MEMS Actuated Deployable Strakes for Slender Bodies
Agency / Branch:
DOD / USAF
Several deployable flow control devices which utilize various MEMs actuators will be designed to enhance the performance capabilities of slender cylindrical bodies with 3:1 ratio tangent ogive nose cone at high angles of attack. The flow control devices will be integrated with a feedback/predictive controller and an integrated array of pressure sensors. The controller will deploy the flow control devices inducing boundary layer transition. The influences of the controlled deployment of the flow control devices on unsteady vortex shedding will be evaluated. The goal of the flow control strategies are to create symmetrical vortex shedding around the nose cone, thus reducing pressure differentials and the resulting yaw forces which cause significant instabilities for missiles (and aircraft) at high angles of attack. The engineer prototype will be tested in a wind tunnel at The Ohio State University. Several flow control strategies will be tested. At least for flow control devices and five MEMs actuators will be evaluated. During this program , the controller will demonstrate its ability to respond to pressure sensor inputs. The ability to control boundary layer transition and vortex shedding will be determined by flow visualization, photogrammetric techniques and static port pressure measurements.
Small Business Information at Submission:
Principal Investigator:Dr. Frederick Lisy
ORBITAL RESEARCH, INC.
11000 Cedar Avenue Cleveland, OH 44106
Number of Employees: