|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/045A ; 244/046|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 12 인용 특허 : 18|
A secondary wing system for use on an aircraft augments the lift, stability, and control of the aircraft at subsonic speeds. The secondary wing system includes a mechanism that allows the canard to be retracted within the contour of the aircraft fuselage from an operational position to a stowed position. The top surface of the canard is exposed to air flow in the stowed position, and is contoured to integrate aerodynamically and smoothly within the contour of the fuselage when the canard is retracted for high speed flight. The bottom portion of the canar...
[ What is claimed is:] [1.] A secondary wing system for use on an aircraft forward fuselage, comprising in combination:a one-piece canard in an elliptical planform shape derived from a waterline cut through the upper portion an area-ruled supersonic fuselage, intermediately positioned between a nose and a main wing; andsaid canard being secured movably relative to the forward fuselage between a stowed position and a deployed position, so that when said canard is deployed, it provides supplementary lift to the aircraft at predetermined speeds, and when sa...