Study on Fatigue Life Estimation for Aircraft Engine Support Structure

항공기 엔진 지지구조물의 피로수명 해석에 관한 연구

  • Hur, Jang-Wook (KHP PMO, Defense Acquisition Program Administration)
  • Received : 2010.05.31
  • Accepted : 2010.09.04
  • Published : 2010.11.01


The fatigue life is estimated while determining the reliability of aircraft structures. In this study, the estimation of fatigue life was carried out on the basis of a cumulative damage theory; the working S-N curve and the equivalent stress on the engine support structure significantly affect the safety of the aircraft. The maximum stress observed was 1,080 MPa in the case of scissors link under crash load condition, and there was a 5% margin for the allowable stress corresponding to the temperature reduction factor. The maximum stress was 876 MPa, and the stress equation coefficient had a maximum value of 0.019 MPa/N in the case of scissors link under fatigue loads. In the results of the fatigue life analysis, the safety life in a fretting area of scissors link upper part was 416,667 flight hour, and other parts showed to infinite life. Therefore, it was demonstrated that the fatigue life requirement of aircraft engine support structure (scissors link, straight link) could be satisfied.


Fatigue Life Analysis;Engine Support Structure;Minor's Rule;Cumulative Damage;Safety Life


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