04053nam a22005055i 4500001001800000003000900018005001700027007001500044008004100059020003700100024003500137050001200172072001600184072002300200072001500223100008800238245019600326250001800522264006900540300006600609336002600675337002600701338003600727347002400763490005300787505014500840520196400985650002502949650002502974650004102999650002503040650001603065650006103081700008503142710003403227773002603261776003603287776003603323776003603359830006003395856004603455912001403501912001503515999001703530978-3-031-47984-7DE-He21320251030111422.0cr nn 008mamaa240212s2024    sz |    s    |||| 0|eng d  a97830314798479978-3-031-47984-77 a10.1007/978-3-031-47984-72doi 4aQA808.2 7aPHD2bicssc 7aSCI0650002bisacsh 7aPHD2thema1 aÖchsner, Andreas.eauthor.4aut4http://id.loc.gov/vocabulary/relators/aut96877612aA Numerical Approach to the Simplified Laminate Theory of Composite Materialsh[electronic resource] :bThe Composite Laminate Analysis Tool—CLAT 1D /cby Andreas Öchsner, Resam Makvandi.  a1st ed. 2024. 1aCham :bSpringer Nature Switzerland :bImprint: Springer,c2024.  aXII, 146 p. 104 illus., 49 illus. in color.bonline resource.  atextbtxt2rdacontent  acomputerbc2rdamedia  aonline resourcebcr2rdacarrier  atext filebPDF2rda1 aAdvanced Structured Materials,x1869-8441 ;v2020 aIntroduction -- Simplified Laminate Theory -- Composite Laminate Analysis Tool – CLAT 1D -- Application Examples -- Source Codes -- Index.  aA typical approach to treat composite materials, which are composed of layered unidirectional lamina, is the so-called classical laminate theory (CLT). This theory is based on the theory for plane elasticity elements and classical (shear-rigid) plate elements under the assumption of orthotropic constitutive equations. The solution of the fundamental equations of the classical laminate theory is connected with extensive matrix operations and many problems require in addition iteration loops. This two-dimensional approach and the underlying advanced continuum mechanical modeling might be very challenging for some students, particularly at universities of applied sciences. Thus, a reduced approach, the so-called simplified classical laminate theory (SCLT), has been recently proposed. The idea was to use solely isotropic one-dimensional elements, i.e., a superposition of bar and beam elements, to introduce the major calculation steps of the classical laminate theory. Understanding this simplified theory is much easier and the final step it to highlight the differences when moving to the general two-dimensional case. This monograph first provides a systematic and thorough introduction to the simplified laminate theory based on the theory for bars and classical beam plate elements. The focus is on stacking of isotropic layers to simplified laminates. In addition to the elastic behavior, failure is investigated based on the maximum stress, maximum strain, Tsai-Hill, and the Tsai-Wu criteria. We provide a Python-based computational tool, the so-called Composite Laminate Analysis Tool (CLAT 1D) to easily solve some standard questions from the context of fiber reinforced composites. The tool runs in any standard web browser and offers a user-friendly interface with many post-processing options. The functionality comprises stress and strain analysis of simplified lamina and laminates and the failure analysis based on different criteria. 0aContinuum mechanics. 0aComposite materials. 0aMathematicsxData processing.96571514aContinuum Mechanics.24aComposites.24aComputational Mathematics and Numerical Analysis.9660731 aMakvandi, Resam.eauthor.4aut4http://id.loc.gov/vocabulary/relators/aut9708752 aSpringerLink (Online service)0 tSpringer Nature eBook08iPrinted edition:z978303147983008iPrinted edition:z978303147985408iPrinted edition:z9783031479861 0aAdvanced Structured Materials,x1869-8441 ;v20296873740uhttps://doi.org/10.1007/978-3-031-47984-7  aZDB-2-SMA  aZDB-2-SXMS  c57577d57577