A Computational Framework for Fluid Structure Interaction in Biologically Inspired Flapping Flight

Willis, David J.; Israeli, Emily; Persson, Per‐Olof; Drela, Mark; Peraire, J.; Swartz, Sharon M.; Breuer, Kenneth S.

doi:10.2514/6.2007-3803

Cited by 43 publications

(34 citation statements)

References 23 publications

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“…The aeroelasticity of flapping wings has only recently been seriously addressed and a full picture of the basic aeroelastic phenomena in flapping flight is still not clear [1,5,[11][12][13][14][15][16][17][18][19][20][21]. In an earlier investigation, Smith [14] has studied the effects of flexibility on the aerodynamics of Moth wings by modeling them as linearly elastic structures using finite elements for a Reynolds number of the order of 10 3 and reduced frequencies of the order of 0.2 and higher.…”

mentioning

confidence: 99%

“…However, when the wing is immersed in water, the chordwise flexibility increased the efficiency and the spanwise flexibility reduced both the thrust and the efficiency. Wills et al [17] have presented a computational framework to design and analyze flapping MAV flight. A series of different geometric and physical fidelity level representations of solution methodologies was described in the work.…”

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confidence: 99%

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Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles

Chimakurthi¹,

Tang²,

Palacios

et al. 2009

AIAA Journal

101

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Due to their small size and flight regime, coupling of aerodynamics, structural dynamics, and flight dynamics is critical for Micro Aerial Vehicles. This paper presents a computational framework for simulating structural models of varied fidelity and a Navier-Stokes solver, aimed at simulating flapping and flexible wings. The structural model utilizes either (i) the in-house developed UM/NLABS, which decomposes the equations of 3-D elasticity into cross-sectional and spanwise analyses for slender wings; or (ii) MSC.Marc, which is a commercial finite element solver capable of modeling geometrically-nonlinear structures of arbitrary geometry.

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confidence: 99%

mentioning

confidence: 99%

Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles

Chimakurthi¹,

Tang²,

Palacios

et al. 2009

AIAA Journal

101

View full text Add to dashboard Cite

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“…In order to show the role of the wing's flexibility in the production of lift, the parameters that regulate the deformation were tuned in order to increase the lift force throughout the stroke cycle with respect to the rigid-wing model. The set of initial conditions for the two cases studied consists of a body angle of 75 and a stroke plane angle of 15 . These values produce a horizontal stroke plane.…”

Section: Dynamics Of Flapping Wingsmentioning

confidence: 99%

“…The primary components of numerical simulations are the aerodynamic solver, the structural-dynamic solver, and the communication between them. Early studies on fluid-structure interactions for vehicles with flapping wings have been based on either two-dimensional models or other simplified aerodynamic models based on thin-airfoil theory or unsteady panel methods or Euler methods and on linear beam finite elements [14][15][16][17]. Nakata and Liu [18] used an unsteady aerodynamic model based on a Navier-Stokes solver [19] coupled with a finite-element formulation specifically developed for insect flight that accounts for the distribution and anisotropy of the wing's veins and membranes.…”

Section: Introductionmentioning

confidence: 99%

Computational Aeroelasticity of Flying Robots with Flexible Wings

Preidikman¹,

Roccia²,

LeonardoVerstraete³

et al. 2017

Aerial Robots - Aerodynamics, Control and Applications

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A computational co-simulation framework for flying robots with flexible wings is presented. The authors combine a nonlinear aerodynamic model based on an extended version of the unsteady vortex-lattice method with a nonlinear structural model based on a segregated formulation of Lagrange's equations obtained with the Floating Frame of Reference formalism. The structural model construction allows for hybrid combinations of different models typically used with multibody systems such as models based on rigid-body dynamics, assumed-modes techniques, and finite-element methods. The aerodynamic model includes a simulation of leading-edge separation for large angles of attack. The governing differentialalgebraic equations are solved simultaneously and interactively to obtain the structural response and the flow in the time domain. The integration is based on the fourth-order predictor-corrector method of Hamming with a procedure to stabilize the iteration. The findings are found to capture known nonlinear behavior of flapping-wing systems. The developed framework should be relevant for conducting aeroelastic studies on a wide variety of air vehicle systems.

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“…We choose the later strategy, and use a multi-fidelity framework that comprises a wake-only method, a quasi-doublet lattice method for inverse wing design and a high fidelity Navier-Stokes simulation. We have shown that our particular multi-fidelity approach is promising for both two-dimensional and three-dimensional settings such as thrust producing flapping foils 1,2 . We present a similar framework here for designing efficient wings and validating those designs at the highest fidelity level.…”

Section: Introductionmentioning

confidence: 99%

High Fidelity Simulations of Flapping Wings Designed for Energetically Optimal Flight

Persson

Willis

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A diversity of efficient solutions for flapping flight have evolved in nature; however, it is often difficult to isolate the key characteristics of efficient flapping flight from biological constraints. Rather than base micro aerial vehicle (MAV) design on natural flyers alone, we propose a multi-fidelity computational approach for analysis and design. At the lowest fidelity level, we use a wake-only energetics model that allows us to rapidly scan the global flapping kinematics for efficient kinematics and configurations. Following the wake-only design space characterization, we determine a series of candidate flapping wing geometries that can produce the desired wake characteristics. To do this, we have developed a quasiinverse wing design strategy that attempts to match the designed vehicle's wake-circulation distribution with that predicted by the energetics model. Using our modified-doublet lattice method, we are able to determine how to modulate wing twist and camber to produce the desired wake vorticity. Because the method assumes inviscid flow, we are able to derive a large number of candidate designs to produce the target wake; however, as we show in this paper, only some of the designs perform adequately in physically relevant viscous fluids. As such, we use a high order, Discontinuous Galerkin, Navier-Stokes solver to simulate and assess the candidate designs, and examine which geometries minimize flow separation, improve performance and increase efficiency. The focus of this paper is on the design and analysis of efficient flapping wings. We present an application of our framework to a MAV design that has similar characteristics as medium sized fruit bat. We examine candidate wing designs to illustrate how adjusting wing section camber may be more favorable than adjusting wing twist alone. We find that the angle the leading edge of the wing presents to the flow is critical to minimizing flow separation.

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A Computational Framework for Fluid Structure Interaction in Biologically Inspired Flapping Flight

Cited by 43 publications

References 23 publications

Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles

Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles

Computational Aeroelasticity of Flying Robots with Flexible Wings

High Fidelity Simulations of Flapping Wings Designed for Energetically Optimal Flight

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