A method to assess reliability and life of selected aircraft components suffering from cumulative effect of destructive processes – an outline
There are two main directions to be distinguished while investigating into the wear-and-tear processes going on within the aircraft’s structural components throughout the operational phase. The first one covers the efforts to explain the physics of the wear-and-tear processes whereas the second one has been intended to generate mathematical models that describe the way how the effects of the wear-and-tear processes accumulate and provoke changes in values of diagnostic parameters. This paper represents the second line of interest and covers the model that formalises the process of the accumulation of effects of the aircraft component’s wear-and-tear up to the moment the permissible boundary condition is reached. What has been used in the below-presented model is the distribution of time of the aircraft structure in service up to the moment the diagnostic parameter reaches the boundary condition. Finally, a numerical example has been presented.