Dynamic analysis of an asymmetric UAV with partial wing damage

The effect of damage on the flight dynamic characteristics was studied. Partial right wing loss was considered for aircraft´s damage. To construct a 6-DOF model for the damaged asymmetric aircraft, a wing body UAV was designed and wind tunnel test for each damaged configuration was performed to identify the aerodynamic coefficient change. The mass, C.G. and MOI were also measured for each damaged configuration. The movement of longitudinal/lateral-directional flight mode poles was examined to evaluate the change of the flight dynamic characteristics. The result of this study shall be applied to the research on the controller design which can overcome the aerodynamic change from damage.