NASA STTR 2018-II Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-2- T15.01-6203
PHASE 1 CONTRACT NUMBER:
 80NSSC18P2128
SUBTOPIC TITLE:
 Aircraft Design, Optimization, and Scaled Model Test
PROPOSAL TITLE:
 Novel Aeroservoelastic Scaled Model Design, Fabrication, and Testing
SMALL BUSINESS CONCERN (SBC):
M4 Engineering, Inc.
4020 Long Beach Boulevard
Long Beach CA  90807 - 2683
Phone: (562) 981-7797
RESEARCH INSTITUTION (RI):
University of Washington
4333 Brooklyn Ave NE, Box 359472
WA  98195 - 9472
Phone: (206) 543-4043

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Myles Baker
E-mail:
mbaker@m4-engineering.com
Address:
4020 Long Beach Boulevard Long Beach, CA 90807 - 2683
Phone:
(562) 305-3391

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Kevin Roughen
E-mail:
kroughen@m4-engineering.com
Address:
4020 Long Beach Boulevard Long Beach, CA 90807 - 2683
Phone:
(562) 981-7797
Estimated Technology Readiness Level (TRL) :
Begin: 6
End: 7
Technical Abstract (Limit 2000 characters, approximately 200 words)

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.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

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.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

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.

Duration: 24

Form Generated on 11/19/2019 09:04:07