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Academic literature on the topic 'Plates, Aluminum Cracking'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Plates, Aluminum Cracking"

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Jaiganesh, V., D. Srinivasan, and P. Sevvel. "Optimization of process parameters on friction stir welding of 2014 aluminum alloy plates." International Journal of Engineering & Technology 7, no. 1.1 (December 21, 2017): 9. http://dx.doi.org/10.14419/ijet.v7i1.1.8906.

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Aluminum Alloy 2014 is a light weight high strength alloy used widely in the aerospace and also in other industries. 2014 is the second most popular of the 2000-series aluminium alloys, after 2024 aluminium alloy. However, it is difficult to weld, as it is subject to cracking. Joining of 2014 aluminium alloy in friction stir welding which is based on frictional heat generated through contact between a rotating tool and the work piece. Determination of the welding parameters such as spindle speed, transverse feed , tilt angle plays an important role in weld strength. The whole optimization process is carried out using Taguchi technique. The SEM analysis is done to check the micro structure of the material after welding by electron interaction with the atoms in the sample. Tensile test have been conducted and the s-n ratio curve is generated. The test is conducted and analysed on the basis of ASTM standards.
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Zivkovic, Predrag, Slobodan Jovanovic, Konstantin Popov, and Nenad Ilic. "Modification of the aluminum for making offset printing plates." Journal of the Serbian Chemical Society 65, no. 12 (2000): 935–38. http://dx.doi.org/10.2298/jsc0012935z.

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Aluminum as the base of offset printing plates should make good contact with wetting agents and the light sensitive layer and should be resistant to wear and cracking. In order to achieve this, the aluminum is roughened and eventually anodized. A thin, electrochemically deposited chromium layer is used as the non-printing element in bimetallic offset printing forms. Chromium shows excellent wettability and wear resistance. The possibility of chemical deposition of chromium on aluminum from an alkaline solution is examined in this paper. The presence of chromium was confirmed and measured by EDAX. A difference in the spectral reflection characteristic between chromium-treated and non-treated specimens was also detected. An influence of a chromium layer on an aluminum surface was examined by water drop spreading. Chromium-treated samples showed better wettability than non-treated samples, but they are less wettable than anodized samples.
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Zhou, Yu Tong, Zheng Qiang Zhou, Jiong Geng Wang, Hong Jian Luo, Jie Zhang, and Jia Yuan Hu. "Study on Cracking of Aluminum Alloy Strain Clamps for 500kV Transmission Line." Solid State Phenomena 279 (August 2018): 10–15. http://dx.doi.org/10.4028/www.scientific.net/ssp.279.10.

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It was found that a large number of aluminum alloy strain clamps cracked. Cracking mainly occurred in the drainage plate of strain clamps. Nondestructive testing technologies and physicochemical analysis devices such as optical microscope, spectrograph, SEM and EDS were adopted to analyze the reasons of cracking. The results tell that there are numerous shrinkage cavities and cracks inside the drainage plate of strain clamps. The maximum area fraction of shrinkage cavities is 10.7%, and the maximum size is over 1mm2. A lot of shrinkage cavities and cracks gather together to form big flaws, which seriously reduce the mechanical properties of the drainage plates. After a long period of vibration, cracks gradually develop to the surrounding cavities and connect adjacent cavities. Eventually, cracks develop to the surface of drainage plates.
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Chang, Hong, and Wei Zhou. "Stiffness and Crack Behavior of Unbonded Posttensioned Concrete Beam Strengthened with Aluminum Alloy Plate." Advances in Civil Engineering 2020 (September 30, 2020): 1–13. http://dx.doi.org/10.1155/2020/3824543.

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Corrosion resistance of aluminum alloy plates externally bonded by magnesium phosphate cement provides the ability to strengthen inshore infrastructures in harsh environments subject to moisture and humidity. In this study, the aim is to study the stiffness and cracking behavior of concrete beams using this strengthening technique. Six damaged unbonded posttensioned concrete beams were repaired and strengthened and then subjected to monotonic load until failure. This technique improved the stiffness and limited the development of cracks. The formula of elastic-plastic stiffness coefficient related to the comprehensive reinforcement index was established. An influence coefficient δ considering the effect of aluminum alloy plates and unbonded tendons was introduced, and the crack expansion coefficient under short-term load was obtained by statistical analysis. Finally, some simplified methods were proposed to evaluate the stiffness and cracks of unbonded posttensioned concrete beams strengthened with aluminum alloy plates.
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Peter, Ildiko, and Mario Rosso. "Study of 7075 Aluminium Alloy Joints." Scientific Bulletin of Valahia University - Materials and Mechanics 15, no. 13 (October 1, 2017): 7–11. http://dx.doi.org/10.1515/bsmm-2017-0011.

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AbstractHigh-strength EN AW 7075 Al-based alloy (Al-Zn-Mg-Cu) is currently employed in many industrial fields where excellent mechanical performances of structural components are required. In contrast to the many positive features this alloy presents, it is not fusion weldable, because it is subjected to solidification and liquation cracking. In this paper, the possibility to weld low thickness plates, made of 7075 aluminum alloy, by the tungsten inert gas welding technique will be presented. Two types of welding have been performed: for the former one, welding involves only one surface, while for the second one, welding has been carried out on both faces of the plates. After welding, microstructural analysis and mechanical properties investigations have been carried out. The present research highlights that the mechanical properties evolution is affected by the welding procedure. In particular, the mechanical strength reached for the samples welded on both faces, in the proposed setting, is comparable to that of the un-welded alloys.
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Yang, Yang, Li Xiao, Wenzhong Qu, and Ye Lu. "Passive detection and localization of fatigue cracking in aluminum plates using Green’s function reconstruction from ambient noise." Ultrasonics 81 (November 2017): 187–95. http://dx.doi.org/10.1016/j.ultras.2017.06.021.

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Li, Yanlei, Shanglei Yang, Zeng Peng, Zhentao Wang, and Zihao Gao. "Microstructure, Fatigue Properties and Stress Concentration Analysis of 6005 Aluminum Alloy MIG Welded Lap Joint." Materials 15, no. 21 (November 2, 2022): 7729. http://dx.doi.org/10.3390/ma15217729.

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This paper studies the microstructure and mechanical properties of MIG (Melt Inert Gas) lap welded 6005 aluminum alloy plates. Microstructure analysis (OM) of the joint showed that 15~30 μm small grains were observed at the fusion line. Mechanical analysis shows that the small grains are broken by shielding gas and molten pool flow force. Hardness test shows that there is a softening zone (41~43 HV) in HAZ much lower than BM and WZ. The low cycle fatigue test showed that the performance of lap joint decreased sharply, and the fatigue strength of weld decreased significantly, which was only 27.34% of the base metal. The fatigue fracture (SEM) of the weld observed slip band cracking and a large number of brittle fracture characteristics. Using the stress concentration factor Kt for analysis, it was found that the cause of brittle fracture was mostly stress concentration. Lap joint stress concentration model appears in two ways: firstly, at the weld toe, the weld is subjected to eccentric force, secondly, there is a small gap between the two plates at the weld root, which cracks along the direction of 45° of the maximum shear stress.
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Lee, Ho Sung, Ye Rim Lee, and Kyung Ju Min. "Influence of Tool Rotational Speed on the Mechanical Properties of Friction Stir Welded Al-Cu-Li Alloy." Materials Science Forum 857 (May 2016): 228–31. http://dx.doi.org/10.4028/www.scientific.net/msf.857.228.

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Aluminum-Lithium alloys have been found to exhibit superior mechanical properties as compared to the conventional aerospace aluminum alloys in terms of high strength, high modulus, low density, good corrosion resistance and fracture toughness at cryogenic temperatures. Even though they do not form low-melting eutectics during fusion welding, there are still problems like porosity, solidification cracking, and loss of lithium. This is why solid state friction stir welding is important in this alloy. It is known that using Al-Cu-Li alloy and friction stir welding to super lightweight external tank for space shuttle, significant weight reduction has been achieved. The objective of this paper is to investigate the effect of friction stir tool rotation speed on mechanical and microstructural properties of Al-Cu-Li alloy. The plates were joined with friction stir welding process using different tool rotation speeds (300-800 rpm) and welding speeds (120-420 mm/min), which are the two prime welding parameters in this process.
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Chen, Wenjing, Wei Lu, Guoqing Gou, Liwen Dian, Zhongyin Zhu, and Junjun Jin. "The Effect of Fatigue Damage on the Corrosion Fatigue Crack Growth Mechanism in A7N01P-T4 Aluminum Alloy." Metals 13, no. 1 (January 4, 2023): 104. http://dx.doi.org/10.3390/met13010104.

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A7N01P-T4 aluminum alloy plates for high-speed trains will experience a certain amount of fatigue damage under alternating loads. Three groups of samples, P0 (no fatigue damage), P1 (loading stress 30 MPa), and P2 (loading stress 70 MPa), were created, and corrosion fatigue crack growth (CFCG) tests were conducted in 3.5 wt.% NaC1 solution. The crack growth rate was found to increase after fatigue damage as the damage degree increased. In addition, the A7N01P-T4 aluminum alloy base metal exhibited obvious secondary cracks and crack bifurcations after fatigue damage. It is believed that fatigue damage causes stress concentration in the material, while a certain degree of stress corrosion cracking occurs during the CFCG growth process. This is because hydrogen (H) easily accumulates and diffuses along the grain boundary, which reduces the strength of the grain boundary, thereby becoming the preferred orientation for crack growth. This explains why the CFCG rate of the material is accelerated following fatigue damage to a certain extent.
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Jiang, Lanxin, Shoune Xiao, Jingke Zhang, Ruijuan Lv, Bing Yang, Dawei Dong, Guangwu Yang, and Tao Zhu. "Experimental and Simulation Studies on the Compressive Properties of Brazed Aluminum Honeycomb Plates and a Strength Prediction Method." Metals 10, no. 11 (November 20, 2020): 1544. http://dx.doi.org/10.3390/met10111544.

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To study the compressive mechanical properties of a new type of brazed aluminum honeycomb plate (BAHP), tensile tests on single- and brazed-cell walls as well as compression tests in the out-of-plane, in-plane longitudinal, and transverse directions were conducted. Compared to the material properties of a traditional glued aluminum honeycomb plate (GAHP), those of the single- and brazed-cell walls of the BAHP are entirely different. Therefore, their characteristics should be considered separately when performing theoretical and simulation analysis. Under out-of-plane compression, the core of the BAHP did not debond, owing to its higher strength than that of the GAHP. In comparison, under in-plane compression in the longitudinal and transverse directions, the load–displacement characteristics, ultimate load, and failure modes also differed, and there was no large-scale cracking. Considering the characteristics of the BAHP, a strength prediction method was proposed. The simulation results demonstrated that the model built based on the new method was highly consistent with the experimental results. Defects with uneven height and debonding will cause the overall instability, and the degree of defects will influence the strength and instability displacement, which have little impact on the elastic stage. Moreover, the model considering defects is closer to the test results.
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Dissertations / Theses on the topic "Plates, Aluminum Cracking"

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Kieboom, Orio Terry Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "The conjunctive use of bonded repairs and crack growth retardation techniques." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2007. http://handle.unsw.edu.au/1959.4/38712.

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In an attempt to find a way of improving the damage tolerance of composite bonded repairs to metallic aircraft structures, the effect of using conventional crack growth retardation techniques in conjunction with bonded repairs was experimentally investigated. Hence, an experimental test program was set up to determine whether fatigue crack growth under bonded repairs is retarded further by giving the crack to be repaired a crack growth retardation treatment prior to repair patch application. In addition, it was set up to determine the influence of a bonded repair on the effectiveness of a crack growth retardation method. Centrally cracked aluminium plates were used. Stop drilling followed by cold hole expansion and the application of single overloads were selected as retardation treatments. Two patch materials were considered; boron/epoxy and Glare 2. Further test variables were the aluminium alloy and the plate thickness. Fatigue testing was carried out under constant amplitude loading and baseline results were determined first. In addition to optically monitoring the crack growth, local and global out-of-plane deformations were visualised with holographic interferometry and shadow moire??. Furthermore, the stress intensity factors under the repair patch were examined with strain gauges and measurement of the central crack opening displacement. Disbonds and fracture surfaces were studied after residual strength tests. The crack growth results obtained showed that retardation treatments decrease crack growth rates under a repair patch and that the effectiveness of a retardation treatment is increased by the patch. Although identical crack growth rates were observed under boron/epoxy and Glare 2 patches, the reinitiation period after the retardation treatment lasted longer when Glare 2 patches were applied. Analytical predictions of the extent of retardation based on existing models showed that the conjunctive effect of retardation treatments and bonded repairs was underestimated. A sustained reduction in crack growth rates was observed under bonded repairs with a prior overload retardation treatment. It was concluded that the damage tolerance of bonded repairs is increased by the application of a crack growth retardation treatment because the crack growth is retarded further. These findings indicate that the range of cracks in aircraft for which bonded repairs can be considered is expanded and that economic benefits can be obtained.
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Books on the topic "Plates, Aluminum Cracking"

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Schra, L. Long-term outdoor stress corrosion testing of overaged 7000 series aluminium alloys. Amsterdam: National Aerospace Laboratory, 1988.

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Center, Langley Research, ed. Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Center, Langley Research, ed. Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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5

Talivaldis, Spalvins, and United States. National Aeronautics and Space Administration., eds. The effect of ion plated silver and sliding friction on tensile stress-induced cracking in aluminum oxide. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Book chapters on the topic "Plates, Aluminum Cracking"

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"Corrosion of Nonferrous Alloy Weldments." In Corrosion of Weldments, 143–68. ASM International, 2006. http://dx.doi.org/10.31399/asm.tb.cw.t51820143.

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Abstract The nonferrous alloys described in this chapter include aluminum and aluminum alloys, copper and copper alloys, titanium and titanium alloys, zirconium and zirconium alloys, and tantalum and tantalum alloys. Some of the factors that affect the corrosion performance of welded nonferrous assemblies include galvanic effects, crevices, assembly stresses in products susceptible to stress-corrosion cracking, and hydrogen pickup and subsequent cracking. The emphasis is placed on the compositions, general welding considerations, and corrosion behavior of these alloys.
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Harmi Tjahjanti, Prantasi, and Septia Hardy Sujiatanti. "Finite Element Method for Ship Composite-Based on Aluminum." In Finite Element Methods and Their Applications. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.94973.

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The structure and construction of ships made of aluminum alloy, generally of the type of wrought aluminum alloy, when experiencing fatigue failure caused by cracking of the ship structure, is a serious problem. Judging from the ‘weaknesses’ of aluminum material for ships, this chapter will explain the use of alternative materials for ship building, namely aluminum-based composite material which is an aluminum alloy AlSi10Mg (b) ship building material based on the European Nation (EN) Aluminum Casting (AC) - 43,100, with silicon carbide (SiC) reinforcement which has been treated with an optimum composition of 15%, so that the composite material is written with EN AC-43100 (AlSi10Mg (b) + SiC * / 15p. Composite ship model using ANSYS (ANalysis SYStem) software to determine the distribution of stress. The overall result of the voltage distribution has a value that does not exceed the allowable stress (sigma 0.2) and has a factor of safety above the minimum allowable limit, so it is safe to use. The reduction in plate thickness on the EN AC-43100 (AlSi10Mg (b)) + SiC * /15p composite vessel is significant enough to reduce the ship’s weight, so it will increase the speed of the ship.
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"Aluminum Alloy 7178-T6 Aircraft Deck Plate That Failed in Service by Fatigue Cracking." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c0047076.

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Conference papers on the topic "Plates, Aluminum Cracking"

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Ostoja-Starzewski, M., Ahmed Al-Ostaz, and I. Jasiuk. "Cracking of Plates With Randomly Distributed Holes by a Maximum Entropy Method." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-1208.

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Abstract It has recently been shown [1] that fracture response of nominally identical elastic-brittle (epoxy) as well as ductile (aluminum) sheets, each containing randomly distributed circular holes, is non-unique. This non-uniqueness pertains, in particular, to the resulting fracture patterns and effective stress-strain curves, whereby both of these characteristics display considerable scatter. This result points to the significant influence which microscale random noise in material parameters may have on the global, macroscopic behavior. In this paper we formulate, on the basis of a maximum entropy method [2], a stochastic fracture mechanics model for this class of problems. The method is based on the statistics of experimental data, obtained for a number of specimens, involving the inter-hole crack lengths and their angles. It allows prediction of probability distributions of damage responses and patterns of Gibbs ensembles of random hole systems such as, for example, porous materials with millions of voids.
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YODER, G., L. COOLEY, T. WATSON, and T. CROOKER. "CRACKING RESISTANCE IN A 4.5-INCH (114-mm) PLATE OF 7075-T7351 ALUMINUM ALLOY." In 19th International Electric Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-984.

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Bourchak, Mostefa, Yousef Dobah, Abdullah Algarni, Adnan Khan, and Waleed K. Ahmed. "Failure Analysis in Hybrid Composite Laminates Using Acoustic Emission and Microscopy." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-53029.

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Fiber Reinforced Plastic (FRP) composite materials are widely used in many applications especially in aircraft manufacturing because they offer outstanding strength to weight ratio compared to other materials such as aluminum alloys. The use of hybrid composite materials is potentially an effective cost saving design while maintaining strength and stiffness requirements. In this work, Woven Carbon Fibers (WCFs) along with Unidirectional Glass Fibers (UDGFs) are added to a an aerospace-rated epoxy matrix system to produce a hybrid carbon and glass fibers reinforced plastic composite plates. The manufacturing method used here is a conventional vacuum bagging technique and the stacking sequence achieved consists of a symmetric and balanced laminate (±451WCF, 03UDGF, ±451WCF) to simulate the layup usually adopted for helicopter composite blades constructions. Then, tensile static tests samples are cut according to ASTM standard using a diamond blade and tested using a servohydraulic test machine. Acoustic Emission (AE) piezoelectric sensors (transducers) are attached to the samples surface using a special adhesive. Stress waves that are released at the moments of various failure modes are then recorded by the transducers in the form of AE hits and events (a burst of hits) after they pass through pre-amplifiers. Tests are incrementally paused at load levels that represent significant AE hits activity which usually corresponds to certain failure modes. The unbroken samples are then thoroughly investigated using a high resolution microscopy. The multi load level test-and-inspect method combined with AE and microscopy techniques is considered here to be an innovation in the area of composite failure analysis and damage characterization as it has not been carried out before. Results are found to show good correlation between AE hits concentration zones and the specimens damage location observed by microscopy. Waveform analysis is also carried out to classify the damage type based on the AE signal strength energy, frequency and amplitude. Most of the AE activity is found to initiate from early matrix cracking that develops into delamination. Whereas little fiber failure activity has been observed at the initial stages of the load curve. The results of this work are expected to clear the conflicting reports reported in the literature regarding the correlation of AE hits characteristics (e.g. amplitude level) with damage type in FRP composite materials. In addition, the use of a hybrid design is qualitatively assessed here using AE and microscopy techniques for potential cost savings purposes without jeopardizing the weight and strength requirements as is the case in a typical aircraft composite structural design.
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Brady, Brian G. "Cracking During the Installation of Interference Fit Fasteners and Bucked Rivets in 7050-T7XXX Machined Aluminum Parts." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-14815.

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This test program evaluated the effect of the installation of solid rivets and interference fit Hi-Tigue bolts on machined 7050 longerons (HiTigue is a registered trademark of the Hi-Shear Corporation of Torrance, (CA). Two simulated longeron specimens were machined from both 7050-T7451 and 7050-T7651 plate. Titanium Hi-Tigues and solid aluminum and Monel rivets were then installed with a pneumatic riveting hammer in sections of various thicknesses in the four machined longeron specimens. After all fasteners were installed, each fastener was subjected to a simulated mishap by applying the pneumatic riveting hammer to the installed fastener without support from an underlying bucking bar. Dye penetrant inspections to detect cracks were performed after the fastener installations and simulated mishaps. All fasteners were then removed and the open holes subjected to eddy current inspection. Visual observations concerning deformation of the machined longeron specimens during fastener installations and simulated mishaps were recorded. Cracking was noted in 0.063 inch thick longeron sections, compelling additional testing involving Hi-Tigues. Recommendations concerning the use of Hi-Tigues and solid rivets in 7050-T7XXX machined parts were made based on the results of the testing.
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Sandeep, R., D. Sudhakara, and G. Prasanthi. "Optimization of Friction Stir Welding Process Parameters to Join Al 5052 and Al 6061 Alloy Plates Using Grey-Taguchi Technique." In ASME 2017 12th International Manufacturing Science and Engineering Conference collocated with the JSME/ASME 2017 6th International Conference on Materials and Processing. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/msec2017-2605.

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Friction stir welding (FSW) is a solid state welding process used for welding similar and dissimilar materials. The process is widely used because it does not have common problems such as solidification and liquefaction cracking associated with the fusion welding techniques. The objective of the present research is to find the best combination of friction stir welding process parameters to join aluminium 5052 and 6061 alloy materials. The combination of process parameters is helpful to improve ultimate tensile strength, yield strength, percentage of elongation and hardness of welded joint. To achieve the research objective taguchi based grey analysis was used. The optimum process parameters were found be at rotational speed is 1400 rpm, transverse speed of 100 mm/min and axial force is at 11 KN.
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Singh, Charandeep, Yeonsung Kim, and Seungbae Park. "Comparative Study of Analytical Models to Predict Warpage in Microelectronics Packages." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38594.

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Warpage is a critical concern in the microelectronics industry for several decades. It is a root cause of failures during manufacturing processes such as open solder joints. Also the excessive warpage generates the delamination and die cracking which degrade the package reliability. Thus, the accurate estimation of package warpage is one of the important factors to improve the package reliability. The purpose of this study is to select the best analytical model for prediction of warpage of microelectronic packages. This paper compares the warpage prediction from corrected Suhir’s theory and classical laminate theory. Both analytical models can provide quick warpage estimation when package is subjected to thermal loading. The warpage evaluation was performed based on both analytical models and compared with the experimental result. Also a finite element analysis (FEA) was performed and the result was compared with analytical models. The digital image correlation (DIC) technique was employed to observe the real-time out-of-plane deformation of the test sample exposed to temperature loading. Three layer test vehicle having the die, underfill, and aluminum plate was assembled for this study. Underfill material properties were characterized with DIC and dynamic mechanical analysis (DMA). The result indicates that Laminate theory provides the better prediction of warpage when underfill layer thickness is comparable with die and substrate layer thickness. This study helps to design more reliable components with design parameters being optimized in early stage of the development using analytical solutions.
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Le Delliou, Patrick, and Samuel Geniaut. "Tests on SENT Specimens to Study Geometry Effects in the Brittle to Ductile Transition." In ASME 2014 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/pvp2014-28099.

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The accurate prediction of ductile fracture behaviour plays an important role in structural integrity assessments of critical engineering structures under fully plastic regime, including nuclear reactors and piping systems. Many structural steels and aluminium alloys generally exhibit significant increases in fracture toughness, characterized by the J-integral, over the first few mm of stable crack extension (Δa), often accompanied by large increases in background plastic deformation. Conventional testing programs to measure crack growth resistance (J–Δa) curves employ three-point bend, SEN(B), or compact, CT. However, laboratory testing of fracture specimens to measure resistance curves (J–Δa) consistently reveals a marked effect of absolute specimen size, geometry, relative crack size (a/W ratio) and loading mode (tension vs. bending) on R-curves. These effects observed in R-curves have enormous practical implications in defect assessments and repair decisions of in-service structures under low constraint conditions. Structural components falling into this category include pressurized piping systems with surface flaws that form during fabrication or during in-service operation. This paper presents the on-going work to study geometry effects (e.g. triaxiality effects) in the brittle to ductile transition of carbon-manganese steels, the basic idea being to compare the results obtained on these specimens with the results obtained on CT specimens. A preliminary program was previously conducted at room temperature using deeply notched specimens (Le Delliou, 2012). Finite element computations were made to optimize the specimen shape and to develop the η-factor, the shape factor F (to compute K) and the normalized compliance μ. For the present program, new specimens have been machined with shallower notches (a/W = 0.4), to get a0/W = 0.5 after fatigue pre cracking. Fatigue pre cracking was conducted in 4-point bending to avoid damaging the back of the notch. Moreover, the specimens have been cut in the TS (Transverse-Short) direction of the plate to get lower toughness properties, and less plasticity during the tests. Tests at room temperature have been conducted first to validate the revised test procedure. Then, the SENT specimens have been tested at −100°C, −60°C, and −40°C, together with CT specimens.
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