Academic literature on the topic 'Laminated plastics Testing'
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Journal articles on the topic "Laminated plastics Testing"
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Ng, S. C., Napsiah Binti Ismail, Aidy Ali, and Barkawi Sahari. "Defect Reconstruction in Laminated Composites by Ultrasonic Imaging." Applied Mechanics and Materials 263-266 (December 2012): 371–77. http://dx.doi.org/10.4028/www.scientific.net/amm.263-266.371.
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Ultrasonic method for the investigation of multi-layered laminates such as glass fiber reinforced plastics (GFRP) has been a challenging task in industry due to their inherent nature as a combination of constituents and the respective fabrication process. The coarse-grain structure of the material, fiber orientation and stacking sequence of laminated composites generate undesirable echoes for the ultrasonic signals during the testing. These echoes distributed randomly in time affects the measurements of ultrasonic parameters. In this paper, the utilization of attenuation and time-of-flight (TOF) of ultrasound signals to reconstruct the internal structure of GFRP subsurface region were investigated. Comparisons of these two methods were conducted on two sets of GFRP with different structure condition. Analysis of C-scan images constructed by amplitude and TOF were conducted in a two dimensional region map of the scanning profile. Experimental results showed that attenuation of amplitude gave a better indication of damage and successfully improved the defect region detection in multi-layered reinforced composite materials.
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Song, Leilei, Jialu Li, Yufen Zhao, Xiaoming Chen, and Li Chen. "Improvement of interlaminar shear strength of 2.5D fabric laminated composites with short-cut web interlayer." Journal of Polymer Engineering 37, no. 3 (2017): 261–69. http://dx.doi.org/10.1515/polyeng-2016-0029.
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Abstract In this study, the short-cut web interlayer and three-dimensional (3D) needle-punched technique were used to improve the interlaminar shear strength (ILSS) of 2.5D fabric laminated composites. The ILSS was measured by the short beam testing method, and the tensile and bending tests were carried out to investigate the in-plane mechanical properties. Observations on microstructure and crack propagation were carried out. The damage mechanisms of different 2.5D fabric laminated composites were analyzed. The results showed that the short-cut web interlayer and 3D needle-punched technique resulted in the improvement of ILSS, and they affected the tensile and bending properties of 2.5D fabric laminated composites.
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Azwan, Syed Mohd Saiful, Yahya Mohd Yazid, Ayob Amran, and Behzad Abdi. "Quasi-Static Flexural and Indentation Behaviour of Polymer-Metal Laminate." Advanced Materials Research 970 (June 2014): 88–90. http://dx.doi.org/10.4028/www.scientific.net/amr.970.88.
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Metal-polymer laminates were subjected to quasi-static flexural and indentation loading. The laminates were made of two aluminium skins heat-bonded (laminated) to a core made of polyethylene plastic material. The samples were trimmed into standard-sized beams and panels which were then tested in flexural and indentation using the Instron universal testing machine at loading rates of 1 mm/min, 10 mm/min and 100 mm/min. The load-displacement and energy absorption curves of the composite beams were recorded. It was found that the loading rate has a large effect on flexural and indentation behaviour of aluminium composite laminate.
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Taheri-Behrooz, F., M. Esmkhani, and A. Yaghoobi-Chatroodi. "Effect of testing procedure on the in-plane shear properties of CNF/glass/epoxy composites." Polymers and Polymer Composites 28, no. 3 (2019): 159–69. http://dx.doi.org/10.1177/0967391119867200.
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Many investigations have demonstrated that the addition of nanoscale particles could affect in-plane shear properties of the laminated composites. Besides, a variety of testing procedures were introduced to evaluate the in-plane shear properties of the multiscale composite materials. In the current research, Iosipescu shear, double V-notched rail, and off-axis tensile testing methods were used to measure in-plane shear modulus and strength of the glass/epoxy and carbon nanofiber (CNF) as 0.25 wt% CNF/glass/epoxy laminated composites. In-plane shear properties of the CNF/glass/epoxy specimens were increased in comparison with the neat glass/epoxy specimens using all three testing procedures. However, the improvements were not identical for all the testing methods. The maximum improvements in the in-plane shear modulus and strength recorded using off-axis tensile test method were as 11% and 15.6%, respectively. In the off-axis tensile test method, all in-plane stress components are activated in the fracture plane parallel to the fiber orientation which are responsible for the failure initiation and propagation. Consequently, enhancing the resin’s mechanical property and interface bonding quality using CNF could remarkably enhance the in-plane shear property of the CNF/glass/epoxy specimens. On the other hand, the special fiber orientation of the specimens in Iosipescu shear and V-notched rail methods prevents the reinforcing effects of the CNF particles to be effectively revealed.
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Chang, Fu-Kuo, Jian Mao Tang, and Douglas G. Peterson. "The Effect of Testing Methods on the Shear Strength Distribution in Laminated Composites." Journal of Reinforced Plastics and Composites 6, no. 4 (1987): 304–18. http://dx.doi.org/10.1177/073168448700600401.
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Cadavid, M. Ospina, O. Al-Khudairi, H. Hadavinia, D. Goodwin, and G. H. Liaghat. "Experimental Studies of Stiffness Degradation and Dissipated Energy in Glass Fibre Reinforced Polymer Composite under Fatigue Loading." Polymers and Polymer Composites 25, no. 6 (2017): 435–46. http://dx.doi.org/10.1177/096739111702500602.
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In this work, tensile and compressive properties and fatigue performances of laminated glass fibre-reinforced polymer (GFRP) composite under constant amplitude sinusoidal load control at frequency of 5 Hz and at room temperature were investigated for three different types of loading: tension-tension at R=0.1 and 0.5, reverse loading tension-compression at R=-1 and compression-compression at R=2 and 10 in the fibre and normal-to-fibre directions. From these series of tests, the corresponding S-N diagrams were obtained. The dynamic stiffness during fatigue loading showed classical degradation of the GFRP laminates. It was observed that the dynamic modulus decreased with time, and the hysteresis loop area changed with some distortion according to the loading conditions. Finally hysteresis loops throughout fatigue testing were examined, and the variation of energy dissipated per cycle throughout the specimen lifetime was quantified. It was demonstrated that the dissipated energy during the fatigue lifetime is dependent on R-ratio and fibre orientation. However, in majority of the cases, the energy dissipated per cycle near the end of the fatigue lifetime increases as a result of an increase in the area captured by hysteresis loops.
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Arnautov, A. K. "Evaluation of the possibilities of using the method of asymmetric bending for shear testing laminated composites." Mechanics of Composite Materials 27, no. 4 (1992): 418–25. http://dx.doi.org/10.1007/bf00613570.
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El-Sagheer, Islam, Amr A. Abd-Elhady, Hossam El-Din M. Sallam, and Soheir A. R. Naga. "An Assessment of ASTM E1922 for Measuring the Translaminar Fracture Toughness of Laminated Polymer Matrix Composite Materials." Polymers 13, no. 18 (2021): 3129. http://dx.doi.org/10.3390/polym13183129.
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The main objective of this work is to predict the exact value of the fracture toughness (KQ) of fiber-reinforced polymer (FRP). The drawback of the American Society for Testing Materials (ASTM) E1922 specimen is the lack of intact fibers behind the crack-tip as in the real case, i.e., through-thickness cracked (TTC) specimen. The novelty of this research is to overcome this deficiency by suggesting unprecedented cracked specimens, i.e., matrix cracked (MC) specimens. This MC exists in the matrix (epoxy) without cutting the glass fibers behind the crack-tip in the unidirectional laminated composite. Two different cracked specimen geometries according to ASTM E1922 and ASTM D3039 were tested. 3-D FEA was adopted to predict the damage failure and geometry correction factor of cracked specimens. The results of the TTC ASTM E1922 specimen showed that the crack initiated perpendicular to the fiber direction up to 1 mm. Failure then occurred due to crack propagation parallel to the fiber direction, i.e., notch insensitivity. As expected, the KQ of the MC ASTM D3039 specimen is higher than that of the TTC ASTM D3039 specimen. The KQ of the MC specimen with two layers is about 1.3 times that of the MC specimen with one layer.
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Kwon, Junbeom, Jaeyoung Choi, Hoon Huh, and Jungju Lee. "Evaluation of the effect of the strain rate on the tensile properties of carbon–epoxy composite laminates." Journal of Composite Materials 51, no. 22 (2016): 3197–210. http://dx.doi.org/10.1177/0021998316683439.
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This paper is concerned with evaluation and prediction of the tensile properties of carbon fiber-reinforced plastics laminates considering the strain rate effect at intermediate strain rates. Uniaxial tensile tests of carbon fiber-reinforced plastics laminates were conducted at various strain rates ranging from 0.001 s–1 to 100 s–1 using Instron 8801 and a high speed material testing machine to measure the variation of the elastic modulus and the ultimate tensile strength. Tensile test specimens were designed based on the ASTM standards and stacked unidirectionally such as [0°], [90°] and [45°] to predict the elastic modulus of carbon fiber-reinforced plastics laminates with various stacking sequences. The axial strain was measured by the digital image correlation method using a high speed camera and ARAMIS software to enhance the accuracy of the strain measurement. A prediction model of the elastic modulus of carbon fiber-reinforced plastics laminates is newly proposed in consideration of the laminate theory and the tensile properties of unidirectional carbon fiber-reinforced plastics laminates. The prediction model was utilized to predict the tensile properties of [0°/90°]s laminates, [±45°]s laminates, and [0°/±45/90°]T laminates for validation of the model. The elastic moduli predicted were compared with the static and dynamic tensile test results to confirm the accuracy of the prediction model.
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Subha, S., Battu Sai Krishna, Dalbir Singh, and R. Gokulnath. "Effect of Graphene Platelets/Fiber on Plastics Nanocomposites under Low-Velocity Impact Response." Applied Mechanics and Materials 852 (September 2016): 23–28. http://dx.doi.org/10.4028/www.scientific.net/amm.852.23.
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In this study, an attempt has made to explore the low-velocity impact response of a Carbon/epoxy laminate (CFRP) and E-Glass/epoxy laminates (GFRP). The composite was reinforced with Graphene Nanoplatelets (GnPs) and impact energy absorption capacity was studied. The plain GFRP and plain CFRP were served as a baseline for comparison. These composite laminate plates were fabricated using hand layup technique. The tests were carried out on the laminate plate as per ASTM D5628 FD. Impact tests were performed using a specially designed vertical drop-weight testing machine with an impactor mass of 1.926 kg. The result shows that laminate plate reinforced with GnPs reinforcement enhances the impact energy absorption capacity of the composites almost 4.5 % in the case Carbon/epoxy laminate and 3.5 % in the case of and E-glass/epoxy laminate. The enhanced impact resistance could be attributed to increased interlaminar fracture toughness of the fibres.
Dissertations / Theses on the topic "Laminated plastics Testing"
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Ramakrishnan, Karthik Ram Engineering & Information Technology Australian Defence Force Academy UNSW. "Low Velocity Impact Behaviour of Unreinforced Bi-layer Plastic Laminates." Awarded by:University of New South Wales - Australian Defence Force Academy. Engineering & Information Technology, 2009. http://handle.unsw.edu.au/1959.4/43918.
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Low velocity impact behaviour of bi-layered laminates of acrylic and polycarbonate was investigated using a combination of drop tower impact experiments and explicit finite element analysis in LS-DYNA. Material characterisation tests were conducted in tension and in compression to obtain material properties for input to the material model in the numerical analysis. Quasistatic plate bending tests were conducted at different loading rates to compare the quasistatic response of the materials to the impact behaviour. Impact tests on circular plates of monolithic acrylic and polycarbonate were carried out using an instrumented drop weight impact tester. The impact force histories were recorded and a multiparameter approach was used to determine critical energy. Acrylic exhibited radial cracking, spalling and pene- tration while polycarbonate underwent large deformation and failed by dishing and plugging. The damage caused by impact in the bilayered laminate included partial or full delamination at the interface and radial cracks in the acrylic layer. The low velocity impact responses were simulated using 8-noded solid elements in LS- DYNA. A node-splitting technique based on maximum tensile stress failure criterion and an erosion approach based on maximum principal stress criteria was used to model the failure of acrylic. A material model that takes into account the asym- metric behaviour in tension and compression was investigated. The delamination between the acrylic and polycarbonate plate was modelled by a tiebreak contact with a shear strength based failure. The results of the finite element simulations are in good agreement with the experimental data.
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Kelly, Gordon. "Joining of Carbon Fibre Reinforced Plastics for Automotive Applications." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3819.
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<p>The introduction of carbon-fibre reinforced plastics in loadbearing automotive structures provides a great potential toreduce vehicle weight and fuel consumption. To enable themanufacture and assembly of composite structural parts,reliable and cost-effective joining technologies must bedeveloped. This thesis addresses several aspects of joining andload introduction in carbon-fibre reinforced plastics based onnon-crimp fabric reinforcement.</p><p>The bearing strength of carbon fibre/epoxy laminates wasinvestigated considering the effects of bolt-hole clearance.The laminate failure modes and ultimate bearing strength werefound to be significantly dependent upon the laminate stackingsequence, geometry and lateral clamping load. Significantreduction in bearing strength at 4% hole deformation was foundfor both pin-loaded and clamped laminates. The ultimatestrength of the joints was found to be independent of theinitial bolt-hole clearance.</p><p>The behaviour of hybrid (bolted/bonded) joints wasinvestigated both numerically and experimentally. Athree-dimensional non-linear finite element model was developedto predict the load transfer distribution in the joints. Theeffect of the joint geometry and adhesive material propertieson the load transfer was determined through a parameter study.An experimental investigation was undertaken to determine thestrength, failure mechanisms and fatigue life of hybrid joints.The joints were shown to have greater strength, stiffness andfatigue life in comparison to adhesive bonded joints. However,the benefits were only observed in joint designs which allowedfor load sharing between the adhesive and the bolt.</p><p>The effect of the environment on the durability of bondedand hybrid joints was investigated. The strength and fatiguelife of the joints was found to decrease significantly withincreased ageing time. Hybrid joints demonstrated increasedfatigue life in comparison to adhesive bonded joints afterageing in a cyclic freeze/thaw environment.</p><p>The strength and failure mechanisms of composite laminatessubject to localised transverse loading were investigatedconsidering the effect of the specimen size, stacking sequenceand material system. Damage was found to initiate in thelaminates at low load levels, typically 20-30% of the ultimatefailure load. The dominant initial failure mode wasintralaminar shear failure, which occurred in sub-surfaceplies. Two different macromechanical failure modes wereidentified, fastener pull-through failure and global collapseof the laminate. The damage patterns and ultimate failure modewere found to depend upon the laminate stacking sequence andresin system. Finite element analysis was used to analyse thestress distribution within the laminates and predict first-plyfailure.</p><p><b>Keywords:</b>Composite, laminate, bearing strength,joining, load introduction, hybrid joint, finite elementanalysis, mechanical testing.</p>
Books on the topic "Laminated plastics Testing"
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Ashter, Syed Ali. Thermoforming of Single and Multilayer Laminates: Plastic Films Technologies, Testing, and Applications. Elsevier Science & Technology Books, 2013.
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Tingley, Dan A. The stress-strain relationships in wood and fiber-reinforced plastic laminae of reinforced glued-laminated wood beams. 1996.
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Tingley, Dan A. The stress-strain relationships in wood and fiber-reinforced plastic laminae of reinforced glued-laminated wood beams. 1996.
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Roland, Hernandez, and Forest Products Laboratory (U.S.), eds. Strength and stiffness of reinforced yellow-poplar glued-laminated beams. U.S. Dept. of Agriculture, Forest Service, Forest Products Laboratory, 1997.
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Roland, Hernandez, and Forest Products Laboratory (U.S.), eds. Strength and stiffness of reinforced yellow-poplar glued-laminated beams. U.S. Dept. of Agriculture, Forest Service, Forest Products Laboratory, 1997.
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IEEE Power Engineering Society. Insulated Conductors Committee., ed. IEEE guide for the design, testing, and application of moisture: Impervious, solid dielectric, 5-35 kV power cable using metal plastic laminates. Institute of Electrical and Electronics Engineers, 1995.
Find full textConference papers on the topic "Laminated plastics Testing"
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Sawant, Sourabh, and Anastasia Muliana. "A Nonlinear Viscoelastic Modeling of Fiber Metal Laminates." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-42152.
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A new class of advanced composite materials namely the fibermetal laminates (FMLs) such as ARALL (Aramid Reinforced Aluminum laminate) and GLARE (Glass Reinforced Aluminum laminate) has been developed for primary load bearing components of aircraft fuselage and wings. The FML is composed of alternating layers of fiber reinforced polymer (FRP) and aluminum sheets and shows good fatigue resistance. The metal layers are placed on the top and bottom of the laminate to provide good impact resistance and resistance to extreme environments (moisture, ultraviolet radiation and solvent). Krishnakumar (1994) has provided a survey of extensive works on manufacturing, testing, and modeling of the FMLs. The FMLs exhibit nonlinear viscoelastic and/or plastic behaviors due to the existence of FRP and metal alloy layers. The nonlinearity and time-dependent responses in the FMLs are intensified under high load levels, elevated temperatures, and humid environments. A predictive capability on the overall nonlinear viscoelastic response of the FMLs that recognizes different responses in the FRP and metallic layers becomes necessary. Literature indicates a few advances in this direction by the consideration of the elastic-plastic behavior and the use of classical lamination theory (Chen & Sun, 1989; Hashagen et al., 1995). Pindera et al. (1989) have carried out an experimental investigation of the creep response of ARALL laminates at 121°C. A pronounced viscoelastic behavior is observed in ARALL at stress levels below its proportional limit. Aluminum exhibits a nonlinear viscoelastic behavior while aramid-FRP shows a linear viscoelastic behavior. The classical lamination theory (CLT) was used to model the overall creep response of the laminates.
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Kavitha, Nijagal Shanthaveeraradhya, and Raghu V. Prakash. "Investigation of Scaling Effects on Post-Fatigue Residual Strength of Nanoclay Added GFRP Composites." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-62916.
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This paper describes the evaluation of post-fatigue residual strength of scaled laminated composites. The effect of thickness size effects of two scaled specimens on residual strength and stiffness of glass fiber reinforced plastic (GFRP) laminate with neat epoxy matrix and Nanoclay (Nanomer® I.30E) containing epoxy matrix are presented in this paper. The residual strength of a both scaled GFRP specimens with neat epoxy matrix and containing Nanoclay of 3% is determined by conducting tensile test on fatigue cycled after 2,00,000 cycles (R = 0.1). Tensile strength, residual strength and stiffness of both scaled specimens are compared with baseline or standard specimen of 4mm thick. The strength of thicker specimen (4 mm) is less compared to thinner (3mm and 2mm) specimens. The loss in strength due to fatigue loading varies with thickness of specimens, depends on the stiffness of the specimens. This complicates the transfer of mechanical properties from small scale specimen testing to use in the design of large scale structures. The stiffness increases in ply level scaled specimens and decreases in sublaminate level scaled specimens with addition of Nanoclay compared to pure epoxy matrix. The reduction in residual strength is same for different thicknesses of scaled nano-composite specimens. There is a potential in reducing scaling effects in composites with the addition of Nanoclay in matrix.
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Prakash, Raghu V., and Deepika Sudevan. "Post-Impact Thermo-Mechanical Response of Woven Mat Composites Subjected to Tensile Loading." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-66343.
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The thermo-mechanical response of carbon fiber reinforced polymer (CFRP) laminates subjected to continuous tensile loading and programmed interrupted tensile loading is examined to understand the changes due to damage progression. Quasi-isotropic laminates were prepared using 500 GSM twill weave carbon fabric with LY 556 resin and HY 991 hardener by hand lay-up technique, followed by curing under hot compression. A few specimens were subjected to an impact loading to 23 J and 51 J energy levels using a hemispherical tip to induce low velocity impact damage. Passive thermal imaging of woven CFRP laminates during tensile testing was captured using a TIM 160 Micro-epsilon infrared thermal camera. Temperature response during tensile testing provided a good correlation with deformation mode esp. for specimens impacted with 51 J of energy. Tensile tests were interrupted at periodic loads and unloaded and reloaded to study the thermal response after prior plastic deformation damage in the specimen. Unlike the case of GFRP specimens, distinct changes in thermo-elastic slope due to prior plastic deformation damage could not be clearly identified. As impact damage resulted in de-lamination of some layers, active thermography technique was used to study the rate of cooling of specimen with time when the damage is closer to the camera face as well as when it is away from the camera face. The cooling curves obtained were found to be dependent on the location of the damage, as well as on heating face of the specimen.
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Ueda, Masahito, Akira Todoroki, and Yasuyuki Kato. "Delamination Identification in Quasi-Isotropic CFRP Laminate Using Electric Potential Technique." In ASME 2008 Pressure Vessels and Piping Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/pvp2008-61451.
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Carbon fiber reinforced plastic (CFRP) laminate is very sensitive to an impact. Even a low impact creates a delamination, which deteriorates the compression strength of the laminate. Monitoring for delamination is indispensable to maintain the reliability of CFRP structures. Electric potential change method (EPCM) has been applied for CFRP as a nondestructive testing method although it has not yet been reported for the successful application to a quasi-isotropic CFRP laminate which is commonly used for various applications. Strong electrical anisotropy and inhomogenity of the laminate makes simple application of the method difficult. In this paper, a new concept was introduced to resolve the problem of the conventional method. The new method utilizes the piezoresistivity of CFRP woven fabric. Variation of strain on laminate surface due to delamination was measured as electric potential change of CFRP woven fabric. As CFRP woven fabric is generally stacked on the laminate on purpose to protect laminate surface, no additional sensor is required in the method. Delaminations were estimated from the electric potential changes as an inverse problem. Finite element studies were performed to investigate the applicability of the method. The simulation results indicated the validity of the method for delamination identification in quasi-isotropic CFRP laminate.
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Vijayakumar, Bhuvaneshwaran, and Yifan Guo. "Warpage Analysis of Panelized Molding Process for Plastic IC Packages." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-59168.
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Panelized molding process is vastly used in low cost molding process for PBGA (Plastic Ball Grid Array), LGA (Land Grid Array), QFP (Quad Flat Pack) and other types of packages. In a panelized molding process, arrays of packages are assembled on a substrate board, which is then molded as a single panel. After the molding process, the package array is cut into single packages. When laminated substrates are used, panel warpage formed during the molding process is very common due to the mismatches of material properties in the substrates and molding compounds. The warpage, however, is one of the major issues in the back-end assembly process. For example, the warpage can cause great difficulties in singulation. Large warpage could also cause high stresses in the components and results in reliability problems in the packages. In this paper, a 3-D finite element model is created to study the relations between the panel warpage and the material properties of the substrate boards and mold compounds. In a 40mmx50mm panel area, the model shows that the global warpage can be as high as +/-10 mils (0.25 mm) using different mold compounds. Test vehicles are assembled to validate the simulation results. The measurement data on warpage from the testing vehicles, although at first seems to vary over a large range across different panel designs, a closer observation and analysis suggests a definite trend and a strong correlation between the substrate panel and the mold compound properties.
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Ichikawa, Daiki, Masayuki Kitamura, Yuqiu Yang, and Hiroyuki Hamada. "Mechanical Properties of the Multilayer Laminated Intra-Hybrid Woven Fabric Composites." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-37864.
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Generally hybrid composite material is with two or more reinforcements or matrixes. They are referred as hybrid matrix and fiber hybrid. Further it is also included hybrid interface using different materials state of the interface. Therefore high functionality which compensates the disadvantages of each other by a hybrid can be expected. At current study, additionally, various strengthening forms were obtained and spread to textile material with hybrid(s). For example, techniques used in the weft and warp fibers/yarns might be different in making a fabric. It will be referred to as intra-layer hybrid fabric. It means in making fabric. It means that different physical properties due to the loading direction in one layer, the mechanical properties unique variety can be expected. In this study, carbon/glass intra-hybrid woven fabric was used to fabricate fiber reinforced plastic (FRP) composite through hand lay-up method. Then, the investigation on the mechanical property and fracture behaviour was carried out. Tensile test combined with acoustic emission (AE) measurement was conducted in this research. Knee point stress was the main factor of initial damage which discussed with AE characteristics during mechanical test. Due to the difference of energy release from fracture between glass fiber and matrix, the fracture characteristics of composite could be monitored during the test through AE facility. Relation between bundle and cracks inside the materials was examined through optical microscope. Scanning electron microscope observation was also carried out to examine the fracture of materials after testing.
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McKinnon, Colin, David J. Miles, and Raymond N. Burke. "Code Compliance of a New Metallic Composite Pipeline." In 2010 8th International Pipeline Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ipc2010-31254.
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The composite pipe system, known as XPipe™, is a steel strip laminate technology which uses high-performance adhesives to manufacture a metallic composite pipe. It offers a new method of low cost pipeline construction suitable for onshore gas and oil pipelines in a variety of configurations. The pipe is based on a thin wall liner that provides the fluid containment, the material of which will vary according to service requirements. Fusion bonded epoxy (FBE) coated martensitic ultra-high strength steel strips are then pre-formed and helically wound around the liner to form a laminated high strength reinforcing layer providing the pipe’s hoop strength. These are bonded using an adhesive. Unlike conventional linepipe that is manufactured in a pipe mill away from the construction site, this lightweight composite pipe can be produced at the construction facility using a portable manufacturing line. All components of the manufacturing process fit within standard ISO containers, each weighing between 5 and 15 tonnes. This allows for easy transportation via truck, and handling or shipping. Existing regulations and codes make no specific reference to metal composite pipes. They are mainly written for steel pipe lines with some mention of plastic pipe. The paper presents a comprehensive review of the following US onshore design codes (ASME B31.4/B31.8) and relevant regulations (CFR (DOT) 49 P192 / P195) in order to establish the applicability of these codes for use on XPipe. The paper describes how XPipe meets the code and regulation requirements with regard to safety, design, material, construction, inspection, testing, operation and maintenance. The paper will identify any areas where XPipe does not meet code and regulation requirements and describe the testing and /or design changes that have been made in order to meet the code requirements. The paper will focus on the how the XPipe can meet the practical requirements of these codes. The paper will describe how the qualification testing is being performed in accordance with DNV-RP-A203 Qualification Procedures for New Technology. The qualification testing focuses on how the XPipe meets or exceeds pipeline safety margins with regard to typical failure modes such as yield, burst, facture, fatigue, collapse, etc. This is a continuous process and is being updated after each step using the available knowledge on the status of the qualification.
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Roberts, Jordan, M. Kaysar Rahim, Safina Hussain, Jeffrey C. Suhling, Richard C. Jaeger, and Pradeep Lall. "Stresses in Area Array Assemblies Subjected to Thermal Cycling." In ASME 2009 International Mechanical Engineering Congress and Exposition. ASMEDC, 2009. http://dx.doi.org/10.1115/imece2009-11925.
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Thermal cycling accelerated life testing is often used to qualify area array packages (e.g. Ball Grid Arrays and Flip Chip) for various applications. Finite element life predictions for thermal cycling configurations are challenging due to the complicated temperature/time dependent constitutive relations and failure criteria needed for solders and encapsulants and their interfaces, aging/evolving material behavior (e.g. solders), difficulties in modeling plating finishes, the complicated geometries of typical electronic assemblies, etc. In addition, in-situ measurements of stresses and strains in assemblies subjected to temperature cycling is difficult because of the extreme environmental conditions and the fact that the primary materials/interfaces of interest (e.g. solder joints, die device surface, wire bonds, etc.) are embedded within the assembly (not at the surface). For these reasons, we really know quite little about the evolution of the stresses, strains, and deformations occurring within sophisticated electronic packaging geometries during thermal cycling. In our research, we are using test chips containing piezoresistive stress sensors to continuously characterize the in-situ die surface stress during long-term thermal cycling of several different area array packaging technologies including plastic ball grid array (PBGA) components, ceramic ball grid array (CBGA) components, and flip chip on laminate assemblies. The utilized (111) silicon test chips are able to measure the complete three-dimensional stress state (all 6 stress components) at each sensor site being monitored by the data acquisition hardware. The die stresses are initially measured at room temperature after packaging. The assemblies are then subjected to thermal cycling over various temperature ranges including 0 to 100 °C, −40 to 125 °C, and −55 to 125 °C, for up to 3000 thermal cycles. During the thermal cycling, sensor resistances at critical locations on the die device surface (e.g. the die center and die corners) are recorded. From the resistance data, the stresses at each site can be calculated and plotted versus time. The experimental observations show significant cycle-to-cycle evolution in the stress magnitudes due to material aging effects, stress relaxation and creep phenomena, and development of interfacial damage. The observed stress variations as a function of thermal cycling duration are also being correlated with the observed delaminations at the die surface (as measured using scanning acoustic microscopy (C-SAM)) and finite element simulations that include material constitutive models that incorporate thermal aging effects.