Relevant bibliographies by topics / Composite laminate design

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Composite laminate design'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Composite laminate design"

1

Bir, Amarpreet S., Hsin Piao Chen, and Hsun Hu Chen. "Optimum Stacking Sequence Design of Composite Sandwich Panel Using Genetic Algorithms." Advanced Materials Research 585 (November 2012): 29–33. http://dx.doi.org/10.4028/www.scientific.net/amr.585.29.

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In the present study, both critical buckling load maximization and face-sheet laminate thickness minimization problems for the composite sandwich panel, subjected to bi-axial compressive loading under various imposed constraints have been investigated using genetic algorithms. In the previously published work, the optimization of simple composite laminate panels with only even number of laminae has been considered [1, 3]. The present work allows the optimization of a composite sandwich panel with both even and odd number of laminae in the face-sheet laminates. Also, the effects of the bending-twisting coupling terms (D16and D26) in bending stiffness matrix which were neglected in the previous studies [1, 2, 3], are considered in the present work for exact solutions. In addition effect of both balanced and unbalanced face-sheet laminates on the optimum solutions have also been investigated, whereas only balanced laminates were considered in the previous studies [1, 2, 3].
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2

Joshi, S. P., and N. G. R. Iyengar. "Optimal Design of Laminated Composite Plates Under Axial Compression." Transactions of the Canadian Society for Mechanical Engineering 9, no. 1 (March 1985): 45–50. http://dx.doi.org/10.1139/tcsme-1985-0007.

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The study is carried out for the optimum design of laminated fiber reinforced composite plates, subjected to multiple in-plane loadings. Angle-ply laminates with orthotropic laminae are considered. Thickness of plies and corresponding fiber orientations are incorporated as design variables. The constrained optimization problem is transformed into a series of unconstrained optimization problems, using an interior penalty function approach. The results have been obtained for different aspect ratios and uniform biaxial in-plane loading ratios. This study shows that the fiber orientations of the plies near mid-plane have little effect on the optimum design. There exists a particular fiber orientation angle for the over all thickness of laminate, which results in the optimum design for a plate of a given aspect ratio under a given set of loadings.
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Mahadevan, S., and X. Liu. "Probabilistic Optimum Design of Composite Laminates." Journal of Composite Materials 32, no. 1 (January 1998): 68–82. http://dx.doi.org/10.1177/002199839803200104.

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This paper proposes a procedure for the optimum design of composite laminates under probabilistic considerations. The problem is formulated to consider the minimization of laminate weight as the objective function and the reliability requirements as the constraints. Both system-level and element-level reliabilities are considered. The first-order reliability method (FORM) is used to estimate the reliability of each ply group, and system reliability is computed based on series or parallel system assumptions. The Tsai-Wu strength criterion is adopted to derive the limit state function of individual ply groups in the laminate. The gradient and sensitivity information of the objective function and the constraints with respect to the design variables are obtained by using sensitivity analysis based on the composite plate theory. Thus the proposed procedure brings together modern concepts of reliability analysis, composite laminate behavior and nonlinear optimization to develop a rational and practical procedure for the optimum design of composite laminates. Numerical examples are presented to demonstrate the effectiveness of the proposed method.
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Chen, Z., J. J. Mecholsky, and S. Hu. "Effect of interface design on high-temperature failure of laminated composites." Journal of Materials Research 11, no. 8 (August 1996): 2035–41. http://dx.doi.org/10.1557/jmr.1996.0256.

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The fracture strength and toughness of alumina can be increased by lamination with strategically placed nickel layers and with a modified Ni/Al2O3 interface through tape casting. In order to examine the potential of this type of laminated composite in high temperature applications, the laminates were tested at elevated temperatures. This paper describes how a modified tortuous interface, instead of a smooth interface, increases the creep resistance of the laminates. Interface modification can control high temperature laminate behavior and is critical to successful composite design.
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Kumar, M. Ashok, A. M. K. Prasad, and D. V. Ravishankar. "Effect of Quasi-Static Loading on the Composite Laminates." Advanced Engineering Forum 20 (January 2017): 10–21. http://dx.doi.org/10.4028/www.scientific.net/aef.20.10.

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The low velocity impact is a common phenomenon which occurs in fiber reinforced polymer composite products like LPG cylinders, fighter aircraft fuel drop tanks, aircraft wing surfaces, sports goods etc. The consequences of low velocity impact will create a considerable damage and ultimately lead to a premature failure of the structure. Hence the polymer composites for engineering applications must be provided with a better design solution. From the literature survey it is observed that, the response of composite laminates subjected to quasi-static loading, exhibits similar results as that of low velocity impact. Polymer reinforced composites are poor in damage tolerance with better strength to weight ratio than conventional materials. However composite materials can be tailored to meet the design requirements by manipulating fiber orientations and laminae stacking sequence. In the present paper, principles of classical laminate theory are considered for analysis. FEM is implemented for thorough understanding of the failure mechanism of each laminate by layer wise. Simulated quasi-static loading tests and observed the layer wise distribution of transverse strain intensity. The experimental setup is designed and fabricated as per ASTM D 6264 standards. The E-glass/epoxy composite laminate is quasi-statically loaded at its center by a steel ball indenter of diameter 8.7mm and its response is measured by the degree of opacity or translucency in terms of interlaminar and intra-laminar damage area. The stacking sequence of composite laminates are chosen as [00/600]12, [00/750]12 and [00/900]12. The damage areas obtained from numerical analysis are in good agreement with experimental results.
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Marzuki, Haslan Fadli Ahmad, Engku Ahmadhilmi Engku Ubaidillah, Sivakumar A/l Sivarasa, Mohd Syamsul, and Mariatti Jaafar. "Study on Effect of Fiber Orientation on Flexural Properties of Glass Fiber Reinforced Epoxy Composite Laminates for Structural Applications." Solid State Phenomena 301 (March 2020): 227–37. http://dx.doi.org/10.4028/www.scientific.net/ssp.301.227.

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Composite laminate design is an important procedure in defining the mechanical properties of laminated composite structure to be used in multi-directional service loading application. Composite technologies or manufacturers who is lack of knowledge regarding the importance of laminate design, tend to develop a composite structure that will collapse or fail below the service requirement. The purpose of this study is to determine the effect of fiber orientation on flexural properties of the designed glass fiber reinforced epoxy laminated composite. Six sets of laminates with different fiber orientation and sequence were simulated using CompositeStar© software to determine its flexural properties. Samples were fabricated to verify the simulated data and were tested in accordance to ASTM D2344. Moreover, crack pattern within the samples after the flexural test is studied. From the simulated results, it shows that laminates which have fiber in tri-direction and quasi-direction display a higher flexural modulus and strength compared to laminates with fiber in uni-directional and bi-directional. In addition, data from tested fabricated laminates samples displayed the same modulus patterns against the simulated data, with variants from 8% to 35%. Additionally, it is found that samples with fiber in ±45 direction shows a transverse and shear cracking which prolonged the cracking propagation before the samples show a complete failure.
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Ali, J. S. Mohamed, and Abeid Abeid Rubeya. "LEADME: An Educational Software for Composite Laminate Analysis and Design." Advanced Materials Research 1115 (July 2015): 578–81. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.578.

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LEADME ( Laminate Analysis and Design Made Easy ), an educational software useful for the analysis and design of laminated composite structure has been developed. The software encompasses both the micro and macro mechanics analysis of lamina and laminate. The highlight of this software is that, apart from usual laminate analysis, the software is capable to solve practical laminate applications such as analysis of beams and also a design module is included. The software has been developed using MATLAB-Graphical User Interface (GUI) which makes it very user friendly. The results obtained from this software have been validated. It is expected that this software will serve as an educational tool complementing textbooks for students to gain better understanding of composite structural analysis.
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Huang, Chunfang, Mingchang He, Yonglyu He, Jiayu Xiao, Jiangwei Zhang, Su Ju, and Dazhi Jiang. "Exploration relation between interlaminar shear properties of thin-ply laminates under short-beam bending and meso-structures." Journal of Composite Materials 52, no. 17 (December 27, 2017): 2375–86. http://dx.doi.org/10.1177/0021998317745586.

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Carbon fiber reinforced polymer matrix composite laminates with standard thickness plies (0.125 mm) usually have weak interlaminar shear strength, meanwhile, for thin-thickness laminate structures such as aircraft wing skin, it is difficult to design a balanced laminate with the standard plies. It is a possible way to improve the interlaminar shear performance of carbon fiber reinforced polymer composite laminates and enlarge the design space of the thin-thickness structures by using thin-plies technology. In this paper, the interlaminar shear strength of carbon fiber/epoxy laminates with thin prepreg thickness subjected to short-beam bending is investigated. Unidirectional, cross-ply and quasi-isotropic laminate specimens were prepared by using prepregs with different ply thicknesses. Results show that, with decreasing of the ply thickness, higher interlaminar shear strength and smaller coefficient of variation of the data are obtained. Compared to laminates made by standard thickness prepreg, the laminates with thin-thickness prepreg exhibit more homogeneous microstructures and more regularly interlaminar shear stress distribution. This indicates that inherent anisotropy of the laminate composites is weakened in the thin-ply laminates and show pseudo-isotropic behavior. Especially in the case of ply thickness less than 0.020 mm, the interlaminar shear stress distributions of the cross-ply and quasi-isotropic laminate are almost the same with that of isotropic materials according to the classic laminate theory. On the other hand, as expected, the design space of the thin-thickness laminate structures will be increased since more ply number are allowed and superior interlaminar properties can be obtained due to the pseudo-isotropic behavior of the thin plies.
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Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.
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Fukunaga, Hisao, and Hideki Sekine. "A Laminate Design for Elastic Properties of Symmetric Laminates with Extension-Shear or Bending-Twisting Coupling." Journal of Composite Materials 28, no. 8 (May 1994): 708–31. http://dx.doi.org/10.1177/002199839402800802.

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A laminate design method for elastic properties of symmetric laminates with extension-shear or bending-twisting coupling is presented using lamination parameters which give a complete expression of laminate configurations. The elastic properties of Young's moduli, Poisson's ratios and shear modulus are represented on the lamination parameter plane. A general method is also developed for determining laminate configurations corresponding to lamination parameters. The graphical representation clarifies the relation between laminate configurations and elastic properties. Effects of extension-shear coupling on in-plane elastic properties are discussed. The elastic properties of Young's moduli and shear modulus have the maximum values when the coupling terms vanish. Two design examples are also presented which utilize bending-twisting couplings. One is concerned with the control of a cross-coupling parameter in an aeroelastic tailoring of a composite wing, and the other is concerned with the shear buckling optimization of a symmetric laminated plate.
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Dissertations / Theses on the topic "Composite laminate design"

1

Soremekun, Grant A. E. "Genetic Algorithms for Composite Laminate Design and Optimization." Thesis, Virginia Tech, 1997. http://hdl.handle.net/10919/36699.

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Genetic algorithms are well known for being expensive optimization tools, especially if the cost for the analysis of each individual design is high. In the past few years, significant effort has been put forth in addressing the high computational cost GAs. The research conducted in the first part of this thesis continues this effort by implementing new multiple elitist and variable elitist selection schemes for the creation of successive populations in the genetic search process. The new selection schemes allow the GA to take advantage of a greater amount of important genetic information that may be contained in the parent designs, information that is not utilized when using a traditional elitist method selection scheme. By varying the amount of information that may be passed to successive generations from the parent population, the explorative and exploitative characteristics of the GA can be adjusted throughout the genetic search also. The new schemes provided slight reductions in the computational cost of the GA and produced many designs with good fitness' in the final population, while maintaining a high level of reliability. Genetic algorithms can be easily adapted to many different optimization problems also. This capability is demonstrated by modifying the basic GA, which utilizes a single chromosome string, to include a second string so that composite laminates comprised of multiple materials can be studied with greater efficiently. By using two strings, only minor adjustments to the basic GA were required. The modified GA was used to simultaneously minimize the cost and weight of a simply supported composite plate under different combinations of axial loading. Two materials were used, with one significantly stronger, but more expensive than the other. The optimization formulation was implemented by using convex combinations of cost and weight objective functions into a single value for laminate fitness, and thus required no additional modifications to the GA. To obtain a Pareto-optimal set of designs, the influence of cost and weight on the overall fitness of a laminate configuration was adjusted from one extreme to the other by adjusting the scale factors accordingly. The modified GA provided a simple yet reliable means of designing high performance composite laminates at costs lower than laminates comprised of one material.
Master of Science
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Hepworth, Ammon Ikaika No Kapono. "Methods to Streamline Laminate Composite Design, Analysis, and Optimization." BYU ScholarsArchive, 2010. https://scholarsarchive.byu.edu/etd/2405.

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Advanced composite materials have seen major market growth in recent years due to their high strength and low weight properties. These materials are often made using a process that creates a composite laminate by stacking several composite layers together. However, the design, analysis and optimization of laminate composite materials are often a labor intensive process when done manually. This thesis discusses CAD independent algorithms that are integrated into commercial CAD tools to streamline these processes. Methods have been developed to automatically create 3D ply geometry for a laminate composite lay-up, streamline the creation of a laminate composite finite element model and optimize the composite lay-up for a multi-layered laminate composite part. Integrating a CAD independent geometry kernel into the NX laminate composite design automation application significantly improves the run time of that application. In addition, the automated composite finite element tool creates laminate composite finite element models that are more detailed than those made with zone based methods. This tool will save engineers, who are making laminate composite finite element models manually, dozens of hours of work per model. The automated composite finite element tool can also be integrated into an optimization framework, used in conjunction with a method to automatically apply boundary conditions, to create an effective optimization of a laminate composite part.
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McMahon, Mathew T. "A Distributed Genetic Algorithm With Migration for the Design of Composite Laminate Structures." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/36962.

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This thesis describes the development of a general Fortran 90 framework for the solution of composite laminate design problems using a genetic algorithm (GA). The initial Fortran 90 module and package of operators result in a standard genetic algorithm (sGA). The sGA is extended to operate on a parallel processor, and a migration algorithm is introduced. These extensions result in the distributed genetic algorithm with migration (dGA). The performance of the dGA in terms of cost and reliability is studied and compared to an sGA baseline, using two types of composite laminate design problems. The nondeterminism of GAs and the migration and dynamic load balancing algorithm used in this work result in a changed (diminished) workload, so conventional measures of parallelizability are not meaningful. Thus, a set of experiments is devised to characterize the run time performance of the dGA. The migration algorithm is found to diminish the normalized cost and improve the reliability of a GA optimization run. An effective linear speedup for constant work is achieved, and the dynamic load balancing algorithm with distributed control and token ring termination detection yield improved run time performance.
Master of Science
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Ananthasubramanian, Srikanth, and Priyank Gupta. "Early assessment of composite structures : Framework to analyse the potential of fibre reinforced composites in a structure subjected to multiple load case." Thesis, KTH, Lättkonstruktioner, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-235309.

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To meet the need of lightweight chassis in the near future, a technological step of introducing anisotropic materials like Carbon Fibre Reinforced Plastics (CFRP) in structural parts of cars is a possible way ahead. Though there are commercially available tools to find suitability of Fibre Reinforced Plastics (FRPs) and their orientations, they depend on numerical optimization and complexity increases with the size of the model. Nevertheless, the user has a very limited control of intermediate steps. To understand the type of material system that can be used in different regions for a lightweight chassis, especially during the initial concept phase, a more simplified, yet reliable tool is desirable.The thesis aims to provide a framework for determining fibre orientations according to the most-ideal loading path to achieve maximum advantage from FRP-materials. This has been achieved by developing algorithms to find best-fit material orientations analytically, which uses principal stresses and their orientations in a finite element originating from multiple load cases. This thesis takes inspiration from the Durst criteria (2008) which upon implementation provides information on how individual elements must be modelled in a component subjected to multiple load cases. This analysis pre-evaluates the potential of FRP-suitable parts. Few modifications have been made to the existing formulations by the authors which have been explained in relevant sections.The study has been extended to develop additional MATLAB subroutines which finds the type of laminate design (uni-directional, bi-axial or quasi-isotropic) that is suitable for individual elements.Several test cases have been run to check the validity of the developed algorithm. Finally, the algorithm has been implemented on a Body-In-White subjected to two load cases. The thesis gives an idea of how to divide the structure into sub-components along with the local fibre directions based on the fibre orientations and an appropriate laminate design based on classical laminate theory.
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Taetragool, Unchalisa. "Optimal Parameters for Doubly Curved Sandwich Shells, Composite Laminates, and Atmospheric Plasma Spray Process." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/81978.

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Optimization is a decision making process to solve problems in a number of fields including engineering mechanics. Bio-inspired optimization algorithms, including genetic algorithm (GA), have been studied for many years. There is a large literature on applying the GA to mechanics problems. However, disadvantages of the GA include the high computational cost and the inability to get the global optimal solution that can be found by using a honeybee-inspired optimization algorithm, called the New Nest-Site Selection (NeSS). We use the NeSS to find optimal parameters for three mechanics problems by following the three processes: screening, identifying relationships, and optimization. The screening process identifies significant parameters from a set of input parameters of interest. Then, relationships between the significant input parameters and responses are established. Finally, the optimization process searches for an optimal solution to achieve objectives of a problem. For the first two problems, we use the NeSS algorithm in conjunction with a third order shear and normal deformable plate theory (TSNDT), the finite element method (FEM), a one-step stress recovery scheme (SRS) and the Tsai-Wu failure criterion to find the stacking sequence of composite laminates and the topology and materials for doubly curved sandwich shells to maximize the first failure load. It is followed by the progressive failure analysis to determine the ultimate failure load. For the sandwich shell, we use the maximum transverse shear stress criterion for delineating failure of the core, and also study simultaneously maximizing the first failure load and minimizing the mass subject to certain constraints. For composite laminates, it is found that the first failure load for an optimally designed stacking sequence exceeds that for the typical [0°/90°]₅ laminate by about 36%. Moreover, the design for the optimal first failure load need not have the maximum ultimate load. For clamped laminates and sandwich shells, the ultimate load is about 50% higher than the first failure load. However, for simply supported edges the ultimate load is generally only about 10% higher than the first failure load. For the atmospheric spray process, we employ the NeSS algorithm to find optimal values of four process input parameters, namely the argon flow rate, the hydrogen flow rate, the powder feed rate and the current, that result in the desired mean particle temperature and the mean particle velocity when they reach the substrate. These optimal values give the desired mean particle temperature and the mean particle velocity within 5% of their target values.
Ph. D.
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Elmushyakhi, Abraham. "In-Plane Fatigue Characterization of Core Joints in Sandwich Composite Structures." University of Dayton / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1510678155755824.

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Naifar, Slim. "Model Based Design of a Magnetoelectric Vibration Converter from Weak Kinetic Sources." Universitätsverlag Chemnitz, 2018. https://monarch.qucosa.de/id/qucosa%3A32774.

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The main challenge in the design of vibration energy harvesters is the optimization of energy outcome relative to the applied excitation to reach a higher efficiency in spite of the weakness of ambient energy sources. One promising principle of vibration converters is magnetoelectricity due to the outstanding properties of magnetostrictive and piezoelectric laminate composites, which provide interesting possibilities to harvest energy from low amplitude and low frequency vibration with relatively high energy outcome. For these devices, ensuring high deformations in the magnetostricive layers, improvement of the magnto-mechanical and the electro-mechanical couplings are highly required for the optimization of the energy outcome. This thesis primarily aims to develop a model based harvester design for magnetoelectric (ME) converters. Based on a comprehensive understanding of the complex energy flow in magnetoelectric transducers, several design parameters are investigated. For instance, magnetostriction in a Terfenol-D plate is investigated by means of atomic force microscopy under similar conditions as within magnetoelectric transducers. A novel measurement approach was successfully developed to detect the evolution of magnetic domains and measure deformations in a Terfenol-D plate in response to externally non-uniform applied magnetic fields. Furthermore, a finite element model is developed to predict the induced voltage in the ME transducer as a response to the magnet’s displacement, corrected based on atomic force microscopy measurements, and used for the design of the harvester. The presented three- dimensional model takes into consideration the nonlinear behaviour of the magnetostrictive and piezoelectric materials. Additionally, three novel converters having different magnetic circuits are designed and analysed analytically based on Lindstedt-Poincaré method. The effects of the structure parameters, such as the nonlinear magnetic forces, the magnetic field distribution and the resonance frequency are discussed, and the electric output performances of the three designed converters are evaluated. In order to improve both mechanical and electrical coupling between the piezoelectric and the magnetostrictive layers, a bonding technique at room temperature is proposed which uses conductive polymer nanocomposites. Two magnetoelectric transducers are fabricated based on this technique having 1 wt.% and 2 wt.% concentration of multiwalled carbon nanotubes in epoxy resin. Another magnetoelectric transducer is fabricated by a classical technique for comparison purposes. In order to validate the design, a series of demonstrators are designed and fabricated according to the simulation and optimization results. The proposed design is composed by a cantilever beam, a magnetic circuit with several magnet arrangements and a magnetoelectric transducer, which is formed by a piezoelectric PMNT plate bonded to two magnetostrictive Terfenol-D layers. In this design, external vibrations are converted to magnetic field changes acting on the magnetostrictive layers leading to deformations, which are transmitted directly to the piezoelectric layer. The converters are tested under harmonic excitations and real vibration profiles reproduced by an artificial vibration source. Different parameters were investigated experimentally including the magnetic forces between the transducer and the magnetic circuit and the used bonding technique. Tuning the resonance frequency of the ME converter is also addressed using a simple screw/nut system, which allows to control the relative position and therefore the magnetic forces between the magnetic circuit and the transducer. The magnetoelectric transducer bonded with 2 wt.% concentration of multiwalled carbon nanotubes shows better output performances than the two other ME transducers under similar excitations. A maximum power output of 2.42 mW is reached under 1 mm applied vibration at 40 Hz. This performance presents an improvement of minimum 20 % of the reached energy outcome by other magnetoelectric vibration converters using single ME transducer at comparable applied excitations.
Die größte Herausforderung bei der Konstruktion von Vibrations-Energiewandlern ist die Optimierung der gewonnenen Energie im Verhältnis zur angewandten Anregung, um trotz schwacher Umgebungsenergiequellen einen hohen Wirkungsgrad zu erreichen. Ein vielversprechendes Prinzip von Vibrationswandlern ist die Magnetoelektrizität aufgrund der hervorragenden Eigenschaften von magnetostriktiven und piezoelektrischen Verbundwerkstoffen, die interessante Möglichkeiten bieten, Energie aus niederfrequenten Schwingungen mit kleinen Amplituden zu gewinnen. Bei diesen Wandlern ist die Sicherstellung hoher Verformungen in den magnetostriktiven Schichten, die Verbesserung der magnetisch-mechanischen und der elektromechanischen Kopplungen für die Optimierung des Energieertrages sehr wichtig. Diese Arbeit zielt in erster Linie auf die Entwicklung eines modellbasierten Entwurfs für magnetoelektrische (ME) Wandler ab. Basierend auf einem umfassenden Verständnis des komplexen Energieflusses in magnetoelektrischen Wandlern werden mehrere Entwurfsparameter untersucht. So wird beispielsweise die Magnetostriktion in einer Terfenol-D-Platte mittels Rasterkraftmikroskopie unter ähnlichen Bedingungen untersucht wie in magnetoelektrischen Wandlern. Dabei wurde eine neuartige Messmethode erfolgreich entwickelt, um die Entwicklung von magnetischen Domänen zu erfassen und die Deformation in einer Terfenol-D-Platte als Reaktion auf extern ungleichmäßig angelegte Magnetfelder zu messen. Darüber hinaus wird ein Finite-Elemente-Modell entwickelt, um die induzierte Spannung im ME-Wandler als Reaktion auf die Verschiebung des Magneten vorherzusagen, welches auf der Grundlage von Atomkraftmikroskopie Messungen korrigiert und für den Entwurf des Energiewandlers verwendet wird. Das vorgestellte dreidimensionale Modell berücksichtigt das nichtlineare Verhalten der magnetostriktiven und piezoelektrischen Materialien. Zusätzlich werden drei neuartige Wandler mit unterschiedlichen Magnetkreisen nach dem Lindstedt-Poincaré Verfahren konzipiert und analytisch analysiert. Die Auswirkungen der Strukturparameter, wie die nichtlinearen Magnetkräfte, die Magnetfeldverteilung und die Resonanzfrequenz, werden diskutiert und die elektrischen Ausgangsleistungen der drei ausgelegten Wandler ausgewertet. Um die mechanische und elektrische Kopplung zwischen der piezoelektrischen und der magnetostriktiven Schicht zu verbessern, wird eine bei Raumtemperatur prozessierbare Verbindungstechnik vorgeschlagen, bei der leitfähige Nanokomposite verwendet werden. Zwei magnetoelektrische Wandler werden basierend auf dieser Technik mit einer Konzentration von 1 wt.% und 2 wt.% an mehrwandigen Kohlenstoff-Nanoröhren in Epoxidharz hergestellt. Ein weiterer magnetoelektrischer Wandler wurde zu Vergleichszwecken mit einer klassischen Technik hergestellt. Für die Validierung des Entwurfes wird eine Reihe von Demonstratoren entsprechend den Simulations- und Optimierungsergebnissen konstruiert und gefertigt. Der vorgeschlagene Entwurf besteht aus einem Trägerbalken, einem Magnetkreis mit mehreren Magnetanordnungen und einem magnetoelektrischen Wandler, der aus einer piezoelektrischen PMNT-Platte besteht, die mit zwei magnetostriktiven Terfenol-D-Schichten verbunden ist. Bei dieser Konstruktion werden externe Schwingungen in Magnetfeldänderungen umgewandelt, die auf die magnetostriktiven Schichten wirken und zu Verformungen führen, die direkt auf die piezoelektrische Schicht übertragen werden. Die Wandler werden unter harmonischen Anregungen und mit realen Schwingungsprofilen getestet, die von einer künstlichen Schwingungsquelle reproduziert werden. Verschiedene Parameter wurden experimentell untersucht, darunter die magnetischen Kräfte zwischen dem Wandler und dem Magnetkreis sowie die verwendete Verbindungstechnik. Die Abstimmung der Resonanzfrequenz des ME-Wandlers erfolgt ebenfalls über ein einfaches Schrauben-Mutter-System, das es ermöglicht, die relative Position und damit die magnetischen Kräfte zwischen Magnetkreis und Wandler zu steuern. Der magnetoelektrische Wandler, der mit einer Konzentration von 2 wt.% mehrwandiger Kohlenstoff-Nanoröhrchen verbunden ist, zeigt bessere Ausgangsleistungen als die beiden anderen ME-Wandler bei ähnlichen Anregungen. Eine maximale Ausgangsleistung von 2,42 mW wird bei 1 mm angelegter Vibration bei 40 Hz erreicht. Diese Leistung stellt eine Verbesserung von mindestens 20 % im Vergleich zu anderen magnetoelektrischen Schwingungsumrichtern dar, welche mit einem einzigen ME-Wandler bei vergleichbaren Anregungen getestet werden.
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8

Bydalek, David Russell. "Manufacture of Complex Geometry Component for Advanced Material Stiffness." DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1919.

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The manufacture, laminate design, and modeling of a part with complex geometry are explored. The ultimate goal of the research is to produce a model that accurately predicts part stiffness. This is validated with experimental results of composite parts, which refine material properties for use in a final prototype part model. The secondary goal of this project is to explore manufacturing methods for improved manufacturability of the complex part. The manufacturing portion of the thesis and feedback into material model has incorporated a senior project team to perform research on manufacturing and create composite part to be used for experimental testing. The senior project was designed, led, and managed by the author with support from the committee chair. Finite element modeling was refined using data from coupon 3-point bend testing to improve estimates on material properties. These properties were fed into a prototype part model which predicted deflection of composite parts with different layups and materials. The results of the model were compared to experimental results from prototype part testing and 3rd party analysis. The results showed that an accurate mid-plane shell element model could be used to accurately predict deflection for 2 of 3 experimental parts. There are recommendations in the thesis to further validate the models and experimental testing.
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Chutima, Surachate. "Computer aided analysis of mechanically fastened composite laminates." Thesis, University College London (University of London), 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.244053.

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Bhagate, Kiran. "Design sensitivity analysis for optimization of composite laminates." Thesis, University of Leeds, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.446049.

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Books on the topic "Composite laminate design"

1

T, Haftka Raphael, and Hajela Prabhat 1956-, eds. Design and optimization of laminated composite materials. New York: Wiley, 1999.

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Rosado, Pablo Rodríguez. Design of multiple-ply laminated composite tapered beams. [Marshall Space Flight Center, Ala.]: National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1993.

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Rosado, Pablo Rodríguez. Design of multiple-ply laminated composite tapered beams. [Marshall Space Flight Center, Ala.]: National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1993.

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Rodriguez, P. Design of multiple-ply laminated composite tapered beams. [Marshall Space Flight Center, Ala.]: National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1993.

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Hiel, C. Snaplock fiber reinforced composites technology applied to overhead sign structures: Design, construct, and test a fiber reinforced composite overhead sign truss. Sacramento, CA: California Dept. of Transportation, Division of Research and Innovation, 2008.

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Design, Fabrication and Mechanics of Composite Structures Seminar (1984 Arlington, Va.). Design, fabrication and mechanics of composite structures: Seminar notes, reference materials for seminar of May 1-4, 1984, Arlington, VA. Lancaster, PA, USA: Technomic Pub. Co., 1985.

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Sun, Guojun. Optimal design of laminated-composite circular-cylindrical shells subjected to combined loads. [S.l.]: American Society of Mechanical Engineers, 1988.

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Hyer, M. W. Innovative design of composite structures: The use of curvilinear fiber format in composite structure design. Blacksburg, VA: College of Engineering, Virginia Polytechnic Institute and State University, 1990.

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Hyer, M. W. Innovative design of composite structures: Axisymmetric deformations of unsymmetrically laminated cylinders loaded in axial compression : semiannual status report. Blacksburg, Va: College of Engineering, Virginia Polytechnic Institute and State University, 1990.

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Hyer, M. W. Innovative design of composite structures: Design, manufacturing, and testing of plates utilitzing [sic] curvilinear fiber trajectories : final report for NASA. Blacksburg, VA: College of Engineering, Virginia Polytechnic Institute and State University ; Hampton, VA, 1994.

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Book chapters on the topic "Composite laminate design"

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Nagarjuna Reddy, S., and M. Trivikrama Sankar. "Design and Analysis on Reinforced Carbon–Basalt Fibres Composite Laminate." In Advances in Applied Mechanical Engineering, 581–89. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1201-8_65.

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Chebbi, Mohamed Ali, Frédéric Lachaud, and Florent Blanchet. "A Finite Element Model for Orthogonal Cutting of Unidirectional [(0,90)2]S Composite Laminate." In Design and Modeling of Mechanical Systems - II, 415–26. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17527-0_42.

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Marom, G., B. Gershon, and D. Cohn. "The Utilization of Composite Laminate Theory in the Design of Filament Wound Synthetic Soft Tissues for Biomedical Prostheses." In Developments in the Science and Technology of Composite Materials, 737–42. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_103.

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Seng, Jocelyn M. "Laminate Design." In Handbook of Composites, 686–708. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4615-6389-1_31.

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Rothwell, Alan. "Composite Laminates." In Optimization Methods in Structural Design, 241–82. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-55197-5_8.

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Murty, A. V. Krishna, H. K. Harikumar, and C. G. Shah. "Towards Damage Tolerant Design of Laminated Components." In Composite Structures, 20–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-662-11345-5_2.

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Roubíček, Tomáš. "Optimal design of laminated composites." In Analysis and Simulation of Multifield Problems, 129–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 2003. http://dx.doi.org/10.1007/978-3-540-36527-3_12.

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Haftka, Raphael T., Zafer Gürdal, and Manohar P. Kamat. "Optimum Design of Laminated Composite Structures." In Elements of Structural Optimization, 341–84. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-015-7862-2_11.

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Haftka, Raphael T., and Zafer Gürdal. "Optimum Design of Laminated Composite Structures." In Elements of Structural Optimization, 415–68. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2550-5_11.

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Ling, Yang, and Ma Zukang. "Optimum Design Based on Reliability for Composite Laminates." In Composite Structures 4, 378–92. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_29.

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Conference papers on the topic "Composite laminate design"

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Nandi, Soumitra, Zahed Siddique, and Cengiz Altan. "A Customization Approach for Design Using Commercially Available Laminated Composite Materials." In ASME 2011 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/detc2011-48461.

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Composite materials can offer wide range of thermo-mechanical properties when designing load bearing components using them. The wide range of properties can be obtained by varying fiber-matrix volumetric ratio. Another advantage of using composite materials in design is that the directional properties of laminated composite materials can be easily manipulated by varying the angle of orientation with respect to the direction of the load. Theoretically it is possible to design composite laminates with any fiber-matrix ratio, and in any orientation. But in practice, only a selective number of laminates with given fiber volume fraction are produced and sold by the companies depending on their market demands. So, it is necessary for a designer to perform the selection of laminates from a list of available composite laminates to make it commercially viable. The manual selection process of composite laminates can be very cumbersome for the designers when multiple design goals need to be satisfied in the load bearing component that is being designed. This paper presents a new customization approach for design of load bearing components where appropriate unidirectional laminated composites can be selected to satisfy multiple property requirements. In this approach, a laminate customization technique is incorporated with a grammatical method that deals with a shape design technique, and loading analysis for the designed shape. A hip-replacement joint is designed using commercially available composite laminates to illustrate the approach.
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Okumuş, F., and A. Turgut. "Thermal Behavior of Aluminum Metal-Matrix Composite During Cooling Process." In ASME 2001 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/detc2001/rsafp-21744.

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Abstract The paper presents a thermal behavior analysis of metal matrix composite lamina and laminates during a cooling process. A long stainless steel fiber reinforced aluminum metal matrix composite lamina and laminate are used for this purpose. Metal matrix composites were manufactured by using modulus under the action of 30 MPa pressure and heating up to 600 °C. The thermal stresses generated during cooling have a profound effect on the distortion and strength of the composite materials. In this study, thermal stresses, residual stresses and effective thermal expansion coefficients as a function of orientation angle of the aluminum metal matrix composite during a cooling process are investigated. The finite element method was used for thermal stress analysis. For this purpose, four noded rectangular elements were used in the ANSYS finite element code.
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Teimouri, Hessamodin, Ali Abedian, and Hengameh Farahpour. "The Influence of Fiber/Matrix Debonding on Inelastic Micro-Mechanical Behavior of Cross-Ply IMC Composites." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-25059.

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In this study the effect of stress field on delamination and fiber/matrix debonding in laminated composite panels is investigated from the micro-mechanical point of view by means of 3-D Finite Element Models. Specifically, the behavior of two-layer cross-ply symmetric laminates made up of SCS-6/Ti-24Al-11Nb Intermetallic Matrix Composite (IMC) during cooling from the processing temperature is studied. The results show that large plastic strains occur at the fiber/matrix interface at the fiber end on the laminate free edge which may eventually extend to the interface of the layers of the laminate inflicting delamination damage. This phenomenon is more serious at the corner areas of the laminate. It also can be shown that this situation is more serious for the four-layer laminate compared to the results of two-layer composite.
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Geier, Bodo, and Rolf Zimmermann. "Composite Laminate Stiffnesses and Their Sensitivities." In ASME 1994 Design Technical Conferences collocated with the ASME 1994 International Computers in Engineering Conference and Exhibition and the ASME 1994 8th Annual Database Symposium. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/detc1994-0133.

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Abstract The great number of possible stacking orders to form laminates suggests to apply optimization, more frequently than usual, in the design of structures made of composite materials. One of the columns upon which optimization of structures is built is the mathematical search procedure for locating a minimum (or maximum) of a constrained function. Efficient algorithms will require the evaluation of derivatives of the object function as well as of the constraints. In that context the sensitivities of laminate stiffness matrices may be required. In order to meet such a requirement the derivatives with respect to both ply thicknesses and ply angles, of laminate stiffnesses, including transverse shear stiffness, will be presented in this report.
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Chamis, C. C., P. L. N. Murthy, and S. N. Singhal. "Computational Simulation of Hot Composite Structures." In ASME 1993 Design Technical Conferences. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/detc1993-0085.

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Abstract Computational procedures are described to simulate the thermal and mechanical behavior of high temperature metal matrix composites (HT-MMC) in the following three broad areas: (1) behavior of HT-MMC from micromechanics to laminate via Metal Matrix Composite Analyzer (METCAN), (2) tailoring of HT-MMC behavior for optimum specific performance via Metal Matrix Laminate Tailoring (MMLT), and (3) HT-MMC structural response for hot structural components via High Temperature Composite Analyzer (HITCAN). The complex composite material behavior, static/fatigue life, and failure sequence of SiC/Ti ring was simulated. The observed experimental degradation in strengths of the SiC/Ti composite with increasing temperature was accurately predicted. The static/fatigue life of the SiC/Ti ring starting with the fabrication process cool-down and subjected to simulated internal pressure was predicted in terms of cyclic-stress-to-static strength-ratio versus cycles to failure.
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Correia, Victor M. F., Cristovao M. M. Soares, and Carlos A. Mota Soares. "Numerical model for the optimal design of composite laminated structures with piezoelectric laminate." In 1999 Symposium on Smart Structures and Materials, edited by Vasundara V. Varadan. SPIE, 1999. http://dx.doi.org/10.1117/12.350094.

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Filippini, Mauro. "Identification of the Mechanical Properties of Composite Materials by Inverse Analysis." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-25101.

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A procedure based on the principles of inverse analysis has been employed to identify the elastic material parameters and the strength characteristics of epoxy carbon fiber reinforced composite laminates. By adopting a classical optimization algorithm, elasticity parameters are chosen by minimizing the mean squared error between the values predicted by the classical theory of elastic laminates and the experimentally observed ones. The average modulus of the laminate has been calculated from elastic parameters of laminas by implementing the classical equations of anisotropic elasticity in a subroutine, in order to speed up the optimization process. In a similar fashion, even though under strongly simplifying hypothesis, the strength characteristic parameters of laminas have been identified by inverse analysis, with the aim of assessing the strength of the composite laminates in the case of complex stress state.
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Akter, Rizwana, and Oliver J. Myers. "Fabrication of a 3D Bistable Composite." In ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2365.

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Abstract Bistable composites have created much attention in engineering applications because of its ability to sustain two stable shapes. A systematic layup of carbon fiber reinforced polymer (CFRP) causes bistability in a lamina. The transition from one stable shape to another is occurred by snap-through and snap-back process. Due to their adaptive nature a lot of study has been conducted on a 2D laminate for over the past 30 years. However, fabrication of a 3D model that exhibits bistability is yet to be explored. In this research we fabricated a 3D bistable composite structure having two parallel cross-ply square laminates connected by a rigid tab at one edge. The entire structure exhibits bistability when the two laminates are actuated simultaneously. The parallel laminates are also independent when actuated individually, making the model achieve four independent stable shapes. Our goal is to understand the bistable behavior and predict the degree of curvature and the snap through response of the solid structure. This paper discusses the fabrication of a solid composite structure that can be further analyzed numerically by creating an FEA model using ABAQUS. The simulation results could be validated experimentally. In this research we also aim to put together an analytical model of this 3D laminate structure. Successful fabrication and mathematical analysis of our 3D laminate using carbon fiber reinforced polymer will hopefully inspire additive manufacturing of bistable composite structure that will lead to more complicated design of bistable materials with more morphing characteristics.
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Hu, Huiwen, Bor-Tsuen Wang, and Jing-Shiang Su. "Application of Modal Analysis to Damage Detection in Composite Laminates." In ASME 7th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2004. http://dx.doi.org/10.1115/esda2004-58296.

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A nondestructive detection of damage in composite laminates by using modal analysis is investigated in this paper. Continued fiber-reinforced composite AS4/PEEK was used to fabricate a symmetrical laminate plate and a surface crack was created in one side of the laminate plate. The results of modal testing are presented for the application of modal analysis to the laminate plate before and after damage. Changes in mode shapes, mode shape slopes and strain energies were used to calculate the damage index for indicating the damage location. Differential quadrature method (DQM) was introduced to solve the problem of partial derivatives function in strain energy formula. A 3-D finite element model was created for comparison with the experimental results. The model accurately predicted the dynamic responses. It was found that damage index using strain energy method provides a more promising result than other methods in locating the damage.
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Chuang, Shui-Nan. "Probabilistic Analysis for the Mechanical Properties of Cross-Ply Fiber-Reinforced Composite Laminate." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13060.

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A probabilistic micromechanics model had been developed for the unidirectional fiber-reinforced composite material design screening. In which, we used the predicted mechanical properties of IM-7 carbon fiber from the existing IM-7/5250-4 composite material system together with the observed 977-3 matrix mechanical properties to predict the probability density functions for the mechanical properties of IM-7/977-3 unidirectional composite. To include the material design in the structural design process, we had extended the probabilistic analysis to predict the probability density functions for the off-axis mechanical properties. The angle-ply and cross-ply laminates have been used extensively in aerospace structural designs. It is logical to extend the probabilistic analysis to predict the probability density functions for the mechanical properties of the laminated composite. We had provided the probabilistic analysis for a symmetric regular angle-ply laminate of IM-7/5250-4 composite laminate. In this report, we will focus on the probabilistic analysis of symmetric and anti-symmetric regular cross-ply laminates of IM-7/5250-4 fiber-reinforced composite with odd-number plies parallel to and even-number plies perpendicular to the laminate principal axes. These probabilistic micromechanics models provide a design-screening tool to help material producers to eliminate the unnecessary time-consuming and costly material fabrications and to reduce the numbers of testing to a minimum but enough to verify the model prediction. They also provide a structural analysis tool to help the structural designer to manage the structural and material uncertainties during the structural design process. And consequently, it provides a means to accelerate the insertion of materials into AF productions.
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Reports on the topic "Composite laminate design"

1

Lange, Fred F., M. P. Rao, A. J. Sanchez-Herencia, G. E. Beltz, and R. M. McMeeking. Reliable Ceramic Structural Composites Designed with a Threshold Strength. Laminar Ceramics That Exhibit a Threshold Strength. Fort Belvoir, VA: Defense Technical Information Center, April 2000. http://dx.doi.org/10.21236/ada389140.

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