An Unsteady Rotor Aerodynamics Analytical Model of Hybrid Compound High-speed Helicopter

In response to the complex nonlinear aerodynamic characteristics of the hybrid compound high-speed helicopter, the vector method is used to derive the relative airflow velocity of the blade element, and an unsteady rotor aerodynamics analytical model of the hybrid compound high-speed helicopter is established based on the blade element theory. Based on the established unsteady rotor aerodynamics mathematical model, numerical simulation is conducted in SIMULINK. In addition, the wind tunnel test is carried out in the FL-13 wind tunnel of the China Aerodynamics Research and Development Center by using the helicopter wind tunnel test rig. The experimental results show that the numerical simulation results of the unsteady rotor aerodynamics model are in good agreement with the wind tunnel test results, with high confidence and reliability, and can be used to guide the design of control strategies and the verification of control laws.