|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/214 ; 244/90R|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 37 인용 특허 : 0|
Individually deflectable, segmented, vortex flaps are provided on the leading edges of a delta wing supersonic aircraft to permit selective lateral and directional control moments to be created on the aircraft at high angles of attack, where conventional elevons and rudders have become ineffective. By selectively deflecting the segmented vortex flaps simultaneously in the same direction or differentially, the lateral and directional control of high-swept, thin wing, supersonic speed aircraft, at high angles of attack, is improved.
Aerodynamic control apparatus for an aircraft comprising, in combination: a supersonic aircraft having a highly swept delta wing; said highly swept delta wing having oppositely disposed thin and nearly sharply beveled leading and trailing edge portions; a pair of deflectable leading edge flap segments disposed on each of said oppositely disposed beveled leading edge portions of said wing; said pair deflectable leading edge flap segments including (a) a first flap segment extending along each entire oppositely disposed leading edge portion of said wing fo...