|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/45A ; 244/46 ; 244/214 ; 244/90R|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 16 인용 특허 : 0|
The present canard type of aircraft comprises steering rudder elements which are tiltable substantially about the leading edge of each wing of the aircraft, whereby the respective edge of the rudder element extends alongside said leading edge of the respective wing. Another edge of the rudder element extends alongside a surface portion of the fuselage or body of the aircraft in close conformity with said surface portion, but movable relative thereto. A sealing may be inserted between the rudder element and the fuselage in such a manner that said movement...
A canard type aircraft comprising fuselage means (6) having a longitudinal axis, wing means (4) operatively secured to said fuselage means, steering means (1′, 1″) operatively secured to said wing means so that said steering means are tiltable about a tilting axis extending at an acute angle relative to said longitudinal axis of said fuselage means (6), said steering means (1′, 1″) each comprising a first edge (5) facing the aircraft fuselage means (6), and a second edge (2, 3) facing the respective wing means (4), said first and second edges (2, 5; 3, 5...