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Inspired by insect flapping wings, a novel flapping wing rotor (FWR) has been developed for micro aerial vehicle (MAV) application.
In this paper, investigation was made into the design, theoretical study, numerical modelling and experiment of a novel flapping wing rotor for micro aerial vehicles (MAV).
Inspired by the high performance of rotary and insect flapping wings capable of vertical take-off and landing and hovering (VTOLH), a novel flapping wing rotor (FWR) has been developed by combining the above two types of wing motions.
To demonstrate the feasibility and effectiveness of the innovative design, a piezoelectric actuated flapping wing rotor model was manufactured and tested.
In the experiment, the total force produced by the flapping wing rotor including the aerodynamic and inertia forces has been measured through a data process approach.
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Wing deformation can improve the performance of flapping wing MAV.
Numerous open issues in flapping wing aerodynamics are highlighted.
The company is developing tiny insect-like UAVs, or drones, with flapping wings instead of rotors.
In addition, the aerodynamics of tandem wings under gusty conditions will be reviewed and compared with isolated wings to demonstrate the gust resistance characteristics of flapping wings.
These results highlight the necessity for modal testing of robotic flapping wings.
Flapping wings with suitable wing kinematics, wing shapes, and flexible structures can enhance lift as well as thrust by exploiting large-scale vortical flow structures under various conditions.
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