Abstract
Integrity evaluation of aging structures is extremely important to ensure economic and safe operation of the flight vehicle. A two step analytical approach has been developed to estimate the residual strength/life of pressurized fuselage stiffened shell panels with widespread fatigue cracking. Global FEA, to obtain the load flow pattern through the damaged panel, is followed by the Schwartz-Neumann Alternating Method to determine the relevant crack tip parameters that govern the growth of cracks & onset of failure. An Elastic-Plastic Alternating Method has been developed and applied to evaluate the residual strength of flat panels with multiple cracks. The computational methodologies presented herein are marked improvements to the present state-of-the-art, and are extremely efficient, both from engineering manpower as well as computational costs point of view.
| Original language | English |
|---|---|
| Pages (from-to) | 1191-1200 |
| Number of pages | 10 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 2 |
| State | Published - 1994 |
| Event | Proceedings of the 35th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 1 (of 5) - Hilton Head, SC, USA Duration: Apr 18 1994 → Apr 20 1994 |