Aviation rules mandate the need for an aircraft structure to meet damage tolerance requirements. The damages structure must maintain adequate residual strength in order to maintain its interity and this is accomplished throuh a continuous inspection programm. The multifold objective of this work is to present a methodology basesd on a direct Monte Carlo simulation (MCS) process to assess the reliability of aircraft structure. Initially, the structure is modeled as a parallel system with active redundancy comprised of elements with uncorrelated strengths. Closed form expressions for the system capacity cumulative distribution function are expanded from three elements in the current literature up to six elements. The second objective is to compute the probability of failure of a fuselage skip lap joint under static load conditions by examining the residual strenght of the fasteners when subjection to various load distributions initally and following subsequent fastener sequentil failures. The last objectove os to present a MCS methodolody for computing the non-preriodoc inspections required in order to maintain a prescribed minimum reliability level.
Monte Carlo simulation methodology for the reliability of aircraft structures: Reliability of aircraft structures under damage tolerance requirements
2008
159 Seiten, Bilder, Tabellen, 64 Quellen
Theses
English
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