Maintaining the structural integrity of aircraft depends on the initial definition of an inspection program to detect structural damage that may occur in service. Prediction of possible fatigue damage due to the applied loads and conditions of use encountered in service is based on an analysis of the probability of incipient cracks and on an evaluation of the development of undetectable faults assumed to exist between two inspections. The validity of evaluation models is generally demonstrated based on comparisons with results obtained on elementary test pieces subjected to predicted local load conditions in service and used to identify the influence of events such as rare overloads or frequent repetitive small loads. This paper presents the principles for processing in flight signals collected in order to predict structural damage by making in flight integrated calculations, considering influences such as: load signals precision (frequency of points taken); elimination of low amplitude variations; and cycle counting methods for the damage calculation.
Assessment of in-Service Aircraft Fatigue Monitoring Process
1994
8 pages
Report
Keine Angabe
Englisch
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