Aeroelastic analysis of CNT reinforced functionally graded laminated composite plates with damage under subsonic regime

Swain, Prasant Kumar; Adhikari, Balakrishna; Maiti, Dipak Kumar; Singh, B.N.

doi:10.1016/j.compstruct.2019.110916

Cited by 27 publications

(3 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The influences of different parameters including the volume fraction, aspect ratio and in‐plane loads on the flutter stability of the panels were discussed. Swain et al 227 used the FEM to analyze the aeroelastic characteristics of the FGM carbon nanotube‐reinforced composite laminated panels with damage in subsonic airflow. The flutter velocities of the panel under different fiber volume fractions and damage locations were calculated and analyzed.…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

View full text Add to dashboard Cite

Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

show abstract

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

View full text Add to dashboard Cite

show abstract

“…Moreover, increasing the thickness resulted to decrease in aeroelastic stability. Swain et al [198] performed the aeroelastic studies of FG-CNTRC laminated plates containing damages under the subsonic regime. The authors found that the flutter properties of the structure were significantly affected by the stacking sequence of layers, and the angle-ply laminate was a better choice than the cross-ply one.…”

Section: Buckling and Postbucklingmentioning

confidence: 99%

The recent progress of functionally graded CNT reinforced composites and structures

Liew

Pan

Zhang

2019

Sci. China Phys. Mech. Astron.

152

View full text Add to dashboard Cite

In the last decade, the functionally graded carbon nanotube reinforced composites (FG-CNTRCs) have attracted considerable interest due to their excellent mechanical properties, and the structures made of FG-CNTRCs have found broad potential applications in aerospace, civil and ocean engineering, automotive industry, and smart structures. Here we review the literature regarding the mechanical analysis of bulk CNTR nanocomposites and FG-CNTRC structures, aiming to provide a clear picture of the mechanical modeling and properties of FG-CNTRCs as well as their composite structures. The review is organized as follows: (1) a brief introduction to the functionally graded materials (FGM), CNTRCs and FG-CNTRCs; (2) a literature review of the mechanical modeling methodologies and properties of bulk CNTRCs; (3) a detailed discussion on the mechanical behaviors of FG-CNTRCs; and (4) conclusions together with a suggestion of future research trends. functionally graded carbon nanotube reinforced composite, modeling methodology, mechanical properties, beam, plate, shell

show abstract

“…The effective material properties of each layer were calculated via the Halpin-Tsai micromechanics model. A functionally graded (FG) composite plate reinforced with carbon nanotubes was simulated by Swain et al, 29 and the results show that the damage significantly affects the dynamic and aeroelastic response. FG plates are considered to showcase the extension-bending coupling effect in another study.…”

Section: Introductionmentioning

confidence: 99%

Uncertain buckling characteristics of thermally loaded and internally defected variable fiber spacing composite laminates

Chandrakar,

Sharma,

Maiti

2024

Journal of Composite Materials

View full text Add to dashboard Cite

The present investigation underscores the efficacy of laminated plates with variable fiber spacing (VFS) in the context of internal defects. The study involves the evaluation of the variability in buckling strength when faced with multiple tiers of damage; this is achieved through the implementation of an improved first-order shear deformation theory (IFSDT) within a finite element (FE) framework. Various types of fiber distribution (DT) are being examined to evaluate the effects of damage situated at both corner and mid locations. The application of a radial basis function network (RBFN)-based surrogate model demonstrates its potential as a feasible alternative to the computationally demanding Monte-Carlo simulations (MCS) for investigating the stochastic nature of buckling; the developed surrogate model requires reduced input sampling data to quantify buckling uncertainty. This study examines the stochastic nature of different material characteristics and observed that the uncertainty in the buckling response decreases with the increased damage severity. The assessment of the probability of failure is conducted subsequently. Following this, the damage ratios are influenced by randomness, leading to the pattern that an increased damage ratio corresponds to a more pronounced deviation in buckling uncertainty.

show abstract

Aeroelastic analysis of CNT reinforced functionally graded laminated composite plates with damage under subsonic regime

Cited by 27 publications

References 21 publications

Aeroelastic analysis and flutter control of wings and panels: A review

Aeroelastic analysis and flutter control of wings and panels: A review

The recent progress of functionally graded CNT reinforced composites and structures

Uncertain buckling characteristics of thermally loaded and internally defected variable fiber spacing composite laminates

Contact Info

Product

Resources

About