Ducted vehicles particularly useful as VTOL aircraft

• US 20030038213A1
• Filed: 08/21/2001
• Published: 02/27/2003
• Est. Priority Date: 08/21/2001
• Status: Active Grant

• Current Assignee: Urban Aeronautics Ltd.
• Original Assignee: Romeo Yankee Limited
• Inventors: Yoeli, Rafi
• Granted Patent: US 6,568,630 B2
• Time in Patent Office: Days
• US Class Current: 244/50
• CPC Class Codes: B64C 11/001 Shrouded propellers
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/0066 with horizontal jet and jet deflector
• CPC Class Codes: B64C 29/0075 the motors being tiltable relative to the fuselage
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/14 ducted or shrouded

Abstract

A VTOL aircraft (or other vehicle such as a sea vehicle) includes a pair of elongated ducts on opposite sides of the vehicle body, and a plurality of powered propellers (or other propulsion units such as jet engines) mounted within and enclosed by each of the elongated ducts, such as to produce an upward lift force to the vehicle. Each of the elongated ducts has a short transverse dimension slightly larger than the diameter of the blades of each propeller enclosed thereby, and a large transverse dimension slightly larger than the sum of the diameters of the blades of all the propellers enclosed thereby.

Claims

1. A vehicle movable in a fluid medium, comprising:

a vehicle body;

a first group of propulsion units mounted on one side of the vehicle body, each of said propulsion units being oriented to produce a downward flow of the fluid and thereby an upward lift force applied to that side of the vehicle body;

a second group of propulsion units mounted on the opposite side of the vehicle body, each of said latter propulsion units being oriented to produce a downward flow of the fluid, and thereby an upward lift force applied to said opposite side of the vehicle body;

a first elongated duct on said one side of the vehicle body enclosing all the propulsion units of said first group and having an upper end and a lower end projecting past the upper and lower ends of said enclosed propulsion units;

and a second elongated duct, separate from said first elongated duct, located on said opposite side of the vehicle body and enclosing all the propulsion units of said second group, said second elongated duct having an upper end and a lower end projecting past the upper and lower ends of said second group of propulsion units;

the cross-sectional area of each of said first and second elongated ducts being larger than the sum of the cross-sectional areas of the plurality of propulsion units enclosed by the respective elongated duct, to augment the lift force produced by the respective propulsion units;

the ends of said first and second elongated ducts being spaced from each other to facilitate entry and exit from said vehicle.

2. The vehicle according to claim 1, wherein the upper inlet end of each elongated duct is circumscribed by a curved surface which guides smoothly the fluid flow into the duct to further augment the lift force produced by the propulsion units.

3. The vehicle according to claim 1, wherein each of said elongated ducts has a short transverse dimension slightly larger than the diameter of the outer outlines of each propulsion unit enclosed thereby, and a large transverse dimension slightly larger than the sum of the diameters of the outer outlines of all the propulsion units enclosed thereby.

4. The vehicle according to claim 1, wherein each elongated duct is of a rectilinear configuration.

5. The vehicle according to claim 1, wherein each elongated duct is of a curvilinear configuration.

6. The vehicle according to claim 1, wherein each propulsion unit is fixedly mounted within its respective duct with its longitudinal axis perpendicular to the horizontal longitudinal axis of the vehicle body.

7. The vehicle according to claim 1, wherein each propulsion unit is swivelly mounted within its respective duct with its longitudinal axis pivotal with respect to the horizontal longitudinal axis of the vehicle body.

8. The vehicle according to claim 1, wherein there are two of said propulsion units mounted within and enclosed by each elongated duct.

9. The vehicle according to claim 1, wherein there are at least three propulsion units mounted within and enclosed by each elongated duct.

10. The vehicle according to claim 1, wherein each of said propulsion units is a rotary propeller.

11. The vehicle according to claim 1, wherein each of said propulsion units is a jet engine.

12. A VTOL aircraft vehicle, comprising:

a vehicle body;

a first group of propulsion units mounted on one side of the vehicle body, each of said propulsion units being oriented to produce a downward flow of the air and thereby an upward lift force applied to that side of the vehicle body;

a second group of propulsion units mounted on the opposite side of the vehicle body, each of said latter propulsion units being oriented to produce a downward flow of the air, and thereby an upward lift force applied to said opposite side of the vehicle body;

a first elongated duct on said one side of the vehicle body enclosing all the propulsion units of said first group and having an upper end and a lower end projecting past the upper and lower ends of said enclosed propulsion units;

and a second elongated duct, separate from said first elongated duct, located on said opposite side of the vehicle body and enclosing all the propulsion units of said second group, said second elongated duct having an upper end and a lower end projecting past the upper and lower ends of said second group of propulsion units;

the cross-sectional area of each of said first and second elongated ducts being larger than the sum of the cross-sectional areas of the plurality of propulsion units enclosed by the respective elongated duct, to augment the lift force produced by the respective propulsion units;

the ends of said first and second elongated ducts being spaced from each other to facilitate entry and exit from said vehicle.

13. The VTOL aircraft according to claim 12, wherein the upper inlet end of each elongated duct is circumscribed by a curved surface which guides smoothly the air flow into the duct to further augment the lift force produced by the propulsion units.

14. The VTOL aircraft according to claim 12, wherein each of said elongated ducts has a short transverse dimension slightly larger than the diameter of the blades each propeller enclosed thereby, and a large transverse dimension slightly larger than the sum of the diameters of the blades of all the propellers enclosed thereby.

15. The VTOL aircraft according to claim 13, wherein each elongated duct is of a rectilinear configuration.

16. The VTOL aircraft according to claim 13, wherein each elongated duct is of a curvilinear configuration.

17. The VTOL aircraft according to claim 13, wherein each rotary propeller is mounted within its respective duct with its rotary axis fixed perpendicularly to the horizontal longitudinal axis of the vehicle body.

18. The VTOL aircraft according to claim 13, wherein each rotary propeller is swivelly mounted within its respective duct with its rotary axis pivotal with respect to the horizontal longitudinal axis of the vehicle body.

19. The VTOL aircraft according to claim 13, wherein said pair of elongated ducts are disposed parallel to the longitudinal axis of the vehicle body.

20. The VTOL aircraft according to claim 13, wherein said pair of elongated ducts are disposed perpendicularly to the longitudinal axis of the vehicle body.