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Non-deterministic dynamic instability of composite shells
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Abumeri, Galib H. Chamis, Christos C. |
| Copyright Year | 2004 |
| Description | A computationally effective method is described to evaluate the non-deterministic dynamic instability (probabilistic dynamic buckling) of thin composite shells. The method is a judicious combination of available computer codes for finite element, composite mechanics, and probabilistic structural analysis. The solution method is incrementally updated Lagrangian. It is illustrated by applying it to thin composite cylindrical shell subjected to dynamic loads. Both deterministic and probabilistic buckling loads are evaluated to demonstrate the effectiveness of the method. A universal plot is obtained for the specific shell that can be used to approximate buckling loads for different load rates and different probability levels. Results from this plot show that the faster the rate, the higher the buckling load and the shorter the time. The lower the probability, the lower is the buckling load for a specific time. Probabilistic sensitivity results show that the ply thickness, the fiber volume ratio and the fiber longitudinal modulus, dynamic load and loading rate are the dominant uncertainties, in that order. |
| File Size | 956010 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040040087 |
| Archival Resource Key | ark:/13960/t9285910q |
| Language | English |
| Publisher Date | 2004-02-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Finite Element Method Probability Theory Shells Structural Forms Dynamic Loads Composite Structures Lagrangian Function Buckling 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 |
