Dynamic Response Of Panel Flutter In Supersonic Airflow

Now the domestic and international research of panel thermal flutter has become thefocus of the researchers the rapid development of high-speed craft technology. Panel thermalflutter on vehicle performance have a significant impact, and even affect the flight safety.Now, the structure design of the supersonic aircraft has a flexible and light trend, whichmakes the panel stability more and more significant. So the study of the stability and dynamicbehavior of the panel under various conditions has practical meanings for the aircraft design.In this dissertation, nonlinear dynamics of the panel in supersonic airflow is investigated. Themain contents are as follows:(1) The mechanical system of panels in supersonic airflow is modeled. The aerodynamicload is simplified In terms of the first-order piston theory. Appling the Von Karmandeformation strain-displacement relation and d’Alembert principle, the partial differentialequations of transverse nonlinear vibration for the panels are derived. By usingnon-dimensionalization and discretization, a set of ordinary differential equations is obtained.(2) The stability and bifurcations of the panel system are researched. According to theRouth-Hurwitz criterion, the stability regions of the system are obtained. Numerical examplesare presented to support the conclusions.(3) The mechanical system of panels in low speed airflow is modeled, and a a newaerodynamic model of wind load was adopt in this paper. The governing equation neglectingnonlinear term is transformed into a set of ordinary differential equations via the Galerkinapproach. The stability of the equilibrium configuration was analyzed. At last, the influenceof stability by average wind speed was discussed and the stability conditions are given.