Author:
Publisher:
ISBN: 9789283507345
Category : Aerodynamic measurements
Languages : en
Pages : 276

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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category :
Languages : en
Pages : 250

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Author: F. Ellyin
Publisher: Springer Science & Business Media
ISBN: 9400915098
Category : Technology & Engineering
Languages : en
Pages : 484

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Book Description
Fatigue failure is a multi-stage process. It begins with the initiation of cracks, and with continued cyclic loading the cracks propagate, finally leading to the rupture of a component or specimen. The demarcation between the above stages is not well-defined. Depending upon the scale of interest, the variation may span three orders of magnitude. For example, to a material scientist an initiated crack may be of the order of a micron, whereas for an engineer it can be of the order of a millimetre. It is not surprising therefore to see that investigation of the fatigue process has followed different paths depending upon the scale of phenomenon under investigation. Interest in the study of fatigue failure increased with the advent of industrial ization. Because of the urgent need to design against fatigue failure, early investiga tors focused on prototype testing and proposed failure criteria similar to design formulae. Thus, a methodology developed whereby the fatigue theories were proposed based on experimental observations, albeit at times with limited scope. This type of phenomenological approach progressed rapidly during the past four decades as closed-loop testing machines became available.

Author: J. C. Newman
Publisher:
ISBN:
Category :
Languages : en
Pages : 98

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Author: D. S. Dawicke
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 24

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Author: C. E. Harris
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 28

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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.

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702

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Author: A. F. Liu
Publisher: ASM International
ISBN: 9781615032037
Category : Technology & Engineering
Languages : en
Pages : 436

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Author: Michael R. Mitchell
Publisher: ASTM International
ISBN: 0803114230
Category : Fracture mechanics
Languages : en
Pages : 495

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Book Description
Twenty-seven papers from fatigue researchers and practitioners review in detail recent progress in the development of methods to predict fatigue performance of materials and structures and to assess the extent to which these new methods are finding their way into practice. The papers, from the ASTM

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725111622
Category :
Languages : en
Pages : 34

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A technique was developed to calculate the stress intensity factor for multiple interacting cracks. The analysis was verified through comparison with accepted methods of calculating stress intensity factors. The technique was incorporated into a fatigue crack growth prediction model and used to predict the fatigue crack growth life for multiple-site damage (MSD). The analysis was verified through comparison with experiments conducted on uniaxially loaded flat panels with multiple cracks. Configuration with nearly equal and unequal crack distribution were examined. The fatigue crack growth predictions agreed within 20 percent of the experimental lives for all crack configurations considered. Dawicke, D. S. and Newman, J. C., Jr. Langley Research Center NASA-TP-3231, L-17006, NAS 1.60:3231 RTOP 505-63-50-04...