Weight investigation is carried out on a novel airplane wing layout configuration where the two wings are split and staggered along the fuselage. This special layout excludes the need of horizontal tails by using the aft wing control surfaces for pitch control. Finite element analyses are carried out to investigate stress, deformation and buckling characteristics. As a comparison, a baseline finite element model is built with conventional wing layout beside the split-wing finite element model. Key failure modes are identified and causes are investigated. Besides finite element analysis, analytical methods are also explored to enable parametric trade studies.
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