Abstract
Thermal eigenvalue characteristics of layered composite panels are obtained numerically utilizing the higher-order deformation kinematics, and the exactness of the solution has been verified with in-house experimenta-tion. The laminated panel configuration bonded with and without shape memory alloy (SMA) fibres is modelled mathematical using the equivalent single-layer theory and third-order displacement kinematics. The functional composite structural properties under the elevated temperature are introduced in the current model for the necessary activation via the marching technique (to include the material nonlinearity due to SMA). The struc-tural governing equation of motion is obtained by Hamilton's principle and discretized using the isoperimetric finite element steps. Further, the computational modal responses are predicted using the in-house MATLAB computer code. The numerical solutions' accuracy and stability have been compared with the earlier research data, including a few experimental verifications of thermal/ambient frequencies for laminated composite without SMA fibre. Further, a few numerical experiments have been carried out to show the significance of SMA fibre on the frequency responses of the parent structure, including temperature-dependent properties. The structural/material inputs, i.e., geometrical shapes, properties, geometrical parameters, and SMA-relevant data (volume fractions, VSMA; pre-strain, and recovery stress), are utilized for the computation of new results. The final insights have shown a significant improvement of frequency values, i.e., 4 %, 6 %, and 8 % of the laminated composite, while the volume fractions of SMA increase V-SMA = 10 %, 15 % and 20 % for 3 % prestrain, respectively.