dot {w}}^{0}\right]~\mathrm {d} x_{3}~\mathrm {d} A~\mathrm {d} t\\&=\int _{0}^{T}\int _{\Omega ^{0}}\int _{-h}^{h}\rho \left({\dot {u}}_{\alpha }^{0}~\delta {\dot {u}}_{\alpha }^{0}-x_{3}~{\dot {w}}_{,\alpha }^{0}~\delta {\dot {u}}_{\alpha }^{0}-x_{3}~{\dot {u}}_{\alpha }^{0}~\delta {\dot {w}}_{,\alpha }^{0}+x_{3}^{2}~{\dot {w}}_{,\alpha }^{0}~\delta {\dot {w}}_{,\alpha }^{0}+{\dot {w}}^{0}~\delta {\dot {w}}^{0}\right)~\mathrm {d} x_{3}~\mathrm {d} A~\mathrm {d} t\end{aligned}}}$ Define, for constant ${\displaystyle \rho }$ through the thickness of the plate, ${\displaystyle J_{1}:=\int _{-h}^{h}\rho ~dx_{3}=2~\rho ~h~;~~J_{2}:=\int _{-h}^{h}x_{3}~\rho ~dx_{3}=0~;~~J_{3}:=\int _{-h}^{h}x_{3}^{2}~\rho ~dx_{3}={\frac {2}{3}}~\rho ~h^{3}}$ Then ${\displaystyle \delta K=\int _{0}^{T}\int _{\Omega ^{0}}\left[J_{1}\left({\dot {u}}_{\alpha }^{0}~\delta {\dot {u}}_{\alpha }^{0}+{\dot {w}}^{0}~\delta {\dot {w}}^{0}\right)+J_{3}~{\dot {w}}_{,\alpha }^{0}~\delta {\dot {w}}_{,\alpha }^{0}\right]~\mathrm {d} A~\mathrm {d} t}$ Integrating by parts, ${\displaystyle \delta K=\int _{\Omega ^{0}}\left[\int _{0}^{T}\left\{-J_{1}\left({\ddot {u}}_{\alpha }^{0}~\delta u_{\alpha }^{0}+{\ddot {w}}^{0}~\delta w^{0}\right)-J_{3}~{\ddot {w}}_{,\alpha }^{0}~\delta w_{,\alpha }^{0}\right\}~\mathrm {d} t+\left|J_{1}\left({\dot {u}}_{\alpha }^{0}~\delta u_{\alpha }^{0}+{\dot {w}}^{0}~\delta w^{0}\right)+J_{3}~{\dot {w}}_{,\alpha }^{0}~\delta w_{,\alpha }^{0}\right|_{0}^{T}\right]~\mathrm {d} A}$ The variations ${\displaystyle \delta u_{\alpha }^{0}}$ and ${\displaystyle \delta w^{0}}$ are zero at ${\displaystyle t=0}$ and ${\displaystyle t=T}$. Hence, after switching the sequence of integration, we have ${\displaystyle \delta K=-\int _{0}^{T}\left\{\int _{\Omega ^{0}}\left[J_{1}\left({\ddot {u}}_{\alpha }^{0}~\delta u_{\alpha }^{0}+{\ddot {w}}^{0}~\delta w^{0}\right)+J_{3}~{\ddot {w}}_{,\alpha }^{0}~\delta w_{,\alpha }^{0}\right]~\mathrm {d} A\right\}~\mathrm {d} t+\left|\int _{\Omega ^{0}}J_{3}~{\dot {w}}_{,\alpha }^{0}~\delta w_{,\alpha }^{0}\mathrm {d} A\right|_{0}^{T}}$ Integration by parts over the mid-surface gives ${\displaystyle {\begin{aligned}\delta K&=-\int _{0}^{T}\left\{\int _{\Omega ^{0}}\left[J_{1}\left({\ddot {u}}_{\alpha }^{0}~\delta u_{\alpha }^{0}+{\ddot {w}}^{0}~\delta w^{0}\right)-J_{3}~{\ddot {w}}_{,\alpha \alpha }^{0}~\delta w^{0}\right]~\mathrm {d} A+\int _{\Gamma ^{0}}J_{3}~n_{\alpha }~{\ddot {w}}_{,\alpha }^{0}~\delta w^{0}~\mathrm {d} s\right\}~\mathrm {d} t\\&\qquad -\left|\int _{\Omega ^{0}}J_{3}~{\dot {w}}_{,\alpha \alpha }^{0}~\delta w^{0}~\mathrm {d} A-\int _{\Gamma ^{0}}J_{3}~{\dot {w}}_{,\alpha }^{0}~\delta w^{0}~\mathrm {d} s\right|_{0}^{T}\end{aligned}}}$ Again, since the variations are zero at the beginning and the end of the time interval under consideration, we have ${\displaystyle \delta K=-\int _{0}^{T}\left\{\int _{\Omega ^{0}}\left[J_{1}\left({\ddot {u}}_{\alpha }^{0}~\delta u_{\alpha }^{0}+{\ddot {w}}^{0}~\delta w^{0}\right)-J_{3}~{\ddot {w}}_{,\alpha \alpha }^{0}~\delta w^{0}\right]~\mathrm {d} A+\int _{\Gamma ^{0}}J_{3}~n_{\alpha }~{\ddot {w}}_{,\alpha }^{0}~\delta w^{0}~\mathrm {d} s\right\}~\mathrm {d} t}$ For the dynamic case, the variation in the internal energy is given by ${\displaystyle \delta U=-\int _{0}^{T}\left\{\int _{\Omega ^{0}}\left[N_{\alpha \beta ,\alpha }~\delta u_{\beta }^{0}+M_{\alpha \beta ,\beta \alpha }~\delta w^{0}\right]~\mathrm {d} A-\int _{\Gamma ^{0}}\left[n_{\alpha }~N_{\alpha \beta }~\delta u_{\beta }^{0}+n_{\alpha }~M_{\alpha \beta ,\beta }~\delta w^{0}-n_{\beta }~M_{\alpha \beta }~\delta w_{,\alpha }^{0}\right]~\mathrm {d} s\right\}\mathrm {d} t}$ Integration by parts and invoking zero variation at the boundary of the mid-surface gives ${\displaystyle \delta U=-\int _{0}^{T}\left\{\int _{\Omega ^{0}}\left[N_{\alpha \beta ,\alpha }~\delta u_{\beta }^{0}+M_{\alpha \beta ,\beta \alpha }~\delta w^{0}\right]~\mathrm {d} A-\int _{\Gamma ^{0}}\left[n_{\alpha }~N_{\alpha \beta }~\delta u_{\beta }^{0}+n_{\alpha }~M_{\alpha \beta ,\beta }~\delta w^{0}+n_{\beta }~M_{\alpha \beta ,\alpha }~\delta w^{0}\right]~\mathrm {d} s\right\}\mathrm {d} t}$ If there is an external distributed force ${\displaystyle q(x,t)}$ acting normal to the surface of the plate, the virtual external work done is ${\displaystyle \delta V_{\mathrm {ext} }=\int _{0}^{T}\left[\int _{\Omega ^{0}}q(x,t)~\delta w^{0}~\mathrm {d} A\right]\mathrm {d} t}$ From the principle of virtual work, or more precisely, Hamilton's principle for a deformable body, we have ${\displaystyle \delta U=\delta K+\delta V_{\mathrm {ext} }}$. Hence the governing balance equations for the plate are ${\displaystyle {\begin{aligned}N_{\alpha \beta ,\beta }&=J_{1}~{\ddot {u}}_{\alpha }^{0}\\M_{\alpha \beta ,\alpha \beta }+q(x,t)&=J_{1}~{\ddot {w}}^{0}-J_{3}~{\ddot {w}}_{,\alpha \alpha }^{0}\end{aligned}}}$

Solutions of these equations for some special cases can be found in the article on vibrations of plates. The figures below show some vibrational modes of a circular plate.

• mode k = 0, p = 1
• mode k = 0, p = 2
• mode k = 1, p = 2

The governing equations simplify considerably for isotropic and homogeneous plates for which the in-plane deformations can be neglected. In that case we are left with one equation of the following form (in rectangular Cartesian coordinates):

${\displaystyle D\,\left({\frac {\partial ^{4}w}{\partial x^{4}}}+2{\frac {\partial ^{4}w}{\partial x^{2}\partial y^{2}}}+{\frac {\partial ^{4}w}{\partial y^{4}}}\right)=-q(x,y,t)-2\rho h\,{\frac {\partial ^{2}w}{\partial t^{2}}}\,.}$

where ${\displaystyle D}$ is the bending stiffness of the plate. For a uniform plate of thickness ${\displaystyle 2h}$,

${\displaystyle D:={\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\,.}$

In direct notation

${\displaystyle D\,\nabla ^{2}\nabla ^{2}w=-q(x,y,t)-2\rho h\,{\ddot {w}}\,.}$

For free vibrations, the governing equation becomes

${\displaystyle D\,\nabla ^{2}\nabla ^{2}w=-2\rho h\,{\ddot {w}}\,.}$

Derivation of dynamic governing equations for isotropic Kirchhoff-Love plates

For an isotropic and homogeneous plate, the stress-strain relations are ${\displaystyle {\begin{bmatrix}\sigma _{11}\\\sigma _{22}\\\sigma _{12}\end{bmatrix}}={\cfrac {E}{1-\nu ^{2}}}{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}\varepsilon _{11}\\\varepsilon _{22}\\\varepsilon _{12}\end{bmatrix}}\,.}$ where ${\displaystyle \varepsilon _{\alpha \beta }}$ are the in-plane strains. The strain-displacement relations for Kirchhoff-Love plates are ${\displaystyle \varepsilon _{\alpha \beta }={\frac {1}{2}}(u_{\alpha ,\beta }+u_{\beta ,\alpha })-x_{3}\,w_{,\alpha \beta }\,.}$ Therefore, the resultant moments corresponding to these stresses are ${\displaystyle {\begin{bmatrix}M_{11}\\M_{22}\\M_{12}\end{bmatrix}}=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}~{\begin{bmatrix}1&\nu &0\\\nu &1&0\\0&0&1-\nu \end{bmatrix}}{\begin{bmatrix}w_{,11}\\w_{,22}\\w_{,12}\end{bmatrix}}}$ The governing equation for an isotropic and homogeneous plate of uniform thickness ${\displaystyle 2h}$ in the absence of in-plane displacements is ${\displaystyle M_{11,11}+2M_{12,12}+M_{22,22}+q(x,t)=2\rho h{\ddot {w}}-{\frac {2}{3}}\rho h^{3}\left({\ddot {w}}_{,11}+{\ddot {w}}_{,22}+{\ddot {w}}_{,33}\right)\,.}$ Differentiation of the expressions for the moment resultants gives us ${\displaystyle {\begin{aligned}M_{11,11}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\left(w_{,1111}+\nu ~w_{,2211}\right)\\M_{22,22}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}\left(\nu ~w_{,1122}+w_{,2222}\right)\\M_{12,12}&=-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}(1-\nu )~w_{,1212}\end{aligned}}}$ Plugging into the governing equations leads to ${\displaystyle {\begin{aligned}-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}&\left(w_{,1111}+\nu ~w_{,2211}+2(1-\nu )~w_{,1212}+\nu ~w_{,1122}+w_{,2222}\right)=\\&-q(x,t)+2\rho h{\ddot {w}}-{\frac {2}{3}}\rho h^{3}\left({\ddot {w}}_{,11}+{\ddot {w}}_{,22}+{\ddot {w}}_{,33}\right)\,.\end{aligned}}}$ Since the order of differentiation is irrelevant we have ${\displaystyle w_{,2211}=w_{,1212}=w_{,1122}}$. Hence ${\displaystyle {\begin{aligned}-{\cfrac {2h^{3}E}{3(1-\nu ^{2})}}&\left(w_{,1111}+2w_{,1212}+w_{,2222}\right)=\\&-q(x,t)+2\rho h{\ddot {w}}-{\frac {2}{3}}\rho h^{3}\left({\ddot {w}}_{,11}+{\ddot {w}}_{,22}+{\ddot {w}}_{,33}\right)\,.\end{aligned}}}$ If the flexural stiffness of the plate is defined as ${\displaystyle D:={\cfrac {2h^{3}E}{3(1-\nu ^{2})}}}$ we have ${\displaystyle D\left(w_{,1111}+2w_{,1212}+w_{,2222}\right)=q(x,t)-2\rho h{\ddot {w}}+{\frac {2}{3}}\rho h^{3}\left({\ddot {w}}_{,11}+{\ddot {w}}_{,22}+{\ddot {w}}_{,33}\right)\,.}$ For small deformations, we often neglect the spatial derivatives of the transverse acceleration of the plate and we are left with ${\displaystyle D\left(w_{,1111}+2w_{,1212}+w_{,2222}\right)=q(x,t)-2\rho h{\ddot {w}}\,.}$ Then, in direct tensor notation, the governing equation of the plate is ${\displaystyle D\nabla ^{2}\nabla ^{2}w=q(x,y,t)-2\rho h{\ddot {w}}\,.}$

• Bending
• Bending of plates
• Infinitesimal strain theory
• Linear elasticity
• Plate theory
• Stress (mechanics)
• Stress resultants
• Vibration of plates