|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-003/56 B64C-003/38 B64C-039/12 F42B-010/14|
|미국특허분류(USC)||244/45A ; 244/327 ; 244/328 ; 244/49|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 8 인용 특허 : 0|
Aerodynamic control apparatus for an aircraft is provided which includes a pair of control surfaces, one for each side of the aircraft, each control surface extending between a root end at the fuselage and a distant tip end. The root end of each control surface is pivotally mounted on the fuselage on a stationary hinge axis which is angularly disposed relative to the longitudinal axis of the aircraft. The hinge axis is elevated or depressed at the leading edge of the control surface relative to the trailing edge such that the hinge axis is in an oblique ...
In combination with an aircraft including a fuselage having a nose, a tail, and a longitudinal axis extending between said nose and said tail, aerodynamic control apparatus comprising: a control surface extending between a root end and a tip end distant from said root end and between a leading edge generally facing in the direction of said nose and a trailing edge generally facing in the direction of said tail; and means mounting said root end of said control surface on said fuselage for single degree of freedom pivotable movement on a stationary hinge a...