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.

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 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.

Using a Large 2 Degree of Freedom Tail for Autonomous Aerobatics on a Flapping Wing Unmanned Aerial Vehicle

2016 ◽  
Author(s):  
Luke Roberts ◽  
Hugh Bruck ◽  
S. K. Gupta
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Flight Control ◽  
Flapping Wing ◽  
Degree Of Freedom ◽  
Simple Method ◽  
Orientation Change ◽  
Aerial Vehicles ◽  
Angular Velocities ◽  
Aerial Vehicle ◽  
Rotary Wing

Flapping wing unmanned aerial vehicles (FWUAVs) provide an alternative to traditional platforms because they are more maneuverable than fixed wing platforms while being faster, quieter, and more natural looking than rotary wing platforms. While real birds are able to execute complex and highly controlled aerobatic maneuvers, executing FWUAV aerobatics presents unique challenges due to difficulty in execution of controlled quick orientation change. This paper demonstrates a simple method for using a large 2 degree of freedom tail for quick orientation changes and flight control, enabling execution of a pre-programmed backflip maneuver on the Robo Raven V, a hybrid FWUAV. The platform reached angular velocities of up to 420° per second during the maneuver.

Development of thickened semi-synthetic engine oil M-5z / 20 AERO for four-stroke gasoline engines aircraft piston of unmanned aerial vehicles (UAVs)

2020 ◽  
Vol 06 ◽  
pp. 44-47
Author(s):  
A.A. Moykin ◽  
◽  
A.S. Medzhibovsky ◽  
S.A. Kriushin ◽  
M.V. Seleznev ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Engine Oil ◽  
Motor Oil ◽  
Gasoline Engines ◽  
State Research Institute ◽  
Technical Requirements ◽  
Aerial Vehicles ◽  
State Research ◽  
Industrial Batch ◽  
The Russian Federation

Nowadays, the creation of remotely-piloted aerial vehicles for various purposes is regarded as one of the most relevant and promising trends of aircraft development. FAU "25 State Research Institute of Chemmotology of the Ministry of Defense of the Russian Federation" have studied the operation features of aircraft piston engines and developed technical requirements for motor oil for piston four-stroke UAV engines, as well as a new engine oil M-5z/20 AERO in cooperation with NPP KVALITET, LLC. Based on the complex of qualification tests, the stated operational properties of the experimental-industrial batch of M-5z/20 AERO oil are generally confirmed.

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