A Study for Damage Mode of Composite Aircraft Structure with Advanced Composite Materials

Abstract

More and more advanced composite materials are used in mainly supporting structure of civil aviation; its airworthiness safety should be the focus of the research. Damage assessment is the key step in the general composite repair procedure. In this paper, the ANSYS calculating method is validated on the basis of classic laminate theory which could be used to calculate composite strength. In one case, it is applied to simulation and modeling of the B767 landing gear door. The case shows that composite damage mode such as low velocity impact damage, curing and fatigue could be evaluated with finite element method, the result of evaluation is provided as a means to composite damage assessment. Thereafter, the finite element method can be used for structural health monitoring to advanced composites.