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An evaluation of the pressure proof test concept for thin sheet 2024-T3The 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 test was longer than that without the proof test 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 test 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
Document Type
Technical Memorandum (TM)
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, James C., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Harris, Charles E.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1990
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:101675
Accession Number
Funding Number(s)
PROJECT: RTOP 505-63-01-05
Distribution Limits
Work of the US Gov. Public Use Permitted.
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