rdf-syntax-grammar
mods:
  schema location: http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
  title info:
    title: Multiscale modeling of damage in multidirectional composite laminates
  name:
    name part: Singh, Chandra Veer.
    role:
      role term: creator
  name:
    name part: Talreja, R.
    role:
      role term: thesis advisor.
  type of resource: text
  genre: bibliography
  origin info:
    place:
      place term: txu
    date issued: 2010
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: electronic
    form: remote
    extent: 1 online resource.
  abstract: The problem of damage accumulation in laminated composite materials has received much attention due to their widespread application in the aerospace, automotive, civil, and sports industries. In the aerospace industry, composites are used to make light weight and efficient structural components. In the Boeing 787, for example, more than 50% of the structure is made of composite materials. Although there have been significant developments in analyzing cross-ply laminates, none of the present approaches provides reasonable predictions for multidirectional laminates in which intralaminar cracks may form in multiple orientations. Nevertheless, the prediction of damage accumulation and its effect on structural performance is a very difficult problem due to complexity of the cracking processes. This study presents a synergistic damage mechanics (SDM) methodology to analyze damage behavior in multidirectional composite laminates with intralaminar cracks in plies of multiple orientations. SDM combines the strengths of micro-damage mechanics (MDM) and continuum damage mechanics (CDM) in predicting the stiffness degradation due to these cracks. The micromechanics is performed on a representative unit cell using a three-dimensional finite element analysis to calculate the crack opening displacement accounting for the influence of the surrounding plies, the so-called constraint effect. This information is then incorporated in the CDM formulation dealing with laminates containing cracks in different ply orientations through a 'constraint parameter.' Following CDM, a separate damage mode is defined for each type of crack and the expressions for engineering moduli of the damaged laminate are then derived in terms of crack density and the constraint parameter. The SDM methodology is implemented for [0m/±[theta]n/0m/2]s laminates containing cracks in ± [theta]-plies. It is then extended to [0m/±[theta]n/90r]s and [0m/90r/±[theta]n]s laminates with cracks additionally in the 90[degre…
  note: by Chandra Veer Singh.
  note: "Major Subject: Aerospace Engineering"
  note: Title from author supplied metadata (automated record created 2010-03-12 12:08:51).
  note: Electronic resource.
  note: Doctor of Philosophy Texas A&M University 2008 http://hdl.handle.net/1969.1/ETD-TAMU-2312
  note: Includes bibliographical references.
  note: Text (Dissertation)
  subject:
    topic: Major Aerospace Engineering
  subject:
    topic: Finite Element Modeling
  subject:
    topic: Matrix Cracking
  subject:
    topic: Damage
  subject:
    topic: Continuum Damage Mechanics
  subject:
    topic: Transverse Cracking
  subject:
    topic: Composites
  subject:
    topic: Design
  identifier: http://hdl.handle.net/1969.1/ETD-TAMU-2312
  record info:
    record content source: TXA
    record creation date: 100427
    record change date: 20151201120210.0
    record identifier: in00002586111