The Numerical Simulation Of Static And Dynamic Responseof Orthotropic Laminated Plates Under Thermal-mechanical Loads

Composite layer plates has been widely applicated on aircraft for its high strength and stiffness, what is more, it will become the basic structural unit of aircraft in21st century. But composite layer plates also have their own shortcomings—failure modes very complex under various forms of load.One of the major damage forms is delamination which is caused by interlaminar stress.Mostly reduce the weight of the structure on the basis of reliability in order to ensure the safety of the structure. the key question is how to improve the ability to composite structures to resist damage, and provide accurate structural failure prediction. So the distribution prediction of interlaminar stess of composite layer plates under different load forms become very important.The article uses SHELL99element in ANSYS which is finite element software to simulate orthotropic laminates and get the distribution of interlaminar shear stress under state load, dynamic load, steady-state temperature field as well as the transient temperature field, then contrast with theoretical values. we can get the main factors which affect the shear stress distribution after research the differents of shear stress distribution by change the geometry of laminates, the elastic parameters, layers, laying as well as boundary conditions.