|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/75R ; 244/87 ; 244/88 ; 244/199|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 6 인용 특허 : 0|
The invention is a rotatable, non-circular forebody flow controller. The apparatus comprises a small geometric device located at a nose of a forebody of an aircraft or missile. The geometric device has a circular base that fits flush upon the remaining forebody of the aircraft and a non-circular cross-sectional area that extends toward the apex of the aircraft. The device is symmetrical about a reference plane and preferably attaches to an axle which in turn attaches to a rotating motor. The motor rotates the device about an axis of rotation. Preferably,...
An apparatus for controlling yawing moment of an aircraft having a forebody with a circular cross-section and an apex, the apparatus comprising: a rotatable, geometric device having a circular base, the circular base of the geometric device fitting flush upon the circular cross-section of the forebody of the aircraft, the geometric device having a plurality of non-circular cross-sections that extend from the circular base thereof to the apex of the aircraft.