민간 항공기에 대한 손상허용해석

Damage Tolerance Analysis of a Commercial Aircraft Structure

The durability and damage tolerance life of aircraft structure is significantly different due to the fastener fit condition like clearance fit fastener(CFF) or interference fit fastener(IFF). these characteristics are not reflected enough in domestic industry, and therefore the structural design is not so efficient. In this study, the analysis for damage tolerance design is proposed to estimate the fatigue crack growth life around the fastener holes. Although most of the aircraft structures are designed as fail-safe structure(FSS) which has the significant benefit to extend the crack growth life, in domestic industry, FSS characteristics have been neglected for simple damage tolerance analysis. In this study, complicate damage tolerance analysis is introduced to account the FSS benefit for wing lower panel with stringers of the commercial aircraft.