Nonlinear aeroelastic stability analysis of a two-stage axially moving telescopic wing by using fully intrinsic equations

During the process of span extension for an aircraft wing equipped with a telescopic morphing mechanism, aspect ratio increases, and hence, geometrical nonlinearities might become more significant. In this regard, paper aims to investigate effect structural nonlinearity on aeroelasticity wings using exact fully intrinsic equations first time. Furthermore, effects various parameters such as thrust force, engine location, chord size, flight altitude, initial angle attack, overlapping mass are studied. The applied aerodynamic loads in incompressible flow regime determined Peters’ unsteady model. order check stability system, resulting nonlinear partial differential discretized by central finite difference method then linearized about static equilibrium. Finally, obtaining eigenvalues is evaluated. It observed that equations, instability axially moving can be accurately. Moreover, results show length have significant aeroelastic wing.