Abstract:
The finite element model is developed for simulating the bird strike test of rotorcraft End plate using the bird numerical modeling techniques. The main design goal is the satisfactory impact resistance of the composite structures in the case of bird strike. The design concept is based on the absorption of the major portion of the bird kinetic energy by the composite skins, in order to protect the inner honeycomb core from damage, thus preserving the End plate functionality for safe landing. To this purpose, the End plate skin is fabricated from composite layers, which unfold under the impact load and increase the energy absorption capability. The numerical modelling of bird strike using the Lagrangian approach and Smooth Particle Hydrodynamics formulation and the critical design parameters are considered in carrying out the analysis. A numerical model of this problem has been developed with an explicit finite element code Autodyn. Analysis is carried out for the developed model using the test parameters. Numerical results by means of bird modelling approaches are substantiated with experimental test results. The results obtained from the analysis and test shows close conformity implying their appropriateness in the simulation of bird strike.