Dynamic buckling analysis of delaminated composite plates using semi-analytical finite strip method

Ovesy, H.R.; Totounferoush, Amin; Ghannadpour, S.A.M.

doi:10.1016/j.jsv.2015.01.003

Cited by 34 publications

(14 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…and (Ovesy, Ghannadpour, & Zia-Dehkordi), have used exact finite strip method to predict buckling analysis of moderately thick composite laminate. In their further work, Ghannadpour (Ovesy, Totounferoush, & Ghannadpour, 2015;Ghannadpour & Ovesy, 2009) and Ghannadpour et al (2014) have presented de-lamination and dynamic buckling of composite laminate using semi analytical finite strip and exact finite strip methods. Other authors (Oktay & Sal, 2015, 2016Oktay & Sultan, 2013) have also explained active and passive control and helicopter rotor blade morphing for energy efficiency.…”

Section: Introductionmentioning

confidence: 99%

Progressive Failure Analysis of Helicopter Rotor Blade Under Aeroelastic Loading

et al. 2020

View full text Add to dashboard Cite

Unlike metal structure, composite structures don’t give any clue till the fatal final collapse. The problem is more complicated when applied load on the structure is aeroelastic in nature. Under such loading, composite laminate experiences stresses. The first layer failure happens when stresses in the weakest ply exceed the allowable strength of the laminate. This initial layer-based failure changes overall material characteristics. It is important now to degrade the composite laminate characteristics for the subsequent failure prediction. The constitutive relations are required to be updated by the reduction in stiffness. The rest of the undamaged laminates continue to take the load till the updated strength is reached. In the present work, layer wise progressive failure analysis under aeroelastic loading has been performed by the inclusion of different failure criteria which allow for the identification of the location of the failure. ANSYS APDL environment has been used to model geometry of helicopter rotor. Under the loading conditions, stresses are calculated in the blade. Using stress tensor and failure criteria, failure location and modes have been predicted. It has been found that failure starts at higher speeds and failure starts from the root chord and tend towards the tip chord.

show abstract

Section: Introductionmentioning

confidence: 99%

Progressive Failure Analysis of Helicopter Rotor Blade Under Aeroelastic Loading

et al. 2020

View full text Add to dashboard Cite

show abstract

“…Also, the transverse shape function of strip element is considered as polynomial function. Buckling load of laminated plates without any cutout subjected to different load cases was evaluated using semi-analytical FSM (Yao et al 2015, Ovesy et al 2015, Dawe et al 1995, Ovesy and Fazilati 2012b. Semi-analytical FSM is very useful and efficient for buckling analysis of laminated plate when the boundary conditions of both ends of strip elements are simply supported (Wang et al 1998, Dawe and Wang 1994, Cheung and Tham 1997.…”

Section: Introductionmentioning

confidence: 99%

A simple spline finite strip for buckling analysis of composite cylindrical panel with cutout

Poorveis

Khajehdezfuly

Moradi

et al. 2019

Lat. Am. j. solids struct.

View full text Add to dashboard Cite

In this study, a new sub-parametric strip element is developed to simulate the axially loaded composite cylindrical panel with arbitrary cutout. For this purpose, a code called SSFSM is developed in FORTRAN to analyze the buckling of panels. The first order shear deformation theory is used to form the straindisplacement relations. Spline and Lagrangian functions are used to derive element shape functions in the longitudinal and transverse directions, respectively. The computational cost of the SSFSM is decreased dramatically, as mapping functions of the strip element are very simple. The results obtained from the SSFSM are compared with those of the literature and the results obtained by ABAQUS to show the validity of the proposed approach. A parametric study is performed to show the capability of the SSFSM in calculating the panel buckling load. Results indicate that increasing the panel thickness and panel central angles cause an increase in panel buckling load. The cutout shape is an important factor influencing the panel buckling load. For instance, when the angle between the direction of big chord of the elliptical cutout and compressive load direction are 0 and 90 degrees, the panel buckling load reaches its minimum and maximum magnitude, respectively.

show abstract

“…Mouhat et al (2015) determined the dynamic buckling of stiffened panels. Ovesy et al (2015) analyzed the dynamic buckling analysis of delaminated composite plates using semi-analytical finite strip method. They studied the effect of through-the-width delimitation on dynamic buckling behavior of a composite plate by implementing semianalytical finite strip method.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear size-dependent dynamic buckling analysis of embedded micro cylindrical shells reinforced with agglomerated CNTs using strain gradient theory

2017

View full text Add to dashboard Cite

This article presents an analysis on the nonlinear dynamic buckling of a micro cylindrical shell reinforced by carbon nanotubes (CNTs) with considering agglomeration effects. The structure is surrounded by an elastic medium and is subjected to magnetic field and harmonic mechanical load. Mindlin theory is employed to model the structure and the modified strain gradient theory (SGT) is also used to capture the size effect. Mori-Tanaka approach is used to estimate the equivalent material properties of the nanocomposite cylindrical shell and consider the CNTs agglomeration effect. The motion equations are derived using Hamilton's principle and the differential quadrature method (DQM) along with Bolotin method is employed to solve them for obtaining the dynamic stability region. The effect of different parameters including magnetic field, CNTs volume percent and agglomeration effect, boundary conditions, elastic medium, size effect and length to thickness ratio on the dynamic buckling behavior of the system is studied. The results indicate that considering elastic medium, magnetic field and size effects, increases the stiffness of the structure and so, the dynamic instability region occurs at higher frequency while considering the CNTs agglomeration effect has inverse effect. Also, by increasing the CNTs volume percent and considering the clamped-clamped boundary condition, the dynamic behavior of the system improves.

show abstract

Dynamic buckling analysis of delaminated composite plates using semi-analytical finite strip method

Cited by 34 publications

References 17 publications

Progressive Failure Analysis of Helicopter Rotor Blade Under Aeroelastic Loading

Progressive Failure Analysis of Helicopter Rotor Blade Under Aeroelastic Loading

A simple spline finite strip for buckling analysis of composite cylindrical panel with cutout

Nonlinear size-dependent dynamic buckling analysis of embedded micro cylindrical shells reinforced with agglomerated CNTs using strain gradient theory

Contact Info

Product

Resources

About