Author(s)

S. Heimbs, H. Lang & T. Havar

Abstract

This paper describes the numerical investigation of the mechanical behaviour of a structural component of an aircraft wing flap support impacted by a wheel rim fragment. A simulation model of the support link made of composite materials was developed, incorporating intralaminar and interlaminar failure modes. Validation studies were performed using quasi-static and low velocity impact test data. Finally, high velocity impact simulations with a metallic rim fragment were performed for several load cases involving different angles, impactor rotation and pre-stress. Keywords: high velocity impact, composites, flap support, rim release, FEM.

Keywords

high velocity impact, composites, flap support, rim release, FEM