Forced vibration analysis of hybrid laminated composite cylindrical shells reinforced with shape memory alloy fibers in thermal environment

Due to aerodynamic heating, temperature of aircrafts and rockets skin increases significantly, leading to reduced flight performance due to forced vibration. Shape Memory Alloys (SMAs) can be used to solve this problem due to their thermo-mechanical properties such as generating force and recovering large strains when exposed to heat. In this study, response of forced vibration in composite cylindrical shells reinforced with Nitinol SMA fibers is investigated. Variation in recovery stress and Young's modulus with temperature in SMA fibers is modeled using the Brinson's constitutive model. Equations of motion are derived based on the classical shell theory using the von Kármán nonlinear geometric strain-displacement relations with the Love's first approximation, applying Hamilton's principle. The governing equations are solved using the generalized differential quadrature method in the longitudinal direction. The effect of pre-strain and volume fraction of SMA fibers on the response of forced vibration in composite cylindrical shells reinforced with SMA fibers are investigated under varying temperatures and different boundary conditions. Numerical results indicate that appropriate use of pre-strained SMA fibers leads to an increase in the resonant frequency and a reduction in the amplitude of forced vibration.