Active flutter control of delaminated composite plate using active fiber composite patches

Swain, Prasant Kumar; Tiwari, Pratik; Maiti, Dipak Kumar; Singh, B. N.; Maity, Damodar

doi:10.1016/j.tws.2021.108856

Cited by 11 publications

(2 citation statements)

References 41 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Thus, it may affects the stiffness of the laminates and hence leads to the variation of few natural frequencies to a larger extent. For the verification of the aeroelastic response with 12 × 12 mesh size, the flutter characteristics of laminated plates of various lamination sequences are computed and compared with the experimental, 26 and numerical solutions 65,66 as listed in Table 3. Further, the efficacy of RBFN-based surrogate model is evaluated by comparing the results with the author’s own published polynomial neural network (PNN) based stochastic frequency analysis of a three-layered VAT laminated plate as given in Table 4.…”

Section: Resultsmentioning

confidence: 99%

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

Sharma

Swain

Maiti

2023

Journal of Composite Materials

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Section: Resultsmentioning

confidence: 99%

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

Sharma

Swain

Maiti

2023

Journal of Composite Materials

Self Cite

View full text Add to dashboard Cite

show abstract

“…A square VAT smart laminated plate, consisting of the substrate with 10 layers of VAT laminae ð½hPihÀ45= À 45i, ð±hθ 1 =45iÞ 2 s Þ integrated with piezoelectric patches denoted as P, is considered. The top and bottom layers of the substrate are taken as straight fibers Experimental 24 28 -Analytical 24 29.2 -Higher order 52 26.2 25.2 Degenerated 72 29. Concerning Figure 6, the coordinates of the various locations of delamination considered for analysis, are given in Table 8.…”

Section: Numerical Resultsmentioning

confidence: 99%

Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Sharma

Swain

Maiti

2022

Journal of Composite Materials

Self Cite

View full text Add to dashboard Cite

The free vibration and aeroelastic analysis of variable angle tow (VAT) laminated composite plate bonded with discrete piezoelectric patches are considered for investigation. A finite element (FE) model is developed using eight noded isoparametric elements to study the impact of delamination size and location on the dynamic response of smart VAT laminated plates. For aeroelastic analysis, the FE model is coupled with MSC. Nastran through Direct Matrix Abstraction Program (DMAP) and the structural parameters obtained with the FE model are supplied to MSC. Nastran solver to generate aerodynamic force matrix using Doublet Lattice Method (DLM). Various parametric studies are performed to find the most critical location of the delamination that severely affects vibration and flutter characteristics. The results showed that the delamination near the leading edge which faces free stream wind is found to be the most critical for the dynamic aeroelastic failure of structures. Further, the most effective location of the piezoelectric patches is identified to enhance the aeroelastic boundary of smart delaminated VAT composite plates using active displacement and velocity feedback gains.

show abstract

Flutter stability analysis of composite corrugated plates in supersonic flow

Zheng,

Wang,

Huang

et al. 2024

Arch Appl Mech

View full text Add to dashboard Cite

Active flutter control of delaminated composite plate using active fiber composite patches

Cited by 11 publications

References 41 publications

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

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

Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Flutter stability analysis of composite corrugated plates in supersonic flow

Contact Info

Product

Resources

About