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A Nonlocal Damage Theory for Laminated Plate with Application to Aircraft Damage Tolerance
| Content Provider | Scilit |
|---|---|
| Author | Nahan, M. Kennedy, T. |
| Copyright Year | 2019 |
| Description | Composite pressure vessel design requires the prediction of failure given large-scale damage. Cracks in composite laminates are known to develop a damage zone that exhibits strain-softening. This investigation sought to develop a computational model that simulates progressive damage and predicts failure of complex laminated shell structures subject to combined tension and flexure. The model assumed a macroscopic definition of orthotropic damage that was allowed to vary linearly through the shell thickness. It was further proposed that nonlocal plate strain and curvature act to force damage growth according to a set of uniaxial criteria. Damage induced strain softening is exhibited by degradation of laminate stiffness. An expression for the damage reduced laminated plate stiffness was derived which assumed the familiar laminated plate [ABD] stiffness matrix format. The model was implemented in a finite element shell program for simulation of fracture and evaluation of damage tolerance. A combined tension plus flexure fracture test was developed for characterizing damage. Analysis was performed on a section of pressurized composite fuselage containing a large crack. Good agreement was found between calculations and test results. |
| Related Links | https://content.taylorfrancis.com/books/download?dac=C2006-0-14209-1&isbn=9780367812720&doi=10.1201/9780367812720-30&format=pdf |
| Ending Page | 304 |
| Page Count | 10 |
| Starting Page | 295 |
| DOI | 10.1201/9780367812720-30 |
| Language | English |
| Publisher | Informa UK Limited |
| Publisher Date | 2019-11-28 |
| Access Restriction | Open |
| Subject Keyword | Aerospace Engineering Stiffness Pressurized Structures Laminated Plate Damage Tolerance |
| Content Type | Text |
