Print Email Facebook Twitter Flight simulation fatigue crack propagation in single and double element lugs Title Flight simulation fatigue crack propagation in single and double element lugs Author Wanhill, R.J.H. Jongebreur, A.A. Morgan, E. Moolhuijsen, E.J. Institution National Aerospace Laboratory NLR Date 1981-10-31 Abstract Flight simulation fatigue crack propagation tests on single and double element lugs made from 2024-T351 and TOT5-TT351 aluminium alloys and Ti-6AJ.-UV titanium alloy were carried out. Initial damage was a throughthickness notch at one side of each hole in one element. Results showed that crack propagation lives for double element lugs were much longer than the lives for single element lugs, and that the choice of loading sequence greatly influenced the life. The significance of the results for selection of design concepts and materials and for fatigue evaluation is discussed Subject crack propagationaluminum alloystitanium alloysdamage toleranceflight simulationfatigue materialslugsgust loads To reference this document use: http://resolver.tudelft.nl/uuid:6ad26946-c042-4093-853f-bb043b987938 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR MP 80023 U Part of collection Aerospace Engineering Reports Document type report Rights (c)1981 National Aerospace Laboratory NLR Files PDF 80023.pdf 8.15 MB Close viewer /islandora/object/uuid:6ad26946-c042-4093-853f-bb043b987938/datastream/OBJ/view