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In aviation safety design, crashworthiness (crash-resistant) accidents are major concern. To overcome this concern, the protection of fuselage structure plays a key role by absorbing its energy. Current probabilistic research focuses on fuselage structure by considering stress–strain parameters through the drop test phenomenon. This study was performed by investigating airframe fall position through (varying) fuselage fall angle in vertical position. The replica design of the fuselage is modeled in SolidWorks software and then for simulation, fuselage model imported in Abacus software for drop test analysis. Simulated results show structural deformation when in contact with the rigid ground. However, due to impact (internal and strain) energies, high structural deformation has been observed under different collision load conditions. The collision condition evaluates with the variation for 4–6 s up to a maximum limit of 10 s. An optimized best stress–strain result is observed at a 15° angle in a vertical position under the stress of 480 MPa for struts, 401 MPa for the skin, and 482 MPa for the cargo frame sections.

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Probability-Based Analysis of Mg-based Aircraft Fuselage Section by Using Drop Test

  • 会议论文

  • 发表日期：

    2025年

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  • Sakshi Singh

摘要

In aviation safety design, crashworthiness (crash-resistant) accidents are major concern. To overcome this concern, the protection of fuselage structure plays a key role by absorbing its energy. Current probabilistic research focuses on fuselage structure by considering stress–strain parameters through the drop test phenomenon. This study was performed by investigating airframe fall position through (varying) fuselage fall angle in vertical position. The replica design of the fuselage is modeled in SolidWorks software and then for simulation, fuselage model imported in Abacus software for drop test analysis. Simulated results show structural deformation when in contact with the rigid ground. However, due to impact (internal and strain) energies, high structural deformation has been observed under different collision load conditions. The collision condition evaluates with the variation for 4–6 s up to a maximum limit of 10 s. An optimized best stress–strain result is observed at a 15° angle in a vertical position under the stress of 480 MPa for struts, 401 MPa for the skin, and 482 MPa for the cargo frame sections.