|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/75R ; 244/199 ; 244/321|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 7 인용 특허 : 0|
An airplane has a control device for providing a directional moment to control yaw during high angles of attack. The control device includes a chine support member carried at the forward end of the airplane forward of the fuselage. The chine support member rotates about a chine axis which is parallel or coaxial with the longitudinal axis of the airplane. A chine is mounted to the chine support member, the chine having a pair of substantially flat, thin, flight control surfaces rigidly mounted on opposite sides of the chine support member. These flight co...
In an airplane having a fuselage which has a forebody terminating in a fuselage nose, the forebody creating forebody vortices during high angle of attack flight, the airplane having a pair of wings extending from opposite sides of the fuselage to provide lift, an improved apparatus for controlling yaw of the airplane during high angles of attack, comprising in combination: a chine support member carried forward of the nose of the airplane, the chine support member having a chine axis which extends along the length of the airplane, the chine support membe...