A Six-Node Curved Triangular Element and a Four-Node Quadrilateral Element for Analysis of Laminated Composite Aerospace Structures
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Home > Reference > Research and information: general > Research methods: general > A Six-Node Curved Triangular Element and a Four-Node Quadrilateral Element for Analysis of Laminated Composite Aerospace Structures
A Six-Node Curved Triangular Element and a Four-Node Quadrilateral Element for Analysis of Laminated Composite Aerospace Structures

A Six-Node Curved Triangular Element and a Four-Node Quadrilateral Element for Analysis of Laminated Composite Aerospace Structures


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About the Book

Mathematical development and some computed results are presented for Mindlin plate and shell elements, suitable for analysis of laminated composite and sandwich structures. These elements use the conventional 3 (plate) or 5 (shell) nodal degrees of freedom, have no communicable mechanisms, have no spurious shear energy (no shear locking), have no spurious membrane energy (no membrane locking) and do not require arbitrary reduction of out-of-plane shear moduli or under-integration. Artificial out-of-plane rotational stiffnesses are added at the element level to avoid convergence problems or singularity due to flat spots in shells. This report discusses a 6-node curved triangular element and a 4-node quadrilateral element. Findings show that in regular rectangular meshes, the Martin-Breiner 6-node triangular curved shell (MB6) is approximately equivalent to the conventional 8-node quadrilateral with integration. The 4-node quadrilateral (MB4) has very good accuracy for a 4-node element, and may be preferred in vibration analysis because of narrower bandwidth. The mathematical developments used in these elements, those discussed in the seven appendices, have been applied to elements with 3, 4, 6, and 10 nodes and can be applied to other nodal configurations.Martin, C. Wayne and Breiner, David M. and Gupta, Kajal K. (Technical Monitor)Ames Research Center; Armstrong Flight Research CenterDYNAMIC STRUCTURAL ANALYSIS; AIRCRAFT STRUCTURES; COMPOSITE STRUCTURES; SANDWICH STRUCTURES; NODES (STANDING WAVES); MINDLIN PLATES; MODULUS OF ELASTICITY; SHEAR PROPERTIES; DEGREES OF FREEDOM; BANDWIDTH; FINITE ELEMENT METHOD; VIBRATION TESTS; AEROSPACE ENGINEERING


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Product Details
  • ISBN-13: 9781720365235
  • Publisher: Createspace Independent Publishing Platform
  • Publisher Imprint: Createspace Independent Publishing Platform
  • Height: 279 mm
  • No of Pages: 60
  • Spine Width: 3 mm
  • Width: 216 mm
  • ISBN-10: 1720365237
  • Publisher Date: 29 May 2018
  • Binding: Paperback
  • Language: English
  • Returnable: N
  • Weight: 163 gr


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A Six-Node Curved Triangular Element and a Four-Node Quadrilateral Element for Analysis of Laminated Composite Aerospace Structures
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