Abstract
An integrated process is presented that advances the design of an aeroelastic joined-wing concept by incorporating physics-based results at the system level. For instance, this process replaces empirical mass estimation with high-fidelity analytical mass estimations. Elements of nonlinear structures, aerodynamics, and aeroelastic analyses were incorporated with vehicle configuration design. This process represents a significantly complex application of aeroelastic structural optimization. Specific fuel consumption for a fixed lift-to-drag ratio was considered in the process for estimating fuel to size the structure to meet range and loiter requirements. This design process was implemented on a single configuration for which two crucial nonlinear phenomena contribute to structural failure: large deformation aerodynamics and geometrically nonlinear structures. A correct model of the nonlinear aeroelastic physics offers the possibility of a successful design. Unconventional features of a joined-wing concept are presented with the aid of this unique design model. Hopefully, insight derived from the nonlinear aeroelastic design might be leveraged to the benefit of future joined-wing designs.
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