Relevant bibliographies by topics / Flapping mechanism

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Flapping mechanism'

Author: Grafiati
Published: 4 June 2021
Last updated: 12 February 2022

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Journal articles on the topic "Flapping mechanism"

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Yang, Wen Qing, Bi Feng Song, Wen Ping Song, Zhan Ke Li, and Ya Feng Zhang. "Aerodynamic Mechanism Research of Flapping Flight." Advanced Materials Research 354-355 (October 2011): 674–78. http://dx.doi.org/10.4028/www.scientific.net/amr.354-355.674.

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Lift makes a vehicle in air and thrust makes advancing. The lift of flapping wing air vehicle is composed of two main parts, flapping lift and advancing lift. The advancing lift of flapping-wing is similar as of fixed-wing, generated mainly by relative velocity and angle of attack. The flapping lift is owned only by flapping wing. The flapping lift is generated by asymmetry flapping motion manner of wings, asymmetry airfoil, and asymmetry folding in flapping cycle, accordingly leading-edge vortex and wake capture effect. The thrust is completely generated by flapping wing and the magnitude of thrust is mainly controlled by flapping frequency and flapping manner. The flapping motion is a thrust generator and lift enhancing manner. Flapping wing air vehicle will be one of the star members of man-made air vehicles.
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Zhang, Yangkun, Yuxin Peng, Yang Cheng, and Haoyong Yu. "A novel piezo-actuated flapping mechanism based on inertia drive." Journal of Intelligent Material Systems and Structures 31, no. 15 (June 29, 2020): 1782–92. http://dx.doi.org/10.1177/1045389x20935624.

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In this article, a novel piezo-actuated flapping mechanism based on inertia drive is proposed and developed. In comparison with the existing flapping mechanisms, the proposed one has a more direct driving form simply via a frictional contact without using any transmission mechanism like crank-rocker or crank-slider, making it easier for miniaturization. In addition, it could principally allow for an arbitrary form of flapping motion with unlimited stroke. The flapping principle and the rationale for an arbitrary form of flapping motion with unlimited stroke are presented. A prototype of the proposed flapping mechanism was constructed and tested. The ability in various modulations of flapping motion, including flapping amplitude, position, asymmetry between downstroke and upstroke flapping speeds, and frequency, is demonstrated.
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Gong, DuHyun, DaWoon Lee, SangJoon Shin, and SangYong Kim. "String-based flapping mechanism and modularized trailing edge control system for insect-type FWMAV." International Journal of Micro Air Vehicles 11 (January 2019): 175682931984254. http://dx.doi.org/10.1177/1756829319842547.

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This paper presents the design process and experimental results of a brand new flapping and trailing edge control mechanism for a flapping wing micro air vehicle. The flapping mechanism, whose main components are fabricated from string, is suggested and optimized further by a modified pattern search method. The trailing edge control mechanisms for pitching and rolling moments are designed to be attached onto the present flapping mechanism in a modularized fashion. Prototypes of both mechanisms are fabricated and experimentally tested in order to examine the feasibility of the designs. It is expected that the present flapping mechanism will generate enough lift for the total weight of the vehicle. The present control mechanism is found to be able to supply sufficient control moment.
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Hassanalian, Mostafa, and Abdessattar Abdelkefi. "Towards Improved Hybrid Actuation Mechanisms for Flapping Wing Micro Air Vehicles: Analytical and Experimental Investigations." Drones 3, no. 3 (September 13, 2019): 73. http://dx.doi.org/10.3390/drones3030073.

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A new strategy is proposed in order to effectively design the components of actuation mechanisms for flapping wing micro air vehicles. To this end, the merits and drawbacks of some existing types of conventional flapping actuation mechanisms are first discussed qualitatively. Second, the relationships between the design of flapping wing actuation mechanism and the entrance requirements including the upstroke and downstroke angles and flapping frequency are determined. The effects of the components of the actuation mechanism on the kinematic and kinetic parameters are investigated. It is shown that there are optimum values for different parameters in order to design an efficient mechanism. Considering the optimized features for an actuation mechanism, the design, analysis, and fabrication of a new hybrid actuation mechanism for FWMAV named “Thunder I” with fourteen components consisting of two six-bar mechanisms are performed. The results show that this designed hybrid actuation mechanism has high symmetrical flapping motion with hinged connections for all components. The proposed methodology for the modeling and fabrication of Thunder I’s actuation mechanism can be utilized as guidelines to design efficient FWMAVs actuation mechanisms.
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Conn, A. T., S. C. Burgess, and C. S. Ling. "Design of a parallel crank-rocker flapping mechanism for insect-inspired micro air vehicles." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 221, no. 10 (September 30, 2007): 1211–22. http://dx.doi.org/10.1243/09544062jmes517.

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In the current paper, a novel micro air vehicle (MAV) flapping mechanism for replicating insect wing kinematics is presented. Insects flap their wings in a complex motion that enables them to generate several unsteady aerodynamic mechanisms, which are extremely beneficial for lift production. A flapping wing MAV that can reproduce these aerodynamic mechanisms in a controlled manner is likely to outperform alternative flight platforms such as rotary wing MAVs. A biomimetic design approach was undertaken to develop a novel flapping mechanism, the parallel crank-rocker (PCR). Unlike several existing flapping mechanisms (which are compared using an original classification method), the PCR mechanism has an integrated flapping and pitching output motion which is not constrained. This allows the wing angle of attack, a key kinematic parameter, to be adjusted and enables the MAV to enact manoeuvres and have flight stability. Testing of a near-MAV scale PCR prototype using a high-speed camera showed that the flapping angle and adjustable angle of attack both closely matched predicted values, proving the mechanism can replicate insect wing kinematics. A mean lift force of 3.35 g was measured with the prototype in a hovering orientation and flapping at 7.15 Hz.
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Hsu, Meng Hui, Hsueh Yu Chen, Ting Sheng Weng, and Feng Chi Liu. "Topology Structure Design of 12 Flapping-Wing Mechanisms." Advanced Materials Research 328-330 (September 2011): 887–91. http://dx.doi.org/10.4028/www.scientific.net/amr.328-330.887.

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People used the Micro Air Vehicles to patrol the military activity or explore the danger region.The important parts of Micro Air Vehicles are the flapping-wing mechanisms those can simulate the wing-motion of flying being.Hence this work is to present a systematic approach for designing new flapping-wing mechanisms with one degree of freedom that can simulate the wing-motion of long ear bats and insects.First,we analyze the topological structure and motion characteristics of existed flapping mechanisms.Then, the design criteria of the topological structure are described.Based on the design criteria of topology, the methodology of mechanism design is applied to synthesize new flapping-wing mechanisms. Finally, this research of the provide method can obtain 12 new flapping -wing mechanisms and one prototype of a flying insect mechanism.
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Zhai, Hai Zhou. "The Design of New Mechanism of Birdlike MAV." Applied Mechanics and Materials 229-231 (November 2012): 470–73. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.470.

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MAV- Micro Air Vehicle which acts like bird has attracted many studies because of outstanding aerodynamic property. Former studies on birdlike MAV with flapping wing had just focused on the flapping motion, but passed over the change of flapping angular velocity and deformation of wing, therefore lost the good aerodynamic capacity. One new mechanism of the birdlike MAV is designed and studied. The mechanism can bring out 3 motions at one time, including flapping, spanning and twisting, so has movement as bird. The kinematic performance including the flapping angle, flapping angular velocity, and the folding angle etc., has been studied and compared with other relative works. The design can help the birdlike aircraft into reality.
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Zhou, Chaoying, Rui Zhang, and Chao Wang. "Flap–control mechanism for flapping-wing micro air vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (January 16, 2018): 1537–45. http://dx.doi.org/10.1177/0954410017752708.

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Flapping-wing micro air vehicles controlled by tail are poor in stability and maneuverability. A crank-slider and double-pendulum control mechanism which integrates flap and control and provides a good maneuverability by breaking the symmetry between the flapping motions of two lateral wings is proposed for the design of flapping-wing micro air vehicles. The kinematics of this mechanism is analyzed and the effects of flapping angles, flapping amplitudes, and the differences between the flapping angles of two lateral wings on the maneuverability are discussed. The results indicate that flapping angle differences between two lateral wings generated by breaking the symmetry play the most important role in providing good maneuverability. The maneuverability of turning is obtained by moving the pivots of the flapping bars in the system and a servo-gear-rack device is used to realize the movement. The proposed novel flap–control mechanism is compact and easy to control.
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Hou, Yu, and Fang Wang. "CPG-Based Movement Control for Bionic Flapping-Wing Mechanism." Applied Mechanics and Materials 226-228 (November 2012): 844–49. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.844.

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Flapping-wing flying is a kind of rhythmic movement with symmetry of time and space essentially, and this movement is generated and controlled by Central Pattern Generator (CPG). A 2-DOF flapping mechanism was designed according to the flapping-wing flying principle of insects, and the flapping-wing flying CPG model was constructed by nonlinear oscillators. The system responses were studied, and the influences of the model parameters to the system characteristics were analyzed. Through the engineering simulation of flapping-wing flying control model, the first modal vibration of the system was selected, and the different flying modes of bionic aircraft were realized by adjusting system parameters. This kind of bionic control strategy promoted the movement and control ability of flapping-wing flying, and provided a new method to the generation and control of flapping-wing rhythmic movement.
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Liu, Yun, Zhi Sheng Jing, Shan Chao Tu, Ming Hao Yu, and Guo Wei Qin. "Character Measurement of Flapping-Wing Mechanism." Applied Mechanics and Materials 48-49 (February 2011): 300–303. http://dx.doi.org/10.4028/www.scientific.net/amm.48-49.300.

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The characteristics and the application prospect are analyzed. It is concluded that bionic flapping-wing flying has better lift fore generation efficiency, which is the development trend of aerial vehicles. By the scaling effect analysis on bionic flying mechanism, it is presented that bionic flying could be realized more easily when the sizes are decreased. In this article, the flying mechanism of inset and Aves was studied and the high lift force mechanism of flapping-winging was concluded. In order to make the flapping-flying easier, we design a new type flapping-flying mechanism. A set of flapping-wing move comparatively. It can provide lift force all the time. We test the lift force in the condition of different speed and different frequency. The lift effect is validated on a simple suspend flight device. An experimental platform to measure the aerodynamic force is devised and developed by ourselves. On this equipment, the aerodynamics force of the prototype is test. The result is that enhancing speed or frequency can improve lift force in evidence
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Dissertations / Theses on the topic "Flapping mechanism"

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George, Ryan Brandon. "Design and Analysis of a Flapping Wing Mechanism for Optimization." BYU ScholarsArchive, 2011. https://scholarsarchive.byu.edu/etd/2737.

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Furthering our understanding of the physics of flapping flight has the potential to benefit the field of micro air vehicles. Advancements in micro air vehicles can benefit applications such as surveillance, reconnaissance, and search and rescue. In this research, flapping kinematics of a ladybug was explored using a direct linear transformation. A flapping mechanism design is presented that was capable of executing ladybug or other species-specific kinematics. The mechanism was based on a differential gear design, had two wings, and could flap in harsh environments. This mechanism served as a test bed for force analysis and optimization studies. The first study was based on a Box-Behnken screening design to explore wing kinematic parameter design space and manually search in the direction of flapping kinematics that optimized the objective of maximum combined lift and thrust. The second study used a Box-Behnken screening design to build a response surface. Using gradient-based techniques, this surface was optimized for maximum combined lift and thrust. Box-Behnken design coupled with response surface methodology was an efficient method for exploring the mechanism force response. Both methods for optimization were capable of successfully improving lift and thrust force outputs. The incorporation of the results of these studies will aid in the design of more efficient micro air vehicles and with the ultimate goal of leading to a better understanding of flapping wing aerodynamics and the development of aerodynamic models.
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Naegle, Nathaniel Stephen. "Force Optimization and Flow Field Characterization from a Flapping Wing Mechanism." BYU ScholarsArchive, 2012. https://scholarsarchive.byu.edu/etd/3278.

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Flapping flight shows promise for micro air vehicle design because flapping wings provide superior aerodynamic performance than that of fixed wings and rotors at low Reynolds numbers. In these flight regimes, unsteady effects become increasingly important. This thesis explores some of the unsteady effects that provide additional lift to flapping wings through an experiment-based optimization of the kinematics of a flapping wing mechanism in a water tunnel. The mechanism wings and flow environment were scaled to simulate the flight of the hawkmoth (Manduca sexta) at hovering or near-hovering speeds. The optimization was repeated using rigid and flexible wings to evaluate the impact that wing flexibility has on aerodynamic performance of flapping wings. The trajectories that produced the highest lift were compared using particle image velocimetry to characterize the flow features produced during the periods of peak lift. A leading edge vortex was observed with all of the flapping trajectories and both wing types, the strength of which corresponded to the measured amount of lift of the wing. This research furthers our understanding of the lift-generating mechanisms used in nature and can be applied to improve the design of micro air vehicles.
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Conn, Andrew T. "Development of novel flapping mechanism technologies for insect-inspired micro air vehicles." Thesis, University of Bristol, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492441.

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Insect-inspired micro air vehicles (MAVs) have the capacity for higher lift forces and greater manoeuvrability at low flight speeds compared to conventional flight platforms, making them suitable for novel indoor flight applications. This thesis presents development studies of an actuated flapping mechanism for an insect-inspired MAV. An original theoretical understanding has shown that the kinematical constraint of a flapping mechanism fundamentally determines its complexity and performance. An under-constrained mechanism is optimal but almost always requires a linear input. A power optimisation study has demonstrated that the only technologically mature actuation devices with viable power densities for flight are rotary. Consequently, previous airborne flapping MAVs utilised constrained rotary-input mechanisms which require conventional control surfaces that significantly reduce flight manoeuvrability.
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DiLeo, Christopher. "Development of a tandem-wing flapping micro aerial vehicle prototype and experimental mechanism." Access to citation, abstract and download form provided by ProQuest Information and Learning Company; downloadable PDF file, 154 p, 2007. http://proquest.umi.com/pqdweb?did=1421622011&sid=3&Fmt=2&clientId=8331&RQT=309&VName=PQD.

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Kummari, Kranti Kiran Lal. "The development of piezoelectric actuated mechanism for flapping wing micro aerial vehicle application." Thesis, Cranfield University, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.515094.

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Jadhav, Gautam. "The Development of a Miniature Flexible Flapping Wing Mechanism for use in a Robotic Air Vehicle." Thesis, Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14594.

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In this study a mechanism which produced flapping and pitching motions was designed and fabricated. These motions were produced by using a single electric motor and by exploiting flexible structures. The aerodynamic forces generated by flexible membrane wings were measured using a two degree of freedom force balance. This force balance measured the aerodynamic forces of lift and thrust. Two sets of wings with varying flexibility were made. Lift and thrust measurements were acquired as the mechanism flapped the wings in a total of thirteen cases. These thirteen cases consisted of zero velocity free stream conditions as well as forward flight conditions of five meters per second. In addition, flapping frequency was varied from two Hertz to four Hertz, while angle of attack offsets varied from zero degrees to fifteen degrees. The four most interesting conditions for both sets of wings were explored in more detail. For each of these conditions, high-speed video of the flapping wing was taken. The images from the video were also correlated with cycle averaged aerodynamic forces produced by the mechanism. Several observations were made regarding the behavior of flexible flapping wings that should aid in the design of future flexible flapping wing vehicles.
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Fader, John. "Study of a novel, four degree-of-freedom spatial flapping mechanism for air vehicles." Access to citation, abstract and download form provided by ProQuest Information and Learning Company; downloadable PDF file, 91 p, 2009. http://proquest.umi.com/pqdweb?did=1654487461&sid=3&Fmt=2&clientId=8331&RQT=309&VName=PQD.

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Karasek, Matej. "Robotic hummingbird: design of a control mechanism for a hovering flapping wing micro air vehicle." Doctoral thesis, Universite Libre de Bruxelles, 2014. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209177.

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The use of drones, also called unmanned aerial vehicles (UAVs), is increasing every day. These aircraft are piloted either remotely by a human pilot or completely autonomously by an on-board computer. UAVs are typically equipped with a video camera providing a live video feed to the operator. While they were originally developed mainly for military purposes, many civil applications start to emerge as they become more affordable.

Micro air vehicles are a subgroup of UAVs with a size and weight limitation; many are designed also for indoor use. Designs with rotary wings are generally preferred over fixed wings as they can take off vertically and operate at low speeds or even hover. At small scales, designs with flapping wings are being explored to try to mimic the exceptional flight capabilities of birds and insects.

The objective of this thesis is to develop a control mechanism for a robotic hummingbird, a bio-inspired tail-less hovering flapping wing MAV. The mechanism should generate moments necessary for flight stabilization and steering by an independent control of flapping motion of each wing.

The theoretical part of this work uses a quasi-steady modelling approach to approximate the flapping wing aerodynamics. The model is linearised and further reduced to study the flight stability near hovering, identify the wing motion parameters suitable for control and finally design a flight controller. Validity of this approach is demonstrated by simulations with the original, non-linear mathematical model.

A robotic hummingbird prototype is developed in the second, practical part. Details are given on the flapping linkage mechanism and wing design, together with tests performed on a custom built force balance and with a high speed camera. Finally, two possible control mechanisms are proposed: the first one is based on wing twist modulation via wing root bars flexing; the second modulates the flapping amplitude and offset via flapping mechanism joint displacements. The performance of the control mechanism prototypes is demonstrated experimentally.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished

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Ryan, Mark. "Design Optimization and Classification of Compliant Mechanisms for Flapping Wing Micro Air Vehicles." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1345403446.

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Liu, Teresa (Teresa H. ). "Design of a flapping mechanism for reproducing the motions at the base of a dragonfly wing." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/40456.

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Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2007.
Includes bibliographical references (p. 48-49).
Insect flight is being studied to aid in the development of micro-air vehicles that use the flapping wing model in an attempt to achieve the high levels of maneuverability that insects have. The flight of the dragonfly has been chosen to be modeled because of its exceptional flight capabilities. This thesis addresses the flapping mechanism designed for the root of each wing. The prototype of the mechanism, built at a scale of four times the size of a dragonfly having a wingspan of 150 mm, is able to create motions in the wing of flapping and feathering, and can vary the stroke plane. The coning angle can be set between tests. The design process began with considering two methods of actuation, a four-bar transmission mechanism used in the Micromechanical Flying Insect developed in the UC Berkeley Biomimetic Millisystem Lab, and by pivoting the wing support directly with cables or rigid links. The second design was chosen to be developed further. A functional prototype was built from acrylic and parts made using stereolithography.
by Teresa Liu.
S.B.
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Books on the topic "Flapping mechanism"

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Berry, John D. Flapping inertia for selected rotor blades. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

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Book chapters on the topic "Flapping mechanism"

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Yang, Lung-Jieh, and Balasubramanian Esakki. "Flapping Wing Mechanism Design." In Flapping Wing Vehicles, 77–130. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9780429280436-3.

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Liu, Lan, Zongde Fang, and Zhaoxia He. "Optimization Design of Flapping Mechanism and Wings for Flapping-Wing MAVs." In Intelligent Robotics and Applications, 245–55. Berlin, Heidelberg: Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-88513-9_27.

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Raste, Hrishikesh, Anupam Saxena, Roger Sauer, and Burkhard Corves. "Bioinspired Mechanism Synthesis for Flapping Flight with Unsteady Flow Effects." In Mechanisms, Transmissions and Applications, 251–60. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17067-1_26.

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Cheng, Huang, Liu Yuhong, Zhu Yaqiang, Cai Kelun, Zhang Hongwei, Wang Shuxin, and Wang Yanhui. "Mechanism Design and Kinematics Analysis of a Bio-Inspired Flexible Flapping Wing." In Advances in Mechanism and Machine Science, 209–18. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20131-9_21.

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Nian, Peng, Bifeng Song, Wenqing Yang, and Shaoran Liang. "Integrated Design and Analysis of an Amplitude-Variable Flapping Mechanism for FMAV." In Intelligent Robotics and Applications, 576–88. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-65298-6_52.

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Moses, Kenneth C., Nathaniel I. Michaels, Joel Hauerwas, Mark Willis, and Roger D. Quinn. "An Insect-Scale Bioinspired Flapping-Wing-Mechanism for Micro Aerial Vehicle Development." In Biomimetic and Biohybrid Systems, 589–94. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-63537-8_54.

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Grand, Ch, P. Martinelli, J. B. Mouret, and S. Doncieux. "Flapping-Wing Mechanism for a Bird-Sized UAVs: Design, Modeling and Control." In Advances in Robot Kinematics: Analysis and Design, 127–34. Dordrecht: Springer Netherlands, 2008. http://dx.doi.org/10.1007/978-1-4020-8600-7_14.

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Li, Youpeng, Chen Qian, Bingqi Zhu, and Yongchun Fang. "Kinematic, Static and Dynamic Analyses of Flapping Wing Mechanism Based on ANSYS Workbench." In Neural Information Processing, 316–23. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-70136-3_34.

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Tewari, Ashish. "Flapping and Rotary Wing Flight." In Basic Flight Mechanics, 87–98. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_5.

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Espinosa Ramírez, Alejandro Camilo, and Anne Cros. "Wake Patterns Behind a Flapping Foil." In Experimental and Computational Fluid Mechanics, 341–47. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-00116-6_29.

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Conference papers on the topic "Flapping mechanism"

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Khan, Z., K. Steelman, and S. Agrawal. "Development of insect thorax based flapping mechanism." In 2009 IEEE International Conference on Robotics and Automation (ICRA). IEEE, 2009. http://dx.doi.org/10.1109/robot.2009.5152822.

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Ryan, Mark, and Hai-Jun Su. "Classification of Flapping Wing Mechanisms for Micro Air Vehicles." In 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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Kalpathy Venkiteswaran, Venkatasubramanian, and Haijun Su. "Optimization of mechanism design of flapping wing MAV." In 55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0573.

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Bryson, Dean, Terrence Weisshaar, Richard Snyder, and Philip Beran. "Aeroelastic Optimization of a Two-Dimensional Flapping Mechanism." In 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
18th AIAA/ASME/AHS Adaptive Structures Conference
12th. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-2961.

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House, Christopher, Jenelle Piepmeier, John Burkhardt, and Samara Firebaugh. "Analysis of flapping mechanism for acoustically actuated microrobotics." In 2014 Spring Symposium: From Lab to Life: Field Based Applications of MEMS & NEMS (MAMNA). IEEE, 2014. http://dx.doi.org/10.1109/mamna.2014.6845236.

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Ma, Nan, Xiaodong Zhou, Guangping He, and Jingjun Yu. "Design and Analysis of a Bat-Like Active Morphing Wing Mechanism." In ASME 2016 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/detc2016-59111.

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The flying style of bats has much difference with the birds and insects, which adopt the backward folding movement of the wing when up flapping. The wingspan is changed during the up and down flapping, which makes the effective flapping area difference and the net lift increase. Firstly, basing on the research of bats’ flapping style, the mechanism of active morphing wing is proposed, then the dimensional synthesis is carried out basing on the movement trajectory of bats’ wing, after that, the kinematic model is build and analyzed, and the analysis result is compared with the ADAMS software. The flapping and morphing of the wing is actuated by a single motor, which can increase the power coefficient of the system and realize the coupled flapping and folding motion of the wing at the same time. The folding and stretching of the wing is actuated by a cam installed on the axis of crank, then the space flapping trajectory of the wing can be planed by changing the cam contour and the installation phase, this mechanism provide a way to design the foldable flapping wing aerial vehicles (FWAV).
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Hailin, Huang, and Li Bing. "Geometric Design of a Bio-Inspired Flapping Wing Mechanism Based on Bennett-Derived 6R Deployable Mechanisms." In ASME 2014 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/detc2014-34741.

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In this paper, we present the concept of designing flapping wing air vehicle by using the deployable mechanisms. A novel deployable 6R mechanism, with the deploying/folding motion of which similar to the flapping motion of the vehicle, is first designed by adding two revolute joints in the adjacent two links of the deployable Bennett linkage. The mobility of this mechanism is analyzed based on a coplanar 2-twist screw system. An intuitive projective approach for the geometric design of the 6R deployable mechanism is proposed by projecting the joint axes on the deployed plane. Then the geometric parameters of the deployable mechanism can be determined. By using another 4R deployable Bennett connector, the two 6R deployable wing mechanisms can be connected together such that the whole flapping wing mechanism has a single degree of freedom (DOF).
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8

Bejgerowski, Wojciech, John W. Gerdes, Satyandra K. Gupta, Hugh A. Bruck, and Stephen Wilkerson. "Design and Fabrication of a Multi-Material Compliant Flapping Wing Drive Mechanism for Miniature Air Vehicles." In ASME 2010 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/detc2010-28519.

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Successful realization of a flapping wing micro air vehicle (MAV) requires development of a light weight drive mechanism converting the rotary motion of the motor into flapping motion of the wings. Low weight of the drive mechanism is required to maximize the payload and battery capacity. In order to make flapping wing MAVs attractive in search, rescue, and recovery missions, they should be disposable from the cost point of view. Injection molded compliant drive mechanisms are an attractive design option to satisfy the weight, efficiency and cost requirements. In the past, we have successfully used multi-piece molding to create mechanisms utilizing distributed compliance for smaller MAVs. However, as the size of the MAV increases, mechanisms with distributed compliance exhibit excessive deformation. Therefore localizing rather than distributing the compliance in the mechanism becomes a more attractive option. Local compliance can be realized through multimaterial designs. A multi-material injection molded mechanism additionally offers reduction in the number of parts. This paper describes an approach for determining the drive mechanism shape and size that meets both the functional design and multi-material molding requirements. The design generated by the approach described in this paper was utilized to realize a flapping wing MAV with significant enhancements in the payload capabilities.
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9

Khan, Zaeem A., and Sunil K. Agrawal. "Design and Optimization of a Biologically Inspired Flapping Mechanism for Flapping Wing Micro Air Vehicles." In 2007 IEEE International Conference on Robotics and Automation. IEEE, 2007. http://dx.doi.org/10.1109/robot.2007.363815.

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Rosly, Muhammad Aliff, Hanafiah Yussof, Muhammad Farid Shaari, Zahurin Samad, Dayana Kamaruzaman, and Abdul Rahman Omar. "Speed control mechanism for IPMC based biomimetic flapping thruster." In 2017 IEEE International Symposium on Robotics and Intelligent Sensors (IRIS). IEEE, 2017. http://dx.doi.org/10.1109/iris.2017.8250125.

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Reports on the topic "Flapping mechanism"

1

Wood, Robert J. PECASE: Soaring Mechanisms for Flapping-Wing Micro Air Vehicles. Fort Belvoir, VA: Defense Technical Information Center, March 2015. http://dx.doi.org/10.21236/ada621719.

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