Calculation Module » Historie » Revision 13
Revision 12 (Andreas Hauffe, 14.09.2021 17:15) → Revision 13/14 (Andreas Hauffe, 15.09.2021 08:47)
h1. Calculation Module
h2. Generall
The calculation module is used to calculate loads or strains, as well as stresses within the specified laminate according to the classical laminated plate theory (!cite{Redd2003},!cite{Schu2004}). In order to be able to directly output the effects of the laminate stacking sequence on the stiffness matrix, the loads or strains and the stresses of the layers, the calculations are updated automatically. Among other things, hygrothermal effects can also be taken into account !cite{Barth2009}.
During a calculation, the system of linear equations listed below is solved with the help of the Gaussian elimination method. The calculated unknowns are entered in the fields of the loads and strains. In addition, the stresses and strains in each laminate layer are calculated. These can be viewed in the internal forces subwindow in the local fiber coordinate system.
h2. Windows Layout
p=. {{thumbnail(berechnung.png,size=500,title=calculation window)}}
h3. 1 - ABD matrix
Based on the stiffness matrices of the individual layers, the membrane stiffness matrix $\mathbf{A}$, coupling stiffness matrix $\mathbf{B}$ and bending stiffness matrix $\mathbf{D}$ of the laminate are automatically calculated with repect to the classical laminated plate theory and the three matrices are shown separately and color-coded within the ABD matrix.
h3. 2 - Internal Loads, Strain and hygrothermal loads
Both membrane internal loads and moments as well as strain and curvatures can be specified as loads on the defined laminate. Either the load or the strain can be specified in the input fields under 2a and 2b for each coordinate direction. In addition, a temperature difference and the percentage change in the relative humidity can be specified in the fields in window section 2c. According to the classical laminated plate theory applies to mechanical and hygrothermal loads and strains
$$\begin{pmatrix} \underline{n} \\ \underline{m} \end{pmatrix}_{mech} = \begin{bmatrix} \mathbf{A} & \mathbf{B} \\ \mathbf{B} & \mathbf{D} \end{bmatrix} \begin{pmatrix} \underline {\varepsilon} \\ \underline {\kappa} \end{pmatrix} - \begin{pmatrix} \underline{n} \\ \underline{m} \end{pmatrix}_{hygrotherm}$$
If no effects of the hygrothermal loads are to be considered, the fields for the temperature difference and the percentage humidity difference must be filled with the values zero. This view is the standard setting in the calculation module of eLamX².
h3. 3 - hygrothermal internal loads
At this point, the resulting hygrothermal internal loads are output based on the specified temperature difference and the percentage difference in humidity on the entire laminate. They are not input data. The selection of the check boxes for mechanical loads and the resulting distortions has no influence on the hygrothermal cutting loads. They result from the direction-dependent thermal conductivity and swelling coefficients of the individual layers as well as their stiffness matrices and the specified temperature and humidity difference.
h3. 4 - Stress and strain distribution button
This button can be used to display the stress and strain distribution within the laminate in local and global coordinates for the coordinate axes of the laminate plane. The output is only qualitative. The specified coordinate directions relate to the fiber angle, the specified x-value reflecting the size in the 0° direction and the y-value reflecting the size in the 90° direction of the laminate. The fiber orientations of the individual layers are shown by the hatching. Horizontal lines correspond to zero degrees and vertical lines to 90 degrees fiber angles. If the fiber angles of adjacent layers are very close together, the hatching is output in different colors.
p=. {{thumbnail(spannungsverteilung.png,size=500,title=call up 3D failure body of the single layer)}}
h3. 5 - Delete button
Pressing the button deletes the specified loads and the calculated unknown internal loads and distortions, as well as the calculated stress distribution.
h3. 6 - Representation of the strains and curvatures on the basis of a square plate
This button can be used to open a window in which the calculated strains and curvatures are visualized on a square plate. This is used for a better understanding of the coupling effects within the ABD matrix.
p=. {{thumbnail(darstellung_eps_kappa.png, size=500, title=call up 3D failure body of the single layer)}}
h3. 7 - Layer data in the local fiber coordinate system
After a calculation, the stresses or strains of each layer of the composite are calculated in this part of the window, depending on the selection. The evaluation is carried out on the top and bottom of each individual layer. The stresses in each layer are compared with their strengths and a reserve factor is calculated on the top and bottom of the layer using the selected failure criterion. In addition, the type of failure to be expected is specified with regard to the failure criterion selected for each layer.
p=. {{thumbnail(aufruf_3d-versagenskoerper_einzelschicht.png, size=500, title=calling up 3D failure body of the single layer)}}
In addition to displaying the failure criteria using the reserve factors, right-click on a layer to call up the Failure Criteria module and display the failure body of the individual layer together with the stress state in the stress area (see figure). The current stress on the composite layer is entered as a red point. If the calculated stress vector lies within the selected failure body, only its line is visible. This makes it clear which tension combination prevails in each layer.
h2. Laminate information / engineering constants
p=. {{thumbnail(laminatinformationen.png, size=500, title=call up 3D failure body of the single layer)}}
This window can be opened by right-clicking on a laminate and then selecting engineering constants.
h3. 1 - ABD matrix
Based on the stiffness matrices of the individual layers, the membrane stiffness matrix $\mathbf{A}$, coupling stiffness matrix $\mathbf{B} $ and bending stiffness matrix $\mathbf{D} $ of the laminate composite are automatically calculated and color-coded when the calculation module is called up on the basis of classical laminated plate theory. laminate theory shown separately within the ABD matrix. This matrix is shown in the form of a table so that all values can be copied out.
h3. 2 - Compliance matrix of the laminate composite
The inverse of the stiffness matrix of the laminate is displayed here. It may be that for symmetrical laminates, terms of the inverse coupling stiffness matrix (b) are different from zero, but very small. This results from numerical inaccuracies in the double precision calculation within the program. This matrix is shown in the form of a table so that all values can be copied out.
h3. 3 - engineering constants of the laminate multilayer composite
The engineering constants of the laminate multi-layer composite are also automatically calculated according to !cite{Schu2004} for membrane and bending loads. This is done both with and without consideration of Poisson effect. transverse contraction hindrance (QKB). In the case of asymmetrical laminates, where in which there is a coupling between membrane and bending deformation is present, deformation, the engineering constants determined in this way have little meaning and should be used with caution.
h3. 4 - Coefficient of expansion of the laminate multilayer composite for heat and moisture
In this part of the window the thermal expansion coefficients $\alpha^T_i$ and the swelling coefficient $\beta_i$ of the total laminate composite are output according to the system of units that was selected for specifying the values of the individual layer. Here, too, the definition according to !cite{Schu2004} applies and thus
\begin{equation}
\left(
\begin{array}{c}
\epsilon_x \\
\epsilon_y \\
\gamma_{xy}
\end{array}
\right)_{T+H} =
\Delta T
\left(
\begin{array}{c}
\alpha^T_x \\
\alpha^T_y \\
\alpha^T_{xy}
\end{array}
\right) +
\Delta c
\left(
\begin{array}{c}
\beta_x \\
\beta_y \\
\beta_{xy}
\end{array}
\right)
\end{equation}
h2. Notes on the engineering constants
The engineering constants can be determined for two types of stress. On the one hand for a membrane stress and on the other hand for a bending stress. In both cases, this is possible with and without Poisson effect. hindrance to lateral contraction.
The approach procedure is presented explained on the basis of the explanations in !cite{Schu2004} for symmetrical laminates. For the membrane state, the ABD matrix becomes
\begin{equation}
\left(
\begin{array}{c}
n \\
m
\end{array}
\right) =
\left[
\begin{array}{cc}
A & B \\
B & D
\end{array}
\right]
\left(
\begin{array}{c}
\epsilon \\
\kappa
\end{array}
\right)
\end{equation}
only the $A$-matrix A-matrix is used, which is feasible for permissible with symmetrical laminates ($B ($ B = 0$). 0 $). This results in
\begin{equation}
\left(
\begin{array}{c}
n_x \\
n_y \\
n_{xy}
\end{array}
\right) =
\left[
\begin{array}{ccc}
A_{11} & A_{12} & A_{13} \\
A_{21} & A_{22} & A_{23} \\
A_{31} & A_{32} & A_{33}
\end{array}
\right]
\left(
\begin{array}{c}
\epsilon_{x} \\
\epsilon_{y} \\
\gamma_{xy}
\end{array}
\right)
\end{equation}
The aim is now to come up with an equation for the stress $\sigma_{x}$, $ \ sigma_ {x} $, which corresponds to the Hooke's uniaxial elasticity law $\sigma=E \epsilon$. $ \ sigma = E \ epsilon $. To do this, the equation is divided by the total thickness of the laminate. This corresponds to a homogenization of the material and one obtains:
\begin{equation}
\left(
\begin{array}{c}
\sigma_x \\
\sigma_y \\
\tau_{xy}
\end{array}
\right) = \frac{1}{t_{ges}}
\left[
\begin{array}{ccc}
A_{11} & A_{12} & A_{13} \\
A_{21} & A_{22} & A_{23} \\
A_{31} & A_{32} & A_{33}
\end{array}
\right]
\left(
\begin{array}{c}
\epsilon_{x} \\
\epsilon_{y} \\
\gamma_{xy}
\end{array}
\right) \ .
\end{equation}
This equation corresponds to a single anisotropic layer across the entire thickness. There are two ways to come up with an equation according to the Hooke's law. uniaxial law of elasticity. On the one hand, $\epsilon_{y}$ $ \ epsilon_ {y} $ and $\gamma_{xy}$ $ \ gamma_ {xy} $ are set to zero without Poisson effect, zero, which corresponds to a transverse contraction hindrance, and the following equations are obtained:
\begin{equation}
\left(
\begin{array}{c}
\sigma_x \\
\sigma_y \\
\tau_{xy}
\end{array}
\right) = \frac{1}{t_{ges}}
\left[
\begin{array}{ccc}
A_{11} & A_{12} & A_{13} \\
A_{21} & A_{22} & A_{23} \\
A_{31} & A_{32} & A_{33}
\end{array}
\right]
\left(
\begin{array}{c}
\epsilon_{x} \\
0 \\
0
\end{array}
\right) \ .
\end{equation}
\begin{equation}
\sigma_x = \frac{A_{11}}{t_{ges}}\epsilon_{x}
\end{equation}
In order to obtain a modulus of elasticity with Poisson effect, without hindrance to transverse contraction, the equation has to be transformed and $\sigma_{y}$ $ \ sigma_ {y} $ and $\tau_{xy} $ \ tau_ {xy} $ are set to zero.
\begin{equation}
\left(
\begin{array}{c}
\epsilon_{x} \\
\epsilon_{y} \\
\gamma_{xy}
\end{array}
\right)
= t_{ges}
\left[
\begin{array}{ccc}
A_{11} & A_{12} & A_{13} \\
A_{21} & A_{22} & A_{23} \\
A_{31} & A_{32} & A_{33}
\end{array}
\right]^{-1}
\left(
\begin{array}{c}
\sigma_x \\
0 \\
0
\end{array}
\right)
\ .
\end{equation}
\begin{equation}
\sigma_x = \frac{1}{(A^{-1})_{11} \cdot t_{ges}}\epsilon_{x}
\end{equation}
In this way, all engineering constants can now be determined. The constants with Poisson effect without hindrance to transverse contractions result from:
\begin{eqnarray}
E_x & = & \frac{1}{(A^{-1})_{11} \cdot t_{ges}} \\
E_y & = & \frac{1}{(A^{-1})_{22} \cdot t_{ges}} \\
G_{xy} & = & \frac{1}{(A^{-1})_{66} \cdot t_{ges}} \\
\nu_{xy} & = & -\frac{(A^{-1})_{12}}{(A^{-1})_{11}} \\
\nu_{yx} & = & -\frac{(A^{-1})_{12}}{(A^{-1})_{22}}
\end{eqnarray}
The constants without Poisson effect with transverse contraction obstruction result from:
\begin{eqnarray}
E_x & = & \frac{A_{11}}{t_{ges}} \\
E_y & = & \frac{A_{22}}{t_{ges}} \\
G_{xy} & = & \frac{A_{66}}{t_{ges}} \\
\end{eqnarray}
If the Poisson effect a transverse contraction hindrance is not taken into account, Poisson's ratios transverse contraction numbers are not useful and are therefore not included.
These homogenized material parameters are only feasible permissible for membrane loads. An equivalent procedure using the D-matrix is necessary for bending, since the position of the layers has a great influence in the case of bending stresses in contrast to membrane stresses. The derivation of the formulas calculation rule is taken from !cite{Schu2004}.
The analogy to the beam is used for bending. Since the laminate board has a rectangular cross-section, it is compared with the bending elasticity law of a rectangular beam and the following applies:
\begin{equation}
M = -EI \cdot w'' = - E \frac{b t^3}{12} \cdot w'' \rightarrow m = -E \frac{t^3}{12} \cdot w'' \ .
\end{equation}
In addition, $w'' $ w '' = -\kappa$ - \ kappa $ applies.
Bending loads with the $D$-matrix D-matrix are described for the laminate. laminate board.
\begin{equation}
\left(
\begin{array}{c}
m_x \\
m_y \\
m_{xy}
\end{array}
\right) =
\left[
\begin{array}{ccc}
D_{11} & D_{12} & D_{13} \\
D_{21} & D_{22} & D_{23} \\
D_{31} & D_{32} & D_{33}
\end{array}
\right]
\left(
\begin{array}{c}
\kappa_{x} \\
\kappa_{y} \\
\kappa_{xy}
\end{array}
\right)
\end{equation}
Now the approach procedure is equivalent to stressing the membrane. Assuming no Poisson effect results in: a transverse contraction hindrance (in this case a transverse curvature hindrance) results:
\begin{equation}
\left(
\begin{array}{c}
m_x \\
m_y \\
m_{xy}
\end{array}
\right) =
\left[
\begin{array}{ccc}
D_{11} & D_{12} & D_{13} \\
D_{21} & D_{22} & D_{23} \\
D_{31} & D_{32} & D_{33}
\end{array}
\right]
\left(
\begin{array}{c}
\kappa_{x} \\
0 \\
0
\end{array}
\right)
\end{equation}
\begin{equation}
m_x = D_{11} \kappa_x
\end{equation}
\begin{equation}
E_{x,b} = \frac{12}{t_{ges}^3}D_{11}
\end{equation}
Thus, all engineering constants without Poisson effect with cross-contact obstruction result in:
\begin{eqnarray}
E_{x,b} & = & \frac{12}{t_{ges}^3}D_{11} \\
E_{y,b} & = & \frac{12}{t_{ges}^3}D_{22} \\
G_{x,b} & = & \frac{12}{t_{ges}^3}D_{66} \\
\end{eqnarray}
and with Poisson effect: without hindrance to transverse contraction:
\begin{eqnarray}
E_{x,b} & = & \frac{12}{(D^{-1})_{11} \cdot t_{ges}^3} \\
E_{y,b} & = & \frac{12}{(D^{-1})_{22} \cdot t_{ges}^3} \\
G_{x,b} & = & \frac{12}{(D^{-1})_{66} \cdot t_{ges}^3} \\
\end{eqnarray}
At this point, too, Poisson's ratios transverse contraction numbers are not very useful. useful, as these correspond more to transverse curvature numbers.
This approach procedure generally only applies to symmetrical laminates. In the case of asymmetrical laminates, the inverse of the entire $ABD$ ABD matrix must be formed and then the corresponding terms must be used.
!putbib{}