A Methodology to Predict Damage Initiation, Damage Growth and Residual Strength in Titanium Matrix Composites PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 48
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Author:
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ISBN:
Category :
Languages : en
Pages : 48
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Author: JG. Bakuckas
Publisher:
ISBN:
Category : Fiber breakage
Languages : en
Pages : 23
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In this research, a methodology to predict damage initiation, damage growth, fatigue life, and residual strength in titanium matrix composites (TMC) is outlined. Emphasis was placed on micromechanics-based engineering approaches. Damage initiation was predicted using a local effective strain approach. A finite element analysis verified the prevailing assumptions made in the formulation of this model. Damage growth, namely, fiber-bridged matrix crack growth, was evaluated using a fiber bridging (FB) model that accounts for thermal residual stresses. This model combines continuum fracture mechanics and micromechanics analyses yielding stress-intensity factor solutions for fiber-bridged matrix cracks. In the FB model, fibers in the wake of the matrix crack are idealized as a closure pressure, and an unknown constant frictional shear stress is assumed to act along the debond length of the bridging fibers. This frictional shear stress was used as a curve-fitting parameter to the available experimental data. Figure life and post-fatigue residual strength were predicted based on the axial stress in the first intact 0° fiber calculated using the FB model and a three-dimensional finite element analysis.
Author: W. Steven Johnson
Publisher: ASTM International
ISBN: 0803120397
Category : Metallic composites
Languages : en
Pages : 625
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Papers presented at the March 1994 symposium are organized into five sections that progress from basic understanding of mechanical damage mechanisms and environmental effects to life prediction methodology. Five papers discuss the interplay between interfacial strength, residual thermal stresses, an
Author:
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Category : Aeronautics
Languages : en
Pages : 892
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 182
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722016609
Category :
Languages : en
Pages : 46
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The translaminate fracture behavior of carbon/epoxy structural laminates with through-penetration notches was investigated to develop a residual strength prediction methodology for composite structures. An experimental characterization of several composite materials systems revealed a fracture resistance behavior that was very similar to the R-curve behavior exhibited by ductile metals. Fractographic examinations led to the postulate that the damage growth resistance was primarily due to fractured fibers in the principal load-carrying plies being bridged by intact fibers of the adjacent plies. The load transfer associated with this bridging mechanism suggests that a progressive damage analysis methodology will be appropriate for predicting the residual strength of laminates with through-penetration notches. A progressive damage methodology developed by the authors was used to predict the initiation and growth of matrix cracks and fiber fracture. Most of the residual strength predictions for different panel widths, notch lengths, and material systems were within about 10% of the experimental failure loads. Coats, Timothy W. and Harris, Charles E. Langley Research Center RTOP 538-13-11-05...
Author:
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ISBN:
Category :
Languages : en
Pages : 28
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Author: D. Harmon
Publisher:
ISBN:
Category : Aluminum matrix composites
Languages : en
Pages : 14
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Elevated temperature applications for advanced fighters and hypersonic vehicles, along with advanced fabrication techniques, such as diffusion bonding and superplastic forming, have brought renewed interest in metal matrix composites for aircraft structures. In order to predict the strength and durability of metal matrix structures, it will be necessary to predict the mode in which failure occurs, such as net section failure, shear along the fiber, or other modes. Test and analysis results demonstrate the differences between strength and fatigue failure modes of uni-directionally reinforced aluminum matrix composites (AMC) and those in titanium matrix composites (TMC). These tests include detailed optical and scanning electron microscope studies of failures in aluminum and titanium matrix composites.
Author:
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Category : Metallurgy
Languages : en
Pages : 762
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Author: Ronald B. Bucinell
Publisher: ASTM International
ISBN: 0803126093
Category : Composite materials
Languages : en
Pages : 315
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