Nonlinear Oscillations of a Composite Stepped Piezoelectric Cantilever Plate with Aerodynamic Force and External Excitation

Axially moving wing aircraft can better adapt to the flight environment, improve performance, reduce resistance, and distance. This paper simplifies fully unfolded axially into a stepped cantilever plate model, analyzes structural nonlinearity of system, studies influence aerodynamic on system vibration. The model is affected by forces, piezoelectric excitation, in-plane excitation. Due Hamilton’s principle least action, mathematical established based Reddy’s higher-order shear deformation theory, using Galerkin’s method, governing dimensionless partial differential equations are simplified two nonlinear ordinary equations, then study various engineering parameters oscillations frequency responses this conducted method multiple scales. It was found that different values a5, a6, b6 b8 change shape amplitude–frequency response curve size plate, while symbols a7 b7 rigidity model. excitations greatly impact dynamic plate.