Дисертації з теми "Insect Flapping"
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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.
Повний текст джерелаAbdul, Hamid Mohd Faisal. "Aerodynamic models for insect flight." Thesis, University of Manchester, 2016. https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html.
Повний текст джерелаWhitney, John Peter. "Design and Performance of Insect-Scale Flapping-Wing Vehicles." Thesis, Harvard University, 2012. http://dissertations.umi.com/gsas.harvard:10374.
Повний текст джерелаEngineering and Applied Sciences
Ma, Kevin Yuan. "Mechanical design and manufacturing of an insect-scale flapping-wing robot." Thesis, Harvard University, 2015. http://nrs.harvard.edu/urn-3:HUL.InstRepos:23845433.
Повний текст джерелаEngineering and Applied Sciences - Engineering Sciences
Phillips, N. "Experimental unsteady aerodynamics relevant to insect-inspired flapping-wing micro air vehicles." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/5824.
Повний текст джерелаConn, 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.
Повний текст джерелаWilkins, P. C. "Some unsteady aerodynamics relevant to insect-inspired flapping-wing micro air vehicles." Thesis, Cranfield University, 2008. http://hdl.handle.net/1826/2913.
Повний текст джерелаGami, A. "Experimental and computational analysis for insect inspired flapping wing micro air vehicles." Thesis, City, University of London, 2016. http://openaccess.city.ac.uk/17454/.
Повний текст джерелаPedersen, C. B. "An indicial-polhamus model of aerodynamics of insect-like flapping wings in hover." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/6456.
Повний текст джерелаTeoh, Zhi Ern. "Design of Hybrid Passive and Active Mechanisms for Control of Insect-Scale Flapping-Wing Robots." Thesis, Harvard University, 2015. http://nrs.harvard.edu/urn-3:HUL.InstRepos:23845481.
Повний текст джерелаEngineering and Applied Sciences - Engineering Sciences
Timmerman, Kathleen M. "A Hardware Compact Genetic Algorithm for Hover Improvement in an Insect-Scale Flapping-Wing Micro Air Vehicle." Wright State University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=wright1347296530.
Повний текст джерелаLundberg, Marcus. "Aerodynamics of Insect Flight : Effects of wind gusts on a rigid flapping NACA 0012 airfoil at Re = 3000." Thesis, KTH, Mekanik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-167123.
Повний текст джерелаInsekter och andra små flygande djur flyger vid låga Reynolds tal som sträcker sig från cirka 10-100 000. Det medför att viskösa krafter är viktiga. På grund av sin ringa storlek och vikt är de känsliga för små förändringar i den friströmmen under flygningen, till exempel vindbyar. Först förklaras teorin bakom aerodynamiken vid flaxande flygning. Sedan simuleras lyftkraft, dragkraft och effektförbrukning för en flaxande NACA 0012 vingprofil vid olika riktningar på friströmmen med hjälp av ANSYS Fluent. Syftet med rapporten är att förstå hur pitching-amplitud, vingslagsfrekvens och vingslagsamplitud kan justeras för att kompensera för inkommande vindbyar. Simuleringen modelleras som kvasistatisk eftersom tidsskalan hos insekters flaxande vingar normalt är mycket kortare än tidsskalan hos vindbyar.
Ansari, Salman Ahmad. "A nonlinear, unsteady aerodynamic model for insect-like flapping wings in the hover with micro air vehicle applications." Thesis, Cranfield University, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.441548.
Повний текст джерелаFeaster, Jeffrey Oden. "Discovering the Complex Aerodynamics of Flapping Flight with Bio-kinematics Using Boltzmann and Eulerian Methods." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/93962.
Повний текст джерелаPHD
Frank, Spencer. "Vortex tilting and the enhancement of spanwise flow in flapping wing flight." Honors in the Major Thesis, University of Central Florida, 2011. http://digital.library.ucf.edu/cdm/ref/collection/ETH/id/384.
Повний текст джерелаB.S.
Bachelors
Mechanical, Materials, and Aerospace Engineering
Engineering and Computer Science
Alford, Lionel Devon Jr. "Aerodynamic Analysis of Natural Flapping Flight Using a Lift Model Based on Spanwise Flow." University of Dayton / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1272639883.
Повний текст джерелаKarasek, 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.
Повний текст джерелаThe 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
Gaston, Zachary Robert. "Computational Investigation of a Hinge-connected Hovering Plate." Wright State University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=wright1344991071.
Повний текст джерелаMoses, Kenneth C. "Biomimicry of the Hawk Moth, Manduca sexta (L.): Forewing and Thorax Emulation for Flapping-Wing Micro Aerial Vehicle Development." Case Western Reserve University School of Graduate Studies / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=case158687503705972.
Повний текст джерелаSwanson, Taylor Alexander. "An experimental and numerical investigation of flapping and plunging wings." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2009. http://scholarsmine.mst.edu/thesis/pdf/Swanson_09007dcc80672efe.pdf.
Повний текст джерелаVita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed June 2, 2009) Includes bibliographical references (p. 115-126).
Khan, Zaeem. "Modeling, optimal kinematics, and flight control of bio-inspired flapping wing micro air vehicles." Access to citation, abstract and download form provided by ProQuest Information and Learning Company; downloadable PDF file, 209 p, 2009. http://proquest.umi.com/pqdweb?did=1885675181&sid=1&Fmt=2&clientId=8331&RQT=309&VName=PQD.
Повний текст джерелаDoan, Le Anh. "Du micro véhicule aérien au nano véhicule aérien : études théoriques et expérimentales sur un insecte artificiel à ailes battantes." Thesis, Valenciennes, 2019. http://www.theses.fr/2019VALE0004/document.
Повний текст джерелаIn recent decades, the prospect of exploiting the exceptional flying capacities of insects has prompted much research on the elaboration of flapping-wing nano air vehicles (FWNAV). However, when designing such a prototype, designers have to wade through a vast array of design solutions that reflects the wide variety of flying insects to identify the correct combination of parameters to meet their requirements. To alleviate this burden, the purpose of this work is to develop a suitable tool to analyze the kinematic and power behavior of a resonant flexible-wing nano air vehicle. The key issue is evaluating its efficiency. However, this ultimate objective is extremely challenging as it is applied to the smallest flexible FWNAV. However, in this work, we worked first with a flapping-wing micro air vehicle (FWMAV) in order to have a tool for the simulation and experimentation of wing actuation, take-off and hovering. Some of the knowledge and experience acquired will then be transferred to better understand how our FWNAV works and identify the energy, power distribution. Although both of the vehicles employ the insect wing kinematics, their wings actuation mechanisms are not the same due to their sizes difference. Since the FWNAV is smaller, their wings flap at a higher frequency than the FWMAV as inspired by nature. As a consequence, from MAV to NAV, the wing actuation mechanism must be changed. Throughout this work, it can be seen clearly that this difference affects the whole vehicles development including the design, the manufacturing method, the modeling approach and the optimizing process. It has been demonstrated that the simulations are in good correlation with the experimental tests. The main result of this work is the proper wing kinematics of both FWMAV and FWNAV which leads to a lift to the weight ratio bigger and equal to one respectively. The FWMAV is even success to take-off and vertically stable hover. Moreover, taking advantage of the Bond Graph-based models, the evolution power according to the wing dynamic and the efficiency of the subsystem can be evaluated. In conclusion, this study shows the key parameters for designing and optimizing efficiency and the lift generated for two flapping wing vehicles in different size regimes
Faux, Damien. "Couplage modal pour la reproduction de la cinématique d'une aile d'insecte et la génération de portance d'un nano-drone bio-inspiré." Thesis, Valenciennes, 2018. http://www.theses.fr/2018VALE0007/document.
Повний текст джерелаThis work in the Nano-Air Vehicle field aims to design a small flying object directly inspired by the nature. For this purpose, a state of the art has been performed on insects flight mecanisms and has reviewed the overall artificial flapping wings solutions developped until today. The result of this analysis is on one hand, that insects use a specific wing kinematics which relies on a flapping motion and a twisting motion coupled in a quadrature phase shift and on the other hand, that the existing Nano-Air Vehicles do not exploit the dynamic behavior of their artificial wings to produce lift. The proposed concept in this research is a departure from those other works. It consists of a vibratory coupling in a quadrature phase shift of a flapping and a twisting mode applied on flexible artificial wings in order to reproduce a kinematics close to the insects ones with a single actuator. The used methodology resulted in the development of an analytic modeling which neglects the aerodynamic forces to calculate the dynamic behavior and dimension the prototype structure. Simulations highlighted the existence of eigen modes of the wings structure whose modal shapes match with the wanted flapping and twisting motion. Noteworthy fact, an optimization allowed to get those modes close in frequency while keeping a non-neglectible amplitude in such a way as to couple them and obtain the expected kinematics. The produced lift force is then estimated with an aeroelastic modeling which has shown that the maximum lift is obtained for two frequencies which provide a quadrature phase shift between the two modes. Those results are then validated by experimental measurements performed on a specific bench made according to the constraints due to the prototype in terms of sensitivity and dynamic behavior. The different generations of prototypes tested are produced with microfabrication process, allowing to integrate a wing membrane in parylene with a thickness comparable to the one existing in insects. The conclusion of this study is that we now have a prototype able to compensate its weight
Vanneste, Thomas. "Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant." Thesis, Valenciennes, 2013. http://www.theses.fr/2013VALE0021/document.
Повний текст джерелаDeveloping insect-like flapping-wing drones from scratch is an ambitious and arduous task for designers due to a lack of well-established know-how. To speed up the development of such vehicles through the preliminary design stage, a framework modeling the aeroelastic phenomena encountered in insect flight is an asset and is the subject of this thesis. Its kernel is a FEM based structural solver coupled in a blade-element approach to a quasi-steady aerodynamic model of insect flight accounting for the wing flexibility, both in the spanwise and in the chordwise direction, and for its large displacement. The complete framework is devised so as to maintain the computation load low while being modular enough for a wide range of applications. To validate the overall aeroelastic framework, a two-steps process has been undertaken with in one hand numerical studies and in the other hand experimental ones acquired on a dedicated test bench. The framework computation agrees satisfactorily, capturing the damping due to the aerodynamic force, and thus paves the way for preliminary design applications of a flapping-wing vehicle. To exhibit the capabilities of the framework as a preliminary design tool, two applications on a resonant nano air vehicle are performed: the definition of an efficient actuation strategy and the search of an aerodynamic potentially interesting wing geometry by plugging the framework to a genetic algorithm. The results are coherent with the ones found in nature and are under implementation on the nano air vehicle
Bontemps, Alexandre. "Prototypage d'un objet volant mimant l'insecte." Thesis, Valenciennes, 2013. http://www.theses.fr/2013VALE0030/document.
Повний текст джерелаThis manuscript reports a work which aims to develop a tiny flying robots inspired by natural flyers. Our main objective is to devise a flying robot mimicking insects in terms of kinematics and scale using MEMS technologies in order to answer the scale challenges: the large-scale manufacturing and the system's small scale. The success this project faces different challenges such as aeroelastic aspects of wings and drone autonomy.In this work we propose the use of original concepts like resonance and passive torsion of the wings which are implemented on all-polymer prototypes obtained using a micromachining SU-8 photoresist process. In order to achieve a better efficiency of the prototype, each element of the energy transduction has been carefully examined and optimized. Especially, the actuation, the transmission and the wings in order to increase the lift. These improvements demonstrate experimentally that the prototype is able to produce a complex kinematic and compensate 75 % of its weight
Mukherjee, Sujoy. "Structural Modeling And Analysis Of Insect Scale Flapping Wing." Thesis, 2012. http://etd.iisc.ernet.in/handle/2005/2021.
Повний текст джерела(9754904), Jesse A. Roll. "Principles & Applications of Insect Flight." Thesis, 2020.
Знайти повний текст джерелаInsects are the most successful animal on the planet, undergoing evolutionary adaptions in size and the development of flight that have allowed access to vast ecological niches and enabled a means by which to both prey and escape predation. Possessing some of the fastest visual systems on the planet, powerful sets of flight muscles, and mechanosensors tuned to perceive complex environments in high-fidelity, they are capable of performing acrobatic maneuvers at speeds that far exceed that of any engineered system. In turn, stable flight requires the coordinated effort of these highly specialized flight systems while performing activities ranging from evasive flight maneuvers to long-distance seasonal migrations in the presence of adverse flow conditions. As a result, the exceptional flight performance of flying insects has inspired a new class of aerial robots expressly tailored to exploit the unique aerodynamic mechanisms inherent to flapping wings. Over the course of three research studies, I explore new actuation techniques to address limitations in power and scalability of current robot platforms, develop new analytical techniques to aid in the design of insect-inspired robot flapping wings, and investigate attributes of flapping wing aerodynamics that allow insects to overcome the difficulties associated with flight in turbulent flow conditions, in an effort to advance the science of animal locomotion.
Recent advancements in the study of insect flight have resulted in bio-inspired robots uniquely suited for the confined flight environments of low Reynolds number flow regimes. Whereas insects employ powerful sets of flight muscles working in conjunction with specialized steering muscles to flap their wings at high frequencies, robot platforms rely on limited sets of mechanically amplified piezoelectric actuators and DC motors mated with gear reductions or linkage systems to generate reciprocating wing motion. As a result, these robotic systems are typically underactuated - with wing rotation induced by inertial and aerodynamic loading - and limited in scale by the efficiency of their actuation method and the electronics required for autonomous flight (e.g., boost converters, microcontrollers, batteries, etc.). Thus, the development of novel actuation techniques addressing the need for scalability and use of low-power components would yield significant advancements to the field of bio-inspired robots. As such, a scalable low-power electromagnetic actuator configurable for a range of resonant frequencies was developed. From physics-based models capturing the principles of actuation, improvements to the electromagnetic coil shape and a reconfiguration of components were made to reduce weight and increases overall efficiency. Upon completion of a proof-of-concept prototype, multiple actuators were then integrated into a full-scale robot platform and validated through a series of free flight experiments. Design concepts and modeling techniques established by this study have since been used to develop subsequent platforms utilizing similar forms of actuation, advancing the state-of-art in bio-inspired robotics.
With the ability to make instantaneous changes in mid-flight orientation through subtle adjustments in angle-of-attack, the maneuverability of flying insects far exceeds that of any man-made aircraft. Yet, studies on insect flight have concluded that the rotation of insect wings is predominately passive. Coincidentally, bio-inspired flapping wing robots almost universally rely on passive rotational mechanisms to achieve desired angles-of-attack - a compromise between actuator mass and the controllable degrees-of-freedom that results in underactuated flight systems. For many platforms, the design of passive mechanisms regulating the rotational response of the wing is determined from either simulations of the wing dynamics or empirically derived data. While these approaches are able to predict the wing kinematics with surprising accuracy, they provide little insight into the effects that wing parameters have on the response or the aerodynamic forces produced. Yet, these models establish a means by which to both study insect flight physiology and explore new design principles for the development of bio-inspired robots. Using a recent model of the passively rotating insect wing aerodynamics, a novel design principle used to tune the compliance of bio-inspired robot wings is developed. Further, through the application of nonlinear analysis methods, parameters optimizing lift production in flapping wings is identified. Results from this analysis are then validated experimentally through tests preformed on miniature flapping wings with passive compliant hinges. This work provides new insight into the role passive rotational dynamics plays in insect flight and aids in the development future flapping wing robots.
Hang, Liang-Tong, and 杭亮同. "Numerical simulation of 3-D flapping-wing insect''s hovering flight under gust wind situations." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/13845357760457815015.
Повний текст джерела淡江大學
航空太空工程學系碩士班
102
Title of Thesis: Total pages: 76 Numerical simulation of 3-D flapping-wing insect''s hovering flight under gust wind situations Keywords: 3-D Flapping Wing, Dynamic Mesh, Gust, UDF Name of Institute: Graduate Institute of Aerospace Engineering, Tamkang University Graduate Date: June 2014 Degree Conferred: Master Name of Student: Liang-Tong Hang Advisor: Dr. Tung Wan 杭亮同 宛 同 博士 Abstract: With advance of science and technology, the development of aerospace technology progress fast. Flapping-wing is a popular and innovative topic. Based on Darwin''s theory of evolution; we can have a general interpretation of each biological behavior patterns are the results of optimization. So it is important to combines aerodynamics and Bionics. Many researchers put effort into study the unsteady aerodynamics and flapping flight but study in flapping-wing Affected by atmospheric environment is much less. Our research team has studied the impact of weather factors for a long time and extensive lots experience in the analysis of different climatic conditions. In this thesis, we will discuss effect of flapping wings for aerodynamics in different gust. Here we use the dynamic grid mechanism of commercial software ANSYS / FLUNET to simulate flapping-wings, edit UDF in C++ and combine Solver to analysis aerodynamic performance under gust. First, we finish the validation of 2-D elliptic flapping wing section with Wang, J. We build 3D model butterfly which species is Morpho peleides Butler by PRO-E. From the morphological data of Morpho peleides is measured by Dudley. We generate mesh by Gambit and ANSYS and use dynamic mesh mechanism of ANSYS / FLUNET to simulate the butterfly forward flight. According to Liang and Yang, we create two type of the gust function with single and multiple frequencies. We analysis the butterfly under different gust and different directions and find lift coefficient is sensitive for the gust from top and bottom. The mean value of lift coefficient can be increased more than tenfold compared with the case without wind effects. And since the assumptions we make, our results may occur tolerance in quantitative values but it is worth referencing in Qualitative physical interpretation. If possible, consider the pitching oscillation of body and the flapping-wing with flexible in the future will improve accuracy of the results.
Cheng, Yuan-Tai, and 鄭元泰. "On the simulation of 3-D flapping-wing insect''s flight performance under abnormal atmospheric conditions." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/79824649727494952987.
Повний текст джерела淡江大學
航空太空工程學系碩士班
102
In recent years, flapping wing technology is becoming more popular, and Micro Air Vehicle (MAV) has received great attention from researchers. For most people their desired MAV performance is limited in the flapping mode of small birds and insects under clear weather situation. But in past years Taiwan has experienced many disasters caused by detrimental and severe weather, such as extremely heavy rain and very thick fog. In such cases if MAV could put into use to help the rescue mission, it could significantly improve the efficiency of rescue. However, the insect-like MAV is very small and light, and it''s very sensitive to sudden change of atmospheric surroundings. Therefore, maintain the flapping wing MAV flight quality in extreme weather will be an important issue. In this study, we constructed a geometric model of the butterfly based on a true Morpho peleides and created a grid system by GAMBIT and ANSYS preprocessing software, then use the CFD software FLUENT combine with the User Define Function (UDF) to analyze the relationship between the flow field and other aerodynamic phenomenon. For our simulation, we programing a grid convergence process first to verify the simulation of our 3-D butterfly flapping motion, and the flapping-wing aerodynamic parameters such as lift coefficient and drag coefficient are almost same with four grid systems in clam atmospheric condition. According to several cases, we can find some result. When the butterfly increases the pitch angle of flapping motion in forward flight, the lift coefficient will increase too. Then the trend of the lift coefficient curve will more approximate with the lift coefficient of the true butterfly in forward flight. In our abnormal atmospheric cases, we used the Discrete Particles Model (DPM) in FLUENT to simulate the 3-D butterfly flapping motion in heavy rain condition. In our result, the average values of lift coefficient under the heavy rain condition are lower than the case in normal atmospheric condition. When the liquid water content (LWC) is 25 g/m3, the reduction rate of lift coefficient would be reduced to 60.389% from 618.6% with the rising angle of attack. In the situation of the liquid water content is 39 g/m3, the reduction rate of lift coefficient will decrease from 1057% to 101.537% with the gradual increase in the angle of attack. Therefore, the effect of the heavy rain can be relieved by changing the angle of attack in forward flight, and the higher angle of attack can relieve more impact of heavy rain.