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UID:0-539@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20150311T163000

DTEND;TZID=Asia/Jerusalem:20150311T173000

DTSTAMP:20230603T193651Z

URL:https://aerospace.technion.ac.il/events/probabilistic-analysis-for-int
 erface-fracture-and-delamination-failure-of-composites/

SUMMARY:Statistical Analysis for Interface Fracture and Delamination Failur
 e of Composites
DESCRIPTION:Lecturer:Prof. Leslie Banks-Sills\n Faculty:The Dreszer Fractur
 e Mechanics Lab\, School of Mechanical Eng.\, Tel Aviv University\n Instit
 ute:\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n 
 Zoom: \n Abstract: \n Details: \n A methodology for measuring the interfac
 e fracture toughness of a crack between two isotropic\, homogeneous materi
 als and a delamination between two laminae of unidirectional composite mat
 erials of differing directions is presented. Four cases are considered. Tw
 o isotropic material pairs are described: glass/epoxy and two ceramic clay
 s. Similar studies are presented for two cross-ply laminates: 0°/90° an
 d +45°/-45°.\nThe Brazilian disk specimen was used to carry out mixed mo
 de fracture tests. The load and crack or delamination length at fracture w
 ere measured and used in a finite element analysis to determine the displa
 cement field. An interaction energy or M-integral was used to determine th
 e stress intensity factors at failure. These in turn were employed to obta
 in the critical interface energy release rate Gic and one phase angles ψ 
 in two dimensions or two phase angles ψ and ϕ in three dimensions which 
 measure the mode mixity. For the M-integral and for each interface crack o
 r delamination\, the first term of the asymptotic solution of the field qu
 antities is required. For two isotropic materials\, these solutions are we
 ll known. For the laminates described here\, they were determined by the S
 troh and Lekhnitskii formalisms. A failure criterion determined from first
  principles is presented. The values of Gic and ψ in two dimensions or ψ
  and ϕ in three dimensions are used to specify the criterion for each mat
 erial pair. A statistical analysis is presented. Two approaches are taken:
  one uses the t-statistic to predict a 10% probability of failure\; the se
 cond uses a standard normal variate to predict a 10% failure probability w
 ith 95% confidence.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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