scholarly journals A Miniature Flapping Mechanism Using an Origami-Based Spherical Six-Bar Pattern

2021 ◽  
Vol 11 (4) ◽  
pp. 1515
Author(s):  
Seung-Yong Bae ◽  
Je-Sung Koh ◽  
Gwang-Pil Jung
Keyword(s):  
Rotation Angle ◽  
Dc Motor ◽  
Flapping Wing ◽  
Linear Motion ◽  
Assembly Process ◽  
Reciprocating Motion ◽  
Successful Performance ◽  
Aerial Vehicles ◽  
Geometrically Constrained ◽  
Flapping Mechanism

In this paper, we suggest a novel transmission for the DC motor-based flapping-wing micro aerial vehicles (FWMAVs). Most DC motor-based FWMAVs employ linkage structures, such as a crank-rocker or a crank-slider, which are designed to transmit the motor’s rotating motion to the wing’s flapping motion. These transmitting linkages have shown successful performance; however, they entail the possibility of mechanical wear originating from the friction between relative moving components and require an onerous assembly process owing to several tiny components. To reduce the assembly process and wear problems, we present a geometrically constrained and origami-based spherical six-bar linkage. The origami-based fabrication method reduces the number of the relative moving components by replacing rigid links and pin joints with facets and folding joints, which shortens the assembly process and reduces friction between components. The constrained spherical six-bar linkage enables us to change the motor’s rotating motion to the linear reciprocating motion. Due to the property that every axis passes through a single central point, the motor’s rotating motion is filtered at the spherical linkage and does not transfer to the flapping wing. Only linear motion, therefore, is passed to the flapping wing. To show the feasibility of the idea, a prototype is fabricated and analyzed by measuring the flapping angle, the wing rotation angle and the thrust.

Bionic Flapping Mechanism of the Wings of a Cursorial Dinosaur Robot for Estimating Its Lift and Thrust

2020 ◽  
Vol 13 (1) ◽  
Author(s):  
Hong-Wei Song ◽  
Yaser Saffar Talori ◽  
Jing-Shan Zhao
Keyword(s):  
Dc Motor ◽  
Flapping Wing ◽  
Current Understanding ◽  
Close Relative ◽  
Avian Flight ◽  
Experimental Approaches ◽  
Ongoing Development ◽  
Twisting Angle ◽  
Thrust Forces ◽  
Flapping Mechanism

Abstract We estimated the lift and thrust of the proto-wings of the dinosaur Caudipteryx, a close relative of birds, using both theoretical and experimental approaches. Our experiments utilized a newly reconstructed flapping wing mechanism in accordance to the fossil specimens of Caudipteryx. To ensure that this reconstructed mechanism could adequately simulate the realistic flapping movements, we investigated the relationships among the flapping angle, twisting angle, and stretching angle of the wing mechanism that was driven by a DC motor. We also used two sensors to measure the lift and thrust forces generated by the flapping movements of the reconstructed wing. Our experiment indicated that both the lift and thrust forces produced by the wings were small but increased at higher flapping frequencies. This study not only contributes to current understanding of the origin of avian flight but also usefully informs the ongoing development of bionic flapping robots.

Conceptual Development of Flapping Wing for Unmanned Aerial Vehicles: Technical Note

2018 ◽  
Vol 10 (1) ◽  
Author(s):  
K. Dhamodaran ◽  
P. Prabhu Shankar ◽  
S. Gowtham
Keyword(s):  
High Resolution ◽  
High Altitude ◽  
Unmanned Aerial Vehicles ◽  
Conceptual Development ◽  
Technical Note ◽  
Flapping Wing ◽  
Laboratory Scale ◽  
Aerial Vehicles ◽  
Battery Consumption ◽  
Flapping Mechanism

From 1940s to till now the Un-manned aerial vehicles (UAVs) technology has been developed and the birds like UAVs are actively used for spying mission to attack enemies. For example, “Smart Bird” is discovered by FESTO in which the seagull is taken as a concept. The battery consumption is more on these UAVs due to their complicated flapping mechanism. This project deals with an UAV (ornithopter) with morphed wing, in which the wing can be foldable to increase the gliding speed. By using such type of wings, endurance and range can be increased. A laboratory scale ornithopter with flapping wing mechanism is fabricated and tested. The flight speed of almost 45mph can be achieved. This mechanism reduces the battery consumption, for e.g. for 8V input, 4 flaps per second is demonstrated by test. UAV has the ability to attack enemy territory without being identified by the RADAR. Moreover, it can be used to drop bombs from high altitude with precision by using high resolution cameras. To overcome this difficulty, the ornithopter with morphing and flapping mechanism concept is considered in this project.

scholarly journals Bioinspired Feathered Flapping Wing UAV Design for Operation in Gusty Environment

2021 ◽  
Vol 2021 ◽  
pp. 1-14
Author(s):  
S. H. Abbasi ◽  
A. Mahmood ◽  
Abdul Khaliq
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Flapping Wing ◽  
Recent Past ◽  
Biologically Inspired ◽  
Multibody Model ◽  
Graph Modeling ◽  
Aerial Vehicles ◽  
Bond Graph Modeling ◽  
Gust Mitigation ◽  
Flapping Mechanism

The flight of unmanned aerial vehicles (UAVs) has numerous associated challenges. Small size is the major reason of their sensitivity towards turbulence restraining them from stable flight. Turbulence alleviation strategies of birds have been explored in recent past in detail to sort out this issue. Besides using primary and secondary feathers, birds also utilize covert feathers deflection to mitigate turbulence. Motivated from covert feathers of birds, this paper presents biologically inspired gust mitigation system (GMS) for a flapping wing UAV (FUAV). GMS consists of electromechanical (EM) covert feathers that sense the incoming gust and mitigate it through deflection of these feathers. A multibody model of gust-mitigating FUAV is developed appending models of the subsystems including rigid body, propulsion system, flapping mechanism, and GMS-installed wings using bond graph modeling approach. FUAV without GMS and FUAV with the proposed GMS integrated in it are simulated in the presence of vertical gust, and results’ comparison proves the efficacy of the proposed design. Furthermore, agreement between experimental results and present results validates the accuracy of the proposed design and developed model.

scholarly journals Dove: A biomimetic flapping-wing micro air vehicle

2017 ◽  
Vol 10 (1) ◽  
pp. 70-84 ◽  
Author(s):  
Wenqing Yang ◽  
Liguang Wang ◽  
Bifeng Song
Keyword(s):  
Mechanism Design ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Flexible Wing ◽  
The Past ◽  
Ground Station ◽  
Air Vehicle ◽  
Research Goal ◽  
Color Video ◽  
Flapping Mechanism

This paper describes the design and development of the Dove, a flapping-wing micro air vehicle (FWMAV), which was developed in Northwestern Polytechnical University. FWMAVs have attracted international attentions since the past two decades. Since some achievements have been obtained, such as the capability of supporting an air vehicle to fly, our research goal was to design an FWMAV that has the ability to accomplish a task. Main investigations were presented in this paper, including the flexible wing design, the flapping mechanism design, and the on-board avionics development. The current Dove has a mass of 220 g, a wingspan of 50 cm, and the ability of operating fully autonomously, flying lasts half an hour, and transmitting live stabilized color video to a ground station over 4 km away.

Autonomous Loitering Control for a Flapping Wing Miniature Aerial Vehicle With Independent Wing Control

2014 ◽  
Author(s):  
Luke Roberts ◽  
Hugh A. Bruck ◽  
Satyandra K. Gupta
Keyword(s):  
Energy Efficient ◽  
Pid Controller ◽  
Control Algorithm ◽  
Flapping Wing ◽  
Flight Testing ◽  
Response Error ◽  
Aerial Vehicles ◽  
Aerial Vehicle

Flapping wing miniature aerial vehicles (FWMAVs) offer advantages over traditional fixed wing or quadrotor MAV platforms because they are more maneuverable than fixed wing aircraft and are more energy efficient than quadrotors, while being quieter than both. Currently, autonomy in FWMAVs has only been implemented in flapping vehicles without independent wing control, limiting their level of control. We have developed Robo Raven IV, a FWMAV platform with independently controllable wings and an actuated tail controlled by an onboard autopilot system. In this paper, we present the details of Robo Raven IV platform along with a control algorithm that uses a GPS, gyroscope, compass, and custom PID controller to autonomously loiter about a predefined point. We show through simulation that this system has the ability to loiter in a 50 meter radius around a predefined location through the manipulation of the wings and tail. A simulation of the algorithm using characterized GPS and tail response error via a PID controller is also developed. Flight testing of Robo Raven IV demonstrated the success of this platform, even in winds of up to 10 mph.

Recent progress in flapping wings for micro aerial vehicle applications

2020 ◽  
pp. 095440622091742
Author(s):  
Naeem Haider ◽  
Aamer Shahzad ◽  
Muhammad Nafees Mumtaz Qadri ◽  
Syed Irtiza Ali Shah
Keyword(s):  
Leading Edge ◽  
Flapping Wing ◽  
Flapping Wings ◽  
Structural Flexibility ◽  
Micro Aerial Vehicles ◽  
Flexible Wings ◽  
Performance Variables ◽  
Aerial Vehicles ◽  
Wide Range ◽  
Wing Geometry

Micro aerial vehicles using flapping wings are under investigation, as an alternative to fixed-wing and rotary-wing micro aerial vehicles. Such flapping-wing vehicles promise key potential advantages of high thrust, agility, and maneuverability, and have a wide range of applications. These applications include both military and commercial domains such as communication relay, search and rescue, visual reconnaissance, and field search. With the advancement in the computational sciences, developments in flapping-wing micro aerial vehicles have progressed exponentially. Such developments require a careful aerodynamic and aeroelastic design of the flapping wing. Therefore, aerodynamic tools are required to study such designs and configurations. In this paper, the role of several parameters is investigated, including the types of flapping wings, the effect of the kinematics and wing geometry (shape, configuration, and structural flexibility) on performance variables such as lift, drag, thrust, and efficiency in various modes of flight. Kinematic variables have a significant effect on the performance of the flapping wing. For instance, a high flap amplitude and pitch rotation, which supports the generation of the strong leading-edge vortex, generates higher thrust. Likewise, wing shape, configuration, and structural flexibility are shown to have a large impact on the performance of the flapping wing. The wing with optimum flexibility maximizes thrust where highly flexible wings lead to performance degradation due to change in the effective angle of attack. This study shows that the development of the flexible flapping wing with performance capabilities similar to those of natural fliers has not yet been achieved. Finally, opportunities for additional research in this field are recommended.

Design of a Foldable Flapping Mechanism

2013 ◽  
Vol 437 ◽  
pp. 366-372
Author(s):  
Xiao Zhou Fan ◽  
Zhi Lin Zhang ◽  
Liang Chen
Keyword(s):  
Lift Force ◽  
Virtual Prototype ◽  
Flapping Wing ◽  
Optimal Parameters ◽  
Cam Mechanism ◽  
Set Up ◽  
3D Software ◽  
Flapping Mechanism

Folding motion is important for a flight creature using flapping wing mode, but it seldom used for flapping-wing robot. In this paper, we propose a new foldable flapping wing mechanism, which consists of spatial crank-rocker mechanism, parallelogram mechanism, and cam mechanism. We establish the kinematical models, calculate the optimal parameters, and set up the virtual prototype using 3D software. The tracks of wingtip and the comparison between foldable and unfoldable flap wing show that folding motion can improve lift force obviously.

scholarly journals Full Flight Envelope and Trim Map of Flapping-Wing Micro Aerial Vehicles

2020 ◽  
Vol 43 (12) ◽  
pp. 2218-2236
Author(s):  
Taylor S. Clawson ◽  
Silvia Ferrari ◽  
E. Farrell Helbling ◽  
Robert J. Wood ◽  
Bo Fu ◽  
...  
Keyword(s):  
Flapping Wing ◽  
Micro Aerial Vehicles ◽  
Aerial Vehicles ◽  
Flight Envelope
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