|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/090.R; 244/091; 244/199|
|발명자 / 주소|
|인용정보||피인용 횟수 : 31 인용 특허 : 3|
This invention relates to aircraft designs with substantial trim drag reduction while maintaining commercially feasible low parasitic and induced drag. The stable or control configured aircraft utilizes controllable winglets to generate pitching, yawing, and rolling moments in flying wing or tailless airframe configurations which are preferably of a swept forward style.
1. An airframe of the flying wing configuration comprising: a swept forward wing with controllable wing tip extensions extending into the wing tip vortices at the ends thereof, said wing tip extensions comprising a first, downwardly extending winglet located forwardly of a spanwise wing centerline, a second, upwardly extending winglet located rearwardly of a spanwise wing centerline, said first and second winglets being independently controllable about a chordwise axis, said first and second winglets being further independently controllable about an a...