Plasma optimized aerostructures for efficient flow control
AssigneesOrbitel Research Inc., University of Notre Dame du Lac
InventorsMehul Patel, Thomas Corke, Alan B. Cain
Life of this patent
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Abstract
The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.
Claims20
An aircraft, missile, projectile, munition, or automobile comprising
- at least one surface over which air flow occurs, the at least one surface having a leading edge and a trailing edge, the at least one surface comprising a modified contour, the modified contour being designed to create a surface flow disturbance along the surface beyond a specific location on the surface, and
- at least one plasma actuator being positioned on the surface to affect the created surface flow disturbance along the surface when actuated,
- wherein the at least one plasma actuator when actuated modifies the air flow over the at least one surface.
An aircraft, missile, projectile, munition, or automobile comprising
- at least one surface over which air flow occurs, the at least one surface having a leading edge and a trailing edge, the at least one surface comprising a modified contour, the modified contour comprising a ramp designed to induce boundary layer separation in flow over the surface beyond a specific location on the surface, and
- at least one plasma actuator positioned on the surface to affect the created surface flow disturbance along the surface when actuated,
- wherein the at least one plasma actuator when actuated modifies the air flow over the at least one surface.
An aircraft, missile, projectile, munition, or automobile comprising
- at least one surface over which air flow occurs, the at least one surface having a leading edge and a trailing edge, the at least one surface comprising a modified contour, the modified contour comprising a Stratford ramp designed to induce continuous boundary layer separation in flow over the surface and a flow detachment point at a specific location on the control surface,
- at least one actuator positioned on the surface to affect the created surface flow disturbance along the surface when actuated, and
- at least one sensor positioned on the surface to measure the flow over the surface near the at least one actuator or to detect or predict flow separation or conditions of the air flow near the at least one actuator
- wherein the at least one actuator when actuated modifies the air flow over the at least one surface.
Dependencies are inferred from the claim text.