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Computational Schemes for Integrity Analyses of Fuselage Panels in Aging Airplanes

1991; Springer Nature; Linguagem: Inglês

10.1007/978-3-642-84364-8_2

1431-8547

Satya N. Atluri, Pin Tong,

Mechanical Behavior of Composites

This paper reviews some simplified computational strategies for the integrity analyses of fuselage panels in aging airplanes. The topics covered include: (i) a “direct stiffness” method for stiffened panels (with fastener flexibility being accounted for) with multiple cracks, using the alternating technique, (ii) MSD near a row of fastener holes, (iii) analysis of cracks with bonded repair patches, (iv) weight functions for multiple cracks, and (v) bulging near crack-tips in pressurized fuselages, and equivalent domain integral methods for computing fracture parameters for bulged cracks.