## Calculation Module » History » Revision 10

Revision 9
*(Andreas Hauffe, 09/12/2021 01:50 PM)*
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Revision 10/14
*(Andreas Hauffe, 09/12/2021 01:57 PM)*

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 consider the effects of the laminate stacking sequence structure on the occupation of the stiffness matrix, matrix of the composite, the cutting 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 sectional loads and strains. distortions. In addition, the stresses and strains in each laminate layer are calculated. These can be viewed in the internal forces Layer sizes subwindow in the local fiber coordinate system. h2. Windows Layout construction p=. {{thumbnail(berechnung.png,size=500,title=calculation window)}} h3. 1 - ABP 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 with repect to and color-coded when the calculation module is called up on the basis of classical laminated plate laminate theory and the three matrices are shown separately and color-coded within the ABD ABP matrix. h3. 2 - Internal Loads, Strain cutting loads, distortions and hygrothermal loads Both membrane sectional loads and moments as well as elongations and curvatures can be specified as loads on the defined composite. Either the load or the distortion 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 laminate theory applies to mechanical and hygrothermal loads and distortions $$\begin{pmatrix} \underline{n} \\ \underline{m} \end{pmatrix}_{mech} = \begin{bmatrix} \mathbf{A} & \mathbf{B} \\ \mathbf{B} & \mathbf{D} \end{bmatrix} \begin{pmatrix} \underline {\varepsilon} \\ \underline {\kappa} \end{pmatrix} - \begin{pmatrix} \underline{n} \\ \underline{m} \end{pmatrix}_{hygrotherm}$$ 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 cutting loads At this point, the resulting hygrothermal cutting 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 shown. 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 sectional loads and distortions, as well as the calculated stress distribution. h3. 6 - Representation of the expansions 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 sizes 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 the 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 - ABP 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 composite are automatically calculated and color-coded when the calculation module is called up on the basis of classical laminate theory shown separately within the ABP 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 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 multilayer composite The engineering constants of the 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 transverse contraction hindrance (QKB). In the case of asymmetrical laminates, in which there is a coupling between membrane and bending deformation, the engineering constants determined in this way have little meaning and should be used with caution. h3. 4 - Coefficient of expansion of the 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 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 hindrance to lateral contraction. The procedure is 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 is used, which is permissible with symmetrical laminates ($ B = 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} $, which corresponds to the uniaxial elasticity law $ \ 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 uniaxial law of elasticity. On the one hand, $ \ epsilon_ {y} $ and $ \ gamma_ {xy} $ are set to 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 without hindrance to transverse contraction, the equation has to be transformed and $ \ sigma_ {y} $ and $ \ 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 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 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 a transverse contraction hindrance is taken into account, transverse contraction numbers are not useful and are therefore not included. These homogenized material parameters are only 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 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 '' = - \ kappa $ applies. Bending loads with the D-matrix are described for the 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 procedure is equivalent to stressing the membrane. Assuming 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 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 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, transverse contraction numbers are not very useful, as these correspond more to transverse curvature numbers. This procedure generally only applies to symmetrical laminates. In the case of asymmetrical laminates, the inverse of the entire ABD matrix must be formed and then the corresponding terms must be used. !putbib{}