Abstract: Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators.

Abstract: Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along, a surface of an it vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators.

Abstract: Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface.

Abstract: Methods and apparatus for suppressing noise. The present invention provides a method that includes directing a laser at a first volume of gas and directing microwave radiation to a second volume. The method includes selecting the location of the second volume so that it is overrun by a shockwave system of a supersonic vehicle. Preferably, the directing of the radiation is from a vehicle that flies at high altitude and is of practical length (e.g., 100-400 feet or more). The radiation may be pulsed and steered. The present invention also provides a system including a laser and microwave antenna for controlling the noise of a supersonic vehicle. The laser is directed at a first volume while the antenna is pointed at a second volume that envelops the first volume. The location of the second volume is such that it will be overrun by the shockwave system of the vehicle.

Abstract: Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface.

Abstract: Methods and apparatus for suppressing noise. The present invention provides a method that includes directing a laser at a first volume of gas and directing microwave radiation to a second volume. The method includes selecting the location of the second volume so that it is overrun by a shockwave system of a supersonic vehicle. Preferably, the directing of the radiation is from a vehicle that flies at high altitude and is of practical length (e.g., 100-400 feet or more). The radiation may be pulsed and steered. The present invention also provides a system including a laser and microwave antenna for controlling the noise of a supersonic vehicle. The laser is directed at a first volume while the antenna is pointed at a second volume that envelops the first volume. The location of the second volume is such that it will be overrun by the shockwave system of the vehicle.

Abstract: A method and apparatus for controlling the throat area, expansion ratio and thrust vector of an aircraft turbine engine exhaust nozzle, includes means, such as deflectors and/or injected air, for producing and controlling regions of locally separated flow. The exhaust nozzle also allows control of the thrust vector angle defined by the gas exiting the nozzle to provide increased directional control of the aircraft.