Effects of Asymmetric Blade-Pitching Kinematics on Forward-Flight Performance of a Micro-Air-Vehicle-Scale Cycloidal-Rotor

2016 ◽  
Vol 53 (5) ◽  
pp. 1568-1573
Author(s):  
Moble Benedict ◽  
Tejaswi Jarugumilli ◽  
Inderjit Chopra
Keyword(s):  
Micro Air Vehicle ◽  
Flight Performance ◽  
Forward Flight ◽  
Air Vehicle

Effect of Flow Curvature on Forward Flight Performance of a Micro-Air-Vehicle-Scale Cycloidal-Rotor

AIAA Journal ◽  
2014 ◽  
Vol 52 (6) ◽  
pp. 1159-1169 ◽  
Author(s):  
Moble Benedict ◽  
Tejaswi Jarugumilli ◽  
Vinod Lakshminarayan ◽  
Inderjit Chopra
Keyword(s):  
Micro Air Vehicle ◽  
Flight Performance ◽  
Forward Flight ◽  
Air Vehicle ◽  
Flow Curvature

scholarly journals Aerodynamic Characteristics of the Ventilated Design for Flapping Wing Micro Air Vehicle

2014 ◽  
Vol 2014 ◽  
pp. 1-11
Author(s):  
G. Q. Zhang ◽  
S. C. M. Yu
Keyword(s):  
Lift Force ◽  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Pressure ◽  
Flight Performance ◽  
Forward Flight ◽  
Careful Control ◽  
Air Vehicle

Inspired by superior flight performance of natural flight masters like birds and insects and based on the ventilating flaps that can be opened and closed by the changing air pressure around the wing, a new flapping wing type has been proposed. It is known that the net lift force generated by a solid wing in a flapping cycle is nearly zero. However, for the case of the ventilated wing, results for the net lift force are positive which is due to the effect created by the “ventilation” in reducing negative lift force during the upstroke. The presence of moving flaps can serve as the variable in which, through careful control of the areas, a correlation with the decrease in negative lift can be generated. The corresponding aerodynamic characteristics have been investigated numerically by using different flapping frequencies and forward flight speeds.

Resonance Hold Control of Flapping Foil System

2008 ◽  
Author(s):  
Hiroshi Isshiki
Keyword(s):  
Numerical Simulation ◽  
Control Method ◽  
Micro Air Vehicle ◽  
Flight Performance ◽  
Flapping Foil ◽  
Flying Insects ◽  
Air Vehicle ◽  
Flapping Foils ◽  
Inertia Forces ◽  
Very High

In case of MAV (Micro Air Vehicle), the generation of lift and thrust by flapping foils is very attractive, since flying insects such as dragonflies show the very high flight performance. However, in case of the flapping foil drive, the increase of load due to variation of the inertia forces takes place in contrast to the case of the rotary foil drive. So, it is extremely important to suppress the variation of the inertia forces. The possibility of canceling the inertia forces by using resonance is shown below. Furthermore, a control method to maintain the resonance is developed and verified by a numerical simulation.

Dynamic Behaviors of Butterfly Wing and Their Application to Micro Flight Robot

2009 ◽  
Author(s):  
Tadatsugu Imura ◽  
Masaki Fuchiwaki ◽  
Kazuhiro Tanaka
Keyword(s):  
Micro Air Vehicle ◽  
Flight Performance ◽  
Butterfly Wing ◽  
Free Flight ◽  
Elastic Deformations ◽  
Bird Flight ◽  
Dynamic Behaviors ◽  
Practical Applications ◽  
Air Vehicle ◽  
Significant Attention

Micro-Air-Vehicle (MAV) and micro-flight robot using insect and bird flight mechanisms has been attracting significant attention in recent years since the micro-electromechanical systems (MEMS) have been developed actively. Many researchers have attempted to develop MAV and micro-flight robot with various actuators and devices so far however their studies have not led to practical applications yet. One of the reasons is that flying mechanism of birds and insects has not been clarified sufficiently. In this study, we evaluate dynamic behaviors of a wing observed from the butterfly’s viewpoint in its flight. The authors conduct a flight observation experiment of Cynthia cardui performing a free flight and fixed flight and an image analysis and calculate flapping angles, lead-lag angle and feathering angles of the butterfly performing flapping flight to clarify the relation between them. Furthermore, we aim at developing the micro flight robot like the butterfly using these results. The butterfly realizes its flapping motions by changing not only flapping angles but also lead-lag angles in free and fixed flights. In a free flight, a butterfly performs flapping by greatly changing feathering angles in the wing span direction. The micro flapping robot has two wings and does not have the tail plane. The micro flapping robot flied stably for 12 minutes, which was the battery’s duration. The elastic deformations of a wing are one of the important parameters to realize stable flight performance.

Based on Pro/E on the Design and Simulation of Bionic Dragonfly Flapping Wing Aircraft

2011 ◽  
Vol 268-270 ◽  
pp. 960-965
Author(s):  
Yu Lan Zhou ◽  
Kun Wang ◽  
Jing Ping Chai
Keyword(s):  
Mechanism Design ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Light Weight ◽  
Flight Performance ◽  
Air Vehicle ◽  
Dragonfly Wings

In order to design an efficient, reliable, light weight, flapping wing mechanism,Improve the flight performance of the micro air vehicle and expand its application areas,this paper is concerned on the design and simulation of bionic dragonfly flapping wing aircraft .An mechanism design to simulate the movement of dragonfly wings isr presented in this paper.Then, simulation and analysis are made based on Pro/E.

scholarly journals Flight Performance Estimation of Bionic Flapping-Wing Micro Air Vehicle

2018 ◽  
Vol 36 (4) ◽  
pp. 636-643
Author(s):  
Wenqing Yang ◽  
Bifeng Song ◽  
Guanglin Gao
Keyword(s):  
High Speed ◽  
Angle Of Attack ◽  
Estimation Method ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Performance Estimation ◽  
Estimation Methods ◽  
Flight Performance ◽  
Air Vehicle ◽  
Performance Calculation

Bionic flapping-wing micro air vehicle(MAV) has received worldwide attention.The flight performance calculation is an important step in the conceptual design.The differences in performance estimation methods between the flapping-wing and conventional fixed-wing aircraft are analyzed.Based on the results of the aerodynamic estimation and wind tunnel experimental measurement, the flight performance estimation method of flapping-wing micro air vehicle is proposed, and the performance of level flight, climbing, and duration are calculated and analyzed.The frequency represents the accelerator in a certain extent, while the frequency is coupled with lift and thrust.The results show that there may be two stable cruising states at certain frequencies, one is the small angle of attack with high speed, the other is the small speed with big angle of attack, and the two states have different power consumption.According to the parameters of the vehicle, climbing performance and duration performance can be obtained.The speed versus power characteristic curve is a U shape, minimum slope of the U curve can be obtained through the mapping method to calculate the farthest flight speed, and the minimum velocity of U-shaped curve is the speed for longest duration.The proposed flight performance calculation method can be used to evaluate the flight capability of bionic micro flapping-wing air vehicle.

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