Personal aircraft

• US 8,485,464 B2
• Filed: 07/19/2012
• Issued: 07/16/2013
• Est. Priority Date: 07/19/2011
• Status: Active Grant

• Current Assignee: Wisk Aero LLC
• Original Assignee: Zee.Aero Inc.
• Inventors: Kroo, Ilan
• Primary Examiner(s): Collins, Timothy D
• Assistant Examiner(s): STEHLE, JAMIE S
• Application Number:
  US13/553,438
• Publication Number:
  US 20130020429A1
• Time in Patent Office: 362 Days
• Field of Search: 244/17.11, 244/17.23, 244/6, 244/45.A, 244/45.R, 244/55
• US Class Current: 244/6
• CPC Class Codes: B64C 29/00 Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft rotorcraft B64C27/00
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 3/16 Frontal aspect
• CPC Class Codes: B64C 39/12 Canard-type aircraft
• CPC Class Codes: B64D 31/00 Power plant control systems; Arrangement of power plant control systems in aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

Claims

1. A personal aircraft comprising:

a fuselage, having a longitudinal axis and a vertical axis;

a forward wing coupled to the fuselage and located forward of a center of gravity of the aircraft;

an aft wing coupled to the fuselage and located aft of the center of gravity of the aircraft;

a port propulsion boom coupled to the fuselage and oriented substantially parallel to the longitudinal axis of the fuselage along its port side;

a port propeller coupled to the port propulsion boom for providing forward thrust;

a first plurality of rotors coupled to the port propulsion boom, the rotors of the first plurality arranged substantially parallel to the longitudinal axis of the fuselage, each rotor coupled to a motor, wherein each rotor provides thrust in a direction primarily along the vertical axis;

a starboard propulsion boom coupled to the fuselage and oriented substantially parallel to the longitudinal axis of the fuselage along its starboard side;

a starboard propeller coupled to the starboard propulsion boom for providing forward thrust;

a second plurality of rotors coupled to the starboard propulsion boom, the rotors of the second plurality arranged substantially parallel to the longitudinal axis of the fuselage, each rotor coupled to a motor, wherein each rotor provides thrust in a direction primarily along the vertical axis;

wherein each motor coupled to the plurality of rotors is adapted to be controlled independently of the other motors; and

wherein at least one of the first plurality of rotors and at least one of the second plurality of rotors is coupled in an orientation to provide a non-zero component of thrust in a direction not on the vertical axis.

2. The personal aircraft of claim 1 wherein the first plurality of rotors includes at least 4 rotors and the second plurality of rotors includes at least 4 rotors.

3. The personal aircraft of claim 1 further comprising a flight computer coupled to the fuselage and adapted to:

determine a current orientation of the personal aircraft;

determine a desired orientation of the personal aircraft; and

command independently each of the plurality of motors attached to the rotors according to a difference between the current orientation of the personal aircraft and the desired orientation of the personal aircraft.

4. The personal aircraft of claim 3, wherein the flight computer further comprises:

a position sensor interface, adapted to receive sensor data that indicates the aircraft'"'"'s position, altitude, attitude and velocity; and

a rotor control module, coupled to the position sensor interface, adapted to determine an amount of thrust required from each of the plurality of rotors to achieve the desired orientation and to command independently each of the plurality of motors to produce the determined required thrust.

5. The personal aircraft of claim 4 wherein the flight computer further comprises:

a propeller control module coupled to the position sensor interface, adapted to determine an amount of forward thrust required from each propeller and to command the propellers to produce the required thrust.

6. The flight computer of claim 4 further comprising:

a database including programmed trajectories for ascent and descent of the aircraft.

7. The personal aircraft of claim 1 wherein the port propulsion boom and the starboard propulsion boom are each coupled to the fuselage by a plurality of struts.

8. An aircraft comprising:

a fuselage;

a forward wing coupled to the fuselage and located forward of a center of gravity;

an aft wing coupled to the fuselage and located aft of the center of gravity;

a first plurality of lift rotors located between the forward wing and the aft wing on a port side of the fuselage, at least one of the first plurality having a first cant and at least one of the plurality having a second cant, the second cant having an angle different from the first cant;

a second plurality of lift rotors located between the forward wing and the aft wing on a starboard side of the fuselage, at least one of the second plurality having a third cant and at least one of the plurality having a fourth cant, the fourth cant having an angle different from the third cant;

a propeller coupled to the fuselage for providing forward thrust; and

a flight computer, coupled to the fuselage, and configured to independently control an amount of thrust provided by each of the first plurality and each of the second plurality of lift rotors.

9. The aircraft of claim 8 wherein a number of rotors in the first plurality of lift rotors is 4 and a number of rotors in the second plurality of lift rotors is 4.

10. The aircraft of claim 8 wherein a number of rotors in the first plurality of lift rotors is 3 and a number of rotors in the second plurality of lift rotors is 3.

11. The aircraft of claim 8 wherein the aft wing includes winglet features.

12. The aircraft of claim 11 wherein the winglets are oriented substantially in an upward vertical direction.

13. The aircraft of claim 11 wherein the winglets are oriented substantially in a downward vertical direction.

14. The aircraft of claim 8 wherein the lift rotors are driven by electric motors.

15. The aircraft of claim 8 wherein the forward and aft wings are not coplanar.

16. The aircraft of claim 8 wherein the wings are foldable.

17. The aircraft of claim 8 wherein an autopilot provides for unmanned operation.

18. The aircraft of claim 8 wherein the lift rotor blades have fixed pitch.

19. An aircraft comprising:

a fuselage;

a forward wing coupled to the fuselage and located forward of a center of gravity;

an aft wing coupled to the fuselage and located aft of the center of gravity;

a first mounting boom coupled to a port side of the fuselage;

a second mounting boom coupled to a starboard side of the fuselage;

a first plurality of lift rotors, each rotor mounted on the first mounting boom between the forward wing and the aft wing on the port side of the fuselage, at least one of the first plurality having a first cant and at least one of the plurality having a second cant, the first cant having an angle different from the second cant;

a second plurality of lift rotors, each rotor mounted on the second mounting boom between the forward wing and the aft wing on the starboard side of the fuselage, at least one of the second plurality having a third cant and at least one of the plurality having a fourth cant, the third cant having an angle different from the fourth cant;

a first propeller coupled to the first mounting boom for providing forward thrust;

a second propeller coupled to the second mounting boom for providing forward thrust; and

a flight computer, coupled to the fuselage, for independently controlling an amount of thrust provided by each of the first plurality and each of the second plurality of lift rotors.

20. The aircraft of claim 19 further comprising a first fence on the port side of the aircraft and a second fence on the starboard side of the aircraft, each fence essentially parallel to the mounting booms and coupled to the fuselage on an outboard side of the plurality of rotors.

21. The aircraft of claim 20 wherein the fences are adapted to reduce a noise footprint of the aircraft.