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NASA Technical Reports Server (NTRS) 19950013069: Residual life and... |
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by NASA Technical Reports Server (NTRS) |
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Economic and safe operation of the flight vehicles flying |
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beyond their initial design life calls for an in-depth |
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structural integrity evaluation of all components with |
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potential for catastrophic damages. Fuselage panels with |
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cracked skin and/or stiffening elements is one such |
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example. A three level analytical approach is developed |
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to analyze the pressurized fuselage stiffened shell |
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panels with damaged skin or stiffening elements. A global |
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finite element analysis is first carried out to obtain |
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the load flow pattern through the damaged panel. As an |
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intermediate step, the damaged zone is treated as a |
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spatially three-dimensional structure modeled by plate |
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and shell finite elements, with all the neighboring |
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elements that can alter the stress state at the crack |
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tip. This is followed by the Schwartz-Neumann alternating |
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method for local analysis to obtain the relevant crack |
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tip parameters that govern the onset of fracture and the |
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crack growth. The methodology developed is generic in |
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nature and aims at handling a large fraction of problem |
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areas identified by the Industry Committee on Wide-Spread |
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Fatigue Damage. |
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Date Published: 2016-10-07 08:50:41 |
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Identifier: NASA_NTRS_Archive_19950013069 |
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Item Size: 19089121 |
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Language: english |
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Media Type: texts |
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