Abstract: Firstly, a dynamic inflow model for electrically controlled rotor (ECR) is developed based on the “PetersHe” generalized dynamic wake theory, and an accurate aerodynamics model of ECR, which is suited for the analysis of ECR helicopter flight dynamics, is built combined with the relationship between flap deflection and blade pitch, the blade flapping equation and the unsteady aerodynamic model of airfoil with trailingedge flap. Then, on this basis, an ECR helicopter flight dynamics model is established combined with the aerodynamics models of airframe, tail rotor, horizontal and vertical tail. Taking Z-11 helicopter as a numerical example, the distributions of ECR induced velocity and angles of attack variations with advance speed are calculated and compared with the baseline rotor. Furthermore, the trim characteristics of the ECR helicopter is investigated.