Numerical Study on Damage Characteristics of Composite Propeller Under Blast Impact Load

The finite element program was used to establish a simulation model to simulate the dynamic response process of the composite propeller of the engine and the connected wing part under the explosion impact load. CONWEP equation of state was used in the model to simulate the explosion impact load. The failure of the composite propeller was controlled by unit removal in combination with the Tsai-Wu tensor strength theory in the VUMAT subroutine. To achieve impact damage of laminate. The damage effect of engine composite propeller under explosion load is analyzed and the dynamic response of composite propeller under different explosive charge and different distance is compared. It is concluded that the damage of composite propeller is more serious with the increase of incident overpressure. Under high incidence overpressure, the composite blade fails and deformates, the nearby skin structure festers, and can not continue to fly, which is severe damage. At this time, the peak incidence overpressure is 0.36 MPa. Under the medium incidence overpressure, the blade deforms greatly and the surrounding skin structure deforms and tears, which is moderate damage. At this time, the peak value of the incident overpressure corresponding to the skin is 0.08 MPa. The blade is slightly deformed under small incident overpressure, which has little effect on flight and is slightly damaged. The evaluation of the damage effect of anti-aircraft weapons on aircraft targets will help to grasp the damage ability of anti-aircraft munitions, improve and optimize the damage efficiency of anti-aircraft warheads, and also provide an important basis for improving the survivability of aircraft under ammunition attack.