Residual Strength After Fatigue of a Cross-Ply Metal Matrix Composite at Elevated Temperature PDF Download
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Author: Alvin Ruiz
Publisher:
ISBN: 9781423579571
Category : Metallic composites
Languages : en
Pages : 109
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Book Description
The objective of this study was to investigate the residual strength of a cross-ply, SCS-6/Ti-15-3, metal matrix composite (MMC) at elevated temperature (427 deg C) when exposed to fatigue loading. Several specimens were subjected to a strain-controlled, fully reversed loading (R=-1), at various strain levels. The specimens were fatigued up to a portion of their life expectancy and then loaded to failure. Stress and strain data obtained during the test provided useful information for the macro-mechanical behavior of the material. It was determined that the residual strength was directly related to the amount of damage present in the matrix, meanwhile, the amount of matrix damage was dependent on the number of cycles and strain level the specimen had been exposed to. It was also observed that the residual strength under the strain controlled mode degraded more consistently than its counterpart under load controlled mode. This variation, however, may be due to the frequency and R-ratio differences between the two loading modes. The comparison of the residual strength degradation of the cross-ply vs. unidirectional laminates reflected a significant difference due to ply orientation. The unidirectional composite exhibited much less residual strength degradation due to the absence of the crack initiation action attributed to the 90 deg plies in the cross-ply.
Author: Alvin Ruiz
Publisher:
ISBN: 9781423579571
Category : Metallic composites
Languages : en
Pages : 109
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Book Description
The objective of this study was to investigate the residual strength of a cross-ply, SCS-6/Ti-15-3, metal matrix composite (MMC) at elevated temperature (427 deg C) when exposed to fatigue loading. Several specimens were subjected to a strain-controlled, fully reversed loading (R=-1), at various strain levels. The specimens were fatigued up to a portion of their life expectancy and then loaded to failure. Stress and strain data obtained during the test provided useful information for the macro-mechanical behavior of the material. It was determined that the residual strength was directly related to the amount of damage present in the matrix, meanwhile, the amount of matrix damage was dependent on the number of cycles and strain level the specimen had been exposed to. It was also observed that the residual strength under the strain controlled mode degraded more consistently than its counterpart under load controlled mode. This variation, however, may be due to the frequency and R-ratio differences between the two loading modes. The comparison of the residual strength degradation of the cross-ply vs. unidirectional laminates reflected a significant difference due to ply orientation. The unidirectional composite exhibited much less residual strength degradation due to the absence of the crack initiation action attributed to the 90 deg plies in the cross-ply.
Author: Sen-Tzer Chiou
Publisher:
ISBN: 9781423572695
Category : Metallic composites
Languages : en
Pages : 93
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Book Description
This study investigated the residual strength of the unidirectional and cross-ply laminates of SCS-6 / Ti-15-3, metal matrix composite at elevated temperature 427 deg C (800 deg F) after under tension-tension load controlled mode. For this purpose, several specimens were fatigued to various fractions of the fatigue life and then loaded monotonically to failure. The purpose of this study was to determine the effects of different levels of fatigue damage on the composite's strength. The unidirectional specimens were cycled at a 900 MPa maximum stress at a frequency of 10 Hz, while, the cross-ply specimens were tested at both 300 MPa and 450 MPa at 5 Hz and 10 Hz, respectively. The residual strength results for the three cases showed similar trends in that residual strength drop with cycles was small until near the end of the fatigue life. Both the unidirectional and cross-ply specimens demonstrated only a small drop of the residual strength with cycles until near the end of the fatigue life. (Author)
Author: Calcaterra, JR.
Publisher:
ISBN:
Category : Automotive medicine
Languages : en
Pages : 9
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Book Description
This study investigates the residual strength degradation of cross-ply, SCS-6/Ti-15-3 titanium matrix composite (TMC) due to elevated temperature fatigue. To accomplish this, several specimens were cycled at 427°C to certain fractions of their expected fatigue lives, then monotonically loaded to failure. Fatigue tests were conducted in both load-control mode with a load ratio (Rs) of 0.05 and strain-control mode with a strain ratio (Re) of - 1. Maximum stresses in the load-controlled tests were 300 and 450 MPa with frequencies of 5 and 10 Hz, respectively. The strain amplitudes ranged from 0.25 to 0.4% in the strain-controlled tests. Rather than being conducted at a constant frequency, these tests were performed at a strain rate of 0.1% per s. Various mechanical responses during cycling are discussed and compared for the load-controlled and strain-controlled tests. After failure, specimens were sectioned and studied using both optical and scanning electron microscopy. Residual strength data were then correlated to the amount and type of each damage mechanism. It was found that the residual strength degradation in cross-ply laminate, when exposed to different fatigue conditions, correlates together with the fraction of the cyclic life left in the composite.
Author: Leon B. Dennis (CAPT, USAF.)
Publisher:
ISBN:
Category : Metallic composites
Languages : en
Pages : 232
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 127
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Book Description
This research extends the existing knowledge of cross-ply metal matrix composites (MMC) to include fatigue behavior under strain-controlled fully reversed loading. This study investigated fatigue life, failure modes and damage mechanisms of the SCS-6/Ti-15-3, (O/9O)2s, MMC. The laminate was subjected to fully reversed fatigue at elevated temperature (427 deg C) at various strain levels. Stress, strain and modulus data were analyzed to characterize the macro-mechanical behavior of the composite. Microscopy and fractography were accomplished to identify and characterize the damage mechanisms at the microscopic level. Failure modes varied according to the maximum applied strain level showing either mixed mode (i.e. combination of both fiber and matrix dominated modes) or matrix dominated fatigue failures. As expected, higher strain loadings resulted in more ductility of the matrix at failure, evidenced by fracture surface features. For testing of the same composite laminate, the fatigue life under strain controlled mode slightly increased, compared to its load-controlled mode counterpart, using the effective strain range comparison basis. However, the respective fatigue life curves converged in the high cycle region, suggesting that the matrix dominated failure mode produces equivalent predicted fatigue lives for both control modes.
Author: Murray L. Scott
Publisher: Woodhead Publishing
ISBN: 9781855733534
Category : Composite materials
Languages : en
Pages : 836
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 170
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The objective of this research was to investigate the initiation and progression of damage which develops in notched (0/90) sub 2S SCS-6/Ti-15-3 at elevated temperature. Testing consisted of a monotonic tensile test at 427 deg C followed by fatigue testing performed under load control with a stress ratio of 0.1 at a frequency of 10 Hz. A crack was defined to have initiated when it had attained a length greater than or equal to 0.124 mm. Crack initiation and progression was monitored by strain and modulus observations and visual inspection via telemicroscope. The cracks were recorded with edge and face replicas. Metallographic and fractographic analysis was performed after specimen failure. Fatigue cracks initiated in the matrix at four locations on the front and back faces of each specimen. Two of these cracks became through-cracks and eventually developed into major cracks which caused the fracture. The applied stress (S) and fatigue lives (N) curves for both initiation and fatigue life were established. Also, crack growth curves as the function of fatigue cycles were established. A detailed metallographic analysis was performed to understand the damage mechanisms and its implication on the observed notched fatigue behavior.
Author: Shankar Mall
Publisher: CRC Press
ISBN: 1000717658
Category : Technology & Engineering
Languages : en
Pages : 478
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Book Description
A review and summary of advancements related to mechanical behavior and related mechanics issues of titanium matrix composites (TMCs), a class of high-temperature materials useful in the propulsion and airframe components in advanced aerospace systems. After an introduction to TMCs, different authors review and summarise the advancements related to mechanical behavior and related mechanics issues of TMCs.
Author: Matthew W. Yocum (2LT, USAF.)
Publisher:
ISBN:
Category : Metallic composites
Languages : en
Pages : 262
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Book Description
