Comparison Study of Membrane Flapping Wing Based on Mooney-Rivlin Model and Linear Model

Chun Jin Yu

doi:10.4028/www.scientific.net/AMR.753-755.1842

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 753-755Comparison Study of Membrane Flapping Wing Based...

Comparison Study of Membrane Flapping Wing Based on Mooney-Rivlin Model and Linear Model

Abstract:

The maximum deformation and stress are compared based on Mooney-Rivlin Model and Linear Model for flapping wing. One flapping cycle was divided into twelve segments, and maximum deformation and stress were calculated in each segment. The results show that max deformation and stress all occur at the beginning of downstroke, the max deformation adopted Mooney-Rivlin model is 25 percent of the max deformation adopted the linear model, and the max stress adopted Mooney-Rivlin model is only 0.37 percent of the max stress adopted the linear model. Mooney-Rivlin Material is very suitable for the membrane flapping wing.

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Periodical:

Advanced Materials Research (Volumes 753-755)

Pages:

1842-1845

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.753-755.1842

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Online since:

August 2013

Authors:

Chun Jin Yu

Keywords:

Flapping Wing, Membrane Wing, Moon-Rivlin

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References

[1] Y. Lian, W. Shyy. Three-Dimensional Fluid-Struture Interactions of a membrane wing for micro air vehicle applications. AIAA 2003-1726.

DOI: 10.2514/6.2003-1726

Google Scholar

[2] C. Yu, H. Ang, Q. Chen, et al. Three-dimension unsteady vortex lattice method for flexible structure flapping-wing aerial vehicle . Journal of Nanjing University of Aeronautics and Astronautics, 40 (2008) 451-455.

Google Scholar

[3] C. Yu, H. Ang, K. Yi, et al. The study of deformation for membrane flapping-wing aerial vehicles . Chinese Journal of Computational Mechanics, 26 (2009) 935-941.

Google Scholar

[4] T. Fitzgerald, M. Valdez and Balachandran. A comparison of computational models for fluid-structure interaction studies of flexible flapping wing systems. AIAA 2011-1115.

DOI: 10.2514/6.2011-1115

Google Scholar

[5] T. Nakata, H. Liu. A fluid-structure interaction model of insect flight with flexible wings. Journal of Computational Physics, 231 (2012) 1822–1847.

DOI: 10.1016/j.jcp.2011.11.005

Google Scholar