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本帖最后由 wdhd 于 2016-8-3 09:55 编辑
Abstract
Random vibration high-cycle fatigue problems are of paramount concern to the U.S. Air Force. Therefore, the Air Force is interested in available methods, used to approximate the fatigue life of aircraft structures exposed to random vibration loading. The purpose of this investigation was to examine and compare the fatigue life estimates of a fully clamped aluminum plate, under the influence of random electrodynamic shaker loading. The experimental probability density function (PDF) was generated using the rainflow cycle counting technique, and the resulting fatigue estimates were compared with spectral based, finite element analysis (FEA) and experimental random response fatigue estimates.
12 The plate was modeled using both
ABAQUS® and a nonlinear FEA code developed by Mei et al of Old Dominion University. 3 4 For all scenarios, the Palmgren-Miner damage accumulation model was utilized.
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