In order to study the impact damage of helicopter rotor blade under maneuvering condition, in the numerical simulation, the effects of the pulling force, swing moment and shimmy moment of the blade on the impact damage were considered previous. For the rotor blade of a certain type of aircraft, the full - size finite element model was used to simulate the impact.First the profile characteristics of the rotor blade were calculated by using the Fortran program and VABS software. After that, the load analysis model of elastic blade structure was established and the software CAMRIDII was used to calculate the blade load in the state of mobility. On this basis, NASTRAN software was used to conduct transient analysis on the the blade, and the prestress state of the blade under load was simulated. Then DYTRAN software was used to simulate the damage caused by the blade bounce based on the adaptive contact method. The research shows that the damage condition of the blade is non-linear with the impact velocity. In addition to the bullet point, the surrounding structure will also be damaged when the projectile hits. The stiffness matching between the structural parts should be considered in the design of the impeller to achieve the best impact energy absorption effect and the minimum damage area.