Fatigue Crack Growth prediction on A310 aircraft wing using static analysis

摘要

Non Destructive Testing (NDT) has been used in aviation industry to predict remaining useful life (RUL) of aerospace structures. RUL knowledge enables aircraft maintenance managers to plan repair/replacement actions well in time thereby making flight operation safe with reduced downtimes. Different Model-based, Stochastic-based and Data-based models are used for prognostics and remaining useful life (RUL) prediction [1]. In the aircraft lifespan, stresses are mainly originated during landing and take-off phases. Due to these stresses, the surface of an aircraft structure undergoes deformation, which leads to crack initiation and subsequent crack growth [2]. The objective of the proposed research work is to predict the remaining useful life of A310 wing using linear elastic fracture mechanics based technique known as Paris Law. Paris Law offers the rate of damage growth with respect to number of loading cycles as each loading cycle comprises of take-off, cruise and landing phases. Stresses subjected to aircraft wings during each loading cycle are required for RUL prediction using Paris law. These stresses are evaluated using finite element analysis of A310 aircraft wing. Actual historical NDT data of crack growth on counter-sunk rivet holes on A310 wing acquired from PIA NDT center is used to show the efficacy of the proposed RUL prediction methodology. The details of modeling and results will be presented in the conference.