Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators

A method of creating lift or side forces on an aerodynamic surface comprising the steps of:

• locating multiple plasma actuators on an aerodynamic surface having a trailing edge or aft end, each at a different placement distance from the trailing edge or aft end;
• locating multiple sensors on the aerodynamic surface, each positioned to detect or predict flow separation near the location of different ones of the multiple plasma actuators;
• measuring, predicting or estimating velocities of a fluid flowing past the surface at or near the plasma actuators using a controller and the sensors;
• using the controller, determining or estimating times of flow separation of the fluid from the surface near the locations of the plasma actuators, and calculating modulation frequencies for the plasma actuators corresponding to desired operating unsteady frequencies based at least in part on the measured, predicted or estimated fluid velocities and the actuator placement distances;
• and
• activating the plasma actuators near the determined or estimated times of flow separation at the calculated modulation frequencies to create lift or side forces on the aerodynamic surface.

A method of controlling flow of fluid across a surface of a missile, aircraft, munition, or ground vehicle having a number of surfaces comprising the steps of:

• locating multiple plasma actuators on a surface of the missile, aircraft, munition or ground vehicle having a trailing edge or aft end, a placement distance from the trailing edge or aft end;
• locating multiple sensors, each having a signal, the sensors being positioned to detect or predict flow separation of a fluid near the locations of the plasma actuators;
• measuring, predicting or estimating velocities of the fluid flowing past the surface of the missile, aircraft, munition or ground vehicle;
• determining or estimating times of flow separation of the fluid from the surface near the locations of the plasma actuators based at least in part on the signals of the sensors;
• computing individual modulation frequencies for the plasma actuators using a controller based at least in part on the determined or estimated times of flow separation, the measured, predicted or estimated velocities, and the actuator placement distances;
• and
• activating and deactivating the plasma actuators near the time of flow separation of the fluid to control flow of fluid across the surface of the missile, aircraft, munition, or ground vehicle
• wherein the control of flow results in lifting, steering, or producing drag upon the missile, aircraft, munition, or ground vehicle.