| 초록 |
The present study evaluates and investigates the fatigue design and fatigue life as the crack propagation occurs around the fastener of the mainframe of the central fuselage (CTR) of a rotary-wing aircraft. For this work, the static and dynamic strain data were acquired according to flight conditions and fastening conditions between the mainframe and rail fitting (bracket). In order to improve the existing stress equation, the modified stress equation was proposed by taking into account all force components transferred from the operating rotor system. As a result, it showed that the predicted fatigue life (655 FHrs) was in a good agreement with the actual life (656.7 FHrs) of crack occurrence by using the modified stress equation respectively. |
