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Relevant bibliographies by topics / Fiber metal laminates

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Academic literature on the topic 'Fiber metal laminates'

Author: Grafiati

Published: 4 June 2021

Last updated: 3 February 2022

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Journal articles on the topic "Fiber metal laminates"

1

Stoll, Matthias, Franziska Stemmer, Sergej Ilinzeer, and Kay André Weidenmann. "Optimization of Corrosive Properties of Carbon Fiber Reinforced Aluminum Laminates due to Integration of an Elastomer Interlayer." Key Engineering Materials 742 (July 2017): 287–93. http://dx.doi.org/10.4028/www.scientific.net/kem.742.287.

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Fiber-Metal-Laminates (FML) show superior dynamic mechanical properties combined with low densities. The mechanical performance of for example commercially available fiber-metal-laminate, glass laminate aluminum reinforced epoxy, can be improved by the substitution of glass fibers with carbon fibers. However, carbon fiber reinforced aluminum laminate introduces a mismatch of coefficients of thermal expansion and the possibility of galvanic corrosion. The fiber-metal-laminate is altered by the integration of an elastomer interlayer which is desired to solve both problems. The high electrical resistance is supposed to inhibit the corrosion. This study focuses on the effect of galvanic corrosion caused by neutral salt spray tests on fiber-metal-laminates, the influence of an elastomer interlayer and the quantification of the residual mechanical properties. The galvanic corrosion affects the interfaces of the laminates, therefore in this study edge shear tests and flexural tests were carried out to quantify the residual properties and thereby the corrosive damage. The elastomer interlayer was found to inhibit galvanic corrosion in the salt spray chamber, whereas the fiber-metal-laminate without interlayer showed corrosive damage. Furthermore, the mechanical properties of the fiber-metal-laminate with elastomer interlayer remained constant after the corrosion tests, whilst the fiber-metal-laminate’s properties decreased with corrosive loads.

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Rubio-González, C., E. José-Trujillo, F. Chávez, and A. Ruiz. "Low velocity impact response of composites and fiber metal laminates with open holes." Journal of Composite Materials 51, no. 6 (July 28, 2016): 797–810. http://dx.doi.org/10.1177/0021998316653817.

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Low-velocity impact response of glass/epoxy composite plates and fiber metal laminates with and without holes is investigated. The critical parameters that affect the delamination characteristics of laminates are impact energy, holes separation distance, type and directionality of fibers. An experimental investigation has been conducted to evaluate the effect of the presence of holes and the incorporation of aluminum layers in the extent of delamination. The extent of damage introduced during the impact event was observed on images obtained from C-scan non-destructive ultrasonic technique. Results indicate that fiber metal laminate made with aluminum layers exhibits an improved dynamic response in comparison with that of conventional laminates. The beneficial effect of using aluminum layers to reduce the extent of delamination produced by impact loading especially on laminates with holes is demonstrated. Furthermore, fiber metal laminates show better load carrying capability than conventional composite plates. The better response of fiber metal laminate with multidirectional fabric in comparison with fiber metal laminate with woven fabric is also examined. These results may be useful to better design the location of holes in composite structures.

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Arpatappeh, Fardin Asghari, Mehdi Abdollahi Azghan, and Reza Eslami-Farsani. "The effect of stacking sequence of basalt and Kevlar fibers on the Charpy impact behavior of hybrid composites and fiber metal laminates." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 16 (March 25, 2020): 3270–79. http://dx.doi.org/10.1177/0954406220914325.

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In this study, the effect of the arrangement of Kevlar and basalt fibers as the reinforcements on the Charpy impact behavior of hybrid epoxy composites was investigated. Also, the effect of adding metal plates (aluminum 2024-T3 and stainless steel 316L) into the basalt/ Kevlar fibers reinforced epoxy composites to fabricate fiber metal laminates under Charpy impact loads was studied. The fabricated fiber metal laminates in this research consisted of three metal plates and two groups of composite layers placed between them and were fabricated by the hand lay-up technique. Results indicated that the stacking sequence of fibers due to the hybridization effect caused a considerable improvement in the energy absorption value (99%) of hybrid composites, compared to specimens with one kind of fibers. Moreover, the effect of adding aluminum plates for the fabrication of fiber metal laminate was greater than adding steel plates. Considering the weight of composites, fiber metal laminates with aluminum and steel sheets, it was found that the average specific energy absorption value of aluminum fiber metal laminates was about 2.5 times higher than those of steel fiber metal laminates and composites.

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Salve, Aniket, Ratnakar Kulkarni, and Ashok Mache. "A Review: Fiber Metal Laminates (FML’s) - Manufacturing, Test methods and Numerical modeling." International Journal of Engineering Technology and Sciences 3, no. 2 (December 30, 2016): 71–84. http://dx.doi.org/10.15282/ijets.6.2016.1.10.1060.

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Weight reduction of components is the main aim of different industrial sectors. This leads to increasing application areas of fiber composites for primary structural components. Aiming this objective, a new lightweight Fiber/Metal Laminate (FML) has been developed. Fiber metal laminate is one such material which is being widely investigated for its performance compared to existing material.. The most commercially available fiber metal laminates (FML’s) are ARALL (Aramid Reinforced Aluminium Laminate), based on aramid fibers, GLARE (Glass Reinforced Aluminium Laminate), based on high strength glass fibers and CARALL (Carbon Reinforced Aluminium Laminate), based on carbon fibers. The mechanical properties of FML show advantages over the properties of both aluminium alloys and composite materials individual. This paper reviews relevant literature which deals with different manufacturing techniques for FML’s with excellent properties under tensile, flexure and impact conditions. It also reviewed recent modeling techniques on FML’s. Modeling of tensile, flexure and impacts behavior on fiber metal laminates requires understanding the bonding between the metal and composite layer. Further research is necessary in the assessment of mechanical performance of complex structures in real world conditions.

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Saadatfard, Alireza, Mahdi Gerdooei, and Abdolhossein Jalali Aghchai. "Drawing potential of fiber metal laminates in hydromechanical forming: A numerical and experimental study." Journal of Sandwich Structures & Materials 22, no. 5 (June 27, 2018): 1386–403. http://dx.doi.org/10.1177/1099636218785208.

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It is known that fiber metal laminates as one of hybrid materials with thin metal sheets and fiber/resin layers have limited formability in conventional forming methods. This paper presents an experimental and numerical study for drawability of glass fiber-reinforced aluminum laminates under hydromechanical drawing technique. Fiber metal laminates comprised of a layer of woven glass fiber-reinforced prepreg, sandwiched between two layers of aluminum alloy. In order to produce fiber metal laminates, the laminates were subjected to a sufficient squeezing pressure under a controlled heating time and temperature by using a hydraulic hot press. A hydromechanical tooling equipped with blank-holder force and fluid pressure control system was used to form the initial circular fiber metal laminate blank. Finally, the effect of parameters such as pre-bulging pressure, final chamber pressure, and drawing ratio on process variables was evaluated. Also, the characteristic curve of hydromechanical drawing of fiber metal laminate i.e. chamber pressure in terms of drawing ratio was achieved by means of experimental tests and numerical simulations. The results showed that the maximum drawing ratio of defect-free fiber metal laminates, namely without any tearing, wrinkling, and delamination was obtained at pre-bulging and chamber pressure of 35 and 80 bar, respectively.

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Vilas Boas, Cristiane, Felipe Moreno, and Demetrio Jackson dos Santos. "Mechanical Analysis of Polybenzoxazine Matrix in Fiber Metal Laminates." Materials Science Forum 869 (August 2016): 215–20. http://dx.doi.org/10.4028/www.scientific.net/msf.869.215.

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In this work we investigated the application of a novel high performance polymer, polybenzoxazine, as a polymeric matrix in Fiber Metal Laminates (FML). This polymer, when applied on the development of FMLs, generated higher mechanical properties in comparison to fiber metal laminates obtained with epoxy. To investigate the mechanical performance of the polybenzoxazine matrix in FMLs, a mechanical behavior comparison was carried out among epoxy matrix laminates - glass fiber reinforced aluminum laminate (GLARE) and carbon fiber reinforced aluminum laminate (CARALL) - and FML constructed with aluminum and carbon fiber reinforced polybenzoxazine. The mechanical properties were characterized by drop weight impact and flexural methods, and the polybenzoxazine curing behavior through differential scanning calorimetry (DSC). Polybenzoxazine FML generated increasing of: 18% of maximum load, 11% of maximum elongation under flexure and 7.5% of impact energy absorption compared to other fiber metal laminates.

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Mohamad, Mawarni, Haslan Fadli Ahmad Marzuki, E. A. E. Ubaidillah, M. F. Z. Abidin, S. Omar, and I. M. Rozi. "Effect of Surface Roughness on Mechanical Properties of Aluminium-Carbon Laminates Composites." Advanced Materials Research 879 (January 2014): 51–57. http://dx.doi.org/10.4028/www.scientific.net/amr.879.51.

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Fiber Metal laminates, FML, is a combination of metal with fiber/resin laminates and it is a well-known application in composite laminates due to its dimension stability and properties consistency. Generally, the strength of these laminates systems is much depends on the mechanical interlocking mechanism between the metal surface and the composite laminates. Therefore, surface treatment is needed to enhance the laminates strength. In this research, aluminum plates with different surface roughness were laminated with carbon-fiber/epoxy laminates. The strength of these hybrid systems was then characterized to study the effect of surface roughness on the interfacial strength. It shows that the higher surface roughness will result in better interfacial interaction between the metal surface and the fiber laminates.

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Xu, Zhuo, Hui Li, Wen-yu Wang, Yuan-ning Liu, and Bang-chun Wen. "Inverse identification of mechanical parameters of fiber metal laminates." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 8 (December 30, 2019): 1516–27. http://dx.doi.org/10.1177/0954406219893719.

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In this paper, an inverse method to identify the mechanical parameters of fiber metal laminates is proposed on the basis of the measured and calculated frequency response functions. The classical laminates theory, orthogonal polynomial method, and energy method are employed to characterize the theoretical modal of a fiber metal-laminated thin plate under pulse excitation. And, an iterative solution on the basis of frequency response functions and least square method is proposed to identify the mechanical parameters of fiber metal laminates, which conclude the elastic modulus, Poisson's ratios, and loss factors. As an example to demonstrate the feasibility of the developed inverse method, the experimental test of a TA2/TC 300 fiber metal-laminated thin plate is implemented to identify the mechanical parameters. Moreover, the influences of approximation points and calculation step sizes on the identification accuracy and efficiency are discussed.

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Thirukumaran, M., I. Siva, JT Winowlin Jappes, and V. Manikandan. "Forming and drilling of fiber metal laminates – A review." Journal of Reinforced Plastics and Composites 37, no. 14 (April 27, 2018): 981–90. http://dx.doi.org/10.1177/0731684418771194.

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In aviation industries, most of the stiffened structural components are manufactured by forming and laminating process. Combination of several conventional manufacturing processes is required in modern industries in hybrid laminate production. Fiber metal laminates undergo various joining process during assembly of aero-structures. Among them, forming and drilling are often required during assembly. Understanding the significance of various process parameters enables quality production and assembly of fiber metal laminates structures. Many researchers explored the cause and effect of few parameters and mechanisms which significantly alter the quality of form and drill. This review describes the progress in forming and drilling of fiber metal laminates for aerospace applications. Especially towards the process parameters, defects and their causes along with the preferred solutions recommended by the researcher society in forming and drilling processes. Numerous factors have controlled the quality of forming and drilling processes. Due to the machining parameters, different failure modes will occur in different layup of the laminates. To overcome the failures in machining/forming of fiber metal laminates, choosing the optimum parameter for the selection based procedure is needed to improve quality of fiber metal laminates.

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Safari, M., M. Salamat-Talab, A. Abdollahzade, A. Akhavan-Safar, and LFM da Silva. "Experimental investigation, statistical modeling and multi-objective optimization of creep age forming of fiber metal laminates." Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications 234, no. 11 (July 27, 2020): 1389–98. http://dx.doi.org/10.1177/1464420720943537.

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The experimental assessment of the creep age forming performance of fiber metal laminates was considered in this study. To this end, different fiber metal laminates with the stacking sequence of [Al/02/Al] were manufactured using aluminum alloy 6061 sheets as skins along with E-glass fiber-reinforced polypropylene and E-glass fiber-reinforced polyamide 6 as two different cores. Next, a comprehensive investigation was conducted on the impacts of two main parameters in the creep forming process, i.e. the effect of time and temperature on the spring-back properties of deformed fiber metal laminates. Initially, using the design of experiments and based on the response surface methodology, an imposed spring-back of the creep age formed fiber metal laminates was modeled and the governing linear regression equations were derived and verified. Then, to find the best combination yielding the minimum spring-back, the process inputs (time and temperature) were optimized. The results proved that with an increase in either time or temperature, the spring-backs of the two types of creep age formed fiber metal laminates decreased due to the decrease in elastic strains and the increase of creep strains. Also, to achieve a creep age formed fiber metal laminate with minimum spring-back according to multi-objective optimization in both fiber metal laminates, the most proper values of time and temperature should be taken as 6 h and approximately 160°C, respectively.

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Dissertations / Theses on the topic "Fiber metal laminates"

1

Stoll, Matthias [Verfasser]. "Behavior of Fiber-Metal-Elastomer-Hybrid-Laminates / Matthias Stoll." Karlsruhe : KIT-Bibliothek, 2018. http://d-nb.info/1172351651/34.

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Lucchi, Andrea. "Numerical simulation of low velocity impact on fiber metal laminates." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2017.

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The diffusion of composite laminates in aerospace industry has been slowed down by complexity in the prediction of fracture behaviours. In this respect the delamination phenomenon caused by Low-Velocity Impacts has been a critical issue. Several criteria that predict the delamination onset and growth have been analysed. The subsequent study has been focused on Cohesive Zone Models able to predict both initiation and propagation of delamination. Several models that represent the dynamic response of composite structures to impacts have been presented. An explicit FEM has been developed to perform 3D simulations of different layup configurations of Al2024T3 and Woven Carbon Prepreg Laminates subjected to a Low-Velocity Impact. ABAQUS, Dassault Systèmes Simulia Corp. has been employed to perform the numerical simulations. Specific attention is paid to the cohesive failure representing delamination.

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3

Hundley, Jacob Michael. "Multi-scale progressive failure modeling of titanium-graphite fiber metal laminates." Diss., Restricted to subscribing institutions, 2009. http://proquest.umi.com/pqdweb?did=2025451991&sid=1&Fmt=2&clientId=1564&RQT=309&VName=PQD.

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Dietrich, Jan [Verfasser]. "Functional adhesives and functionally graded adhesives in fiber metal laminates / Jan Dietrich." Paderborn : Universitätsbibliothek, 2020. http://d-nb.info/1217325867/34.

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Chang, Po-Yu. "Modeling of fatigue behavior and damage tolerance/durability in fiber metal laminates." Diss., Restricted to subscribing institutions, 2008. http://proquest.umi.com/pqdweb?did=1608577901&sid=1&Fmt=2&clientId=1564&RQT=309&VName=PQD.

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Bandi, Raghava. "Effect of Surface Treatment on the Performance of CARALL, Carbon Fiber Reinforced Aluminum Dissimilar Material Joints." Thesis, University of North Texas, 2017. https://digital.library.unt.edu/ark:/67531/metadc1011869/.

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Fiber-metal laminates (FML) are the advanced materials that are developed to improve the high performance of lightweight structures that are rapidly becoming a superior substitute for metal structures. The reasons behind their emerging usage are the mechanical properties without a compromise in weight other than the traditional metals. The bond remains a concern. This thesis reviews the effect of pre-treatments, say heat, P2 etch and laser treatments on the substrate which modifies the surface composition/roughness to impact the bond strength. The constituents that make up the FMLs in our present study are the Aluminum 2024 alloy as the substrate and the carbon fiber prepregs are the fibers. These composite samples are manufactured in a compression molding process after each pre-treatment and are then subjected to different tests to investigate its properties in tension, compression, flexural and lap shear strength. The results indicate that heat treatment adversely affects properties of the metal and the joint while laser treatments provide the best bond and joint strength.

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Jetela, Václav. "Hybridní lepené spoje kovových a kompozitních materiálů." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-241199.

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The first part of the diploma thesis with name „Hybrid adhesive bonded joints of metals and composite materials“ comprise surface pretreatment review. There is also mentioned current review of adhesives for composite and aluminium adherends. The second part of the thesis is dedicated to lap hybrid joint shear strength tests. The effects of adherend thickness, overlap lenght and surface pretreatment on shear strength were investigated. Measured parameters of hybrid joints are proved with a FE analysis with enough accuracy. Conclusions could be used for optimum design of hybrid joint with aluminium and composite adherends.

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Michalička, Jan. "Lomová houževnatost kompozitu s Al-matricí a uhlíkovými vlákny." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-228117.

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Abstract The objective of this study was a values evaluation of fracture toughness of fiber-metal laminates (FML) compounded from carbon fibers in epoxy matrix and aluminium plates of lay-up 6/5. Samples with unidirectional and bidirectional orientation were tested experimentally. In the case of unidirectionally oriented samples an effect of moisture absorption to epoxy matrix on the values of fracture toughness was reviewed. A fracture toughness calculation was realized by COD method firstly. A bigger pop-ins in F – COD diagram as critical moments for "delta"c evaluation were considered; it was determined by 5% tangential line. It was found out, that results of this measurement weren’t in agreement with plane deformation condition and for this the results couldn’t be rated as fracture toughness "delta"Ic. A method of J integral for fracture toughness evaluation was used consequently. A test of elastic compliance changes before J integral calculation by all of samples was performed. Beginning of stable grow of crack was determined by this method. A critical forces Fc from beginnings were established, which were used for calculation of Jc. A functional dependence of elastic compliance on crack opening had specific waved shape before its linear (up to exponential) grow. It was observed in all cases. The critical forces Fc from the end of “wave” preceding the continual grow of compliance were determined. Equations stated in standards for J integral calculation were used, which are for metal materials normally used. Despite this was found out all of results of Jc were in good agreement with plane deformation condition and could be rated as fracture toughness JIc. In this study were found out these pieces of knowledge about fracture toughness of FML CARE: Unidirectional CARE had fracture toughness JIc about 76 kJ/m^2 and the same type but with bigger amount of absorbed moisture had JIc about 4 % higher. In this case negative moisture influences on CARE weren’t found. Bidirectional CARE had fracture toughness JIc about 31 kJ/m^2; it was about 65 % less then in the case of unidirectional CARE

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Carey, Christian. "Laser forming of fibre metal laminates." Thesis, University of Liverpool, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.511073.

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van, Tonder Talita. "Adhesive properties of thermoset fibre metal laminates." Master's thesis, University of Cape Town, 2014. http://hdl.handle.net/11427/9133.

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Includes bibliographical references.
Fibre metal laminates (FMLs) are composite materials that consist of layers of metal and fibre reinforced polymers. FMLs are used in the construction of aircraft fuselage skins, such as the Airbus A380. GLARE, the only commercially available FML, is of particular interest due to its damage tolerance and potential impact and blast resistance. GLARE is not commercially available and attempts at manufacturing FMLs similar to GLARE at the Blast Impact Survivability and Research Unit (BISRU) laboratories have been unsuccessful. The FMLs readily exhibited debonding between the aluminium and glass fibre reinforced epoxy, often upon handling prior to impact or blast events. The purpose of this study was therefore to investigate manufacturing techniques in order to produce FMLs that would be able to withstand impact and blast loads. Adhesive surface pre-treatment techniques and manufacturing methods typically employed in aircraft construction were investigated with particular emphasis on the adhesion of aluminium to epoxy in FMLs. This interface was of particular interest as good bonding facilitates load transfer under dynamic loading and was identified as the point of failure of the previously manufactured FMLs. The effects of surface treatment techniques used to enhance adhesion were investigated under quasi-static conditions using Single Leg Bend tests. Chemical surface treatments such as alodining, etching, anodising, silane treatments and combinations thereof were investigated. The effect of resin and the inclusion of a film adhesive were also investigated. The silane treatments were identified as the chemical treatments that provided the best adhesion, however the film adhesive significantly improved the fracture toughness regardless of the chemical surface treatment.

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Books on the topic "Fiber metal laminates"

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Krishnakumar, S. Fiber metal laminates: The synthesis of metals and composites. [Ottawa]: National Research Council Canada, Institute for Aerospace Research, 1993.

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Vlot, Ad, and Jan Willem Gunnink, eds. Fibre Metal Laminates. Dordrecht: Springer Netherlands, 2001. http://dx.doi.org/10.1007/978-94-010-0995-9.

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Alderliesten, René. Fatigue and Fracture of Fibre Metal Laminates. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-56227-8.

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J. C. F. N. van Rijn. Preliminary model for the blunt notch behaviour of fibre metal laminates. Amsterdam: National Aerospace Laboratory, 1994.

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(Editor), Ad Vlot, and Jan Willem Gunnink (Editor), eds. Fibre Metal Laminates - An Introduction. Springer, 2001.

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(Editor), Ad Vlot, and Jan Willem Gunnink (Editor), eds. Fibre Metal Laminates: An Introduction. Springer, 2001.

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1962-, Vlot Ad, and Gunnink Jan Willem, eds. Fibre metal laminates: An introduction. Dordrecht: Kluwer Academic Publishers, 2001.

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Alderliesten, René. Fatigue and Fracture of Fibre Metal Laminates. Springer, 2018.

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Alderliesten, René. Fatigue and Fracture of Fibre Metal Laminates. Springer, 2017.

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Vlot, A. High Strain Rate Tests on Fibre Metal Laminates (Series 07 - Aerospace Materials , No 06). Delft Univ Pr, 1998.

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Book chapters on the topic "Fiber metal laminates"

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Kuznetsova, R., H. Ergun, and B. Liaw. "Acoustic Emission of Failure in Fiber-Metal Laminates." In Nondestructive Testing of Materials and Structures, 619–25. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0723-8_88.

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Sharma, Ankush, and Venkitanarayanan Parameswaran. "High Strain Rate Tensile Behavior of Fiber Metal Laminates." In Conference Proceedings of the Society for Experimental Mechanics Series, 457–61. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-21762-8_54.

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Cantwell, W. J., and R. Day. "The Impact Resistance of Fiber Metal Laminates and Hybrid Materials." In Impact Engineering of Composite Structures, 265–304. Vienna: Springer Vienna, 2011. http://dx.doi.org/10.1007/978-3-7091-0523-8_6.

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Yaghoubi, A. Seyed, Y. X. Liu, and B. M. Liaw. "Drop-Weight Impact Studies of GLARE 5 Fiber-Metal Laminates." In Experimental and Applied Mechanics, Volume 6, 267–79. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-0222-0_33.

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Abhishek, S. K., G. Sunil Kumar, and R. Ramesh Kumar. "DIC Correlation with Analysis Under Impact of Fiber Metal Laminates." In Lecture Notes in Mechanical Engineering, 335–45. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5519-0_25.

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Gardner, Casey, Young Ko, Michael Koutoumbas, Eric Flynn, Ian Cummings, and Phil Cornwell. "Delamination Detection in Fiber Metal Laminates Using Ultrasonic Wavefield Imaging." In Rotating Machinery, Optical Methods & Scanning LDV Methods, Volume 6, 59–72. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-76335-0_6.

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Jones, Martin P. "Intrinsic Amplitude Distributions and the Ultrasonic Inspection of Fiber-Metal Laminates." In Nondestructive Characterization of Materials VI, 525–29. Boston, MA: Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2574-5_66.

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Sánchez Carrilero, M., M. Alvarez, J. E. Ares, J. R. Astorga, M. J. Cano, and Mariano Marcos Bárcena. "Dry Drilling of Fiber Metal Laminates CF/AA2024. A Preliminary Study." In Materials Science Forum, 73–78. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-417-0.73.

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Bose, Tanmoy, Subhankar Roy, and Kishore Debnath. "Detection of Delamination in Fiber Metal Laminates Based on Local Defect Resonance." In Reinforced Polymer Composites, 147–64. Weinheim, Germany: Wiley-VCH Verlag GmbH & Co. KGaA, 2019. http://dx.doi.org/10.1002/9783527820979.ch8.

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Beklemysheva, Katerina A., Alexey V. Vasyukov, and Igor B. Petrov. "Numerical Modeling of Delamination in Fiber-Metal Laminates Caused by Low-Velocity Impact." In Smart Modeling for Engineering Systems, 132–42. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-06228-6_12.

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Conference papers on the topic "Fiber metal laminates"

1

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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Toi, Y., and Y. Fujiwara. "Fatigue characterization of fiber/metal laminates." In Aircraft Engineering, Technology, and Operations Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3932.

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Jadhav, Vishwas S., and Ajit D. Kelkar. "Innovative Hole Making Process in Woven Composite Laminates." In ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-11441.

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Abstract This paper proposes an innovative hole making manufacturing method for the composite laminates. The laminates were fabricated using heated vacuum assisted resin transfer molding (HVARTM) technique using plain weave carbon fibers and epoxy resin. Plain weave carbon fabric laminae were stacked together, and five metal pins were inserted in dry fabric at specific distances without causing any damage to the carbon fiber strands. The stacked plies were then infused with epoxy resin to fabricate laminates, which were about 2.6 mm (0.1″) thick. The laminates were cured as per the manufacturer specifications and after curing metal pins were popped out from the laminate. This resulted in holes in the panels without any damage to the continuous carbon fiber strands. The fabricated laminates then were cut into open hole compression coupons using a water jet machine to obtain holes precisely at the center of the coupon. From the remaining panel, ten coupons were machined and half of them were drilled using traditional drilling machine and the remaining half were drilled by nontraditional water jet machining process. The coupons were then tested using ASTM D6484 method to study the mechanical properties of the laminates. The present method shows promising fabrication technique to create holes in the composite laminates without sacrificing the integrity of the continuous fibers.

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Yeh, P. C., P. Y. Chang, J. M. Yang, P. H. Wu, and M. C. Liu. "Bolt Bearing Strength of Commingled Boron/Glass Fiber Reinforced Aluminum Laminates." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85925.

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The bearing properties of recently developed hybrid fiber/metal laminates, or COmmingled Boron/glass fiber Reinforced Aluminum laminates (COBRA), are investigated in this study. The bolt-type bearing tests on GLass REinforced aluminum laminates (GLARE), non-commingled hybrid boron/glass/aluminum fiber/metal laminates (HFML) and COBRA were carried out as a function of e/D ratio, metal volume fraction, fiber volume fraction, and fiber orientation. Experimental results show that with the same joint geometry and metal volume fraction, the commingling of boron fibers improves the bearing strength of fiber/metal laminates. The bearing strength of COBRA with longitudinal fibers is lower than that with transverse fibers due to the fact that shearout failure takes place before maximum bearing strength is reached. The experimental results show that, with only either transverse fiber orientation or longitudinal fiber orientation, COBRA with 18% boron fiber volume fraction possesses a higher bearing strength when compared to HFML with 6% boron fiber volume fraction. In addition to the properties in COBRA with parallel-plies commingled prepreg, the bearing properties of various COBRA with [0°/90°] and [0°/90°/90°/0°] cross-ply commingled prepregs are also discussed.

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Pettit, R. G. "Damage Tolerance Philosophy for Fiber/Metal Laminates." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/912233.

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Sepiani, H. A., A. Afaghi-Khatibi, and M. Mosavi-Mashhadi. "Micromechanical Modeling of Fiber Reinforced Metal Laminates Under Biaxial Deformation." In ASME 2008 Pressure Vessels and Piping Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/pvp2008-61279.

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This presentation examines theoretically the elastic behavior of fiber reinforced metal laminates composed of layers of two types. Woven flexible fabric and metal, in which woven flexible fabric layer includes of sinusoidal shaped fibers. The composite is subjected under biaxial/uniaxial deformation. The theoretical analysis is based upon the Lagrangian description of deformation and the strain-energy density which is assumed to be a function of the Lagrangian strain components referring to the principle material coordinates. The micromechanical model has been obtained using strain energy of components. Finally, the model was solved numerically and then results were compared with published literatures.

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Reyes-Villanueva, G., H. Kang, R. Singh, and S. Gupta. "Formability Analysis of Thermoplastic Lightweight Fiber-Metal Laminates." In SAE 2006 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2006. http://dx.doi.org/10.4271/2006-01-0118.

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Sadighi, M., and S. Dariushi. "Effect of Fiber Orientation and Stacking Sequence on Bending Properties of Fiber/Metal Laminates." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68857.

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Fiber metal laminates (FMLs) are hybrid composites consisting of alternating thin layers of metal sheets and fiber reinforced epoxy. In this work, the bending behavior of this attractive material is investigated. 9 sets of specimens were made with different fiber orientation. Also, the effect of stacking sequence is studied. Test results show that suitable layering and using aluminum layers in the back and front of specimens improve the bending strength. Statistical analysis of data shows that the most important parameter is glass fibers orientation in the lower glass/epoxy layer.

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Newaz, Golam, Marco Sasso, Dario Amodio, and Edoardo Mancini. "Behavior of fiber reinforced metal laminates at high strain rate." In PROCEEDINGS OF THE 21ST INTERNATIONAL ESAFORM CONFERENCE ON MATERIAL FORMING: ESAFORM 2018. Author(s), 2018. http://dx.doi.org/10.1063/1.5034819.

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Zhang, Jipeng, Yue Wang, Jiazhen Zhang, and Zhengong Zhou. "Notched behavior of hybrid glass/aluminum/titanium fiber metal laminates." In 2ND INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS AND MATERIAL ENGINEERING (ICCMME 2017). Author(s), 2017. http://dx.doi.org/10.1063/1.4983588.

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Reports on the topic "Fiber metal laminates"

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Randall, Christian E., and S. van der Zwaag. On Subsurface Crack Growth in Fibre Metal Laminate Materials. Fort Belvoir, VA: Defense Technical Information Center, August 2003. http://dx.doi.org/10.21236/ada416579.

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