 # Description

Laminate theory enables analytical stress-strain analysis of the arbitrary laminated structures (with plane laminae) subjected to mechanical or thermal load. Arbitrary number of layers, layer thicknesses and material type (isotropic, anisotropic) can be taken into account. The classical laminate theory enables to calculate stresses and strains within layers, apparent laminate properties or total deformation of the laminate (bending, twisting). Laminate theory considers always structure of the infinite dimensions, so the stresses and strains which are obtained, corresponds to the state enough far from the free edges of the real finite laminate.

This tool is provided by ISFK to show the functionality of the classical laminate theory on the simple example of periodic laminate. The use of the tool is free of charge.

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# Basic principle of the CLT

• Set up the layer stiffness matrices for all layers (in XY CS).
• Set up the global laminate stiffness matrix („Hooke’s law“ of the laminate) – using condition of the stress and moment equilibrium over the laminate height -Eqs. (1) and (2).
• Solve the global laminate behaviour under given boundary conditions (apparent behaviour of the laminate middle plane) – Eqs. (3)-(8)
• Calculation of the arbitrary quantities in individual layers from the global laminate behaviour substitution of results from Eq.(3) to (1).

Hooke’s law of the single layer:

where S ij prime are components of the material stiffness matrix (transformated from LT coordinate system to XY coordinate system – see Fig. 1.),  ? - strain vector, ? – curvature vector, ? – vector of the CTEs.

Stress and moment equilibrium over the laminate height:

By substitution of the Eqs.(1) for all layers to Eq. (2), the global laminate stiffness matrix K is obtained (the so-called A-B-D matrix – see Eq. (3)).

Where N, M are vectors of the boundary conditions - forces and moments. By solving Eq. (3) elongations and curvatures vectors ? 0 and ? 0 are obtained. By substitution of these results into the Hooke´s law of the particular layer (2), stresses at arbitrary point over the laminate height can be computed.