Fatigue Crack Growth in a Unidirectional SCS-6/Ti-15-3 Composite PDF Download
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Author: P. Kantzos
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 21
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Book Description
An investigation was conducted to characterize and model the fatigue crack growth (FCG) behavior of a SCS-6/Ti-15-3 metal matrix composite. Part of the study was conducted using a fatigue loading stage mounted inside a scanning electron microscope (SEM). This unique facility allowed high magnification viewing of the composite fatigue processes and measurement of the near crack tip displacements. The unidirectional composite was tested in the [0]8 (that is, longitudinal) and [90]8 (that is, transverse) orientations. For comparison purposes, unreinforced matrix material produced by the identical process as the reinforced material was also tested.
Author: P. Kantzos
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 21
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Book Description
An investigation was conducted to characterize and model the fatigue crack growth (FCG) behavior of a SCS-6/Ti-15-3 metal matrix composite. Part of the study was conducted using a fatigue loading stage mounted inside a scanning electron microscope (SEM). This unique facility allowed high magnification viewing of the composite fatigue processes and measurement of the near crack tip displacements. The unidirectional composite was tested in the [0]8 (that is, longitudinal) and [90]8 (that is, transverse) orientations. For comparison purposes, unreinforced matrix material produced by the identical process as the reinforced material was also tested.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: Peter Kantzos
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 18
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792714870
Category :
Languages : en
Pages : 36
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Book Description
A study was performed to determine the fatigue crack growth (FCG) behavior and the associated fatigue damage processes in a (0)(8) and (90)(8) oriented SCS(6)/Ti-15-3 composite. Companion testing (CT) was also done on identically processed Ti-15-3 unreinforced material. The active fatigue crack growth failure processes were very similar for both composite orientations tested. For both orientations, fatigue crack growth was along the fiber direction. It was found that the composite constituent most susceptible to fatigue damage was the interface region and in particular the carbon coating surrounding the fiber. The failure of the interface region lead to crack initiation and also strongly influenced the FCG behavior in this composite. The failure of the interface region was apparently driven by normal stresses perpendicular to the fiber direction. The FCG rates were considerably higher for the (90)(8) oriented CT specimens in comparison to the unreinforced material. This is consistent with the scenario in which the interface has lower fatigue resistance than the matrix, causing lower composite fatigue resistance. The FCG rates of the (0)(8) composite could not be directly compared to the (90)(8) composite but were shown to increase with an increase in the crack length. Kantzos, Peter and Telesman, Jack Glenn Research Center NASA-TM-102332, E-5041, NAS 1.15:102332 RTOP 510-01-01...
Author: T. Kevin O'Brien
Publisher: ASTM International
ISBN: 0803114192
Category : Composite materials
Languages : en
Pages : 831
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722241032
Category :
Languages : en
Pages : 56
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Book Description
Several fiber bridging models were reviewed and applied to study the matrix fatigue crack growth behavior in center notched (0)(sub 8) SCS-6/Ti-15-3 and (0)(sub 4) SCS-6/Ti-6Al-4V laminates. Observations revealed that fatigue damage consisted primarily of matrix cracks and fiber matrix interfacial failure in the (0)(sub 8) SCS-6/Ti-15-3 laminates. Fiber-matrix interface failure included fracture of the brittle reaction zone and cracking between the two carbon rich fiber coatings. Intact fibers in the wake of the matrix cracks reduce the stress intensity factor range. Thus, an applied stress intensity factor range is inappropriate to characterize matrix crack growth behavior. Fiber bridging models were used to determine the matrix stress intensity factor range in titanium metal matrix composites. In these models, the fibers in the wake of the crack are idealized as a closure pressure. An unknown constant frictional shear stress is assumed to act along the debond or slip length of the bridging fibers. The frictional shear stress was used as a curve fitting parameter to available data (crack growth data, crack opening displacement data, and debond length data). Large variations in the frictional shear stress required to fit the experimental data indicate that the fiber bridging models in their present form lack predictive capabilities. However, these models provide an efficient and relatively simple engineering method for conducting parametric studies of the matrix growth behavior based on constituent properties. Bakuckas, J. G., Jr. and Johnson, W. S. Langley Research Center...
Author: American Society for Composites. Technical Conference
Publisher: CRC Press
ISBN: 9781566761031
Category : Technology & Engineering
Languages : en
Pages : 1168
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Author: W. Steven Johnson
Publisher: ASTM International
ISBN: 0803120397
Category : Metallic composites
Languages : en
Pages : 625
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Book Description
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: K. Salama
Publisher: Elsevier
ISBN: 1483294064
Category : Technology & Engineering
Languages : en
Pages : 3063
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Book Description
Held every four years, the International Congress on Fracture is the premier international forum for the exchange of ideas between scientists and engineers involved in producing and using materials resistant to fracture and fatigue. This major six-volume work which forms the proceedings of the Seventh International Congress on Fracture therefore provides the most comprehensive account available of the current status of research into fracture and fatigue, and the application of this knowledge to the design, fabrication and operation of materials and structures. As such, it will be an essential reference for materials scientists and mechanical, structural, aeronautical and design engineers with an interest in fracture and its prevention.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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