An experimental study on fatigue safety life assessment of aircraft engine support structure

摘要

Correction may be needed on S-N curve using standard samples of structural material to secure its dependability when doing the design of the aircraft structure for fatigue load and its verification. In this paper, experimental methods are suggested with the purpose of correction of S-N curve of structural material samples. By application of the fatigue test results on static load and dynamic load that are placed on the structure of an aircraft in flight, we were able to come up with a mean S-N curve in consideration of the structural shape and load type on the structure. The mean S-N curve would then need to be additionally altered again into a working S-N curve which takes into account the operation temperature and a safety factor where an evaluation on safety life with respect to fatigue load can be made if design load spectrum is considered. Safety life against fatigue load in the upper part of the Scissors link, at the fretting is 27,394,283H, and other parts made out to be of infinite life, this turned out to be satisfying the design requirements for safety life of engine support structure of an aircraft.