Abstract
This paper develops a framework of dynamic simulation driven fatigue life analysis of a landing probe system for a typical 12-ton tricycle landing gear helicopter for embarked operations on the typical frigate. By integrating a novel dynamic helicopter/ship interface simulation with the rainflow cycle counting method, fatigue spectra, including all possible probe load cases under the wide range of operating and environmental conditions, have been developed with a confidence level of greater than 99.9%: otherwise, they would be practically unobtainable, even by limited sea trial testing. Furthermore, the fatigue stresses of the probe assembly were obtained by the finite element method, and the cumulative fatigue damage analyses were conducted by monitoring the fatigue life of the critical locations on each component of the probe assembly using the Palmgren-Miner rule against the design life requirement. This new approach provides an innovative and efficient design tool, through virtual prototyping, that can speed up the design process and reduce cost.
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