Large Throw, Imbedded Microactuator Drag Reducers

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$750,000.00
Award Year:
1996
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
28194
Agency Tracking Number:
28194
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
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Robert N. Schmidt
(216) 791-6720
Business Contact:
() -
Research Institute:
n/a
Abstract
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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