II.1.6.7 Calculation algorithm for shear stiffness
One describes below the calculation sequences that is used to calculate the laminate out-of-plane shear
stiffness properties, and the out-of-plane shear stresses related to a given loading of the
laminate.
The calculation sequence is described below. It involves two loops on the laminate
layers.
-
1.
- Calculate laminate in-plane and flexural properties. This is necessary because one needs
the matrices
and
to calculate out-of-plane shear properties.
-
2.
- One initializes the
matrix
to zero.
-
3.
- Then for each layer
with ,
one performs the following sequence of operations:
-
(a)
- One estimates the
matrix of in-plane stiffness coefficients in laminate axes .
For other calculations, one also need properties like the laminate thickness
and the positions
of different layer interfaces.
-
(b)
- This matrix is used to calculate the two matrices
and .
(See section II.1.6.3 for more details.) One has:
|
-
(c)
- Then, one calculates two other
matrices
and .
(See section II.1.6.3.) One has:
|
-
(d)
- Then one calculates the
matrices:
|
As the expression of
is recursive, one needs another expression for the first value. The expression
is:
-
(e)
- One calculates the
matrix. (See the end of section II.1.6.6 for the expressions to be used.) Then to
,
one adds one term:
|
-
4.
- At the end of the loop on layers, the shear stiffness matrix
is calculated
by inversion of .
One also defines an out-of-plane shear compliance matrix calculated as follows:
This matrix allows to calculate the laminate out-of-plane shear moduli:
Note that the values calculated above do not correspond to an out-of-plane shear stiffness of
a material equivalent to the defined laminate. To convince yourself of this you can
define a laminate with a single ply of orthotropic material. Then, you will observe that
in which
is material shear
modulus. (The usual
factor in shell theory is recovered.)