| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a system and a method for a plasma actuator for controlling the direction and/or the attitude thereof adapted to the use of an air movable platform such as an aircraft. <P>SOLUTION: The system comprises at least one plasma actuator having first and second electrodes mounted on the surface of the aircraft. The first and second electrodes are parallel to a boundary layer flow path on the surface. A third electrode is mounted between the first and second electrodes while being laterally displaced from the first and second electrodes. When a high AC voltage signal is applied between the first and third electrodes, a fluid flow is induced between the electrodes excited to assist the delay of the peeling of a boundary layer. When the AC voltage signal is applied between the second and third electrodes, an induced fluid flow is caused to form a reverse effect for peeling the boundary layer from the surface. A plurality of actuators can be selectively disposed at various positions of the aircraft, and selectively so excited as to provide a directional control and/or an attitude control. <P>COPYRIGHT: (C)2009,JPO&INPIT |
