I'm trying to design a section of aircraft structure that bolts an aluminium panel (secondary structure) to a carbon composite panel (primary structure). There is the need to account for extreme hot & cold temperatures and this is generating large thermal stresses and bolt loads dur to the thermal mismatch. Any ideas on how best to deal with this? I thought about slotted holes to allow for some expansion in the critial direction. Is the use of slotted holes acceptable?
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