This project deals with the fatigue analysis of aircraft composite fuselage,it will be designed t... more This project deals with the fatigue analysis of aircraft composite fuselage,it will be designed to have optimal structural weight with the required safety margins. The structural stress, deflection, strain, and margins of safety distributions are to be visualized and the design is to be improved. The elasticity, stiffness, strength and stress distribution is more in the nodes of the structure. Where the fuselage frame is semimonocoque in construction holding former and skin.In the semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurization and is strengthen using frames and stringers. When coming to the material section, the Aluminum alloy material are mostly used, but as metal designs have reached a high degree of perfection, extraordinary weight and cost savings are unlikely in the future. The carbon fiber composites have high strength to weight ratio when compared to aluminum alloy. The fuselage structure of aircraft is modeled using CATIA software. The original model is imported to ANSYS and the fatigue analysis is carried out. The applicability of the proposed procedure was demonstrated. Based on finite element analyses. The main objective analysis is importing composites in fuselage is merely considered applied and compared with aluminum. These comparison asses the weight reduction and fatigue life obtained with the use of composite materials for designing.
This project deals with the fatigue analysis of aircraft composite fuselage,it will be designed t... more This project deals with the fatigue analysis of aircraft composite fuselage,it will be designed to have optimal structural weight with the required safety margins. The structural stress, deflection, strain, and margins of safety distributions are to be visualized and the design is to be improved. The elasticity, stiffness, strength and stress distribution is more in the nodes of the structure. Where the fuselage frame is semimonocoque in construction holding former and skin.In the semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurization and is strengthen using frames and stringers. When coming to the material section, the Aluminum alloy material are mostly used, but as metal designs have reached a high degree of perfection, extraordinary weight and cost savings are unlikely in the future. The carbon fiber composites have high strength to weight ratio when compared to aluminum alloy. The fuselage structure of aircraft is modeled using CATIA software. The original model is imported to ANSYS and the fatigue analysis is carried out. The applicability of the proposed procedure was demonstrated. Based on finite element analyses. The main objective analysis is importing composites in fuselage is merely considered applied and compared with aluminum. These comparison asses the weight reduction and fatigue life obtained with the use of composite materials for designing.
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