This paper proposes a dynamic landing simulation method for helicopters， considering the effects of ship wake， atmospheric turbulence， and ship motion， as well as the ground effect between the rotor and the deck， on the control quantities and attitude during the dynamic landing process of helicopters. Firstly， a dynamics model of the helicopter affected by the ship’s wake and atmospheric turbulence is established and its trim and dynamic response are verified. Secondly， based on the principle of differential flatness， the dynamic landing process of the helicopter is transformed into a trajectory generation problem， and a reasonable and feasible dynamic trajectory for the helicopter’s dynamic landing is obtained. Then， a helicopter dynamic landing control law based on nonlinear dynamic inversion is designed. This control law is based on a two-layer progressive control architecture， combining the advantages of good decoupling and rapid response of nonlinear dynamic inversion， with the characteristics of smooth trajectory generation path and easy tracking. Finally， dynamic landing simulations are carried out with the UH-60 helicopter and SFS2 frigate as examples， and the simulation results under two conditions， with and without wind field， are compared. The results show that the adopted trajectory generation method can be updated quickly and meet the real-time requirements of helicopter dynamic landing. The designed control law can effectively improve the landing accuracy and resist wind field interference. The proposed helicopter dynamic landing method can effectively capture the influence of the stern current of the ship on the helicopter model， and effectively simulate the time history of the helicopter handling quantity and motion during the dynamic landing process of the helicopter.