Adaptive Aeroservoelastic Suppression for Aircraft Upset and Damage Conditions

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,313.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CD60P
Agency Tracking Number:
104629
Solicitation Year:
2010
Solicitation Topic Code:
A1.07
Solicitation Number:
n/a
Small Business Information
Impact Technologies, LLC
NY, Rochester, NY, 14623-2893
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
073955507
Principal Investigator:
Michael Roemer
Principal Investigator
(585) 424-1990
mike.roemer@impact-tek.com
Business Contact:
Carol Marquardt
Business Official
(585) 424-1990
carol.marquardt@impact-tek.com
Research Institution:
Stub




Abstract
Impact Technologies, in collaboration with Tennessee State University, propose to develop and demonstrate an adaptive system identification and multi-loop control methodology that provides real-time aircraft structural mode suppression associated with aeroservoelastic interaction under upset and damage conditions. The proposed program will develop an effective real-time aircraft structural model, including rigid body dynamics and structural flexible modes, which will be used by the on-line, adaptive control system proposed. In parallel, the research team will also develop an innovative time/frequency domain system identification algorithm that can provide continuous updates to the real-time aircraft model and automatically assess the level of existing structural mode excitation. Next, a singular value decomposition technique will be implemented to capture and quantify the associated dominant parameter uncertainties of the dynamic aircraft model and adjust accordingly. Finally, a multi-loop adaptive control structure will be developed that provides both structure and robustness of the aircraft by using the continuously identified model with the overall goal of responding to the structural safety and performance needs including the effects of aeroservoelastic interaction and structural flexible mode changes. The proposed approach uses a generalized predictive control (GPC) scheme, which can be used to both update the real-time model and design a controller, for active aeroservoelastic suppression under upset conditions.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government