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Elastic buckling analysis for composite stiffened panels and other structures subjected to biaxial inplane loads
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Tamekuni, M. Viswanathan, A. V. |
| Copyright Year | 1973 |
| Description | An exact linear analysis method is presented for predicting buckling of structures with arbitrary uniform cross section. The structure is idealized as an assemblage of laminated plate-strip elements, curved and planar, and beam elements. Element edges normal to the longitudinal axes are assumed to be simply supported. Arbitrary boundary conditions may be specified on any external longitudinal edge of plate-strip elements. The structure or selected elements may be loaded in any desired combination of inplane transverse compression or tension side load and axial compression load. The analysis simultaneously considers all possible modes of instability and is applicable for the buckling of laminated composite structures. Numerical results correlate well with the results of previous analysis methods. |
| File Size | 3853363 |
| Page Count | 91 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730022131 |
| Archival Resource Key | ark:/13960/t9q28pg3h |
| Language | English |
| Publisher Date | 1973-09-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Numerical Analysis Mechanical Properties Elastic Properties Laminates Composite Structures Buckling Loads Forces 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 |
