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장기 운영 항공기 주익 구조물의 응력스펙트럼 및 피로수명 추정에 관한 연구
강기원(Ki-Weon Kang),고승기(Seung-Ki Koh),최동수(Dong-Soo Choi),심기중(Ki-Joung Shim) 대한기계학회 2009 대한기계학회 춘추학술대회 Vol.2009 No.11
Aged Aircraft has the several cracks due to the long-term service and these cracks deteriorate the safety and the rate of operation. To solve this, the crack propagation analysis for flight critical location is of utmost required. maneuver. It is, however, almost impossible to obtain the stress spectrum, which is crucial for the crack propagation analysis, at the FCLs of aged aircraft wing structure. In this study, to analyze the fatigue crack propagation behavior at FCL in aged aircraft, firstly the finite element analysis is performed for the 3D geometry model of wing assembly, which is obtained using CATIA from the paper drawings. And then, transfer function and stress-spectrum at FCL are derived from based on the limited load factor data and the FEA results. Finally, crack propagation rates at the FCL are analyzed using the commercial code, NASGRO.