AEROELASTICITY USING THE FINITE ELEMENT METHOD

Uses advanced structural theories to formulate and describe the coupling between finite elements and classical aerodynamic theories

Aeroelasticity using the Finite Element Method deals with the Aeroelasticity of lifting bodies (wings and panels) by the Finite Element Method (FEM). It focuses on Aeroelasticity problems related to wings and panels: wings in subsonic range and panel in supersonic regime are treated. The structural models used are built by using classical and advanced one-dimensional (beams) and two-dimensional models (plates/shells) for the analysis of metallic and layered structures made by advanced composite materials. The elastic problems are formulated by means of finite element method. The aerodynamic fields and loadings are expressed by considering known theories used in classical aeroelasticity analysis: strip theory (in both steady and unsteady form), Theodorsen models, Vortex Lattice Method, Double Lattice Method and Piston Theory. Static and dynamic aeroelastic responses are both addressed. Static (divergence) and dynamic (flutter) response, including panel flutter are detailed in the book. 

• Formulates and describes the details of coupling between finite elements and classical aerodynamic theories.
• Proposes advanced 1D and 2D structural FE models in a form similar to the formulation used in classical beam, plate, shell theories. These advanced theories permit exploration of aeroelastic phenomena that are not considered by classical theories.
• Discusses classical aeroelasticity problems related to wings and panels.

A valuable resource for Researchers in continuum mechanic of solids and structures