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Fatigue Crack Growth Prediction Study Based On The Onera Model For Constant Amplitude And Simplified Flight Simulation Loading
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Book Synopsis Fatigue Crack Growth Prediction Study Based on the ONERA Model for Constant-amplitude and Simplified Flight-simulation Loading by : U.H. Padmadinata
Download or read book Fatigue Crack Growth Prediction Study Based on the ONERA Model for Constant-amplitude and Simplified Flight-simulation Loading written by U.H. Padmadinata and published by . This book was released on 1988 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Methods and Models for Predicting Fatigue Crack Growth Under Random Loading by :
Download or read book Methods and Models for Predicting Fatigue Crack Growth Under Random Loading written by and published by ASTM International. This book was released on with total page 147 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fatigue Crack Growth Modelling Under Flight Simulation Loading by : Mustafa Öztürk
Download or read book Fatigue Crack Growth Modelling Under Flight Simulation Loading written by Mustafa Öztürk and published by . This book was released on 1995 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt: A literature survey has been done on the computer models that predict fatigue crack growth under variable amplitude loading using Elber's crack closure concept. The PREFFAS, ONERA, and CORPUS crack closure models were analyzed qualitatively and quantitatively. Computer codes were developed for the PREFFAS, ONERA, and CORPUS crack closure models. The models were run under standardized flight simulation loading histories, FALSTAFF and F-27, for which computer codes were also developed. For two different materials, 2024 T3 and 7075 T6, the performance of the models under several variations of flight simulation load histories were analyzed. The predictions were compared with the experimental data supplied by Padmadinata, and acceptable agreement was observed. Predictions using the three models were also compared with those from a simple equivalent constant amplitude load approach which does not account for crack closure and interaction effects. Better performance of the crack closure models was definitely observed. The sensitivities of the models against variations in material parameters were also analyzed.
Book Synopsis Expert System for Fatigue Crack Growth Predictions Based on Fatigue Crack Closure by : Ji-Ho Song
Download or read book Expert System for Fatigue Crack Growth Predictions Based on Fatigue Crack Closure written by Ji-Ho Song and published by Springer Nature. This book was released on 2022-03-04 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book demonstrates fatigue crack growth under random loading graphically. This state-of-the-art monograph introduces an expert system for crack growth predictions, particularly based on crack closure. The system is developed after years of research by the authors by using the Math-type software consisting of 5 parts. This system is unique as it is fundamentally different from previous systems as it focuses on fatigue crack growth predictions based on fatigue crack closure. This book can be a useful guide for practicing engineers, researchers, and students in the fields of mechanical, aerospace, or civil engineering.
Book Synopsis The Effect of Periodic Overloads on Flight-by-flight Fatigue Crack Growth Rates by : Margery A. Dean
Download or read book The Effect of Periodic Overloads on Flight-by-flight Fatigue Crack Growth Rates written by Margery A. Dean and published by . This book was released on 1983 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The life prediction of aerospace structures subjected to service loading conditions can be complex and expensive. Fortunately, many flight-by- flight loadings can be analyzed as constant amplitude loading if the variability in crack growth rate is low. A test program was designed such that the stress intensity factor (Kmax) was held constant by uniformly reducing the load as the fatigue crack grew. With a constant Kmax, the crack growth rate remains constant throughout the life of the test. The baseline fatigue crack growth rate variability was established for the 7075-T6 center-cracked panels under a flight-by-flight load history. The effect of introducing overloads to the baseline flight history on the crack growth rate variability was reported. The results indicate that the delay region for the applied 114% overloads was predicted by Irwin's plastic zone model and was equal to 0.0382 inches which was equal to 225 flights. The delay behavior was consistent for the several overload conditions that were studied. When the occurrence of overload increased, the fatigue crack growth decreased. The standard error of estimate remained relatively constant, suggesting that a block approach to life prediction is feasible for flight-by-flight load history.
Book Synopsis Prediction of Fatigue-crack Growth Under Variableamplitude and Spectrum Loading Using a Closure Model by :
Download or read book Prediction of Fatigue-crack Growth Under Variableamplitude and Spectrum Loading Using a Closure Model written by and published by . This book was released on 1981 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fatigue Crack Growth by : Hans Albert Richard
Download or read book Fatigue Crack Growth written by Hans Albert Richard and published by Springer. This book was released on 2016-06-13 with total page 305 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book offers a concise introduction to fatigue crack growth, based on practical examples. It discusses the essential concepts of fracture mechanics, fatigue crack growth under constant and variable amplitude loading and the determination of the fracture-mechanical material parameters. The book also introduces the analytical and numerical simulation of fatigue crack growth as well as crack initiation. It concludes with a detailed description of several practical case studies and some exercises. The target group includes graduate students, researchers at universities and practicing engineers.
Book Synopsis A Practical Engineering Approach to Predicting Fatigue Crack Growth in Riveted Lap Joints by : C. E. Harris
Download or read book A Practical Engineering Approach to Predicting Fatigue Crack Growth in Riveted Lap Joints written by C. E. Harris and published by . This book was released on 2000 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis A Crack-closure Model for Predicting Fatigue-crack Growth Under Aircraft Spectrum Loading by :
Download or read book A Crack-closure Model for Predicting Fatigue-crack Growth Under Aircraft Spectrum Loading written by and published by . This book was released on 1981 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721209279 Total Pages :28 pages Book Rating :4.2/5 (92 download)
Book Synopsis A Strip-Yield Model for Predicting the Growth of Part-Through Cracks Under Cyclic Loading by : National Aeronautics and Space Administration (NASA)
Download or read book A Strip-Yield Model for Predicting the Growth of Part-Through Cracks Under Cyclic Loading written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flaws exist in aircraft structures due to manufacturing operations and material defects. Under variable amplitude cyclic loading, these flaws grow as part-through cracks reducing the residual strength of structural components. To meet damage tolerant design requirements, accurate flaw growth predictions are needed which account for continual changes in crack shape as well as crack growth retardation and acceleration. Predicting the growth of part-through cracks under cyclic loading using an innovative and computationally efficient model is the focus of the research summarized in this report. In this research effort, a slice synthesis methodology was developed and used to construct a modified strip-yield model for the part-through semi-elliptical surface flaw, enabling prediction of plasticity-induced closure along the crack front and subsequent fatigue crack growth under constant amplitude and variable amplitude loading. While modeling the plasticity-induced closure in a part-through flaw may be performed using three dimensional elastic-plastic finite element analysis, this type of effort is impractical from an engineering perspective. A modified strip-yield model similar to that used in FASTRAN for part-through flaws is a much needed engineering design tool, particularly when computational resources are limited. Daniewicz, S. R. and Newman, J. C., Jr. (Technical Monitor) Langley Research Center
Book Synopsis Fatigue Crack Growth Under Spectrum Loads by : Ralph Ivan Stephens
Download or read book Fatigue Crack Growth Under Spectrum Loads written by Ralph Ivan Stephens and published by ASTM International. This book was released on 1976 with total page 345 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fatigue Life and Crack Growth Prediction Methodology by : J. C. Newman (Jr)
Download or read book Fatigue Life and Crack Growth Prediction Methodology written by J. C. Newman (Jr) and published by . This book was released on 1993 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 652 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Prediction of Fatigue Crack Growth Under Constant Amplitude and Random Loading Using Specimens with Multiple Cracks by :
Download or read book Prediction of Fatigue Crack Growth Under Constant Amplitude and Random Loading Using Specimens with Multiple Cracks written by and published by . This book was released on 1994 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fatigue crack growth under stationary Gaussian random loading is considered. A specially developed computerized testing system and software are used for generation of the random loading and investigation of crack growth. The sliding summation numerical method was used for generation of a random loading history characterized by a given autocorrelation function. As far as the loading history of a sufficient length is generated a sequence of maxima and minima is extracted and arranged with the predetermined frequency. The next Operation is elimination of the small amplitude cycles in accordance with the predetermined threshold value and. determination of the minima and maxima two-dimensional distribution of the edited process. A specially built transition matrix derived from this distribution was used for the real-time generation of the random loading during the test. Experimental investigation of the developed random loading generation procedure and crack growth process was performed using aluminium alloy multicrack panel type specimens providing possibility of observation of an array of simultaneously growing cracks. Dependence of fatigue crack life time on random loading parameters as well as stochastic characteristics of crack growth were studied. (MM).
Download or read book Metals Abstracts written by and published by . This book was released on 1990 with total page 1108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fatigue Crack Growth Prediction Methods for Variable Amplitude Loading by :
Download or read book Fatigue Crack Growth Prediction Methods for Variable Amplitude Loading written by and published by . This book was released on 1988 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Considerable data on fatigue properties of materials under constant amplitude loading is available in the literature under the forms representative of the different aspects of the fatigue phenomenon. To employ these data, the design engineer must adapt it to the particular service conditions that he is concerned with. The stress vs. life or S-N curve is largely related to the fatigue initiation behaviour of materials and defines the endurance limit which is used for design. The strain-life curve is of more recent origin and relates the elastic and plastic strain amplitudes to the initiation life. Fatigue propagation data are presented on a crack growth rate vs. stress intensity factor range diagram.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722193744 Total Pages :50 pages Book Rating :4.1/5 (937 download)
Book Synopsis Effects of Constraint on Crack Growth Under Aircraft Spectrum Loading by : National Aeronautics and Space Administration (NASA)
Download or read book Effects of Constraint on Crack Growth Under Aircraft Spectrum Loading written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective is to study the effects of constraint on fatigue crack growth under aircraft spectrum loading. A plasticity-induced crack-closure model that accounts for constraint variations during the transition from flat-to-slant crack growth was used to correlate crack-growth rate data under constant-amplitude loading and to calculate crack growth under simulated aircraft spectrum loading. The model was applied to several thin-sheet aluminum alloy materials. Under laboratory air conditions, the transition was shown to be related to the size of the cyclic plastic zone based on the effective stress-intensity factor range for several sheet materials and thicknesses. Results from three-dimensional, elastic-plastic, finite-element analyses of a flat, straight-through crack in a thin-sheet aluminum alloy specimen showed a constraint loss similar to that assumed in the model. Using test data and the closure model, the location of the constraint-loss regime in terms of growth rate and the value of the constraint factor at these rates were determined by trial and error. The model was then used to calculate crack growth under the TWIST spectrum. The calculated results agreed reasonably well with test data. In general, the model predicted shorter crack-growth lives than tests under the TWIST spectrum by about 40 percent. For the TWIST spectrum clipped at Level 3, the calculated lives were within about 20 percent. The results demonstrated that constraint variations, especially for thin-sheet alloys, should be accounted for to predict crack growth under typical aircraft spectra. Newman, J. C., Jr. Langley Research Center RTOP 538-02-10-01...
