GVT-Based Ground Flutter Test without Wind Tunnel

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX08CD34P
Agency Tracking Number: 070179
Amount: $99,913.00
Phase: Phase I
Program: STTR
Awards Year: 2008
Solitcitation Year: 2007
Solitcitation Topic Code: T2.02
Solitcitation Number: N/A
Small Business Information
ZONA Technology, Inc.
9489 E. Ironwood Square Drive, Scottsdale, AZ, 85258-4578
Duns: 182103291
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Ping-Chih Chen
 Principal Investigator
 () -
Business Contact
 Jennifer Scherr
Title: Business Official
Phone: (480) 945-9988
Email: jennifer@zonatech.com
Research Institution
 Arizona State University
 Not Available
 P.O. Box 873503
Tempe, AZ, 85287
 (480) 965-1158
 Domestic nonprofit research organization
ZONA Technology, Inc (ZONA) and Arizona State University (ASU) propose a R&D effort to develop a ground flutter testing system without wind tunnel, called the Dry Wind Tunnel (DWT) system. The DWT system consists of a ground vibration test (GVT) hardware system and a real-time unsteady aerodynamic force generation software developed from an aerodynamic reduced order model (ROM). The ground flutter test using the DWT system operates on the real structural model, thereby no scale-down structural model is involved. Furthermore, the impact of the structural nonlinearities on the aeroelastic stability can be automatically included. Moreover, the aeroservoelastic characteristics of the aircraft can be easily measured by simply including the flight control system in the loop. In addition, the unsteady aerodynamics generated computationally is interference-free from the wind tunnel walls. Finally, the DWT can be conveniently and inexpensively carried out as a post GVT test with the same hardware. In Phase I, we will validate this DWT concept on a rectangular flat plate with a reference flutter solution. Through this validation process, the most significant hardware issues will be resolved to pave the way for a successful Phase II validation on a complex structure, such as a real aircraft.

* information listed above is at the time of submission.

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