By Balasubramanian Datchanamourty and George E. Blandford University of Kentucky Lexington, KY Assumptions Finite Element Equations Buckling Analysis Numerical Results Summary and Conclusions Each lamina is generally orthotropic Piecewise linear variation of electromagnetic potential through the depth of each piezoelectric lamina Piezoelectric surface is grounded where it is in contact with structural composite material Linear variation of temperature through the plate thickness Displacement assumptions consistent with Mindlin theory Nonlinear strains consistent with von Karman approximation [K uu ] [K u ] [0] uu u uQ e N [K ] [K ] [K ] N ˆ {u } {f u } N u e u Q ˆ [0] [0] { } {0} [K ] [K ] [K ] [K N ] Qu ˆ e {0} Q QQ e [K ] [K ] [K ] [0] [0] [0] {Q } e e {f u } {f u} {f } {f } {0} {0} e e e ˆ {u }i = ith element node displacement vector; five displacements per node: u, v, w, x, y ˆ e }i = ith element node electromagnetic potential { ˆ e} {Q i = ith element Gauss point transverse shear stress resultant vector; two per node: Qx and Qy {f u }e = mechanical load vector of element e {f }e = electrical load vector of element e {f u }e = temperature-stress load vector {f }e = pyroelectric load vector u {f N }e = nonlinear temperature-stress load vector uu = linear stiffness matrix for {u ˆ e} [K] u = linear coupling matrix between e and [K] {uˆ } uQ [K] e = linear coupling matrix between{u ˆ } and e ˆ { } ˆ e} {Q [K] = linear matrix for { ˆ e} ˆ e} ˆ e } and {Q [K]Q = linear coupling matrix between{ QQ = linear stiffness matrix for ˆ e {Q } [K] uu [K N ] u [K N ] = nonlinear stiffness matrix consistent with the von Karman approximation = nonlinear coupling matrix between displacements and electromagnetic potentials in the piezoelectric laminae [K L ] [K ] {U} {0} [K uu ] [K u ] [K L ] [K u ]T [K ] [K ] [K u ] [0] [0] [0] = linear coefficient matrix = geometric stiffness matrix = inplane stress magnification factor (U) [K(U)]{U} {FN } {F} {0} (U) = residual force vector [K(U)] [K L ] [K N ] [K N ] = nonlinear stiffness matrix consistent with a total Lagrangian formulation {F}, {FN } = linear and nonlinear force vectors Nonlinear Solution Schematic Thermal Buckling of (0/90/0/90)s Graphite-Epoxy laminate plus top and bottom piezoelectric lamina – PVDF or PZT Simply supported square plate PVDF PZT Graphite-Epoxy E1 = E2 = E3 =2 GPa E1 = E2 = E3 = 60 Gpa E1 =138 GPa, E2 = 8.28 GPa 12 = 13 = 23 = 0.333 12 = 13 = 23 = 0.333 12 = 0.33 G12 = G13 = G23 = 0.75 GPa G12 = G13 = G23 = 22.5 GPa G12 = G13 = G23 = 6.9 GPa 1 = 2 = 3 = 1.2x10-4 /0C 1 = 2 = 3 = 1x10-6 /0C 11 = 22 = 33 = 1x10-10 F/m 11 = 22 = 33 = 1.5x10-8 F/m d31 = d32 = -d24 = -d15 d31 = d32 = -1.75x10-8 0C/N 23x10-12 0C/N d24 = d15 = 6x10-10 0C/N p3 = -2.5x10-5 0C/K/m2 p3 = 7.5x10-4 0C/K/m2 1 = 0.18x10-6 /0C 2 = 27x10-6 /0C ------- T a T 0 h FE Mixed Formulation 2UC Uncoupled Piezoelectric Analysis 3C Coupled Piezoelectric Analysis 1MF 2 a/h 5 10 15 20 25 30 35 40 60 80 100 1000 Analytical UC2 1.457 1.811 1.898 1.930 1.946 1.954 1.960 1.963 1.969 1.971 1.972 1.973 MF1 UC2 1.457 1.813 1.899 1.932 1.947 1.956 1.961 1.964 1.970 1.972 1.973 1.975 C3 1.502 1.869 1.958 1.992 2.008 2.016 2.022 2.025 2.031 2.034 2.035 2.037 T MF1 a T 0 h FE Mixed Formulation 2UC Uncoupled Piezoelectric Analysis 3C Coupled Piezoelectric Analysis 1MF 2 a/h 5 10 15 20 25 30 35 40 60 80 100 1000 UC2 4.208 5.475 5.799 5.922 5.981 6.013 6.033 6.045 6.069 6.077 6.081 6.088 C3 -6.584 -9.010 -9.675 -9.931 -10.055 -10.123 -10.165 -10.192 -10.242 -10.260 -10.268 -10.283 Results have demonstrated the impact of piezoelectric coupling on the buckling load magnitudes by calculating the buckling loads that include the piezoelectric effect (coupled) and exclude the effects (uncoupled). As would be expected, the relatively weak PVDF layers do not significantly alter the calculated results when considering piezoelectric coupling. The net increase is about 3% for the thermal loaded ten-layer laminate (PVDF/0/90/0/90)s. However, adding the relatively stiff PZT as the top and bottom layers produces significant differences between the uncoupled and coupled results. A reversal of stress is required to cause buckling in the coupled analyses due to the sign on the pyroelectric constant for the PZT material. Neglecting the sign change, an increase of approximately 67% is observed in the absolute buckling load magnitude for the coupled analysis compared with the uncoupled analysis. Six layer laminate: (PZT5/0/90)s Simply supported a = b = 0.2m h = 0.001 m