sandwich composite panel
I am trying to simulate a composite sandwich panel with honeycomb at its core. I am using epoxy as adhesive to join the honeycomb to the both facesheets. For this i created a honeycomb structure in a mechanical model and two facesheets in two different aACPs. Then i imported the honeycomb and two facesheets in static structure module( with "transfer shell data " setting for ACPs).
i also created the legal contacts (formulation= pur penalty) between the honeycomb and facesheet. But when i am trying the define CZM it does not account the contact.
I know in a sandwich panel like this the honeycomb would fail first before the epoxy.But I want to know the forces at the contact.