초록 ▼

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 e

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.

대표청구항 ▼

1. An apparatus for controlling air vehicle airflow, comprising: an airflow surface;a two-dimensional array of individually addressable actuators positioned at the airflow surface, with individual actuators coupled to a power source to deliver energy into boundary layer flow adjacent to the airflow

1. An apparatus for controlling air vehicle airflow, comprising: an airflow surface;a two-dimensional array of individually addressable actuators positioned at the airflow surface, with individual actuators coupled to a power source to deliver energy into boundary layer flow adjacent to the airflow surface; anda controller operatively coupled to the individual actuators, the controller being programmed with instructions for sequentially pulsing the actuators in a generally streamwise direction to cause shock waves from individual actuators to coalesce. 2. The apparatus of claim 1 wherein the individual actuators are dielectric barrier discharge actuators. 3. The apparatus of claim 1 wherein the individual actuators include ultraviolet energy emitters. 4. The apparatus of claim 1 wherein the individual actuators include particle accelerators. 5. The apparatus of claim 1 wherein the controller is programmed with instructions to activate different actuators at different times. 6. The apparatus of claim 1 wherein an individual actuator includes: a radiation emitter positioned to direct radiation generally parallel to the airflow surface; anda receiver spaced apart from the emitter to receive radiation after the radiation has transited over at least a portion of the airflow surface. 7. The apparatus of claim 6 wherein the radiation emitter includes a laser emitter. 8. The apparatus of claim 6 wherein the radiation emitter includes an emitter of radiation at wavelengths greater than about 200 nm. 9. The apparatus of claim 6 wherein the radiation emitter is positioned to direct radiation transverse to a direction of airflow over the airflow surface. 10. The apparatus of claim 6 wherein the receiver includes a reflective surface positioned to reflect received radiation back over the airflow surface. 11. The apparatus of claim 1 wherein an individual actuator includes: a hollow cathode actuator positioned to inject high energy electrons at an angle to the airflow surface. 12. The apparatus of claim 11 wherein individual hollow cathode actuators are positioned to inject high energy electrons generally normal to the airflow surface. 13. An apparatus for controlling air vehicle airflow, comprising: an airflow surface;a two-dimensional array of individually addressable actuators positioned at the airflow surface, with individual actuators coupled to a power source to deliver energy into boundary layer flow adjacent to the airflow surface; anda controller operatively coupled to the individual actuators, the controller being programmed with instructions that, when executed: sequentially pulse the actuators in a generally streamwise direction to cause shock waves form individual actuators to coalesce.