Test and Simulation of Horizontal Tail Leading Edge Impacted by Bird

In this paper, the finite-element (FE) method combined with smoothed particle hydrodynamic (SPH) method is used to simulate the bird strike process, and a new type of tail leading edge structure is designed. This kind of bird is represented by the SPH model, and the structure is simulated by traditional Lagrangian elements. The design for the novel structure can be described as incorporating a triangular reinforcement component into traditional tail leading edge structure. Numerical simulations of bird strikes with the novel structure indicate that the anti-bird-strike capacity of the new type of tail leading edge is greatly enhanced. Then, the corresponding bird strike tests are carried out to verify the numerical simulation model. The simulation results are in good agreement with the test results, indicating that the SPH-FE coupling method gives a useful tool for predicting the deformation and damage behavior of aircraft structure under bird impact, and for the design of bird-strike-resistant structure. Finally, through bird strike simulation and test of the horizontal tail leading edge with the new design of commercial aircraft, it can be observed that the front beam does not penetrate, which indicates that the new design meets the requirements of the China Civil Aviation Regulations (CCAR) Part 25 on the certification of the bird strike resistance of the wing leading edge.


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  • Accession Number: 01851989
  • Record Type: Publication
  • Files: TRIS, ASCE
  • Created Date: Jul 21 2022 11:30AM