Experimental Investigation of Aerodynamics of Flapping-Wing Micro-Air-Vehicle by Force and Flow-Field Measurements

Deng, Shuanghou; Perçin, Mustafa; Oudheusden, B.W. van

doi:10.2514/1.j054403

Cited by 25 publications

(17 citation statements)

References 29 publications

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“…The lumped parameter is also a dimensionless number. From (17), it is clearly seen that it does not vary with the body mass. As is shown in (18), the lumped parameter is inversely proportional to the average lift coefficient, which indicates that the larger the lumped parameter is, the less lift is produced at a constant angle attack.…”

Section: Flapping Wing Lift Productionmentioning

confidence: 93%

“…However, the ratio for other species excluding hummingbirds rises slightly in size. Similarly, the lumped value is also constant based on (17). In this study, the average value of various species is considered and studied.…”

Section: Wing Loading Aspect Ratio and Lumped Parametermentioning

confidence: 99%

“…Besides, rigid hawkmoth-like wings are also studied by Lua et al [15]. Although certain results were obtained on rigid flat wings, rigid wings had worse performance than flexible wings [16][17][18][19]. Natural flyers have wings with several degrees of freedom when flapping.…”

Section: Introductionmentioning

confidence: 99%

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Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers?

Nan

Peng

Chen

et al. 2018

International Journal of Aerospace Engineering

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Lift production is constantly a great challenge for flapping wing micro air vehicles (MAVs). Designing a workable wing, therefore, plays an essential role. Dimensional analysis is an effective and valuable tool in studying the biomechanics of flyers. In this paper, geometric similarity study is firstly presented. Then, the pw−AR ratio is defined and employed in wing performance estimation before the lumped parameter is induced and utilized in wing design. Comprehensive scaling laws on relation of wing performances for natural flyers are next investigated and developed via statistical analysis before being utilized to examine the wing design. Through geometric similarity study and statistical analysis, the results show that the aspect ratio and lumped parameter are independent on mass, and the lumped parameter is inversely proportional to the aspect ratio. The lumped parameters and aspect ratio of flapping wing MAVs correspond to the range of wing performances of natural flyers. Also, the wing performances of existing flapping wing MAVs are examined and follow the scaling laws. Last, the manufactured wings of the flapping wing MAVs are summarized. Our results will, therefore, provide a simple but powerful guideline for biologists and engineers who study the morphology of natural flyers and design flapping wing MAVs.

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Section: Flapping Wing Lift Productionmentioning

confidence: 93%

Section: Wing Loading Aspect Ratio and Lumped Parametermentioning

confidence: 99%

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Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers?

Nan

Peng

Chen

et al. 2018

International Journal of Aerospace Engineering

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“…1 Flapping wing UAVs, the most intriguing type in the UAV family, are regarded as the most efficient prototype due to the high lift unsteady mechanisms. Successful flapping-wing UAVs can be recognized such as Microbat, 2 DelFly, 3,4 hummingbird, 5 Robobee, 6 etc. Ducted-fan UAV, as one special rotary manned aerial vehicle (MAV), has obtained a considerable attention recently.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of a ducted contra-rotating lift fan for vertical/short takeoff and landing unmanned aerial vehicle application

Deng

Ren

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study explores the aerodynamic characteristics of a ducted contra-rotating lift fan for vertical/short takeoff and landing application by means of force, pressure, and flow field measurements. The effect of rotating frequency and contra-locomotion on the force generation was examined using a miniature six-component force sensor. Additionally, for the sake of considering the ground effect, the flow field at the exit was investigated using high-response pressure measurement. Results revealed that the lift shows a quadratic generation trend on increasing the r/min where the inherent unsteady flow contradicts the conventional quasi-steady model of propeller. The contra-rotating mechanism can significantly augment the lift while still being lower than double single rotors. The unsteadiness of the contra-rotating rotors is quite obvious where two high-pressure regions are revealed and rotate. When the lift fan approaches the ground, the lift will be augmented significantly due to the surplus of the wake jet.

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“…That is the reason that only few of the existing flapping MAVs adopt the single wings mode which the natural flyers use. In contrast, tandem and biplane configurations are widely used in flapping MAVs, such as "DelFly" [6,7], to obtain extra aerodynamic forces, high propulsive efficiency and reliable control capability. Understanding and predicting of the aerodynamic characteristics interaction between wing and tail or between the close coupled wings therefore becomes essential.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic characteristics of multiple flapping wing configurations

Shen¹,

Cai²

2016

J. vibroeng.

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Natural flyers and man-made MAVs generally use multiple flapping wing configurations. To understand the aerodynamic performance, three different flapping configurations: single wing, tandem wings, and biplane wings are numerically simulated by a URANS solver coupled with an overset grid method. Moreover, effect of kinematics including oscillating frequency, angle of attack and wing to tail distance are detailed investigated. Results show that the wing-tail interaction significantly benefits the thrust generation when the wings are tandem arranged. Additionally, the tandem arrangement is the most efficiency configuration when applied with high frequencies.Biplane wings model has the most inefficiency propulsive performance, nevertheless it can provide an extensive aerodynamic force. With the increasing AOA, biplane has the largest critical angle from thrust to drag. Wing-tail interaction becomes weaker when the tail is mounted further from the flapping wings. The present of the tail in tandem model bring more benefits compared with the tail in biplane model. The tail in biplane model is only functional for flight control when applied with a non-zero angle of attack.

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Experimental Investigation of Aerodynamics of Flapping-Wing Micro-Air-Vehicle by Force and Flow-Field Measurements

Cited by 25 publications

References 29 publications

Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers?

Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers?

Experimental study of a ducted contra-rotating lift fan for vertical/short takeoff and landing unmanned aerial vehicle application

Aerodynamic characteristics of multiple flapping wing configurations

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