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Sökning: WFRF:(Lundgren J) > Mittuniversitetet

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1.
  • Ginnarsson, K., et al. (författare)
  • Equilibrium and nonequilibrium magnetic behaviour of a reentrant Ising spin glass.
  • 1992
  • Ingår i: Journal of Magnetism and Magnetic Materials. - : Elsevier BV. - 0304-8853 .- 1873-4766. ; 104-107:3, s. 1607-1608
  • Tidskriftsartikel (refereegranskat)abstract
    • The reentrant Ising spin glass Fe0.62Mn0.38TiO3 has been investigated using SQUID magnetometry. The system is antiferromagnetic below TN(H = 0) = 33 K, and enters a mixed antiferromagnetic/spin glass phase below Tg(H = 0) = 25.8 K. Within the concept of a recent mean field model, a ratio TN(0)/Tg(0) close to unity indicates both intra- and interlayer frustration. The existence of an overlap length, lΔT, below which equilibrium spin correlations at temperatures T and T + ΔT are indistinguishable has been verified by magnetic relaxation experiments on this spin glass system
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2.
  • Kapidzic, Z., et al. (författare)
  • Incremental fatigue damage model : Application to plane problems with non-proportional loading
  • 2022
  • Ingår i: ICAS PROCEEDINGS 33th Congress of the International Council of the Aeronautical Sciences Stockholm, Sweden. - : international council of the aeronautical sciences.
  • Konferensbidrag (refereegranskat)abstract
    • Modern airframe aluminum structures are increasingly manufactured in large and complex integral parts. Suchparts are often exposed to in–plane, non–proportional loading and contain stress–raisers with complex geometry. Conventional methods, based on the stress concentration factor and cycle counting, are unsuitable forassessment of this type of problem. We present a fatigue damage model, based on the concept of movingendurance surface and incremental damage evolution. The fatigue damage is entirely dependent on the localstress history and the notch effect is accounted for by introduction of the relative stress gradient. Also, wepresent an automated and efficient implementation of the model, for the purpose of computing fatigue damageat stress raisers in plane problems with non–proportional loading. We demonstrate the implementation by anexample of a fatigue calculation in an aircraft frame.
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