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Artykuły w czasopismach na temat "Flapping wing, MAV, piezoelectric actuator"
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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.
Rozprawy doktorskie na temat "Flapping wing, MAV, piezoelectric actuator"
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Nabawy, Mostafa. "Design of insect-scale flapping wing vehicles". Thesis, University of Manchester, 2015. https://www.research.manchester.ac.uk/portal/en/theses/design-of-insectscale-flapping-wing-vehicles(5720b8af-a755-4c54-beb6-ba6ef1a13168).html.
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This thesis contributes to the state of the art in integrated design of insect-scale piezoelectric actuated flapping wing vehicles through the development of novel theoretical models for flapping wing aerodynamics and piezoelectric actuator dynamics, and integration of these models into a closed form design process. A comprehensive literature review of available engineered designs of miniature rotary and flapping wing vehicles is provided. A novel taxonomy based on wing and actuator kinematics is proposed as an effective means of classifying the large variation of vehicle configurations currently under development. The most successful insect-scale vehicles developed to date have used piezoelectric actuation, system resonance for motion amplification, and passive wing pitching. A novel analytical treatment is proposed to quantify induced power losses in normal hover that accounts for the effects of non uniform downwash, wake periodicity and effective flapping disc area. Two different quasi-steady aerodynamic modelling approaches are undertaken, one based on blade element analysis and one based on lifting line theory. Both approaches are explicitly linked to the underlying flow physics and, unlike a number of competing approaches, do not require empirical data. Models have been successfully validated against experimental and numerical data from the literature. These models have allowed improved insight into the role of the wing leading-edge vortex in lift augmentation and quantification of the comparative contributions of induced and profile drag for insect-like wings in hover. Theoretical aerodynamic analysis has been used to identify a theoretical solution for the optimum planform for a flapping wing in terms of chord and twist as a function of span. It is shown that an untwisted elliptical planform minimises profile power, whereas a more highly tapered design such as that found on a hummingbird minimises induced power. Aero-optimum wing kinematics for hovering are also assessed. It is shown that for efficient flight the flapping velocity should be constant whereas for maximum effectiveness the flapping velocity should be sinusoidal. For both cases, the wing pitching at stroke reversal should be as rapid as possible. A dynamic electromechanical model of piezoelectric bending actuators has been developed and validated against data obtained from experiments undertaken as part of this thesis. An expression for the electromechanical coupling factor (EMCF) is extracted from the analytical model and is used to understand the influence of actuator design variables on actuator performance. It is found that the variation in EMCF with design variables is similar for both static and dynamic operation, however for light damping the dynamic EMCF will typically be an order of magnitude greater than for static operation. Theoretical contributions to aerodynamic and electromechanical modelling are integrated into a low order design method for propulsion system sizing. The method is unique in that aside from mass fraction estimation, the underlying models are fully physics based. The transparency of the design method provides the designer with clear insight into effects of changing core design variables such as the maximum flapping amplitude, wing mass, transmission ratio, piezoelectric characteristics on the overall design solution. Whilst the wing mass is only around 10% of the actuator mass, the effective wing mass is 16 times the effective actuator mass for a typical transmission ratio of 10 and hence the wing mass dominates the inertial contribution to the system dynamics. For optimum aerodynamic effectiveness and efficiency it is important to achieve high flapping amplitudes, however this is typically limited by the maximum allowable field strength of the piezoelectric material used in the actuator.
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Chattaraj, Nilanjan. "A Design Procedure for Flapping Wings Comprising Piezoelectric Actuators, Driver Circuit, and a Compliant Mechanism". Thesis, 2015. http://etd.iisc.ernet.in/2005/3661.
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Flapping-wing micro air vehicle (MAV) is an emerging micro-robotic technology, which has several challenges toward its practical implementation. Inspired by insect flight, researchers have adopted bio-mimicking approach to accomplish its engineering model. There are several methods to synthesize such an electromechanical system. A piezoelectric actuator driven flapping mechanism, being voltage controlled, monolithic, and of solid state type exhibits greater potential than any conventional motor driven flapping wing mechanism at small scale. However, the demand for large tip deflection with constrained mass introduces several challenges in the design of such piezoelectric actuators for this application. The mass constraint restricts the geometry, but applying high electric field we can increase the tip deflection in a piezoelectric actuator.
Here we have investigated performance of rectangular piezo-actuator at high electric field. The performance measuring attributes such as, the tip deflection, block force, block moment, block load, output strain energy, output energy density, input electrical energy, and energy efficiency are analytically calculated for the actuator at high electric field. The analytical results suggest that the performance of such an actuator can be improved by tailoring the geometry while keeping the mass and capacitance constant. Thereby, a tapered piezoelectric bimorph cantilever actuator can provide better electromechanical performance for out-of-plane deflection, compared to a rectangular piezoelectric bimorph of equal mass and capacitance. The constant capacitance provides facility to keep the electronic signal bandwidth unchanged. We have analytically presented improvement in block force and its corresponding output strain energy, energy density and energy effi- ciency with tapered geometry. We have quantitatively and comparatively shown the per- formance improvement. Then, we have considered a rigid extension of non-piezoelectric material at the tip of the piezo-actuator to increase the tip deflection. We have an- alytically investigated the effect of thick and thin rigid extension of non-piezoelectric material on the performance of this piezo-actuator. The formulation provides scope for multi-objective optimization for the actuator subjected to mechanical and electrical con- straints, and leads to the findings of some useful pareto optimal solutions. Piezoelectric materials are polarized in a certain direction. Driving a piezoelectric actuator by high electric field in a direction opposite to the polarized direction can destroy the piezo- electric property. Therefore, unipolar high electric field is recommended to drive such actuators. We have discussed the drawbacks of existing switching amplifier based piezo- electric drivers for flapping wing MAV application, and have suggested an active filter based voltage driver to operate a piezoelectric actuator in such cases. The active filter is designed to have a low pass bandwidth, and use Chebyshev polynomial to produce unipolar high voltage of low flapping frequency. Adjustment of flapping frequency by this voltage driver is compatible with radio control communication.
To accomplish the flapping-wing mechanism, we have addressed a compatible dis- tributed compliant mechanism, which acts like a transmission between the flapping wing of a micro air vehicle and the laminated piezoelectric actuator, discussed above. The mechanism takes translational deflection at its input from the piezoelectric actuator and provides angular deflection at its output, which causes flapping. The feasibility of the mechanism is investigated by using spring-lever (SL) model. A basic design of the com- pliant mechanism is obtained by topology optimization, and the final mechanism is pro- totyped using VeroWhitePlus RGD835 material with an Objet Connex 3D printer. We made a bench-top experimental setup and demonstrated the flapping motion by actuating the distributed compliant mechanism with a piezoelectric bimorph actuator.
Części książek na temat "Flapping wing, MAV, piezoelectric actuator"
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Harish, Ajay Bangalore, i Dineshkumar Harursampath. "Algorithms and Principles for Intelligent Design of Flapping Wing Micro Aerial Vehicles". W Handbook of Research on Computational Intelligence for Engineering, Science, and Business, 521–55. IGI Global, 2013. http://dx.doi.org/10.4018/978-1-4666-2518-1.ch020.
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Almost all Micro Aerial Vehicles (MAVs) designed so far facilitate the flapping motion of their wings by means of a mounted actuating mechanism, driven, for example, by a piezoelectric crystal. The developments over the past decade or so in smart material technologies like the invention of Piezoelectric Fiber Reinforced Composite (PFRC) materials and innovative manufacturing techniques to reduce cost have resulted in favorable materials for dynamic actuating applications. Thus, the concept of actively deformable wings to produce combined flapping and feathering actions is evolving as an attractive enabler for design of future MAVs. A smart material like PFRC can both sense and actuate in a collocated fashion, thus building an additional level of computational intelligence into the MAV itself. Such a promising opportunity indicates an urgent need for reliable design tools to accelerate development of MAVs. In this work, the authors propose a modular design tool specifically for design of self-actuating flapping wing MAVs.
Streszczenia konferencji na temat "Flapping wing, MAV, piezoelectric actuator"
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Olympio, K. R., i Guylaine Poulin-Vittrant. "A honeycomb-based piezoelectric actuator for a flapping wing MAV". W SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring, redaktor Mehrdad N. Ghasemi-Nejhad. SPIE, 2011. http://dx.doi.org/10.1117/12.877073.
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Riddick, Jaret C., Asha J. Hall i Oliver J. Myers. "Numerical Investigation of the Response of Active Bend-Twist PZT Actuator". W ASME 2012 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/smasis2012-8226.
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Army combat operations have placed a high premium on reconnaissance missions for micro air vehicles (MAVs). An analysis of insect flight indicates that in addition to the bending excitation (flapping), simultaneous excitation of the twisting degree-of-freedom is required to manipulate the control surface adequately. By adding a layer of angled piezoelectric segments to a Pb(Zr,Ti)O3 (also referred to as PZT) bimorph actuator, a bend-twist coupling may be introduced to the flexural response of the layered PZT, thereby creating a biaxial actuator capable of driving wing oscillation in flapping wing MAVs. The present study presents numerical investigation of the response of functionally–modified bimorph designs intended for active bend-twist actuation of cm-scale flapping wing devices. The relationships of geometry and orientation of the angled segments with bimorph bend-twist response will be presented using results of finite-element analyses.
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Hall, Asha J., i Jaret C. Riddick. "Active Bend-Twist PZT Actuator for Centimeter-Scale Flapping Wing Micro-Air Vehicle". W ASME 2011 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2011. http://dx.doi.org/10.1115/smasis2011-5085.
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The present study focuses on development of a flapping wing micro-air vehicle (FWMAV) that employs a piezoelectric actuator to drive the leading edge of the wing. An analysis of insect flight indicates that in addition to the bending excitation (flapping), simultaneous excitation of the twisting degree-of-freedom is required to adequately manipulate the control surface. A functionally-modified piezoelectric bimorph composed of Pb(Zr0.55Ti0.45)O3 (PZT) is being used to produce two degree-of-freedom motion, namely the flapping and twisting facilitated by an off-axis layer of piezoelectric segments affixed to the top surface of a traditional bimorph actuator. The modification of the top surface of a traditional PZT bimorph actuator introduces active bend-twist coupling to the flexural response of the resulting layered PZT. This paper presents analytical and experimental investigation of functionally-modified bimorph designs intended for active bend-twist actuation of cm-scale flapping wing devices.
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Ryan, Mark, i Hai-Jun Su. "Classification of Flapping Wing Mechanisms for Micro Air Vehicles". W ASME 2012 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/detc2012-70953.
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The purpose of this paper is to categorize the current state of technology in flapping wing mechanisms of micro air vehicles (MAVs). One of the major components of MAVs is the flapping mechanism, which actuates wings to generate sufficient lift and propulsion force. The goal of the flapping wing mechanism design is to develop a highly efficient and highly robust mechanism, which converts the input motion, either rotational or translational, to a beating motion at a frequency ranging from several to hundreds of Hz. The current practice of designing flapping mechanisms follows an ad-hoc approach with multiple design, build, and test cycles. This design process is very inefficient, costly, time-consuming, and not applicable to mass production of MAVs. This work will be an important step towards a systematic approach for the design of flapping mechanisms for MAVs. In this paper, we will study 15 flapping mechanisms used in recent MAV projects worldwide. We classify these mechanisms based on workspace, compliant or rigid body, type synthesis, mobility, and actuator type. This survey of mechanism classification will serve as a resource for the continued design and development of smaller and more efficient MAVs.
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Shan, Xin, i Onur Bilgen. "A Reduced-Order Multi-Body Model for Ornithopters With Piezocomposite Flapping Wings". W ASME 2022 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/smasis2022-90409.
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Abstract Mechanism-free ornithopters, also referred to as solid-state ornithopters, based on piezoelectric actuators do not need electromagnetic motors or conventional mechanisms, potentially saving weight and energy consumption, and reducing mechanical complexity. In such vehicles, the aim is to achieve lift and thrust purely by surface-mounted piezoelectric actuators; however, the generating sufficient lift and thrust without mechanism augmentation is extremely difficult; and has not been demonstrated. The optimization of wing substrate topology, actuator placement, and excitation parameters requires a computationally efficient model of the dynamic behavior of a solid-state ornithopter. In this article, a reduced-order lumped-parameter model is proposed for ornithopters with piezocomposite flapping wings. The piezoelectric, mechanical, and fluid domains are modeled and coupled by Hamilton’s principle. Based on the Rayleigh-Ritz method, the wing motion is described by the assumed bending and twisting modes to predict plunging and pitching motions. The fluid effects considered are added mass and quasi-static aerodynamic forces. A vortex lattice code is used to obtain aerodynamic coefficients for the wing. The body-wing and the wing-fluid interactions are accounted for in the model. Gliding flapping flight simulations with initial velocity and height are conducted. Contribution of active flapping are found by comparison to flight with non-flapping compliant wings.
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Katibeh, Mohammad, i Onur Bilgen. "Parametric Analysis of Structural Properties of a Rectangular Partially-Clamped Wing". W ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2212.
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Abstract The so-called solid-state ornithopter concept seeks to employ piezoelectric materials to generate flapping motion instead of relying on conventional mechanisms and multi-component actuation systems. The motion can be induced on a wing-like partially-clamped composite substrate with a piezocomposite device (i.e. the Macro-Fiber Composite actuator.) In this research, a design for a flapping wing is proposed based on the analysis of critical system parameters such as geometric properties and boundary conditions. A series of finite element simulations are conducted based on the variation of those parameters. Consequently, the effects of parameters on the structural response is studied. Also, modal analysis is done to examine the effects of geometric parameters on the resonant frequencies of the system. Heaving and pitching responses are examined.
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Yang, Shibin, i Stefan Seelecke. "FE Analysis of SMA-Based Bio-Inspired Bone-Joint System". W ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-627.
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The application of shape memory alloys (SMA) as actuators in a smart structure is a quickly developing field. The particular focus of this paper is on the aspects of modeling and simulation of a bio-inspired bone-joint system using the finite element method (FEM). The actuation of a typical bat’s humerus-radius system is effected by means of micro-scale actuator wires performing like metal muscles when heated. In addition, the elbow is modeled as a flexible hinge using superelastic SMA wires. This system serves as a first step towards the design of a flapping wing to propel the next generation Micro Aerial Vehicle (MAV). In this bio-inspired bone-joint-system, the humerus and radius were modeled as standard elastic beams. Shape memory alloys were employed in two different ways: one is an SMA wire in the martensite phase, the other is an SMA beam in the austenite phase. The SMA wires work as muscles to actuate the bio-system due to contraction upon electric heating. The SMA beams work as flexible joints due to their superelastic character. In this work, the modeling and simulation of the adaptive structure was implemented in COMSOL Multiphysics. The active material model used is based on the Muller-Achenbach-Seelecke shape memory alloy model. The paper has a particular focus on the implementation of the SMA model into COMSOL combining general PDE modes with structural mechanics truss and beam elements. COMSOL has been chosen because of its natural way of handling multi-physics situations such as the thermomechanical coupling relevant for the SMA application.