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Mid-Fidelity CFD-Based Aeroservoelastic Analysis Method for Supporting Design and Testing

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC22PA990
Agency Tracking Number: 221703
Amount: $149,388.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A1
Solicitation Number: SBIR_22_P1
Solicitation Year: 2022
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-07-20
Award End Date (Contract End Date): 2023-01-25
Small Business Information
34 Lexington Avenue
Ewing, NJ 08618-2302
United States
DUNS: 096857313
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Glen Whitehouse
 (609) 538-0444
Business Contact
 Melissa Kinney
Phone: (609) 538-0444
Research Institution

Ongoing work in ultra-efficient subsonic and supersonic air-vehicles clearly shows the potential of evolutionary and revolutionary concepts to meet the performance goals of future aircraft. With their incorporation of lightweight flexible structures, such configurations may require active/adaptive control systems for load redistribution, flutter suppression and gust load alleviation to ensure reliability and safety. Unfortunately, contemporary analysis methods are unsuitable for aeroselastic and aeroservoelastic analysis of such configurations. Design tools are dependent on low-fidelity approaches that are inadequate for reliably analyzing advanced configurations, whereas CFD coupled to finite element structural models require significant user input to define and support advanced configurations, not to mention extensive computational resources. A new efficient approach that automates the geometry setup, mesh generation, and assembly of fluid-structural coupling interfaces is needed for aeroselastic/aeroservoelastic analysis of conventional and new concepts. To address this critical need, Continuum Dynamics, Inc. proposes the development of a mid-fidelity CFD-based aeroservoelastic analysis to support vehicle design, active/adaptive control effector design and integration, as well as control system development and flight and wind-tunnel testing. Building on CDIrsquo;s legacy in the relevant disciplines, the project emphasizes technology development to streamline workflows and eliminate user involvement associated with mesh generation and fluid-structural model interfacing to efficiently and accurately undertake full flight envelope vehicle evaluation and optimize when and where to utilize high-fidelity models. nbsp;

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

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