Flight dynamic characteristics of canard rotor/wing aircraft in hover

Flight test identification is adopted in the study of flight dynamics of Canard Rotor/Wing (CRW) aircraft because conventional methods and empirical formulas are not suitable for flight dynamic analysis of CRW aircraft due to its unique layout. The flight test is first designed and high quality data are obtained. Based on the frequency response, the state pace model of the CRW aircraft is simplified, and the kinetic parameters of the aircraft are optimized in the frequency domain. A high confidence dynamics model of the CRW aircraft in hover is then obtained and confirmed by the flight data. A comparison between the CRW model and the conventional helicopter model in hover shows that the control derivatives and the damping derivatives of the CRW aircraft are smaller than those of the conventional helicopter. It is found that the decrease of the control derivatives is mainly due to the rotor aerodynamic characteristics, and the reason for the decrease of damping derivatives is mainly the design of canard, horizontal tail and vertical fin. The comparison results provide guidance and reference for further optimization of CRW aircraft rotor mode design, and the dynamics model can be used to design the control system.