Delamination Growth Using Cohesive Zone Model for Adhesive Bonding Under Compression

Islam, Mohammad Majharul; Kapania, Rakesh K.

doi:10.1007/978-1-4614-0222-0_63

Cited by 2 publications

(2 citation statements)

References 27 publications

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“…[15][16][17] Recently, Marc instead of Abaqus, is being used in EBF3PanelOpt for damage tolerance calculation. [18][19][20][21][22][23][24][25] Our well established development of curvilinear blade-stiffened panel framework is discussed. [26][27][28][29][30][31][32][33][34] Currently, EBF3PanelOpt framework allows the user to perform multi-objective design optimization of flat multi-sided panels with straight/curved edges having curvilinear, blade and 'T' stiffeners.…”

Section: Ebf3panelopt Frameworkmentioning

confidence: 99%

EBF3PanelOpt: A Computational Design Environment for Panels Fabricated by Additive Manufacturing

Kapania

Mulani

Tamijani

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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We have developed an optimization framework, EBF3PanelOpt to design stiffened panels with curvilinear stiffeners. The curvilinear stiffening tries to utilize the larger design space created by such additive manufacturing techniques like Electron Beam Free Form Fabrication, Friction Stir Welding, and Selective Laser Sintering. Structural loads of future aerospace vehicles may not be well characterized using our knowledge-based databases, so medium-fidelity modeling capabilities of software, Msc.Patran (geometry and meshing), and Msc.Nastran (finite element analysis) are integrated in EBF3PanelOpt. The EBF3PanelOpt minimizes the mass of the stiffened panel with the constraints on buckling, von Mises stress and crippling of the stiffeners. The panel/stiffener geometry is parameterized using design variables that include variables for orientation and shape of the stiffeners, the thicknesses and height of the stiffeners, and the plate thickness. The plate can have uniform thickness or non-uniform thicknesses for the pockets created by the stiffeners. The EBF3PanelOpt is enhanced to have curvilinear T stiffeners with or without axial loads in addition to loads through plate Both the vibro-acoustic and structural optimization are supported using multi-objective optimization in EBF3PanelOpt. To enhance the computational efficiency, an improved surrogate model built using artificial neural network and kriging is utilized. To quantify the uncertainty in the design variables or parameters, reliability analysis is supported in EBF3PanelOpt.

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Section: Ebf3panelopt Frameworkmentioning

confidence: 99%

EBF3PanelOpt: A Computational Design Environment for Panels Fabricated by Additive Manufacturing

Kapania

Mulani

Tamijani

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…[14,15]) and changes the dynamic properties significantly, and therefore has a major influence on the lifetime of the structure. The delamination behavior of composite materials is characterized by different specimens for mode-I [16][17][18][19][20][21][22][23], mode-II [24][25][26], mixed-mode I/II [27][28][29][30][31][32][33][34][35][36][37], mode-III [38][39][40][41][42][43][44][45][46][47][48], mixed-mode I/III [49] mixed-mode II/III [42,[50][51][52][53][54][55][56][57][58][59] and mixed-mode I/II/III [60][61]…”

Section: Introductionmentioning

confidence: 99%

Antiplane–inplane shear mode delamination between two second-order shear deformable composite plates

Szekrényes

2016

Mathematics and Mechanics of Solids

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The second-order laminated plate theory is utilized in this work to analyze orthotropic composite plates with asymmetric delamination. First, a displacement field satisfying the system of exact kinematic conditions is presented by developing a double-plate system in the uncracked plate portion. The basic equations of linear elasticity and Hamilton's principle are utilized to derive the system of equilibrium and governing equations. As an example, a delaminated simply supported plate is analyzed using Lévy plate formulation and the state-space model by varying the position of the delamination along the plate thickness. The displacements, strains, stresses and the J-integral are calculated by the plate theory solution and compared with those by linear finite-element calculations. The comparison of the numerical and analytical results shows that the second-order plate theory captures very well the mechanical fields. However, if the delamination is separated by only a relatively thin layer from the plate boundary surface, then the second-order plate theory approximates badly the stress resultants and so the mode-II and mode-III J-integrals and thus leads to erroneous results.

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Delamination Growth Using Cohesive Zone Model for Adhesive Bonding Under Compression

Cited by 2 publications

References 27 publications

EBF3PanelOpt: A Computational Design Environment for Panels Fabricated by Additive Manufacturing

EBF3PanelOpt: A Computational Design Environment for Panels Fabricated by Additive Manufacturing

Antiplane–inplane shear mode delamination between two second-order shear deformable composite plates

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