Abstract
Composite materials have many advantages in macro materials and nanomaterials. The strength of composite material is fully based on the orientation of ply. This research deals with the pressurized inner wing. Such design of the wing and fuselage remains a significant challenge for Flying Wing aircraft. Since the inner wing is nearly rectangular, it is relatively inefficient to resist the pressure loads by bending that consequently brings weight penalty. The wing structure was evaluated by using carbon fibre material at different orientations on fabric. To reduce this weight penalty of the wing, the internal multi-shell structure was combined to form a boxed multi bubble section configuration. The novel section was modelled and the structural properties were evaluated.
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