Abstract
The last decade has witnessed a surge of scientific interest in flight at the micro air vehicle (MAV) scale. To date, a MAV utilizing an adaptable, flexible smart wing design has yet to come to fruition. While highly flexible aerodynamic surfaces have repeatedly demonstrated improved performance through passive adaptation, limited structural and flow state knowledge prevents the inclusion of active control strategies which could improve performance of such designs.
In this work, a flexible membrane wing constructed of latex was considered. The goal of estimating lift was approached through experimental and theoretical correlation of wing strain state due to flow-induced pressure. Using visual image correlation, elastic deformations, strains and membrane pretensions of the wing were measured in the Oregon State University wind tunnel. In addition, a six-degree-of-freedom sting balance was used to determine aerodynamic loads.
A linear membrane wing formulation was utilized to correlate the wing’s structural strain to lift and wing-tip vorticity. Results of the forces measured by a sting balance were then compared to those predicted by flow simulation. This work describes experimental results that illustrate the effectiveness of low fidelity models in predicting and estimating useful information for flexible wing designs.
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Shyy W (2008) Aerodynamics of low Reynolds number flyers. Cambridge University Press, New York
Sutton MA, Cheng M, Peters WH, Chao YJ, McNeill SR (1986) Application of an optimized digital correlation method to planar deformation analysis. Image Vis Comput 4(3):143–151
Sutton MA, Turner JL, Bruck HA, Chae TA (1991) Full field representation of the discretely sampled surface deformations for displacement and strain analysis. Exp Mech 31(2):168–177
Schmit R, Glauser M (2005) Use of low-dimensional methods for wake flowfield estimation from dynamic strain. Am Inst Aeronaut Astronaut J 43(5):1133–1136
Schmit R (2002) Low dimensional tools for flow-structure interaction problems: application to micro air vehicles. Doctoral dissertation, Clarkson University
Song A, Tian X, Israeli E, Galvao R, Bishop K, Swartz S, Breuer K (2008) Aeromechanics of membrane wings with implications for animal flight. Am Inst Aeronaut Astronaut J 46(8):2096–2106
Posada JA (2007) Numerical study of wingtip shed vorticity reduction by wing boundary layer control. Doctoral dissertation. Available from ProQuest Disserations & Teses database (Publication no. 3298564), West Virginia University Libraries
Imamura T, Enomoto S, Yamamoto K (2006) Noise generation around NACA0012 wingtip using large-eddy simulation. Int Congr Aeronaut Sci 25:1–10
Acknowledgments
The authors would like to thank the support of the Air Force Office of Scientific Research, Flow Control & Aeroelasticity under Contract FA9550-10-1-0325, with Douglas R. Smith as project monitor and the Air Force Office of Scientific Research under the Multidisciplinary University Research Initiative grant FA9550-07-1-0540. The authors would also like to acknowledge Dr. Belinda Batten’s continuous and critical support to the project and the University of Florida for assistance with contractual aspects.
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© 2013 The Society for Experimental Mechanics, Inc.
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Carpenter, T., Ray, C., Albertani, R. (2013). Correlation of Structural Strain to Tip Vorticity and Lift for a MAV Pliant Membrane Wing. In: Ventura, C., Crone, W., Furlong, C. (eds) Experimental and Applied Mechanics, Volume 4. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, New York, NY. https://doi.org/10.1007/978-1-4614-4226-4_1
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DOI: https://doi.org/10.1007/978-1-4614-4226-4_1
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