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Relevant bibliographies by topics / Flapping wing, MAV, piezoelectric actuator / Journal articles

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Journal articles on the topic 'Flapping wing, MAV, piezoelectric actuator'

Author: Grafiati

Published: 6 September 2023

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1

Ozaki, Takashi, and Norikazu Ohta. "Power-Efficient Driver Circuit for Piezo Electric Actuator with Passive Charge Recovery." Energies 13, no. 11 (2020): 2866. http://dx.doi.org/10.3390/en13112866.

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Piezoelectric actuation is a promising principle for insect-scaled robots. A major concern while utilizing a piezoelectric actuator is energy loss due to its parasitic capacitance. In this paper, we propose a new concept to recover the charge stored in the parasitic capacitance; it requires only three additional lightweight passive components: two diodes and a resistor. The advantages of our concept are its small additional mass and simple operating procedure compared with existing charge recovery circuits. We provided a guideline for selecting a resistor using a simplified theoretical model a

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2

Zhou, Yu Hua, Yu Tao Ju, and Chang Sheng Zhou. "Design of Flexible Wing with Embedded Piezoelectric Actuator." Applied Mechanics and Materials 325-326 (June 2013): 951–55. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.951.

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This paper introduces a new kind of flexible wing with embedded piezoelectric actuator as framework for Micro Air Vehicles (MAV), which was fixed spar in the previous flexible wing. This made it a controllable flexible wing because the new flexible wing can not only works as previous model without control, but also can change its wing profiles in our purpose by using the embedded piezoelectric actuator when its necessary. The mathematical model of the deformation of piezoelectric actuator under control has developed. with which the structure of the flexible wing was designed. The simulation of

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3

Marimuthu, Navanitha, Ermira Junita Abdullah, Dayang L. A. Majid, and Fairuz I. Romli. "Conceptual Design of Flapping Wing Using Shape Memory Alloy Actuator for Micro Unmanned Aerial Vehicle." Applied Mechanics and Materials 629 (October 2014): 152–57. http://dx.doi.org/10.4028/www.scientific.net/amm.629.152.

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Micro Air Vehicle (MAV) has the capability to fly autonomously in complex environments which enables human to conduct surveillance in areas which are deemed too dangerous or in confined spaces that does not allow human entry. Research and development of MAVs aim to reduce their size further, thus novel techniques need to be explored in order to achieve this objective while still maintaining the MAVs’ current performance. In this paper, a conceptual design of an MAV with a main drive system using shape memory alloy (SMA) actuator to provide the flapping motion is proposed. SMA is considered sup

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4

Ozaki, Takashi, Norikazu Ohta, and Kanae Hamaguchi. "Resonance-Driven Passive Folding/Unfolding Flapping Wing Actuator." Applied Sciences 10, no. 11 (2020): 3771. http://dx.doi.org/10.3390/app10113771.

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The wings of flapping-wing micro aerial vehicles (MAVs) face the risk of breakage. To solve this issue, we propose the use of a biomimetic foldable wing. In this study, a resonant-driven piezoelectric flapping-wing actuator with a passive folding/unfolding mechanism was designed and fabricated, in which the folding/unfolding motion is passively realized by the centrifugal and lift forces due to the stroke motion of the wings. Although the passive folding/unfolding is a known concept, its feasibility and characteristics in combination with a resonant system have not yet been reported. Because t

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5

Kong, Guoli, and Yu Su. "A dual-stage low-power converter driving for piezoelectric actuator applied in flapping-wing micro aerial vehicles." International Journal of Advanced Robotic Systems 16, no. 3 (2019): 172988141985171. http://dx.doi.org/10.1177/1729881419851710.

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It is essential for flapping-wing micro aerial vehicles to have a driver with compact size, low mass, and high conversion efficiency in low-power application. In this article, a dual-stage low-power converter driving for piezoelectric actuator was designed and implemented, which can be applied in flapping-wing micro aerial vehicles. Using the “simultaneous drive” method, an Residual Current Devices (RCD) passive snubber flyback DC/DC step-up converter cascaded with a bidirectional active half-bridge drive stage is designed. The flyback converter is controlled by pulse width modulation in disco

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6

Kim, Inrae, Seungkeun Kim, and Jinyoung Suk. "Disturbance Observer Based Control of Flapping Wing MAV Considering Actuator and Sensor Model." Journal of Institute of Control, Robotics and Systems 25, no. 11 (2019): 950–59. http://dx.doi.org/10.5302/j.icros.2019.19.0180.

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7

Ozaki, Takashi, and Kanae Hamaguchi. "Electro-Aero-Mechanical Model of Piezoelectric Direct-Driven Flapping-Wing Actuator." Applied Sciences 8, no. 9 (2018): 1699. http://dx.doi.org/10.3390/app8091699.

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We present an analytical model of a flapping-wing actuator, including its electrical, aerodynamic, and mechanical systems, for estimating the lift force from the input electrical power. The actuator is modeled as a two-degree-of-freedom kinematic system with semi-empirical quasi-steady aerodynamic forces and the electromechanical effect of piezoelectricity. We fabricated actuators of two different scales with wing lengths of 17.0 and 32.4 mm and measured their performances in terms of the stroke/pitching angle, average lift force, and average consumed power. The experimental results were in go

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8

Shakya, N. K., and S. S. Padhee. "Study on piezo-electric flapping wing mechanism for bio-inspired micro aerial vehicles." Journal of Physics: Conference Series 2070, no. 1 (2021): 012144. http://dx.doi.org/10.1088/1742-6596/2070/1/012144.

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Abstract The Micro Aerial Vehicle (MAV) with a flapping wing configuration is much more efficient and capable of generating substantial lift at low flight speeds and has excellent maneuverability. Different motor-driven mechanisms have been developed to mimic this flapping motion, but these mechanisms introduced mechanical complexity and heavy weight to the system. Piezo-electric based mechanisms have been used to solve these problems, but provide very small flapping amplitudes within the size limitation of MAVs. So some kind of amplification mechanism is needed. In this paper, a flexible wing

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9

Huang, Fang Sheng, Zhi Hua Feng, Yu Ting Ma, and Qiao Sheng Pan. "Investigation on high-frequency performance of spiral-shaped trapezoidal piezoelectric cantilever." Modern Physics Letters B 32, no. 17 (2018): 1850187. http://dx.doi.org/10.1142/s0217984918501877.

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Trapezoidal structure has been proposed for construction of piezoelectric cantilever to increase inherent frequency. To further break through the limitation on frequency value, trapezoidal piezoelectric cantilever is rolled into spiral-shaped piezoelectric cantilever with identical effective length in this study, which is verified in COMSOL simulations and experiments. A prototype shows that after rolling the straight shape into a spiral shape for the trapezoidal piezoelectric cantilever, the first inherent frequency promotes 4.5 times from 98100 Hz to 441,900 Hz, which is consistent with theo

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10

Jeong, Seung-hee, Jeong-hwan Kim, Seung-ik Choi, Jung-keun Park, and Tae-sam Kang. "Platform Design and Preliminary Test Result of an Insect-like Flapping MAV with Direct Motor-Driven Resonant Wings Utilizing Extension Springs." Biomimetics 8, no. 1 (2022): 6. http://dx.doi.org/10.3390/biomimetics8010006.

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In this paper, we propose a platform for an insect-like flapping winged micro aerial vehicle with a resonant wing-driving system using extension springs (FMAVRES). The resonant wing-driving system is constructed using an extension spring instead of the conventional helical or torsion spring. The extension spring can be mounted more easily, compared with a torsion spring. Furthermore, the proposed resonant driving system has better endurance compared with systems with torsion springs. Using a prototype FMAVRES, it was found that torques generated for roll, pitch, and yaw control are linear to c

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11

Ozaki, Takashi, and Kanae Hamaguchi. "Performance of direct-driven flapping-wing actuator with piezoelectric single-crystal PIN-PMN-PT." Journal of Micromechanics and Microengineering 28, no. 2 (2018): 025007. http://dx.doi.org/10.1088/1361-6439/aaa2c8.

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12

Hauris, Francis, and Onur Bilgen. "Parametric modal analysis of an induced-strain actuated wing-like plate for pitch and heave coupling response." Journal of Intelligent Material Systems and Structures 31, no. 15 (2020): 1793–807. http://dx.doi.org/10.1177/1045389x20930078.

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This article investigates the feasibility of a plate-like flapping wing with varying geometric and boundary conditions actuated by surface-bonded piezoelectric material devices. The most influential structural parameters that vary dynamic response and heave–pitch mode coupling are investigated. An analytically and experimentally validated dynamic finite element model is developed to analyze the structure. A parametric analysis is conducted by varying critical geometric parameters and boundary conditions, such as aspect ratio, actuator position, actuator angle, clamp size, and position; substra

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13

Huang, Fang Sheng, Zhi Hua Feng, Yu Ting Ma, et al. "High-frequency performance for a spiral-shaped piezoelectric bimorph." Modern Physics Letters B 32, no. 10 (2018): 1850111. http://dx.doi.org/10.1142/s0217984918501117.

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Piezoelectric cantilever is suitable as an actuator for micro-flapping-wing aircraft. Higher resonant frequency brings about stronger flight energy, and the flight amplitude can be compensated by displacement–amplification mechanism, such as lever. To obtain a higher resonant frequency, straight piezoelectric bimorph was rolled into spiral-shaped piezoelectric bimorph with identical effective length in this study, which is verified in COMSOL simulations. Simulation results show that compared with the straight piezoelectric bimorph, the spiral-shaped piezoelectric bimorph with two turns has hig

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14

Hope, Daniel K., Anthony M. DeLuca, and Ryan P. O’Hara. "Investigation into Reynolds number effects on a biomimetic flapping wing." International Journal of Micro Air Vehicles 10, no. 1 (2018): 106–22. http://dx.doi.org/10.1177/1756829317745319.

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This research investigated the behavior of a Manduca sexta inspired biomimetic wing as a function of Reynolds number by measuring the aerodynamic forces produced by varying the characteristic wing length and testing at air densities from atmospheric to near vacuum. A six degree of freedom balance was used to measure forces and moments, while high speed cameras were used to measure wing stroke angle. An in-house created graphical user interface was used to vary the voltage of the drive signal sent to the piezoelectric actuator which determined the wing stroke angle. The Air Force Institute of T

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15

Chellapurath, Mrudul, Sam Noble, and KG Sreejalekshmi. "Design and kinematic analysis of flapping wing mechanism for common swift inspired micro aerial vehicle." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, November 26, 2020, 095440622097404. http://dx.doi.org/10.1177/0954406220974046.

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The article presents a novel flapping wing mechanism for Micro Aerial Vehicle (MAV) inspired by one of the most efficient flyers of the aerial world, the Common swift ( Apus apus). The flight characteristics such as wing beat frequency, wing beat amplitude, and fore and aft movements, as well as wing rotation of the bird at a flight speed 8 m /s, were studied. The common swift rotates its hand wing keeping the pitch of the arm wing constant during the entire wingbeat cycle. The hand wing undergoes forward rotation during the downstroke and backward rotation during the upstroke. This complex wi

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16

Guo, Yueyang, Wenqing Yang, Yuanbo Dong, and Jianlin Xuan. "Numerical investigation of an insect-scale flexible wing with a small amplitude flapping kinematics." Physics of Fluids, July 8, 2022. http://dx.doi.org/10.1063/5.0098082.

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To maintain flight, insect-scale air vehicles must adapt to their low Reynolds number flight conditions and generate sufficient aerodynamic force. Researchers conducted extensive studies to explore the mechanism of high aerodynamic efficiency on such a small scale. In this paper, a centimeter-level flapping wing is used to investigate the mechanism and feasibility of whether a simple motion with certain frequency can generate enough lift. The unsteady numerical simulations are based on fluid structure interaction (FSI) method and dynamic mesh technology. The flapping motion is in a simple harm

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17

Helps, Tim, Christian Romero, Majid Taghavi, Andrew T. Conn, and Jonathan Rossiter. "Liquid-amplified zipping actuators for micro-air vehicles with transmission-free flapping." Science Robotics 7, no. 63 (2022). http://dx.doi.org/10.1126/scirobotics.abi8189.

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Flapping micro-air vehicles (MAVs) can access a wide range of locations, including confined spaces such as the inside of industrial plants and collapsed buildings, and offer high maneuverability and tolerance to disturbances. However, current flapping MAVs require transmission systems between their actuators and wings, which introduce energetic losses and additional mass, hindering performance. Here, we introduce a high-performance electrostatic flapping actuation system, the liquid-amplified zipping actuator (LAZA), which induces wing movement by direct application of liquid-amplified electro

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