摘要
Panel flutter phenomena can be strongly affected by thermal loads,and so a refined aeroelastic model is presented.Higher-order shell theories are used as structural models.The aerodynamic forces are described using the Piston theory.The temperature is considered uniform over the thickness of the panel.The aero-thermo-elastic model is derived in the framework of the Carrera unified formulation(CUF),therefore the matrices are expressed in a compact form using the″fundamental nuclei″.Composite and sandwich structures are considered and different boundary conditions are taken into account.The effects of the thermal load on the aeroelastic behavior are investigated.
Panel flutter phenomena can be strongly affected by thermal loads, and so a refined aeroelastic model is presented. Higher-order shell theories are used as structural models. The aerodynamic forces are described using the Piston theory. The temperature is considered uniform over the thickness of the panel. The aero-thermo-elastic model is derived in the framework of the Carrera unified formulation （CUF）, therefore the matrices are expressed in a compact form using the ＂fundamental nuclei＂. Composite and sandwich structures are considered and different boundary conditions are taken into account. The effects of the thermal load on the aeroelastic behavior are investi- gated.
