|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/122 ; 244/23C ; 244/34A|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 50 인용 특허 : 0|
An unmanned aerial vehicle having a toroidal fuselage that surrounds a pair of coaxial, multi-bladed, counter-rotating rotors. The toroidal fuselage has an airfoil profile that is optimized to provide high hover efficiency and produce a pressure distribution that provide high lift forces. The airfoil profile is further optimized to counteract the undesirable nose-up pitching moments experienced by ducted rotary-type UAVs in forward translational flight.
An unmanned aerial vehicle, comprising: a toroidal fuselage having a coaxial fuselage axis, said toroidal fuselage defining an inner duct flow channel; and rotor assembly means for providing collective and cyclic pitch to control flight operations of said unmanned aerial vehicle, said rotor assembly means including a pair of multi-bladed, counter-rotating rotors coaxially mounted in said inner duct flow channel to provide high hover efficiency, said multi-bladed, counter-rotating rotors having an axis of rotation coaxial with said fuselage axis; said tor...