BRL-CR-272
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Numerical Analysis of Laminated, Orthotropic Composite Structures
During the first part of this investigatim two finite-element were developedl.2 for the purpose of malysis of laminar. orthotropic struc- tures in the forn of bodies of revolution. mdels al IN for orthotropic axes to be a±itrarily oriented with respect to the cylindrical coordinates. Because of this, the models allow for three COQcnents of displacements in- eluding the tH0 cnponents in the æridian plane md the circumferential com- ponent. As a result, the be used to malyze unbalanced laminar configurations ud stresses can be predicted. The two Ndels have been developed differ in the basic finite-element shape which was used. The shape is defined by the cross-section Of the eleænts in the xridim plute. In the first Ndell, a nine degree-of-freedom, straight sided, tri- mgular elexnt was used. In this elexnt, the three cmponents of dis- placernt are defined at eaå comer of the trimgle md a linear displace- variation is assurd inside the eleznt. In the second Nde12, a hiØ1er order, isoparaNtric elenent was used with quadratic displacxnt variations for two of the *Tidian displacernts md a linear variation for the circtnferential coponent. These elemnts are triangular with curved sides md mid-side nodes in additim to the comer nodes. of these elements possesses fifteen degrees-of-freedom. A nt*er of m=rical exaQles were analyzed with both of Chese mdels to check-out the *thods md the associated coquter progrns. One of these exuples was malyzed by both nodels md was intended to coQare the relative accuracy Of *thod. It was fowtd that, for en equivalent of total degrees-of-freedom. the results given by both *thods were very close2. AlthouØ1 the total Of degrees-of-freedom in both Mdels was the sau, fewer of the isoparuetric eleynts had to be used. The con- elusion fron this study was that eaå of these mdels was equally accurate md either me could be used for any given problem.
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