Abstract: A method of controlling an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition and or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.

Abstract: The present invention is related to an abrasive tool comprising a core and abrasive segments attached to said core wherein said abrasive segments comprise a bond material and superabrasive grains and wherein said segments comprise at least two circumferentially spaced regions and wherein said superabrasive grains are alternately dispersed in said regions in high and low concentrations of superabrasive grains. The present invention is further related to an abrasive tool comprising a core and abrasive segments attached to said core wherein said abrasive segments comprise a bond material and superabrasive grains, wherein said abrasive segments comprise at least two circumferentially spaced regions and wherein said superabrasive grains are alternately dispersed in every other region.