Three methods give access to the ply results stored in ClaLam object:
“getPliesStrains” returns the components of the strain tensor stored in the layered results of the laminate.
“getPliesStresses” returns the components of the stress tensor stored in the layered results of the laminate.
“getPliesMechanicalStrains” returns the components of the Mechanical Strain Tensor stored in the layered results of the laminate according to (II.1.18). This tensor corresponds to the “Mechanical Strain Tensor” presented in Tables X.C.3 and III.2.4.
These three methods:
Have an arbitrary number of arguments. Each argument corresponds to an identifier of the layer and location at which the layered components are recovered. The identifier is given as an Array of two elements: the ply local integer index and a String that can have "Inf", "Mid" or "Sup" value. Among these layers, only those for which layered components have been previously calculated and stored are returned by the method. If the call is done without argument, all the layered results stored in the laminate are returned.
They return components expressed in the ply coordinate system.
The components are calculated assuming that .
The components are returned by the method only if their calculation and storage has been required in the last call to “calcResponse”. (See section II.4.7.1.)
The methods return an Array of which each element corresponds to the stresses/strains at one given location in the thickness of the laminate. More precisely, each element is an Array of 2+6=8 elements containing:
The two first elements identify the layer: they correspond to the integer index of the ply between 0 and , and the String location in the ply ("Inf", "Mid" or "Sup"). (Note that this does not correspond to the ply identifier. The integer index corresponds to the position of the ply in laminate lay-up.)
The next 6 real elements contain the components of the result in the following order: 11, 22, 33, 23, 13, 12.
To the three methods listed above correspond three other methods that return the ply stresses or strains with components expressed in a coordinate system defined with respect to the laminate, and not expressed in ply axes. The three methods are called:
The first argument of these three methods are a real value corresponding to the rotation of restitution coordinate system with respect to the laminate axes. The following arguments are the same as those of the three first methods defined above.