Abstract
Aerodynamic shape optimization is a valuable tool for aircraft design, but geometric constraints have had limited design freedom or have failed to capture spatial integration requirements in sufficient detail. Using a detailed representation of an aircraft’s systems and payload geometries in a packaging constraint allows for more accurate and higher-performance spatial integration. We use a previously developed general and differentible packaging constraint formulated for gradient-based optimization for aerodynamic shape optimization of a full aircraft configuration. We explore the design of the NASA tiltwing concept vehicle with aerodynamic shape optimization using packaging constraints to examine the tradeoffs between aerodynamics and mission performance. The resulting design can be more targeted to our design requirements than one that can be achieved with conventional geometric constraints.
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