Abstract:

A formula in terms of DFR value to describe the relationship between the fatigue properties of aircraft structure and the corrosion time was presented. The viewpoint of the same corrosion damage corresponding with the same fatigue property was clarified. A corrosion equivalent law in terms of the fatigue strength normalization was presented clearly. And the corrosion equivalent relationships of the aluminum alloy specimens exposed to the four typical service environments during grounding versus the accelerated simulation environment in laboratory were established.

Key words: aircraft structures, corrosion, fatigue properties, typical service environments, accelerated simulation environment, corrosion equivalent relationships