Aircraft rotor and aircraft

• US 6,837,457 B2
• Filed: 05/29/2001
• Issued: 01/04/2005
• Est. Priority Date: 11/29/1999
• Status: Expired due to Fees

• Current Assignee: Natural Colour Kari Kirjavainen Oy
• Original Assignee: Natural Colour Kari Kirjavainen Oy
• Inventors: Kirjavainen, Kari
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US09/865,540
• Publication Number:
  US 20020014554A1
• Time in Patent Office: 1,316 Days
• Field of Search: 244/17.11, 244/17.23, 244/21, 244/23.C, 244/12.2, 446/36, 446/37, 446/58, 446/46
• US Class Current: 244/17.23
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 39/001 Flying saucers

Abstract

An aircraft rotor and an aircraft which aircraft has a body and a rotor arranged to it, the rotor having at least two blades. The rotor is arranged to rotate around a substantially vertical axis. The blades are arranged in such a manner that, when rotating, they form a conical surface, whereby to provide ascending force, the ascending force coefficients of the blades are adjusted to be positive and to provide propulsive force, the ascending force coefficients of the blades on the forward side and on the rear side are adjusted to have opposite signs.

Claims

1. An aircraft which comprises a body and a first rotor connected to the body and arranged to rotate around a substantially vertical axis and comprising at least two blades, wherein the blades when rotating form a conical surface,

whereby to provide ascending force, ascending force coefficients of the blades can be adjusted to be positive and

to provide propulsive force, the ascending force coefficients of the blades on a forward side and on a rear side can be adjusted to have opposite signs,

wherein the aircraft has a rotating circular rotor rim to which roots of the blades are connected, and

wherein the aircraft has at least a second rotor.

2. An aircraft as claimed in claim 1, wherein the ascending force coefficients of the blades can be adjusted as a function of the angle of rotation of each rotor.

3. An aircraft as claimed in claim 1, wherein the ascending force coefficients of the blades are arranged to be adjusted by changing the blade angle of the blades.

4. An aircraft as claimed in claim 1, wherein the aircraft has at least two rotors arranged on top of each other, whose blades form a conical surface when rotating.

5. An aircraft as claimed in claim 4, wherein the aircraft has at least two rotors arranged on top of each other and rotating in opposite directions, the blades of the rotors forming conical surfaces in such a manner that the cone tips of the conical surfaces point downward.

6. An aircraft as claimed in claim 1, wherein the ends of the blades belonging to the same rotor are connected.

7. An aircraft as claimed in claim 1, wherein the aircraft has an electric motor for rotating the rotor and electric motors for adjusting the blade angles of the blades.

8. An aircraft as claimed in claim 1, wherein at least a part of the surfaces of the aircraft is made up of solar cells.

9. An aircraft as claimed in claim 1, wherein the aircraft can be arranged to function as a wind generator.

10. An aircraft as claimed in claim 1, wherein batteries and/or fuel cells are use as the energy source and energy storage of the aircraft.

11. An aircraft as claimed in claim 1, wherein the aircraft can be arranged to be a dwelling and/or water vehicle.

12. The aircraft as claimed in claim 1, wherein the rotor rim encompasses a circumference of said body.

13. The aircraft as claimed in claim 1, wherein the second rotor comprises at least two blades, wherein the blades of the second rotor, when rotating, form a conical surface and has a rotating circular rotor rim to which roots of blades are connected.

14. An aircraft which comprises a body and at least two rotors connected to rotating circular rotor rims and arranged to rotate around a substantially vertical axis and each comprising at least two blades, wherein the blades when rotating form a conical surface,

whereby to provide ascending force, ascending force coefficients of the blades are adjustable to be positive and

to provide propulsive force, the ascending force coefficient of the blades on a forward side and on a rear side are adjustable to have opposite signs, and

wherein in level flight, the body of the aircraft produces an ascending force.

15. The aircraft as claimed in claim 14, wherein blade angles of the blades are controlled so that airflow is made to flow along the surface of the body by increased velocity over the upper surface of the body to increase the ascending force and to produce propulsive force during level flight.

16. The aircraft as claimed in claim 15, wherein during level flight, the blade angles of the blades on a front side of the aircraft are adjusted to be negative and the blade angles of the blades on rear side of the aircraft are adjusted to be positive.

17. An aircraft comprising:

a body having an upper part and a lower part, the upper part of the body is more convex than the lower part of the body so that when the aircraft is in level flight the body produces an ascending force;

a rotor rim situated on a level of a surface of the body; and

a plurality of blades connected by respective roots to the rotor rim,

wherein the blades when rotating form a conical surface such that blade angle of the blades are controlled so that airflow is made to flow along the surface of the body by increased velocity over the upper surface of the body to increase the ascending force and to produce propulsive force during level flight.

18. The aircraft as claimed in claim 17, wherein during level flight, the blade angles of the blades on a front side of the aircraft are adjusted to be negative and the blade angles of the blades on a rear side of the aircraft are adjusted to be positive.

19. The aircraft as claimed in claim 17, wherein the rotor rim encompasses an outer periphery of said upper part.