Spectrum Loading Test of the C-130E Main and Nose Landing Gear Assembly.

摘要

The report presents the results of an experimental stress analysis to first determine the critical fatigue areas, and then to evaluate the fatigue damage level caused by application of the C-130E aircraft main and nose landing gear load spectrum. Critical stress locations were determined by performing a photoelastic coating analysis of the gear specimens using a series of simulated aircraft loads selected from the load spectra. After high stress areas were established rosette strain gages were affixed to those locations deemed critical and a complete load/test spectrum was conducted. The strategic points from both the main and nose landing gears were analyzed.