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Novel Aeroservoelastic Scaled Model Design, Fabrication, and Testing

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC20C0019
Agency Tracking Number: 186203
Amount: $749,342.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: T15
Solicitation Number: STTR_18_P2
Solicitation Year: 2018
Award Year: 2020
Award Start Date (Proposal Award Date): 2019-12-20
Award End Date (Contract End Date): 2021-12-19
Small Business Information
4020 Long Beach Boulevard
Long Beach, CA 90807-2683
United States
DUNS: 133626544
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: No
Principal Investigator
 Myles Baker
 (562) 305-3391
Business Contact
 Michelle Darlington
Phone: (562) 735-0421
Research Institution
 University of Washington
4333 Brooklyn Ave NE, Box 359472
Seattle, WA 98195-9472
United States

 Federally Funded R&D Center (FFRDC)

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.nbsp; 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.nbsp; This allows novel sensing and control approaches such as trim shape control, induced drag tailoring, flutter suppression, and load alleviation to be accomplished.nbsp; In Phase II we will demonstrate this technology in a subscale flight demonstration, raising the TRL of the technology to 8 or perhaps 9.nbsp; 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.

* Information listed above is at the time of submission. *

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