An assessment of shell theories for buckling ofcircular cylindrical laminated composite panels loaded inaxial compression

Jaunky, Navin; Knight, Norman F.

doi:10.1016/s0020-7683(98)00177-2

Cited by 57 publications

(18 citation statements)

References 14 publications

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“…Note that the buckling behavior develops from the bottom of the VACNT arrays. [32][33][34][35][36] Generally, a cylindrical shell under a uniform axial compression will have many axissymmetrical buckling waves in the longitudinal direction due to the surrounding constraint force from its continuous shell structure, and the amplitudes of buckling waves will gradually decrease upwards, and eventually go to zero. 31 As seen in Fig.…”

Section: Buckling Behavior Characterization In Quasi-static Compressionsmentioning

confidence: 99%

Understanding the nanoscale local buckling behavior of vertically aligned MWCNT arrays with van der Waals interactions

Kim

Wei

et al. 2015

Nanoscale

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The local buckling behavior of vertically aligned carbon nanotubes (VACNTs) has been investigated and interpreted in the view of a collective nanotube response by taking van der Waals interactions into account. To the best of our knowledge, this is the first report on the case of collective VACNT behavior regarding van der Waals force among nanotubes as a lateral support effect during the buckling process. The local buckling propagation and development of VACNTs were experimentally observed and theoretically analyzed by employing finite element modeling with lateral support from van der Waals interactions among nanotubes. Both experimental and theoretical analyses show that VACNTs buckled in the bottom region with many short waves and almost identical wavelengths, indicating a high mode buckling. Furthermore, the propagation and development mechanism of buckling waves follow the wave damping effect.

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Section: Buckling Behavior Characterization In Quasi-static Compressionsmentioning

confidence: 99%

Understanding the nanoscale local buckling behavior of vertically aligned MWCNT arrays with van der Waals interactions

Kim

Wei

et al. 2015

Nanoscale

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“…There has been a reasonable amount of work on buckling and post-buckling behaviour of cylindrical shells and panels [12][13][14][15][16][17][18]. Due to its mathematical complexity and modelling, very limited information on the subject of delamination buckling of cylindrical shells and panels is currently available [19][20][21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

Efficient modelling of delamination buckling in composite cylindrical shells under axial compression

Tafreshi

2004

Composite Structures

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Composite cylindrical shells and panels are widely used in aerospace structures. These are often subjected to defects and damage from both in-service and manufacturing events.Delamination is the most important of these defects. This paper deals with the computational modelling of delamination in isotropic and laminated composite cylindrical shells. The use of three-dimensional finite elements for predicting the delamination buckling of these structures is computationally expensive. Here combined double-layer and single-layer of shell elements are employed to study the effect of delamination on the global load-carrying capacity of such systems under axial compressive load. It is shown that through-the-thickness delamination can be modelled and analysed effectively without requiring a great deal of computing time and memory. A parametric study is carried out to study the influence of the delamination size, orientation and through-the-width position of a series of laminated cylinders. The effect of material properties is also investigated. Some of the results are compared with the corresponding analytical results. It is shown that ignoring the contact between the delaminated layers can result in wrong estimations of the critical buckling loads in cylindrical shells under compressive load.

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“…The results are compared against solutions available in the literature. 35,36 Once the results are reproduced successfully there by validating the code, it can be directly employed to analyze the grid-stiffened models for stability. Results from parametric studies on stability and strength evaluations are not presented in this report.…”

Section: Bending Instabilitymentioning

confidence: 99%

Advanced Grid-Stiffened Composite Shells for Heavy-Lift Helicopter Blade Spars

Nampy

Smith

Bakis

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Heavy-lift helicopter blades are estimated to be large and heavy (upwards of 360 kg per blade) when the spars are constructed as monocoque structures. It is proposed to replace these conventional spar designs with lighter grid-stiffened composite shells. Composite stiffened shells have been known to provide superior strength to weight ratio and damage tolerance with a great potential to reduce weight. The design space for grid-stiffened rotor blade spar structures is new and the behavior of these structures under axial, bending, and torsion loads needs to be accurately predicted. The overall objective of the present research is to develop and integrate the necessary design analysis tools to conduct a feasibility study in employing grid-stiffened shells for heavy-lift rotor blade spars. A new analytical model was developed to accurately model various grid stiffening configurations and the results were compared with current state-of-the-art analysis, finite element analysis (FEA) and in certain cases, experiments. Parametric studies of grid density, stiffener angle, and aspect ratio of stiffener cross section showed excellent correlation (within 5-7%) between FEA and the new model. On the other hand, differences in the range of 26-60% between current state-of-theart analysis and FEA were seen for certain designs. A preliminary design study was conducted to evaluate the weight saving potential of a simple cylindrical grid-stiffened rotor blade spar structure compared to a baseline monocoque design. Discretized design variables were stiffener density, stiffener angle, shell laminate, and stiffener aspect ratio and the design constraints were stiffness, material strength, and stability. For the range of the design variables explored, a weight saving of 9% compared to the baseline was obtained without violating any of the design constraints. Nomenclature ̅ = non-dimensional shear correction parameters δ i = beam end deflections ε i , γ ij = in-plane normal strains, shear strains θ = stiffener orientation angle κ x , κ y , κ xy = curvatures a ij , b ij , d ij = equivalent stiffness compliance coefficients (i, j =1,2,6) b s , h s = width, depth of the stiffener cross section d 0 , d 90 , d θ = spacing between longitudinal, transverse, and angle stiffeners EI, EA, GJ, = bending, axial, torsion stiffness GA = shear stiffness of the beam k bc = local and global stiffness matrices of a beam-column L 0 , L 90 , L θ = length of the longitudinal, transverse, and angle stiffeners m i , n i = plate or shell moments, forces per unit width (i= x,y,ψ,z) R g , R s = radius of the grid layer, shell at mid-plane

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An assessment of shell theories for buckling ofcircular cylindrical laminated composite panels loaded inaxial compression

Cited by 57 publications

References 14 publications

Understanding the nanoscale local buckling behavior of vertically aligned MWCNT arrays with van der Waals interactions

Understanding the nanoscale local buckling behavior of vertically aligned MWCNT arrays with van der Waals interactions

Efficient modelling of delamination buckling in composite cylindrical shells under axial compression

Advanced Grid-Stiffened Composite Shells for Heavy-Lift Helicopter Blade Spars

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