Abstract: A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.

Abstract: A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.

Abstract: A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.

Abstract: A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.

Abstract: A plasma generating device intended to induce a flow in a fluid via plasma generation includes a dielectric separating two electrodes and a power supply. The first electrode is exposed to a fluid flow while the second electrode is positioned under the dielectric. The power supply is electrically coupled to a switch and the first and second electrodes. When the power supply is energized by repeated action of the switch, it causes a pulsed DC current between the electrodes which causes the fluid to ionize generating a plasma. The generation of the plasma induces a force with a velocity component in the fluid.

Abstract: A plasma generating device intended to induce a flow in a fluid via plasma generation includes a dielectric separating two electrodes and a power supply. The first electrode is exposed to a fluid flow while the second electrode is positioned under the dielectric. The power supply is electrically coupled to a switch and the first and second electrodes. When the power supply is energized by repeated action of the switch, it causes a pulsed DC current between the electrodes which causes the fluid to ionize generating a plasma. The generation of the plasma induces a force with a velocity component in the fluid.

Abstract: A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary method for directing airflow exiting a cascade of internal airfoils includes coupling a first plasma generating device on a first surface and a rounded trailing edge of each of the internal airfoils. The method also includes coupling a second plasma generating device on an opposite second surface and the rounded trailing edge of each of the internal airfoils. Further, the method includes selectively energizing the first plasma generating device and the second plasma generating device on each of the internal airfoils to produce a plasma and to selectively alter a direction of local airflow around each of the internal airfoils to produce a combined airflow exiting the cascade in a desired direction.

Abstract: An adaptive plasma optics cell includes a housing defining a chamber, and a gas disposed within the housing chamber. A first light transmissive electrode layer is coupled to a first side of the housing and a first light transmissive dielectric layer is coupled between the first light transmissive electrode layer and the housing chamber. A second electrode layer is coupled to a second side of the housing such that the housing chamber is at least partially disposed between the first and second electrode layers and a second dielectric layer coupled between the second electrode layer electrode and the housing chamber. In operation, a power supply is controlled such that the power supply selectively supplies an electric signal sufficient to cause the gas to generate a plasma having a desired plasma gradient.

Abstract: An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

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: A vehicle includes a surface over which airflow passes. A plasma actuator is configured to generate plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of airflow from a surface of the vehicle includes generating plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

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 or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.

Abstract: An adaptive plasma optics cell includes a housing defining a chamber, and a gas disposed within the housing chamber. A first light transmissive electrode layer is coupled to a first side of the housing and a first light transmissive dielectric layer is coupled between the first light transmissive electrode layer and the housing chamber. A second electrode layer is coupled to a second side of the housing such that the housing chamber is at least partially disposed between the first and second electrode layers and a second dielectric layer coupled between the second electrode layer electrode and the housing chamber. In operation, a power supply is controlled such that the power supply selectively supplies an electric signal sufficient to cause the gas to generate a plasma having a desired plasma gradient.

Abstract: An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Abstract: A plasma generator for delaying the onset of rotation stall by tip gap flow control in, for example, an axial flow compressor is disclosed. The tip gap flow control system includes a housing surrounding a rotor of blades and having an inner wall. At least one plasma generating device is coupled to the inner wall of the housing and circumscribes at least a portion of the rotor of blades. A power supply is electrically coupled to the plasma generating device such that when the power supply energizes the plasma generating device, the axial momentum of a fluid flow between the inner wall of the housing and the tips of the rotor of blades in increased in the direction of the fluid flow.

Abstract: A single dielectric barrier aerodynamic plasma actuator apparatus based on the dielectric barrier discharge phenomenon is disclosed and suggested for application to aerodynamic uses for drag reduction, stall elimination and airfoil efficiency improvement. In the plasma actuator apparatus non-uniform in time and space, partially ionized gasses are generated by one or more electrode pairs each having one electrically encapsulated electrode and one air stream exposed electrode and energization by a high-voltage alternating current waveform. The influence of electrical waveform variation, electrode polarity, electrode size and electrode shape on the achieved plasma are considered along with theoretical verification of achieved results. Light output, generated thrust, ionizing current waveform and magnitude and other variables are considered. Misconceptions prevailing in the present day plasma generation art are addressed and are believed-to-be corrected.

Abstract: A vehicle includes a surface over which airflow passes. A plasma actuator is configured to generate plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of airflow from a surface of the vehicle includes generating plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.