Uncertainty quantification in free vibration and aeroelastic response of variable angle tow laminated composite plate

Abstract

The influence of uncertainty in material properties on free vibration and aeroelastic response of variable angle tow (VAT) laminated plates is presented in this work. Free vibration analysis is conducted by a finite element model based on third-order shear deformation theory. The FE model is further coupled with MSC. Nastran to carry out aeroelastic analysis of VAT laminates in the subsonic regime. MSC. Nastran helps to extract the aerodynamic influence coefficient matrix at discrete values of reduced frequencies using Doublet Lattice Method. The accuracy and adaptability of the highly efficient radial basis neural network (RBFN) based surrogate model developed for uncertainty analysis are checked by comparing the result with that of the Monte Carlo simulation. Stochastic analysis of natural frequencies and flutter characteristics of VAT laminates are conducted through various parametric studies. Variance-based sensitivity analysis is used to calculate the contribution of individual material properties to the free vibration and aeroelastic response of VAT laminates. Further, the influence of the highly sensitive properties on the structural failure probability is estimated. This research can be leveraged to predict the probability of failure of the structure at different levels of material uncertainty present in it.

Review of elasto-static models for three-dimensional analysis of thick-walled anisotropic tubes

“…For this purpose, the recent studies by Sharma et al 17 on stochastic frequency analysis of composite plates with curvilinear fiber and Sharma et al 18 on stochastic aeroelastic analysis of laminated composite plates with variable fiber spacing can be considered. The aeroelastic analysis of plates made of lightweight materials with material uncertainty is described in Swain et al 19 Methods for quantifying the uncertainty in the free vibration and aeroelastic response of an angularly adjustable laminates are given in Sharma et al 20 The aeroelastic control of delaminated angle tow laminated composite plates using piezoelectric patches is given in Sharma et al 21 The use of piezoelectric patches is also described in the study by Sharma et al 22 to investigate active flutter suppression of damaged variable stiffness laminated rectangular plate. Further investigations in the field of free vibration can be found in Sharma et al, 23 who studied the static and free vibration analysis of smart variable stiffness composite plates with delaminations.…”

“…Further investigations in the field of free vibration can be found in Sharma et al, 23 who studied the static and free vibration analysis of smart variable stiffness composite plates with delaminations. On the other hand, in Sharma et al 20 a study is made for uncertainty quantification in free vibration and aeroelastic response of variable angle tow laminated composite plates. Uncertainty quantification under thermal loading in buckling strength of variable stiffness laminated composite plates can be found in Sharma et al 24 For functionally graded sandwich plates using layerwise theory, a vibration and certainty analysis has been carried out in Sharma et al 25…”