Flight Dynamics Modeling and Control of a New Type High-speed Helicopter in Take-off and Landing

Canard Rotor / wing (CRW) aircraft, as a new type of high-speed helicopter, combines the advantages of vertical take-off and landing of helicopter and high-speed cruise of fixed wing aircraft. At the same time, it also has a unique aerodynamic layout, which leads to large coupling and interference during take-off and landing and is prone to accidents. This paper studies the flight dynamics modeling and control system design of CRW aircraft automatic take-off and landing. In order to obtain the model with high reliability, the paper adopts the methods of mechanism modeling, flight identification and empirical formula. Firstly, the flight dynamics model of helicopter in hover mode is derived by using mechanism modeling, and the key parameters in the model are obtained by using flight identification; secondly, the flight dynamics model of helicopter in take-off and landing mode is obtained by considering the influence of ground effect according to empirical formula; then, the explicit model following control method is used to design the inner loop stability augmentation system during take-off and landing, and the outer loop control system is designed based on classical control theory. Finally, the take-off and landing command model is designed, and the explicit model stability augmentation control system and automatic take-off and landing system are simulated and verified, respectively. The results show that the design method proposed in this paper is effective and the control system designed is feasible, which lays a solid foundation for the engineering flight test of CRW aircraft.