Wing Force & Moment Characterization of Flapping Wings for Micro Air Vehicle Application

Abstract

This paper presents a general method for investigating the unsteady aerodynamics of flapping wings for micro air vehicle application. For this purpose, a dynamically scaled robotic flapper was designed and fabricated which can flap the wings in a desired kinematic pattern. A quasisteady aerodynamic model and wing testing methodology was developed based on unsteady aerodynamic mechanisms. This model additionally accounts for the wing twisting. The experimental results show a good agreement with published data. 24 kinematic patterns were tested and the quasi-steady aerodynamic model compares well with the experimental results. The focus of the present work is on hovering flight, however, the methodology is general and can be extended to slow forward flight in future.