Multicopter with wide span rotor configuration and protective fuselage
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/08
B64C-025/54
B64C-027/00
출원번호
US-0649293
(2017-07-13)
등록번호
US-9944386
(2018-04-17)
발명자
/ 주소
Reichert, Todd
Robertson, Cameron
Cutler, Mark Johnson
출원인 / 주소
Kitty Hawk Corporation
대리인 / 주소
Van Pelt, Yi & James LLP
인용정보
피인용 횟수 :
6인용 특허 :
11
초록▼
An aircraft includes a plurality of rotors and a fuselage. The plurality of rotors are attached to the aircraft at a fixed roll angle and a fixed pitch angle and the plurality of rotors rotate independently of one another. The fuselage includes a side wall with a top edge where the top edge of the s
An aircraft includes a plurality of rotors and a fuselage. The plurality of rotors are attached to the aircraft at a fixed roll angle and a fixed pitch angle and the plurality of rotors rotate independently of one another. The fuselage includes a side wall with a top edge where the top edge of the side wall is higher than the plurality of rotors.
대표청구항▼
1. An aircraft, comprising: a plurality of rotors, wherein: the plurality of rotors are attached to the aircraft at a fixed roll angle and a fixed pitch angle;the plurality of rotors rotate independently of one another; andthe plurality of rotors include: an outer back rotor which is attached to the
1. An aircraft, comprising: a plurality of rotors, wherein: the plurality of rotors are attached to the aircraft at a fixed roll angle and a fixed pitch angle;the plurality of rotors rotate independently of one another; andthe plurality of rotors include: an outer back rotor which is attached to the aircraft at a highest height associated with the plurality of rotors;an outer front rotor which is attached to the aircraft at a second highest height associated with the plurality of rotors;an inner back rotor which is attached to the aircraft at a third highest height associated with the plurality of rotors;an inner front rotor which is attached to the aircraft at a lowest height associated with the plurality of rotors; andan inner middle rotor which is attached to the aircraft at the lowest height associated with the plurality of rotors; anda fuselage which includes a side wall with a top edge, wherein the top edge of the side wall is higher than the plurality of rotors. 2. The aircraft recited in claim 1, wherein the plurality of rotors further include: a right inner front rotor which is configured to rotate in a first direction;a right outer front rotor which is configured to rotate in the first direction;a right inner middle rotor which is configured to rotate in a second direction;a right outer back rotor which is configured to rotate in the second direction;a right inner back rotor which is configured to rotate in the first direction;a left inner back rotor which is configured to rotate in the second direction;a left outer back rotor which is configured to rotate in the first direction;a left inner middle rotor which is configured to rotate in the first direction;a left outer front rotor which is configured to rotate in the second direction; anda left inner front rotor which is configured to rotate in the second direction. 3. The aircraft recited in claim 1, wherein the plurality of rotors further include: a right inner front rotor which is configured to rotate in a counterclockwise direction when viewed from above;a right outer front rotor which is configured to rotate in the counterclockwise direction when viewed from above;a right inner middle rotor which is configured to rotate in a clockwise direction when viewed from above;a right outer back rotor which is configured to rotate in the clockwise direction when viewed from above;a right inner back rotor which is configured to rotate in the counterclockwise direction when viewed from above;a left inner back rotor which is configured to rotate in the clockwise direction when viewed from above;a left outer back rotor which is configured to rotate in the counterclockwise direction when viewed from above;a left inner middle rotor which is configured to rotate in the counterclockwise direction when viewed from above;a left outer front rotor which is configured to rotate in the clockwise direction when viewed from above; anda left inner front rotor which is configured to rotate in the clockwise direction when viewed from above. 4. The aircraft recited in claim 1, wherein the plurality of rotors further include: a right inner front rotor which is attached to the aircraft at a positive roll angle and a zero pitch angle; anda left inner front rotor which is attached to the aircraft at a negative roll angle and a zero pitch angle. 5. The aircraft recited in claim 1, wherein the plurality of rotors further include: a right outer front rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right inner middle rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right outer back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right inner back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a left inner back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;a left outer back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;a left inner middle rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; anda left outer front rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle. 6. The aircraft recited in claim 1, wherein: the plurality of rotors further include: a right outer front rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right inner middle rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right outer back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a right inner back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;a left inner back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;a left outer back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;a left inner middle rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; anda left outer front rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; andthe plurality of rotors are attached to the aircraft at roll angles and pitch angles with magnitudes in the range of 0 degrees and 10 degrees. 7. The aircraft recited in claim 1, wherein the fuselage narrows at the midsection of the fuselage. 8. The aircraft recited in claim 1, wherein the fuselage narrows at the midsection of the fuselage creating an overhang beneath which at least part of an inner middle rotor rotates. 9. The aircraft recited in claim 1, wherein: the plurality of rotors are attached to the aircraft at heights in the range of 45 cm-55 cm. 10. The aircraft recited in claim 1, wherein the fuselage further includes a headrest with a cutout. 11. An aircraft, comprising: a plurality of rotors, wherein: the plurality of rotors are attached to the aircraft at a fixed roll angle and a fixed pitch angle; andthe plurality of rotors rotate independently of one another;a fuselage which includes a side wall with a top edge, wherein the top edge of the side wall is higher than the plurality of rotors; anda left float and a right float, wherein: a left inner front rotor, a left inner middle rotor, and a left inner back rotor are attached to the left float;a right inner front rotor, a right inner middle rotor, and a right inner back rotor are attached to the right float;the left float includes a first plurality of batteries for the left inner front rotor, the left inner middle rotor, the left inner back rotor, a left out front rotor, and a left outer back rotor; andthe right float includes a second plurality of batteries for the right inner front rotor, the right inner middle rotor, the right inner back rotor, a right out front rotor, and a right outer back rotor. 12. The aircraft recited in claim 11, wherein: the left float includes at least one access panel on a top surface of the left float; andthe right float includes at least one access panel on a top surface of the right float. 13. The aircraft recited in claim 11, wherein the plurality of rotors include: the right inner front rotor which is configured to rotate in a first direction;the right outer front rotor which is configured to rotate in the first direction;the right inner middle rotor which is configured to rotate in a second direction;the right outer back rotor which is configured to rotate in the second direction;the right inner back rotor which is configured to rotate in the first direction;the left inner back rotor which is configured to rotate in the second direction;the left outer back rotor which is configured to rotate in the first direction;the left inner middle rotor which is configured to rotate in the first direction;the left outer front rotor which is configured to rotate in the second direction; andthe left inner front rotor which is configured to rotate in the second direction. 14. The aircraft recited in claim 11, wherein the plurality of rotors include: the right inner front rotor which is configured to rotate in a counterclockwise direction when viewed from above;the right outer front rotor which is configured to rotate in the counterclockwise direction when viewed from above;the right inner middle rotor which is configured to rotate in a clockwise direction when viewed from above;the right outer back rotor which is configured to rotate in the clockwise direction when viewed from above;the right inner back rotor which is configured to rotate in the counterclockwise direction when viewed from above;the left inner back rotor which is configured to rotate in the clockwise direction when viewed from above;the left outer back rotor which is configured to rotate in the counterclockwise direction when viewed from above;the left inner middle rotor which is configured to rotate in the counterclockwise direction when viewed from above;the left outer front rotor which is configured to rotate in the clockwise direction when viewed from above; andthe left inner front rotor which is configured to rotate in the clockwise direction when viewed from above. 15. The aircraft recited in claim 11, wherein the plurality of rotors include: the right inner front rotor which is attached to the aircraft at a positive roll angle and a zero pitch angle; andthe left inner front rotor which is attached to the aircraft at a negative roll angle and a zero pitch angle. 16. The aircraft recited in claim 11, wherein the plurality of rotors include: the right outer front rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right inner middle rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right outer back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right inner back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the left inner back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;the left outer back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;the left inner middle rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; andthe left outer front rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle. 17. The aircraft recited in claim 11, wherein: the plurality of rotors include: the right outer front rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right inner middle rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right outer back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the right inner back rotor which is attached to the aircraft at a negative roll angle and a negative pitch angle;the left inner back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;the left outer back rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle;the left inner middle rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; andthe left outer front rotor which is attached to the aircraft at a positive roll angle and a negative pitch angle; andthe plurality of rotors are attached to the aircraft at roll angles and pitch angles with magnitudes in the range of 0 degrees and 10 degrees. 18. The aircraft recited in claim 11, wherein the fuselage narrows at the midsection of the fuselage. 19. The aircraft recited in claim 11, wherein the fuselage narrows at the midsection of the fuselage creating an overhang beneath which at least part of an inner middle rotor rotates. 20. The aircraft recited in claim 11, wherein the plurality of rotors are attached to the aircraft at heights in the range of 45 cm-55 cm. 21. The aircraft recited in claim 11, wherein the fuselage further includes a headrest with a cutout.
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이 특허에 인용된 특허 (11)
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