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Experiments and Numerical Simulations for the Quantification of Lift in Flapping Flight

K. R. Sreenivas

Abstract


Research in the area of flapping flight has attracted renewed interest with an endeavor to use this mechanism for Micro Air vehicles (MAVs). Primary aim of the research is to identify a simple and efficient flapping-kinematics that could generate sustained lift with capabilities of high-endurance and larger payload carrying capacity. We identify a simple wing kinematics (asymmetric-flapping) that could generate a sustained lift. Results from our simulations of the flapping-flight elucidate the effects of wing flexibility, flapping-amplitude and wing-inclination on the lift coefficient. Simulation results indicate that for a given flapping-amplitude and wing inclination, lift generated can be maximized for an optimum value of wing-deflection. Similarly, when the wing-stiffness is held constant, lift coefficient increases with increase in flapping amplitude and flapping frequency. We present design of a six-axis micro-balance and flapping test-rig used for measuring forces generated in flapping flight. Results include calibration of the balance and preliminary force measurement using flapping test rig.

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References


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DOI: http://dx.doi.org/10.21535%2FProICIUS.2010.v6.437

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