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Experiment verification of the analytical methodology to predict the residual strength of metallic shell structure
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Harris, Charles E. Starnes Jr., James H. Ambur, Damodar R. Young, Richard D. |
| Copyright Year | 1999 |
| Description | Experimental and analysis results for a curved, stiffened aluminum fuselage panel tested in a combined loads test machine with combined internal pressure, axial compression, and torsional shear loads are described. The experimental and analytical strain results for the panel with and without discrete source damage are presented. The effect of notch tip geometry on crack growth predictions is addressed. The crack growth trajectory predictions for the panel are presented for the applied loading conditions at failure. |
| File Size | 543544 |
| Page Count | 4 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040086694 |
| Archival Resource Key | ark:/13960/t6q004v57 |
| Language | English |
| Publisher Date | 1999-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Aluminum Structural Failure Notches Curved Panels Axial Loads Residual Strength Crack Propagation Failure Analysis Fuselages Torsion Loads Forces Internal Pressure Structural Analysis 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 |
