Geometrically nonlinear modeling of smart aircraft wing with application of disturbance rejection control

Due to lightweight demanding, aircraft structures are prone to large deflections and vibrations under the influence of fluid forces. In this work, we develop a geometrically nonlinear continuous dynamics model of flexible wing based on the Euler-Bernoulli beam theory and Lagrange’s principle. To this end, piezoelectric constitutive relations of macro-fiber composite material are introduced to the continuous dynamics equation for consideration of electromechanically coupling effect. Furthermore, the assumed mode method is applied to discrete the continuous dynamics equations and establish the wing characteristic equations. The nonlinear model is solved using the Newmark- (Formula presented.) method and verified by comparing with the ANSYS. Finally, a variety of unknown disturbances are used to verify the effectiveness of the disturbance rejection control with generalized proportional integral observer on the suppression of structural vibration response.