Plasma flow control actuator system and method

A system for controlling flight of an airborne mobile platform, comprising:

• a plasma actuator disposed adjacent a surface of said mobile platform;
• an AC voltage source for electrically energizing said plasma actuator;
• said plasma actuator having:
• a first electrode disposed adjacent said surface of said mobile platform so as to be in a path of a boundary layer flow over said surface;
• a second electrode disposed adjacent said surface downstream of said first electrode, relative to a direction of flow of said boundary layer;
• a third electrode separated from said first and second electrodes by a dielectric layer, and disposed between said first and second electrodes and within a plane that is laterally offset from said first and second electrodes;
• and
• a controller for controlling the application of an AC voltage from said AC voltage source to said electrodes to at least one of:
• apply said AC voltage across said first and third electrodes, to cause ionization of air between said first and third electrodes that delays separation of said boundary layer flow on said surface;
• and
• apply said AC voltage across said second and third electrodes, to cause ionization of air between said second and third electrodes that causes separation of said boundary layer flow on said surface.

A plasma actuator for influencing a boundary layer flow over a surface of an object, said actuator comprising:

• a first electrode disposed adjacent said surface;
• a second electrode disposed adjacent said surface and downstream of said first electrode, relative to a flow direction of said boundary layer flow;
• a third electrode disposed between said first and second electrodes, and laterally offset from said first and second electrodes;
• and
• an AC voltage source for applying an AC voltage across at least one of:
• said first and third electrodes, to cause ionization of air between said first and third electrodes that delays separation of said boundary layer flow on said surface;
• and
• said second and third electrodes, to cause ionization of air between said second and third electrodes that causes separation of said boundary layer flow on said surface.

An aircraft comprising:

• a plasma actuator for influencing a boundary layer flow over a surface of said mobile platform, said actuator comprising:
• a first electrode disposed adjacent said surface;
• a second electrode disposed adjacent said surface and downstream of said first electrode, relative to a direction of said boundary layer flow;
• a third electrode disposed between said first and second electrodes, and laterally offset from said first and second electrodes;
• and
• an AC voltage source for applying an AC voltage across at least one of:
• said first and third electrodes, to cause ionization of air between said first and third electrodes that delays separation of said boundary layer flow on said surface;
• and
• said second and third electrodes, to cause ionization of air between said second and third electrodes that causes separation of said boundary layer flow on said surface.