Continuous Dynamic Simulation of Nonlinear Aerodynamics/Nonlinear Structure Interaction (NANSI) for Morphing Vehicles

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$742,934.00
Award Year:
2008
Program:
STTR
Phase:
Phase II
Contract:
FA9550-08-C-0004
Award Id:
77912
Agency Tracking Number:
F064-016-0261
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
9489 E. Ironwood Square Drive, Suite 100, Scottsdale, AZ, 85258
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
182103291
Principal Investigator:
Danny Liu
President
(480) 945-9988
danny@zonatech.com
Business Contact:
Jennifer Scherr
Assistant
(480) 945-9988
jennifer@zonatech.com
Research Institute:
ARIZONA STATE UNIV.
Cindy Haverstock
P.O. Box 873503
Tempe, AZ, 85287-3503
(480) 965-7381
Nonprofit college or university
Abstract
ZONA Team proposes in Phase II to develop a general nonlinear methodology with a new and expedient reduced-order-modeling-based procedure as well as direct numerical simulation capability for nonlinear aeroelastic design/analysis of air-vehicles and MAVs under continuous dynamic morphing The proposed methodology, called NANSI.AE, has significant novelty and merits in that it integrates multidisciplinary domains including nonlinear structures, computational aerodynamics, ROM methodology for wings in morphing with large amplitude motions. The promising outcome of Phase I will lead to the success of the proposed Phase II program. Thus, the multi-body-dynamics wing modeling will be extended to include distributed and local nonlinearities for morphing wings subject to structural uncertainty. The gridless-boundary-condition-Cartesian grid (GBCC3D) method will be further developed to include a viscous option and the separated-flow option adopting the vortex confinement method. A generalized ROM-ROM procedure will be developed to combine the nonlinear structural morphing ROM (extended ELSTEP) with the nonlinear aerodynamic ROM (using nonlinear system identification) to solve for nonlinear aeroelastic responses under continuous wing morphing. Finally, NANSI.AE along with each sub-domain solvers will be validated on a folding wing and MAV wings with available solutions and measured data. ZONA plans to work closely with AFRL in Phase II.

* information listed above is at the time of submission.

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