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Fully Integrated Aeroelastic Simulation of Complete Vertical Lift Configurations

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-16-C-0010
Agency Tracking Number: A153-103-0024
Amount: $149,699.66
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A15-103
Solicitation Number: 2015.3
Solicitation Year: 2016
Award Year: 2016
Award Start Date (Proposal Award Date): 2016-04-08
Award End Date (Contract End Date): 2017-05-26
Small Business Information
13290 Evening Creek Drive South Suite 250
San Diego, CA 92128
United States
DUNS: 133709001
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Nicolas Reveles
 Project Engineer
 (256) 258-8406
Business Contact
 Joshua Davis
Phone: (858) 480-2028
Research Institution

Current approaches for resolving rotorcraft fuselage responses in the presence of aerodynamic/structural excitation require ample conservatism because current CFD-based aeromechanic solutions lack the capability to include detailed elastic fuselage models. Instead, a siloed approach is employed where results of one analysis are replayed into another. A particular limitation of the siloed method is its inability to capture rotor wake impingement, which has resulted in empennage buffet problems not being encountered until flight testing of a new design. To provide a fully integrated aeroelastic simulation capability for complete vertical lift configurations that will overcome these limitations, ATA Engineering, Inc. (ATA) proposes the development of a novel simulation coupling methodology. The proposed project will develop a three-code coupling (comprehensive rotor, fluid, and structural dynamics) framework and leverage existing and emerging computational technologies for integrating disparate solution strategies of each domain. The methodology, which will accommodate both loose and tight rotor coupling schemes, will ultimately be integrated in the DoD CREATE HELIOS framework. In Phase I, ATA will develop data communication utilities to couple simulation codes widely used in industry. The utilities will be extended to a robust software product in Phase II and used to simulate a real world rotorcraft aeroelastity problem.

* Information listed above is at the time of submission. *

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