This study is a continuing effort to understand the effect of wing root tilting on a symmetrical flapping wing platform to pave the way for the implementation of tailless flight control on a hovering flapping wing micro air vehicle. A symmetrical flapping mechanism was designed and fabricated to conduct the study. The flapping mechanism consists of two four bar linkage crank-rockers flapping mechanism, but the connection of the coupler to the rocker is a slot, such that only one crank-rocker is used to drive the wings at any given time. Both wings are synchronized using strings. Study shows that tilting the wing roots creates a linear trend of pitch and yaw moment at the compromise of lift. Wing kinematics was captured and wing inertia was estimated to provide better insight of the effect of wing root tilting.
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