21 April 2008 Experimental evaluation of a flapping-wing aerodynamic model for MAV applications
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Abstract
In the preliminary design phase of the bio-inspired flapping-wing MAV (micro air vehicle), it is necessary to predict the aerodynamic forces around the flapping-wing under flapping-wing motion at cruising flight. In this study, the efficient quasi-steady flapping-wing aerodynamic model for MAV application is explained and it is experimentally verified. The flapping-wing motion is decoupled to the plunging and pitching motion, and the plunging-pitching motion generator with load cell assembly is developed. The compensation of inertial forces from the measured lift and thrust is studied to measure the pure aerodynamic loads on the flapping-wing. Advanced ratio is introduced to evaluate the unsteadiness of the flow and to make an application range of flapping-wing aerodynamic model.
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Jun-Seong Lee, Jun-Seong Lee, Dae-Kwan Kim, Dae-Kwan Kim, Jin-Young Lee, Jin-Young Lee, Jae-Hung Han, Jae-Hung Han, } "Experimental evaluation of a flapping-wing aerodynamic model for MAV applications", Proc. SPIE 6928, Active and Passive Smart Structures and Integrated Systems 2008, 69282M (21 April 2008); doi: 10.1117/12.776169; https://doi.org/10.1117/12.776169
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