Multicopter with angled rotors

Patent metadata

Field	Value
Publication number	US-11932384-B2
Application number	US-202217744145-A
Country	US
Kind code	B2
Filing date	May 13, 2022
Priority date	Oct 18, 2016
Publication date	Mar 19, 2024
Grant date	Mar 19, 2024

Abstract

A multicopter with angled rotors includes a fuselage and a plurality of rotors. At least some of the rotors are disposed on opposite sides of the fuselage and each is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage; and
a plurality of lift rotors disposed on a wing on each side of the fuselage, the plurality of lift rotors including a set of forward lift rotors provided forward of the wing and a set of aft lift rotors provided aft of the wing on each side of the fuselage;
wherein each lift rotor is oriented at a corresponding non-zero angle to a substantially horizontal plane of the aircraft, wherein the non-zero angle for at least one pair of lift rotors on each side of the fuselage is such that the at least one pair of lift rotors tilt outboard away from the fuselage, wherein the set of forward lift rotors are coupled to the wing with a forward tilt.

2. The aircraft of claim 1 , wherein an outermost pair of lift rotors on each side of the fuselage is oriented at the non-zero angle relative to the substantially horizontal plane of the aircraft such that the outermost pair of lift rotors is tilted outboard away from the fuselage.

3. The aircraft of claim 1 , wherein at least two pairs of lift rotors on each side of the fuselage are oriented at the non-zero angle relative to the substantially horizontal plane of the aircraft such that the two pairs of lift rotors are tilted toward the fuselage.

4. The aircraft of claim 1 , further comprising:
a human occupied portion provided in a forward part of the fuselage.

5. The aircraft of claim 1 , wherein the plurality of lift rotors are mounted on booms, the plurality of lift rotors comprises:
a first plurality of lift rotors, each rotor in the first plurality of lift rotors being mounted on a forward end of a corresponding one of said booms; and
a second plurality of lift rotors, each rotor in the second plurality of lift rotors being mounted on an aft end of the corresponding one of said booms,
wherein each rotor in the first plurality of lift rotors and each rotor in the second plurality of lift rotors produces an amount of vertical thrust independent of levels of vertical thrust produced by other lift rotors.

6. The aircraft of claim 1 , wherein the plurality of lift rotors are mounted on booms, and wherein each lift rotor is oriented at said corresponding non-zero angle at least in part by mounting a corresponding boom at said corresponding non-zero angle.

7. The aircraft of claim 1 , wherein the set of forward lift rotors are mounted forward of a center of gravity of the aircraft and the set of aft lift rotors are mounted aft of the center of gravity of the aircraft.

8. The aircraft of claim 1 , wherein a respective plane of rotation of each one of the plurality of lift rotors do not intersect the fuselage.

9. The aircraft of claim 1 , wherein the plurality of lift rotors are driven by electric motors.

10. The aircraft of claim 1 , further comprising one or more batteries to drive the plurality of lift rotors.

11. The aircraft of claim 1 , wherein the aircraft is configured to perform a hover operation, a vertical takeoff operation and a vertical landing operation.

12. The aircraft of claim 1 , wherein the set of aft lift rotors are coupled to the wing with a forward tilt.

13. The aircraft of claim 1 , wherein the set of aft lift rotors are coupled to the wing with a backward tilt.

14. An aircraft comprising:
a fuselage; and
a plurality of lift rotors disposed on a wing on each side of the fuselage, the plurality of lift rotors including a set of forward lift rotors provided forward of the wing and a set of aft lift rotors provided aft of the wing on each side of the fuselage,
wherein the set of forward lift rotors are coupled to the wing with a forward tilt,
wherein each lift rotor is oriented at a corresponding non-zero angle to a substantially horizontal plane of the aircraft, wherein the non-zero angle for at least two pairs of lift rotors on each side of the fuselage is such that the at least two pairs of lift rotors tilt toward the fuselage; and
wherein an outermost pair of lift rotors on each side of the fuselage is oriented at the non-zero angle relative to the substantially horizontal plane of the aircraft such that the outermost pair of lift rotors tilt outboard away from the fuselage.

15. The aircraft of claim 14 , further comprising:
a human occupied portion provided in a forward part of the fuselage.

16. The aircraft of claim 14 , wherein the plurality of lift rotors are mounted on booms, the plurality of lift rotors comprises:
a first plurality of lift rotors, each rotor in the first plurality of lift rotors being mounted on a forward end of a corresponding one of said booms; and
a second plurality of lift rotors, each rotor in the second plurality of lift rotors being mounted on an aft end of the corresponding one of said booms,
wherein each rotor in the first plurality of lift rotors and each rotor in the second plurality of lift rotors produces an amount of vertical thrust independent of levels of vertical thrust produced by other lift rotors.

17. The aircraft of claim 14 , wherein the plurality of lift rotors are mounted on booms, and wherein each lift rotor is oriented at said corresponding non-zero angle at least in part by mounting a corresponding boom at said corresponding non-zero angle.

18. The aircraft of claim 14 , wherein the set of forward lift rotors are mounted forward of a center of gravity of the aircraft and the set of aft lift rotors are mounted aft of the center of gravity of the aircraft.

19. The aircraft of claim 14 , wherein a first subset of lift rotors rotate in a first direction and are provided on a starboard side of the fuselage, and a second subset of lift rotors rotate in a second direction opposite to the first direction and are provided on a port side of the fuselage.

20. The aircraft of claim 14 , wherein the plurality of lift rotors are driven by electric motors.

21. The aircraft of claim 14 , further comprising one or more batteries to drive the plurality of lift rotors.

22. The aircraft of claim 14 , wherein the aircraft is configured to perform a hover operation, a vertical takeoff operation and a vertical landing operation.

Assignees

• Wisk Aero Llc

Inventors

• Tighe James Joseph
• Allison Eric

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• G05D1/652 Primary

  Take-off (delivering or retrieving payloads G05D1/667) · CPC title

• B64C29/0025 Primary

  the propellers being fixed relative to the fuselage · CPC title

• G05D1/0858 Primary

  specially adapted for vertical take-off of aircraft · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title