Relevant bibliographies by topics / Composite flexible hinges

Academic literature on the topic 'Composite flexible hinges'

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

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Journal articles on the topic "Composite flexible hinges"

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Shi, Yunlai, Chengshu Lou, and Jun Zhang. "Investigation on a Linear Piezoelectric Actuator Based on Stick-Slip/Scan Excitation." Actuators 10, no. 2 (February 20, 2021): 39. http://dx.doi.org/10.3390/act10020039.

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To perform a high resolution and long stroke application in optical precision instruments, a linear piezoelectric actuator operated in stick-slip/scan modes for driving a linear motion table is presented. The proposed piezoelectric actuator is a piezoelectric composite structure, which includes a metal elastomer, a piezoelectric stack, and a frictional ball. The purpose of this paper is to describe the operation principle, design, and the running test and resolution test of the linear motion table driven by the proposed piezoelectric actuator. The notable feature is the flexible hinges of the actuator, including composite hinge, pre-pressure adjustment flexible hinge, and transmission flexible hinge, which are designed for decoupling the motion in the action direction of the piezoelectric stack and the direction in which the pre-pressure is applied. A prototype has been fabricated and two operation modes of the piezoelectric actuator, stick-slip and scan mode, were utilized to test the driving characteristics of the linear motion table. Experimental results show that the finest step resolutions in stick-slip mode and scan mode achieved 12 nm and 4 nm, respectively.
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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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Gao, Hang, James Lynch, and Nick Gravish. "Soft Molds with Micro-Machined Internal Skeletons Improve Robustness of Flapping-Wing Robots." Micromachines 13, no. 9 (September 7, 2022): 1489. http://dx.doi.org/10.3390/mi13091489.

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Mobile millimeter and centimeter scale robots often use smart composite manufacturing (SCM) for the construction of body components and mechanisms. The fabrication of SCM mechanisms requires laser machining and laminating flexible, adhesive, and structural materials into small-scale hinges, transmissions, and, ultimately, wings or legs. However, a fundamental limitation of SCM components is the plastic deformation and failure of flexures. In this work, we demonstrate that encasing SCM components in a soft silicone mold dramatically improves the durability of SCM flexure hinges and provides robustness to SCM components. We demonstrate this advance in the design of a flapping-wing robot that uses an underactuated compliant transmission fabricated with an inner SCM skeleton and exterior silicone mold. The transmission design is optimized to achieve desired wingstroke requirements and to allow for independent motion of each wing. We validate these design choices in bench-top tests, measuring transmission compliance, kinematics, and fatigue. We integrate the transmission with laminate wings and two types of actuation, demonstrating elastic energy exchange and limited lift-off capabilities. Lastly, we tested collision mitigation through flapping-wing experiments that obstructed the motion of a wing. These experiments demonstrate that an underactuated compliant transmission can provide resilience and robustness to flapping-wing robots.
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Monteleone, Angelo, Gianluca Rodonò, Antonio Gagliano, and Vincenzo Sapienza. "SLICE: An Innovative Photovoltaic Solution for Adaptive Envelope Prototyping and Testing in a Relevant Environment." Sustainability 13, no. 16 (August 4, 2021): 8701. http://dx.doi.org/10.3390/su13168701.

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The development of adaptive architectural envelopes is one of the goals of researchers that aim to improve the energy performance of buildings. Traditional devices often have drawbacks linked to the complexity of the kinetic systems used, as the mechanical systems for guaranteeing proper operation are complex and expensive (e.g., hinges). Adaptive envelopes require energy for driving the mechanical components and management systems. Thus, it is useful for such adaptive elements to be self-sufficient, generating the energy necessary for their functioning. This study presents a prototype of a lightweight and stand-alone component for dynamic envelopes, characterized by a flexible composite material integrated with high-efficiency photovoltaic cells called the Solar Lightweight Intelligent Component for Envelopes (SLICE). The management and control of the SLICE is based on the Arduino platform. This paper describes the multidisciplinary design process that led to the realization of the current prototypes, the laboratory test phases, as well as the results of the preliminary experiments carried out under real environmental conditions.
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Ying, Zhiping, Xudong Hu, Xiaoying Cheng, and Zhenyu Wu. "Numerical investigation on the effect of tow tension on the geometry of three-dimensional orthogonally woven fabric." Textile Research Journal 89, no. 18 (December 30, 2018): 3779–91. http://dx.doi.org/10.1177/0040517518821912.

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The fabric geometry determines the mechanical performance of a textile composite. This paper investigates the effect of tow tension on the fabric geometry during the weaving process. A numerical model at the fiber scale was established by representing the fiber as a chain of truss elements connected by fully flexible hinges and having strong tensile modules. Fabric samples were woven on a homemade loom under different tension configurations to verify the numerical model. The model results with respect to the tow cross-section and path are in good agreement with observations of the homemade fabric sample. The tow cross-section deformation is the consequence of fiber rearrangement due to the transverse force originating from Z-binder tension. It is also found that the crimps of weft tows are different to those of warp tows. For weft tows, appreciable crimping is found in the regions of intercrossing with the Z-binder tow. Meanwhile, fibers undulate at the edges and remain straight in the middle of warp tows.
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Yang, Run Lin, Jie Kong, and Juan Hua Zhou. "Impact-Resistant Analysis of Hinged Reinforced Concrete Beam with Composite Laminates." Applied Mechanics and Materials 501-504 (January 2014): 1000–1003. http://dx.doi.org/10.4028/www.scientific.net/amm.501-504.1000.

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Under the impact loads, once the key load-bearing member is damaged, it will endanger the entire building structures. Hence, it is very important to study impact-resistant performance of structural members. In order to verify effectiveness of a new composite protective device proposed in the earlier time, a reinforced concrete beam hinged at both ends was choosen as the observed object. During the process of numerical simulation, the four different protective measures including the unprotected, the rigid, the flexible and the composite one were considered in sequence. Numerical results show that the proposed composite measure can achieve the best protective effect, and it may be considered as a new option for impact-resistant protection of structural memebers.
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Bowen, Aileen G., Giovanni Zucco, and Paul M. Weaver. "Flexible hinges in orthotropic cylindrical shells facilitated by nonlinear elastic deformations." Composite Structures 268 (July 2021): 113726. http://dx.doi.org/10.1016/j.compstruct.2021.113726.

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Yang, Run Lin, Li Zhao, and Juan Hua Zhou. "Impact-Resistant Performance Analysis of Composite Laminates for Reinforced Concrete Beam Fixed and Hinged at Different Ends." Applied Mechanics and Materials 482 (December 2013): 30–33. http://dx.doi.org/10.4028/www.scientific.net/amm.482.30.

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Structural members are vulnerable to be damaged under the impact loads. According to traditional design methods, the impact load is seldomly considered. However, recently this situation is changed gradually. In view of this, impact-resistant performance of a new composite protective device was analyzed. A reinforced concrete beam with composite laminates, which was fixed at one end and hinged at the other end, was studied. Totally, the four cases including the unprotected, the rigid, the flexible and the composite protective measures were considered. The protective effects of the different measures can be compared by observing the strain, the displacement, the acceleration and the impact force of the target beam. Simulation results show that the composite protective measure can improve the impact-resistant effect of the target beam significantly and its dynamic response is suppressed effectively.
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Li, Yan, Bo Liu, Wenjie Ge, and Xinxing Tong. "Optimization design of compliant focusing mechanism for space optical camera with light weight." Advances in Mechanical Engineering 14, no. 8 (August 2022): 168781322211197. http://dx.doi.org/10.1177/16878132221119707.

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Thermal radiation and vacuum lead to the deformation of bearing cylinder with carbon fiber composites which generates the defocus phenomenon for space optical camera. As heavier weight and higher complexity of the rigid focusing mechanism for the space optical camera, a novel compliant focusing mechanism with lighter weight and simple structure was designed and tested in this paper. In order to achieve stroke range and ensure image quality for the compliant focusing mechanism, micro driving displacement from the piezoelectric ceramics was amplified by two-stage flexible hinge lever-type mechanism. Taking the size parameters of the flexure hinges and beams as the design variables, an optimization model of the compliant focusing mechanism was established in which minimizing weight was considered as objection function under the stroke requirements. Consequently, optimal structure parameters of the compliant focusing mechanisms under different input forces can be obtained under the allowable stress and lighter weight. The effectiveness of the proposed compliant focusing mechanism was verified by the simulations and experiments. The results show that the compliant focusing mechanism can achieve a stroke of 2 mm for the focal plane assembly. The proposed method provided a new idea to design the focusing mechanism with lighter weight, simpler structure and higher reliability.
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Baur, Werner H. "Self-limiting distortion by antirotating hinges is the principle of flexible but noncollapsible frameworks." Journal of Solid State Chemistry 97, no. 1 (March 1992): 243–47. http://dx.doi.org/10.1016/0022-4596(92)90031-p.

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Book chapters on the topic "Composite flexible hinges"

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Rath, Jan-Erik, Robert Graupner, and Thorsten Schüppstuhl. "Die-Less Forming of Fiber-Reinforced Plastic Composites." In Lecture Notes in Mechanical Engineering, 3–14. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-18326-3_1.

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AbstractFiber-reinforced plastics (FRP) are increasingly popular in light weight applications such as aircraft manufacturing. However, most production processes of thin-walled FRP parts to date involve the use of expensive forming tools. This especially hinders cost-effective production of small series as well as individual parts and prototypes. In this paper, we develop new possible alternatives of highly automated and die-less production processes based on a short review of current approaches on flexible thin-walled FRP production. All proposed processes involve robot guided standard tools, similar to incremental sheet metal forming, for local forming of the base materials. These include woven glass fiber fabrics which are locally impregnated with thermoset resin and cured using UV-light, woven commingled yarns made out of glass fibers and thermoplastic fibers which are locally heated and pressed, as well as pre-consolidated thermoplastic organo sheets which require selective heating for forming. General applicability of the processes is investigated and validated in practical experiments.
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Conference papers on the topic "Composite flexible hinges"

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Sauder, Jonathan F., and Brian Trease. "Deployment Testing of Flexible Composite Hinges in Bi-Material Beams." In 3rd AIAA Spacecraft Structures Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0967.

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Heim, Michael, Kyle Pyne, Adrian Bialy, Meghan Burns, Glendon Mohan, Noah Beaty, Connor MacNeal, et al. "Design and Demonstration of a Flexible Matrix Composite Actuated Flap in a UAV." In ASME 2015 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/smasis2015-9033.

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Morphing wings are of great interest in the aerospace community. Control surfaces with continuously variable geometry can increase the efficiency of aircraft aerodynamics. This research focuses on demonstrating a morphing flap on a small span-wise section of the trailing edge in a wing for a small unmanned air vehicle (UAV). The flaps used flexible matrix composite (FMC) actuators embedded in a flexible structure, rather than hinged control surfaces with conventional actuators. This created a local aerodynamic control force whose effect can be measured using the UAV’s on-board flight control system. After multiple design iterations, in which the FMC actuator material and structure were varied, the final design incorporates a carbon fiber frame with an actuator system embedded in a foam matrix. The FMC control surfaces were successfully demonstrated in flight tests on the eSPAARO unmanned aerial vehicle.
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