Abstract
Fatigue is an important design aspect, especially for the large number of geometrical notches in aircraft structures. The amount of flight cycles needed for a fatigue crack to grow from a detectable length to the critical length determines the maintenance inspection intervals, whereas the initiation life determines the threshold and start of frequent inspections. The longer the fatigue life of a cracked structure, the larger the inspection intervals can be, which reduces maintenance costs. Glare has excellent fatigue crack growth characteristics due to its laminated composition. In this chapter the fatigue mechanisms in Glare will be highlighted.
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© 2001 Springer Science+Business Media Dordrecht
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Alderliesten, R.C. (2001). Fatigue. In: Vlot, A., Gunnink, J.W. (eds) Fibre Metal Laminates. Springer, Dordrecht. https://doi.org/10.1007/978-94-010-0995-9_11
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DOI: https://doi.org/10.1007/978-94-010-0995-9_11
Publisher Name: Springer, Dordrecht
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