Abstract
A model is presented for functionally-graded material (FGM), thick, circular cylindrical shells under an unsteady supersonic flow, following first-order shear deformation theory (FSDT) with varied shear correction coefficients. Some interesting vibration results of the dynamics are calculated by using the generalized differential quadrature (GDQ) method. The varied shear correction coefficients are usually functions of FGM total thickness, power law index, and environment temperature. Two parametric effects of the environmental temperature and FGM power law index on the thermal stress and center deflection are also presented. The novelty of the paper is that the maximum flutter value of the center deflection amplitude can be predicted and occurs at a high frequency of applied heat flux for a supersonic air flow.
Highlights
There are some aero-elastic flutter and vibration research articles of beams, shells, and plates.Samadpour et al [1] investigated the supersonic flutter of composite beams with shape memory alloys (SMA) under thermal and aerodynamic loads, the aero-thermal flutter characteristics can be enhanced by embedding with SMA fibers in the laminated beam
Li and Narita [3] presented the optimal design in flutter analysis of supersonic flow over doubly-curved shallow laminated shells by using MATLAB code, the optimal fiber orientation angles are obtained
Ramos et al [11] used a unified new trigonometric displacement field expansion under Carrera unified formulation (CUF) to investigate the static problem of laminated plates under thermal loads, the stress results including the effects of shear deformation are obtained and compared
Summary
There are some aero-elastic flutter and vibration research articles of beams, shells, and plates. Ramos et al [11] used a unified new trigonometric displacement field expansion under CUF to investigate the static problem of laminated plates under thermal loads, the stress results including the effects of shear deformation are obtained and compared. The non-linear coefficient term of the displacement field, e.g., TSDT, can be used to derive the equations of motion for thermal vibration of FGM when using a higher-order shell theory It is interesting in the linear FSDT with the varied value effects of shear correction coefficients on air flow over the outer surface of FGM thick circular cylindrical shells under four supported edges, that the thermal stresses and center deflection of GDQ computational results for supersonic air flow are obtained. Circular cylindrical cylindrical shells used in the material body ofmight the morphing aircraft to FGM suppress shells and used in the body of the morphing aircraft to suppress flutter
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