INTEGRATED STRUCTURAL TAILORING AND CONTROL USING ADAPTIVE MATERIALS FOR ADVANCED AIRCRAFT WINGS

This study combines structural tailoring with the adaptive capabilitie s of piezoelectric materials for the purpose of controlling the vibrat ion and static aeroelastic characteristics of advanced aircraft wings. The structural model consists of a thin/thick-walled closed cross-sec tional cantilevered beam whose constituent layers exhibit elastic anis otropic properties and incorporates a number of nonclassical features. Results reveal that a combination of structural tailoring and control using adaptive materials can play a major role in enhancing the vibra tional and static aeroelastic response characteristics of aircraft win gs.