structural analysis of Composite laminates

drssp

I am new in Composite laminate  structures. . And interested in using Mecway  for Composite laminate analysis for static loading conditions.

Any case study or tutorial if available will help me to get some hands on . 

Regards. 

Dr Patil.  

Victor

Here's a simple cantilever beam sandwich panel.

Skin thickness = 0.2 mm

Overall thickness = 10 mm

Bending moment per unit length at the support = force per unit length * beam length

= 20 N/m * 1 m = 20 N.m/m

Mecway solution: Moment per Length U = 20.0 N

Tensile stress in the skin:

Because the skin layers are very thin relative to the laminate's overall thickness, we assume each skin layer is in pure tension or compression.

Because the skin layers have a much higher Young's modulus than the core, we assume no load is carried by the core.

tensile stress = moment per unit length / laminate thickness / skin thickness

= 20 N.m/m / 0.01 m  / 0.0002 m = 1.0e7 Pa

Mecway solution: Principal Stress 1, Upper surface = 1.04e7 Pa

Mecway solution: Principal Stress 2, Bottom surface = -1.04e7 Pa