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Nonlinear response and failure characteristics of internally pressurized composite cylindrical panels
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Starnes, J. H. Johnson, E. R. Boitnott, R. L. |
| Copyright Year | 1985 |
| Description | Results of an experimental and analytical study of the nonlinear response and failure characteristics of internally pressurized 4- to 16-ply-thick graphite-epoxy cylindrical panels are presented. Specimens with clamped boundaries simulating the skin between two frames and two stringers of a typical transport fuselage were tested to failure. Failure results of aluminum specimens are compared with the graphite-epoxy test results. The specimens failed at their edges where the local bending gradients and interlaminar stresses are maximum. STAGS nonlinear two-dimensional shell analysis computer code results are used to identify regions of the panels where the response is independent of the axial coordinate. A geometrically nonlinear one-dimensional cylindrical panel analysis was derived and used to determine panel response and interlaminar stresses. Inclusion of the geometric nonlinearity was essential for accurate prediction of panel response. The maximum stress failure criterion applied to the predicted tensile stress in the fiber direction agreed best with the experimentally determined first damage pressures. |
| File Size | 59316783 |
| Page Count | 209 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850025233 |
| Archival Resource Key | ark:/13960/t8pc7vx60 |
| Language | English |
| Publisher Date | 1985-06-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Panels Stress Analysis Tensile Stress Failure Analysis Cylindrical Bodies Nonlinearity Graphite-epoxy Composites Fuselages Laminates Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
