Coupled micromechanics-finite element Progressive Failure Dynamic Analysis approach: F-16 canopy case study

This work presents a numerical approach for predicting damage evolution in aerospace structures subject to impact through the use of an explicit finite element code coupled with a micromechanics damage analysis module. Soft body impact, in the form of bird strike on an F- 16 canopy, is simulated using this Progressive Failure Dynamic Analysis (PFDA) approach. First, bird impact on a canopy is studied for three finite element modeling approaches: (1) Lagrangian, (2) Arbitrary Lagrangian-Eulerian, and (3) Smoothed Particle Hydrodynamics. From these results, one method is chosen for incorporation into the PFDA methodology. Validation of results is performed by comparing against test data for the canopy deformation versus time and canopy failure at different bird impact velocities. The completed methodology clearly identifies impact failure mechanisms and their percent contribution to the multisite structural failure in order to guide aerospace design efforts.