In the present work, an analytical investigation is introduced to determine the aeroelastic behavior of unswept, rectangular wings simulated by cantilevered composite plates using energy formulation and incompressible aerodynamic theory. Modified higher order shear deformation theory is used in the structural formulation. Doublet point method is used to solve the subsonic unsteady flow over the proposed rectangular wing. The flutter and divergence velocities are obtained using U-g method, which are validated by the analytical, finite element, wind tunnel test results available in the literature. The effect of composite fiber orientation on natural frequency, flutter and divergence speeds is discussed.

The main objective of this research is to study the capability of piezoelectric (PZT) self-sensing actuators to suppress the transonic wing box flutter, which is a flow-structure interaction phenomenon. The unsteady general frequency modified transonic small disturbance (TSD) equation is used to model the transonic flow about the wing. The wing box structure and piezoelectric actuators are modeled using the equivalent plate method, which is based on the first order shear deformation plate theory (FSDPT). The piezoelectric actuators are bonded to the skin. The optimal electromechanical coupling conditions between the piezoelectric actuators and the wing are collected from previous work. Three main different control strategies, a linear quadratic Gaussian (LQG) which combines the linear quadratic regulator (LQR) with the Kalman filter estimator (KFE), an optimal static output feedback (SOF), and a classic feedback controller (CFC), are studied and compared. The optimum actuator and sensor locations are determined using the norm of feedback control gains (NFCG) and norm of Kalman filter estimator gains (NKFEG) respectively. A genetic algorithm (GA) optimization technique is used to calculate the controller and estimator parameters to achieve a target response.

In the present work, static deformation, dynamic characteristic, and time response of laminated composite plates with surface-bonded shape-memory alloy (SMA) sheets are modeled. A modified higher order shear deformation theory with Ritz method is utilized. The energy balance equations are used to formulate the nonlinear heat transfer governing equations. The time response of the SMA/elastomer plate and the deflection as well as dynamic characteristics before and after activation of the SMA is computed. A Mathematica code is developed to analyze different plate problems. Parametric studies are performed for proposed structure system to demonstrate the effect of thickness ratio, aspect ratio, material properties, thermal expansion coefficient, electric input power, and thickness of SMA sheet on the transverse deflections, natural frequencies, and response time of the SMA layer. The obtained results are compared to the available studies solved by different theories.

A Laminated composite plate with embedded shape memory alloy wires are modeled and analyzed based on the modified higher-order shear deformation theory. The Hamilton's principle in conjunction with Brinson's constitutive model is used to obtain the three-dimensional governing equations. The Ritz solution technique is used to get the static response as well as the dynamic characteristics of the proposed plates. A simply-supported and cantilevered plates subjected to mechanical loads are used in the analysis with a prepared program using Mathematica langue. Parametric studies are conducted to demonstrate the effect of plate dimensions, fiber orientation angle and volume fraction of composite fibers and shape memory alloy wires, on the activated plate natural frequencies. The obtained results are compared to the available studies solved by different theories and found convenient.