NDLI: An evaluation of the pressure proof test concept for thin sheet 2024-t3

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An evaluation of the pressure proof test concept for thin sheet 2024-t3

Content Provider	NASA Technical Reports Server (NTRS)
Author	Newman Jr., James C. Harris, Charles E. Dawicke, D. S. Poe Jr., C. C.
Copyright Year	1990
Description	The 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.
File Size	1520135
Page Count	34
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19900012108
Archival Resource Key	ark:/13960/t1pg6kh5j
Language	English
Publisher Date	1990-04-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Panels Cycles Fatigue Life Fracture Mechanics Transport Aircraft Structural Failure Aluminum Alloys Crack Arrest Crack Closure Crack Propagation Cracks Proving Fuselages Lap Joints Failure 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

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