Aspects of Damage Tolerance and Fatigue of CFRP Structural Components

Burger, Uli; Rochat, Ludovic

doi:10.1007/978-3-319-17999-5_14

Cited by 1 publication

(2 citation statements)

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“…The LCC approach to design looks at the total cost of design options by examining all of the factors that affect an airplane over its lifetime. 85 Military aircraft as the Lockheed Martin F-22 and F-35 have more than 30% by weight of aircraft structure made of composites. According to Hale, 82 reduced risk of corrosion and fatigue associated with composites combined with the composite repair techniques will lower overall maintenance costs and increase availability of these planes.…”

Section: Effect Of Scatter On Life Estimationmentioning

confidence: 99%

“…Outof-plane loads and low velocity impacts may create hard to detect while affecting the load-carrying capacity. 85 Military aircraft as the Lockheed Martin F-22 and F-35 have more than 30% by weight of aircraft structure made of composites. The trend for increase in usage of composites raises the question of the appropriateness of current aircraft structural integrity methodologies for application to these structures.…”

Section: Effect Of Scatter On Life Estimationmentioning

confidence: 99%

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An overview of fatigue in aircraft structures

Tavares

Castro

2017

Fatigue Fract Eng Mat Struct

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From safe‐life to fail‐safe and damage‐tolerance approaches, the last one emerged as the main design philosophy for aerostructures, allowing weight savings and at the same time increasing reliability and structural integrity in the presence of damages which may have occurred during the manufacturing process or during service. The application of damage‐tolerance philosophy requires extensive know‐how of the fatigue and fracture properties, corrosion strength, potential failure modes and non‐destructive inspection techniques, particularly minimum detectable defect and inspection intervals. To face scatter in material properties, conservative approaches considering the worst scenario or statistical methods dealing with the variability of material have been employed in the fatigue assessment of structures. The fatigue life estimation can display substantial variability, illustrating the need for a probabilistic assessment in practical applications. As an example, the variation in the fatigue life for the common scenario of a through crack in an Al alloy plate was evaluated taking into account scatter of properties. The 2010 FAA rule establishing a limit of validity (LOV) puts a bound in the indefinite operational life allowed for by earlier regulations. This requirement, together with the diminishing role of aluminium in airframes, will certainly shape the directions of fatigue, fracture and damage mechanics research in years to come, expanding the knowledge base upon which substantiation of LOV values is made, and ensuring safety under sustainable conditions.

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Section: Effect Of Scatter On Life Estimationmentioning

confidence: 99%

Section: Effect Of Scatter On Life Estimationmentioning

confidence: 99%