| Author | Search for: Shadmehri, F.; Search for: Hoa, S. V.; Search for: Hojjati, M.1 |
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| Affiliation | - National Research Council Canada. NRC Institute for Aerospace Research
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| Format | Text, Article |
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| Conference | 24th Annual Technical Conference of the American Society for Composites 2009 and 1st Joint Canadian-American Technical Conference on Composites, September 15-17, 2009, Newark, DE, United States |
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| Subject | bending behavior; composite material; cross-ply laminated conical shell; first-order theory |
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| Abstract | An analytical solution is considered to investigate the bending behavior of cross-ply laminated conical shells using first-order shear deformation theory. Linear strain displacement relation simplified for conical shell is assumed. The governing equations are derived from Hamilton's principle. Assuming Levy-type solution, the governing equations are then converted to ordinary differential equations and changed to state-space form introducing ten unknown variables. The new first-order ordinary differential equation system is solved for displacements using numeric technique. As a loading case, a distributed sinusoidal transverse load is applied. Different lamination sequences including symmetric and asymmetric laminate are studied and compared. The effect of cone angle, various boundary conditions (i.e. clamped, simply supported and free edge), radius to thickness and length to thickness ratio on the displacement of mid surface is investigated. |
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| Publication date | 2009 |
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| Publisher | Curran |
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| In | |
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| Language | English |
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| Peer reviewed | Yes |
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| NPARC number | 23004539 |
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| Export citation | Export as RIS |
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| Report a correction | Report a correction (opens in a new tab) |
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| Record identifier | dcf4e1d9-c427-4947-bfed-f964c2bfe8c6 |
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| Record created | 2018-11-16 |
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| Record modified | 2020-04-16 |
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