Vertical/short take-off and landing passenger aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/28
B64C-029/00
출원번호
US-0562484
(2012-07-31)
등록번호
US-8857755
(2014-10-14)
발명자
/ 주소
Karim, Munawar
출원인 / 주소
Utterfly Aircraft, LLC
대리인 / 주소
Tracy Jong Law Firm
인용정보
피인용 횟수 :
2인용 특허 :
4
초록▼
The present aircraft comprises a pair of spaced apart and parallelly disposed fuselages, a pair of wings, each wing is attached to an outer portion to each fuselage, a pyramid structure adapted to connect the pair of fuselages and an articulated propulsion system having a thrust axis, wherein the ar
The present aircraft comprises a pair of spaced apart and parallelly disposed fuselages, a pair of wings, each wing is attached to an outer portion to each fuselage, a pyramid structure adapted to connect the pair of fuselages and an articulated propulsion system having a thrust axis, wherein the articulated propulsion system is pivotably attached to the pyramid structure and configured for angle of rotation of from about 0 degrees corresponding to the thrust axis disposed substantially parallel but at an offset to a longitudinal axis of the aircraft to about 90 degrees corresponding to the thrust axis disposed substantially at right angle to the longitudinal axis. The thrust axis substantially intersects the center of gravity when the thrust axis is disposed substantially at right angle to the longitudinal axis and the thruster is capable of angle of rotation of about 0 degrees or 90 degrees during take-off or landing.
대표청구항▼
1. An aircraft comprising: (a) a pair of spaced apart and parallelly disposed elongated fuselages forming a gap, wherein said pair of fuselages each comprise a longitudinal axis;(b) a pair of wings, each wing is attached to an outboard side of each said fuselage;(c) a pyramid truss structure adapted
1. An aircraft comprising: (a) a pair of spaced apart and parallelly disposed elongated fuselages forming a gap, wherein said pair of fuselages each comprise a longitudinal axis;(b) a pair of wings, each wing is attached to an outboard side of each said fuselage;(c) a pyramid truss structure adapted to connect said pair of fuselages; and(d) an articulated propulsion system having a thrust axis, wherein said articulated propulsion system is pivotably attached to said pyramid structure and configured for angle of rotation of from substantially 0 degrees, corresponding to said thrust axis disposed substantially parallel but at a vertical offset to said longitudinal axis and above the fuselages, to substantially 90 degrees corresponding to said thrust axis disposed substantially at right angle to said longitudinal axis,wherein said thrust axis substantially intersects a center of gravity of said aircraft when said thrust axis is disposed substantially at right angle to said longitudinal axis and said propulsion system is capable of an angle of rotation ranging from about 0 degrees to about 90 degrees during take-off or landing. 2. The aircraft of claim 1, wherein said articulated propulsion system is a counter-rotating co-axial propeller system. 3. The aircraft of claim 1, wherein said articulated propulsion system is a counter-rotating co-axial propeller system connected to two engines. 4. The aircraft of claim 2, wherein said counter-rotating co-axial propeller system comprises a means for cyclical control. 5. The aircraft of claim 1, wherein the ratio of said offset to said gap ranges from about ⅓ to about ⅚. 6. The aircraft of claim 1, wherein each fuselage comprises at least one passenger access door on the outboard side of each fuselage. 7. The aircraft of claim 1, wherein said pyramid structure comprises more than one spar connecting said pair of fuselages. 8. The aircraft of claim 1, further comprising at least one airbag configured to be mountable on an exterior surface of one of said pair of fuselages, wherein said at least one airbag is configured to provide cushioning of said aircraft with an exterior object. 9. An aircraft comprising: (a) a pair of spaced apart and parallelly disposed elongated fuselages forming a gap, wherein said pair of fuselages each comprise a longitudinal axis;(b) a pair of wings, each wing is attached to an outboard side of each said fuselage;(c) a pyramid truss structure adapted to connect said pair of fuselages; and(d) a counter-rotating co-axial propeller system having a thrust axis, wherein said propeller system is pivotably attached to said pyramid structure and configured for angle of rotation of from substantially 0 degrees, corresponding to said thrust axis disposed substantially parallel but at a vertical offset to said longitudinal axis and above the fuselages, to substantially 90 degrees corresponding to said thrust axis disposed substantially at right angle to said longitudinal axis,wherein said thrust axis substantially intersects a center of gravity of said aircraft when said thrust axis is disposed substantially at right angle to said longitudinal axis and said propulsion system is capable of an angle of rotation ranging from about 0 degrees to about 90 degrees during take-off or landing. 10. The aircraft of claim 9, wherein said counter-rotating co-axial propeller system is connected to two engines. 11. The aircraft of claim 10, wherein said counter-rotating co-axial propeller system comprises a means for cyclical control. 12. The aircraft of claim 9, wherein the ratio of said offset to said gap ranges from about ⅓ to about ⅚. 13. The aircraft of claim 9, wherein each fuselage comprises at least one passenger access door on the outboard side of each fuselage. 14. The aircraft of claim 9, wherein said pyramid structure comprises more than one spar connecting said pair of fuselages. 15. The aircraft of claim 9, further comprising at least one airbag configured to be mountable on an exterior surface of one of said pair of fuselages, wherein said at least one airbag is configured to provide cushioning of said aircraft with an exterior object. 16. An aircraft comprising: (a) a pair of spaced apart and parallelly disposed elongated fuselages forming a gap, wherein said pair of fuselages each comprise a longitudinal axis;(b) a pair of wings, each wing is attached to an outer portion to said each of said pair of fuselages;(c) a pyramid truss structure adapted to connect said pair of fuselages; and(d) a counter-rotating co-axial propeller system having a thrust axis and comprising a means for cyclical control, wherein said thruster is pivotably attached to said structure and configured for angle of rotation of from substantially 0 degrees, corresponding to said thrust axis disposed substantially parallel but at a vertical offset to said longitudinal axis and above the fuselages, to substantially 90 degrees corresponding to said thrust axis disposed substantially at right angle to said longitudinal axis,wherein said thrust axis substantially intersects a center of gravity of said aircraft when said thrust axis is disposed substantially at right angle to said longitudinal axis and said propulsion system is capable of an angle of rotation ranging from about 0 degrees to about 90 degrees during take-off or landing and said means for cyclical control enables fine position control of the aircraft during vertical flight. 17. The aircraft of claim 16, wherein said counter-rotating co-axial propeller system is connected to two engines. 18. The aircraft of claim 16, wherein the ratio of said offset to said gap ranges from about ⅓ to about ⅚. 19. The aircraft of claim 16, wherein each fuselage comprises at least one passenger access door on the outboard side of each fuselage. 20. The aircraft of claim 16, wherein said pyramid structure comprises more than one spar connecting said pair of fuselages.
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