2013
DOI: 10.1016/j.ast.2011.10.011
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Optimal thickness distributions of aeroelastic flapping shells

Abstract: The severe weight limitations of flapping wing micro air vehicles necessitates the use of thin flexible wings, which in turn requires an aeroelastic modeling tool for proper numerical characterization. Furthermore, due to the unconventional nature of these vehicles, wing design guidelines for thrust and/or power considerations are not generally available; numerical design optimization then becomes a valuable tool. This work couples a nonlinear shell model to an unsteady vortex lattice solver, and then computes… Show more

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Cited by 11 publications
(6 citation statements)
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“…In this study, the UVLM was employed to model the airflow around the flexible sheet under the assumption of unsteady three-dimensional potential flow. The UVLM is a popular technique for evaluating the aerodynamic and aeroelastic characteristics of a wing because it requires a significantly reduced computational cost relative to CFD analysis (Katz and Plotkin, 2001) (Fritz and Long, 2004) (Stanford and Beran, 2013) (Abdelkefi et al, 2014).…”
Section: Aerodynamic Model Around the Sheetmentioning
confidence: 99%
See 1 more Smart Citation
“…In this study, the UVLM was employed to model the airflow around the flexible sheet under the assumption of unsteady three-dimensional potential flow. The UVLM is a popular technique for evaluating the aerodynamic and aeroelastic characteristics of a wing because it requires a significantly reduced computational cost relative to CFD analysis (Katz and Plotkin, 2001) (Fritz and Long, 2004) (Stanford and Beran, 2013) (Abdelkefi et al, 2014).…”
Section: Aerodynamic Model Around the Sheetmentioning
confidence: 99%
“…We have also presented a numerical model to avoid these problems in previous studies (Yamano et al, 2018(Yamano et al, , 2020. In our approach, three-dimensional fluid flow was modeled using the UVLM without the above-mentioned assumption, which involves reduced computing costs compared with CFD analysis (Katz and Plotkin, 2001) (Fritz and Long, 2004) (Stanford and Beran, 2013) (Abdelkefi et al, 2014). Thereby, many parameter combinations including large deformation can be surveyed.…”
Section: Introductionmentioning
confidence: 99%
“…Research works 25,26 show that the flexibility of the membrane wing would dominate the aerodynamic characteristics, a parametric study was primarily carried out to investigate the effects of wing deformation on aerodynamic characteristics, so as to determine the rigidity distribution of the flexible wing. The preconditioned Reynold-averaged Navier-Stokes equations, based on chimera grid, 27 were developed to implement this numerical study.…”
Section: Flapping-wing Designmentioning
confidence: 99%
“…Thus, UVLM requires the fluid to leave the beam smoothly at the trailing edge to satisfy the Kutta condition (Preidikman and Mook, 2000; Hall et al., 2001; Wang, 2004) and does not cover the cases of flow separation at the leading edge and extreme situations where strong beam–wake interactions take place. In spite of these restrictions, the use of UVLM remains adequate for our application of interest (Preidikman and Mook, 2000; Hall et al., 2001; Wang, 2004; Stanford and Beran, 2011).…”
Section: Aeroelastic Modelingmentioning
confidence: 99%