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ZEUS-DO: A Design Oriented CFD-Based Unsteady Aerodynamic Capability for Flight Vehicle Multidisciplinary Configuration Shape Optimization

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX10CB31C
Agency Tracking Number: 085048
Amount: $599,851.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: A2.04
Solicitation Number: N/A
Solicitation Year: 2008
Award Year: 2010
Award Start Date (Proposal Award Date): 2009-12-10
Award End Date (Contract End Date): 2011-12-09
Small Business Information
9489 E. Ironwood Square Drive
Scottsdale, AZ 85258-4578
United States
DUNS: 182103291
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Ping-Chih Chen
 Principal Investigator
 (480) 945-9988
Business Contact
 Jennifer Scherr
Title: Business Official
Phone: (480) 945-9988
Research Institution

CFD-based design-oriented (DO) steady/unsteady aerodynamic analysis tools for Aeroelastic / Aeroservoelastic (AE/ASE) evaluation lag significantly behind other multidisciplinary design optimization (MDO) developments for flight vehicle design. In practically all studies to date involving configuration multidisciplinary shape optimization, dynamic AE/ASE constraints were left out, thus, rendering the design results incomplete. Flutter, gust stresses, vibration, fatigue, ride comfort, handling qualities – all extremely important – still cannot be accounted for in an automated design process involving configuration shape variations. Proposed here is the creation of a comprehensive design-oriented CFD-based unsteady-aerodynamic methodology to enhance current flight vehicle shape MDO capabilities by the creation of AE/ASE shape sensitivities and efficient approximations tailored for large-scale design optimization. ZONA Technology's proven ZEUS code serves as the aerodynamic base for this development. In Phase II aerodynamic shape sensitivities for AE/ASE shape optimization will be developed for general 3D configurations made of lifting surfaces and bodies. The subsonic, transonic, supersonic, and hypersonic flight regimes will be covered. Integration with shape optimization finite-element structural codes will be demonstrated, covering diverse AE/ASE constraints including flutter and gust response. This new general capability will fit any aerospace vehicle MDO environment, and will provide a critically needed MDO building block.

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

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