Abstract
An integrated design process for generating high fidelity analytical weight estimations of joined-wing concepts is described. Elements of configuration, structures, aerodynamics and aeroelastic analyses are incorporated. Drag and loads are modeled for sizing fuel and structures to meet range and loiter requirements. The joined-wing is a radical departure from the world's inventory of vehicles. We are motivated because the joined-wing concept may offer weight savings where structural stiffness is a design constraint. Two crucial non-linear phonomena contribute to structural failure: large deformation aerodynamics and geometric non-linear structures. A correct model of the non-linear aeroelastic model offers the possibility of a successful design that leverages these non-linear effects to the benefit of joined-wing designs.
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