Modified Unsteady Vortex-Lattice Method to Study Flapping Wings in Hover Flight

Roccia, Bruno Antonio; Preidikman, Sergio; Massa, Julio C.; Mook, Dean T.

doi:10.2514/1.j052262

Cited by 65 publications

(45 citation statements)

References 54 publications

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“…These results are significant because they justify the use of the nonlinear unsteady vortex-lattice method to study the three-dimensional aerodynamics of insects executing different maneuvers. Similar results were found for the symmetrical and delayed patterns [38]. These results suggest that the present model will also serve well for the study of aerial robots.…”

Section: Aerodynamics Of Flapping Wingssupporting

confidence: 84%

“…The boundary layers are represented by bound-vortex lattices, which are attached or bound to the lifting surface and move with it. The wakes are represented by free-vortex lattices, which move freely with the flow so that their position and vorticity distribution are determined as part of the solution [35,[37][38][39].…”

Section: Aerodynamic Modelmentioning

confidence: 99%

“…Here, the effects of leading-edge separation are included through an on/off mechanism that consists mainly of computing the value of the effective angle of attack α e at each time step and comparing it with a reference value α c . Only when α e ≥ α c is leading-edge separation included [38].…”

Section: Leading-edge Separation Modelmentioning

confidence: 99%

“…The difference between the predicted mean lift force and the experimental mean lift force for the advanced pattern is about 4.5%. For a detailed study of the aerodynamic Aerial Robots -Aerodynamics, Control and Applicationsof flapping wings using a modified version of the unsteady vortex-lattice method, the reader is referred to the work of Roccia et al [38].…”

Section: Aerodynamics Of Flapping Wingsmentioning

confidence: 99%

See 3 more Smart Citations

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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Section: Aerodynamics Of Flapping Wingssupporting

confidence: 84%

Section: Aerodynamic Modelmentioning

confidence: 99%

Section: Leading-edge Separation Modelmentioning

confidence: 99%

Section: Aerodynamics Of Flapping Wingsmentioning

confidence: 99%

See 2 more Smart Citations

Computational Aeroelasticity of Flying Robots with Flexible Wings

Preidikman¹,

Roccia²,

LeonardoVerstraete³

et al. 2017

Aerial Robots - Aerodynamics, Control and Applications

Self Cite

View full text Add to dashboard Cite

show abstract

“…However, extensions for flow separation at the leading edge have been in use since the 1970s [22][23][24][25]. Roccia et al [26] used such a modification to model flapping wings in hover conditions. Many of the VLM simulations have been coupled to structural solvers in order to simulate flexible flapping wings [27][28][29].…”

Section: Introductionmentioning

confidence: 99%

Vortex Lattice Simulations of Attached and Separated Flows around Flapping Wings

2017

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Abstract:Flapping flight is an increasingly popular area of research, with applications to micro-unmanned air vehicles and animal flight biomechanics. Fast, but accurate methods for predicting the aerodynamic loads acting on flapping wings are of interest for designing such aircraft and optimizing thrust production. In this work, the unsteady vortex lattice method is used in conjunction with three load estimation techniques in order to predict the aerodynamic lift and drag time histories produced by flapping rectangular wings. The load estimation approaches are the Katz, Joukowski and simplified Leishman-Beddoes techniques. The simulations' predictions are compared to experimental measurements from wind tunnel tests of a flapping and pitching wing. Three types of kinematics are investigated, pitch-leading, pure flapping and pitch lagging. It is found that pitch-leading tests can be simulated quite accurately using either the Katz or Joukowski approaches as no measurable flow separation occurs. For the pure flapping tests, the Katz and Joukowski techniques are accurate as long as the static pitch angle is greater than zero. For zero or negative static pitch angles, these methods underestimate the amplitude of the drag. The Leishman-Beddoes approach yields better drag amplitudes, but can introduce a constant negative drag offset. Finally, for the pitch-lagging tests the Leishman-Beddoes technique is again more representative of the experimental results, as long as flow separation is not too extensive. Considering the complexity of the phenomena involved, in the vast majority of cases, the lift time history is predicted with reasonable accuracy. The drag (or thrust) time history is more challenging.

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