|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-003/50 B64C-009/16 B64C-009/20|
|미국특허분류(USC)||244/212 ; 244/215 ; 244/216 ; 244/217|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 10 인용 특허 : 0|
A split rudder control system for an aircraft which reduces the net opening hinge moments opposing return of the split rudders to the fully closed position from small deflection angles. The split rudder control system provides a smoothly faired aerodynamic protuberance on the upper surfaces of the split rudder control members adjacent to the trailing edge of the wing when the control members are in the closed position and at small deflection angles relative to the closed position. The aerodynamic protuberance smoothly deflects the airstream flow over the...
A split rudder control system for an aircraft, comprising: a wing having a leading edge, a trailing edge, an upper wing surface, a lower wing surface, and a chord line; a lower control member mounted to said wing, said lower control member having a first forward edge, a first aft edge, a lower surface extending between said first forward edge and said first aft edge, a convex-upward first upper surface extending forward from said first aft edge and away from said lower surface to a peak edge, and an upper opposing surface extending between said peak edge...