Simulation of helicopter rotor aerodynamic force in conditions of high angle of attack and dynamic stall

Using Pitt-Peters dynamic inflow model and Wang's vortex theory, helicopter inflow model was set up. The distribution and magnitude of rotor induced velocity in helicopter maneuvering flight were obtained. According to blade element theory and state-space function, rotor unsteady aerodynamic model was established, and the rotor dynamic response characteristics were calculated for different azimuth angles. The agreement between the computational results and the referenced data indicates that the models are feasible and effective. Finally, for the two flight conditions with dynamic stall and deep dynamic stall, MATLAB software was taken as the computational platform, and rotor loads responses at high angles of attack for pop-up maneuver can be obtained. The theoretical method can provide the references for the simulation of the unsteady aerodynamic forces in helicopter maneuvering flight.