Six rotor helicopter

• US 20100044499A1
• Filed: 08/22/2008
• Published: 02/25/2010
• Est. Priority Date: 08/22/2008
• Status: Abandoned Application

• Current Assignee: Draganfly Innovations Inc. (Frontier Energy Corp.)
• Original Assignee: Draganfly Innovations Inc. (Frontier Energy Corp.)
• Inventors: Dragan, Zenon, Wood, Greg, Olm, Orville
• Application Number:
  US12/230,119
• Publication Number:
  US 20100044499A1
• Time in Patent Office: Days
• US Class Current: 244/17.230
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/16 with five or more distinct rotor axes, e.g. octocopters
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/21 Rotary wings
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

A rotary wing aircraft is provided having at least three rotor pairs. Each rotor pair has an upper rotor and a lower rotor. During operation, the upper rotor and lower rotor rotate around a shared rotor axis with the upper rotor rotating in a first direction and the lower rotor rotating in an opposite direction By independently controlling the speed of rotation of each upper rotor and each lower rotor the aircraft can be made to ascend, descend, move forward, move backward, move side to side, yaw right and yaw left by only varying the relative speeds of rotations of the upper rotors and lower rotors.

Claims

1. A rotary wing aircraft comprising:

a body;

at least three rotor pairs connected to the body,

each rotor pair comprising a horizontally oriented upper rotor having at least two rotor blades and a horizontally oriented lower rotor having at least two rotor blades,

wherein during operation the upper rotor and lower rotor rotate around a shared rotor axis with the upper rotor rotating in a first direction in a first plane fixed relative to the rotor axis and the lower rotor rotating in an other direction in a second plane fixed relative to the rotor axis,

and wherein the speed of rotation of each upper rotor can be varied independently from the lower rotors and the other upper rotors and the speed of rotation of each lower rotor can be varied independently from the upper rotors and the other lower rotors,

whereby the aircraft can be made to ascend, descend, move forward, move backward, move side to side, yaw right and yaw left by only varying the relative speeds of rotations of the upper rotors and lower rotors.

2. The aircraft of claim 1 wherein there are an odd number of rotor pairs.

3. The aircraft of claim 1 wherein for each rotor pair the first plane is substantially parallel to the second plane.

4. The aircraft of claim 3 wherein each rotor blade has a pitch angle that is fixed relative to the rotor axis.

5. The aircraft of claim 4 wherein there are three rotor pairs and each rotor pair attached to the body by a shaft, each shaft positioned approximately one hundred twenty degrees around a central axis from a shaft supporting an adjacent rotor pair.

6. The aircraft of claim 5 further comprising a plurality of motors with each motor driving one of:

one of the upper rotors and one the lower rotors.

7. The aircraft of claim 6 wherein each motor is an electric motor and wherein the speed of each motor can be varied independently of the other motors by altering a current directed to the motor.

8. The aircraft of claim 7 wherein each rotor pair further comprises the motor for the upper rotor and the motor for the lower rotor positioned between the upper rotor and lower rotor.

9. The aircraft of claim 1 wherein increasing the speed of rotation of all of the upper rotors and all of the lower rotors increases the lift generated by the rotor pairs and causes the aircraft to ascend.

10. The aircraft of claim 1 wherein increasing the speed of rotation of all of the upper rotors and all of the lower rotors rotating in a first direction around a central axis of the aircraft causes the aircraft to rotate in the opposite direction around the central axis.

11. The aircraft of claim 1 wherein decreasing the speed of the rotation of all of the upper rotors and lower rotors rotating in a first direction around a central axis of the aircraft causes the aircraft to rotate in the first direction around the central axis.

12. The aircraft of claim 1 wherein decreasing the speed of rotation of the upper rotor and lower rotor in at least one rotor pair on a side of the aircraft causes the aircraft to tilt downwards to the side of the aircraft and move in the direction of the side of the aircraft.

13. The aircraft of claim 1 wherein increasing the speed of rotation of the upper rotor and lower rotor in at least one rotor pair on a side of the aircraft causes the aircraft to tilt downwards on an opposite side of the aircraft and move in the direction of the opposite side of the aircraft.

14. The aircraft of claim 1 wherein all the upper rotors rotate in a first direction and all of the lower rotors rotate in a second direction.

15. The aircraft of claim 4 wherein two of the shafts extend to the sides of the body and the other shaft extends to rearward from the body when the aircraft is in a flying position.

16. The aircraft of claim 15 wherein the two of the shafts are pivotally connected to the body of the aircraft such that the two of the shafts can be rotated so that the two of the shafts are positioned adjacent to the other shaft extending to the rearward from the body placing the aircraft in a folded position.

17. The aircraft of claim 16 wherein the two of the shafts are biased towards the flying position and a mechanism is used to hold the two of the shafts in place in the folded position.