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.
This paper investigates the stabilization and control for flapping-wing flight of a simple flapping-wing vehicle. The
aerodynamic forces and moments of flapping-wing flight are estimated by modified strip theory. From the resultant
forces of the aerodynamics the flight dynamic analyses have been performed. For simulating cruising flight, one of the
proper conditions has been chosen through parametric study and is assigned to the dynamics. As a result the trajectory
and the body orientation of the vehicle are obtained which shows phugoid and short period motion in trim condition.
With an adequate tail-wing pitch control, the vehicle simulated level-up movement from a trim condition to another.
The present study proposed a coupling method for the fluid-structural interaction analysis of a flexible flapping wing. An
efficient numerical aerodynamic model was suggested, which was based on the modified strip theory and further
improved to take into account a high relative angle of attack and dynamic stall effects induced by pitching and plunging
motions. The aerodynamic model was verified with experimental data of rigid wings. A reduced structural model of a
rectangular flapping wing was also established by using flexible multibody dynamics and a modal approach technique,
so as to consider large flapping motions and local elastic deformations. Then, the aeroelastic analysis method was
developed by coupling these aerodynamic and structural modules. To measure the aerodynamic forces of the rectangular
flapping wing, static and dynamic tests were performed in a low speed wind-tunnel for various flapping pitch angles,
flapping frequencies and the airspeeds. Finally, the aerodynamic forces predicted by the aeroelastic analysis method
showed good agreement with the experimental data of the rectangular flapping wing.