Real-Time Methods for Adaptive Suppression of Adverse Aeroservoelastic Dynamics

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$649,949.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
NNX11CA31C
Award Id:
n/a
Agency Tracking Number:
094763
Solicitation Year:
2009
Solicitation Topic Code:
A1.07
Solicitation Number:
n/a
Small Business Information
CA, Hawthorne, CA, 90250-7083
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
028281020
Principal Investigator:
Brian Danowsky
Principal Investigator
(310) 679-2281
bdanowsky@systemstech.com
Business Contact:
Suzie Fosmore
Contracts Administrator
(310) 679-2281
suzie@systemstech.com
Research Institution:
Stub




Abstract
Adverse aeroservoelastic interaction is a problem on aircraft of all types causing repeated loading, enhanced fatigue, undesirable oscillations and catastrophic flutter. Traditionally, to suppress adverse aeroservoelastic interaction, notch and/or roll off filters are used in the primary flight control system architecture. This solution has pitfalls; rigid body performance is degraded due to resulting phase penalty and it is not robust to off nominal behavior. In Phase I, an approach was developed that is entitled, Modal Isolation and Damping for Adaptive Aeroservoelastic Suppression (MIDAAS). This adaptive technique determines an optimal blend of multiple outputs that effectively isolates a problematic lightly damped mode and simultaneously determines an optimal blend of multiple inputs to suppress the problematic mode via feedback. Adverse effects on aircraft rigid body performance are minimized, resulting in virtually no phase penalty. MIDAAS was validated against aeroservoelastic F/A-18C aircraft models with varying stores configurations and demonstrated very successful performance. In the proposed Phase II program, a robust real-time adaptive aeroservoelastic suppression solution will be developed with a buildup approach that includes further MIDAAS enhancements, extensive validation studies utilizing a high-fidelity CFD-based aeroelastic model of the NASA X-53 aircraft, and extensive validation studies utilizing real-time pilot in the loop simulation capability.

* information listed above is at the time of submission.

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