Progressive failure analysis of tow-placed, variable-stiffness composite panels

By Cláudio S. Lopes, Pedro P. Camanho, Zafer Gürdal, Brian F. Tatting. 2007

190 citations recorded by the source corpus.

Subfields: Civil and Structural Engineering, Mechanics of Materials

View Paper: https://www.semanticscholar.org/paper/8a83f6bae4bf82f43f97d97c43ed199c2475e06a

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In Civil and Structural Engineering

In Mechanics of Materials

Citations in the corpus

Multi-objective optimization of curvilinear fiber shapes for laminated composite plates by using NSGA-II (2013, background): “[1, 7-11] defined fiber shapes by the linear changes in fiber orientation angles to require locally desired material properties for plates and conical shells, and confirmed that such structures have superior mechanical properties compared with homogenous plates by research including experimental and”
Optimization of a composite cylinder under bending by tailoring stiffness properties in circumferential direction (2010, background): “Table 1: AS4/8773 Mechanical properties [13]”
Initial post-buckling of variable-stiffness curved panels (2014, methodology): “In addition to buckling optimisation, it has also been shown that VAT laminates can be used to delay first ply failure of plates under compression (Lopes et al., 2007); tune the fundamental frequency of shells (Blom et al., 2008) and increase global structural stiffness of cylindrical shells (Wu,…”
Tailoring for strength of composite steered-fibre panels with cutouts (2010, result): “Numerical investigations in which thermal stresses were taken into account [13,16,17] achieved good correlation between simulated and experimental results.”
A review on design for manufacture of variable stiffness composite laminates (2016, background): “In many studies, the ply thickness is supposed to be constant for the optimisation of fibre angle orientations.(6,7,23,24) However, the buckling load for the physical specimens (plates manufactured with dry fibres) may not match the results from finite element analysis (FEA), when the thickness is c”
Defect layer method to capture effect of gaps and overlaps in variable stiffness laminates made by Automated Fiber Placement (2013, background): “It was found that introducing gaps reduces the laminate strength [10], and the average strain [11], while the overlaps can cause an increase in strength of maximum 13% compared to a non-defective laminate [12], and 93% improvement in buckling load of a panel compared to a straight fiber case [13].”
Optimum stacking sequence design of composite materials Part II: Variable stiffness design (2010, background): “constant stiffness design have been demonstrated for different properties such as buckling capacity [38,91,1], elastic behaviour [28], stiffness [89], compressive buckling and first-plyfailure [63], maximum fundamental frequency [12] and postbuckling progressive damage [62].”
Progressive Failure Analysis of Composites (2008, background): “For example, in Figure 3, the post-peak response is scaled as a function of the element size to keep the computed energy dissipation independent of the element size, and equal to the material fracture energy (a process called ‘energy regularization’ [107]).”
A Theoretical Model to Study the Influence of Tow-drop Areas on the Stiffness and Strength of Variable-stiffness Laminates (2009, methodology): “This concept is shared by the research of Tatting [2], Gürdal [4], Jegley [5], Wu [6,7], Blom [10,11], and Lopes [8,9].”
Optimization of variable stiffness composites with embedded defects induced by Automated Fiber Placement (2014, result): “[17] further extended the previous results to account for the progressive damage behavior and final structural failure.”