Aerodynamic characteristic modeling of electrically controlled rotor and wind tunnel test verification

Firstly,the unsteady aerodynamic model of the airfoil with trailing-edge flap was developed.Secondly,the finite state wake model of electrically controlled rotor(ECR) based on the Peters-He generalized dynamic wake theory was developed,in which the effect of the trailing-edge flap on the rotor aerodynamic environment was considered.Combined with the relationship among the blade flapping angle, the blade pitch and the deflection angle of the trailing-edge flap,the model of calculating the aerodynamic characteristics of ECR was established finally.Then,wind tunnel tests were conducted,in which the aerodynamic force,the blade pitch,the deflection angle of the trailing-edge flap and the blade flapping angle varying with different test statuses were measured.Theoretical results basically coincided with the experimental data, which verified the correction of the theoretical model. Conclusions are drawn as follows: with the fixed rotor speed, there is a linear relationship between blade pitch response and flap control; rotor thrust decreases with the increase of flap collective control, and actual aerodynamic efficiency of the flap decreases under large collective control; in forward flight, flap collective control can cause changes of blade cyclic pitch.