|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|인용정보||피인용 횟수 : 17 인용 특허 : 24|
The present invention provides a system and method for rapidly and precisely controlling vortex symmetry or asymmetry on aircraft forebodies to avoid yaw departure or provide supplemental lateral control beyond that available from the vertical tail surfaces with much less power, obtrusion, weight and mechanical complexity than current techniques. This is accomplished with a plasma discharge to manipulate the boundary layer and the angular locations of its separation points in cross flow planes to control the symmetry or asymmetry of the vortex pattern. P...
1. An aircraft, comprising:a forebody, andplasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma to control a yawing moment on said forebody. 2. The aircraft of claim 1, wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices, said plasma discharge elements being adapted to generate the plasma to control an angular location of separation points S + and S "...