Physics-Based Identification, Modeling and Management Infrastructure of Aeroelastic Limit-Cycle Oscillations

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$99,999.00
Award Year:
2007
Program:
STTR
Phase:
Phase I
Contract:
FA9550-07-C-0090
Award Id:
83316
Agency Tracking Number:
F074-006-0076
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
1500 Bull Lea Road, Suite 203, Lexington, KY, 40511
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
790637867
Principal Investigator:
Patrick Hu
President and Chairman
(859) 559-7362
Patrick.g.hu@advanceddynamics-usa.com
Business Contact:
Patrick Hu
President and Chairman
(859) 559-7362
patrick.g.hu@advanceddynamics-usa.com
Research Institution:
DUKE UNIV.
Earl H Dowell
Mechanical Engineering Dept.
Duke University 180 Hudson Bld
Durham, NC, 27708
(919) 660-5321
Nonprofit college or university
Abstract
The proposed research program aims to develop a physics-based identification, modeling and management infrastructure for aeroelastic limit-cycle oscillations. This infrastructure will be built upon high fidelity state-of-the-art theoretical/computational methods as validated and verified by available experimental data bases, and will include (1) rapid flutter boundary determination for a wide range of configurations; (2) an assessment of the relative importance of various aerodynamic and structural nonlinearities for aircraft and aerospace configurations that are determined to be flutter critical and hence potentially capable of LCO; (3) an assessment of expected LCO amplitudes based upon high fidelity computational models; (4) an assessment of the potential for active and/or passive alleviation of LCO; and (5) a proposed management system that incorporates a prediction of tolerable LCO amplitudes and the capability for reducing unacceptable LCO response. Key challenges and milestones to by met include (1) a demonstration of the use of Navier-Stokes based CFD models and nonlinear structural models, including the use of system identification methods as appropriate and needed to predict flutter and LCO; (2) a demonstration of accurate modeling of aerodynamic and structural nonlinearities such as large shock wave motion, separated flow, structural freeplay and large geometric structural deflections and their impact on flutter and LCO; (3) characterization and evaluation of nonlinear dampers and nonlinear stiffness devices for alleviating LCO; (4) characterization and evaluation of active control systems for alleviating LCO; and (5) design and demonstration in wind tunnel test and flight test of an LCO alleviation device.

* information listed above is at the time of submission.

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