<title>Suppression of postbuckling deflection and panel flutter using shape memory alloy</title>

Thermal post-buckling and flutter characteristics of composite plates embedded with shape memory alloy fibers

“…Therefore, the marching method is introduced for determining the thermal large deflection and predicting the critical temperature. The marching method is summarized as follows [16].…”

“…The simply supported boundary conditions are considered for all edges which are immovable for the inplane directions. Table 1 represents the material properties of the composite matrix and SMA fiber [13,16]. The uniform temperature change was applied to the plate, and the reference temperature is assumed to be T ref Z 24 8C in this study.…”

“…Ostachowicz [14,15] researched the linear problems for the free vibration, thermal buckling, and panel flutter with delaminations of the composite plate with SMA fibers. Tawfik [16] studied the thermal post-buckling and panel flutter of SMA reinforced plates. In the work, the isotropic plate embedded with SMA fibers was modeled by the classical plate theory.…”

“…Fig. 1a and b show that the Young's modulus E s and the recovery stress s r of SMA vary as the temperature with high nonlinearity [16]. Therefore, the incremental method is needed to account for the temperature-dependent nonlinear properties of materials.…”

“…(a) SMA modulus of elasticity versus temperature[16]. (b) SMA recovery stress versus temperature[16].…”