|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/90R ; 244/214|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 38 인용 특허 : 5|
Traditional roll control systems such as ailerons, elevons or spoilers are least effective at high angles of attack due to boundary layer separation over the wing. This invention uses independently deployed leading edge flaps 16 and 18 on the upper surfaces of vortex stabilized wings 12 and 14, respectively, to shift the center of lift outboard. A rolling moment is created that is used to control roll in flight at high angles of attack. The effectiveness of the rolling moment increases linearly with angle of attack. No adverse yaw effects are induced. In...
A roll control system for an aircraft capable of subsonic, transonic, supersonic or hypersonic flight comprising: a fuselage; a highly swept-back, slender wing section attached to each side of said fuselage; means for stabilizing vortex flows over said wing sections; said wing sections each including an associated flap means, the leading and trailing edges of which are sharp, and the leading edges of which are attached along the leading edges of the wing sections; means for independently moving each said flap means from a first position flush with the wi...