Wind tunnel test of UAV fault detection using principal component based aerodynamic model

In our previous work the fault detection using aerodynamic model was proposed as more directly method to detect the fault such as configuration damage of the UAV. In this paper the wind tunnel test is performed with the object of verifying the capability of this method to detect the damage during flight. The result shows that by observing the residual of the aerodynamic force coefficient the damage can be detected instantaneously when it occurs.