Relevant bibliographies by topics / Morphing composites

Academic literature on the topic 'Morphing composites'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Morphing composites"

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Rivera-Tarazona, L. K., V. D. Bhat, H. Kim, Z. T. Campbell, and T. H. Ware. "Shape-morphing living composites." Science Advances 6, no. 3 (January 2020): eaax8582. http://dx.doi.org/10.1126/sciadv.aax8582.

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This work establishes a means to exploit genetic networks to create living synthetic composites that change shape in response to specific biochemical or physical stimuli. Baker’s yeast embedded in a hydrogel forms a responsive material where cellular proliferation leads to a controllable increase in the composite volume of up to 400%. Genetic manipulation of the yeast enables composites where volume change on exposure to l-histidine is 14× higher than volume change when exposed to d-histidine or other amino acids. By encoding an optogenetic switch into the yeast, spatiotemporally controlled shape change is induced with pulses of dim blue light (2.7 mW/cm2). These living, shape-changing materials may enable sensors or medical devices that respond to highly specific cues found within a biological milieu.
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Arrieta, Andres F., Onur Bilgen, Michael I. Friswell, and Peter Hagedorn. "Dynamic control for morphing of bi-stable composites." Journal of Intelligent Material Systems and Structures 24, no. 3 (June 27, 2012): 266–73. http://dx.doi.org/10.1177/1045389x12449918.

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Adaptive structures have been the focus of much research due to performance gains not possible to achieve using conventional designs. Within this context, the idea of morphing promises augmented capabilities in terms of manoeuvrability, fuel efficiency and the ability to perform dissimilar tasks in an optimal manner. To achieve morphing, materials capable of changing shape requiring minimum actuation are necessary. Bi-stable composites are a type of composite structures which have two statically stable configurations. This bi-stability property, resulting from locked in-plane residual stresses, has attracted considerable attention from the adaptive structure community for morphing structures as actuation is no required to hold each stable configuration. The change between stable states is physically realised as a jump phenomenon or snap-through, which is strongly non-linear in nature. Morphing strategies exploiting snap-through have been studied showing encouraging preliminary results. This article exploits the dynamic response of bi-stable composites as a means of augmenting the actuation for morphing control. A morphing strategy targeting modal frequencies leading to snap-through of the structure is successfully developed. This results in a full-state configuration control by inducing and reversing snap-through as desired. The strategy is tested on a specimen using Macro Fiber Composites as smart actuators validating the proposed concept.
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Chillara, Venkata Siva C., Leon M. Headings, Ryohei Tsuruta, Eiji Itakura, Umesh Gandhi, and Marcelo J. Dapino. "Shape memory alloy–actuated prestressed composites with application to morphing automotive fender skirts." Journal of Intelligent Material Systems and Structures 30, no. 3 (November 23, 2018): 479–94. http://dx.doi.org/10.1177/1045389x18812702.

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This work presents smart laminated composites that enable morphing vehicle structures. Morphing panels can be effective for drag reduction, for example, adaptive fender skirts. Mechanical prestress provides tailored curvature in composites without the drawbacks of thermally induced residual stress. When driven by smart materials such as shape memory alloys, mechanically-prestressed composites can serve as building blocks for morphing structures. An analytical energy-based model is presented to calculate the curved shape of a composite as a function of force applied by an embedded actuator. Shape transition is modeled by providing the actuation force as an input to a one-dimensional thermomechanical constitutive model of a shape memory alloy wire. A design procedure, based on the analytical model, is presented for morphing fender skirts comprising radially configured smart composite elements. A half-scale fender skirt for a compact passenger car is designed, fabricated, and tested. The demonstrator has a domed unactuated shape and morphs to a flat shape when actuated using shape memory alloys. Rapid actuation is demonstrated by coupling shape memory alloys with integrated quick-release latches; the latches reduce actuation time by 95%. The demonstrator is 62% lighter than an equivalent dome-shaped steel fender skirt.
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Kwon, O.-Hyun, and Jin-Ho Roh. "Origami-inspired shape memory dual-matrix composite structures." Journal of Intelligent Material Systems and Structures 30, no. 17 (September 18, 2019): 2639–47. http://dx.doi.org/10.1177/1045389x19873429.

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A sandwiched morphing structure is developed using an Origami-inspired shape memory dual-matrix composite core and shape memory polymer composite skins. The geometric parameters of the morphing structure are designed to have a zero Poisson’s ratio. In addition, an analytical model is developed to analyze the three-dimensional morphing structure easily. The shape memory dual-matrix composites are fabricated with woven fabrics based on the shape memory polymers, and an epoxy matrix is used to ensure a flexible and shape-recoverable structure. The shape recoverability of the shape memory polymer composite skins is verified by measuring the shape recovery ratio at various temperatures. Based on the tensile tests for the shape memory polymer composite skins and shape memory polymer hinges, it is found that the morphing structure can be highly flexible depending on temperature. Finally, the bending and shape recovery behaviors of the morphing structure are demonstrated.
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Elsheikh, Ammar. "Bistable Morphing Composites for Energy-Harvesting Applications." Polymers 14, no. 9 (May 5, 2022): 1893. http://dx.doi.org/10.3390/polym14091893.

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Bistable morphing composites have shown promising applications in energy harvesting due to their capabilities to change their shape and maintain two different states without any external loading. In this review article, the application of these composites in energy harvesting is discussed. Actuating techniques used to change the shape of a composite structure from one state to another is discussed. Mathematical modeling of the dynamic behavior of these composite structures is explained. Finally, the applications of artificial-intelligence techniques to optimize the design of bistable structures and to predict their response under different actuating schemes are discussed.
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Nguyen, Vinh Quang, Anansa S. Ahmed, and Raju V. Ramanujan. "Morphing Soft Magnetic Composites." Advanced Materials 24, no. 30 (July 3, 2012): 4041–54. http://dx.doi.org/10.1002/adma.201104994.

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Bishay, Peter L., and Christian Aguilar. "Parametric Study of a Composite Skin for a Twist-Morphing Wing." Aerospace 8, no. 9 (September 13, 2021): 259. http://dx.doi.org/10.3390/aerospace8090259.

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Although the benefits of morphing wings have been proven in many studies in the last few decades, the wing skin design remains one of the challenges to advancing and implementing the morphing technology. This is due to the conflicting design requirements of high out-of-plane stiffness to withstand aerodynamic loads and low in-plane stiffness to allow morphing with the available actuation forces. Advancements in the design of hybrid and flexible composites might allow for design solutions that feature this balance in stiffness required for this application. These composites offer new design parameters, such as the number of plies, the fiber-orientation angle of each ply in the skin laminate, and the spatial distribution of the plies on the skin surface. This paper presents a parametric study of a composite skin for a twist-morphing wing. The skin is made of periodic laminated composite sections, called “Twistkins”, integrated in an elastomeric outer skin. The twisting deformation is localized in the elastomeric sections between the Twistkins. The design parameters considered are the number of plies in the composite Twistkins, the fiber-orientation angle of the plies, the torsional rigidity of the elastomer, the width ratio, and the number of elastomeric sections. The computational analysis results showed that the torsional compliance can be increased by increasing the width ratio, decreasing the number of elastomeric sections, number of composite plies and the elastomer’s torsional rigidity. However, this would also lead to a decrease in the out-of-plane stiffness. The nonlinearity and rates at which these parameters affect the skin’s behavior are highlighted, including the effect of the fiber-orientation angle of the laminate plies. Hence, the study guides the design process of this twist-morphing skin.
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Li, Ting, Jian Sun, Jinsong Leng, and Yanju Liu. "An electrical heating shape memory polymer composite incorporated with conductive elastic fabric." Journal of Composite Materials 56, no. 11 (March 27, 2022): 1725–36. http://dx.doi.org/10.1177/00219983221085630.

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Shape memory polymers (SMPs) are a class of smart materials with large deformation performance and variable stiffness characteristics, and have exhibited great potential in morphing skins. The thermal stimulation of SMPs is one of the hotspots in recent years. Shape memory polymer composites (SMPC) filled with conductive materials are activated by Joule heating without external heating facilities. The existing electro-induced SMPCs filled with conductive materials would limit large tension deformation, cannot be heated in a large area, or damage the heating circuit under cyclic loading. These aspects restrict the application of SMPC for morphing skins. In this work, an electro-induced SMP composite was fabricated by the styrene-based SMP incorporated with conductive elastic fabric (CEF) to remove the limiting factors as much as possible. The thermos-mechanical properties and electro-active characteristics of CEF/SMP composite were systematically investigated. The maximum strain at break of CEF/SMP composites reached 206% at 80°C, exhibiting excellent deformation performance. The resistance remained relatively stable after 50 cycles under 40% tensile strain. Furthermore, the CEF/SMP composite with a dimension of 160×160×3 mm3 was successfully heated above the glass transition temperature, demonstrating the actuating ability with a relatively large region. In general, the CEF/SMP composite is promising for the application of morphing skins.
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Karthik, R., S. Guru Prasath, and K. R. Swathi. "Surface Morphing using Macro Fiber Composites." Materials Today: Proceedings 5, no. 5 (2018): 12863–71. http://dx.doi.org/10.1016/j.matpr.2018.02.271.

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Arrieta, A. F., D. J. Wagg, and S. A. Neild. "Dynamic Snap-through for Morphing of Bi-stable Composite Plates." Journal of Intelligent Material Systems and Structures 22, no. 2 (January 2011): 103–12. http://dx.doi.org/10.1177/1045389x10390248.

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Composite laminate plates designed to have two statically stable configurations have been the focus of recent research, with a particular emphasis on morphing applications. In this article, we consider how external vibration energy can be used to assist with the actuation between stable states. This is of interest in the case when surface bonded macro-fiber composites (MFC) actuators are employed as the actuation system. Typically, these type of actuators have been found to require considerably high voltage inputs to achieve significant levels of actuation authority. Therefore, assisting the actuation process will allow lower voltages and/or stiffer plates to be actuated. Two bi-stable plates with different thickness, [04 - 904]T and [02 - 902]T, are tested. The results show a significant reduction in the force required to change state for the case where dynamic excitation provided by an MFC actuator is used to assist the process. This strategy demonstrates the potential of dynamically assisting actuation as a mechanism for morphing of bi-stable composites.
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Dissertations / Theses on the topic "Morphing composites"

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Chillara, Venkata Siva Chaithanya. "Multifunctional Laminated Composites for Morphing Structures." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1524104865278235.

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Ruangjirakit, Kitchanon. "Polyurethane corrugated composites for morphing wing applications." Thesis, Imperial College London, 2014. http://hdl.handle.net/10044/1/18064.

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The morphing wing can be considered as a wing with seamless control surfaces and high-lift devices, which is capable of changing its shape during flight. As a result, an aircraft with the morphing wing can fly multi-mission tasks effectively and efficiently. The morphing wing should be stiff in spanwise direction to withstand aerodynamic and actuation loads while, in chordwise direction, the wing should be compliant in order to allow shape change. In this thesis, corrugated carbon fibre reinforced polyurethane composite is introduced as a candidate for the skin of morphing wing applications as the corrugated composite is considered highly anisotropic. A parametric study of three corrugated profiles (sinusoidal, trapezoidal and U-shape) with differnet amplitudes and unit cell lengths was performed numerically using finite element analysis and compared with analytical model in order to investigate the effects of the corrugation geometry on the mechanical response under tensile load. The results indicate that the trapezoidal profile offers the lowest extensional stiffness followed by U-shape and sinusoidal, respectively. In terms of corrugation geometry, the extensional stiffness of the corrugation is inversely proportional to both unit cell length and amplitude. An aerodynamic analysis of an aerofoil with corrugated lower skin was performed experimentally at four different Reynolds numbers and compared with an aerofoil with smooth skin. The conclusion drawn from the wind tunnel testing is that the aerofoil with corrugated skin on the pressure side is feasible to be used for a morphing wing of a small unmanned aerial vehicle (UAV) that operates at Reynolds number of approximately 10[superscript 5]. A bench-top demonstrator was constructed as a proof of concept and experimentally tested for repeatability and structural integrity. Moreover, the mechanical advantage was evaluated through a simple experiment.
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Panesar, Ajit S. "Multistable morphing composites using variable angle tows (VAT)." Thesis, University of Bristol, 2012. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.574264.

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The continual need to better aircraft performance is increasingly prompting designers towards the realisation of morphing structures. One such enabling morphing technology are "multistable composites", and interest in them stems from the fact that they are able to sustain significant changes in shape without the need for a continuous power supply. This research benefits from the tow-steering technique to develop laminates with curved fibre-paths or Variable Angle Tows (VAT) in a ply (i.e. exploiting the anisotropy of composites), to introduce residual thermal stresses capable of imparting bistability. The principle idea is that VAT laminates can impart bistability with the new feature of ensuring fibre continuity within the wider structure facilitating structural integration (i.e. blending of lay-ups across components). Additional structural strength is shown to be imparted due to the load path continuity achieved via the tow-steering technique. The thermally induced bistable behaviour of VAT laminates is investigated through Finite Element (FE) modelling and experimental studies. The effect on the stable shapes for variations in the resin layers, fibre volume fraction (Vf), resin thermal expansion and laminate thickness are reported and found to be influential (from high to low) in the same quoted order. An approach, aiding the development of well- defined finite element models that are capable of predicting the bistable behaviour of manufactured laminates, is presented. It is shown that despite the inherent variabilities in laminates, a shell model capturing sufficient detail (i.e. resin layer[s), ply thicknesses and the Vf of a ply) is successful in predicting the cured shape(s). An optimisation based design framework aimed at realising the morphing potential of VAT laminates is presented. A morphing alternative to the plain flap is achieved, and the two potential solutions: one aiming to maximise the deployed flap-angle, and the other to attain maximum flap-angle increment, are discussed. Moreover, a good agreement exists between the FE predictions and the experimental observations for the manufactured laminates, demonstrating the feasibility of the morphing flap concept.
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Mulakkal, Manu. "Development of bio-inspired cellulosic smart composites for morphing." Thesis, University of Bristol, 2018. http://hdl.handle.net/1983/6c3e48d3-78f7-4ae3-a50d-2dd7f0f65857.

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Materials capable of self-actuation and architectures facilitating re-configuration are highly valued and profoundly sought-after for numerous applications in the fields of robotics, deployable and morphing structures. Here, a bio-inspired approach to realising a programmable materials system capable of morphing was explored and implemented with a specific focus on the sustainability of the material components. The deployment of manually folded paper architectures using a fluid medium as the morphing stimulus presents a simple and inexpensive methodology capable of self-actuation. The materials-based as well as the stimuli parameters of this system were found to be programmable to control the actuation response of folded paper architectures. These results confirmed the suitability of cellulose as a cost effective and sustainable smart material capable of further functionalisation, and thus justified its consideration in developing programmable morphing systems. Following nature’s inspiration, a strain-gradient mediated methodology for self-folding paper architectures was realised by locally patterning ‘fold-lines’ with a compatible hydrogel system. The architectures were designed to actuate along the principles of paper folding techniques such as origami and kirigami thus providing proven and elegant programmability and actuation attributes. As such, a novel methodology for self-folding and subsequent stimuli responsive deployment of cellulosic architectures was established. The developments in 3D printing (3DP) technology allow the controlled placement of building materials in 3D space and this feature was harnessed to complement the strain-gradient mediated actuation of the cellulosic substrates. Therefore, a bespoke bio-inspired cellulose-hydrogel (carboxymethyl cellulose - CMC) composite for 3D printing was developed which can morph in the time domain (4D) according to the design rules developed from the previous chapters to mimic the actuation of responsive cellulosic structures observed in nature. Consequently, these responsive materials permit 4D printing - a process which pertains the transformation of 3D printed forms with respect to time. In this material system, the cellulose-hydrogel composite constitutes the programmable substrate and the CMC hydrogel acts as the localised component responsible for actuation. The strategy of drying and crosslinking following 3D printing results in a high fibre volume fraction cellulosic composites. The versatility of the materials and fabrication strategies demonstrated here enables the development of complex morphing architectures from computer aided design files with the tuneable material and structural features permitting programmability of the actuation responses. As such, this project demonstrates the realisation of sustainable cellulosic architectures capable of morphing via 4D Printing.
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Mattioni, Filippo. "Thermally induced multi-stable composites for morphing aircraft applications." Thesis, University of Bristol, 2009. http://hdl.handle.net/1983/1a808d25-f44d-42b9-8c43-d5664f1d2417.

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This research focuses on the realisation of 'shape-adaptable' systems through unsymmetrical laminates. The residual stress field which is built-into this type of laminates, is used to obtain panels with two or more equilibrium states. Such systems provide a possible solution for the realisation of morphing structures because they allow to simultaneously fulfil the contradictory requirements of flexibility and stiffness.
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Arrieta-Diaz, Andres Felipe. "Nonlinear Dynamics and Control of Bi-stable Composites for Morphing Applications." Thesis, University of Bristol, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.521093.

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Wang, Bing. "Viscoelastically prestressed composites : towards process optimisation and application to morphing structures." Thesis, University of Hull, 2016. http://hydra.hull.ac.uk/resources/hull:15173.

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This thesis covers research that focuses on facilitating the industrial application of viscoelastically prestressed polymeric matrix composites (VPPMCs). With nylon 6,6 fibre as the reinforcement and polyester resin as the matrix material, unidirectional prestressed composite samples were produced and investigated, to expand the knowledge of existing VPPMC technology, and identify the potential application of viscoelastic fibre prestressing to morphing (shape-changing) structures. To produce a VPPMC, a tensile load is applied to polymeric fibre yarns to induce viscoelastically prestress; following load removal, the yarns are cut and moulded into a matrix. Previous research has shown that by using viscoelastic fibre prestressing within a composite, mechanical properties, such as tensile strength, flexural modulus and impact toughness can be increased by up to 50%. To further understand the underlying prestress mechanisms, the viscoelastic performance of nylon 6,6 fibre was investigated in terms of creep, recovery and recovery force measurement. By using various creep loading conditions, the viscoelastic behaviour of the fibre also provided the basis for investigations into the optimisation of load-time conditions for producing prestress. This provides the first step towards facilitating the production of VPPMCs for industrial application. Since there are increasing demands for using composites within morphing technology, the application of VPPMC principles to morphing structures was studied through both experimental and numerical investigations. The viscoelastic behaviour of nylon 6,6 fibre showed approximately linear viscoelasticity under 24 h creep conditions with up to 590 MPa stress. This was further verified through use of the time-stress superposition principle: instead of a nonlinear relationship as predicted by the well-known WLF equation, a linear relationship between the applied creep stress and the stress shift factor was found. By approaching the maximum creep potential of the fibre material, impact benefits from the prestressing effect were further improved by ~75% (at ~4.0% creep strain level). Charpy impact testing and recovery force measurement demonstrated that there was an optimum level of viscoelastic fibre prestressing to maximise the mechanical benefits. A viscoelastic deformation mechanism based on the three-phase microstructural model and latch-based mechanical model was then proposed. It was found that the fibre processing time for viscoelastically generated prestress could be significantly reduced from 24 h to tens of minutes. By employing the time-temperature superposition principle, the impact benefits from viscoelastically generated prestress under the standard 330 MPa, 24 h creep (at ~3.4% creep strain level), was found broadly to be the same as subjecting the yarns to 590 MPa for 37 min creep. Hence, there was no deterioration in prestress benefits from VPPMC samples produced under both creep conditions to an equivalent of 20,000 years at a constant 20˚C. Two viscoelastic creep strain levels (i.e. ~3.4% and ~4.0%) were evaluated through Charpy impact testing, the relationships between applied creep stress and the corresponding fibre processing time followed a logarithmic trend. This suggested that the fibre processing time for prestress could be reduced further, subjecting to avoiding fibre damage. The effects from increasing creep time were found to compare with increasing stress in terms of optimum VPPMC performance. Finally, the principle of viscoelastic fibre prestressing was successfully used to produce a bistable composite structure, which could snap from one stable cylindrical shape to another when subjected to external loading. The bistable structure was produced by bonding four prestressed strips to the sides of a thin, flexible resin-impregnated fibre-glass sheet. Here, bistability was achieved through pairs of strips orientated to give opposing cylindrical configurations within the sheet. Snap-through behaviour of the bistable structure was investigated through both experimental and numerical simulation; a snap-through mechanism was subsequently proposed based on these observations.
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Rubenking, Samuel Kim. "Dual Mode Macro Fiber Composite-Actuated Morphing Tip Feathers for Controlling Small Unmanned Aircraft." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/78433.

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The transition of flight from manned to unmanned systems has led to new research and applications of technology within the field that, until recently, were previously thought to be unfeasible. The industry has become interested in alternative control surfaces and uses for smart materials. A Macro Fiber Composite (MFC), a smart material, takes advantage of the piezoelectric effect and provides an attractive alternative actuator to servos in the Small Unmanned Aerial Systems (SUAS) regime of flight. This research looks to take MFC actuated control surfaces one step further by pulling inspiration from and avian flight. A dual mode control surface, created by applying two sets of two MFCs to patch of carbon fiber, can mimic the tip feathers of a bird. This actuator was modeled both using Finite Element Analysis (FEA) and Computational Fluid Dynamics (CFD). Real-world static testing on a feather confirmed preliminary FEA results, and wind tunnel tests simulating assumed cruise conditions confirmed the feather would not exhibit any adverse structural behaviors, such as flutter or aeroelastic divergence. From its modeled performance on a wing using CFD, the MFC feather proved to be a success. It was able to produce a wing that, when compared to a traditional rectangular wing, yielded 73% less induced drag and generated proverse yaw. However, the MFC feathers alone, in the configuration tested, did not produce enough roll authority to feasibly control an aircraft.
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Chabaud, Guillaume. "3D and 4D printing of high performance continuous synthetic and natural fibre composites for structural and morphing applications." Thesis, Lorient, 2020. http://www.theses.fr/2020LORIS563.

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L’impression 3D et plus spécifiquement la technique de Fused Filament Fabrication (FFF) de matériaux composites à renforts continus est un domaine d’étude en plein essor visant à pallier les faibles performances mécaniques rencontrées par les composites élaborés en impression 3D et ainsi ouvrir les champs d’applications (aéronautique, course au large…). Autre tendance, l’impression 4D qui permet de développer des matériaux stimulables (capteurs et/ou actionneurs) et d’envisager des structures architecturées complexes se déformant sous l’action de divers stimuli (humidité, électricité, température, pression…). Le travail de thèse s’inscrit dans ce contexte pluriel et vise à développer de nouveaux matériaux multifonctionnels par impression 3D et 4D. Dans un premier temps, le travail de thèse a pour objectif scientifique de comprendre les relations entre le procédé, la microstructure induite, les performances mécaniques et hygro-mécaniques en vue d’applications structurelles (aéronautique, course au large …) sur des matériaux composites renforcés de fibres synthétiques (carbone et verre) et naturelles (lin). La deuxième partie des travaux de thèse vise à développer des matériaux composites hygromorphes renforcés de fibres continues (synthétiques et naturelles) par impression 4D avec une architecture en bilame bio-inspirée de la pomme de pin. Le caractère conducteur des fibres de carbone est utilisé pour développer de nouveaux actionneurs electro- thermo-hygromorphes présentant un actionnement contrôlé et accéléré par rapport aux hygromorphes classiques. Enfin, la liberté de design offerte par l’impression 3D a été utilisée pour contrôler localement la rigidité et l’actionnement d’actionneurs composites renforcés de fibres de lin continues
3D printing and especially Fused Filament Fabrication (FFF) technology for composite materials reinforced by continuous fibers is an emerging research field which aims to enhance the mechanical performance of 3D printing structures and to widen the field of application (aerospace, sailing…). Another trend, 3D printing allows to develop stimulable materials (sensor and/or actuators) and to consider parts with complex architecture that can be deployed under various stimulation (electricity temperature, pressure…). The present work is therefore part of this context and aims to develop new multi-functional materials elaborated by 4D printing. First, the scientific objective of this work is to better understand the relationship between the process, the induced microstructure, mechanical and the hygromechanical performances in order to target structural applications (aeronautic, sailing) for composite materials reinforced with synthetic fibers (carbon and glass) and natural fibers (flax). The second part of this work aimed to develop hygromorphic composites reinforced with continuous fibers (synthetic and natural) by 4D printing with a bioinspired bilayer architecture inspired by the pinecone scale. The conductive behavior of carbon fiber was used to create new electro-thermo-hygromorph actuators with controlled and accelerated actuation compared to conventional hygromorphs. Finally, the design freedom provided by 4D printing made it possible to control the local stiffness and actuation of composite actuators reinforced with continuous flax fiber
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Basit, Abdul. "Development and characterization of a shape memory polymer composite actuator for morphing structures." Thesis, Mulhouse, 2012. http://www.theses.fr/2012MULH8494/document.

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Les polymères à mémoire de forme (SMP) sont des matériaux qui peuvent revenir à leur forme d'origine lorsqu'un stimulus approprié (par exemple de la chaleur) est prévu. Ces polymères sont programmés par cycle de mémoire de forme qui se compose de deux parties: une partie de la programmation qui donne un effet mémoire de forme (SME) à savoir la forme temporaire pour le polymère et la partie de récupération où il revient à sa forme initiale. Les SMP ont une faible rigidité, donc, produisent de grandes déformations récupérables, mais produisent des forces de récupération faibles. Cependant, les composites SMP produisent des forces de récupération plus grandes car ils sont relativement rigide mais ont des souches moins récupérables. En outre, de forts actionneurs à mémoire de forme peuvent être produits si deux effets différents peuvent être combinés dans une structure unique. Une structure déjà active (par exemple des alliages à mémoire de forme) peut être intégré dans SMP. Par conséquent, un fort actionneur couplé peut être obtenu. [...]
Shape memory polymers (SMPs) are the materials which can return to their original shape when a suitable stimulus (e.g. heat) is provided. These polymers are programmed through shape memory cycle that consists of two parts: programming part which gives shape memory effect (SME) i.e. temporary shape to the polymer and the recovery part which return it to its original shape. SMPs have low stiffness, therefore, produce large recoverable strains, but produce low recovery forces. However, SMP composites produce larger recovery forces as they are relatively rigid but have less recoverable strains. Moreover, strong shape memory actuators can be produced if two different effects can be combined in a single structure. An already active structure (e.g shape memory alloys) can be embedded in SMP. Consequently, a strong coupled actuator can be obtained. In this work, the shape memory property of CBCM composite (an active composite that works on bimetallic affect) has been studied. CBCM stands for controlled behavior of composite material. CBCM activeness and its SM property has been coupled together to obtain a strong actuator. SM property has been obtained through thermo-mechanical programming at a temperature higher than glass transition temperature (Tg) of Epoxy resin used for its fabrication. The CBCM actuating properties have been studied through different one-step recoveries (unconstrained, constrained and recovery under load). Moreover, different asymmetrical CBCM composites have been developed by changing the position and orientation of the different layers used. These have been studied for their different actuation properties. Similarly, multi-step recoveries (unconstrained and constrained) have also been performed to show multi step actuation capabilities in CBCM. The actuating properties of CBCM have also been compared with symmetrical composite (SYM) to show the advantage of coupled properties in CBCM. It has been found that CBCM has the ability to give high strain, high recovery forces. Also, it can recover under load and recover to its original position at the temperatures lower than the deforming temperature used in the programming cycle
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Books on the topic "Morphing composites"

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Harnden, Ross, and Kungl Tekniska högskolan Staff. Lightweight Multifunctional Composites: An Investigation into Ion-Inserted Carbon Fibres for Structural Energy Storage, Shape-Morphing, Energy Harvesting and Strain-Sensing. Unknown Publisher, 2021.

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Book chapters on the topic "Morphing composites"

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LaCroix, Bradley W., and Peter G. Ifju. "Macro Fiber Composites and Substrate Materials for MAV Wing Morphing." In Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials, Volume 6, 89–101. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-00873-8_12.

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Mennu, M. M., B. Tran, P. G. Ifju, and E. Santamaria. "Full-Field Deformation Measurement of Morphing Wings." In Mechanics of Composite and Multi-functional Materials, Volume 5, 101–4. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-30028-9_16.

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Mennu, M. M., B. Tran, C. S. Tripp, and P. G. Ifju. "Design Study of Morphing Wing with MFC Actuators." In Mechanics of Composite, Hybrid and Multifunctional Materials , Volume 6, 61–64. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-59868-6_9.

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Mennu, M. M., B. Tran, and P. G. Ifju. "Piezoelectric Actuators as Control Surfaces for Morphing Vehicle." In Mechanics of Composite, Hybrid and Multifunctional Materials, Fracture, Fatigue, Failure and Damage Evolution, Volume 3, 85–88. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-86741-6_14.

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"Wing Morphing Design Using Macro-Fiber Composites." In Smart Composites, 183–226. CRC Press, 2013. http://dx.doi.org/10.1201/b16257-11.

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Mat Yazik, M. H., and M. T. H. Sultan. "Shape memory polymer and its composites as morphing materials." In Failure Analysis in Biocomposites, Fibre-Reinforced Composites and Hybrid Composites, 181–98. Elsevier, 2019. http://dx.doi.org/10.1016/b978-0-08-102293-1.00009-7.

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Airoldi, Alessandro, Giuseppe Sala, Luca Angelo Di Landro, Paolo Bettini, and Alessandro Gilardelli. "Composite Corrugated Laminates for Morphing Applications." In Morphing Wing Technologies, 247–76. Elsevier, 2018. http://dx.doi.org/10.1016/b978-0-08-100964-2.00009-5.

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Kim, J., and S. Ahn. "Fabrication of a soft morphing structure using a Shape Memory Alloy (SMA) wire/polymer skeleton composite." In Innovative Developments in Virtual and Physical Prototyping, 819–23. CRC Press, 2011. http://dx.doi.org/10.1201/b11341-132.

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Conference papers on the topic "Morphing composites"

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Eckstein, E., and Paul Weaver. "Developments in Morphing Composites." In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1378.

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Brinkmeyer, Alex, Alberto Pirrera, Paul Weaver, and Matthew Santer. "Pseudo-Bistable Morphing Composites." In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1576.

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Le Ferrand, Hortense. "Bioinspired multifunctional composites with morphing capabilities." In nanoGe Fall Meeting 2021. València: Fundació Scito, 2021. http://dx.doi.org/10.29363/nanoge.nfm.2021.001.

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TSUSHIMA, NATSUKI, TOMOHIRO YOKOZEKI, WEIHUA SU, and HITOSHI ARIZONO. "Nonlinear Aeroelastic Analysis of Composite Morphing Wing with Corrugated Structures." In American Society for Composites 2018. Lancaster, PA: DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/26174.

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Eckstein, Eric, Michael C. Halbig, and Paul Weaver. "Thermally-Driven Morphing with High Temperature Composites." In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1241.

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Chillara, Venkata Siva, and Marcelo Dapino. "Shape memory alloy-actuated bistable composites for morphing structures." In Behavior and Mechanics of Multifunctional Materials and Composites XII, edited by Hani E. Naguib. SPIE, 2018. http://dx.doi.org/10.1117/12.2296713.

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Murugan, Senthil, Eric I. Saavedra Flores, Michael I. Friswell, and Sondipon Adhikari. "Optimal Design of Elastomer Composites for Morphing Skins." In ASME 2011 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2011. http://dx.doi.org/10.1115/smasis2011-5021.

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Morphing aircraft concepts aim to enhance the aircraft performance over multiple missions by designing time variant wing configurations. The morphing concepts require wing skins that are flexible enough to allow large in-plane stretching and high bending stiffness to resist the aerodynamic loads. In this study, an optimization problem is formed to enhance the in-plane flexibility and bending stiffness of wing skins modeled as composite plates. Initially, the optimal fiber and elastomer materials for highly flexible fiber reinforced elastomer laminates are studied using materials available in the literature. The minor Poisson’s ratio of the laminate is almost zero for all the fiber and elastomer combinations. In the next stage, the effects of boundary conditions and aspect ratio on the out-of-plane deflection of the laminate are studied. Finally, an optimization is performed to minimize the in-plane stiffness and maximize the bending stiffness by spatially varying the volume fraction of fibers of a laminate. The optimization results show that the in-plane flexibility and bending stiffness of the laminate with a variable fiber distribution is 30–40% higher than for the uniform fiber distribution.
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Chillara, Venkata Siva C., and Marcelo J. Dapino. "Bistable morphing composites with selectively pre-stressed laminae." In SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring, edited by Nakhiah C. Goulbourne. SPIE, 2017. http://dx.doi.org/10.1117/12.2259787.

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Lele, Aditya, Oliver J. Myers, and Suyi Li. "Fabrication and Testing of Kirigami-Inspired Multi-Stable Composites." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-7981.

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This paper aims at highlighting the fabrication procedures and proof-of-concept tests of a Kirigami inspired multi-stable composite laminate. Bistable composites consisting of asymmetric fiber layout have shown great potentials for shape morphing and energy harvesting applications. However, a patch of such a bistable composite is limited to very simple deformation when being snapped between its two stable equilibria (or states). To address this issue, this study investigates the idea of utilizing Kirigami, the ancient art of paper cutting, into the design and fabrication of bistable composite laminates. Via combining multiple patches of laminates and cutting according to prescribed Kirigami pattern, one can create a structure with multiple stable states and sophisticated deformation paths between them. This can significantly expand the application potentials of the multi-stable composites. This paper details the fabrication procedures for an elementary unit cell in the envisioned Kirigami composite and the results of proof-of-concept experiments, which measure the force required to switch the Kirigami composite between its different stable states. Preliminary results confirm that the Kirigami unit cell possesses multiple stable states depending on the underlying fiber layout. Each patch in the Kirigami composite could be snapped independently between stable states without triggering any undesired snapping in other patches. Moreover, a transient propagation of curvature change is observed when a patch in the Kirigami composite is snapped between its stable states. Such a phenomenon has not been reported in the bistable composite studies before. Results of this paper indicate that Kirigami is a powerful approach for designing and fabricating multi-stable composites with a strong appeal for morphing and adaptive systems. This paper highlights the feasibility and novelty of combining Kirigami art and bistable adaptive composites.
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Eckstein, Eric, Alberto Pirrera, and Paul Weaver. "Thermally Driven Morphing with Hybrid Laminates and Metal Matrix Composites." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1428.

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