A new rotor dynamic wake model is presented and verified for helicopter real-time large maneuvering flight simulation. Vortex ring elements which have five rigid body motion freedoms and one radius extending-compressing freedom are used to represent the rotor wake vortices. The proposed model can describe the stretch, compression, inclination, bending and other dynamic distortion behaviors of rotor wakes during large maneuvering flight, and give transient induced velocity distribution of rotor wake in the rotor disk or any area of the space. The thrust and pitch angular velocity ramping up conditions of a hovering rotor are chosen to verify the correctness and timeliness of the proposed model by comparison with wake distortion augmented Pitt-Peters dynamic inflow model, and some new conclusions are presented.