Novel Aeroservoelastic Scaled Model Design, Fabrication, and Testing

In Phase I we demonstrated the feasibility of a novel aeroservoelastic design approach for scaled model design, and demonstrated fabrication of the resulting designs as a ground test article. The test article from Phase I successfully replicated the scaled structural dynamic behavior, and demonstrated the integration of an instrumentation backbone based on PCB technology which allows integration of numerous sensors such as accelerometers, unsteady pressure sensors, and fiber optic strain sensors, along with the associated data acquisition, logging, and telemetry hardware. This allows novel sensing and control approaches such as trim shape control, induced drag tailoring, flutter suppression, and load alleviation to be accomplished. In Phase II we will demonstrate this technology in a subscale flight demonstration, raising the TRL of the technology to 8 or perhaps 9. This work will advance the state of the art by creating technology for rapid aeroelastic scaling of new designs to model level, rapid manufacturing of aeroelastic models (both wind tunnel and scaled flying models), and richer instrumentation and sensing that would lead to more insight and more useful information for the flight vehicle designer or flight test engineer regarding the aeroelastic characteristics of the new configurations in development. In the Phase II E program, we will utilize and further the development of the ASM dynamic scaling technology. Specifically, the scaling technology will be enhanced to support the application to the JetZero Ascent 12.5% scaled model pivot-piston landing gear. Next the technology will be utilized in the design of 12.5% scaled outboard wing model of the JetZero Ascent configuration. Lastly, we wil perform additional ground and flight testing of the ASM configuration to validate the methodology.

This technology is directly applicable to virtually all NASA air vehicles. The resulting scaling and model design and simulation capabilities will contribute to model design and simulation of scaled research UAVs for NASA or new small UAVs at full scale.. The resulting flight vehicle (and duplicates, if more funding would become available later) would allow NASA to test advanced sensing and actuation technologies on new configurations, including configurations where nonlinear structural dynamic effects become significant.

The resulting flight vehicle would allow NASA to test advanced sensing and actuation technologies on new configurations, including configurations where nonlinear structural dynamic effects become significant. In particular, we believe there is a good niche in the UAV market, where configuration are becoming more and more complex, and more and more players are entering the market.

This is a mature technology (TRL 8) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.