Proof test and fatigue crack growth modeling on 2024-T3 aluminum alloyPressure proof testing of aircraft fuselage structures has been suggested as a means of screening critical crack sizes and of extending their useful life. The objective of this paper is to study the proof-test concept and to model the crack-growth process on a ductile material. Simulated proof and operational fatigue life tests have been conducted on cracked panels made of 2024-T3 aluminum alloy sheet material. A fatigue crack-closure model was modified to simulate the proof test and operational fatigue cycling. Using crack-growth rate and resistance-curve data, the model was able to predict crack growth during and after the proof load. These tests and analyses indicate that the proof test increases fatigue life; but the beneficial life, after a 1.33 or 1.5 proof, was less than a few hundred cycles.
Document ID
19920037204
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Newman, J. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Poe, C. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Dawicke, D. S. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Metallic Materials
Meeting Information
Meeting: Fatigue 90: International Conference on Fatigue and Fatigue Thresholds