Description: We propose the demonstration of a novel aeroservoelastic scaled model design, optimization, and fabrication approach combining aeroservoelastic scaling with a combined topology/sizing optimization to match the target structural dynamic and aeroelastic behavior. Fabrication is using 3D printing techniques (metal and plastic/elastomer), along with automated electronic assembly techniques for in-situ instrumentation. A scaled model will be designed, fabricated, and tested in a low speed wind tunnel during Phase I to demonstrate the feasibility of dramatically reducing the cost of aeroservoelastic model tests.

Benefits: Applies to all NASA aircraft and aviation technology development programs, including subsonic, supersonic, and hypersonic vehicles.

Applies to wind tunnel and flight test validation of aeroelastic and aeroservoelastic behavior, which is relevant to any new aircraft development program.