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Panel stiffener debonding analysis using a shell/3d modeling technique
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Minguet, Pierre J. Krueger, Ronald Ratcliffe, James G. |
| Copyright Year | 2008 |
| Description | A shear loaded, stringer reinforced composite panel is analyzed to evaluate the fidelity of computational fracture mechanics analyses of complex structures. Shear loading causes the panel to buckle. The resulting out -of-plane deformations initiate skin/stringer separation at the location of an embedded defect. The panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot, web and noodle as well as the panel skin near the delamination front were modeled with a local 3D solid model. Across the width of the stringer fo to, the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with a mixed-mode failure criterion of the graphite/epoxy material. The objective was to study the effect of the fidelity of the local 3D finite element model on the computed mixed-mode strain energy release rates and the failure index. |
| File Size | 3712530 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20090042542 |
| Archival Resource Key | ark:/13960/t7cs0ss97 |
| Language | English |
| Publisher Date | 2008-06-11 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Finite Element Method Position Location Fracture Mechanics Debonding Materials Delaminating Computational Mechanics Graphite-epoxy Composites Mathematical Models Composite Structures Buckling Loads Forces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
