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- W3184404120 abstract "This paper aims to optimize the full blended wing body aircraft structure with buckling constraints to get a better estimation of its structural weight. A structural model of the NASA Hybrid Wing Body primary structure was created, with the centerbody consisting of thin cabin walls reinforced through grid stiffeners and frames. Known secondary and non-structural weights are determined through empirical equations while a conservative estimate was applied for the uncertainty in the centerbody secondary weight. The stress and their sensitivities were computed with Nastran and a localized buckling method was used to calculate the buckling strength of the structural panels. Using only conventional aircraft alloys, the optimized structure achieved an OEW/MTOW ratio of 47% (similar to current airliners), indicating that the BWB can still be feasible despite its inefficient cabin structure." @default.
- W3184404120 created "2021-08-02" @default.
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- W3184404120 date "2021-07-28" @default.
- W3184404120 modified "2023-10-16" @default.
- W3184404120 title "Structural Optimization of Blended Wing Body Transport Aircraft With Buckling Constraints" @default.
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- W3184404120 doi "https://doi.org/10.2514/6.2021-3022" @default.
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