Fatigue-Crack Propagation in Aluminum-Alloy Tension Panels PDF Download
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Author: Richard E. Whaley
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Book Description
Results are presented of a series of fatigue tests to study crack propagation and the resulting stress distributions in tension panels. The panels were all of the same general design, and configurations varied mainly in the relative amount of cross-sectional area in the skin, stiffeners, and flanges. The panels were constructed of 2024-T3 and 7075-T6 aluminum alloys. It was found that the average rate of crack growth was slower in panels made of 2024-T3 aluminum alloy than in panels made of 7075-T6 aluminum alloy. All cracks initiated in the skin, and the slowest crack growth was measured in configurations where the highest percentage of cross-sectional area was in the stiffeners. Strain-gage surveys were made to determine the redistribution of stress as the crack grew across the panels. As a crack approached a given point in the skin, the stress at that point increased rapidly. The stress in the stiffeners also increased as the crack approached the stiffeners. During the propagation of the crack the stress was not distributed uniformly in the remaining area.
Author: Richard E. Whaley
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Book Description
Results are presented of a series of fatigue tests to study crack propagation and the resulting stress distributions in tension panels. The panels were all of the same general design, and configurations varied mainly in the relative amount of cross-sectional area in the skin, stiffeners, and flanges. The panels were constructed of 2024-T3 and 7075-T6 aluminum alloys. It was found that the average rate of crack growth was slower in panels made of 2024-T3 aluminum alloy than in panels made of 7075-T6 aluminum alloy. All cracks initiated in the skin, and the slowest crack growth was measured in configurations where the highest percentage of cross-sectional area was in the stiffeners. Strain-gage surveys were made to determine the redistribution of stress as the crack grew across the panels. As a crack approached a given point in the skin, the stress at that point increased rapidly. The stress in the stiffeners also increased as the crack approached the stiffeners. During the propagation of the crack the stress was not distributed uniformly in the remaining area.
Author: Richard E. Whaley
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
Author: Richard E. Whaley
Publisher:
ISBN:
Category : Aluminum
Languages : en
Pages : 30
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Book Description
Author: D. Y. Wang
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 16
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Book Description
The effects of panel width and crack length on fracture toughness and the fatigue crack propagation rate of Alclad 2024-T3 and X7475 were investigated in sheet specimens ranging from 30 to 120 in. wide. The unstiffened, wide panels containing a through-the-thickness central crack were tested under uniaxial loadings to generate fatigue crack growth, stable crack growth, and residual strength data. In addition, 48-in. wide 7075-T6 and 7079-T6 aluminum alloy panels were tested at -65° F to determine low-temperature effects. The analysis was conducted to define the parameters contributing to the apparent panel size effects and to outline the procedures to obtain valid data applicable to full-scale structural design. Excellent correlation was found in the stable crack growth resistance curve (KR versus ?a) data obtained from panels of various width which contained initial crack lengths ranging from 3.6 to 30 in. The results suggest that the crack growth resistance curve is a material parameter which is independent of crack length and panel width under an appropriate test condition. The effects of -65° F significantly reduce fatigue crack propagation resistance at a relatively high ?K level and stable static crack growth resistance of some aluminum alloy sheets.
Author: Walter Illg
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 24
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Author: Samuel Harrison Smith
Publisher:
ISBN:
Category : Aluminum
Languages : en
Pages : 108
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Author:
Publisher:
ISBN:
Category : Metals
Languages : en
Pages : 560
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 44
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Author: Robert G. Dubensky
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 36
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Author: C. E. Harris
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 28
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Book Description
An extensive experimental database has been assembled from very detailed teardown examinations of fatigue cracks found in rivet holes of fuselage structural components. Based on this experimental database, a comprehensive analysis methodology was developed to predict the onset of widespread fatigue damage in lap joints of fuselage structure. Several computer codes were developed with specialized capabilities to conduct the various analyses that make up the comprehensive methodology. Over the past several years, the authors have interrogated various aspects of the analysis methods to determine the degree of computational rigor required to produce numerical predictions with acceptable engineering accuracy. This study led to the formulation of a practical engineering approach to predicting fatigue crack growth in riveted lap joints. This paper describes the practical engineering approach and compares predictions with the results from several experimental studies.
