The shipboard helicopter is in a harsh environment and its rotor tip is prone to over-swing and collision with the body. The research on the aeroelastic response on the ship surface of the helicopter can prevent such accidents. In this paper, CFD method is used to obtain the data of ship flow field. Combining with blade dynamic model, a comprehensive calculation and analysis method of rotor aeroelastic response is proposed and the aeroelastic response of the rotor under different inflow speed, hovering position and wind direction is studied. The results show that the method used in this paper is correct. The maximum response of rotor tip increases with the increase of ship inflow speed. When the speed changes from 20m/s to 40m/s, the response amplitude increases by 8.35%; The hovering position mainly affects the distribution of tip displacement response along the azimuth angle of the rotor disc. The change of inflow wind direction angle significantly affects the aeroelastic response of the rotor. The maximum flapping displacement of the blade tip is related to the vertical velocity distribution of the ship"s wake flow field. The greater the change gradient, the greater the maximum flapping of the blade tip.