PLASMA FLOW CONTROL ACTIVATOR AND PLASMA FLOW CONTROL METHOD

摘要

FIELD: transport.;SUBSTANCE: invention relates to aircraft engineering. Plasma activator is intended for aircraft for yaw or attitude control. System comprises plasma activator including first and second electrodes arranged on aircraft surface. First and second electrodes are directed parallel with flow direction in boundary layer along the surface. Third electrode is arranged between first and second electrodes and shifted from first to second electrode. AC HV signal is fed to first and third electrodes to create fluid flow between electrodes to prevent boundary layer separation from said surface. AC voltage feed to second and third electrodes caused force fluid flow affecting that in boundary layer to separated from the surface. Several activators may be selectively arranged at various points and actuated for yaw or attitude control.;EFFECT: improved aerodynamics.;16 cl, 2 dwg