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A Parametric Study of EHD Plasma Actuators for Munition Control

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8651-04-C-0225
Agency Tracking Number: F041-166-2324
Amount: $99,939.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF04-166
Solicitation Number: 2004.1
Solicitation Year: 2004
Award Year: 2004
Award Start Date (Proposal Award Date): 2004-05-25
Award End Date (Contract End Date): 2004-11-25
Small Business Information
924 Corridor Park Dr.
Knoxville, TN 37932
United States
DUNS: 158986732
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Alan Wintenberg
 Director of Engineering
 (865) 777-3776
Business Contact
 Sharon Draper
Title: CFO
Phone: (865) 777-3776
Research Institution

The development of subsonic plasma actuators has the potential to revolutionize the flight performance of munitions. The addition of surface mounted flow controllers based on the electrical manipulation of surface plasma to aerodynamic control surfaces has the promise of offering a dynamic in-flight augmentation of the flight characteristics of the munitions. Plasma actuators, physically comprised of thin dielectric films with printed strip electrodes, can be added to the surface of any aerodynamic body. These plasma actuators have very small physical presence and are comprised of no moving parts. Due to these characteristics they are robust enough to withstand both being walked on and impacted. Using little electrical power the addition of plasma actuators to the surfaces of aerodynamic test shapes has resulted in delaying flow separation, altering the surface drag, inducing vorticity and generating controllable thrust. Atmospheric Glow Technologies (AGT) proposes to parametrically vary the design criteria of plasma actuators based on their licensed OAUGDP technology. The aerodynamic performance of the plasma actuators will be experimentally determined, optimized, analyzed and fitted into both mathematical and computational models. Results of this study will be used to design improved flight control of munitions and augment the internal aerodynamics of machinery.

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

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