Abstract
Based on the structures of unmanned aerial vehicle (UAV) wings, nonlinear dynamic analysis of macrofiber composite (MFC) laminated shells is presented in this paper. The effects of piezoelectric properties and aerodynamic forces on the dynamic stability of the MFC laminated shell are studied. Firstly, under the flow condition of ideal incompressible fluid, the thin airfoil theory is employed to calculate the effects of the mean camber line to obtain the circulation distribution of the wings in subsonic air flow. The steady aerodynamic lift on UAV wings is derived by using the Kutta–Joukowski lift theory. Then, considering the geometric nonlinearity and piezoelectric properties of the MFC material, the nonlinear dynamic model of the MFC laminated shell is established with Hamilton’s principles and the Galerkin method. Next, the effects of electric field, external excitation force, and nonlinear parameters on the stability of the system are studied under 1 : 1 internal resonance and the effects of material parameters on the natural frequency of the structure are also analyzed. Furthermore, the influence of the aerodynamic forces and electric field on the nonlinear dynamic responses of MFC laminated shells is discussed by numerical simulation. The results indicate that the electric field and external excitation have great influence on the structural dynamic responses.
Highlights
MFC material, which was invented by NASA in 1996, has great application prospect in many engineering structures, especially in aviation and aerospace eld
Tan et al [1] studied the dynamic characteristics of a beam system with active piezoelectric ber-reinforced composite layers. en, more researches are reported on the MFC materials as sensors and actuators in di erent structures to adjust the deformation or vibration of the system, such as rotating composite thinwalled beams [2], thin beams [3], cylindrical shells [4], and smart composite plates [5]
Zhang et al [29] investigated the structural deformation of composite laminated thin-walled structures bonded with orthotropic MFCs by establishing the finite element (FE) model based on linear piezoelectric constitutive equations
Summary
MFC material, which was invented by NASA in 1996, has great application prospect in many engineering structures, especially in aviation and aerospace eld. Rafiee et al [17] investigated the nonlinear vibration and dynamic behavior of supported piezoelectric functionally graded shells under electrical, thermal, mechanical, and aerodynamic loadings. Rafiee et al [20] provided numerical simulation about the nonlinear dynamics of piezoelectric nanotubes/fibers/polymer multiscale composite plates, including the effects of different parameters of single-walled carbon nanotubes (SWCNTs) and multiwalled carbon nanotubes (MWCNTs) on the linear and nonlinear natural frequencies. Zhang et al [29] investigated the structural deformation of composite laminated thin-walled structures bonded with orthotropic MFCs by establishing the finite element (FE) model based on linear piezoelectric constitutive equations. E effect of different forces on the dynamic behaviors of MFC laminated shells is investigated in numerical simulation. Moderating effects of piezoelectric performance on the stability of the system are presented here, which would provide guidance in controlling strategy of the nonlinear vibration for UAV wings
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