Flapping Wing Structural Deformation and Thrust Correlation Study with Flexible Membrane Wings

Wu, Pin; Ifju, Peter; Stanford, Bret

doi:10.2514/1.j050310

Cited by 79 publications

(49 citation statements)

References 19 publications

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“…The previous two cases were proposed by Heathcote and Gursul [64] and Heathcote, Wang, and Gursul [65] to assess the effects of chordwise and spanwise flexibilities, respectively, on the thrust generation of plunging wing in forward flight at low density ratio. Motivated by the experimental studies on the three-dimensional Zimmerman wing planform [31], a three-dimensional hovering flapping isotropic wing in air is considered. The wing is a flat plate wing of m = 0.0196 m and = 3.825 with a thickness ratio of * = 2.0×10 -2 having a Zimmerman planform, see Figure V-10, hovering in air at = 1.5×10 3 .…”

Section: V1c Hovering Isotropic Zimmerman Wing In Airmentioning

confidence: 99%

Effects of Flexibility on the Aerodynamic Performance of Flapping Wings

Kang

Aono

et al. 2011

6th AIAA Theoretical Fluid Mechanics Conference

210

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Effects of chordwise, spanwise, and isotropic flexibility on the force generation and propulsive efficiency of flapping wings are elucidated. For a moving body immersed in viscous fluid, different types of forces, as a function of the Reynolds number, reduced frequency (k), and Strouhal number (St), acting on the moving body are identified based on a scaling argument. In particular, at the Reynolds number regime of O(10 3 -10 4 ) and the reduced frequency of O(1), the added mass force, related to the acceleration of the wing, is important. Based on the order of magnitude and energy balance arguments, a relationship between the propulsive force and the maximum relative wing tip deformation parameter (γ) is established. The parameter depends on the density ratio, St, k, natural and flapping frequency ratio, and flapping amplitude. The lift generation, and the propulsive efficiency can be deduced by the same scaling procedures. It seems that the maximum propulsive force is obtained when flapping near the resonance, whereas the optimal propulsive efficiency is reached when flapping at about half of the natural frequency; both are supported by the reported studies. The established scaling relationships can offer direct guidance for MAV design and performance analysis.

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Section: V1c Hovering Isotropic Zimmerman Wing In Airmentioning

confidence: 99%

Effects of Flexibility on the Aerodynamic Performance of Flapping Wings

Kang

Aono

et al. 2011

6th AIAA Theoretical Fluid Mechanics Conference

210

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“…Such an assumption mimics the set-up commonly found in bench-top experiments (for example, Wu et al (2010)), but an actual flapping wing MAV may show relevant interactions between the flight dynamics of a body and the aeroelastic behavior of the flapping wings. The goal of this work is to discuss numerical methods by which these interactions may be captured, quantify the stability of the resulting time-periodic system, and introduce these metrics into the optimization process.…”

Section: Introductionmentioning

confidence: 94%

Stability and Power Optimality in Time-Periodic Flapping Wing Structures

Stanford¹,

Beran²,

Snyder³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite

5
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a b s t r a c tThis paper investigates the nonlinear dynamics of a vehicle with two flexible flapping wings. The body dynamics and the wings' deformation are monolithically grouped into a single system of equations, with aerodynamics accounted for by a quasi-steady blade element method. A periodic shooting method is then used to locate closed orbits of this non-autonomous system, and Floquet multipliers assess the linearized stability about the nonlinear orbit. This framework is then exposed to a gradient based optimizer, in order to quantify the role of wing planform variables, wing structure variables, and kinematic actuation variables in obtaining vehicles with superior open-loop stability characteristics, and/or low-power requirements.Published by Elsevier Ltd.

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“…This can take the form of stroboscopic lighting synchronised to the loading [7] or directly synchronising the image trigger to the loading cycle [8]. However, such synchronisation introduces additional complexity and cost to the test set-up and does not provide any improvement in terms of strain or spatial resolution compared to the standard static approach.…”

Section: Introductimentioning
confidence: 99%

The use of a lock-in amplifier to apply digital image correlation to cyclically loaded components
Fruehmann
¹
,
Dulieu-Barton
²
,
Quinn
³

et al. 2015
Optics and Lasers in Engineering
22
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16
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Flapping Wing Structural Deformation and Thrust Correlation Study with Flexible Membrane Wings

Cited by 79 publications

References 19 publications

Effects of Flexibility on the Aerodynamic Performance of Flapping Wings

Effects of Flexibility on the Aerodynamic Performance of Flapping Wings

Stability and Power Optimality in Time-Periodic Flapping Wing Structures

The use of a lock-in amplifier to apply digital image correlation to cyclically loaded components

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