Personal aircraft

• US 8,393,564 B2
• Filed: 09/10/2011
• Issued: 03/12/2013
• Est. Priority Date: 07/19/2010
• 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:
  US13/229,717
• Publication Number:
  US 20120012692A1
• Time in Patent Office: 549 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 27/08 with two or more rotors
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• 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 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 39/08 having multiple wings
• 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. 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 extending a port side of the fuselage via a first plurality of struts;

a second mounting boom extending from a starboard side of the fuselage via a second plurality of struts;

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, wherein each rotor produces an amount of vertical thrust independent of levels of vertical thrust produced by the other rotors;

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, wherein each rotor produces an amount of vertical thrust independent of levels of vertical thrust produced by the other rotors; and

a propeller coupled to the fuselage and adapted to provide forward thrust.

2. The aircraft of claim 1 further comprising:

a first shroud coupled to the fuselage and coplanar to the first plurality of rotors, and extending substantially around an outboard portion of the first plurality of rotors; and

a second shroud coupled to the fuselage and coplanar to the second plurality of rotors, and extending substantially around an outboard portion of the second plurality of rotors.

3. The aircraft of claim 1 wherein the aft wing further comprises a first winglet coupled to an outboard port edge of the aft wing and a second winglet coupled to an outboard starboard edge of the aft wing.

4. The aircraft of claim 1 wherein the first plurality of lift rotors is 4 and the second plurality of lift rotors is 4.

5. The aircraft of claim 1 wherein the lift rotors in the first and second plurality of lift rotors are driven by electric motors.

6. The aircraft of claim 1 wherein the forward wing and the aft wing are not in the same horizontal plane.

7. The aircraft of claim 1 wherein the propeller is coupled to a port side of the aft wing and further comprising a second propeller coupled to a starboard side of the aft wing.

8. The aircraft of claim 1 further comprising:

a forward landing gear coupled to the fuselage;

a port main landing gear coupled to the fuselage; and

a starboard main landing gear coupled to the fuselage.

9. The aircraft of claim 1 further comprising a skid landing gear coupled to the fuselage.

10. A method for flying a VTOL aircraft, the method comprising:

providing the aircraft of claim 1;

producing using the first and second plurality of rotors a vertical thrust to cause the aircraft to ascend;

producing forward thrust to the aircraft using the propeller.

11. The method of claim 10 further comprising:

transitioning the aircraft from vertical to forward flight by reducing the vertical thrust produced by the rotors while increasing the forward thrust produced by the propeller.