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An evaluation of the pressure proof test concept for 2024-T3 aluminium alloy sheetThe concept of pressure proof testing of fuselage structures with fatigue cracks to insure structural integrity was evaluated from a fracture mechanics viewpoint. A generic analytical and experimental investigation was conducted on uniaxially loaded flat panels with crack configurations and stress levels typical of longitudinal lap splice joints in commercial transport aircraft fuselages. The results revealed that the remaining fatigue life after a proof cycle was longer than that without the proof cycle because of crack growth retardation due to increased crack closure. However, based on a crack length that is slightly less than the critical value at the maximum proof stress, the minimum assured life or proof test interval must be no more than 550 pressure cycles for a 1.33 proof factor and 1530 pressure cycles for a 1.5 proof factor to prevent in-flight failures.
Document ID
19930061783
Document Type
Conference Proceedings
Authors
Dawicke, D. S. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Poe, C. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Newman, J. C. (NASA Langley Research Center Hampton, VA, United States)
Harris, C. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1991
Publication Information
Publication: In: Structural integrity of aging airplanes (A93-45772 19-01)
Subject Category
STRUCTURAL MECHANICS
Distribution Limits
Public
Copyright
Other