During modification aircraft structure is possible as new critical areas in redesigned structure parts, so too new spectrum aircraft applying, as a consequence - new load spectrum for initial structure parts. For compliance with airworthiness requirements, from the fatigue point of view, proposing to use bunch of final element analyses (linear static) together with engineer-analytical analyses. Effective stress concentration to have estimate through design, analyses, fatigue test of “design-like” samples with typical for this aircraft joints (bolts, rivets). The estimation of maintenance conditions aircrafts with redesigned structure concerning variable loads can perform by applying “Load Monitoring System” (LMS), based on FDR (Flight Data Recorder) information or special system.
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