Large Throw, Imbedded Microactuator Drag Reducers

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: N/A
Agency Tracking Number: 28194
Amount: $750,000.00
Phase: Phase II
Program: SBIR
Awards Year: 1996
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
11000 Cedar Avenue Suite 461, Cleveland, OH, 44106
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Robert N. Schmidt
 (216) 791-6720
Business Contact
Phone: () -
Research Institution
Control of vortices on the leading edge of an airfoil has the potential to decrease drag and increase lift by decreasing the pressure on the forward facing and upper airfoil surfaces. A novel microactuator is proposed which allows for arbitrarily large displacements to be achieved. The actuator is also mechanically robust as compared to "conventional" silicon-based microactuators. Large arrays of the actuators can be deployed in order to obtain fine control of the boundary layer, without a large weight penalty which is typical of macroscopic systems. The system will allow for the elimination of fixed stall fences and vortex generators, thereby eliminating the drag which they induce during most flight regimes. The anticipated effects may be great enough to allow the elimination or the reduction of traditional flight control devices such as rudders and ailerons, when used in a laterally asymmetrical configurations. The program will accomplish four objectives. The principal of microactuator controlled vortex generation will be demonstrated in a wind tunnel. Scale-up and implementation factors will be evaluated. A simplified microactuator system will be designed and fabricated to demonstrate the feasibility of implementing the novel microactuator. Finally, preliminary design of a complete system will be performed to prepare for, and help ensure the success of Phase II and Phase III programs.

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

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