Artykuły w czasopismach: „Flapping wing, MAV, piezoelectric actuator”

1

Ozaki, Takashi, i Norikazu Ohta. "Power-Efficient Driver Circuit for Piezo Electric Actuator with Passive Charge Recovery". Energies 13, nr 11 (4.06.2020): 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 and found that half of the charge can be recovered by employing a resistor that has a resistance sufficiently larger than the forward resistance of the additional diode. In addition, we experimentally demonstrated the concept. With a capacitive load (as a replacement for the piezoelectric actuator), it was successfully observed that the proposed concept decreased the power consumption to 58% of that in a circuit without charge recovery. Considering micro aerial vehicle (MAV) applications, we measured the lift-to-power efficiency of a flapping wing piezoelectric actuator by applying the proposed concept. The lift force was not affected by charge recovery; however, the power consumption was reduced. As a result, the efficiency was improved to 30.0%. We expect that the proposed circuit will contribute to the advancement of energy-saving microrobotics.

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Zhou, Yu Hua, Yu Tao Ju i Chang Sheng Zhou. "Design of Flexible Wing with Embedded Piezoelectric Actuator". Applied Mechanics and Materials 325-326 (czerwiec 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 dynamic characteristic of the flexible wing with embedded piezoelectric actuator has been done with ANSYS software.

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Marimuthu, Navanitha, Ermira Junita Abdullah, Dayang L. A. Majid i Fairuz I. Romli. "Conceptual Design of Flapping Wing Using Shape Memory Alloy Actuator for Micro Unmanned Aerial Vehicle". Applied Mechanics and Materials 629 (październik 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 superior to other smart materials due to its efficiency and large energy storage capacity. By incorporating SMA in the flapping wing MAV, it will provide users the flexibility to add more payloads by reducing bulky cables or reduce operating cost by using less fuel. However, there are some drawbacks in using SMAs such as nonlinear response of the strain to input current and hysteresis characteristic as a result of which their control is inaccurate and complicated.

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Ozaki, Takashi, Norikazu Ohta i Kanae Hamaguchi. "Resonance-Driven Passive Folding/Unfolding Flapping Wing Actuator". Applied Sciences 10, nr 11 (29.05.2020): 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 the resonant actuation is necessary for extremely small, insect-scale MAVs, research is required to realize such MAVs with a foldable-wing mechanism. Therefore, we first examine and report the performance of the resonant-driven passive folding/unfolding mechanism. We also present a simplified theoretical model demonstrating an interaction between the resonant actuation system and folding/unfolding mechanism. We successfully demonstrate the folding/unfolding motion by the fabricated actuator. In addition, the theoretical model showed good agreement with the experiment.

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Kong, Guoli, i 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, nr 3 (1.05.2019): 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 discontinuous conduction mode to ensure the stability of the output high voltage. The half-bridge drive stage takes the approach of comparing the output voltage signal with an ideal waveform lookup table to generate arbitrary unipolar signals. The proposed converter has a weight of 345 mg, a size of 285 mm2 (19 × 15 mm2), a maximum output power of 500 mW, and a maximum conversion efficiency of 64.5%. An experiment driving for piezoelectric actuator was performed to observe the displacement generated by the converter. According to the experimental results, this converter can be applied in flapping-wing micro aerial vehicles.

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Kim, Inrae, Seungkeun Kim i Jinyoung Suk. "Disturbance Observer Based Control of Flapping Wing MAV Considering Actuator and Sensor Model". Journal of Institute of Control, Robotics and Systems 25, nr 11 (30.11.2019): 950–59. http://dx.doi.org/10.5302/j.icros.2019.19.0180.

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Ozaki, Takashi, i Kanae Hamaguchi. "Electro-Aero-Mechanical Model of Piezoelectric Direct-Driven Flapping-Wing Actuator". Applied Sciences 8, nr 9 (19.09.2018): 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 good agreement with the analytical calculation for both types of actuators; the errors in the evaluated characteristics were less than 30%. The results indicated that the analytical model well simulates the actual prototypes.

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Shakya, N. K., i S. S. Padhee. "Study on piezo-electric flapping wing mechanism for bio-inspired micro aerial vehicles". Journal of Physics: Conference Series 2070, nr 1 (1.11.2021): 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 is created by attaching a polymer skin to a pair of carbon fiber reinforced plastic spars. This wing is connected by means of an elastic-element (EE) to a pair of piezoelectric unimorphs (piezofan). The motion from the piezofan to the wing is transferred through this EE. Simulation has been done by applying sinusoidal voltages of varying frequency to this piezofan and observations have been made for the flapping amplitude of the wing for different stiffness of the EE. It is observed that the amplitude of the peak flapping amplitude initially increases, attains a maximum value, then decreases again with an increase in the stiffness of the EE. It is also observed that as the EE stiffness increases, the corresponding peak of the flapping amplitude shifts towards higher frequency.

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Huang, Fang Sheng, Zhi Hua Feng, Yu Ting Ma i Qiao Sheng Pan. "Investigation on high-frequency performance of spiral-shaped trapezoidal piezoelectric cantilever". Modern Physics Letters B 32, nr 17 (18.06.2018): 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 theoretic analysis. The spiral-shaped trapezoidal piezoelectric cantilever is suitable for working as an actuator in micro flapping-wing aircraft.

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Jeong, Seung-hee, Jeong-hwan Kim, Seung-ik Choi, Jung-keun Park i 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, nr 1 (23.12.2022): 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 control input signals. Considering transient responses, each torque response as an actuator is modelled as a simple first-order system. Roll, pitch, and yaw control commands affect each other. They should be compensated in a closed loop controller design. Total weight of the prototype FMAVRES is 17.92 g while the lift force of it is 21.3 gf with 80% throttle input. Thus, it is expected that the new platform of FMAVRES could be used effectively to develop simple and robust flapping MAVs.

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Ozaki, Takashi, i Kanae Hamaguchi. "Performance of direct-driven flapping-wing actuator with piezoelectric single-crystal PIN-PMN-PT". Journal of Micromechanics and Microengineering 28, nr 2 (9.01.2018): 025007. http://dx.doi.org/10.1088/1361-6439/aaa2c8.

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Hauris, Francis, i 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, nr 15 (29.06.2020): 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; substrate thickness variation; and substrate-to-actuator-thickness ratio. Response metrics representing heave and pitch motions are taken as longitudinal curvature and lateral slope, respectively—the surface regression analysis and results leading to these choices are presented. Maximum longitudinal curvature and lateral slope amplitudes and phase shifts are reported for key parameter choices. Longitudinal curvature to lateral slope coupling is achieved with the introduction of a leading edge stiffener to the otherwise uniform thickness plate. Conditions and parameters that lead to and influence heave–pitch coupling are presented and discussed in detail. This article presents a unique approach to flapping mode of flight compared to the literature. The article proposes a purely induced-strain actuation approach rather than the typical “mechanisms” based approach.

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Huang, Fang Sheng, Zhi Hua Feng, Yu Ting Ma, Qiao Sheng Pan, Lian Sheng Zhang, Yong Bin Liu i Liang Guo He. "High-frequency performance for a spiral-shaped piezoelectric bimorph". Modern Physics Letters B 32, nr 10 (10.04.2018): 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 higher inherent frequencies (from 204.79 Hz to 504.84 Hz in terms of axial oscillation mode, and from 319.77 Hz to 704.48 Hz in terms of tangential torsional mode). The spiral-shaped piezoelectric bimorph is fabricated by a precise laser cutting process and consists of two turns with effective length of 60 mm, width of 2.5 mm, and thickness of 1.6 mm, respectively. With the excitation voltage of 100 Vpp applying an electric field across the thickness of the bimorph, the tip displacement of the actuator in the axial oscillation and tangential torsional modes are 85 [Formula: see text]m and 15 [Formula: see text]m, respectively.

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Hope, Daniel K., Anthony M. DeLuca i Ryan P. O’Hara. "Investigation into Reynolds number effects on a biomimetic flapping wing". International Journal of Micro Air Vehicles 10, nr 1 (3.01.2018): 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 Technology baseline 50 mm wing was compared to wings manufactured with 55, 60, 65, and 70 mm spans, while maintaining a constant aspect ratio. Tests were conducted in a vacuum chamber at air densities between 0.5% and 100% of atmospheric pressure. Increasing the wingspan increased the wing’s weight, which reduced the first natural frequency; and did not result in an increase in vertical force over the baseline 50 mm wing. However, if the decrease in natural frequency corresponding to the increased wing span was counteracted by increasing the thickness of the joint material in the linkage mechanism, vertical force production increased over the baseline wing planform. Of the wings built with the more robust flapping mechanism, the 55 mm wing span produced 95% more vertical force at a 26% higher flapping frequency, while the 70 mm wing span produced 165% more vertical force at a 10% lower frequency than the Air Force Institute of Technology baseline wing. Negligible forces and moments were measured at vacuum, where the wing exhibited predominantly inertial motion, revealing flight forces measured in atmosphere are almost wholly limited to interaction with the surrounding air. Lastly, there was a rough correlation between Reynolds number and vertical force, indicating Reynolds number is a useful modelling parameter to predict lift and corresponding aerodynamic coefficients for a specific wing design.

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Chellapurath, Mrudul, Sam Noble i 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, 26.11.2020, 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 wing kinematics enables swift to generate various unsteady aerodynamic mechanisms. Using the geometric and kinematic details, a flapping wing mechanism that emulates the wing kinematics of the bird was designed. The flapping wing mechanism based on the epicyclic ellipsograph mechanism presented herein integrates flapping motion, fore and aft motion, and selective wing rotation. Importantly, this fully constrained mechanism allows performing all the key kinematic motions of the common swift with a single actuator. A kinematic model of the mechanism is presented to calculate the design parameters based on the scale of the MAV. Kinematic simulation of the mechanism is also presented to verify the design.

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Guo, Yueyang, Wenqing Yang, Yuanbo Dong i Jianlin Xuan. "Numerical investigation of an insect-scale flexible wing with a small amplitude flapping kinematics". Physics of Fluids, 8.07.2022. 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 harmonic law of small amplitude with high frequency, which corresponds to the flapping wing driven by a piezoelectric actuator. The inertial and aerodynamic forces of the wing can cause chordwise torsion, thereby improving aerodynamic performance. The concerned flapping frequency refers to the structural modal frequency and FSI modal frequency. The study shows that this flapping motion can satisfy the requirements of lift to sustain the flight on this scale. At a certain frequency, the flapping wing can effectively utilize the strain energy storage and release mechanism of the flexible wing to provide sufficient lift. The modal frequency of the structure can amplify the deformation of the wing, but it cannot improve the aerodynamic performance, however, the aerodynamic efficiency can achieve the highest at the first order FSI modal frequency. There is a flapping frequency smaller than the first order FSI modal frequency maximizes the aerodynamic force in the vertical direction.

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Helps, Tim, Christian Romero, Majid Taghavi, Andrew T. Conn i Jonathan Rossiter. "Liquid-amplified zipping actuators for micro-air vehicles with transmission-free flapping". Science Robotics 7, nr 63 (2.02.2022). 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 electrostatic forces at the wing root, eliminating the requirement of any transmission system and their associated downsides. The LAZA allows for accurate control of flapping frequency and amplitude, exhibits no variation in performance over more than 1 million actuation cycles, and delivers peak and average specific powers of 200 and 124 watts per kilogram, respectively, exceeding mammalian and insect flight muscle and on par with modern flapping MAV actuation systems. The inclusion of 50-millimeter-long passively pitching wings in a dragonfly-sized LAZA flapping system allowed the rectification of net directional thrust up to 5.73 millinewtons. This thrust was achieved while consuming only 243 milliwatts of electrical power, implying a thrust-to-power ratio of 23.6 newtons per kilowatt, similar to state-of-the-art flapping MAVs, helicopter rotors, and commercial drone motors. Last, a horizontally moving LAZA flapping system supported by a taut nylon wire was able to accelerate from at-rest and travel at speeds up to 0.71 meters per second. The LAZA enables lightweight, high-performance transmission-free flapping MAVs for long-term remote exploration and search-and-rescue missions.

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Artykuły w czasopismach na temat „Flapping wing, MAV, piezoelectric actuator”

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