In this work we are concerned with advanced progressive damage analysis of laminated fiber-reinforced composites structures and address the problem of design of a composite wing leading edge capable of resisting a bird impact scenario according to FAR regulations. This is a complex task since study of damage leading to failure is dependent on a range of parameters including geometry, material, lay up, loading conditions, load history and failure modes. The proposed approach try to unify the modeling of in-plane distributed damage such as transverse matrix cracking, with out-of-plane damage such as delamination. This requires the implementation of VUMAT and WINTER subroutines in ABAQUS. Different analysis algorithms including pure Lagrangian, ALE and the coupled Eulerian- Lagrangian approach are then utilized to assess the capability of ABAQUS/explicit as an advanced composite design tool. The problem of secondary debris bird impact is considered as good candidate of typical problems encountered in aircraft design and certification process where post impact debris distribution and kinetic energy must be known accurately in order to establish their potential harmfulness to surrounding fragile structures. Due very large deformation and fragmentation involved in the process, the application of a messhless based method such as SPH is more suitable and is applied successfully.
Assessment of impact response of composite aircraft structures under high velocity loading
Einschätzung der Stossbelastung von Compositwerkstoffen für dieLuftfahrt unter Hochgeschwindigkeitsbelastung
2009
17 Seiten, 19 Bilder, 1 Tabelle, 11 Quellen
Conference paper
English
Simulation methodology for high velocity impact in composite aircraft structures
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