Print Email Facebook Twitter Damage tolerance of stiffened-skin structures: prediction and experimental verification Title Damage tolerance of stiffened-skin structures: prediction and experimental verification Author Vlieger, H. Institution National Aerospace Laboratory NLR Date 1986-06-11 Abstract Some consequences of application of the current damage tolerance airworthiness requirements for transport aircraft in designing stiffened-skin structures to be safe under all operational load conditions are discussed. Compliance with these requirements may be shown by analysis supported by test evidence. To provide the designer with analytical tools to demonstrate that design meets the required residual strength and crack propagation properties a number of computer routines were developed by the NLR. The principles underlying the calculation procedures used in these computer programs to predict the residual strength of stiffened panels with a skin of ductile material (like 2024) are included. Applications of these programs to some practical stiffened skin structures are presented together with analysis test correlations. Subject Stress intensity factorsCrack arrestCrack tipsStiffeningDamage assessmentComputer programsFail-safe systemsAircraft structuresSkin (structural member)Residual strengthFatigue (materials)Aircraft maintenanceInspectionCrack closureAiivorthiness requirements To reference this document use: http://resolver.tudelft.nl/uuid:e2b04b66-7638-4854-814f-d7ac31d8c2f8 Publisher Nationaal lucht- en ruimtevaartlaboratorium Access restriction Campus only Source NLR MP 86041 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1986 National Aerospace Laboratory NLR Files PDF 86041.pdf 44.42 MB Close viewer /islandora/object/uuid:e2b04b66-7638-4854-814f-d7ac31d8c2f8/datastream/OBJ/view