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Effect Of Ply Thickness On The Damage Development In Composite Laminates Preprint
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Book Synopsis Effect of Ply Thickness on the Damage Development in Composite Laminates (Preprint). by :
Download or read book Effect of Ply Thickness on the Damage Development in Composite Laminates (Preprint). written by and published by . This book was released on 2006 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper describes the experimental investigation on the effect of ply thickness on the first ply failure, delamination, and the subsequent final failure of graphite/epoxy composite laminates. The laminates considered in this paper are a cross-ply and two quasi-isotropic laminates containing thin plies in the desired interface. The onset of the first ply failure and delamination, and the stress-free temperature are experimentally determined. The experimental results for ply crack and delamination development were compared with an analytical model. The results indicated that ply thickness played a significant role on delaying damage onset. The experimental results were compared with the Weibull statistical theory in conjunction with the weakest link theory and discussed on the effect of size (ply thickness) on damage initiation.
Book Synopsis Analytical and Experimental Characterization of Damage Processes in Composite Laminates by : George J. Dvorak
Download or read book Analytical and Experimental Characterization of Damage Processes in Composite Laminates written by George J. Dvorak and published by . This book was released on 1988 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents a brief summary of the principal results obtained in a research program on damage development in fibrous composite laminates. The following technical subjects are described: (i) Effect of transverse cracks and fiber breaks on stiffness changes in unidirectional and laminated plates. (ii) Effect of ply thickness on initial failure and on progressive cracking in brittle matrix laminates, and (iii) Analysis of progressive cracking in metal and polymer composite laminates. Work in progress is discussed as well. Keywords: Composite materials, Cracking, Damage accumulation. (jes).
Book Synopsis Effect of Ply Constraint on Fatigue Damage Development in Composite Material Laminates by : WW. Stinchcomb
Download or read book Effect of Ply Constraint on Fatigue Damage Development in Composite Material Laminates written by WW. Stinchcomb and published by . This book was released on 1981 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laminae of composite materials are bonded together to form a laminate for the purpose of achieving strength and stiffness in certain desired directions. Although a direct use of laminae strength and stiffness properties can be used to determine the properties of an undamaged laminate, it is well known that the manner in which local damage initiates, grows, and combines is not the same in an unconstrained lamina as it is when the same lamina is constrained by other laminae in a laminate. This paper addresses the question of constraint effects directly and discusses the consequences of such effects on the development of fatigue damage in graphite epoxy laminates. Results of monotonic tension tests, tension-tension fatigue tests, and nondestructive investigations are reported for several constraint situations and are compared with the results of several analyses.
Book Synopsis The Effect of Ply Thickness on the Initiation and Growth of Delamination in Graphite/epoxy Laminates with Holes Under Compressive Cyclic Loading by : Stephen C. Nolet
Download or read book The Effect of Ply Thickness on the Initiation and Growth of Delamination in Graphite/epoxy Laminates with Holes Under Compressive Cyclic Loading written by Stephen C. Nolet and published by . This book was released on 1984 with total page 362 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of "effective ply thickness" on initiation and growth of damage in [+-45xn/0xn]s (qhwew n=1,2, and 3) graphite/epoxy laminates with 6.35 mm holes under compressive cyclic loading has been investigated. Static and cyclic compressive testing was done on axially loaded sandwich specimens. Out-of-plane Moire interferometry and pulse-echo ultrasonic inspection was used to monitor cyclic test specimens for delamination damage. The compressive static tests on the [+-45xn/Oxns sandwich specimens showed no "effective ply thickness" dependence on the compressive fracture stress of 423 MPa. Cyclic tests on the [+-45/0]s specimens showed three different types of damage development for the same applied peak stress: one, a damage mode that led to immediate transverse failure; two, delamination that initiated at the hole edge and grew radially from the hole; and three, a delamination that initiated at the top and bottom of the hole and grew longitudinally within the width of the hole. However, all the [+-45x2/0x2]s and [+-45x3/0x3]s laminates developed only the longitudinal delamination type of damage. The growth of longitudinal delamination was found to be a linear function of the logarithm of the number of applied load cycles. This damage initiates earlier as the "effective ply thickness" and/or peak cyclic stress increases. Furthermore, the growth rate increases with "effective ply thickness." Longitudinal delamination develops due to splitting in the 0° plies of the laminate and subsequent shear failure of the -45°/0° interface between the 0 splits. This mode of damage was also observed in two tensile cyclic tests. results of residual strength testing showed that laminates with longitudinal delamination had an average residual tensile stress of 640 MPa. This is approximate a 50% increase over the ultimate tensile stress of 455 MPa determined from static tensile tests on six coupons and eight sandwich specimens (uncycled) of the [+-45/0]s laminate.
Book Synopsis Fatigue Damage-Strength Relationships in Composite Laminates. Volume 2 by : Kenneth L. Reifsnider
Download or read book Fatigue Damage-Strength Relationships in Composite Laminates. Volume 2 written by Kenneth L. Reifsnider and published by . This book was released on 1984 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents information and experience generated during the subject investigation which provided support for the major thrust of the effort, but was not the eventual focus of the program. The activities are discussed in the context of the various experimental techniques used (and developed) to investigate the context of the damage development. Whil much of the information discussed is not complete, it is thought that a description of the experimental methods and experiences will be valuable to the technical community. Included are descriptions of virtually every experimental technique used in this program and a variety of findings not discussed elsewhere.
Book Synopsis The Effect of Ply Thickness on Longitudinal Splitting and Delamination in Graphite/epoxy Under Compressive Cyclic Load by : Paul A. Lagace
Download or read book The Effect of Ply Thickness on Longitudinal Splitting and Delamination in Graphite/epoxy Under Compressive Cyclic Load written by Paul A. Lagace and published by . This book was released on 1984 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The initiation and growth of damage due to compressive cyclic loading was investigated in [±45n/0/n]s graphite/epoxy laminates where the "effective ply thickness" was varied by allowing n to take on the values 1, 2, and 3. A total of thirty-five axially-loaded sandwich specimens with 6.35 mm diameter holes were cycled at 7 Hz at peak stress levels of 52% to 72% of the static ultimate compressive stress of 425 MPa (which was experimentally determined to be independent of the value of n). Out-of-plane moire interferometry and pulse-echo ultrasound techniques were used to nondestructively inspect the specimens and showed that three distinct modes of damage growth occur in these laminates. Delamination which initiates at the hole and grows in a radial or transverse fashion occurred only in 60% of the [±45/0]s specimens. For these two types of damage, the growth was rapid and led to catastrophic failure of the specimen. The remainder of the [±45/0]s specimens and all the laminates where the effective ply thickness was doubled and tripled, [±45 2/02]s and [± 45 3/03]s, exhibited delaminations which initiated at the hole edges and grew parallel to the load direction with the width of the delamination equal to the width of the hole. Catastrophic failure did not occur in these cases. There is a linear relationship between the delamination length and the logarithm of the number of applied load cycles in all these cases. However, the delamination initiated earlier and at lower stress levels for laminates with larger effective ply thicknesses. Specimen sectioning and microscopic examination shows that this damage depends on the development of splitting in the 0° plies and subsequent delamination as a result of shear failure at the -45°/0° ply interface in the region between the splits. Several [0/±45]s and [02/±45 2]s coupon specimens were cycled in tension and this splitting and subsequent delamination also developed. Residual tensile strength tests conducted on graphite/epoxy coupons debonded from the honeycomb after cycling showed a 50% increase in tensile strength over undamaged specimens with 6.35 mm diameter holes. This is attributed to the redistribution of stress around the hole due to the relieving of stress concentration in the 0° plies by the splitting and delamination
Book Synopsis Quantifying Distributed Damage in Composites Via the Thermoelastic Effect by : Brian Joseph Mahoney
Download or read book Quantifying Distributed Damage in Composites Via the Thermoelastic Effect written by Brian Joseph Mahoney and published by . This book was released on 1992 with total page 440 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effects of Ply Damage on Failure of Composite Laminates Containing a Circular Hole by : Roger DeWayne Howell
Download or read book The Effects of Ply Damage on Failure of Composite Laminates Containing a Circular Hole written by Roger DeWayne Howell and published by . This book was released on 1983 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thickness Effects on Impact Response of Composite Laminates by :
Download or read book Thickness Effects on Impact Response of Composite Laminates written by and published by . This book was released on 1998 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: In an effort to understand the impact response of composite laminates, various degrees of impact ranging from subperforation to perforation were introduced to glass/epoxy laminates through an instrumented drop-weight impactor. In addition, composite laminates of two thicknesses were examined for thickness effects. Experimental results showed that thickness plays a very important role in impact response. The impacted composite laminates were then subjected to compression after impact (CAI) tests for characterizations of residual mechanical properties. Experimental results showed that perforation was the most important damage stage in composite laminates subjected to impact loading since impact characteristics (peak force, contact duration, and absorbed energy) and mechanical properties degradation (residual compressive maximum force and residual compressive absorbed energy) of composite laminates became stable once perforation took place. Since the impact response of composite laminates is due to plate bending to some extent, bending analysis was used to explain the thickness effect.
Book Synopsis Scaling Effects on Damage Development, Strength, and Stress-rupture Life of Laminated Composites in Tension by : J. André Lavoie
Download or read book Scaling Effects on Damage Development, Strength, and Stress-rupture Life of Laminated Composites in Tension written by J. André Lavoie and published by . This book was released on 1997 with total page 290 pages. Available in PDF, EPUB and Kindle. Book excerpt: About strength scaling, size effects, microcracking, first-ply failure, delamination, composite material, Weibull statistics, tension testing, flexural testing, carbon epoxy, glass epoxy, creep, stress-rupture, creep-rupture, stress relaxation, stress-corrosion cracking, durability, and stress-rupture life of E-glass/913 quasi-isotropic composite laminates. Discusses the effects of creep in the various plies and increasing thickness by ply-level scaling.
Book Synopsis Fatigue Life Prediction of Cross-Ply Composite Laminates by : IM. Daniel
Download or read book Fatigue Life Prediction of Cross-Ply Composite Laminates written by IM. Daniel and published by . This book was released on 1989 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fatigue damage development in cross-ply laminates consists of transverse matrix cracking followed by longitudinal matrix cracking, local delaminations at crack intersections, and ultimately longitudinal fiber breakage of the load-carrying plies. Ultimate failure is determined by the manner in which the load is redistributed and transferred into the load-carrying plies. A model was developed for predicting fatigue life of cross-ply laminates which develop transverse cracking up to the characteristic damage state (CDS) level before fatigue failure. The fatigue life consists of two portions: the portion necessary to reach the CDS and the residual life after attainment of the CDS. A procedure for estimating the CDS life is described based on the relationship between residual stiffness and crack density and the stress-life (S-N) curve of the 90° lamina. The residual life after CDS was obtained by calculating the stress carried by the 0° plies and assuming that these plies within the damaged laminate behave like a 0° lamina under cyclic loading. Fatigue life predictions were in good agreement with experimental results for three graphite/epoxy cross-ply laminates.
Book Synopsis The Development of Fatigue Damage Around Fastener Holes in Thick Graphite/Epoxy Composite Laminates by : D. S. Saunders
Download or read book The Development of Fatigue Damage Around Fastener Holes in Thick Graphite/Epoxy Composite Laminates written by D. S. Saunders and published by . This book was released on 1993 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper discusses the mechanisms by which damage develops and grows around countersunk fastener holes in composite laminates under fatigue loading conditions. Experiments have shown that the erosion of material between ply layers nucleates delaminations which then grow through the laminate under the action of the fatigue loads. The damage at the hole bore surface produces sites for the nucleation of delaminations. The morphology of the delaminations and ply cracking was mapped extensively and from these maps it was found that the volume of material around the fastener hole, .damaged by the fatigue loading, adopted a characteristic shape, the volume of damaged laminate increased towards the faying surface of the laminate and (metal) fixture. This characteristic damage volume was generated by the fastener rocking under the fatigue loads. Growth of the delaminations has been shown to be preceded by intraply cracking and, as fatigue loading proceeded, more delaminations were generated at the hole bore surface. The interfacial region between the composite laminate and the fixture also provided the nucleation site for fatigue cracks in the fasteners. The effects of initial fastener-hole clearances on damage nucleation and growth, . did not appear to follow any clear pattern. However, coupons with excessive initial hole clearances did appear to exhibit greater than expected damage growth after only one sequence block. Composite materials, Mechanically fastened joints, Fatigue loading, Fatigue damage, Damage development, Damage mechanisms, Thick laminates, Graphite/epoxy.
Book Synopsis Advanced Fatigue Damage Development in Graphite Epoxy Laminates by : Russell Douglas Jamison
Download or read book Advanced Fatigue Damage Development in Graphite Epoxy Laminates written by Russell Douglas Jamison and published by . This book was released on 1982 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental investigation of damage development in T300/5208 graphite epoxy laminates subjected to tension-tension cyclic loading are reported. The concept of laminate stiffness reduction as a damage analogue is shown to be a valuable means of test control and damage interpretation. The relationship between stiffness and number of cycles is shown to be unique for each laminate type studied, each possessing three distinct stages, but markedly different among the laminate types. By using two complementary nondestructive evaluation (NDE) techniques, edge replication and penetrant-enhanced stereo X- ray radiography along with a method for deploying fatigue-damaged specimens, the stages of stiffness reduction were found to correspond variously to the predominance of matrix cracking or delamination or interactions of these matrix damage modes. A number of subordinate matrix damage modes including interior delamination, microcracking, and longitudinal splitting are identified with the matrix cracks which produce them.
Book Synopsis The Effect of Ply Thickness on Delamination of Advanced Composites by : John C. Brewer
Download or read book The Effect of Ply Thickness on Delamination of Advanced Composites written by John C. Brewer and published by . This book was released on 1984 with total page 67 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of ply and laminate thickness on the fracture of graphite/epoxy due to delamination was investigated. Four laminate types were tested: [±15na]s, [±l5n/0n]s', [0n/±l5n]s' and [±45n/0/n]s. "Effective ply thickness" was varied by stacking several plies of the same orientation together. It was found that an increase in effective ply thickness caused a decrease in fracture stress due to delamination in all cases. It was also found that the thickness dependence is not merely a laminate thickness dependence. "Back-to-back" [0/±15]s-type laminates (i.e. [[O/±15]s]2 and [[O/±15]s]3 laminates) were found to have the same strength as [0/±15]s laminates.
Book Synopsis An Investigation Into the Effects of Damage on the Stresses in a Composite Laminate by : Eric Walter Nottorf
Download or read book An Investigation Into the Effects of Damage on the Stresses in a Composite Laminate written by Eric Walter Nottorf and published by . This book was released on 1990 with total page 310 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Analytical Study of Fatigue Damage in Notched Graphite/epoxy Laminates by :
Download or read book Experimental and Analytical Study of Fatigue Damage in Notched Graphite/epoxy Laminates written by and published by . This book was released on 1979 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Damage Prediction in Cross-plied Curved Composite Laminates by :
Download or read book Damage Prediction in Cross-plied Curved Composite Laminates written by and published by . This book was released on 1991 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
