Prakash, Raghu V and Sunder, R (1993) Fatigue Life Under Random Load History Derived From Exceedance Curves Using Different Algorithms. In: Fatigue & Fracture of Engineering Materials & Structures, 16 (7). pp. 707-721.Full text not available from this repository. (Request a copy)
Low cycle fatigue life and crack growth rates were analysis established for random load sequences, generated from three combat aircraft load exceedance curves using different algorithms, including simulated rain-flow cycle count,extreme-to-extreme excursions, upper to lower bound excursions and unrestricted peak-trough excursions. Also, the response of a fatigue meter to a random load sequence was simulated. Fatigue damage for the different load histories was computed using material constants for an Al-Cu alloy. Computed fatigue damage was relatively insensitive to the algorithm used for load sequence generation from combat aircraft load exceedance curves. Fatigue meter data based damage estimates were, however,sometimes unconservative.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to John Wiley & Sons, Inc.|
|Department/Centre:||Division of Mechanical Sciences > Mechanical Engineering|
|Date Deposited:||08 Jul 2008|
|Last Modified:||27 Aug 2008 13:33|
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