Analysis and Development of Impact Resistant Light Weight Composite Aircraft Structure

Light weight aircraft structure is subject to impact from high speed debris resulting in many instances of damage to metallic wings. In addition to weight reduction, improved debris impact resistance was a primary goal of a recent Carbon Epoxy Reinforced Plastic (CFRP) wing re-design. Pursuant to this goal, non-linear, explicit finite element simulation methods were developed for the impact event and were qualified by comparison to observed field damage. The analysis methods were employed to develop a weight-optimized, damage-resistant design for CFRP wing leading edge, tip, and lower surface. These structures were fabricated and damage resistance was verified through risk reduction and qualification testing. Analytic methods and results and qualification results are presented herein.